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HIGHLIGHTS

REVISION NO. 17 Aug 01/02

Pages which have been revised are outlined below, together with the Highlights of the
Revision

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CH/SE/SU C REASON FOR CHANGE EFFECTIVITY
PAGES
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CHAPTER 34
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L.E.P. 1-10 REVISED TO REFLECT THIS REVISION INDICATING

NEW,REVISED, AND/OR DELETED PAGES
T. OF C. REVISED TO REFLECT THIS REVISION
12- 20
34-11-16 CORRECTION/ADDITION/AMPLIFICATION 001-099,
404- 405, ADDED A NOTE.
408, 410- TITLE OF TASK(S) DATA UPDATED 006-099,
412

34-11-19 CONSUMABLE INGREDIENT DATA UPDATED ALL

406

34-22-00 EFFECTIVITY UPDATED

504, 506- CIRCUIT BREAKER(S) DATA UPDATED ALL
512 EFFECTIVITY UPDATED (THROUGHOUT THE TEXT) ALL

34-22-24 CORRECTION/ADDITION/AMPLIFICATION ALL

401- 403 ADDED CAUTION IN 4.A.PROCEDURE.

34-36-11 CONSUMABLE INGREDIENT DATA UPDATED ALL

405- 406

34-36-16 TITLE OF TASK(S) DATA UPDATED ALL

406, 412 CONSUMABLE INGREDIENT DATA UPDATED ALL

34-36-18 CONSUMABLE INGREDIENT DATA UPDATED ALL

405- 406

34-41-00 SB 34-1151 01 INCORPORATED 001-002, 005-099,

515 NAVIGATION - WEATHER RADAR SYSTEM - INSTALL W
EATHER RADAR TRANSCEIVER COLLINS P/N 622-5132
-622.
EFFECTIVITY UPDATED (THROUGHOUT THE TEXT) 001-002, 005-099,

34-41-33 CORRECTION/ADDITION/AMPLIFICATION ALL

403 MODIFIED FRONT FACE OF THE WEATHER RADAR

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34-41-41 CONSUMABLE INGREDIENT DATA UPDATED ALL

406

34-42-00 EFFECTIVITY UPDATED

504- 513 CORRECTION/ADDITION/AMPLIFICATION ALL
ADDED REFERENCE OF THE DIGITAL RADIO
ALTIMETER TEST SET
LAYOUT IMPROVED/MATERIAL RELOCATED ALL
TITLE OF TASK(S) DATA UPDATED ALL

34-42-11 CONSUMABLE INGREDIENT DATA UPDATED ALL

407

34-42-45 TITLE OF TASK(S) DATA UPDATED ALL

405- 406

34-42-45 MOD.20011P0003 INCORPORATED ALL

701- 704 ELECTRICS- GENERATION- DISTRIBUTION-
V.U.<S AND AVIONICS- DEFINE SYSTEMS OF
THE BASIC AIRCRAFT-
NEW TOPIC/NEW CONFIGURATION ALL

34-43-00 EFFECTIVITY UPDATED

3- 4, SB 34-1179 09 INCORPORATED ALL
13- 14, NAVIGATION - TCAS - INSTALL COLLINS TCAS COMP
51- 52, UTER TTR-920 PN 622-8971-322 (WITH CHANGE 7).
54- 97 CIRCUIT BREAKER(S) DATA UPDATED 005-099,
EFFECTIVITY UPDATED (THROUGHOUT THE TEXT) ALL

34-43-00 CIRCUIT BREAKER(S) DATA UPDATED 005-099,

402 EFFECTIVITY UPDATED (THROUGHOUT THE TEXT) 005-099,

34-43-00 CIRCUIT BREAKER(S) DATA UPDATED 005-099,

502, 506 EFFECTIVITY UPDATED (THROUGHOUT THE TEXT) 005-099,

34-43-11 CONSUMABLE INGREDIENT DATA UPDATED ALL

402, 406- CIRCUIT BREAKER(S) DATA UPDATED 005-099,
407 EFFECTIVITY UPDATED (THROUGHOUT THE TEXT) 005-099,

34-43-34 CIRCUIT BREAKER(S) DATA UPDATED 005-099,

401, 405 EFFECTIVITY UPDATED (THROUGHOUT THE TEXT) 005-099,

34-48-00 MOD.26489P4867 REMOVED ALL

1, 9, NAVIGATION - GROUND PROXIMITY WARNING
86- 87, SYSTEM (GPWS) - INSTALL EGPWC
92 (NEW SPEC)

34-51-11 CONSUMABLE INGREDIENT DATA UPDATED ALL

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405

34-52-00 TECHNICAL CORRECTIONS ALL

515- 516, ADDED STEPS
522

34-52-11 CONSUMABLE INGREDIENT DATA UPDATED ALL

405

34-53-00 CIRCUIT BREAKER(S) DATA UPDATED ALL

502 EFFECTIVITY UPDATED (THROUGHOUT THE TEXT) ALL

34-53-11 CONSUMABLE INGREDIENT DATA UPDATED ALL

402, 405 CIRCUIT BREAKER(S) DATA UPDATED ALL
EFFECTIVITY UPDATED (THROUGHOUT THE TEXT) ALL

34-53-31 CIRCUIT BREAKER(S) DATA UPDATED ALL

401- 402, EFFECTIVITY UPDATED (THROUGHOUT THE TEXT) ALL
405- 406

34-55-11 CONSUMABLE INGREDIENT DATA UPDATED ALL

406

34-55-18 CONSUMABLE INGREDIENT DATA UPDATED ALL

404

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 CHAPTER 34
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NAVIGATION

LIST OF EFFECTIVE PAGES

_______________________
N, R or D indicates pages which are New, Revised or Deleted respectively
Remove and insert the affected pages and complete the Record of Revisions and
the Record of Temporary Revisions as necessary

CH/SE/SU C PAGE DATE CH/SE/SU C PAGE DATE CH/SE/SU C PAGE DATE

RECORD 34-10-00 207 Aug01/01 34-11-00 1 Aug01/97

OF TEMP. 34-10-00 208 Aug01/01 34-11-00 2 Aug01/97
REVISION 34-10-00 209 Aug01/01 34-11-00 3 Aug01/97
34-10-00 210 Aug01/01 34-11-00 4 Aug01/97
L.E.P. R 1-10 Aug01/02 34-10-00 211 Aug01/01 34-11-00 5 Aug01/97
T. of C. 1 May01/02 34-10-00 212 Aug01/97 34-11-00 6 Aug01/97
T. of C. 2 Feb01/02 34-10-00 213 Aug01/97 34-11-00 7 Aug01/97
T. of C. 3 May01/02 34-10-00 301 Nov01/00 34-11-00 8 Aug01/97
T. of C. 4 Feb01/02 34-10-00 302 Aug01/97 34-11-00 9 Aug01/97
T. of C. 5 Feb01/02 34-10-00 303 Nov01/00 34-11-00 10 Aug01/97
T. of C. 6 Feb01/02 34-10-00 304 Nov01/00 34-11-00 11 Aug01/97
T. of C. 7 Feb01/02 34-10-00 305 Feb01/02 34-11-00 12 Aug01/97
T. of C. 8 Feb01/02 34-10-00 306 Nov01/00 34-11-00 13 Aug01/97
T. of C. 9 Feb01/02 34-10-00 307 Feb01/02 34-11-00 14 Feb01/98
T. of C. 10 Feb01/02 34-10-00 308 Feb01/02 34-11-00 15 Aug01/01
T. of C. 11 Feb01/02 34-10-00 309 Aug01/97 34-11-00 16 Aug01/01
T. of C. R 12 Aug01/02 34-10-00 310 Nov01/00 34-11-00 17 Aug01/01
T. of C. R 13 Aug01/02 34-10-00 311 Nov01/00 34-11-00 18 Aug01/01
T. of C. R 14 Aug01/02 34-10-00 312 Nov01/00 34-11-00 19 Aug01/01
T. of C. R 15 Aug01/02 34-10-00 401 May01/00 34-11-00 20 Aug01/01
T. of C. R 16 Aug01/02 34-10-00 402 Aug01/97 34-11-00 21 Aug01/01
T. of C. R 17 Aug01/02 34-10-00 403 May01/00 34-11-00 22 Aug01/01
T. of C. R 18 Aug01/02 34-10-00 404 May01/00 34-11-00 23 Aug01/01
T. of C. R 19 Aug01/02 34-10-00 405 May01/00 34-11-00 24 Aug01/01
T. of C. R 20 Aug01/02 34-10-00 406 May01/00 34-11-00 25 Aug01/01
34-10-00 407 May01/00 34-11-00 26 Aug01/01
34-00-00 1 May01/02 34-10-00 408 May01/00 34-11-00 27 Aug01/01
34-00-00 2 May01/02 34-10-00 501 Aug01/97 34-11-00 28 Aug01/01
34-00-00 3 May01/02 34-10-00 502 Aug01/01 34-11-00 29 Aug01/01
34-00-00 4 May01/02 34-10-00 503 Aug01/01 34-11-00 30 Aug01/01
34-00-00 5 May01/02 34-10-00 504 Aug01/01 34-11-00 31 Aug01/01
34-00-00 6 May01/02 34-10-00 505 Aug01/97 34-11-00 32 Aug01/01
34-00-00 7 May01/02 34-10-00 506 May01/01 34-11-00 33 Aug01/01
34-00-00 8 May01/02 34-10-00 507 Aug01/01 34-11-00 34 Aug01/01
34-10-00 508 Aug01/01 34-11-00 501 Aug01/97
34-10-00 1 Feb01/02 34-10-00 509 Aug01/01 34-11-00 502 Feb01/02
34-10-00 201 Aug01/97 34-10-00 510 Aug01/01 34-11-00 503 May01/00
34-10-00 202 Aug01/01 34-10-00 511 Aug01/01 34-11-00 504 Nov01/01
34-10-00 203 Aug01/01 34-10-00 512 Aug01/01 34-11-00 505 Aug01/01
34-10-00 204 Aug01/97 34-10-00 513 Nov01/01 34-11-00 506 Feb01/02
34-10-00 205 Aug01/01 34-10-00 514 Nov01/01 34-11-00 507 Aug01/97
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34-11-15 401 Feb01/98 34-11-18 403 Aug01/01 34-12-00 29 Nov01/99
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34-11-15 604 Aug01/01 34-11-19 405 Aug01/01 34-12-34 407 Aug01/01
34-11-16 401 May01/02 34-11-19 R 406 Aug01/02 34-12-34 408 Aug01/01
34-11-16 402 May01/02 34-11-19 407 Aug01/01 34-12-34 409 Feb01/02
34-11-16 403 May01/02 34-11-19 408 Aug01/01 34-12-51 401 Aug01/01
34-11-16 R 404 Aug01/02 34-11-19 409 Aug01/01 34-12-51 402 Aug01/01
34-11-16 R 405 Aug01/02 34-11-19 410 Aug01/01 34-12-51 403 Aug01/01
34-11-16 406 May01/02 34-11-19 411 Aug01/01 34-12-51 404 Aug01/01
34-11-16 407 May01/02 34-12-51 405 Nov01/01
34-11-16 R 408 Aug01/02 34-12-00 1 Aug01/97 34-12-51 406 Aug01/01
34-11-16 409 May01/02 34-12-00 2 Aug01/97 34-12-51 407 Aug01/01
34-11-16 R 410 Aug01/02 34-12-00 3 Aug01/97 34-12-51 408 Aug01/01
34-11-16 R 411 Aug01/02 34-12-00 4 Aug01/97 34-12-51 409 Aug01/01
34-11-16 R 412 Aug01/02 34-12-00 5 Aug01/97 34-12-51 410 May01/02
34-11-16 501 Feb01/98 34-12-00 6 Aug01/97 34-12-51 411 Nov01/01
34-11-16 502 May01/00 34-12-00 7 Aug01/97 34-12-51 412 Nov01/01
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34-11-17 401 Aug01/01 34-12-00 9 Aug01/01
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34-11-17 409 Aug01/01 34-12-00 17 Nov01/99 34-13-00 8 Aug01/97
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34-51-00 11 Aug01/97 34-52-00 6 May01/00 34-52-00 524 Nov01/00
34-51-00 12 Aug01/97 34-52-00 7 May01/00 34-52-00 525 Nov01/00
34-51-00 13 Aug01/97 34-52-00 8 Nov01/00 34-52-00 526 Nov01/00
34-51-00 14 Aug01/97 34-52-00 9 Nov01/01 34-52-00 527 Nov01/00
34-51-00 15 Aug01/97 34-52-00 10 May01/00 34-52-00 528 Nov01/00
34-51-00 16 Aug01/97 34-52-00 11 May01/00 34-52-11 401 Aug01/97
34-51-00 17 Aug01/97 34-52-00 12 May01/00 34-52-11 402 Aug01/97
34-51-00 18 Aug01/97 34-52-00 13 Nov01/01 34-52-11 403 Aug01/97
34-51-00 19 Aug01/97 34-52-00 14 Nov01/01 34-52-11 404 Aug01/97
34-51-00 20 Aug01/97 34-52-00 15 Nov01/01 34-52-11 R 405 Aug01/02

34-L.E.P. Page 9
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CH/SE/SU C PAGE DATE CH/SE/SU C PAGE DATE CH/SE/SU C PAGE DATE

34-52-11 406 Nov01/99 34-53-00 507 Nov01/00 34-55-00 33 Nov01/99

34-52-11 407 Nov01/97 34-53-00 508 Nov01/00 34-55-00 34 Nov01/99
34-52-11 408 May01/99 34-53-00 509 Nov01/00 34-55-00 501 Aug01/97
34-52-11 409 Nov01/97 34-53-11 401 May01/02 34-55-00 502 Nov01/01
34-52-12 401 Aug01/97 34-53-11 R 402 Aug01/02 34-55-00 503 Aug01/97
34-52-12 402 Nov01/01 34-53-11 403 Aug01/97 34-55-00 504 Nov01/97
34-52-12 403 Aug01/97 34-53-11 404 May01/00 34-55-00 505 Aug01/97
34-52-12 404 Nov01/01 34-53-11 R 405 Aug01/02 34-55-00 506 Nov01/00
34-52-12 405 Aug01/97 34-53-11 406 May01/02 34-55-00 507 Aug01/97
34-52-33 401 Aug01/97 34-53-11 407 May01/02 34-55-00 508 Aug01/97
34-52-33 402 Feb01/98 34-53-11 408 May01/02 34-55-00 509 Nov01/00
34-52-33 403 Aug01/97 34-53-11 409 Aug01/98 34-55-00 510 Feb01/98
34-52-33 404 Feb01/02 34-53-31 R 401 Aug01/02 34-55-00 511 Nov01/01
34-52-33 405 Aug01/97 34-53-31 R 402 Aug01/02 34-55-00 512 Nov01/01
34-52-33 406 Feb01/02 34-53-31 403 Aug01/97 34-55-00 513 May01/00
34-53-31 404 Feb01/02 34-55-00 514 Feb01/98
34-53-00 1 Nov01/99 34-53-31 R 405 Aug01/02 34-55-00 515 Feb01/98
34-53-00 2 Aug01/97 34-53-31 R 406 Aug01/02 34-55-11 401 Aug01/97
34-53-00 3 Aug01/01 34-55-11 402 Aug01/97
34-53-00 4 Aug01/01 34-55-00 1 Aug01/01 34-55-11 403 Aug01/97
34-53-00 5 Nov01/99 34-55-00 2 Nov01/99 34-55-11 404 Aug01/97
34-53-00 6 Nov01/99 34-55-00 3 Nov01/99 34-55-11 405 Aug01/97
34-53-00 7 Nov01/99 34-55-00 4 Nov01/99 34-55-11 R 406 Aug01/02
34-53-00 8 Nov01/00 34-55-00 5 Nov01/99 34-55-11 407 May01/00
34-53-00 9 Aug01/01 34-55-00 6 Nov01/99 34-55-11 408 May01/00
34-53-00 10 Nov01/99 34-55-00 7 Nov01/99 34-55-11 409 Aug01/97
34-53-00 11 Nov01/99 34-55-00 8 Nov01/99 34-55-18 401 Aug01/97
34-53-00 12 Nov01/99 34-55-00 9 Nov01/99 34-55-18 402 Aug01/97
34-53-00 13 Nov01/99 34-55-00 10 Nov01/99 34-55-18 403 Aug01/97
34-53-00 14 Nov01/99 34-55-00 11 Nov01/99 34-55-18 R 404 Aug01/02
34-53-00 15 Nov01/99 34-55-00 12 Nov01/99 34-55-18 405 Aug01/97
34-53-00 16 Aug01/01 34-55-00 13 Nov01/99 34-55-18 406 Aug01/97
34-53-00 17 Nov01/99 34-55-00 14 Nov01/99 34-55-31 401 Aug01/97
34-53-00 18 Aug01/01 34-55-00 15 Nov01/99 34-55-31 402 Feb01/98
34-53-00 19 Nov01/99 34-55-00 16 Nov01/99 34-55-31 403 Feb01/98
34-53-00 20 Nov01/99 34-55-00 17 Nov01/99 34-55-31 404 Feb01/02
34-53-00 21 Aug01/01 34-55-00 18 Nov01/99 34-55-31 405 Feb01/98
34-53-00 22 Aug01/01 34-55-00 19 Nov01/99 34-55-31 406 Feb01/02
34-53-00 23 Nov01/99 34-55-00 20 Nov01/99
34-53-00 24 Nov01/99 34-55-00 21 Nov01/99 34-57-22 401 Feb01/99
34-53-00 25 Nov01/99 34-55-00 22 Nov01/99 34-57-22 402 Aug01/97
34-53-00 26 Nov01/99 34-55-00 23 Nov01/99 34-57-22 403 Aug01/97
34-53-00 27 Nov01/99 34-55-00 24 Nov01/99 34-57-22 404 Feb01/99
34-53-00 28 Nov01/99 34-55-00 25 Nov01/99 34-57-22 405 Aug01/97
34-53-00 29 Nov01/99 34-55-00 26 Nov01/99
34-53-00 501 May01/99 34-55-00 27 Nov01/99 34-58-00 1 Aug01/01
34-53-00 R 502 Aug01/02 34-55-00 28 Nov01/99
34-53-00 503 Aug01/97 34-55-00 29 Nov01/99
34-53-00 504 May01/99 34-55-00 30 Nov01/99
34-53-00 505 May01/99 34-55-00 31 Nov01/99
34-53-00 506 May01/99 34-55-00 32 May01/00

34-L.E.P. Page 10
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TABLE OF CONTENTS
_________________

_______
SUBJECT ________
CH/SE/SU C
_ PAGE ___________
____ EFFECTIVITY
NAVIGATION - GENERAL
____________________ 34-00-00
DESCRIPTION AND OPERATION 1 ALL
General 1 ALL
System Description 1 ALL
ADIRS 1 ALL
Integrated Standby Instrument 3 ALL
System (ISIS) (optional system)
Landing and Taxiing Aids 4 ALL
Independent Position Determining 5 ALL
Dependent Position Determining 7 ALL

__________________________________
AIR DATA/INERTIAL REFERENCE SYSTEM 34-10-00
_______
(ADIRS)
DESCRIPTION AND OPERATION 1 ALL
General 1 ALL

___________________________________
AIR DATA/INERTIAL REFERENCE SYSTEM 34-10-00
________
(ADIRS)
MAINTENANCE PRACTICES 201 ALL
ADIRS Start Procedure 201 ALL
IR Alignment Procedure 204 ALL
ADIRS Stop Procedure 212 ALL

___________________________________
AIR DATA/INERTIAL REFERENCE SYSTEM 34-10-00
________
(ADIRS)
SERVICING 301 ALL
Flushing of the Principal Total 301 ALL
Pressure Lines
Flushing of the Principal Static 305 ALL
Pressure Lines
Draining and Flushing of the 308 ALL
Standby Static and Standby Total
Pressure Lines

___________________________________
AIR DATA/INERTIAL REFERENCE SYSTEM 34-10-00
________
(ADIRS)
DEACTIVATION/REACTIVATION 401 ALL
Check of the ADR1 401 ALL
Refer to the MMEL TASK: 34-10-01 401 ALL
ADIRS - Check of all Flight 407 ALL
Control Accelerometers for Correct
Operation
Refer to the MMEL TASK: 34-10-01 407 ALL

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TABLE OF CONTENTS
_________________

SUBJECT
_______ CH/SE/SU
________ C
_ PAGE ___________
____ EFFECTIVITY

___________________________________
AIR DATA/INERTIAL REFERENCE SYSTEM 34-10-00
________
(ADIRS)
ADJUSTMENT/TEST 501 ALL
Check of the ADIRS CDU Brightness 501 ALL
and Display
Test of the Angle of Attack 505 ALL
Warning
Operational Test of the 5-minute 511 ALL
Time Delay of ADIRU 2 and 3 Power
Disconnection in Emergency
Configuration

SENSORS, POWER SUPPLY AND SWITCHING 34-11-00

DESCRIPTION AND OPERATION 1 ALL
General 1 ALL
Component Location 2 ALL
Power Supply 5 ALL
General 5 ALL
ADIRS Power Supply Distribution 7 ALL
in Normal Configuration
ADIRS Power Supply Distribution 9 ALL
after Loss of Main Electrical
Generation
Circuit Breakers 11 ALL
Component Description 12 ALL
Static Probes 12 ALL
Pitot Probes 12 ALL
Air Data Modules (ADM) 15 ALL
Total Air Temperature (TAT) 26 ALL
Sensor
Angle Of Attack (AOA) Sensor 28 ALL
Selector Switches 33 ALL

SENSORS, POWER SUPPLY AND SWITCHING 34-11-00

ADJUSTMENT/TEST 501 ALL
Functional Test of the ADM 501 ALL
Test of the Monitoring of the 507 ALL
ADR/AOA 26VAC Power Supply
Test of the Monitoring of the 512 ALL
ADIRS Power Supply (115VAC-28VDC)
PROBE - PITOT 34-11-15
REMOVAL/INSTALLATION 401 ALL
Removal of the Pitot Probe (9DA1, 401 ALL

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TABLE OF CONTENTS
_________________

_______
SUBJECT CH/SE/SU
________ C
_ PAGE ___________
____ EFFECTIVITY
9DA2, 9DA3)
Installation of the Pitot Probe 405 ALL
(9DA1, 9DA2, 9DA3)
PROBE - PITOT 34-11-15
ADJUSTMENT/TEST 501 ALL
Test of the Pitot Probe (9DA1, 501 ALL
9DA2, 9DA3) without the CFDS
PROBE - PITOT 34-11-15
INSPECTION/CHECK 601 ALL
Inspection/Check of the Pitot 601 ALL
Probe (9DA1, 9DA2, 9DA3)
PROBE - STATIC 34-11-16
REMOVAL/INSTALLATION 401 ALL
Removal of the Static Probe (7DA1, 401 ALL
7DA2, 7DA3, 8DA1, 8DA2, 8DA3)
Installation of the Static Probe 407 ALL
(7DA1, 7DA2, 7DA3, 8DA1, 8DA2,
8DA3)
PROBE - STATIC 34-11-16
ADJUSTMENT/TEST 501 ALL
Test of the Static Probe (7DA1, 501 ALL
8DA1, 7DA2, 8DA2, 7DA3, 8DA3)
without the CFDS.
MODULE - AIR DATA 34-11-17
REMOVAL/INSTALLATION 401 ALL
Removal of the Air Data Module 401 ALL
(19FP1, 19FP2, 19FP3, 19FP4,
19FP5, 19FP6, 19FP7, 19FP8)
Installation of the Air Data 410 ALL
Module (19FP1, 19FP2, 19FP3,
19FP4, 19FP5, 19FP6, 19FP7, 19FP8)
MODULE - AIR DATA 34-11-17
ADJUSTMENT/TEST 501 ALL
Test of the Air Data Module 501 ALL
without the CFDS
SENSOR - TOTAL TEMPERATURE 34-11-18
REMOVAL/INSTALLATION 401 ALL
Removal of the TAT Sensor (11FP1, 401 ALL
11FP2)
Installation of the TAT Sensor 405 ALL
(11FP1, 11FP2)
SENSOR - TOTAL TEMPERATURE 34-11-18
ADJUSTMENT/TEST 501 ALL
Test of the TAT Sensor (11FP1, 501 ALL
11FP2) without the CFDS
SENSOR - ANGLE OF ATTACK 34-11-19

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TABLE OF CONTENTS
_________________

_______
SUBJECT CH/SE/SU
________ C
_ ____ ___________
PAGE EFFECTIVITY
REMOVAL/INSTALLATION 401 ALL
Removal of the Angle of Attack 401 ALL
Sensor (3FP1, 3FP2, 3FP3)
Installation of the Angle of 406 ALL
Attack Sensor (3FP1, 3FP2, 3FP3)

AIR DATA/INERTIAL REFERENCE SYSTEM 34-12-00

(ADIRU & CDU)
DESCRIPTION AND OPERATION 1 ALL
General 1 ALL
Component Location 1 ALL
Interface 4 ALL
Mechanical Interface 4 ALL
Electrical Interface 4 ALL
Component Description 25 ALL
ADIRS CDU 25 ALL
ADIRU 29 ALL
CONTROL AND DISPLAY UNIT (CDU) - ADIRS 34-12-12
REMOVAL/INSTALLATION 401 ALL
Removal of the ADIRS CDU (2FP) 401 ALL
Installation of the ADIRS CDU 404 ALL
(2FP)
REFERENCE UNIT - AIR DATA/INERTIAL 34-12-34
(ADIRU)
REMOVAL/INSTALLATION 401 ALL
Removal of the ADIRU (1FP1, 1FP2, 401 ALL
1FP3)
Installation of the ADIRU (1FP1, 405 ALL
1FP2, 1FP3)
MOUNT - ADIRU 34-12-51
REMOVAL/INSTALLATION 401 ALL
Removal of the ADIRU Mount 401 ALL
Installation of the ADIRU Mount 405 ALL

AIR DATA 34-13-00

DESCRIPTION AND OPERATION 1 ALL
General 1 ALL
System Description 1 ALL
ADR Operation 1 ALL
Operation/Control and Indicating 37 ALL
Control 37 ALL
Indicating 37 ALL
Warnings 46 ALL

AIR DATA 34-13-00

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TABLE OF CONTENTS
_________________

_______
SUBJECT CH/SE/SU
________ C
_ ____ ___________
PAGE EFFECTIVITY
REMOVAL/INSTALLATION 401 ALL
PFD Mach Number - Overspeed Check 401 ALL
Reactivation of PFD Mach Number - 404 ALL
Overspeed Check

AIR DATA 34-13-00

ADJUSTMENT/TEST 501 ALL
Operational Test of the AIR DATA 501 ALL
Switching Function
Operational Test of the VMO/MMO 506 ALL
Overspeed Warnings
Operational Test of the ALT 514 ALL
Comparison Warning
Operational Test of the ALT 519 ALL
DYNAMIC SLEW TEST
Operational Test of the CAS 524 ALL
DYNAMIC SLEW TEST
Operational Test of the AOA SENSOR 529 ALL
TEST
Operational Test of the Overspeed 530 ALL
Warnings in the Slats/Flaps and
Landing Gear Extended (VFE/VLE)
Configuration
Functional Test of the Altitude 540 ALL
and Airspeed Data
Leak Test of the Principal Static 547 ALL
and Total Air Data System
INTERFACE TEST of the ADR 552 ALL
SYSTEM TEST of the ADR 560 ALL
Read the CFDIU for the ADR INPUT 564 ALL
STATUS

ATTITUDE, HEADING AND POSITION 34-14-00

DESCRIPTION AND OPERATION 1 ALL
General 1 ALL
System Description 1 ALL
General 1 ALL
Inputs 1 001-004,
Inputs 2 ALL
Software Computation 9 ALL
IR Output Data 19 001-004,
IR Output Data 26 ALL
Operation/Control and Indicating 52 ALL
Control 52 ALL
Indicating 59 ALL

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TABLE OF CONTENTS
_________________

SUBJECT
_______ CH/SE/SU
________ C
_ ____ ___________
PAGE EFFECTIVITY
Warnings 69 ALL
ADIRUs Performance Criteria 76 ALL

ATTITUDE, HEADING AND POSITION 34-14-00

ADJUSTMENT/TEST 501 ALL
Operational Test of the 501 ALL
Attitude/Heading (ATT/HDG)
Switching Function
Operational Test of the 506 ALL
Attitude/Heading (ATT/HDG)
Comparison Warning
Interface Test of the IR 512 ALL
Read CFDIU for IR INPUT STATUS 519 ALL

ADIRS - BITE 34-18-00

DESCRIPTION AND OPERATION 1 ALL
General 1 ALL
Component Location 3 ALL
Computers Directly Linked to the 3 ALL
CFDS
ADIRS Control Panel 3 ALL
Other LRUs of the System 4 ALL
System Description 5 ALL
Reporting Function 5 ALL
Interactive Function 23 ALL

STANDBY DATA : ALTITUDE AND AIRSPEED 34-21-00

DESCRIPTION AND OPERATION 1 ALL
General 1 ALL
Component Location 1 ALL
System Description 1 ALL
Standby Altimeter 1 ALL
Standby Airspeed Indicator 6 ALL

STANDBY DATA : ALTITUDE AND AIRSPEED 34-21-00

ADJUSTMENT/TEST 501 ALL
Leak Test of the Standby Air Data 501 ALL
System
Functional Test of the Standby 506 ALL
Airspeed Indicator
Functional Test of the Standby 509 ALL
Altimeter
ALTIMETER - STANDBY 34-21-22
REMOVAL/INSTALLATION 401 ALL

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NAVIGATION

TABLE OF CONTENTS
_________________

_______
SUBJECT CH/SE/SU
________ C
_ ____ ___________
PAGE EFFECTIVITY
Removal of the Standby Altimeter 401 ALL
(3FN)
Installation of the Standby 406 ALL
Altimeter (3FN)
ALTIMETER - STANDBY 34-21-22
ADJUSTMENT/TEST 501 ALL
ADJUSTING/ALIGNING/CALIBRATING of 501 ALL
the Standby Altimeter
INDICATOR - STANDBY AIRSPEED 34-21-26
REMOVAL/INSTALLATION 401 ALL
Removal of the Standby Airspeed 401 ALL
Indicator (9FN)
Installation of the Standby 406 ALL
Airspeed Indicator (9FN)
INDICATOR - STANDBY AIRSPEED 34-21-26
ADJUSTMENT/TEST 501 ALL
ADJUSTING/ALIGNING/CALIBRATING of 501 ALL
the Standby Airspeed Indicator

STANDBY DATA : ATTITUDE AND HEADING 34-22-00

DESCRIPTION AND OPERATION 1 ALL
General 1 ALL
Standby Heading 1 ALL
Standby Attitude 1 ALL
Component Location 1 ALL
System Description 4 001-004,
Standby Compass 4 001-004,
System Description 4 005-099,
Standby Compass 4 005-099,
Standby Horizon Indicator 4 ALL

STANDBY DATA : ATTITUDE AND HEADING 34-22-00

ADJUSTMENT/TEST 501 ALL
Operational Test of the Standby 501 ALL
Compass
Compensation Adjustment/Test of 504 ALL
the Standby Compass
COMPASS - STANDBY 34-22-23
REMOVAL/INSTALLATION 401 ALL
Removal of the Standby Compass 401 ALL
(2FN)
Installation of the Standby 405 ALL
Compass (2FN)
COMPASS - STANDBY 34-22-23
INSPECTION/CHECK 601 ALL

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Feb 01/02
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TABLE OF CONTENTS
_________________

_______
SUBJECT CH/SE/SU
________ C
_ ____ ___________
PAGE EFFECTIVITY
Detailed Visual Inspection of the 601 ALL
Standby Compass Damping Fluid
INDICATOR - STANDBY HORIZON 34-22-24
REMOVAL/INSTALLATION 401 ALL
Removal of the Standby Horizon 401 ALL
Indicator (7FN)
Installation of the Standby 404 ALL
Horizon Indicator (7FN)

ILS 34-36-00
DESCRIPTION AND OPERATION 1 1 001-004,
General 1 001-004,
Component Location 1 001-004,
System Description 1 001-004,
Principle 1 001-004,
System Architecture 1 001-004,
Utilization Technical Data 7 001-004,
Warnings 11 001-004,
Power Supply 12 001-004,
Component Description 12 001-004,
Receiver 12 001-004,
Antennas 18 001-004,
Operation 20 001-004,
Control 20 001-004,
Reconfiguration Switching 20 001-004,
BITE Function 22 001-004,
Access to ILS Sub-Menu Functions 22 001-004,
Activation of the Test Function 22 001-004,
Power-up Tests Initialization 22 001-004,
and Cockpit Repercussions

ILS ((MMR)) 34-36-00

DESCRIPTION AND OPERATION 2 1 ALL
General 1 ALL
ILS Receiver 1 ALL
GPS Receiver 1 ALL
Component Location 1 ALL
System Description 3 ALL
ILS Operation 3 ALL
GPS Operation 3 ALL
Maintenance Operation 6 ALL
Power Supply 6 ALL
Component Description 7 ALL
MMR 7 ALL
GPS Antenna 17 ALL
Localizer Antenna 19 ALL

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TABLE OF CONTENTS
_________________

SUBJECT
_______ CH/SE/SU
________ C
_ ____ ___________
PAGE EFFECTIVITY
Glide Slope Antenna 19 ALL
Operation 21 ALL
ILS Function 21 ALL
GPS Function 29 ALL
BITE Function 38 ALL
CFDIU Interface 38 ALL
BITE Implementation 51 ALL

ILS 34-36-00
ADJUSTMENT/TEST 1 501 001-004,
BITE Test of the ILS 501 001-004,
Operational Test of the ILS 507 001-004,
Functional Test of the ILS 510 001-004,

ILS ((MMR)) 34-36-00

ADJUSTMENT/TEST 2 501 ALL
BITE Test of the MMR 501 ALL
Operational Test of the GPS 505 ALL
Operational Test of the ILS 510 ALL
Functional Test of the ILS 513 ALL
ANTENNA - LOCALIZER 34-36-11
REMOVAL/INSTALLATION 401 ALL
Removal of the Localizer Antenna 401 ALL
(3RT)
Installation of the Localizer 404 ALL
Antenna (3RT)
ANTENNA - GPS ACTIVE 34-36-16
REMOVAL/INSTALLATION 401 ALL
Removal of the GPS Active Antenna 401 ALL
(43RT1, 43RT2)
Installation of the GPS Active 405 ALL
Antenna (43RT1, 43RT2) with Teflon
Seal
Installation of the GPS Active 411 ALL
Antenna (43RT1, 43RT2) without
Teflon Seal
ANTENNA - GLIDE/SLOPE 34-36-18
REMOVAL/INSTALLATION 401 ALL
Removal of the Glide/Slope Antenna 401 ALL
(4RT)
Installation of the Glide/Slope 404 ALL
Antenna (4RT)
RECEIVER - ILS 34-36-31
REMOVAL/INSTALLATION 1 401 001-004,
Removal of the ILS Receiver (2RT1, 401 001-004,

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TABLE OF CONTENTS
_________________

_______
SUBJECT CH/SE/SU
________ C
_ PAGE ___________
____ EFFECTIVITY
2RT2)
Installation of the ILS Receiver 404 001-004,
(2RT1, 2RT2)
RECEIVER - MULTI MODE (MMR) 34-36-31
REMOVAL/INSTALLATION 2 401 ALL
Removal of the Multi Mode Receiver 401 ALL
(40RT1, 40RT2)
Installation of the Multi Mode 405 ALL
Receiver (40RT1, 40RT2)

WEATHER RADAR SYSTEM 34-41-00

DESCRIPTION AND OPERATION 1 ALL
General 1 ALL
Component Location 2 ALL
System Description 5 ALL
General 5 ALL
Peripherals 9 ALL
General Technical 12 ALL
Characteristics
Power Supply 13 ALL
Interface 13 ALL
Digital Interface Special for 13 ALL
WR/PWS
Component Description 17 ALL
Transceiver 17 ALL
Weather Radar Antenna 21 ALL
Weather Radar Control Unit 21 ALL
Weather Radar Wave Guide 21 ALL
Operation 23 ALL
Operation 23 ALL
Timing of Transmitted Pulses in 27 ALL
WX/MAP Mode, in Doppler Mode
(Turbulence) and in W/S Mode
Controls and Indicating 27 ALL
Utilization of Controls and 32 ALL
Indicating
Reconfiguration switching 45 ALL
Test 46 ALL
BITE Description 46 ALL

WEATHER RADAR SYSTEM 34-41-00

ADJUSTMENT/TEST 501 ALL
Functional test of the Tilt 501 ALL
Control of the Weather-Radar
Antenna Drive-Unit

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NAVIGATION

TABLE OF CONTENTS
_________________

_______
SUBJECT CH/SE/SU
________ C
_ ____ ___________
PAGE EFFECTIVITY
BITE Test of the Weather Radar 508 ALL
System Test of the Weather Radar 513 ALL
ANTENNA ASSEMBLY - WEATHER RADAR 34-41-11
REMOVAL/INSTALLATION 401 ALL
Removal of the Antenna Assembly - 401 ALL
Weather Radar (7SQ, 11SQ)
Installation of the Antenna 405 ALL
Assembly - Weather Radar (7SQ,
11SQ)
CONTROL UNIT - WEATHER RADAR 34-41-12
REMOVAL/INSTALLATION 401 ALL
Removal of the Weather Radar 401 ALL
Control Unit (3SQ)
Installation of the Weather Radar 404 ALL
Control Unit (3SQ)
TRANSCEIVER - WEATHER RADAR 34-41-33
REMOVAL/INSTALLATION 401 ALL
Removal of the Weather Radar 401 ALL
Transceiver (1SQ1, 1SQ2)
Installation of the Weather Radar 404 ALL
Transceiver (1SQ1, 1SQ2)
MOUNTING TRAY - WEATHER RADAR 34-41-37
TRANSCEIVER
REMOVAL/INSTALLATION 401 ALL
Removal of the Weather Radar 401 ALL
Transceiver Mounting Tray (9SQ)
Installation of the Weather Radar 404 ALL
Transceiver Mounting Tray (9SQ)
WAVE GUIDE ASSEMBLY 34-41-41
REMOVAL/INSTALLATION 401 ALL
Removal of the Wave Guide Assembly 401 ALL
Installation of the Wave Guide 406 ALL
Assembly

RADIO ALTIMETER 34-42-00

DESCRIPTION AND OPERATION 1 ALL
General 1 ALL
Component Location 1 ALL
System Description 1 ALL
Principle 1 ALL
System Architecture 7 ALL
Utilization Technical Data 10 ALL
Warnings 12 ALL
Power Supply 12 ALL
Component Description 12 ALL
Transceiver 12 ALL

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TABLE OF CONTENTS
_________________

SUBJECT
_______ CH/SE/SU
________ C
_ ____ ___________
PAGE EFFECTIVITY
Antennas 15 ALL
Fans 17 ALL
Operation 17 ALL
Control 17 ALL
Reconfiguration Switching 17 ALL
Test 18 ALL
Access to Radio Altimeter 18 ALL
Sub-menu Functions
Activation of the Test Function 18 ALL
Power-up Tests Initialization 19 001-004,
and Cockpit Repercussions
CFDIU Interface 19 ALL

RADIO ALTIMETER 34-42-00

ADJUSTMENT/TEST 501 ALL
BITE Test of the Radio Altimeter 501 ALL
Detailed Inspection and 504 ALL
Operational Check of the Radio
Altimeter Fan
Ramp Test of the Radio Altimeter 508 ALL
Warning Test of the Radio 511 ALL
Altimeter
ANTENNA - RADIO ALTIMETER 34-42-11
REMOVAL/INSTALLATION 401 ALL
Removal of the Radio Altimeter 401 ALL
Antennas 5SA1, 5SA2, 6SA1, 6SA2
Installation of the Radio 406 ALL
Altimeter Antennas 5SA1, 5SA2,
6SA1, 6SA2
TRANSCEIVER - RADIO ALTIMETER 34-42-33
REMOVAL/INSTALLATION 401 ALL
Removal of the Radio Altimeter 401 ALL
Transceiver 2SA1 and 2SA2
Installation of the Radio 404 ALL
Altimeter Transceiver 2SA1 and
2SA2
FAN - RADIO ALTIMETER TRANSCEIVER 34-42-45
REMOVAL/INSTALLATION 401 ALL
Removal of the Radio 401 ALL
Altimeter-Transceiver Fan 3SA1
(3SA2)
Installation of the Radio 405 ALL
Altimeter-Transceiver Fan 3SA1
(3SA2)
FAN - RADIO ALTIMETER TRANSCEIVER 34-42-45

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TABLE OF CONTENTS
_________________

_______
SUBJECT CH/SE/SU
________ C
_ ____ ___________
PAGE EFFECTIVITY
CLEANING/PAINTING 701 ALL
Cleaning of the Radio Altimeter 701 ALL
Transceiver Fan

TCAS (TRAFFIC COLLISION AVOIDANCE 34-43-00

SYSTEM)
DESCRIPTION AND OPERATION 1 ALL
General 1 001-004,
Presentation 1 001-004,
General 3 ALL
Presentation 3 ALL
Principle 5 ALL
Advisories 5 ALL
Display 5 ALL
Coordination 6 ALL
Component Location 6 ALL
System Description 10 ALL
TCAS Computer 10 ALL
Directional Antennas 10 ALL
ATC/TCAS Control Unit 10 ALL
Associated Items 10 ALL
Peripherals 12 ALL
Power Supply 13 ALL
Component Description 14 ALL
TCAS Computer 14 ALL
ATC/TCAS Control Unit 18 ALL
TCAS Antennas 18 ALL
Operation 20 ALL
Intruder Detection 20 ALL
Measurement of Intruder 32 ALL
Parameters
Coordination 35 ALL
Principles of Computation 42 ALL
Definition of Target Aircraft 48 001-004,
Definition of Target Aircraft 51 ALL
Sensitivity Level 60 001-004,
Sensitivity Level 63 ALL
Information Display 66 ALL
ATC/TCAS Control Unit 74 ALL
Operational Use
Test 79 ALL
Self-Test 79 ALL
CFDS 81 ALL

TCAS (TRAFFIC COLLISION AVOIDANCE 34-43-00

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_________________

_______
SUBJECT CH/SE/SU
________ C
_ PAGE ___________
____ EFFECTIVITY
SYSTEM)
SERVICING 301 ALL
Uploading Procedure with Portable 301 001-004,
Data Loader (SFIM) to Load the
Operational Software of the TCAS

TCAS (TRAFFIC COLLISION AVOIDANCE 34-43-00

SYSTEM)
DEACTIVATION/REACTIVATION 401 ALL
Deactivation of the TCAS 401 ALL
Refer to the MMEL TASK: 34-43-01 401 ALL
Reactivation of the TCAS 403 ALL
Refer to the MMEL TASK: 34-43-01 403 ALL

TCAS (TRAFFIC COLLISION AVOIDANCE 34-43-00

SYSTEM)
ADJUSTMENT/TEST 501 ALL
BITE Test of the TCAS 501 ALL
Functional Test of the TCAS 505 ALL
Antennas
ANTENNA - TCAS 34-43-11
REMOVAL/INSTALLATION 401 ALL
Removal of the TCAS Antenna (7SG1, 401 ALL
7SG2)
Installation of the TCAS Antenna 405 ALL
(7SG1, 7SG2)
COMPUTER - TCAS 34-43-34
REMOVAL/INSTALLATION 401 ALL
Removal of the TCAS Computer (1SG) 401 ALL
Installation of the TCAS Computer 404 ALL
(1SG)

ENHANCED GROUND PROXIMITY WARNING SYSTEM 34-48-00

(GPWS)
DESCRIPTION AND OPERATION 1 ALL
General 1 ALL
Basic GPWS Modes 1 ALL
Enhanced Features 1 ALL
Component Location 3 ALL
System Description 3 ALL
General 3 ALL
Warnings 3 ALL
Digital Data Inputs 6 001-004,
Digital Data Inputs 6 ALL

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_________________

SUBJECT
_______ CH/SE/SU
________ C
_ ____ ___________
PAGE EFFECTIVITY
Discrete Data Inputs 6 ALL
Warning Outputs 10 ALL
Monitor Outputs 12 ALL
Bus Output 12 ALL
Audio Output 12 ALL
Power Supply 12 ALL
Interface 12 ALL
Digital Outputs 12 ALL
Component Description 29 ALL
Enhanced GPWC 29 ALL
Pushbutton Switches 37 ALL
Operation 40 ALL
General 40 ALL
Detailed Operation - Modes 1 41 ALL
through 5
Envelope Modulation 55 001-004,
Envelope Modulation 59 ALL
Enhanced Features 64 001-004,
Enhanced Features 70 ALL
Warning Generation and 85 ALL
Inhibition
Enhanced GPWC Maintenance Output 87 ALL
Test 87 001-004,
Self-Tests 87 001-004,
CFDS Interface 94 001-004,
Test A 2 ALL
Self-Tests A 2 ALL
CFDS Interface A 4 ALL
BITE Implementation A 11 ALL

GROUND PROXIMITY WARNING SYSTEM (GPWS) 34-48-00

SERVICING 301 ALL
Uploading of the Enhanced GPWC 301 ALL
Data Base

GROUND PROXIMITY WARNING SYSTEM (GPWS) 34-48-00

ADJUSTMENT/TEST 501 ALL
Operational Test of Enhanced GPWS 501 ALL
Ground Self-test Function
Operational Test of the Enhanced 509 ALL
GPWS with Stall Warning Test and
Activation of the GPWS/SYS
Pushbutton Switch and EMER CANC
Key

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TABLE OF CONTENTS
_________________

_______
SUBJECT CH/SE/SU
________ C
_ ____ ___________
PAGE EFFECTIVITY
BITE Test of the Enhanced GPWC 513 ALL
COMPUTER - GROUND PROXIMITY WARNING 34-48-34
(GPWC)
REMOVAL/INSTALLATION 401 ALL
Removal of the GPWC (1WZ) 401 ALL
Installation of the GPWC (1WZ) 404 ALL

DME 34-51-00
DESCRIPTION AND OPERATION 1 ALL
General 1 ALL
Component Location 1 ALL
System Description 1 ALL
Principle 1 ALL
System Architecture 1 ALL
Utilization Technical Data 7 ALL
Power Supply 9 ALL
Component Description 9 ALL
DME Interrogator 9 ALL
DME Antenna 14 ALL
Operation 16 ALL
Control 16 ALL
Reconfiguration Switching 16 ALL
BITE Function 18 ALL
Access to DME Sub-menu Functions 18 ALL
Activation of the Test Function 18 ALL
CFDIU Interface 18 ALL
BITE Implementation 27 ALL

DME 34-51-00
ADJUSTMENT/TEST 501 ALL
BITE Test of the DME 501 ALL
Operational Test of the DME 506 ALL
Functional Test of the DME 509 ALL
ANTENNA - DME 34-51-11
REMOVAL/INSTALLATION 401 ALL
Removal of the DME Antenna (3SD1, 401 ALL
3SD2)
Installation of the DME Antenna 404 ALL
(3SD1, 3SD2)
INTERROGATOR - DME 34-51-33
REMOVAL/INSTALLATION 401 ALL
Removal of the DME Interrogator 401 ALL
(2SD1, 2SD2)
Installation of the DME 404 ALL
Interrogator (2SD1, 2SD2)

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TABLE OF CONTENTS
_________________

SUBJECT
_______ CH/SE/SU
________ C
_ PAGE ___________
____ EFFECTIVITY

ATC/MODE S (SELECT) 34-52-00

DESCRIPTION AND OPERATION 1 ALL
General 1 ALL
Component Location 1 ALL
System Description 4 ALL
Principle 4 ALL
System Architecture 4 ALL
Warning 4 ALL
Power Supply 7 ALL
Component Description 7 ALL
ATC Transponder 7 ALL
Control Unit 18 ALL
Antenna 22 ALL
Operation 22 ALL
Control 24 ALL
Reconfiguration Switching 24 ALL
Test 25 ALL
CFDIU Interface 25 ALL
BITE Implementation 32 ALL
Power-up Tests Initialization 33 ALL
and Cockpit Repercussions

ATC 34-52-00
ADJUSTMENT/TEST 501 ALL
BITE Test of the ATC 501 ALL
Operational Test of the ATC 504 ALL
Functional Test of the Altitude 507 ALL
Reporting Function
Functional Test of the ATC/Mode S 511 ALL
Transponder
Functional Test of the ATC/Mode S 517 ALL
Transponder
Functional Test of the ATC 526 ALL
Antennas
ANTENNA - ATC 34-52-11
REMOVAL/INSTALLATION 401 ALL
Removal of the ATC Antenna (7SH1, 401 ALL
7SH2, 7SH3, 7SH4)
Installation of the ATC Antenna 405 ALL
(7SH1, 7SH2, 7SH3, 7SH4)
CONTROL UNIT - ATC/TCAS 34-52-12
REMOVAL/INSTALLATION 401 ALL
Removal of the ATC/TCAS Control 401 ALL
Unit (3SH)

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TABLE OF CONTENTS
_________________

_______
SUBJECT CH/SE/SU
________ C
_ ____ ___________
PAGE EFFECTIVITY
Installation of the ATC/TCAS 404 ALL
Control Unit (3SH)
TRANSPONDER - ATC/MODE S 34-52-33
REMOVAL/INSTALLATION 401 ALL
Removal of the ATC/Mode S 401 ALL
Transponder (1SH1, 1SH2)
Installation of the ATC/Mode S 404 ALL
Transponder (1SH1, 1SH2)

ADF 34-53-00
DESCRIPTION AND OPERATION 1 ALL
General 1 ALL
Component Location 1 ALL
System Description 1 ALL
Principle 1 ALL
System Architecture 3 ALL
Utilisation Technical Data 3 ALL
Warning 8 ALL
Power Supply 9 ALL
Component Description 9 ALL
ADF Receiver 9 ALL
Loop and Sense Antenna 16 ALL
Operation 16 ALL
Test 18 ALL
Maintenance Test 18 ALL
Power-up Tests Initialization 21 001-004,
and Cockpit Repercussions
CFDIU Interface 21 ALL

ADF 34-53-00
ADJUSTMENT/TEST 501 ALL
BITE Test of the ADF 501 ALL
Operational Test of the ADF 506 ALL
ANTENNA - ADF LOOP AND SENSE 34-53-11
REMOVAL/INSTALLATION 401 ALL
Removal of the ADF Loop and Sense 401 ALL
Antenna
Installation of the ADF Loop and 405 ALL
Sense Antenna
RECEIVER - ADF 34-53-31
REMOVAL/INSTALLATION 401 ALL
Removal of the ADF Receiver (2RP1, 401 ALL
2RP2)
Installation of the ADF Receiver 404 ALL
(2RP1, 2RP2)

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TABLE OF CONTENTS
_________________

SUBJECT
_______ CH/SE/SU
________ C
_ PAGE ___________
____ EFFECTIVITY

VOR/MARKER 34-55-00
DESCRIPTION AND OPERATION 1 ALL
General 1 001-004,
Foreword 1 001-004,
VOR System 1 001-004,
MARKER System 1 001-004,
General 1 ALL
Foreword 1 ALL
VOR System 2 ALL
MARKER System 2 ALL
Component Location 2 ALL
System Description 2 ALL
Principle 2 ALL
System Architecture 4 ALL
Utilization Technical Data 9 ALL
Warning 12 ALL
Power Supply 12 ALL
Component Description 12 ALL
VOR/MKR Receiver 12 ALL
Antennas 21 ALL
Operation 21 ALL
Control 21 ALL
Reconfiguration Switching 25 ALL
BITE Function 25 ALL
Access to the VOR/MKR Sub-menu 25 ALL
Functions
Activation of the Test Function 25 ALL
BITE Test 27 ALL
CFDIU Interface 27 ALL

VOR/MARKER 34-55-00
ADJUSTMENT/TEST 501 ALL
BITE Test of the VOR/MKR 501 ALL
Operational Test of the VOR/MKR 506 ALL
Functional Test of the VOR/MKR 509 ALL
ANTENNA - VOR 34-55-11
REMOVAL/INSTALLATION 401 ALL
Removal of the VOR Antenna 4RS 401 ALL
Installation of the VOR Antenna 405 ALL
4RS
ANTENNA - MARKER 34-55-18
REMOVAL/INSTALLATION 401 ALL
Removal of the Marker Antenna 401 ALL
(1RS)

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TABLE OF CONTENTS
_________________

_______
SUBJECT CH/SE/SU
________ C
_ ____ ___________
PAGE EFFECTIVITY
Installation of the Marker Antenna 404 ALL
(1RS)
RECEIVER - VOR/MARKER 34-55-31
REMOVAL/INSTALLATION 401 ALL
Removal of the VOR/MKR Receiver 401 ALL
(3RS1, 3RS2)
Installation of the VOR/MKR 404 ALL
Receiver (3RS1, 3RS2)
RMI - VOR/DME 34-57-22
REMOVAL/INSTALLATION 401 ALL
Removal of the VOR/DME RMI (11FN) 401 ALL
Installation of the VOR/DME RMI 404 ALL
(11FN)

SATELLITE NAVIGATION 34-58-00

DESCRIPTION AND OPERATION 1 ALL
General 1 ALL

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 NAVIGATION - GENERAL - DESCRIPTION AND OPERATION
________________________________________________

1. _______
General
R (Ref. Fig. 001)
The aircraft navigation systems provide the crew with the data required for
flight within the most appropriate safety requirements.
These data can be divided into four groups :
- Air Data/Inertial Reference System (ADIRS)
- Landing and taxing aids
- Independent position determining
- Dependent position determining.

2. __________________
System Description

A. ADIRS
This part of the navigation system comprises :
- three Air Data/Inertial Reference Units (ADIRU)
- standby systems.
Each ADIRU performs :
- the air data function through its Air Data Reference (ADR) portion.
- the attitude, heading and position function through its Inertial
Reference (IR) portion.

(1) Air data function

Air data are provided by four independent sources :

(a) Three main systems

Each of the three main systems includes static probes, pitot
probes and their associated Air Data Modules (ADM), Total Air
Temperature (TAT) sensors and Angle of Attack (AOA) sensors.
They provide the ADR portion of the ADIRU with the necessary data
for the generation of parameters which are transmitted to the
Primary Flight Displays (PFD) and Navigation Displays (ND) and
the Angle of Attack (AOA) indicator (optional) and to the various
aircraft systems.

(b) A standby system

1
_ The standby system includes a standby altimeter, a standby
airspeed indicator and a metric altimeter (optional) (Ref.
34-21) and the optional system ISIS (Ref. 34-22). They are
provided with pressure by static probes and pitot probe linked
to the ADIRU 3.
More explanations are given in the ADIRU system (Ref. 34-13).

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R Navigation - Systems Overvieww
R Figure 001

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 (2) Attitude, heading and position function
Attitude, heading and position data are provided by four independent
sources:

(a) Three main systems

The three main systems are made up of the following components :
- three IR portions
- a Control and Display Unit (CDU).
They provide inertial reference information, attitude (pitch,
roll and yaw), heading, ground speed and present position.
The primary information of rotation rates and linear acceleration
measured by the IR portions are directly used by the Auto Flight
System (AFS), by the Flight Augmentation Computer (FAC) and the
Flight Management and Guidance Computer (FMGC).
The IR data are transmitted to the indicators (PFD, ND and RMI)
and to the various aircraft systems.

(b) A standby system

1
_ The standby system includes a standby horizon indicator and a
standby compass (Ref. 34-22).
More explanations are given in the ADIRU system (Ref. 34-14).

B. Integrated Standby Instrument System (ISIS) (optional system)

The Integrated Standby Instrument System (ISIS) indicator replaces the
three conventional standby instruments i.e.:
- the standby altimeter (and standby altimeter in meters -optional-)
- the standby airspeed indicator
- the standby horizon indicator.
The standby heading is given by a magnetic compass, which is an
independent instrument.

(1) The ISIS indicator, provides the following standby data on a Liquid
Crystal Display (LCD) installed in place of the standby horizon:
- Attitude,
- Standard or baro-corrected altitude and related barometric pressure
- Indicated airspeed and Mach number
- Lateral acceleration
and the following optional parameters:
- ILS deviation
- V-bar aircraft symbol
- Barometric pressure in hPa or in hPa and in.Hg
- Altitude in meters.
In addition, two specific functions are available:
- Display and adjustment of four airspeed bugs and four airspeed
altitude bugs
- Automatic test procedure.

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 More explanations are given in the ISIS system (Ref. 34-22).

C. Landing and Taxiing Aids

This part of the navigation system comprises :

(1) Paravisual Indicator (PVI) (optional system)

The aircraft is equipped with one PVI installed on the glareshield
panel 131VU, Captain<s side.
This system provides the Captain with an image which serves as a
piloting aid for take-off and landing in reduced visibility
conditions.
The system receives parameters from the DMC1 which can be switched to
the DMC3, and generates the image.
More explanations are given in the PVI system (Ref. 34-34).

(2) Head Up Display (HUD) (optional system)

The aircraft is equipped with :
- a HUDC (Head Up Display Computer)
- a OHU (Optical Head Unit).
This system provides the Captain with an image superimposed on the
outside world in his field of view. This image gives the guidance
information in take-off, landing or approach configurations.
The HUDC processes the input parameters received from the Display
Management Computer 1 (DMC1), which can be switched to the DMC3, and
sends them to the OHU after transformation.
More explanations are given in the HUD system (Ref. 34-35).

(3) Instrument Landing System (ILS) or Multi-Mode Receiver (MMR)

(optional system)
Both ILS or MMR receivers are controlled from FMGCs and Radio
Management Panels (RMPs) featuring two output channels, one command
output and one dialog output.
All data are shown on the EFIS displays.
More explanations are given in the ILS system (Ref. 34-36).

(a) The ILS system enables to know the aircraft position during the
landing phase with respect to a predetermined descent path.
This system is composed of:
- two ILS receivers
- a Localizer antenna
- a Glide/Slope antenna.

(b) The MMR system is a navigation system with two internal

receivers, the Instrument Landing System (ILS) and the Global
Positioning System (GPS).

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 1
_ The ILS function is to provide the crew and the airborne
system users with lateral (LOC) and vertical (Glide/Slope)
deviations signals, with respect to the approach ILS radio
beam transmitted by a ground station.

2
_ The GPS function is a radio aid to worldwide navigation which
provides:
- the crew with a readout of accurate navigation information,
e.g. position, track and speed.
- the Flight Management and Guidance Computer (FMGC) with
position information, for accurate position fixing.
The MMR system is composed of:
- two MMR receivers
- a Localizer antenna
- a Glide/Slope antenna
- two GPS ACTIVE antennas.

D. Independent Position Determining

This part of the navigation system, which is basically independent of
ground installations, provides data on the position of the aircraft. It
comprises :

(1) Weather radar system

The weather radar system is a X-band system which can be capable of
the Predictive Windshear function. This system enables:
- detection and localization of the atmospheric disturbances in the
area defined by the antenna scanning with visual display of their
intensity
- presentation of terrain mapping information by the combination of
the orientation of the radar beam and of the receiver gain
- detection and presentation of windshear events in the area defined
by the antenna scanning (if the Predictive Windshear function is
operative).

NOTE : The Electronic Flight Instrumental System (EFIS) controls the

____
operation and superimposes the weather picture on the
Navigation Display.

This system is made up of the following components :

- one or two transceivers (transceiver 2 is optional)
- a control unit
- a flat plate antenna and its drive unit.
More explanations are given in the W/R system (Ref. 34-41).

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 (2) Radio altimeter
The function of the radio altimeter is to determine precisely and
continuously, the height of the aircraft from 0 to 2500 ft above the
terrain independently of the atmospheric pressure.
The Height and Decision Height data are displayed on the PFD. The
selection and reading of Decision Height are performed on the
Multipurpose Control and Display unit (MCDU).
The radio altimeter system is composed of:
- two transceivers
- four identical antennas, one for transmission and one for reception
for each transceiver.
More explanations are given in the RA system (Ref. 34-42).

(3) Traffic Collision Avoidance System (TCAS) (optional system)

The TCAS is designed to protect a volume of airspace around the TCAS
equipped aircraft. The function of the TCAS II is to determine the
range, altitude and bearing of other aircraft equipped with ATC
transponders. The system monitors the trajectory of the other
aircraft for the purpose of determining if any of them constitute a
potential collision hazard. If a potential conflict exists, the
system provides the pilots with aural and visual advisories which
indicate the vertical avoidance maneuvers.
The aircraft is equipped with :
- a TCAS computer unit
- two TCAS antennas.
The system exchanges data with the Air Traffic Control (ATC) System.
Traffic advisories are shown on the EFIS displays.
More explanations are given in the TCAS system (Ref. 34-43).

(4) Gound Proximity Warning System (GPWS)

This system is used to inform the crew if the aircraft is in a
dangerous configuration when approaching the ground in a
non-predetermined manner.

(a) The GPWS generates aural and visual warnings if the aircraft
adopts a potentially hazardous condition with respect to:
- Mode 1 - Excessive rate of descent
- Mode 2 - Excessive closure rate with terrain
- Mode 3 - Descent after takeoff and minimum terrain clearance
- Mode 4 - Unsafe terrain clearance
- Mode 5 - Descent below glide slope.
The system is operative between 30ft and 2450ft radio altitude.

(b) Enhanced Ground Proximity Warning System (Enhanced GPWS)

(optional system)
The purpose of the Enhanced GPWS is to alert the flight crew of
potentially hazardous conditions with respect to the terrain.

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 The following Enhanced features have been added to existing basic
Ground Proximity Warning Modes 1 to 5 which are the backbone of
the system:
- Terrain Clearance Floor (TCF) function. It creates an
increasing terrain clearance envelope around the intended
airport runway directly related to the distance from the
runway. The TCF function generates aural and visual alerts.
- Terrain Awareness alerting and Display (TAD) function. This
function uses aircraft geographic position, aircraft altitude
and a terrain data base to predict potential conflicts between
the aircraft flight path and the terrain, and to provide
graphic displays of the conflicting terrain on the NDs.
The terrain awareness alerting algorithms continuously compute
terrain clearance envelopes ahead of the aircraft.
More explanations are given in the GPWS system (Ref. 34-48).

E. Dependent Position Determining

This part of the navigation system comprises :

(1) Distance Measuring Equipment (DME)

The DME enables the distance separating the aircraft from one or two
DME station being received to be known.
The DME is made up of two systems comprising respectively :
- a DME interrogator
- a transmission/reception antenna.
The system receives frequency information from FMGCs or RMPs.
The slant range distance is displayed on NDs and PFDs.
More explanations are given in the DME system (Ref. 34-51).
The slant range distance is displayed also on a VOR/DME Radio
Magnetic Indicator (RMI) or a VOR/ADF/DME RMI (optional) (Ref.
34-57).

(2) Air Traffic Control (ATC)

The ATC allows an operator of the corresponding equipment on the
ground to locate and identify the aircraft in flight without having
to communicate with the crew.
The system is made up of the following components :
- two ATC transponders
- a ATC/TCAS control unit
- four ATC antennas: two bottom antennas and two top antennas
(optional).
More explanations are given in the ATC system (Ref. 34-52).

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 (3) Automatic Direction Finder (ADF)
The ADF enables the bearings of one or two ADF ground transmitter
stations to be permanently indicated with respect to the aircraft
heading.
The system is made up of the following components :
- one or two transceivers (transceiver 2 is optional)
- two ADF loop and sense antennas.
The system receives frequency information from FMGCs or RMPs.
The ADF bearings are displayed on:
- two EFIS Navigation Displays (in Rose mode).
- a Radio Magnetic Indicator (RMI) (optional) (Ref. 34-57).
More explanations are given in the ADF system (Ref. 34-53).

(4) VHF Omni-Range (VOR)

The VOR firstly enables the bearings of one or two VOR ground
transmitter stations to be permanently indicated with respect to the
aircraft heading, and secondly it indicates the aircraft course
deviation with respect to a preselected course.
The system is made up of the following components :
- two VOR/MKR receivers
- a VOR antenna to supply the two VOR/MKR receivers
- a MARKER antenna to supply the VOR/MKR receiver 1 which is the only
one to ensure the MARKER function.
The system receives frequency information from FMGCs or RMPs.
VOR data are displayed on:
- two EFIS PFDs
- two EFIS NDs
- a VOR/DME Radio magnetic Indicator (RMI) or a VOR/ADF/DME RMI
(optional) (Ref. 34-57).
Marker data are displayed on CAPT and F/O PFDs and NDs.
More explanations are given in the VOR/MARKER system (Ref. 34-55).

(5) Global Positioning System (GPS) (optional system)

The GPS system is a radio aid to worldwide navigation which provides:
- the crew with a readout of accurate navigation information, e.g.
position, track and speed.
- the Flight Management and Guidance Computer (FMGC) with position
information for accurate position fixing.
To this end, the GPS system uses signals broadcast by a constellation
of 24 satellites at a frequency of 1575.42 MHz.
The GPS system is composed of:
- two GPS Sensor Units (GPSSUs)
- two GPS antennas.
More explanations are given in the GPS system (Ref. 34-58).

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 AIR DATA/INERTIAL REFERENCE SYSTEM (ADIRS) - DESCRIPTION AND OPERATION
______________________________________________________________________

1. General
_______
R
The main air data and heading/attitude data are provided by a three-channel
Air Data Inertial Reference System (ADIRS).
This configuration provides for triple redundant information for all
inertial and air data functions.
Each channel is isolated from the others and provides independent
information as defined by ARINC Characteristic 738.
The ADIRS comprises:
- Three Air Data/Inertial Reference Units (ADIRU(s)) (ATA 34-12)
- A control and Display Unit (CDU) (ATA 34-12)
- Three pitot probes (ATA 34-11)
- Six static probes (ATA 34-11)
- Eight Air Data Modules (ADMs) Linked to the pitot and static probes (ATA
34-11)
- Two Total Air Temperature (TAT) sensors (ATA 34-11)
- Three Angle of Attack (AOA) sensors (ATA 34-11)
Each of the ADIRUs contains two portions:
- the Air Data Reference (ADR) portion which supplies air data parameters
(ATA 34-13)
- the Inertial Reference (IR) portion which supplies attitude and navigation
parameters (ATA 34-14).
These parameters are transmitted to the user systems on ARINC 429 BUSES.
The Built-In Test Equipment (BITE) is included in the ADIRUs and the ADMs.
It detects and identifies a failure related to the ADIRS and reports it to
the Centralized Fault Display System (CFDS) (ATA 34-18).

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 AIR DATA/INERTIAL REFERENCE SYSTEM (ADIRS) - MAINTENANCE PRACTICES
__________________________________________________________________

TASK 34-10-00-860-002

ADIRS Start Procedure

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
31-60-00-860-001 EIS Start Procedure

3. __________
Job Set-up

Subtask 34-10-00-860-061

A. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-

002).

(2) Do the EIS start procedure (PFDs and NDs only) (Ref. TASK 31-60-00-
860-001).

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 Subtask 34-10-00-010-065

B. Get Access

(1) Put the access platform in position at the access door 822.

(2) Open the access door 822

(3) On the battery power center 105VU:

- loosen the two screws and remove the protective cover

Subtask 34-10-00-865-070

C. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV PROBES/ADIRU3/PWR/SWTG 8FP F09
49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07
49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06
105VU ADIRS/ADIRU1/28VDC 6FP1 C02

R **ON A/C 001-004,

121VU ADIRS/ADIRU/2PWR/SHED 10FP N11

121VU ADIRS/ADIRU/3PWR/SWTG 9FP N10
121VU ADIRS/ADIRU/2/26VAC AND AOA 5FP2 N09
121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N08
121VU ADIRS/ADIRU/2/115VAC 4FP2 N07
121VU ADIRS/ADIRU/3/115VAC 4FP3 N06
121VU ADIRS/ADIRU/2/28VDC 6FP2 N05
121VU ADIRS/ADIRU/3/28VDC 6FP3 N04

R **ON A/C 005-099,

R 121VU ADIRS/ADIRU/2PWR/SHED 10FP N10

R 121VU ADIRS/ADIRU/3PWR/SWTG 9FP N09
R 121VU ADIRS/ADIRU/2/26VAC AND AOA 5FP2 N08
R 121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N07
R 121VU ADIRS/ADIRU/2/115VAC 4FP2 N06
R 121VU ADIRS/ADIRU/3/115VAC 4FP3 N05
R 121VU ADIRS/ADIRU/2/28VDC 6FP2 N04
R 121VU ADIRS/ADIRU/3/28VDC 6FP3 N03

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R **ON A/C ALL

4. Procedure
_________

Subtask 34-10-00-710-065

A. ADIRS Start Procedure

(1) On the overhead panel, on the ADIRS CDU, set the three OFF/NAV/ATT
selector switches to NAV.

(2) Make sure that the ON BAT light comes on for 5 seconds and the ALIGN
legend of the IR1, IR2 and IR3 annunciators comes on.

(3) Make sure that the FAULT and OFF legends of the ADR1, ADR2 and ADR3
pushbutton switches are off.

(4) On the CAPT and F/O main instrument panels, on the PFDs :
- make sure that the CAS, ALT and V/S come into view.
- make sure that the attitude data come into view 40 seconds
approximetaly after the three selector switches are at NAV.

(5) On the ADIRS CDU, set the SYS DISPLAY selector switch to 1 and the
DATA DISPLAY selector switch to PPOS, and make sure that dashes are
shown on the CDU display.

5. Close-up
________

Subtask 34-10-00-410-065

A. Close Access

(1) Install the protective cover on the battery power center 105VU.

(2) Tighten the two screws.

(3) Close the access door 822.

(4) Remove the access platform(s).

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 TASK 34-10-00-860-004

IR Alignment Procedure

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
31-60-00-860-001 EIS Start Procedure

3. __________
Job Set-up

Subtask 34-10-00-860-057

A. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-

002).

(2) Do the EIS start procedure (Ref. TASK 31-60-00-860-001).

(3) On the overhead panel:

- on the FLT CTL panels 23VU and 24VU, make sure that the FAC, ELAC
and SEC pushbutton switches are not pushed (in). The OFF legends
are on.
- on the ADIRS CDU, make sure that the three OFF/NAV/ATT selector
switches are at OFF.

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 (4) On the glareshield, on the CAPT and F/O EFIS control sections of the
FCU, set the mode selector switches to ROSE/NAV.

NOTE : (1) During the alignment phase until the NAV mode is got, the
____
aircraft must not move.

NOTE : (2) During the alignment phase necessary to get the NAV mode,
____
the time for alignment is shown:
- in the right part of the display of the ADIRS CDU, if the
DATA DISPLAY selector switch is at HDG. The indication is as
follows: TTN5
- on the upper ECAM display unit, minute after minute (from 6
MN to 1 MN) as follows: IRS IN ALIGN 6 MN.

Subtask 34-10-00-010-062

B. Get Access

(1) Put the access platform in position at the access door 822.

(2) Open the access door 822.

(3) On the battery power center 105VU:

- loosen the two screws and remove the protective cover.

Subtask 34-10-00-865-079

C. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU AUTO FLT/FCU/1 9CA1 B05
49VU AUTO FLT/FMGC/1 10CA1 B02
49VU AUTO FLT/MCDU/1 11CA1 B01
49VU L/G/LGCIU/SYS1/NORM 1GA C09
49VU NAV PROBES/ADIRU3/PWR/SWTG 8FP F09
49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07
49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06
105VU ADIRS/ADIRU1/28VDC 6FP1 C02

R **ON A/C 001-004,

R
121VU ADIRS/ADIRU/2PWR/SHED 10FP N11
121VU ADIRS/ADIRU/3PWR/SWTG 9FP N10

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 -------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
121VU ADIRS/ADIRU/2/26VAC AND AOA 5FP2 N09
121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N08
121VU ADIRS/ADIRU/2/115VAC 4FP2 N07
121VU ADIRS/ADIRU/3/115VAC 4FP3 N06
121VU ADIRS/ADIRU/2/28VDC 6FP2 N05
121VU ADIRS/ADIRU/3/28VDC 6FP3 N04

R **ON A/C ALL

R 121VU CFDS/CFDIU/SPLY 2TW J18

R 121VU CFDS/CFDIU/BACK/UP 8TW J17
R 121VU AUTO FLT/FCU/2 9CA2 M21
R 121VU AUTO FLT/FMGC/2 10CA2 M17
R 121VU AUTO FLT/MCDU/2 11CA2 N20
121VU HYDRAULIC/LGCIU/SYS2 2GA Q35
121VU HYDRAULIC/LGCIU/SYS1/GRND SPLY 52GA Q34

R **ON A/C 005-099,

R 121VU ADIRS/ADIRU/2PWR/SHED 10FP N10

R 121VU ADIRS/ADIRU/3PWR/SWTG 9FP N09
R 121VU ADIRS/ADIRU/2/26VAC AND AOA 5FP2 N08
R 121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N07
R 121VU ADIRS/ADIRU/2/115VAC 4FP2 N06
R 121VU ADIRS/ADIRU/3/115VAC 4FP3 N05
R 121VU ADIRS/ADIRU/2/28VDC 6FP2 N04
R 121VU ADIRS/ADIRU/3/28VDC 6FP3 N03

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R **ON A/C ALL

4. Procedure
_________

Subtask 34-10-00-860-058

A. IR Alignment from the ADIRS CDU

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the ADIRS CDU: On the ADIRS CDU:

- set the three OFF/NAV/ATT - the OFF legend of the ADR1, ADR2 and
selector switches to NAV ADR3 pushbutton switches stays off.
- the ON BAT light stays on for 5
seconds.
- the ALIGN legend comes on.
After approximately 40 seconds:
- on the CAPT and F/O PFDs:
. the ATT warning flags go out of
view.
. the attitude data come into view.
- on the upper ECAM display unit, the
memo section shows IRS IN ALIGN > 7
MN.

- set the DATA DISPLAY selector

switch to PPOS
- set the SYS DISPLAY selector
switch to 1

- on the CDU keyboard, enter the The ADIRS CDU shows the coordinates
present position (example for N 43-36-8 (in the left part of the
Toulouse): display) and
N 43⁰ 36< 8<< then push the ENT E 1-21-9 (in the right part of the
key, display).
E 1⁰ 21< 9<< then push the ENT
key.

NOTE : If the coordinates are

____
incorrect, push the CLR
key and enter new data as
above.

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
NOTE : If an incorrect longitude
____
is entered two times in
sequence during PPOS
entry, the ADIRU<s will
accept this position until
the subsequent alignment.

- set the SYS DISPLAY selector After a time delay of approximately 5

switch to 2, then to 3 and make minutes:
sure that the coordinates shown - on the CAPT and F/O NDs , the HDG
are the same for the three warning flags go out of view and the
ADIRUs. Set the SYS DISPLAY heading dial comes into view.
selector switch to 1. After a time delay of approximately 10
minutes:
- on the ADIRS CDU, the ALIGN legend of
the IR1, IR2 and IR3 annunciators
goes off
- on the upper ECAM display unit, the
IRS IN ALIGN 1 MN indication goes out
of view and the IRS ALIGNED
indication comes into view (the
ADIRUs are in the NAV mode).

-----------------------------------------------------------------------------
MAINTENANCE INDICATION | DESCRIPTION
ON THE CDU |
-----------------------------------------------------------------------------
STS - IRU FAULT | Critical failure. Remove the IRU for
| maintenance.
STS - DELAYED MAINT | Non critical failure. Remove the IRU
| if necessary.
STS - ENTER P POS | Enter the present position.
STS - SELECT ATT | Non critical failure. Set the ATT mod
STS - XCESS MOTION | Excessive movements of the aircraft
| during the alignment.
STS - ADR FAULT | ADR non valid.
STS - CHECK CK/BK | Do the check of the circuit breaker.
STS - CDU FAULT | Remove the CDU for maintenance.
STS - ENT MAG HDG | Enter the magnetic heading in
| attitude mode.

NOTE : These status indications are given to help you. They come into
____
view only when the DATA DISPLAY selector switch on the ADIRS CDU
is at STS, after a fault detection.

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 Subtask 34-10-00-860-059

B. IR Alignment from the MCDU:

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the circuit breaker panel

121VU:
- open the circuit breaker 10CA2.

2. On the ADIRS CDU: On the ADIRS CDU:

- set the three OFF/NAV/ATT - the OFF legend of the ADR pushbutton
selector switches to NAV. switches stays off after flashing
twice
- the ON BAT light comes on for 5
seconds.
- the ALIGN legend of the IR1, IR2 and
IR3 annunciators comes on.
On the upper ECAM display unit the memo
section shows IRS IN ALIGN > 7 MN (only
if the FMGEC 1 and 2 energized)
On the CAPT and F/O PFDs:
- CAS, V/S and ALT data come into view.
- after approximately 40 seconds the
ATT warning flags go out of view and
the attitude data come into view.

- set the SYS DISPLAY selector

switch to 1 (2 or 3) and the
DATA DISPLAY selector switch to
PPOS.

3. On the MCDU1 or 2: On the MCDU1 or 2:

- turn the BRT knob. The MCDU MENU page comes into view.
- push the MCDU MENU mode key.

- push the line key adjacent to The A/C status page comes into view.
FMGC indication.

- push the INIT mode key. The INIT A page comes into view.

- enter an airline code route. The code number is shown in the

scratchpad line (lower part of the
MCDU).

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
- push the line key adjacent to - The code number comes into view below
the CO RTE indication the CO RTE indication.
- The latitude and longitude are shown
below the LAT and LONG indications.
The slew prompts (arrow up and arrow
down) adjacent to the LAT indication
are shown.
- The ALIGN IRS indication is shown on
the line above the LONG coordinates.

NOTE : You can increase or decrease the

____
LAT or/and LONG magnitude as
indicated in para. 4 and 5. If
no LAT or LONG change is
necessary, go to the para. 6.

NOTE : If an incorrect longitude is

____
entered two times in sequence
during PPOS entry, the ADIRU<s
will accept this position until
the subsequent alignment.

4. For the LAT change:

- on the MCDU keyboard, push one The LAT coordinates increase or

of the two slew keys. decrease:
- by 1 minute, each time you push the
slew key
- by 1 minute/second, if you push and
hold the slew key.

5. For the LONG change:

- on the MCDU, push the line key The slew prompts (arrow up and arrow
adjacent to the LONG down) move to the LONG indication.
coordinates.

- on the MCDU keyboard, push one The LONG coordinates increase or

of the two slew keys. decrease as for the LAT.

6. On the MCDU, push the line key On the MCDU, the ALIGN IRS indication
adjacent to the ALIGN IRS goes out of view.
indication.

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
7. On the ADIRS CDU, set the SYS The coordinates which are in view on
DISPLAY selector switch to 2, the ADIRS CDU are the same as the
then to 3 and make sure that the coordinates shown on the MCDU
coordinates shown are the same After a time delay of approximately 5
for the three ADIRUs. Set the SYS minutes:
DISPLAY selector switch to 1 - on the CAPT and F/O NDs, the HDG
warning flags go out of view and the
heading dial comes into view.
After a time delay of approximately 10
minutes:
- on the ADIRS CDU, the ALIGN legend of
the IR1, IR2 and IR3 goes off.
- on the upper ECAM display unit, the
IRS IN ALIGN 1 MN indication goes out
of view.

8. On the related circuit breaker:

- open the circuit breaker 10CA1.
- close the circuit breaker
10CA2.

9. Do the same test from the para. Same results.

2.

10. On the related circuit breaker

panel, close the circuit breaker
10CA1.

5. Close-up
________

Subtask 34-10-00-410-062

A. Close Access

(1) Install the protective cover on the battery power center 105VU.

(2) Tighten the two screws.

(3) Close the access door 822.

(4) Remove the access platform(s).

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 TASK 34-10-00-860-005

ADIRS Stop Procedure

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied

from the External Power

3. __________
Job Set-up

Subtask 34-10-00-860-069

A. Aircraft Maintenance Configuration

(1) On the center pedestal, on the SWITCHING control panel 8VU:

- set the AIR DATA selector switch to NORM
- set the ATT HDG selector switch to NORM.

4. Procedure
_________

Subtask 34-10-00-860-070

A. ADIRS Stop Procedure

(1) On the ADIRS CDU, set the OFF/NAV/ATT selector switches to OFF.

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 5. Close-up
________

Subtask 34-10-00-860-071

A. Put the aircraft back to its initial configuration.

(1) On the panels 301VU and 500VU, set the PFD and ND potentiometers to
OFF.

(2) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

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 AIR DATA/INERTIAL REFERENCE SYSTEM (ADIRS) - SERVICING
______________________________________________________

TASK 34-10-00-170-001

R Flushing of the Principal Total Pressure Lines

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific dry nitrogen source - 2 bars (29 psi)

No specific access platform 1.6 m (5 ft. 3 in.)
98D34103002000 1 ADAPTERS - AIR DATA SYSTEM FLUSHING
98D34103003000 1 ADAPTER, PITOT - PNEUMATIC CLEANER

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

34-10-00-991-001 Fig. 301

3. __________
Job Set-up

(Ref. Fig. 301/TASK 34-10-00-991-001)

NOTE : The hose couplings are self-sealing.

____

Subtask 34-10-00-010-059

A. Get access to the Avionics Compartment

(1) Put the access platform in position in the zone 123 at the access
door 812 (in the zone 122 at the access door 822).

(2) Open the access door: for ADM 19FP1 (19FP2): 812 (822).

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 Routing of Pressure Lines
Figure 301/TASK 34-10-00-991-001

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 Subtask 34-10-00-860-051

B. Connect the Dry Nitrogen Source

(1) Disconnect the quick-disconnect coupling from the ADM 19FP1 (19FP2).

R (2) Connect a ADAPTERS - AIR DATA SYSTEM FLUSHING 3-pin adapter

R (98D34103002100) to the total pressure hose. Then connect it to the
R dry nitrogen source - 2 bars (29 psi).

R (3) Connect the ADAPTER, PITOT - PNEUMATIC CLEANER (98D34103003000) to

the dry nitrogen source - 2 bars (29 psi).

(4) Attach the hose to prevent movement.

4. Procedure
_________

Subtask 34-10-00-170-050

A. Flushing of the Total Pressure Line

(1) Blow the gas into the hose at a pressure of 2 bars (29 psi) for
approximately 3 minutes.

(2) Put the pneumatic cleaner pitot adapter on the draining hole of the
pitot probe 1(2) and blow the gas for approximately 30 seconds.

(3) Make sure that there is no contamination in the pressurized gas at

the outlet of the pitot probe 1(2).

(4) Stop the flow of gas.

(5) Disconnect the dry nitrogen source.

R (6) Remove the 3-pin adapter .

(7) Release the hose.

(8) Connect the quick-disconnect coupling to the ADM 19FP1 (19FP2).

NOTE : After the connection:

____
- make sure that a colored ring is shown on the
quick-disconnect coupling
- pull the connectors to be sure that they are correctly
attached.

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 5. Close-up
________

Subtask 34-10-00-410-059

A. Close Access

(1) Make sure that the work area is clean and clear of tool(s) and other
items.

(2) Close the access door 812 (822).

(3) Remove the access platform(s).

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 TASK 34-10-00-170-002

Flushing of the Principal Static Pressure Lines

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific dry nitrogen source - 2 bars (29 psi)

No specific access platform 1.6 m (5 ft. 3 in.)
98D34103002000 1 ADAPTERS - AIR DATA SYSTEM FLUSHING

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

R 52-41-00-410-002 Close the Avionics Compartment Doors after Access

34-10-00-991-001 Fig. 301

3. __________
Job Set-up

(Ref. Fig. 301/TASK 34-10-00-991-001)

NOTE : The hose couplings are self-sealing.

____

Subtask 34-10-00-010-060

A. Get access to the Avionics Compartment

(1) Put the access platform in position in the zone 128 at the access
door 824.

(2) Open the access door 824.

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 Subtask 34-10-00-860-052

B. Connect the Dry Nitrogen Source

(1) Disconnect the quick-disconnect coupling from the ADM 19FP4 or 19FP5
(19FP6 or 19FP7).

R (2) Connect a ADAPTERS - AIR DATA SYSTEM FLUSHING (98D34103002000) 3-pin

R adapter (98D34103002100) to the static pressure hose. Then connect it
R to the dry nitrogen source - 2 bars (29 psi).

(3) Attach the hose to prevent movement.

4. Procedure
_________

Subtask 34-10-00-170-051

A. Flushing of the Static Pressure Line

(1) Blow the gas into the hose at a pressure of 2 bars (29 psi) for
approximately 1 minute.

(2) Make sure that there is no contamination in the pressurized gas at

the outlet of the L or R static probe 1 (L or R static probe 2).

(3) Stop the flow of gas.

(4) Disconnect the dry nitrogen source.

R (5) Remove the 3-pin adapter .

(6) Release the hose.

(7) Connect the quick-disconnect coupling to the ADM 19FP4 or 19FP5

(19FP6 or 19FP7).

NOTE : After the connection:

____
- make sure that a colored ring is shown on the
quick-disconnect coupling
- pull the connectors to be sure that they are correctly
attached.

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 5. Close-up
________

Subtask 34-10-00-410-060

A. Close Access

(1) Make sure that the work area is clean and clear of tool(s) and other
items.

R (2) Close the access door 824 (Ref. TASK 52-41-00-410-002).

(3) Remove the access platform(s).

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 TASK 34-10-00-170-003

Draining and Flushing of the Standby Static and Standby Total Pressure Lines

1. __________________
Reason for the Job

Refer to the MPD TASK: 342100-02

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific blanking cap

No specific dry nitrogen source - 2 bars (29 psi)
No specific access platform 1.6 m (5 ft. 3 in.)
98D34003500000 2 ADAPTER COVER-STATIC PORT
98D34103002000 1 ADAPTERS - AIR DATA SYSTEM FLUSHING
98D34103003000 1 ADAPTER, PITOT - PNEUMATIC CLEANER

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

12-24-34-600-001 Bleeding of the Standby Air Data System

34-21-00-790-001 Leak Test of the Standby Air Data System
34-21-22-000-001 Removal of the Standby Altimeter (3FN)
34-21-22-400-001 Installation of the Standby Altimeter (3FN)
34-21-26-000-001 Removal of the Standby Airspeed Indicator (9FN)
34-21-26-400-001 Installation of the Standby Airspeed Indicator (9FN)
34-10-00-991-002 Fig. 302

3. __________
Job Set-up

(Ref. Fig. 302/TASK 34-10-00-991-002)

NOTE : The hose couplings are self-sealing.

____

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 Location of Components Related to the Standby Pressure Lines-Schematic
Figure 302/TASK 34-10-00-991-002

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 Subtask 34-10-00-010-061

A. Get Access

(1) Put the access platform in position in the zone 110 at the access
door 811.

(2) Open the access door 811.

Subtask 34-10-00-860-053

B. Aircraft Maintenance Configuration

(1) Drain the standby air data system (Ref. TASK 12-24-34-600-001).

(2) Disconnect the quick-disconnect coupling (4) from the ADM 19FP8 and
the quick-disconnect coupling (8) from the ADM 19FP3.

(3) Disconnect the cabin-pressure detection pressure-switch 14WN (3) from

the quick-disconnect coupling. Put a blanking cap on the pressure
switch.

(4) Remove the water drain plug (2) from the water drain (1).

(5) In the cockpit, on the center instrument panel:

- remove the standby altimeter 3FN (Ref. TASK 34-21-22-000-001)
- remove the standby airspeed indicator (6) 9FN (Ref. TASK 34-21-26-
000-001).

(6) Disconnect the quick-disconnect coupling (7) from the red 2-pin
coupling of the standby airspeed indicator (6) and disconnect the
quick-disconnect couplings (5) from the yellow 3-pin couplings of the
standby instruments 3FN and 9FN.

R (7) Connect a ADAPTERS - AIR DATA SYSTEM FLUSHING 3-pin adapter

R (98D34103002100) ) to the hose of the standby altimeter and a
R ADAPTERS - AIR DATA SYSTEM FLUSHING 2-pin adapter (98D34103002102) to
R the hose (7). Then connect to the dry nitrogen source - 2 bars (29
psi).

(8) Connect the ADAPTER, PITOT - PNEUMATIC CLEANER to the dry nitrogen
source - 2 bars (29 psi).

(9) Attach the hoses to prevent movement.

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 4. Procedure
_________

Subtask 34-10-00-170-052

A. Draining and Flushing of the Standby Static and the Standby Total
Pressure Lines

(1) Blow the gas into each of the instrument hoses (5) and into the hose
(7), from one to the other, at a pressure of 2 bars (29 psi). Do this
for approximately 5 minutes.

(2) Put the pneumatic cleaner pitot adapter on the draining hole of the
pitot probe 3 and blow the gas for approximately 30 seconds.

(3) Make sure that there is no contamination in the pressurized gas at

these outlets:
- L static probe 3 and R static probe 3
- Pitot probe 3
- Water drain
- Pipe of the cabin-pressure detection pressure-switch.

(4) Put an ADAPTER COVER-STATIC PORT on the L static probe 3 then on the
R static probe 3.

(5) Make sure that the flow of gas is correct at :

- the pipe of the pressure switch
- the water drain.

(6) Stop the flow of gas.

Subtask 34-10-00-860-054

B. Put the aircraft back to its initial configuration.

(1) Disconnect the dry nitrogen source.

R (2) Remove the adapters.

(3) Install the water drain plug (2) on the water drain (1).

(4) Remove the blanking cap from the pressure switch 14WN (3).

(5) Connect the quick-disconnect coupling to the pressure switch 14WN

(3).

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 (6) Connect the quick-disconnect coupling (8) to the ADM 19FP3 and the
quick-disconnect coupling (4) to the ADM 19FP8.

NOTE : After the connection:

____
- make sure that a colored ring is shown on the
quick-disconnect couplings (4) and (8)
- pull the connectors to be sure that they are correctly
attached.

(7) Install the standby airspeed indicator (Ref. TASK 34-21-26-400-001)

and the standby altimeter (Ref. TASK 34-21-22-400-001) on the center
instrument panel.

(8) Release the hoses.

Subtask 34-10-00-790-052

C. Leak test

(1) Make sure that all the hoses are connected correctly.

(2) Do a leak test of the standby air data system

(Ref. TASK 34-21-00-790-001).

5. Close-up
________

Subtask 34-10-00-410-061

A. Close Access

(1) Make sure that the work area is clean and clear of tool(s) and other
items.

(2) Remove the ground support and maintenance equipment, the special and
standard tools and all other items.

(3) Close the access door 811.

(4) Remove the access platform(s).

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 AIR DATA/INERTIAL REFERENCE SYSTEM (ADIRS) - DEACTIVATION/REACTIVATION
______________________________________________________________________

TASK 34-10-00-040-001

Check of the ADR1

1. __________________
Reason for the Job

Refer to the MMEL TASK: 34-10-01

Air data inertial reference
ADIRS

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

R No specific circuit breaker(s) safety clip(s)

No specific access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
31-32-00-860-010 Procedure to Get Access to the SYSTEM REPORT/TEST NAV
Page
31-60-00-860-001 EIS Start Procedure
31-60-00-860-002 EIS Stop Procedure

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 3. __________
Job Set-up

Subtask 34-10-00-860-072

A. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-

002).

(2) On the center pedestal, on the MCDU, get the SYSTEM REPORT/TEST/NAV
page
(Ref. TASK 31-32-00-860-010).

(3) Do the EIS start procedure (Ref. TASK 31-60-00-860-001).

(4) On the overhead panel:

- on the ADIRS CDU, set the OFF/NAV/ATT selector for ADR1 to NAV.
- on the ELEC panel 35VU, make sure that the battery voltage is
correct, between 26VDC and 30VDC.

(5) On the center pedestal, on the ECAM control panel, push the STS key.

(6) On the glareshield 13VU, on the CAPT EFIS control sections of the
FCU, set the mode selector switch to ROSE/NAV.

Subtask 34-10-00-010-066

B. Get Access

(1) Put the access platform in position at the access door 822.

(2) Open the access door 822.

(3) On the battery power center 105VU:

- loosen the two screws and remove the protective cover.

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 Subtask 34-10-00-865-080

C. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU AUTO FLT/FCU/1 9CA1 B05
49VU L/G/LGCIU/SYS1/NORM 1GA C09
49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07
49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06
105VU ADIRS/ADIRU1/28VDC 6FP1 C02
121VU AUTO FLT/FCU/2 9CA2 M21
121VU HYDRAULIC/LGCIU/SYS2 2GA Q35
121VU HYDRAULIC/LGCIU/SYS1/GRND SPLY 52GA Q34

R Subtask 34-10-00-865-081

R D. Open, safety and tag this(these) circuit breaker(s):

R -------------------------------------------------------------------------------
R PANEL DESIGNATION IDENT. LOCATION
R -------------------------------------------------------------------------------
R 105VU ELEC/CSM/G /EV AUTO/SPLY 7XE C01

4. Procedure
_________

Subtask 34-10-00-740-052

A. Check of the ADR1

NOTE : - Ignore the warnings and indications (VLE, ...) which are not
____
related to this ADR1 test.
- The actions and the results of this procedure occur on the MCDU
used.

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the ADIRS CDU:

- push the ADR2 and ADR3 The OFF legend of the ADR2 and ADR3
pushbutton switches pushbutton switches comes on.
On the CAPT PFD, the SPD and ALT flags
go out view. The speed and altitude
indications (30 Kts and local altitude)
are shown.

2. On the MCDU: On the MCDU:

- push the line key adjacent to - the ADIRS ADR1 1/2 page comes into
the ADR1 indication view.

- push the line key adjacent to - the ADIRS ADR1 INTERFACE TEST page
the INTERFACE TEST indication comes into view.

- push the line key adjacent to From 0 to 5 seconds:

the TEST START indication - on the ADIRS CDU, the FAULT and OFF
legends of the ADR1 pushbutton switch
come on then go off
- on the CAPT PFD, the symbols on the
speed and altitude scale go out view.
The SPD and ALT warning flags flash
for some seconds
- on the CAPT ND, the TAS indication
goes out view
- on the panels 130VU and 131VU, the
MASTER CAUT lights come on
- you can hear the single chime.
From 5 to 10 seconds:
- on the CAPT PFD, the warnings go out
of view
- on the lower ECAM display unit, in
the Inop System part, the message ADR
2 + 3 comes into view
- on the CAPT (F/O) PFD, the altitude
increases.
After 10 seconds:
- on the CAPT (F/O) PFD, these values
are shown:
CAS: 367.7Kts
MACH: 0.66 M

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
ALTITUDE: 10000 Ft
- on the CAPT (F/O) ND, this value is
shown:
TAS: 433 Kts
- on the upper ECAM display unit, this
indication is shown:
OVERSPEED
VMO/MMO 350/.82

- push the line key adjacent to The test procedure stops:

the RETURN/TEST STOP - on the upper ECAM display unit, the
indication. OVERSPEED warning indication goes out
of view
- on the CAPT PFD, the speed and
altitude indications go back to their
initial value
- on the MCDU, make sure that there are
no class 1 or Class 2 messages.
These messages can come into view:
- SFCC1 (21CV)/SFCC2 (22CV)/ADIRU1
(1FP1)
or
- SFCC 1/2 (21CV/22CV)/ADIRU1 (1FP1)
AOA INPUT A
or
- SFCC 1/2 (21CV/22CV)/ADIRU1 (1FP1)
AOA INPUT B
or
- SFCC1 (21CV) /SFCC2 (22CV)

5. Close-up
________

Subtask 34-10-00-860-073

A. Put the aircraft back to its initial configuration.

(1) On the MCDU, push the line key adjacent to the RETURN indication
until the CFDS menu page comes into view.

(2) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002).

(3) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

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 Subtask 34-10-00-410-066

B. Close Access

(1) Install the protective cover on the battery power center 105VU.

(2) Tighten the two screws.

(3) Close the access door 822.

(4) Remove the access platform(s).

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 TASK 34-10-00-040-002

ADIRS - Check of all Flight Control Accelerometers for Correct Operation

1. __________________
Reason for the Job

Refer to the MMEL TASK: 34-10-01

Air data inertial reference
ADIRS
ADIRS (FAA Only)

2. ______________________
Job Set-up Information

A. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

AMM 24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
AMM 24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
AMM 27-96-00-740-001 BITE Test of the EFCS (Ground Scanning)
AMM 31-60-00-860-001 EIS Start Procedure
AMM 31-60-00-860-002 EIS Stop Procedure

3. __________
Job Set-up

Subtask 34-10-00-860-077

A. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits

(Ref. AMM TASK 24-41-00-861-002).

(2) Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only)
(Ref. AMM TASK 31-60-00-860-001).

(3) On the center pedestal, on the ECAM control panel, push the STS key
(on the lower ECAM DU, the STATUS page comes into view).

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 4. Procedure
_________

Subtask 34-10-00-040-050

A. Make sure that there is no F/CTL maintenance status on the STATUS page.
If there is the F/CTL maintenance status:

(1) Do the BITE test of the EFCS (Ground Scanning) (Ref. AMM TASK 27-96-
00-740-001).

(2) Make sure that there are no maintenance messages related to the
flight control accelerometers 12CE1, 12CE2, 12CE3 and 12CE4.

5. Close-up
________

Subtask 34-10-00-860-078

A. Put the aircraft back to its initial configuration.

(1) Do the EIS stop procedure

(Ref. AMM TASK 31-60-00-860-002).

(2) Make an entry in the logbook.

(3) De-energize the aircraft electrical circuits

(Ref. AMM TASK 24-41-00-862-002).

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 AIR DATA/INERTIAL REFERENCE SYSTEM (ADIRS) - ADJUSTMENT/TEST
____________________________________________________________

TASK 34-10-00-710-001

Check of the ADIRS CDU Brightness and Display

WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE
_______
YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power

3. __________
Job Set-up

Subtask 34-10-00-860-063

A. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits. (Ref. TASK 24-41-00-861-

002)

(2) on the panel 20VU, on the ADIRS CDU, make sure that the three
OFF/NAV/ATT selector switches are at OFF.

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 Subtask 34-10-00-010-063

B. Get Access

(1) Put the access platform in position at the access door 822.

(2) Open the access door 822.

(3) On the battery power center 105VU:

- loosen the two screws and remove the protective cover.

Subtask 34-10-00-865-050

C. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV PROBES/ADIRU3/PWR/SWTG 8FP F09
49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07
49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06
105VU ADIRS/ADIRU1/28VDC 6FP1 C02

R **ON A/C 001-004,

121VU ADIRS/ADIRU/2PWR/SHED 10FP N11

121VU ADIRS/ADIRU/3PWR/SWTG 9FP N10
121VU ADIRS/ADIRU/2/26VAC AND AOA 5FP2 N09
121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N08
121VU ADIRS/ADIRU/2/115VAC 4FP2 N07
121VU ADIRS/ADIRU/3/115VAC 4FP3 N06
121VU ADIRS/ADIRU/2/28VDC 6FP2 N05
121VU ADIRS/ADIRU/3/28VDC 6FP3 N04

R **ON A/C 005-099,

R 121VU ADIRS/ADIRU/2PWR/SHED 10FP N10

R 121VU ADIRS/ADIRU/3PWR/SWTG 9FP N09
R 121VU ADIRS/ADIRU/2/26VAC AND AOA 5FP2 N08
R 121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N07
R 121VU ADIRS/ADIRU/2/115VAC 4FP2 N06
R 121VU ADIRS/ADIRU/3/115VAC 4FP3 N05
R 121VU ADIRS/ADIRU/2/28VDC 6FP2 N04
R 121VU ADIRS/ADIRU/3/28VDC 6FP3 N03

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R **ON A/C ALL

4. Procedure
_________

Subtask 34-10-00-710-050

A. Check from the ADIRS CDU:

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the ADIRS CDU:

- set the three OFF/NAV/ATT
selector switches to NAV

- set the DATA DISPLAY selector - the display (LCD) segments come on
switch to TEST and keep it in - the ENT and CLR keys come on green.
this position.

2. Release the DATA DISPLAY selector

switch.

Subtask 34-10-00-710-051

B. Check from the INT LT ANN LT switch:

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the panel 25VU, set the INT LT On the ADIRS CDU:

ANN LT switch to TEST. - the display (LCD) segments come on
- the ENT and CLR keys come on green
- the ON BAT light comes on
- the FAULT/OFF legends of the ADR
pushbutton switches come on. The
FAULT/ALIGN legends of the IR
annunciators come on.

2. Set the INT LT ANN LT switch to

BRT or DIM.

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 5. Close-up
________

Subtask 34-10-00-860-064

A. De-energize the aircraft electrical circuits. (Ref. TASK 24-41-00-862-

002)

Subtask 34-10-00-410-063

B. Close Access

(1) Install the protective cover on the battery power center 105VU.

(2) Tighten the two screws.

(3) Close the access door 822.

(4) Remove the access platform(s).

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 TASK 34-10-00-710-007

Test of the Angle of Attack Warning

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific circuit breaker(s) safety clip(s)

No specific access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
27-50-00-866-009 Retraction of the Flaps on the Ground
31-32-00-860-010 Procedure to Get Access to the SYSTEM REPORT/TEST NAV
Page
31-60-00-860-001 EIS Start Procedure
31-60-00-860-002 EIS Stop Procedure

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 3. __________
Job Set-up

R CAUTION : MAKE SURE THAT THE AOA SENSOR CAN MOVE FREELY DURING THE TEST (IT
_______
R WILL MOVE FROM THE STANDBY POSITION TO THE TEST POSITION).

Subtask 34-10-00-860-065

A. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-

002).

(2) On the overhead panel:

- on the FLT CTL panels 23VU and 24VU, make sure that the FAC, ELAC
and SEC pushbutton switches are not pushed (in). The OFF legends
are on.
- On the panel 20VU, on the ADIRS CDU, make sure that the three
OFF/NAV/ATT selector switches are at OFF.

(3) Fully retract the flaps (Ref. TASK 27-50-00-866-009)

NOTE : This test is for the system 1. For the systems 2 and 3, use
____
the indications between the parentheses.

(4) Do the EIS start procedure (PFD only) (Ref. TASK 31-60-00-860-001).

(5) On the MCDU, get the SYSTEM REPORT/TEST/NAV page

(Ref. TASK 31-32-00-860-010).

Subtask 34-10-00-010-064

B. Get Access

(1) Put the access platform in position at the access door 822.

(2) Open the access door 822.

(3) On the battery power center 105VU:

- loosen the two screws and remove the protective cover.

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 Subtask 34-10-00-865-064

C. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU L/G/LGCIU/SYS1/NORM 1GA C09
49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07
49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06
105VU ADIRS/ADIRU1/28VDC 6FP1 C02

R **ON A/C 001-004,

121VU ADIRS/ADIRU/2PWR/SHED 10FP N11

121VU ADIRS/ADIRU/3PWR/SWTG 9FP N10
121VU ADIRS/ADIRU/2/26VAC AND AOA 5FP2 N09
121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N08
121VU ADIRS/ADIRU/2/115VAC 4FP2 N07
121VU ADIRS/ADIRU/3/115VAC 4FP3 N06
121VU ADIRS/ADIRU/2/28VDC 6FP2 N05
121VU ADIRS/ADIRU/3/28VDC 6FP3 N04

R **ON A/C ALL

121VU EIS/HORN/SPLY 2WC P09

121VU HYDRAULIC/LGCIU/SYS2 2GA Q35
121VU HYDRAULIC/LGCIU/SYS1/GRND SPLY 52GA Q34

R **ON A/C 005-099,

R 121VU ADIRS/ADIRU/2PWR/SHED 10FP N10

R 121VU ADIRS/ADIRU/3PWR/SWTG 9FP N09
R 121VU ADIRS/ADIRU/2/26VAC AND AOA 5FP2 N08
R 121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N07
R 121VU ADIRS/ADIRU/2/115VAC 4FP2 N06
R 121VU ADIRS/ADIRU/3/115VAC 4FP3 N05
R 121VU ADIRS/ADIRU/2/28VDC 6FP2 N04
R 121VU ADIRS/ADIRU/3/28VDC 6FP3 N03

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R **ON A/C ALL

Subtask 34-10-00-865-076

D. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU AUTO FLT/FAC1/28VDC 5CC1 B04
121VU AUTO FLT/FAC2/28VDC 5CC2 M19

4. Procedure
_________

Subtask 34-10-00-710-062

A. Test of the Angle of Attack Warning

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the ADIRS CDU: On the CAPT and F/O PFDs:

- set the three OFF/NAV/ATT - make sure that the CAS, ALT, V/S data
selector switches to NAV. are shown.
- make sure that the attitude data is
shown 40 seconds after start up.

2. On one MCDU, on the NAV page: On the MCDU:

- push the line key adjacent to - the ADIRS ADR1 (ADR2) (ADR3) page
the ADR1 (ADR2) (ADR3) comes into view.
indication.

- push the line key adjacent to - the OUTPUT TESTS page comes into
the OUTPUT TESTS indication. view.

- push the line key adjacent to - the AOA SENSOR TEST page comes into
the AOA SENSOR TEST indication. view with these indications: AOA
SENSOR COMMANDED TO FIXED POSITION
MAKE SURE THAT THE AURAL STALL
WARNING IS GENERATED.
On the L (R) side of the fuselage, in
the zone 231 (232) (127), the angle of
attack sensor 3FP1 (3FP2) (3FP3) under
test moves to the test position.

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
On the panels 130VU and 131VU, the
MASTER WARN lights flash.
You can hear the cricket aural warning
and the STALL voice.

- Push the line key adjacent to On the MCDU:

the YES indication. - the TEST OK indication comes into
view.

- push the line key adjacent to The test procedure stops.

the RETURN indication until the The warning goes out of view.
CFDS menu page comes into view. On the MCDU:
- the CFDS menu page comes into view.

5. Close-up
________

Subtask 34-10-00-860-066

A. Put the aircraft back to its initial configuration.

(1) On the ADIRS CDU, set the three OFF/NAV/ATT selector switches to OFF.

(2) Do the EIS stop procedure

(Ref. TASK 31-60-00-860-002)

(3) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

(4) Remove the access platform(s).

Subtask 34-10-00-865-077

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
5CC1, 5CC2

Subtask 34-10-00-410-064

C. Close Access

(1) Install the protective cover on the battery power center 105VU.

(2) Tighten the two screws.

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 (3) Close the access door 822.

(4) Remove the access platform(s).

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 TASK 34-10-00-710-009

Operational Test of the 5-minute Time Delay of ADIRU 2 and 3 Power

Disconnection in Emergency Configuration

1. __________________
Reason for the Job

Refer to the MPD TASK: 341300-05

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
31-60-00-860-001 EIS Start Procedure
31-60-00-860-002 EIS Stop Procedure

3. __________
Job Set-up

Subtask 34-10-00-860-067

A. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-

002).

(2) Do the EIS start procedure (Ref. TASK 31-60-00-860-001).

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 (3) On the overhead panel:
- on the FLT CTL panels 23VU and 24VU, make sure that the FAC, ELAC
and SEC pushbutton switches are not pushed (in). The OFF legends
are on.
- on the panel 20VU, on the ADIRS CDU, make sure that the three
OFF/NAV/ATT selector switches are at OFF.
- on the ELEC panel 35VU, make sure that the battery voltage is
correct, between 26VDC and 30VDC.

Subtask 34-10-00-010-057

B. Get Access

(1) Put the access platform in position at the access door 822.

(2) Open the access door 822.

(3) On the battery power center 105VU:

- loosen the two screws and remove the protective cover.

Subtask 34-10-00-865-068

C. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU L/G/LGCIU/SYS1/NORM 1GA C09
49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07
49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06
105VU ADIRS/ADIRU1/28VDC 6FP1 C02

R **ON A/C 001-004,

121VU ADIRS/ADIRU/2PWR/SHED 10FP N11

121VU ADIRS/ADIRU/3PWR/SWTG 9FP N10
121VU ADIRS/ADIRU/2/26VAC AND AOA 5FP2 N09
121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N08
121VU ADIRS/ADIRU/2/115VAC 4FP2 N07
121VU ADIRS/ADIRU/3/115VAC 4FP3 N06
121VU ADIRS/ADIRU/2/28VDC 6FP2 N05
121VU ADIRS/ADIRU/3/28VDC 6FP3 N04

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 -------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
**ON A/C ALL

121VU EIS/HORN/SPLY 2WC P09

121VU HYDRAULIC/LGCIU/SYS2 2GA Q35
121VU HYDRAULIC/LGCIU/SYS1/GRND SPLY 52GA Q34

**ON A/C 005-099,

121VU ADIRS/ADIRU/2PWR/SHED 10FP N10

121VU ADIRS/ADIRU/3PWR/SWTG 9FP N09
121VU ADIRS/ADIRU/2/26VAC AND AOA 5FP2 N08
121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N07
121VU ADIRS/ADIRU/2/115VAC 4FP2 N06
121VU ADIRS/ADIRU/3/115VAC 4FP3 N05
121VU ADIRS/ADIRU/2/28VDC 6FP2 N04
121VU ADIRS/ADIRU/3/28VDC 6FP3 N03

**ON A/C ALL

4. Procedure
_________

Subtask 34-10-00-710-064

A. Operational Test of the 5-minute Time Delay of ADIRU 2 and 3 Power

Disconnection in Emergency Configuration

NOTE : Ignore the ECAM warnings that can occur when you open the circuit
____
breakers 9FP, 10FP, 4FP2, 4FP3 and 2WC.

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the ADIRS CDU: On the ADIRS CDU:

- set the OFF/NAV/ATT selector - the ON BAT light comes on for 5

switches related to the IR 2 seconds.
and IR 3 to NAV. - the ALIGN legend comes on.

R - push the ADR 2 and ADR 3 - the OFF legend comes on.
pushbutton switches. On the F/O PFD:

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
- after approximately 35 seconds, the
attitude is shown.

2. On the circuit breaker panel On the ADIRS CDU:

121VU:

- open the circuit breakers 2WC, - the ON BAT light comes on.
10FP and 4FP2. - the ALIGN legend of the IR 2
annunciator stays on.
R - the OFF legend ADR2 p/b sw goes off.
After 5 minutes
R - the ALIGN legend of the IR 2
R annunciator and the ON BAT light go
R off.
R
On the F/O PFD:
- the ATT warning flag is shown.

3. On the circuit breaker panel On the ADIRS CDU:

121VU:

- close the circuit breakers 10FP - the ON BAT light stays off.
and 4FP2. - the ALIGN legend of the IR 2
annunciator comes on.

4. On the circuit breaker panel On the ADIRS CDU:

121VU:

- open the circuit breakers 9FP - the ON BAT light comes on.
and 4FP3. After 5 minutes:
- the ALIGN legend of the IR 3
annunciator, the OFF legend ADR3 p/b
R sw and the ON BAT light go off.

5. On the circuit breaker panel

121VU:

- close the circuit breakers 2WC, - the ON BAT light stays off.
9FP and 4FP3. - the ALIGN legend of the IR 3
annunciator comes on.

6. On the ADIRS CDU:

- set the two OFF/NAV/ATT
selector switches to OFF.

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 5. Close-up
________

Subtask 34-10-00-860-068

A. Put the aircraft back to its initial configuration.

Do the EIS stop procedure
(Ref. TASK 31-60-00-860-002)

(1) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-

002).

Subtask 34-10-00-410-057

B. Close Access

(1) Install the protective cover on the battery power center 105VU.

(2) Tighten the two screws.

(3) Close the access door 822.

(4) Remove the access platform(s).

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 SENSORS, POWER SUPPLY AND SWITCHING - DESCRIPTION AND OPERATION
_______________________________________________________________

1. _______
General
The aircraft is equipped with three Air Data/Inertial Reference Units
(ADIRUs).
Each ADIRU receives data from the four types of sensors after:
- three pitot probes which provide total pressure data,
- six static probes which provide static pressure data,
- two Total Air Temperature (TAT) sensors which provide air temperature
data,
- three Angle Of Attack (AOA) sensors which provide angle of attack data of
the aircraft.
The TAT sensors and the angle of attack sensors are directly connected to
the ADIRUs. The pitot probes and the static probes are connected to eight
Air Data Modules (ADM) which convert pressure data before they send them to
the ADIRUs.
The sensors, the probes, the ADMs and the ADIRUs are power supplied as
follows:

-------------------------------------------
| EQUIPMENT | 28VDC | 115VAC | 26VAC |
-------------------------------------------
| ADIRU | X | X | X |
|----------------|-------|--------|-------|
| AOA Sensor | | X | X |
|----------------|-------|--------|-------|
| PITOT Probe | | X | |
|----------------|-------|--------|-------|
| TAT Sensor | | X | |
|----------------|-------|--------|-------|
| STATIC Probe | X | | |
|----------------|-------|--------|-------|
| ADM |13.5VAC from ADIRU |
-------------------------------------------

In normal configuration, the Captain Primary Flight Display (PFD) and

Navigation Display (ND) show the data computed by the ADIRU 1.
The First Officer PFD and ND show the data computed by the ADIRU 2.
The data from the ADIRU 3 can be displayed by action on the AIR DATA
selector switch or on the ATT HDG selector switch located on the SWITCHING
panel.
These selector switches which define a priority order for the ADIRUs are
also used by several other aircraft systems (Ref. Para. 4.F.).

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 2. Component
__________________
Location
(Ref. Fig. 001)
The sensors, probes and ADMs are located on the aircraft as follows:

-------------------------------------------------------------------------------
FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA
| | | | DOOR | REF.
-------------------------------------------------------------------------------
3FP1 SENSOR-ANGLE OF ATTACK, 1 127 824 34-11-19
3FP2 SENSOR-ANGLE OF ATTACK, 2 128 824 34-11-19
3FP3 SENSOR-ANGLE OF ATTACK, 3 127 824 34-11-19
11FP1 SENSOR-TAT, 1 121 34-11-18
11FP2 SENSOR-TAT, 2 122 34-11-18
19FP1 ADM-L TOTAL PRESSURE NONE 125 812 34-11-17
19FP2 ADM-R TOTAL PRESSURE 126 822 34-11-17
19FP3 ADM-STBY TOTAL PRESSURE 125 812 34-11-17
19FP4 ADM-R STATIC PRESSURE 128 824 34-11-17
19FP5 ADM-L STATIC PRESSURE 127 824 34-11-17
19FP6 ADM-R STATIC PRESSURE 128 824 34-11-17
19FP7 ADM-L STATIC PRESSURE 127 824 34-11-17
19FP8 ADM-STBY STATIC PRESSURE 121 811 34-11-17
7DA1 PROBE-L STATIC, 1 127 824 34-11-16
7DA2 PROBE-L STATIC, 2 127 824 34-11-16
7DA3 PROBE-L STATIC, 3 121 811 34-11-16
8DA1 PROBE-R STATIC, 1 128 824 34-11-16
8DA2 PROBE-R STATIC, 2 128 824 34-11-16
8DA3 PROBE-R STATIC, 3 122 811 34-11-16
9DA1 PROBE-PITOT, 1 125 812 34-11-15
9DA2 PROBE-PITOT, 2 126 822 34-11-15
9DA3 PROBE-PITOT, 3 125 812 34-11-15

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 ADIRS - Probe and Sensor Location
Figure 001

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 The different ADIRS switching devices are located on the aircraft as
follows:

-------------------------------------------------------------------------------
FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA
| | | | DOOR | REF.
-------------------------------------------------------------------------------
12FP RELAY-ADIRS ON BAT/GROUND WARN 103VU 126 34-11-00
13FP SEL SW-ATT HDG 8VU 210 34-11-00
14FP RELAY-ADIRS 3 PWR SHEDDING 103VU 126 34-11-00
15FP SEL SW-AIR DATA 8VU 210 34-11-00
16FP RELAY-ADIRS 3 28VDC CONTROL 103VU 126 34-11-00
17FP RELAY-ADIRS 2 PWR SHEDDING 103VU 126 34-11-00
21FP1 RELAY-AOA1 TEST 103VU 126 34-11-00
21FP2 RELAY-AOA2 TEST 103VU 126 34-11-00
21FP3 RELAY-AOA3 TEST 103VU 126 34-11-00
22FP SW-L/G DOWN VMO/MMO SELECTION 188VU 128 34-11-00
23FP RELAY-ADIRS LGCIU GND POS 103VU 126 34-11-00
------------------------------------------------------------------------------

NOTE : The function of the switch (22FP) is described in 34-12-00.

____

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 3. ____________
Power Supply

A. General
(Ref. Fig. 002)
The ADIRU is normally supplied with 115VAC, 400 Hz power for the ADR and
IR functions. However its AOA resolver converter module is supplied with
26VAC, 400 Hz.
The 28VDC back-up generation is provided by batteries and is
automatically used when the main power exceeds its normal limits.
At the beginning of each power cycle the ADIRU switches from the main to
the back-up power to test the electrical generation.
The table below gives the power consumption of each unit of the ADIRS:

------------------------------------------------------------------
| EQUIPMENT | 28VDC | 115VAC | 26VAC |
| |-------------------|-------------------| |
| | Typical | Maximum | Typical | Maximum | |
------------------------------------------------------------------
| ADIRU (1) | 67 W | 84 W | 79 VA | 98 VA | 1 VA |
|----------------|---------|---------|---------|---------|-------|
| AOA Sensor | | | 250 VA | 320 VA |3.5 VA |
|----------------|---------|---------|---------|---------|-------|
| PITOT Probe | | | 281 VA | 360 VA | |
|----------------|---------|---------|---------|---------|-------|
| TAT Sensor | | | 200 VA | 350 VA | |
|----------------|---------|---------|---------|---------|-------|
| STATIC Probe | | 2X75 W | | | |
|----------------|---------|---------|---------|---------|-------|
| PHC | | 14 W | | | |
------------------------------------------------------------------

(1) ADIRU power consumption includes the supply of three ADMs.

With ON BAT annunciator, add 5 W.
With IR FAULT annunciator at I = 250 mA, add 10.5 W.
Other annunciators are open/ground discretes and so they are
energized by a power which is different from the ADIRU power.
When the ADIRU is in the OFF mode, all the circuitry in the ADIRU is
de-energized except for any logic associated with the power off
function. Current does not exceed 10 mA DC.
Each ADIRU supplies the power for the ADM of its side (CAPT, F/O,
STBY).
The ADIRU also supplies the CDU with a 28VDC signal. The consumption
of the CDU is 6 W (typical) and 10 W (maximum).

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 ADIRS - Power Supply Distribution
Figure 002

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 B. ADIRS Power Supply Distribution in Normal Configuration

(1) Captain side

The ADIRU 1 is supplied with 115VAC by the 115VAC SHED ESS BUS
801XP-A. The back-up 28VDC is provided by the 28VDC HOT BUS 701PP.
The resolvers of the AOA sensor 1 and the AOA resolver converter
module of the ADIRU 1 are supplied with 26VAC by the 26VAC ESS BUS
431XP-A.
The sensors and probes (static, TAT, pitot, AOA) are supplied for
heating through the Probe Heat Computer 1:
- the heating element of the AOA sensor 1 receives 115VAC from the
115VAC SHED ESS BUS 801XP
- the heating element of the TAT sensor 1 receives 115VAC from the
115VAC BUS 1 101XP-A
- the heating element of the L and R static probes 1 receives 28VDC
from the 28VDC BUS 1 101PP
- the heating element of the pitot probe 1 receives 115VAC from the
115VAC ESS BUS 401XP.
(Ref. Fig. 003)

NOTE : Figure ADIRS/PHC Interface, is a principle diagram which does

____
not show the interface between the PHC and the sensors.
(Ref. 30-31-00 for more details on probe ice protection).

(2) First Officer side

The ADIRU 2 is supplied with 115VAC by the 115VAC BUS 2 204XP. The
back-up 28VDC is provided by the 28VDC HOT BUS 702PP. The resolvers
of the AOA sensor 2 and the AOA resolver converter module of the
ADIRU 2 are supplied with 26VAC by the 26VAC BUS 2 231XP-A.
The sensors and probes are supplied for heating through the PHC 2:
- the heating element of the AOA sensor 2 receives 115VAC from the
115VAC BUS 2 202XP-B
- the heating element of the TAT sensor 2 receives 115VAC from the
115VAC BUS 2 202XP-C
- the heating element of the L and R static probes 2 receives 28VDC
from the 28VDC BUS 2 206PP
- the heating element of the pitot probe 2 receives 115VAC from the
115VAC BUS 2 202XP-B.

(3) Standby side

The ADIRU 3 is supplied with 115VAC by the 115VAC BUS 1 101XP-C. The
back-up 28VDC is provided by the 28VDC HOT BUS 701PP. The resolvers
of the AOA sensor 3 and the AOA resolver converter module of the
ADIRU 3 are supplied with 26VAC by the 26VAC BUS 1 131XP-A.
The sensors and probes are supplied for heating through the PHC 3:
- the heating element of the AOA sensor 3 receives 115VAC from the
115VAC BUS 1 103XP

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 ADIRS/PHC Interface
Figure 003

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 - the heating element of the L and R static probes 3 receives 28VDC
from the 28VDC BUS 1 103PP
- the heating element of the pitot probe 3 receives 115VAC from the
115VAC BUS 1 103XP.
In normal configuration of the aircraft electrical generation, the
distribution described before is independent of the switching
selector switches.

C. ADIRS Power Supply Distribution after Loss of Main Electrical Generation

(1) Loss of the main generation and ATT HDG selector switch in NORM
position

(a) Captain side

The ADIRU 1 is supplied as in normal configuration.
(Ref.Para B.(1)).

(b) First Officer side

The ADIRU 2 is no more supplied with 115VAC and 26VAC. When the
26VAC is lost, the ADR detects a fault and flags the output
parameters. The ADIRU is still powered with 28VDC from the 28VDC
HOT BUS 702PP but the Time Delay Opening (TDO) relay 17FP will
cut this supply after 5 minutes in emergency configuration.
The ADR 2 function is lost immediately.
The IR 2 function is lost after 5 minutes.

(c) Standby side

The ADIRU 3 is no more supplied with 115VAC and 26VAC.
When the 26VAC is lost, the ADR detects a fault and flags the
output parameters. The ADIRU is still powered with 28VDC from the
28VDC HOT BUS 701PP but the Time Delay Opening (TDO) relay 14FP
will cut this supply after 5 minutes in emergency configuration.
The ADR3 function is lost immediately.
The IR 3 function is lost after 5 minutes.

(2) Loss of the main generation and ATT HDG selector switch in CAPT/3
position
The CAPT/3 position of the ATT HDG selector switch corresponds to the
selection of the IR 3 in place of the IR 1. The power supply
distribution must then be modified to keep the IR 3 in emergency
configuration.

(a) Captain side

The ADIRU 1 is supplied as in normal configuration
(Ref. Para. B.(1)).

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 (b) First Officer side
ADIRU 2 supply: Ref. Para. (1)(b).

(c) Standby side

The ADIRU 3 is no more supplied with 115VAC. The ADIRU 3 is still
powered with 28VDC from the 28VDC HOT BUS 701PP.
The ADR 3 function is lost immediately.
The IR 3 function is available.

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 D. Circuit Breakers
The system is supplied through these circuit breakers:

-----------------------------------------------------------------------------
FIN PANEL/ DESIGNATION BUS ATA. REF. AMM
LOCATION P. BLOCK 001
-----------------------------------------------------------------------------
4FP1 49VU NAV AND PROBES/ADIRU1/115VAC 801XP-A 34-11-00
4FP2 121VU ADIRS/ADIRU/2/115VAC 204XP-C 34-11-00
4FP3 121VU ADIRS/ADIRU/3/115VAC 101XP-C 34-11-00
5FP1 49VU NAV AND PROBES/ADIRU1 & 431XP-A 34-11-00
AOA/26VAC
5FP2 121VU ADIRS/ADIRU/2/26VAC AND AOA 231XP-A 34-11-00
5FP3 121VU ADIRS/ADIRU/3/26VAC AND AOA 131XP-A 34-11-00
6FP1 105VU ADIRS/ADIRU1/28VDC 704PP 34-11-00
6FP2 121VU ADIRS/ADIRU/2/28VDC 702PP 34-11-00
6FP3 121VU ADIRS/ADIRU/3/28VDC 701PP 34-11-00
8FP 49VU NAV AND PROBES/ADIRU 3/ 401PP 34-11-00
SWTG/SPLY
9FP 121VU ADIRS/ADIRU/3 SWTG/SPLY 301PP 34-11-00
10FP 121VU ADIRS/ADIRU/2 PWR/SHED 206PP 34-11-00
1DA1 122VU ANTI ICE/PROBES/1/TAT 101XP-A 30-31-00
1DA2 122VU ANTI ICE/PROBES/2/TAT 202XP-C 30-31-00
2DA1 49VU ANTI ICE/PROBES/PHC/1 401PP 30-31-00
2DA2 122VU ANTI ICE/PROBES/2/PHC 206PP 30-31-00
2DA3 122VU ANTI ICE/PROBES/PHC/3 101PP 30-31-00
3DA1 49VU ANTI ICE/PROBES/PITOT/1 401XP-B 30-31-00
3DA2 122VU ANTI ICE/PROBES/2/PITOT 202XP-B 30-31-00
3DA3 122VU ANTI ICE/PROBES/3/PITOT 103XP-C 30-31-00
4DA1 49VU ANTI ICE/PROBES/1/AOA 801XP-C 30-31-00
4DA2 122VU ANTI ICE/PROBES/2/AOA 202XP-B 30-31-00
4DA3 122VU ANTI ICE/PROBES/3/AOA 103XP-C 30-31-00
5DA1 122VU ANTI ICE/PROBES/1/STATIC 101PP 30-31-00
5DA2 122VU ANTI ICE/PROBES/2/STATIC 206PP 30-31-00
5DA3 122VU ANTI ICE/PROBES/3/STATIC 103PP 34-11-00

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 4. _____________________
Component Description

A. Static Probes
(Ref. Fig. 004)
Each of the three systems (CAPT (1), F/O (2), STBY (3)) comprises two
static probes which are linked to each ADR portion of the ADIRUs through
five ADMs.
The probe is protected from icing with a 28VDC heater circuit.
The static probes linked to ADIRU 1 and ADIRU 2 are set at 48.64 deg.
below the fuselage datum line (Z=0).
The static probes linked to ADIRU 3 are set at 29.5 deg. below the
fuselage datum line.

B. Pitot Probes
(Ref. Fig. 005)
Each system comprises one pitot probe (CAPT (1), F/O (2), STBY (3)) which
is linked to each ADR portion of the ADIRUs through one ADM.
The probe is protected from icing with a 115VAC - 400 Hz heater circuit.
The pitot probes 1 and 2 are set at 40.08 deg. below the fuselage datum
line (Z=0).
The pitot probe 3 is set at 59.56 deg. below the fuselage datum line
(Z=0).

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 ADIRS - Static Probe
Figure 004

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R ADIRS - Pitot Probe
R Figure 005

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 C. Air Data Modules (ADM)

R **ON A/C 001-004,

(Ref. Fig. 006)

R **ON A/C 005-099,

R (Ref. Fig. 006A)

R **ON A/C ALL

The term Air Data Module (ADM) refers to any remotely located LRU which
senses pressure information and transmits it to the ADIRU in ARINC 429
format.
The ADMs are remotely mounted near and above the level of the pitot and
static probes, this in order to make the ADM pneumatic plumbing self
draining when the aircraft is stationary on the ground.

(1) Internal description

The ADM comprises the following components
(Ref. Fig. 007)

(a) Transducer board

This device provides two signals (Pressure Time Pulse (PTP) and
Temperature Time Pulse (TTP)) used by the processor board.

(b) Processor board

The microcomputer comprises the following circuits:
- a micro-controller 80C31
- two memories: ROM (storage of software program) and RAM
(temporary storage of data)
- a Non Volatile Memory (NVM) (Storage of transducer modelling
coefficients and failure information)
- a RS-232C Serial Digital Input/Output (used for bench test and
calibration purposes)
- an ARINC 429 transmitter.
The processor board uses the PTP and TTP signals sent by the
transducer board and the transducer modelling coefficients stored
in the NVM to compute the pressure.

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 Air Data Module
Figure 006

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R Air Data Module
R Figure 006A

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 ADM - Block Diagram
Figure 007

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 (c) EMI/lightning board
This board comprises the following devices:
- power supply: the ADM is supplied by the associated ADIRU with
+/- 13.5VAC. Power consumption is less than 200 mA on the
+13.5VDC input and less than 50 mA on the -13.5VDC input.
- EMI filters
- lightning protection
- input discretes filtering.

(2) Modes of operation

The ADM has three modes of operation:
- initialization
- normal operation
- Memory Access/Calibration (MA/C).

(a) Initialization mode

The ADM automatically enters the initialization mode immediately
after power is applied to the device or after a Watchdog Timer is
activated due to an ADM failure.
The ADM performs several tasks while in the initialization mode.
It:
- initializes software variables and hardware interfaces
- performs various self-monitoring tests to determine if the ADM
operates properly
- reads the fixed Program Pin discretes.
The ARINC 429 bus is disabled during the initialization mode. The
ADM does not output any data on the ARINC 429 bus.
The initialization mode is completed within 900 ms (maximum)
after valid power is applied to the ADM. Upon completion of the
initialization mode, the ADM automatically enters the normal
operation mode.

(b) Normal operation mode

The ADM enters the normal operation mode after the completion of
the initialization mode. It remains in the normal operation mode
until either power is removed from the ADM, or an internal
failure activates the Watchdog Timer, or an internal BITE detects
an unsafe condition at which time a failure warning is
annunciated or ARINC 429 transmissions cease.
The ADM performs the following functions in the normal operation
mode.
It:
- measures the pressure and temperature outputs from the
transducer
- uses filtering or averaging techniques consistent with the
noise, resolution, and dynamic frequency response requirements

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 - computes the Applied Pressure based upon the pressure and
temperature signals
- filters the Computed Pressure
- formats the ARINC 429 word to be transmitted
- transmits the ARINC 429 Computed Pressure word
- formats and transmits two ADM discrete words (labels 270, 271)
- reads and debounces the MA/C discretes
- performs the BITE functions
- formats and transmits ADM software and equipment I.D. words
(labels 040,377).

(c) Memory Access/Calibration mode

The Memory Access/Calibration (MA/C) mode is used for purposes of
transducer calibration and fault analysis. The MA/C mode requires
external test equipment which interfaces to the ADM via a RS-232C
bus. This mode can be considered as an auxiliary mode which is
accessible in a repair shop environment only.

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 (3) Discrete inputs
Table 1 gives the identification of the ADM discrete inputs:

--------------------------------------------
| ADM Pin | Identification |
--------------------------------------------
| K | SDI 1 (LSB) (2) |
| L | SDI 2 (MSB) (2) |
| M | Configuration code 1 (3) |
| N | Configuration code 2 (3) |
| P | Parity (1) |
| a | Memory Access/Calibration 1 |
| b | NVM reset discrete |
| c | Memory Access/Calibration 2 |
--------------------------------------------

Table 1 = Discrete Inputs

NOTE : (1) An odd number of pins K, L, M, N and P must be grounded to

____
signify a valid installation. After the desired Source Data
Identifier (SDI) and the configuration pins have been
selected, the parity pin P must be selectively left open or
grounded to ensure that an odd number of pins K through P
inclusive have been grounded.

NOTE : (2) Program pins used for identification of the installation

____
position on the aircraft and the corresponding SDI code to be
transmitted. The code definition is provided in table 2.

NOTE : (3) The ADM transmits the measured pressure with a label
____
depending on the configuration code input discretes. The
configuration code definition is provided in table 3.

------------------------------------------------------------------------
|Input discrete SDI output |Input discrete SDI output |Installation|
| pin L Bit 10 state| pin K Bit 09 state| |
|----------------------------------------------------------------------|
| open 0 | open 0 | Invalid |
| open 0 | ground 1 | 1 |
| ground 1 | open 0 | 2 |
| ground 1 | ground 1 | 3 |
------------------------------------------------------------------------

Table 2 = SDI Code

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 ---------------------------------------------------------------------
| Installation function | Config. code 1 | Config. code 2 | Label |
| | Pin N | Pin M | |
|-------------------------------------------------------------------|
| Total pressure | open | open | 242 |
| Left static pressure | open | ground | 176 |
| Right static pressure | ground | open | 177 |
| Averaged static | ground | ground | 245 |
| pressure (uncorrected)| | | |
---------------------------------------------------------------------

Table 3 = Configuration Code

(4) Output bus

All data are transmitted via a single ARINC 429 low-speed serial
digital output bus. The outputs from the ADM are a single pressure
word having an installation selectable label, two discrete data
words, and two identification words.
The following table gives:
- EQ.SYS.LAB.SDI: (SDAC, FWC, DMC...) output label for which the
parameter is available
- PARAMETER DEFINITION: parameter name
- WORD RANGE/OPER RANGE/RESOLUTION ACCURACY: measurement range.
Maximum value transmitted. When the digital value changes, the
change step is equal to the accuracy
- UNIT: unit in which the digital value is transmitted
- SIG BIT: indicates whether a sign bit is available
- BITS: number of bits used by the parameter in the label
- XMSN/INTV: output transmission interval. The refresh rate is given
in milliseconds
- CODE :
BNR: binary data word
BCD: binary coded decimal data word
ISO: data word coded in ISO5 code
DIS: discrete data word
HEX: hexadecimal coded
HYB: mixed code parameters are given in the table 4 below:
- ALPHA CODE: indicates the parameter mnemonic code
- SOURCE ORIGIN: parameter source computer or system.
All these parameters are given in the table 4 below:

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 -------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
| 242 |TOTAL |100-1400 |hPa | | 18 |29- |BNR | | |
| |PRESSURE |+/- 0.25 | | | |31 | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 176 |LEFT STAT |100-1100 |hPa | | 18 |29- |BNR | | |
| |PRESSURE |+/- 0.25 | | | |31 | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 177 |RIGHT STAT|100-1100 |hPa | | 18 |29- |BNR | | |
| |PRESSURE |+/- 0.25 | | | |31 | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 245 |AVERAGED |100-1100 |hPa | | 18 |29- |BNR | | |
| |STATIC |+/- 0.25 | | | |31 | | | |
| |PRESSURE | | | | | | | | |
| |(UNCORRTD)| | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 270 |DISCRETE |Table 5 | | | |460-|BCD | | |
| |WORD 1 | | | | |500 | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 271 |DISCRETE |Table 6 | | | |460-|BCD | | |
| |WORD 2 | | | | |500 | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 377 |EQUIPMENT |Table 7 | | | |460-|BCD | | |
| |IDENT | | | | |500 | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 040 |SOFTWARE |Table 8 | | | |460-|BCD | | |
| |IDENT | | | | |500 | | | |
-------------------------------------------------------------------------------
Table 4 = Digital Outputs

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 ---------------------------------------------------------------------
| Bit |Data |
| Position | |
|-------------------------------------------------------------------|
| 1-8 |Octal Label 270 |
| 9-10 |SDI |
| 11-12 |Logic 0 |
| 13-16 |LSD device revision number (currently 4H) |
| 17-20 |MSD device revision number (currently 0H) |
| 21-24 |LS device revision letter (currently CH) |
| 25-28 |MS device revision letter (currently AH) |
| 29 |Logic 0 |
| 30-31 |Logic 0. Set the SSM to Normal Operation for a discrete |
| |maintenance word |
| 32 |Odd parity |
---------------------------------------------------------------------

Table 5 = Discrete Word 1 (Label 270)

---------------------------------------------------------------------
| Bit |Data |
| Position | |
|-------------------------------------------------------------------|
| 1-8 |Octal Label 271 |
| 9-10 |SDI |
| 11-13 |Logic 0 |
| 14 |ADM LRU Status |
| 15 |Pin configuration status |
| 16 |Environment status |
| 17-24 |Current fault byte matrix |
| 25-28 |Word counter |
| 29 |Logic 0 |
| 30-31 |Logic 0. Set the SSM to Normal Operation for a discrete |
| |maintenance word |
| 32 |Odd parity |
---------------------------------------------------------------------

Table 6 = Discrete Word 2 (Label 271)

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 ---------------------------------------------------------------------
| Bit |Data |
| Position | |
|-------------------------------------------------------------------|
| 1-8 |Octal Label 377 |
| 9-10 |SDI |
| 11-14 |LSD equipment identification (8H) |
| 15-18 |MSD equipment identification (3H) |
| 19-29 |Logic 0 |
| 30-31 |Logic 0. Set the SSM to Normal Operation for a discrete |
| |maintenance word |
| 32 |Odd parity |
---------------------------------------------------------------------

Table 7 = Equipment Ident (Label 377)

---------------------------------------------------------------------
| Bit |Data |
| Position | |
|-------------------------------------------------------------------|
| 1-8 |Octal Label 040 |
| 9-10 |SDI |
| 11-12 |Logic 0 |
| 13-16 |LSD software revision number |
| 17-20 |MSD software revision number |
| 21-24 |LSD manufacturer ident number (1H) |
| 25-28 |MSD manufacturer ident number (0H) |
| 29 |Logic 0 |
| 30-31 |Logic 0. Set the SSM to Normal Operation for a discrete |
| |maintenance word |
| 32 |Odd parity |
---------------------------------------------------------------------

Table 8 = Software Ident (Label 040)

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 D. Total Air Temperature (TAT) Sensor
(Ref. Fig. 008)
The aircraft is equipped with two TAT sensors with two sensing elements
each. The sensing elements of the sensor have variable resistances. The
TAT sensor 1 is linked to the ADR portion of ADIRUs 1 and 3, the TAT
sensor 2 is linked to the ADR portion of ADIRU 2.
The TAT sensors are set at 2.33 m from the nose and at 0.60 m of the
aircraft axis below the fuselage. The TAT sensor 1 is located on the left
side and the TAT sensor 2 on the right side.
The air flow enters the scoop of the sensor, goes through a calibrated
choke and flows over the hermetically sealed platinum resistance sensing
element where the temperature is measured. The speed of the flow over the
element is controlled by the choke in the element tube.
The ADR portion is designed to operate with 500 ohms (at 0 deg. C )
temperature sensor unit corresponding to the basic Callender - Van Dusen
equation. To improve the accuracy of the sensor, a network of precision
resistors is used. This technique is identified by the term Precision
Calibration Interchangeability (PCI).
These sensors are heated with 115VAC through the probe heating system.
The heating element must not be energized on the ground.
The heating element is implanted in the scoop and strut and keeps the
probe free of ice under the most severe icing conditions.

NOTE : Probe ice protection is described in 30-31-00.

____

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 ADIRS - TAT Sensor
Figure 008

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 E. Angle Of Attack (AOA) Sensor

R **ON A/C 001-004,

(Ref. Fig. 009)

R **ON A/C 005-099,

R (Ref. Fig. 009A)

R **ON A/C ALL

The aircraft is equipped with three AOA sensors. Two are located on the
right side and one on the left side of the fuselage. Each of these AOA
sensors is respectively linked to each ADR portion of the ADIRUs. The AOA
sensors 1 and 3 are set at 6.08 deg. and 31 deg. below the fuselage datum
line (Z = 0) on the left side. The AOA sensor 2 is set at 6.08 deg. below
the fuselage datum line (Z = 0) on the right side.
The angle of attack sensor is of the wind vane type. Its sensing element
is a small wing which is positioned in the direction of airflow. The
small wing is mechanically linked to a free turn-shaft which drives the
devices transmitting the local angle of attack signal. These transmitting
devices are made up of resolver transformers which convert the angular
information into proportional electrical information (angle sine and
cosine). The resolvers are supplied with a 26VAC signal. The same signal
is also received by the ADIRU as a reference for the decoding of AOA
values. Each sensor has three resolver outputs but only two are wired to
the ADIRU.
The whole mechanism is stabilized around the rotation axis. In addition,
a damping device enables a satisfactory dynamic response to be obtained
(filtering of mechanical oscillation).
A self-regulated heating element (CTP resistances: positive coefficient
of temperature) inserted into the vane eliminates or avoids icing. It is
supplied with 115VAC through the PHC (Ref. 30-31-00).
The AOA sensor is equipped with a self-test device which is activated by
a 28VDC signal, from the ADR (through the relay 21FP1, 21FP2 or 21FP3)
when the test is entered via the maintenance system (CFDIU and MCDU). The
self-test positions the vane at a resolver angle of +15 deg. (left side
test) or -15 deg. (right side test).
The mounting and wing of AOA resolvers determine the relationship between
the measured resolver angle and indicated angle of attack. This
relationship for each resolver input is as follows:
(Ref. Fig. 010)

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 ADIRS - AOA Sensor
Figure 009

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R ADIRS - AOA Sensor
R Figure 009A

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 AOA Sensor - Installation Definition
Figure 010

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 ------------------------------------------------------------------------
| | Indicated AOA: | +85 | +60 | +25 | 0 | -35 |
| AOA 1 and AOA 3 |----------------------------------------------------|
| in degrees | Resolver angle: | -60 | -35 | 0 | +25 | +60 |
------------------------------------------------------------------------
| | Indicated AOA: | +85 | +60 | +25 | 0 | -35 |
| AOA 2 |----------------------------------------------------|
| in degrees | Resolver angle: | +60 | +35 | 0 | -25 | -60 |
------------------------------------------------------------------------
The ADRs receive the same 26VAC, 400 Hz reference as the AOA resolvers.
This reference is common to both AOA resolver inputs 1 and 2.
Characteristics:
Excitation : 26 V 400 Hz
Phase shift : 18 deg. to 30 deg.
Resolver transformer
ratio RT : 0.4029 to 0.4629
Rotor impedance : Zro = 125 + j175 ohms +/-20%
Stator impedance : Zso = 115 + j90 ohms +/-30%
Range : +/-60 deg.
Scale factor : 1 deg. resolver/1 deg. local AOA
The accuracy of the AOA sensor, at 100 knots, is +/-0.3 deg.

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 F. Selector Switches
(Ref. Fig. 011)
The two selector switches AIR DATA and ATT HDG are rotary selector
switches with 3 positions: CAPT/3, NORM and F/O/3.
These selector switches are used for the functions listed below (Ref. the
respective section for more details):
- AIR DATA SEL SW (15FP):
34-14-00 Selection of the ADR used by the IR3
34-52-00 ATC mode S
31-68-00 DMC
22-85-00 FMGC
- ATT HDG SEL SW (13FP):
34-11-00 Power Supply
34-14-00 Selection of the ADR used by the IR3
34-41-00 Weather Radar
34-57-00 VOR/DME RMI
31-68-00 DMC
22-85-00 FMGC.

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 ADIRS Switching
Figure 011

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 SENSORS, POWER SUPPLY AND SWITCHING - ADJUSTMENT/TEST
_____________________________________________________

TASK 34-11-00-720-001

Functional Test of the ADM

CAUTION : OBEY THESE PRECAUTIONS WHEN YOU DO THE TEST TO PREVENT DAMAGE TO
_______
INSTRUMENTS:
- PRESSURE SET MUST NOT BE MORE THAN 1050 hPa (31 in Hg) OR LESS THAN
115 hPa (3.39 in Hg)
- CHANGES IN PRESSURE MUST NOT BE MORE THAN 6000 FEET/MINUTE
- DO NOT SUDDENLY OPEN LINES TO AMBIENT AIR WHILE THE PRESSURE
GENERATOR IS CONNECTED.

CAUTION : THE TOTAL PRESSURE IN THE PITOT SYSTEM MUST NEVER BE LESS THAN THE
_______
STATIC PRESSURE. THE DIFFERENCE BETWEEN THE PITOT AND THE STATIC
PRESSURE CIRCUITS MUST NEVER BE MORE THAN 368 hPa (10.86 in Hg).

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific circuit breaker(s) safety clip(s)

No specific colored adhesive tape
No specific ARINC reader
No specific access platform 1.6 m (5 ft. 3 in.)
36122 1 ADAPTOR-CHARGING,PITOT PROBE
87202126V15 1 GENERATOR - GROUND PRESSURE
98D34003500000 1 ADAPTER COVER-STATIC PORT

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 B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
31-60-00-860-001 EIS Start Procedure
31-60-00-860-002 EIS Stop Procedure
34-10-00-860-002 ADIRS Start Procedure
34-10-00-860-005 ADIRS Stop Procedure
R 52-41-00-410-002 Close the Avionics Compartment Doors after Access

3. __________
Job Set-up

Subtask 34-11-00-010-050

A. Get Access to the Avionics Compartment

(1) Put the access platform in position and open the access door 824.

Subtask 34-11-00-860-056

B. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits

(Ref. TASK 24-41-00-861-002).

(2) Do the EIS start procedure (PFDs only) (Ref. TASK 31-60-00-860-001).

(3) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002).

(4) On the center pedestral, on the SWITCHING panel 8VU, make sure that
the AIR DATA selector switch is at NORM.

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 Subtask 34-11-00-865-050

C. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU ANTI ICE/PROBES/PITOT/1 3DA1 D02
R 122VU ANTI ICE/PROBES/2/PITOT 3DA2 Y14
R 122VU ANTI ICE/PROBES/2/STATIC 5DA2 Y11
R 122VU ANTI ICE/PROBES/3/PITOT 3DA3 Z16
R 122VU ANTI ICE/PROBES/3/STATIC 5DA3 Z14
R 122VU ANTI ICE/PROBES/1/STATIC 5DA1 Z13

Subtask 34-11-00-480-050

D. Install the Ground Pressure Generator and the ARINC Reader.

(1) Remove the slip on covers from the static probes and the pitot
probes.

(2) Connect the static port of the GENERATOR - GROUND PRESSURE to the
static and/or total probes on which you do the test :

(a) the static probes with the ADAPTER COVER-STATIC PORT

(98D34003500102)
For CAPT circuit (ADIRU 1) and F/O circuit (ADIRU 2):
- 7DA1 ZONE 127 STA 8750 for the LH static pressure ADM (19FP5)
- 7DA2 ZONE 127 STA 8700 for the LH static pressure ADM (19FP7)
and
- 8DA1 ZONE 128 STA 9300 for the RH static pressure ADM (19FP4)
- 8DA2 ZONE 128 STA 9350 for the RH static pressure ADM (19FP6)

(b) the static probes with the ADAPTER COVER-STATIC PORT

(98D34003500100)
For the standby circuit (ADIRU 3) :
- 7DA3 ZONE 121 STA 4250 for the static pressure ADM (19FP8) or
- 8DA3 ZONE 122 STA 4250 for the static pressure ADM (19FP8)

(c) the pitot probes with the ADAPTOR-CHARGING,PITOT PROBE or

equivalent
For CAPT circuit (ADIRU 1) :
- 9DA1 ZONE 125 STA 5500 for the total pressure ADM (19FP1)
For F/O circuit (ADIRU 2) :
- 9DA2 ZONE 126 STA 5500 for the total pressure ADM (19FP2)
For the standby circuit (ADIRU 3) :
- 9DA3 ZONE 125 STA 5500 for the total pressure ADM (19FP3)

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 (3) seal the Stby probes:

CAUTION : WHEN YOU SEAL THE DRAIN HOLE IN THE PITOT PROBE, DO NOT
_______
SEAL THE HOLE DIRECTLY WITH THE COLORED ADHESIVE TAPE.
ALWAYS PUT A PIECE OF PLASTIC ON THE HOLE AND USE THE TAPE
TO ATTACH THE PLASTIC.
IF YOU SEAL THE DRAIN HOLE DIRECTLY WITH THE ADHESIVE TAPE,
THERE IS A RISK THAT SOME OF THE ADHESIVE WILL STAY ON THE
HOLE AND COLLECT PARTICLES. THIS CAN SUBSEQUENTLY CAUSE
BLOCKAGE OF THE HOLE AND THUS INCORRECT OPERATION OF THE
PROBE.

R (a) Seal the drain holes of the pitot probes with a piece of plastic
R and colored adhesive tape of very bright color.

(b) Seal the opposite static probe of the standby ADM with the
ADAPTER COVER-STATIC PORT (98D34003500103).

(4) Start the ground pressure generator.

(5) Connect the ARINC reader to :

- the connector 199VC (pins GG/HH) for the CAPT circuit (ADIRU 1)
- the connector 198VC (pins GG/HH) for the F/O circuit (ADIRU 2)
- the connector 199VC (pins <Y/<Z) for the standby circuit (ADIRU 3)

(6) Start the ARINC reader.

4. Procedure
_________

Subtask 34-11-00-720-050

A. Functional Test of the ADM

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the ground pressure generator, On the ARINC reader, compare the

set a static pressure as given in pressure values of the static and total
the table below. ADM read on the following labels :
ADIRU 1
NOTE : You can also set an other
____ - Label 242 (ADM 19FP1)
pressure value. The - Label 176 (ADM 19FP5)
tolerance for the values - Label 177 (ADM 19FP4)

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
read on the ARINC reader ADIRU 2
is the same as these - Label 242 (ADM 19FP2)
indicated in the table - Label 176 (ADM 19FP7)
below. - Label 177 (ADM 19FP6)
ADIRU 3
- Label 242 (ADM 19FP3)
- Label 245 (ADM 19FP8)

2. On the ground pressure generator, The rate of descent must not be more
slowly decrease the pressure. than 6000 ft/mn.

3. Stop the ground pressure The test procedure stops.

generator.

-----------------------------------------------------
| PT | Altitude | Pressure value from |
| | (approx.) | the ADM |
|----------|--------------|-------------------------|
| 836 hpa | 5000 ft | 836 +/- 0.3 hpa |
|----------|--------------|-------------------------|
| 690 hpa | 10000 ft | 690 +/- 0.3 hpa |
|----------|--------------|-------------------------|
| 460 hpa | 20000 ft | 460 +/- 0.3 hpa |
|----------|--------------|-------------------------|
| 300 hpa | 30000 ft | 300 +/- 0.3 hpa |
|----------|--------------|-------------------------|
| 196 hpa | 39000 ft | 196 +/- 0.3 hpa |
-----------------------------------------------------

5. Close-up
________

Subtask 34-11-00-080-050

A. Remove the Ground Pressure Generator

(1) Remove the ground support and maintenance equipment, the special and
standard tools and all other items.

R (2) Make sure that there is no remaining piece of plastic and/or adhesive
R tape on the pitot probes. Make sure that the pitot drain holes are
R serviceable.

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 Subtask 34-11-00-865-052

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU ANTI ICE/PROBES/PITOT/1 3DA1 D02
122VU ANTI ICE/PROBES/2/PITOT 3DA2 Y14
122VU ANTI ICE/PROBES/2/STATIC 5DA2 Y11
122VU ANTI ICE/PROBES/3/PITOT 3DA3 Z16
122VU ANTI ICE/PROBES/3/STATIC 5DA3 Z14
122VU ANTI ICE/PROBES/1/STATIC 5DA1 Z13

Subtask 34-11-00-410-050

C. Close Access

R (1) Close the access door 824 (Ref. TASK 52-41-00-410-002).

(2) Remove the access platform(s).

Subtask 34-11-00-860-051

D. Put the aircraft back to its initial configuration.

(1) Install the slip on covers on the static probes and on the pitot
probes.

(2) Do the ADIRS Stop Procedure(Ref. TASK 34-10-00-860-005).

(3) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002).

(4) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

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 TASK 34-11-00-710-001

Test of the Monitoring of the ADR/AOA 26VAC Power Supply

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
31-60-00-860-001 EIS Start Procedure
31-60-00-860-002 EIS Stop Procedure

3. __________
Job Set-up

Subtask 34-11-00-010-051

A. Get Access

(1) Put the access platform in position in zone 126 at the access door
822.

(2) Open the access door 822.

(3) On the battery power center 105VU:

- loosen the two screws and remove the protective cover.

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 Subtask 34-11-00-860-052

B. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-

002).

(2) Do the EIS start procedure (Ref. TASK 31-60-00-860-001).

(3) On the overhead panel:

- on the FLT CTL panels 23VU and 24VU, make sure that the FAC, ELAC
and SEC pushbutton switches are not pushed (in). The OFF legends
are on.
- on the ELEC panel 35VU, make sure that the battery voltage is
correct, between 26VDC and 30VDC.
- on the ADIRS CDU, make sure that the 3 OFF/NAV/ATT selector
switches are at OFF.

NOTE : This test is for the system 1. For the systems 2 and 3, use
____
the indications between the parentheses.

Subtask 34-11-00-865-053

C. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU L/G/LGCIU/SYS1/NORM 1GA C09
49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07
49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06
105VU ADIRS/ADIRU1/28VDC 6FP1 C02

R **ON A/C 001-004,

121VU ADIRS/ADIRU/2PWR/SHED 10FP N11

121VU ADIRS/ADIRU/3PWR/SWTG 9FP N10
121VU ADIRS/ADIRU/2/26VAC AND AOA 5FP2 N09
121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N08
121VU ADIRS/ADIRU/2/115VAC 4FP2 N07
121VU ADIRS/ADIRU/3/115VAC 4FP3 N06
121VU ADIRS/ADIRU/2/28VDC 6FP2 N05
121VU ADIRS/ADIRU/3/28VDC 6FP3 N04

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 -------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
R **ON A/C ALL

121VU EIS/HORN/SPLY 2WC P09

121VU HYDRAULIC/LGCIU/SYS2 2GA Q35
121VU HYDRAULIC/LGCIU/SYS1/GRND SPLY 52GA Q34

R **ON A/C 005-099,

R 121VU ADIRS/ADIRU/2PWR/SHED 10FP N10

R 121VU ADIRS/ADIRU/3PWR/SWTG 9FP N09
R 121VU ADIRS/ADIRU/2/26VAC AND AOA 5FP2 N08
R 121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N07
R 121VU ADIRS/ADIRU/2/115VAC 4FP2 N06
R 121VU ADIRS/ADIRU/3/115VAC 4FP3 N05
R 121VU ADIRS/ADIRU/2/28VDC 6FP2 N04
R 121VU ADIRS/ADIRU/3/28VDC 6FP3 N03

R **ON A/C ALL

4. Procedure
_________

Subtask 34-11-00-710-050

A. Test of the Monitoring of the ADR/AOA 26VAC Power Supply

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the ADIRS CDU:

- set the OFF/NAV/ATT selector - the CAPT and F/O PFDs show the speed
switch related to the IR1, IR2 and altitude indications.
and IR3 to NAV.

2. On the panel 49VU (121VU):

- open the circuit breaker 5FP1 - on the ADIRS CDU, the FAULT legend of
(5FP2). the ADR1 (ADR2) pushbutton switch
comes on.

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
- on the CAPT (F/O) PFD, the SPD and
ALT warning flags come into view.
- on the lower ECAM DU, on the status
page, in the INOP SYST section, the
ADR1 indication comes into view.

3. On the panel 8VU:

- set the AIR DATA selector - on the CAPT (F/O) PFD, the speed and
switch to CAPT/3 (F/O/3). altitude indications come into view.

4. On the panel 121VU:

- open the circuit breaker 5PF3. - on the CAPT (F/O) PFD, the SPD and
ALT warning flags come into view.
- on the lower ECAM display unit, in
the INOP SYST section, the ADR 1 + 3
(ADR 2 + 3) indication comes into
view.
- on the ADIRS CDU, the FAULT legend of
the ADR3 pushbutton switch comes on.

5. On the panel 49VU (121VU):

- close the circuit breaker 5FP1 - on the lower ECAM display unit, in
(5FP2). the INOP SYST section, the ADR3
indication comes into view.
- on the ADIRS CDU, the FAULT legend of
the ADR1 (ADR2) pushbutton switch
goes off.

6. On the panel 8VU:

- set the AIR DATA selector - on the CAPT (F/O) PFD, the speed and
switch to NORM. altitude indications come into view.

7. On the panel 121VU:

- close the circuit breaker 5FP3. - on the lower ECAM display unit, in
the INOP SYST section, the ADR3
indication goes out of view.
- on the ADIRS CDU, the FAULT legend of
the ADR3 pushbutton switch goes off.

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
8. Refer to the indications in the You must get the same results on the
parentheses specified in the F/O side.
para. 1 to 5 and do the ADR2
test.

5. Close-up
________

Subtask 34-11-00-860-053

A. Put the aircraft back to its initial configuration.

(1) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002).

(2) On the ADIRS CDU, set the 3 OFF/NAV/ATT selector switches to OFF.

(3) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

Subtask 34-11-00-410-051

B. Close Access

(1) Install the protective cover of the 105VU with two bolts.

(2) Close the access door 822.

(3) Remove the access platform(s).

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 TASK 34-11-00-710-002

Test of the Monitoring of the ADIRS Power Supply (115VAC-28VDC)

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
31-60-00-860-001 EIS Start Procedure
31-60-00-860-002 EIS Stop Procedure

3. __________
Job Set-up

Subtask 34-11-00-010-052

A. Get Access

(1) Put the access platform in position in zone 126 at the access door
822.

(2) Open the access door 822.

(3) On the battery power center 105VU:

- loosen the two screws and remove the protective cover.

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 Subtask 34-11-00-860-054

B. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-

002).

(2) Do the EIS start procedure (Ref. TASK 31-60-00-860-001).

(3) On the overhead panel:

- On the FLT CTL panels 23VU and 24VU, make sure that the FAC, ELAC
and SEC pushbutton switches are not pushed (in). The OFF legends
are on.
- On the ADIRS CDU, on the panel 20VU, make sure that the 3
OFF/NAV/ATT selector switches are at OFF.
- On the ELEC panel 35VU, make sure that the battery voltage is
correct, between 26VDC and 30VDC.

NOTE : This test is for the system 1. For the systems 2 and 3, use
____
the indications between the parentheses.

Subtask 34-11-00-865-054

C. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU L/G/LGCIU/SYS1/NORM 1GA C09
49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07
49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06
105VU ADIRS/ADIRU1/28VDC 6FP1 C02

R **ON A/C 001-004,

121VU ADIRS/ADIRU/2PWR/SHED 10FP N11

121VU ADIRS/ADIRU/3PWR/SWTG 9FP N10
121VU ADIRS/ADIRU/2/26VAC AND AOA 5FP2 N09
121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N08
121VU ADIRS/ADIRU/2/115VAC 4FP2 N07
121VU ADIRS/ADIRU/3/115VAC 4FP3 N06
121VU ADIRS/ADIRU/2/28VDC 6FP2 N05
121VU ADIRS/ADIRU/3/28VDC 6FP3 N04

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 -------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
R **ON A/C ALL

121VU EIS/HORN/SPLY 2WC P09

121VU HYDRAULIC/LGCIU/SYS2 2GA Q35
121VU HYDRAULIC/LGCIU/SYS1/GRND SPLY 52GA Q34

R **ON A/C 005-099,

R 121VU ADIRS/ADIRU/2PWR/SHED 10FP N10

R 121VU ADIRS/ADIRU/3PWR/SWTG 9FP N09
R 121VU ADIRS/ADIRU/2/26VAC AND AOA 5FP2 N08
R 121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N07
R 121VU ADIRS/ADIRU/2/115VAC 4FP2 N06
R 121VU ADIRS/ADIRU/3/115VAC 4FP3 N05
R 121VU ADIRS/ADIRU/2/28VDC 6FP2 N04
R 121VU ADIRS/ADIRU/3/28VDC 6FP3 N03

R **ON A/C ALL

4. Procedure
_________

Subtask 34-11-00-710-051

A. Test of the Monitoring of the ADIRS Power Supply (115VAC-28VDC)

NOTE : Ignore all warnings / indications which are not related to this
____
test.

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the panel 49VU (121VU):

- open the circuit breaker 4FP1
(4FP2).

2. On the ADIRS CDU:

- set the OFF/NAV/ATT selector
switch related to the IR 1 (IR
2) to NAV.

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
- set the SYS DISPLAY selector - on the ADIRS CDU:
switch to 1 (2). * the related ALIGN legend is on,
* the ON BAT light is on,
* the related FAULT legend flashes.
- On the upper ECAM display unit, the
IR 1 FAULT (IR 2 FAULT) warning comes
into view.
- on the panels 130VU and 131VU, the
MASTER CAUT lights are on.
- you can hear the single chime.
- after a time delay of 15 s, you can
hear the horn.

3. On the panel 49VU (121VU), close - on the ADIRS CDU,

the circuit breaker 4FP1 (4FP2). The related FAULT legend continues to
flash.
The ON BAT light goes off.
The ALIGN legend stays on.
- The horn stops.

4. On the ADIRS CDU: - on the ADIRS CDU, the related FAULT

- set the OFF/NAV/ATT selector legend continues to flash then goes
switch related to the IR 1 (IR off after a short time,
2) to OFF. - on the upper ECAM display unit, the
IR1 FAULT (IR2 FAULT) warning goes
out of view.
- on the panels 130VU and 131VU the
MASTER CAUT lights go off,
- on the ADIRS CDU, the related ALIGN
legend goes off.

5. Do the IR 2 test as specified in You must get the same results on the
para. 1 to 4. F/O side.

6. On the ADIRS CDU: On the ADIRS CDU:

- set the OFF/NAV/ATT selector - the related ALIGN legend comes on,
switch related to the IR 1 (IR - then, the ON BAT light comes on
2) to NAV. during 5 s.

7. On the panel 49VU (121VU):

- open the circuit breaker 4FP1 - on the ADIRS CDU, the ON BAT light
(4FP2). comes on.
- in the nose gear wheel:

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
* after a time delay of 15 s approx
you can hear the horn.
* on the door 121AL, on the panel
108VU, the ADIRU & AVNCS VENT light
comes on.
- on the CAPT (F/O) PFD and ND, the
attitude indications are shown.

8. On the panel 49VU (121VU):

- close the circuit breaker 4FP1 - on the ADIRS CDU, the ON BAT light
(4FP2). goes off.
- the horn stops.

9. On the ADIRS CDU: On the ADIRS CDU:

set the OFF/NAV/ATT selector the ALIGN legend goes off.
switch related to the IR1 (IR2)
to OFF.

10. Do the IR 2 test as specified in You must get the same results on the
para. 6 to 8. F/O side.

11. On the panel 121VU:

- open the circuit breaker 4FP3.

12. On the panel 8VU:

- set the ATT HDG selector - on the CAPT PFD and ND the attitude
switch to CAPT/3. and heading indications from the IR 1
are not shown.

13. On the ADIRS CDU:

- set the OFF/NAV/ATT selector
switch related to the IR 3 to
NAV.

- set the SYS DISPLAY selector - on the ADIRS CDU:

switch to 3. * the related ALIGN legend is on,
* the ON BAT light is on.
* the related FAULT legend flashes.
- on the upper ECAM display unit, the
IR 3 FAULT warning comes into view.
- on the panels 130VU and 131VU, the
MASTER CAUT lights are on.

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
- you can hear the single chime.
- after a time delay of 15 s, you can
hear the horn.

14. On the panel 121VU:

- close the circuit breaker - on the ADIRS CDU:

4FP3. * the related FAULT legend goes off.
* the ON BAT light goes off.
* the ALIGN legend stays on.

15. On the ADIRS CDU:

- set the OFF/NAV/ATT selector - on the ADIRS CDU:

switch related to the IR 3 to * the related FAULT legend continues
OFF. to flash then goes off after a short
time,
* the ALIGN legend goes off.

16. On the ADIRS CDU:

- set the OFF/NAV/ATT selector - on the ADIRS CDU:

switch related to the IR 3 to * the ON BAT light comes on during 5
NAV. s.
* then, the ALIGN legend comes on.

17. On the panel 121VU:

- open the circuit breaker 4FP3. - on the ADIRS CDU, the ON BAT light
comes on.
- in the nose gear well:
* after a time delay of 15 s approx
you can hear the horn.
* on the door 121AL, on the panel
108VU, the ADIRU & AVNCS VENT light
comes on.
- on the CAPT (F/O) PFD , the attitude
indications stay in view.

18. On the panel 121VU: - on the ADIRS CDU, the ON BAT light
- close the circuit breaker goes off.
4FP3. - the horn stops.

19. On the ADIRS CDU:

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
- set the 3 OFF/NAV/ATT selector - The related ALIGN legend goes off.
switches to OFF.

20. On the panel 8VU:

- set the ATT HDG selector
switch to NORM.

5. Close-up
________

Subtask 34-11-00-860-055

A. Put the aircraft back to its initial configuration.

(1) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002).

(2) On the overhead panel:

- On the FLT CTL panels 23VU and 24VU, make sure that the FAC, ELAC
and SEC pushbutton switches are pushed. The off legends are off.

(3) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

Subtask 34-11-00-410-052

B. Close Access

(1) Install the protective cover on the battery power center 105VU.

(2) Tighten the two screws.

(3) Close the access door 822.

(4) Remove the access platform(s).

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 PROBE - PITOT (9DA1,9DA2,9DA3) - REMOVAL/INSTALLATION
_____________________________________________________

TASK 34-11-15-000-001

Removal of the Pitot Probe (9DA1, 9DA2, 9DA3)

R WARNING : MAKE SURE THAT THE CIRCUIT BREAKERS RELATED TO THE WEATHER RADAR ARE
_______
R OPENED, SAFETIED AND TAGGED.

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific blanking cap

No specific blanking plug
No specific circuit breaker(s) safety clip(s)
No specific access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

R 34-11-15-991-001-A Fig. 401

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 3. __________
Job Set-up

Subtask 34-11-15-865-050

A. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
121VU COM NAV/RADAR/1 5SQ1 K13
FOR 9DA1
49VU ANTI ICE/PROBES/AOA/1 4DA1 D04
49VU ANTI ICE/PROBES/PHC/1 2DA1 D03
49VU ANTI ICE/PROBES/PITOT/1 3DA1 D02
R 122VU ANTI ICE/PROBES/1/STATIC 5DA1 Z13
R 122VU ANTI ICE/PROBES/1/TAT 1DA1 Z12
FOR 9DA2
R 122VU ANTI ICE/PROBES/2/TAT 1DA2 Y15
R 122VU ANTI ICE/PROBES/2/PITOT 3DA2 Y14
122VU ANTI ICE/PROBES/2/AOA 4DA2 Y13
122VU ANTI ICE/PROBES/2/PHC 2DA2 Y12
R 122VU ANTI ICE/PROBES/2/STATIC 5DA2 Y11
FOR 9DA3
122VU ANTI ICE/PROBES/PHC/3 2DA3 Y16
R 122VU ANTI ICE/PROBES/3/PITOT 3DA3 Z16
122VU ANTI ICE/PROBES/3/AOA 4DA3 Z15
R 122VU ANTI ICE/PROBES/3/STATIC 5DA3 Z14

Subtask 34-11-15-010-050

B. Get Access

(1) Put the access platform in position at zone 125 to get access to
pitot probes 1 and 3 and at zone 126 to get access to pitot probe 2.

(2) Open the access door:

FOR 9DA1, 9DA3
812
FOR 9DA2
822

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 4. Procedure
_________

R (Ref. Fig. 401/TASK 34-11-15-991-001-A)

Subtask 34-11-15-020-050

A. Removal of the Pitot Probe (9DA1, 9DA2, 9DA3)

CAUTION : BE VERY CAREFUL WITH THE PITOT PROBES:

_______
- DO NOT LET THEM FALL
- DO NOT BEND THEM
- DO NOT CAUSE SCRATCHES.

(1) Disconnect the electrical connector (2).

(2) Disconnect the quick-disconnect coupling (1).

(3) Put a blanking cap on the disconnected electrical connector (2).

(4) Put a blanking plug on the quick-disconnect coupling (1).

(5) Loosen the two nuts (3) from the inner side of the aircraft.

NOTE : A second person is necessary to hold the pitot probe from the
____
outer side of the aircraft.

(6) Carefully remove the pitot probe (5) from the fuselage.

(7) Remove and discard the gasket (4).

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R Pitot Probe
R Figure 401/TASK 34-11-15-991-001-A

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 TASK 34-11-15-400-001

Installation of the Pitot Probe (9DA1, 9DA2, 9DA3)

WARNING : MAKE SURE THAT THE CIRCUIT BREAKERS RELATED TO THE WEATHER RADAR ARE
_______
OPENED, SAFETIED AND TAGGED.

CAUTION : MAKE SURE THAT:

_______
- THERE IS NO SIGN OF CORROSION OR DAMAGE ON THE EQUIPMENT
- THERE IS NO FOREIGN OBJECT IN THE EQUIPMENT
TO PREVENT ANY DAMAGE IN THE SYSTEM.

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific access platform 1.6 m (5 ft. 3 in.)

B. Expendable Parts

-------------------------------------------------------------------------------
FIG.ITEM |DESIGNATION |IPC-CSN
-------------------------------------------------------------------------------

4 gasket 34-11-01 03 -040

R 4 gasket 34-11-01 03 -040A

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 C. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

R 20-28-00-720-005 Check of the Electrical Bonding of the Different

R Components (But not the Fluid Systems and the
R Components Installed on Composite materials)
30-31-00-710-001 Operational Test of the Probe Ice Protection
34-11-15-200-001 Inspection/Check of the Pitot Probe (9DA1,9DA2,9DA3)
34-11-15-710-001 Test of the Pitot Probe (9DA1, 9DA2, 9DA3) without
the CFDS
34-11-15-991-001-A Fig. 401

3. __________
Job Set-up

Subtask 34-11-15-860-050

A. Aircraft Maintenance Configuration

(1) Make sure that the access platform is in position at zone 125 to get
access to pitot probes 1 and 3 and at zone 126 to get access to pitot
probe 2.

(2) Make sure that the access door are open:

FOR 9DA1, 9DA3
812
FOR 9DA2
822

Subtask 34-11-15-865-051

B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and
tagged

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
121VU COM NAV/RADAR/1 5SQ1 K13
FOR 9DA1
49VU ANTI ICE/PROBES/AOA/1 4DA1 D04
49VU ANTI ICE/PROBES/PHC/1 2DA1 D03
49VU ANTI ICE/PROBES/PITOT/1 3DA1 D02
122VU ANTI ICE/PROBES/1/STATIC 5DA1 Z13
122VU ANTI ICE/PROBES/1/TAT 1DA1 Z12
FOR 9DA2

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 -------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
122VU ANTI ICE/PROBES/2/TAT 1DA2 Y15
122VU ANTI ICE/PROBES/2/PITOT 3DA2 Y14
122VU ANTI ICE/PROBES/2/AOA 4DA2 Y13
122VU ANTI ICE/PROBES/2/PHC 2DA2 Y12
122VU ANTI ICE/PROBES/2/STATIC 5DA2 Y11
FOR 9DA3
122VU ANTI ICE/PROBES/PHC/3 2DA3 Y16
122VU ANTI ICE/PROBES/3/PITOT 3DA3 Z16
122VU ANTI ICE/PROBES/3/AOA 4DA3 Z15
122VU ANTI ICE/PROBES/3/STATIC 5DA3 Z14

4. Procedure
_________

(Ref. Fig. 401/TASK 34-11-15-991-001-A)

Subtask 34-11-15-420-050

A. Installation of the Pitot Probe (9DA1, 9DA2, 9DA3)

(1) Clean the component interface and/or the adjacent area.

(2) Do an inspection of the component interface and/or the adjacent area.

(3) Install the new gasket (4) .

NOTE : A second person is necessary to hold the pitot probe from the
____
outer side of the aircraft.

(4) Carefully install the pitot probe (5).

NOTE : You must turn the sensor element (6) to the front of the
____
aircraft.

(5) Tighten the two nuts (3) from the inner side of the fuselage.

(6) Remove the blanking cap from the electrical connector (2).

(7) Remove the blanking plug from the quick-disconnect coupling (1).

(8) Make sure that the electrical connectors are clean and in the correct
condition.

(9) Connect the electrical connector (2) to the pitot probe (5).

(10) Connect the quick-disconnect coupling (1) to the pitot probe (5).

NOTE : After the connection:

____
- make sure that a colored ring is shown on the
quick-disconnect coupling

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 - pull the connectors to be sure that they are correctly
attached.

R (11) Check the bonding contact resistance between the pitot probe (5) and
R the fuselage structure (Ref. TASK 20-28-00-720-005).

Subtask 34-11-15-865-052

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
5SQ1
FOR 9DA1
1DA1, 2DA1, 3DA1, 4DA1, 5DA1
FOR 9DA2
1DA2, 2DA2, 3DA2, 4DA2, 5DA2
FOR 9DA3
2DA3, 3DA3, 4DA3, 5DA3

Subtask 34-11-15-710-050

C. Do the tests that follow:

(1) Do the operational test of the Probe Ice Protection.

(Ref. TASK 30-31-00-710-001).

NOTE : As an alternative procedure, you can do this operational test

____
without the CFDS
(Ref. TASK 34-11-15-710-001).

5. Close-up
________

Subtask 34-11-15-410-050

A. Close Access

(1) Make sure that the work area is clean and clear of tool(s) and other
items.

(2) Make sure that the drain holes on the pitot probes are not blocked by
unwanted materials. (Ref. TASK 34-11-15-200-001)

(3) Close the access door :

FOR 9DA1, 9DA3
812
FOR 9DA2
822

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 (4) Remove the access platform(s).

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 PROBE - PITOT (9DA1,9DA2,9DA3) - ADJUSTMENT/TEST
________________________________________________

TASK 34-11-15-710-001

Test of the Pitot Probe (9DA1, 9DA2, 9DA3) without the CFDS

CAUTION : REMOVE THE PROTECTIVE COVERS FROM THE PROBES BEFORE YOU DO THE TEST.
_______

CAUTION : DO NOT CONTINUE THE TEST FOR MORE THAN ONE MINUTE TO PREVENT DAMAGE
_______
TO THE PROBES.

WARNING : DO NOT TOUCH THE PROBES IMMEDIATELY AFTER THE TEST.

_______
THEY ARE HOT AND CAN BURN YOU.

1. __________________
Reason for the Job

Do this test after the removal/installation of the Pitot Probe

(9DA1,9DA2,9DA3) when the CFDS is unserviceable.

2. ______________________
Job Set-up Information

A. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
31-60-00-860-001 EIS Start Procedure
34-10-00-860-002 ADIRS Start Procedure
34-10-00-860-005 ADIRS Stop Procedure

3. __________
Job Set-up

Subtask 34-11-15-860-051

A. Aircraft Maintenance Configuration

R (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-

002).

(2) Do the EIS start procedure ECAM only(Ref. TASK 31-60-00-860-001).

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 (3) Do the ADIRS start procedure for the related system:
For 9DA1
ADIRU1
For 9DA2
ADIRU2
For 9DA3
ADIRU3
(Ref. TASK 34-10-00-860-002).

Subtask 34-11-15-865-056

B. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
FOR 9DA1
49VU ANTI ICE/PROBES/PITOT/1 3DA1 D02
R FOR 9DA2
R 122VU ANTI ICE/PROBES/2/PITOT 3DA2 Y14
R FOR 9DA3
R 122VU ANTI ICE/PROBES/3/PITOT 3DA3 Z16

4. Procedure
_________

Subtask 34-11-15-710-051

A. Heating Test

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the overhead panel on the

PROBE/WINDOW HEAT section of the
panel 25VU:

- push the AUTO pushbutton switch the ON legend comes on.

2. On the circuit breaker panel :

- on the panel 49VU, open the - on the panels 131VU and 132VU, the
circuit breaker 3DA1 MASTER CAUT lights come on
- you can hear the single chime
- on the upper ECAM display unit the
ANTI ICE CAPT PITOT indication comes
into view.

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
- or on the panel 122VU, open the - on the panels 131VU and 132VU, the
circuit breaker 3DA2 MASTER CAUT lights come on
- you can hear the single chime
- on the upper ECAM display unit the
ANTI ICE F/O PITOT indication comes
into view.

- or on the panel 122VU, open the - on the panels 131VU and 132VU, the
circuit breaker 3DA3. MASTER CAUT lights come on
- you can hear the single chime
- on the upper ECAM display unit the
ANTI ICE STBY PITOT indication comes
into view.

3. Close the circuit breaker(s) that - on the panels 131VU and 132VU, the
you opened before. MASTER CAUT lights go off.
- on the upper ECAM display unit, the
indication given above goes out of
view.
- on the upper ECAM display unit, the
MEMO page comes into view.

4. On the overhead panel, on the

PROBE/WINDOW HEAT section of the
panel 25VU:

- release the AUTO pushbutton The ON legend goes off.

switch

5. Close-up
________

Subtask 34-11-15-860-052

A. Put the aircraft back to its initial configuration.

(1) On the center pedestal, on the ECAM control panel, set the UPPER
DISPLAY and LOWER DISPLAY potentiometers to OFF.

(2) Do the ADIRS Stop Procedure(Ref. TASK 34-10-00-860-005).

(3) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

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 PROBE - PITOT (9DA1,9DA2,9DA3) - INSPECTION/CHECK
_________________________________________________

TASK 34-11-15-200-001

Inspection/Check of the Pitot Probe (9DA1,9DA2,9DA3)

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific circuit breaker(s) safety clip(s)

R
No specific access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

34-11-15-000-001 Removal of the Pitot Probe (9DA1, 9DA2, 9DA3) (for

corrective action)
R 34-11-15-400-001 Installation of the Pitot Probe (9DA1, 9DA2, 9DA3)
R (for corrective action)
34-11-15-991-002-A Fig. 601

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 3. __________
Job Set-up

Subtask 34-11-15-865-053

A. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
FOR 9DA1
49VU ANTI ICE/PROBES/PITOT/1 3DA1 D02
FOR 9DA2
122VU ANTI ICE/PROBES/2/PITOT 3DA2 Y14
FOR 9DA3
122VU ANTI ICE/PROBES/3/PITOT 3DA3 Z16

Subtask 34-11-15-860-054

B. Aircraft Maintenance Configuration

(1) Put the access platform in position in Zone 125 to get access to the
pitot probes 1 and 3 and in Zone 126 to get access to the pitot probe
2.

(2) Remove the cover of the pitot probe.

4. Procedure
_________

(Ref. Fig. 601/TASK 34-11-15-991-002-A)

Subtask 34-11-15-220-050

A. Inspection/Check of the Pitot Probe (9DA1,9DA2,9DA3)

R (1) Do a general visual inspection of the Pitot Probe.

R

R (a) Color
During the ageing of the probe, the color of the tube becomes
brownish and/or blackish.
This coloration has no effect on the operation of the probe.
R

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R Pitot Probe Tip Configuration
R Figure 601/TASK 34-11-15-991-002-A

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R (b) Internal Obstruction (b)

CAUTION : DO NOT USE SHARP AND/OR METAL TOOLS OR OBJECTS TO CLEAN

_______
THE PITOT PROBE. SUCH TOOLS OR OBJECTS CAN CAUSE DAMAGE
TO THE PITOT PROBE.

It must be possible to insert 40 mm (1.5748 in.) of a nylon rod

(diameter 4 mm (0.1574 in.)) into the tube without any friction
or blockage.
If not, remove the pitot probe (Ref. TASK 34-11-15-000-001), blow
R compressed air into the pitot tube at the pneumatic connector and
R out of the tube entrance.
Maximum air pressure: 57 psi (3.9300 bar).

NOTE : The compressed air line must have an oil trap to make sure
____
that no oil gets into the pitot probe.

R Install the pitot probe (Ref. TASK 34-11-15-400-001).

R (c) Make sure that the drain holes are not blocked.

5. Close-up
________

Subtask 34-11-15-860-053

A. Put the aircraft back to its initial configuration.

(1) Install the cover on the pitot probe.

(2) Make sure that the work area is clean and clear of tool(s) and other
items.

(3) Remove the access platform.

Subtask 34-11-15-865-054

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
FOR 9DA1
3DA1
FOR 9DA2
3DA2
FOR 9DA3
3DA3

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 PROBE - STATIC (7DA1,7DA2,7DA3,8DA1,8DA2,8DA3) - REMOVAL/INSTALLATION
_____________________________________________________________________

TASK 34-11-16-000-001

Removal of the Static Probe (7DA1,7DA2,7DA3,8DA1,8DA2,8DA3)

WARNING : MAKE SURE THAT THE CIRCUIT BREAKERS RELATED TO THE WEATHER RADAR ARE
_______
OPENED, SAFETIED AND TAGGED.

WARNING : MAKE SURE THAT:

_______
- THE STATIC PROBE IS NOT HOT
- THE ELECTRICAL SUPPLY TO THE HEATING ELEMENT OF THE PROBE IS
ISOLATED
BEFORE YOU START THE TASK.

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific blanking plug

No specific circuit breaker(s) safety clip(s)
No specific access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

R **ON A/C 001-005,

34-11-16-991-001 Fig. 401

R **ON A/C 006-099,

R 34-11-16-991-001-A Fig. 401A

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R **ON A/C ALL

3. __________
Job Set-up

Subtask 34-11-16-865-050

A. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
121VU COM NAV/RADAR/1 5SQ1 K13
FOR 7DA1, 8DA1
49VU ANTI ICE/PROBES/AOA/1 4DA1 D04
49VU ANTI ICE/PROBES/PHC/1 2DA1 D03
49VU ANTI ICE/PROBES/PITOT/1 3DA1 D02
122VU ANTI ICE/PROBES/1/STATIC 5DA1 Z13
122VU ANTI ICE/PROBES/1/TAT 1DA1 Z12
FOR 7DA2, 8DA2
122VU ANTI ICE/PROBES/2/TAT 1DA2 Y15
122VU ANTI ICE/PROBES/2/PITOT 3DA2 Y14
122VU ANTI ICE/PROBES/2/AOA 4DA2 Y13
122VU ANTI ICE/PROBES/2/PHC 2DA2 Y12
122VU ANTI ICE/PROBES/2/STATIC 5DA2 Y11
FOR 7DA3, 8DA3
122VU ANTI ICE/PROBES/PHC/3 2DA3 Y16
122VU ANTI ICE/PROBES/3/PITOT 3DA3 Z16
122VU ANTI ICE/PROBES/3/AOA 4DA3 Z15
122VU ANTI ICE/PROBES/3/STATIC 5DA3 Z14

Subtask 34-11-16-010-050

B. Get Access

(1) Put the access platform in position at the zone 128 for the static
probes 7DA1, 8DA1, 7DA2 and 8DA2.

(2) Put the access platform in position at the zone 120 for static probes
7DA3 and 8DA3.

(3) Open the access door :

FOR 7DA1, 8DA1, 7DA2, 8DA2
824
FOR 7DA3, 8DA3
811

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 4. Procedure
_________

R **ON A/C 001-005,

(Ref. Fig. 401/TASK 34-11-16-991-001)

R **ON A/C 006-099,

R (Ref. Fig. 401A/TASK 34-11-16-991-001-A)

R **ON A/C 001-005,

Subtask 34-11-16-020-050

A. Removal of the Static Probe

NOTE : This procedure is the same for the six static probes.
____

(1) Remove the covers (12).

(2) Remove the two nuts (8), the washers (10) and the bolts (11).

(3) Disconnect the nut (1) and remove the static line (13).

(4) Put a blanking plug on the nut (1).

(5) Remove the union (2).

(6) Remove the packing (4) and discard it.

(7) Remove the four nuts (3).

(8) Remove the static probe (5).

(9) Remove the packing (6) and discard it.

(10) Keep the bolts (7).

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R Static Probe
Figure 401/TASK 34-11-16-991-001

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R Static Probe
Figure 401A/TASK 34-11-16-991-001-A

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R **ON A/C 006-099,

R Subtask 34-11-16-020-050-A

R A. Removal of the Static Probe

R NOTE : This procedure is the same for the six static probes.
____

R (1) Remove the covers (12).

R (2) Remove the two nuts (8), the washers (10) and the bolts (11).

R (3) Disconnect the nut (1) and remove the static line (13).

R (4) Put a blanking plug on the nut (1).

R (5) Remove the union (2).

R (6) Remove the packing (4) and discard it.

R (7) Remove the four nuts (3).

R (8) Remove the washer (16) and the bonding strip (15).

R (9) Remove the static probe (5).

R (10) Remove the packing (6) and discard it.

R (11) Keep the bolts (7).

R
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R **ON A/C ALL

TASK 34-11-16-400-002

Installation of the Static Probe (7DA1,7DA2,7DA3,8DA1,8DA2,8DA3)

WARNING : MAKE SURE THAT THE CIRCUIT BREAKERS RELATED TO THE WEATHER RADAR ARE
_______
OPENED, SAFETIED AND TAGGED.

CAUTION : MAKE SURE THAT:

_______
- THERE IS NO SIGN OF CORROSION OR DAMAGE ON THE EQUIPMENT
- THERE IS NO FOREIGN OBJECT IN THE EQUIPMENT
TO PREVENT ANY DAMAGE IN THE SYSTEM.

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific access platform 1.6 m (5 ft. 3 in.)

No specific Torque Wrench : to 0.1 m.daN (8.84 lbf.in)

B. Expendable Parts

-------------------------------------------------------------------------------
FIG.ITEM |DESIGNATION |IPC-CSN
-------------------------------------------------------------------------------

4 packing 34-11-01 02 -060

R 4 packing 34-11-01 02A-060
6 packing 34-11-01 02 -030
R 6 packing 34-11-01 02A-030

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 C. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

20-28-00-912-004 Electrical Bonding of Components With Conductive

Bolts and Screws and Bonding Straps in the Fuselage
R and in the Wings (this does not include the tanks)-
30-31-00-710-001 Operational Test of the Probe Ice Protection
34-11-16-710-001 Test of the Static Probe
(7DA1,8DA1,7DA2,8DA2,7DA3,8DA3) without the CFDS.
34-13-00-790-002 Leak Test of the Principal Static and Total Air Data
System
34-21-00-790-001 Leak Test of the Standby Air Data System
FOR FIN 7DA1, 8DA1, 7DA2, 8DA2
52-41-00-410-002 Close the Avionics Compartment Doors after Access

3. __________
Job Set-up

Subtask 34-11-16-860-052

A. Aircraft Maintenance Configuration

(1) Make sure that the access platform is in position at the zone 128 for
the static probes 7DA1, 8DA1, 7DA2 and 8DA2.

(2) Make sure that the access platform is in position at the zone 120 for
the static probes 7DA3 and 8DA3.

(3) Open the access door:

FOR 7DA1, 8DA1, 7DA2, 8DA2
824
FOR 7DA3, 8DA3
811

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 Subtask 34-11-16-865-055

B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and
tagged

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
121VU COM NAV/RADAR/1 5SQ1 K13
FOR 7DA1, 8DA1
49VU ANTI ICE/PROBES/AOA/1 4DA1 D04
49VU ANTI ICE/PROBES/PHC/1 2DA1 D03
49VU ANTI ICE/PROBES/PITOT/1 3DA1 D02
122VU ANTI ICE/PROBES/1/STATIC 5DA1 Z13
122VU ANTI ICE/PROBES/1/TAT 1DA1 Z12
FOR 7DA2, 8DA2
122VU ANTI ICE/PROBES/2/TAT 1DA2 Y15
122VU ANTI ICE/PROBES/2/PITOT 3DA2 Y14
122VU ANTI ICE/PROBES/2/AOA 4DA2 Y13
122VU ANTI ICE/PROBES/2/PHC 2DA2 Y12
122VU ANTI ICE/PROBES/2/STATIC 5DA2 Y11
FOR 7DA3, 8DA3
122VU ANTI ICE/PROBES/PHC/3 2DA3 Y16
122VU ANTI ICE/PROBES/3/PITOT 3DA3 Z16
122VU ANTI ICE/PROBES/3/AOA 4DA3 Z15
122VU ANTI ICE/PROBES/3/STATIC 5DA3 Z14

4. Procedure
_________

R **ON A/C 001-005,

Subtask 34-11-16-420-051

A. Installation of the Static Probe

NOTE : This procedure is the same for the six static probes.
____

(1) Clean the component interface and/or the adjacent area.

(2) Do an inspection of the component interface and/or the adjacent area.

(3) Install a new packing (6).

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 (4) Carefully engage the static probe (5) in position on the bolts (7).
The heating element must point to the nose of the aircraft for static
probes 7DA1, 8DA1, 7DA2 and 8DA2. It must point down for static
probes 7DA3 and 8DA3.

(5) Install the four nuts (3). Tighten the nuts which are diagonally
opposite (X sequence) and TORQUE them to 0.1 m.daN (8.84 lbf.in).

(6) Install a new packing (4).

(7) Install the union (2).

(8) Remove the blanking plug from the nut (1).

(9) Install the static line (13).

(10) Connect the nut (1).

(11) Install the lugs (9) on the terminals (14) with the bolts (11), the
washers (10) and the nuts (8).

R NOTE : The covers (12) of the static probe (8DA2) must not touch the
____
R static line. Thus, make sure that the lugs (9) connected to
R the terminals (14) are correctly installed as shown in the
R figure given in this procedure.

(12) Install the covers (12).

**ON A/C 006-099,

Subtask 34-11-16-420-051-A

A. Installation of the Static Probe

NOTE : This procedure is the same for the six static probes.
____

(1) Clean the component interface and/or the adjacent area.

(2) Do an inspection of the component interface and/or the adjacent area.

(3) Install a new packing (6).

(4) Carefully engage the static probe (5) in position on the bolts (7).
The heating element must point to the nose of the aircraft for static
probes 7DA1, 8DA1, 7DA2 and 8DA2. It must point down for static
probes 7DA3 and 8DA3.

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 (5) Install the bonding strip (15) and the washer (16) (Ref. TASK 20-28-
00-912-004).

(6) Install the four nuts (3). Tighten the nuts which are diagonally
opposite (X sequence) and TORQUE them to 0.1 m.daN (8.84 lbf.in).

(7) Install a new packing (4).

(8) Install the union (2).

(9) Remove the blanking plug from the nut (1).

(10) Install the static line (13).

(11) Connect the nut (1).

(12) Install the lugs (9) on the terminals (14) with the bolts (11), the
washers (10) and the nuts (8).

R NOTE : The covers (12) of the static probe (8DA2) must not touch the
____
R static line. Thus, make sure that the lugs (9) connected to
R the terminals (14) are correctly installed as shown in the
R figure given in this procedure.

(13) Install the covers (12).

**ON A/C ALL

Subtask 34-11-16-865-056

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
5SQ1
FOR 7DA1, 8DA1
1DA1, 2DA1, 3DA1, 4DA1, 5DA1
FOR 7DA2, 8DA2
1DA2, 2DA2, 3DA2, 4DA2, 5DA2
FOR 7DA3, 8DA3
2DA3, 3DA3, 4DA3, 5DA3

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 Subtask 34-11-16-790-051

C. Leak Test

NOTE : The leak test is mandatory if you disconnect/connect components of

____
two static systems.

(1) Do a leak test of the main static system (Ref. TASK 34-13-00-790-
002).

(2) Do a leak test of the standby static system

(Ref. TASK 34-21-00-790-001).

Subtask 34-11-16-710-052

D. Do an operational test of the Static Probe with the CFDS:

Do the operational test of the Probe Ice Protection
(Ref. TASK 30-31-00-710-001).

NOTE : As an alternative procedure, you can do this operational test

____
without the CFDS
(Ref. TASK 34-11-16-710-001).

5. Close-up
________

Subtask 34-11-16-410-051

A. Close Access

(1) Make sure that the work area is clean and clear of tool(s) and other
items.

(2) Close the access door :

FOR 7DA1, 8DA1, 7DA2, 8DA2
824 (Ref. TASK 52-41-00-410-002).
FOR 7DA3, 8DA3
811

(3) Remove the access platform(s).

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 PROBE - STATIC (7DA1,7DA2,7DA3,8DA1,8DA2,8DA3) - ADJUSTMENT/TEST
________________________________________________________________

TASK 34-11-16-710-001

Test of the Static Probe (7DA1,8DA1,7DA2,8DA2,7DA3,8DA3) without the CFDS.

CAUTION : REMOVE THE PROTECTIVE COVERS FROM THE PROBES BEFORE YOU DO THE TEST.
_______

CAUTION : DO NOT CONTINUE THE TEST FOR MORE THAN ONE MINUTE TO PREVENT DAMAGE
_______
TO THE PROBES.

WARNING : DO NOT TOUCH THE PROBES IMMEDIATELY AFTER THE TEST.

_______
THEY ARE HOT AND CAN BURN YOU.

1. __________________
Reason for the Job

Do this test after the removal/installation of the Static Probe

(7DA1,8DA1,7DA2,8DA2,7DA3,8DA3) when the CFDS is unserviceable.

2. ______________________
Job Set-up Information

A. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
31-60-00-860-001 EIS Start Procedure
34-10-00-860-002 ADIRS Start Procedure
34-10-00-860-005 ADIRS Stop Procedure

3. __________
Job Set-up

Subtask 34-11-16-860-050

A. Aircraft Maintenance Configuration

R (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-

002).

(2) Do the EIS start procedure (ECAM only) (Ref. TASK 31-60-00-860-001).

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 (3) Do the ADIRS start procedure for the related system:
For 7DA1,8DA1
ADIRU1
For 7DA2,8DA2
ADIRU2
For 7DA3,8DA3
ADIRU3
(Ref. TASK 34-10-00-860-002).

Subtask 34-11-16-865-054

B. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
R FOR 7DA1, 8DA1
R 122VU ANTI ICE/PROBES/1/STATIC 5DA1 Z13
R FOR 7DA2, 8DA2
R 122VU ANTI ICE/PROBES/2/STATIC 5DA2 Y11
R FOR 7DA3, 8DA3
R 122VU ANTI ICE/PROBES/3/STATIC 5DA3 Z14

4. Procedure
_________

Subtask 34-11-16-710-051

A. Heating test

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the overhead panel, on the

PROBE/WINDOW HEAT section of the
panel 25VU :

- push the AUTO pushbutton - the ON legend comes on.

switch.

2. On the circuit breaker panel

122VU :

- Open the circuit breaker - on the panels 131VU and 132VU, the
ANTI-ICE PROBES 1 STATIC-5DA1 MASTER CAUT lights come on.
or - you can hear the single chime.

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
ANTI-ICE PROBES 2 STATIC-5DA2 - on the upper ECAM display unit, this
or indication comes into view:
ANTI-ICE PROBES 3 STATIC-5DA3. ANTI ICE CAPT L STAT (R STAT) or,
ANTI ICE F/O L STAT (R STAT) or,
ANTI ICE STBY L STAT (R STAT).

3. Close the circuit breaker(s) that - on the panels 131VU and 132VU, the
you opened before. MASTER CAUT lights go off.
- on the upper ECAM display unit, the
MEMO page comes into view.

4. On the overhead panel, on the

PROBE/WINDOW HEAT section of the
panel 25VU :

- release the AUTO pushbutton - the ON legend goes off.

switch.

5. Close-up
________

Subtask 34-11-16-860-051

A. Put the aircraft back to its initial configuration.

(1) On the center pedestal, on the ECAM control panel, set the UPPER
DISPLAY and LOWER DISPLAY potentiometers to OFF.

(2) Do the ADIRS Stop Procedure(Ref. TASK 34-10-00-860-005).

(3) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

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 ___________________________________________________________________
MODULE - AIR DATA (19FP1,19FP2,19FP3,19FP4,19FP5,19FP6,19FP7,19FP8)
____________________
REMOVAL/INSTALLATION

TASK 34-11-17-000-001

Removal of the Air Data Module (19FP1,19FP2,19FP3,19FP4,19FP5,19FP6,

19FP7,19FP8)

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific blanking caps

No specific blanking plugs
No specific circuit breaker(s) safety clip(s)
No specific warning notice
No specific access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

R **ON A/C 001-004,

34-11-17-991-001 Fig. 401

R **ON A/C 005-099,

R 34-11-17-991-001-A Fig. 401A

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R **ON A/C ALL

3. __________
Job Set-up

Subtask 34-11-17-010-050

A. Get Access

(1) Put the access platform in position :

(a) In the zone 123 for the Total Pressure ADM 19FP1 and 19FP3.

(b) In the zone 122 for the Total Pressure ADM 19FP2.

(c) In the zone 128 for the Static Pressure ADM 19FP4, 19FP5, 19FP6
and 19FP7.

(d) In zone 110 for the Static Pressure ADM 19FP8.

(e) At the access door 822.

(2) Open the access door :

FOR 19FP1, 19FP3
812
FOR 19FP2
822
FOR 19FP5, 19FP7
824
FOR 19FP8
811
FOR 19FP4, 19FP6
824

(3) Open the access door 822.

(4) On the battery power center 105VU:

-loosen the two screws and remove the protective cover.

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 Subtask 34-11-17-865-050

B. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
FOR 19FP1, 19FP4, 19FP5
49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06
105VU ADIRS/ADIRU1/28VDC 6FP1 C02
FOR 19FP2, 19FP6, 19FP7

R **ON A/C 001-004,

121VU ADIRS/ADIRU/2/115VAC 4FP2 N07

121VU ADIRS/ADIRU/2/28VDC 6FP2 N05

R **ON A/C 005-099,

R 121VU ADIRS/ADIRU/2/115VAC 4FP2 N06

R 121VU ADIRS/ADIRU/2/28VDC 6FP2 N04

R **ON A/C ALL

FOR 19FP3, 19FP8

R **ON A/C 001-004,

121VU ADIRS/ADIRU/3/115VAC 4FP3 N06

121VU ADIRS/ADIRU/3/28VDC 6FP3 N04

R **ON A/C 005-099,

R 121VU ADIRS/ADIRU/3/115VAC 4FP3 N05

R 121VU ADIRS/ADIRU/3/28VDC 6FP3 N03

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R **ON A/C ALL

4. Procedure
_________

R **ON A/C 001-004,

(Ref. Fig. 401/TASK 34-11-17-991-001)

R **ON A/C 005-099,

R (Ref. Fig. 401A/TASK 34-11-17-991-001-A)

R **ON A/C ALL

Subtask 34-11-17-020-050

A. Removal of the ADM

(1) Precaution :

NOTE : During the removal of the Static Pressure ADM 19FP4 and 19FP6,
____
you must close the door 824. Before you close, put a warning
notice in position to tell persons not to open the door.

(2) Disconnect the electrical connector (7).

(3) Disconnect the quick-disconnect coupling (6).

(4) Put blanking caps on the disconnected electrical connectors (7) and
(8).

(5) Put blanking plugs on the disconnected quick-disconnect couplings (5)

and (6).

(6) Remove the four screws (3) and the washers (4); when you do this,
hold the ADM (2).

(7) Remove the ADM (2).

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 INTENTIONALLY BLANK

R
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 Pressure ADM
Figure 401/TASK 34-11-17-991-001- 12 (SHEET 1)

R
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 Pressure ADM
Figure 401/TASK 34-11-17-991-001- 22 (SHEET 2)

R
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R Pressure ADM
R Figure 401A/TASK 34-11-17-991-001-A12 (SHEET 1)

R
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R Pressure ADM
R Figure 401A/TASK 34-11-17-991-001-A22 (SHEET 2)

R
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 TASK 34-11-17-400-001

Installation of the Air Data Module (19FP1,19FP2,19FP3,19FP4,19FP5,19FP6,

19FP7,19FP8)

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific warning notice

No specific access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

34-11-17-710-001 Test of the Air Data Module without the CFDS

34-13-00-740-003 SYSTEM TEST of the ADR

**ON A/C 001-004,

34-11-17-991-001 Fig. 401

**ON A/C 005-099,

34-11-17-991-001-A Fig. 401A

FOR FIN 19FP4, 19FP5, 19FP6, 19FP7
R 52-41-00-410-002 Close the Avionics Compartment Doors after Access

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R **ON A/C ALL

3. __________
Job Set-up

Subtask 34-11-17-860-050

A. Get Access

NOTE : During the installation of the Static Pressure ADM 19FP4 and
____
19FP6, you must close the door 824. Before you close, put a
warning notice in position to tell persons not to open the door.

(1) Make sure that the access platform are in position:

(a) In the zone 123 for the Total Pressure ADM 19FP1 and 19FP3.

(b) In the zone 122 for the Total Pressure ADM 19FP2.

(c) In the zone 128 for the Static Pressure ADM 19FP4, 19FP5, 19FP6
and 19FP7.

(d) In zone 110 for the Static Pressure ADM 19FP8.

(e) At the access door 822.

(2) Make sure that the access door are open:

FOR 19FP1, 19FP3
812
FOR 19FP2
822
FOR 19FP5, 19FP7
824
FOR 19FP8
811
FOR 19FP4, 19FP6
824

(3) Make sure that the protective cover is removed from the battery power
center 105VU.

(4) Clean the component interface and/or the adjacent area.

(5) Do an inspection of the component interface and/or the adjacent area.

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 Subtask 34-11-17-865-051

B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and
tagged

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
FOR 19FP1, 19FP4, 19FP5
49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06
105VU ADIRS/ADIRU1/28VDC 6FP1 C02
FOR 19FP2, 19FP6, 19FP7

R **ON A/C 001-004,

121VU ADIRS/ADIRU/2/115VAC 4FP2 N07

121VU ADIRS/ADIRU/2/28VDC 6FP2 N05

R **ON A/C 005-099,

R 121VU ADIRS/ADIRU/2/115VAC 4FP2 N06

R 121VU ADIRS/ADIRU/2/28VDC 6FP2 N04

R **ON A/C ALL

FOR 19FP3, 19FP8

R **ON A/C 001-004,

121VU ADIRS/ADIRU/3/115VAC 4FP3 N06

121VU ADIRS/ADIRU/3/28VDC 6FP3 N04

R **ON A/C 005-099,

R 121VU ADIRS/ADIRU/3/115VAC 4FP3 N05

R 121VU ADIRS/ADIRU/3/28VDC 6FP3 N03

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R **ON A/C ALL

4. Procedure
_________

R **ON A/C 001-004,

(Ref. Fig. 401/TASK 34-11-17-991-001)

R **ON A/C 005-099,

R (Ref. Fig. 401A/TASK 34-11-17-991-001-A)

R **ON A/C ALL

Subtask 34-11-17-420-050

A. Installation of the ADM

(1) Put the ADM (2) in position on its support and hold it in this
position.

(2) Attach the ADM (2) with the four screws (3) and the washers (4).

(3) Remove the blanking caps from the disconnected electrical connectors
(7) and (8). Make sure that the electrical connectors are in the
correct condition.

(4) Remove the blanking plugs from the disconnected quick-disconnect

couplings (5) and (6). Make sure that the quick-disconnect couplings
are in the correct condition.

(5) Connect the electrical connector (7).

(6) Connect the quick-disconnect coupling (6).

NOTE : After the connection:

____
- make sure that a colored ring is shown on the
quick-disconnect coupling
- pull the connectors to be sure that they are correctly
attached.

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 Subtask 34-11-17-710-050

B. Do the SYSTEM TEST of the ADR with the CFDS

(Ref. TASK 34-13-00-740-003).

NOTE : As an alternative procedure, you can do this operational test

____
without the CFDS (Ref. TASK 34-11-17-710-001).

5. Close-up
________

Subtask 34-11-17-410-050

A. Close Access

(1) Make sure that the work area is clean and clear of tool(s) and other
items.

(2) Close the access door :

FOR 19FP1, 19FP3
812
FOR 19FP2
822
FOR 19FP4, 19FP5, 19FP6, 19FP7
R 824 (Ref. TASK 52-41-00-410-002)
FOR 19FP8
811

(3) Remove the warning notice(s).

(4) Install the protective cover on the battery power center 105VU.

(5) Tighten the two screws.

(6) Close the access door 822.

(7) Remove the access platform(s).

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 ___________________________________________________________________
MODULE - AIR DATA (19FP1,19FP2,19FP3,19FP4,19FP5,19FP6,19FP7,19FP8)
_______________
ADJUSTMENT/TEST

TASK 34-11-17-710-001

Test of the Air Data Module without the CFDS

1. __________________
Reason for the Job

Do this test after the removal/installation of the Air Data Module when the
CFDS is unserviceable.

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
31-60-00-860-001 EIS Start Procedure
34-10-00-860-002 ADIRS Start Procedure
34-10-00-860-005 ADIRS Stop Procedure

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 3. __________
Job Set-up

Subtask 34-11-17-860-051

A. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-

002).

(2) Do the ADIRS start procedure (ADIRU related to the installed ADM
only)
(Ref. TASK 34-10-00-860-002)

(3) Do the EIS start procedure (PFD only).

(Ref. TASK 31-60-00-860-001)

Subtask 34-11-17-010-051

B. Get Access

(1) Put the access platform in position at the access door 822.

(2) Open the access door 822.

(3) On the battery power center 105VU:

- loosen the two screws and remove the protective cover.

Subtask 34-11-17-865-053

C. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06
105VU ADIRS/ADIRU1/28VDC 6FP1 C02

R **ON A/C 001-004,

121VU ADIRS/ADIRU/2/115VAC 4FP2 N07

121VU ADIRS/ADIRU/3/115VAC 4FP3 N06
121VU ADIRS/ADIRU/2/28VDC 6FP2 N05
121VU ADIRS/ADIRU/3/28VDC 6FP3 N04

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 -------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
R **ON A/C 005-099,

R 121VU ADIRS/ADIRU/2/115VAC 4FP2 N06

R 121VU ADIRS/ADIRU/3/115VAC 4FP3 N05
R 121VU ADIRS/ADIRU/2/28VDC 6FP2 N04
R 121VU ADIRS/ADIRU/3/28VDC 6FP3 N03

R **ON A/C ALL

4. Procedure
_________

Subtask 34-11-17-710-051

A. Make sure that the PFD of the onside ADIRU related to the installed ADM
shows the correct altitude (the ALT flag goes out of view and the SPD
flag goes out of view on the speed scale).

NOTE : To do the check of the altitude display with the ADIRU3 set the
____
AIR DATA selector switch to CAPT/3 (F/O/3) on the SWITCHING panel
8VU.

5. Close-up
________

Subtask 34-11-17-860-052

A. Put the aircraft back to its initial configuration.

(1) Do the ADIRS Stop Procedure(Ref. TASK 34-10-00-860-005).

(2) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

Subtask 34-11-17-410-051

B. Close Access

(1) Install the protective cover on the battery power center 105VU.

(2) Tighten the two screws.

(3) Close the access door 822.

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 (4) Remove the access platform(s).

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 SENSOR - TOTAL TEMPERATURE (11FP1,11FP2) - REMOVAL/INSTALLATION
_______________________________________________________________

TASK 34-11-18-000-001

Removal of the TAT Sensor (11FP1, 11FP2)

R WARNING : MAKE SURE THAT THE CIRCUIT BREAKERS RELATED TO THE WEATHER RADAR ARE
_______
R OPENED, SAFETIED AND TAGGED.

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific blanking caps

No specific circuit breaker(s) safety clip(s)
No specific access platform 1 m (3 ft. 3 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

34-11-18-991-001 Fig. 401

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 3. __________
Job Set-up

Subtask 34-11-18-865-050

A. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
121VU COM NAV/RADAR/1 5SQ1 K13
FOR 11FP1
49VU ANTI ICE/PROBES/AOA/1 4DA1 D04
49VU ANTI ICE/PROBES/PHC/1 2DA1 D03
49VU ANTI ICE/PROBES/PITOT/1 3DA1 D02
49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06

R **ON A/C 001-004,

121VU ADIRS/ADIRU/3/115VAC 4FP3 N06

R **ON A/C 005-099,

R 121VU ADIRS/ADIRU/3/115VAC 4FP3 N05

R **ON A/C ALL

122VU ANTI ICE/PROBES/1/STATIC 5DA1 Z13

122VU ANTI ICE/PROBES/1/TAT 1DA1 Z12
FOR 11FP2

R **ON A/C 001-004,

121VU ADIRS/ADIRU/2/115VAC 4FP2 N07

R **ON A/C 005-099,

R 121VU ADIRS/ADIRU/2/115VAC 4FP2 N06

R **ON A/C ALL

122VU ANTI ICE/PROBES/2/TAT 1DA2 Y15

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 -------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
122VU ANTI ICE/PROBES/2/PITOT 3DA2 Y14
122VU ANTI ICE/PROBES/2/AOA 4DA2 Y13
122VU ANTI ICE/PROBES/2/PHC 2DA2 Y12
122VU ANTI ICE/PROBES/2/STATIC 5DA2 Y11

Subtask 34-11-18-860-052

B. Put the access platform in position at zone 120.

4. Procedure
_________

(Ref. Fig. 401/TASK 34-11-18-991-001)

Subtask 34-11-18-020-051

A. Removal of the TAT Sensor (11FP1, 11FP2)

(1) Loosen the six screws (6).

(2) Pull the sensor (5) from its housing (2).

(3) Hold the sensor (5) and disconnect the connector (1).

(4) Put blanking caps on the disconnected electrical connectors (1) and
(4).

(5) Remove the sensor (5).

(6) Remove and discard the seal (3).

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 Total Air Temperature (TAT) Sensor
Figure 401/TASK 34-11-18-991-001

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 TASK 34-11-18-400-001

Installation of the TAT Sensor (11FP1, 11FP2)

R WARNING : MAKE SURE THAT THE CIRCUIT BREAKERS RELATED TO THE WEATHER RADAR ARE
_______
R OPENED, SAFETIED AND TAGGED.

CAUTION : MAKE SURE THAT:

_______
- THERE IS NO SIGN OF CORROSION OR DAMAGE ON THE EQUIPMENT
- THERE IS NO FOREIGN OBJECT IN THE EQUIPMENT
TO PREVENT ANY DAMAGE IN THE SYSTEM.

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific access platform 1.6 m (5 ft. 3 in.)

B. Expendable Parts

-------------------------------------------------------------------------------
FIG.ITEM |DESIGNATION |IPC-CSN
-------------------------------------------------------------------------------

3 seal 34-11-01 01 -040

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 C. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

20-28-00-720-005 Check of the Electrical Bonding of the Different

Components (But not the Fluid Systems and the
Components Installed on Composite materials)
24-41-00-861-002 Energize the Aircraft Electrical Circuits from the
External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
30-31-00-710-001 Operational Test of the Probe Ice Protection
34-11-18-710-001 Test of the TAT Sensor (11FP1, 11FP2) without the
CFDS
34-11-18-991-001 Fig. 401

3. __________
Job Set-up

Subtask 34-11-18-860-054

A. Aircraft Maintenance Configuration

(1) Make sure that the access platform is in position at zone 120.

Subtask 34-11-18-865-051

B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and
tagged

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
121VU COM NAV/RADAR/1 5SQ1 K13
FOR 11FP1
49VU ANTI ICE/PROBES/AOA/1 4DA1 D04
49VU ANTI ICE/PROBES/PHC/1 2DA1 D03
49VU ANTI ICE/PROBES/PITOT/1 3DA1 D02
49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06

R **ON A/C 001-004,

121VU ADIRS/ADIRU/3/115VAC 4FP3 N06

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 -------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
R **ON A/C 005-099,

R 121VU ADIRS/ADIRU/3/115VAC 4FP3 N05

R **ON A/C ALL

122VU ANTI ICE/PROBES/1/STATIC 5DA1 Z13

122VU ANTI ICE/PROBES/1/TAT 1DA1 Z12
FOR 11FP2

R **ON A/C 001-004,

121VU ADIRS/ADIRU/2/115VAC 4FP2 N07

R **ON A/C 005-099,

R 121VU ADIRS/ADIRU/2/115VAC 4FP2 N06

R **ON A/C ALL

122VU ANTI ICE/PROBES/2/TAT 1DA2 Y15

122VU ANTI ICE/PROBES/2/PITOT 3DA2 Y14
122VU ANTI ICE/PROBES/2/AOA 4DA2 Y13
122VU ANTI ICE/PROBES/2/PHC 2DA2 Y12
122VU ANTI ICE/PROBES/2/STATIC 5DA2 Y11

4. Procedure
_________

(Ref. Fig. 401/TASK 34-11-18-991-001)

Subtask 34-11-18-420-051

A. Installation of the TAT Sensor (11FP1, 11FP2)

(1) Clean the component interface and/or the adjacent area.

(2) Do an inspection of the component interface and/or the adjacent area.

(3) Install the new seal (3) on the sensor (5).

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 (4) Remove the blanking caps from the connectors (1) and (4).

(5) Make sure that the electrical connectors are clean and in the correct
condition.

(6) Connect the connector (1) to the sensor (5) out of the housing (2).

(7) Install the sensor (5) in its housing (2) and hold it.

NOTE : Make sure that the seal (3) is in the correct position.
____

(8) Tighten the six screws (6).

(9) Check the bonding contact resistance between the TAT Sensor (5) and
the fuselage structure (2) (Ref. TASK 20-28-00-720-005).

Subtask 34-11-18-860-053

B. Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002).

Subtask 34-11-18-865-052

C. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
5SQ1
FOR 11FP1
4FP1, 4FP3, 1DA1, 2DA1, 3DA1, 4DA1, 5DA1
FOR 11FP2
4FP2, 1DA2, 2DA2, 3DA2, 4DA2, 5DA2

Subtask 34-11-18-710-050-A

D. Do the operational test of the TAT sensor with the CFDS.

(1) Do the operational test of the Probe Ice Protection.

(Ref. TASK 30-31-00-710-001)

(2) Do the operational test of the INPUT STATUS:

NOTE : The TAT sensor 1 is related to the ADIRU 1 and 3. The TAT
____
sensor 2 is related to the ADIRU 2.

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

R 1. On the center pedestal, on one On the MCDU:

R MCDU:

- push the MCDU MENU mode key. - the MCDU MENU page comes into view.

- push the line key adjacent to - the CFDS MENU page comes into view.
the CFDS indication.

- push the line key adjacent to - the SYSTEM REPORT/TEST page comes
the SYSTEM REPORT/TEST into view.
indication.

- push the line key adjacent to - the SYSTEM REPORT/TEST NAV page comes
the NAV indication. into view.

- push the line key adjacent to - the ADR1 (ADR2) (ADR3) page comes
the ADR1 (ADR2) (ADR3) into view.
indication (related to the
removed TAT sensor).

- push the line key adjacent to - the INPUT STATUS page comes into
the INPUT STATUS indication. view.

- push NEXT PAGE key until you - INPUT STATUS pages 3/8 and 7/8 come
get ADR1 (ADR2) (ADR3)/INPUT into view:
STATUS pages 3/8 and 7/8. do a check of the TAT data (OPEN, XXX
⁰ C).

NOTE : As an alternative procedure, you can do this operational test

____
without the CFDS
(Ref. TASK 34-11-18-710-001).

5. Close-up
________

Subtask 34-11-18-860-055

A. Put the aircraft back to its initial configuration.

(1) On the MCDU , push the MCDU MENU mode key.

(2) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-

002).

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 (3) Make sure that the work area is clean and clear of tool(s) and other
items.

(4) Remove the access platform(s).

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 SENSOR - TOTAL TEMPERATURE (11FP1,11FP2) - ADJUSTMENT/TEST
__________________________________________________________

TASK 34-11-18-710-001

Test of the TAT Sensor (11FP1, 11FP2) without the CFDS

1. __________________
Reason for the Job

Do this test after the removal/installation of the TAT Sensor (11FP1,11FP2)

when the CFDS is unserviceable.

2. ______________________
Job Set-up Information

A. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
34-10-00-860-005 ADIRS Stop Procedure
FOR FIN 11FP2
31-60-00-860-001 EIS Start Procedure
34-10-00-860-002 ADIRS Start Procedure

3. __________
Job Set-up

Subtask 34-11-18-860-051

A. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits

(Ref. TASK 24-41-00-861-002).

(2) Do the EIS start procedure

FOR 11FP1
Lower ECAM DU and CAPT ND only
FOR 11FP2
Lower ECAM DU only
(Ref. TASK 31-60-00-860-001).

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 (3) Do the ADIRS start procedure
FOR 11FP1
ADIRU 1 and 3 only
FOR 11FP2
ADIRU 2 only
(Ref. TASK 34-10-00-860-002).

Subtask 34-11-18-865-053

B. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
FOR 11FP1
49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06

R **ON A/C 001-004,

121VU ADIRS/ADIRU/3/115VAC 4FP3 N06

R **ON A/C 005-099,

R 121VU ADIRS/ADIRU/3/115VAC 4FP3 N05

R **ON A/C ALL

122VU ANTI ICE/PROBES/1/TAT 1DA1 Z12

FOR 11FP2

R **ON A/C 001-004,

121VU ADIRS/ADIRU/2/115VAC 4FP2 N07

R **ON A/C 005-099,

R 121VU ADIRS/ADIRU/2/115VAC 4FP2 N06

R **ON A/C ALL

122VU ANTI ICE/PROBES/2/TAT 1DA2 Y15

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 4. Procedure
_________

Subtask 34-11-18-710-051

A. Test of the TAT Sensor

(1) Operational test of the TAT sensor 11FP1:

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

On the SWITCHING panel 8VU:

- set the ECAM/ND XFR selector - the display of the lower ECAM DU
switch to CAPT. moves to the CAPT ND.
- make sure that the SAT and TAT
indications are shown at the bottom
of the CAPT ND, on the left side.

- set the AIR DATA selector switch - make sure that the SAT and TAT
to CAPT/3. indications stay in view on the CAPT
ND.

- set the ECAM/ND XFR and AIR DATA

selector switches to NORM.

(2) Operational test of the TAT sensor 11FP2:

- Make sure that the SAT and TAT indications are shown at the bottom
section of the lower ECAM DU, on the left side.

5. Close-up
________

Subtask 34-11-18-860-050

A. Put the aircraft back to its initial configuration.

(1) Do the ADIRS Stop Procedure(Ref. TASK 34-10-00-860-005).

(2) On the center pedestal,on the ECAM control panel, set the LOWER
DISPLAY potentiometer to OFF.

(3) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

(4) Make sure that the work area is clean and clear of tool(s) and other
items.

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 SENSOR - ANGLE OF ATTACK (3FP1,3FP2,3FP3) - REMOVAL/INSTALLATION
________________________________________________________________

TASK 34-11-19-000-001

Removal of the Angle of Attack Sensor (3FP1, 3FP2, 3FP3)

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific blanking caps

No specific circuit breaker(s) safety clip(s)
No specific access platform 3.4 m (11 ft. 2 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

34-11-19-991-001 Fig. 401

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 3. __________
Job Set-up

Subtask 34-11-19-865-050

A. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
FOR 3FP1
49VU ANTI ICE/PROBES/AOA/1 4DA1 D04
49VU ANTI ICE/PROBES/PHC/1 2DA1 D03
49VU ANTI ICE/PROBES/PITOT/1 3DA1 D02
49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07
49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06

R **ON A/C 001-004,

121VU ADIRS/ADIRU/3PWR/SWTG 9FP N10

R **ON A/C 005-099,

R 121VU ADIRS/ADIRU/3PWR/SWTG 9FP N09

R **ON A/C ALL

122VU ANTI ICE/PROBES/1/STATIC 5DA1 Z13

122VU ANTI ICE/PROBES/1/TAT 1DA1 Z12
FOR 3FP2

R **ON A/C 001-004,

121VU ADIRS/ADIRU/2PWR/SHED 10FP N11

121VU ADIRS/ADIRU/2/26VAC AND AOA 5FP2 N09
121VU ADIRS/ADIRU/2/115VAC 4FP2 N07

R **ON A/C 005-099,

R 121VU ADIRS/ADIRU/2PWR/SHED 10FP N10

R 121VU ADIRS/ADIRU/2/26VAC AND AOA 5FP2 N08
R 121VU ADIRS/ADIRU/2/115VAC 4FP2 N06

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 -------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
R **ON A/C ALL

122VU ANTI ICE/PROBES/2/TAT 1DA2 Y15

122VU ANTI ICE/PROBES/2/PITOT 3DA2 Y14
122VU ANTI ICE/PROBES/2/AOA 4DA2 Y13
122VU ANTI ICE/PROBES/2/PHC 2DA2 Y12
122VU ANTI ICE/PROBES/2/STATIC 5DA2 Y11
FOR 3FP3

R **ON A/C 001-004,

121VU ADIRS/ADIRU/3PWR/SWTG 9FP N10

121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N08
121VU ADIRS/ADIRU/3/115VAC 4FP3 N06

R **ON A/C 005-099,

R 121VU ADIRS/ADIRU/3PWR/SWTG 9FP N09

R 121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N07
R 121VU ADIRS/ADIRU/3/115VAC 4FP3 N05

R **ON A/C ALL

122VU ANTI ICE/PROBES/PHC/3 2DA3 Y16

122VU ANTI ICE/PROBES/3/PITOT 3DA3 Z16
122VU ANTI ICE/PROBES/3/AOA 4DA3 Z15
122VU ANTI ICE/PROBES/3/STATIC 5DA3 Z14

Subtask 34-11-19-860-050

B. Put an access platform in position in zone 231 for 3FP1 (232 for 3FP2)
(127 for 3FP3).

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 4. Procedure
_________

(Ref. Fig. 401/TASK 34-11-19-991-001)

Subtask 34-11-19-020-050

A. Removal of the Angle of Attack Sensor (3FP1, 3FP2, 3FP3)

NOTE : The procedure is the same for angle of attack sensors 3FP1, 3FP2
____
and 3FP3.

(1) Remove the potting compound from the screw (6).

(2) Loosen the seven screws (8).

(3) Remove the blanking plate (7).

(4) Remove the screw (6).

NOTE : Carefully remove the plate so as not to cause damage to the

____
sensor (5).

(5) Disengage and hold the sensor (5).

(6) Disconnect the connector (1).

(7) Remove the angle of attack sensor (5).

(8) Remove and discard the seal (3).

(9) Put blanking caps on the disconnected electrical connectors (1) and
(9).

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 Angle of Attack Sensor
Figure 401/TASK 34-11-19-991-001

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 TASK 34-11-19-400-001

Installation of the Angle of Attack Sensor (3FP1, 3FP2, 3FP3)

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific access platform 1.6 m (5 ft. 3 in.)

B. Consumable Materials

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

R Material No. 09-016 USA MIL-PRF-81733D TYPE II CLASS B

CORROSION INHIBITING FILLET CONSISTENCY
(Ref. 20-31-00)

C. Expendable Parts

-------------------------------------------------------------------------------
FIG.ITEM |DESIGNATION |IPC-CSN
-------------------------------------------------------------------------------

3 seal 34-11-02 01 -070

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 D. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

20-28-00-720-005 Check of the Electrical Bonding of the Different

Components (But not the Fluid Systems and the
Components Installed on Composite materials)
30-31-00-710-001 Operational Test of the Probe Ice Protection
34-10-00-710-007 Test of the Angle of Attack Warning
34-11-00-710-001 Test of the Monitoring of the ADR/AOA 26VAC Power
Supply
34-11-19-991-001 Fig. 401

3. __________
Job Set-up

Subtask 34-11-19-860-051

A. Aircraft Maintenance Configuration

(1) Make sure that the access platform is in position in zone 231 for
3FP1 (232 for 3FP2) (127 for 3FP3).

Subtask 34-11-19-865-051

B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and
tagged

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
FOR 3FP1
49VU ANTI ICE/PROBES/AOA/1 4DA1 D04
49VU ANTI ICE/PROBES/PHC/1 2DA1 D03
49VU ANTI ICE/PROBES/PITOT/1 3DA1 D02
49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07
49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06

R **ON A/C 001-004,

121VU ADIRS/ADIRU/3PWR/SWTG 9FP N10

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 -------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
R **ON A/C 005-099,

R 121VU ADIRS/ADIRU/3PWR/SWTG 9FP N09

R **ON A/C ALL

122VU ANTI ICE/PROBES/1/STATIC 5DA1 Z13

122VU ANTI ICE/PROBES/1/TAT 1DA1 Z12
FOR 3FP2

R **ON A/C 001-004,

121VU ADIRS/ADIRU/2PWR/SHED 10FP N11

121VU ADIRS/ADIRU/2/26VAC AND AOA 5FP2 N09
121VU ADIRS/ADIRU/2/115VAC 4FP2 N07

R **ON A/C 005-099,

R 121VU ADIRS/ADIRU/2PWR/SHED 10FP N10

R 121VU ADIRS/ADIRU/2/26VAC AND AOA 5FP2 N08
R 121VU ADIRS/ADIRU/2/115VAC 4FP2 N06

R **ON A/C ALL

122VU ANTI ICE/PROBES/2/TAT 1DA2 Y15

122VU ANTI ICE/PROBES/2/PITOT 3DA2 Y14
122VU ANTI ICE/PROBES/2/AOA 4DA2 Y13
122VU ANTI ICE/PROBES/2/PHC 2DA2 Y12
122VU ANTI ICE/PROBES/2/STATIC 5DA2 Y11
FOR 3FP3

R **ON A/C 001-004,

121VU ADIRS/ADIRU/3PWR/SWTG 9FP N10

121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N08
121VU ADIRS/ADIRU/3/115VAC 4FP3 N06

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 -------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
R **ON A/C 005-099,

R 121VU ADIRS/ADIRU/3PWR/SWTG 9FP N09

R 121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N07
R 121VU ADIRS/ADIRU/3/115VAC 4FP3 N05

R **ON A/C ALL

122VU ANTI ICE/PROBES/PHC/3 2DA3 Y16

122VU ANTI ICE/PROBES/3/PITOT 3DA3 Z16
122VU ANTI ICE/PROBES/3/AOA 4DA3 Z15
122VU ANTI ICE/PROBES/3/STATIC 5DA3 Z14

4. Procedure
_________

(Ref. Fig. 401/TASK 34-11-19-991-001)

Subtask 34-11-19-420-050

A. Installation of the Angle of Attack Sensor (3FP1, 3FP2, 3FP3)

NOTE : The procedure is the same for angle of attack sensors 3FP1, 3FP2
____
and 3FP3.

(1) Clean the component interface and/or the adjacent area.

(2) Do an inspection of the component interface and/or the adjacent area.

(3) Remove the blanking caps from the connectors (1) and (9).

(4) Make sure that the connectors (1) and (9) are clean and in the
correct condition.

(5) Put the seal (3) in its housing (2).

(6) Connect the connector (1).

(7) Push the connector (1) into the fuselage.

(8) Put the angle of attack sensor (5) in position with the stud (4) and
hold it.

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 (9) Tighten the screw (6).

NOTE : During installation, the screw (6) must be inserted in the

____
only c-sink hole of the AOA sensor (5).As the other holes have
no c-sink, mounting the screw (6) in one of them may create
non-flush surface.

(10) Install and hold the blanking plate (7).

NOTE : The AOA blanking plate (7) is manufactured with a radius that
____
corresponds to the fuselage curve.The rotation of this plate
around the AOA sensor may also create non-flush surface.
The blanking plate (7) contains 8 attaching holes.Out of these
8 holes, 7 have a c-sink, 1 has not.Whilst mounting the
blanking plate (7), it must be ensured that the only hole
without the c-sink is aligned with the screw (6).

NOTE : The 7 remaining screws (8) must all be inserted in each of the
____
7 c-sink holes of the blanking plate (7).

NOTE : Carefully install plate so as not to cause damage to the

____
sensor (5).

(11) Tighten the seven screws (8).

(12) Check the bonding contact resistance between the AOA Sensor (7) and
the fuselage struture (2) (Ref. TASK 20-28-00-720-005).

(13) Apply SEALANTS (Material No. 09-016) on the screw (6) head and around
the blanking plate (7).

Subtask 34-11-19-865-052

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
FOR 3FP1
4FP1, 5FP1, 9FP, 1DA1, 2DA1, 3DA1, 4DA1, 5DA1
FOR 3FP2
4FP2, 5FP2, 10FP, 1DA2, 2DA2, 3DA2, 4DA2, 5DA2
FOR 3FP3
4FP3, 5FP3, 9FP, 2DA3, 3DA3, 4DA3, 5DA3

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 Subtask 34-11-19-710-050

C. Test

(1) Do the operational test of the Probe Ice Protection

(Ref. TASK 30-31-00-710-001).

(2) Do the test of the angle of attack warning.

(Ref. TASK 34-10-00-710-007).

NOTE : As an alternative procedure, you can do an operational test

____
without the CFDS.
(Ref. TASK 34-11-00-710-001).

5. Close-up
________

Subtask 34-11-19-860-052

A. Put the aircraft back to its initial configuration.

(1) Make sure that the work area is clean and clear of tool(s) and other
items.

(2) Remove the access platform(s).

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 AIR DATA/INERTIAL REFERENCE SYSTEM (ADIRU & CDU) - DESCRIPTION AND OPERATION
____________________________________________________________________________

1. _______
General
The Air Data/Inertial Reference System (ADIRS) provides the main air data
and heading/attitude/navigation data to the aircraft systems.
The main computers of the ADIRS are the three Air Data/Inertial Reference
Units (ADIRU) which are controlled by the ADIRS Control and Display Unit
(CDU).
The ADIRS is a three channel system. Each channel is isolated from the
others and provides independent information as defined in ARINC 738.
Each ADIRU contains:
- an Air Data Reference (ADR) portion. Its operation is described in 34-13
- an Inertial Reference (IR) portion. Its operation is described in 34-14.
Power supply is common for ADR and IR and described in 34-11.

2. __________________
Component Location

(Ref. Fig. 001, 002)

The three ADIRUs are installed in the avionics compartment.
The ADIRS CDU is installed in the cockpit.

-------------------------------------------------------------------------------
FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA
| | | | DOOR | REF.
-------------------------------------------------------------------------------
1FP1 ADIRU-1 127 824 34-12-34
1FP2 ADIRU-2 128 824 34-12-34
1FP3 ADIRU-3 127 824 34-12-34
2FP CDU-ADIRS 20VU 211 831 34-12-12

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 ADIRS - Component Location
Figure 001

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 ADIRS CDU - Component Location
Figure 002

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 3. Interface
_________

A. Mechanical Interface
The ADIRUs are installed and aligned on a specific mounting tray in the
avionics compartment in accordance with the installation design defined
in ARINC 738. The ADIRU is to 4 MCU size. In order to ensure attitude and
azimuth accuracy, the mounting tray orientation complies with the
following tolerances:
- pitch and roll: plus or minus 12 minutes
- azimuth: plus or minus 12 minutes.

B. Electrical Interface

(1) ADIRS CDU

(a) General

(Ref. Fig. 003)

The ADIRS CDU contains three identical connectors. Each connector
is linked to one ADIRU by means of an insert position keying.
The four annunciator discretes ADR OFF, ADR FAULT, IR ALIGN and
IR FAULT are linked to the ADIRS CDU from the ADIRU, through the
annunciator light test and interface boards.
The CDU panel lighting and LCD backlighting are provided by bulbs
supplied with 5VAC (from the A/C electrical generation).
The CDU exchanges data with the ADIRU.
The data sent by the CDU can be used for the initialization of
the IR portion. The data received by the CDU are displayed on the
Liquid Crystal Display (LCD).

(b) CDU Digital Form

The tables below contain all the output parameters in the digital
form.
They are sorted as per the numerical order of their output label.
The following tables give:
- EQ.SYS.LAB.SDI: (SDAC, FWC, DMC...) output label for which the
parameter is available
- PARAMETER DEFINITION: parameter name
- WORD RANGE/OPER RANGE/RESOLUTION ACCURACY: measurement range
Maximum value transmitted. When the digital value changes, the
change step is equal to the accuracy
- UNIT: unit in which the digital value is transmitted
- SIG BIT: indicates whether a sign bit is available
- BITS: number of bits used by the parameter in the label
- XMSN/INTV: output transmission interval. The refresh rate is
given in milliseconds.
- CODE:

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 ADIRS CDU - Electrical Interface
Figure 003

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 BNR: binary data word
BCD: binary coded decimal data word
ISO: data word coded in ISO5 code
DIS: discrete data word
HEX: hexadecimal coded
HYB: mixed code.
- ALPHA CODE: indicates the parameter mnemonic code
- SOURCE ORIGIN: parameter source computer or system.

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 1
_ CDU bus inputs
The CDU receives an ARINC 429 High Speed bus from the IR
portion of each ADIRU.

-------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
| 010 |PRESENT |90S-90N |DEG | | 6 | | BCD| |
| |POS LAT-D |(POSITIVE: |& | | | | | |
| | |NORTH FROM |MIN | | | | | |
| | |0 DEG) | | | | | | |
| | |RESOL = .1 | | | | | | |
|-----------------------------------------------------------------------------|
| 011 |PRESENT |180E-180W |DEG | | 6 | | BCD| |
| |POS LONG-D |(POSITIVE: |& | | | | | |
| | |EAST FROM |MIN | | | | | |
| | |0 DEG) | | | | | | |
| | |RESOL = .1 | | | | | | |
|--------------|-----------|-----------|----|---|----|----|----|--------------|
| 012 |GROUND |0-2000 |Kt | | 4 | | BCD| |
| |SPEED-D |(ALWAYS | | | | | | |
| | |POSITIVE) | | | | | | |
| | |RESOL = 1 | | | | | | |
|--------------|-----------|-----------|----|---|----|----|----|--------------|
| 013 |TRACK |0-359.9 |DEG | | 4 | | BCD| |
| |ANGLE TRUE |(POSITIVE: | | | | | | |
| | |CW FROM | | | | | | |
| | |NORTH) | | | | | | |
| | |RESOL = .1 | | | | | | |
|--------------|-----------|-----------|----|---|----|----|----|--------------|
| 014 |MAGNETIC |0-359.9 |DEG | | 4 | | BCD| |
| |HEADING |(POSITIVE: | | | | | | |
| | |CW FROM | | | | | | |
| | |NORTH) | | | | | | |
| | |RESOL = .1 | | | | | | |
|--------------|-----------|-----------|----|---|----|----|----|--------------|
| 015 |WIND SPEED |0-256 |Kt | | 3 | | BCD| |
| | |(ALWAYS | | | | | | |
| | |POSITIVE) | | | | | | |
| | |RESOL = 1 | | | | | | |
|--------------|-----------|-----------|----|---|----|----|----|--------------|

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 -------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
| 016 |WIND DIR |0-359 |DEG | | 3 | | BCD| |
| |TRUE |(POSITIVE: | | | | | | |
| | |CW FROM | | | | | | |
| | |NORTH) | | | | | | |
| | |RESOL = 1 | | | | | | |
|--------------|-----------|-----------|----|---|----|----|----|--------------|
| 044 |TRUE |0-359.9 |DEG | | 4 | | BCD| |
| |HEADING |(POSITIVE: | | | | | | |
| | |CW FROM | | | | | | |
| | |NORTH) | | | | | | |
| | |RESOL = .1 | | | | | | |
|--------------|-----------|-----------|----|---|----|----|----|--------------|
| 270 |IR DISCRETE| | | | 19 | | DIS| |
| |(1) | | | | | | | |
|--------------|-----------|-----------|----|---|----|----|----|--------------|
| 277 |CDU TEST | | | | 18 | | DIS| |
| |WORD (1) | | | | | | | |
|--------------|-----------|-----------|----|---|----|----|----|--------------|
| 350 |ACTION | | | | 19 | | DIS| |
| |CODE (1) | | | | | | | |
-------------------------------------------------------------------------------
CDU IR Input Labels

NOTE : (1) The complete definition of the labels 270, 277 and
____
350 is detailed in 34-14-00 Para. 2.D.(1).

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 2
_ CDU bus outputs
The CDU sends the parameters detailed in the following table
to the IR portion of each ADIRU:

-------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
| 041 |SET | 90S-90N |DEG | | 6 | | BCD| |
| |LATITUDE | (POSITIVE: |& | | | | | |
| | | NORTH) |MIN | | | | | |
| | | RESOL = 0.1| | | | | | |
|--------------|----------|------------|----|----|----|----|----|-------------|
| 042 |SET | 180E-180W |DEG | | 6 | | BCD| |
| |LONGITUDE | (POSITIVE: |& | | | | | |
| | | EAST) |MIN | | | | | |
| | | RESOL = 0.1| | | | | | |
|--------------|----------| -----------|----|----|----|----|----|-------------|
| 043 |SET | 0-359 |DEG | | 3 | | BCD| |
| |MAGNETIC | (POSITIVE: | | | | | | |
| |HDG | CW FROM N) | | | | | | |
| | | RESOL = 1 | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-------------|
| 277 |CDU TEST | | | | 19 | | DIS| |
-------------------------------------------------------------------------------
CDU Output Labels

R **ON A/C 001-004,

(2) ADIRU
The ADIRU receives data and computes outputs in accordance with ARINC
738. It uses an ARINC 600 type 2 floating-connector.

(a) Digital inputs

- Air Data Module (ADM) inputs
The ADR provides up to five ADM input buses. Only three of them
are used to receive air mass data from remotely mounted ADM
(Ref. 34-11), two linked to the static probe and one linked to
the pitot probe.

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 NOTE : For the ADIRU 3, only two ADM input buses are used: one
____
for the total pressure data and the other for the averaged
static pressure data.

- digital baro-correction inputs

The ADR provides two baro-correction digital data input ports.
The incoming data from the Flight Control Unit (FCU) are in
ARINC 429 low speed format.
The ADR receives data from baro-correction bus A.
The baro-correction is used to compensate baro-corrected
altitude output.
- initialization data inputs
The IR portion of the ADIRU receives data from either ARINC 702
Flight Management and Guidance Computer (FMGC). The data are in
ARINC 429 low speed format. The initialization parameters are
latitude and longitude or magnetic heading.
- CFDIU input
The ADIRU provides one Centralized Fault Display Interface Unit
(CFDIU) input bus. The data are in ARINC 429 low speed format.
The CFDIU continuously transmits data to all systems. The ADIRU
uses these data to accept commands from the CFDIU.
- Air Data Reference inputs
The IR portion of the ADIRU provides two digital data input
ports for receiving data from the other ADIRUs.
The incoming data are in ARINC 429 low speed format and include
altitude and true airspeed.
- the ADIRU provides provision for digital input buses (two buses
are reserved for the Global Positioning System (GPS)).
- CDU inputs
The IR portion of the ADIRU receives data from one ARINC 738
CDU. The data are in ARINC 429 low speed format. These data are
initialization parameters (latitude and longitude or magnetic
heading) and CDU status.

(b) Analog inputs

- analog AOA input
The ADR portion of the ADIRU accepts two resolver inputs of
indicated angle of attack.
The characteristics of the resolvers, as seen by the ADR, are
as follows:
. scale factor: 1⁰/Degree of AOA
. index reference: 0⁰ resolver input = 25⁰ AOA
- Total Air Temperature (TAT) sensor
The ADR portion of the ADIRU accepts a standard 500 ohm
platinum sensing element input from the TAT sensor.
The ADR derives the measured temperature from the TAT sensor
input using the Callender-Van Dusen equation from ARINC 738.

R
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 - 115VAC
The ADIRU operates from the 115VAC/400 Hz primary power.
- 28VDC back-up
The ADIRU can operate from the 28VDC back-up power.
- 26VAC reference
The ADIRU accepts up to three 26VAC resolver reference inputs.
Only one is used for the AOA resolver.
The ADIRU provides provisions for analog inputs (two 26VAC
reference inputs, and three analog baro-correction inputs are
reserved).

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 (c) Discrete inputs
These inputs are generally pin programs except for:
- Static Source Error Correction (SSEC) and AOA correction and
selection discretes which come from the Slat and Flap Control
Computers (SFCC) and are linked to flap position
(Ref. Fig. 004)
- heat discretes which come from the associated Probe Heat
Computer (PHC)
- VMO/MMO discrete provided by the position of the L/G DOWN
VMO/MMO SELECTION switch (22FP).
- ADR selection:
It indicates, to the IR, the air data source to be used.
- CDU ON/OFF:
It indicates, to the ADIRU, whether the ADIRU data are
currently displayed on the CDU.
- ADR OFF:
It indicates, to the ADIRU, that the crew has pushed the ADR
pushbutton switch on the ADIRS CDU. This commands the ADIRU to
stop the transmission of the ADR output buses.
- IR MODE SELECT:
It indicates, to the ADIRU, the position of the associated
selector switch on the CDU. Three positions can be coded: OFF,
NAV, ATT. This gives the computer operating mode.

The functions of the pin program discretes are:

- aircraft identification:
seven discretes provide the ADIRU with the identification of
the aircraft.
They are used by the ADR to select the appropriate SSEC and AOA
correction laws and by the IR to select the appropriate
filtering (bandwidth) of the output labels.
- baro-correction source selection:
This discrete provides the ADIRU with the following:
. the form (digital or analog) in which the baro-correction
transmission is made
. the number of sources (2 or 3)
. the type of transmission used by the digital sources (single
bus or various buses).
On the A/C, the FCU transmits the CAPT and F/O baro-correction
in digital form on separate buses.
- AOA average/unique:
The ADIRU receives the AOA on two resolvers.
This discrete indicates whether the computation must use an
average value from the two resolvers or the value of resolver 1
in priority with the second as a back-up in case of failure.
This last solution is chosen on the A/C.
- ADR ARINC the filter select:

R
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 ADIRS - ADIRUs/SFCCs Interface
Figure 004

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 Unused (the selection of the ADR outputs filtering is done by
the A/C ident pin programming).
- mounting position:
This indicates the orientation of the unit to the IR portion.
It is used to know where are the longitudinal and lateral axes
of the aircraft and the sign of motion measured.
- SDI:
This indicates on which side (CAPT, F/O, Standby) the ADIRU is
installed.
- CMC-CFDS message select:
The ADIRU could be installed on other A/C version. In this
case, the ADIRU selects a table of maintenance messages with a
different syntax.

**ON A/C ALL

R Post SB 34-1147 For A/C 001-004,

(2) ADIRU
The ADIRU receives data and computes outputs in accordance with ARINC
738. It uses an ARINC 600 type 2 floating-connector.

(a) Digital inputs

- Air Data Module (ADM) inputs
The ADR provides up to five ADM input buses. Only three of them
are used to receive air mass data from remotely mounted ADM
(Ref. 34-11), two linked to the static probe and one linked to
the pitot probe.

NOTE : For the ADIRU 3, only two ADM input buses are used: one
____
for the total pressure data and the other for the averaged
static pressure data.

- digital baro-correction inputs

The ADR provides two baro-correction digital data input ports.
The incoming data from the Flight Control Unit (FCU) are in
ARINC 429 low speed format.
The ADR receives data from baro-correction bus A.
The baro-correction is used to compensate baro-corrected
altitude output.
- initialization data inputs
The IR portion of the ADIRU receives data from either ARINC 702
Flight Management and Guidance Computer (FMGC). The data are in
ARINC 429 low speed format. The initialization parameters are
latitude and longitude or magnetic heading.
- CFDIU input

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R The ADIRU provides one Centralized Fault Display Interface Unit
R (CFDIU) input bus. The data are in ARINC 429 low speed format.
R The CFDIU continuously transmits data to all systems. The ADIRU
R uses these data to accept commands from the CFDIU.
R - Air Data Reference inputs
R The IR portion of the ADIRU provides two digital data input
R ports for receiving data from the other ADIRUs.
R The incoming data are in ARINC 429 low speed format and include
R altitude and true airspeed.
R - CDU inputs
R The IR portion of the ADIRU receives data from one ARINC 738
R CDU. The data are in ARINC 429 low speed format. These data are
R initialization parameters (latitude and longitude or magnetic
R heading) and CDU status.
R - GPS inputs
R The IR portion of the ADIRU receives data from the GPS portion
R of the Multi-Mode Receivers (MMRs).
R The data are in ARINC 429 high speed format. These data concern
R various parameters such as position, velocity, and integrity.
R - the ADIRU provides provision for digital input buses.

R (b) Analog inputs

R - analog AOA input
R The ADR portion of the ADIRU accepts two resolver inputs of
R indicated angle of attack.
R The characteristics of the resolvers, as seen by the ADR, are
R as follows:
R . scale factor: 1⁰/Degree of AOA
R . index reference: 0⁰ resolver input = 25⁰ AOA
R - Total Air Temperature (TAT) sensor
R The ADR portion of the ADIRU accepts a standard 500 ohm
R platinum sensing element input from the TAT sensor.
R The ADR derives the measured temperature from the TAT sensor
R input using the Callender-Van Dusen equation from ARINC 738.
R - GPS Time Mark inputs
R This allows the ADIRU to be synchronized with the GPS portion
R of the MMRs.
R - 115VAC
R The ADIRU operates from the 115VAC/400 Hz primary power.
R - 28VDC back-up
R The ADIRU can operate from the 28VDC back-up power.
R - 26VAC reference
R The ADIRU accepts up to three 26VAC resolver reference inputs.
R Only one is used for the AOA resolver.
R The ADIRU provides provisions for analog inputs (two 26VAC
R reference inputs, and three analog baro-correction inputs are
R reserved).

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R (c) Discrete inputs
R These inputs are generally pin programs except for:
R - Static Source Error Correction (SSEC) and AOA correction and
R selection discretes which come from the Slat and Flap Control
R Computers (SFCC) and are linked to flap position
R (Ref. Fig. 004)
R - heat discretes which come from the associated Probe Heat
R Computer (PHC)
R - VMO/MMO discrete provided by the position of the L/G DOWN
R VMO/MMO SELECTION switch (22FP).
R - ADR selection:
R It indicates, to the IR, the air data source to be used.
R - CDU ON/OFF:
R It indicates, to the ADIRU, whether the ADIRU data are
R currently displayed on the CDU.
R - ADR OFF:
R It indicates, to the ADIRU, that the crew has pushed the ADR
R pushbutton switch on the ADIRS CDU. This commands the ADIRU to
R stop the transmission of the ADR output buses.
R - IR MODE SELECT:
R It indicates, to the ADIRU, the position of the associated
R selector switch on the CDU. Three positions can be coded: OFF,
R NAV, ATT. This gives the computer operating mode.
R
R The functions of the pin program discretes are:
R - aircraft identification:
R seven discretes provide the ADIRU with the identification of
R the aircraft.
R They are used by the ADR to select the appropriate SSEC and AOA
R correction laws and by the IR to select the appropriate
R filtering (bandwidth) of the output labels.
R - baro-correction source selection:
R This discrete provides the ADIRU with the following:
R . the form (digital or analog) in which the baro-correction
R transmission is made,
R . the number of sources (2 or 3),
R . the type of transmission used by the digital sources (single
R bus or various buses).
R On the A/C, the FCU transmits the CAPT and F/O baro-correction
R in digital form on separate buses.
R - AOA average/unique:
R The ADIRU receives the AOA on two resolvers.
R This discrete indicates whether the computation must use an
R average value from the two resolvers or the value of resolver 1
R in priority with the second as a back-up in case of failure.
R This last solution is chosen on the A/C.
R - ADR ARINC filter select:

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R Unused (the selection of the ADR outputs filtering is done by
R the A/C ident pin programming).
R - mounting position:
R This indicates the orientation of the unit to the IR portion.
R It is used to know where are the longitudinal and lateral axes
R of the aircraft and the sign of motion measured.
R - SDI:
R This indicates on which side (CAPT, F/O, Standby) the ADIRU is
R installed.
R - CMC-CFDS message select:
R The ADIRU could be installed on other A/C versions. In this
R case, the ADIRU selects a table of maintenance messages with a
R different syntax.
R - GPS sensor present:
R This indicates, to the ADIRU, the presence on-board the
R aircraft of one or two MMRs (GPS portion).
R - GPS priority select:
R This indicates, to the ADIRU, the priority for using the MMRs
R (GPS portion).

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R **ON A/C ALL

(d) Digital outputs

- The ADR portion of the ADIRU provides eight identical ARINC 429
Low Speed buses. Two of these buses are dedicated to the
interface with the Electronic Control Units (ECU).
The number of these buses is 5 and 6.
The system users are described in the table below:

----------------------------------------------------------------------------
| USERS | ADR 1 BUS | ADR 2 BUS | ADR 3 BUS |
| |-----------------|-----------------|-----------------|
| |1 |2 |3 |4 |5 |6 |1 |2 |3 |4 |5 |6 |1 |2 |3 |4 |5 |6 |
|--------------------------------------------------------------------------|
|ADIRU 1 | | | | | | | | |* | | | | | |* | | | |
|--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|
|ADIRU 2 | |* | | | | | | | | | | | |* | | | | |
|--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|
|ADIRU 3 | | |* | | | | | | |* | | | | | | | | |
|--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|
|FMGC 1 | | |* | | | | | |* | | | | | |* | | | |
|--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|
|FMGC 2 | |* | | | | | |* | | | | | |* | | | | |
|--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|
|DMC 1 |* | | | | | | | | | | | | | |* | | | |
|--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|
|DMC 2 | | | | | | |* | | | | | | |* | | | | |
|--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|
|DMC 3 | | |* | | | | | |* | | | |* | | | | | |
|--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|
|ATC 1 | | | |* | | | | | | | | | | | |* | | |
|--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|
|ATC 2 | | | | | | | |* | | | | | |* | | | | |
|--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|
|FWC 1 | | |* | | | | | |* | | | | | |* | | | |
|--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|
|FWC 2 | |* | | | | | |* | | | | | |* | | | | |
|--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|
|CFDIU | | | |* | | | | | |* | | | | | |* | | |
|--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|
|EEC ENG 1 | | | | |* | | | | | |* | | | | | | | |
|--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|
|EEC ENG 2 | | | | | |* | | | | | |* | | | | | | |
|--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|
|SFCC 1 | | |* | | | | | |* | | | | | | | | | |
|--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|

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 ----------------------------------------------------------------------------
| USERS | ADR 1 BUS | ADR 2 BUS | ADR 3 BUS |
| |-----------------|-----------------|-----------------|
| |1 |2 |3 |4 |5 |6 |1 |2 |3 |4 |5 |6 |1 |2 |3 |4 |5 |6 |
|--------------------------------------------------------------------------|
|SFCC 2 | |* | | | | | |* | | | | | | | | | | |
|--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|
|FAC 1 | | |* | | | | | |* | | | | | |* | | | |
|--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|
|FAC 2 | |* | | | | | |* | | | | | |* | | | | |
|--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|
|ELAC 1 | | |* | | | | | |* | | | | | |* | | | |
|--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|
|ELAC 2 | |* | | | | | |* | | | | | |* | | | | |
|--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|
|SEC 1 | | |* | | | | | | | | | | | |* | | | |
|--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|
|SEC 2 | |* | | | | | |* | | | | | | | | | | |
|--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|
|SEC 3 | | | | | | | |* | | | | | |* | | | | |
|--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|
|GPWC | | | |* | | | | | | | | | | | | | | |
|--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|
|DMU | |* | | | | | | | | | | | | | | | | |
|--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|
|CABIN PRESSURE | | |* | | | | | | |* | | | | |* | | | |
|CONTROLLER1 | | | | | | | | | | | | | | | | | | |
|--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|
|CABIN PRESSURE | | | |* | | | |* | | | | | | | |* | | |
|CONTROLLER2 | | | | | | | | | | | | | | | | | | |
|--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|
|ZONE TEMPERATURE | | | | | | | | | | | | | | | |* | | |
|CONTROLLER | | | | | | | | | | | | | | | | | | |
|--------------------|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|--|
|TEST 1 CONNECTORS | | | |* | | | | | |* | | | | | |* | | |
----------------------------------------------------------------------------

Table 11 : ADR Data Users

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R **ON A/C 001-004,

- The IR portion of the ADIRU provides four identical ARINC 429

High Speed buses. The system users are described in the table
below:

-----------------------------------------------------------------------------
| USERS | IR 1 BUS | IR 2 BUS | IR 3 BUS |
| |-------------------|-------------------|-------------------|
| | 1 | 2 | 3 | 4 | 1 | 2 | 3 | 4 | 1 | 2 | 3 | 4 |
|---------------------------------------------------------------------------|
|FAC 1 | | | * | | | | * | | | | * | |
|---------------|----|----|----|----|----|----|----|----|----|----|----|----|
|FAC 2 | | * | | | | * | | | | * | | |
|---------------|----|----|----|----|----|----|----|----|----|----|----|----|
|ELAC 1 | | | * | | | | * | | | | * | |
|---------------|----|----|----|----|----|----|----|----|----|----|----|----|
|ELAC 2 | | * | | | | * | | | | * | | |
|---------------|----|----|----|----|----|----|----|----|----|----|----|----|
|SEC 1 | | | * | | | | | | | | * | |
|---------------|----|----|----|----|----|----|----|----|----|----|----|----|
|SEC 2 | | * | | | | * | | | | | | |
|---------------|----|----|----|----|----|----|----|----|----|----|----|----|
|SEC 3 | | | | | | * | | | | * | | |
|---------------|----|----|----|----|----|----|----|----|----|----|----|----|
|DMC 1 | * | | | | | | | | | | * | |
|---------------|----|----|----|----|----|----|----|----|----|----|----|----|
|DMC 2 | | | | | | * | | | | * | | |
|---------------|----|----|----|----|----|----|----|----|----|----|----|----|
|DMC 3 | | | * | | | | * | | * | | | |
|---------------|----|----|----|----|----|----|----|----|----|----|----|----|
|CDU | | * | | | | * | | | | * | | |
|---------------|----|----|----|----|----|----|----|----|----|----|----|----|
|FMGC 1 | | | * | | | | * | | | | * | |
|---------------|----|----|----|----|----|----|----|----|----|----|----|----|
|FMGC 2 | | * | | | | * | | | | * | | |
|---------------|----|----|----|----|----|----|----|----|----|----|----|----|
|FQIC | | * | | | | * | | | | | | |
|---------------|----|----|----|----|----|----|----|----|----|----|----|----|
|BSCU | | * | | | | | * | | | * | | |
|---------------|----|----|----|----|----|----|----|----|----|----|----|----|
|CFDIU | | | * | | | | * | | | | * | |
|---------------|----|----|----|----|----|----|----|----|----|----|----|----|
|GPWC | | | * | | | | | | | | | |
|---------------|----|----|----|----|----|----|----|----|----|----|----|----|
|WR 1 | | | * | | | | | | | | * | |

R
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 -----------------------------------------------------------------------------
| USERS | IR 1 BUS | IR 2 BUS | IR 3 BUS |
| |-------------------|-------------------|-------------------|
| | 1 | 2 | 3 | 4 | 1 | 2 | 3 | 4 | 1 | 2 | 3 | 4 |
|---------------------------------------------------------------------------|
|---------------|----|----|----|----|----|----|----|----|----|----|----|----|
|TCAS | | | * | | | | | | | | | |
|---------------|----|----|----|----|----|----|----|----|----|----|----|----|
|DMU | | * | | | | | * | | | | | |
|---------------|----|----|----|----|----|----|----|----|----|----|----|----|
|RMI-VOR/DME | | * | | | | | | | | * | | |
|---------------|----|----|----|----|----|----|----|----|----|----|----|----|
|TEST PLUG | | | * | | | * | | | | | * | |
-----------------------------------------------------------------------------

Table 12 : IR Data Users - Basic version

R
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 **ON A/C ALL

R Post SB 34-1147 For A/C 001-004,

- The IR portion of the ADIRU provides four identical ARINC 429

High Speed buses. The system users are described in the table
below:

-----------------------------------------------------------------------------
| USERS | IR 1 BUS | IR 2 BUS | IR 3 BUS |
| |-------------------|-------------------|-------------------|
| | 1 | 2 | 3 | 4 | 1 | 2 | 3 | 4 | 1 | 2 | 3 | 4 |
|---------------------------------------------------------------------------|
|FAC 1 | | | * | | | | * | | | | * | |
|---------------|----|----|----|----|----|----|----|----|----|----|----|----|
|FAC 2 | | * | | | | * | | | | * | | |
|---------------|----|----|----|----|----|----|----|----|----|----|----|----|
|ELAC 1 | | | * | | | | * | | | | * | |
|---------------|----|----|----|----|----|----|----|----|----|----|----|----|
|ELAC 2 | | * | | | | * | | | | * | | |
|---------------|----|----|----|----|----|----|----|----|----|----|----|----|
|SEC 1 | | | * | | | | | | | | * | |
|---------------|----|----|----|----|----|----|----|----|----|----|----|----|
|SEC 2 | | * | | | | * | | | | | | |
|---------------|----|----|----|----|----|----|----|----|----|----|----|----|
|SEC 3 | | | | | | * | | | | * | | |
|---------------|----|----|----|----|----|----|----|----|----|----|----|----|
|DMC 1 | * | | | | | | | | | | * | |
|---------------|----|----|----|----|----|----|----|----|----|----|----|----|
|DMC 2 | | | | | | * | | | | * | | |
|---------------|----|----|----|----|----|----|----|----|----|----|----|----|
|DMC 3 | | | * | | | | * | | * | | | |
|---------------|----|----|----|----|----|----|----|----|----|----|----|----|
|CDU | | * | | | | * | | | | * | | |
|---------------|----|----|----|----|----|----|----|----|----|----|----|----|
|FMGC 1 | | | * | | | | * | | | | * | |
|---------------|----|----|----|----|----|----|----|----|----|----|----|----|
|FMGC 2 | | * | | | | * | | | | * | | |
|---------------|----|----|----|----|----|----|----|----|----|----|----|----|
|FQIC | | * | | | | * | | | | | | |
|---------------|----|----|----|----|----|----|----|----|----|----|----|----|
|BSCU | | * | | | | | * | | | * | | |
|---------------|----|----|----|----|----|----|----|----|----|----|----|----|
|CFDIU | | | * | | | | * | | | | * | |
|---------------|----|----|----|----|----|----|----|----|----|----|----|----|
|GPWC | | | * | | | | | | | | | |
|---------------|----|----|----|----|----|----|----|----|----|----|----|----|

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 -----------------------------------------------------------------------------
| USERS | IR 1 BUS | IR 2 BUS | IR 3 BUS |
| |-------------------|-------------------|-------------------|
| | 1 | 2 | 3 | 4 | 1 | 2 | 3 | 4 | 1 | 2 | 3 | 4 |
|---------------------------------------------------------------------------|
R |WR 1 | | | * | | | | | | | | * | |
R |---------------|----|----|----|----|----|----|----|----|----|----|----|----|
R |MMR 1 | | * | | | | | * | | | | * | |
R |---------------|----|----|----|----|----|----|----|----|----|----|----|----|
R |MMR 2 | | | * | | | * | | | | | * | |
R |---------------|----|----|----|----|----|----|----|----|----|----|----|----|
R |TCAS | | | * | | | | | | | | | |
R |---------------|----|----|----|----|----|----|----|----|----|----|----|----|
R |DMU | | * | | | | | * | | | | | |
R |---------------|----|----|----|----|----|----|----|----|----|----|----|----|
R |RMI-VOR/DME | | * | | | | | | | | * | | |
R |---------------|----|----|----|----|----|----|----|----|----|----|----|----|
R |TEST PLUG | | | * | | | * | | | | | * | |
R -----------------------------------------------------------------------------

R Table 12 : IR Data Users - Basic version

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R **ON A/C ALL

(e) Analog outputs

The ADIRUs, through analog outputs, supply the ADMs with
+13.5/-13.5VDC and the CDU with 28VDC.

(f) Discrete outputs

The discrete outputs are either open/ground or open/28VDC
discretes (for ON BAT, IR FAILURE WARNING and ALIGN NOT READY
discretes). The LOW SPEED WARNING discretes are set according to
a speed threshold (with an hysteresis of 4 knots). These
thresholds are respectively:

---------------------------------
|Lower threshold|Upper threshold|
| value | value |
--------------------------|---------------|---------------|
| LOW SPEED WARNING 1 | 100 | 104 |
| LOW SPEED WARNING 2 | 50 | 54 |
| LOW SPEED WARNING 3 | 155 | 159 |
| LOW SPEED WARNING 4 | 260 | 264 |
-----------------------------------------------------------

The LOW SPEED WARNING 1 discrete is used in the Ram Air Turbine
extension logic and in the power generation logic. The LOW SPEED
WARNING 2 discrete is used in the power generation logic.
The following discretes are used to control the CDU annunciators:
- ON BAT
- ADR OFF
- ADR FAILURE WARNING
- IR FAILURE WARNING
- IR ALIGN.

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 4. _____________________
Component Description

A. ADIRS CDU
(Ref. Fig. 005)
The CDU is a three-channel unit. Each CDU channel includes the following
features:
- a three-position mode selector switch. The modes are:
. power off (OFF)
. navigation (NAV)
. reversionary attitude (ATT)
- an indicator announcing when the IR is aligning (ALIGN legend of IR
annunciator)
- an IR fault indicator (FAULT legend of IR annunciator)
- a pushbutton switch to disable ADR output buses. It is a momentary
action pushbutton switch
- an indicator announcing when the ADR output buses are turned off (OFF
legend of ADR pushbutton switch)
- an ADR fault indicator (FAULT legend of ADR pushbutton switch).
The following items of equipment are shaped between the three channels :
- a keyboard to enter the initial position in degrees, minutes and tenth
of minutes or magnetic heading in the attitude mode
- two data pushbutton switches (ENT and CLR) with cue lights
- a liquid crystal display for selected parameters. The LCD has 16 digits
and each digit has 14 segments
- a DATA DISPLAY selector switch to select parameters for display on the
LCD:
* wind (WIND)
* present position (PPOS)
* true heading (HDG)
* status of selected system (STS)
* track and ground speed (TK/GS)
* test values (TEST)
- a SYS DISPLAY selector switch with four positions: OFF, 1, 2, 3. The
OFF position disables the display of the CDU but the mode control of
the ADIRUs remains active
- an ON BAT annunciator.
The CDU contains three identical connectors referenced J1, J2 and J3.
(Ref. Fig. 006)
This LRU uses an Intel 8031 microprocessor. The CDU receives an IR bus
from each ADIRU to display navigation data.
It provides one bus per ADIRU to permit IR initialization.
(Ref. Fig. 007)
No cooling air is provided to the CDU.
The CDU is supplied with 28VDC from the selected ADIRU to drive internal
circuits and the data display. The 28VDC inputs are isolated from each
other. The aircraft supplies 5VAC power for panel lighting/LCD
backlighting and for annunciator lighting.

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 ADIRS CDU
Figure 005

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 ADIRS CDU - Identical Connectors
Figure 006

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 ADIRS CDU - Internal Block Diagram
Figure 007

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 B. ADIRU
(Ref. Fig. 008)

(1) General
The ADIRU is contained in a 4 MCU case as defined in ARINC 600. The
ADIRU has to be aligned on a special shelf in the avionics
compartment in accordance with the installation design described in
ARINC 738. This installation involves modification of the ARINC 600
standard to include three alignment pins and a floating connector.
Pins 12 and 13 of the bottom plug have been modified with a reducer
to accept power input instead of coax input as defined in ARINC 738.
All input discretes are electrically isolated by an in-line diode or
an equivalent device. The discrete outputs are protected by means of
diodes to permit a wired OR circuit with other outputs.
The ADIRU is designed to reach a high level of protection for
lightning and Electromagnetic Interference (EMI). The lightning
protection circuitry is made up of discrete components which consist
of high-powered Zener diode type semiconductors called Transzorbs.
Varistors are used on the power supply input lines. Varistors are
voltage-controlled resistors that go to a low impedance state when a
voltage above their clamp voltage is applied, thus shunting the
lightning current.
As each ADIRU is a common point to all engines installed on the
aircraft, special care is taken to make impossible any electrical
disturbance to propagate through the ADIRU/engine interface to other
inputs/outputs dedicated to engines.
The ADIRU contains an ADR and an IR portion supplied by a common
power (115VAC, 28VDC).

(2) ADR portion

(Ref. Fig. 009)
This portion uses a 68000 microprocessor. Five resolvers can be used
for the analog baro-correction and the AOA inputs. The ADR provides
eight ARINC 429 Low-Speed output buses (buses 5 to 8 are reserved for
engine control).
A bus isolation is provided using in-line fuses in all ADR buses 5-8
reserved to the engine control.
Each bus can drive twenty ARINC bus loads.

(3) IR portion
(Ref. Fig. 009)
This portion uses a 80960 microprocessor.
It provides a high-voltage power supply used by the gyros.
The gyros/accel sensors block contains three accels and three gyros
mounted along each axis.
The IR provides four ARINC 429 High-Speed output buses. Each bus can
drive twenty loads.

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 ADIRS - General View
Figure 008

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 ADIRU - Block Diagram
Figure 009

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 CONTROL AND DISPLAY UNIT (CDU) - ADIRS (2FP) - REMOVAL/INSTALLATION
___________________________________________________________________

TASK 34-12-12-000-001

Removal of the ADIRS CDU (2FP)

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific blanking caps

No specific circuit breaker(s) safety clip(s)
No specific access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

34-12-12-991-001 Fig. 401

3. __________
Job Set-up

Subtask 34-12-12-010-050

A. Get Access

(1) Put the access platform in position at the access door 822.

(2) Open the access door 822.

(3) On the battery power center 105 VU:

- loosen the two screws and remove the protective cover.

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 Subtask 34-12-12-865-050

B. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06
105VU ADIRS/ADIRU1/28VDC 6FP1 C02

R **ON A/C 001-004,

121VU ADIRS/ADIRU/2/115VAC 4FP2 N07

121VU ADIRS/ADIRU/3/115VAC 4FP3 N06
121VU ADIRS/ADIRU/2/28VDC 6FP2 N05
121VU ADIRS/ADIRU/3/28VDC 6FP3 N04

R **ON A/C 005-099,

R 121VU ADIRS/ADIRU/2/115VAC 4FP2 N06

R 121VU ADIRS/ADIRU/3/115VAC 4FP3 N05
R 121VU ADIRS/ADIRU/2/28VDC 6FP2 N04
R 121VU ADIRS/ADIRU/3/28VDC 6FP3 N03

R **ON A/C ALL

122VU LIGHTING/TST/BOARD/SPLY 30LP X06

122VU LIGHTING/ANN LT SPLY/XFMR/BUS 2 27LP X05
122VU LIGHTING/ANN LT SPLY/XFMR/BUS 1 26LP X04
122VU LIGHTING/INSTL LT/OVHD/PNL 3LF Y03

4. Procedure
_________

(Ref. Fig. 401/TASK 34-12-12-991-001)

Subtask 34-12-12-020-050

A. Removal of the ADIRS CDU (2FP)

(1) Hold the CDU (4) and loosen the four quarter turn fasteners (5).

(2) Disengage the CDU (4) from its housing (1).

(3) Disconnect the three electrical connectors (2).

(4) Remove the CDU (4).

(5) Put blanking caps on the disconnected electrical connectors (2) and
(3).

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 ADIRS - Control and Display Unit (CDU)
Figure 401/TASK 34-12-12-991-001

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 TASK 34-12-12-400-001

Installation of the ADIRS CDU (2FP)

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific access platform

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

34-10-00-710-001 Check of the ADIRS CDU Brightness and Display

34-12-12-991-001 Fig. 401

3. __________
Job Set-up

Subtask 34-12-12-010-051

A. Get Access

(1) Make sure that the access platform is in position at the access door
822.

(2) Make sure that the access door 822 is open.

(3) Make sure that the protective cover is removed from the battery power
center 105VU.

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 Subtask 34-12-12-865-051

B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and
tagged

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06
105VU ADIRS/ADIRU1/28VDC 6FP1 C02

R **ON A/C 001-004,

121VU ADIRS/ADIRU/2/115VAC 4FP2 N07

121VU ADIRS/ADIRU/3/115VAC 4FP3 N06
121VU ADIRS/ADIRU/2/28VDC 6FP2 N05
121VU ADIRS/ADIRU/3/28VDC 6FP3 N04

R **ON A/C 005-099,

R 121VU ADIRS/ADIRU/2/115VAC 4FP2 N06

R 121VU ADIRS/ADIRU/3/115VAC 4FP3 N05
R 121VU ADIRS/ADIRU/2/28VDC 6FP2 N04
R 121VU ADIRS/ADIRU/3/28VDC 6FP3 N03

R **ON A/C ALL

122VU LIGHTING/TST/BOARD/SPLY 30LP X06

122VU LIGHTING/ANN LT SPLY/XFMR/BUS 2 27LP X05
122VU LIGHTING/ANN LT SPLY/XFMR/BUS 1 26LP X04
122VU LIGHTING/INSTL LT/OVHD/PNL 3LF Y03

4. Procedure
_________

(Ref. Fig. 401/TASK 34-12-12-991-001)

Subtask 34-12-12-420-050

A. Installation of the ADIRS CDU (2FP)

(1) Clean the component interface and/or the adjacent area.

(2) Do an inspection of the component interface and/or the adjacent area.

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 (3) Remove the blanking caps from the electrical connectors (2) and (3).

(4) Make sure that the electrical connectors are clean and in the correct
condition.

(5) Connect the electrical connectors (2) to the related receptacles (3).

(6) Install the CDU (4) in its housing (1).

(7) Tighten the four quarter turn fasteners (5).

Subtask 34-12-12-865-052

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
4FP1, 4FP2, 4FP3, 6FP1, 6FP2, 6FP3, 3LF, 26LP, 27LP, 30LP

Subtask 34-12-12-710-050

C. Do the test of the ADIRS CDU brightness and display.

(Ref. TASK 34-10-00-710-001)

5. Close-up
________

Subtask 34-12-12-860-050

A. Make sure that the work area is clean and clear of tool(s) and other
items.

Subtask 34-12-12-410-050

B. Close Access

(1) Install the protective cover on the battery power center 105VU.

(2) Tighten the two screws.

(3) Close the access door 822

(4) Remove the access platform(s).

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 ___________________________________________________________
REFERENCE UNIT - AIR DATA/INERTIAL (ADIRU) (1FP1,1FP2,1FP3)
____________________
REMOVAL/INSTALLATION

TASK 34-12-34-000-001

Removal of the ADIRU (1FP1, 1FP2, 1FP3)

CAUTION : DO NOT REMOVE THE RACK OF THIS UNIT.

_______
PRECISION ADJUSTMENT IS NECESSARY TO INSTALL THE RACK CORRECTLY. THE
MANUFACTURER DOES THIS ADJUSTMENT BEFORE DELIVERY OF THE AIRCRAFT.

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific circuit breaker(s) safety clip(s)

No specific access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

34-12-34-991-002 Fig. 401

3. __________
Job Set-up

Subtask 34-12-34-010-050

A. Get Access

(1) Put the access platform in position at the access door 822

(2) Open the access door 822.

(3) On the battery power center 105VU:

- loosen the two screws and remove the protective cover.

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 (4) Put the access platform in position in the zone 128 at the acces door
824

(5) Open the access door 824

Subtask 34-12-34-865-050

B. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
FOR 1FP1
49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07
49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06
105VU ADIRS/ADIRU1/28VDC 6FP1 C02
FOR 1FP2

R **ON A/C 001-004,

121VU ADIRS/ADIRU/2PWR/SHED 10FP N11

121VU ADIRS/ADIRU/2/26VAC AND AOA 5FP2 N09
121VU ADIRS/ADIRU/2/115VAC 4FP2 N07
121VU ADIRS/ADIRU/2/28VDC 6FP2 N05

R **ON A/C 005-099,

R 121VU ADIRS/ADIRU/2PWR/SHED 10FP N10

R 121VU ADIRS/ADIRU/2/26VAC AND AOA 5FP2 N08
R 121VU ADIRS/ADIRU/2/115VAC 4FP2 N06
R 121VU ADIRS/ADIRU/2/28VDC 6FP2 N04

R **ON A/C ALL

FOR 1FP3
49VU NAV PROBES/ADIRU3/PWR/SWTG 8FP F09

R **ON A/C 001-004,

121VU ADIRS/ADIRU/3PWR/SWTG 9FP N10

121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N08
121VU ADIRS/ADIRU/3/115VAC 4FP3 N06
121VU ADIRS/ADIRU/3/28VDC 6FP3 N04

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 -------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
R **ON A/C 005-099,

R 121VU ADIRS/ADIRU/3PWR/SWTG 9FP N09

R 121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N07
R 121VU ADIRS/ADIRU/3/115VAC 4FP3 N05
R 121VU ADIRS/ADIRU/3/28VDC 6FP3 N03

R **ON A/C ALL

4. Procedure
_________

(Ref. Fig. 401/TASK 34-12-34-991-002)

Subtask 34-12-34-020-050

A. Removal of the ADIRU (1FP1, 1FP2, 1FP3)

NOTE : The procedure is the same for the three ADIRUs 1FP1, 1FP2 and
____
1FP3.

(1) Loosen the nuts (4).

(2) Lower the nuts (4).

(3) Pull the ADIRU (6) on its rack (3) to disconnected the electrical
connectors (1).

(4) Remove the ADIRU (6) from its rack (3).

(5) Put blanking caps on the disconnected electrical connectors (1).

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 Air Data/Inertial Reference Unit (ADIRU)
Figure 401/TASK 34-12-34-991-002

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 TASK 34-12-34-400-001

Installation of the ADIRU (1FP1, 1FP2, 1FP3)

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

22-97-00-710-001 Operational Test of the LAND CAT III Capability

34-13-00-740-002 INTERFACE TEST of the ADR
34-14-00-740-001 Interface Test of the IR
R 52-41-00-410-002 Close the Avionics Compartment Doors after Access
34-12-34-991-002 Fig. 401

3. __________
Job Set-up

Subtask 34-12-34-860-050

A. Aircraft Maintenance Configuration

(1) Make sure that the access platform is in position at the access door
824.

(2) Make sure that the access door 824 is open.

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 Subtask 34-12-34-010-051

B. Get Access

(1) Make sure that the access platform is in position at the access door
822.

(2) Make sure that the access door is open.

(3) Make sure that the protective cover is removed from the battery power
center 105VU.

Subtask 34-12-34-865-051

C. Make sure that this(these) circuit breaker(s) is(are) open, safetied and
tagged

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
FOR 1FP1
49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07
49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06
105VU ADIRS/ADIRU1/28VDC 6FP1 C02
FOR 1FP2

R **ON A/C 001-004,

121VU ADIRS/ADIRU/2PWR/SHED 10FP N11

121VU ADIRS/ADIRU/2/26VAC AND AOA 5FP2 N09
121VU ADIRS/ADIRU/2/115VAC 4FP2 N07
121VU ADIRS/ADIRU/2/28VDC 6FP2 N05

R **ON A/C 005-099,

R 121VU ADIRS/ADIRU/2PWR/SHED 10FP N10

R 121VU ADIRS/ADIRU/2/26VAC AND AOA 5FP2 N08
R 121VU ADIRS/ADIRU/2/115VAC 4FP2 N06
R 121VU ADIRS/ADIRU/2/28VDC 6FP2 N04

R **ON A/C ALL

FOR 1FP3
49VU NAV PROBES/ADIRU3/PWR/SWTG 8FP F09

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 -------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
R **ON A/C 001-004,

121VU ADIRS/ADIRU/3PWR/SWTG 9FP N10

121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N08
121VU ADIRS/ADIRU/3/115VAC 4FP3 N06
121VU ADIRS/ADIRU/3/28VDC 6FP3 N04

R **ON A/C 005-099,

R 121VU ADIRS/ADIRU/3PWR/SWTG 9FP N09

R 121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N07
R 121VU ADIRS/ADIRU/3/115VAC 4FP3 N05
R 121VU ADIRS/ADIRU/3/28VDC 6FP3 N03

R **ON A/C ALL

4. Procedure
_________

(Ref. Fig. 401/TASK 34-12-34-991-002)

Subtask 34-12-34-420-050

A. Installation of the ADIRU (1FP1, 1FP2, 1FP3)

(1) Clean the component interface and/or the adjacent area.

(2) Do an inspection of the component interface and/or the adjacent area.

(3) Remove the blanking caps from the electrical connectors (1).

(4) Make sure that the electrical connectors (1) are clean and in the
correct condition.

(5) Push the ADIRU (6) on its rack (3) to connect the electrical
connectors (1).

NOTE : Make sure that the ADIRU (6) correctly engages in the
____
centering pins (2).

(6) Engage the nuts (4) on the lugs (5) and tighten.

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 Subtask 34-12-34-865-052

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
FOR 1FP1
4FP1, 5FP1, 6FP1
FOR 1FP2
4FP2, 5FP2, 6FP2, 10FP
FOR 1FP3
4FP3, 5FP3, 6FP3, 8FP, 9FP

Subtask 34-12-34-740-050

C. BITE Test

(1) Do the BITE Test of the ADIRS (Ref. TASK 34-13-00-740-002) (Ref. TASK
34-14-00-740-001).

NOTE : If the airline operates the aircraft in CAT 3 conditions, do

____
the LAND CAT III capability test
(Ref. TASK 22-97-00-710-001).

(2) As an alternative procedure, you can do an operational test without

the CFDS (installed ADIRU only)

5. Close-up
________

Subtask 34-12-34-860-051

A. Put the aircraft back to its initial configuration.

(1) On the overhead panel 23VU, release and push the FLT CTL/ELAC1 and
FLT CTL/SEC1 pushbutton switches (the OFF legend comes on and goes
off).

(2) On the overhead panel 24VU, release and push the FLT CTL/ELAC2, FLT
CTL/SEC2 and FLT CTL/SEC3 pushbutton switches (the OFF legend comes
on and goes off).

(3) Make sure that the work area is clean and clear of tool(s) and other
items.

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 Subtask 34-12-34-410-050

B. Close Access

R (1) Close the access door 824 (Ref. TASK 52-41-00-410-002).

(2) Install the protective cover on the battery power center 105VU.

(3) Tighten the two screws.

(4) Close the access door 822.

(5) Remove the access platform(s).

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 MOUNT - ADIRU - REMOVAL/INSTALLATION
____________________________________

TASK 34-12-51-000-001

Removal of the ADIRU Mount

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific blanking caps

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

08-22-00-200-001 Precise Leveling

21-26-41-000-001 Removal of the Check Valve (2140HM)
21-26-42-000-001 Removal of the Avionics Equipment Ventilation Duct
21-26-43-000-002 Removal of the Filter Assembly (2081HM,2082HM,2083HM)
21-27-42-000-001 Removal of the Avionics Equipment Ground Cooling Duct
34-12-34-000-001 Removal of the ADIRU (1FP1, 1FP2, 1FP3)
34-12-51-991-001 Fig. 401

3. __________
Job Set-up

Subtask 34-12-51-210-050

A. Do the aircraft precise leveling (Ref. TASK 08-22-00-200-001) to put the

aircraft in position to have a 0 degree pitch, 0 degree roll. Use the
standard reference marks of the aircraft (tolerance +/- 5 minutes).

NOTE : You must keep the aircraft in this position during the removal and
____
installation procedures.

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 Subtask 34-12-51-020-050

B. Remove the ADIRUs 1FP1, 1FP2 and 1FP3 (Ref. TASK 34-12-34-000-001).

4. Procedure
_________

Subtask 34-12-51-020-051

A. Removal of the ADIRU Mount

(Ref. Fig. 401/TASK 34-12-51-991-001)

(1) Remove the nuts (4), the washers (8) and the screws (7) which attach
the bonding leads (5) to the mount (13).

(2) Remove the nuts (14) from the screws (11).

(3) Remove the electrical connectors (12) from the mount (13). Use some
straps to attach the electrical connectors (12).

(4) Put blanking caps on the disconnected electrical connectors.

(5) Remove the nuts (1), the washers (2) and the screws (6).

(6) Lift the mount (13) off its support. Be careful not to cause damage
to the peel shims (3) and the air conditioning pipe (9).

(7) Put marks on the peel shims (3) with a felt-tip pen or equivalent, to
make sure that you put them back in their initial positions when you
install the mount (13).

(8) Remove the nuts (10).

(9) Remove the air conditioning pipe (9).

(10) Remove the mount (13).

Subtask 34-12-51-020-052

B. Removal of the Air Conditioning Pipes

(1) Remove the check valve (2140HM) (Ref. TASK 21-26-41-000-001).

(2) Remove the filter assembly (2081HM, 2082HM, 2083HM) (Ref. TASK 21-26-
43-000-002).

(3) Remove the avionics-equipment ground cooling-duct (Ref. TASK 21-27-

42-000-001).

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 ADIRU Mount
Figure 401/TASK 34-12-51-991-001

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 (4) Remove the avionics equipment ventilation-duct (Ref. TASK 21-26-42-
000-001).

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 TASK 34-12-51-400-001

Installation of the ADIRU Mount

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific access platform 1.8 m (5 ft. 11 in.)

3028000 1 CLINOMETER
R 98D34103000000 1 INSTALLATION PLATFORM - IRU BRACKETS
98D34203000000 1 ALIGNMENT TOOL - MOUNT, ADIRU

B. Expendable Parts

-------------------------------------------------------------------------------
FIG.ITEM |DESIGNATION |IPC-CSN
-------------------------------------------------------------------------------

5 cotter pins 32-21-01 01 -010

7 packings 32-21-01 01 -075

C. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

07-11-00-586-002 Lowering of the Aircraft for Maintenance Operations

08-22-00-200-001 Precise Leveling
21-26-41-400-001 Installation of the Check Valve (2140HM)
21-26-42-400-001 Installation of the Avionics Equipment Ventilation
Duct
21-26-43-400-002 Installation of the Filter Assembly
(2081HM,2082HM,2083HM)
21-27-42-400-002 Installation of the Avionics Equipment Ground Cooling
Duct
34-12-34-400-001 Installation of the ADIRU (1FP1, 1FP2, 1FP3)
34-12-51-991-001 Fig. 401

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 -------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

34-12-51-991-002 Fig. 402

34-12-51-991-003 Fig. 403

3. __________
Job Set-up

Subtask 34-12-51-210-051

A. Make sure that the aircraft is in precise leveling (Ref. TASK 08-22-00-
200-001). Do this procedure to put the aircraft in position to have a 0
degree pitch and a 0 degree roll. Use the standard reference marks of the
aircraft (tolerance +/- 5 minutes).

Subtask 34-12-51-010-050

B. Get Access

(1) Make sure that the access platform is in position in the zone 126 at
the access door 822.

(2) Make sure that the access door 822 is open.

(3) Make sure that the two screws and the protective cover are removed
from the battery power center 105VU.

(4) Make sure that the access platform is in position in the zone 128 at
the access door 824.

(5) Make sure that the access door 824 is open.

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 Subtask 34-12-51-865-050

C. Make sure that this(these) circuit breaker(s) is(are) open, safetied and
tagged

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV PROBES/ADIRU3/PWR/SWTG 8FP F09
49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07
49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06
105VU ADIRS/ADIRU1/28VDC 6FP1 C02

**ON A/C 001-004,

121VU ADIRS/ADIRU/2PWR/SHED 10FP N11

121VU ADIRS/ADIRU/3PWR/SWTG 9FP N10
121VU ADIRS/ADIRU/2/26VAC AND AOA 5FP2 N09
121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N08
121VU ADIRS/ADIRU/2/115VAC 4FP2 N07
121VU ADIRS/ADIRU/3/115VAC 4FP3 N06
121VU ADIRS/ADIRU/2/28VDC 6FP2 N05
121VU ADIRS/ADIRU/3/28VDC 6FP3 N04

**ON A/C 005-099,

121VU ADIRS/ADIRU/2PWR/SHED 10FP N10

121VU ADIRS/ADIRU/3PWR/SWTG 9FP N09
121VU ADIRS/ADIRU/2/26VAC AND AOA 5FP2 N08
121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N07
121VU ADIRS/ADIRU/2/115VAC 4FP2 N06
121VU ADIRS/ADIRU/3/115VAC 4FP3 N05
121VU ADIRS/ADIRU/2/28VDC 6FP2 N04
121VU ADIRS/ADIRU/3/28VDC 6FP3 N03

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 **ON A/C ALL

4. Procedure
_________

Subtask 34-12-51-210-052

A. Heading Check

CAUTION : IF YOU MUST MOVE THE TOOL IN THE AIRCRAFT, BE CAREFUL NOT TO
_______
DAMAGE THE PEEL SHIMS OF THE SUPPORTS OF THE ADIRU MOUNT.

NOTE : Assemble the tool in the aircraft avionics compartment. The

____
assembled tool is too large to go through the access door of the
zone.

(Ref. Fig. 402/TASK 34-12-51-991-002)

(1) Installation of the ALIGNMENT TOOL - MOUNT, ADIRU (98D34203000000)

(a) Remove and discard the cotter pins (5).

(b) Remove the nuts (4) and the washers (3).

(c) Remove the flanges (6) from the pintles (1) of the nose gear.

(d) Remove and discard the packings (7) and (2).

(e) Install the support shafts (8) on the pintles (1) of the nose
gear.

(f) Install the washers (3) and the nuts (4).

(g) Install the new cotter pins (5).

(h) Assemble the three parts of the tool (11) with the bolts (9).

NOTE : The left and right parts of the tool are not
____
interchangeable. Make sure that they are installed on the
correct side.

(i) Install the tool (11) on the support shafts (8). To do this:
- tilt the top of the tool (11) forward to engage it on the
support shafts (8).
- let the tool (11) turn down until it touches the surfaces of
the ADIRU mount support.

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 Alignment Tool
Figure 402/TASK 34-12-51-991-002

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 (j) Install the shim (13) between the tool (11) and the right support
shaft (8) to prevent movement in the Y-axis (Roll) direction.

(k) Install and tighten the knurled nuts (12) on each support shaft
(8).

(2) Heading Check

R (a) Manually push the four pins (10) into the inspection bushes of
R the tool (11). The pins (10) must go easily in the attachment
R holes of the ADIRU mount support.

R NOTE : If it is not easy manually to push the four pins (10) into
____
R the attachment holes for the ADIRU mount support, there is
R a heading angle mismatch.
You must get more information from the Airbus Customer
Service.

(3) Removal of the ALIGNMENT TOOL - MOUNT, ADIRU (98D34203000000)

(a) Remove the four pins (10).

(b) Remove the knurled nuts (12).

(c) Remove the tool (11) and the shim (13) from the support shafts
(8).

(d) Remove the bolts (9) and disassemble the three parts of the tool
(11).

(e) Remove and discard the cotter pins (5).

(f) Remove the nuts (4) and the washers (3).

(g) Remove the support shafts (8) from the pintles (1) of the nose
gear.

(h) Install the new packings (7) (7) and (2) and the flanges (6) on
the pintles (1) of the nose gear.

(i) Install the washers (3) and the nuts (4).

(j) TORQUE the nuts (4) to between 1.2 and 1.35 m.daN (106.19 and
119.46 Ibf.in).

(k) Install the new cotter pins (5).

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 Subtask 34-12-51-210-053

B. Flatness Check
(Ref. Fig. 403/TASK 34-12-51-991-003)

(1) If necessary, replace the damaged peel shims (2) . Carefully clean
the sealing bearing on the support surfaces of the ADIRU mount.
Remove the unwanted thickness from the peel shims (2).

R (2) Put the INSTALLATION PLATFORM - IRU BRACKETS (98D34103000000) (1) in

position on the three peel shims (2) with the right angle of the tool
(1) at position 2.

(3) Put a CLINOMETER (3028000) on the two perpendicular arms of the tool
(1).

(4) Adjust the assembly until it is horizontal. To do this, remove the

unwanted thickness from the peel shims (2).
Tolerance for X (pitch)= +/-5<30W (+/-0.09⁰).
Tolerance for Y (roll)= +/-3<.30W (+/-0.06⁰).

(5) Turn the tool (1) 180 degrees until its right angle is at position 4.

(6) Adjust the assembly until it is horizontal. To do this, remove the

unwanted thickness from the peel shims (2).

(7) Do a check to make sure that all the assembly is horizontal. If not,
go back to step (2).

(8) Remove the CLINOMETER (3028000) and the tool (1).

Subtask 34-12-51-420-050

C. Installation of the Air Conditioning Pipes

(1) Install the avionics equipment ventilation-duct (Ref. TASK 21-26-42-

400-001).

(2) Install the avionics-equipment ground cooling-duct (Ref. TASK 21-27-

42-400-002).

(3) Install the filter assembly (2081HM, 2082HM, 2083HM) (Ref. TASK 21-
26-43-400-002).

(4) Install the check valve (2140HM) (Ref. TASK 21-26-41-400-001).

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R Installation Platform - IRU Brackets
Figure 403/TASK 34-12-51-991-003

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 Subtask 34-12-51-420-051

D. Installation of the ADIRU Mount

(Ref. Fig. 401/TASK 34-12-51-991-001)

(1) Install the air conditioning pipe (9).

(2) Install the nuts (10).

(3) Remove the blanking caps from the electrical connectors.

(4) Install the electrical connectors (12) on the mount (13).

(5) Install the nuts (14).

(6) Install the mount (13) on the peel shims (3). Be careful not to cause
damage to the peel shims (3).

(7) Install the screws (6), the washers (2) and the nuts (1).

(8) Install the bonding leads (5), the screws (7) and the washers (8).

(9) Install the nuts (4).

5. Close-up
________

Subtask 34-12-51-420-052

A. Put the aircraft back to its initial configuration.

(1) Make sure that the work area is clean and clear of tool(s) and other
items.

(2) Install the ADIRUs 1FP1, 1FP2 and 1FP3 (Ref. TASK 34-12-34-400-001).

(3) Lower the aircraft (Ref. TASK 07-11-00-586-002).

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 AIR DATA - DESCRIPTION AND OPERATION
____________________________________

1. _______
General
The Air Data Reference (ADR) portion of the Air Data/Inertial Reference Unit
(ADIRU) provides main data sources which are air data references for the
aircraft avionics systems.
The ADR receives and processes the outputs of the Air Data Modules (ADM) and
other sensors (Ref. 34-11-00). It computes the aerodynamic parameters in the
form of ARINC 429 low speed buses.
For more details concerning the user systems, ref. 34-12-00.

2. __________________
System Description

A. ADR Operation

(1) General
The ADR software performs five basic computational elements which are
under the air data calculations as follows:
- pressure altitude functions (ALT/ALT rate)
- Mach calculation (M)
- airspeed calculation (CAS/TAS)
- temperature calculation (SAT/TAT)
- output signal processing.
Aircraft-dependent calculations are also included in the operational
software:
- static source error correction
- angle of attack (AOA)
- maximum operating speed (MMO/VMO).
The system tests include continuous in-flight monitoring and
manually-activated test modes. The in-flight monitoring includes test
of:
- input signal integrity
- input interface integrity
- memory integrity
- computational integrity
- output signal integrity.
The continuous monitoring detects and annunciates faults in the ADR
during normal operation.
Faults are stored in BITE history in Non Volatile Memory (NVM) and
sent to the Centralized Fault Display System (CFDS) via digital
words.

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 (2) Inputs

(a) Digital inputs

1
_ Air Data Modules (ADM) inputs
The ADR receives three input bus from its corresponding ADM.
These buses transmit the following input data words depending
on the ADM installation:
Label 242 : Total Pressure
Label 176 : Left Static Pressure
Label 177 : Right Static Pressure
Label 245 : Averaged Static Pressure
Each of these words is a 32-bit word with the following
format:

----------------------------------------------------------
| BIT POSITION | DATA |
----------------------------------------------------------
| 1 - 8 | Label |
| 9 - 10 | SDI |
| 11 - 28 | Pressure Value |
| 29 | Sign bit (0 = positive) |
| 30 - 31 | Status matrix |
| 32 | Parity bit |
----------------------------------------------------------
ADM Input Label

These data words are output on all eight Air Data output data
buses and used for calculation of corrected pressure data.

2
_ Flight Control Unit (FCU) inputs
The ADR receives one input bus from the FCU, for digital baro
corrections.
The FCU output bus sends:
BCD label 234 Baro Correction 1(hPa) for CAPT side
BCD label 236 Baro Correction 2(hPa) for F/O side.
Each ADR receives the two FCU output bus according to the
discrete selection as explained in Para. 2.A.(2)(c) (discrete
inputs).
Each of these words is a 32-bit BCD word with the following
format:

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 -----------------------------------------------------------
| BIT POSITION | DATA |
-----------------------------------------------------------
| 1 - 8 | Label |
| 9 - 10 | SDI |
| 11 - 28 | Value |
| 29 | Sign bit |
| 30 - 31 | Status matrix |
| 32 | Parity |
-----------------------------------------------------------
FCU Input Label

3
_ Centralized Fault Display Interface Unit (CFDIU) input
For maintenance purposes, the ADR receives one input bus from
the CFDIU.
For more details, ref. 34-18-00.

4
_ Air Data Reference (ADR) input
Each ADR receives two intercommunication buses from the other
ADRs for cross channel comparison purpose.

(b) Analog inputs

1
_ Total Air Temperature (TAT) input
The ADR measures the resistance of the sensing element of the
TAT sensor (Ref. 34-11-00).
The ADR subtracts a fixed value (1.04 ohm) from the measured
input resistance to compensate for aircraft wiring resistance.

2
_ Angle of Attack (AOA) inputs
(Ref. Fig. 001)
The ADR receives two resolver inputs for angle of attack
computation.
The following requirements apply to the analog resolver
inputs:
- load: 15 kilohms minimum
- reference: 26V, 400 Hz (same as AOA)
- transformer ratio: 0.415 nominal plus or minus 10 %
- phase shift: 8.8 to 30 deg. leading
- source impedance:
Zro = A + jB A less than 315, B less than 725
Zso = C + jD C less than 150, D less than 165
- voltage range: 23 to 31.7 VRMS
- peak factor: 1.31 to 1.51
- electrical range input: plus or minus 60 deg.

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 AOA/ADR Wiring
Figure 001

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 3
_ Analog baro correction inputs
The ADR receives three resolver inputs for analog baro
correction (from the altimeter for example).
These inputs are not used.

(c) Discrete inputs

For pin assignment, Ref. 34-12-00.
The ADR is provided with the following input discretes:

----------------------------------------------------------------
| INPUT SIGNAL | INPUT | INPUT DEFINITION |
----------------------------------------------------------------
| ADR ARINC Filter Select | Open/GND | Type A/Type B |
R | CFDS Message Select | Open/GND | Active/Not Active |
| SDI LSB (Middle Insert) | Open/GND | 0/1 |
| SDI MSB (Middle Insert) | Open/GND | 0/1 |
| Pitot Probe Ht Disc | Open/GND | No Fault/Fault |
| Right Static Ht Disc | Open/GND | No Fault/Fault |
| Left Static Ht Disc | Open/GND | No Fault/Fault |
| TAT Ht Disc | Open/GND | Off/On |
| AOA 1 Ht Disc | Open/GND | No Fault/Fault |
| AOA Average/Unique | Open/GND | Average/Unique |
| VMO/MMO Disc 1 | Open/GND | No/Yes |
| VMO/MMO Disc 2 | Open/GND | No/Yes |
| VMO/MMO Disc 3 | Open/GND | No/Yes |
| VMO/MMO Disc 4 | Open/GND | No/Yes |
| SSEC Alternate Disc A | Open/GND | No/Yes |
| SSEC Alternate Disc B | Open/GND | N0/Yes |
| AOA Alternate Disc 1A | Open/GND | Off/On |
| AOA Alternate Disc 1B | Open/GND | Off/On |
| AOA Alternate Disc 2A | Open/GND | Off/On |
| AOA Alternate Disc 2B | Open/GND | Off/On |
| Baro Port WAW | Open/GND | Port B/Port A |
| Zero MACH SSEC | Open/GND | Use SSEC/Ignore SSEC |
| Zero AOA SSEC | Open/GND | Use SSEC/Ignore SSEC |
| AIR FRM ID Code 1/0 |Open/A.I.Com | No/Yes |
| AIR FRM ID Code 2/0 |Open/A.I.Com | No/Yes |
| AIR FRM ID Code 4/0 |Open/A.I.Com | No/Yes |
| AIR FRM ID Code 8/0 |Open/A.I.Com | No/Yes |
| AIR FRM ID Code 16/0 |Open/A.I.Com | No/Yes |
| AIR FRM ID Code Parity |Open/A.I.Com | No/Yes |
| ADR Remote Test | Open/GND | No Test/Test |
| ADR OFF DISCR Input | Open/GND | Released/Pressed |
| Dual Baro | Open/GND | Sgl Port/Dual Port |
| Baro Analog/Digital Sel.| Open/GND | Digital/Analog |
| Baro Corr. 3 Active | Open/GND | Not Active/Active |
----------------------------------------------------------------

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 ----------------------------------------------------------------
| INPUT SIGNAL | INPUT | INPUT DEFINITION |
----------------------------------------------------------------
Discrete Input Signal

NOTE : WOpenW means either a high logic voltage level or the

____
Wbinary zeroW state.
WGNDW means either a low logic voltage level or the
Wbinary oneW state.
WA.I. ComW means grounded to the WAircraft Ident CommonW
pin through a resistance of 10 ohms or less.
For program pin inputs other than Aircraft I.D., WGNDW
means grounded to the WProgram Pin CommonW pin through a
resistance of 10 ohms or less.

1
_ ADR ARINC Filter Select discrete
This discrete is used to select the characteristics of the ADR
output filter.
Two sets of characteristics are available:
Open/Ground = Type A/Type B
The A/C is defined with the ADR ARINC filter select discrete
open.

--------------------------------------------------------------
| | | TYPE A | TYPE B |
| OCTAL | | MAXIMUM | MAXIMUM |
| LABEL | SIGNAL | 3db FILTER | 3db FILTER |
| | | BANDWIDTH | BANDWIDTH |
| | | (HZ)(1) | (HZ) |
--------------------------------------------------------------
| 203 |Altitude | 8 | 3 |
| 204 |Baro Cor. Alt. 1 | 8 | 3 |
| 205 |Mach | 8 | 3 |
| 206 |Computed Airspeed | 8 | 3 |
| 207 |Max Allow. Airspeed | 8 | 8 |
| 210 |True Airspeed | 8 | 3 |
| 211 |Total Air Temp | 4 | 3 |
| 212 |Altitude Rate | 1.8 | 1.8 |
| 213 |Static Air Temp | 4 | 3 |
| 215 |Impact Pressure | 8 | 3 |
| 220 |Baro Cor. Alt. 2 | 8 | 3 |
| 221 |Ind. Angle of Attack | 8 | 3 |
| 241 |Cor. Angle of Attack | 8 | 3 |
| 242 |Total Pressure | N/A (2) | N/A (2) |
| 176 |Left Static Pressure | N/A (2) | N/A (2) |
| 177 |Right Static Pressure | N/A (2) | N/A (2) |
| 245 |Uncorr Avg Static Pressure| N/A (2) | N/A (2) |

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 --------------------------------------------------------------
| | | TYPE A | TYPE B |
| OCTAL | | MAXIMUM | MAXIMUM |
| LABEL | SIGNAL | 3db FILTER | 3db FILTER |
| | | BANDWIDTH | BANDWIDTH |
| | | (HZ)(1) | (HZ) |
--------------------------------------------------------------
| 246 |Corr Avg Static Pressure | N/A (2) | N/A (2) |
| 251 |Baro Cor. Alt. 3 | 8 | 3 |
--------------------------------------------------------------
ADR Output Filter Characteristics

NOTE : (1) Filters present only as provisions, except for

____
Altitude Rate.
(2) Filtering of pressure data is performed by the ADM.

R 2
_ CFDS Message Select discrete
R
When open, this discrete is used to select and display fault
messages.

3
_ Source Data Identifier (SDI) program pins
These discretes code the installation side of the ADIRU. This
item of information is used to choose the appropriate
correction laws (for Static Source Error Correction (SSEC) and
corrected angle of attack).
The following table gives the ADR side according to the SDI:

--------------------------------------------------------
| DEBOUNCED STATUS | | |
|-----------------------------| SDI | ADIRU |
| SDI-MSB | SDI-LSB | CODE | NUMBER |
|------------------------------------------------------|
| OPEN | GND | 01 | 1 |
| GND | OPEN | 10 | 2 |
| GND | GND | 11 | 3 |
--------------------------------------------------------
ADR SDI Code

4
_ sensor heat status discretes
These discrete inputs are used to provide the sensors heat
status to the ADR.
These discretes are of the open/ground type.
When the TAT HEAT DISC is grounded, the TAT sensor is heated.
When one of the STATIC, PITOT or AOA HEAT discretes is
grounded, it means that the output of the Probe Heat Computer

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 (PHC) heating power supply is faulty and that the concerned
probe is no longer heated.
In this case the ADR operates as a relay which sends these
information signals to the FWC for warning purposes.

5
_ AOA Average/Unique program pin
The ADR uses the AOA Average/Unique program pin to determine
whether one or two angle of attack resolver inputs are used
for angle of attack computations. When this program pin
indicates WUniqueW, the ADR uses only a single angle of attack
input.
If this first AOA input fails, the ADR uses the opposite AOA
input, as shown in table below. When this program pin
indicates WAverageW, the ADR calculates angle of attack based
on the average of the angle of attack inputs 1 and 2.

-------------------------------------------------------
| SYSTEM | INITIAL NON-FAULT | INPUT TO ADR |
| NUMBER | INPUT TO ADR | AFTER FAULT |
-------------------------------------------------------
| 1 | input number 1 | input number 2 |
| 2 | input number 2 | input number 1 |
| 3 | input number 1 | input number 2 |
-------------------------------------------------------
AOA Resolver Input

The characteristics of these discretes are OPEN/GROUND =

AVERAGE/UNIQUE.
The A/C is defined with the AOA average/unique discrete
grounded.

6
_ VMO/MMO Program Discretes 1 through 4
These discretes are used to select alternate VMO/MMO levels.
There are four alternates and a basic VMO/MMO for each
aircraft type. Table below defines VMO/MMO versus state of the
VMO/MMO program discretes.
With no VMO/MMO discretes in the ground state (yes) the ADR
defaults to the BASIC LAW values for VMO/MMO.
Only one of the four VMO/MMO program discretes can be in the
ground state at any one time.
If more than one VMO/MMO program discrete is in the ground
state at any one time, the ADR defaults to the lowest
available alternate condition.

7
_ on the A/C only the VMO/MMO DISC 2 is available and is
provided by the L/G DOWN VMO/MMO SELECTION switch (22FP).

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 The normal position of this switch is open and it is grounded
after crew action for particular flights (ferry flight for
example).
Table below defines VMO/MMO state according to the switch
(22FP) position.

----------------------------------------------------------
| | VMO | MMO | SWITCH |
| LAW | (kts) | (Mach) | 22FP |
----------------------------------------------------------
| BASIC | 350 | 0.82 | OPEN |
| ALT 1 | | | |
| ALT 2 | 235 | 0.60 | GROUND |
| ALT 3 | | | |
| ALT 4 | | | |
----------------------------------------------------------

VMO/MMO Selection

8
_ SSEC Alternate discrete
The ADR is provided with two Static Source Error Correction
(SSEC) data sets stored in the computer for each SDI and for
each of sixteen aircraft types, one for use in WnormalW
conditions and the other for use in WalternateW conditions.
With the two SSEC selection discretes open (no), the ADR
employs the WnormalW SSEC curve for the aircraft type in which
it is installed. With the two SSEC selection discretes
grounded (yes), the ADR employs the WalternateW condition
curve.

9
_ AOA Alternate discrete
The ADR uses the alternate discrete inputs from the two
redundant SFCCs to select the angle of attack correction which
is appropriate for the current slat and flap settings.
Three laws are available for each aircraft type and SDI:
- the normal law is activated when all the discretes are open
- the alternate 1 law is activated when discretes 1A and 2A
are grounded
- the alternate 2 law is activated when discretes 1A, 2A, 1B
and 2B are grounded.

10
__ Baro Port A discrete
The ADR uses this discrete to select which ARINC 429 port is
used as a source for all baro-correction input data.
If this discrete is grounded, the baro port A is selected.
If this discrete is open, the baro port B is selected.

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 The A/C is wired with this discrete grounded (Ref. Dual Baro
discrete).

11
__ Dual Baro discrete
The ADR uses this discrete to select which ARINC 429 port is
used as a source for all baro-correction input data.
If this discrete is grounded, the baro port A and the baro
port B are selected and the baro port A discrete selection is
overriden. If this discrete is open, the baro port A or the
baro port B is selected depending on the baro port A discrete
selection. The A/C is wired with this discrete open.

12
__ Zero MACH SSEC discrete
The ADR uses this discrete to select the SSEC as a function of
Mach. When this program pin indicates Use SSEC (open), the
SSEC as a function of Mach is computed. When this program pin
indicates Ignore SSEC (ground), the ADR uses zero correction.
The A/C is wired with this discrete open.

13
__ Zero AOA SSEC discrete
The ADR uses this discrete to select the SSEC as a function of
angle of attack. When this program pin indicates Use SSEC
(open), the SSEC as a function of AOA is computed. When this
program pin indicates Ignore SSEC (ground), the ADR uses zero
correction.
The A/C is wired with this discrete open.

14
__ AIR FRM ID Code discrete
The ADR uses input discretes to identify the aircraft (type,
engine model) on which the ADIRU is fitted, and to select the
appropriate set of correction laws for Static Source Error
Correction (SSEC) and AOA corrections.
The ADIRU memory has the capacity to store 128 different sets
of laws.
To perform this coding, the ADR wires seven input discretes
and one discrete for parity to a common.

15
__ ADR Remote Test discrete
The ADR uses one discrete to select the remote test by
external control.
When this discrete is open, the test is not activated.
When this discrete is grounded, the test is activated.
The A/C is wired with this discrete open (unused).
The test is activated via the CFDS (Ref. 34-18-00).

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 16
__ ADR OFF DISCR input discrete
The ADR uses this discrete input to toggle its state between
ON and OFF. When the ADR is OFF, the output buses are disabled
and the ADR FAULT legend is inhibited whenever the momentary
action ADR pusbutton switch is pushed. When the ADR is ON, the
output buses output data and the ADR FAULT legend operates
normally. The ADR OFF DISCR input does not modify Air Data
computation.

17
__ Baro Analog/Digital Sel discrete
The ADR uses this discrete to select either the analog or
digital baro correction.
When this discrete is grounded, the analog baro correction is
selected.
When this discrete is open, the digital baro correction is
selected.
The A/C is wired with this discrete open.

18
__ Baro Corr 3 Active discrete
The ADR uses this discrete to determine for BITE purposes
whether the baro correction 3 is connected or not.
When the discrete is grounded, the baro correction 3 is
connected.
When the discrete is open, the baro correction 3 is not
connected.
The A/C is wired with this discrete open.

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 (3) Acquisition and processing of the sensor inputs

(a) Pressure computation

(Ref. Fig. 002)
Based on pressure raw data received from the ADM (Ref. para.
2.A.(2)(a)1), the software converts the asynchronous pressure
inputs into regularly-scheduled pressure data.
During correction of static pressure, the software calculates the
limited left, right and average static pressure in a range of 100
to 1100 hPa from the ADM inputs.
From the average static pressure (Psm), the software calculates
the corrected static pressure based on the SSEC factor:
( G1 G2 )
Psc = Psm (1 + ---- + ----)
( 1000 1000)
- G1 depends on flaps and Mach is interpolated in a table (2
flaps position and 19 Mach values are considered)
- G2 depends on Mach and AOA corrected and is interpolated in a
table (6 AOA values and 18 Mach values are considered).
The correct SSEC factor depends on the sensor location and on the
aircraft configuration.
The ADR memory contains several tables and the appropriate one is
selected according to the following input discretes:
. SDI
. aircraft Ident
. SSEC Alternate.
Two input discretes can be used to force the SSEC factor to be
independent from AOA or Mach:
. zero MACH SSEC
. zero AOA SSEC.
Ref. Para. 2.A.(2)(c) for more details.
The results of the above computation is available on these output
labels:
. label 176 Left Static Pressure
. label 177 Right Static Pressure
. label 242 Total Pressure
. label 245 Averaged Static Pressure
. label 246 Corrected Static Pressure

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 Pressure Computation - Block Diagram
Figure 002

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 (b) Temperature computation
(Ref. Fig. 003)
The resistance measured by the ADR and compensated for aircraft
wiring is then converted into a temperature value (TAT) according
to the Callender-Van Dusen equation given for a 500 ohm platinum
sensing element:
- -
| 3|
Rt | (TAT ) (TAT ) (TAT ) (TAT) |
-- = 1 + a | TAT - d (--- -1) (--- ) - b (--- -1) (---) |
Ro | (100 ) (100 ) (100 ) (100) |
- -
TAT = temperature in deg.C (TAT)
Rt = Resistance at temperature TAT
Ro = Resistance at 0 deg.C = 500 ohm
a = 0.003832
d = 1.81
b = 0.1 for temperature below 0 deg.C
b = 0 for temperature above 0 deg.C
The computation also compensates the TAT value for heating
effect. The ADR knows when the sensor is heated by the state of
the TAT Heat input discrete from the PHC. The heating
compensation law is provided by the TAT sensor supplier and is
function of Mach and air density.
The PHC 1 controls the heating of the TAT sensor 1 and the PHC 2
controls the heating of the TAT sensor 2. On the ground, the
sensors are not heated (Ref. 30-31-00 for more details).
The result of the above computation is available on the following
output labels:
- label 211 Total Air Temperature (BNR)
- label 231 Total Air Temperature (BCD).

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 Temperature (TAT) Computation - Block Diagram
Figure 003

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 (c) AOA computation
(Ref. Fig. 004)
The A/C is wired in the AOA unique selection, so the ADR computes
the AOA with the reading of one resolver. The second resolver is
used as a back-up. The monitoring function is described in 34.18
The ADR determines the corrected angle of attack value which
depends on the system number and the slat/flap position.
For a CAS less than 60 kts: AOAc = 0 and status matrix is coded
NCD.
For a CAS more than or equal to 60 kts, the corrected angle of
attack is calculated as follows:
AOA ind
AOAc = ------- + I
K
where:
AOA ind = Indicated Angle of Attack (Ref. 34-11-00 for
the relation between resolver and AOA indication)
K, I = Correction coefficients which depend on system
number, slat and flap configuration and magnitude
AOA indication.
The configuration is defined by the status of four input
discretes (Ref. 2.A.(2)(c)).
The results of the above computation is available on the labels:
- label 221 = Indicated Angle of Attack
- label 241 = Corrected Angle of Attack

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 SFCC/AOA Alternate Discrete Signals
Figure 004

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 (4) Parameter computation

(a) General
The operational software of the ADR performs the following
computations:
- pressure altitude and pressure altitude rate function (ALT)
- Mach function (M)
- airspeed function (CAS/TAS)
- temperature function (SAT/TAT)
- maximum operating speed function (VMO/MMO).

(b) Altitude computation

The ADR software computes these different parameters:
label 203 Pressure Altitude
label 212 Altitude Rate
label 204 Baro Corrected Altitude 1 (CAPT)
label 220 Baro Corrected Altitude 2 (F/O)
label 235 Baro Correction In Hg 1 (CAPT)
label 237 Baro Correction In Hg 2 (F/O)

1
_ Altitude pressure and altitude rate computation
(Ref. Fig. 005)
The altitude is derived from the corrected static pressure.
The conversion from pressure to altitude is based on the
geopotential altitude tables of the US Standard Atmosphere,
1962. The accepted range is (-2000 ft, +50,000 ft).
The altitude rate is calculated by multiplying the rate of
change of the corrected static pressure by the derivative of
altitude with respect to corrected static pressure:
dH d Ps dH
-- = ---- x ----
dt dt d Ps

2
_ Corrected altitude computation
(Ref. Fig. 006)
The ADR receives the baro correction introduced on the FCU by
each crew member. The ADR uses the values in hPa (labels 234
and 236 from the FCU).
The ADR also converts these values into inches of mercury (in.
Hg) and the result is sent on the output labels 235, 237.
The corrected altitude is calculated by a shift of the
pressure altitude to a value corresponding to the entered baro
correction. The result is sent on label 204 for CAPT baro
corrected altitude and label 220 for F/O baro corrected
altitude.

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 Altitude and Altitude Rate Computation - Block Diagram
Figure 005

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 Corrected Altitude Computation - Block Diagram
Figure 006

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 (c) CAS/Mach computation
(Ref. Fig. 007)
The ADR software computes these different parameters:
label 206 Computed Airspeed
label 205 Mach
label 207 Maximum Allowable Airspeed.
The CAS and Mach computation is based on the conversion of the
impact pressure:
impact pressure = Pt - Ps.
- the CAS computation converts input of impact pressure to output
corresponding to computed airspeed with:
______________________
/ Qc 2/7
CAS = Cso X V 5 X ((-- + 1) - 1)
Po
CAS = Computed Airspeed in knots
Cso = Speed of sound under standard day sea level
conditions = 661.4746 kts
Qc = Impact pressure in hPa
Po = Standard day sea level pressure = 1013.25 hPa
For accuracy reason, the CAS is output with a valid (NO) SSM
only after 30 kts. If the CAS is below 30 kts, the label 206
indicates 0 kt with SSM = NCD.
- the Mach computation converts Qc/Ps to Mach, with:
_______________________
/ Qc 2/7
MACH = V 5 ((-- + 1) - 1)
Ps
MACH = Mach number
Qc/Ps = Ratio of impact pressure to static pressure
If Mach is below 0.1, the label 205 indicates 0 with SSM = NCD.

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 CAS/Mach Computation - Block Diagram
Figure 007

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 (d) SAT/TAS computation
(Ref. Fig. 008)
The ADR software calculates these different parameters:
label 213 BNR Static Air Temperature (SAT)
label 233 BCD Static Air Temperature (SAT)
label 210 BNR True Airspeed (TAS)
label 230 BCD True Airspeed (TAS).
- the calculation of the BNR SAT converts TAT to SAT with:
TAT
SAT = --------- - 273.15
2
1 + 0.2M
SAT = Static Air Temperature (in deg. C)
TAT = Total Air Temperature (in deg. Kelvin)
M = Mach number (corrected for static source error)
- the calculation converts Static Air Temperature from BNR to BCD
format.
- the calculation of the BNR TAS converts Mach and SAT to TAS
with:
___
/
TAS = 38.96695 x M x V SAT
TAS = True Airspeed (in knots)
M = Mach Number (corrected for Static Source Error)
SAT = Static Air Temperature (in deg. Kelvin)
- the calculation converts True Airspeed from BNR to BCD format.
For accuracy reason, the TAS is output with a valid (NO) SSM
only after 60 kts. If TAS is below 60 kts, the label 210
indicates 0 kt with SSM = NCD.

(e) VMO/MM0 computation

(Ref. Fig. 009)
The software determines the normal or alternate VMO/MMO law
selected by the VM0/MM0 input 2 discrete state; then it computes
the label 207 Maximum Allowable Airspeed.
This airspeed is based on the Maximum Allowable Airspeed under a
certain altitude and on the Maximum Allowable Mach above this
altitude. It is always indicated in knots and decreases when the
altitude increases.

NOTE : At a constant Mach, the Vc value decreases when the

____
altitude increases.

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 SAT/TAS Computation - Block Diagram
Figure 008

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 VMO/MMO Computation - Block Diagram
Figure 009

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 (5) ADR data outputs
The ADR data outputs are transmitted in two forms: digital and
discrete.

(a) Digital form

The table below contains all the output parameters in the digital
form.
They are sorted as per the numerical order of their output label.
The following table gives:
- EQ.SYS.LAB.SDI: (SDAC, FWC, DMC...) output label for which the
parameter is available
- PARAMETER DEFINITION: parameter name
- WORD RANGE/OPER RANGE/RESOLUTION ACCURACY: measurement range
Maximum value transmitted. When the digital value changes, the
change step is equal to the accuracy
- UNIT: unit in which the digital value is transmitted
- SIG BIT: indicates whether a sign bit is available
- BITS: number of bits used by the parameter in the label
- XMSN/INTV: output transmission interval. The refresh rate is
given in milliseconds.
- CODE:
BNR: binary data word
BCD: binary coded decimal data word
ISO: data word coded in ISO5 code
DIS: discrete data word
HEX: hexadecimal coded
HYB: mixed code.
- ALPHA CODE: indicates the parameter mnemonic code
- SOURCE ORIGIN: parameter source computer or system.

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 -------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
| 176 |L STATIC |W2048 |hPa | | 16 |125 |BNR | | |
| |PRESSURE |100 to 1100 | | | | | | | |
| | |R 0.03125 | | | | | | | |
| | |+/- 0.3 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 177 |R STATIC |W2048 |hPa | | 16 |125 |BNR | | |
| |PRESSURE |100 to 1100 | | | | | | | |
| | |R 0.03125 | | | | | | | |
| | |+/- 0.3 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 203 |ALTITUDE |W+/- 131072 | ft | 29 | 17 | 62 |BNR | ALT | |
| |1013.25mb |-2000 to | | | | | | | |
| | | 50000 | | | | | | | |
| | |R 1 +/-30 | | | | | | | |
| | |(30,000) | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 204 |BARO CORR |W+/- 131072 | ft | 29 | 17 | 62 |BNR | | |
| |ALT 1 |-2000 to | | | | | | | |
| | | 50000 | | | | | | | |
| | |R 1 +/-30 | | | | | | | |
| | |(30,000) | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 205 |MACH |W4096 |Mach| | 16 |125 |BNR | MN | |
| | |0.1 to 1.00 | | | | | | | |
| | |R 6.25 E-5 | | | | | | | |
| | |+/-0.010 | | | | | | | |
| | |(0.1) | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 206 |COMPUTED |W1024 |Kts | | 14 |125 |BNR | CAS | |
| |AIRSPEED |30 to 450 | | | | | | | |
| | |R 0.0625 | | | | | | | |
| | |+11.5 (100) | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 207 |MAXIMUM |W1024 |Kts | | 12 |125 |BNR | | |
| |ALLOWABLE |150 to 450 | | | | | | | |
| |AIRSPEED |R 0.25 +/- 1| | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 210 |TRUE |W2048 |Kts | | 15 |125 |BNR | | |

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 -------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
| |AIRSPEED |60 to 599 | | | | | | | |
| | |R 0.0625 | | | | | | | |
| | |+/- 3 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 211 |TOTAL AIR |W +/- 512 |Deg.| 29 | 11 |500 |BNR | TAT | |
| |TEMP |-60 to 99 |C | | | | | | |
| | |R 0.25 | | | | | | | |
| | |+/- 0.5 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 212 |ALTITUDE |W+/- 32768 |ft/ | 29 | 11 | 62 |BNR | | |
| |RATE |-20,000 to |mn | | | | | | |
| | | 20,000 | | | | | | | |
| | |R 16.0 | | | | | | | |
| | |+/-30 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 213 |STATIC AIR|W+/- 512 |Deg.| 29 | 11 |500 |BNR | SAT | |
| |TEMP |-99 to +80 |C | | | | | | |
| | |R 0.25 | | | | | | | |
| | |+/- 1 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 215 |IMPACT |W512 |hPa | | 14 |125 |BNR | | |
| |PRESSURE |0 to 372.5 | | | | | | | |
| | |R 0.03125 | | | | | | | |
| | |+/- 0.5 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 220 |BARO CORR |W +/- 131072| ft | 29 | 17 | 62 |BNR | | |
| |ALT 2 |-1000 to | | | | | | | |
| | | 50000 | | | | | | | |
| | |R 1 +/- 30 | | | | | | | |
| | | (30,000) | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 221 |IND ANGLE |W +/- 180 |Deg.| 29 | 12 | 62 |BNR | | |
| |OF ATTACK |-35 to +85 | | | | | | | |
| | |R 0.0439 | | | | | | | |
| | |+/- 0.25 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 230 |TRUE |W +/- 799 |Kts | | 3 |500 |BCD | | |
| |AIRSPEED |60 to 599 | | | | | | | |

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 -------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
| | |R 1 +/- 3 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 231 |TOTAL AIR |W +/- 799 |Deg.| | 2 |500 |BCD | | |
| |TEMP |-60 to 99 |C | | | | | | |
| | |R 1 +/- 1 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 233 |STATIC AIR|W +/- 799 |Deg.| | 2 |500 |BCD | | |
| |TEMP |-99 to +80 |C | | | | | | |
| | |R 1 +/- 1 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 234 |BARO |W +/- 7999.9|hPa | | 5 |500 |BCD | | |
| |CORRECT 1 |745 to 1100 | | | | | | | |
| | |R 0.1 | | | | | | | |
| | |+/- 0.25 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 235 |BARO |W +/- 79.999|inHg| | 5 |500 |BCD | | |
| |CORRECT 1 |22.0 to 32.5| | | | | | | |
| | |R 0.001 | | | | | | | |
| | |+/- 0.0074 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 236 |BARO |W +/- 7999.9|hPa | | 5 |500 |BCD | | |
| |CORRECT 2 |745 to 1100 | | | | | | | |
| | |R 0.1 | | | | | | | |
| | |+/- 0.25 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 237 |BARO |W +/- 79.999|inHg| | 5 |500 |BCD | | |
| |CORRECT 2 |22.0 to 32.5| | | | | | | |
| | |R 0.001 | | | | | | | |
| | |+/- 0.0074 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 240 |VMO/MMO |W 399/0.99 |Kts/| |3/2 |1000|BCD | | |
| |STATUS |0 to 399 / |Mach| | | | | | |
| | |0 to 0.99 | | | | | | | |
| | |R 1 /0.01 | | | | | | | |
| | |1 / 0.01 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 241 |CORRECTED |W +/- 180 |Deg.| 29 | 12 | 62 |BNR | AOA | |
| |ANGLE OF |-35 to +85 | | | | | | | |

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 -------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
| |ATTACK |R 0.0439 | | | | | | | |
| | |+/- 0.25 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 242 |TOTAL |W2048 |hPa | | 16 |125 |BNR | | |
| |PRESSURE |100 to 1400 | | | | | | | |
| | |R 0.03125 | | | | | | | |
| | |+/- 0.3 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 245 |UNCRCTD |W2048 |hPa | | 16 |125 |BNR | | |
| |AVG STAT |100 to 1100 | | | | | | | |
| |PRESSURE |R 0.03125 | | | | | | | |
| | |+/- 0.3 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 246 |CORCTD |W2048 |hPa | | 16 |125 |BNR | | |
| |AVG STAT |100 to 1100 | | | | | | | |
| |PRESSURE |R 0.03125 | | | | | | | |
| | |+/- 0.3 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 270 |DSCT WORD | | | | |500 |DIS | | |
| | 1 | | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 271 |DSCT WORD | | | | |500 |DIS | | |
| | 2 | | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 272 |DSCT WORD | | | | |500 |DIS | | |
| | 3 | | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 350 |MAINT WORD| | | | |500 |DIS | | |
| | 1 | | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 351 |MAINT WORD| | | | |500 |DIS | | |
| | 2 | | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 352 |MAINT WORD| | | | |500 |DIS | | |
| | 3 | | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 155 |MAINT WORD| | | | |500 |DIS | | |
| | 4 | | | | | | | | |

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 -------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 354 |LRU ID | | | | | |ISO | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 356 |FAULT STAT| | | | | |ISO | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 377 |EQPT IDENT| | | | |500 |HEX | | |
-------------------------------------------------------------------------------
Output Label

--------------------------------------------------------------------------
| BIT N⁰ | FUNCTION | 1 = GND | 0 = OPEN |
--------------------------------------------------------------------------
| 11 | Icing Detector Heat | NO FAULT | FAULT |
| 12 | Pitot Probe Heat | NO FAULT | FAULT |
| 13 | ADR FAULT | FAULT | NO FAULT |
| 14 | Right Static Heat | NO FAULT | FAULT |
| 15 | Left Static Heat | NO FAULT | FAULT |
| 16 | TAT Heat | HEAT | NO HEAT |
| 17 | AOA 1 Heat | NO FAULT | FAULT |
| 18 | AOA 2 Heat | NO FAULT | FAULT |
| 19 | Overspeed Warning | WARN | NO WARN |
| 20 | Spare (Primary AOA Fault) | | |
| 21 | AOA Average/Unique | UNIQUE | AVERAGE |
| 22 | VMO/MMO 1 | YES | NO |
| 23 | VMO/MMO 2 | YES | NO |
| 24 | VMO/MMO 3 | YES | NO |
| 25 | VMO/MMO 4 | YES | NO |
| 26 | SSEC Alternate Select 1 | YES | NO |
| 27 | SSEC Alternate Select 2 | YES | NO |
| 28 | Baro Port A Select | Port A | Port B |
| 29 | Zero Mach SSEC Select | YES | NO |
--------------------------------------------------------------------------
Label 270 - Discrete Word 1

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 --------------------------------------------------------------------------
| BIT N⁰ | FUNCTION | 1 = GND | 0 = OPEN |
--------------------------------------------------------------------------
| 11 | Zero AOA SSEC Select | YES | NO |
| 12 | AOA Test Active | ACTIVE | NOT ACTIVE |
| 13 | Low Speed Warning 1 | FAST | SLOW |
| 14 | Low Speed Warning 2 | FAST | SLOW |
| 15 | Low Speed Warning 3 | FAST | SLOW |
| 16 | Low Speed Warning 4 | SLOW | FAST |
| 17 | Spare | | |
| 18 | Spare | | |
| 19 | Spare | | |
| 20 | AOA Correction 1A | YES | NO |
| 21 | AOA Correction 1B | YES | NO |
| 22 | AOA Correction 2A | YES | NO |
| 23 | AOA Correction 2B | YES | NO |
|24 to 29| Spare | | |
--------------------------------------------------------------------------
Label 271 - Discrete Word 2

--------------------------------------------------------------------------
| BIT N⁰ | FUNCTION | 1 = GND | 0 = OPEN |
--------------------------------------------------------------------------
| 11 | SDI 2 | GROUND | OPEN |
| 12 | SDI 1 | GROUND | OPEN |
| 13 | Dual Baro Select | DUAL PORT | SINGLE PORT|
| 14 | Analog Baro Select | ANALOG | DIGITAL |
| 15 | Spare IDSC 1 | GROUND | OPEN |
| 16 | Spare IDSC 2 | GROUND | OPEN |
| 17 | Spare IDSC 3 | GROUND | OPEN |
| 18 | Baro 3 Present | PRESENT | ABSENT |
| 19 | Spare IDSC 4 | GROUND | OPEN |
R | 20 | CFDS Select | NOT ACTIVE| ACTIVE |
| 21 | Spare | | |
| 22 | BITE Memory Clear Enable | ENABLE | DISABLE |
| 23 | BITE Write Inhibit | INHIBIT | ENABLE |
| 24 | ADR Interface Test | TEST | NORMAL |
| 25 | ADR Off Command | GROUND | OPEN |
| 26 | Reserved | | |
| 27 | ADR On/Off Status | OFF | ON |
| 28 | Spare | | |
| 29 | Spare | | |
--------------------------------------------------------------------------
Label 272 - Discrete Word 3

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 -------------------------------------------------------------------------
| BIT N⁰ | FUNCTION | 1 = GND | 0 = OPEN |
-------------------------------------------------------------------------
| 11 | A/C ID Code 32/0 | GROUND | OPEN |
| 12 | A/C ID Code 64/0 | GROUND | OPEN |
|13 to 23| Spare | | |
| 24 | A/C ID Code 1/0 | GROUND | OPEN |
| 25 | A/C ID Code 2/0 | GROUND | OPEN |
| 26 | A/C ID Code 4/0 | GROUND | OPEN |
| 27 | A/C ID Code 8/0 | GROUND | OPEN |
| 28 | A/C ID Code 16/0 | GROUND | OPEN |
| 29 | A/C ID Parity | GROUND | OPEN |
-------------------------------------------------------------------------
Label 352 - Discrete Word 4

-------------------------------------------------------------------------
| BIT N⁰ | FUNCTION |
-------------------------------------------------------------------------
| 11 | = 0 -- |
| 12 | = 1 | LSD = 6 |
| 13 | = 1 | |
| 14 | = 0 -- |
| 15 | = 0 -- |
| 16 | = 0 | MSD = 0 |
| 17 | = 0 | |
| 18 | = 0 -- |
|19 to 29| Spare |
-------------------------------------------------------------------------
Label 377 - Equipment Ident

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 - On the ground the output labels are in the following state:

--------------------------------------------------------------------------
| LABEL | PARAMETER DEFINITION | SSM | ON GND CRITERION |
|-------------------------------------------------------------------------
| 203 | Altitude | NO | |
| 204 | Baro Corr Alt 1 | NO | |
| 220 | Baro Corr Alt 2 | NO | |
| 251 | Baro Corr Alt 3 | NO | |
| 205 | Mach | NCD | 0 Mach less than 0.1 |
| 206 | Computed Airspeed | NCD | 0 kt CAS less than 30 kts |
| 207 | Max Allowable Airspeed | NO | |
| 210 | True Airspeed | NCD | 0 kt CAS less than 60 kts |
| 211 | Total Air Temp | NO | |
| 212 | Altitude Rate | NO | |
| 213 | Static Air Temp | NO | |
| 215 | Impact Pressure | NO | |
| 221 | Indicated AOA | NCD | NOTE CAS less than 60 kts |
| 230 | True Airspeed | NCD | 0 kt CAS less than 60 kts |
| 231 | Total Air Temp | NO | |
| 233 | Static Air Temp | NO | |
| 234 | Baro Corr (hPa) 1 & 2 & 3| NO | |
| 236 | Baro Corr (hPa) 2 | NO | |
| 034 | Baro Corr (hPa) 3 | NO | |
| 235 | Baro Corr (in.Hg) 1 | NO | |
| 237 | Baro Corr (in.Hg) 2 | NO | |
| 035 | Baro corr (in.Hg) 3 | NO | |
| 240 | VMO/MMO status | NO | |
| 241 | Corrected AOA | NCD | 0⁰ CAS less than 60 kts |
| 242 | Total Pressure | NO | |
| 176 | L. Static Pressure | NO | |
| 177 | R. Static Pressure | NO | |
| 245 | Uncrctd Avg Stat Pressure| NO | |
| 246 | Corctd Avg Stat Pressure | NO | |
| 270 | Discrete words | NO | |
| 271 | Discrete words | NO | |
| 272 | Discrete words | NO | |
| 350 | Discrete words | NO | |
| 351 | Discrete words | NO | |
| 352 | Discrete words | NO | |
| 377 | Discrete words | NO | |
| 354 | LRU ID | N/A | N/A |
| 356 | Fault Status | N/A | N/A |
--------------------------------------------------------------------------
Output Label Value on Ground

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 (b) Discrete form
The ADR provides seven standard OPEN/GROUND output discretes.

--------------------------------------------------------------------------
| SIGNAL | PIN | OUTPUT | DEFINITION |
|------------------------------|------------|-------------|--------------|
| ADR OFF Light | TP- 4E | OPEN/GROUND | ON/OFF |
| ADR FAULT | TP- 4D | OPEN/GROUND | NO/FAULT |
| Low Speed Warning Discrete 1 | TP- 2F | OPEN/GROUND | SLOW/FAST |
| Low Speed Warning Discrete 2 | TP- 2G | OPEN/GROUND | SLOW/FAST |
| Low Speed Warning Discrete 3 | TP- 6F | OPEN/GROUND | SLOW/FAST |
| Low Speed Warning Discrete 4 | TP-13H | OPEN/GROUND | FAST/SLOW |
| AOA Special Test | TP-12G | OPEN/28VDC | NO/TEST |
--------------------------------------------------------------------------
ADR - Discrete Output Signals

NOTE : The ADR OFF light, the low speed warning 4 and ADR FAULT
____
discretes are forced to the ground state when the watchdog
timer (WDT) has timed out.

1
_ ADR OFF Light
When the ADR is commanded OFF, it issues a ground state to the
ADR OFF light discrete to enable the legend to come on.

2
_ ADR FAULT
When an ADR FAULT is detected, the ADR issues a ground state
to the ADR FAULT discrete to enable the legend to come on.

3
_ Low speed warning discretes 1, 2, 3, 4
The ADR provides four standard Open/Ground low speed warning
output discretes.
- Airspeed conditions
Airspeed decreasing
Discrete 1 = OPEN for Airspeed less than or equal to 100
knots
Discrete 2 = OPEN for Airspeed less than or equal to 50
knots
Discrete 3 = OPEN for Airspeed less than or equal to 155
knots
Discrete 4 = GROUND for Airspeed less than or equal to 260
knots
Airspeed increasing
Discrete 1 = GROUND for Airspeed greater than 104 knots
Discrete 2 = GROUND for Airspeed greater than 54 knots
Discrete 3 = GROUND for Airspeed greater than 159 knots
Discrete 4 = OPEN for Airspeed greater than 264 knots
- Power off conditions

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 Discrete 1 = OPEN
Discrete 2 = OPEN
Discrete 3 = OPEN
Discrete 4 = OPEN
- CAS detected failure condition
Discrete 1 = previous state
Discrete 2 = previous state
Discrete 3 = previous state
Discrete 4 = OPEN

4
_ AOA special test
The ADR provides an OPEN/GROUND output discrete to drive the
AOA self-test.
The AOA self-test is commanded via the CFDIU interface bus.
When the AOA test is active, the AOA sensor is offset to +15
deg. (plus or minus 1 deg.). All AOA dependent parameters
reflect this offset and their SSMs indicate Functional Test
(FT).
The RETURN command from the MCDU results in the discrete
output set to OPEN.
Ref. 34-18-00 for more details.

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 3. ________________________________
Operation/Control and Indicating

A. Control

(1) ADIRS Control and Display Unit (CDU)

(Ref. Fig. 010)
The ADIRS CDU provides the control and warning of the three ADRs by
means of three ADR illuminated pushbutton switches:
- the pushbutton switch is used to disable the ADR output buses. It
is a momentary action pushbutton switch
- when the ADR output buses are disabled, the ADR controls the
activation of the ADR OFF legend by its output discrete: ADR OFF
status
- when an ADR failure is detected, the ADR controls the activation of
the ADR FAULT legend by its output discrete: ADR FAULT
- each ADR is de-energized when the associated OFF/NAV/ATT selector
switch is set to OFF
- when the associated OFF/NAV/ATT selector switch is set to NAV or
ATT, each ADR is switched on independently of the previous
selection on the ADR pushbutton switch.

B. Indicating
Altitude (ALT), Computed Airspeed (CAS), Mach number (M) and Vertical
Speed (V/S) are computed by the ADIRU (ADR portion), processed by the
associated DMC and displayed on the PFDs.
True Airspeed (TAS) is supplied in the same way but is displayed on the
NDs.
In normal configuration, with the AIR DATA selector switch in NORM
position, the ADR 1 displays information on CAPT PFD and ND. The ADR 2
displays information on F/O PFD and ND.
Static Air Temperature (SAT) and Total Air Temperature (TAT) are also
supplied in the same way but are permanently displayed on the lower part
of the lower ECAM DU.
These items of information are displayed by the ADR 2.

(1) PFD display

For further details concerning speed, altitude or vertical speed
scale, Ref. 31-64-00.

(a) Computed Airspeed (CAS)

(Ref. Fig. 011)
The CAS indication is displayed in analog form by means of a
white tape with graduations every 10 kts and digital values every
20 kts. This tape moves up and down so as to indicate the A/C
actual speed value in front of a fixed yellow reference line.

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 ADR Control on CDU
Figure 010

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 Computed Airspeed and Mach Indication Display
Figure 011

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 The displayed part of the scale represents an 84 kts range. The
scale is graduated from 30 kts to 520 kts and the digital values
from 40 to 520 kts (item A).
In no case can the displayed CAS be lower than 30 kts.
In case of computed airspeed failure, the speed scale goes out of
view and is replaced by a red SPD flag (item B).

(b) Mach number (M)

When the Mach number is above 0.5, it is displayed just below the
speed scale.
In case of failure, a red MACH flag is presented.

(c) Altitude (ALT)

(Ref. Fig. 012)
The baro altitude indication is provided by means of a tape which
moves up and down behind a window within which the A/C actual
altitude is displayed.
The tape of the scale is graduated every 100 ft and digital
values are displayed every 500 ft in hundreds.
The A/C actual altitude is provided by a counter located at the
middle of the scale in which the actual value is displayed in
green digits.
The hundreds of feet are written in a large size whereas the tens
and units are displayed by a drum operating as a classical
mechanical altimeter.
Small white marks are positioned in front of each number on the
tape (item A).
If the altitude is negative, a NEG white indication is added at
the left of the digital value. The digital value is limited to
minus 1500 ft (item B).
Different displays are presented depending on the baro setting
reference (standard or baro corrected), Ref. 31-64-00.
In case of baro altitude failure, the scale goes out of view and
a red ALT flag flashes for a few seconds in the altitude window,
then remains steady (item C).
In case of discrepancy between the altitude given by the CAPT air
data source and the altitude given by the F/O air data source, a
CHECK ALT amber flag is presented on the right side of the
altitude scale (item D).

(d) Vertical Speed (V/S)

(Ref. Fig. 013)
The baro vertical speed is automatically displayed in the right
side of the PFD when the inertial vertical speed is not available
(item A). It is a degraded mode.
The vertical speed scale consists of:
- a trapezoidal grey background colored surface

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 Altitude Indication Display
Figure 012

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 Vertical Speed Indication Display
Figure 013

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 - a fixed white scale with 500 ft/mn spaced marks from -2000
ft/mn to +2000 ft/mn
- a needle giving, in analog form, the actual vertical speed
value
- a number in a moving amber window. This window accompanies the
needle (above the needle if V/S > 0, below if V/S < 0).
The number gives the V/S value in hundreds of ft/mn.
Between -200 ft/mn and +200 ft/mn, both the window and the
number disappear.
- above +6000 ft/mn (or below -6000 ft/mn), the needle remains
stopped where it is.
When the vertical speed exceeds +6000 ft/mn or -6000 ft/mn, the
digital indication and the analog needle change from green to
amber.
In addition, those indications change to amber in approach, in
the following cases:
- V/S less than -2000 ft/mn below 2500 ft RA
- V/S less than -1200 ft/mn below 1000 ft RA.
In case of a failure warning, the vertical speed scale is removed
and replaced by a red V/S flag which flashes for a few seconds,
then remains steady (item B).

(2) ND display
(Ref. Fig. 014)
The true airspeed (TAS) is displayed on the ND in ROSE, ARC and PLAN
mode (item A).
The TAS information is displayed by a numerical indication of three
digits preceded by TAS indication. This information is displayed in
the left upper corner of the ND for speed higher than 100 kts. Below
this value TAS indication remains visible but is followed by three
dashes (item B).

(3) Display on the lower ECAM DU

(Ref. Fig. 015)
The Static Air Temperature (SAT) and the Total Air Temperature (TAT)
are permanently displayed on the lower part of the lower ECAM DU by a
numerical indication of two digits preceded by the plus or minus sign
(item A).
R These data are delivered by the ADR 2.
R In case of failure or when NCD information is received from the ADR
R 2, these data are replaced by crosses (item B).

(4) Reconfiguration display

In case of loss of AIR DATA parameters on CAPT or F/O PFD and ND, the
ADR 3 can be used as a back up source by placing the AIR DATA
selector switch in CAPT/3 position for EFIS 1 and F/O/3 position for
EFIS 2.

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 True Airspeed Indication Display
Figure 014

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 TAT/SAT Indication Display
Figure 015

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 In case of loss of TAT/SAT parameters on the lower ECAM DU, the ADR 3
R can be used as a back up source by placing the AIR DATA selector
R switch in F/O/3 position.

C. Warnings
In addition to the AIR DATA flags displayed on the PFDs and NDs and on
the CDU, warning messages are displayed on the lower part of the upper
ECAM DU.
Two kinds of warning messages can be displayed:
- failure warning messages in case of loss of AIR DATA parameters
- configuration warning messages in case of dangerous configuration of
the aircraft.
When the CLR key is pushed on the ECAM control panel, a STATUS page is
displayed on the lower ECAM DU and indicates the STATUS and INOP SYS
(systems).

(1) Failure warning messages

(Ref. Fig. 016, 017, 018)

(a) NAV ADR 1(2)(3) FAULT

NAV ADR 1(2) + 2(3) FAULT
When these messages are displayed:
- the MASTER CAUT lights on the glareshield come on
- the Single Chime (SC) sounds
- the FAULT legend of the ADR pushbutton switch on the CDU comes
on.

(b) NAV ALTI DISCREPANCY

(Ref. Fig. 019)
This message is displayed when a difference higher than plus or
minus 250 ft is detected by the external comparison inside the
FWCs between the baro-corrected altitude (or plus or minus 500 ft
for the standard altitude) provided by two ADRs.
When it is displayed:
- the MASTER CAUT lights on the glareshield come on
- the Single Chime (SC) sounds
- the CHECK ALT message appears on the PFD.

(2) Configuration warning messages

(Ref. Fig. 020, 021)

(a) OVERSPEED VM0/MM0

OVERSPEED VFE/VLE
When these messages are displayed:
- the MASTER WARN lights on the glareshield flash
- the Continuous Repetitive Chime (CRC) sounds.

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 NAV ADR 1(2)(3) FAULT Message
Figure 016

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 NAV ADR 1+3 (2+3) FAULT Message
Figure 017

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 NAV ADR 1 + 2 FAULT Message
Figure 018

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 NAV ALTI DISCREPANCY Message
Figure 019

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 OVERSPEED VMO/MMO Message
Figure 020

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 OVERSPEED VFE/VLE Message
Figure 021

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 OVERSPEED VMO/MMO warning processed by the FWC is triggered when
the CAS/Mach calculated by the ADR exceed the VMO/MMO threshold
by more than 4 kts/0.006 Mach.
OVERSPEED VFE/VLE processed by the FWC is a function of Vc and
depends on slat/flap position for the VFE and landing gear
position for the VLE.
For overspeed VLE, the warning is triggered at 284 knots.

(b) Stall warning

(Ref. Fig. 022)
When this warning is activated:
- the MASTER WARN lights on the glareshield flash
- the cricket and the voice STALL sound.
This warning is processed by the FWC and is a function of angle
of attack value and slat position following three conditions:
- normal law:
if corrected angle of attack exceeds 23⁰ or if corrected angle
of attack exceeds 15⁰ and slat < 15⁰.
- alternate law
if corrected angle of attack exceeds 13⁰ or if corrected angle
of attack exceeds 8⁰ and slat < 15⁰.

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 Stall Warning Message
Figure 022

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 AIR DATA - REMOVAL/INSTALLATION
_______________________________

TASK 34-13-00-040-001

PFD Mach Number - Overspeed Check

WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE
_______
YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
31-32-00-860-010 Procedure to Get Access to the SYSTEM REPORT/TEST NAV
Page
31-60-00-860-001 EIS Start Procedure
34-10-00-860-002 ADIRS Start Procedure
34-10-00-860-005 ADIRS Stop Procedure
34-13-00-740-002 INTERFACE TEST of the ADR

3. __________
Job Set-up

Subtask 34-13-00-865-070

A. On the circuit breaker panels 49VU, 121VU and 122VU, close the circuit
breakers related to the NAVIGATION, EIS, FCU, CFDS and LGCIU systems.

Subtask 34-13-00-860-081

B. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-

002).

(2) Do the EIS start procedure (Ref. TASK 31-60-00-860-001).

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 (3) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002).

(4) On the MCDU, get the SYSTEM REPORT/TEST NAV menu page
(Ref. TASK 31-32-00-860-010)

(5) On the overhead panel :

- on the FLT CTL panels 23VU and 24VU, make sure that the FAC, ELAC
and SEC pushbutton switches are not pushed (in). The OFF legends
are on.
- on the ELEC panel 35VU, make sure that the battery voltage is
correct, between 26VDC and 30VDC.

4. Procedure
_________

Subtask 34-13-00-710-056

A. Overspeed Check

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the overhead panel, on the

ADIRS CDU:

- set the 3 OFF/NAV/ATT selector The OFF legend of the 3 ADR pushbutton
switches to NAV. switches must be off.

- push the ADR3 pushbutton The related OFF legend comes on.
switch.

2. On the MCDU, on the NAV menu

page:

- push the line key adjacent to The ADR1 (ADR2) page comes into view.
the ADC1 (ADC2) indication.

- push the line key adjacent to The ADR1 (ADR2) OUTPUT TESTS page comes
the OUTPUT TESTS indication. into view.

- push the line key adjacent to The ADR1 (ADR2) INTERFACE TEST 1/2 page
the INTERFACE TEST indication. comes into view.

- on the keyboard push the NEXT The ADR1 (ADR2) INTERFACE TEST 2/2 page
PAGE function key. comes into view.

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
- push the line key adjacent to From 0 to 10 seconds ignore the
the START TEST indication. warnings and indications.
(Ref. TASK 34-13-00-740-002). From 10 seconds:
- the black and red strip comes into
view on the speedscale on the CAPT
(F/O) PFD
- ignore the related warnings.

- push the line key adjacent to The test procedure stops, the warnings
the RETURN indication. above stop.

5. Close-up
________

Subtask 34-13-00-860-082

A. Put the aircraft back to its initial configuration.

(1) On the ECAM control panel, set the LOWER DISPLAY and the UPPER
DISPLAY potentiometers to OFF.

(2) On the MCDU, push the MCDU MENU mode key.

(3) Do the ADIRS Stop Procedure(Ref. TASK 34-10-00-860-005).

(4) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

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 TASK 34-13-00-440-001

Reactivation of PFD Mach Number - Overspeed Check

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

TSM 22 PB 101 (for corrective action)

TSM 34 PB 101 (for corrective action)

3. __________
Job Set-up

Subtask 34-13-00-869-085

A. Not Applicable

4. Procedure
_________

Subtask 34-13-00-810-050

A. Do the trouble-shooting of the auto-flight function.

(Ref. TSM 22 PB 101) and (Ref. TSM 34 PB 101).

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 AIR DATA - ADJUSTMENT/TEST
__________________________

TASK 34-13-00-710-001

Operational Test of the AIR DATA Switching Function

WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE
_______
YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.

1. __________________
Reason for the Job

Refer to the MPD TASK: 341300-02

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
31-60-00-860-001 EIS Start Procedure
31-60-00-860-002 EIS Stop Procedure

3. __________
Job Set-up

Subtask 34-13-00-860-056

A. Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002).

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 Subtask 34-13-00-010-057

B. Get Access

(1) Put the access platform in position at the access door 822.

(2) Open the access door 822.

(3) On the battery power center 105VU:

- loosen the two screws and remove the protective cover.

Subtask 34-13-00-865-063

C. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU L/G/LGCIU/SYS1/NORM 1GA C09
49VU NAV PROBES/ADIRU3/PWR/SWTG 8FP F09
49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07
49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06
105VU ADIRS/ADIRU1/28VDC 6FP1 C02

R **ON A/C 001-004,

121VU ADIRS/ADIRU/2PWR/SHED 10FP N11

121VU ADIRS/ADIRU/3PWR/SWTG 9FP N10
121VU ADIRS/ADIRU/2/26VAC AND AOA 5FP2 N09
121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N08
121VU ADIRS/ADIRU/2/115VAC 4FP2 N07
121VU ADIRS/ADIRU/3/115VAC 4FP3 N06
121VU ADIRS/ADIRU/2/28VDC 6FP2 N05
121VU ADIRS/ADIRU/3/28VDC 6FP3 N04

R **ON A/C ALL

121VU HYDRAULIC/LGCIU/SYS2 2GA Q35

121VU HYDRAULIC/LGCIU/SYS1/GRND SPLY 52GA Q34

R **ON A/C 005-099,

R 121VU ADIRS/ADIRU/2PWR/SHED 10FP N10

R 121VU ADIRS/ADIRU/3PWR/SWTG 9FP N09

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 -------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
R 121VU ADIRS/ADIRU/2/26VAC AND AOA 5FP2 N08
R 121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N07
R 121VU ADIRS/ADIRU/2/115VAC 4FP2 N06
R 121VU ADIRS/ADIRU/3/115VAC 4FP3 N05
R 121VU ADIRS/ADIRU/2/28VDC 6FP2 N04
R 121VU ADIRS/ADIRU/3/28VDC 6FP3 N03

R **ON A/C ALL

Subtask 34-13-00-860-057

D. Aircraft Maintenance Configuration

(1) Do the EIS start procedure (PFDs and NDs only) (Ref. TASK 31-60-00-
860-001).

(2) On the overhead panel:

- on the FLT CTL panels 23VU and 24VU, make sure that the FAC, ELAC
and SEC pushbutton switches are not pushed (in). The OFF legends
are on.
- on the ADIRS CDU, on the panel 20VU, make sure that the 3
OFF/NAV/ATT selector switches are at NAV.

(3) On the CAPT and F/O main instrument panels, on the PFDs:
- make sure that the altitude and airspeed data come into view.

4. Procedure
_________

Subtask 34-13-00-710-050

A. BITE Test of the AIR DATA Switching Function

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the ADIRS CDU:

- push the ADR1 pushbutton On the ADIRS CDU, the OFF legend of the
switch. ADR1 pushbutton switch comes on
On the CAPT PFD, the speed and altitude
indications go out of view (ignore the
related flag warnings).

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
2. On the center pedestal, on the On the CAPT PFD:
SWITCHING panel 8VU:

- set the AIR DATA selector - the speed and altitude indications
switch to CAPT/3 from the ADR3 come into view.

- set the AIR DATA selector - the speed and altitude indications go
switch to NORM. out of view (ignore the related flag
warnings).

3. On the ADIRS CDU: On the ADIRS CDU, the OFF legend of the
- push the ADR2 pushbutton ADR2 pushbutton switch comes on
switch. On the F/O PFD, the speed and altitude
indications go out of view (ignore the
related flag warnings).

4. On the center pedestal, on the On the F/O PFD:

SWITCHING panel 8VU:

- set the AIR DATA selector - the speed and altitude indications
switch to F/O/3 from the ADR3 come into view

- set the AIR DATA selector - the speed and altitude indications go
switch to NORM. out of view (ignore the related flag
warnings).

5. On the ADIRS CDU:

- push the ADR1 and ADR2 On the ADIRS CDU, the OFF legend of the
pushbutton switches again ADR1 and ADR2 pushbutton switches goes
off
On the CAPT and F/O PFDs, the speed and
altitude indications come into view.

- set the three OFF/NAV/ATT

selector switches to OFF.

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 5. Close-up
________

Subtask 34-13-00-860-058

A. Put the aircraft back to its initial configuration.

(1) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002)

(2) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-

002).

Subtask 34-13-00-410-057

B. Close Access

(1) Install the protective cover on the battery power center 105VU.

(2) Tighten the two screws.

(3) Close the access door 822.

(4) Remove the access platform(s).

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 TASK 34-13-00-710-002

Operational Test of the VMO/MMO Overspeed Warnings

WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE
_______
YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.

1. __________________
Reason for the Job

Refer to the MPD TASK: 341300-01

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific circuit breaker(s) safety clip(s)

No specific access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
31-32-00-860-010 Procedure to Get Access to the SYSTEM REPORT/TEST NAV
Page
31-60-00-860-001 EIS Start Procedure
31-60-00-860-002 EIS Stop Procedure
34-10-00-860-002 ADIRS Start Procedure
34-10-00-860-005 ADIRS Stop Procedure
34-13-00-740-002 INTERFACE TEST of the ADR

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 3. __________
Job Set-up

Subtask 34-13-00-010-052

A. Get Access

(1) Put the access platform in position at the access door 822.

(2) Open the access door 822.

(3) On the battery power center 105VU:

- loosen the two screws and remove the protective cover.

Subtask 34-13-00-860-059

B. Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002).

Subtask 34-13-00-865-064

C. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU L/G/LGCIU/SYS1/NORM 1GA C09
121VU HYDRAULIC/LGCIU/SYS2 2GA Q35
121VU HYDRAULIC/LGCIU/SYS1/GRND SPLY 52GA Q34

Subtask 34-13-00-865-069

D. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU AUTO FLT/FAC1/28VDC 5CC1 B04
105VU ELEC/CSM/G /EV AUTO/SPLY 7XE C01
121VU AUTO FLT/FAC2/28VDC 5CC2 M19

Subtask 34-13-00-860-061

E. Aircraft Maintenance Configuration

(1) Do the EIS start procedure (Ref. TASK 31-60-00-860-001).

(2) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002).

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 (3) On the center pedestal, on one MCDU, get the SYSTEM REPORT/TEST/NAV
page (Ref. TASK 31-32-00-860-010).

(4) On the overhead panel :

- on the FLT CTL panels 23VU and 24VU, make sure that the FAC, ELAC
and SEC pushbutton switches are not pushed (in). The OFF legends
are on.
- on the ELEC panel 35VU, make sure that the battery voltage is
correct, between 26VDC and 30VDC.

(5) Make sure that the L/G doors are closed and the slats/flaps are fully
retracted.

4. Procedure
_________

Subtask 34-13-00-710-051

A. OVERSPEED Warning VMO/MMO 1 (L/G DOWN VMO/MMO SELECTION Switch 22FP at

NORM)

NOTE : This test is for the VMO/MMO overspeed warning only. Ignore the
____
warnings and indications (VLE, ...) which are not related to this
test.

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the overhead panel, on the

ADIRS CDU:

- set the three OFF/NAV/ATT - the OFF legend of the three ADR
selector switches to NAV. pushbutton switches must be off.

- push the ADR2 and ADR3 - the OFF legend of the ADR2 and ADR3
pushbutton switches. pushbutton switches comes on.

2. On the MCDU: On the MCDU:

- push the line key adjacent to - the ADR1 page comes into view.
the ADR1 indication.

- push the line key adjacent to - the ADR1 OUTPUT TESTS page comes into
the OUTPUT TESTS indication. view.

- push the line key adjacent to - the ADR1 INTERFACE TEST 1/2 page
the INTERFACE TEST indication. comes into view.

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
- on the keyboard push the NEXT - the ADR1 INTERFACE TEST 2/2 page
PAGE function key. comes into view.

- push the line key adjacent to From 0 to 10 seconds, ignore the

the START TEST indication. warnings and indications.
From 10 seconds and more, on the
CAPT(F/O) PFD, the speed increases to
367.7 Kts. When the value is 354 Kts:
- on the upper ECAM display unit, this
indication is shown:
OVERSPEED
VMO/MMO 350/.82
- On the panels 130VU and 131VU, the
MASTER WARN lights flash.
- You can hear the continuous
repetitive chime aural warning.

- push the line key adjacent to The test procedure stops.

the RETURN indication. The warnings above stop.

- push the line key adjacent to The SYSTEM REPORT/TEST/NAV page comes
the RETURN indication. into view.

3. On the ADIRS CDU:

- push the ADR2 pushbutton - the OFF legend of the ADR2 pushbutton
switch. switch goes off.

- push the ADR1 pushbutton - the OFF legend of the ADR1 pushbutton
switch. switch comes on.

4. On the MCDU:

- push the line key adjacent to Same results on the F/O PFD.
the ADR2 indication.
Do the same test as specified
in the para 2 and 3.

5. On the ADIRS CDU:

- push the ADR3 pushbutton On the ADIRS CDU, the OFF legend of the
switch. ADR3 pushbutton switch goes off.

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
6. On the SWITCHING panel 8VU: On the CAPT PFD, the speed and altitude
- set the AIR DATA selector indications from the ADR3 come into
switch to CAPT/3. view.

7. On the ADIRS CDU:

- push the ADR2 pushbutton On the ADIRS CDU, the OFF legend of the
switch. ADR2 pushbutton switch comes on.

8. On the MCDU:

- push the line key adjacent to Same results on the CAPT PFD.
the ADR3 indication.
Do the same test as specified
in the para 2 and 3.

9. On the ADIRS CDU:

- push the ADR1 and ADR2 On the ADIRS CDU, the OFF legend of the
pushbutton switches ADR1 and ADR2 pushbutton switches goes
off.

- set the three OFF/NAV/ATT

selector switches to OFF.

10. On the SWITCHING panel 8VU:

- set the AIR DATA selector
switch to NORM.

Subtask 34-13-00-710-052

B. OVERSPEED Warning VMO/MMO 2 (L/G DOWN VMO/MMO SELECTION Switch 22FP at

L/G DOWN)

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. In the avionics compartment, on

the panel 188VU:
- remove the lockwire from the
safety cover of the L/G DOWN
VMO/MMO SELECTION switch.
- set the switch to L/G DOWN.

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
2. In the cockpit on the overhead On the ADIRS CDU:
panel, on the ADIRS CDU:

- set the three OFF/NAV/ATT - the OFF legend of the ADR pushbutton
selector switches to NAV. switches must be off.

- push the ADR2 and ADR3 - the OFF legend of the ADR2 and ADR3
pushbutton switches. pushbutton switches comes on.

3. On the MCDU: On the MCDU:

- push the line key adjacent to - the ADR1 page comes into view.
the ADR1 indication.

- push the line key adjacent to - the ADR1 OUTPUT TESTS page comes into
the OUTPUT TESTS indication. view.

- push the line key adjacent to - the ADR1 INTERFACE TEST 1/2 page
the INTERFACE TEST indication. comes into view.

- on the keyboard push the NEXT - the ADR1 INTERFACE TEST 2/2 page
PAGE function key. comes into view.

- push the line key adjacent to From 0 to 10 seconds, ignore the

the START TEST indication. warnings and indications.
(Ref. TASK 34-13-00-740-002). From 10 seconds and more, on the
CAPT(F/O) PFD, the speed increases to
367.7 Kts. When the value is 239Kts:
- on the upper ECAM display unit, this
indication is shown:
OVERSPEED
VMO/MMO 235/.60
- on the panels 130VU and 131VU, the
MASTER WARN lights flash.
- you can hear the continuous
repetitive chime aural warning.

- push the line key adjacent to The test procedure stops.

the RETURN indication. The warnings above stop.

- push the line key adjacent to The SYSTEM REPORT/TEST/NAV page comes
the RETURN indication. into view.

4. On the ADIRS CDU: On the ADIRS CDU:

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
- push the ADR2 pushbutton switch - the OFF legend of the ADR2 pushbutton
switch goes off.

- push the ADR1 pushbutton - the OFF legend of the ADR1 pushbutton
switch. switch comes on.

5. On the MCDU:

- push the line key adjacent to Same results on the F/O PFD.
the ADR2 indication.
Do the same test as specified
in the para 3 and 4.

6. On the ADIRS CDU:

- push the ADR3 pushbutton On the ADIRS CDU, the OFF legend of the
switch. ADR3 pushbutton switch goes off.

7. On the SWITCHING panel 8VU: On the CAPT PFD, the speed and altitude
- set the AIR DATA selector indications from the ADR3 come into
switch to CAPT/3. view.

8. On the ADIRS CDU:

- push the ADR2 pushbutton On the ADIRS CDU, the OFF legend of the
switch. ADR2 pushbutton switch comes on.

9. On the MCDU:

- push the line key adjacent to Same results on the CAPT PFD.
the ADR3 indication.
Do the same test as specified
in the para 3 and 4.

10. ON the ADIRS CDU:

- push the ADR1 and ADR2 On the ADIRS CDU, the OFF legend of the
pushbutton switches. ADR1 and ADR2 pushbutton switches goes
off.

- set the three OFF/NAV/ATT

selector switches to OFF.

11. On the SWITCHING panel 8VU:

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
- set the AIR DATA selector
switch to NORM.

12. In the avionics compartment, on

the panel 188VU:
- set the L/G DOWN VMO/MMO
SELECTION switch to NORM.
- lock the safety cover and
secure it with lockwire.

5. Close-up
________

Subtask 34-13-00-860-062

A. Put the aircraft back to its initial configuration.

(1) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005).

(2) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002).

(3) On the MCDU, push the line key adjacent to the RETURN indication
until the CFDS menu page comes into view.

Subtask 34-13-00-865-065

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
7XE, 5CC1, 5CC2

Subtask 34-13-00-860-060

C. De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

Subtask 34-13-00-410-052

D. Close Access

(1) Make sure that the work area is clean and clear of tool(s) and other
items.

(2) Install the protective cover on the battery power center 105VU.

(3) Tighten the two screws.

(4) Close the access door 822.

(5) Remove the access platform(s).

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 TASK 34-13-00-710-003

Operational Test of the ALT Comparison Warning

WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE
_______
YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.

1. __________________
Reason for the Job

Refer to the MPD TASK: 341300-04

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific circuit breaker(s) safety clip(s)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
31-32-00-860-010 Procedure to Get Access to the SYSTEM REPORT/TEST NAV
Page
31-60-00-860-001 EIS Start Procedure
31-60-00-860-002 EIS Stop Procedure
34-10-00-860-002 ADIRS Start Procedure
34-10-00-860-005 ADIRS Stop Procedure

3. __________
Job Set-up

Subtask 34-13-00-860-063

A. Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002).

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 Subtask 34-13-00-865-066

B. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
R 49VU L/G/LGCIU/SYS1/NORM 1GA C09
121VU HYDRAULIC/LGCIU/SYS2 2GA Q35
121VU HYDRAULIC/LGCIU/SYS1/GRND SPLY 52GA Q34

Subtask 34-13-00-865-071

C. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU AUTO FLT/FAC1/28VDC 5CC1 B04
121VU AUTO FLT/FAC2/28VDC 5CC2 M19

Subtask 34-13-00-860-065

D. Aircraft Maintenance Configuration

(1) Do the EIS start procedure (Ref. TASK 31-60-00-860-001).

(2) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002).

(3) When the circuit breakers 5CC1 and 5CC2 are open:
- - the WAUTO FLT FAC 1+2 FAULTW message and the MASTER CAUT light
come on
- - you can hear the single chime.

(4) Before the test, on the ECAM Control Panel, push the CLR key to clear
the message.

(5) On the glareshield 13VU, on the CAPT and F/O EFIS control sections of
the FCU, set the mode selector switch to ROSE/NAV.

(6) On the center pedestal, on one MCDU, get the SYSTEM REPORT/TEST/NAV
menu page.
(Ref. TASK 31-32-00-860-010).

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 4. Procedure
_________

Subtask 34-13-00-710-053

A. Operational Test of the ALT Comparison Warning

NOTE : This test is for the system 1. For the systems 2 and 3, use the
____
indications between parentheses.

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the glareshield 13VU, on the

CAPT and F/O EFIS control
sections of the FCU:

- pull the baro reference The baro display (above the baro
selector knob. reference selector knob) shows STD.
The CAPT and F/O PFDs show the altitude
related to the standard barometric
pressure.
Below this indication the PFDs show
STD.

2. On the MCDU: On the MCDU:

- push the line key adjacent to - the ADR1 (ADR2) (ADR3) page comes
the ADR1 (ADR2) (ADR3) into view.
indication.

NOTE : When you test the ADR3 ,

____
set the AIR DATA selector
switch 15FP, on the
SWITCHING panel 8VU, to
CAPT/3.

- push the line key adjacent to - the ADR1 (ADR2) (ADR3) OUTPUT TESTS
the OUTPUT TESTS indication. page comes into view.

- push the line key adjacent to - the ADR1 (ADR2) (ADR3) SLEW TESTS
the SLEW TESTS indication. page comes into view.

- push the line key adjacent to - the ADR1 (ADR2) (ADR3) ALT DYNAMIC
the ALT DYNAMIC SLEW SLEW page comes into view.
indication.

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
R - on the keyboard, enter: - the display shows:
R *the airfield altitude value / *the airfield altitude value /
R (airfield altitude value plus (airfield altitude value plus 1500)
R 1500)
R *(Example: for an airfield
R altitude value of 1800ft enter:
R 1800 / 3300).
R and push the line key adjacent
R to the ALT LIMITS (FT)
R indication.
R

- on the keyboard, enter 1000 and - the display shows 1000.

push the line key adjacent to
the ALT SLEW RATE (FT/MIN)
indication.

- push the line key adjacent to The test starts:

the UP (START SLEW) indication.
NOTE : For the ADR3 test, the CAPT PFD
____
shows the ADR3 indications.

- the ADR1 ALT DYNAMIC SLEW TEST page

with SLEWING IN PROGRESS 90 S
information comes into view.
R - On the CAPT (F/O) PFD the altitude
R increase.
When the difference of altitude between
the CAPT PFD and the F/O PFD is 650 ft
approximately:
- the vertical CHECK ALT indication
comes into view on the two PFDs.
- the upper ECAM DU shows this warning:
NAV ALTI DISCREPANCY
- on the glareshield panels 130VU and
131VU, the MASTER CAUT light comes
on.
- you can hear the single chime.
On the MCDU:
- at the end of the test, the END OF
SLEWING indication comes into view.

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
- push the line key adjacent to
the RETURN indication until the
CFDS menu page comes into view.

NOTE : After the ADR3 test, set

____
the AIR DATA selector
switch 15FP to NORMAL.

5. Close-up
________

Subtask 34-13-00-860-066

A. Put the aircraft back to its initial configuration.

(1) On the CAPT and F/O EFIS control sections of the FCU, push the baro
reference selector knob.

(2) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005).

(3) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002).

Subtask 34-13-00-865-072

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
5CC1, 5CC2

Subtask 34-13-00-860-064

C. Close Access

(1) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

(2) Make sure that the work area is clean and clear of tool(s) and other
items.

(3) Put the aircraft back to the serviceable condition.

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 TASK 34-13-00-710-004

Operational Test of the ALT DYNAMIC SLEW TEST

WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE
_______
YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.

1. __________________
Reason for the Job

This test simulates a change in altitude.

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific circuit breaker(s) safety clip(s)

No specific access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
31-32-00-860-010 Procedure to Get Access to the SYSTEM REPORT/TEST NAV
Page
34-10-00-860-002 ADIRS Start Procedure
34-10-00-860-005 ADIRS Stop Procedure

3. __________
Job Set-up

Subtask 34-13-00-860-067

A. Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002).

Subtask 34-13-00-010-058

B. Get Access

(1) Put the access platform in position at the access door 822.

(2) Open the access door 822

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 (3) On the battery power center 105VU:
- loosen the two screws and remove the protective cover

Subtask 34-13-00-865-067

C. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV PROBES/ADIRU3/PWR/SWTG 8FP F09
49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07
49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06
105VU ADIRS/ADIRU1/28VDC 6FP1 C02

R **ON A/C 001-004,

121VU ADIRS/ADIRU/2PWR/SHED 10FP N11

121VU ADIRS/ADIRU/3PWR/SWTG 9FP N10
121VU ADIRS/ADIRU/2/26VAC AND AOA 5FP2 N09
121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N08
121VU ADIRS/ADIRU/2/115VAC 4FP2 N07
121VU ADIRS/ADIRU/3/115VAC 4FP3 N06
121VU ADIRS/ADIRU/2/28VDC 6FP2 N05
121VU ADIRS/ADIRU/3/28VDC 6FP3 N04

R **ON A/C 005-099,

R 121VU ADIRS/ADIRU/2PWR/SHED 10FP N10

R 121VU ADIRS/ADIRU/3PWR/SWTG 9FP N09
R 121VU ADIRS/ADIRU/2/26VAC AND AOA 5FP2 N08
R 121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N07
R 121VU ADIRS/ADIRU/2/115VAC 4FP2 N06
R 121VU ADIRS/ADIRU/3/115VAC 4FP3 N05
R 121VU ADIRS/ADIRU/2/28VDC 6FP2 N04
R 121VU ADIRS/ADIRU/3/28VDC 6FP3 N03

R **ON A/C ALL

Subtask 34-13-00-865-073

D. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU AUTO FLT/FAC1/28VDC 5CC1 B04
121VU AUTO FLT/FAC2/28VDC 5CC2 M19

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 Subtask 34-13-00-860-069

E. Aircraft Maintenance Configuration

(1) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002).

(2) On the center pedestal, on one MCDU, get the SYSTEM REPORT/TEST/NAV
page
(Ref. TASK 31-32-00-860-010).

4. Procedure
_________

Subtask 34-13-00-710-054

A. Operational Test of the ALT DYNAMIC SLEW TEST

NOTE : This test is for the system 1. For the other system(s), use the
____
indications between the parentheses.

NOTE : This test is an example of the altitude ramp test. Ignore the
____
warnings which are the result of a difference in altitude between
the CAPT and F/O PFD.

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the glareshield 13VU, on the

CAPT and F/O EFIS control
sections of the FCU:

- pull the baro reference the baro display (above the baro
selector knob. reference selector knob) shows STD.
the CAPT and F/O PFDs show the altitude
related to the standard barometric
pressure and the STD indication.

2. On the MCDU: On the MCDU:

- push the line key adjacent to - the ADR1 (ADR2) (ADR3) page comes
the ADR1 (ADR2) (ADR3) into view.
indication.

- push the line key adjacent to - the ADR1 (ADR2) (ADR3) OUTPUT TESTS
the OUTPUT TESTS indication. page comes into view.

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
- push the line key adjacent to - the ADR1 (ADR2) (ADR3) SLEW TESTS
the SLEW TESTS indication. page comes into view.

- push the line key adjacent to - the ADR1 (ADR2) (ADR3) ALT DYNAMIC
the ALT DYNAMIC SLEW SLEW page comes into view.
indication.

- on the keyboard, enter 0/1500 - the display shows 0/1500.

and push the line key adjacent
to the ALT LIMITS (FT)
indication.

- on the keyboard, enter 1000 and - the display shows 1000.

push the line key adjacent to
the ALT SLEW RATE (FT/MIN)
indication.

- push the line key adjacent to The test starts:

the UP (START SLEW) indication. - the CAPT (F/O) PFD shows 0 ft and the
altitude increases to 1500 ft in
approximately 90 seconds.

5. Close-up
________

Subtask 34-13-00-410-058

A. Close Access

(1) Install the protective cover on the battery power center 105VU.

(2) Tighten the two screws.

(3) Close the access door 822.

(4) Remove the access platform(s).

Subtask 34-13-00-865-074

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
5CC1, 5CC2

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 Subtask 34-13-00-860-068

C. Put the aircraft back to its initial configuration.

(1) On the MCDU, push the line key adjacent to the RETURN indication
until the CFDS menu page comes into view.

(2) On the CAPT and F/O EFIS control sections of the FCU, push the baro
reference selector knob.

(3) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005).

(4) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

(5) Make sure that the work area is clean and clear of tool(s) and other
items.

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 TASK 34-13-00-710-005

Operational Test of the CAS DYNAMIC SLEW TEST

WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE
_______
YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.

1. __________________
Reason for the Job

This test simulates a change in airspeed.

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific circuit breaker(s) safety clip(s)

R No specific safety barriers
No specific access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
31-32-00-860-010 Procedure to Get Access to the SYSTEM REPORT/TEST NAV
Page
34-10-00-860-002 ADIRS Start Procedure
34-10-00-860-005 ADIRS Stop Procedure

3. __________
Job Set-up

Subtask 34-13-00-860-070

A. Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002).

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 Subtask 34-13-00-010-059

B. Get Access

(1) Put the access platform in position at the access door 822.

(2) Open the access door 822

(3) On the battery power center 105VU:

- loosen the two screws and remove the protective cover

Subtask 34-13-00-865-068

C. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV PROBES/ADIRU3/PWR/SWTG 8FP F09
49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07
49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06
105VU ADIRS/ADIRU1/28VDC 6FP1 C02

R **ON A/C 001-004,

121VU ADIRS/ADIRU/2PWR/SHED 10FP N11

121VU ADIRS/ADIRU/3PWR/SWTG 9FP N10
121VU ADIRS/ADIRU/2/26VAC AND AOA 5FP2 N09
121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N08
121VU ADIRS/ADIRU/2/115VAC 4FP2 N07
121VU ADIRS/ADIRU/3/115VAC 4FP3 N06
121VU ADIRS/ADIRU/2/28VDC 6FP2 N05
121VU ADIRS/ADIRU/3/28VDC 6FP3 N04

R **ON A/C 005-099,

R 121VU ADIRS/ADIRU/2PWR/SHED 10FP N10

R 121VU ADIRS/ADIRU/3PWR/SWTG 9FP N09
R 121VU ADIRS/ADIRU/2/26VAC AND AOA 5FP2 N08
R 121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N07
R 121VU ADIRS/ADIRU/2/115VAC 4FP2 N06
R 121VU ADIRS/ADIRU/3/115VAC 4FP3 N05
R 121VU ADIRS/ADIRU/2/28VDC 6FP2 N04
R 121VU ADIRS/ADIRU/3/28VDC 6FP3 N03

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R **ON A/C ALL

Subtask 34-13-00-865-075

D. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU AUTO FLT/FAC1/28VDC 5CC1 B04
105VU ELEC/CSM/G /EV AUTO/SPLY 7XE C01
121VU AUTO FLT/FAC2/28VDC 5CC2 M19

Subtask 34-13-00-860-072

E. Aircraft Maintenance Configuration

(1) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002).

(2) on the center pedestal, on the MCDU, get the SYSTEM REPORT/TEST/NAV
page
(Ref. TASK 31-32-00-860-010).

(3) Put the safety barriers in position around the RAT area.

4. Procedure
_________

Subtask 34-13-00-710-055

A. Operational Test of the CAS DYNAMIC SLEW TEST

NOTE : This test is for the system 1. For the other system(s), use the
____
indications between the parentheses.

NOTE : This test is an example of the CAS ramp test. Ignore the warnings
____
which are the result of an overspeed.

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On one MCDU: On the MCDU:

- push the line key adjacent to - the ADR1 (ADR2) (ADR3) page comes
the ADR1 (ADR2) (ADR3) into view.
indication.

- push the line key adjacent to - the ADR1 (ADR2) (ADR3) OUTPUT TESTS
OUTPUT TESTS indication. page comes into view.

- push the line key adjacent to - the ADR1 (ADR2) (ADR3) SLEW TESTS
SLEW TESTS indication. page comes into view.

- push the line key adjacent to - the ADR1 (ADR2) (ADR3) CAS DYNAMIC
the CAS DYNAMIC SLEW SLEW page comes into view.
indication.

- on the keyboard, enter these - the slew limits set come into view
limits: 175/225 and push the below the related indication.
line key adjacent to the CAS
LIMITS (FT) indication.

- on the keyboard, enter this - the slew rate comes into view below
slew rate: 0020 and push the the related indication.
line key adjacent to the CAS
SLEW RATE (FT/MIN) indication.

- push the line key adjacent to On the CAPT and F/O PFDs:
the UP-START SLEW indication. - the speed scale moves from 175 Kts to
225 Kts.
The warnings above stop.

5. Close-up
________

Subtask 34-13-00-410-059

A. Close Access

(1) Install the protective cover on the battery power center 105VU.

(2) Tighten the two screws.

(3) Close the access door 822.

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 (4) Remove the access platform(s).

Subtask 34-13-00-865-076

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
5CC1, 5CC2, 7XE

Subtask 34-13-00-860-071

C. Put the aircraft back to its initial configuration.

(1) On the MCDU, push the line key adjacent to the RETURN indication
until the CFDS menu page comes into view.

(2) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005).

(3) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

(4) Make sure that the work area is clean and clear of tool(s) and other
items.

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 TASK 34-13-00-710-006

Operational Test of the AOA SENSOR TEST

WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE
_______
YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.

1. __________________
Reason for the Job

This test controls the angle of attack (AOA) sensors to the special test
position.

2. ______________________
Job Set-up Information

A. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

34-10-00-710-007 Test of the Angle of Attack Warning

3. __________
Job Set-up

Subtask 34-13-00-860-073

A. Not Applicable

4. Procedure
_________

Subtask 34-13-00-710-060

A. Refer to the operational test of the angle of attack warning.

(Ref. TASK 34-10-00-710-007)

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 TASK 34-13-00-710-007

Operational Test of the Overspeed Warnings in the Slats/Flaps and Landing Gear
Extended (VFE/VLE) Configuration

NOTE : This test is for the system 1. For the systems 2 and 3, use the
____
indications between parentheses.

1. __________________
Reason for the Job

Refer to the MPD TASK: 341300-03

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific circuit breaker(s) safety clip(s)

No specific access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
29-10-00-863-001 Pressurize the Green Hydraulic System
29-10-00-863-002 Pressurize the Yellow Hydraulic System
29-10-00-863-003 Pressurize the Blue Hydraulic System with a Ground
Power Supply
29-10-00-864-001 Depressurize the Green Hydraulic System
29-10-00-864-002 Depressurize the Yellow Hydraulic System
29-10-00-864-003 Depressurize the Blue Hydraulic System
31-32-00-860-010 Procedure to Get Access to the SYSTEM REPORT/TEST NAV
Page
31-60-00-860-001 EIS Start Procedure
31-60-00-860-002 EIS Stop Procedure
32-22-00-010-001 Nose Gear Doors - Ground Doors Opening
32-22-00-410-001 Nose Gear Doors - Ground Doors Closing

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 3. __________
Job Set-up

Subtask 34-13-00-860-050

A. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-

002).

(2) Make sure that the nose landing gear doors are closed
(Ref. TASK 32-22-00-410-001).

(3) Pressurize the aircraft hydraulic systems

(Ref. TASK 29-10-00-863-001)
(Ref. TASK 29-10-00-863-002)
(Ref. TASK 29-10-00-863-003) (NOTE : You can use the electric pumps).

Subtask 34-13-00-860-052

B. Aircraft Maintenance Configuration

(1) Do the EIS start procedure (Ref. TASK 31-60-00-860-001).

(2) On the center pedestal, on one MCDU, get the SYSTEM REPORT/TEST/NAV
page
(Ref. TASK 31-32-00-860-010).

(3) On the overhead panel, on the FLT CTL panels 23VU and 24VU:
- make sure that the FAC, ELAC and SEC pushbutton switches are not
pushed (in). The OFF legends are on.

(4) On the center pedestal (panel 114VU), set the flap and slat control
lever to the FULL position.

(5) On the panel 50VU, release the ENG/FADEC GND PWR/1 and ENG/FADEC GND
PWR/2 pushbutton switches. The ON legends come on.

Subtask 34-13-00-010-060

C. Get Access

(1) Put the access platform in position at the access door 822.

(2) Open the access door 822

(3) On the battery power center 105VU:

- loosen the two screws and remove the protective cover

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 Subtask 34-13-00-865-082

D. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU L/G/LGCIU/SYS1/NORM 1GA C09
49VU NAV PROBES/ADIRU3/PWR/SWTG 8FP F09
49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07
49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06
105VU ADIRS/ADIRU1/28VDC 6FP1 C02

R **ON A/C 001-004,

121VU ADIRS/ADIRU/2PWR/SHED 10FP N11

121VU ADIRS/ADIRU/3PWR/SWTG 9FP N10
121VU ADIRS/ADIRU/2/26VAC AND AOA 5FP2 N09
121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N08
121VU ADIRS/ADIRU/2/115VAC 4FP2 N07
121VU ADIRS/ADIRU/3/115VAC 4FP3 N06
121VU ADIRS/ADIRU/2/28VDC 6FP2 N05
121VU ADIRS/ADIRU/3/28VDC 6FP3 N04

R **ON A/C ALL

121VU HYDRAULIC/LGCIU/SYS2 2GA Q35

R **ON A/C 005-099,

R 121VU ADIRS/ADIRU/2PWR/SHED 10FP N10

R 121VU ADIRS/ADIRU/3PWR/SWTG 9FP N09
R 121VU ADIRS/ADIRU/2/26VAC AND AOA 5FP2 N08
R 121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N07
R 121VU ADIRS/ADIRU/2/115VAC 4FP2 N06
R 121VU ADIRS/ADIRU/3/115VAC 4FP3 N05
R 121VU ADIRS/ADIRU/2/28VDC 6FP2 N04
R 121VU ADIRS/ADIRU/3/28VDC 6FP3 N03

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R **ON A/C ALL

Subtask 34-13-00-865-085

E. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU AUTO FLT/FAC1/28VDC 5CC1 B04
105VU ELEC/CSM/G /EV AUTO/SPLY 7XE C01
121VU AUTO FLT/FAC2/28VDC 5CC2 M19

Subtask 34-13-00-860-090

F. Aircraft Maintenance Configuration

(1) On the center pedestal, on the ECAM control panel:

- push the CLR key until the MASTER CAUT and MASTER WARN lights go
off on the panels 131VU and 130VU.
- push the CLR key until the memo section comes into view in the
lower part of the upper ECAM display unit.

4. Procedure
_________

Subtask 34-13-00-710-057

A. Test of the VFE Overspeed Warning

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the overhead panel 20VU, on

the ADIRS CDU:
- set the three OFF/NAV/ATT
selector switches to NAV

- push the ADR2 and ADR3 On the ADIRS CDU, the OFF legend of the
pushbutton switches. ADR2 and ADR3 pushbutton switches comes
on.

2. On the MCDU: On the MCDU:

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
- push the line key adjacent to - the SYSTEM REPORT/TEST page which
the NAV indication contains the three ADR comes into
view.

- push the line key adjacent to - the ADR1 (ADR2) (ADR3) page comes
the ADR1 (ADR2) (ADR3) into view.
indication

- push the line key adjacent to - the ADR1 (ADR2) (ADR3) OUTPUT TESTS
the OUTPUT TESTS indication page comes into view.

- push the line key adjacent to - the ADR1 (ADR2) (ADR3) SLEW TESTS
the SLEW TESTS indication page comes into view.

- push the line key adjacent to - the ADR1 (ADR2) (ADR3) CAS DYNAMIC
the CAS DYNAMIC SLEW indication SLEW page comes into view.

- on the keyboard, enter these

limits: 175/260

- push the line key adjacent to The slew limits set come into view
the CAS LIMITS (KT) indication below the related indication.

R - on the keyboard, enter this

R slew rate: 020

- push the line key adjacent to The slew rate set comes into view below
the CAS SLEW RATE (KTs/MIN) the related indication.
indication

- push the line key adjacent to On the CAPT (F/O) PFD, the speed scale
the UP-START SLEW indication moves from 175 kts to 260 kts as
specified in the following table
On the upper ECAM display unit, make
sure that all the indications given in
the table below come into view
On the panels 130VU and 131VU, the
MASTER WARN lights flash when the
speeds set come into view
The continuous repetitive chime sounds
On the panels 130VU and 131VU, the
MASTER WARN lights go off when you set
the flap and slat control lever to a
lower position.

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 Subtask 34-13-00-710-061

B. Speed values

NOTE : Make sure that speed values are reached before you move the
____
flaps/slats control lever.

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 -------------------------------------------------------------------------------
| SLATS AND FLAPS |
|---------------------------------|
| | |
SPEED | Position | Indication | INDICATION
IS MORE | of CTL LEVER | on the upper | ON THE UPPER ECAM
THAN | | ECAM DU | DISPLAY UNIT
| | |
---------|----------------|----------------|-----------------------------------
181 Kts | FULL | FULL | OVERSPEED
| | | - VFE 177
|----------------|----------------|-----------------------------------
| 3 | 3 | The indication goes out of view
---------|----------------|----------------|-----------------------------------
189 Kts | 3 | 3 | OVERSPEED
| | | - VFE 185
|----------------|----------------|-----------------------------------
| 2 | 2 | The indication goes out of view
---------|----------------|----------------|-----------------------------------
204 Kts | 2 | 2 | OVERSPEED
| | | - VFE 200
|----------------|----------------|-----------------------------------
| 1 | 1+F | The indication goes out of view
---------|----------------|----------------|-----------------------------------
219 Kts | 1 | 1+F | OVERSPEED
| | | - VFE 215
---------|----------------|----------------|-----------------------------------
234 Kts | 1 | 1+F | OVERSPEED
(or equal) | | - VFE 215
|----------------|----------------|-----------------------------------
| | | When OVERSPEED
| 0 | 0 | - VFE 215
| | | indication goes out of view:
| | | OVERSPEED
| | | - VFE 230
R | | |this indication can come into view
R | | |for some seconds then goes out of
R | | |view.
R
-------------------------------------------------------------------------------

Subtask 34-13-00-860-053

C. Depressurize the aircraft hydraulic systems (Ref. TASK 29-10-00-864-001)

(Ref. TASK 29-10-00-864-002) (Ref. TASK 29-10-00-864-003).

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 Subtask 34-13-00-710-059

D. Test of the VLE Overspeed Warning

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. Open the nose landing gear doors

(Ref. TASK 32-22-00-010-001).

2. On the overhead panel 20VU, on

the ADIRS CDU:
- set the three OFF/NAV/ATT
selector switches to NAV

- push the ADR2 and ADR3 On the ADIRS CDU, the OFF legend of the
pushbutton switches. ADR2 and ADR3 pushbutton switches comes
on.

3. On the MCDU: On the MCDU:

- push the line key adjacent to - the ADR1 (ADR2) (ADR3) page comes
the ADR1 (ADR2) (ADR3) into view.
indication

- push the line key adjacent to - the ADR1 (ADR2) (ADR3) OUTPUT TESTS
the OUTPUT TESTS indication page comes into view.

- push the line key adjacent to - the ADR1 (ADR2) (ADR3) SLEW TESTS
the SLEW TESTS indication page comes into view.

- push the line key adjacent to - the ADR1 (ADR2) (ADR3) CAS DYNAMIC
the CAS DYNAMIC SLEW indication SLEW page comes into view.

- on the keyboard, enter these - the slew limits come into view on the
limits: 275/290 bottom line (scratch pad) of the
MCDU.

- push the line key adjacent to - the slew limits set come into view
the CAS LIMITS (FT) indication. below the related indication.

- on the keyboard, enter this - the slew rate comes into view on the
slew rate: 025 bottom line (scratch pad) of the
MCDU.

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
- push the line key adjacent to - the slew rate set comes into view
the CAS SLEW RATE (FT/MIN) below the related indication.
indication.

- push the line key adjacent to On the CAPT (F/O) PFD, the speed scale
the UP-START SLEW indication moves from 275 kts to 290 kts.
On the upper ECAM display unit, when
the CAS reaches 284 kts, make sure that
this indication comes into view:
OVERSPEED
VLE...............280/.67
On the panels 130VU and 131VU, the
MASTER WARN lights flash
The continuous repetitive chime sounds.

- push the line key adjacent to On the CAPT (F/O) PFD, the speed scale
the RETURN/STOP indication. moves down
On the panels 130VU and 131VU, the
MASTER WARN lights do not flash
The continuous repetitive chime stops.

4. On the ADIRS CDU: On the ADIRS CDU:

- push the ADR1 and ADR2 - the OFF legend of the ADR1 pushbutton
pushbutton switches. switch comes on
- the OFF legend of the ADR2 pushbutton
switch goes off.

5. Do the ADR2 test as specified in Same results on the F/O side.

step 3.

6. On the ADIRS CDU: On the ADIRS CDU:

- push the ADR2 and ADR3 - the OFF legend of the ADR2 pushbutton
pushbutton switches. switch comes on
- the OFF legend of the ADR3 pushbutton
switch goes off.

7. On the SWITCHING panel 8VU: On the CAPT PFD, the speed and altitude
- set the AIR DATA selector indications from the ADR3 come into
switch to CAPT/3. view.

8. Do the ADR3 test as specified in Same results on the CAPT side.

the step 3.

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
9. On the ADIRS CDU:

- push the ADR1 and ADR2 On the ADIRS CDU, the OFF legend of the
pushbutton switches again ADR1 and ADR2 pushbutton switches goes
- set the three OFF/NAV/ATT off.
selector switches to OFF.

5. Close-up
________

Subtask 34-13-00-410-060

A. Close Access

(1) Install the protective cover on the battery power center 105VU.

(2) Tighten the two screws.

(3) Close the access door 822.

(4) Remove the access platform(s).

Subtask 34-13-00-865-083

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
5CC1, 5CC2, 7XE

Subtask 34-13-00-860-051

C. Put the aircraft back to its initial configuration.

(1) Do the EIS STOP procedure (Ref. TASK 31-60-00-860-002).

(2) On the MCDU, push the line key adjacent to the RETURN indication
until the CFDS menu page comes into view.

(3) De-energize the aircraft electrical circuit

(Ref. TASK 24-41-00-862-002).

(4) Close the nose landing gear doors (Ref. TASK 32-22-00-410-001).

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 TASK 34-13-00-720-009

Functional Test of the Altitude and Airspeed Data

CAUTION : OBEY THESE PRECAUTIONS WHEN YOU DO THE TEST TO PREVENT DAMAGE TO
_______
INSTRUMENTS:
- PRESSURE SET MUST NOT BE MORE THAN 1050 hPa (31 in Hg) OR LESS THAN
115 hPa (3.39 in Hg)
- CHANGES IN PRESSURE MUST NOT BE MORE THAN 6000 FEET/MINUTE
- DO NOT SUDDENLY OPEN LINES TO AMBIENT AIR WHILE THE PRESSURE
GENERATOR IS CONNECTED.

CAUTION : THE TOTAL PRESSURE IN THE PITOT SYSTEM MUST NEVER BE LESS THAN THE
_______
STATIC PRESSURE. THE DIFFERENCE BETWEEN THE PITOT AND THE STATIC
PRESSURE CIRCUITS MUST NEVER BE MORE THAN 368 hPa (10.86 in Hg).

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific circuit breaker(s) safety clip(s)

No specific colored adhesive tape
36122 1 ADAPTOR-CHARGING,PITOT PROBE
87202126V15 1 GENERATOR - GROUND PRESSURE
98D34003500000 1 ADAPTER COVER-STATIC PORT

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 B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
27-50-00-866-009 Retraction of the Flaps on the Ground
31-60-00-860-001 EIS Start Procedure
34-10-00-860-002 ADIRS Start Procedure
34-10-00-860-005 ADIRS Stop Procedure
34-11-15-200-001 Inspection/Check of the Pitot Probe (9DA1,9DA2,9DA3)

3. __________
Job Set-up

Subtask 34-13-00-860-054

A. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits

(Ref. TASK 24-41-00-861-002).

(2) Do the EIS start procedure (PFD DUs only) (Ref. TASK 31-60-00-860-
001).

(3) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002).

(4) On the SWITCHING panel 8VU, make sure that the AIR DATA selector
switch is at NORM.

(5) Make sure that the flaps are fully retracted (Ref. TASK 27-50-00-866-
009).

(6) On the FCU, set the CAPT (F/O) Baro-Correction to display STD below
the altitude scale on the CAPT (F/O) PFD .

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 Subtask 34-13-00-865-086

B. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU ANTI ICE/PROBES/PITOT/1 3DA1 D02
105VU ELEC/CSM/G /EV AUTO/SPLY 7XE C01
122VU ANTI ICE/PROBES/2/PITOT 3DA2 Y14
122VU ANTI ICE/PROBES/2/STATIC 5DA2 Y11
122VU ANTI ICE/PROBES/3/PITOT 3DA3 Z16
122VU ANTI ICE/PROBES/3/STATIC 5DA3 Z14
122VU ANTI ICE/PROBES/1/STATIC 5DA1 Z13

Subtask 34-13-00-480-050

C. Install the Ground Pressure Generator

(1) Remove the slip on covers from the static probes and the pitot
probes.

(2) Connect the GENERATOR - GROUND PRESSURE to the static and pitot
probes of the aircraft:

For CAPT circuit (ADIRU 1) and F/O circuit (ADIRU 2), connect the
ground pressure generator to the static probes with the ADAPTER
COVER-STATIC PORT (98D34003500102):
- L static probe 1 7DA1, zone 127, STA 8750, for the L static
pressure ADM (19FP5)
- L static probe 2 7DA2, zone 127, STA 8700, for the L static
pressure ADM (19FP7)
and
- R static probe 1 8DA1, zone 128, STA 9300, for the R static
pressure ADM (19FP4)
- R static probe 2 8DA2, zone 128, STA 9350, for the R static
pressure ADM (19FP6)
For the standby circuit (ADIRU 3), connect the ground pressure
generator to the static probes with the ADAPTER COVER-STATIC PORT
(98D34003500100):
- L static probe 3 7DA3, zone 121, STA 4250, for the static pressure
ADM (19FP8) or
- R static probe 3 8DA3, zone 122, STA 4250, for the static pressure
ADM (19FP8).

Connect the ground pressure generator to the pitot probes with the
ADAPTOR-CHARGING,PITOT PROBE or equivalent:

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 For CAPT circuit:
- pitot probe 1 9DA1, zone 125, for the L total pressure ADM (19FP1).

For F/O circuit:

- pitot probe 2 9DA2, zone 126, for the R total pressure ADM (19FP2).

For the standby circuit:

- pitot probe 3 9DA3, zone 125, for the standby total pressure ADM
(19FP3).

(3) Seal the Stby probes:

CAUTION : WHEN YOU SEAL THE DRAIN HOLE IN THE PITOT PROBE, DO NOT
_______
SEAL THE HOLE DIRECTLY WITH THE COLORED ADHESIVE TAPE.
ALWAYS PUT A PIECE OF PLASTIC ON THE HOLE AND USE THE TAPE
TO ATTACH THE PLASTIC.
IF YOU SEAL THE DRAIN HOLE DIRECTLY WITH THE ADHESIVE TAPE,
THERE IS A RISK THAT SOME OF THE ADHESIVE WILL STAY ON THE
HOLE AND COLLECT PARTICLES. THIS CAN SUBSEQUENTLY CAUSE
BLOCKAGE OF THE HOLE AND THUS INCORRECT OPERATION OF THE
PROBE.

(a) Seal the drain holes of the pitot probes with colored adhesive
tape.

(b) Seal the opposite static probe of the standby ADM with the
ADAPTER COVER-STATIC PORT (98D34003500103).

R (4) Move the vane of the three AOA sensors to the upper position. Keep
R the AOA sensors in position with colored adhesive tape.

(5) Start the ground pressure generator.

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 4. Procedure
_________

Subtask 34-13-00-720-061

A. Functional Test of the Altitude and Airspeed Data

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the ground pressure generator, On the CAPT and F/O PFDs, compare and
set a static pressure and a total write the altitude and airspeed values
pressure as given in the table for the ADIRU 1 and 2.
below.

2. On the SWITCHING panel 8VU:

- set the AIR DATA selector to On the CAPT and F/O PFDs, compare and
CAPT/3. write the altitude and airspeed values
for the ADIRU 3 and 2.

- set the AIR DATA selector to On the CAPT and F/O PFDs, compare and
F/O/3. write the altitude and airspeed values
for the ADIRU 1 and 3.

3. At the end of the test, on the

ground pressure generator:

- slowly balance the pressure in The rate of descent must not be more
the static and total pressure than 6000 ft/mn.
lines.
- open the lines to get the
atmospheric pressure.

4. Stop the pressure generator.

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 ------------------------------------------------------------------------------
Pressure | CAPT PFD and F/O PFD
generator | AIR DATA switch at |AIR DATA switch
| NORM |at CAPT/3 or F/O/3
------------------------------|-----------------------|------------------------
Ps | Pt | QC |Hp 1/2| Vc 1/2|Mach 1/2| Hp 3 | Vc 3| Mach 3
(ft)|(hpa)| (ft)|(hpa)|Pt-Ps | (ft) |(Kts) | | (ft) |(Kts) |
| | | | (hpa)| | +/- 2| | | +/-2 |
-----|-----|-----|-----|------|------|-------|--------|------|------|----------
5305|833.5| 1828|948 |114.5 |5000 | 250 | 0.413 | 5401 | 264 | 0.439
| | | | |+/-12 | |+/-0.004|+/- 12| |+/-0.004
-----|-----|-----|-----|------|------|-------|--------|------|------|----------
10335|687.8| 6335|801.8|114 |10000 | 250 | 0.452 | 10474| 264 | 0.481
| | | | |+/-15 | |+/-0.004|+/- 15| |+/-0.004
-----|-----|-----|-----|------|------|-------|--------|------|------|----------
20464|456.6|13011|619.2|162.6 |20000 | 300 | 0.651 | 21094| 319 | 0.704
| | | | |+/- 22| |+/-0.004|+/- 22| |+/-0.004
-----|-----|-----|-----|------|------|-------|--------|------|------|----------
30515|293.9|20579|454.4|160.5 |30000 | 300 | 0.790 | 31845| 322 | 0.873
| | | | |+/- 30| |+/-0.003|+/- 30| |+/-0.003
-----|-----|-----|-----|------|------|-------|--------|------|------|----------
40487|183.2|30618|292.5|109.3 |40000 | 250 | 0.823 | 41761| 267 | 0.903
| | | | |+/- 42| |+/-0.003|+/- 42| |+/-0.003
-------------------------------------------------------------------------------

5. Close-up
________

Subtask 34-13-00-080-050

A. Remove the ground support and maintenance equipment, the special and
standard tools and all other items.
R Make sure that there is no remaining piece of plastic and/or adhesive
R tape on the pitot probes and AOA sensors. Make sure the pitot drain holes
R are operational and that the AOA sensors move freely.

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 Subtask 34-13-00-865-088

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU ANTI ICE/PROBES/PITOT/1 3DA1 D02
105VU ELEC/CSM/G /EV AUTO/SPLY 7XE C01
122VU ANTI ICE/PROBES/2/PITOT 3DA2 Y14
122VU ANTI ICE/PROBES/2/STATIC 5DA2 Y11
122VU ANTI ICE/PROBES/3/PITOT 3DA3 Z16
122VU ANTI ICE/PROBES/3/STATIC 5DA3 Z14
122VU ANTI ICE/PROBES/1/STATIC 5DA1 Z13

Subtask 34-13-00-860-055

C. Put the aircraft back to its initial configuration.

(1) Install the slip on covers on the static probes and on the pitot
probes.

(2) Make sure that the drain holes on the pitot probes are not blocked by
unwanted materials. (Ref. TASK 34-11-15-200-001)

(3) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005).

(4) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

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 TASK 34-13-00-790-002

Leak Test of the Principal Static and Total Air Data System

WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE
_______
YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.

CAUTION : OBEY THESE PRECAUTIONS WHEN YOU DO THE TEST TO PREVENT DAMAGE TO
_______
INSTRUMENTS:
- PRESSURE SET MUST NOT BE MORE THAN 1050 hPa (31 in Hg) OR LESS THAN
115 hPa (3.39 in Hg)
- CHANGES IN PRESSURE MUST NOT BE MORE THAN 6000 FEET/MINUTE
- DO NOT SUDDENLY OPEN LINES TO AMBIENT AIR WHILE THE PRESSURE
GENERATOR IS CONNECTED.

CAUTION : THE TOTAL PRESSURE IN THE PITOT SYSTEM MUST NEVER BE LESS THAN THE
_______
STATIC PRESSURE. THE DIFFERENCE BETWEEN THE PITOT AND THE STATIC
PRESSURE CIRCUITS MUST NEVER BE MORE THAN 368 hPa (10.86 in Hg).

1. __________________
Reason for the Job

Make sure that there are no leaks in the Captain and First Officer pitot and
static circuits.

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific circuit breaker(s) safety clip(s)

No specific colored adhesive tape
36122 1 ADAPTOR-CHARGING,PITOT PROBE
87202126V15 1 GENERATOR - GROUND PRESSURE
98D34003500000 1 ADAPTER COVER-STATIC PORT

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 B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
31-60-00-860-001 EIS Start Procedure
34-10-00-860-005 ADIRS Stop Procedure
34-11-15-200-001 Inspection/Check of the Pitot Probe (9DA1,9DA2,9DA3)

3. __________
Job Set-up

Subtask 34-13-00-860-074

A. Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002).

Subtask 34-13-00-865-061

B. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU ANTI ICE/PROBES/PITOT/1 3DA1 D02
105VU ELEC/CSM/G /EV AUTO/SPLY 7XE C01
122VU ANTI ICE/PROBES/2/PITOT 3DA2 Y14
122VU ANTI ICE/PROBES/2/STATIC 5DA2 Y11
122VU ANTI ICE/PROBES/1/STATIC 5DA1 Z13

Subtask 34-13-00-480-051

C. Installation of the Main Air Data System

(1) Remove the slip on covers from the static probes and the pitot probes
of the main system.

(2) Connect the static port of the GENERATOR - GROUND PRESSURE to the
static probes with the ADAPTER COVER-STATIC PORT (98D34003500102).
For CAPT circuit (ADIRU 1) and F/O circuit (ADIRU 2):
- L static probe 1 7DA1, zone 127, STA 8750, for the LH static
pressure ADM (19FP5)
- L static probe 2 7DA2, zone 127, STA 8700, for the LH static
pressure ADM (19FP7)

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 and
- R static probe 1 8DA1, zone 128, STA 9300, for the RH static
pressure ADM (19FP4)
- R static probe 2 8DA2, zone 128, STA 9350, for the RH static
pressure ADM (19FP6).

(3) Connect the ground pressure generator to the pitot probe with the
ADAPTOR-CHARGING,PITOT PROBE.
For CAPT circuit:
- pitot probe 1 9DA1, zone 125
For F/O circuit:
- pitot probe 2 9DA2, zone 126.

R (4) Seal the drain holes:

R CAUTION : WHEN YOU SEAL THE DRAIN HOLE IN THE PITOT PROBE, DO NOT
_______
R SEAL THE HOLE DIRECTLY WITH THE COLORED ADHESIVE TAPE.
R ALWAYS PUT A PIECE OF PLASTIC ON THE HOLE AND USE THE TAPE
R TO ATTACH THE PLASTIC.
R IF YOU SEAL THE DRAIN HOLE DIRECTLY WITH THE ADHESIVE TAPE,
R THERE IS A RISK THAT SOME OF THE ADHESIVE WILL STAY ON THE
R HOLE AND COLLECT PARTICLES. THIS CAN SUBSEQUENTLY CAUSE
R BLOCKAGE OF THE HOLE AND THUS INCORRECT OPERATION OF THE
R PROBE.

R Seal the drain holes of the pitot probes with a piece of plastic
R and/or colored adhesive tape of very bright color.

Subtask 34-13-00-860-076

D. Aircraft Maintenance Configuration

(1) Do the EIS start procedure (PFD only)

(Ref. TASK 31-60-00-860-001).

(2) On the ADIRS CDU ,set the OFF/NAV/ATT selector switches to NAV.

(3) Start the ground pressure generator.

4. Procedure
_________

Subtask 34-13-00-790-050

A. Leak Test of the Main Air Data System

NOTE : You can do the test below for a static pressure of 697 hPa (10,000
____
ft) and an impact pressure of 53.5 hPa (180 Kts) but it is less
accurate.
After 5 min:
- the change of altitude must not be more than 275 ft.
- the change of speed must not be more than 10 Kts.

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 NOTE : The difference between the input parameters for the ground test
____
(speed and altitude) and the values shown on the cockpit displays,
is normal.

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the glareshield 13VU ,on the

EFIS control section of the FCU,
set a barometric pressure of 1013
hPa.

2. On the ground pressure generator:

- set a static pressure of 465.5
hPa (20,000 ft).

- set an impact pressure of 176

hPa (320 Kts).

3. Close the electrovalves to After 5 minutes, on the CAPT (F/O) PFD:

isolate the static and total - make sure that the change of altitude
pressure lines of the aircraft is not more than 320 ft.
from the pressure generator. After 10 minutes, on the CAPT (F/O)
PFD:
- make sure that the change of speed is
not more than 10 Kts.

4. On the pressure generator: The rate of descent must not be more

- slowly balance the pressure in than 6000 ft/mn.
the main static and total
pressure lines
- open the electrovalves to get
atmospheric pressure.

5. Stop the pressure generator.

5. Close-up
________

Subtask 34-13-00-080-051

A. Disconnect the ground pressure generator.

(1) Remove the adapters from the static probes and the pitot probes.

R (2) Remove the piece of plastic and the colored adhesive tape from the
R drain holes of the pitot probe.

(3) Install the slip on covers on the static probes and the pitot probes.

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 Subtask 34-13-00-865-062

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU ANTI ICE/PROBES/PITOT/1 3DA1 D02
105VU ELEC/CSM/G /EV AUTO/SPLY 7XE C01
122VU ANTI ICE/PROBES/2/PITOT 3DA2 Y14
122VU ANTI ICE/PROBES/2/STATIC 5DA2 Y11
122VU ANTI ICE/PROBES/1/STATIC 5DA1 Z13

Subtask 34-13-00-860-075

C. Put the aircraft back to its initial configuration.

(1) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005).

(2) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

(3) Make sure that the work area is clean and clear of tool(s) and other
items.

(4) Make sure that the drain holes on the pitot probes are not blocked by
unwanted materials. (Ref. TASK 34-11-15-200-001)

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 TASK 34-13-00-740-002

INTERFACE TEST of the ADR

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific circuit breaker(s) safety clip(s)

No specific safety barriers
No specific access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
31-32-00-860-010 Procedure to Get Access to the SYSTEM REPORT/TEST NAV
Page
31-60-00-860-001 EIS Start Procedure
31-60-00-860-002 EIS Stop Procedure

3. __________
Job Set-up

Subtask 34-13-00-860-077

A. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-

002).

(2) On the center pedestal, on the MCDU, get the SYSTEM REPORT/TEST/NAV
page
(Ref. TASK 31-32-00-860-010).

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 (3) Do the EIS start procedure (Ref. TASK 31-60-00-860-001).

(4) On the overhead panel:

- on the FLT CTL panels 23VU and 24VU, release the FAC,ELAC and SEC
pushbutton switches. The OFF legends are on.
- on the ADIRS CDU, make sure that the 3 OFF/NAV/ATT selectors are at
off
- on the ELEC panel 35VU, make sure that the battery voltage is
correct, between 26VDC and 30VDC.

(5) On the center pedestal, on the ECAM control panel, push the STS key.

(6) On the glareshield 13VU, on the CAPT and F/O EFIS control sections of
the FCU, set the mode selector switch to ROSE/NAV.

(7) Put the safety barriers in position around the RAT area.

NOTE : This test is for the system 1. For the systems 2 and 3, use
____
the indications between parentheses.

Subtask 34-13-00-010-055

B. Get Access

(1) Put the access platform in position at the access door 822.

(2) Open the access door 822.

(3) On the battery power center 105VU:

- loosen the two screws and remove the protective cover.

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 Subtask 34-13-00-865-089

C. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU AUTO FLT/FCU/1 9CA1 B05
49VU L/G/LGCIU/SYS1/NORM 1GA C09
49VU NAV PROBES/ADIRU3/PWR/SWTG 8FP F09
49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07
49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06
105VU ADIRS/ADIRU1/28VDC 6FP1 C02

R **ON A/C 001-004,

R
121VU ADIRS/ADIRU/2PWR/SHED 10FP N11
121VU ADIRS/ADIRU/3PWR/SWTG 9FP N10
121VU ADIRS/ADIRU/2/26VAC AND AOA 5FP2 N09
121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N08
121VU ADIRS/ADIRU/2/115VAC 4FP2 N07
121VU ADIRS/ADIRU/3/115VAC 4FP3 N06
121VU ADIRS/ADIRU/2/28VDC 6FP2 N05
121VU ADIRS/ADIRU/3/28VDC 6FP3 N04

R **ON A/C ALL

R 121VU AUTO FLT/FCU/2 9CA2 M21

121VU HYDRAULIC/LGCIU/SYS2 2GA Q35
121VU HYDRAULIC/LGCIU/SYS1/GRND SPLY 52GA Q34

R **ON A/C 005-099,

R 121VU ADIRS/ADIRU/2PWR/SHED 10FP N10

R 121VU ADIRS/ADIRU/3PWR/SWTG 9FP N09
R 121VU ADIRS/ADIRU/2/26VAC AND AOA 5FP2 N08
R 121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N07
R 121VU ADIRS/ADIRU/2/115VAC 4FP2 N06
R 121VU ADIRS/ADIRU/3/115VAC 4FP3 N05
R 121VU ADIRS/ADIRU/2/28VDC 6FP2 N04
R 121VU ADIRS/ADIRU/3/28VDC 6FP3 N03

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R **ON A/C ALL

Subtask 34-13-00-865-091

D. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU AUTO FLT/FAC1/28VDC 5CC1 B04
105VU ELEC/CSM/G /EV AUTO/SPLY 7XE C01
121VU AUTO FLT/FAC2/28VDC 5CC2 M19

4. Procedure
_________

Subtask 34-13-00-740-050

A. INTERFACE TEST of the ADR

NOTE : - Ignore the warnings and indications (VLE, ...) which are not
____
related to this interface test.
- When you test the ADR3, set the AIR DATA selector switch 15FP,
on the SWITCHING panel 8VU, to CAPT/3.

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the ADIRS CDU:

- Set the three OFF/NAV/ATT

selector switches to NAV

- push the ADR1, ADR2 and ADR3 The OFF legend of the ADR1, ADR2 and
pushbutton switches ADR3 pushbutton switches comes on.

- push the ADR1 (ADR2) (ADR3), On the ADIRS CDU, the OFF legend of the
only if the AIR DATA selector ADR pushbutton switch goes off
switch is to CAPT/3 or F/O/3) On the CAPT (F/O) PFD, the SPD and ALT
pushbutton switch again. flags go out of view. The speed and
altitude indications (30 Kts and local
altitude) are shown
On the lower ECAM display unit, the
local temperature values SAT and TAT
are shown (only with ADR2 set).

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
2. On the MCDU:

- push the line key adjacent to - the ADR1 (ADR2) (ADR3) page comes
the ADR1 (ADR2) (ADR3) into view.
indication

- push the line key adjacent to - the ADR1 (ADR2) (ADR3) OUTPUT TESTS
the OUTPUT TESTS indication. page comes into view.

- push the line key adjacent to - the ADR1 (ADR2) (ADR3) INTERFACE TEST
the INTERFACE TEST indication 1/2 page comes into view.

- on the keyboard push the NEXT - the ADR1 (ADR2) (ADR3) INTERFACE TEST
PAGE function key. 2/2 page comes into view.

- push the line key adjacent to From 0 to 5 seconds:

the START TEST indication - on the ADIRS CDU, the FAULT and OFF
legends of the ADR1 (ADR2) (ADR3)
pushbutton switch come on then go off
- on the CAPT (F/O) PFD, the symbols on
the speed and altitude scale go out
of view. The SPD and ALT warning
flags flash for some seconds
- on the CAPT (F/O) ND, the TAS
indication goes out of view
From 5 to 10 seconds:
- on the CAPT (F/O) PFD, the warnings
go out of view
- on the lower ECAM display unit, in
the Inop System part, the message ADR
2 + 3 (ADR 1 + 3) (ADR 1 + 2) comes
into view.
- on the CAPT (F/O) PFD, the altitude
increases.
After 10 seconds:
- on the CAPT (F/O) PFD, these values
are shown:
CAS: 367.7 Kts
MACH: 0.66 M
ALTITUDE: 10000 Ft
- on the CAPT (F/O) ND, this value is
shown:
TAS: 433 Kts

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
- on the lower ECAM display unit, (if
ADR2 set) these values are shown:
TAT: + 35 deg. C
SAT: + 10 deg. C
- on the upper ECAM display unit, this
indication is shown:
OVERSPEED
VMO/MMO 350/.82

- push the line key adjacent to The test procedure stops:

the RETURN indication. - on the upper ECAM display unit, the
OVERSPEED warning indication goes out
of view
- on the CAPT (F/O) PFD, the speed and
altitude indications go back to their
initial value
- on the lower ECAM display unit, the
TAT and SAT values show the local
temperature (only with ADR2 set).

3. On the ADIRS CDU, push the ADR2 On the ADIRS CDU, the OFF legend of the
pushbutton switch. ADR2 pushbutton switch goes off

4. Do the ADR2 test as specified in Same results on the F/O side.

the para. 1 and 2.

5. On the ADIRS CDU:

- push the ADR3 pushbutton switch On the ADIRS CDU, the OFF legend of the
ADR3 pushbutton switch goes off

- push the ADR1 pushbutton On the ADIRS CDU, the OFF legend of the
switch. ADR1 pushbutton switch comes on
On the CAPT PFD, the speed and altitude
indications go out of view.

6. On the SWITCHING panel 8VU: On the CAPT PFD, the speed and altitude
- set the AIR DATA selector indications from the ADR3 are shown.
switch to CAPT/3.

7. Do the ADR3 test as specified in Same results on the CAPT side.

the para. 1 and 2.

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
8. On the ADIRS CDU, push the ADR1 On the ADIRS CDU, the OFF legend of the
pushbutton switch. ADR1 pushbutton switch goes off

9. On the SWITCHING panel 8VU: On the CAPT PFD, the speed and altitude
- set the AIR DATA selector indications stay in view.
switch to NORM.

10. On the ADIRS CDU, set the three

OFF/NAV/ATT selector switches to
OFF.

After the ADR3 test, set the AIR

DATA selector switch 15FP to
NORMAL.

5. Close-up
________

Subtask 34-13-00-860-078

A. Put the aircraft back to its initial configuration.

(1) On the MCDU, push the line key adjacent to the RETURN indication
until the CFDS menu page comes into view.

(2) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002).

(3) On the FLT CTL panels 23VU and 24VU, push the FAC, ELAC and SEC
pushbutton switches. The related OFF legend goes off.

(4) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

Subtask 34-13-00-410-055

B. Close Access

(1) Install the protective cover on the battery power center 105VU.

(2) Tighten the two screws.

(3) Close the access door 822.

(4) Remove the access platform(s).

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 Subtask 34-13-00-865-092

C. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
7XE, 5CC1, 5CC2

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 TASK 34-13-00-740-003

SYSTEM TEST of the ADR

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
31-32-00-860-010 Procedure to Get Access to the SYSTEM REPORT/TEST NAV
Page
34-10-00-860-002 ADIRS Start Procedure
34-10-00-860-005 ADIRS Stop Procedure

3. __________
Job Set-up

Subtask 34-13-00-860-079

A. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits

(Ref. TASK 24-41-00-861-002).

(2) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002).

(3) On the center pedestal, on the MCDU, get the SYSTEM REPORT/TEST/NAV
page (Ref. TASK 31-32-00-860-010).

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 (4) On the overhead panel, on the ADIRS CDU, make sure that the OFF
legend of the ADR pushbutton switches is off).

Subtask 34-13-00-010-056

B. Get Access

(1) Put the access platformin position at the access door 822.

(2) Open the access door 822.

(3) On the battery power center 105VU:

- loosen the two screws and remove the protective cover.

Subtask 34-13-00-865-093

C. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU AUTO FLT/FCU/1 9CA1 B05
49VU L/G/LGCIU/SYS1/NORM 1GA C09
49VU NAV PROBES/ADIRU3/PWR/SWTG 8FP F09
49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07
49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06
105VU ADIRS/ADIRU1/28VDC 6FP1 C02

R **ON A/C 001-004,

R
121VU ADIRS/ADIRU/2PWR/SHED 10FP N11
121VU ADIRS/ADIRU/3PWR/SWTG 9FP N10
121VU ADIRS/ADIRU/2/26VAC AND AOA 5FP2 N09
121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N08
121VU ADIRS/ADIRU/2/115VAC 4FP2 N07
121VU ADIRS/ADIRU/3/115VAC 4FP3 N06
121VU ADIRS/ADIRU/2/28VDC 6FP2 N05
121VU ADIRS/ADIRU/3/28VDC 6FP3 N04

R **ON A/C ALL

R 121VU AUTO FLT/FCU/2 9CA2 M21

121VU HYDRAULIC/LGCIU/SYS2 2GA Q35
121VU HYDRAULIC/LGCIU/SYS1/GRND SPLY 52GA Q34

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 -------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
R **ON A/C 005-099,

R 121VU ADIRS/ADIRU/2PWR/SHED 10FP N10

R 121VU ADIRS/ADIRU/3PWR/SWTG 9FP N09
R 121VU ADIRS/ADIRU/2/26VAC AND AOA 5FP2 N08
R 121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N07
R 121VU ADIRS/ADIRU/2/115VAC 4FP2 N06
R 121VU ADIRS/ADIRU/3/115VAC 4FP3 N05
R 121VU ADIRS/ADIRU/2/28VDC 6FP2 N04
R 121VU ADIRS/ADIRU/3/28VDC 6FP3 N03

R **ON A/C ALL

4. Procedure
_________

Subtask 34-13-00-740-051

A. SYSTEM TEST of the ADR

NOTE : - The actions and the results of this procedure occur on the MCDU
____
used.
- It is not necessary to do an IR alignment procedure before you
start the ADR SYSTEM TEST.

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. Push the line key adjacent to the The ADR 1(ADR 2)(ADR 3) page comes into
ADR 1(ADR 2)(ADR 3) indication view.

2. Push the line key adjacent to the The SYSTEM TEST page comes into view.
SYSTEM TEST indication

3. Push the line key adjacent to the The TEST IN PROGRESS indication comes
START TEST indication into view.
At the end of the test, the TEST OK
indication comes into view.

4. Push the line key adjacent to the These indications come into view:
TEST CLOSE UP indication - TEST CLOSE UP . IR RE-ALIGNMENT
- ENTER PPOS WITH AN UNUSED MCDU

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
(Refer to the NOTE given above)

5. Push the line key adjacent to the The test procedure stops.
RETURN indication

5. Close-up
________

Subtask 34-13-00-860-080

A. Put the aircraft back to its initial configuration.

(1) On the MCDU, push the line key adjacent to the RETURN indication
until the CFDS menu page comes into view.

(2) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005).

(3) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

Subtask 34-13-00-410-056

B. Close Access

(1) Install the protective cover on the battery power center 105VU.

(2) Tighten the two screws.

(3) Close the access door 822.

(4) Remove the access platform(s).

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 TASK 34-13-00-740-005

Read the CFDIU for the ADR INPUT STATUS

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific circuit breaker(s) safety clip(s)

No specific access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
31-32-00-860-010 Procedure to Get Access to the SYSTEM REPORT/TEST NAV
Page
34-10-00-860-002 ADIRS Start Procedure
34-10-00-860-005 ADIRS Stop Procedure

3. __________
Job Set-up

Subtask 34-13-00-860-085

A. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-

002).

(2) Do the ADIRS start procedure (ADIRU related to the installed ADM
only) (Ref. TASK 34-10-00-860-002).

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 (3) On the center pedestal, on one MCDU, get the SYSTEM REPORT/TEST/NAV
page (Ref. TASK 31-32-00-860-010).

Subtask 34-13-00-010-062

B. Get Access

(1) Put the access platform in position at the access door 822.

(2) Open the access door 822.

(3) On the battery power center 105VU:

- loosen the two screws and remove the protective cover.

Subtask 34-13-00-865-097

C. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU AUTO FLT/FCU/1 9CA1 B05
49VU L/G/LGCIU/SYS1/NORM 1GA C09
49VU NAV PROBES/ADIRU3/PWR/SWTG 8FP F09
49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07
49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06
105VU ADIRS/ADIRU1/28VDC 6FP1 C02

R **ON A/C 001-004,

R
121VU ADIRS/ADIRU/2PWR/SHED 10FP N11
121VU ADIRS/ADIRU/3PWR/SWTG 9FP N10
121VU ADIRS/ADIRU/2/26VAC AND AOA 5FP2 N09
121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N08
121VU ADIRS/ADIRU/2/115VAC 4FP2 N07
121VU ADIRS/ADIRU/3/115VAC 4FP3 N06
121VU ADIRS/ADIRU/2/28VDC 6FP2 N05
121VU ADIRS/ADIRU/3/28VDC 6FP3 N04

R **ON A/C ALL

R 121VU AUTO FLT/FCU/2 9CA2 M21

121VU HYDRAULIC/LGCIU/SYS2 2GA Q35
121VU HYDRAULIC/LGCIU/SYS1/GRND SPLY 52GA Q34

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 -------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
R **ON A/C 005-099,

R 121VU ADIRS/ADIRU/2PWR/SHED 10FP N10

R 121VU ADIRS/ADIRU/3PWR/SWTG 9FP N09
R 121VU ADIRS/ADIRU/2/26VAC AND AOA 5FP2 N08
R 121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N07
R 121VU ADIRS/ADIRU/2/115VAC 4FP2 N06
R 121VU ADIRS/ADIRU/3/115VAC 4FP3 N05
R 121VU ADIRS/ADIRU/2/28VDC 6FP2 N04
R 121VU ADIRS/ADIRU/3/28VDC 6FP3 N03

R **ON A/C ALL

Subtask 34-13-00-865-098

D. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU AUTO FLT/FAC1/28VDC 5CC1 B04
105VU ELEC/CSM/G /EV AUTO/SPLY 7XE C01
121VU AUTO FLT/FAC2/28VDC 5CC2 M19

4. Procedure
_________

Subtask 34-13-00-740-053

A. Read the CFDIU for the ADR INPUT STATUS

NOTE : This test is for the system 1. For the systems 2 and 3, use the
____
indications between the parentheses.
The actions and the results of this procedure occur on the MCDU
used.

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. Push the line key adjacent to the - the ADR 1(ADR 2)(ADR 3) page comes
ADR 1(ADR 2)(ADR 3) indication. into view.

2. Push the line key adjacent to the - the INPUT STATUS page 1/8 comes into
INPUT STATUS indication. view with the current on-the-ground
status of the ADR1 (ADR2) (ADR3)
parameters.

3. Push the down arrow function key - the related pages come into view.
to set the INPUT STATUS page 2/8
to 8/8.

4. Push the line key adjacent to the - the test procedure stops.
RETURN indication.

5. Close-up
________

Subtask 34-13-00-410-062

A. Close Access

(1) Install the protective cover on the battery power center 105VU.

(2) Tighten the two screws.

(3) Close the access door 822.

(4) Remove the access platform(s).

Subtask 34-13-00-860-086

B. Put the aircraft back to its initial configuration.

(1) On the center pedestal, on the MCDU, push the line key adjacent to
the RETURN indication until the MCDU MENU page comes into view.

(2) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005).

(3) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

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 Subtask 34-13-00-865-099

C. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
5CC1, 5CC2

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 ATTITUDE, HEADING AND POSITION - DESCRIPTION AND OPERATION
__________________________________________________________

1. _______
General
The Inertial Reference (IR) portion of the Air Data/Inertial Reference Unit
(ADIRU) provides main data sources which are precision attitude, magnetic
heading references and navigation data to the aircraft avionics systems.
Attitude, heading and navigation data are displayed on the Electronic Flight
Instrument System (EFIS) displays (Primary Flight Display (PFD); Navigation
Display (ND)) and on the VOR/DME RMI which recopies the heading data.
The IR portion also provides data from the selected GPSSU and accurate GPIR
hybrid position.

2. __________________
System Description

A. General
The IR portion is a strapdown inertial system which provides a quality
reference for attitude, heading (true and magnetic), angular rates and
accelerations.
The IR software also computes:
- the inertial position
- the ground velocities
- the baro inertial vertical speed
- the drift angle
- the wind data
- the flight path data.

R **ON A/C 001-004,

B. Inputs

(1) Digital inputs

(a) FMGC inputs

The IR portion is provided with two ARINC 429 low speed buses
from the two ARINC 702 Flight Management and Guidance Computers
(FMGCs). These buses transmit the following data words:
- label 041: SET LATITUDE
- label 042: SET LONGITUDE
- label 270: FMGC DISCRETES.
These data words are used for initialization and BITE purposes.

(b) CDU inputs

The IR portion is provided with one ARINC 429 low speed buses
from the CDU.
This bus transmits the following data words:
- label 041: SET LATITUDE

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 - label 042: SET LONGITUDE
- label 043: SET MAGNETIC HEADING
- label 277: CDU TEST.
These data words are used for initialization and BITE purposes.

(c) ADR inputs

The IR portion is provided with three ARINC 429 low speed buses
from the two other ADIRUs (ADR portion) and from its associated
ADR. These buses transmit the following data words:
- label 203: ALTITUDE
- label 210: TRUE AIRSPEED

(d) CFDS input

The IR portion is provided with one ARINC 429 low speed bus from
the Centralized Fault Display System (CFDS). This bus transmits
the following data words:
- label 125: UTC
- label 126: FLIGHT PHASE
- label 155: AIRCRAFT CONFIG
- label 227: CFDS COMMAND
- label 260: DATE
- labels 233 to 236: FLIGHT NUMBER
- labels 301 to 303: AIRCRAFT TAIL NUMBER
For more details Ref. 34-18-00.

(2) Analog inputs

The IR portion is provided with analog inputs for power supply
purposes.
For more details Ref. 34-12-00.

**ON A/C ALL

R Post SB 34-1147 For A/C 001-004,

B. Inputs

(1) Digital inputs

(a) FMGC inputs

The IR portion is provided with two ARINC 429 low speed buses
from the two ARINC 702 Flight Management and Guidance Computers
(FMGCs). These buses transmit the following data words:
- label 041: SET LATITUDE
- label 042: SET LONGITUDE
- label 270: FMGC DISCRETES.
These data words are used for initialization and BITE purposes.

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R (b) CDU inputs
R The IR portion is provided with one ARINC 429 low speed buses
R from the CDU.
R This bus transmits the following data words:
R - label 041: SET LATITUDE
R - label 042: SET LONGITUDE
R - label 043: SET MAGNETIC HEADING
R - label 277: CDU TEST.
R These data words are used for initialization and BITE purposes.

R (c) ADR inputs

R The IR portion is provided with three ARINC 429 low speed buses
R from the two other ADIRUs (ADR portion) and from its associated
R ADR. These buses transmit the following data words:
R - label 203: ALTITUDE
R - label 210: TRUE AIRSPEED

R (d) CFDS input

R The IR portion is provided with one ARINC 429 low speed bus from
R the Centralized Fault Display System (CFDS). This bus transmits
R the following data words:
R - label 125: UTC
R - label 126: FLIGHT PHASE
R - label 155: AIRCRAFT CONFIG
R - label 227: CFDS COMMAND
R - label 260: DATE
R - labels 233 to 236: FLIGHT NUMBER
R - labels 301 to 303: AIRCRAFT TAIL NUMBER
R For more details Ref. 34-18-00.

R (e) GPS inputs

R The IR portion is provided with two ARINC 429 high speed buses
R from the GPS portion of the Multi-Mode Receivers (MMRs).
R These buses transmit the following data words:
R - label 060: MEASUREMENT STATUS
R - label 061: PSEUDO RANGE
R - label 062: PSEUDO RANGE FINE
R - label 063: RANGE RATE
R - label 064: DELTA RANGE
R - label 065: SV POSITION X
R - label 066: SV POSITION X FINE
R - label 070: SV POSITION Y
R - label 071: SV POSITION Y FINE
R - label 072: SV POSITION Z
R - label 073: SV POSITION Z FINE
R - label 074: UTC MEASURE TIME
R - label 076: GPS ALTITUDE (MSL)

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R - label 101: GPS HDOP
R - label 102: GPS VDOP
R - label 103: GPS TRACK ANGLE
R - label 110: GPS LATITUDE
R - label 111: GPS LONGITUDE
R - label 112: GPS GROUND SPEED
R - label 120: GPS LATITUDE FINE
R - label 121: GPS LONGITUDE FINE
R - label 125: GPS UTC BCD
R - label 130: GPS HORIZONTAL INTEGRITY LIMIT
R - label 136: GPS VERTICAL FOM
R - label 140: GPS UTC FINE
R - label 141: GPS UTC FINE FRACTIONS
R - label 143: TERMINAL AREA HIL
R - label 150: GPS UTC BIN
R - label 162: DESTINATION ETA
R - label 163: ALT WAYPOINT ETA
R - label 165: GPS VERTICAL VELOCITY
R - label 166: GPS N/S VELOCITY
R - label 174: GPS E/W VELOCITY
R - label 247: GPS HORIZONTAL FOM
R - label 260: GPS DATE
R - label 273: GPS SENSOR STATUS
R - label 343: DESTINATION HIL
R - label 347: ALT WAYPOINT HIL
R - label 377: EQUIPMENT IDENT

R (2) Analog inputs

R The IR portion is provided with analog inputs for power supply
R purposes.
R For more details Ref. 34-12-00.

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R **ON A/C ALL

(3) Discrete inputs

The IR portion is provided with the following discrete inputs:

---------------------------------------------------------------------
| INPUT SIGNAL | INPUT | INPUT |
| | | DEFINITION |
---------------------------------------------------------------------
| Mounting position 1 | Open/GND | see table 2 |
| Mounting position 2 | Open/GND | see table 2 |
| SDI MSB (Middle insert) | Open/GND | 0/1 |
| SDI LSB (Middle insert) | Open/GND | 0/1 |
| CDU ON/OFF | Open/GND |Not displayed/displayed|
| IR mode select M1 | Open/GND | see table 3 |
| IR mode select M2 | Open/GND | see table 3 |
| Auto ADR.DADS select | Open/GND | see table 4 |
| Manual ADR.DADS select | Open/GND | see table 4 |
| Aircraft Ident Code 1/0 |Open/A.I. Com| 0/1 |
| Aircraft Ident Code 2/0 |Open/A.I. Com| 0/1 |
| Aircraft Ident Code 4/0 |Open/A.I. Com| 0/1 |
| Aircraft Ident Code 8/0 |Open/A.I. Com| 0/1 |
| Aircraft Ident Code 16/0 |Open/A.I. Com| 0/1 |
| Aircraft Ident Code 32/0 |Open/A.I. Com| 0/1 |
| Aircraft Ident Code 64/0 |Open/A.I. Com| 0/1 |
| Aircraft Ident Code Parity |Open/A.I. Com| 0/1 |
| IR remote test | Open/GND | No test/test |
| MAGVAR select | Open/GND |Standard/expended model|
| GPS sensor 1 present | Open/GND | GND = present |
| GPS sensor 2 present | Open/GND | GND = present |
| GPS priority select | Open/GND |Normal priority/ |
| | |Reserved priority |
---------------------------------------------------------------------
Table 1 : IR Discrete Inputs

(a) Mounting positions 1 and 2

These discrete inputs are used to indicate to the IR the
orientation of the unit. It is needed to know the longitudinal
and lateral axis of the aircraft.
Table 2 below gives the unit position in function of the discrete
selection.

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 ---------------------------------------------------------------
| Mounting | Mounting | Connector Position/Aircraft |
| Position 1 | Position 2 | |
---------------------------------------------------------------
| Open * | Open * | FWD * |
| Ground | Open | AFT |
| Open | Ground | RIGHT |
| Ground | Ground | LEFT |
---------------------------------------------------------------
Table 2 : Mounting Position Discretes

* The discretes are wired in FWD position.

(b) IR mode select

The IR portion uses these discrete inputs to know the position of
the OFF/NAV/ATT selector switch as follows:

----------------------------------------------
| M1 | M2 | OFF/NAV/ATT |
| | | Selector Switch Position |
|--------------------------------------------|
| Open | Open | OFF |
| Ground | Open | NAV |
| Open | Ground | ATT |
----------------------------------------------
Table 3 : IR Mode Select

(c) ADR DADS select

The IR portion uses these discrete inputs to know which air data
source to use:

--------------------------------------------------------------------
| Auto | Manual | IR Selection |
| ADR DADS | ADR DADS | |
--------------------------------------------------------------------
| Open | Open | The IR uses the air data received |
| | | on port 1 |
|-------------|----------------|-----------------------------------|
| Open | Ground | The IR uses the air data received |
| | | on port 2 |
|-------------|----------------|-----------------------------------|
| Ground * | Open | The IR goes automatically from one|
| | | air data source to the others |
| | | according to their validity and |
| | | priority. * |
--------------------------------------------------------------------
Table 4 : ADR DADS Select

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 * The discretes are wired in the automatic ADR selection mode
with the following priority:
1: its own ADR unit
2: ADR received on port 1
3: ADR received on port 2.

(d) SDI program pins

These discretes code the installation side of the ADIRU.
The following table gives the IR side according to the SDI.

--------------------------------------------
| SDI-MSB | SDI-LSB | ADIRU NUMBER |
--------------------------------------------
| OPEN | GROUND | 1 |
| GROUND | OPEN | 2 |
| GROUND | GROUND | 3 |
--------------------------------------------
Table 5 : IR SDI Code

R **ON A/C 001-004,

(e) IR remote test

The IR portion uses one discrete to select the remote test by
external control.
When this discrete is open, the test is not activated.
When this discrete is grounded, the test is activated.
In normal operation this discrete is open (unused) but can be
also activated via the CFDIU on ground (Ref. 34-18-00).

(f) CFDS message select

On the A/C, this discrete is open.

(g) GPS present

These discretes are used to activate GPS/IRS hybridization
(computation, BITE function).

(h) GPS priority select

The GPIRS function uses this discrete to modify the GPS priority.
Each ADIRU receives data from the two GPSSUs on the primary and
secondary inputs.
For each ADIRU, the primary and secondary GPS inputs are defined
as follows:

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 ---------------------------------------
| ADIRU | PRIMARY | SECONDARY |
| SDI | INPUT | INPUT |
---------------------------------------
| 1 | GPSSU 1 | GPSSU 2 |
| 2 | GPSSU 2 | GPSSU 1 |
| 3 | GPSSU 1 | GPSSU 2 |
---------------------------------------

Depending on the GPS validity and GPS priority select input

discrete status, the GPS source is defined as follows:

---------------------------------------------------------------------
| PRIORITY | PRIMARY | SECONDARY | GPSSU SOURCE |
| STATUS | GPSSU | GPSSU |-----------------------------------
| | | | GPS PRIORITY | GPS PRIORITY |
| | | | SELECT = OPEN | SELECT = GROUND |
---------------------------------------------------------------------
| 1 | Valid | Valid | Primary | Secondary |
| 2 | Valid | Fail | Primary | Primary |
| 3 | Fail | Valid | Secondary | Secondary |
| 4 | Fail | Fail | Primary | Secondary |
---------------------------------------------------------------------

**ON A/C ALL

R Post SB 34-1147 For A/C 001-004,

(e) IR remote test

The IR portion uses one discrete to select the remote test by
external control.
When this discrete is open, the test is not activated.
When this discrete is grounded, the test is activated.
In normal operation this discrete is open (unused) but can be
also activated via the CFDIU on ground (Ref. 34-18-00).

(f) CFDS message select

On the A/C, this discrete is open.

(g) GPS present

These discretes are used to activate GPS/IRS hybridization
(computation, BITE function).

(h) GPS priority select

The GPIRS function uses this discrete to modify the GPS priority.
Each ADIRU receives data from the two GPS portions of the MMRs on
the primary and secondary inputs.

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R For each ADIRU, the primary and secondary GPS inputs are defined
R as follows:

R ---------------------------------------------
R | ADIRU | PRIMARY | SECONDARY |
R | SDI | INPUT | INPUT |
R ---------------------------------------------
R | 1 | GPSSU 1 (MMR 1) | GPSSU 2 (MMR 2) |
R | 2 | GPSSU 2 (MMR 2) | GPSSU 1 (MMR 1) |
R | 3 | GPSSU 1 (MMR 1) | GPSSU 2 (MMR 2) |
R ---------------------------------------------

R Depending on the GPS validity and GPS priority select input

R discrete status, the GPS source is defined as follows:

R ---------------------------------------------------------------------
R | PRIORITY | PRIMARY | SECONDARY | GPSSU SOURCE |
R | STATUS | GPSSU | GPSSU |-----------------------------------
R | | | | GPS PRIORITY | GPS PRIORITY |
R | | | | SELECT = OPEN | SELECT = GROUND |
R ---------------------------------------------------------------------
R | 1 | Valid | Valid | Primary | Secondary |
R | 2 | Valid | Fail | Primary | Primary |
R | 3 | Fail | Valid | Secondary | Secondary |
R | 4 | Fail | Fail | Primary | Secondary |
R ---------------------------------------------------------------------

R **ON A/C ALL

C. Software Computation
(Ref. Fig. 001, 002)
The software contains the program memory and provides the following basic
functions:
- real-time executive
- attitude integration
- velocity integration
- position integration
- output computation
- built-in test (Ref. 34-18-00).
The IR software operates in one of three basic modes: alignment,
navigation, or a reversionary attitude mode. These modes include various
portions of the major functions. The real-time executive and built-in
test functions interface with each function in each mode.

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 ADIRU - IR Block Diagram
Figure 001

R
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 ADIRU - IR Signal Flow Diagram
Figure 002

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 (1) Alignment mode
The alignment is the initialization mode for the IR. Its primary
function is to initialize the attitude, velocity and position
integration functions implemented in the navigation mode. This mode
operates on the ground only.
The IR alignment mode is divided into three parts:
- coarse level processing
The coarse level processing is engaged during the first 30 seconds
of the IR alignment mode. This processing estimates the local
vertical using the three accelerometers and the measured gravity.
During coarse level processing of the alignment mode, the software
computes the level coordinate frame, pitch and roll, and associated
rates and accelerations.
- gyro-compass (or azimuth) processing and level processing
Gyro-compass processing is engaged after the 30 seconds of the IR
alignment mode (coarse level complete) and runs for a minimum of
9.5 minutes.
Gyro-compass processing is used to orient body frame to North
(using earth rotation detection by gyros).
During this alignment submode, an estimated latitude is computed
using local vertical component of the earth rotation.
During this submode, the results of the coarse level processing are
sharpened to have a better knowledge of the coordinate frame.
- position entry data processing
This position initialization can take place in coarse level
processing or gyro-compass processing.
The latitude and longitude pair processed for position
initialization is received from the same source (FMGC 1, FMGC 2 or
CDU).
As soon as a valid position initialization pair is received, the
software performs a BITE test to check if the entered latitude and
longitude are within the following limits versus the position
recorded at the end of the last power- up cycle:

Abs val( lat entered - lat recorded ) less than or equal to 1 deg.

Abs val( long entered - long recorded ) less than or equal to 1 deg
(Ref. 34-18-00).

A second BITE test is performed on the entered latitude when an

estimated latitude is available during the gyro-compass processing:

Abs val(cos (lat est) - cos (lat ent)) less than or equal to
0.01234.

Abs val(sin (lat est) - sin (lat ent)) less than or equal to
0.01234.

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 The alignment is completed after 10 minutes if a valid position
data has been received and verified by the IR.
If not, the automatic sequencing to the NAV mode will be delayed
(up to 1 minute) after position data is received.
The operations to enter position and the warnings associated to the
tests performed in alignment mode are described in para. 3
(operation/control and indicating).
The IR also offers the possibility to enter into a variant of the
alignment mode called Wrapid realignW or W30-second realignW. This
mode is selected by moving the CDU selector switch from NAV to OFF,
then to NAV within five seconds, when the aircraft is on ground
(ground speed less than 20 knots). Valid position data must be
received. During the Wrapid realignW mode, all computed velocities
are set to zero and a fine tuning of the alignment is performed
using the attitude reference vertical and the heading data
available from the last NAV phase as initial conditions.
During the alignment mode, the IR outputs on the ARINC 429 bus may
not be available. The chronology of the validation of the outputs
during the alignment is given in para. 2-D (IR output data).

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 (2) Navigation (NAV) mode
(Ref. Fig. 003)
The NAV mode is the primary operating mode for the IR and is
implemented in software as unaided strapdown inertial navigation
computation. The basic operating elements consist of three
integration functions (attitude, velocity and position) driven by
input gyro and accelerometer strapdown sensor data.
The equations used to compute the main parameters are the following:

- body pitch, roll, yaw rates (labels 326, 327, 330):

they are representative of the aircraft body rotations relative to
the aircraft body axes and are directly measured by the laser
gyros.

- body longitudinal, lateral, normal accelerations (labels 331, 332,

333):
they are directly measured by the accelerometers but with the
gravity effect substracted to have 0g on the normal acceleration
when in level.

- pitch and roll attitude rate (labels 336, 337)

Pitch Att rate = Q. cos (Ra) - R. sin (Ra)

Q. sin (Ra) + R. cos (Ra)
Roll Att rate = P + -------------------------
cos (Pa)/sin (Pa)
where : Ra = Roll angle
Pa = Pitch angle
P = Body roll rate
Q = Body pitch rate
R = Body yaw rate

- flight path angle (label 322) = angle between the aircraft velocity
vector and the horizontal plane
(VZ)
FPA = Arc tan (--)
(VG)
where : VZ = inertial vertical speed (label 365)
VG = ground speed (label 312)

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 ADIRU - Navigation Mode Functions
Figure 003

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 - flight path acceleration (label 323) = aircraft acceleration along
the total velocity vector
Vx.Ax + Vy.Ay + Vz.Az
Flt Path Accel = ---------------------
______________
/ 2 2 2
V Vx + Vy + Vz
where : Ax, Ay, Az, Vx, Vy, Vz: accelerations and velocities in the
earth frame.

- wind speed and direction computation (labels 315 and 316)

___________________
/ 2 2
Wind speed = V Vwind N + Vwind E
(Vwind E)
Wind direction = Arc tan (-------) + 180 deg.
(Vwind N)
Vwind E = Veast - cos (Pa). sin (Hdg). TAS

Vwind N = Vnorth - cos (Pa). cos (Hdg). TAS

where : Veast = east velocity = label 367

Vnorth = north velocity = label 366
Pa = pitch angle = label 324
Hdg = heading = label 314
TAS = true airspeed.

The TAS is received from the ADR. The ADR source to be used is
selected according to the configuration of the discretes described
in para. 2.B.(3)(d). The IR does not compute the wind if the TAS is
less than 100 knots or if the air data sources are no more
available. In this case, the wind labels are sent with their status
matrix coded NCD (No Computed Data).

- inertial vertical speed and inertial altitude computation (labels

365 and 361)
The IR software contains a baro-inertial loop to compute the
Inertial Vertical Speed and Inertial Altitude. This loop permits to
take advantage of the different qualities of the inertial and air
data systems. The IR brings its better behaviour in dynamic
maneuvers while the ADR brings its stability in time (no drift of
the outputs like in IR). The principle of the baro-inertial loop is
given in: the figure
(Ref. Fig. 004)

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 IR - Baro Inertial Altitude Filter
Figure 004

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 The ADR source to be used is selected according to the
configuration of the discretes described in para. 2.B.(3)(d). When
no ADR source is available, the labels 361 and 365 are sent with
their status matrix coded NCD (No Computed Data).

- magnetic deviation computation

The principle of the inertial system is based on geographic
referenced measurements and computation. To create the labels which
are magnetic referenced (magnetic heading, magnetic track angle ;
labels 320, 317) the IR computes a magnetic variation which is
added to the true values (labels 314, 313).
The magnetic variation is computed as a function of the present
position (latitude and longitude) within the range of 82⁰N to 60⁰S
excluding the magnetic polar region (latitude exceeds 73⁰N and
longitude between 120⁰W and 90⁰W). The magnetic variation at any
given point is calculated by using four grid intersection data
values and a two-dimensional linear interpolation. The grid data
comes from the National Oceanic and Atmospheric Administration and
must be updated every 10 years in order to meet the accuracy
requirements.
The computation and display of navigation data by the FMGS and the
EIS are in magnetic references (using magnetic referenced labels
from the IR).
- GPS/IRS hybridization computation
At the end of GPIR NAV mode ground align processing, an 18-state
PR/DR (Pseudo Range / Delta Range) mechanized Kalman filter is
engaged to estimate the system error states. The hybrid solution is
then corrected by removing its errors estimated from the Kalman
filter.

(3) Attitude mode

The attitude mode is a reversionary mode which can be activated only
by manual selection of the ATT mode on the CDU.
The mode can be activated on the ground or in flight and is intended
to provide a rapid attitude/heading restart capability if the IR has
experienced total power shutdown or failures which do not disable the
mechanization of the attitude computation. The necessity of selecting
ATT is indicated by the IR on its action code (label 350 - code 04 =
select ATT) and this data is used by the FWC to display a message on
the ECAM displays.
On the CDU, the STS-SELECT ATT indication comes into view if the
DISPLAY/DATA selector switch is in STS (status) position.
This mode needs a 20-second initialization phase with the aircraft in
level flight. During this phase, all the ARINC bus outputs are sent
with their status matrix coded NCD (No Computed Data). At the end of
the initialization phase the IR sends valid outputs of:
- body axis accelerations and angular rates

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 - pitch and roll attitude and rate
- vertical acceleration
- vertical velocity
- baro-inertial altitude and vertical speed (Ref. para. D - IR output
data, list of valid labels).
The magnetic heading may also be valid if an initialization value
has been sent by the FMGC (through the MCDU) or the CDU. (Ref.
para. D - IR output data for the complete list of valid outputs).

R **ON A/C 001-004,

D. IR Output Data

(1) Digital output characteristics

The IRs have 4 independently buffered high-speed ARINC 429 digital
output buses, designated bus output 1, 2, 3 and 4
- digital output table:
This table contains all the output parameters in the digital form.
They are sorted as per the numerical order of their output label.
The following table gives:
- EQ.SYS.LAB.SDI : (SDAC, FWC, DMC...) output label for which the
parameter is available
- PARAMETER DEFINITION: parameter name
- WORD RANGE/OPER RANGE/RESOLUTION ACCURACY : measurement range
Maximum value transmitted. When the digital value changes, the
change step is equal to the accuracy
- UNIT : unit in which the digital value is transmitted
- SIG BIT : indicates whether a sign bit is available
- BITS : number of bits used by the parameter in the label
- XMSN/INTV : output transmission interval. The refresh rate is given
in milliseconds.
- CODE:
BNR: binary data word
BCD: binary coded decimal data word
ISO: data word coded in ISO5 code
DIS: discrete data word
HEX: hexadecimal coded
HYB: mixed code.
- ALPHA CODE: indicates the parameter mnemonic code
- SOURCE ORIGIN: parameter source computer or system.
When the input discretes of THE GPS PRESENT programming pins are
grounded (indicating GPS present), both the GPSSU outputs and the
GPIRS integrated navigation solution outputs are transmitted on the
IR output buses with the IR output data.

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 -------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
| 010 |PPOS LAT |W |Deg | | 6 |500 |BCD |LATP | |
| | |90S-90N |& | | | | | | |
| | |0.1 |min | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 011 |PPOS LONG |W |Deg | | 6 |500 |BCD | | |
| | |180E-180W |& | | | | | | |
| | |0.1 |min | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 012 |GROUND |W 0 to 2000 |Kts | | 4 |500 |BCD | GS | |
| |SPEED |0 to 1000 | | | | | | | |
| | |R 1 | | | | | | | |
| | |+/- 8 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 013 |TRK ANGLE |W 0 to 359.9|Deg | | 4 |500 |BCD | | |
| |TRUE |R 0.1 | | | | | | | |
| | |+/- 2.3 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 014 |MAG HDG |W 0 to 359.9|Deg | | 4 |500 |BCD | MH | |
| | |R 0.1 | | | | | | | |
| | |+/- 3 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 015 |WIND SPEED|W 0 to 256 |Kts | | 3 |500 |BCD | WS | |
| | |R 1 | | | | | | | |
| | |+/- 9 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 016 |WIND DIR |W 0 to 359 |Deg | | 3 |500 |BCD | WD | |
| |TRUE |R 1 | | | | | | | |
| | |+/- 10 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 041 |SET LAT |W +/- 180 |Deg | | 6 |500 |BCD | | |
| | |90S-90N |& | | | | | | |
| | |R 0.1 |min | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 042 |SET LONG |W +/- 180 |Deg | | 6 |500 |BCD | | |
| | |R 0.1 |& | | | | | | |
| | | |min | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 043 |SET MAG |W 0 to 359.9|Deg | | 4 |500 |BCD | | |

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 -------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
| |HDG |R 0.1 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 044 |TRUE HDG |W 0 to 359.9|Deg | | 4 |500 |BCD |THDG | |
| | |R 0.1 | | | | | | | |
| | |+/- 0.4 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 052 |PITCH |W +/- 64 |Deg/| | 15 | 20 |BNR | | |
| |ANGULAR |R 0.002 |sec2| | | | | | |
| |ACCEL | | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 053 |ROLL |W +/- 64 |Deg/| | 15 | 20 |BNR | | |
| |ANGULAR |R 0.002 |sec2| | | | | | |
| |ACCEL | | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 054 |YAW |W +/- 64 |Deg/| | 15 | 20 |BNR | | |
| |ANGULAR |R 0.002 |sec2| | | | | | |
| |ACCEL | | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 310 |PPOS LAT |W +/- 180 |Deg | 29 | 20 |200 |BNR | | |
| | |+/- 90 |& | | | | | | |
| | |R 0.00017 |min | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 311 |PPOS LONG |W +/- 180 |Deg | 29 | 20 |200 |BNR |LONP | |
| | |R 0.00017 |& | | | | | | |
| | | |min | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 312 |GROUND |W 0 to 4096 |Kts | | 15 | 40 |BNR | | |
| |SPEED |R 0.125 | | | | | | | |
| | |+/- 8 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 313 |TRK - TRUE|W +/- 180 |Deg | 29 | 15 | 40 |BNR | | |
| | |R 0.0055 | | | | | | | |
| | |+/- 0.23 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 314 |TRUE HDG |W +/- 180 |Deg | 29 | 15 | 40 |BNR | | |
| | |R 0.0055 | | | | | | | |
| | |+/- 0.4 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|

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 -------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
| 315 |WIND |W 0 to 256 |Kts | | 15 |100 |BNR | | |
| |SPEED |0 to 100 | | | | | | | |
| | |R 0.0078 | | | | | | | |
| | |+/- 8 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 316 |WIND DIR |W +/- 180 |Deg | 29 | 15 |100 |BNR | | |
| |- TRUE |+/- 180 | | | | | | | |
| | |R 0.0055 | | | | | | | |
| | |+/- 10 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 317 |TRK - MAG |W +/- 180 |Deg | 29 | 15 | 40 |BNR | | |
| | |R 0.0055 | | | | | | | |
| | |+/- 3 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 320 |MAG HDG |W +/- 180 |Deg | 29 | 15 | 40 |BNR | | |
| | |82 N to 60 S| | | | | | | |
| | |R 0.0055 | | | | | | | |
| | |+/- 3 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 321 |DRIFT |W +/- 180 |Deg | 29 | 15 | 40 |BNR | DA | |
| |ANGLE |+/- 90 | | | | | | | |
| | |R 0.0055 | | | | | | | |
| | |+/- 2.3 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 322 |FLIGHT |W +/- 180 |Deg | 29 | 15 | 40 |BNR | FPA | |
| |PATH |+/- 90 | | | | | | | |
| |ANGLE |R 0.0055 | | | | | | | |
| | |+/- 0.28 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 323 |FLT PATH |W +/- 4 | g | 29 | 15 | 20 |BNR |FPAC | |
| |ACCEL |R 0.0001 | | | | | | | |
| | |+/- 10 % of | | | | | | | |
| | |outp | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 324 |PITCH |W +/- 180 |Deg | 29 | 15 | 20 |BNR |PTCH | |
| |ANGLE |-90 to + 90 | | | | | | | |
| | |R 0.0055 | | | | | | | |
| | |+/- 0.05 | | | | | | | |

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 -------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 325 |ROLL |W +/- 180 |Deg | 29 | 15 | 20 |BNR |ROLL | |
| |ANGLE |-90 to + 90 | | | | | | | |
| | |R 0.0055 | | | | | | | |
| | |+/- 0.05 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 326 |BODY AXIS |W +/- 128 |Deg/| 29 | 15 | 20 |BNR |PTCR | |
| |PITCH RATE|+/- 45 |s | | | | | | |
| | |R 0.0039 | | | | | | | |
| | |+/- 0.1 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 327 |BODY AXIS |W +/- 128 |Deg/| 29 | 15 | 20 |BNR |ROLR | |
| |ROLL RATE |+/- 45 |s | | | | | | |
| | |R 0.0039 | | | | | | | |
| | |+/- 0.1 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 330 |BODY AXIS |W +/- 128 |Deg/| 29 | 15 | 20 |BNR |YAW | |
| |YAW RATE |+/- 45 |s | | | | | | |
| | |R 0.0039 | | | | | | | |
| | |+/- 0.1 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 331 |BODY LONG |W +/- 4 | g | 29 | 15 | 20 |BNR |LONG | |
| |ACCEL |+/- 4.000 | | | | | | | |
| | |R 0.0001 | | | | | | | |
| | |+/- 0.01 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 332 |BODY LAT |W +/- 4 | g | 29 | 15 | 20 |BNR |LATG | |
| |ACCEL |+/- 4.000 | | | | | | | |
| | |R 0.0001 | | | | | | | |
| | |+/- 0.01 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 333 |BODY NORM |W +/- 4 | g | 29 | 15 | 20 |BNR |VRTG | |
| |ACCEL |+/- 4.000 | | | | | | | |
| | |R 0.0001 | | | | | | | |
| | |+/- 0.01 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 334 |PLATFORM |W +/- 180 |Deg | 29 | 15 | 40 |BNR | | |
| |HEADING |R 0.0055 | | | | | | | |

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 -------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
| | |+/- 0.23 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 335 |TRK ANGLE |W +/- 32 |Deg/| 29 | 15 | 20 |BNR | | |
| |RATE |R 0.001 |s | | | | | | |
| | |+/- 0.17 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 336 |PITCH ATT |W +/- 128 |Deg/| 29 | 15 | 20 |BNR | | |
| |RATE |R 0.0039 |s | | | | | | |
| | |+/- 0.1 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 337 |ROLL ATT |W +/- 128 |Deg/| 29 | 15 | 20 |BNR | | |
| |RATE |R 0.0039 |s | | | | | | |
| | |+/- 0.1 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 340 |TRACK |W +/- 180 |Deg | 29 | 15 | 40 |BNR | | |
| |ANGLE |R 0.0055 | | | | | | | |
| |GRID |+/- 3 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 341 |GRID |W +/- 180 |Deg | 29 | 15 | 40 |BNR | | |
| |HEADING |R 0.0055 | | | | | | | |
| | |+/- 3 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 360 |POTENTIAL |W +/- 32768 |ft /| 29 | 15 | 20 |BNR | | |
| |V/S |R 1.0 | min| | | | | | |
| | |+/- 30 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 361 |INERTIAL |W +/- 131072|ft | 29 | 20 | 40 |BNR | | |
| |ALT |R 0.125 | | | | | | | |
| | |+/- 5 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 362 |ALONG TRK |W +/- 4 | g | 29 | 15 | 20 |BNR | | |
| |HORIZ |R 0.00012 | | | | | | | |
| |ACCEL |+/- 10 % | | | | | | | |
| | |of outp | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 363 |CROSS TRK |W +/- 4 | g | 29 | 15 | 20 |BNR | | |
| |HORIZ |R 0.00012 | | | | | | | |
| |ACCEL |+/- 10 % | | | | | | | |

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 -------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
| | |of outp | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 364 |VERTICAL |W +/- 4 | g | 29 | 15 | 20 |BNR |VACC | |
| |ACCEL |+/- 4.000 | | | | | | | |
| | |R 0.00012 | | | | | | | |
| | |+/- 0.01 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 365 |INERTIAL |W +/- 32768 |ft /| 29 | 15 | 20 |BNR |IVV | |
| |V/S |R 1.0 |min | | | | | | |
| | |+/- 30 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 366 |N - S |W +/- 4096 |Kts | 29 | 15 |100 |BNR | | |
| |VELOCITY |R 0.125 | | | | | | | |
| | |+/- 8 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 367 |E - W |W +/- 4096 |Kts | 29 | 15 |100 |BNR | | |
| |VELOCITY |R 0.125 | | | | | | | |
| | |+/- 8 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 270 |DSCRT DATA| | | | |500 |DIS | | |
| |WORD 1 | | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 275 |DSCRT DATA| | | | |500 |DIS | | |
| |WORD 2 | | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 276 |DSCRT DATA| | | | |500 |DIS | | |
| |WORD 3 | | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 277 |IRS TEST | | | | |500 |HYB | | |
| |WORD | | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 350 |ACTION | | | | |500 |HYB | | |
| |CODE | | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 351 |IR MAINT | | | | |500 |DIS | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 354 |LRU IDENT | | | | | |ISO | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|

R
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 -------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
| 356 |FAULT | | | | | |ISO | | |
| |STAT | | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 377 |EQUIP | | | | |500 |HEX | | |
| |IDENT | | | | | | | | |
|-----------------------------------------------------------------------------|

**ON A/C ALL

R Post SB 34-1147 For A/C 001-004,

D. IR Output Data

(1) Digital output characteristics

The IRs have 4 independently buffered high-speed ARINC 429 digital
output buses, designated bus output 1, 2, 3 and 4
- digital output table:
This table contains all the output parameters in the digital form.
They are sorted as per the numerical order of their output label.
The following table gives:
- EQ.SYS.LAB.SDI : (SDAC, FWC, DMC...) output label for which the
parameter is available
- PARAMETER DEFINITION: parameter name
- WORD RANGE/OPER RANGE/RESOLUTION ACCURACY: measurement range
Maximum value transmitted. When the digital value changes, the
change step is equal to the accuracy
- UNIT : unit in which the digital value is transmitted
- SIG BIT : indicates whether a sign bit is available
- BITS : number of bits used by the parameter in the label
- XMSN/INTV: output transmission interval. The refresh rate is given
in milliseconds.
- CODE:
BNR: binary data word
BCD: binary coded decimal data word
ISO: data word coded in ISO5 code
DIS: discrete data word
HEX: hexadecimal coded
HYB: mixed code.

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R - ALPHA CODE: indicates the parameter mnemonic code
R - SOURCE ORIGIN: parameter source computer or system.
R When the input discretes of THE GPS PRESENT programming pins are
R grounded (indicating GPS present), both the GPSSU outputs and the
R GPIRS integrated navigation solution outputs are transmitted on the
R IR output buses with the IR output data.

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R -------------------------------------------------------------------------------
R | PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
R -------------------------------------------------------------------------------
R |EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
R | |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
R | |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
R | |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
R | | | | | | | | | |CONV |
R -------------------------------------------------------------------------------
R | 010 |PPOS LAT |W |Deg | | 6 |500 |BCD |LATP | |
R | | |90S-90N |& | | | | | | |
R | | |0.1 |min | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 011 |PPOS LONG |W |Deg | | 6 |500 |BCD | | |
R | | |180E-180W |& | | | | | | |
R | | |0.1 |min | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 012 |GROUND |W 0 to 2000 |Kts | | 4 |500 |BCD | GS | |
R | |SPEED |0 to 1000 | | | | | | | |
R | | |R 1 | | | | | | | |
R | | |+/- 8 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 013 |TRK ANGLE |W 0 to 359.9|Deg | | 4 |500 |BCD | | |
R | |TRUE |R 0.1 | | | | | | | |
R | | |+/- 2.3 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 014 |MAG HDG |W 0 to 359.9|Deg | | 4 |500 |BCD | MH | |
R | | |R 0.1 | | | | | | | |
R | | |+/- 3 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 015 |WIND SPEED|W 0 to 256 |Kts | | 3 |500 |BCD | WS | |
R | | |R 1 | | | | | | | |
R | | |+/- 9 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 016 |WIND DIR |W 0 to 359 |Deg | | 3 |500 |BCD | WD | |
R | |TRUE |R 1 | | | | | | | |
R | | |+/- 10 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 041 |SET LAT |W +/- 180 |Deg | | 6 |500 |BCD | | |
R | | |90S-90N |& | | | | | | |
R | | |R 0.1 |min | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 042 |SET LONG |W +/- 180 |Deg | | 6 |500 |BCD | | |
R | | |R 0.1 |& | | | | | | |
R | | | |min | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 043 |SET MAG |W 0 to 359.9|Deg | | 4 |500 |BCD | | |

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 -------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
R | |HDG |R 0.1 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 044 |TRUE HDG |W 0 to 359.9|Deg | | 4 |500 |BCD |THDG | |
R | | |R 0.1 | | | | | | | |
R | | |+/- 0.4 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 052 |PITCH |W +/- 64 |Deg/| | 15 | 20 |BNR | | |
R | |ANGULAR |R 0.002 |sec2| | | | | | |
R | |ACCEL | | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 053 |ROLL |W +/- 64 |Deg/| | 15 | 20 |BNR | | |
R | |ANGULAR |R 0.002 |sec2| | | | | | |
R | |ACCEL | | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 054 |YAW |W +/- 64 |Deg/| | 15 | 20 |BNR | | |
R | |ANGULAR |R 0.002 |sec2| | | | | | |
R | |ACCEL | | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 310 |PPOS LAT |W +/- 180 |Deg | 29 | 20 |200 |BNR | | |
R | | |+/- 90 |& | | | | | | |
R | | |R 0.00017 |min | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 311 |PPOS LONG |W +/- 180 |Deg | 29 | 20 |200 |BNR |LONP | |
R | | |R 0.00017 |& | | | | | | |
R | | | |min | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 312 |GROUND |W 0 to 4096 |Kts | | 15 | 40 |BNR | | |
R | |SPEED |R 0.125 | | | | | | | |
R | | |+/- 8 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 313 |TRK - TRUE|W +/- 180 |Deg | 29 | 15 | 40 |BNR | | |
R | | |R 0.0055 | | | | | | | |
R | | |+/- 0.23 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 314 |TRUE HDG |W +/- 180 |Deg | 29 | 15 | 40 |BNR | | |
R | | |R 0.0055 | | | | | | | |
R | | |+/- 0.4 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|

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 -------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
R | 315 |WIND |W 0 to 256 |Kts | | 15 |100 |BNR | | |
R | |SPEED |0 to 100 | | | | | | | |
R | | |R 0.0078 | | | | | | | |
R | | |+/- 8 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 316 |WIND DIR |W +/- 180 |Deg | 29 | 15 |100 |BNR | | |
R | |- TRUE |+/- 180 | | | | | | | |
R | | |R 0.0055 | | | | | | | |
R | | |+/- 10 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 317 |TRK - MAG |W +/- 180 |Deg | 29 | 15 | 40 |BNR | | |
R | | |R 0.0055 | | | | | | | |
R | | |+/- 3 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 320 |MAG HDG |W +/- 180 |Deg | 29 | 15 | 40 |BNR | | |
R | | |82 N to 60 S| | | | | | | |
R | | |R 0.0055 | | | | | | | |
R | | |+/- 3 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 321 |DRIFT |W +/- 180 |Deg | 29 | 15 | 40 |BNR | DA | |
R | |ANGLE |+/- 90 | | | | | | | |
R | | |R 0.0055 | | | | | | | |
R | | |+/- 2.3 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 322 |FLIGHT |W +/- 180 |Deg | 29 | 15 | 40 |BNR | FPA | |
R | |PATH |+/- 90 | | | | | | | |
R | |ANGLE |R 0.0055 | | | | | | | |
R | | |+/- 0.28 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 323 |FLT PATH |W +/- 4 | g | 29 | 15 | 20 |BNR |FPAC | |
R | |ACCEL |R 0.0001 | | | | | | | |
R | | |+/- 10 % of | | | | | | | |
R | | |outp | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 324 |PITCH |W +/- 180 |Deg | 29 | 15 | 20 |BNR |PTCH | |
R | |ANGLE |-90 to + 90 | | | | | | | |
R | | |R 0.0055 | | | | | | | |
R | | |+/- 0.05 | | | | | | | |

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 -------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 325 |ROLL |W +/- 180 |Deg | 29 | 15 | 20 |BNR |ROLL | |
R | |ANGLE |-90 to + 90 | | | | | | | |
R | | |R 0.0055 | | | | | | | |
R | | |+/- 0.05 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 326 |BODY AXIS |W +/- 128 |Deg/| 29 | 15 | 20 |BNR |PTCR | |
R | |PITCH RATE|+/- 45 |s | | | | | | |
R | | |R 0.0039 | | | | | | | |
R | | |+/- 0.1 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 327 |BODY AXIS |W +/- 128 |Deg/| 29 | 15 | 20 |BNR |ROLR | |
R | |ROLL RATE |+/- 45 |s | | | | | | |
R | | |R 0.0039 | | | | | | | |
R | | |+/- 0.1 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 330 |BODY AXIS |W +/- 128 |Deg/| 29 | 15 | 20 |BNR |YAW | |
R | |YAW RATE |+/- 45 |s | | | | | | |
R | | |R 0.0039 | | | | | | | |
R | | |+/- 0.1 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 331 |BODY LONG |W +/- 4 | g | 29 | 15 | 20 |BNR |LONG | |
R | |ACCEL |+/- 4.000 | | | | | | | |
R | | |R 0.0001 | | | | | | | |
R | | |+/- 0.01 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 332 |BODY LAT |W +/- 4 | g | 29 | 15 | 20 |BNR |LATG | |
R | |ACCEL |+/- 4.000 | | | | | | | |
R | | |R 0.0001 | | | | | | | |
R | | |+/- 0.01 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 333 |BODY NORM |W +/- 4 | g | 29 | 15 | 20 |BNR |VRTG | |
R | |ACCEL |+/- 4.000 | | | | | | | |
R | | |R 0.0001 | | | | | | | |
R | | |+/- 0.01 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 334 |PLATFORM |W +/- 180 |Deg | 29 | 15 | 40 |BNR | | |
R | |HEADING |R 0.0055 | | | | | | | |

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 -------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
R | | |+/- 0.23 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 335 |TRK ANGLE |W +/- 32 |Deg/| 29 | 15 | 20 |BNR | | |
R | |RATE |R 0.001 |s | | | | | | |
R | | |+/- 0.17 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 336 |PITCH ATT |W +/- 128 |Deg/| 29 | 15 | 20 |BNR | | |
R | |RATE |R 0.0039 |s | | | | | | |
R | | |+/- 0.1 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 337 |ROLL ATT |W +/- 128 |Deg/| 29 | 15 | 20 |BNR | | |
R | |RATE |R 0.0039 |s | | | | | | |
R | | |+/- 0.1 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 340 |TRACK |W +/- 180 |Deg | 29 | 15 | 40 |BNR | | |
R | |ANGLE |R 0.0055 | | | | | | | |
R | |GRID |+/- 3 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 341 |GRID |W +/- 180 |Deg | 29 | 15 | 40 |BNR | | |
R | |HEADING |R 0.0055 | | | | | | | |
R | | |+/- 3 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 360 |POTENTIAL |W +/- 32768 |ft /| 29 | 15 | 20 |BNR | | |
R | |V/S |R 1.0 | min| | | | | | |
R | | |+/- 30 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 361 |INERTIAL |W +/- 131072|ft | 29 | 20 | 40 |BNR | | |
R | |ALT |R 0.125 | | | | | | | |
R | | |+/- 5 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 362 |ALONG TRK |W +/- 4 | g | 29 | 15 | 20 |BNR | | |
R | |HORIZ |R 0.00012 | | | | | | | |
R | |ACCEL |+/- 10 % | | | | | | | |
R | | |of outp | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 363 |CROSS TRK |W +/- 4 | g | 29 | 15 | 20 |BNR | | |
R | |HORIZ |R 0.00012 | | | | | | | |
R | |ACCEL |+/- 10 % | | | | | | | |

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 -------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
R | | |of outp | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 364 |VERTICAL |W +/- 4 | g | 29 | 15 | 20 |BNR |VACC | |
R | |ACCEL |+/- 4.000 | | | | | | | |
R | | |R 0.00012 | | | | | | | |
R | | |+/- 0.01 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 365 |INERTIAL |W +/- 32768 |ft /| 29 | 15 | 20 |BNR |IVV | |
R | |V/S |R 1.0 |min | | | | | | |
R | | |+/- 30 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 366 |N - S |W +/- 4096 |Kts | 29 | 15 |100 |BNR | | |
R | |VELOCITY |R 0.125 | | | | | | | |
R | | |+/- 8 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 367 |E - W |W +/- 4096 |Kts | 29 | 15 |100 |BNR | | |
R | |VELOCITY |R 0.125 | | | | | | | |
R | | |+/- 8 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 270 |DSCRT DATA| | | | |500 |DIS | | |
R | |WORD 1 | | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 275 |DSCRT DATA| | | | |500 |DIS | | |
R | |WORD 2 | | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 276 |DSCRT DATA| | | | |500 |DIS | | |
R | |WORD 3 | | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 277 |IRS TEST | | | | |500 |HYB | | |
R | |WORD | | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 350 |ACTION | | | | |500 |HYB | | |
R | |CODE | | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 351 |IR MAINT | | | | |500 |DIS | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 354 |LRU IDENT | | | | | |ISO | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|

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 -------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
R | 356 |FAULT | | | | | |ISO | | |
R | |STAT | | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 377 |EQUIP | | | | |500 |HEX | | |
R | |IDENT | | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 076 |GPS ALT |W +/- 131072|ft | | 20 |666 |BNR | | |
R | |(MLS) |R 0.125 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 101 |HDOP |W 0 to 1024 | | | 15 |666 |BNR | | |
R | | |R 0.031 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 102 |VDOP |W 0 to 1024 | | | 15 |666 |BNR | | |
R | | |R 0.031 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 103 |GPS TRACK |W +/- 180 |DEG | | 15 |666 |BNR | | |
R | |ANGLE TRUE|R 0.0055 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 110 |GPS PRES |W +/- 90 |DEG | | 20 |666 |BNR | | |
R | |POS-LAT |R 0.000172 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 111 |GPS PRES |W +/- 180 |DEG | | 20 |666 |BNR | | |
R | |POS-LONG |R 0.000172 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 112 |GPS GROUND|W 0 to 4096 |KTS | | 15 |666 |BNR | | |
R | |SPEED |R 0.125 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 120 |GPS PRES |W +/- |DEG | | 11 |666 |BNR | | |
R | |POS-LAT |0.000172 | | | | | | | |
R | |FINE |R 8.38 E-8 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 121 |GPS PRES |W +/- |DEG | | 11 |666 |BNR | | |
R | |POS-LONG |0.000172 | | | | | | | |
R | |FINE |R 8.38 E-8 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 125 |GPS UTC |W 23:59.9 |H/ | | 5 |666 |BCD | | |
R | | |R 0.1 min |min | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|

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 -------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
R | 130 |GPS INTEG |W 0 to 16 |NM | | 18 |666 |BNR | | |
R | |LIMIT |R 1.2 E-4 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 131 |HYB INTEG |W 0 to 16 |NM | | 18 |666 |BNR | | |
R | |LIMIT |R 6.1 E-5 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 132 |HYB TRUE |W +/- 180 |DEG | | 15 | 40|BNR | | |
R | |HEADING |R 0.0055 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 135 |HYB VERT |W 0 to 32768|ft | | 18 |666 |BNR | | |
R | |FOM |R 0.125 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 136 |GPS VERT |W 0 to 32768|ft | | 18 |666 |BNR | | |
R | |FOM |R 0.125 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 137 |HYB TRACK |W +/- 180 |DEG | | 15 | 40|BNR | | |
R | |ANGLE TRUE|R 0.0055 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 143 |TERMINAL |W 0 to 16 |NM | | 17 |666 |BNR | | |
R | |AREA HIL |R 1.22 E-4 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 150 |GPS UTC |W 23:59:59 |H:M | | 17 |666 |BNR | | |
R | | |R 1.0 |:S | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 162 |DESTINA- |W 23:59 |H:M | | 11 |333 |BNR | | |
R | |TION ETA |R 1 |M | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 163 |ALT |W 23:59 |H:M | | 11 |333 |BNR | | |
R | |WAYPOINT |R 1 |M | | | | | | |
R | |ETA | | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 165 |GPS VERT |W +/- 32768 |ft/ | | 15 |666 |BNR | | |
R | |SPEED |R 1.0 |mn | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 166 |GPS N/S |W +/- 4096 |kts | | 15 |666 |BNR | | |
R | |VELOCITY |R 0.125 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 174 |GPS E/W |W +/- 4096 |kts | | 15 |666 |BNR | | |

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 -------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
R | |VELOCITY |R 0.125 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 175 |HYB GROUND|W 0 TO 4096 |kts | | 15 | 40|BNR | | |
R | |SPEED |R 0.125 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 247 |GPS HORIZ |W 0 TO 16 |NM | | 18 |666 |BNR | | |
R | |FOM |R 6.1 E-5 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 254 |HYB LAT |W +/- 90 |DEG | | 20 |80 |BNR | | |
R | | |R 0.000172 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 255 |HYB LONG |W +/- 180 |DEG | | 20 |80 |BNR | | |
R | | |R 0.000172 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 256 |HYB LAT |W 0.000172 |DEG | | 11 |80 |BNR | | |
R | |FINE |R 8.38 E-8 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 257 |HYB LONG |W 0.000172 |DEG | | 11 |80 |BNR | | |
R | |FINE |R 8.38 E-8 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 260 |GPS DATE |W 31:12:99 |D:M | | 6 |666 |BCD | | |
R | | |R 1 |:D | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 261 |HYB ALT |W +/- 131072|ft | | 20 | 40|BNR | | |
R | |(MSL) |R 0.125 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 263 |HYB FLIGHT|W +/- 90 |DEG | | 12 | 40|BNR | | |
R | |PATH ANGLE|R 0.044 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 264 |HYB HORIZ |W 0 to 16 |NM | | 18 |666 |BNR | | |
R | |FOM |R 6.1 E-S | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 266 |HYB N/S |W 0 TO 4096 |kts | | 15 |80 |BNR | | |
R | |VELOCITY |R 0.125 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 267 |HYB E/W |W 0 TO 4096 |kts | | 15 |80 |BNR | | |
R | |VELOCITY |R 0.125 | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|

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 -------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
R | 273 |GPS SENSOR| N/A | | | |666 |DIS | | |
R | |STATUS | | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 274 |GPIRS | | | | |666 |DIS | | |
R | |SENSOR | N/A | | | | | | | |
R | |STATUS | | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 343 |DESTINA- |W 0 to 16 |NM | | 13 |333 |BNR | | |
R | |TION HIL | | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 345 |HYB VERT |W +/- 32768 |ft/ | | 15 | 40|BNR | | |
R | |VELOCITY |R 1.0 |mn | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 347 |ALT |W 0 to 16 |NM | | 13 | 333|BNR | | |
R | |WAYPOINT | | | | | | | | |
R | |HIL | | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 352 |GPSSU RCVR| N/A | | | |666 |DIS | | |
R | |MAINT | | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 353 |GPIRS | N/A | | | |666 |DIS | | |
R | |MAINT WORD| | | | | | | | |
R |--------------|----------|------------|----|----|----|----|----|-----|-------|
R | 355 |GPSSU NAV | N/A | | | |666 |DIS | | |
R | |MAINT | | | | | | | | |
R -------------------------------------------------------------------------------
R Table 7A :IR Digital Output Characteristics

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R **ON A/C ALL

----------------------------------------------------------------------------
| BIT | SIGNAL | W1W CONDITION |
|-----|--------------------|-----------------------------------------------|
| 1 | 1 - | |
| 2 | 0 | | |
| 3 | 1 | | |
| 4 | 1 | LABEL 270 | |
| 5 | 1 | | |
| 6 | 0 | | |
| 7 | 0 | | |
| 8 | 0 - | |
| 9 | SDI - LSB | |
| 10 | SDI - MSB | |
| 11 | Alignment Not Ready| In Align Submode |
| 12 | Rev Att Mode | In Attitude Mode |
| 13 | Nav Mode | In Nav Mode |
| 14 | Valid Set Heading | A valid set heading has to be input to the |
| | | IR. Magnetic heading outputs are no longer |
| | | being computed, but have the characteristics |
| | | of a WFree Direction GyroW. |
| 15 | Attitude Invalid | Attitude Critical Fault |
| 16 | DC Fail | DC Power Less Than 18V |
| 17 | On DC | On DC Power |
| 18 | ADR Fault | The IR has detected an ADR input (TAS, ALT |
| | | and ALT RATE) as FW or NCD. Note functional |
| | | test data is ignored by the IR and last valid |
| | | input is used. |
| 19 | IR Failure | Navigation (Non Critical) Fault |
| 20 | DC Fail - On DC | The IR has detected that a DC fail occurred |
| | | while on DC from last turn on. |
| 21 | Align Fault | The IR has detected a position miscompare |
| | | or a Quality of Align fault. |
| 22 | No IR Initial | IR does not have position data or data |
| | | received is invalid. |
| 23 | Excess Motion Error| X or Y velocity greater than 0.011 ft/s |
| | | during align. |
| 24 | ADR/IR Fault | No data has been received from the ADR or |
| | | was received with a parity error. |
| 25 | Extreme Latitude | Latitude exceeds 73⁰N (+/-0.5⁰ hysteresis) |
| | | while Longitude is between 120⁰W and 90⁰W |
| | | (+/-2.5⁰ hysteresis) or Latitude exceeds |
| | | 82⁰N (+/-0.5⁰ hysteresis) or Latitude |
| | | exceeds 60⁰S (+/-0.5⁰ hysteresis). |
| | | Magnetic Deviation is set to zero. |

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 ----------------------------------------------------------------------------
| BIT | SIGNAL | W1W CONDITION |
|-----|--------------------|-----------------------------------------------|
| 26 | Align Time Status | Bits 28 27 26 Time Until Nav |
| 27 | | 1 1 1 7 - 10 minutes |
| 28 | | 1 1 0 6 minutes |
| | | 1 0 1 5 minutes |
| | | 1 0 0 4 minutes |
| | | 0 1 1 3 minutes |
| | | 0 1 0 2 minutes |
| | | 0 0 1 1 minute |
| | | 0 0 0 IN NAV MODE ONLY |
| 29 | COMPUT LAT MISCOMP | SIN/COS OF LATITUDE TEST FAILED |
| 30 | SSM | |
| 31 | SSM | |
| 32 | Parity | |
----------------------------------------------------------------------------
Digital Word 270 (IR Discretes)

(Ref. Fig. 005, 006, 007)

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 Digital Word 275 IR Discrete 2
Figure 005

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 Digital Word 276 IR Discrete 3
Figure 006

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 Digital Word 351 IR Maintenance
Figure 007

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 The data field of the test word 277 (21 bits) alternates between the
four first patterns shown in the following table below, except during
the REALIGN DECISION submode and the POWER OFF submode. During these
submodes the data field shall be as shown in pattern 5.

----------------------------------------------------------------------------
| BIT | DEFINITION |
|--------------------------------------------------------------------------|
| 1 | 1 - |
| 2 | 0 | |
| 3 | 1 | |
| 4 | 1 | LABEL 277 |
| 5 | 1 | |
| 6 | 1 | |
| 7 | 1 | |
| 8 | 1 - |
|--------------------------------------------------------------------------|
| 9 | SDI |
| 10 | SDI |
|---------|----------------------------------------------------------------|
| |PATTERN 1 |PATTERN 2|PATTERN 3|PATTERN 4| PATTERN 5 |
|---------|----------|---------|---------|---------|-----------------------|
| 11 | 0 | 0 | 1 | 1 | BCD MODE TIMER |
| 12 | 1 | 1 | 0 | 0 | (LSD) |
| 13 | 0 | 1 | 1 | 0 | (REALIGN AND |
| 14 | 1 | 1 | 0 | 0 | POWER OFF) |
|---------|----------|---------|---------|---------------------------------|
| 15 | 0 | 0 | 1 | 1 | BCD MODE TIMER |
| 16 | 1 | 1 | 0 | 0 | (MSD) |
| 17 | 0 | 1 | 1 | 0 | (REALIGN AND |
| 18 | 1 | 1 | 0 | 0 | POWER OFF) |
|---------|----------|---------|---------|---------------------------------|
| | | | | | MODE FLAG: |
| 19 | 0 | 0 | 1 | 1 | 00 = PWR OFF SUBMODE |
| 20 | 1 | 1 | 0 | 0 | 11 = REALIGN DECISION |
| | | | | | SUBMODE |
|---------|----------|---------|---------|---------|-----------------------|
| 21 | 0 | 1 | 1 | 0 | 0 |
| 22 | 1 | 1 | 0 | 0 | 0 |
| 23 | 0 | 0 | 1 | 1 | 0 |
| 24 | 1 | 1 | 0 | 0 | 0 |
| 25 | 0 | 1 | 1 | 0 | 0 |
| 26 | 1 | 1 | 0 | 0 | 0 |
| 27 | 0 | 0 | 1 | 1 | 0 |
| 28 | 1 | 1 | 0 | 0 | 0 |
| 29 | 0 | 1 | 1 | 0 | 0 |
| 30 | 0 | 0 | 1 | 0 | 0 |

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 ----------------------------------------------------------------------------
| BIT | DEFINITION |
|--------------------------------------------------------------------------|
| 31 | 0 | 0 | 1 | 1 | 0 |
|---------|----------|---------|---------|---------|-----------------------|
| 32 | Parity |
----------------------------------------------------------------------------
Digital Word 277 (CDU Test Word)

NOTE : Time (seconds) remaining in the POWER OFF submode and the time
____
(seconds) remaining in the REALIGN DECISION submode are
transmitted with the BCD data (bits 11-18).

----------------------------------------------------------------------------
| BIT | DEFINITION |
|--------------------------------------------------------------------------|
| 1 | 1 - |
| 2 | 1 | |
| 3 | 1 | |
| 4 | 0 | LABEL 350 |
| 5 | 1 | |
| 6 | 0 | |
| 7 | 0 | |
| 8 | 0 - |
|--------------------------------------------------------------------------|
| 9 | SDI - LSB |
| 10 | SDI - MSB |
|--------------------------------------------------------------------------|
| 11 TO 14 | SPARE |
|----------|---------------------------------------------------------------|
| 15 | TIME UNTIL NAV LEAST |
| 16 | TIME UNTIL NAV SIGNIFICANT |
| 17 | TIME UNTIL NAV DIGIT |
| 18 | TIME UNTIL NAV (BCD) |
|----------|---------------------------------------------------------------|
| 19 | TIME UNTIL NAV MOST |
| 20 | TIME UNTIL NAV SIGNIFICANT |
| 21 | TIME UNTIL NAV DIGIT |
| 22 | TIME UNTIL NAV (BCD) |
|----------|---------------------------------------------------------------|
| 23 | Action Code (1) Least |
| 24 | Action Code (1) Significant |
| 25 | Action Code (1) Digit |
| 26 | Action Code (1) |
|----------|---------------------------------------------------------------|
| 27 | Action Code (1) Most |
| 28 | Action Code (1) Significant |

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 ----------------------------------------------------------------------------
| BIT | DEFINITION |
|--------------------------------------------------------------------------|
| 29 | Action Code (1) Digit |
|----------|---------------------------------------------------------------|
| 30 | SSM |
| 31 | SSM |
| 32 | Parity |
----------------------------------------------------------------------------
Digital Word 350 (Action Code)

NOTE : (1) The action codes corresponding to the maintenance messages

____
are listed in the following table.

---------------------------------------------------------------------------
| ACTION CODE | MAINTENANCE MESSAGE | DESCRIPTION |
|-------------|---------------------|-------------------------------------|
| 01 | IR FAULT | Critical failure; Remove ADIRU for |
| | | maintenance |
| 02 | DELAYED MAINT | Non-Critical failure; Service ADIRU |
| | | when convenient |
| 03 | ENTER PPOS | Enter present position |
| 04 | SELECT ATT | Hard failure; Select ATTITUDE MODE |
| 05 | EXCESS MOTION | Excess motion detected during ALIGN |
| 06 | SWITCH ADR | Air Data Reference invalid |
| 07 | CHK C/B | Check circuit breakers |
| 08 | CDU FAULT | Remove CDU for maintenance |
| 09 | ENTER HEADING | Enter heading for ATTITUDE MODE |
| 10 | | Unassigned TBD |
----------------------------------------------------------------------------
Action Code - Maintenance Messages

(Ref. Fig. 005, 006, 008)

-------------------------------------------------------------------------------
| BIT No.| FUNCTION |
|--------|--------------------------------------------------------------------|
| 9 | SDI |
| 10 | SDI |
| 11 | MSB OF SATELLITES VISIBLE (16) |
| 12 | DADS STATUS Present = 0 Not present = 1 |
| 13 | DADS SOURCE Primary = 0 Secondary = 1 |
| 14 | IRS/FMS STATUS Present = 0 Not present = 1 |
| 15 | IRS/FMS SOURCE Primary = 0 Secondary = 1 |
| 16 | - |
| 17 | | NUMBER OF SATELLITES VISIBLE (0-15) |
| 18 | | |

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 IR - Binary Output Words
Figure 008

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 -------------------------------------------------------------------------------
| BIT No.| FUNCTION |
|--------|--------------------------------------------------------------------|
| 19 | - |
| 20 | - |
| 21 | | NUMBER OF SATELLITES TRACKED (0-15) |
| 22 | | |
| 23 | - |
| 24 | - 00 = GPS |
| | | SYSTEM DESIGNATOR 01 = GLONASS |
| | | 10 = GPS GLONASS |
| 25 | - 11 = Spare |
| 26 | - |
| 27 | | GPSSU OPERATIONAL MODE (Ref table below) |
| 28 | - |
| 29 | MSB OF TRACKED SATELLITES |
| 30 | SSM |
| 31 | SSM |
| 32 | PARITY |
-------------------------------------------------------------------------------
Discrete Word 273 Output Format

-----------------------------------------------------------
| GPSSU MODE | BIT 28 | BIT 27 | BIT 26 |
-----------------------------------------------------------
| SELF TEST | 0 | 0 | 0 |
| INITIALIZATION | 0 | 0 | 1 |
| ACQUISITION | 0 | 1 | 0 |
| NAVIGATION | 0 | 1 | 1 |
| ALTITUDE AIDING | 1 | 0 | 0 |
| DIFFERENTIAL MODE | 1 | 0 | 1 |
| DIR/SPEED AIDING MODE | 1 | 1 | 0 |
| FAULT | 1 | 1 | 1 |
-----------------------------------------------------------

-------------------------------------------------------------------------------
| BIT No.| FUNCTION |
|--------|--------------------------------------------------------------------|
| 9 | - |
| 10 | | |
| 11 | | SPARE |
| 12 | | |
| 13 | | |
| 14 | - |
| 15 | - |
| | | SECONDARY GPSSU VALIDITY 00 = Valid |
| 16 | - 01 = Inactive |

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 -------------------------------------------------------------------------------
| BIT No.| FUNCTION |
|--------|--------------------------------------------------------------------|
| 17 | - 10 = Functional Test |
| | | PRIMARY GPSSU VALIDITY 11 = Fail |
| 18 | - |
| 19 | GPSSU SOURCE Primary = 0 Secondary = 1 |
| 20 | - |
| 21 | | NUMBER OF SATELLITES TRACKED (0-15) |
| 22 | | |
| 23 | - |
| 24 | - |
| | | SPARE |
| 25 | - |
| 26 | - |
| 27 | | GPIRS SENSOR OPERATIONAL MODE (Ref table below) |
| 28 | - |
| 29 | MSB OF TRACKED SATELLITES (16) |
| 30 | SSM |
| 31 | SSM |
| 32 | PARITY |
-------------------------------------------------------------------------------
Discrete Word 274 Output Format

-----------------------------------------------------------
| GPIRS MODE | BIT 28 | BIT 27 | BIT 26 |
-----------------------------------------------------------
| SELF TEST | 0 | 0 | 0 |
| INITIALIZATION | 0 | 0 | 1 |
| ACQUISITION | 0 | 1 | 0 |
| NAVIGATION | 0 | 1 | 1 |
| ALTITUDE AIDING | 1 | 0 | 0 |
| SPARE | 1 | 0 | 1 |
| SPARE | 1 | 1 | 0 |
| FAULT | 1 | 1 | 1 |
-----------------------------------------------------------

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 -------------------------------------------------------------------------------
| BIT N⁰ | FUNCTION |
|--------|--------------------------------------------------------------------|
| 9 | GPS SYSTEM FAILURE |
| 10 | DUAL GPS CHANNEL FAIL |
| 11 | NO IR DATA |
| 12 | INVALID IR DATA |
| 13 | TM MISSING ON PRIMARY |
| 14 | TM MISSING ON SECONDARY |
| 15 | ARINC TRANSMISSION FAULT |
| 16 | NO AUTONOMOUS DATA FROM PRIMARY |
| 17 | NO AUTONOMOUS DATA FROM SECONDARY |
| 18 | AUTONOMOUS/IRS LATITUDE MISCOMPARE |
| 19 | SPARE |
| 20 | AUTONOMOUS/IRS LONGITUDE MISCOMPARE |
| 21 | SPARE |
| 22 | CLOCK PHASE MISCOMPARE ON PRIMARY |
| 23 | CLOCK PHASE MISCOMPARE ON SECONDARY |
| 24 | TM TIMING/UTC MISCOMPARE ON PRIMARY |
| 25 | TM TIMING/UTC MISCOMPARE ON SECONDARY |
| 26 | - |
| 27 | | RESERVED |
| 28 | | |
| 29 | - |
| 30 | SSM |
| 31 | SSM |
| 32 | PARITY |
-------------------------------------------------------------------------------
ADIRU Maintenance Word 353

-------------------------------------------------------------------------------
| BIT No.| FUNCTION |
|--------|--------------------------------------------------------------------|
| 9 | SDI (LSB) |
| 10 | SDI (MSB) |
| 11 | - |
| 12 | | |
| 13 | | |
| 14 | | RESERVED |
| 15 | | |
| 16 | | |
| 17 | - |
| 18 | CMC INPUT BUS (OMS) No activity = 1 |
| 19 | DIFF BUS No. 2 No activity = 1 |
| 20 | DIFF BUS No. 2 No activity = 1 |
| 21 | DADS BUS 2 No activity = 1 |
| 22 | DADS BUS 1 No activity = 1 |

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 -------------------------------------------------------------------------------
| BIT No.| FUNCTION |
|--------|--------------------------------------------------------------------|
| 23 | IRS INPUT BUS 2 No activity = 1 |
| 24 | IRS INPUT BUS 1 No activity = 1 |
| 25 | GPS Fail = 1 |
| 26 | RF INPUT Fail = 1 |
| 27 | SENSOR UNIT Fail = 1 |
| 28 | TEST INHIBIT Inhibit = 1 |
| 29 | COMMAND WORD ACKNOWLEDGE Forced = 0 |
| 30 | SSM |
| 31 | SSM |
| 32 | PARITY |
-------------------------------------------------------------------------------
GPSSU Navigation Maintenance Word (Label 355)

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 (2) Discrete outputs
The IR provides 3 discrete outputs.
The following table defines the characteristics of these discretes.

---------------------------------------
| SIGNAL | OUTPUT | DEFINITION |
|----------|-------------|------------|
| ON BAT | OPEN/+28VDC | NO/YES |
| IR FAULT | OPEN/+28VDC | NO/YES |
| IR ALIGN | OPEN/GROUND | NO/YES |
---------------------------------------
Discrete Outputs

- ON BAT
When the IR is powered with batteries, this discrete delivers a
28VDC state and sets the ON BAT light to on.
- IR FAULT
When a failure is detected by the IR, this discrete delivers a
28VDC state and sets the FAULT legend to on.
- IR ALIGN
When the IR is aligning, this discrete delivers a ground and sets
the ALIGN legend to on.

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 3. Operation/Control
________________________________
and Indicating
(Ref. Fig. 009)

A. Control

(1) Modes of operation

Operation interface with the IR is performed through the Multipurpose
Control and Display Unit 1(2) or the CDU. The MCDU 1(2) is used for
entering initialization data and displaying IR data.
(Ref. Fig. 010)
The CDU is used for mode selection, IR annunciation (FAULT, ALIGN),
for entering initialization data and displaying IR data.
The IR has three selectable modes: OFF, NAV and ATT.
The relation between the mode selection and system response is shown
in the figure
(Ref. Fig. 011)

(2) OFF mode

When the OFF/NAV/ATT selector switch on the CDU is in the OFF
position, all circuitry in ADIRU is de-energized except for any logic
associated with the power-off function. When the ADIRU has turned
off, it consumes less than 10 milliamps (needed for power supply
turn-on control). The power supply of the ADMs is switched off.
A period of 15 seconds is required between switching to OFF and
actual power off. During this sequence, the last position computed is
stored in NVM.

(3) NAV (Navigation) mode

After selection of the NAV mode on the ground, the IR automatically
enters the NAV mode if a self-determined satisfactory alignment has
been completed. If alignment is not completed, the IR remains in the
Align submode.
No updating of the IR present position latitude and longitude is
allowed once the IR has completed the Align submode.
The IR latitude and longitude entered during alignment is the
starting point for its computation.
The following logical processes are mechanized:
- OFF to NAV provides automatic alignment in 10 minutes for latitudes
between 73⁰N and 60⁰S, with automatic entry to NAV mode. Requires
initial position data to be entered.

NOTE : The automatic alignment requires 15 min delay for latitudes

____
between 73⁰N and 82⁰N.
For high latitudes, the alignment is provided by an
operational procedure which delays the entering of the initial
position by the crew. Accuracies of the system are slightly
degraded.

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 IR - Operation/Control and Indicating
Figure 009

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 IR - Alignment Procedure from the MCDU
Figure 010

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 IR - Mode State Diagram
Figure 011

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 - a message on the UPPER ECAM DU indicates that the IRs are in ALIGN
submode with the maximum time until NAV
- in the NAV mode, rapid realignment of the IR is initiated by
switching the OFF/NAV/ATT selector switch from NAV to OFF and back
to NAV within 5 seconds. The IR starts a 30-second realignment
submode with existing attitude and heading angles and rezeroed
velocities
- the system does not enter the rapid realignment sequence if the
ground speed is greater than 20 knots.
The CDU permits to observe some particular parameters (Ref.
34-12-00).

(a) Initialization data

(Ref. Fig. 012)
IR alignment is carried out on the ground before takeoff and
after the entry of the current aircraft coordinates on the INIT
page of the MCDU 1(2) (Ref. 22-72-00) or on the CDU (DATA DISPLAY
selector switch in PPOS position).
Valid initial position data must be received and verified by the
IR during the 10-minute alignment or automatic sequencing to the
NAV mode will be delayed after position data is received.
Initial position data are verified by the IR if Set Latitude and
Set Longitude compare within one degree of the last latitude and
longitude from the previous flight. If a miscompare exists then:
- on the ADIRS CDU, the ALIGN light flashes.
- a message ENTER PPOS is displayed on the CDU (DATA DISPLAY
selector switch in STS position).
The miscompare is removed and the position data verified by the
IR when:
- the last two Set Latitudes received by the IR are identical and
the last two Set Longitudes received by the IR are identical,
or
- the last Set Latitude and Set Longitude received by the IR
compare within one degree of the latitude and longitude from
the previous flight.

(b) Latitude comparison

The IR compares Set Latitude with a self-computed gyro-compass
latitude after 10 minutes into alignment or any subsequent time
when a valid Set Latitude is available.
In case of discrepancy, on the ADIRS CDU the ALIGN light flashes.
The message ENTER PPOS is displayed on the CDU (DATA DISPLAY
selector switch in STS position).
The discrepancy exists when:
- the cosine of entered latitude differs from the computed cosine
of latitude by more than 0.01234, or

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 MCDU - INIT Page
Figure 012

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 - the sine of entered latitude differs from the computed sine of
latitude by more than 0.01234.
The miscompare is removed if a subsequent entry of Set Latitude
passes the test.
If sin/cos test fails two times with identical set latitude
inputs then:
- the IR FAULT legend flashes on the CDU
- a warning message appears on the upper ECAM DU:
NAV IR 1(2)(3) FAULT.

(c) Excessive motion

The IR performs an excessive motion test during the Align
submode.
If taxiing or towing causes a step input which exceeds 0.5 ft/s
in the X or Y velocity, then:
- the EXCESS MOTION message is displayed on the CDU (DATA DISPLAY
selector switch in STS position)
- the following message is displayed on the upper ECAM DU:
NAV
IR 1(2)(3) NOT ALIGN
EXCESS MOTION
IR 1(2)(3) IN ALIGN

- the attitude information is flagged on the PFD.

Thirty seconds after motion detection, the system reverts to a
full alignment (time to the end of alignment will revert to 9 min
30 s).
It is not necessary to re-enter the position.

(d) Thirty-second rapid realignment

A thirty-second rapid realignment is provided by moving the
OFF/NAV/ATT selector switch on the CDU from NAV to OFF and back
to NAV within five seconds.
A subsequent switching on the selector switch from NAV to OFF and
back to NAV within 5 seconds during the 30-second realignment
causes the system to start the 30-second realignment again.
The realignment is initialized with existing attitude and heading
angles. Velocities are zeroed.
Valid position data must be received and verified by the IR
during the 30-second realignment.

(4) ATT (Attitude) mode

The IR has a reversionary mode which can be activated only by manual
selection of ATT mode on the CDU. The mode can be activated on the
ground or in the flight and is intended to provide a rapid
attitude/heading restart capability in the event that the IR has

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 experienced a total power shutdown or a failure has occurred
resulting in the following:
- IR FAULT legend flashing on the CDU
- IR 1(2)(3) FAULT message displayed on the upper ECAM DU:
IR x MODE SEL...ATT
- SELECT ATT message displayed on the CDU (DATA DISPLAY selector
switch in STS position).
The IR is designed so that the ATT mode can be used after BITE has
detected failures which will cause excessive NAV mode data errors but
does not disable the ATT mode mechanization. However, it is
recommended to stay in NAV mode even with excessive navigation errors
because of higher accuracy of attitude signals and a more complete
signal processing. The ATT mode must always be used after loss of
power or a similar situation in flight where a new alignment/leveling
is required.
The ENTER HEADING message is displayed on the CDU (DATA DISPLAY
selector switch in STS position) when the ATT mode is selected until
valid heading initialization is received from the MCDU or the CDU.
The ATT mode is normally engaged with the aircraft in level flight.
A 20-second period is needed with the aircraft in level flight to
perform an attitude erection to initialize a WlevelW attitude. During
this period, the data normally computed in ATT mode have SSMs set to
NCD.
In the event the ATT mode is engaged with the aircraft not in level
flight, an erection cut-out function delays erection when yaw rate
exceeds 0.5 deg/s and permits erection to continue when yaw rate
drops below 0.25 deg/s. Twenty seconds of flight with the erection
cut-out switch disengaged is required to erect the attitude.

B. Indicating
Attitude and heading information is computed by the ADIRU (IR portion)
and processed by the associated DMC. The attitude data are displayed on
R the PFD and the heading data are displayed on the PFD, the ND and the
R RMI.
In addition, vertical speed (V/S) is displayed on the PFD and Ground
Speed and wind indications are displayed on the ND.
In normal configuration, with the ATT/HDG selector switch in NORM
R position, the IR1 data are displayed on the CAPT PFD, ND and the RMI
R (Ref. ATA 34-57-00). The IR2 data are displayed on the F/O PFD and ND.
The following parameters can be displayed on the CDU liquid crystal
display according to the position of the DATA DISPLAY selector switch on
the CDU:
- wind (WIND)
- present position (PPOS)
- true heading (HDG)
- status of selected system conditions (STS)
- track and ground speed (TK/GS)

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 - test values (TEST).
The sources of the data displayed are controlled by the SYS DISPLAY
selector switch on the CDU.

(1) Attitude information

(Ref. Fig. 013)
The aircraft roll and pitch attitude is indicated in the center part
of the PFD by a sphere representing a conventional ADI drum. (Ref.
31-64-00 for sphere definition and display).

(a) Pitch angle information (item A)

The A/C present pitch angle is given by the vertical
displacements of the pitch attitude scale with respect to the
center of the A/C reference. The scale moves behind the
cut-sphere shaped window, limited by the lines of an upper and a
lower sector. The scale rotates around the center of the A/C
reference in accordance with the A/C present roll angle.
The pitch scale comprises white reference lines and associated
pitch angle values. The lines are given every 2.5 degrees from 0
to 10 degrees, then for the 15 degrees, 20 degrees, 30 degrees,
50 degrees and 80 degrees values. Beyond 30 degrees, red large
arrow heads (V-shaped) indicate an excessive attitude and the
direction to follow in order to reduce it (item B).

(b) Roll angle information (item A)

A yellow triangle which remains on the line going through the
center of the A/C reference and which is perpendicular to the
horizon line, moves against the fixed roll scale on the upper
contour of the attitude sphere.
This fixed roll scale comprises white marks for the 10 degrees,
20 degrees, 30 degrees and 45 degrees significant values, on
either side of the zero position (horizontal wings) which is
indicated by a small fixed triangle. The 60 degrees roll
indication corresponds to the limits of the upper contour of the
cut-sphere shaped window.

(c) Attitude failure

In case of attitude failure concerning the pitch and/or roll
information the attitude sphere goes out of view and is replaced
by a red ATT flag which flashes for a few seconds then remains
steady (item C).
In case of discrepancy detected by the FWC between the pitch or
roll attitude information presented on the CAPT and F/O PFDs, a
CHECK ATT amber message flashes for a few seconds on both PFDs,
then remains steady (item D).

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 IR - Attitude Information Display
Figure 013

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 (2) Heading information
(Ref. Fig. 014)
The aircraft magnetic or true heading is displayed on the PFD, the ND
R and the RMI.
The true heading can be displayed on the CDU.

(a) On the PFD

When true heading is displayed, a TRUE white message appears
above the heading scale (item A).
A blank heading scale (with 10 deg. spaced marks without any
indicated value) is provided on the horizon line. The marks are
just under this line.
This scale moves as the aircraft heading varies. For important
nose-up or nose- down, the heading graduations remain at the
lower or upper sector limit.
Below the sphere, a heading scale provides the pilot with the
aircraft actual track and relative selection. This heading scale
is graduated every 5 deg. (item A).
In case of failure, the heading graduation disappears on the two
scales and a red HDG flag appears on the lower heading scale
(item B). It flashes for a few seconds, then remains steady.
Furthermore, in case of discrepancy detected by the FWC between
CAPT and F/O heading indications, with the heading signal valid,
a CHECK HDG amber message is displayed at the center of the
heading scale (item C).

(b) On the ND
(Ref. Fig. 015)
The heading data is displayed on the ND in the three following
operating modes: ROSE, ARC and PLAN.
The ROSE mode and the ARC mode are oriented with respect to the
aircraft heading, while the PLAN mode is oriented with respect to
the true north.

1
_ True heading display
In ROSE or ARC mode, when true heading is displayed, a cyan
TRUE message appears at the top of the ND.

2
_ ROSE mode (item A)
In this mode each pilot has three different sub-modes of
presentation on his ND: ROSE-ILS/ROSE-VOR/ROSE-NAV.
In the three ROSE sub-modes, the ND provides a display which
is similar to that of a conventional HSI, i.e. a rotating
heading dial orientated to the North and giving to the pilot
the aircraft actual magnetic or true heading with as reference
the fixed yellow lubber line at the top of the dial.

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 IR - Heading Information Display on the PFD
Figure 014

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 IR - Heading Information Display on the ND
Figure 015

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 3
_ ARC mode (item B)
In this mode, the ND displays a 90 deg. heading sector ahead
of the aircraft giving the aircraft actual magnetic or true
heading with respect to the fixed yellow lubber line at the
top of the scale.

4
_ PLAN mode
The ND displays a static map orientated with respect to the
true North.

5
_ Heading failure (items C and D)
In case of heading failure, the scale and all symbols
positioned on the ROSE and ARC scales go out of view; a red
HDG flag comes into view below the scale after flashing for a
few seconds, when the DMC has detected an anomaly concerning
the heading parameter.
In addition, if a discrepancy between CAPT and F/O sides is
detected by the comparison inside the FWCs, the CHECK HDG
message is displayed in amber on both NDs (item E).

R (c) On the RMI

(Ref. Fig. 016)
The heading indication is given by a dial which rotates in front
of a fixed index (item A).
In case of heading failure, the fire orange warning flag with the
black HDG inscription comes into view at the top of the compass
card (item B).
For more details, ref. 34-57-00.

(d) On the CDU

The time heading can be displayed on the CDU if the DATA DISPLAY
selector switch is placed in the HDG position.

(3) Ground speed

(Ref. Fig. 017)
The ground speed is displayed in the left upper corner of the ND for
ROSE, ARC or PLAN mode (item A).
The GS title is displayed in white color and the ground speed value
in green.
In case of failure or NCD, the ground speed value is replaced by
three dashed lines (item B).
The ground speed can also be displayed on the CDU if the DATA DISPLAY
selector switch is placed in the TK/GS position.

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 IR - Heading Information Display on the VOR/DME RMI
Figure 016

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 IR - GS, Wind, Vertical Speed Information Display
Figure 017

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 (4) Wind indications
(Ref. Fig. 017)
The wind origin, force and direction is displayed in the left upper
corner of the ND, for ROSE, ARC and PLAN mode (item A):
- the wind origin is displayed in green color in degrees with respect
to the true North
- the wind force is displayed in green color in knots
- the wind direction, in analog form, is represented by means of a
green arrow orientated with respect to the north reference in use.
This arrow is displayed only if the wind force is greater than 2
knots.
In case of failure or NCD, the digital data are replaced by three
dashed lines and the wind direction arrow disappears (item B). The
wind indications can also be displayed on the CDU if the DATA
DISPLAY selector switch is placed in the WIND position.

(5) Vertical speed

(Ref. Fig. 017)
The inertial vertical speed is displayed in the right side of the PFD
(item C).
The vertical speed scale consists of:

(a) a trapezoidal grey background colored surface

(b) a fixed white scale with 500 ft/mn spaced marks from -2000 ft/mn
to +2000 ft/mn

(c) a needle giving in analog form the actual vertical speed value

(d) a number in a moving blanking window. This window accompanies the

needle (above) the needle if V/S > 0, below if V/S < 0).
The number gives the V/S value in hundreds of ft/mn.
Between -200 ft/mn and +200 ft/mn, both the window and the number
disappear.

(e) above +6000 ft/mn (or below -6000 ft/mn), the needle remains
stopped where it is.
When the vertical speed exceeds +6000 ft/mn or -6000 ft/mn, the
digital indication and the analog needle change from green to
amber.

(f) In addition, those indications change to amber in approach, in

the following cases:
- V/S less than -2000 ft/mn below 2500 ft RA.
- V/S less than -1200 ft/mn below 1000 ft RA.

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 In case of failure, the inertial vertical speed display is
automatically replaced by the baro vertical speed display. (Ref.
34-13-00).

(6) Reconfiguration display

In case of loss of inertial parameters on the CAPT or F/O PFD and ND,
the IR3 can be used as a back up source by placing the ATT HDG
selector switch in CAPT/3 position for the CAPT PFD and ND or in
F/O/3 position for the F/O PFD and ND.

C. Warnings
(Ref. Fig. 018, 019, 020, 021, 022)

(1) In addition to the ATT or HDG flags displayed on the PFDs, NDs and on
the CDU, warning messages are displayed on the lower part of the
upper ECAM DU.

(a) NAV IR 1(2)(3) FAULT

NAV IR 1(2) + 2(3) FAULT
When these messages are displayed:
- the MASTER CAUT lights on the glareshield come on
- the Single Chime (SC) sounds
- the IR FAULT legend flashes on the CDU.

(b) NAV ATT DISCREPANCY

This message is displayed when a difference higher than 5 deg. is
detected by comparison inside the FWCs between the roll angle or
the pitch angle provided by two IRs. When it is displayed:
- the MASTER CAUT lights on the glareshield come on
- the Single Chime (SC) sounds
- the CHECK ATT message appears on the PFD.

(c) NAV HDG DISCREPANCY

this message is displayed when a difference higher than 7 deg.
(or 5 deg. in true heading) is detected by comparison inside the
FWCs between the heading value provided by two IRs. When it is
displayed:
- the MASTER CAUT lights on the glareshield come on
- the Single Chime (SC) sounds
- the CHECK HDG message appears on the PFDs and NDs.

(d) NAV GPS 1(2) FAULT

(Ref. Fig. 023)

The GPSSUs are monitored by the three ADIRUs using the status
word sent by the GPSSU and the BITE of the IR partion.
This message is accompanied by:

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 NAV IR 1(2)(3) fault message
Figure 018

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 NAV IR 1+2 FAULT Message
Figure 019

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 NAV IR 1+3 (2+3) FAULT Message
Figure 020

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 NAV ATT DISCREPANCY Message
Figure 021

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 NAV HDG DISCREPANCY Message
Figure 022

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 NAV GPS - Fault Messages
Figure 023

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 - activation of the MASTER CAUT lights on the glareshield panel
- aural warning: single chime (SC).

D. ADIRUs Performance Criteria

(1) History
The inertial parameters to be considered to evaluate the level of
performance of an inertial system after flight completion are:
- the radial position error (in NM)
- the residual ground speed error (in kts).
Depending on their magnitude noticed at the end of the flight, the
concerned inertial system(s) shall or shall not be removed from the
aircraft.

(2) Radial position error

In order to address the statistical term of this requirement with the
most relevant approximation, the removal criteria use a limit based
on the recording of the radial position error on two consecutive
flights.
The use of a two-strike method presents the advantage to decrease the
removal rate of healthy units that have shown, by chance, or by an
inaccurate position entry at alignment, a radial position error
beyond the specified criterion.
The removal boundaries described on the figure present three
different areas:
(Ref. Fig. 024)
- Area 1 - ADIRU OK all the time
- Area 2 - ADIRU to be checked after second flight
- Area 3 - ADIRU to be replaced.

NOTE : Area 2 is applicable when the residual radial position error

____
ranges within the limits described in following Para.

(a) Lower limit for removal criteria

The integration of the drift rate results in a lower limit for
the radial position error:
Radial position error (NM) = (2 (NM/h) * T (h)) + Offset (NM)
The presence of an offset is necessary to avoid the unjustified
removal of healthy units subject to the natural Schuler effects
and to the Present Position inaccuracies entered during
initialization.
It should be pointed out that the adverse impacts of such
inaccuracies over the radial position error will reveal stronger
for short flight durations (below 1.5 hour).
- Flight duration < 1.5 FH:
The lower limit of the grey band is fixed at 5 NM.
- 1.5 FH < Flight duration < 10 FH:

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 ADIRU RPE removal criteria
Figure 024

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 The lower limit of the grey band is fixed at 2T + 2.
- Flight duration > 10 FH:
The lower limit of the grey band is fixed at 22 NM.

(b) Upper limit for removal criteria

- Flight duration < 1.5 FH:
The upper limit of the grey band is fixed at 7.5 NM.
- 1.5 FH < Flight duration < 10 FH:
The upper limit of the grey band is fixed at 3T + 3.
- Flight duration > 10 FH:
The upper limit of the grey band is fixed at 33 NM.

(3) Residual Ground Speed Error

The residual ground speed for each IR is determined at the end of the
flight when the aircraft has come to a complete stop.

(a) Check of the residual ground speed can be made:

- On the CAPT (IR1) and F/O (IR2) Navigation Displays (ND):
The residual ground speed of the IR3 can be read on the CAPT ND
by setting the ATT HDG selector switch to CAPT/3.
- On the ADIRS CDU:
. set the DATA DISPLAY selector switch to TK/GS
. set the SYS DISPLAY selector switch to 1, 2, 3
. read the respective ground speed in the CDU display.

(b) Compare the recorded ground speed values with the following
limits:
- if the residual ground speed error is 15 kts or greater after
each of two consecutive flights, replace the ADIRU
- if the residual ground speed error is 21 kts or greater at the
end of any one flight, replace the ADIRU.

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 IR - BCD and Special Output Words
Figure 025

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 ATTITUDE, HEADING AND POSITION - ADJUSTMENT/TEST
________________________________________________

TASK 34-14-00-710-003

Operational Test of the Attitude/Heading (ATT/HDG) Switching Function

WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE
_______
YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.

1. __________________
Reason for the Job

Refer to the MPD TASK: 341400-01

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
31-60-00-860-001 EIS Start Procedure
31-60-00-860-002 EIS Stop Procedure

3. __________
Job Set-up

Subtask 34-14-00-010-050

A. Get Access

(1) Put the access platform in position at the access door 822.

(2) Open the access door 822.

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 (3) On the battery power center 105VU:
- loosen the two screws and remove the protective cover.

Subtask 34-14-00-865-054

B. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU L/G/LGCIU/SYS1/NORM 1GA C09
49VU NAV PROBES/ADIRU3/PWR/SWTG 8FP F09
49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07
49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06
105VU ADIRS/ADIRU1/28VDC 6FP1 C02

R **ON A/C 001-004,

121VU ADIRS/ADIRU/2PWR/SHED 10FP N11

121VU ADIRS/ADIRU/3PWR/SWTG 9FP N10
121VU ADIRS/ADIRU/2/26VAC AND AOA 5FP2 N09
121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N08
121VU ADIRS/ADIRU/2/115VAC 4FP2 N07
121VU ADIRS/ADIRU/3/115VAC 4FP3 N06
121VU ADIRS/ADIRU/2/28VDC 6FP2 N05
121VU ADIRS/ADIRU/3/28VDC 6FP3 N04

R **ON A/C ALL

121VU HYDRAULIC/LGCIU/SYS2 2GA Q35

121VU HYDRAULIC/LGCIU/SYS1/GRND SPLY 52GA Q34

R **ON A/C 005-099,

R 121VU ADIRS/ADIRU/2PWR/SHED 10FP N10

R 121VU ADIRS/ADIRU/3PWR/SWTG 9FP N09
R 121VU ADIRS/ADIRU/2/26VAC AND AOA 5FP2 N08
R 121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N07
R 121VU ADIRS/ADIRU/2/115VAC 4FP2 N06
R 121VU ADIRS/ADIRU/3/115VAC 4FP3 N05
R 121VU ADIRS/ADIRU/2/28VDC 6FP2 N04
R 121VU ADIRS/ADIRU/3/28VDC 6FP3 N03

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R **ON A/C ALL

Subtask 34-14-00-860-055

C. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-

002).

(2) On the overhead panel :

- on the FLT CTL panels 23VU and 24VU, make sure that the FAC, ELAC
and SEC pushbutton switches are not pushed (in). The OFF legends are
on.
- on the ADIRS CDU, make sure that the three OFF/NAV/ATT selector
switches are at OFF.

(3) Do the EIS start procedure (PFD and ND only) (Ref. TASK 31-60-00-860-
001).

4. Procedure
_________

Subtask 34-14-00-710-054

A. Operational Test of the Attitude/Heading (ATT/HDG) Switching Function

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the ADIRS CDU : On the ADIRS CDU :

- set the three OFF/NAV/ATT - the ON BAT light comes on for 5
selector switches to NAV. seconds
- the three ALIGN legends come on.
On the Captain and First Officer PFD :
- the ATT flags go out of view after
approximately 30 seconds
- the pitch and roll attitudes are
shown.

- push the ADR1, ADR2 and ADR3 - make sure that the OFF legends of the
pushbutton switches. ADR1, ADR2 and ADR3 pushbutton
switches are on.

2. On the center pedestal, on the

SWITCHING panel 8VU, set the ATT
HDG selector switch to CAPT/3.

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
3. On the ADIRS CDU, set the On the ADIRS CDU, the ALIGN legend of
OFF/NAV/ATT selector switch the IR1 annunciatior goes off
related to the IR1 to OFF. On the Captain PFD, the pitch and roll
attitudes stay in view.

4. On the center pedestal, on the On the Captain PFD, the ATT flag is
SWITCHING panel 8VU, set the ATT shown (ignore the related warnings).
HDG selector switch to NORM then
to F/O/3.

5. On the ADIRS CDU, set the - On the ADIRS CDU, the ALIGN legend of
OFF/NAV/ATT selector switch the IR2 annunciator goes off
related to the IR2 to OFF. - On the First Officer PFD, the pitch
and roll attitudes stay in view.

6. On the center pedestal, on the On the First Officer PFD, the ATT flag
SWITCHING panel 8VU, set the ATT is shown (ignore the related warnings).
HDG selector switch to NORM.

7. On the ADIRS CDU :

- set the OFF/NAV/ATT selector On the ADIRS CDU, the ALIGN legend of
switch related to the IR3 to the IR3 annunciator goes off.
OFF

5. Close-up
________

Subtask 34-14-00-860-056

A. Put the aircraft back to its initial configuration.

(1) Do the EIS stop procedure

(Ref. TASK 31-60-00-860-002).

(2) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

(3) Make sure that the work area is clean and clear of tool(s) and other
items.

(4) Put the aircraft back to the serviceable condition.

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 Subtask 34-14-00-410-050

B. Close Access

(1) Install the protective cover on the battery power center 105VU.

(2) Tighten the two screws.

(3) Close the access door 822.

(4) Remove the access platform.

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 TASK 34-14-00-710-004

Operational Test of the Attitude/Heading (ATT/HDG) Comparison Warning

WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE
_______
YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.

1. __________________
Reason for the Job

Refer to the MPD TASK: 341400-02

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific circuit breaker(s) safety clip(s)

No specific safety barriers
No specific access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
31-32-00-860-010 Procedure to Get Access to the SYSTEM REPORT/TEST NAV
Page
31-60-00-860-001 EIS Start Procedure
31-60-00-860-002 EIS Stop Procedure
34-10-00-860-004 IR Alignment Procedure

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 3. __________
Job Set-up

Subtask 34-14-00-010-051

A. Get Access

(1) Put the access platform in position at the access door 822.

(2) Open the access door 822.

(3) On the battery power center 105VU:

- loosen the two screws and remove the protective cover.

Subtask 34-14-00-865-055

B. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU L/G/LGCIU/SYS1/NORM 1GA C09
49VU NAV PROBES/ADIRU3/PWR/SWTG 8FP F09
49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07
49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06
105VU ADIRS/ADIRU1/28VDC 6FP1 C02

R **ON A/C 001-004,

121VU ADIRS/ADIRU/2PWR/SHED 10FP N11

121VU ADIRS/ADIRU/3PWR/SWTG 9FP N10
121VU ADIRS/ADIRU/2/26VAC AND AOA 5FP2 N09
121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N08
121VU ADIRS/ADIRU/2/115VAC 4FP2 N07
121VU ADIRS/ADIRU/3/115VAC 4FP3 N06
121VU ADIRS/ADIRU/2/28VDC 6FP2 N05
121VU ADIRS/ADIRU/3/28VDC 6FP3 N04

R **ON A/C ALL

121VU HYDRAULIC/LGCIU/SYS2 2GA Q35

121VU HYDRAULIC/LGCIU/SYS1/GRND SPLY 52GA Q34

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 -------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
R **ON A/C 005-099,

R 121VU ADIRS/ADIRU/2PWR/SHED 10FP N10

R 121VU ADIRS/ADIRU/3PWR/SWTG 9FP N09
R 121VU ADIRS/ADIRU/2/26VAC AND AOA 5FP2 N08
R 121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N07
R 121VU ADIRS/ADIRU/2/115VAC 4FP2 N06
R 121VU ADIRS/ADIRU/3/115VAC 4FP3 N05
R 121VU ADIRS/ADIRU/2/28VDC 6FP2 N04
R 121VU ADIRS/ADIRU/3/28VDC 6FP3 N03

R **ON A/C ALL

Subtask 34-14-00-865-056

C. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU AUTO FLT/FAC1/28VDC 5CC1 B04
105VU ELEC/CSM/G /EV AUTO/SPLY 7XE C01
121VU AUTO FLT/FAC2/28VDC 5CC2 M19

Subtask 34-14-00-860-057

D. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-

002).

(2) Do the EIS start procedure (Ref. TASK 31-60-00-860-001).

(3) On the ADIRS CDU, make sure that the three OFF/NAV/ATT selector
switches are at OFF.

(4) On the FCU, on the CAPT and F/O EFIS control sections, set the mode
selector switch to the ROSE-NAV .

(5) On one MCDU, get the SYSTEM REPORT/TEST/NAV page.

(Ref. TASK 31-32-00-860-010)

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 (6) Put thesafety barriers in position around the RAT area.

4. Procedure
_________

Subtask 34-14-00-710-055

A. Operational Test of the Attitude/Heading (ATT/HDG) Comparison Warning

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the ADIRS CDU, set the

OFF/NAV/ATT selector switches
related to the IR1 and IR2 to
NAV.

2. Align the two ADIRUs (IR)

(Ref. TASK 34-10-00-860-004).
After approximately 5 minutes,
the CAPT and F/O NDs show the
heading dial.

3. On the MCDU, on the NAV page: On the MCDU:

- push the line key adjacent to The IR1 page comes into view.
the IR1 indication

- push the line key adjacent to The IR1 INTERFACE TEST 1/2 page comes
the INTERFACE TEST indication into view.

- on the keyboard push the NEXT The IR1 INTERFACE TEST 2/2 page comes
PAGE function key. into view.

- push the line key adjacent to After two seconds :

the START TEST indication - the CAPT PFD shows this position :
ROLL 45⁰ Right.
PITCH 5⁰ Up.
- the CAPT ND shows this position :
HDG 15⁰.

NOTE : Only the test values used for

____
comparison in the FWC are shown.

On the CAPT and F/O PFDs, the CHECK ATT

indication flashes during a short time
then stays stable

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
On the CAPT and F/O NDs, the CHECK HDG
indication comes into view
On the upper ECAM display unit, these
indications come into view :
NAV IR1 FAULT
- ATT HDG SWTG....CAPT
NAV HDG DISCREPANCY
- HDG.............X CHECK
- ATT HDG SWTG....AS RQRD
NAV ATT DISCREPANCY
- ATT.............X CHECK
- ATT HDG SWTG....AS RQRD
On the panels 130VU and 131VU, the
MASTER CAUT lights come on
You can hear the single chime.

NOTE : If the aircraft heading is equal to 15 degrees, plus or minus 5

____
degrees, the CHECK HDG and HDG DISCREPANCY indications do not come
into view.

- push the line key adjacent to The test stops.

the RETURN indication. The indications above go out of view.
The attitude and heading indications
come into view.

4. On the ADIRS CDU, set the

OFF/NAV/ATT selector switches
related to the IR1 and IR2 to
OFF.

5. Close-up
________

Subtask 34-14-00-860-058

A. Put the aircraft back to its initial configuration.

(1) On the MCDU, push the MCDU MENU mode key.

(2) Do the EIS stop procedure

(Ref. TASK 31-60-00-860-002) potentiometers to OFF.

(3) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

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 (4) Make sure that the work area is clean and clear of tool(s) and other
items.

(5) Put the aircraft back to the serviceable condition.

Subtask 34-14-00-865-057

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
R 7XE, 5CC1, 5CC2

Subtask 34-14-00-410-051

C. Close Access

(1) Install the protective cover on the battery power center 105VU.

(2) Tighten the two screws.

(3) Close the access door 822.

(4) Remove the access platform.

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 TASK 34-14-00-740-001

Interface Test of the IR

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific circuit breaker(s) safety clip(s)

No specific access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
31-32-00-860-010 Procedure to Get Access to the SYSTEM REPORT/TEST NAV
Page
31-60-00-860-001 EIS Start Procedure
31-60-00-860-002 EIS Stop Procedure

3. __________
Job Set-up

Subtask 34-14-00-010-052

A. Get Access

(1) Put the access platform in position at the access door 822.

(2) Open the access door 822.

(3) On the battery power center 105VU:

- loosen the two screws and remove the protective cover.

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 Subtask 34-14-00-860-050

B. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-

002).

(2) Do the EIS start procedure (PFD and ND only) (Ref. TASK 31-60-00-860-
001).

(3) On the overhead panel :

- on the FLT CTL panels 23VU and 24VU, make sure that the FAC, ELAC
and SEC pushbutton switches are not pushed (in). The OFF legends
are on.
- on the panel 20VU, on the ADIRS CDU, make sure that the three
OFF/NAV/ATT selector switches are at OFF.

(4) On the panel 13VU, on the CAPT and F/O EFIS control sections of the
FCU, set the mode selector switch to ROSE-NAV .

(5) On the MCDU, get the SYSTEM REPORT/TEST/NAV page

(Ref. TASK 31-32-00-860-010).

NOTE : This test is for the system 1. For the systems 2 and 3, use
____
the indications between the parentheses.

Subtask 34-14-00-865-058

C. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU AUTO FLT/FCU/1 9CA1 B05
49VU L/G/LGCIU/SYS1/NORM 1GA C09
49VU NAV PROBES/ADIRU3/PWR/SWTG 8FP F09
49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07
49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06
105VU ADIRS/ADIRU1/28VDC 6FP1 C02

R **ON A/C 001-004,

R
121VU ADIRS/ADIRU/2PWR/SHED 10FP N11
121VU ADIRS/ADIRU/3PWR/SWTG 9FP N10
121VU ADIRS/ADIRU/2/26VAC AND AOA 5FP2 N09

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 -------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N08
121VU ADIRS/ADIRU/2/115VAC 4FP2 N07
121VU ADIRS/ADIRU/3/115VAC 4FP3 N06
121VU ADIRS/ADIRU/2/28VDC 6FP2 N05
121VU ADIRS/ADIRU/3/28VDC 6FP3 N04

R **ON A/C ALL

R 121VU AUTO FLT/FCU/2 9CA2 M21

121VU HYDRAULIC/LGCIU/SYS2 2GA Q35
121VU HYDRAULIC/LGCIU/SYS1/GRND SPLY 52GA Q34

R **ON A/C 005-099,

R 121VU ADIRS/ADIRU/2PWR/SHED 10FP N10

R 121VU ADIRS/ADIRU/3PWR/SWTG 9FP N09
R 121VU ADIRS/ADIRU/2/26VAC AND AOA 5FP2 N08
R 121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N07
R 121VU ADIRS/ADIRU/2/115VAC 4FP2 N06
R 121VU ADIRS/ADIRU/3/115VAC 4FP3 N05
R 121VU ADIRS/ADIRU/2/28VDC 6FP2 N04
R 121VU ADIRS/ADIRU/3/28VDC 6FP3 N03

R **ON A/C ALL

Subtask 34-14-00-865-059

D. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU AUTO FLT/FAC1/28VDC 5CC1 B04
105VU ELEC/CSM/G /EV AUTO/SPLY 7XE C01
121VU AUTO FLT/FAC2/28VDC 5CC2 M19

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 4. Procedure
_________

NOTE : In the test that follows, we use the name DDRMI for the VOR/DME RMI
____
and the VOR/ADF/DME RMI (refer to equipment on your aircraft).

Subtask 34-14-00-740-068

A. BITE Test of the IR System

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the ADIRS CDU: On the ADIRS CDU:

- set the OFF/NAV/ATT selector - the ON BAT light comes on for 5

switch related to the IR1 (IR2) seconds,
(IR3) to NAV. - the ALIGN legend of the IR1 (IR2)
(IR3) annunciator comes on.

- set the DATA DISPLAY selector

switch to TK/GS,
- set the SYS DISPLAY selector
switch to 1 (2) (3).

2. On one MCDU, on the NAV page: On the MCDU:

- push the line key adjacent to The IR1 (IR2) (IR3) page comes into
the IR1 (IR2) (IR3) indication. view.

- push the line key adjacent to The IR1 (IR2) (IR3) INTERFACE TEST 1/2
the INTERFACE TEST indication. page comes into view.

- on the keyboard, push the The IR1 (IR2) (IR3) INTERFACE TEST 2/2
function key to get the page comes into view.
INTERFACE TEST 2/2 page.

- push the line key adjacent to - from 0 to 2 seconds:

the START TEST indication. * on the ADIRS CDU, the ON BAT light,
the ALIGN (if the IRs are aligned)
and FAULT legends and the ENT and CLR
keys come on then go off,
- from 2 seconds and more:
* on the CAPT (F/O) PFD, the HDG
warning flag is no more shown and
these values come into view:
ROLL 45 deg. Right

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
PITCH 5 deg. Up.
SLIP Left
IVS -600 ft/mn.
* on the CAPT (F/O) ND, the HDG
warning flag is no more shown,
* on the DDRMI, the HDG warning flag
is no more shown,
* the CAPT (F/O) ND shows these
values:
G/S 200 Kts
WIND 030/100
HDG 15 deg.
* the DDRMI shows this value:
HDG 15 deg.
* on the ADIRS CDU, the left part of
the display window shows this track
angle true value:
00.0
The right part of the display window
shows this ground speed value:
0200

3. On the ADIRS CDU, set the DATA On the ADIRS CDU, the left part of the
DISPLAY selector switch to HDG. display window shows this true HDG
value:
010.0

4. On the MCDU, push the line key The test procedure stops.
adjacent to the RETURN
indication.

5. On the ADIRS CDU: On the ADIRS CDU:

- set the OFF/NAV/ATT selector

switch related to the IR1 to
OFF,

- set the OFF/NAV/ATT selector - the ON BAT light comes on for 5

switch related to the IR2 to seconds,
NAV. - the related ALIGN legend comes on.

6. Do the IR2 test as written in You must get the same results only on
para. 2. the F/O PFD and ND and on the ADIRS CDU
(no indication on the DDRMI).

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
7. On the ADIRS CDU: On the ADIRS CDU:

- set the OFF/NAV/ATT selector

switch related to the IR2 to
OFF,

- set the OFF/NAV/ATT selector - the ON BAT light comes on for 5

switch related to the IR3 to seconds,
NAV. - the related ALIGN legend comes on.

8. On the center pedestal, on the

SWITCHING panel 8VU, set the
ATT/HDG selector switch to
CAPT/3.

9. Do the IR3 test as written in You must get the same results as for
para. 2. the IR1 on the CAPT PFD and ND, the
ADIRS CDU and the DDRMI.

10. On the ADIRS CDU, set the

OFF/NAV/ATT selector switch
related to the IR3 to OFF.

5. Close-up
________

Subtask 34-14-00-860-051

A. Put the aircraft back to its initial configuration.

(1) On the MCDU, push the line key adjacent to the RETURN indication
until the CFDS menu page comes into view.

(2) Do the EIS stop procedure

(Ref. TASK 31-60-00-860-002)

(3) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

Subtask 34-14-00-865-060

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
R 5CC1, 5CC2, 7XE

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 Subtask 34-14-00-410-052

C. Close Access

(1) Install the protective cover on the battery power center 105VU.

(2) Tighten the two screws.

(3) Close the access door 822.

(4) Remove the access platform.

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 TASK 34-14-00-740-003

Read CFDIU for IR INPUT STATUS

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific circuit breaker(s) safety clip(s)

No specific access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
31-32-00-860-001 Procedure to Get Access to the SYSTEM REPORT/TEST
Menu Page
34-10-00-860-002 ADIRS Start Procedure
34-10-00-860-005 ADIRS Stop Procedure

3. __________
Job Set-up

Subtask 34-14-00-010-054

A. Get Access

(1) Put the access platform in position at the access door 822.

(2) Open the access door 822.

(3) On the battery power center 105VU:

- loosen the two screws and remove the protective cover.

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 Subtask 34-14-00-860-059

B. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-

002).

(2) Do the ADIRS start procedure (ADIRU related to the installed ADM
only)
(Ref. TASK 34-10-00-860-002)

Subtask 34-14-00-865-064

C. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU AUTO FLT/FCU/1 9CA1 B05
49VU L/G/LGCIU/SYS1/NORM 1GA C09
49VU NAV PROBES/ADIRU3/PWR/SWTG 8FP F09
49VU NAV PROBES/ADIRU 1/AND AOA 1/26VAC 5FP1 F07
49VU NAV PROBES/ADIRU1/115VAC 4FP1 F06
105VU ADIRS/ADIRU1/28VDC 6FP1 C02

R **ON A/C 001-004,

R
121VU ADIRS/ADIRU/2PWR/SHED 10FP N11
121VU ADIRS/ADIRU/3PWR/SWTG 9FP N10
121VU ADIRS/ADIRU/2/26VAC AND AOA 5FP2 N09
121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N08
121VU ADIRS/ADIRU/2/115VAC 4FP2 N07
121VU ADIRS/ADIRU/3/115VAC 4FP3 N06
121VU ADIRS/ADIRU/2/28VDC 6FP2 N05
121VU ADIRS/ADIRU/3/28VDC 6FP3 N04

R **ON A/C ALL

R 121VU AUTO FLT/FCU/2 9CA2 M21

121VU HYDRAULIC/LGCIU/SYS2 2GA Q35
121VU HYDRAULIC/LGCIU/SYS1/GRND SPLY 52GA Q34

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 -------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
R **ON A/C 005-099,

R 121VU ADIRS/ADIRU/2PWR/SHED 10FP N10

R 121VU ADIRS/ADIRU/3PWR/SWTG 9FP N09
R 121VU ADIRS/ADIRU/2/26VAC AND AOA 5FP2 N08
R 121VU ADIRS/ADIRU/3/26VAC AND AOA 5FP3 N07
R 121VU ADIRS/ADIRU/2/115VAC 4FP2 N06
R 121VU ADIRS/ADIRU/3/115VAC 4FP3 N05
R 121VU ADIRS/ADIRU/2/28VDC 6FP2 N04
R 121VU ADIRS/ADIRU/3/28VDC 6FP3 N03

R **ON A/C ALL

Subtask 34-14-00-865-065

D. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU AUTO FLT/FAC1/28VDC 5CC1 B04
121VU AUTO FLT/FAC2/28VDC 5CC2 M19

4. Procedure
_________

Subtask 34-14-00-740-065

A. Read the CFDIU for the IR INPUT STATUS

NOTE : This test is for the system 1. For the systems 2 and 3, use the
____
indications between the parentheses.
The actions and the results of this procedure occur on the MCDU
used.

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

On the center pedestral, on one

MCDU:

1. Get the SYSTEM REPORT/TEST/NAV The SYSTEM REPORT/TEST/NAV page comes

page (Ref. TASK 31-32-00-860- into view.
001).

2. On the NAV page

- Push the line key adjacent to - the IR1 (IR2) (IR3) page comes into
the IR1 (IR2) (IR3) indication view.

3. Push the line key adjacent to the - the INPUT STATUS page 1/6 comes into
INPUT STATUS indication view with the current on-the-ground
status of the IR1 (IR2) (IR3) inputs.

4. Push the NEXT PAGE function key - the related pages come into view.
to get the INPUT STATUS page 2/6
to 6/6

5. Push the line key adjacent to the - the test procedure stops.
RETURN indication

5. Close-up
________

Subtask 34-14-00-860-060

A. Put the aircraft back to its initial configuration.

(1) On the center pedestal, on the MCDU, push the line key adjacent to
the RETURN indication until the MCDU MENU page comes into view.

(2) Do the ADIRS Stop Procedure(Ref. TASK 34-10-00-860-005).

(3) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

Subtask 34-14-00-865-066

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
5CC1, 5CC2

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 Subtask 34-14-00-410-054

C. Close Access

(1) Install the protective cover on the battery power center 105VU:

(2) Tighten the two screws.

(3) Close the access door 822.

(4) Remove the access platform.

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 ADIRS - BITE - DESCRIPTION AND OPERATION
________________________________________

1. _______
General
The Built-in Test Equipment (BITE) facilitates maintenance on in-service
aircraft.
It detects and identifies faults related to the Air Data/Inertial Reference
System (ADIRS) and reports them to the Centralized Fault Display Interface
Unit (CFDIU).
The BITE is included in the following LRUs:
- Air Data/Inertial Reference Unit (ADIRU)
- Air Data Module (ADM)
- Control and Display Unit (CDU).
It is linked to the CFDIU through the ADIRU (ADR and IR portions) which
summarizes the BITE results for its own channel
(Ref. Fig. 001)
.
The ADM performs various tests to detect its own faults (watchdog timer, RAM
addressing, ROM, CPU, RAM, NVM etc.) and failed input signals (check of
programming pins).
Faults are annunciated to the ADR by omission or labeling of a faulty output
word (pressure label) and through the use of a discrete fault-code word
output on the ARINC bus. Fault reports are also stored in a non-volatile
memory inside the ADM.
The IR BITE monitors: the performance of both IR NAV and IR I/O processors,
external inputs (both digital and discrete), the functionality of the other
internal hardware including the power supply and the inertial sensors (gyro,
accelerometers). These BITE tests are performed either at power-up or
continuously (Ref. Para. 3.A.(2)).
Some tests enable to monitor operation errors. These are: Align in air,
Excessive Motion, Latitude Sin/Cos test. They result in IR warnings but
without fault message sent to the CFDIU. Tests and fault reactions are
described in Para. 3.B.
The ADR BITE monitors: the performance of the ADR processor, the
functionality of other ADR internal hardware, the status of analog, digital
and discrete inputs and cross-channel comparisons with the other ADRs. These
BITE tests are performed either at power-up or continuously (Ref. Para.
3.A.(3)) with the exception of cross-channel comparisons which are run once
at takeoff.
The common BITE monitors the computer performances (INTEL 80960 processor
and memories) with the following tests : watchdog timer, checksum, RAM
pattern monitor.
The ADR and IR BITEs send reports to the CFDIU through the ARINC output bus,
on label 356. These reports memorize the faults which occurred during the
last 63 flight legs with their context. They operate in two modes:
- NORMAL mode: fault reporting to the CFDIU during the flight
- INTERACTIVE mode: on the ground. Access by the MCDU MENU pages (Ref. Para.
3.B.).

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 ADIRS - Interface between one ADIRU and the CFDIU
Figure 001

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 2. __________________
Component Location

A. Computers Directly Linked to the CFDS

-------------------------------------------------------------------------------
FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA
| | | | DOOR | REF.
-------------------------------------------------------------------------------
1FP1 ADIRU-1 127 824 34-12-34
1FP2 ADIRU-2 128 824 34-12-34
1FP3 ADIRU-3 127 824 34-12-34

B. ADIRS Control Panel

-------------------------------------------------------------------------------
FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA
| | | | DOOR | REF.
-------------------------------------------------------------------------------
2FP CDU-ADIRS 20VU 211 831 34-12-12

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 C. Other LRUs of the System

-------------------------------------------------------------------------------
FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA
| | | | DOOR | REF.
-------------------------------------------------------------------------------
3FP1 SENSOR-ANGLE OF ATTACK, 1 127 824 34-11-19
3FP2 SENSOR-ANGLE OF ATTACK, 2 128 824 34-11-19
3FP3 SENSOR-ANGLE OF ATTACK, 3 127 824 34-11-19
11FP1 SENSOR-TAT, 1 121 34-11-18
11FP2 SENSOR-TAT, 2 122 34-11-18
9DA1 PROBE-PITOT, 1 125 812 34-11-15
9DA2 PROBE-PITOT, 2 126 822 34-11-15
9DA3 PROBE-PITOT, 3 125 812 34-11-15
7DA1 PROBE-L STATIC, 1 127 824 34-11-16
7DA2 PROBE-L STATIC, 2 127 824 34-11-16
7DA3 PROBE-L STATIC, 3 121 811 34-11-16
8DA1 PROBE-R STATIC, 1 128 824 34-11-16
8DA2 PROBE-R STATIC, 2 128 824 34-11-16
8DA3 PROBE-R STATIC, 3 122 811 34-11-16
19FP1 ADM-L TOTAL PRESSURE NONE 125 812 34-11-17
19FP2 ADM-R TOTAL PRESSURE 126 822 34-11-17
19FP3 ADM-STBY TOTAL PRESSURE 125 812 34-11-17
19FP4 ADM-R STATIC PRESSURE 128 824 34-11-17
19FP5 ADM-L STATIC PRESSURE 127 824 34-11-17
19FP6 ADM-R STATIC PRESSURE 128 824 34-11-17
19FP7 ADM-L STATIC PRESSURE 127 824 34-11-17
19FP8 ADM-STBY STATIC PRESSURE 121 811 34-11-17

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 3. __________________
System Description

A. Reporting Function
Each ADIRS BITE message is described in the following pages, with the
corresponding fault description and the consequences on the system and in
the cockpit.

(1) General
- IR and ADR faults are classified as follows:
. class 1: faults with cockpit effect
. class 2: non-critical faults
. class 3: minor faults without cockpit effects.
- use of indexes in BITE messages:
ADIRUi stands for ADIRU 1, ADIRU 2 or ADIRU 3.
- ECAM messages:
. xxx stands for CAPT or F/O, depending on the ADIRU side (1 or 2)
. the letter in parentheses indicates the color used to display the
text: (A) Amber, (C) Cyan and (W) White.
- IR FAULT:
the FAULT legend of the IR pushbutton switch flashes in NAV mode
and is steady in ATT mode.

(2) Inertial reference faults

(Ref. Fig. 002, 003, 004, 005, 006, 007, 008, 009)
Some IR faults resulting in warnings (fault annunciation, invalid
outputs) are due to an incorrect operational use of the system and
not to a system fault.
These tests are:
- align in air
- position-entry (comparison with the last stored position and
computed latitude).
- Test on motion.

(a) Align in air

The test fails if, with the OFF/NAV/ATT selector switch on the
CDU in NAV position, the aircraft is detected in flight (TAS
greater than 100 kts) at power-up or during the ALIGN phase. The
following occurs:
- NAV IRi FAULT message is displayed on the upper ECAM display
unit.
- the FAULT legend of the IR pushbutton switch, on the CDU, comes
on.
- the IN FLIGHT ALIGNMENT message is sent to the CFDIU
- all BNR output labels are coded Failure Warning (F/W) and all
BCD labels are not transmitted.
- the SELECT ATT indication is displayed on the CDU (DATA DISPLAY
selector switch in STS position).

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 ADIRS BITE - Inertial Reference System - Class 1 Internal Faults 1/5
Figure 002

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 ADIRS BITE - Inertial Reference System - Class 1 Internal Faults 2/5
Figure 003

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 ADIRS BITE - Inertial Reference System - Class 1 Internal Faults 3/5
Figure 004

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 ADIRS BITE - Inertial Reference System - Class 1 Internal Faults 4/5
Figure 005

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 ADIRS BITE - Inertial Reference System - Class 1 Internal Faults 5/5
Figure 006

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 ADIRS BITE - Inertial Reference System - Class 1 External Faults
Figure 007

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 ADIRS BITE - Inertial Reference System - Class 3 Faults
Figure 008

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 ADIRS BITE - Inertial Reference System - Class 2 Internal Faults
Figure 009

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 The IR portion can be recovered by setting the OFF/NAV/ATT
selector switch on the CDU to ATT and by applying the procedure
(level flight) to initialize the ATT mode.

(b) Position-entry test

- Initial position (latitude, longitude) must compare within one
degree of the last computed latitude and longitude from the
previous flight. If a miscompare exists, then the NOT ALIGN
message is displayed on the upper ECAM display unit with a text
indicating to enter again the initial position (Ref. 34-14
Para. 3.). The miscompare is removed if the new entered
position is identical to the previous one or is within the
one-degree threshold. If not, the system waits for other
position entry.
- At the end of the alignment submode, the IR portion compares
the initial latitude to a self-computed latitude. The test
fails and the NOT ALIGN message is displayed on the upper ECAM
display unit with action to enter again the position, when:
. the cosine of entered latitude differs from the cosine of computed latitude
by more than 0.01234 or
. the sine of entered latitude differs from the sine of computed latitude by
more than 0.01234.
The miscompare is removed if a subsequent entry of latitude
passes the test. If the sin/cos test fails two times with
identical initial latitude entries, the IR system goes in a
fault reaction: IR FAULT warning message on the upper ECAM
display unit and FAULT legend on the CDU on, invalid outputs.

NOTE : No fault message is sent to the CFDIU.

____

(c) Test on motion

If taxiing or towing causes a step input which exceeds 0.11 ft/s
in the X or Y velocity, the align process is stopped with a
message on the upper ECAM display unit indicating IR NOT ALIGN
and excessive motion (Ref. 34-14). The status matrix of the
attitude data (pitch, roll, heading) is set at NCD which implies
a flag on the PFD.

NOTE : No fault message is sent to the CFDIU.

____

When the motion is no more detected, the IR reverts to the

beginning of the align submode. It is not necessary to
re-initialize the position.

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 (3) Air data reference faults

(Ref. Fig. 010, 011, 012, 013, 014, 015, 016)

(a) SDI validity test at power-up

A number of data are computed in the ADR portion according to air
data correction laws (SSEC, AOA) which are dependent on the ADR
side (SDI = 1, 2, 3).
The determination of the SDI at power-up is consolidated by the
ADR with a logic vote between the SDI discrete inputs and the SDI
read on the labels received from the total pressure ADM and the
static pressure ADM. Faults are either miscompare between the
different sources of SDI or unability to compute the SDI.
In this last case, detection of the fault leads to the ADR FAULT
annunciation (message on the upper ECAM display unit; FAULT
legend on the CDU) associated to invalid outputs.
A number of messages can be sent to the CFDIU on the label 356
according to the detected miscompare. These messages point the
ADIRU or ADM pin program or a mix of them:

341117 ADMi (19FPi) (i = 1, 2 or 3)

341117 ADMi (19FPi)/ADMj(19FPj) (i,j) = (1,5), (2,7) or (3,8)
341234 WRG: SDI PIN PROG/ADIRUi (1FPi)
341234 WRG: SDI PIN PROG/ADMi (19FPi)/ADIRUi (1FPi)
341234 WRG: SDI PIN PROG/ADMj (19FPj)/ADIRUi (1FPi) (i,j) =
(1,5), (2,7) or (3,8).
341234 WRG: SDI PIN PROG/ADMi/j ADIRUi (1FPi) (19FPi/j) (i,j) =
(1,5), (2,7) or (3,8).

(b) Cross-channel comparison tests

A cross-channel comparison of pressures, angle-of-attack, and
temperature parameters is performed to identify drifted air data
input sensors. These tests are done for maintenance purpose only
and they have no operational effects (no fault warning, output
parameters are always valid, class 3 failures).
To run these tests, each ADR portion receives one ADR output bus
of the other side computers
(Ref. Fig. 001)
As the air data sensors are installed per design in different
zones and measure different values, the comparison can only be
done in an identified flight phase.
The tests are performed at takeoff with a CAS between 90 and 200
kts and only if the received ADR data are valid. The thresholds
used in the comparison are:

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 ADIRS BITE - Air Data Reference System - Class 1 Internal Faults 1/4
Figure 010

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R ADIRS BITE - Air Data Reference System - Class 1 Internal Faults 2/4
Figure 011

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R ADIRS BITE - Air Data Reference System - Class 1 Internal Faults 3/4
Figure 012

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 ADIRS BITE - Air Data Reference System - Class 1 Internal Faults 4/4
Figure 013

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R ADIRS BITE - Air Data Reference System - Class 2 Faults
Figure 014

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 ADIRS BITE - Air Data Reference System - Class 1 External Faults
Figure 015

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 ADIRS BITE - Air Data Reference System - Class 3 Faults
Figure 016

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 ------------------------------------------------
| Parameter | Threshold |
|----------------------------------------------|
| Total pressure | 5 hPa |
| Averaged static pressure | 5 hPa |
| Left static pressure | 2 hPa |
| Right static pressure | 2 hPa |
| Angle-of-attack | 4⁰ |
| Total air temperature | 3⁰C |
------------------------------------------------
Table 1 : Comparison Thresholds

The messages resulting from a miscompare between parameters point

the faulty sensor if it can be identified (one data differs from
the two others which are identical) or the sensors which
disagree. They are sent to the CFDIU in normal mode through label
356 of the ADR output and can be accessed by the LAST (PREVIOUS)
LEG REPORT page on the MCDU menu.
The messages have the following format: e.g. for the AOA sensors

341119 AOA SENSORi (3FPi)

or
341119 AOA SENSORi (3FPi)/AOA SENSORj (3FPj)
or
341119 AOA SNSR1 (3FP1)/SNSR2 (3FP2)/SNSR3 (3FP3)

The principle of the messages is the same for other sensors (ADM,
TAT).

B. Interactive Function

(1) General
The interactive mode is activated via the SYSTEM REPORT/TEST page
related to ATA 34 chapter (Navigation) including the Air Data and
Inertial Reference System (ADIRS).
As this system includes two parts (Air Data Reference and Inertial
Reference), two interactive functions are available:
- IR interactive function
(Ref. Fig. 017)
- ADR interactive function.
(Ref. Fig. 018)

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 ADIRS BITE - Activation of IR Interactive Function
Figure 017

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 ADIRS BITE - Activation of ADR Interactive Function
Figure 018

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 (2) IR interactive function

(Ref. Fig. 019)

(a) LAST LEG REPORT

This item describes the in-flight class 1 and 2 fault status of
the selected IR during the last leg (flight leg 00).

(b) PREVIOUS LEGS REPORT

This item describes the in-flight class 1 and 2 fault status of
the selected IR during the previous legs (flight legs 01-62).

(c) LRU IDENTIFICATION

(Ref. Fig. 020)

This item provides the ADIRU Part Number and Serial Number.
The Part Number and the Serial Number of the CDU are also
displayed.

(d) GROUND SCANNING

(Ref. Fig. 020)

This item describes the current on-the-ground fault status of the
selected IR.

(e) TROUBLE SHOOTING DATA

(Ref. Fig. 021)

This item provides, for each fault message stored in the LAST LEG
or PREVIOUS LEGS REPORT, additional data required by the
maintenance for failure investigation.

(f) CLASS 3 FAULTS

(Ref. Fig. 021)

This item reports all class 3 faults recorded since the last
takeoff.

(g) SYSTEM TEST

(Ref. Fig. 022)
This item activates a complete test of the IR system and presents
a report to the user.

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 ADIRS BITE - IR Main Menu 1/7
Figure 019

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 ADIRS BITE - IR Main Menu 2/7
Figure 020

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 ADIRS BITE - IR Main Menu 3/7
Figure 021

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 ADIRS BITE - IR Main Menu 4/7
Figure 022

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 (h) INTERFACE TEST
(Ref. Fig. 023)
This item controls the functional test modes of the selected IR.
The test mode is inhibited whenever any of the following
conditions exists:
- ground speed greater than or equal to 20 kts
- IR in the ATT mode.
The text displayed describes the various steps of the interface
test; when you push the line key adjacent to the START TEST
indication, the following test sequence is run:
- 0-2 seconds
BCD, BNR and Discrete Words are output with SSM set to
Functional Test and data set as shown in the following tables.
Annunciator discretes are energized:

. ALIGN
. ON BAT
. DC FAIL (See nota)
. IR FAULT
. IR OFF (See nota)
. SPARE IR OUT 1 (See nota)
. SPARE IR OUT 2 (See nota)

- after 2 seconds
BCD, BNR and Discrete Words are output with SSM set to
Functional Test and data set as shown in the following tables.
Annunciator discretes are de-energized to the previously
indicated status.

NOTE : No associated annunciator in the cockpit.

____

----------------------------------------------------------------
| | | SELF TEST VALUE |
| LABEL | PARAMETER |--------------------------|
| | | 0 to 2 s. | After 2 s. |
|--------------------------------------------------------------|
| 010 | PRESENT POSITION LAT | 188⁰88.8< | N 22⁰30.0< |
| 011 | PRESENT POSITION LONG | 188⁰88.8< | E 22⁰30.0< |
| 012 | GROUND SPEED | 6888 Kts | 200 Kts |
| 013 | TRACK ANGLE-TRUE | 688.8⁰ | 00.0⁰ |
| 014 | MAGNETIC HEADING | 688.8⁰ | 15⁰ |
| 015 | WIND SPEED | 688 Kts | 100 Kts |
| 016 | WIND DIRECTION-TRUE | 688⁰ | 30⁰ |
| 041 | SET LATITUDE | 188⁰88.8< | N 22⁰30.0< |
| 042 | SET LONGITUDE | 188⁰88.8< | E 22⁰30.0< |
| 043 | SET MAGNETIC HEADING | 688⁰ | 15⁰ |
| 044 | TRUE HEADING | 688.8⁰ | 10⁰ |

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 ADIRS BITE - IR Main Menu 5/7
Figure 023

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 ----------------------------------------------------------------
| | | SELF TEST VALUE |
| LABEL | PARAMETER |--------------------------|
| | | 0 to 2 s. | After 2 s. |
|--------------------------------------------------------------|
----------------------------------------------------------------
Table 2 : Output BCD Words

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 ----------------------------------------------------------------
| LABEL | PARAMETER | SELF TEST VALUE |
|--------------------------------------------------------------|
| 052 | PITCH ANGULAR ACCEL | 5.0⁰/s/s |
| 053 | ROLL ANGULAR ACCEL | 5.0⁰/s/s |
| 054 | YAW ANGULAR ACCEL | 5.0⁰/s/s |
| 076 | GPS ALTITUDE | 10,000 ft |
| 101 | GPS HDOP | 4.0 |
| 102 | GPS VDOP | 3.0 |
| 103 | GPS TRACK ANGLE | 0.0⁰ |
| 110 | GPS LATITUDE | N 22.50⁰ |
| 111 | GPS LONGITUDE | E 22.50⁰ |
| 112 | GPS GROUND SPEED | 200 kts |
| 120 | GPS LATITUDE FINE | N 00.00⁰ |
| 121 | GPS LONGITUDE FINE | E 00.00⁰ |
| 125 | UTC TIME | 12:00:00 |
| 130 | GPS HORIZ INTEGRITY LIM | 10.0 NM |
| 131 | HYBRID HORIZ INTEGRITY | 5.0 NM |
| | LIMIT | |
| 132 | HYBRID TRUE HEADING | 10⁰ |
| 135 | HYBRID VERTICAL FOM | 300 ft |
| 136 | GPS VERTICAL FOM | 100 ft |
| 137 | HYBRID TRACK ANGLE | 0.0⁰ |
| 143 | TERMINAL AREA HIL | 0.8 NM |
| 150 | UTC | 12:00:00 |
| 162 | DESTINATION ETA | 06:30:00 |
| 163 | ALT WAYPOINT ETA | 06:35:00 |
| 165 | GPS VERTICAL VELOCITY | -600 ft/mn |
| 166 | GPS N/S VELOCITY | 200 kts |
| 174 | GPS E/W VELOCITY | 200 kts |
| 175 | HYBRID GROUND SPEED | 200 kts |
| 247 | GPS HORIZONTAL FOM | 6.0 NM |
| 254 | HYBRID LATITUDE | N 22.50⁰ |
| 255 | HYBRID LONGITUDE | E 22.50⁰ |
| 256 | HYBRID LATITUDE FINE | N 00.00⁰ |
| 257 | HYBRID LONGITUDE FINE | E 00.00⁰ |
| 260 | DATE | 1/1/99 |
| 261 | HYBRID ALTITUDE | 10,000 ft |
| 263 | HYBRID FLIGHT PATH ANGLE| -5.0⁰ |
| 264 | HYBRID HORIZONTAL FOM | 7.0 NM |
| 266 | HYBRID N/S VELOCITY | 200 kts |
| 267 | HYBRID E/W VELOCITY | 200 Kts |
| 310 | PRESENT POSITION LAT | N 22.50⁰ |
| 311 | PRESENT POSITION LONG | E 22.50⁰ |
| 312 | GROUND SPEED | 200 Kts |
| 313 | TRACK ANGLE-TRUE | 00.0⁰ |
| 314 | TRUE HEADING | 10.0⁰ |

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 ----------------------------------------------------------------
| LABEL | PARAMETER | SELF TEST VALUE |
|--------------------------------------------------------------|
| 315 | WIND SPEED | 100 Kts |
| 316 | WIND DIRECTION-TRUE | 30⁰ |
| 317 | TRACK ANGLE-MAG | 5⁰ |
| 320 | MAGNETIC HEADING | 15⁰ |
| 321 | DRIFT ANGLE | -10⁰ (Left) |
| 322 | FLIGHT PATH ANGLE | -5⁰ |
| 323 | FLIGHT PATH ACCEL | 0.02g |
| 324 | PITCH ANGLE | 5⁰ |
| 325 | ROLL ANGLE | 45⁰ (Right) |
| 326 | BODY AXIS PITCH RATE | 10⁰/s |
| 327 | BODY AXIS ROLL RATE | 10⁰/s |
| 330 | BODY AXIS YAW RATE | 10⁰/s |
| 331 | BODY LONGIT ACCEL | 0.02g |
| 332 | BODY LATERAL ACCEL | 0.10g |
| 333 | BODY NORMAL ACCEL | 0.10g |
| 334 | PLATFORM HEADING | 22.50⁰ |
| 335 | TRACK ANGLE RATE | 4.0⁰/s |
| 336 | PITCH ATT RATE | 10⁰/s |
| 337 | ROLL ATT RATE | 10⁰/s |
| 340 | TRACK ANGLE GRID | 10⁰ |
| 341 | GRID HEADING | 20⁰ |
| 343 | DESTINATION HIL | 1.0 NM |
| 345 | HYBRID VERTICAL VELOCITY| -600 ft/mn |
| 347 | ALT WAYPOINT HIL | 2.0 NM |
| 360 | POTENTIAL VERT SPEED | -600 ft/mn |
| 361 | INERTIAL ALTITUDE | 10,000 ft |
| 362 | ALONG TRACK HORIZ ACCEL | 0.02g |
| 363 | CROSS TRACK HORIZ ACCEL | 0.02g |
| 364 | VERTICAL ACCEL | 0.1g |
| 365 | INERTIAL VERT SPEED | -600 ft/mn |
| 366 | N-S VELOCITY | 200 Kts (N) |
| 367 | E-W VELOCITY | 200 Kts (E) |
----------------------------------------------------------------
Table 3 : Binary Output Labels

(i) GROUND REPORT

(Ref. Fig. 024)
This item reports all internal faults detected since the last
landing.

(j) INPUT STATUS

(Ref. Fig. 025)
This item describes the current state/value of the selected IR
inputs (discrete and binary inputs).

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 ADIRS BITE - IR Main Menu 6/7
Figure 024

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 ADIRS BITE - IR Main Menu 7/7
Figure 025

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 (3) ADR interactive function

(a) LAST LEG REPORT

(Ref. Fig. 026)

This item describes the in-flight class 1 and 2 fault status of
the selected ADR and related LRUs during the last leg (flight leg
00).

(b) PREVIOUS LEGS REPORT

(Ref. Fig. 026)

This item describes the in-flight class 1 and 2 fault status of
the selected ADR and related LRUs during the previous legs
(flight legs 01-62).

(c) LRU IDENTIFICATION

(Ref. Fig. 027)
This item describes the Part Number and Serial Number of the
selected ADIRU, as well as the Part Number of the ADMs.

(d) GROUND SCANNING

(Ref. Fig. 027)
This item describes the current on-the-ground fault status of the
selected ADR.

(e) TROUBLE SHOOTING DATA

(Ref. Fig. 028)
This item provides, for each fault message stored in the LAST LEG
or PREVIOUS LEGS REPORT, additional data required by the
maintenance for failure investigation.

(f) CLASS 3 FAULTS

(Ref. Fig. 028)
This item reports all class 3 faults recorded since the last
takeoff.

(g) SYSTEM TEST

(Ref. Fig. 028)
This item activates a complete test of the ADR system and
presents a report to the user.

(h) INTERFACE TEST (OUTPUT TESTS MENU)

(Ref. Fig. 029, 030)

This item controls the functional test modes of the selected ADR.

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 ADIRS BITE - ADR Main Menu 1/8
Figure 026

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 ADIRS BITE - ADR Main Menu 2/8
Figure 027

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 ADIRS BITE - ADR Main Menu 3/8
Figure 028

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 ADIRS BITE - ADR Main Menu 4/8
Figure 029

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 ADIRS BITE - ADR Main Menu 5/8
Figure 030

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 The text displayed describes the various steps of the interface
test; when you push the line key adjacent to the START TEST
indication, the following test sequence is run:
- 0-5 seconds: Failure Warning Test
For 0-5 seconds after initiation of the test mode, the ADR
outputs are transmitted per the following tables. Since this is
the failure warning test period, the BCD output parameters are
not transmitted and the SSM of the BNR parameters are set to
F/W. Timing tolerance is plus or minus 0.5 seconds.
- 5-10 seconds: Altitude Ramp Test
For 5-10 seconds after initiation of the test mode, the ADR
outputs are transmitted per the following tables with an SSM
coded FT (except for discrete words). Since this is the
altitude ramp test period, the altitude outputs are slewed in a
positive direction for the entire 5-second period at a rate of
600 ft/mn, starting at the ambient computed altitude. Timing
tolerance is plus or minus 0.5 seconds.
- 10 second until test completion: Fixed Output Test
From 10 seconds after initialization of the test mode until the
test completion is commanded, the ADR outputs are transmitted
per the following tables, outputting the fixed values specified
by these tables with an SSM coded FT (except for discrete
words). Timing tolerance is plus or minus 0.5 seconds.

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 ADR Interface test values are shown in the following tables:

------------------------------------------------------------------------
| | | SELF TEST VALUE |
| LABEL | PARAMETER |--------------------------------------|
| | | 0 to 5 s | 5 to 10 s | After 10 s |
|----------------------------------------------------------------------|
| 176 | LEFT STATIC PRESSURE | Last Valid | Last Valid | 696.8 hPa |
| 177 | RIGHT STATIC PRESSURE | Last Valid | Last Valid | 696.8 hPa |
| 203 | STANDARD ALTITUDE | Last Valid | Slewed | 10,000 ft |
| 204 | BARO CORR ALT 1 | Last Valid | Slewed | 10,000 ft |
| 205 | MACH | 0 | 0 | 0.66 |
| 206 | COMPUTED AIRSPEED | 0 Kts | 0 Kts | 367.7 Kts |
| 207 | MAX ALLOWABLE AIRSPEED| Last Valid | Last Valid | Last Valid |
| 210 | TRUE AIRSPEED | 0 Kts | 0 Kts | 433 Kts |
| 211 | TOTAL AIR TEMP | Last Valid | Last Valid | 35⁰C |
| 212 | ALTITUDE RATE | Last Valid | 600 ft/mn | 0 ft/mn |
| 213 | STATIC AIR TEMP | Last Valid | Last Valid | 10.3⁰C |
| 215 | IMPACT PRESSURE | Last Valid | Last Valid | 236.6 hPa |
| 220 | BARO CORR ALT 2 | Last Valid | Slewed | 10,000 ft |
| 221 | IND ANGLE OF ATTACK | NOTE 1 | NOTE 1 | 5⁰ |
| 241 | CORCTD ANGLE OF ATTACK| NOTE 1 | NOTE 1 | 5⁰ |
| 242 | TOTAL PRESSURE | Last Valid | Last Valid | 933.4 hPa |
| 245 | UNCRCTD AVG STAT PRESS| Last Valid | Last Valid | 696.8 hPa |
| 246 | CORCTD AVG STAT PRESS | Last Valid | Last Valid | 696.8 hPa |
| 251 | BARO CORR ALT 3 | Last Valid | Slewed | 10,000 ft |
------------------------------------------------------------------------

NOTE : Indicated AOA is a function of the AOA sensor position.

____
Corrected AOA is a function of AOA alternate discrete
inputs, SDI discrete inputs and indicated AOA. Corrected
AOA is set to 0⁰ when CAS is less than 60 kts.
Output Binary Words

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 --------------------------------------------------------------------------
| | | SELF TEST VALUE |
| LABEL | PARAMETER |----------------------------------------|
| | | 0 to 5 s | 5 to 10 s | After 10 s |
|------------------------------------------------------------------------|
| 034 | BARO CORR (hPa) 3 |Not Transmit.| 745.0 hpa | 1013.3 hPa |
| 035 | BARO CORR (in.Hg) 3 |Not Transmit.| 22.0 in.Hg | 29.92 in.Hg |
| 230 | TRUE AIRSPEED |Not Transmit.| 0 Kts | 433 Kts |
| 231 | TOTAL AIR TEMP |Not Transmit.| Last Valid | 35 ⁰C |
| 233 | STATIC AIR TEMP |Not Transmit.| Last Valid | 10 ⁰C |
| 234 | BARO CORR (hPa) 1 |Not Transmit.| Last Valid | 1013.3 hPa |
| 235 | BARO CORR (in.Hg) 1 |Not Transmit.| Last Valid | 29.92 in.Hg |
| 236 | BARO CORR (hPa) 2 |Not Transmit.| Last Valid | 1013.3 hPa |
| 237 | BARO CORR (in.Hg) 2 |Not Transmit.| Last Valid | 29.92 in.Hg |
--------------------------------------------------------------------------
Output BCD Words

--------------------------------------------------------------------------
| | | SELF TEST VALUE |
| LABEL | BIT - PARAMETER |----------------------------------------|
| | | 0 to 5 s | 5 to 10 s | After 10 s |
|------------------------------------------------------------------------|
| 270 | 13 - ADR FAULT | 1 | 0 | 0 |
| 270 | 19 - OVERSPEED WARNING| 0 | 0 | 1 |
| 271 | 13 - LOW SPD WARN 1 | 0 | 0 | 1 |
| 271 | 14 - LOW SPD WARN 2 | 0 | 0 | 1 |
| 271 | 15 - LOW SPD WARN 3 | 0 | 0 | 0 |
| 271 | 16 - LOW SPD WARN 4 | 1 | 1 | 0 |
--------------------------------------------------------------------------
Output Discretes Words

--------------------------------------------------------------------------
| | SELF TEST VALUE |
| PARAMETER |----------------------------------------|
| | 0 to 5 s | 5 to 10 s | After 10 s |
|------------------------------------------------------------------------|
| LOW SPEED WARNING 1 | OPEN | OPEN | GROUND |
| LOW SPEED WARNING 2 | OPEN | OPEN | GROUND |
| LOW SPEED WARNING 3 | OPEN | OPEN | OPEN |
| LOW SPEED WARNING 4 | GROUND | GROUND | OPEN |
| OVERSPEED WARNING | OPEN | OPEN | GROUND |
| ADR FAULT | GROUND | OPEN | OPEN |
| ADR OFF | GROUND | OPEN | OPEN |
--------------------------------------------------------------------------
Discrete Outputs

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 (i) ALT DYNAMIC SLEW (OUTPUT TESTS menu/SLEW TESTS submenu)
(Ref. Fig. 029, 030)
The activation of the ALT DYNAMIC SLEW test causes the ADR to
output a simulated ramp of altitude (label 203) between low and
high altitude limits specified by the operator. These limits, as
well as the slew rate, are entered by the operator by means of
the MCDU keyboard.
The altitude limit values are tested to be within -2000 and
+50,000 ft. The altitude lower limit is tested to be less than
the altitude upper limit. The altitude slew rate is tested to be
within 1 to +20,000 ft/mn.

(j) CAS DYNAMIC SLEW (OUTPUT TESTS menu/SLEW TESTS submenu)

(Ref. Fig. 029, 031)
The activation of the CAS DYNAMIC SLEW test causes the ADR to
output a simulated ramp of computed airspeed (label 206) between
low and high speed limits specified by the operator. These
limits, as well as the slew rate, are entered by the operator by
means of the MCDU keyboard.
The CAS limit values are tested to be within 0 and +450 kts. The
CAS lower limit is tested to be less than the CAS upper limit.
The speed slew rate is tested to be within 1 to +100 Kts/mn.

(k) AOA SENSOR TEST (OUTPUT TESTS menu)

(Ref. Fig. 029, 032)
The activation of the AOA SENSOR TEST causes the ADR to output
the actual measured values of indicated and corrected AOA with an
SSM coded FT, and the AOA special test discrete output to be
commanded to the ground state, which causes the AOA sensor to be
commanded to a fixed position greater than the stall warning
threshold. Thus, the Flight Warning Computer (FWC) activates the
aural stall warning.

(l) GROUND REPORT

(Ref. Fig. 029)
This item reports all internal faults detected since the last
landing.

(m) INPUT STATUS

(Ref. Fig. 029, 033)
This item describes the current state/value of the selected ADR
inputs (discrete, analog and binary inputs).

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 ADIRS BITE - ADR Main Menu 6/8
Figure 031

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 ADIRS BITE - ADR Main Menu 7/8
Figure 032

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 ADIRS BITE - ADR Main Menu 8/8
Figure 033

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 STANDBY DATA : ALTITUDE AND AIRSPEED - DESCRIPTION AND OPERATION
________________________________________________________________

1. _______
General
One standby airspeed indicator and one standby altimeter are directly
connected to the standby pitot and static sources. Each indicator is
contained in a 2 ATI case (ARINC 408) and installed on the center instrument
panel. The standby circuit can be drained by means of a water drain.

2. Component
__________________
Location
(Ref. Fig. 001)

-------------------------------------------------------------------------------
FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA
| | | | DOOR | REF.
-------------------------------------------------------------------------------
3FN ALTM-STANDBY 4VU 211 831 34-21-22
9FN IND-STANDBY AIRSPEED 4VU 211 831 34-21-26
15FN ALTIMETER-METRIC 4VU 211 831 34-21-25

3. System
__________________
Description
(Ref. Fig. 002, 003, 004)

A. Standby Altimeter
R The standby altimeter is supplied with static pressure by the standby air
R data system to indicate the barometric altitude of the aircraft in feet.
R
The barometric altitude is displayed by means of:
- a pointer (4) performing one revolution of the dial for 1000 feet
- a display counter (5) made up of two drums displaying respectively the
tens of thousands and the thousands of feet.
When the altitude is below 10,000 feet, the figure zero of the left
drum is replaced by black and white stripes. The figure nine is
replaced by an orange fire stripped zone.
the altitude dial (6) is calibrated from 0 to 1000 feet with 20 feet
graduations
- the baro correction (2) is displayed on a counter graduated in hecto
Pascal
- a knob (1) located at the L corner of the indicator enables the display
of the reference baro correction in the range of 750 to 1050 hPa.
- four manually adjustable white bugs (3) are provided for manual
altitude setting.
R To improve accuracy, 28VDC supplies the internal vibrator of the
R standby altimeter through a landing gear relay.
R In straight and level flight, with the internal vibrator operating, the
R standby altimeter gives the following accuracy:
R plus or minus 20 ft. at sea level
R plus or minus 40 ft. at 6000 ft.

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 Standby Data - Altitude and Airspeed - Component Location
Figure 001

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 Standby Data - Altitude and Airspeed - Pneumatic Circuit
Figure 002

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 Standby Data - Altitude and Airspeed - Electrical Circuit
Figure 003

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 Standby Data - Altitude and Airspeed - Data Indication
Figure 004

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R plus or minus 80 ft. at 10,000 ft.
R plus or minus 130 ft. at 20,000 ft.
R plus or minus 205 ft. at 35,000 ft.

R NOTE : On the ground, with the internal vibrator not supplied, the above
____
R figures may be plus or minus 300ft.
Integral lighting supplied with external 5VAC is provided to
illuminate the presentation.
R

B. Standby Airspeed Indicator

The standby airspeed indicator contains a capsule-operated mechanism
which measures the pitot/static pressure differential from the standby
air data system and provides airspeed indication in terms of knots with
the following accuracy:
- plus or minus 3 kts for VC < 200 kts
- plus or minus 4 kts for 200 kts < VC < 300 kts
- plus or minus 5 kts for 300 kts < VC < 450 kts.
The airspeed indication is displayed by means of:
- a pointer (9) which moves on a dial (7) graduated between 60 kts and
450 kts. The scale is linear from 60 kts to 250 kts with 5 kts
graduations and from 250 kts to 450 kts with 10 kts graduations.
- four manually adjustable white bugs (8) provided for manual speed
setting.
Integral lighting supplied with external 5VAC is provided to illuminate
the presentation.

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 STANDBY DATA : ALTITUDE AND AIRSPEED - ADJUSTMENT/TEST
______________________________________________________

TASK 34-21-00-790-001

Leak Test of the Standby Air Data System

WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE
_______
YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.

CAUTION : OBEY THESE PRECAUTIONS WHEN YOU DO THE TEST TO PREVENT DAMAGE TO
_______
INSTRUMENTS:
- PRESSURE SET MUST NOT BE MORE THAN 1050 hPa (31 in Hg) OR LESS THAN
115 hPa (3.39 in Hg)
- CHANGES IN PRESSURE MUST NOT BE MORE THAN 6000 FEET/MINUTE
- DO NOT SUDDENLY OPEN LINES TO AMBIENT AIR WHILE THE PRESSURE
GENERATOR IS CONNECTED.

CAUTION : THE TOTAL PRESSURE IN THE PITOT SYSTEM MUST NEVER BE LESS THAN THE
_______
STATIC PRESSURE. THE DIFFERENCE BETWEEN THE PITOT AND THE STATIC
PRESSURE CIRCUITS MUST NEVER BE MORE THAN 368 hPa (10.86 in Hg).

1. __________________
Reason for the Job

Refer to the MPD TASK: 342100-01

- Make sure that there are no leaks in the standby static and pitot
circuits.

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific circuit breaker(s) safety clip(s)

No specific colored adhesive tape
R No specific safety barriers
No specific GENERATOR - GROUND PRESSURE
36122 1 ADAPTOR-CHARGING,PITOT PROBE
98D10103500001 1 COVER-STATIC PROBE
98D34003500000 1 ADAPTER COVER-STATIC PORT

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 B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power

3. __________
Job Set-up

Subtask 34-21-00-860-056

R A. Aircraft Maintenance Configuration

R

R (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-

002).

R (2) Put the safety barriers in position around the RAT area.

Subtask 34-21-00-865-050

B. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
105VU ELEC/CSM/G /EV AUTO/SPLY 7XE C01
122VU ANTI ICE/PROBES/3/PITOT 3DA3 Z16
122VU ANTI ICE/PROBES/3/STATIC 5DA3 Z14

Subtask 34-21-00-865-052

C. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV/STBY/ALTM 16FN F14

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 Subtask 34-21-00-420-050

D. Connection of the Ground Pressure Generator

(1) Remove the slip on covers from the static probe and the pitot probe
of the standby system.

(2) Connect the GENERATOR - GROUND PRESSURE to one standby static probe
with the ADAPTER COVER-STATIC PORT (98D34003500100).

(3) Connect the ground pressure generator to the standby pitot probe with
the ADAPTOR-CHARGING,PITOT PROBE.

(4) Seal the Stby probes:

CAUTION : WHEN YOU SEAL THE DRAIN HOLE IN THE PITOT PROBE, DO NOT
_______
SEAL THE HOLE DIRECTLY WITH THE COLORED ADHESIVE TAPE.
ALWAYS PUT A PIECE OF PLASTIC ON THE HOLE AND USE THE TAPE
TO ATTACH THE PLASTIC.
IF YOU SEAL THE DRAIN HOLE DIRECTLY WITH THE ADHESIVE TAPE,
THERE IS A RISK THAT SOME OF THE ADHESIVE WILL STAY ON THE
HOLE AND COLLECT PARTICLES. THIS CAN SUBSEQUENTLY CAUSE
BLOCKAGE OF THE HOLE AND THUS INCORRECT OPERATION OF THE
PROBE.

R (a) Seal the drain holes of the pitot probe with a piece of plastic
R and colored adhesive tape of very bright color.

(b) Seal the opposite standby static probe with the COVER-STATIC
PROBE (98D34003500103).

(5) Start the ground pressure generator.

4. Procedure
_________

Subtask 34-21-00-790-050

A. Leak Test

NOTE : You can do the test below for a static pressure of 697 hpa (10,000
____
ft) and an impact pressure of 53.5 hpa (180 Kts) but it is less
accurate.
After 5 minutes:
- the change of altitude must not be more than 370 ft.
- the change of speed must not be more than 10 Kts.

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the standby altimeter, set a

barometric pressure of 1013 hPa.

2. On the ground pressure generator:

- set a static pressure of 465.5
hpa (20,000 ft).

- set an impact pressure of 176

hpa (320 Kts).

3. Close the electrovalves to After 5 minutes :

isolate the static and pitot - make sure that the change of altitude
circuits of the aircraft from the is not more than 500 ft.
ground pressure generator. After 10 minutes :
- make sure that the change of speed is
not more than 20 Kts.

4. On the ground pressure generator: The rate of descent must not be more
- slowly balance the pressure in than 6000 ft.mn.
the standby static and pitot
circuits and open the
electrovalves to get
atmospheric pressure.

5. Stop the ground pressure

generator.

5. Close-up
________

Subtask 34-21-00-020-050

A. Remove the ground pressure generator

(1) Disconnect the ground pressure generator.

(2) Remove the adaptors from the standby static probe and the standby
pitot probe.

(3) Remove the cover from the opposite standby static probe.

R (4) Remove the piece of plastic and colored adhesive tape from the drain
R holes of the standby pitot probe.

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 (5) Install the slip on covers on the standby static probe and the
standby pitot probe.

Subtask 34-21-00-865-051

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
R 105VU ELEC/CSM/G /EV AUTO/SPLY 7XE C01
122VU ANTI ICE/PROBES/3/PITOT 3DA3 Z16
122VU ANTI ICE/PROBES/3/STATIC 5DA3 Z14

Subtask 34-21-00-860-057

C. Put the aircraft back to its initial configuration.

(1) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

(2) Make sure that the work area is clean and clear of tool(s) and other
items.

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 TASK 34-21-00-720-001

Functional Test of the Standby Airspeed Indicator

1. __________________
Reason for the Job

To make sure that the standby instruments operate independently.

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

R No specific circuit breaker(s) safety clip(s)

No specific GENERATOR - GROUND PRESSURE
36122 1 ADAPTOR-CHARGING,PITOT PROBE
98D34003500000 1 ADAPTER COVER-STATIC PORT

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

12-24-34-600-001 Bleeding of the Standby Air Data System

3. __________
Job Set-up

Subtask 34-21-00-860-050

A. Aircraft Maintenance Configuration

(1) Drain the standby air data system (Ref. TASK 12-24-34-600-001).

(2) Remove the slip on covers from the standby static probes and the
standby pitot probe and connect the GENERATOR - GROUND PRESSURE to :
- the L or R standby static probe with the ADAPTER COVER-STATIC PORT
(98D34003500100).
- the standby pitot probe with the ADAPTOR-CHARGING,PITOT PROBE.

(3) Seal the opposite standby static probe with the ADAPTER COVER-STATIC
PORT (98D34003500103).

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 (4) Precautions

CAUTION : OBEY THESE PRECAUTIONS WHEN YOU DO THE TEST TO PREVENT

_______
DAMAGE TO INSTRUMENTS:
- PRESSURE SET MUST NOT BE MORE THAN 1050 hPa (31 in Hg) OR
LESS THAN 115 hPa (3.39 in Hg)
- CHANGES IN PRESSURE MUST NOT BE MORE THAN 6000
FEET/MINUTE
- DO NOT SUDDENLY OPEN LINES TO AMBIENT AIR WHILE THE
PRESSURE GENERATOR IS CONNECTED.

CAUTION : THE TOTAL PRESSURE IN THE PITOT SYSTEM MUST NEVER BE LESS
_______
THAN THE STATIC PRESSURE. THE DIFFERENCE BETWEEN THE PITOT
AND THE STATIC PRESSURE CIRCUITS MUST NEVER BE MORE THAN
368 hPa (10.86 in Hg).

(5) Start the ground pressure generator.

R Subtask 34-21-00-865-056

R B. Open, safety and tag this(these) circuit breaker(s):

R -------------------------------------------------------------------------------
R PANEL DESIGNATION IDENT. LOCATION
R -------------------------------------------------------------------------------
R 105VU ELEC/CSM/G /EV AUTO/SPLY 7XE C01

4. Procedure
_________

Subtask 34-21-00-720-050

A. Test of the Standby Airspeed Indicator

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

On the ground pressure generator : On the standby airspeed indicator:

- set a static pressure of 314.8 hPa - the pointer shows 340 Kts (+ or - 5
(29,000 ft) Kts).
- set an impact pressure of 200.1
hPa (340 Kts).

- set a static pressure of 571.8 hPa - the pointer shows 300 Kts (+ or - 4
(15,000 ft) Kts).
- set an impact pressure of 153.5
hPa (300 Kts).

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
- set a static pressure of 843 hPa - the pointer shows 180 Kts (+ or - 3
(5000 ft) Kts).
- set an impact pressure of 53.5 hPa
(180 Kts).

5. Close-up
________

Subtask 34-21-00-860-051

A. Put the aircraft back to its initial configuration.

(1) On the ground pressure generator, slowly decrease the pressure until
you get atmospheric pressure.

(2) Stop the ground pressure generator.

(3) Remove the adaptors from the standby static probes and the standby
pitot probe.

(4) Remove the ground pressure generator.

(5) Remove the cover from the opposite standby static probe.

(6) Install the slip on covers on the standby static probes and the
standby pitot probe.

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 TASK 34-21-00-720-002

Functional Test of the Standby Altimeter

1. __________________
Reason for the Job

To make sure that the standby altimeter and the metric altimeter operate
correctly with information from the ground pressure generator.

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific circuit breaker(s) safety clip(s)

R No specific GENERATOR - GROUND PRESSURE
98D10103500001 1 COVER-STATIC PROBE
98D34003500000 1 ADAPTER COVER-STATIC PORT

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

12-24-34-600-001 Bleeding of the Standby Air Data System

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the
External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
32-00-00-860-001 Flight Configuration Precautions
32-00-00-860-002 Ground Configuration after Flight Configuration

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 3. __________
Job Set-up

WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE
_______
YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.

Subtask 34-21-00-860-052

A. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits

(Ref. TASK 24-41-00-861-002).

(2) Take the applicable safety precautions before you open the LGCIU
circuit breakers
(Ref. TASK 32-00-00-860-001).

(3) Precautions

CAUTION : OBEY THESE PRECAUTIONS WHEN YOU DO THE TEST TO PREVENT

_______
DAMAGE TO INSTRUMENTS:
- PRESSURE SET MUST NOT BE MORE THAN 1050 hPa (31 in Hg) OR
LESS THAN 115 hPa (3.39 in Hg)
- CHANGES IN PRESSURE MUST NOT BE MORE THAN 6000
FEET/MINUTE
- DO NOT SUDDENLY OPEN LINES TO AMBIENT AIR WHILE THE
PRESSURE GENERATOR IS CONNECTED.

CAUTION : THE TOTAL PRESSURE IN THE PITOT SYSTEM MUST NEVER BE LESS
_______
THAN THE STATIC PRESSURE. THE DIFFERENCE BETWEEN THE PITOT
AND THE STATIC PRESSURE CIRCUITS MUST NEVER BE MORE THAN
368 hPa (10.86 in Hg).

(4) Remove the slip on covers from the L and R static probes 7DA3 and
8DA3 of the standby system.

R (5) Connect the GENERATOR - GROUND PRESSURE to one standby static probe
with the ADAPTER COVER-STATIC PORT (98D34003500100).

(6) Seal the opposite standby static probe with the COVER-STATIC PROBE
(98D34003500103).

(7) Start the ground pressure generator and set a static pressure of 1013
mb.

(8) Drain the standby air data system (Ref. TASK 12-24-34-600-001).

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 Subtask 34-21-00-865-053

B. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU L/G/LGCIU/SYS1/NORM 1GA C09
R 105VU ELEC/CSM/G /EV AUTO/SPLY 7XE C01
121VU HYDRAULIC/LGCIU/SYS2 2GA Q35
121VU HYDRAULIC/LGCIU/SYS1/GRND SPLY 52GA Q34

Subtask 34-21-00-865-054

C. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV/STBY/ALTM 16FN F14

4. Procedure
_________

Subtask 34-21-00-720-051

A. Test of the Standby Altimeter

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the standby altimeter, set a

barometric pressure of 1013 hPa.

2. On the ground pressure generator: - Make sure that the standby altimeter
- set a static pressure of 977.1 indicates 1000 ft (+ or - 20 ft).
hPa (1000 ft).

- Set a static pressure of 908.1 - Make sure that the standby altimeter
hPa (3000 ft). indicates 3000 ft (+ OR - 30 ft).

- Set a static pressure of 843 - make sure that the standby altimeter
hPa (5000 ft). indicates 5000 ft (+ or - 40 ft).

- set a static pressure of 571.8 - make sure that the standby altimeter
hPa (15,000 ft). indicates 15,000 ft (+ or - 105 ft).

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
- set a static pressure of 314.8 - make sure that the standby altimeter
hPa (29,000 ft). indicates 29,000 ft (+ or - 180 ft).

- slowly decrease the pressure

until you get atmospheric
pressure.

3. Stop the ground pressure

generator.

5. Close-up
________

Subtask 34-21-00-860-054

A. Put the aircraft back to its initial configuration.

(1) Disconnect the ground pressure generator.

(2) Remove the adaptor from the standby static probe.

(3) Remove the cover from the opposite standby static probe.

(4) Install the slip on covers on the static probes.

(5) Close the LGCIU circuit breakers and put the aircraft back to its
inertial cofiguration (Ref. TASK 32-00-00-860-002).

(6) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

Subtask 34-21-00-865-055

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
R 49VU L/G/LGCIU/SYS1/NORM 1GA C09
121VU HYDRAULIC/LGCIU/SYS2 2GA Q35
121VU HYDRAULIC/LGCIU/SYS1/GRND SPLY 52GA Q34

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 ALTIMETER - STANDBY (3FN) - REMOVAL/INSTALLATION
________________________________________________

TASK 34-21-22-000-001

Removal of the Standby Altimeter (3FN)

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific blanking caps

No specific blanking plugs
No specific circuit breaker(s) safety clip(s)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

R **ON A/C 001-004,

34-21-22-991-001 Fig. 401

R **ON A/C 005-099,

R 34-21-22-991-001-A Fig. 401A

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R **ON A/C ALL

3. __________
Job Set-up

Subtask 34-21-22-865-050

A. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV/STBY/ALTM 16FN F14
122VU LIGHTING/INSTL LT/MAIN INST/PNL AND/PED 4LF Y04

Subtask 34-21-22-010-050

B. Remove the thermoformed cover from the center instrument panel.

4. Procedure
_________

R **ON A/C 001-004,

(Ref. Fig. 401/TASK 34-21-22-991-001)

R **ON A/C 005-099,

R (Ref. Fig. 401A/TASK 34-21-22-991-001-A)

R **ON A/C ALL

Subtask 34-21-22-020-050

A. Removal of the Standby Altimeter (3FN)

(1) Loosen the screws (1). Do not remove them.

(2) Disengage the standby altimeter (2) from its housing.

(3) Disconnect the electrical connector (6).

(4) Disconnect the quick-disconnect coupling (5).

(5) Remove the standby altimeter (2).

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 Standby Altimeter
Figure 401/TASK 34-21-22-991-001

R
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R Standby Altimeter
R Figure 401A/TASK 34-21-22-991-001-A

R
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 (6) Put blanking caps on the disconnected electrical connectors (4) and
(6).

(7) Put blanking plugs on the disconnected line ends (3) and (5).

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 TASK 34-21-22-400-001

Installation of the Standby Altimeter (3FN)

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

33-13-00-710-001 Operational Test of the Instrument and Panel Integral

Lighting

R **ON A/C 001-004,

34-21-22-991-001 Fig. 401

R **ON A/C 005-099,

R 34-21-22-991-001-A Fig. 401A

R **ON A/C ALL

3. __________
Job Set-up

Subtask 34-21-22-865-051

A. Make sure that this(these) circuit breaker(s) is(are) open, safetied and
tagged

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV/STBY/ALTM 16FN F14
122VU LIGHTING/INSTL LT/MAIN INST/PNL AND/PED 4LF Y04

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 4. Procedure
_________

R **ON A/C 001-004,

(Ref. Fig. 401/TASK 34-21-22-991-001)

R **ON A/C 005-099,

R (Ref. Fig. 401A/TASK 34-21-22-991-001-A)

R **ON A/C ALL

Subtask 34-21-22-420-050

A. Installation of the Standby Altimeter (3FN)

(1) Clean the component interface and/or the adjacent area.

(2) Do an inspection of the component interface and/or the adjacent area.

(3) Remove the blanking caps from the electrical connectors (4) and (6).

(4) Remove the blanking plugs from the line ends (3) and (5).

(5) Make a loop of the flexible hose and connect the quick-disconnect
coupling (5) to the receptacle (3) of the standby altimeter (2).

NOTE : After the connection:

____
- make sure that a colored ring is shown on the
quick-disconnect coupling
- pull the connectors to be sure that they are correctly
attached.

(6) Connect the electrical connector (6) to the receptacle (4) of the
standby altimeter (2).

(7) Install the standby altimeter (2) in its housing.

(8) Tighten the screws (1).

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 Subtask 34-21-22-865-052

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
16FN, 4LF

Subtask 34-21-22-710-050

C. Do the operational test of the instrument and panel integral lighting

(Ref. TASK 33-13-00-710-001).

5. Close-up
________

Subtask 34-21-22-410-050

A. Close Access

(1) Install the thermoformed cover on the center instrument panel.

(2) Make sure that the work area is clean and clear of tool(s) and other
items.

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 ALTIMETER - STANDBY (3FN) - ADJUSTMENT/TEST
___________________________________________

TASK 34-21-22-820-001

ADJUSTING/ALIGNING/CALIBRATING of the Standby Altimeter

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

34-21-22-000-001 Removal of the Standby Altimeter (3FN)

34-21-22-400-001 Installation of the Standby Altimeter (3FN)
CMM 342122

3. __________
Job Set-up

Subtask 34-21-22-869-050

A. Not Applicable

4. Procedure
_________

Subtask 34-21-22-020-053

A. Remove the standby altimeter (Ref. TASK 34-21-22-000-001).

Subtask 34-21-22-820-050

B. Do a calibration test of the standby altimeter

(Ref. CMM 342122).

Subtask 34-21-22-420-053

C. Install the standby altimeter (Ref. TASK 34-21-22-400-001).

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 INDICATOR - STANDBY AIRSPEED (9FN) - REMOVAL/INSTALLATION
_________________________________________________________

TASK 34-21-26-000-001

Removal of the Standby Airspeed Indicator (9FN)

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific blanking caps

No specific blanking plugs
No specific circuit breaker(s) safety clip(s)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

R **ON A/C 001-004,

34-21-26-991-001 Fig. 401

R **ON A/C 005-099,

R 34-21-26-991-001-A Fig. 401A

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R **ON A/C ALL

3. __________
Job Set-up

Subtask 34-21-26-865-053

A. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
122VU LIGHTING/INSTL LT/MAIN INST/PNL AND/PED 4LF Y04

Subtask 34-21-26-010-050

B. Remove the thermoformed cover from the center instrument panel.

4. Procedure
_________

R **ON A/C 001-004,

(Ref. Fig. 401/TASK 34-21-26-991-001)

R **ON A/C 005-099,

R (Ref. Fig. 401A/TASK 34-21-26-991-001-A)

R **ON A/C ALL

Subtask 34-21-26-020-050

A. Removal of the Standby Airspeed Indicator (9FN)

(1) Loosen the screws (1). Do not remove them.

(2) Disengage the standby airspeed indicator (2) from its housing.

(3) Disconnect the electrical connector (6).

(4) Disconnect the red and green quick-disconnect couplings (5) from the
connectors (4).

(5) Remove the standby airspeed indicator (2).

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 Standby Airspeed Indicator
Figure 401/TASK 34-21-26-991-001

R
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R Standby Airspeed Indicator
R Figure 401A/TASK 34-21-26-991-001-A

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 (6) Put blanking caps on the disconnected electrical connectors (3) and
(6).

(7) Put blanking plugs on the disconnected line ends (4) and (5).

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 TASK 34-21-26-400-001

Installation of the Standby Airspeed Indicator (9FN)

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

33-13-00-710-001 Operational Test of the Instrument and Panel Integral

Lighting

R **ON A/C 001-004,

34-21-26-991-001 Fig. 401

R **ON A/C 005-099,

R 34-21-26-991-001-A Fig. 401A

R **ON A/C ALL

3. __________
Job Set-up

Subtask 34-21-26-865-054

A. Make sure that this(these) circuit breaker(s) is(are) open, safetied and
tagged

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
122VU LIGHTING/INSTL LT/MAIN INST/PNL AND/PED 4LF Y04

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 4. Procedure
_________

R **ON A/C 001-004,

(Ref. Fig. 401/TASK 34-21-26-991-001)

R **ON A/C 005-099,

R (Ref. Fig. 401A/TASK 34-21-26-991-001-A)

R **ON A/C ALL

Subtask 34-21-26-420-050

A. Installation of the Standby Airspeed Indicator (9FN)

(1) Clean the component interface and/or the adjacent area.

(2) Do an inspection of the component interface and/or the adjacent area.

(3) Remove the blanking caps from the electrical connectors (3) and (6).

(4) Remove the blanking plugs from the line ends (4) and (5).

(5) Connect the quick-disconnect couplings (5) of the pressure lines

(green and red) to the related connectors (4) of the standby airspeed
indicator (2).

NOTE : After the connection:

____
- make sure that a colored ring is shown on the
quick-disconnect coupling
- pull the connectors to be sure that they are correctly
attached.

(6) Make sure that the electrical connectors are clean and in the correct
condition.

(7) Connect the electrical connector (6) to the receptacle (3) of the
standby airspeed indicator (2).

(8) Install the Standby Airspeed Indicator (2) in its housing.

(9) Tighten the screws (1).

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 Subtask 34-21-26-865-055

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
4LF

Subtask 34-21-26-710-050

C. Do the operational test of the instrument and panel integral lighting

(Ref. TASK 33-13-00-710-001).

5. Close-up
________

Subtask 34-21-26-410-050

A. Put the aircraft back to its initial configuration.

(1) Install the thermoformed cover on the center instrument panel.

(2) Make sure that the work area is clean and clear of tool(s) and other
items.

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 INDICATOR - STANDBY AIRSPEED (9FN) - ADJUSTMENT/TEST
____________________________________________________

TASK 34-21-26-820-001

ADJUSTING/ALIGNING/CALIBRATING of the Standby Airspeed Indicator

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

34-21-26-000-001 Removal of the Standby Airspeed Indicator (9FN)

34-21-26-400-001 Installation of the Standby Airspeed Indicator (9FN)
CMM 341002

3. __________
Job Set-up

Subtask 34-21-26-020-053

A. Remove the standby airspeed indicator (Ref. TASK 34-21-26-000-001).

4. Procedure
_________

Subtask 34-21-26-820-050

A. Do a calibration test of the standby airspeed indicator

(Ref. CMM 341002).

5. Close-up
________

Subtask 34-21-26-420-053

A. Install the standby airspeed indicator (Ref. TASK 34-21-26-400-001).

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 STANDBY DATA : ATTITUDE AND HEADING - DESCRIPTION AND OPERATION
_______________________________________________________________

1. General
_______

A. Standby Heading
The standby heading is performed by a magnetic compass that is an
independent instrument which provides the flight crew with the A/C
magnetic heading.
It is installed on the top of the windshield center post and allows a
check of the heading provided by the main sources of the heading system.
It acts in standby when these systems are inoperative.

B. Standby Attitude
The standby attitude is performed by a gyroscopic horizon that is an
independent instrument which provides the flight crew, with a constant
indication of the aircraft attitude. It is contained in a 3 ATIs case and
installed on the center instrument panel. It allows a check of the
attitude provided by the main sources of attitude system. It acts in
standby when these systems are inoperative.

2. __________________
Component Location

R **ON A/C 001-004,

(Ref. Fig. 001)

R **ON A/C 005-099,

R (Ref. Fig. 001A)

R **ON A/C ALL

-------------------------------------------------------------------------------
FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA
| | | | DOOR | REF.
-------------------------------------------------------------------------------
2FN COMPASS-STANDBY 211 831 34-22-23
7FN IND-STANDBY HORIZON 4VU 211 831 34-22-24

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 Standby Data - Attitude and Heading - Component Location
Figure 001

R
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R Standby Data - Attitude and Heading - Component Location
R Figure 001A

R
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R **ON A/C 001-004,

3. System
__________________
Description
(Ref. Fig. 002, 003)

A. Standby Compass
The standby compass consists of a magnetic element rotating inside a
compass bowl, immersed in a damping liquid. The magnetic element (1) is
linked to a graduated compass card which moves against a lubber line (2)
and gives the magnetic heading.
Below the viewing window are two apertures (4) marked N.S and E.W,
allowing to achieve compensation by positioning the two small magnetized
bars (compensator).
Above the viewing window is a non-magnetic lamp (3) assembly which
provides illumination of the compass card.

R **ON A/C 005-099,

R 3. System
__________________
Description
R (Ref. Fig. 002, 003A)

R A. Standby Compass
R The standby compass consists of a magnetic element rotating inside a
R compass bowl, immersed in a damping liquid. The magnetic element (1) is
R linked to a graduated compass card which moves against a lubber line (2)
R and gives the magnetic heading.
R Above the viewing window are two apertures (4) marked B (E.W) and C (N.S)
R , allowing to achieve compensation by positioning the two small
R magnetized bars (compensator).
R Below the viewing window is a non-magnetic lamp (3) assembly which
R provides illumination of the compass card.

R **ON A/C ALL

B. Standby Horizon Indicator

The standby horizon indicator is supplied with 28VDC from essential bus
401PP.
A static inverter in the instrument converts this 28VDC into three phase
alternate current to supply the gyroscopic motor. The gyro rotor rotates
at high speed (> 23,000 RPM) around its vertical axis and provides the
vertical reference.
The gimbal assy comprises two orthogonal axes (pitch and roll).

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 Standby Data - Attitude and Heading - Electrical Circuit
Figure 002

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 Standby Data - Attitude and Heading - Data Indicating
Figure 003

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R Standby Data - Attitude and Heading - Data Indicating
R Figure 003A

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 The internal gimbal which includes the stator controls the rotation of
the drum in the pitch axis by means of gear. The pitch gimbal is
restricted to approximately plus or minus 85 degrees around the pitch
axis (mechanical stop).
The external gimbal controls the roll rotation. The roll gimbal has
unrestricted 360 degrees rotation around the roll axis.
The gyro pin axis is maintained in the vertical position by the erection
system (unstable pendulum erector) which is removed when the rotor axis
deviates more than 9 degrees plus or minus 2 degrees. The accuracy of the
vertical position in clean configuration is less than 0.5 degree. The
fast resetting of the gyroscopic horizon can be activated by pulling the
knob (8) located in the lower R corner of the indicator.
The indicator provides the following information :
- roll angle,
- pitch angle,
- instrument failure (RED flag).

(1) Pitch information

The aircraft symbol (black and yellow) (7) is fixed.
The pitch drum (9), in the center of the instrument is divided into
two zones separated by the reference horizon (white) :
the upper part is blue, the lower part is brown.
The pitch indications are displayed by means of a drum which is
graduated between -80 and +80 degrees.

(2) Roll information

The roll information is given by a pointer (10) which moves in front
of a dial (5) graduated in 10 degrees increments between -30 and +30
degrees.

(3) Failure warning

The flag (6) comes into view if a failure is detected in the
electrical power supply or if the gyro rotor speed drops below 18,000
RPM.

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 STANDBY DATA : ATTITUDE AND HEADING - ADJUSTMENT/TEST
_____________________________________________________

TASK 34-22-00-710-001

Operational Test of the Standby Compass

WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE
_______
YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.

1. __________________
Reason for the Job

To make sure that:

- the difference between the magnetic heading values on the standby compass
and the ND is not more than + or - 8⁰
- the lighting of the standby compass operates correctly
- you can read the compass cards .

2. ______________________
Job Set-up Information

A. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
31-60-00-860-001 EIS Start Procedure
31-60-00-860-002 EIS Stop Procedure
34-10-00-860-004 IR Alignment Procedure
34-22-00-730-001 Compensation Adjustment/Test of the Standby Compass

3. __________
Job Set-up

Subtask 34-22-00-860-050

A. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-

002).

(2) Do the EIS start procedure (CAPT ND only)(Ref. TASK 31-60-00-860-

001).

(3) Do the IR alignement procedure (Ref. TASK 34-10-00-860-004).

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 (4) On the windshield center post, pull the standby compass support that
you can retract from its housing.

4. Procedure
_________

Subtask 34-22-00-710-050

A. Operational Test of the Standby Compass

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the CAPT ND, read the magnetic Make sure that:

heading value. - the difference between the magnetic
heading values on the standby compass
and the ND is not more than + or -
8⁰.

NOTE : If the difference between the

____
magnetic heading values on the
standby compass and the ND is
more than + or - 8⁰ : do the
compensation adjustment/test of
the standby compass (Ref. TASK
34-22-00-730-001).

2. On the overhead panel, on the

ADIRS CDU:
- set the OFF/NAV/ATT selector
switch related to the IR1 to
OFF.

3. On the INT LT section of the On the standby compass:

overhead panel 25VU:

- set the STBY COMPASS switch to - the lighting is on

ON. - you can read the compass cards from
the CAPT and F/O seats.

- set the STBY COMPASS switch to - the lighting goes off.

STBY COMPASS.

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 5. Close-up
________

Subtask 34-22-00-860-051

A. Put the aircraft back to its initial configuration.

(1) Do the EIS stop procedure(Ref. TASK 31-60-00-860-002).

(2) On the windshield center post, push the standby compass support into
its housing.

(3) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-

002).

(4) Put the aircraft back to the serviceable condition.

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 TASK 34-22-00-730-001

Compensation Adjustment/Test of the Standby Compass

WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE
_______
YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.

1. __________________
Reason for the Job

- to adjust the compensation of the standby compass

- to find the deviation curve of the compass values when they are more than
+ or - 8⁰ from the magnetic heading.

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific 2 mm-wide non magnetic screwdriver

CE2-40 1 COMPENSATION KEY

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

APU
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the APU
31-60-00-860-001 EIS Start Procedure
31-60-00-860-002 EIS Stop Procedure
34-10-00-860-004 IR Alignment Procedure
34-10-00-860-005 ADIRS Stop Procedure
34-22-00-710-001 Operational Test of the Standby Compass

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 3. __________
Job Set-up

Subtask 34-22-00-860-052

A. Aircraft Maintenance Configuration

NOTE : For this procedure the aircraft must be on a compensation base

____
that can support the weight of the aircraft. The compensation base
must be:
- a compensation base certified by the applicable authorities or,
- a compensation base with these properties:
. a horizontal area in which the horizontal component of the
earth<s magnetic field is ( +/- 1 degree ),
.sufficiently large for the aircraft be turn smoothly 360
degrees,
.with no metal objects near it ( no vehicles or other aircraft
in a radius of 250ft, no buildings with magnetic materials in a
radins of 600ft around the ai rcraft ).

(1) Make sure that there are no ferromagnetic parts installed near the
standby compass.
Ferromagnetic parts near the standby compass can cause compass
heading errors(fasteners, tools, etc...).

(2) Energize the aircraft electrical circuits from the APU (Ref. TASK 24-
41-00-861-002).

(3) Make sure that the standby compass operates correctly (Ref. TASK 34-
22-00-710-001).

(4) Do the EIS start procedure (NDs only)(Ref. TASK 31-60-00-860-001).

(5) Do the IR alignment procedure(Ref. TASK 34-10-00-860-004).

(6) Adjust the position of the aircraft until its lubber line points to
the North with a deviation less than 2⁰.

(7) On the ADIRS CDU set the DISPLAY DATA selector switch to HDG.

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 Subtask 34-22-00-865-050

B. Make sure that these circuit breakers are closed to get the radio/
magnetic environment that usually occurs in flight :

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV/VOR/1 2RS1 G13
49VU COM/VHF/1 2RC1 G09
49VU NAV/ADF/1 1RP1 H14
R 121VU COM NAV/VOR/2 2RS2 K08
R
121VU COM NAV/ADF/2 1RP2 K02
R
121VU COM NAV/VHF/3 2RC3 L05
121VU COM NAV/VHF/2 2RC2 L04

**ON A/C 001-004,

Subtask 34-22-00-020-050

C. Below the display window on the front face of the standby compass:
- remove and safety the protection cover of the compensator.

**ON A/C ALL

4. Procedure
_________

**ON A/C 001-004,

Subtask 34-22-00-730-050

A. Compensation Adjustment/Test of the Standby Compass

NOTE : The reference magnetic heading referred to in this procedure is

____
the true heading indication read on the ADIRS CDU.
Magnetic heading = true heading + magnetic variation you must
correct this reference each year because the magnetic variation
changes.

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 (1) On the standby compass:
- put the 2 mm-wide non magnetic screwdriver into the EW hole below
the display window
- use the non magnetic screwdriver to set the EW compensation system
to zero
- put the non magnetic screwdriver into the NS hole below the display
window
- use the non magnetic screwdriver to set the NS compensation system
to zero.

(2) Use the system in operation to set the aircraft to north (MHN)
(Magnetic Heading North):
- calculate and write the magnetic deviation DN between the MHN and
the CH (Compass Heading Indication of the Standby Compass):
DN = MHN - CH
- the Adjustment Value (AV) is equal to DN
- correct the CH with the AV to get the compensated compass heading
indication (CCH)
- put the non magnetic screwdriver into the NS hole of the standby
compass
- use the non magnetic screwdriver to set the standby compass to CCH.
Example:
. if MHN = 360⁰ and CH = 356⁰
DN = 360⁰ - 356⁰ = +4⁰
AV (adjustment value) = +4
Correct the Compass Heading indication of the standby compass (CH)
with the AV to get the CCH
356⁰ + 3 = 359⁰
. if MHN = 0⁰ and CH = 002⁰
DN = 0⁰ - 2⁰ = -2⁰
AV (Adjustment Value) = -2⁰
Correct the Compass Heading indication of the standby compass (CH)
with the AV to get the CCH
2⁰ +(-2⁰) = 0

(3) Set the aircraft to East (MHE):

- calculate and write the magnetic deviation DE between the MHE and
the CH
DE = MHE - CH
- the Adjustment Value (AV) is equal to DE
- correct the CH with the AV to get the CCH
- put the non magnetic screwdriver into the EW hole of the standby
compass
- use the non magnetic screwdriver to set the standby compass to CCH
(Ref. Para. (2)).

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 (4) Set the aircraft to South (MHS):
- calculate and write the magnetic deviation DS between the MHS and
the CH
DS = MHS - CH
DS
the Adjustment Value (AV) is equal to --
2
- correct the CH with the AV to get the CCH
- put the non magnetic screwdriver into the NS hole of the standby
compass
- use the non magnetic screwdriver to set the standby compass to CCH.
Example:
. if MHS = 180⁰ and CH = 174⁰
DS = 180⁰ - 174⁰ = +6⁰
DS 6
AV = -- = + - = +3
2 2
Correct the Compass Heading indication of the standby compass (CH)
with the Adjustment Value (AV) to get the CCH
174⁰ + 3⁰ = 177⁰
. if MHS = 180⁰ and CH = 182⁰
DS = 180⁰ - 182⁰ = -2⁰
DS 2
AV = -- = - - = -1
2 2
Correct the Compass Heading indication of the standby compass (CH)
with the Adjustment Value (AV) to get the CCH
182 + (-1) = 181

(5) Set the aircraft to West (MHW)

- calculate and write the magnetic deviation DW between the MHW and
the CH
DW = MHW - CH
DW
the Adjustment Valve (AV) is equal to --
2
- correct the CH with the AV to get the CCH
- put the non magnetic screwdriver into the EW hole of the standby
compass
- use the non magnetic screwdriver to set the standby compass to CCH.
(Ref. Para. (4)).

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 **ON A/C 005-099,

Subtask 34-22-00-730-050-A

A. Compensation Adjustment/Test of the Standby Compass

NOTE : The reference magnetic heading referred to in this procedure is

____
the true heading indication read on the ADIRS CDU.
Magnetic heading = true heading + magnetic variation you must
correct this reference each year because the magnetic variation
changes.

(1) On the standby compass:

- put the COMPENSATION KEY (CE2-40) into the B hole above the display
window
- use the non magnetic Compensation Key to set the B compensation
system to zero
- put the non magnetic Compensation Key into the C hole above the
display window
- use the non magnetic Compensation Key to set the C compensation
system to zero.

(2) Use the system in operation to set the aircraft to north (MHN)
(Magnetic Heading North):
- calculate and write the magnetic deviation DN between the MHN and
the CH (Compass Heading Indication of the Standby Compass):
DN = MHN - CH
- the Adjustment Value (AV) is equal to DN
- correct the CH with the AV to get the compensated compass heading
indication (CCH)
- put the non magnetic Compensation Key into the C hole of the
standby compass
- use the non magnetic Compensation Key to set the standby compass to
CCH.
Example:
. if MHN = 360⁰ and CH = 356⁰
DN = 360⁰ - 356⁰ = +4⁰
AV (adjustment value) = +4
Correct the Compass Heading indication of the standby compass (CH)
with the AV to get the CCH
356⁰ + 3 = 359⁰
. if MHN = 0⁰ and CH = 002⁰
DN = 0⁰ - 2⁰ = -2⁰
AV (Adjustment Value) = -2⁰
Correct the Compass Heading indication of the standby compass (CH)
with the AV to get the CCH

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 2⁰ +(-2⁰) = 0

(3) Set the aircraft to East (MHE):

- calculate and write the magnetic deviation DE between the MHE and
the CH
DE = MHE - CH
- the Adjustment Value (AV) is equal to DE
- correct the CH with the AV to get the CCH
- put the non magnetic Compensation Key into the B hole of the
standby compass
- use the non magnetic Compensation Key to set the standby compass to
CCH (Ref. Para. (2)).

(4) Set the aircraft to South (MHS):

- calculate and write the magnetic deviation DS between the MHS and
the CH
DS = MHS - CH
DS
the Adjustment Value (AV) is equal to --
2
- correct the CH with the AV to get the CCH
- put the non magnetic Compensation Key into the C hole of the
standby compass
- use the non magnetic Compensation Key to set the standby compass to
CCH.
Example:
. if MHS = 180⁰ and CH = 174⁰
DS = 180⁰ - 174⁰ = +6⁰
DS 6
AV = -- = + - = +3
2 2
Correct the Compass Heading indication of the standby compass (CH)
with the Adjustment Value (AV) to get the CCH
174⁰ + 3⁰ = 177⁰
. if MHS = 180⁰ and CH = 182⁰
DS = 180⁰ - 182⁰ = -2⁰
DS 2
AV = -- = - - = -1
2 2
Correct the Compass Heading indication of the standby compass (CH)
with the Adjustment Value (AV) to get the CCH
182 + (-1) = 181

(5) Set the aircraft to West (MHW)

- calculate and write the magnetic deviation DW between the MHW and
the CH
DW = MHW - CH

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 DW
the Adjustment Valve (AV) is equal to --
2
- correct the CH with the AV to get the CCH
- put the non magnetic Compensation Key into the B hole of the
standby compass
- use the non magnetic Compensation Key to set the standby compass to
CCH. (Ref. Para. (4)).

**ON A/C ALL

Subtask 34-22-00-730-051

B. Find the deviation curve

NOTE : During the adjustment, the standby compass turns 360⁰. Make sure
____
that the letters and graduations on the compass card are not
damaged.
- set the aircraft to the twelve headings one after the other
which are necessary to find the deviation curve:
0⁰, 30⁰, 60⁰, 90⁰, 120⁰, 150⁰, 180⁰, 210⁰, 240⁰, 270⁰, 300⁰,
330⁰
- write the values of the standby compass and of the NDs or ADIRS
CDU for each aircraft position
- calculate the remaining deviation values R(⁰):
R(⁰) = MH - indication of standby compass
- make sure that:
* the remaining deviation values R(⁰) are not more than + or -
8⁰ for each heading
* the maximum range between the positive and negative deviation
values R(⁰) is not more than 10⁰
* the difference between each magnetic heading value on the
standby compass and the ND is not more than 8⁰. If the
difference is more than 8⁰, adjust the compensation
- write the remaining deviation values on the two correction
cards. Put the cards on each side of the support of the standby
compass.

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 5. Close-up
________

**ON A/C 001-004,

Subtask 34-22-00-860-053

A. Put the aircraft back to its initial configuration.

(1) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002).

(2) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005).

(3) Install the protection cover on the compensator.

(4) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-

002).

(5) Put the aircraft back to the serviceable condition.

(6) Remove the ground support and maintenance equipment, the special and
standard tools and all other items.

**ON A/C 005-099,

Subtask 34-22-00-860-053-A

A. Put the aircraft back to its initial configuration.

(1) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002).

(2) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005).

(3) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-

002).

(4) Put the aircraft back to the serviceable condition.

(5) Remove the ground support and maintenance equipment, the special and
standard tools and all other items.

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 COMPASS - STANDBY (2FN) - REMOVAL/INSTALLATION
______________________________________________

TASK 34-22-23-000-001

Removal of the Standby Compass (2FN)

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific blanking caps

No specific circuit breaker(s) safety clip(s)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

R **ON A/C 001-004,

34-22-23-991-001 Fig. 401

R **ON A/C 005-099,

R 34-22-23-991-001-A Fig. 401A

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R **ON A/C ALL

3. __________
Job Set-up

Subtask 34-22-23-865-053

A. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU LIGHTING/ICE AND STBY/COMP/LIGHT 1LF H04

4. Procedure
_________

R **ON A/C 001-004,

(Ref. Fig. 401/TASK 34-22-23-991-001)

R **ON A/C 005-099,

R (Ref. Fig. 401A/TASK 34-22-23-991-001-A)

R **ON A/C ALL

Subtask 34-22-23-020-050

A. Removal of the Standby Compass (2FN)

(1) Pull the support (3) that can be retracted from its housing (2).

(2) Loosen the four screws (6).

(3) Remove the four screws (6).

(4) Disengage the standby compass (5) from its support (3).

(5) Disconnect the electrical connector (1).

(6) Remove the standby compass (5).

(7) Put blanking caps on the disconnected electrical connectors (1) and
(4).

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 Standby Compass
Figure 401/TASK 34-22-23-991-001

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R Standby Compass
R Figure 401A/TASK 34-22-23-991-001-A

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 TASK 34-22-23-400-001

Installation of the Standby Compass (2FN)

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

33-13-00-710-001 Operational Test of the Instrument and Panel Integral

Lighting
34-22-00-730-001 Compensation Adjustment/Test of the Standby Compass

R **ON A/C 001-004,

34-22-23-991-001 Fig. 401

R **ON A/C 005-099,

R 34-22-23-991-001-A Fig. 401A

R **ON A/C ALL

3. __________
Job Set-up

Subtask 34-22-23-865-054

A. Make sure that this(these) circuit breaker(s) is(are) open, safetied and
tagged

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU LIGHTING/ICE AND STBY/COMP/LIGHT 1LF H04

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 4. Procedure
_________

R **ON A/C 001-004,

(Ref. Fig. 401/TASK 34-22-23-991-001)

R **ON A/C 005-099,

R (Ref. Fig. 401A/TASK 34-22-23-991-001-A)

R **ON A/C ALL

Subtask 34-22-23-420-050

A. Installation of the Standby Compass (2FN)

(1) Clean the component interface and/or the adjacent area.

(2) Do an inspection of the component interface and/or the adjacent area.

(3) Remove the blanking caps from the electrical connectors (1) and (4).

(4) Make sure that the electrical connectors (1) and (4) are clean and in
the correct condition.

(5) Connect the electrical connector (1) to the standby compass (5).

(6) Install the Standby Compass (5) in its support (3) that can be
retracted.

(7) Attach the standby compass (5) with the four screws (6).

(8) Tighten the four screws (6).

Subtask 34-22-23-865-055

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
1LF

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 Subtask 34-22-23-710-050

C. Test

(1) Do the compensation adjustment/test of the standby compass

(Ref. TASK 34-22-00-730-001)

(2) Do the operational test of the instrument and panel integral lighting
(Ref. TASK 33-13-00-710-001)

5. Close-up
________

Subtask 34-22-23-860-050

A. Put the aircraft back to its initial configuration.

(1) Make sure that the work area is clean and clear of tool(s) and other
items.

(2) Install the support (3) that can be retracted in its housing (2).

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 COMPASS - STANDBY (2FN) - INSPECTION/CHECK
__________________________________________

TASK 34-22-23-200-001

Detailed Visual Inspection of the Standby Compass Damping Fluid

1. __________________
Reason for the Job

Refer to the MPD TASK: 342200-01

To make sure that the standby compass operates.

2. ______________________
Job Set-up Information

Not Applicable

3. __________
Job Set-up

Subtask 34-22-23-860-051

A. Aircraft Maintenance Configuration

(1) On the windshield center post, pull the standby compass support that
you can retract from its housing.

(2) On the INT LT section of the overhead panel 25VU:

- set the STBY COMPASS switch 2LF to STBY COMPASS.
Make sure that the lighting of the standby compass is on.

4. Procedure
_________

Subtask 34-22-23-210-050

A. Visual Inspection of the Standby Compass

(1) Make sure that:

- the support is in good condition
- the standby compass is correctly attached to the support
- there are no leaks.

(2) In the compass bowl, make sure that the liquid:

- is clear
- does not contain bubbles or sediment.

(3) Make sure that the two correction cards of the compass are on each
side of the support.

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 5. Close-up
________

Subtask 34-22-23-860-052

A. Put the aircraft back to its initial configuration.

(1) On the INT LT section of the overhead panel 25VU:

- set the STBY COMPASS switch 2LF to OFF.

(2) On the windshield center post, push the standby compass support into
its housing.

(3) Put the aircraft back to the serviceable condition.

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 INDICATOR - STANDBY HORIZON (7FN) - REMOVAL/INSTALLATION
________________________________________________________

TASK 34-22-24-000-001

Removal of the Standby Horizon Indicator (7FN)

CAUTION : DO NOT REMOVE THE INDICATOR IMMEDIATELY AFTER DE-ENERGIZATION OF THE

_______
INDICATOR. THERE MUST BE 10 MINUTES OR MORE BETWEEN ITS
DE-ENERGIZATION AND THE START OF THE REMOVAL PROCEDURE. BE CAREFUL
WITH INDICATOR DURING THE REMOVAL/INSTALLATION PROCEDURES, THE
STANDBY HORIZON INDICATOR IS A FRAGILE INSTRUMENT.

NOTE : After long low-rate turns (less than 10 degree bank) the standby horizon
____
indicator does not give accurate bank indications immediately. The
specification of the standby horizon indicator accepts this type of
operation. Thus, it is not necessary to replace the indicator.

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific blanking caps

No specific circuit breaker(s) safety clip(s)
R No specific locking wedge.

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

34-22-24-991-001 Fig. 401

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 3. __________
Job Set-up

Subtask 34-22-24-865-050

A. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV/STBY/HORIZON 5FN F12
122VU LIGHTING/INSTL LT/MAIN INST/PNL AND/PED 4LF Y04

Subtask 34-22-24-010-050

B. Remove the thermoformed cover from the center instrument panel.

4. Procedure
_________

(Ref. Fig. 401/TASK 34-22-24-991-001)

Subtask 34-22-24-020-050

A. Removal of the Standby Horizon Indicator (7FN)

R CAUTION : IF YOU MOVE THE STANDBY HORIZON INDICATOR WHEN IT IS REMOVED,

_______
R MAKE SURE THAT YOU FIRST BLOCK THE GYROSCOPE ASSEMBLY WITH THE
R LOCKING WEDGE (SUPPLIED WITH THE INSTRUMENT).

R (1) To cage the standby horizon indicator: pull knob (1) and insert the
R locking wedge.

R (2) Loosen the two screws (2). Do not remove them.

R (3) Push the screws (2) to release the standby horizon indicator (3) from
R the clamp.

R (4) Disengage the standby horizon indicator (3) from its housing.

R (5) Disconnect the electrical connector (5).

R (6) Remove the standby horizon indicator (3).

R (7) Put blanking caps on the disconnected electrical connectors (4) and
R (5).

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R Standby Horizon Indicator
Figure 401/TASK 34-22-24-991-001

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 TASK 34-22-24-400-001

Installation of the Standby Horizon Indicator (7FN)

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

33-13-00-710-001 Operational Test of the Instrument and Panel Integral

Lighting

3. Procedure
_________

Subtask 34-22-24-865-051

A. Make sure that this(these) circuit breaker(s) is(are) open, safetied and
tagged

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV/STBY/HORIZON 5FN F12
R 122VU LIGHTING/INSTL LT/MAIN INST/PNL AND/PED 4LF Y04

Subtask 34-22-24-420-050

B. Installation of the Standby Horizon Indicator (7FN)

(1) Clean the component interface and/or the adjacent area.

(2) Do an inspection of the component interface and/or the adjacent area.

(3) Remove the blanking caps from the electrical connectors (3) and (4).

(4) Make sure that the electrical connectors are clean and in the correct
condition.

(5) Connect the electrical connector (4) to the standby horizon indicator
(2).

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 (6) Install the standby horizon indicator (2) in its housing.

(7) Tighten the two screws (1).

Subtask 34-22-24-865-053

C. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
5FN, 4LF

Subtask 34-22-24-710-050

D. Operational Test

(1) Do the operational test of the instrument and panel integral lighting
(Ref. TASK 33-13-00-710-001).

(2) Make sure that the flag is out of view.

(3) One minute and 30 seconds after the energization, pull the resetting
knob until the horizon line is stable. Release the knob rapidly.

(4) Make sure that the roll index reads zero.

(5) Make sure that the horizon line is stable and in line with the
aircraft symbol.

4. Close-up
________

Subtask 34-22-24-410-050

A. Put the aircraft back to its initial configuration.

(1) Install the thermoformed cover on the center instrument panel.

(2) Make sure that the work area is clean and clear of tool(s) and other
items.

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 ILS - DESCRIPTION AND OPERATION
_______________________________

1. _______
General
The function of the instrument landing system is to measure deviations
between aircraft flight path and
- glide slope
- runway alignment axis (localizer).
The localizer operates in a frequency band which ranges from 108 MHz to
111.95 MHz.
The glide operates in a frequency band which ranges from 328.6 MHz to 335.4
MHz.

2. Component
__________________
Location
(Ref. Fig. 001)

-------------------------------------------------------------------------------
FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA
| | | | DOOR | REF.
-------------------------------------------------------------------------------
2RT1 RECEIVER-ILS, 1 95VU 121 811 34-36-31
2RT2 RECEIVER-ILS, 2 96VU 122 811 34-36-31
3RT ANTENNA-LOCALIZER 1/2 110 110AL 34-36-11
4RT ANTENNA-GLIDE/SLOPE 1/2 110 110AL 34-36-18

3. __________________
System Description

A. Principle
The principle of the ILS is to receive and demodulate LOC and GLIDE
signals.
An ILS station located near the airport runway transmits these signals.
Each LOC and GLIDE signal consists of two intersecting lobes modulated
with two different frequencies (90 Hz and 150 Hz).
The ILS receiver detects and compares the two radiated modulation signals
(two for LOC and two for GLIDE). The receiver gives the crew a display in
relation to a given descent axis. In addition, the ground station
provides a Morse identification.

B. System Architecture
(Ref. Fig. 002)
The ILS comprises two independent ILS receivers 2RT1 and 2RT2 linked to a
common localizer antenna 3RT and a glide slope antenna 4RT.
The components given after can control the ILS system:
(Ref. Fig. 003)
- the Multipurpose Control and Display Unit 1(2) (MCDU) 3CA1 (3CA2) and
the Flight Management and Guidance Computer 1(2) (FMGC) 1CA1 (1CA2) for
frequency/course selection in normal mode of operation,

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 ILS - Component Location
Figure 001

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 ILS - Block Diagram
Figure 002

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 INTENTIONALLY BLANK

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 ILS - Control and Indicating
Figure 003

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 - the Radio Management Panel (RMP) 1RG1 (1RG2) for frequency/course
selection in back-up mode,
- the MCDU and the Centralized Fault Display Interface Unit (CFDIU) 1TW
for test purposes.
The Morse-coded audio identification signals are sent to the Audio
Management Unit (AMU) 1RN. These signals can be heard in the boomset and
on loudspeaker according to the crew selection performed on the CAPT
(F/O) Audio Control Panel (ACP) 2RN1 (2RN2).
The EFIS display units show the ILS data:
- the CAPT Primary Flight Display (PFD) and the F/O Navigation Display
(ND) show the deviations from the ILS1,
- the F/O PFD and the CAPT ND show the deviations from the ILS2.
The MCDU(s) shows the maintenance data.

C. Utilization Technical Data

(1) Data display

(Ref. Fig. 004)

(a) On the PFDs

On the right and below the attitude sphere, the deviation
indications come into view in approach. These are :
- the vertical deviation scale,
- the lateral deviation scale,
- the related aircraft deviation symbols.
If you select an ILS approach, the scales and symbols give
GLIDE/SLOPE and LOCALIZER deviations. The scales come into view
when you push the ILS pushbutton switch on the EFIS control
section of the Flight Control Unit (FCU). The deviation symbols
come into view when the related G/S and LOC signals from the ILS
receiver are valid.
If the ILS indications are available with the ILS pushbutton
switch pushed they have priority over the deviation information
of the R NAV approach.
In this mode the data given after are shown (item 5): in the left
bottom corner:
- ILS frequency (plus ILS identification if available),
- ILS - DME distance.
At the top section of the PFD a Flight Mode Annunciator shows the
various armed/active longitudinal and lateral modes:
(item 1): the G/S longitudinal modes are shown in the 2nd column
(cyan for armed or green for active)
(item 2): the LOC longitudinal modes are shown in the 3rd column
(cyan for armed or green for active)
VERTICAL DEVIATION (item 3)

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 ILS - Data Display
Figure 004

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 The vertical scale shows a classical glide slope deviation. It is
linear with 2 dots on each side. Two dots correspond to plus (or
minus) 0.175 ddm (150 microA) deviation. The index shows magenta
G/S indication.
Until the glide beam is captured, the glide index is not shown
(Non Computed Data). When the index is against one stop only one
half of it is in view (the outer half index).
The glide slope index and the scale flash permanently in case of
G/S excessive deviation warning.
With a glide fault, the G/S index goes out of view and a red G/S
failure warning message is shown in the middle of the scale.
(Ref. Fig. 005)
LATERAL DEVIATION (item 4)
The horizontal scale shows a classical LOC deviation with 2 dots
on each side. Two dots correspond to plus (or minus) 0.155 ddm
(150 micro A) deviation. The index shows magenta LOC indication.
Until the LOC is captured, the LOC index is not shown (Non
Computed Data). When the index is against one stop, only one half
of it is shown.
The LOC index and the scale flash permanently in case of LOC
excessive deviation warning.
With a localizer fault, the LOC index goes out of view and a red
LOC failure warning message is shown in the middle of the scale.
(Ref. Fig. 005)

(b) On NDs in the ROSE ILS mode

In the ROSE ILS mode, the ND gives a display which is similar to
that of a conventional HSI : a heading dial orientated to the
magnetic North turns and gives the actual magnetic heading of the
aircraft in relation to the stable yellow lubber line.
The ND is always heading up :
a yellow aircraft model, at the center of the heading dial is
stable and pointed up to the yellow lubber line.
Small white triangles are put each 45 deg. on the circumference
in relation to the lubber line.
They are stable and do not turn with the heading dial.
A green diamond-shaped symbol moves around the heading dial and
gives the actual track of the aircraft.
The ND shows the indications given after, when available, in its
right top corner (item 8):
- the side of the displayed ILS receiver,
- the frequency,
- the course,
- the identification.
The ND shows the ILS APP message in its center top section (item
7) when the pilot has selected the ILS approach on the MCDU.
LATERAL DEVIATION (item 6)

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 ILS - Warning Display
Figure 005

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 a dagger-shaped pointer points to the selected ILS course. Its
center part is the lateral deviation bar, which can move on a
scale which is perpendicular to the pointer and has 2 dots on
each side. The position of the bar on the scale gives the
localizer deviation. The extreme dots correspond to plus or minus
0.155 ddm (plus or minus 150 micro A). With LOC fault a red LOC
warning message comes into view in the middle of the LOC scale
and the LOC deviation bar goes out of view.
VERTICAL DEVIATION (item 9)
a magenta lozenge gives the glide slope deviation on a vertical
scale at the right of the heading dial if the aircraft is within
the condition of reception of the ILS glide slope signal.
The extreme dots of the vertical scale correspond to plus or
minus 0.175 ddm (plus or minus 150 micro A). With G/S fault, a
red G/S warning message comes into view at the top of the scale
and the index goes out of view.

(c) On ND in ARC and ROSE NAV modes

When you push the ILS pushbutton switch in ARC or ROSE NAV mode,
the ND shows the symbols given after:
- a magenta dagger-shaped pointer which points to the selected
QFU,
- an arrow which indicates the lateral deviation of the aircraft
related to the localizer axis.

(2) Audio control

The ILS receiver applies its audio output to the audio integrating
system. This system controls and directs the output to the headsets
and/or the loudspeakers. The Audio Management Unit (AMU) controls the
audio level through the Audio Control Panel (ACP). On the ACP, the
pilot must push the ILS pushbutton switch and adjust the related
potentiometer to the correct audio level.
With ILS/DME collocated stations, the DME identification Morse code
can be listened in sequence with the ILS audio signal when you push
the ILS pushbutton switch on the ACP and the ILS pushbutton switch on
the FCU.

D. Warnings
(Ref. Fig. 005)
The warnings related to the ILS are :
- local warning on the instruments that use the ILS information
- MASTER CAUT lights on CAPT and F/O glareshield panels
- aural warning : single chime (SC)
- warning message shown on the upper display unit of the ECAM system.

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 4. Power
____________
Supply
(Ref. Fig. 002)
Energization of each system is through 115VAC 400 Hz buses :
- 115VAC ESS BUS 401XP via circuit breaker 1RT1 for system 1
- 115VAC BUS 2 204XP via circuit breaker 1RT2 for system 2
The system is supplied through these circuit breakers:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV/ILS/1 1RT1 G12
121VU COM NAV/ILS/2 1RT2 K09

5. _____________________
Component Description

A. Receiver

(1) External description

(Ref. Fig. 006)
The face of the receiver is fitted with a handle, two attaching
parts, a TEST pushbutton switch and three LEDs.
The name, color and function of the three LEDs are as follows:
- ILS fail (red) indicates that an internal fault is detected.
- ILS pass (green) indicates that no internal fault is detected.
- DATA IN fail (red) indicates that no control input is available or
that input is in incorrect ARINC 429 format.
The back of the ILS receiver contains an ARINC 600, shell size
connector to provide electrical connections to the aircraft wiring
via mount.
Contact grouping is as follows :
- Top contact set - ATE interface
- Center contact set - System interconnections
- Bottom contact set - Power supply and bonding

(2) Internal description

(Ref. Fig. 007)
The ILS receiver includes:
- a LOC tuner
- a GLIDE tuner
- a BITE module
- an ILS module
- a CPU module
- a CPU monitor module
- a DATA interface module
- POWER SUPPLY modules.

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 ILS Receiver
Figure 006

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 ILS Receiver - Block Diagram
Figure 007

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 (a) LOC tuner
The LOC tuner receives and demodulates the signal from one of the
40 LOC channels ranging from 108.10 to 111.95 MHz with a 50 KHz
spacing. The tuner includes:
- a preselector:it is tuned to the selected localizer channel by
a tuning voltage provided by the CPU module.
- a mixer: it subtracts the local oscillator frequency from the
preselector localizer signal to produce a 18.1 MHz IF signal.
- two IF amplifiers: the second one is a three-stage amplifier.
- an envelope detector: it detects the low frequency envelope of
the received signal.

(b) GLIDE tuner

The GLIDE tuner receives and demodulates the signal from one of
the 40 channels ranging from the 329.15 to 335 MHz with a 150 KHz
spacing and coupled with the LOC frequencies.
The tuner includes:
- a preselector: it is formed by a broadband front-end filter
which functions as a fixed tune preselector.
- a mixer: it subtracts the local oscillator frequency from the
preselector glide slope signal to produce a 30.2 MHz IF signal.
- two IF amplifiers: the second one is a three-stage amplifier.
- an envelope detector: its detects the low frequency envelope of
the received signal.

(c) BITE module

The BITE module generates ILS
90 Hz/150 Hz test composite signals during the test sequence. The
test composite signals can be applied directly to the ILS module
or used to modulate test oscillator signals injected into the
localizer and glide slope receiver mixers.
ILS or test composite signals are switched in this module
following requirements for processing.

(d) ILS module

It processes the localizer and the glide slope composite signals.
Its circuits separate the 90 Hz and 150 Hz tones from each
composite signal and generate a DC voltage proportional to the
modulation level of each tone.

(e) CPU module

It performs the primary control, timing, logic and computations
required for receiver operation. The major device of this module
is the 80C85 microprocessor.

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 (f) CPU monitor module
It reads the eight analog localizer and glide slope tones from
the ILS module, converts the analog voltages to digital format,
computes the localizer and glide slope course deviation in DDM
and compares its computations with the primary CPU computation
transmitted on the ARINC 429 data bus.

(g) DATA interface module

The data interface module provides a two-way ARINC 429
communication path between the receiver, the remote control unit
and the cockpit display units. Separate 32 bit data words that
contain localizer and glide slope course deviations data are
converted from parallel to serial format by an LSI circuit and
transmitted over the ARINC 429 data bus to the cockpit display
units. Serial receiver tuning data and control discretes are
received by the data interface module and processed by a second
LSI circuit and other digital interface circuits.

(h) POWER SUPPLY modules

The complete power supply system is made up of two modules:
- the control module which contains the major rectifier
assemblies and part of the regulator circuit.
- the output module which develops the regulated DC outputs from
the DC voltages supplied by the control module.
The power supply develops four voltage outputs: +5V, +15V,-15V
and +8VDC.
A power monitor output is also developed and applied to a voltage
comparator in the CPU module.

(3) Operation
Ground station transmitters located near the airport<s runway
instruments transmit two separate ILS frequencies. Both carrier
frequencies are amplitude modulated with 90 Hz and 150 Hz. The ILS
receiver receives the transmitted ILS signals and compares the
relative strengths of the 90 Hz and 150 Hz carrier modulations to
determine the position of the aircraft relative to the ILS ground
station transmitters. The LOC tuner provides azimuth bearing data.
The GLIDE tuner provides elevation data. Microprocessor circuits
calculate the glide slope and localizer deviations, and output these
signals as two separate digital data words to an ARINC 429 data bus.
The data bus connects the ILS deviations to the cockpit display
units.
An audio output signal identifies the selected ILS station.

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 (4) Digital outputs
This table contains all the output parameters in the digital form.
They are sorted as per the numerical order of their output label.
The following table gives :
- EQ.SYS.LAB.SDI: (SDAC, FWC, DMC...) output label for which the
parameter is available
- PARAMETER DEFINITION: parameter name
- WORD RANGE OPER RANGE RESOLUTION ACCURACY: measurement range.
Maximum value transmitted. When the digital value changes, the
change step is equal to the accuracy
- UNIT: unit in which the digital value is transmitted
- SIG BIT: indicates whether a sign bit is available
- BITS: number of bits used by the parameter in the label
- XMSN/INTV: output transmission interval. The refresh rate is given
in milliseconds
- CODE :
BNR: binary data word
BCD: binary coded decimal data word
ISO: data word coded in ISO5 code
DIS: discrete data word
HEX: hexadecimal coded
HYB: mixed code
- ALPHA CODE: indicates the parameter mnemonic code
- SOURCE ORIGIN: parameter source computer or system.

-------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
| 033 |ILS FREQ| 108/111.95 |MHZ | | 4 |2560|BCD | | |
| | | 0.01 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 105 |RWY HDG | +/- 180 |DEG | 29 | 11 |160 |BNR | | |
| | | 0.0878 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 173 |LOC DEVN | +/- 0.4 |DDM | 29 | 12 | 80 |BNR | LOC | |
| | | 0.000097 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 174 |G/S DEVN | +/- 0.8 |DDM | 29 | 12 | 80 |BNR | GLS | |
| | | 0.000195 | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 263 |ILS GROUND| | | | 14 |200 |HYB | | |

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 -------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
| |STATION | | | | | | | | |
| |IDENT | | | | | | | | |
| |WORD 1 | | | | | | | | |
| | | | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 264 |ILS GROUND| | | | 14 |200 |HYB | | |
| |STATION | | | | | | | | |
| |IDENT | | | | | | | | |
| |WORD 2 | | | | | | | | |
| | | | | | | | | | |
-------------------------------------------------------------------------------

NOTE : Station identification consists of 4 characters max. : label

____
263 provides the first two characters (bits 11 to 17 for the
first character and bits 19 and 25 for the second one) and
label 264 gives the last two characters (bits 11 to 17 for the
third character and bits 19 to 25 for the fourth one).

B. Antennas
(Ref. Fig. 008)

(1) Localizer antenna

The localizer antenna is an airborne antenna used to receive LOC
signals in the 108-112 MHz range. It is a folded half-loop type
driven by capacitive coupling. The antenna has two independent RF
connectors used to feed two items of equipment. Connector separation
is provided by a hybrid junction in the antenna.

(2) Glide/slope antenna

The glide/slope antenna is an airborne antenna used to receive GLIDE
signals in the 329-335 MHz range. It is a folded half-loop type
driven by capacitive coupling. The antenna has two independent RF
connectors used to feed two items of equipment. Connector separation
is provided by a hybrid junction in the antenna.

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 ILS Antennas
Figure 008

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 6. _________
Operation
(Ref. Fig. 002)

A. Control
- each ILS receiver is connected to one Radio Management Panel (RMP). The
ILS receiver 1 is connected to the RMP1 (the ILS receiver 2 to the
RMP2). The ILS receiver 1 receives management bus from the FMGC1
through the RMP1 (the ILS receiver 2 from the FMGC2 through the RMP2)
- in normal operation, the FMGC1(2) tunes the ILS 1(2) receiver either
automatically or manually by means of the MCDU1(2). In this case the
RMP1(2) operates as a relay which sends the frequency information from
the FMGC1(2) to the receiver 1(2).
- by a second port, the ILS receiver 1(2) receives a second management
bus (ILS1 FREQ + RWY HDG1 + INTERRO BYTE) directly from the FMGC2(1).
The receiver selects one of the two port functions by a discrete signal
(RMP1 NAV DISC) which is received from the FMGC1(2) through the
RMP1(2).
With fault of one FMGC, the second FMGC can control the two ILS
receivers, one directly, the other through its RMP.
With fault of the RMP1(2) or two RMPs, the concerned RMP is transparent
to data and discrete from FMGC.
In manual operation (at any time, or with fault of two FMGCs) the RMP1
can control the ILS receiver 1 after ON NAV mode selection. Same
possibility for the RMP2 (ILS receiver 2).
(Ref. Fig. 009)
In this mode the RMP1 can control the ILS2 through the RMP2 after ON NAV
mode selection on the RMP2. Same possibility for ILS2 through RMP1.
After any frequency selection it is always necessary to select the
associated course.
- In LAND mode below 700 ft., the FMGC sends a ground signal on the TUNE
TEST INHIBIT discrete to the ILS receiver.
In this case, whether the frequency is sent by the FMGC or by the RMP,
the ILS receiver does not take into account any frequency change.

B. Reconfiguration Switching
In normal utilization, the ILS1 data are shown on the CAPT PFD and the
F/O ND ; the ILS2 data on the F/O PFD and the CAPT ND.
In addition the DMC 1 supplies data to the CAPT PFD and ND ; the DMC 2 to
the F/O PFD and ND.
With fault of the DMC 1(2), it is possible to switch over to the DMC 3
with the EIS DMC selector switch. This selector switch is located on
panel 8VU on the center pedestal. In this case, the DMC 3 totally
replaces the DMC 1(2) through the stage of the output switching relay of
the failed DMC. With fault of the PFD, there is an automatic transfer of
the PFD image onto the ND.

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 ILS - Frequency and Course Selection in Emergency Mode
Figure 009

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 With fault of the ND, you obtain the transfer of the ND image onto the
PFD when you push the PFD/ND XFR pushbutton switch on panel 301VU
(500VU).
When you set the PFD potentiometer to OFF on panel 301VU (500VU), this
causes :
- deactivation of the PFD
- transfer of the PFD image onto the ND.

7. BITE
_____________
Function
(Ref. Fig. 010)

A. Access to ILS Sub-Menu Functions

It is possible to select the maintenance functions of the ILS receiver 1
(2) by pressing the line key adjacent to the SYSTEM REPORT/TEST
indication on the CFDS menu, and then selecting the relevant ILS on the
NAV menu.
After these actions, the ILS 1 (2) provides its own menu page and the
sub-menu functions can then be chosen by the operator.

B. Activation of the Test Function

The ILS 1 (2) test function can be activated by pressing the line key
adjacent to the TEST indication on the ILS 1 (2) maintenance sub-menu or
by pressing the pushbutton switch on the face of the receiver.

C. Power-up Tests Initialization and Cockpit Repercussions

(1) Conditions of power-up tests initialization

- How long the computer must be de-energized: 1 s.
- A/C configuration:
- whatever the A/C configuration on ground

(2) Progress of power-up tests

- Duration: 1 s.
- Cockpit repercussions directly linked to power-up test
accomplishment (some other repercussions may occur depending on the
A/C configuration but these can be disregarded):
- MASTER CAUT light on

(3) Results of power-up tests

(cockpit repercussions, if any, in case of tests pass/tests failed).
- Tests pass:
- MASTER CAUT light off
- ILS information available on ND and PFD if ILS selected on the
FCU
- Tests failed:
- MASTER CAUT light on
- ECAM warning

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 ILS - Maintenance Test Procedure
Figure 010

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 NAV ILS 1 or 2 FAULT
- ECAM STATUS
ILS 1 or 2 INOP
* if ILS selected on FCU
- CAPT (F/O) PFD
ILS 1 (2) and LOC and GLIDE scales in red
- CAPT (F/O) ND
ILS 1 (2) in red

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 **ON A/C ALL

R Post SB 34-1147 For A/C 001-004,

ILS ((MMR)) - DESCRIPTION AND OPERATION

_______________________________________

1. _______
General
The primary function of the Multi-Mode Receiver (MMR) is to receive and
process Instrument Landing System (ILS) and Global Positioning System (GPS)
signals. The MMR is a navigation sensor with two internal receivers.

A. ILS Receiver
The function of the ILS is to provide the crew and airborne system users
with lateral (LOC) and vertical (G/S) deviation signals, with respect to
the approach ILS radio beam transmitted by a ground station.
The localizer operates in a frequency band which ranges from 108.1 MHz to
111.95 MHz and the glide uses the band from 329.15 MHz to 335 MHz as
defined by ARINC specification 710.

B. GPS Receiver
The GPS is a radio aid to worldwide navigation which provides:
- the crew with a readout of accurate navigation information, e.g.
position, track and speed
- the Flight Management and Guidance Computer (FMGC) with position
information, after hybridization in the Air Data/Inertial Reference
Unit (ADIRU) with inertial parameters, for accurate position fixing.

2. Component
__________________
Location
(Ref. Fig. 001)
The MMR system units are located in the aircraft as follows.

-------------------------------------------------------------------------------
FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA
| | | | DOOR | REF.
-------------------------------------------------------------------------------
40RT1 MMR-1 95VU 120 811 34-36-31
40RT2 MMR-2 96VU 120 811 34-36-31
3RT ANTENNA-LOCALIZER 1/2 110 110AL 34-36-11
4RT ANTENNA-GLIDE/SLOPE 1/2 110 110AL 34-36-18
43RT1 ANTENNA-GPS ACTIVE, 1 210 831 34-36-16
43RT2 ANTENNA-GPS ACTIVE, 2 210 831 34-36-16

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 MMR - Component Location
Figure 001

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 3. System
__________________
Description
(Ref. Fig. 002, 003)
The A/C comprises two independent MMRs, 40RT1 and 40RT2, linked to:
- a common localizer antenna 3RT
- a common glide/slope antenna 4RT
- a GPS active antenna 43RT1 (linked to MMR1)
- a GPS active antenna 43RT2 (linked to MMR2).

A. ILS Operation
The equipment given below can control the ILS operation:
- the Multipurpose Control and Display Units (MCDU) and the Flight
Management and Guidance Computers (FMGC) for frequency/course selection
in normal operating mode.
- the Radio Management Panels (RMPs) for frequency/course selection in
back-up mode.
The ILS data are shown on the EFIS displays:
- the CAPT Primary Flight Display (PFD) and F/O Navigation Display (ND)
show the deviations from the ILS1.
- the F/O PFD and CAPT ND show the deviations from the ILS2.
The Morse-coded audio identification signals are sent to the Audio
Management Unit (AMU). These signals can be heard in the boomset and on
the loudspeaker according to the selection by the crew on the Audio
Control Panel (ACP).

B. GPS Operation

(1) Normal operation

In normal operation, the GPS 1 data are used by the ADIRUs 1 and 3;
the GPS 2 data by the ADIRU 2.

NOTE : In order to reduce GPS initialization time, the GPS 1(2)

____
receives data from the ADIRU 1(2).

The Inertial Reference (IR) portion of the ADIRU 1(2) provides the
FMGC 1(2) with:
- pure IR data
- pure GPS data (in this case the ADIRU operates as a relay)
- hybrid GPIR data.
The hybrid GPIR 1(2) data are used by the FMGC 1(2) for position
fixing purposes.
The pure GPS data are used for display on the MCDU 1 and 2.

In case of one GPS failure, the three ADIRUs automatically select the
only operative GPS to compute hybrid GPIR data.
In case of ADIRU 1 failure, the FMGC 1 uses ADIRU 3/GPS 1 data.
In case of ADIRU 2 failure, the FMGC 2 uses ADIRU 3/GPS 2 data.

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 MMR - Monitoring and Display
Figure 002

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 MMR - Data Acquisition
Figure 003

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 NOTE : The primary source of the ADIRU 3 being the GPS
____ 1, it is
necessary to select the secondary input port of the ADIRU 3
(GPS 2) by means of the ATT HDG selector switch (13FP) to
preserve side 1/side 2 segregation (GPS 1/ADIRU 1/FMGC 1 and
GPS 2/ADIRU 3/FMGC 2 architecture).

In case of failure of two ADIRUs, the two FMGCs use only the
operative ADIRU.
This ADIRU receives data from its own side GPS (e.g. ADIRU 1 - GPS
1).

C. Maintenance Operation
The MMR system provides the Centralized Fault Display Interface Unit
(CFDIU) with an interface for onboard testing and fault reporting
purposes. The MCDUs show the maintenance data.

4. Power
____________
Supply
Each system is energized through 115VAC busbars as follows:
- 401XP for system 1
- 204XP for system 2.
The system is supplied through these circuit breakers:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV/MMR/1 42RT1 G12

R **ON A/C 005-099,

R 121VU COM NAV/MMR/2 42RT2 L07

R **ON A/C 001-004,

R Post SB 34-1147 For A/C 001-004,

R 121VU COM NAV/MMR/2 42RT2 K09

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 **ON A/C ALL

R Post SB 34-1162 For A/C 001-004,

5. _____________________
Component Description

A. MMR

(1) External description

(Ref. Fig. 004)
The face of the MMR is fitted with a handle, two attaching parts, a
TEST pushbutton switch and three LEDs. The LRU STATUS LED has two
colors (red/green).
The three LEDs have the following name, color and function:
- LRU STATUS (red) indicates that an internal fault is detected
during the front panel self-test sequence
- LRU STATUS (green) indicates that no internal fault is detected
during the front panel self-test sequence
- CONTROL FAIL (red) indicates that no control input is available
during the test sequence.
- ANT FAIL (red) indicates that a failed antenna is detected during
the test sequence.
The back of the MMR is equipped with one ARINC 600 size one
connector, which includes three plugs:
- Top Plug (TP): connection with the GPS antenna
- Middle Plug (MP): service interconnection
- Bottom Plug (BP): connection with the power supply circuit, and the
LOC and G/S coaxial interconnections.

(2) Internal description

(Ref. Fig. 005)
The MMR consists of four parts:
- the power supply unit
- the ILS receiver
- the GPS receiver
- the system processor unit.
The primary function of the MMR is to receive and process ILS and GPS
signals. The ILS receiver and the GPS receiver make up two of the
subassemblies. The ILS signals, including both localizer and
glideslope, are used to determine flight path deviations during
precision approach and landing, and are supplied to the aircraft
flight control and instrument systems. These deviations are based on
radio frequency signals that the unit receives from a ground-based
instrument landing system.

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 MMR - External Description
Figure 004

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R MMR - Block Diagram
Figure 005

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 The GPS receiver simultaneously tracks signals from up to twelve GPS
satellites. The signals are processed to generate a three-dimensional
position and a precise time. The receiver generates an estimate of
the positional accuracy provided. An integrity alert is activated if
an unannounced satellite malfunction is detected. The receiver has
the capability of excluding satellites that are malfunctioning.
The system processor card has the functions that follow:
- output position and deviation data to other aircraft systems,
- receive ILS frequency selections,
- receive ADIRU & FMGC data for GPS initialization,
- dialog with the Centralized Fault Display Interface Unit (CFDIU).

- Power supply
The aircraft supplies the 115 VAC, 400 Hz, single phase power to
the MMR. The input power is routed from the rear interconnect to
the forward power supply. The forward power supply provides power
factor corrections, and outputs +200 VDC for the aft power supply.
The aft power supply steps the +200 VDC down to +/- 6.5 and +/-
13.5 VDC outputs. These unregulated voltages are routed to the
other subassemblies where they are post-regulated to +/- 5 VDC and
+/- 12 VDC. Post-regulation provides a level of separation between
the subassemblies and possible noise on the power lines. It will
also allow shut-off of the circuit areas when not needed for a
specific phase of flight (not used today).

- ILS Receiver
The MMR receives VHF localizer and UHF glideslope signals at the
antenna jacks in the bottom plug of the rear connector. Coaxial
cables route the RF from the rear connector to the ILS receiver.
The ILS receiver includes four functional areas: VHF receiver, UHF
receiver, primary instrumentation processor, and monitor
instrumentation processor.

The VHF receiver filters, mixes and amplifies VHF signals. The
resulting intermediate frequency signals are converted into serial
data and processed by both the primary and the monitor
instrumentation circuits. The UHF receiver filters, mixes,
amplifies, and detects UHF signals. The detected signals are
converted into serial data and processed by the instrumentation
processors. The primary instrumentation processor outputs flight
path deviations to the system processor. The system processor
forwards the flight path deviations to the aircraft instrumentation
and auto-pilot computers (FMGC).
The monitor instrumentation processor performs a validity check of
the primary instrumentation processor deviation output, and
disables the outputs if the check fails. The primary and monitor
instrumentation processors use ARINC 429 buses for

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 intercommunications and for communications with the system
processor.

- GPS Receiver
The MMR receives RF signals through an active GPS antenna
(preamplifier implemented within the antenna). The GPS receiver
filters, mixes, and performs analog-to-digital conversions. The
resulting data is processed by microprocessors that output
position, velocity, time, and integrity data to the system
processor. The system processor transmits ARINC 743A-compliant data
for use by other aircraft systems. The GPS receiver also outputs a
time mark discrete signal that tells users of the ARINC 743A data
the instant in time when the position solution is valid.

- System Processor
The system processor controls the flow of data to the ILS and GPS
receivers including mode and frequency selections, GPS
initialization, and maintenance data requests. The system processor
also controls the transmission of output data including ILS
deviation, GPS position, velocity, time, integrity, time marks and
maintenance data. Circuitry on the system processor converts
received data from serial into parallel and also formats parallel
data to serial data for transmission on the bus.

**ON A/C ALL

(3) ILS digital outputs

The ILS transmits data in compliance with the low speed ARINC 429
standards. The table below contains all the output parameters in the
numerical form.

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 -------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
| 173 | LOCALIZER|+ or - 0.155| DDM| 29 | 12 | 50 | BNR| | |
| | DEVIATION| | | | | ms | | | |
| | | | | | | | | | |
| 174 | GLIDE |+ or - 0.175| DDM| 29 | 12 | 50 | BNR| | |
| | SLOPE | | | | | ms | | | |
| | DEVIATION| | | | | | | | |
| | | | | | | | | | |
| 033 | ILS |FROM 108.10 |MHz | | 15 |200 |BCD | | |
| | FREQUENCY| TO 111.95 | | | | ms | | | |
| | | | | | | | | | |
| 017 | RUNWAY | FROM 0 TO |Deg.| | 15 |300 |BCD | | |
| | HEADING | 359.9 | | | | ms | | | |
| | | | | | | | | | |
| 105 | RUNWAY | FROM 0 TO |Deg.| | 11 |300 |BNR | | |
| | HEADING | 359.9 | | | | ms | | | |
| | | | | | | | | | |
| 263 |ILS GROUND| | | | 14 |150 |HYB | | |
| | STATION | | | | | ms | | | |
| | IDENT | | | | | | | | |
| | | | | | | | | | |
| 264 |ILS GROUND| | | | 14 |150 |HYB | | |
| | STATION | | | | | ms | | | |
| | IDENT | | | | | | | | |
| | | | | | | | | | |
| 271 | MMR | | | | 19 |400 |DIS | | |
| | DISCRETE | | | | | ms | | | |
-------------------------------------------------------------------------------

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 (4) GPS digital outputs
The GPS has three independently buffered high-speed ARINC 429 digital
output buses connected to the three ADIRUs.
The table below contains all the output parameters in numerical form.

-------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
| | | | | | | | | |
| 060 | MEASURE- | Pack | N/A| N/A| | 1s | | |
| | MENT STS | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-------------|
| | |+/-268435456| | | | | | |
| 061 | PSEUDO | 256 | M | 20 | | 1s |BNR | |
| | RANGE | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-------------|
| 062 | PSEUDO | 256 | M | 11 | | 1s |BNR | |
| | RANGE | 0.125 | | | | | | |
| | FINE | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-------------|
| 063 | RANGE | +/-4096 | M/S| 20 | | 1s |BNR | |
| | RATE | 0.0039 | | | | | | |
| | | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-------------|
| | | | | | | | | |
| 064 | DELTA | +/-4096 | M | 20 | | 1s |BNR | |
| | RANGE | 0.0039 | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-------------|
| | | | | | | | | |
| 065 | SV POS X | +/-67108864| M | 20 | | 1s |BNR | |
| | | 64 | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-------------|
| | | | | | | | | |
| 066 | SV POS X | 64 | M | 14 | | 1s |BNR | |
| | FINE | 0.0039 | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-------------|
| | | +/-67108864| | | | | | |
| 070 | SV POS Y | 64 | M | 20 | | 1s |BNR | |
| | | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-------------|
| | | | | | | | | |

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 -------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
| 071 | SV POS Y | 64 | M | 14 | | 1s |BNR | |
| | FINE | 0.0039 | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-------------|
| | | | | | | | | |
| 072 | SV POS Z | +/-67108864| M | 20 | | 1s |BNR | |
| | | 64 | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-------------|
| | | | | | | | | |
| 073 | SV POS Z | 64 | M | 14 | | 1s |BNR | |
| | FINE | 0.0039 | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-------------|
| | UTC MEA- | 10.0 | | | | | | |
| 074 | SURE TIME| 9.536743 | S | 20 | | 1s |BNR | |
| | | micro sec | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-------------|
| | GPS ALT | +/-131072 | | | | | | |
| 076 | (MSL) | 0.125 | Ft | 20 | | 1s |BNR | |
| | | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-------------|
| | | 1024 | | | | | | |
| 101 | HDOP | 0.031 | N/A| 15 | | 1s |BNR | |
| | | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-------------|
| | | 1024 | | | | | | |
| 102 | VDOP | 0.031 | N/A| 15 | | 1s |BNR | |
| | | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-------------|
| | GPS TRACK| +/-180 | | | | | | |
| 103 | ANGLE | 0.0055 | Deg| 15 | | 1s |BNR | |
| | | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-------------|
| | GPS | +/-180 | | | | | | |
| 110 | LATITUDE | 0.000172 | Deg| 20 | | 1s |BNR | |
| | | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-------------|
| | GPS | +/-180 | | | | | | |
| 111 | LONGITUDE| 0.000172 | Deg| 20 | | 1s |BNR | |
|--------------|----------|------------|----|----|----|----|----|-------------|

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 -------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
| | GPS | 4096 | | | | | | |
| 112 | GROUND | 0.125 | Kts| 15 | | 1s |BNR | |
| | SPEED | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-------------|
| | GPS | 0.000172 | | | | | | |
| 120 | LATITUDE | 8.38 E-8 | Deg| 11 | | 1s |BNR | |
| | FINE | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-------------|
| | GPS | 0.000172 | | | | | | |
| 121 | LONGITUDE| 8.38 E-8 | Deg| 11 | | 1s |BNR | |
| | FINE | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-------------|
| 125 | UTC | 23:59.9 |HR: | 5 | | 1s |BCD | |
| | | 0.1 MIN |MIN | | | | | |
|--------------|----------|------------|----|----|----|----|----|-------------|
| |HORIZONTAL| 16 | NM | 17 | | 1s |BNR | |
| 130 | INTEGRITY| 0.00012 | | | | | | |
| | LIMIT | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-------------|
| | VERTICAL | 32768 | Ft | 17 | | 1s |BNR | |
| 133 | INTEGRITY| 0.25 | | | | | | |
| | LIMIT | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-------------|
| | VERTICAL | 32768 | | | | | | |
| 136 | FIGURE | 0.125 | Ft | 18 | | 1s |BNR | |
| | OF MERIT | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-------------|
| | | 1.0 | | | | | | |
| 140 | UTC FINE | 0.9536743 | S | 20 | | 1s |BNR | |
| | | micro sec | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-------------|
| | UTC FINE | 0.953674 | S | 10 | | 1s |BNR | |
| 141 | FRACTIONS| micron s | | | | | | |
| | | 0.9313225ns| | | | | | |
|--------------|----------|------------|----|----|----|----|----|-------------|
| | APPROACH | 16 | NM | 17 | | 1s |BNR | |
| 143 | AREA | 0.00012 | | | | | | |
| | HIL | | | | | | | |

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 -------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
|--------------|----------|------------|----|----|----|----|----|-------------|
| | APPROACH | 32768 | Ft | 17 | | 1s |BNR | |
| 144 | AREA | 0.25 | | | | | | |
| | HIL | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-------------|
| | | |HR: | | | | | |
| 150 | UTC | 23:59:59 |MIN:| 17 | | 1s |BNR | |
| | | 1.0 s |S | | | | | |
|--------------|----------|------------|----|----|----|----|----|-------------|
| 162 | DEST | 23:59 |HR: | 11 | |0.5s|BNR | |
| | ETA | 1 MIN |MIN | | | | | |
|--------------|----------|------------|----|----|----|----|----|-------------|
| 163 | ALT | 23:59 |HR: | 11 | |0.5s|BNR | |
| | WAYPNT | 1 MIN |MIN | | | | | |
| | ETA | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-------------|
| | VERTICAL | +/-32768 | Ft/| | | | | |
| 165 | VELOCITY | 1.0 | Mn | 15 | | 1s |BNR | |
| | | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-------------|
| | N/S | +/-4096 | | | | | | |
| 166 | VELOCITY | 0.125 | Kts| 15 | | 1s |BNR | |
| | | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-------------|
| | E/W | +/-4096 | | | | | | |
| 174 | VELOCITY | 0.125 | Kts| 15 | | 1s |BNR | |
| | | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-------------|
| 226 | DATA | N/A |N/A |N/A | |N/A |ISO | |
| | LOADER | | | | | |*5 | |
|--------------|----------|------------|----|----|----|----|----|-------------|
| |HORIZONTAL| 16 | | | | | | |
| 247 | FIGURE | 6.1E-5 | NM | 18 | | 1s |BNR | |
| | OF MERIT | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-------------|
| | | N/A |DAY:| | | | | |
| 260 | DATE | 1 Day |MON:| 6 | | 1s |BCD | |
| | | |YEAR| | | | | |

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 -------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
|--------------|----------|------------|----|----|----|----|----|-------------|
| | GPS | | | | | | | |
| 273 | SENSOR | N/A |N/A |N/A | | 1s |DIS | |
| | STATUS | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-------------|
| 343 | DEST | 16 |NM | 11 | |0.5s|BNR | |
| | HIL | 0.0078 | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-------------|
| | ALT | | | | | | | |
| 347 | WAYPNT | 16 |NM | 11 | |0.5s|BNR | |
| | HIL | 0.0078 | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-------------|
| 354 | GPSSU | N/A |N/A |N/A | | |ISO | |
| | IDENT | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-------------|
| 356 | MAINT | N/A |N/A |N/A | | |ISO | |
| | DATA | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-------------|
| | EQUIP- | | | | | | | |
| 377 | MENT | N/A |N/A |N/A | | 1s |BCD | |
| | ID | | | | | | | |
-------------------------------------------------------------------------------

B. GPS Antenna
(Ref. Fig. 006)
Two L-Band Antennas are mounted on the top of the fuselage, at the
centerline, to receive signals from the GPS satellites. The GPS antenna
is an active antenna with an integrated preamplifier and filter. It
receives GPS signals at 1575.42 MHz and matches to a 50 -ohms coaxial
cable at the input to the MMR. The antenna has a right-hand circular
polarized and omnidirectional radiation pattern.
The power supply of the preamplifier is provided by the MMR through the
coaxial cable.

NOTE : The antenna connectors have a hole to install a lockwire and

____
safety the coaxial cable.

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 GPS Active - Antenna
Figure 006

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 C. Localizer Antenna
(Ref. Fig. 007)
The localizer antenna is an airborne antenna used to receive LOC signals
in the 108-112MHz range. It is a folded half-loop type driven by
capacitive coupling. The antenna has two independent RF connectors used
to feed two independent ILS receivers. Connector separation is provided
by a hybrid junction in the antenna.

D. Glide Slope Antenna

(Ref. Fig. 007)
The glide slope antenna is an airborne antenna used to receive GLIDE
signals in the 329-335MHz range. It is a folded half-loop type driven by
capacitive coupling. The antenna has two independent RF connectors used
to feed two independent ILS receivers. Connector separation is provided
by a hybrid junction in the antenna.

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 ILS - Antennas
Figure 007

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 6. Operation
_________

A. ILS Function

(1) Normal operation

(Ref. Fig. 008)
Each MMR is connected to one Radio Management Panel (RMP). The MMR 1
is connected to the RMP 1 (the MMR 2 to the RMP 2). The MMR 1
receives management bus from the FMGC 1 through the RMP 1 (the MMR 2
from the FMGC 2 through the RMP 2).
In normal operation, the FMGC 1(2) tunes the MMR 1(2) either
automatically or manually by means of the MCDU. In this case the RMP
1(2) operates as a relay which sends the frequency information from
the FMGC 1(2) to the receiver 1(2).
Via a second port, the MMR 1(2) receives a second management bus (ILS
FREQ + RWY HDG) directly from the FMGC 2(1).
The receiver selects one of the two input ports according to the
FREQ/FUNCT DATA SOURCE SEL discrete signal, which is received from
the FMGC 1(2) through the RMP 1(2).

(2) Operation in case of failure

With failure of one FMGC, the second FMGC, after pilot action (Ref.
22-70), can control the two MMRs, the off side directly, the on side
through its RMP.
With failure of the RMP 1(2) or two RMPs, the RMP concerned is
transparent to data and discrete from FMGC.

(3) Manual operation

In manual operation (at any time, or with failure of two FMGCs) the
RMP 1 can control the MMR 1 after ON NAV mode selection. Same
possibility for the RMP 2 (MMR 2).
(Ref. Fig. 009)
In this mode the RMP 1 can control the MMR 2 through the RMP 2 after
ON NAV mode selection on the RMP 2. Same possibility for RMP 2
through RMP 1.
After any frequency selection it is always necessary to select the
associated course.

(4) Reconfiguration switching

In normal utilization, the ILS 1 data are shown on the CAPT PFD and
the F/O ND; the ILS 2 data on the F/O PFD and the CAPT ND.
The DMC 1 supplies data to the CAPT PFD and ND; the DMC 2 to the F/O
PFD and ND.
With failure of the DMC 1(2) it is possible to switch over to the DMC
3 with the EIS DMC selector switch located on the panel 8VU on the
center pedestal.

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 MMR - Control and Indicating
Figure 008

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 MMR - ILS - Course and Frequency Selection in Manual Mode
Figure 009

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 In this case, the DMC 3 totally replaces the DMC 1(2) through the
stage of the output switching relay of the failed DMC. With failure
of the PFD, there is an automatic transfer of the PFD image onto the
ND.
With failure of the CAPT (F/O) ND, you obtain the transfer of the ND
image onto the CAPT (F/O) PFD when you push the PFD/ND XFR pushbutton
switch on panel 301VU (500VU).
When you set the PFD potentiometer to OFF on the panel 301VU (500VU)
this causes:
- deactivation of the CAPT (F/O) PFD
- transfer of the PFD image onto the CAPT (F/O) ND.

(5) Audio control

The MMR applies its audio output to the audio integrating system.
This system controls and directs the output to the headsets and/or
the loudspeakers. The Audio Management Unit (AMU) controls the audio
level through the ACP. On the ACP, the pilot must push the ILS
pushbutton switch and adjust the related potentiometer to the correct
audio level.
With ILS/DME collocated stations, the DME identification morse code
can be listened in sequence with the ILS audio signal when you push
the ILS pushbutton switch on the ACP and the ILS pushbutton switch on
the FCU.

(6) Data display

(Ref. Fig. 010)

(a) On the PFDs

On the right and below the attitude sphere, the deviation
indications come into view in approach. These are:
- the vertical deviation scale
- the lateral deviation scale
- the related aircraft deviation symbols.
If you select an ILS approach, the scales and symbols give GLIDE
SLOPE and LOCALIZER deviations. The scales come into view when
you push the ILS pushbutton switch on the EFIS control section of
the Flight Control Unit (FCU). The deviation symbols come into
view when the related G/S and LOC signals from the ILS receiver
are valid.
If the ILS indications are available with the ILS pushbutton
switch pushed they have priority over the deviation information
of the R NAV approach.
In this mode the data given after are shown (item 5): in the left
bottom corner:
- ILS frequency (plus ILS identification if available)
- ILS - DME distance.

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 MMR - ILS Data Display
Figure 010

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 At the top section of the PFD a Flight Mode Annunciator shows the
various armed/active longitudinal and lateral modes:
(item 1): the G/S longitudinal modes are shown in the 2nd column
(cyan for armed or green for active)
(item 2): the LOC longitudinal modes are shown in the 3rd column
(cyan for armed or green for active)
VERTICAL DEVIATION (item 3)
The vertical scale shows a classical glide slope deviation. It is
linear with 2 dots on each side. Two dots correspond to plus (or
minus) 0.175 ddm (150 microA) deviation. The index shows magenta
G/S indication.
Until the glide beam is captured, the glide index is not shown
(No Computed Data). When the index is against one stop only one
half of it is in view (the outer half index).
The glide slope index and the scale flash permanently in case of
G/S excessive deviation warning.
With a glide fault, the G/S index goes out of view and a red G/S
failure warning message is shown in the middle of the scale.
(Ref. Fig. 011)
LATERAL DEVIATION (item 4)
The horizontal scale shows a classical LOC deviation with 2 dots
on each side. Two dots correspond to plus (or minus) 0.155 ddm
(150 microA) deviation. The index shows magenta LOC indication.
Until the LOC is captured, the LOC index is not shown (No
Computed Data). When the index is against one stop, only one half
of it is shown.
The LOC index and the scale flash permanently in case of LOC
excessive deviation warning.
With a localizer fault, the LOC index goes out of view and a red
LOC failure warning message is shown in the middle of the scale.
(Ref. Fig. 010, 011)

(b) On NDs in the ROSE ILS mode

In the ROSE ILS mode, the ND gives a display which is similar to
that of a conventional Horizontal Situation Indicator (HSI): a
heading dial orientated to the magnetic North turns and gives the
actual magnetic heading of the aircraft in relation to the stable
yellow lubber line.
The ND is always heading up:
A yellow aircraft model, at the center of the heading dial is
stable and pointed up to the yellow lubber line.
Small white triangles are put each 45 deg. on the circumference
in relation to the lubber line.
They are stable and do not turn with the heading dial.
A green diamond-shaped symbol moves around the heading dial and
gives the actual track of the aircraft.

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 MMR - ILS Warning Display
Figure 011

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 The ND shows the indications given after, when available, in its
right top corner (item 8):
- the side of the displayed ILS receiver
- the frequency
- the course
- the identification.
The ND shows the ILS APP message in its center top section (item
7) when the pilot has selected the ILS approach on the MCDU.
LATERAL DEVIATION (item 6)
A dagger-shaped pointer points to the selected ILS course. Its
center part is the lateral deviation bar, which can move on a
scale which is perpendicular to the pointer and has two dots on
each side. The position of the bar on the scale gives the
localizer deviation. The extreme dots correspond to plus or minus
0.155 ddm (plus or minus 150 microA). With LOC fault a red LOC
warning message comes into view in the middle of the LOC scale
and the LOC deviation bar goes out of view.
VERTICAL DEVIATION (item 9)
A magenta lozenge gives the glide slope deviation on a vertical
scale at the right of the heading dial if the aircraft is within
the condition of reception of the ILS glide slope signal.
The extreme dots of the vertical scale correspond to plus or
minus 0.175 ddm (plus or minus 150 microA). With G/S fault, a red
G/S warning message comes into view at the top of the scale and
the index goes out of view.

(c) On NDs in ARC and ROSE NAV modes

When you push the ILS pushbutton switch in ARC or ROSE NAV mode,
the ND shows the symbols given after (item 11):
- a magenta dagger-shaped pointer which points to the selected
QFU
- an arrow which indicates the lateral deviation of the aircraft
related to the localizer axis.

(7) Warnings
(Ref. Fig. 011)
The warnings related to the ILS are:
- local warning on the instruments that use the ILS information
- MASTER CAUT lights on CAPT and F/O glareshield panels
- aural warning: single chime (SC)
- warning message shown on the upper display unit of the ECAM system.

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 B. GPS Function

(1) Normal operation

(a) General
To reduce initialization time, the MMR 1(2) receives position
data, LAT/LONG (labels 310/311) from the ADIRU 1(2) and SET LAT,
SET LONG (labels 041, 042) UTC/Date from the FMGC 1(2) through
the ADIRU 1(2).
Each MMR receives the GPS satellite RF signals from the active
antenna to compute and provide the three ADIRUs with:
- UTC, date
- position, altitude
- ground speed, track angle
- N/S speed, E/W speed, vertical speed
- horizontal and vertical dilution of precision, figure of merit
- satellite position
- satellite measurement (pseudo-range, delta range, range rate,
UTC measurement time)
- GPS measurement status, sensor status
- real time and predictive integrity data.

Within each ADIRU an hybridization function performs the

following:
- monitoring of the MMR using GPS status word and ADIRU BITE
- generation of failure message for ECAM display
- use of pseudo-range/delta range data to compute GPS position
- use of inertial data to smooth GPS position/velocity
- use of a Kalman filter to estimate and minimize errors
- use of IR data to improve the robustness of the MMR RAIM
algorithm.
- transmission of GPS and GPIR data to the FMGC for position
fixing and display purposes.

(b) GPS primary navigation function principle in the FMGC

A navigation mode with the least error is chosen based upon the
mixed IR position and the best GPIR or radio position available.

NOTE : The GPIR position used by the FMGC to determine the

____
aircraft position is computed in the GPIR partition of the
ADIRU (hybrid solution).

The FMS mode of navigation is selected according to the following

hierarchy:
- GPIR/Inertial
- DME/DME/Inertial
- DME/VOR/Inertial

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 - Inertial only.
The GPIR/INERTIAL mode is selected as long as the following
conditions are satisfied:
- GPIR position is available and with an estimated accuracy
consistent with the intended operation.
- GPIR integrity is available and compatible with the applicable
phase of flight requirement.
As long as the GPS/INERTIAL mode is active, no DME/DME or
VOR/DME radio updating is allowed. However, LOC updating can
apply to GPS/INERTIAL position.
In this navigation mode, N IR/GPS indication is displayed on
the POSITION MONITOR page with N being the number of IRs used
to compute mixed IR position.
The selected hybrid GPIRS position is displayed on the POSITION
MONITOR page in place of the radio position.
The mixed IR position and the IR deviations displayed on the
POSITION MONITOR page do not change and are still computed
using pure IR inputs.
Aircraft position is generated by a series of filters which use
inertial position, GPIR position or radio position, and
aircraft velocity as input.
A position bias is computed once every second through the
position bias filter. This position bias is computed as the
difference between the GPIR position (or radio position) and
the inertial position.
The aircraft position is finally computed every 200 ms based on
the corrected inertial position and the aircraft velocity using
the aircraft position filter.
The GPS/INERTIAL mode can be manually inhibited by pushing the
line key adjacent to the DESELECT GPS indication on the
SELECTED NAVAIDS page.
(Ref. Fig. 012)
FMGC computed integrity:
When the GPIR position is available in the FMGC but the GPIR
integrity is not delivered by the ADIRS, the FMGC is capable of
computing an equivalent integrity called AIM (Alternate
Integrity Monitoring), using IR data, during a limited period
of time. The goal of this FMGC functionality is to improve the
availability of the GPS Primary function in the cockpit.

R (c) Clock synchronization on GPS time

R 1
_ If a GPS signal is present and valid when the power is on, the
R clock synchronizes on the GPS time using labels 150 and 260.

R 2
_ If the signal is not present during synchronization, the clock
R dispalys dashes on all the digits.

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 MMR - GPS SELECTED NAVAIDS Page on MCDU
Figure 012

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R 3
_ If the signal is present but not valid during synchronization,
R the clock indicates 00:00:00.

R 4
_ If the signal becomes not valid after synchronization, the
R clock runs on its internal time base.

R (d) Display of GPS data on MCDU

1
_ GPS MONITOR
(Ref. Fig. 013)
The GPS data are displayed on the GPS MONITOR page of the
MCDU.
To get the GPS MONITOR page, push the DATA key on the MCDU,
then the line key adjacent to the GPS MONITOR indication.
The upper part is dedicated to GPS 1 data, the lower part to
GPS 2 data.
The following data are displayed:
- GPS position (lat/long)
- true track
- GPS altitude
- figure of merit (in meters)
- ground speed
- number of satellites tracked
- mode.

2
_ PREDICTIVE GPS
(Ref. Fig. 014)
The integrity prediction results given by the GPS portion of
the MMR on Flight Management System (FMS) request are
displayed on the PREDICTIVE GPS page of the MCDU (from the
progress page which displays required navigation accuracy and
estimated position accuracy and GPS PRIMARY indication).
The prediction concerns the destination (DEST) and any pilot
entered waypoint (WPT) and the integrity availability (HIL <
0.3 Nm) is displayed by Yes (Y) or No (N) for the seven times
defined by the five minutes increments for plus or minus 15
minutes around DEST or WPT.

3
_ Progress page
The progress page indicates whether the GPS is used by the
FMGC for navigation. If it is used, the GPS PRIMARY indication
is displayed. If it is not used, the GPS PRIMARY LOST message
is shown.

4
_ MCDU scratchpad
GPS PRIMARY in white or GPS PRIMARY LOST in amber show on the
MCDU scratchpad.

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 GPS - GPS MONITOR Page on MCDU
Figure 013

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 GPS - PREDICTIVE GPS Page
Figure 014

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 5
_ SELECTED NAVAIDS page
It is possible to select GPS for navigation computation within
the FMS on the SELECTED NAVAIDS page.
If you deselected GPS, the message GPS IS DESELECTED appears
on the MCDU when a GPS approach starts.

6
_ ARRIVAL page
To select a GPS approach, use the ARRIVAL page.

R (e) Display of GPS messages on ND

(Ref. Fig. 015)

1
_ Display of GPS PRIMARY LOST amber message
This message is displayed at the bottom of the image in all
the ND modes (except engine standby modes) when the GPS
primary is lost (this message cannot be cleared from the
MCDU). In this case, the GPS is not used for navigation
(accuracy and integrity for the intended operation can still
be met by the use of alternate navigation means).

2
_ Display of GPS PRIMARY white message
This message is displayed at the bottom of the image in all
the ND modes (except engine standby modes) when the GPS
becomes primary (this message can be cleared from the MCDU).

3
_ Display of GPS APP green message
This approach message is displayed at the top of the image in
all the ND modes (except engine standby modes) when a GPS
approach is selected in the flight plan.

(2) Warning

(a) GPS failure

The GPSs are monitored by the both FWCs using a status word sent
by each GPS.
In case of GPS failure, the NAV GPS 1(2) FAULT message is
displayed in the lower part of the upper ECAM DU.
This message is accompanied by:
- activation of the MASTER CAUT lights on the glareshield
- aural warning: Single Chime (SC).

NOTE : The failure is reminded on the INOP SYSTEM page of the

____
lower ECAM DU. The message displayed is GPS 1(2).

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 MMR - GPS Data Displayed on the NDs
Figure 015

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 (b) Loss of the GPS primary navigation
When the GPS navigation is lost for any reason, the navigation
function is degraded and reverts to the traditional navigation
function with IRS positions and radio positions if available (in
this case the RNP (Required Navigation Performance) features are
still available).
Warnings are generated to indicate the loss of GPS PRIMARY
navigation:
- GPS PRIMARY LOST message on the NDs (cannot be cleared) and
MCDU (can be cleared)
- in case of GPS non-precision approach, an aural alert is
generated (Triple Click)

(c) GPS/FMS position disagreement

When GPS Primary is active and either FMGC 1 or FMGC 2 latitude
(longitude) deviates from either MMR 1 or MMR 2 latitude
(longitude) by more than 0.5 Nm, the NAV FMS/GPS POS DISAGREE and
A/C POS...........CHECK messages are displayed in amber and cyan
respectively on the ECAM DU.
These messages are accompanied by:
- activation of the MASTER CAUT lights on the glareshield
- aural warning: Single Chime (SC).

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 7. _____________
BITE Function

**ON A/C ALL

R Post SB 34-1162 For A/C 001-004,

A. CFDIU Interface

(1) BITE description

The BITE facilitates maintenance on in-service aircraft. It detects
and identifies a failure related to the MMR. The BITE of the MMR is
connected to the CFDIU.
The BITE:
- transmits permanently MMR status and its identification message to
the CFDIU,
- memorizes the failures which occurred during the last 63 flight
legs,
- monitors data inputs from the various peripherals,
- transmits to the CFDIU the result of the tests performed and
self-tests,
- can communicate with the CFDIU through the menus.
The BITE can operate in two modes:
- the normal mode,
- the menu mode.

(a) Normal mode

During the normal mode, the BITE cyclically monitors the status
of the MMR. It transmits its information to the CFDIU during the
concerned flight.
In case of fault detection, the BITE stores the information in
the fault memories.
These items of information are transmitted to the CFDIU by an
ARINC 429 message with label 356.

(b) Menu mode

The menu mode can only be activated on ground.
This mode enables communication between the CFDIU and the MMR
BITE by means of the MCDU.
(Ref. Fig. 016)
All the information displayed on the MCDU during the BITE Test
configuration can be printed by the printer (Ref. 31-35-00).
The MMR menu mode is composed of:
- LAST LEG REPORT
(Ref. Fig. 017)
This menu contains the fault messages (class 1 internal and
external) detected during the last flight.
- PREVIOUS LEGS REPORT

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 MMR - Maintenance Test Procedure
Figure 016

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 MMR - Last Leg Report
Figure 017

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 (Ref. Fig. 018)
This report contains the fault messages related to the external
or internal failures (class 1) recorded during the previous 63
flight legs.
- LRU IDENTIFICATION

R **ON A/C 001-003, 005-099,

Post SB 34-1162 For A/C 001-003,

(Ref. Fig. 019)

**ON A/C ALL

R Post SB 34-1162 For A/C 001-004,

Allows to display the P/N and the software numbers of the

equipment.
- GND SCANNING
(Ref. Fig. 020)
Based on the monitoring and fault analysis during flight,
provides information of the failures detected while using this
function.
- TROUBLE SHOOTING DATA
(Ref. Fig. 021)
Provides correlation parameters and snapshot data concerning
the failure displayed in the LAST LEG REPORT and PREVIOUS LEGS
REPORT.
- CLASS 3 FAULTS
(Ref. Fig. 022)
Allows to display the class 3 faults recorded during the last
flight leg.
- GROUND REPORT
(Ref. Fig. 023)
Allows to present the class 1 or 3 internal failures detected
on ground.
- SYSTEM TEST
(Ref. Fig. 024, 025)
Allows a check of the correct operation of the MMR.

(2) List of components

All the components are listed in Para. 2. Component Location.

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 MMR - Previous Legs Report
Figure 018

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 MMR - LRU Identification
Figure 019

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 MMR - Ground Scanning
Figure 020

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 MMR - Trouble Shooting Data
Figure 021

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 MMR - Last Leg Class 3 Faults
Figure 022

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 MMR - Ground Report
Figure 023

JKKKKKKKKKKKKKKKKKKKKKKKKKKKKKKKKKKKKKKKKKKKKKKKL
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 MMR - System Test
Figure 024

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 MMR - System Test
Figure 025

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 **ON A/C ALL

(3) Reporting function

The tables below give the list of internal/external failures.

(a) Internal failure:

-----------------------------------------------------------------------------
I ATA I CLASS I MESSAGE I
I I (A/C) I I
I----------------------------------------------------------------------------
I 34-36-31 I 1 I MMRi (40RTi) I
I 34-36-11 I 1 I LOCALIZER ANTENNA (3RT)/COAX CABLE/MMRi(40RTi) I
I 34-36-18 I 1 I GLIDE ANTENNA (4RT)/COAX CABLE/MMRi (40RTi) I
I 34-36-16 I 1 I GPS ANTENNAi (43RTi)/COAX CABLE/MMRi(40RTi) I
I I I i = (1,2) I
-----------------------------------------------------------------------------

(b) External failure:

-----------------------------------------------------------------------------
I ATA I CLASS I MESSAGE I
I I (A/C) I I
-----------------------------------------------------------------------------
I 31-32-34 I 3 I CFDIU (1TW)/MMRi (40RTi) I
I 22-83-34 I 3 I FMGCi (1CAi)/RMPi (1RGi)/MMRi (40RTi) I
I 22-83-34 I 3 I FMGCj (1CAj) BUS ILS/MMRi (40RTi) I
I 22-83-34 I 3 I FMGC1 (1CA1) BUS GPS/MMRi (40RTi) I
I 22-83-34 I 3 I FMGC2 (1CA2) BUS GPS/MMRi (40RTi) I
I 34-12-34 I 3 I ADIRUk (1FPk)/MMRi (40RTi) I
I 32-31-71 I 3 I LGCIUi (5GAi)/FMGCi (1CAi)/MMRi (40RTi) I
I 31-62-34 I 1 I DMCi (1WTi)/MMRi (40RTi) I
I I I j,i = (1,2) or (2,1) I
I I I k = 1, 2 or 3 I
-----------------------------------------------------------------------------

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 **ON A/C ALL

R Post SB 34-1162 For A/C 001-004,

(4) Interactive function

To gain access to the BITE, it is necessary to use one MCDU (Ref.
22-82-00).
(Ref. Fig. 017, 018)

R **ON A/C 001-003, 005-099,

Post SB 34-1162 For A/C 001-003,

(Ref. Fig. 019)

**ON A/C ALL

R Post SB 34-1162 For A/C 001-004,

(Ref. Fig. 020, 021, 022, 023, 024, 025)

All the information displayed on the MCDU during the BITE TEST
configuration can be printed by the printer (Ref. 31-35-00).

B. BITE Implementation

(1) Activation of the receiver face test

The receiver face test can be activated by pushing the TEST
pushbutton switch on the receiver face, if the test inhibit discrete
is not active.
The sequence below is then generated on the receiver face.
Depending on the outcome of the receiver face test, one of the
following results is displayed:

-----------------------------------------------------------------------------
I SEQUENCE I LRU STATUS I CONTROL I ANT FAIL I I TIME I
I NO. I LED (DS1) I FAIL LED I LED I DEFINITION I DEFINITION I
I I I (DS2) I (DS3) I I I
I---------------------------------------------------------------------------I
I 1 I Red I Red I Red I LED self- I 2 seconds I
I I I I I test I I
I---------------------------------------------------------------------------I
I 2 I Green I Red I Red I LED self- I 2 seconds I
I I I I I test I I
I---------------------------------------------------------------------------I
I 3 I Off I Off I Off I Unit self- I 2 seconds I
I I I I I test I minimum I
I---------------------------------------------------------------------------I

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 -----------------------------------------------------------------------------
I SEQUENCE I LRU STATUS I CONTROL I ANT FAIL I I TIME I
I NO. I LED (DS1) I FAIL LED I LED I DEFINITION I DEFINITION I
I I I (DS2) I (DS3) I I I
I---------------------------------------------------------------------------I
I 4 I Green I Off I Off I Unit passedI 30 seconds I
I I-------------------------------------------------I I
I I Red I I I Unit I I
I I I I I failed I I
I I-------------------------------------------------I I
I I I Red I I Control I I
I I I I Iinput failedI I
I I-------------------------------------------------I I
I I I I Red I Antenna I I
I I I I I failed I I
I---------------------------------------------------------------------------I
I 5 I Off I Off I Off I Test I Until next I
I I I I I complete I requested I
I I I I I I self-test I
-----------------------------------------------------------------------------

(2) Activation of the functional test

The functional test can be activated by pushing the line key adjacent
to the TEST indication on the MMR maintenance sub-menu.
It is similar to the receiver face test except that the receiver face
LEDs are not controlled to reflect the status of the unit, which is
reported on the MCDU.

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 ILS - ADJUSTMENT/TEST
_____________________

TASK 34-36-00-740-002

BITE Test of the ILS

WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE
_______
YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
31-32-00-860-010 Procedure to Get Access to the SYSTEM REPORT/TEST NAV
Page
31-60-00-860-002 EIS Stop Procedure
34-10-00-860-004 IR Alignment Procedure
34-36-00-991-001 Fig. 501

3. __________
Job Set-up

Subtask 34-36-00-860-054

A. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-

002).

(2) Do the IR alignment procedure

(Ref. TASK 34-10-00-860-004).

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 (3) On the center pedestal, on the RMP1 and RMP2:
- set the ON/OFF switch to ON.
- push the NAV and then the ILS pushbutton switches (the green LEDs
on these pushbutton switches come on).
- on the RMP1 or RMP2:
set a non local frequency of the ILS1 (ILS2) beacon.
(Ref. Fig. 501/TASK 34-36-00-991-001)

Subtask 34-36-00-865-057

B. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV/ILS/1 1RT1 G12
121VU COM NAV/ILS/2 1RT2 K09

4. Procedure
_________

NOTE : The ILS1 shows indications on the CAPT PFD and the F/O ND. The ILS2
____
shows indications on the F/O PFD and the CAPT ND.

Subtask 34-36-00-740-051

A. BITE Test of the ILS

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the CAPT and F/O EFIS control

sections of the FCU:

- push the ILS pushbutton On the CAPT and F/O PFDs:

switches. - the LOC and G/S scales come into
view.

- set the mode selector switches On the CAPT and F/O NDs:
to ROSE/ILS. - the LOC and G/S scales and the course
pointer come into view.

2. On the center pedestal, on one

MCDU, get the SYSTEM
REPORT/TEST/NAV page (Ref. TASK
31-32-00-860-010).

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 ILS - Frequency and Course Selection
Figure 501/TASK 34-36-00-991-001

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
- push the line key adjacent to A fault indication comes into view for
the ILS1 (ILS2) indication then approximately 3 seconds:
push the line key adjacent to - On the CAPT (F/O) PFD:
the TEST indication. . the LOC scale goes out of view.
. the LOC flag replaces the scale.
. the G/S scale goes out of view.
. the G/S flag comes into view on the
right side of the sphere.
. the ILS1 (ILS2) flag comes into
view in the left lower corner.
- On the F/O (CAPT) ND:
. the LOC scale stays in view.
. the LOC flag comes into view in the
middle of the heading dial.
. the G/S scale stays in view.
. the G/S flag comes into view in the
middle of the scale.
. the ILS1 (ILS2) flag comes into
view in the right upper corner.
- On the glareshield:
. the MASTER CAUT lights come on.
- On the upper ECAM display unit:
* the NAV ILS 1(2) FAULT indication
comes into view.
- In the loud speakers:
. you can hear the single chime.
An NCD indication comes into view for
approximately 2 seconds:
- On the CAPT (F/O) PFD:
. the LOC flag goes out of view.
. the LOC scale comes into view.
. the G/S flag goes out of view.
. the G/S scale comes into view.
. the ILS1 (ILS2) goes out of view.
- On the F/O (CAPT) ND:
. the LOC flag goes out of view.
. the G/S flag goes out of view.
. the ILS1 (ILS2) flag goes out of
view.
- On the glareshield:
. the MASTER CAUT lights go off.
- On the upper ECAM display unit:
. the NAV ILS 1(2) FAULT indication
goes out of view.

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
A deviation up and to the left side
comes into view for approximately 3
seconds:
- On the CAPT (F/O) PFD:
. the LOC index comes into view and
moves 1 point to the left side.
. the G/S index comes into view and
moves up 1 point.
- On the F/O (CAPT) ND:
. the LOC deviation bar comes into
view and moves 1 point to the left
side.
. the G/S index comes into view and
moves up 1 point.
A deviation down and to the right side
comes into view for approximately 6
seconds:
- On the CAPT (F/O) PFD:
. the LOC index moves 1 point to the
right side.
. the G/S index moves down 1 point.
- On the F/O (CAPT) ND:
. the LOC deviation bar moves 1 point
to the right side.
. the G/S index moves down 1 point.
At the end of the test:
- On the CAPT (F/O) PFD:
. the LOC and G/S indexes go out of
view.
- On the F/O (CAPT) ND:
. the LOC deviation bar and the G/S
index go out of view.
- On the MCDU:
. the TEST OK indication comes into
view.

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 5. Close-up
________

Subtask 34-36-00-860-055

A. Put the aircraft back to its initial configuration.

(1) On the MCDU, push the line key adjacent to the RETURN indication
until the CFDS menu page comes into view.

(2) On the CAPT and F/O EFIS control sections of the FCU, release the ILS
pushbutton switches.

(3) On the center pedestal, on the RMP1 (RMP2) :

- push the NAV and the ILS pushbutton switches (the green LEDs go
off).
- set the ON/OFF switch to OFF.

(4) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002).

(5) On the ADIRS CDU, set the OFF/NAV/ATT selector switches to OFF.

(6) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

(7) Make sure that the work area is clean and clear of tool(s) and other
items.

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 TASK 34-36-00-710-001

Operational Test of the ILS

WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE
_______
YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.

1. __________________
Reason for the Job

Reception Test of the ILS beacon.

2. ______________________
Job Set-up Information

A. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
34-36-00-991-001 Fig. 501

3. __________
Job Set-up

Subtask 34-36-00-860-050

A. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-

002).

(2) On the center pedestal, on the RMP1 (RMP2), set the ON/OFF switch to
ON.

Subtask 34-36-00-865-052

B. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV/ILS/1 1RT1 G12
121VU COM NAV/ILS/2 1RT2 K09

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 4. Procedure
_________

Subtask 34-36-00-710-055

A. Operational Test of the ILS

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the RMP1 (RMP2): On the RMP1 (RMP2):

- push the NAV pushbutton switch. - the green LED on the NAV pushbutton
switch comes on.

- set the local frequency of an - the set frequency comes into view in
ILS 1 (ILS 2) beacon with the the right display (STBY/CRS).
dual selector knob .
(Ref. Fig. 501/TASK 34-36-00-
991-001)

- push the transfer (double - the set frequency comes into view in
arrow) pushbutton switch. the left display.

2. On the center pedestal, on one

ACP:

- release the ILS 1 (ILS 2) - in the loud speakers, you can hear
pushbutton switch. the Morse signal of the station.

3. On the RMP1 (RMP2): - On the RMP1 (RMP2):

- push the NAV pushbutton switch. - the green LED on the NAV pushbutton
switch goes off.

5. Close-up
________

Subtask 34-36-00-860-051

A. Put the aircraft back to its initial configuration.

(1) On the center pedestral, on the RMP1 (RMP2), set the ON/OFF switch to
OFF.

(2) On the center pedestral, on the ACP, push the ILS1 (ILS2) pushbutton
switch.

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 (3) De-energize the aircraft electrical circuits
(Ref. TASK 24-41-00-862-002).

(4) Make sure that the work area is clean and clear of tool(s) and other
items.

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 TASK 34-36-00-720-001

Functional Test of the ILS

WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE
_______
YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific VOR-ILS ground test unit

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
31-60-00-860-002 EIS Stop Procedure
34-10-00-860-004 IR Alignment Procedure
34-36-00-991-001 Fig. 501

3. __________
Job Set-up

Subtask 34-36-00-860-052

A. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-

002).

(2) Do the IR alignment procedure (Ref. TASK 34-10-00-860-004).

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 (3) On the CAPT and F/O EFIS control sections of the FCU, push the ILS
pushbutton switches. Set the mode selector switches to ROSE/ILS.

(4) On the center pedestal, on the RMP1 (RMP2), set the ON/OFF switch to
ON.

Subtask 34-36-00-865-054

B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and
tagged

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV/ILS/1 1RT1 G12
121VU COM NAV/ILS/2 1RT2 K09

Subtask 34-36-00-480-050

C. Install the VOR-ILS ground test unit near the radome. To do this, refer
to the installation instructions.
Set the ON/OFF switch to ON.

4. Procedure
_________

NOTE : The ILS1 shows indications on the CAPT PFD and the F/O ND. The ILS2
____
shows indications on the F/O PFD and the CAPT ND.

Subtask 34-36-00-720-050

A. ILS Reception Test

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the circuit breaker panel 49VU

(121VU):

- close the circuit breaker 1RT1 On the CAPT (F/O) PFD and the F/O
(1RT2). (CAPT) ND:
- the G/S, LOC and ILS flags go out of
view.

2. On the RMP1 (RMP2): On the RMP1 (RMP2):

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
- push the NAV pushbutton switch. - the green LED on the NAV pushbutton
switch comes on.

- set the frequency related to - the set frequency comes into view in
the signal given by the ground the left display.
test unit
(Ref. Fig. 501/TASK 34-36-00-
991-001)

3. On the ground test unit:

- set the LOC and G/S selector On the CAPT (F/O) PFD:
switches to 0. - the G/S and LOC indexes come into
view in the middle of the scale.
On the F/O (CAPT) ND:
- the G/S index and the LOC deviation
bar come into view in the middle of
the scale.

- set the G/S selector switch to On the CAPT (F/O) PFD and the F/O
up 1 point then up 2 points. (CAPT) ND:
- the G/S index moves up 1 point then
up 2 points.

- set the G/S selector switch to On the CAPT (F/O) PFD and the F/O
down 1 point then down 2 (CAPT) ND:
points. - the G/S index moves down 1 point then
down 2 points.

- set the G/S selector switch to On the CAPT (F/O) PFD and the F/O
0. (CAPT) ND:
- the G/S index moves to the middle of
the scale.

- set the LOC selector switch to On the CAPT (F/O) PFD and the F/O
left 1 point then left 2 (CAPT) ND:
points. - the LOC index and deviation bar move
1 point then 2 points to the left
side.

- set the LOC selector switch to On the CAPT (F/O) PFD and the F/O
right 1 point then right 2 (CAPT) ND:

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
points. - the LOC index and deviation bar move
1 point then 2 points to the right
side.

- set the LOC selector switch to On the CAPT (F/O) PFD and the F/O
0. (CAPT) ND:
- the LOC index and deviation bar move
to the middle of the scale.

4. On one RMP1 (RMP2):

- set the CRS related to the On the F/O (CAPT) ND:

aircraft heading +20⁰, then to - the aircraft heading +20⁰, then the
the aircraft heading -20⁰. aircraft heading -20⁰ come into view
in the right upper corner.
- the course pointer moves to the
aircraft heading +20⁰, then to the
aircraft heading -20⁰.

5. On the circuit breaker panel

121VU (49VU):
- close circuit breaker 1RT2
(1RT1).

Subtask 34-36-00-720-051

B. ILS Identification Test

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the circuit breaker panel 49VU

(121VU), close the circuit
breaker 1RT1 (1RT2).

2. On the ground test unit, set the

IDENT selector switch to ON.

3. On the center pedestal, on one

ACP :

- release the ILS1 (ILS2) - you can hear the identification

pushbutton switch. signal in the loud speakers.

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
- adjust slowly and continously
until the volume is correct.

5. Close-up
________

Subtask 34-36-00-080-050

A. De-energize the VOR/ILS ground test unit and remove it.

Subtask 34-36-00-860-053

B. Put the aircraft back to its initial configuration.

(1) On the CAPT and F/O EFIS control sections of the FCU, release the ILS
pushbutton switches.

(2) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002).

(3) On the center pedestal, on the RMP1 (RMP2):

- push the NAV pushbutton switch (the green LED goes off).
- set the ON/OFF switch to OFF.

(4) On the ADIRS CDU, set the OFF/NAV/ATT selector switches to OFF.

(5) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

(6) Make sure that the work area is clean and clear of tool(s) and other
items.

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 **ON A/C ALL

R Post SB 34-1147 For A/C 001-004,

ILS ((MMR)) - ADJUSTMENT/TEST

_____________________________

TASK 34-36-00-740-003

BITE Test of the MMR

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
31-32-00-860-010 Procedure to Get Access to the SYSTEM REPORT/TEST NAV
Page
31-60-00-860-001 EIS Start Procedure
31-60-00-860-002 EIS Stop Procedure
34-10-00-860-004 IR Alignment Procedure
34-10-00-860-005 ADIRS Stop Procedure

3. __________
Job Set-up

Subtask 34-36-00-861-053

A. Energize the aircraft electrical circuits

(Ref. TASK 24-41-00-861-002).

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 Subtask 34-36-00-860-056

B. Aircraft Maintenance Configuration

NOTE : Do this test in an open area (not in the hangar).

____

(1) Do the EIS start procedure (PFD DU, ND DU and upper ECAM DU only)
(Ref. TASK 31-60-00-860-001).

(2) Align the IRs (Ref. TASK 34-10-00-860-004).

(3) On the center pedestal, on the RMP1 and RMP2:

- set the ON/OFF switch to ON
- push the NAV and the ILS pushbutton switches

(4) On the RMP1 or RMP2:

- set a non local ILS frequency.

(5) On the EFIS control panel of the FCU:

- push the ILS pushbutton switch

(6) Do the procedure to get the SYSTEM REPORT/TEST NAV page (Ref. TASK
31-32-00-860-010).

Subtask 34-36-00-865-058

C. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU AUTO FLT/FMGC/1 10CA1 B02
49VU COM/RMP/1 2RG1 G10
49VU NAV/MMR/1 42RT1 G12
121VU COM NAV/RMP/2 2RG2 L02
121VU AUTO FLT/FMGC/2 10CA2 M17

R **ON A/C 005-099,

R 121VU COM NAV/MMR/2 42RT2 L07

R **ON A/C 001-004,

R 121VU COM NAV/MMR/2 42RT2 K09

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 **ON A/C ALL

4. Procedure
_________

**ON A/C ALL

Post SB 34-1162 For A/C 001-004,

Subtask 34-36-00-740-052

A. BITE Test of the MMR

NOTE : the MMR1 shows indications on the CAPT PFD.

____
The MMR2 shows indications on the F/O PFD.

This test is for the MMR1. For the MMR2 use the indications between the
parentheses.

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the MCDU: On the MCDU:

- push the line key adjacent to - the MMR1 (MMR2) page comes into view.
the MMR1 (MMR2) indication.

R - push the line key adjacent to - the MMR1 (MMR2) TEST 1/3 page with
R the SYSTEM TEST indication. instructions comes into view.

- push the NEXT PAGE key. - the MMR1 (MMR2) TEST 2/3 page with
instructions comes into view.

- push the NEXT PAGE key. - the MMR1 (MMR2) TEST 3/3 page with
instructions comes into view.

- push the line key adjacent to - On the MCDU, the TEST IN PROGRESS 16S
the START TEST indication. indication comes into view.
- On the CAPT (F/O) PFD:
the LOC and G/S scales go out of
view,
R the LOC and G/S red warnings come
R into view for some seconds,
R the MASTER CAUT lights come on and
R the single chime sounds,
the LOC and G/S scales come into
view,
the G/S index comes into view, moves
up, moves down, then goes out of
view, and simultaneously, the LOC
index comes into view, moves to the

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
R left then to the right, then goes out
R of view,
R the MASTER CAUT lights go off and the
R single chime stops.

R - push the line key adjacent to - the TEST OK indication comes into
R the YES indication. view.

R - push the line key adjacent to - the TEST CLOSE-UP indication comes
R the RETURN indication. into view.

- push the line key adjacent to - the test procedure stops.

the RETURN indication.

**ON A/C ALL

5. Close-up
________

Subtask 34-36-00-860-057

A. Put the aircraft back to its initial configuration.

(1) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005).

(2) On the RMP1 or on the RMP2, set the ON/OFF switch to OFF.

(3) On the EFIS control panel of the FCU, release the ILS pushbutton
switch.

(4) Do the EIS stop procedure

(Ref. TASK 31-60-00-860-002).

(5) On the MCDU, push the line key adjacent to the RETURN indication
until the CFDS menu page comes into view.

(6) On the MCDU, set the BRT knob OFF.

Subtask 34-36-00-862-053

B. De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

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 TASK 34-36-00-710-002

Operational Test of the GPS

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
34-10-00-860-004 IR Alignment Procedure

3. __________
Job Set-up

Subtask 34-36-00-860-058

A. Aircraft Maintenance Configuration

NOTE : Do this test in an open area (not in the hangar).

____

(1) Energize the aircraft electrical circuits

(Ref. TASK 24-41-00-861-002).

(2) Do the IR alignment procedure (Ref. TASK 34-10-00-860-004).

(3) On the center pedestal, on the SWITCHING panel 8VU, make sure that
the ATT HDG selector switch is at NORM.

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 Subtask 34-36-00-865-059

B. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV/MMR/1 42RT1 G12

**ON A/C 005-099,

121VU COM NAV/MMR/2 42RT2 L07

**ON A/C 001-004,

121VU COM NAV/MMR/2 42RT2 K09

**ON A/C ALL

4. Procedure
_________

Subtask 34-36-00-710-056

R A. Operational Test of the GPS

R NOTE : The actions and the results of this procedure occur on the MCDU
____
R used.

R NOTE : The second part of this test concerns system 1. For system 2, use
____
R the indications between parentheses.

R -------------------------------------------------------------------------------
R ACTION RESULT
R -------------------------------------------------------------------------------
R Part 1: Test of GPS data acquisition with IRS aligned

R 1. On the MCDU: On the MCDU:

R - push the DATA mode key. - the DATA INDEX page comes into view.

R 2. Open the circuit breakers 42RT1 On the upper ECAM DU:

R and 42RT2. - the NAV GPS 1 FAULT and NAV GPS 2
R FAULT warnings come into view.

R 3. On the MCDU: On the MCDU:

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
R - push the line key adjacent to - the GPS MONITOR page comes into view:
R the GPS MONITOR indication. . no data is shown below the GPS
R POSITION, GPS ALT, TTRK, GS and MERIT
R indications for the two GPS.

R On CAPT and F/O NDs:

R - the amber GPS PRIMARY LOST indication
R is shown

R 4. Close the circuit breakers 42RT1 On the upper ECAM DU:

R and 42RT2. - the NAV GPS 1 FAULT and NAV GPS 2
R FAULT warnings go out of view.

R On the MCDU, on the GPS MONITOR page:

R NOTE : If you do this test after

____
R replacement of the MMR, one
R minute to twenty minutes are
R necessary to get the GPS data on
R the MCDU.

R - the TEST indication comes into view

R below the MODE/SAT indication for
R some seconds
R - then the ACQ indication comes into
R view
R - the number below the SAT indication
R increases (number of satellites
R tracked)
R - after 75 to 300 seconds, the ACQ
R indication goes out of view and the
R NAV indication comes into view below
R the MODE indication
R - the related values come into view
R below the GPS POSITION, GPS ALT,
R MERIT and GS indications:
R . the GPS 1 and the GPS 2 POSITION
R indications give the lat/long
R position of the aircraft,
R - make sure that the values of the two
R GPS positions are approximately the
R same.

R On CAPT and F/O NDs:

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
R - the amber GPS PRIMARY LOST indication
R goes out of view
R - the white GPS PRIMARY indication
R comes into view

R 5. On the overhead panel, on the On the MCDU, on the GPS MONITOR page:
R ADIRS CDU: - make sure that the GPS position data
R - set the DISPLAY DATA selector are approximately the same as the
R switch to PPOS. ADIRS position data on the ADIRS CDU.

R Part 2: Test of the GPS operation

R through the PREDICTIVE GPS page
R on the MCDU

R 6. Open the circuit breaker 42RT2

R (42RT1).

R 7. On the MCDU1 (MCDU2): On the MCDU1 (MCDU2):

R - push the INIT mode key - the INIT page comes into view

R - enter origin/destination - the origin/destination airport data

R airport data that are in the come into view on the bottom line of
R database. the INIT page

R - push the line key adjacent to - the RTE SELECTION page comes into
R the FROM/TO indication view

R - push the line key adjacent to - the INIT page comes into view
R the INSERT indication - the company route number is shown
R below the CO RTE indication.

R 8. Set CAPT (F/O) clock to the GMT

R reference.

R 9. On MCDU1 (MCDU2): On MCDU1 (MCDU2):

R - push the PROG mode key. - the PROGRESS page comes into view

R - push the line key adjacent to - the PREDICTIVE GPS page comes into
R the PREDICTIVE GPS indication view

R - enter the destination below the - after some seconds, the Y or N

R DEST indication indication comes into view below the
R - enter GMT plus 1 hour below the -15, -10, -5, ETA, +5, +10, +15

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
R ETA indication (Estimated Time indications.
R of Arrival).

R 10. Close the circuit breaker 42RT2

R (42RT1).

5. Close-up
________

Subtask 34-36-00-860-059

A. Put the aircraft back to its initial configuration.

(1) On the MCDU, push the MCDU MENU page.

(2) On the ADIRS CDU, set the 3 OFF/NAV/ATT selector switches to OFF.

(3) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

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 TASK 34-36-00-710-003

Operational Test of the ILS

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power

3. __________
Job Set-up

Subtask 34-36-00-860-060

A. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-

002).

(2) On the center pedestal, on the RMP1 (RMP2), set the ON/OFF switch to
ON.

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 Subtask 34-36-00-865-060

B. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV/MMR/1 42RT1 G12

**ON A/C 005-099,

121VU COM NAV/MMR/2 42RT2 L07

**ON A/C 001-004,

121VU COM NAV/MMR/2 42RT2 K09

**ON A/C ALL

4. Procedure
_________

Subtask 34-36-00-710-057

A. Operational Test of the ILS

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the RMP1 (RMP2): On the RMP1 (RMP2):

- push the NAV pushbutton switch. - the green LED on the NAV pushbutton
switch comes on.

- set the local frequency of an - the set frequency comes into view in
ILS 1 (ILS 2) beacon with the the right display (STBY/CRS).
dual selector knob.

- push the transfer (double - the set frequency comes into view in
arrow) pushbutton switch. the left display.

2. On the center pedestal, on one

ACP:

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
- release the ILS 1 (ILS 2) - in the loud speakers, you can hear
pushbutton switch. the Morse signal of the station.

3. On the RMP1 (RMP2): - On the RMP1 (RMP2):

- push the NAV pushbutton switch. - the green LED on the NAV pushbutton
switch goes off.

5. Close-up
________

Subtask 34-36-00-860-061

A. Put the aircraft back to its initial configuration.

(1) On the center pedestral, on the RMP1 (RMP2), set the ON/OFF switch to
OFF.

(2) On the center pedestral, on the ACP, push the ILS1 (ILS2) pushbutton
switch.

(3) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

(4) Make sure that the work area is clean and clear of tool(s) and other
items.

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 TASK 34-36-00-720-002

Functional Test of the ILS

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific VOR-ILS ground test unit

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
31-60-00-860-002 EIS Stop Procedure
34-10-00-860-004 IR Alignment Procedure

3. __________
Job Set-up

Subtask 34-36-00-869-063

A. General

(1) Use the VOR/ILS Ramp Test Set T30CS or NAV401L.

Subtask 34-36-00-860-062

B. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-

002).

(2) Do the IR alignment procedure (Ref. TASK 34-10-00-860-004).

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 (3) On the CAPT and F/O EFIS control sections of the FCU, push the ILS
pushbutton switches. Set the mode selector switches to ROSE/ILS.

(4) On the center pedestal, on the RMP1 (RMP2), set the ON/OFF switch to
ON.

Subtask 34-36-00-865-061

C. Make sure that this(these) circuit breaker(s) is(are) open, safetied and
tagged

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV/MMR/1 42RT1 G12

**ON A/C 005-099,

121VU COM NAV/MMR/2 42RT2 L07

**ON A/C 001-004,

121VU COM NAV/MMR/2 42RT2 K09

**ON A/C ALL

Subtask 34-36-00-480-051

D. Install the VOR-ILS ground test unit near the radome. To do this, refer
to the installation instructions.
Set the ON/OFF switch to ON.

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 4. Procedure
_________

Subtask 34-36-00-720-052

A. ILS Reception Test

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the circuit breaker panel 49VU

(121VU):

- close the circuit breaker 42RT1 On the CAPT (F/O) PFD and the F/O
(42RT2). (CAPT) ND:
- the G/S, LOC and ILS flags go out of
view.

2. On the RMP1 (RMP2): On the RMP1 (RMP2):

- push the NAV pushbutton switch. - the green LED on the NAV pushbutton
switch comes on.

- set the frequency related to - the set frequency comes into view in
the signal given by the ground the left display.
test unit

3. On the ground test unit:

- set the LOC and G/S selector On the CAPT (F/O) PFD:
switches to 0. - the G/S and LOC indexes come into
view in the middle of the scale.
On the F/O (CAPT) ND:
- the G/S index and the LOC deviation
bar come into view in the middle of
the scale.

- set the G/S selector switch to On the CAPT (F/O) PFD and the F/O
up 1 point then up 2 points. (CAPT) ND:
- the G/S index moves up 1 point then
up 2 points.

- set the G/S selector switch to On the CAPT (F/O) PFD and the F/O
down 1 point then down 2 (CAPT) ND:
points. - the G/S index moves down 1 point then
down 2 points.

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
- set the G/S selector switch to On the CAPT (F/O) PFD and the F/O
0. (CAPT) ND:
- the G/S index moves to the middle of
the scale.

- set the LOC selector switch to On the CAPT (F/O) PFD and the F/O
left 1 point then left 2 (CAPT) ND:
points. - the LOC index and deviation bar move
1 point then 2 points to the left
side.

- set the LOC selector switch to On the CAPT (F/O) PFD and the F/O
right 1 point then right 2 (CAPT) ND:
points. - the LOC index and deviation bar move
1 point then 2 points to the right
side.

- set the LOC selector switch to On the CAPT (F/O) PFD and the F/O
0. (CAPT) ND:
- the LOC index and deviation bar move
to the middle of the scale.

4. On one RMP1 (RMP2):

- set the CRS related to the On the F/O (CAPT) ND:

aircraft heading +20⁰, then to - the aircraft heading +20⁰, then the
the aircraft heading -20⁰. aircraft heading -20⁰ come into view
in the right upper corner.
- the course pointer moves to the
aircraft heading +20⁰, then to the
aircraft heading -20⁰.

5. On the circuit breaker panel

121VU (49VU):
- close circuit breaker 42RT2
(42RT1).

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 Subtask 34-36-00-720-053

B. ILS Identification Test

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the circuit breaker panel 49VU

(121VU), close the circuit
breaker 42RT1 (42RT2).

2. On the ground test unit, set the

IDENT selector switch to ON.

3. On the center pedestal, on one

ACP :

- release the ILS1 (ILS2) - you can hear the identification

pushbutton switch. signal in the loud speakers.

- adjust slowly and continously

until the volume is correct.

5. Close-up
________

Subtask 34-36-00-080-051

A. De-energize the VOR/ILS ground test unit and remove it.

Subtask 34-36-00-860-063

B. Put the aircraft back to its initial configuration.

(1) On the CAPT and F/O EFIS control sections of the FCU, release the ILS
pushbutton switches.

(2) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002).

(3) On the center pedestal, on the RMP1 (RMP2):

- push the NAV pushbutton switch (the green LED goes off).
- set the ON/OFF switch to OFF.

(4) On the ADIRS CDU, set the OFF/NAV/ATT selector switches to OFF.

(5) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

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 (6) Make sure that the work area is clean and clear of tool(s) and other
items.

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 ANTENNA - LOCALIZER (3RT) - REMOVAL/INSTALLATION
________________________________________________

TASK 34-36-11-000-001

Removal of the Localizer Antenna (3RT)

CAUTION : MAKE SURE THAT YOU DO NOT DAMAGE THE FUSELAGE WHEN YOU REMOVE THE
_______
SCUFF PLATES.

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific blanking caps

No specific circuit breaker(s) safety clip(s)
No specific warning notice
No specific access platform 3.5 m (11 ft. 6 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

53-15-11-010-001 Opening of the Radome 110AL

34-36-11-991-001 Fig. 401

3. __________
Job Set-up

Subtask 34-36-11-865-050

A. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------

R **ON A/C 001-004,

49VU NAV/ILS/1 1RT1 G12

R
121VU COM NAV/ILS/2 1RT2 K09

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 -------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
R **ON A/C ALL

R 121VU COM NAV/RADAR/1 5SQ1 K13

Subtask 34-36-11-010-050

B. Get Access

(1) In the cockpit, place a warning notice on the center pedestal to tell
persons not to operate the weather radar system.

(2) Put the access platform in position below the radome in zone 110.

(3) Open the radome 110AL (Ref. TASK 53-15-11-010-001)

4. Procedure
_________

(Ref. Fig. 401/TASK 34-36-11-991-001)

Subtask 34-36-11-020-050

A. Removal of the Localizer Antenna

(1) Remove the screws (5).

(2) Isolate the antenna (1) from the bulkhead (2).

(3) Disconnect the two coaxial connectors (3).

(4) Remove and discard the O-ring (4).

(5) Remove the localizer antenna (1).

(6) Put blanking caps on the disconnected coaxial connectors (3) and (6).

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 Localizer Antenna
Figure 401/TASK 34-36-11-991-001

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 TASK 34-36-11-400-001

Installation of the Localizer Antenna (3RT)

WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS

_______
ONLY WITH A GOOD SUPPLY OF AIR.
OBEY THE MANUFACTURERS INSTRUCTIONS.
PUT ON PROTECTIVE CLOTHING.
DO NOT GET THEM IN YOUR MOUTH.
DO NOT SMOKE.
DO NOT BREATHE THE GAS.
THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT.
GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED.

WARNING : DO NOT GET THE COMPOUND ON YOUR SKIN.

_______
IF YOU DO:
- RUB IT OFF IMMEDIATELY WITH A CLEAN CLOTH
- WASH THE SKIN WITH SOAP AND RINSE WITH CLEAN WATER.

WARNING : IF YOU GET THE FLUID ON YOUR SKIN OR IN YOUR EYES:

_______
- FLUSH IT AWAY WITH CLEAN WATER
- GET MEDICAL AID.

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific lint free cloth

No specific nonmetallic scraper
No specific warning notice
No specific access platform 3.5 m (11 ft. 6 in.)

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 B. Consumable Materials

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

Material No. 05-013 D TV-53-3507/73

RELEASE AGENT (OBSOLETE USE 05-013A) (Ref. 20-31-00)
R Material No. 09-016 USA MIL-PRF-81733D TYPE II CLASS B
CORROSION INHIBITING FILLET CONSISTENCY
(Ref. 20-31-00)
Material No. 09-019 USA AMS 3267/3
LOW ADHESION CORROSION INHIBITING SEALANT
(Ref. 20-31-00)
Material No. 11-003 USA TT-M-261
METHYL-ETHYL-KETONE (Ref. 20-31-00)

C. Expendable Parts

-------------------------------------------------------------------------------
FIG.ITEM |DESIGNATION |IPC-CSN
-------------------------------------------------------------------------------

4 O-ring 34-36-11 01 -010

D. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

20-28-00-720-007 Test of the Bonding of the Electrical and Electrical

Equipment (that is not Related to the Fluid Systems)
34-36-00-720-001 Functional Test of the ILS
34-36-00-720-002 Functional Test of the ILS
51-76-11-300-001 Repair of the Sealing
53-15-11-010-001 Opening of the Radome 110AL
53-15-11-410-001 Closing of the Radome 110AL
34-36-11-991-001 Fig. 401

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 3. __________
Job Set-up

Subtask 34-36-11-860-050

A. Aircraft Maintenance Configuration

(1) In the cockpit, make sure that the warning notice is in position on
the center pedestal to tell persons not to operate the weather radar
system.

(2) Make sure that the access platform is in position below the radome in
zone 110.

(3) Make sure that the radome 110AL is open (Ref. TASK 53-15-11-010-001).

Subtask 34-36-11-865-051

B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and
tagged

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------

**ON A/C 001-004,

49VU NAV/ILS/1 1RT1 G12

121VU COM NAV/ILS/2 1RT2 K09

**ON A/C ALL

121VU COM NAV/RADAR/1 5SQ1 K13

Subtask 34-36-11-160-050

C. Preparation for Installation

(1) Precautions :

NOTE : If you install the same antenna it is necessary to clean it

____
with CLEANING AGENTS (Material No. 11-003).

(2) Remove the used sealant from the bulkhead with CLEANING AGENTS
(Material No. 11-003) and a lint free cloth.

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 (3) Clean the component interface and/or the adjacent area.

(4) Do an inspection of the component interface and/or the adjacent area.

4. Procedure
_________

(Ref. Fig. 401/TASK 34-36-11-991-001)

WARNING : OBEY THE MANUFACTURER<S INSTRUCTIONS WHEN YOU USE THE SPECIAL
_______
MATERIAL.
THIS MATERIAL IS DANGEROUS.

CAUTION : MAKE SURE THAT YOU DO NOT DAMAGE THE FUSELAGE WHEN YOU REMOVE THE
_______
SCUFF PLATES.

Subtask 34-36-11-420-050

A. Installation of the Localizer Antenna

(1) On the bulkhead (2), apply SPECIAL MATERIALS (Material No. 05-013)
with nonmetallic scraper to the attachment of the localizer antenna
and to the support of the localizer antenna (1).

(2) On the bulkhead (2), apply SEALANTS (Material No. 09-019) with a
nonmetallic scraper to the attachment of the localizer antenna and to
the support of the localizer antenna (1) (Ref. TASK 51-76-11-300-
001).

NOTE : Make sure that the screw holes do not show any signs of
____
sealing compound.

(3) Remove the blanking caps from the coaxial connectors (3) and (6).

(4) Make sure that the coaxial connectors (3) and (6) are in the correct
condition.

(5) Put the O-ring (4) in the correct position on the antenna (1).

(6) Connect the coaxial connectors (3) and (6) to the localizer antenna
(1).

(7) Attach the localizer antenna (1) with the screws (5).

(8) Remove the unwanted sealing compound from the support of the
localizer antenna (1) with a nonmetallic scraper.

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 (9) Make sure that the bonding contact resistance between the antenna (1)
and the fuselage structure (2) is not higher than 5 milliohms
(Ref. TASK 20-28-00-720-007) .

(10) Make a seal around the support of the localizer antenna with SEALANTS
(Material No. 09-016) (Ref. TASK 51-76-11-300-001).

Subtask 34-36-11-865-052

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
1RT1, 1RT2, 5SQ1

R **ON A/C 001-004,

Subtask 34-36-11-720-050

C. Do the functional test of the two ILS (para. Identification test with
tool) (Ref. TASK 34-36-00-720-001).

**ON A/C ALL

R Post SB 34-1147 For A/C 001-004,

Subtask 34-36-11-720-050-A

C. Do the functional test of the two MMRs (para. Identification test with
tool) (Ref. TASK 34-36-00-720-002).

**ON A/C ALL

5. Close-up
________

Subtask 34-36-11-410-050

A. Close Access

(1) Make sure that the work area is clean and clear of tool(s) and other
items.

(2) Close the radome 110AL (Ref. TASK 53-15-11-410-001).

(3) Remove the access platform(s).

(4) Remove the warning notice(s).

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 **ON A/C ALL

R Post SB 34-1147 For A/C 001-004,

ANTENNA - GPS ACTIVE - REMOVAL/INSTALLATION

___________________________________________

TASK 34-36-16-000-001

Removal of the GPS Active Antenna (43RT1, 43RT2)

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific blanking caps

No specific circuit breaker(s) safety clip(s)
No specific nonmetallic scraper
No specific access platform 6.0 m (19 ft. 8 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

R **ON A/C 001-003, 005-099,

34-36-16-991-001 Fig. 401

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 **ON A/C ALL

3. __________
Job Set-up

Subtask 34-36-16-865-050

A. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV/MMR/1 42RT1 G12

R **ON A/C 005-099,

R 121VU COM NAV/MMR/2 42RT2 L07

R **ON A/C 001-004,

R 121VU COM NAV/MMR/2 42RT2 K09

R **ON A/C ALL

Subtask 34-36-16-010-050

B. Get Access

(1) Put the access platform in position at zone 220 to get access to the
antenna 43RT1 (43RT2).

4. Procedure
_________

R **ON A/C 001-003, 005-099,

(Ref. Fig. 401/TASK 34-36-16-991-001)

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 GPS Active Antenna
Figure 401/TASK 34-36-16-991-001

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 **ON A/C ALL

Subtask 34-36-16-020-050

A. Removal of the GPS Active Antenna

(1) Remove the sealant from the screw heads and around the antenna base
with a nonmetallic scraper.

(2) Remove the four screws (2) and pull the antenna (1) away from the
structure (3).

(3) Remove the lockwire and disconnect the coaxial connector (4).

(4) Remove the antenna (1) and put blanking caps on the disconnected
coaxial connectors.

NOTE : The coaxial connector (4) must not go into the fuselage.
____
Attach it to the fuselage with masking tape.

(5) If installed, remove the teflon seal (6).

NOTE : The teflon seal is optional: you can use sealant as an

____
alternative. You can use the teflon seal again. Do an
inspection of the seal and discard it only if necessary.

(6) Remove and discard the O-ring (5).

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 TASK 34-36-16-400-001

Installation of the GPS Active Antenna (43RT1, 43RT2) with Teflon Seal

WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS

_______
ONLY WITH A GOOD SUPPLY OF AIR.
OBEY THE MANUFACTURERS INSTRUCTIONS.
PUT ON PROTECTIVE CLOTHING.
DO NOT GET THEM IN YOUR MOUTH.
DO NOT SMOKE.
DO NOT BREATHE THE GAS.
THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT.
GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED.

WARNING : DO NOT GET THE COMPOUND ON YOUR SKIN.

_______
IF YOU DO:
- RUB IT OFF IMMEDIATELY WITH A CLEAN CLOTH
- WASH THE SKIN WITH SOAP AND RINSE WITH CLEAN WATER.

WARNING : IF YOU GET THE FLUID ON YOUR SKIN OR IN YOUR EYES:

_______
- FLUSH IT AWAY WITH CLEAN WATER
- GET MEDICAL AID.

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific lint-free cloth

No specific nonmetallic scraper
No specific access platform 6.0 m (19 ft. 8 in.)

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 B. Consumable Materials

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

No specific lockwire, CRES dia. 0.8 mm (0.030 in.)

Material No. 07-001B
ELECTRICAL BONDING COATING (BLUE COLOR)
(Ref. 20-31-00)
R Material No. 09-016 USA MIL-PRF-81733D TYPE II CLASS B
CORROSION INHIBITING FILLET CONSISTENCY
(Ref. 20-31-00)
Material No. 11-004 USA MIL-T-81533
1.1.1TRICHLOROETHANE (METHYL CHLOROFORM)
(Ref. 20-31-00)
Material No. 16-003 F ASNB70720
COATING (OBSOLETE USE 16-021) (Ref. 20-31-00)

C. Expendable Parts

-------------------------------------------------------------------------------
FIG.ITEM |DESIGNATION |IPC-CSN
-------------------------------------------------------------------------------

R 5 O-ring 34-36-16 01 -010

R 6 teflon seal 34-36-01 02 -030
6 teflon seal 34-36-01 02A-030
6 teflon seal 34-36-01 02C-030

D. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

20-28-00-720-007 Test of the Bonding of the Electrical and Electrical

Equipment (that is not Related to the Fluid Systems)
34-10-00-860-004 IR Alignment Procedure
51-76-11-300-001 Repair of the Sealing

**ON A/C 001-003, 005-099,

34-36-16-991-001 Fig. 401

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 **ON A/C ALL

3. __________
Job Set-up

Subtask 34-36-16-865-051

A. Make sure that this(these) circuit breaker(s) is(are) open, safetied and
tagged

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV/MMR/1 42RT1 G12

R **ON A/C 005-099,

R 121VU COM NAV/MMR/2 42RT2 L07

R **ON A/C 001-004,

R 121VU COM NAV/MMR/2 42RT2 K09

R **ON A/C ALL

Subtask 34-36-16-010-051

B. Aircraft Maintenance Configuration

(1) Make sure that the access platform is in position at zone 220 to get
access to the antenna.

4. Procedure
_________

R **ON A/C 001-003, 005-099,

(Ref. Fig. 401/TASK 34-36-16-991-001)

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 **ON A/C ALL

WARNING : OBEY THE MANUFACTURER<S INSTRUCTIONS WHEN YOU USE THE SPECIAL
_______
MATERIAL.
THIS MATERIAL IS DANGEROUS.

Subtask 34-36-16-420-050

A. Installation of the GPS Active Antenna

(1) Remove the used sealant from the fuselage structure (3) with a
nonmetallic scraper.

(2) Clean the mating surfaces with CLEANING AGENTS (Material No. 11-004)
and a lint-free cloth.

(3) Do an inspection of the component interface and/or the adjacent area.

NOTE : The antenna electrical bonding is made through the attachment

____
screws. On the antenna make sure that there is no paint,
sealant or corrosion in the recesses of the attachment screw
heads.

(4) Put a new O-ring (5) in the correct position on the antenna (1).

(5) Put the seal that you removed or a new teflon seal (6) on the antenna
base.

(6) Remove the blanking caps and connect the coaxial connector (4).
Install it with the lockwire, CRES dia. 0.8 mm (0.030 in.).

(7) Put the antenna (1) in the correct position on the fuselage.

NOTE : Use the small triangle and the F indication which are under
____
the antenna: the triangle must point to the front of the
aircraft.

(8) Install and tighten the four screws (2).

(9) Apply a bead of SEALANTS (Material No. 09-016) around the antenna
base and make it smooth (Ref. TASK 51-76-11-300-001)

(10) Apply SEALANTS (Material No. 09-016) to the screw heads and make the
antenna contour smooth.

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 (11) Make sure that the electrical bonding of the antenna is not higher
than 5 milliohms (Ref. TASK 20-28-00-720-007).

(12) Let the sealant become dry.

(13) Apply STRUCTURE PAINTS (Material No. 16-003) to the sealant around
the base of the antenna (1).

(14) Apply PAINTS FOR DETAIL (INTERNAL AND EXTERN AL) (Material No. 07-
001B) to the sealant on the head of the screws (2).

Subtask 34-36-16-865-052

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
42RT1, 42RT2

Subtask 34-36-16-710-050

C. Do the operational test of the GPS.

(1) Make sure that the IR system is aligned (Ref. TASK 34-10-00-860-004).

(2) On one MCDU, push the DATA key to get the DATA INDEX page and then
push the line key adjacent to the GPS MONITOR indication.

(3) On the GPS MONITOR page, after some minutes, make sure that:
- the GPS1(2) POSITION indication is correct.
- the TTRK indication shows dashes.
- the MERIT indication shows approx. 100 m.
- the GS indication shows approx. 000.
- the MODE indication shows NAV.

(4) On the upper ECAM DU, make sure that there is no GPS fault message.

(5) De-energize the aircraft electrical circuits.

(6) Put the aircraft back to its initial configuration.

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 5. Close-up
________

Subtask 34-36-16-410-050

A. Close Access

(1) Make sure that the work area is clean and clear of tool(s) and other
items.

(2) Remove the access platform(s).

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 TASK 34-36-16-400-001- 01

Installation of the GPS Active Antenna (43RT1, 43RT2) without Teflon Seal

WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS

_______
ONLY WITH A GOOD SUPPLY OF AIR.
OBEY THE MANUFACTURERS INSTRUCTIONS.
PUT ON PROTECTIVE CLOTHING.
DO NOT GET THEM IN YOUR MOUTH.
DO NOT SMOKE.
DO NOT BREATHE THE GAS.
THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT.
GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED.

WARNING : DO NOT GET THE COMPOUND ON YOUR SKIN.

_______
IF YOU DO:
- RUB IT OFF IMMEDIATELY WITH A CLEAN CLOTH
- WASH THE SKIN WITH SOAP AND RINSE WITH CLEAN WATER.

WARNING : IF YOU GET THE FLUID ON YOUR SKIN OR IN YOUR EYES:

_______
- FLUSH IT AWAY WITH CLEAN WATER
- GET MEDICAL AID.

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific lint-free cloth

No specific masking tape
No specific nonmetallic scraper
No specific access platform 6.0 m (19 ft. 8 in.)

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 B. Consumable Materials

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

No specific lockwire, CRES dia. 0.8 mm (0.030 in.).

Material No. 05-013 D TV-53-3507/73
RELEASE AGENT (OBSOLETE USE 05-013A) (Ref. 20-31-00)
Material No. 07-001B
ELECTRICAL BONDING COATING (BLUE COLOR)
(Ref. 20-31-00)
R Material No. 09-016 USA MIL-PRF-81733D TYPE II CLASS B
CORROSION INHIBITING FILLET CONSISTENCY
(Ref. 20-31-00)
Material No. 09-019 USA AMS 3267/3
LOW ADHESION CORROSION INHIBITING SEALANT
(Ref. 20-31-00)
Material No. 11-003 USA TT-M-261
METHYL-ETHYL-KETONE (Ref. 20-31-00)
Material No. 16-003 F ASNB70720
COATING (OBSOLETE USE 16-021) (Ref. 20-31-00)

C. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

20-28-00-912-004 Electrical Bonding of Components With Conductive

Bolts and Screws and Bonding Straps in the Fuselage
R and in the Wings (this does not include the tanks)-
34-10-00-860-004 IR Alignment Procedure
51-76-11-300-001 Repair of the Sealing

**ON A/C 001-003, 005-099,

34-36-16-991-001 Fig. 401

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 **ON A/C ALL

3. __________
Job Set-up

Subtask 34-36-16-865-053

A. Make sure that this(these) circuit breaker(s) is(are) open, safetied and
tagged

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV/MMR/1 42RT1 G12

R **ON A/C 005-099,

R 121VU COM NAV/MMR/2 42RT2 L07

R **ON A/C 001-004,

R 121VU COM NAV/MMR/2 42RT2 K09

R **ON A/C ALL

Subtask 34-36-16-010-052

B. Aircraft Maintenance Configuration

(1) Make sure that the access platform is in position at zone 220 to get
access to the antenna.

4. Procedure
_________

R **ON A/C 001-003, 005-099,

(Ref. Fig. 401/TASK 34-36-16-991-001)

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 **ON A/C ALL

WARNING : OBEY THE MANUFACTURER<S INSTRUCTIONS WHEN YOU USE THE SPECIAL
_______
MATERIAL.
THIS MATERIAL IS DANGEROUS.

Subtask 34-36-16-420-051

A. Installation of the GPS Active Antenna

(1) Remove the used sealant from the fuselage structure (3) with a
nonmetallic scraper.

(2) Clean the mating surfaces with CLEANING AGENTS (Material No. 11-003)
and a lint-free cloth.

(3) Do an inspection of the component interface and/or the adjacent area.

NOTE : The antenna electrical bonding is made through the attachment

____
screws. On the antenna make sure that there is no paint,
sealant or corrosion in the recesses of the attachment screws
heads.

(4) Apply masking tape to the structure (3), the edge of the antenna (1),
the screw holes and the hole for the antenna connector.

(5) Apply SPECIAL MATERIALS (Material No. 05-013) to the bottom of the
antenna (1).

(6) Apply SEALANTS (Material No. 09-019) to the area of the fuselage (3)
that makes an interface with the antenna (1) (Ref. TASK 51-76-11-300-
001).

(7) Remove the masking tape from the screw holes and the hole for the
antenna connector.

(8) Remove the blanking caps from the electrical connectors.

(9) Make sure that the electrical connectors are clean and in the correct
condition.

(10) Install the new O-ring (5).

(11) Connect the coaxial connector (4) to the GPS antenna connector.

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 (12) Safety the coaxial connector (4) with lockwire, CRES dia. 0.8 mm
(0.030 in.).

(13) Put the antenna (1) in position and install the screws (2).

(14) Tighten the screws (2) in a diagonal sequence.

(15) Remove the unwanted sealant with a nonmetallic scraper.

(16) Remove the remaining masking tape.

(17) Make sure that the bonding contact resistance between the antenna (1)
and the fuselage structure (3) is not higher than 5 milliohms
(Ref. TASK 20-28-00-912-004).

(18) Make a sealing bead with SEALANTS (Material No. 09-016) around the
antenna (1) (Ref. TASK 51-76-11-300-001).

(19) Apply SEALANTS (Material No. 09-016) to the heads of the screws (2).

(20) Make the contour of the sealant on the screws (2) and around the
antenna (1) smooth.

(21) Let the sealant cure.

(22) Apply STRUCTURE PAINTS (Material No. 16-003) to the sealant around
the base of the antenna (1).

(23) Apply PAINTS FOR DETAIL (INTERNAL AND EXTERN AL) (Material No. 07-
001B) to the sealant on the head of the screws (2).

Subtask 34-36-16-865-054

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
42RT1, 42RT2

Subtask 34-36-16-710-051

C. Do the operational test of the GPS.

(1) Make sure that the IR system is aligned (Ref. TASK 34-10-00-860-004).

(2) On one MCDU, push the DATA key to get the DATA INDEX page and then
push the line key adjacent to the GPS MONITOR indication.

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 (3) On the GPS MONITOR page, after some minutes, make sure that:
- the GPS1(2) POSITION indication is correct.
- the TTRK indication shows dashes.
- the MERIT indication shows approx. 100 m.
- the GS indication shows approx. 000.
- the MODE indication shows NAV.

(4) On the upper ECAM DU, make sure that there is no GPS fault message.

(5) De-energize the aircraft electrical circuits.

(6) Put the aircraft back to its initial configuration.

5. Close-up
________

Subtask 34-36-16-410-051

A. Close Access

(1) Make sure that the work area is clean and clear of tool(s) and other
items.

(2) Remove the access platform(s).

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 ANTENNA - GLIDE/SLOPE (4RT) - REMOVAL/INSTALLATION
__________________________________________________

TASK 34-36-18-000-001

Removal of the Glide/Slope Antenna (4RT)

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific blanking caps

No specific circuit breaker(s) safety clip(s)
No specific warning notice
No specific access platform 3.5 m (11 ft. 6 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

53-15-11-010-001 Opening of the Radome 110AL

34-36-18-991-001 Fig. 401

3. __________
Job Set-up

Subtask 34-36-18-865-050

A. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------

R **ON A/C 001-004,

49VU NAV/ILS/1 1RT1 G12

R
121VU COM NAV/ILS/2 1RT2 K09

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 -------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
R **ON A/C ALL

R 121VU COM NAV/RADAR/1 5SQ1 K13

Subtask 34-36-18-010-050

B. Get Access

(1) In the cockpit, put a warning notice on the center pedestal to tell
persons not to operate or to start the weather radar system.

(2) Put the access platform in position in zone 110 below the radome.

(3) Open the radome 110AL (Ref. TASK 53-15-11-010-001) .

4. Procedure
_________

(Ref. Fig. 401/TASK 34-36-18-991-001)

Subtask 34-36-18-020-050

A. Removal of the Glide/Slope Antenna

(1) Loosen the screws (6).

(2) Disengage the antenna (1) away from the bulkhead (4).

(3) Remove and discard the O-rings (2).

(4) Disconnect the coaxial connectors (3).

(5) Remove the antenna (1).

(6) Put blanking caps on the disconnected coaxial connectors (3) and (5).

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 Glide/Slope Antenna
Figure 401/TASK 34-36-18-991-001

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 TASK 34-36-18-400-001

Installation of the Glide/Slope Antenna (4RT)

WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS

_______
ONLY WITH A GOOD SUPPLY OF AIR.
OBEY THE MANUFACTURERS INSTRUCTIONS.
PUT ON PROTECTIVE CLOTHING.
DO NOT GET THEM IN YOUR MOUTH.
DO NOT SMOKE.
DO NOT BREATHE THE GAS.
THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT.
GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED.

WARNING : DO NOT GET THE COMPOUND ON YOUR SKIN.

_______
IF YOU DO:
- RUB IT OFF IMMEDIATELY WITH A CLEAN CLOTH
- WASH THE SKIN WITH SOAP AND RINSE WITH CLEAN WATER.

WARNING : IF YOU GET THE FLUID ON YOUR SKIN OR IN YOUR EYES:

_______
- FLUSH IT AWAY WITH CLEAN WATER
- GET MEDICAL AID.

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific lint-free cloth

No specific warning notice
No specific access platform 3.5 m (11 ft. 6 in.)

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 B. Consumable Materials

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

Material No. 05-013 D TV-53-3507/73

RELEASE AGENT (OBSOLETE USE 05-013A) (Ref. 20-31-00)
R Material No. 09-016 USA MIL-PRF-81733D TYPE II CLASS B
CORROSION INHIBITING FILLET CONSISTENCY
(Ref. 20-31-00)
Material No. 09-019 USA AMS 3267/3
LOW ADHESION CORROSION INHIBITING SEALANT
(Ref. 20-31-00)
Material No. 11-003 USA TT-M-261
METHYL-ETHYL-KETONE (Ref. 20-31-00)

C. Expendable Parts

-------------------------------------------------------------------------------
FIG.ITEM |DESIGNATION |IPC-CSN
-------------------------------------------------------------------------------

2 O-rings 34-36-18 01 -010

D. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

34-36-00-720-001 Functional Test of the ILS

34-36-00-720-002 Functional Test of the ILS
51-76-11-300-001 Repair of the Sealing
53-15-11-010-001 Opening of the Radome 110AL
53-15-11-410-001 Closing of the Radome 110AL
34-36-18-991-001 Fig. 401

3. __________
Job Set-up

Subtask 34-36-18-860-050

A. Aircraft Maintenance Configuration

(1) In the cockpit, make sure that the warning notice is in position on
the center pedestal to tell persons not to operate or to start the
weather radar system.

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 (2) Make sure that the access platform is in position below the radome in
zone 110.

(3) Make sure that the radome 110AL is open (Ref. TASK 53-15-11-010-001).

Subtask 34-36-18-865-051

B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and
tagged

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------

**ON A/C 001-004,

49VU NAV/ILS/1 1RT1 G12

121VU COM NAV/ILS/2 1RT2 K09

**ON A/C ALL

121VU COM NAV/RADAR/1 5SQ1 K13

Subtask 34-36-18-160-050

C. Preparation for Installation

(1) Precautions

NOTE : If you install the same antenna, it is necessary to clean it

____
with CLEANING AGENTS (Material No. 11-003)

(2) Remove the used sealant from the fuselage with CLEANING AGENTS
(Material No. 11-003) and a lint-free cloth.

(3) Clean the component interface and/or the adjacent area.

(4) Do an inspection of the component interface and/or the adjacent area.

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 4. Procedure
_________

(Ref. Fig. 401/TASK 34-36-18-991-001)

WARNING : OBEY THE MANUFACTURER<S INSTRUCTIONS WHEN YOU USE THE SPECIAL
_______
MATERIAL.
THIS MATERIAL IS DANGEROUS.

Subtask 34-36-18-420-050

A. Installation of the Glide/Slope Antenna

(1) Apply SPECIAL MATERIALS (Material No. 05-013) to the bulkhead (4)
where you install the antenna and to the antenna (1) mount.

(2) Apply SEALANTS (Material No. 09-019) to the bulkhead (4) where you
install the antenna and to the antenna (1) mount (Ref. TASK 51-76-11-
300-001).

NOTE : Make sure that there is no sealant in the screws holes.

____

(3) Remove the blanking caps from the coaxial connectors (3) and (5).

(4) Put the O-rings (2) in the correct position on the antenna (1).

(5) Connect the coaxial connectors (3) to the antenna (1).

(6) Put the antenna (1) in position on the bulkhead (4).

(7) Attach the antenna (1) with the screws (6).

(8) Remove the sealant which is not necessary.

(9) Apply a sealing bead with SEALANTS (Material No. 09-016) around the
antenna (1).

(10) Make the antenna contour smooth.

Subtask 34-36-18-865-052

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
1RT1, 1RT2, 5SQ1

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R **ON A/C 001-004,

Subtask 34-36-18-720-050

C. Do the functional test of the two ILS (para. Reception test with tool)
(Ref. TASK 34-36-00-720-001).

**ON A/C ALL

R Post SB 34-1147 For A/C 001-004,

Subtask 34-36-18-720-050-A

C. Do the functional test of the two MMRs (para. Reception test with tool)
(Ref. TASK 34-36-00-720-002).

**ON A/C ALL

5. Close-up
________

Subtask 34-36-18-410-050

A. Close Access

(1) Make sure that the work area is clean and clear of tool(s) and other
items.

(2) Close the radome 110AL (Ref. TASK 53-15-11-410-001).

(3) Remove the access platform(s).

(4) Remove the warning notice(s).

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 RECEIVER - ILS (2RT1,2RT2) - REMOVAL/INSTALLATION
_________________________________________________

TASK 34-36-31-000-001

Removal of the ILS Receiver (2RT1,2RT2)

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific blanking caps

No specific circuit breaker(s) safety clip(s)
No specific access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

34-36-31-991-001 Fig. 401

3. __________
Job Set-up

Subtask 34-36-31-865-050

A. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
FOR 2RT1
49VU NAV/ILS/1 1RT1 G12
FOR 2RT2
121VU COM NAV/ILS/2 1RT2 K09

R
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 Subtask 34-36-31-010-050

B. Get Access

(1) Put the access platform in position at the access door 811 in zone
122.

(2) Open the access door 811.

4. Procedure
_________

(Ref. Fig. 401/TASK 34-36-31-991-001)

Subtask 34-36-31-020-050

A. Removal of the ILS Receiver (2RT1, 2RT2)

(1) Loosen the nuts (4).

(2) Lower the nuts (4).

(3) Pull the ILS receiver (1) on its rack (3) to disconnect the
electrical connectors (2).

(4) Remove the ILS receiver (1) from its rack.

(5) Put blanking caps on the disconnected electrical connectors (2).

R
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 ILS Receiver.
Figure 401/TASK 34-36-31-991-001

R
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 TASK 34-36-31-400-001

Installation of the ILS Receiver (2RT1,2RT2)

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

22-97-00-710-001 Operational Test of the LAND CAT III Capability

34-36-00-710-001 Operational Test of the ILS
34-36-00-740-002 BITE Test of the ILS
34-36-31-991-001 Fig. 401

3. __________
Job Set-up

Subtask 34-36-31-010-051

A. Get Access

(1) Make sure that the access platform is in position at the access door
811 in zone 122.

(2) Make sure that the access door 811 is open.

Subtask 34-36-31-865-051

B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and
tagged

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
FOR 2RT1
49VU NAV/ILS/1 1RT1 G12
FOR 2RT2
121VU COM NAV/ILS/2 1RT2 K09

R
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 4. Procedure
_________

(Ref. Fig. 401/TASK 34-36-31-991-001)

Subtask 34-36-31-420-050

A. Installation of the ILS Receiver (2RT1, 2RT2)

(1) Clean the component interface and/or the adjacent area.

(2) Do an inspection of the component interface and/or the adjacent area.

(3) Remove the blanking caps from the electrical connectors (2).

(4) Make sure that the electrical connectors (2) are clean and in the
correct condition.

(5) Install the ILS receiver (1) on its rack (3).

(6) Push the ILS Receiver (1) on its rack (3) to connect the electrical
connectors (2).

(7) Engage the nuts (4) on the lugs (5) and tighten.

Subtask 34-36-31-865-052

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
FOR 2RT1
1RT1
FOR 2RT2
1RT2

Subtask 34-36-31-740-050

C. BITE test of the ILS

(1) Do the BITE test of the ILS (Ref. TASK 34-36-00-740-002)

NOTE : If the airline operates the aircraft in CAT 3 conditions, do

____
the LAND CAT III capability test
(Ref. TASK 22-97-00-710-001).

(2) As an alternative procedure, without the CFDS, you can do the

operational test of the ILS (Ref. TASK 34-36-00-710-001).

R
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 5. Close-up
________

Subtask 34-36-31-410-050

A. Close Access

(1) Make sure that the work area is clean and clear of tool(s) and other
items.

(2) Close the access door 811.

(3) Remove the access platform(s).

R
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 **ON A/C ALL

R Post SB 34-1147 For A/C 001-004,

RECEIVER - MULTI MODE (MMR) - REMOVAL/INSTALLATION

__________________________________________________

TASK 34-36-31-000-002

Removal of the Multi Mode Receiver (40RT1, 40RT2)

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific blanking caps

No specific circuit breaker(s) safety clip(s)
No specific access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

R 31-32-00-860-010 Procedure to Get Access to the SYSTEM REPORT/TEST NAV

R Page

R **ON A/C 001-003, 005-099,

34-36-31-991-002 Fig. 401

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 **ON A/C ALL

3. __________
Job Set-up

R Subtask 34-36-31-810-050

R A. Trouble Shooting Data

R If available, you can print the Trouble Shooting Data (TSD) as follows:
R - get access to the SYSTEM/REPORT TEST NAV page (Ref. TASK 31-32-00-860-
R 010).
R - on this page, push the line key adjacent to the MMR1 (MMR2) indication.
R - on the MMR1 (MMR2) page, push the line key adjacent to the TROUBLE
R SHOOTING DATA indication to get the TROUBLE SHOOTING DATA page.
R - print the TROUBLE SHOOTING DATA (TSD) page(s).

Subtask 34-36-31-865-053

R B. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
FOR 40RT1
49VU NAV/MMR/1 42RT1 G12
R FOR 40RT2

R **ON A/C 005-099,

R 121VU COM NAV/MMR/2 42RT2 L07

R **ON A/C 001-004,

R 121VU COM NAV/MMR/2 42RT2 K09

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R **ON A/C ALL

Subtask 34-36-31-010-052

R C. Get Access

(1) Put the access platform in position at the access door 811 in zone
122.

(2) Open the access door 811.

4. Procedure
_________

R **ON A/C 001-003, 005-099,

(Ref. Fig. 401/TASK 34-36-31-991-002)

**ON A/C ALL

Subtask 34-36-31-020-051

A. Removal of the Multi Mode Receiver (40RT1, 40RT2)

(1) Loosen the nuts (4).

(2) Lower the nuts (4).

(3) Pull the Multi Mode Receiver (1) from its rack (3) to disconnect the
electrical connectors (2).

(4) Remove the Multi Mode Receiver (1) from its rack.

(5) Put blanking caps on the disconnected electrical connectors (2).

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 Multi Mode Receiver
Figure 401/TASK 34-36-31-991-002

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 TASK 34-36-31-400-002

Installation of the Multi Mode Receiver (40RT1, 40RT2)

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

22-97-00-710-001 Operational Test of the LAND CAT III Capability

34-36-00-710-003 Operational Test of the ILS
34-36-00-740-003 BITE Test of the MMR

R **ON A/C 001-003, 005-099,

34-36-31-991-002 Fig. 401

**ON A/C ALL

3. __________
Job Set-up

Subtask 34-36-31-010-053

A. Get Access

(1) Make sure that the access platform is in position at the access door
811 in zone 122.

(2) Make sure that the access door 811 is open.

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 Subtask 34-36-31-865-054

B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and
tagged

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
FOR 40RT1
49VU NAV/MMR/1 42RT1 G12
R FOR 40RT2

R **ON A/C 005-099,

R 121VU COM NAV/MMR/2 42RT2 L07

R **ON A/C 001-004,

R 121VU COM NAV/MMR/2 42RT2 K09

R **ON A/C ALL

4. Procedure
_________

R **ON A/C 001-003, 005-099,

(Ref. Fig. 401/TASK 34-36-31-991-002)

**ON A/C ALL

Subtask 34-36-31-420-051

A. Installation of the Multi Mode Receiver (40RT1, 40RT2)

(1) Clean the component interface and/or the adjacent area.

(2) Do an inspection of the component interface and/or the adjacent area.

(3) Remove the blanking caps from the electrical connectors (2).

(4) Make sure that the electrical connectors (2) are clean and in the
correct condition.

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 (5) Install the Multi Mode Receiver (1) on its rack (3).

(6) Push the Multi Mode Receiver (1) on its rack (3) to connect the
electrical connectors (2).

(7) Engage the nuts (4) on the lugs (5) and tighten.

Subtask 34-36-31-865-055

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
FOR 40RT1
42RT1
FOR 40RT2
42RT2

Subtask 34-36-31-740-051

C. BITE test of the Multi Mode Receiver

(1) Do the BITE test of the Multi Mode Receiver (Ref. TASK 34-36-00-740-
003)

NOTE : If the airline operates the aircraft in CAT 3 conditions, do

____
the LAND CAT III capability test
(Ref. TASK 22-97-00-710-001).

(2) As an alternative procedure, without the CFDS, you can do the

operational test of the ILS (Ref. TASK 34-36-00-710-003).

5. Close-up
________

Subtask 34-36-31-410-051

A. Close Access

(1) Make sure that the work area is clean and clear of tool(s) and other
items.

(2) Close the access door 811.

(3) Remove the access platform(s).

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 WEATHER RADAR SYSTEM - DESCRIPTION AND OPERATION
________________________________________________

1. _______
General
The aircraft is equipped with an X-band weather radar system with Predictive
Windshear capability. This system complies with the ARINC Characteristics
708A.
The weather radar system enables:
- detection and localization of the atmospheric disturbances in the area
defined by the antenna scanning: plus or minus 90 deg. of aircraft
centerline and up to 320NM in front of the aircraft,
- detection of turbulence areas caused by the presence of precipitations up
to a distance of 40NM,
- presentation of terrain mapping information by the combination of the
orientation of the radar beam and of the receiver gain,
- detection, if the Predictive Windshear System is operative, of a
microburst windshear event in the area defined by the antenna scanning:
plus or minus 60 deg.
- presentation, if the Predictive Windshear System is operative, of
windshear events within an area plus or minus 30 deg. of aircraft
centerline and up to 5NM in front of the aircraft.

NOTE : A microburst is a cool shaft of air, like a cylinder, between 1000

____
and 3000 ft. When it encounters the ground (airflow velocity from 40
to 110 kts) the downward moving airflow is translated to a horizontal
flow (from 80 to 220 kts), at the base of the air shaft. Two types of
microburst exist, wet and dry.

Five color displays are used to show precipitations, turbulence and ground
mapping to the crew.
The location of the windshear events, if the Predictive Windshear System is
operative, is indicated by an icon (symbol consisting of alternating red and
black arcs).

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 2. Component
__________________
Location
(Ref. Fig. 001, 002)
The components of the weather radar system are located in the aircraft as
follows:

-------------------------------------------------------------------------------
FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA
| | | | DOOR | REF.
-------------------------------------------------------------------------------
1SQ1 XCVR-WEATHER RADAR, 1 109VU 121 125AL 34-41-33
3SQ CTL UNIT-WEATHER RADAR 11VU 210 831 34-41-12
7SQ DRIVE-WR ANTENNA 110 110AL 34-41-11
9SQ MTG TRAY-WR XCVR 109VU 121 811 34-41-37
11SQ ANTENNA-WEATHER RADAR 110 110AL 34-41-11

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 Weather Radar - Component Location
Figure 001

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 Weather Radar - Control and Indicating
Figure 002

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 3. System
__________________
Description
R (Ref. Fig. 003, 004)
The weather radar system is composed of items closely associated with its
operation, such as peripherals supplying parameters, EFIS display units or
maintenance functions.

NOTE : The weather radar image is shown on the CAPT and F/O Navigation
____
Displays (ND).
The NDs are connected to the three Display Management Computers (DMC)
and to the CAPT and F/O EFIS control panels of the FCU.

NOTE : The three ADIRUs give the altitude and ground speed information to
____
the weather radar system. These data ensure the radar antenna
stabilization (plus or minus 45 deg.) and the corrections of the
doppler mode (turbulence).

NOTE : Only the antenna drive of the weather radar system is the same as
____
that of the normal weather radar system.

A. General
The weather radar system, which complies with ARINC Characteristics 708A,
consists of:
- a transceiver 1SQ1,
- a single control unit 3SQ,
- a single antenna drive 7SQ,
- an antenna 11SQ,
- a transceiver single mounting tray 9SQ with a wave guide.

(1) Weather Radar Transceiver

The receiver-transmitter is the heart of the WR/PWS, the additional
necessary wiring and interfaces enable the weather radar transceiver
to operate as a PWS (WR/PWS).
The receiver-transmitter ensures the following functions:
- generation of the very short intense pulses of microwave energy via
an X-band wave guide to the antenna, and the processing of their
echoes (radio frequency signals) to obtain the desired information,
- the receiver signal is formatted into 1600-bit ARINC 453 words and
sent to the DMCs,
- acquisition of data from Radio Altimeters (RA1 and RA2) and other
specific interfaces,
- windshear event detection and generation of the appropriate signal
- BITE function of the system.

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R Weather Radar Block Diagram - Data Acquisition
R Figure 003

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R Weather Radar Block Diagram - Control and Display
R Figure 004

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 (2) Weather Radar Control Unit
The control unit generates a 32-bit (label 270) serial control word
which describes the selected operating modes (ON/OFF, WX, WX + T,
TURB, MAP, GND CLTR SPRS, PWS).
The WR/PWS receives one ARINC 429 bus coming from the control unit.
Moreover, the predictive winshear system function can be de-activated
if the PWS does not operate correctly (PWS AUTO/OFF switch).

(3) WR Antenna Drive

The weather radar system has one dual antenna drive which is the
interface of the transceiver to control and monitor the azimuth and
elevation of the antenna.

(4) Weather Radar Antenna

The antenna is used for transmitting and receiving radar radio
frequency signals.

(5) Transceiver Mounting Tray with a Wave Guide

It allows to install the transceiver on the aircraft rack and
connects the transceiver to the wave guide.

R NOTE : The weather radar and windshear detection image is shown on

____
R the Captain and First Officer Navigation Displays (ND) and the
R windshear warning is shown on Captain and First Officer
R Primary Flight Displays (PFD) and on the upper ECAM DU. The
R NDs and PFDs are connected to the three Display Management
R Computers (DMC) and to the Captain and First Officer EFIS
R control sections of the FCU.

R NOTE : If the Enhanced GPWS is operative, the WR image is replaced by

____
R the terrain image, on the Captain and First Officer NDs,
R during a terrain alert or a crew action.
R More explanations are given in 34-48.

R NOTE : The ADIRUs give to the weather radar system:

____
R - the altitude and the true airspeed (TAS) information (Ref.
R 34-13-00),
R - the attitude, ground speed, magnetic heading, true heading,
R E/W velocity, N/S velocity, track angle and drift angle
R (Ref. 34-14-00).
R These data ensure the radar antenna stabilization and the
R corrections of the Doppler mode (turbulence).

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 B. Peripherals

(1) Digital serial data inputs

The transceiver receives digital serial data inputs from the
following components:

(a) Radio Altimeter

The Radio Altimeter provides altitude information over two ARINC
429 bus inputs to the WR/PWS (label 164).
This data is used for automatic activation of the windshear
function.
The second bus is for redundancy.

(b) Air Data Reference

Two ARINC 429 low-speed buses provide:
- true airspeed data (label 210) and computed airspeed (label
206) used for velocity calculations,
- altitude data (label 203) used for sensitivity time control
(STC) calculations,
- corrected altitude data (label 204) used only when label 203 is
not available.

(c) Inertial Reference

Two ARINC 429 high-speed buses provide:
- pitch (label 324) and roll (label 325) data for the
stabilization and control of the antenna,
- east/west velocity (label 367 or 374) and north/south velocity
(label 366 or 373) used for velocity calculations,
- ground speed (label 312) used for velocity calculations,
- track angle (label 317) and drift angle (label 321) used for
velocity calculations,
- true heading (label 314),
- Magnetic heading (label 320).

NOTE : The main air data and heading altitude data are provided
____
by the Air Data/Inertial Reference System (ADIRS).

(d) Centralized Fault Display Interface Unit (CFDIU)

The WR/PWS communicates with the CFDIU via 2 low-speed ARINC 429
buses.

(e) EFIS Control Section

Two ARINC 429 buses provide the CAPT and F/O range selection
(label 271).
The receiver/transmitter receives one bus from the CAPT EFIS
control section and another one from the F/O EFIS control
section.

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 (2) Discrete inputs
The transceiver receives the following discrete inputs:

(a) Ground/flight signal and landing gear extended signal.

These signals are provided by the Landing Gear Control and
Interface Unit (LGCIU).
- Ground/flight signal is used to determine the identifying
flight phase for BITE

(b) Attitude/heading signal provided by the ATT HDG selector switch

(13FP) to determine if the transceiver 1 receives data from the
ADIRU1 or 3 and if the transceiver 2 receives data from the
ADIRU2 or 3.

R (3) Outputs
R The transceiver provides the following outputs:

R (a) Displays
R The WR/PWS is connected to the DMCs by an ARINC 453 bus to
R transmit the weather radar data and windshear data on the data
R word of label 055.
R All the weather and windshear data received by the DMCs are
R processed to display weather radar image and windshear events by
R the Electronic Instrument System (EIS).

R 1
_ The Navigation Display (ND) provides the following
R indications:
R - weather radar image,
R - windshear events location for advisory, caution or warning
R alert,
R - windshear failures.

R 2
_ The Primary Flight Display (PFD) provides all visual alerts
R for caution or warning alert.

R NOTE : The Flight Warning Computers (FWC) and the FDIU receive
____
R WR/PWS data through the DMCs. These data are used by
R the FWCs to display PWS failure and windshear function
R OFF.
R The FDIU records the windshear alert and failure.

R (b) Centralized Fault Display System (CFDS)

R The WR/PWS is connected to the CFDS to transmit the following
R words:
R - label 354: LRU identification P/N and S/N (coded in ISO5),
R - label 356: fault message (coded in ISO5),
R - label 377: equipment identification.

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R (c) Audio Mixing Box
R An analog audio output allows to transmit the aural alert
R windshear (synthetic voice message) to an audio mixing box
R connected to loud speakers.

R (d) Enhanced Ground Proximity Warning System (Enhanced GPWS)

R The Enhanced GPWS receives WR/PWS alerts from WXR1 Hazard bus to
R determine the alert priorities.
R Predictive Windshear alerts override a terrain display and revert
R to the WR display with the corresponding windshear data.
R The alert priorities between the WR/PWS and the Enhanced GPWS
R have been defined as follows:
R 1- WR/PWS Warning,
R 2- WR/PWS Caution,
R 3- Terrain Warning,
R 4- Terrain Caution,
R 5- WR/PWS advisory (no audio),
R 6- Terrain background (no audio).

(4) Audio Inhibit Discrete Signals

These discretes are used to indicate whether the aural alert output
has to be active or not.
- predictive windshear aural alerts (audio inhibit discrete input)
are inhibited by the Reactive Windshear System and stall warning.
- predictive windshear audio inhibit discrete output is used to
inhibit other aural alerts generated by systems such as: Traffic
Alert and Collision Avoidance System (TCAS) or Ground Proximity
Warning System (GPWS) or other FWC warnings.
This inhibition occurs each time there is a PWS aural alert.

(5) Pin Programming

- audio level program pins set the audio output level of the
synthetic voice (windshear aural alert).
- SDI (Source Destination Identification Encoder) program pins encode
the location of the WR/PWS unit on the aircraft.
- qualifier polarity program pins: for both qualifiers, this pin
program indicates the validity of the signal.
- CFDIU interface program pins: when the second WR/PWS is installed
on the aircraft, this program pin is activated. The WR/PWS can
communicate with the CFDIU.
- caution alert audio program: two program pins are provided to
select the type of windshear caution aural alert.
The MONITOR RADAR DISPLAY synthetic voice is generated instead of
the chime.

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 C. General Technical Characteristics
The WR/PWS system is mainly used to detect and localize various types of
atmospheric disturbances and windshear events in the area scanned by the
antenna. The system shows the disturbance intensity through the use of
colors which vary with the atmospheric precipitation rate.
The disturbances are shown to the crew members on the NDs with different
colors:
- black, green, yellow, red to quantify the precipitation rates,
- magenta to represent the turbulence areas up to 40 NM.
The system can show the location of the windshear events via the NDs:
alternating black and red arcs depict the windshear event.
As the minimum display range is 10 NM, two yellow radials appear at the
edges and start beyond the windshear (W/S) event.

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 4. Power
____________
Supply
Energization of the system is through a 115VAC/400 Hz bus:
- 1XP via the sub-busbar 101 XP-C for transceiver 1.
Energization of the weather radar control unit and of the WR antenna drive
is through the transceiver.
Consumption of the transceiver is 145 W maximum.
The system is supplied through this (these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
121VU COM NAV/RADAR/1 5SQ1 K13

5. Interface
_________

A. Digital Interface Special for WR/PWS

The weather radar data are transmitted via ARINC 429 and 453 buses in
compliance with ARINC 708A.
The table below contains all the output parameters in the digital form.

-------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
| 270 | CONTROL | | | | 32 |100 | DIS| | |
| | WORD 1 | | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 271 | CONTROL | | | | 32 |100 | DIS| | |
| | WORD 2 | | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 055 | WXR DATA | | | |1600|7.82| DIS| | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| 356 | Mainte- | | | | |100 |ISO5| | |
| | nance | | | | | | | | |
| | message | | | | | | | | |
| | word | | | | | | | | |
-------------------------------------------------------------------------------

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 (1) Control Words (Labels 270 and 271)
The control words are transmitted on the control buses which connect
the weather radar control unit to the transceiver.
The control word 1 (label 270) provides the following data:
- gain,
- tilt angle,
- selected mode,
- stabilization (on/off),
- scan angle (normal/reduced),
- anticlutter (on/off).
The control word 2 (label 271) provides the following data:
- range,
- anticlutter (on/off),
- WR selected on the EFIS control section (master/slave).

(2) Data Word (Label 055)

The signal transmitted on the data bus line which connects the WR/PWS
to the Display Management Computers (DMC) complies with data word
format (label 055) as defined by the ARINC Specification 708A
(Appendix 15.2).
The data bus line transmits 190 data words per second; each word is
made up of 1600 bits sent on 1 Megabit/s frequency (ARINC
Specification 453) as per MANCHESTER II BI PHASE 2 format.
R (Ref. Fig. 005)
Data word message includes mainly the radar return intensity and
windshear data.

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 Weather Radar - Manchester II Biphase Format
R Figure 005

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 -----------------------------------------------------------------------------
| BITS | FUNCTION |
|----------|----------------------------------------------------------------|
| 1-8 | Label 00101101 : 055 |
| 9-10 | Control Accept |
| 11 | Spare |
| 12 | Windshear Caution |
| 13 | Windshear Warning |
| 14-15 | Turbulence and Weather Alert |
| 16 | Anticlutter (not used) |
| 17 | Sector Scan |
| 18 | Stabilization Limits |
| 19 | Cooling Transceiver |
| 20 | Display Fault (not used) |
| 21 | Calibration or Air Data Input |
| 22 | Attitude Input |
| 23 | Control or Heading Input |
| 24 | Antenna |
| 25 | R/T or Radio Altimeter |
| 26 | Stabilization |
| 27-29 | Mode |
| 30-36 | Tilt Angle |
| 37-42 | Gain |
| 43-48 | Range |
| 49 | Windshear External Input Fault |
| 50-51 | Data Accept |
| 52-63 | Scan Angle |
| 64 | Windshear Failure |
| 65-1600 | Range Bin Data |
-----------------------------------------------------------------------------

The WR/PWS uses the WTime Shared usageW technology defined by the
ARINC specification 708A for transmission of information on data bus
lines. This is achieved by two identical data bus lines, each
associated with a different control bus line.

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 6. _____________________
Component Description

A. Transceiver
R (Ref. Fig. 006, 007)
The weather radar transceiver with PWS is a completely solid-state
airborne unit.
It contains:

(1) A power amplifier

A single 777.77 MHz multiplier drive signal is developed by the power
amplifier. The power amplification of the transmit section is
accomplished by splitting the power amplifier drive before
recombining the signals into a single multiplier drive signal.

(2) A power multiplier

The power multiplier produces the 9333.24 MHz transmitter output
signal from the single multiplier drive signal (from the power
amplifier).
The multiplier drive signal is multiplied by 3 to produce a 2333.31
MHz signal. The 2333.31 MHz signal is their quadrupled to produce the
9333.24 MHz transmitter output signal.

(3) A duplexer/monitor
The transmitter output is coupled through a duplexer/monitor to the
waveguide antenna feed through a 4-port circulator. Incorporated in
the duplexer operation are monitor circuits to monitor the output
power level and develop a frequency loop error signal for the
correction of frequency chirp.
The monitor circuit also accepts a test signal which causes a portion
of the reference signal to be injected into the receiver for test
calibration. The 4-port circulator also couples the RF return from
the waveguide antenna feed through the preamplifier to the receiver
portion of the transceiver.

(4) A preamplifier
The preamplifier assembly perform the waveguide limiter functions
(protects the mixer diodes from all high power pulses), contains a
noise diode circuit and contains a 2-stage RF amplifier which
provides +18dB of RF gain.

(5) A mixer
The mixer circuit processes the detected RF return signal by mixing
it with the First local oscillator signal and amplifying the
resultant Intermediate Frequency (IF) signal in the First IF
amplifier.
The first IF amplifier provides 25dB amplification before the First
IF signal is applied to the second IF amplifier.

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R Weather Radar - Architecture
R Figure 006

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 Weather Radar Transceiver - Component Description
R Figure 007

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 (6) A second IF amplifier
The second IF amplifier completes the receiver amplification of the
RF return signal. The output from the first IF is converted to the
13.8888 MHz second IF signal by mixing it with the 152.77 MHz second
local oscillator signal. The second IF signal is double-buffered and
applied to a synchronous detector. The third local oscillator signal
is phase-split to obtain one signal in phase with the transmitter
frequency and one signal phase shifted by 90 deg.

(7) A sampler
The sampler commands and controls the receive and transmit functions
within the receiver-transmitter. A digital signal processor is used
to control transmitter timing and receiver normalizer.

(8) A digital signal processsor

The digital signal processor circuit card performs the weather
processing, clutter identification, clutter filtering, velocity
extraction and editing, hazard computation and hazard recognition
algorithms. Command and control information is passed from the
digital signal processor to the sampler through a dual port RAM.

(9) A central processing unit

Control of internal functions, antenna servo controls, monitoring of
system operation and formatting the processed data is accomplished by
the central processing unit. It uses a microprocessor and a stored
program to execute the following major routines that control the
transceiver and system operations:
- attitude routine, providing pitch and roll parameters for the
stabilization routine
- stabilization routine, providing elevation position to the
elevation maintenance routine
- scan maintenance routine, providing antenna scan drive
- elevation maintenance routine, providing antenna elevation drive
control bus manager routine, determining correct control
configuration
- problem control monitor routine, programming the internal data
collection parameters of the transceiver
- data bus formatter routine, processing and assembling the control
message of the serial data word sent to the EFIS.

(10) An input/output unit

All interface functions between the microprocessor of the central
processing unit and the rest of the transceiver and units in the
system are provided by the input/output unit. Control word buses,
digital and analog attitude buses, radio altitude inputs and discrete
buses are all connected to the multiplexer and shift register of the
input/output unit. In addition, the input/output unit contains speech

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 circuits for windshear hazard annunciation, the synchro-to-digital
conversion circuits, discrete warning annunciation outputs, aural
warning outputs and remote turn-on circuits.

(11) A BITE/monitor
The BITE/monitor provides the BITE power supply voltages to BITE
functions and circuits, a power monitor for the detected transmitter
output and an interconnect for various signals used throughout the
transceiver.

B. Weather Radar Antenna

R (Ref. Fig. 008)
The weather radar antenna is controlled in azimuth and elevation by the
transceiver CPU. The binary control data are decoded and activate the
antenna scan and elevation steeper motors through corresponding power
circuits. The indication of these positions is sent to the CPU for
comparison. The RF signal (transmitted or received) is conveyed by a wave
guide between the antenna and the transceiver.
Energization of the antenna is 115VAC/400 Hz through the transceiver.

C. Weather Radar Control Unit

The gain and tilt potentiometric data are digitized by an 8-bit
analog-to-digital converter.
Moreover the different positions of the mode selector switch and the
potentiometric data are formatted according to the ARINC 429 control
word.

D. Weather Radar Wave Guide

A wave guide assembly ensures the RF connection between the WR antenna
drive and the WR transceiver mounting tray.
The wave guide assembly is made up of rigid and flexible parts which have
a standard rectangular section (1 in. x 0.5 in.).

R
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 Weather Radar - Antenna
R Figure 008

R
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 7. Operation
_________

A. Operation

(1) Weather Radar modes

The weather radar system uses the principle of radio echoing. It
works at a normal frequency of 9333 MHz. The peak power emitted is
120 W approx. The weather radar transceiver generates microwave
energy in the form of electromagnetic pulses via an X-band wave guide
to the antenna. When these pulses intercept an appropriate target,
part of the energy is reflected back to the weather radar antenna
then to the transceiver. For each case, the system uses a different
mode of operation which allows to vary the scanning of the antenna,
the timing of the pulses and the processing of the WR/PWS returns.
The electronics circuits of the transceiver measure the elapsed time
between the transmission of the wave and the reception of the echo to
determine the target distance (it takes around 12.36 microseconds for
the electromagnetic wave to travel out and back for each nautical
mile of target range).
The angular position of the target is detected by the angular
position of the antenna in its scanning in azimuth. As the quantity
of energy reflected to the antenna is proportional to the target
density, the different levels of atmospheric disturbances (see table
1 below) are shown on the displays by different colors.
The detection of the turbulence areas are based on the Doppler
phenomenon.

--------------------------------------------------------------------------
| LEVEL DETECTED | PRECIPITATION RATE | COLOR OF ECHOES |
|------------------------|-----------------------|-----------------------|
| Z1 < 20 dBz | less than 1 mm/h | black |
| 20 less than or equal | from 1 to 4 mm/h | green |
| to Z2 < 30 dBz | | |
| 30 less than or equal | from 4 to 12 mm/h | yellow |
| to Z3 < 40 dBz | | |
| 40 less than or equal | 12 mm/h and above | red |
| to Z4/Z5 < 50 dBz | | |
|------------------------|-----------------------|-----------------------|
| Turbulence | 5 m/s | magenta |
-------------------------------------------------------------------------|
Table 1: Color Correspondence Table

(2) Windshear mode

The WR/PWS, by a doppler mode, determines the wind field ahead of the
aircraft.
By a mathematical treatment, the system determines the hazard factor
(so-called WF factorW) related to the danger of a windshear event.
An hazard factor exceeding a value of 0.13 and within 5NM ahead of
the aircraft is considered as the presence of a dangerous event and a
corresponding windshear alert is generated. The display of windshear
hazard consits of an icon of red and black bands superimposed on the
radar returns. As these events are dangerous during takeoff and

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 landing maneuvers, the PWS mode is automatically activated below 2300
ft radio altimeter and at least one of the qualifier-A and one
qualifier-B inputs have to be valid. Windshear detection operates
automatically with the above-mentioned reasons, even if the radar
function selector switch is set to OFF, but windshear switch has to
be set to AUTO.
The windshear mode is transparent to the pilot until a windshear
event is detected.
When a windshear event is detected, the system generates the
appropriate annunciations (visual and aural) to the flight crew.
The WR/PWS generates a graphic symbol (icon) to the displays
indicating where the windshear was detected.
The windshear function detection can operate either with weather
radar modes activated or independently without these modes.
If the radar is already operating in a weather detection mode when a
windshear is detected, no pilot intervention will be required.
If the radar is OFF when this event is detected, the radar operation
will automatically change to WX+T mode (if selected range is less
than 60NM) or WX mode (if selected range is more than 60NM), to
display weather and windshear icons.
The selected range does not change.
In windshear mode, the TILT and GAIN are controlled automatically on
the WR/PWS for the scanning.
However, the TILT displayed on the NDs is in accordance with this
selected on the radar control panel.
When the weather radar transceiver fails, the amber message PRED W/S
is displayed on the NDs associated with the amber messages:
- NAV: PRED W/S DET FAULT on the upper ECAM DU,
- PRED W/S DET in the INOP SYS item of the STATUS page on the SD.
The system 2 (if installed), has to be selected on the weather radar
control unit to display windshear information.

NOTE : The system has to reject echoes due to ground clutter or

____
moving surface.

NOTE : In some cases, the pilot has to deselect windshear mode (PWS/
____
OFF/AUTO switch to OFF) for the following reasons:
- when the aircraft is at a gate area or in maintenance
hangars to avoid radiating danger for persons,
- when nuisance aural alerts are generated.

R NOTE : There is no danger of radiation to persons on the ground if

____
R the ATC switch on the ATC/TCAS control unit is set to OFF or
R STBY after landing, even if the WINDSHEAR switch on the
R weather radar control unit is still at AUTO.

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 NOTE : In order to ensure optimum performance for the predictive
____
windshear function, the radome must be at least equal to class
B category 1.

(3) Logic of scanning mode

R (Ref. Fig. 009)
The antenna scan pattern varies depending on the mode of operation.

(a) Weather radar scan pattern

In weather radar mode, the antenna scans a 180 deg. in azimuth
and has tilt (pitch) coverage of plus or minus 15 deg.
Stabilization limits are plus or minus 25 deg. in the pitch axis
and plus or minus 40 deg. in the roll axis. The antenna scans the
zone 15 times per minute. Beam opening is 3.6 deg. in elevation
and 3.5 deg. in azimuth.
An antenna scanning is performed in 4 seconds, this causes the
transmission of 720 data words to the data bus lines.
When the two ranges selected on both EFIS control panels are
identical, the radar images displayed on the NDs are refreshed
every 4 seconds.
On the contrary, when two different ranges are selected on the
EFIS control panels, the images are refreshed every 8 seconds.

(b) Weather and windshear scan pattern

When the system is placed into alternate weather/windshear mode,
the weather processing is operating during left-to-right scans
and windshear processing is operating during right-to-left scans.
In this case, the antenna scans only plus or minus 60 deg.
But windshear the targets are displayed only in the area plus or
minus 30 deg. from the aircraft centerline.
An antenna scanning is performed in 3 seconds three other seconds
are used to refresh data inside the CPU.
Then, when the two ranges selected on both EFIS control panels
are identical, the radar images displayed on the NDs are
refreshed every 6 seconds.
On the contrary, when two different ranges are selected on the
EFIS control panels, the images are refreshed every 12 seconds.

(c) Windshear scan pattern

The windshear processing is operating during right-to-left scans
and left-to-right scans.
The antenna scans only plus or minus 60 deg.
The detected windshear targets are displayed only in the area
plus or minus 30 deg. From the aircraft centerline.
When the two ranges selected on both EFIs control panels are
identical, the radar images displayed on the NDs are refreshed
every 6 seconds.

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 WXR/PWS - Logic of Scanning Mode
R Figure 009

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 On the contrary, when two different ranges are selected on the
EFIS control panels the images are refreshed every 12 seconds.

NOTE : For roll angle exceeding 28 deg., the windshear detection

____
is not active.

B. Timing of Transmitted Pulses in WX/MAP Mode, in Doppler Mode (Turbulence)

and in W/S Mode
R (Ref. Fig. 010)
- in WX and MAP modes, at short ranges (less than or equal to 60NM) the
period of pulse (four) transmission-reception is 5.6 ms. This causes an
interrogation frequency (PRF) of 1280 Hz. For medium ranges (greater
than 60NM and less than or equal to 165 NM), the period of pulse (two)
transmission-reception is 8.4 ms at a PRF of 360 Hz. For ranges greater
than 165 NM, the period of pulse (two) transmission-reception is 8.4 ms
at a PRF of 240 Hz.
- in the turbulence mode (High PRF), the PRF is increased from 240 to
1280 pulses per second.
The threshold of turbulent targets is precipitation velocities of 5
m/s. This threshold translates into a Doppler frequency shift of
312,5Hz. It explains the increased PRF.
With this high PRF rate, the maximum range for turbulence detection is
approximately 56 NM.
- in the windshear mode (Very High PRF), 64 pulses are transmitted during
a period of 23 ms. The PRF is 3000 Hz.

C. Controls and Indicating

The various system controls are grouped on the weather radar control unit
and on the EFIS control sections of the FCU.
Radar image control on the NDs is achieved through the scale selector
switches located on the Captain and First Officer EFIS control sections
of the FCU.

(1) Weather radar control unit

R (Ref. Fig. 011)
The face of the weather radar control unit includes the following
controls:

(a) A mode selector switch, item 4, which enables the selection of

the WX, WX+T, TURB or MAP function.

(b) A TILT selector switch, item 2, which enables the control of the
antenna elevation.
Antenna position is read in degrees, opposite the notch on the
switch:
- either from 0 to 15 deg. upwards (UP),
- or from 0 to 15 deg. downwards (DN).

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 Weather Radar - Pulse Transmission Timing Diagram
R Figure 010

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 Weather Radar - Control Unit
R Figure 011

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 (c) A GAIN potentiometer, item 1, which enables the manual adjustment
of the transceiver gain.

(d) A switch, item 5, with two stable positions ON/OFF, which enables
the activation of the transceiver.

(e) A GND CLTR SPRS switch, item 3, which enables the selection of
the ground clutter suppression (ON/OFF).
The face of the control unit is provided with integral lighting.
The INTEG LT potentiometer enables lighting adjustment. The
potentiometer is located on the panel 111VU, at the left aft
section of the center pedestal 100VU.

(2) EFIS control section (on the FCU)

R (Ref. Fig. 012)
In this part, the controls related to the selection of WX and W/S
functions are described.

(a) A mode selector switch, item 1, made up of a rotary switch

enables the selection of the ROSE or ARC function for display of
a weather radar image on the CAPT and F/O NDs.
Windshear information is available in ARC and ROSE mode.

(b) A scale selector switch, item 2, common to EFIS, FMGS and radar
systems, enables the selection of 10, 20, 40, 80, 160 or 320
operation range in nautical miles (NM) for display of the weather
radar image on the CAPT and F/O NDs.
Windshear information is presented in the 10 NM minimum range and
on other selected ranges. Morever, yellow radial lines are
displayed to indicate the W/S included location.

NOTE : In the ARC or ROSE mode, if the CAPT or the F/O switches
____
to the OFF mode FM, the offside weather image will also be
transferred on the ND. Only one scale selector switch can
then control the weather radar image display.

(3) Lighting/LOUDSPEAKER control panel

R (Ref. Fig. 012)
CAPT and F/O lighting/LOUDSPEAKER control panels 301VU and 500VU
which are connected to CAPT and F/O NDs, include ND concentric
potentiometers for adjusting the brightness of the image displayed on
the NDs. The outer knob of each potentiometer controls the brightness
of the radar image only, item 3.

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 EFIS Control Sections and EFIS Switching Panels
R Figure 012

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 D. Utilization of Controls and Indicating
Special precautions to be taken.
Before selecting the WX, WX+T, TURB or MAP mode on the control unit, make
sure that:
- no one is within a distance less than 1.50 m from the antenna in
movement within an arc of plus or minus 135 deg. on either side of the
aircraft centerline,
- the aircraft is not directed towards any large metallic obstacle, such
as a hangar, which is within 5 m in an arc of plus or minus 90 deg. on
either side of the aircraft centerline.

(1) Operation of the transceiver

The transceiver is always supplied in order to achieve maintenance
function. On the weather radar control unit, after selection of a
mode (WX, WX+T, TURB, MAP) the ON/OFF switch has to be set to ON
position to set the transceiver in operation.

NOTE : No pre-heating time is necessary for the operation of the

____
weather radar transceiver.

NOTE : When the aircraft is parked, the TEST mode on the MCDU must be
____
preferably selected as a safety precaution.

On either EFIS control section of the FCU, the mode selector switch
must be set to the ARC or ROSE position to obtain the image display
on the corresponding ND.

NOTE : The radar transceiver is de-activated when the ON/OFF switch

____
on the weather radar control unit is set to the OFF position
or by placing the mode selector switches on both EFIS control
sections in any position other than ROSE or ARC.

(2) Utilization of the weather radar control unit

R (Ref. Fig. 011)

(a) Mode selection (item 4)

The modes (WX, WX+T, TURB, MAP) are selected by placing the notch
provided in the mode selector switch in front of the engraving of
the function selected.
- WX
This mode corresponds to the normal operation in weather
detection. It provides disturbances up to 320 NM.
The radar images are displayed on the NDs in four colors
(black, green, yellow, red); their intensity corresponds to the
strength of the return signal.
- WX+T

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 This mode corresponds to the operation in weather and
turbulence detections.
All turbulent/non turbulent areas beyond 50 NM are displayed in
the conventional black, green, yellow and red as in the weather
(WX) mode.
- TURB
This mode corresponds to the operation in turbulence detection.
Turbulence detection is limited to the first 50 NM regardless
of the weather radar range selected and displayed.
Turbulence areas are displayed on the NDs in magenta.

NOTE : There is no detection of turbulence in clear sky.

____

- MAP
This mode is only used for display of the ground map. A
combination of transceiver gain, antenna position (TILT) and
range selection enables the display of a larger area and the
identification of major changes in the ground map (e.g. a sea
cost, a lake, a mountain, an island...).
The color display follows the color mentioned in correspondence
table (see table 1 - para. 7. A.)
If the image is too bright, due to too great reflection
intensity, it can be dimmed by the GAIN potentiometer, item 1.

(b) System selection and start up: ON/OFF switch (item 5)

This switch enables:
- the selection and activation of the transceiver,
- the suppression of the radar image on the NDs when these NDs
are in the ARC or ROSE mode.

(c) Gain control (item 1)

The GAIN potentiometer enables the manual control of transceiver
sensitivity in the WX, WX+T, TURB and MAP modes.
When the potentiometer is rotated fully clockwise, the CAL
position provides preset calibrated transceiver gain level
(minimum receiver sensitivity). Clockwise rotation of the GAIN
potentiometer increases the gain towards the MAX position.
In the CAL position, no indication appears in the R lower corner
of the NDs. For the other positions, the MAN indication is
displayed in white.

(d) TILT control (item 2)

The TILT selector switch enables the variation of the antenna
elevation angle in 1/4 deg. steps on a non-linear scale graduated
in degrees, within a range of +15 deg. (UP) to -15 deg. (DOWN) in
relation to a horizontal plane defined by the stabilization
system.

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 This antenna elevation angle is displayed in cyan in the R lower
corner of the ND and progresses in steps of 0.25 deg.
If the antenna position is different from the TILT selector
switch position, a red ANT failure warning message replaces the
TILT indication in the R lower corner of the ND.

(e) Ground clutter suppression (item 3)

Activation of the GND CLTR SPRS switch, in weathers modes (WX,
WX+T, TURB), reduces the intensity of the ground clutter.
These ground returns are replaced by black areas on the radar
image when the GND CLTR SPRS switch is placed in ON position.

(3) Utilization of the EFIS control sections and lighting/loud speacker

control panels
R (Ref. Fig. 012)

(a) Mode selector switch (item 1)

This mode selector switch enables the image display on the
corresponding ND whenever the ARC or ROSE mode is selected and
the transceiver is supplied. In that case, the radar image is
displayed in the background of the navigation image.
If neither ROSE or ARC mode is selected, the message W/S CHANGE
MODE is shown on both NDs, if there is a windshear alert. The
pilot is advised to select ARC or ROSE mode to see the W/S icon.
The color depends on the W/S alert level.

(b) Scale selector switch (item 2)

This selector switch enables the display of the range selected
for an optimum use of the radar image on the corresponding ND.
For each of the following ranges: 10, 20, 40, 80, 160 and 320,
four concentric range arcs are displayed respectively spaced 2.5,
5, 10, 20, 40 and 80 NM, when the mode selector switch is in the
ARC position. Only 2 range arcs are displayed in the ROSE mode.
Windshear information is presented in the 10 NM range only. If a
windshear alert is generated but the selected range is greater
than 10 NM, the message W/S: SET RNG 10 NM is shown on the NDs.
In this case, the pilot is advised to select the 10 NM range. The
color depends on the W/S alert level.

(c) Radar image brightness control (item 3)

The ND potentiometer enables the adjustment of brightness and
contrast of radar echoes in relation to the navigation image,
which is superimposed.
However, the adjustment range does not allow total extinction of
the image. The OFF position of the potentiometer corresponds to
the minimum brightness. The BRT position corresponds to the
maximum brightness.

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 NOTE : A photoelectric cell associated with each ND also adjusts
____
image brightness as a function of ambient light
variations.

(4) Weather radar data displayed on the NDs

R (Ref. Fig. 013)
On the figure, the details A) and B) respectively correspond to the
ARC and ROSE ND modes for which the display of the radar image is
possible.
Messages inform the crew of the tilt angle and gain selected on the
weather radar control unit. Other messages indicate the failures
which affect the operation of the radar system. All these messages
are displayed in the R lower corner of each ND whenever a radar image
is selected.

NOTE : Tilt information and gain selection are displayed on the ND

____
when no failure warning message is generated, or when the TEST
mode is not selected.

The various failures which can affect the radar image are listed in
decreasing order of importance. If several failures occur, only the
most important one is displayed (Ref. details C) and D) on the
figure).

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 Weather Radar - Data Displayed on the NDs
R Figure 013

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 Two types of failures can affect the radar system:

(a) Failures which result in the loss of the radar image

The corresponding messages are displayed in red
- WR : indicates a failure of the weather radar transceiver
R/T
- WR : indicates a failure of the weather radar antenna
ANT
- WR : indicates a failure of the weather radar control unit
CTL
- WR : indicates an error of comparison between the range
RNG from the EFIS control section and the copy data received
on the symbol generator via the radar data bus.

R NOTE : In case of insufficient avionics ventilation, the weather

____
R radar image is lost in order to prevent NDs overheat.

(b) Failures which do not affect the radar image

The corresponding messages are displayed in amber
- WR : indicates the loss of the transceiver calibration
WEAK
- WR : indicates an attitude failure from the ADIRU
ATT
- WR : indicates the loss of the radar antenna stabilization
STAB
- WR : indicates the selection of the radar TEST mode.
TEST

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 (5) Windshear data displayed (Ref. table 2 below)
R (Ref. Fig. 014)

(a) Windshear indications

The location of a windshear phenomenon is indicated to the crew
by means of an icon superimposed on the radar image.
This icon consists of alternating red and black arcs. For 10 NM
range selection and above, yellow radial lines appear at the
edges and start beyond the windshear event. These lines,
superimposed on the radar image, continue to the edge of the
display area to provide directional information for the event.
The windshear data are always displayed even if the ON/OFF
selector switch on the radar control unit is set to OFF.
The PWS/OFF/AUTO switch on the radar control unit has to be set
to AUTO.

(b) Windshear alert

R (Ref. Fig. 015, 016)

1
_ Alert levels
There are three alert levels defined in function of event
seriousness and distance from the aircraft. The weather radar
provides the crew with visual and aural warnings which vary in
function of the level detected.

a
_ Windshear warning alert (level 3)
This alert corresponds to the most dangerous phenomenons.
It is generated for windshear events detected within +/-
0.25 NM from the longitudinal axis of the aircraft and
within +/- 30 deg. scan of the aircraft heading.
On the ground, the maximum range is 3 NM. In flight, the
maximum range is reduced to 1.5 NM.
During takeoff, level 3 covers ranges from 0 to 1.5 NM,
from 50 to 1200 ft Above Ground Level (AGL). During
landing, this coverage is from 1.5 to 0.5 NM, from 370 to
50 ft.
Range reduction is a linear function of altitude: at 370
ft, range is equal to 1.5 NM and reaches 0.5 NM at 50 ft.
During takeoff, this warning is inhibited from the time the
aircraft attains 100 kts and until it reaches 50 ft AGL.
Level 3 warning is inhibited below 50 ft (in approach
phase) and above 1200 ft.
The windshear warning alert is announced by:
- an aural warning message: GO AROUND WINDSHEAR AHEAD in
approach or WINDSHEAR AHEAD, WINDSHEAR AHEAD at takeoff,
generated by the radar synthesized voice,
- a visual warning: red W/S AHEAD message on the PFD.

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 Windshear - Data Displayed on the NDs
R Figure 014

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 Windshear - Windshear Alert Ranges and Altitudes
R Figure 015

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 Windshear - Windshear Alert Levels and Locations
R Figure 016

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 Display priority on PFD is given to level 3.
The computer has to determine whether the aircraft is
taking-off or landing to generate the aural warning message
WGO AROUND, WINDSHEAR AHEADW or WWINDSHEAR AHEAD, WINDSHEAR
AHEADW.
Transition between the GO AROUND, WINDSHEAR AHEAD and
WINDSHEAR AHEAD, WINDSHEAR AHEAD aural warning messages is
controlled by the GEAR UP discrete input.

b
_ Windshear caution alert (level 2)
This level covers the events detected in a region from 0 to
3 NM, within +/- 30 deg. of the aircraft heading but
outside the windshear warning alert region (level 3).
This caution alert is inhibited:
- during takeoff, from the time the aircraft attains 100
kts and until it reaches 50 ft AGL,
- during landing, below 50 ft AGL.
There should be no windshear caution alert (level 2) above
1200 ft.
The windshear caution alert is announced by:
- an aural warning: MONITOR RADAR DISPLAY,
- a visual warning: amber W/S AHEAD message on the PFD.

c
_ Windshear advisory alert (level 1)
This level covers the events located within 5 NM from the
aircraft, within +/- 30 deg. of the aircraft heading but
outside the windshear warning and caution alert regions
(levels 2 and 3).
There should be no windshear advisory alert (level 1) above
1500 ft.
No aural or visual warnings are provided for this advisory
alert: only the windshear icon is superimposed on the radar
image.
The weather radar transmits the windshear alerts following
their detection order. A maximum of 8 events can be
transmitted. Therefore, alerts of different levels can be
generated simultaneously.

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 -------------------------------------------------------------------------------
| ALERTS | PFD | ND | AURAL WARNING |
|-------------|-----------------|-------------------|-------------------------|
| Advisory | | windshear icon | |
|-------------|-----------------|-------------------|-------------------------|
| Caution | W/S AHEAD | windshear icon | MONITOR |
| | (AMBER) | | RADAR DISPLAY |
|-------------|-----------------|-------------------|-------------------------|
| Warning | W/S AHEAD | windshear icon | during takeoff: |
| | (RED) | | WINDSHEAR AHEAD |
| | | | WINDSHEAR AHEAD |
| | | | during landing: |
| | | | GO AROUND |
| | | | WINDSHEAR AHEAD |
-------------------------------------------------------------------------------
Table 2: Windshear Data Displayed

(6) Windshear warning displayed (Ref. table 3 below)

R (Ref. Fig. 017)

(a) Windshear flags on NDs

When a windshear fault occurs, an amber PRED W/S message comes
into view. The radar image remains available if this fault does
not affect the radar modes or detection function.
A detected fault is displayed when:
- the aircraft is on the ground or the flap and slat control
lever is in a position different from 0.
- the windshear PWS/OFF/AUTO switch on the radar control unit is
set to AUTO (the fault message is not displayed whent the
switch is set to OFF).

(b) Warning display on Upper ECAM Display Unit

A detected windshear fault is indicated by the following amber
messages:
- NAV: PRED. W/S DET FAULT on EWD.
- PRED. W/S DET on SD INOP SYSTEM area.
This message is associated to the indications presented on the
NDs.
When the PWS/OFF/AUTO switch is set to OFF on the weather radar
control unit, a green or amber PRED W/S OFF memo message is
presented to the crew.
The color of this message depends on the flight phases.

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R Messages Displayed on ND and upper ECAM DU
Figure 017

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 -------------------------------------------------------------------------------
| | UPPER DU ECAM | ND | AURAL WARNING |
|-------------|-----------------|-------------------|-------------------------|
| PWS | NAV: | PRED W/S | Single chime |
| SYSTEM | PRED. W/S DET | (AMBER) | |
| FAULT | FAULT | | |
| | (AMBER) | | |
|-------------|-----------------|-------------------|-------------------------|
| WINDSHEAR | PRED. W/S OFF | | |
| AUTO/OFF | (GREEN or AMBER)| | |
| SWITCH ON | | | |
| CONTROL | | | |
| UNIT IN | | | |
| OFF | | | |
| POSITION | | | |
-------------------------------------------------------------------------------
Table 3: PWS INOPERATIVE - Warning Data Displayed

(7) Record in the Flight Data Interface Unit (FDIU)

The FDIU receives, for recording, the following PWS data through the
DMCs:
- W/S caution alert (level 2),
- W/S warning alert (level 3),
- W/S auto/off,
- W/S internal fault,
- W/S external fault,
- DMCs/FWCs PWS pin program status.
This data, except the PWS pin program status, is only transmitted
from the DMCs if the DMCs/FWCs PWS pin program is valid (grounded).

E. Reconfiguration switching
(Ref. Fig. 002)
In normal configuration, the weather radar transceiver receives the
altitude information from its corresponding ADIRU.
In case of ADIRU1 failure, the pilot can select the altitude information
from the ADIRU3.
This selection is through the AIR DATA selector switch installed on panel
8VU, on the center pedestal.

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 8. Test
____

A. BITE Description

(1) General
The BITE facilitates maintenance on in-service aircraft. It detects
and identifies a failure related to the system.
The BITE of the WR/PWS is situated in the radar transceiver and
through two ARINC 429 low-speed buses (an input bus from the CFDIU
and an output bus to the CFDIU).
The BITE:
- transmits permanently weather radar system status and its
identification message to the CFDIU,
- memorizes the failures which occurred during the last 63 flight
legs,
- monitors data inputs from the various peripherals (EFIS control
section, ADIRUs, RAs),
- transmits to the CFDIU the result of the tests performed and
self-tests,
- can communicate with the CFDIU through the MCDU menus.
- acquires the general maintenance parameters (UTC, date, A/C
ident...) and command codes from the CFDIU.
The PWS interface with the CFDIU is composed of:
- an ARINC 429 low speed bus from the CFDIU.
The data sent by the CFDIU are:

---------------------------------------------------------
| LABEL | PARAMETER | FORMAT |
---------------------------------------------------------
| 125 | UTC | BCD |
| 155 | AIRCRAFT CONFIGURATION 1 | DISC |
| 156 | AIRCRAFT CONFIGURATION 2 | DISC |
| 227 | COMMAND | DISC |
| 260 | DATE | BCD |
| 301 | AIRCRAFT IDENT | ISO |
| 302 | AIRCRAFT IDENT | ISO |
| 303 | AIRCRAFT IDENT | ISO |
---------------------------------------------------------

- an ARINC 429 low speed output bus to the CFDIU:

The data sent to the CFDIU are:

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 ---------------------------------------------------------
| LABEL | PARAMETER | FORMAT |
---------------------------------------------------------
| 354 | LRU IDENTIFICATION | ISO |
| 356 | FAULT MESSAGES | ISO |
| 377 | EQUIPMENT IDENTIFICATION | BCD |
---------------------------------------------------------
The BITE can operate in two operating modes:
* in normal mode, to report continuously the failures of all
classes, depending on the maintenance flight phase,
* in interactive mode, to provide an interactive dialog with
an operator using an MCDU.

NOTE : The WR/PWS complies with Specification ABD0048, issue C.

____

(2) Normal mode

During the normal mode the BITE monitors cyclically the status of the
WR/PWS. It transmits its information to the CFDIU during the
concerned flight.
In case of fault detection the BITE stores the information in the
fault memories. These items of information are transmitted to the
CFDIU by an ARINC 429 message with label 356.

(3) Interactive mode

The interactive mode can only be activated on the ground and through
the line key adjacent to the RADAR 1 indication, presented on the
SYSTEM REPORT/TEST/NAV page of any MCDU.
This mode enables communication between the CFDIU and the BITE of the
weather radar transceiver by means of the MCDU.
R (Ref. Fig. 018)
The interactive mode is composed of:
- LAST LEG REPORT
R (Ref. Fig. 019)
This report contains the fault messages related to the external or
internal failures (class 1 and 2) recorded during the last flight
leg.
The following tables give the list of the failure messages which
can be reported and indicate the failure class assigned to them as
defined by the CFDIU standard.

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 Weather Radar - Maintenance Test Procedure - Access to the RADAR Page
R Figure 018

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R Weather Radar - Maintenance Test Procedure - Sub-menus (Sheet 1)
R Figure 019

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 -------------------------------------------------------------
| Reported Internal Failures |
|-----------------------------------------------------------|
| MESSAGE | CLASS | ATA |
-------------------------------------------------------------
| WXR1 (1SQ1) | 1 | 34-41-33 |
| WXR ANTENNA (11SQ) | 1 | 34-41-11 |
| WXR CNT PNL (3SQ)/WXR1 (1SQ1) | 1 | 34-41-12 |
-------------------------------------------------------------

-------------------------------------------------------------
| Reported External Failures |
|-----------------------------------------------------------|
| MESSAGE | CLASS | ATA |
-------------------------------------------------------------
| ADIRU1 (1FP1) IR BUS/WXR1 (1SQ1) | 1 | 34-12-34 |
| ADIRU3 (1FP3) IR BUS/WXR1 (1SQ1) | 1 | 34-12-34 |
| FCU (3CA) CP-L BUS/WXR1 (1SQ1) | 1 | 22-81-12 |
| FCU (3CA) CP-R BUS/WXR1 (1SQ1) | 1 | 22-81-12 |
| CFDIU (1TW)/WXR1 (1SQ1) | 3 | 31-32-34 |
| POWER SUPPLY INTERRUPT | 1 | 24-00-00 |
-------------------------------------------------------------

- PREVIOUS LEGS REPORT

R (Ref. Fig. 019)
This report contains the fault messages related to the external or
internal failures (class 1 and 2) recorded during the previous 63
flight legs.
- LRU IDENTIFICATION
R (Ref. Fig. 019)
Allows to display the P/N, the S/N and the SW/N of the equipment.
- GND SCANNING
R (Ref. Fig. 020)
Based on the monitoring and fault analysis during flight, provides
information of the failures detected while using this function.
The WR/PWS peripheral monitoring and internal cycle tests are used
to detect transient failures.
By pressing the line key adjacent to the failure message, the
operator is allowed to the corresponding Trouble Shooting Data. The
peripheral monitoring and WR/PWS internal cyclic tests are used to
detect transient failures.
- TROUBLE SHOOTING DATA
R (Ref. Fig. 020)
Provides correlation parameters and snapshot data concerning the
failure displayed in the LAST LEG REPORT and PREVIOUS LEGS REPORT.
- CLASS 3 FAULTS
R (Ref. Fig. 021)

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R Weather Radar - Maintenance Test Procedure - Sub-menus (Sheet 2)
R Figure 020

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 Weather Radar - Maintenance Test Procedure - Sub-menus (Sheet 3)
R Figure 021

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 Allows to display the class 3 faults recorded during the last
flight leg.
- GROUND REPORT
R (Ref. Fig. 021)
Allows to present the class 1, 2 or 3 internal failures detected on
ground.
These failures differ from those displayed on the LAST LEG REPORT
and CLASS 3 FAULTS.
By pressing the line key adjacent to the failure message, the
operator is allowed to access to the corresponding Trouble Shooting
Data.
- TEST
R (Ref. Fig. 022, 023)
Allows a check of the correct operation of the WR/PWS on ground.
This test can be performed through the CFDS by selecting on the
MCDU the test function on the RADAR 1 main menu page.
At the end of the BITE TEST, the test pattern comes into view.
R (Ref. Fig. 024)

NOTE : If a failure of the windshear system is detected during the

____
BITE TEST, the windshear flags come into view.
If the failure does not affect the radar mode, the test
pattern stays available.
If the failure affects the radar mode, nothing is shown.

All the information displayed on the MCDU during the BITE TEST
configuration can be printed by the printer (Ref. 31-35-00).
R By pressing the line key adjacent to the internal failure message,
R the operator is allowed to access to the corresponding Trouble
R Shooting Data.

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R Weather Radar - Maintenance Test Procedure - Sub-menus (Sheet 4)
R Figure 022

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R Weather Radar - Maintenance Test Procedure - Sub-menus (Sheet 5)
R Figure 023

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R Weather Radar - Test Pattern
R Figure 024

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 WEATHER RADAR SYSTEM - ADJUSTMENT/TEST
______________________________________

R TASK 34-41-00-720-002

R Functional test of the Tilt Control of the Weather-Radar Antenna Drive-Unit

R WARNING : MAKE SURE THAT:

_______
R -ALL PERSONS ARE MORE THAN 5 METERS (16.4FT) FROM THE ANTENNA.
R -NO PERSON IS IN THE AREA MADE BY AN ARC OF 135⁰ ON EACH SIDE OF THE
R AIRCRAFT CENTERLINE. -THERE IS A MINIMUM SAFETY DISTANCE OF 5 METERS
R (16.4FT) BETWEEN THE AIRCRAFT AND ANY OBSTACLE IN THE AREA MADE BY AN
R ARC OF 90⁰ ON EACH SIDE OF THE AIRCRAFT CENTERLINE.

R 1. __________________
Reason for the Job

R Self Explanatory

R 2. ______________________
Job Set-up Information

R A. Fixtures, Tools, Test and Support Equipment

R -------------------------------------------------------------------------------
R REFERENCE QTY DESIGNATION
R -------------------------------------------------------------------------------

R No specific circuit breaker(s) safety clip(s)

R No specific dummy load
R No specific access platform 4.6 m (15 ft. 1 in.)

R B. Referenced Information

R -------------------------------------------------------------------------------
R REFERENCE DESIGNATION
R -------------------------------------------------------------------------------

R 24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

R External Power
R 24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
R from the External Power
R 31-60-00-860-001 EIS Start Procedure
R 31-60-00-860-002 EIS Stop Procedure
R 34-10-00-860-002 ADIRS Start Procedure
R 34-10-00-860-005 ADIRS Stop Procedure
R 53-15-11-010-001 Opening of the Radome 110AL
R 53-15-11-410-001 Closing of the Radome 110AL

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R 3. __________
Job Set-up

R Subtask 34-41-00-010-052

R A. Get Access

R WARNING : DO NOT OPEN THE RADOME IF THE WIND SPEED IS MORE THAN 35 KNOTS.
_______

R NOTE : Two persons are necessary to open the radome.

____

R (1) Put the access platform in position below the radome.

R (2) Open the radome 110AL (Ref. TASK 53-15-11-010-001).

R (3) Make sure that the retaining arms of the radome lock correctly.

R Subtask 34-41-00-480-050

R B. In the radome, on the weather radar antenna:

R (1) Release the quick-disconnect fastener to disconnect the waveguide

R assembly from the antenna drive unit.

R (2) Remove the O-ring.

R (3) Install the dummy load (the cone in the down direction) in the
R antenna drive unit.

R (4) Do not install the O-ring between the waveguide assembly and the
R dummy load.

R (5) Connect the waveguide assembly to the antenna drive unit.

R (6) Make sure that there is no space between the waveguide assembly and
R the dummy load and that their connection is correct.

R (7) Remove the two screws that prevent operation of the AZ and EL
R selector switches on the antenna drive unit.

R (8) Make sure that the AZ and EL selector switches are at ON and that the
R antenna is free to move in azimuth and in elevation.

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R Subtask 34-41-00-865-059

R C. Open, safety and tag this(these) circuit breaker(s):

R -------------------------------------------------------------------------------
R PANEL DESIGNATION IDENT. LOCATION
R -------------------------------------------------------------------------------
R 121VU COM NAV/RADAR/1 5SQ1 K13

R Subtask 34-41-00-860-062

R D. Aircraft Maintenance Configuration

R (1) Energize the aircraft electrical circuits

R (Ref. TASK 24-41-00-861-002).

R (2) Do the EIS start procedure (EFIS only) (Ref. TASK 31-60-00-860-001).

R (3) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002).

R (4) On the EFIS control panels of the FCU:

R - set the mode selector switches to ARC.

R (5) On the EFIS switching panels 417VU and 418VU:

R - set the outer ND potentiometer to the middle position.

R (6) On the center pedestal, on the weather radar control unit, set:
R - the system switch to OFF
R - the GAIN potentiometer to AUTO (or CAL)
R - the TILT selector switch to 0⁰
R - the mode selector switch to WX
R - the windshear mode switch to OFF.

R 4. Procedure
_________

R Subtask 34-41-00-720-050

R A. Functional Test of the Tilt Control of the Antenna Drive Unit

R NOTE : Two persons are necessary to do the test:

____
R - one person must be in the cockpit to set the switches on the
R weather radar control unit
R - another person must be near the weather radar antenna to do the
R check of the tilt value on the indicator of the antenna drive
R unit.

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R -------------------------------------------------------------------------------
R ACTION RESULT
R -------------------------------------------------------------------------------

R 1. On the weather radar control Make sure that the antenna turns in
R unit: azimuth.
R - set the system switch to 1 (or
R ON).

R 2. On the antenna drive unit: Make sure that the antenna scanning
R - set the EL and AZ selector stops after some seconds.
R switches to OFF

R On Capt and F/O NDs:

R - the red WXR ANT indication comes into
R view.

R 3. Turn the antenna manually and

R carefully along the aircraft
R centerline.

R 4. On the antenna drive unit:

R - set the EL selector switch to
R ON (the AZ selector switch
R stays at OFF position).

R 5. On the weather radar control On the elevation indicator of the

R unit: antenna drive unit:
R - gradually turn the TILT - make sure that the antenna turns in
R selector switch to 5 deg. up (5 elevation 5 deg. up.
R UP notch)

R 6. On the weather radar control On the elevation indicator of the

R unit: antenna drive unit:
R - gradually turn the TILT - make sure that the antenna turns in
R selector switch to 10 deg. up elevation 10 deg. up.
R (10 UP notch)

R 7. On the weather radar control On the elevation indicator of the

R unit: antenna drive unit:
R - gradually turn the TILT - make sure that the antenna turns in
R selector switch to 15 deg. up elevation 15 deg. up.
R (15 UP notch)

R 8. On the weather radar control On the elevation indicator of the

R unit: antenna drive unit:

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
R - gradually turn the TILT - make sure that the antenna turns in
R selector switch to 5 deg. down elevation 5 deg. down.
R (5 DN notch)

R 9. On the weather radar control On the elevation indicator of the

R unit: antenna drive unit:
R - gradually turn the TILT - make sure that the antenna turns in
R selector switch to 10 deg. down elevation 10 deg. down.
R (10 DN notch)

R 10. On the weather radar control On the elevation indicator of the

R unit: antenna drive unit:
R - gradually turn the TILT - make sure that the antenna turns in
R selector switch to 15 deg. elevation 15 deg. down.
R down (15 DN notch)

R 11. On the weather radar control On the elevation indicator of the

R unit: antenna drive unit:
R - gradually turn the TILT - make sure that the antenna turns in
R selector switch to 0 deg. elevation 0 deg.

R 12. Turn manually and carefully the

R antenna to 90 deg. right and do
R again steps 7 through 13.

R 13. Turn manually and carefully the

R antenna to 90 deg. left and do
R again steps 7 through 13.

R 14. Turn manually and carefully the

R antenna along the aircraft
R centerline (0 deg. in azimuth
R and in elevation).

R 15. On the weather radar control

R unit:
R - set the system switch to OFF.

R 16. On the antenna drive unit:

R - set the AZ selector switch to
R ON.

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R 5. Close-up
________

R Subtask 34-41-00-860-063

R A. Put the aircraft back to its initial configuration.

R (1) On the CAPT and F/O EFIS switching panels 417VU and 418VU, set the ND
R potentiometers to OFF.

R (2) Do the EIS stop procedure (EFIS only) (Ref. TASK 31-60-00-860-002).

R (3) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005).

R (4) De-energize the aircraft electrical circuits

R (Ref. TASK 24-41-00-862-002).

R Subtask 34-41-00-080-050

R B. In the radome, on the weather radar antenna:

R (1) Disconnect the waveguide assembly from the dummy load on the antenna
R drive unit.

R (2) Remove the dummy load.

R (3) Install the O-ring on the waveguide connector on the antenna drive
R unit.

R (4) Connect the waveguide assembly to the antenna drive unit and lock the
R quick-disconnect fastener.

R (5) Make sure that the AZ and EL selector switches are at ON and that the
R antenna is free to move in azimuth and in elevation.

R (6) Tighten the two screws that prevent operation of the AZ and EL
R selector switches on the antenna drive unit.

R Subtask 34-41-00-410-052

R C. Close Access

R (1) Make sure that the work area is clean and clear of tool(s) and other
R items.

R (2) Close the access door 811 and the radome 110AL (Ref. TASK 53-15-11-
R 410-001).

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R (3) Remove the access platform(s).

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 TASK 34-41-00-740-002

BITE Test of the Weather Radar

WARNING : MAKE SURE THAT:

_______
-ALL PERSONS ARE MORE THAN 5 METERS (16.4FT) FROM THE ANTENNA.
-NO PERSON IS IN THE AREA MADE BY AN ARC OF 135⁰ ON EACH SIDE OF THE
AIRCRAFT CENTERLINE. -THERE IS A MINIMUM SAFETY DISTANCE OF 5 METERS
(16.4FT) BETWEEN THE AIRCRAFT AND ANY OBSTACLE IN THE AREA MADE BY AN
ARC OF 90⁰ ON EACH SIDE OF THE AIRCRAFT CENTERLINE.

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
31-32-00-860-010 Procedure to Get Access to the SYSTEM REPORT/TEST NAV
Page
31-60-00-860-001 EIS Start Procedure
34-10-00-860-002 ADIRS Start Procedure
34-41-00-991-001 Fig. 501

3. __________
Job Set-up

**ON A/C 001-004,

Subtask 34-41-00-860-053

A. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-

002).

(2) Do the EIS start procedure (EFIS only) (Ref. TASK 31-60-00-860-001).

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 (3) On the center pedestal, on the radar control unit, set :
- the ON/OFF selector switch to OFF
- the GAIN potentiometer to CAL
- the TILT selector switch to 0⁰
- the mode selector switch to WX
- the GND CLTR SPRS switch to OFF.

(4) On the ADIRS CDU, on the panel 20VU :

- set the three OFF/NAV/ATT selector switches to NAV.

(5) On the FCU, on the CAPT and F/O EFIS control sections :
- set the mode selector switches to ARC.

(6) On one MCDU :

- get the SYSTEM REPORT/TEST NAV menu page
(Ref. TASK 31-32-00-860-010)
- push the next page function key.

**ON A/C 005-099,

Subtask 34-41-00-860-053-A

A. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-

002).

(2) Do the EIS start procedure (Ref. TASK 31-60-00-860-001).

(3) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002).

(4) On the center pedestal, on the radar control unit, set:

- The ON/OFF switch to OFF.
- The GAIN potentiometer to CAL.
- The TILT selector switch to 0 deg.
- The mode selector switch to WX.
- The GND CLTR SPRS switch to OFF.
- The PWS/OFF/AUTO switch to OFF.

(5) On the ADIRS CDU, on the panel 20VU:

- set the three OFF/NAV/ATT selector switches to NAV.

(6) On the FCU, on the CAPT and F/O EFIS control sections:
- set the mode selector switches to ARC.

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 (7) On one MCDU:
- get the SYSTEM REPORT/TEST NAV menu page
(Ref. TASK 31-32-00-860-010)
- push the next page function key.

**ON A/C ALL

Subtask 34-41-00-865-055

B. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
121VU COM NAV/RADAR/1 5SQ1 K13

4. Procedure
_________

Subtask 34-41-00-740-050

A. BITE Test of the Weather Radar

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the center pedestal, on the

radar control unit :
- set the ON/OFF selector switch
to ON.

2. On one MCDU, on the NAV menu

page :
- push the line key adjacent to
the RADAR 1 indication

- push the line key adjacent to - On the CAPT and F/O NDs :
the TEST indication. * a TILT indication comes into view
on the right side until the end of
the test.
* the TEST PATTERN is shown from one
side to the opposite side
(Ref. Fig. 501/TASK 34-41-00-991-001)
* a WR TEST indication comes into
view on the right side with scan from
0⁰ to 135⁰.

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 Weather Radar Test
Figure 501/TASK 34-41-00-991-001

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
At the end of the test, on the MCDU,
the TEST OK indication comes into view.

- push the line key adjacent to - on the CAPT and F/O NDs :
the RETURN indication. the TEST PATTERN and the WR TEST
indication go out of view.

3. On the center pedestal, on the

radar control unit :
- set the ON/OFF selector switch
to OFF.

5. Close-up
________

Subtask 34-41-00-860-054

A. Put the aircraft back to its initial configuration.

(1) On the MCDU, push the line key adjacent to the RETURN indication
until the CFDS menu page comes into view.

(2) On the panels 301VU and 500VU, set the PFD and ND potentiometers to
OFF.

(3) On the ADIRS CDU, set the OFF/NAV/ATT selector switches to OFF.

(4) Make sure that the work area is clean and clear of tool(s) and other
items.

(5) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002)

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 TASK 34-41-00-730-001

System Test of the Weather Radar

WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE
_______
YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.

WARNING : STOP THE FUEL TANKER 200 ft. (60 m) FROM THE AIRCRAFT NOSE WHILE THE
_______
WEATHER RADAR OPERATES.
DO NOT OPERATE THE FUEL TANKER/PUMP UNIT UNTIL YOU STOP THE OPERATION
OF THE WEATHER RADAR.

WARNING : MAKE SURE THAT:

_______
-ALL PERSONS ARE MORE THAN 5 METERS (16.4FT) FROM THE ANTENNA.
-NO PERSON IS IN THE AREA MADE BY AN ARC OF 135⁰ ON EACH SIDE OF THE
AIRCRAFT CENTERLINE. -THERE IS A MINIMUM SAFETY DISTANCE OF 5 METERS
(16.4FT) BETWEEN THE AIRCRAFT AND ANY OBSTACLE IN THE AREA MADE BY AN
ARC OF 90⁰ ON EACH SIDE OF THE AIRCRAFT CENTERLINE.

1. __________________
Reason for the Job

- antenna stabilization test by the ADIRU 3

- antenna control test

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific circuit breaker(s) safety clip(s)

No specific warning notice
No specific access platform 3.5 m (11 ft. 6 in.)

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 B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
31-32-00-860-010 Procedure to Get Access to the SYSTEM REPORT/TEST NAV
Page
31-60-00-860-001 EIS Start Procedure
53-15-11-010-001 Opening of the Radome 110AL
53-15-11-410-001 Closing of the Radome 110AL

3. __________
Job Set-up

Subtask 34-41-00-865-053

A. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
121VU COM NAV/RADAR/1 5SQ1 K13

Subtask 34-41-00-010-050

B. Get Access

WARNING : MAKE SURE THAT THE CIRCUIT BREAKERS RELATED TO THE WEATHER
_______
RADAR ARE OPENED, SAFETIED AND TAGGED.

(1) In the cockpit, put a warning notice on the center pedestal to tell
persons not to operate the weather radar.

(2) Put the access platform in position in zone 110 below the radome.

(3) Open the radome 110AL (Ref. TASK 53-15-11-010-001).

NOTE : Two persons are necessary to open the radome.

____

(4) Make sure that the retaining arms of the radome lock correctly.

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 **ON A/C 001-004,

Subtask 34-41-00-860-050

C. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-

002).

(2) Do the EIS start procedure (EFIS only) (Ref. TASK 31-60-00-860-001).

(3) On the ADIRS CDU, set the OFF/NAV/ATT selector switch of the ADIRU1
and ADIRU3 to NAV to get the ND display.

(4) On the panel 8VU, make sure that the ATT HDG selector switch is at
NORM.

(5) On the FCU, on the CAPT and F/O EFIS control sections :
- set the mode selector switches to ROSE NAV or ARC.

(6) On the center pedestal, on the radar control unit, set :

- the ON/OFF selector switch to OFF
- the GAIN potentiometer to CAL
- the TILT selector switch to 0⁰
- the mode selector switch to WX
- the GNR CLTR SPRS switch to OFF.

R **ON A/C 001-002, 005-099,

R Post SB 34-1151 For A/C 001-002,

Subtask 34-41-00-860-050-A

C. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-

002).

(2) Do the EIS start procedure (EFIS only) (Ref. TASK 31-60-00-860-001).

(3) On the ADIRS CDU, set the OFF/NAV/ATT selector switch of the ADIRU1
and ADIRU3 to NAV to get the ND display.

(4) On the panel 8VU, make sure that the ATT HDG selector switch is at
NORM.

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 (5) On the FCU, on the CAPT and F/O EFIS control sections :
- set the mode selector switches to ROSE NAV or ARC.

(6) On the center pedestal, on the radar control unit, set :

- the ON/OFF selector switch to OFF
- the GAIN potentiometer to CAL
- the TILT selector switch to 0⁰
- the mode selector switch to WX
- the GNR CLTR SPRS switch to OFF.
R - the PWS AUTO/OFF switch to OFF.

**ON A/C ALL

Subtask 34-41-00-865-054

D. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
121VU COM NAV/RADAR/1 5SQ1 K13

4. Procedure
_________

Subtask 34-41-00-730-050

A. Antenna Stabilization Test by the ADIRU 3

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the center pedestal, on the

radar control unit :

- set the ON/OFF selector switch The CAPT and F/O NDs show the radar
to ON. display.

2. On the panel 8VU :

- set the ATT HDG selector switch On the CAPT and F/O NDs, the radar
to CAPT 3. display stays in view.

3. On the ADIRS CDU :

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
- set the OFF/NAV/ATT selector On the CAPT and F/O NDs, the radar
switch of the ADIRU 1 to OFF. display stays in view.

4. On the ADIRS CDU : On the CAPT and F/O NDs :

- set the OFF/NAV/ATT selector - after some seconds, the WR ATT
switch of the ADIRU 3 to OFF. warning indication is shown on the
right.
- the radar display stays in view.

5. On the center pedestal, on the On the CAPT and F/O NDs :

radar control unit : - after some seconds, the radar display
- set the ON/OFF selector switch and the WR ATT warning indication go
to OFF. out of view.

Subtask 34-41-00-730-051

B. Antenna Control Test

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On one MCDU :
- get the SYSTEM REPORT/TEST NAV
menu page
(Ref. TASK 31-32-00-860-010)

- push the line key adjacent to During the test sequence, make sure
the RADAR 1 indication. that the antenna :
- push the line key adjacent to - turns in elevation (+ 15⁰, - 15⁰)
the TEST indication. - turns in azimuth from the right side
to the left side, then becomes stable
at 0⁰, vertical to the aircraft
centerline.
At the end of the test, on the MCDU,
the TEST OK indication comes into
view.
On the CAPT and F/O NDs, ignore the
radar indications.

- push the line key adjacent to On the MCDU :

the RETURN indication. - the MCDU MENU page comes into view.

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 5. Close-up
________

Subtask 34-41-00-860-051

A. Put the aircraft back to its initial configuration.

(1) On the panels 301VU and 500VU, set the PFD and ND potentiometers to
OFF.

(2) On the panel 8VU, set the ATT HDG selector switch to NORM.

(3) Make sure that the work area is clean and clear of tool(s) and other
items.

(4) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

Subtask 34-41-00-410-050

B. Close Access

(1) Close the radome 110AL (Ref. TASK 53-15-11-410-001).

NOTE : Make sure that the radome locks correctly.

____

(2) Remove the access platform(s).

(3) Remove the warning notice(s).

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 ANTENNA ASSEMBLY - WEATHER RADAR (7SQ,11SQ) - REMOVAL/INSTALLATION
__________________________________________________________________

TASK 34-41-11-000-002

Removal of the Antenna Assembly - Weather Radar (7SQ,11SQ)

WARNING : MOVE THE RADAR ANTENNA ASSEMBLY CAREFULLY TO PREVENT INJURY TO

_______
PERSONS AND DAMAGE TO EQUIPMENT.
THE RADAR ANTENNA ASSEMBLY (ANTENNA/DRIVE) WEIGHS APPROXIMATELY 15kg
(33lb).

CAUTION : DO NOT USE THE LOCALIZER ANTENNA AT THE BOTTOM OF THE RADOME AS A
_______
SUPPORT.

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific blanking caps

No specific circuit breaker(s) safety clip(s)
No specific warning notice
No specific access platform 3.5 m (11 ft. 6 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

53-15-11-010-001 Opening of the Radome 110AL

34-41-11-991-002 Fig. 401

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 3. __________
Job Set-up

Subtask 34-41-11-865-053

A. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
121VU COM NAV/RADAR/1 5SQ1 K13

Subtask 34-41-11-010-051

B. Get Access

(1) In the cockpit, put a warning notice on the center pedestal, to tell
persons not to operate the weather radar system.

(2) Put the access platform in position in zone 110 below the radome.

(3) Open the radome 110AL (Ref. TASK 53-15-11-010-001).

4. Procedure
_________

(Ref. Fig. 401/TASK 34-41-11-991-002)

Subtask 34-41-11-020-058

A. Removal of the Antenna Plate

NOTE : During this job, one person must hold the antenna.
____

(1) Remove the two bolts (15).

(2) Remove the antenna (1) and put the antenna in a plastic bag and a
correct container.

Subtask 34-41-11-020-059

B. Removal of the Antenna Assembly

(1) Disconnect the electrical connectors (12).

(2) Disconnect the wave guide (5) from the antenna drive (2) with the
quick disconnect clamp (3) and remove the O-ring (4).

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 Radar Antenna
Figure 401/TASK 34-41-11-991-002

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 (3) Put blanking caps on the disconnected connectors (12) and (13) and
the flange of the wave guide (5).

(4) Remove the two screws (11) at the bottom and the washers (10).

(5) Loosen the two screws (8) and the washers (7) at the top, do not
remove them at this time.

(6) Lift the antenna drive (2) until the holes (6) are at the same level
as the two top screws (8), pull carefully.

(7) Remove the antenna drive (2) and put it in a plastic bag and a
correct container.

5. Close-up
________

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 TASK 34-41-11-400-006

Installation of the Antenna Assembly - Weather Radar (7SQ,11SQ)

WARNING : MOVE THE RADAR ANTENNA ASSEMBLY CAREFULLY TO PREVENT INJURY TO

_______
PERSONS AND DAMAGE TO EQUIPMENT.
THE RADAR ANTENNA ASSEMBLY (ANTENNA/DRIVE) WEIGHS APPROXIMATELY 15kg
(33lb).

CAUTION : DO NOT USE THE LOCALIZER ANTENNA AT THE BOTTOM OF THE RADOME AS A
_______
SUPPORT.

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific warning notice

No specific access platform 3.5 m (11 ft. 6 in.)

B. Consumable Materials

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

No specific lockwire corrosion resistant steel 0.8mm (0.30 in.)

C. Expendable Parts

-------------------------------------------------------------------------------
FIG.ITEM |DESIGNATION |IPC-CSN
-------------------------------------------------------------------------------

4 O-ring 34-41-01 02B-120

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 D. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

34-41-00-730-001 System Test of the Weather Radar

53-15-11-010-001 Opening of the Radome 110AL
53-15-11-410-001 Closing of the Radome 110AL
34-41-11-991-002 Fig. 401

3. __________
Job Set-up

Subtask 34-41-11-860-054

A. Aircraft Maintenance Configuration

(1) Make sure that the warning notice, which tells persons not to operate
the Weather Radar System, is in position in the cockpit on the center
pedestal.

(2) Make sure that the access platform is in position in zone 110 below
the radome.

(3) Make sure that the radome 110AL is open (Ref. TASK 53-15-11-010-001).

Subtask 34-41-11-865-062

B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and
tagged

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
121VU COM NAV/RADAR/1 5SQ1 K13

4. Procedure
_________

(Ref. Fig. 401/TASK 34-41-11-991-002)

Subtask 34-41-11-420-058

A. Installation of the Antenna Assembly

R NOTE : Do not remove the clear plastic windows that are installed at the
____
R inlet of the antenna drive and at the interface between the
R antenna drive and the antenna plate.

(1) Clean the component interface and/or the adjacent area.

(2) Do an inspection of the component interface and/or the adjacent area.

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 (3) Make sure that the two top screws (8) are sufficiently loose.

(4) Lift the antenna drive (2) up to its support (9) and engage it in the
two top screws (8).

(5) Install the two bottom screws (11) and the washers (10).

(6) Attach the antenna drive (2). To do this, tighten the screws (8) and
(11) with the washers (7) and (10).

(7) Remove the blanking caps from the electrical connectors (12) and (13)
and the flange of the wave guide (5).

(8) Put the O-ring (4) in the correct position on the flange of the wave
guide (3).

(9) Connect the wave guide (5) to the antenna drive (2) with the quick
disconnect (3).

(10) Connect the electrical connectors (12).

Subtask 34-41-11-420-059

B. Installation of the Antenna Plate

NOTE : Two persons are necessary to do this job.

____
It is possible to install the antenna (1) with the antenna drive
(2) installed on the aircraft.

(1) Put the dowels (16) in the holes (18) of the antenna (1). Then engage
the plate (19) between the two slots (17). Tighten the two bolts
(15).

(2) Safety the two bolts (15) with lockwire corrosion resistant steel
0.8mm (0.30 in.).

(3) Make sure that the antenna assembly turns correctly in azimuth (AZ)
R and in elevation (EL).
R

Subtask 34-41-11-865-063

C. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
5SQ1

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 Subtask 34-41-11-730-054

D. Do the system test of the weather radar system (para. Antenna control)
(Ref. TASK 34-41-00-730-001).

5. Close-up
________

Subtask 34-41-11-410-054

A. Close Access

(1) Make sure that the work area is clean and clear of tool(s) and other
items.

(2) Close the radome 110AL (Ref. TASK 53-15-11-410-001).

(3) Remove the access platform(s).

(4) Remove the warning notice(s).

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 CONTROL UNIT - WEATHER RADAR (3SQ) - REMOVAL/INSTALLATION
_________________________________________________________

TASK 34-41-12-000-001

Removal of the Weather Radar Control Unit (3SQ)

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific blanking caps

No specific circuit breaker(s) safety clip(s)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

34-41-12-991-001 Fig. 401

3. __________
Job Set-up

Subtask 34-41-12-865-050

A. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
121VU COM NAV/RADAR/1 5SQ1 K13

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 4. Procedure
_________

(Ref. Fig. 401/TASK 34-41-12-991-001)

Subtask 34-41-12-020-051

A. Removal of the Weather Radar Control Unit

(1) Loosen the four quarter-turn fasteners (1).

(2) Pull the weather radar control unit (2) from its housing (5).

(3) Disconnect the electrical connector(s) (4) and hold it them away from
the panel.

(4) Remove the weather radar control unit (2).

(5) Put blanking caps on the disconnected electrical connectors (3) and
(4).

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 Weather Radar Control Unit
Figure 401/TASK 34-41-12-991-001

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 TASK 34-41-12-400-001

Installation of the Weather Radar Control Unit (3SQ)

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

34-41-00-740-002 BITE Test of the Weather Radar

34-41-12-991-001 Fig. 401

3. __________
Job Set-up

Subtask 34-41-12-865-051

A. Make sure that this(these) circuit breaker(s) is(are) open, safetied and
tagged

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
121VU COM NAV/RADAR/1 5SQ1 K13

4. Procedure
_________

(Ref. Fig. 401/TASK 34-41-12-991-001)

Subtask 34-41-12-420-051

A. Installation of the Weather Radar Control Unit

(1) Clean the component interface and/or the adjacent area.

(2) Do an inspection of the component interface and/or the adjacent area.

(3) Remove the blanking caps from the electrical connectors (3) and (4).

(4) Make sure that the electrical connectors are clean and in the correct
condition.

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 (5) Connect the electrical connector(s) (4) to the weather radar control
unit (2).

(6) Install the weather radar control unit (2) in its housing (5).

(7) Tighten the four quarter-turn fasteners (1).

Subtask 34-41-12-865-052

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
5SQ1

Subtask 34-41-12-740-050

C. Do the BITE test of the weather radar system

(Ref. TASK 34-41-00-740-002).

5. Close-up
________

Subtask 34-41-12-860-050

A. Make sure that the work area is clean and clear of tool(s) and other
items.

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 TRANSCEIVER - WEATHER RADAR (1SQ1,1SQ2) - REMOVAL/INSTALLATION
______________________________________________________________

TASK 34-41-33-000-004

Removal of the Weather Radar Transceiver (1SQ1, 1SQ2)

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific blanking caps

No specific circuit breaker(s) safety clip(s)
No specific access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

R 31-32-00-860-010 Procedure to Get Access to the SYSTEM REPORT/TEST NAV

R Page
34-41-33-991-003 Fig. 401

3. __________
Job Set-up

R Subtask 34-41-33-810-050

R A. Print the Trouble Shooting Data

R (1) If required and applicable, print the Trouble Shooting Data (TSD) as
R follows:

R (a) Get access to the SYSTEM/REPORT TEST NAV page (Ref. TASK 31-32-
R 00-860-010).

R (b) Get access to the WXR1 (WXR2) page.

R (c) Get access to the Trouble Shooting Data page.

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R (d) Print the Trouble Shooting Data (TSD).

Subtask 34-41-33-865-058

R B. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
121VU COM NAV/RADAR/1 5SQ1 K13

Subtask 34-41-33-010-052

R C. Get Access

(1) Put the access platform in position at the access door 811 in zone
122.

(2) Open the access door 811.

4. Procedure
_________

(Ref. Fig. 401/TASK 34-41-33-991-003)

Subtask 34-41-33-020-050

A. Removal of the Weather Radar Transceiver

(1) Loosen the nuts (5).

(2) Lower the nuts (5).

(3) Pull the weather radar transceiver (2) on its rack (1) to disconnect
the electrical connectors (4) and (6).

(4) Remove the weather radar transceiver (2) from its rack (1).

(5) Put blanking caps on the disconnected electrical connectors (4) and
(6).

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R Weather Radar Transceivers
Figure 401/TASK 34-41-33-991-003

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 TASK 34-41-33-400-003

Installation of the Weather Radar Transceiver (1SQ1, 1SQ2)

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

34-41-00-740-002 BITE Test of the Weather Radar

34-41-33-991-003 Fig. 401

3. __________
Job Set-up

Subtask 34-41-33-860-050

A. Aircraft Maintenance Configuration

(1) Make sure that the access platform is in position at the access door
811 in zone 122.

(2) Make sure that the access door 811 is open.

Subtask 34-41-33-865-059

B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and
tagged

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
121VU COM NAV/RADAR/1 5SQ1 K13

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 4. Procedure
_________

(Ref. Fig. 401/TASK 34-41-33-991-003)

Subtask 34-41-33-420-050

A. Installation of the Weather Radar Transceiver

(1) Clean the component interface and/or the adjacent area.

(2) Do an inspection of the component interface and/or the adjacent area.

(3) Remove the blanking caps from the electrical connectors (4) and (6).

(4) Make sure that the electrical connectors are clean and in the correct
condition.

(5) Install the weather radar transceiver (2) on its rack (1).

(6) Push the weather radar transceiver (2) on its rack (1) to connect the
electrical connectors (4) and (6).

(7) Engage the nuts (5) on the lugs (3) and tighten.

Subtask 34-41-33-865-060

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
5SQ1

Subtask 34-41-33-740-050

C. Do the BITE test of the weather radar

(Ref. TASK 34-41-00-740-002).

5. Close-up
________

Subtask 34-41-33-860-051

A. Make sure that the work area is clean and clear of tool(s) and other
items.

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 Subtask 34-41-33-410-050

B. Close Access

(1) Close the access door 811.

(2) Remove the access platform(s).

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 MOUNTING TRAY - WEATHER RADAR TRANSCEIVER (9SQ) - REMOVAL/INSTALLATION
______________________________________________________________________

TASK 34-41-37-000-001

Removal of the Weather Radar Transceiver Mounting Tray (9SQ)

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific blanking caps

No specific blanking plug

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

34-41-33-000-004 Removal of the Weather Radar Transceiver (1SQ1, 1SQ2)

34-41-37-991-001 Fig. 401

3. __________
Job Set-up

Subtask 34-41-37-020-050

A. Remove the Weather Radar Transceiver (Ref. TASK 34-41-33-000-004).

4. Procedure
_________

(Ref. Fig. 401/TASK 34-41-37-991-001)

Subtask 34-41-37-020-052

A. Removal of the MTG tray

(1) Disconnect the electrical connector (9).

(2) Loosen the two clamps (7).

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 Weather Radar Transceiver Mounting Tray
Figure 401/TASK 34-41-37-991-001

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 (3) Disconnect the ventilation line (8).

(4) Put blanking plug on the disconnected line end (8).

(5) Cut and remove the lockwire from the screws (10).

(6) Remove the four screws (10) and the washers (11).

(7) Remove the wave guide (12) from its support. Remove the window (13)
and the O-rings (14).

(8) Remove the ten screws (6), the washers (5) and the attachment plates
(4).

(9) Remove the electrical connectors (3) from their housings.

(10) Put blanking caps on the disconnected electrical connectors (1), (3)
and (9).

(11) Remove the four screws (16) and the washers (17).

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 TASK 34-41-37-400-001

Installation of the Weather Radar Transceiver Mounting Tray (9SQ)

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific access platform 1.6 m (5 ft. 3 in.)

B. Expendable Parts

-------------------------------------------------------------------------------
FIG.ITEM |DESIGNATION |IPC-CSN
-------------------------------------------------------------------------------

14 O-rings 34-41-01 02B-120

C. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

34-41-33-400-003 Installation of the Weather Radar Transceiver (1SQ1,

1SQ2)
34-41-37-991-001 Fig. 401

3. __________
Job Set-up

Subtask 34-41-37-860-050

A. Aircraft Maintenance Configuration

(1) Make sure that the access platform is in position at the access door
811 in zone 122.

(2) Make sure that the access door 811 is open.

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 4. Procedure
_________

Subtask 34-41-37-420-052

A. Installation of Mounting Tray

(1) Install the Mounting tray (15) in its housing (2) with the four
washers (17) and the screws (16).

(2) Remove the blanking caps from the disconnected electrical connectors
(1), (3) and (9).

(3) Make sure that the electrical connectors are clean and in the correct
condition.

(4) Install the electrical connectors (3) in their housing.

(5) Install the attachment plates (4) and attach them with the ten
washers (5) and the screws (6).

(6) Put the O-rings (14) in their housings.

(7) Put the window (13) and the wave guide (12) in position.

(8) Install the four washers (11) and the screws (10).

(9) Tighten the screws (10) and safety them with the lockwire.

(10) Remove the blanking plug from the disconnected line end (8).

(11) Connect the ventilation line (8). Tighten the clamps (7).

(12) Connect the connector (9) to the receptacle (1).

(13) Make sure that the electrical connectors are clean and in the correct
condition.

5. Close-up
________

(Ref. Fig. 401/TASK 34-41-37-991-001)

Subtask 34-41-37-420-051

A. Install the Weather Radar Transceiver (Ref. TASK 34-41-33-400-003).

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 WAVE GUIDE ASSEMBLY (301FM) - REMOVAL/INSTALLATION
__________________________________________________

TASK 34-41-41-000-001

Removal of the Wave Guide Assembly

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific blanking caps

No specific circuit breaker(s) safety clip(s)
No specific access platform 1.6 m (5 ft. 3 in.)
No specific access platform 3.5 m (11 ft. 6 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

53-15-11-010-001 Opening of the Radome 110AL

34-41-41-991-001 Fig. 401

3. __________
Job Set-up

Subtask 34-41-41-865-050

A. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
121VU COM NAV/RADAR/1 5SQ1 K13

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 Subtask 34-41-41-010-050

B. Get Access

(1) In the cockpit, put a warning notice on the center pedestal to tell
persons not to operate the weather radar.

(2) Put the access platform in position.

(3) Open the radome 110AL (Ref. TASK 53-15-11-010-001).

(4) Put the access platform in position at the access door 811.

(5) Open the access door 811.

4. Procedure
_________

(Ref. Fig. 401/TASK 34-41-41-991-001)

WARNING : MAKE SURE THAT THE CIRCUIT BREAKERS RELATED TO THE WEATHER RADAR
_______
ARE OPENED, SAFETIED AND TAGGED.

Subtask 34-41-41-020-050

A. Removal of the Flexible Wave Guide Part (10) Connected to the Mounting
Tray of the Weather Radar Transceiver

(1) Remove the lockwire and then the four screws (18) and the four
washers (17).

(2) Disconnect the flange (11). Remove and discard the two O-rings (13)
and (16) and the adaptor (12).

(3) At the other end, remove the lockwire and then the four screws (5)
and washers (6).

(4) Disconnect the flange (9) from the flange (7).

Remove and discard the O-ring (8).

(5) Remove the flexible wave guide part (10).

(6) Put blanking caps on the disconnected ends.

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 Wave Guide Assembly
Figure 401/TASK 34-41-41-991-001

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 Subtask 34-41-41-020-051

B. Removal of the Rigid Wave Guide Part (14) Installed in the Avionics
Compartment

(1) Remove the lockwire and then the four screws (5) and the four washers
(6).

(2) Disconnect the flange (9). Remove and discard the O-ring (8).

(3) At the wave guide feedthrough (25), remove the lockwire and then the
four screws (36) and the four washers (35).

(4) Hold the wave guide part (14) and remove the screw (21) and the
washer (20) which attach the clamp (19) to the structure.

(5) Move the rigid wave guide part (14) away from the structure. Remove
and discard the O-ring (24).

(6) Remove the clamp (19) and the two half bushings (22) from the wave
guide.

(7) Remove the rigid wave guide part (14).

(8) Put blanking caps on the disconnected ends.

Subtask 34-41-41-020-052

C. Removal of the Wave Guide Feedthrough (25)

NOTE : Two persons are necessary to remove the wave guide feedthrough.
____

(1) If necessary, remove the two rigid wave guide parts (14) and (37)
which are connected to the feedthrough. Refer to Para. B. above and
Para. D. below.

(2) Remove the eight screws (34), the washers (33) and the nuts (32).

(3) Move the wave guide feedthrough (25) away from the pressure bulkhead
(27). Remove and discard the packing (26).

(4) Remove the wave guide feedthrough (25) and put blanking caps on the
disconnected ends.

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 Subtask 34-41-41-020-053

D. Removal of the Rigid Wave Guide Part (37) Installed in the Radome

(1) Remove the lockwire and then the four screws (38) and the washers
(39).

(2) Disconnect the flange (2). Remove and discard the O-ring (3).

(3) At the wave guide feedthrough (25), remove the lockwire and then the
four screws (30) and the four washers (31).

(4) Hold the wave guide part (37) and remove the screw (21) and the
washer (20) which attach the clamp (19) to the structure.

(5) Move the rigid wave guide part (37) away from the structure. Remove
and discard the O-ring (28).

(6) Remove the clamp (19) and the two half bushings (22) from the wave
guide.

(7) Remove the rigid wave guide part (37) and put blanking caps on the
disconnected ends.

Subtask 34-41-41-020-054

E. Removal of the Flexible Wave Guide Part (1) Connected to the Antenna
Drive

(1) Release the quick-disconnect attach (40).

Disconnect the flange (42) from the antenna drive. Remove and discard
the O-ring (41).

(2) Remove the screw (21) and the washer (20).

Then remove the clamp (19) and the two half bushings (22) from the
wave guide.

(3) At the other end, remove the lockwire and then the four screws (38)
and the four washers (39).

(4) Disconnect the flange (2) from the flange (4).

Remove and discard the O-ring (3).

(5) Remove the flexible wave guide part (1) and put blanking caps on the
disconnected ends.

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 TASK 34-41-41-400-001

Installation of the Wave Guide Assembly

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific access platform 1.6 m (5 ft. 3 in.)

No specific access platform 3.5 m (11 ft. 6 in.)
No specific Torque Wrench : range 0.19 to 0.21 m.daN
(16.81 to 18.58 lbf.in)

B. Consumable Materials

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

No specific corrosion resistant steel lockwire dia. 0.5 mm

(0.020 in.)
R Material No. 09-016 USA MIL-PRF-81733D TYPE II CLASS B
CORROSION INHIBITING FILLET CONSISTENCY
(Ref. 20-31-00)

C. Expendable Parts

-------------------------------------------------------------------------------
FIG.ITEM |DESIGNATION |IPC-CSN
-------------------------------------------------------------------------------

41 O-ring (7) 34-41-01 02B-120

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 D. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
31-60-00-860-001 EIS Start Procedure
31-60-00-860-002 EIS Stop Procedure
53-15-11-410-001 Closing of the Radome 110AL
34-41-41-991-001 Fig. 401

3. __________
Job Set-up

Subtask 34-41-41-860-050

A. Aircraft Maintenance Configuration

(1) Make sure that the access platform is in position and that the radome
110AL is open.

(2) Make sure that the access platform is in position at the access door
811 and that the access door 811 is open.

(3) In the cockpit make sure that there is a warning notice on the center
pedestal to tell persons not to operate the weather radar.

NOTE : Remove the blanking caps before you install parts of the wave
____
guide. Make sure that all mating surfaces are clean and in
correct condition.

NOTE : Each part of the wave guide is identified (ANT, 1, 2, 3, 4 and

____
RT or ANTENNE 1, 2, 3, 4 and EMETTEUR depending on the Vendor
marking).
When you install the wave guide part, make sure that the
number sequence is correct.

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 Subtask 34-41-41-865-051

B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and
tagged

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
121VU COM NAV/RADAR/1 5SQ1 K13

4. Procedure
_________

(Ref. Fig. 401/TASK 34-41-41-991-001)

Subtask 34-41-41-420-050

A. Installation of the Flexible Wave Guide Part (1) Connected to the Antenna
Drive

(1) Install a new O-ring (41) and put the flange (ANT reference) in
position.

(2) Lock the quick-disconnect attach (40).

(3) At the other end, install a new O-ring (3) and connect the flanges
(2) and (4).

(4) Install the four washers (39) and the four screws (38).
TORQUE the screws to between 0.19 and 0.21 m.daN (16.81 and 18.58
lbf.in) and install the corrosion resistant steel lockwire dia. 0.5
mm (0.020 in.).

(5) Install the two half bushings (22) and the clamp (19) on the wave
guide.
Put the clamp in position and install the washer (20) and the screw
(21).

Subtask 34-41-41-420-051

B. Installation of the Rigid Wave Guide Part (37) in the Radome

(1) If necessary, install the wave guide feedthrough (25). Refer to Para.
C. below.

(2) At the two ends, install new O-rings (3) and (28).

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 (3) Hold the rigid wave guide part (37) in position: install the eight
washers (31) and (39) and the eight screws (30) and (38).

(4) Tighten the screws and install lockwire.

(5) Install the two half bushings (22) and the clamp (19) on the wave
guide. Put the clamp in position and install the washer (20) and the
screw (21).

Subtask 34-41-41-420-052

C. Installation of the Wave Guide Feedthrough (25)

NOTE : Two persons are necessary to install the wave guide feedthrough.
____

(1) Install a new packing (26) and put the feedthrough (25) into the
cutout of the pressure bulkhead (27).

(2) Install the eight screws (34), the washers (33) and the nuts (32).
TORQUE the nuts to between 0.19 and 0.21 m.daN (16.81 and 18.58
lbf.in). Seal the nuts with SEALANTS (Material No. 09-016).

(3) If necessary, install the rigid wave guide parts (14) and (37) which
are connected to the feedthrough. Refer to Para. B. above and to
Para. D. below.

Subtask 34-41-41-420-053

D. Installation of the Rigid Wave Guide Part (14) in the Avionics

Compartment

(1) If necessary, install the wave guide feedthrough (25). Refer to Para.
C. above.

(2) At the two ends, install new O-rings (24) and (8).

(3) Hold the rigid wave guide part (14) in position and install eight
washers (35) and (6) and eight screws (36) and (5).

(4) TORQUE the screws to between 0.19 and 0.21 m.daN (16.81 and 18.58
lbf.in) and install the lockwire.

(5) Install the two half bushings (22) and the clamp (19) on the wave
guide. Put the clamp in position and install the washer (20) and the
screw (21).

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 Subtask 34-41-41-420-054

E. Installation of the Flexible Wave Guide Part (10) Connected to the

Mounting Tray of the Weather Radar Transceiver

(1) Install a new O-ring (8) and connect the flange (9) to the flange
(7).

(2) Install the four washers (6) and the four screws (5). TORQUE the
screws to between 0.19 and 0.21 m.daN (16.81 and 18.58 lbf.in) and
install the lockwire.

(3) On the flange of the mounting tray (15), install a new O-ring (13).

(4) On the flange (11) (RT reference), install a new O-ring (16).

(5) Put the adaptor (12) in position with the arrow which points in the
direction of the mounting tray.

(6) Install the flange (11) with the four washers (17) and the four
screws (18). TORQUE the screws to between 0.19 and 0.21 m.daN (16.81
and 18.58 lbf.in) and install the lockwire.

(7) Make sure that the pressurization hole in the wave guide is clean.

Subtask 34-41-41-865-052

F. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
5SQ1

Subtask 34-41-41-710-050

G. Test

WARNING : MAKE SURE THAT:

_______
-ALL PERSONS ARE MORE THAN 5 METERS (16.4FT) FROM THE ANTENNA.
-NO PERSON IS IN THE AREA MADE BY AN ARC OF 135⁰ ON EACH SIDE
OF THE AIRCRAFT CENTERLINE. -THERE IS A MINIMUM SAFETY DISTANCE
OF 5 METERS (16.4FT) BETWEEN THE AIRCRAFT AND ANY OBSTACLE IN
THE AREA MADE BY AN ARC OF 90⁰ ON EACH SIDE OF THE AIRCRAFT
CENTERLINE.

(1) Make sure that all wave guide parts are correctly installed.

(2) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-

002).

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 (3) Do the EIS start procedure (ND only) (Ref. TASK 31-60-00-860-001).

(4) On the ADIRS CDU, on the panel 20VU:

- set the three OFF/NAV/ATT selector switches to NAV.

(5) On the center pedestal, on the weather radar control unit, set the
system to ON.

(6) Make sure that the system operates normally: on the ND, the weather
radar display is shown.

(7) On the weather radar control unit, set the system to OFF.

5. Close-up
________

Subtask 34-41-41-860-052

A. Put the aircraft back to its initial configuration.

(1) Do the EIS Stop Procedure (ND only)(Ref. TASK 31-60-00-860-002).

(2) On the ADIRS CDU set the OFF/NAV/ATT selector switches to OFF.

(3) Make sure that the work area is clean and clear of tool(s) and other
items.

(4) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-

002).

(5) Remove the warning notice(s).

Subtask 34-41-41-410-050

B. Close Access

(1) Close the access door 811.

(2) Close the radome 110AL (Ref. TASK 53-15-11-410-001).

(3) Remove the access platform(s).

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 RADIO ALTIMETER - DESCRIPTION AND OPERATION
___________________________________________

1. _______
General
The LRA-900 provides vertical distance to the terrain via the ARINC 429 bus
outputs. The RA transmit a FM/CW (Frequency Modulated Continuous Wave) RF
signal to the terrain, via the transmit antenna, and receives the reflection
of that signal via the receive antenna. It independently computes an
altitude by measuring and processing the characteristics of the transmitted
and received RF signal.
R

2. __________________
Component Location
R
(Ref. Fig. 001)
R

-------------------------------------------------------------------------------
FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA
| | | | DOOR | REF.
-------------------------------------------------------------------------------
2SA1 XCVR-RA, 1 152 826 34-42-33
2SA2 XCVR-RA, 2 152 826 34-42-33
3SA1 FAN-RA XCVR 1 152 826 34-42-45
3SA2 FAN-RA XCVR 2 152 826 34-42-45
5SA1 ANTENNA-RA RCPTN, 1 153 34-42-11
5SA2 ANTENNA-RA RCPTN, 2 153 34-42-11
6SA1 ANTENNA-RA XMSN, 1 153 34-42-11
6SA2 ANTENNA-RA XMSN, 2 153 34-42-11

3. __________________
System Description

A. Principle
R (Ref. Fig. 002, 003)
The principle of the radio altimeter is to :
- transmit a frequency modulated signal from the aircraft to the ground
- receive the ground reflected signal after a certain delay.
The time between the transmitted frequency and the received frequency is
proportional to the aircraft height.

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 Radio Altimeter - Component Location
R Figure 001

R
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 Radio Altimeter - Principle of Operation
R Figure 002

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 INTENTIONALLY BLANK

R
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 Radio Altimeter - Simplified Block Diagram
R Figure 003

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 the height of the aircraft is calculated by determining the difference
between the frequency of the reflected signal and the signal being
transmitted at the instant the reflected signal is received. This
difference frequency is directly proportional to the time required for
the reflected signal to traverse the distance from the aircraft to the
ground and back to the aircraft. The difference frequency is measured and
converted to distance by a microprocessor in the altitude processor which
also transmits the measured distance to user equipment over the ARINC 429
bus.
The reflected signal is fed from a dedicated receive antenna to the
receiver where it is mixed with a portion of the transmitted signal now
being radiated at the transmit antenna to develop a beat frequency (Fb).
The beat frequency is processed by the IF system and is sent to the
altitude and monitor processors.
Two independent samples of transmitted RF are fed to two reference signal
generators. Each generator produces an output (Fr) corresponding to the
delay time that represents a 300-foot altitude. Fr1 is the reference
signal for the altitude processor, Fr2 is the reference signal for the
monitor processor.
The altitude processor samples the beat frequency input signal (Fb) and
the reference frequency signal (Fr1) and converts each to digital form.
The ratio of the measured frequency input signal (Fb) to the output of
the 300-foot reference channel is calculated and multiplied by 300 to
produce the total radio altitude. The total radio altitude is further
modified by the AID and internal box delays to produce the actual
aircraft altitude above terrain.

B. System Architecture
R (Ref. Fig. 004)
The radio altimeter comprises two independent systems. Each system
consists of :
- one transceiver 2SA1 (2SA2)
- one transmission antenna 6SA1 (6SA2)
- one reception antenna 5SA1 (5SA2)
- one fan 3SA1 (3SA2).
In addition, the Centralized Fault-Display Interface-Unit (CFDIU) 1TW
controls the system through the Multipurpose Control and Display Unit 1
(2) (MCDU) 3CA1 (3CA2) for test causes.
R (Ref. Fig. 005)
The radio height data is shown on the Primary Flight Display (PFD). In
normal operation, system 1 provides information to the CAPT PFD and
system 2 to the F/O PFD.

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 Radio Altimeter - Block Diagram
R Figure 004

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 Radio Altimeter - Control and Indicating
R Figure 005

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 C. Utilization Technical Data
R (Ref. Fig. 006)

(1) Height data display (Item 3)

The aircraft height data with respect to the ground is shown in the
sector 2 of the PFD. This indication is at the bottom of the attitude
sphere, for height less than or equal to 2500 ft.
The dimension and color of the digits change in relation to the
height (H) and decision height (DH) as follows :
H more than or equal to 400 ft. : 3 mm green digits
400 ft. > H > DH + 100 ft. : 4 mm green digits
H < DH + 100 ft. : 4 mm amber digits.
The sensitivity of the digits is also a function of the height :
H > 50 ft. : 10 ft. increments
50 ft > or = to H and H > or = to 5 ft : 5 ft. increments
H < 5 ft. : 1 ft. increments.
With failure of both radio altimeters, a red RA warning message is
shown in place of the radio height information (Item 4) in slats
extented configuration only. The message flashes during 3 seconds
then remains on.
When the aircraft is below 500 ft. height above the terrain : a red
ribbon comes into view on the bottom of the altitude scale and moves
up with this scale as the aircraft is in the descent phase (Item 2).
When the aircraft has touched down the ground : the top of this
ribbon is at the middle of the altitude window.
With failure of both radio altimeters, the ribbon goes out of view.
Below 300 ft., the height is shown by the distance between the
horizon line and the limit of the sector 2. The limit of the sector 2
moves up as the aircraft is in the descent phase.
The distance between these two lines is proportional to the ground
height (sensitivity 5 ft./mm).
As it moves up, the limit line erases the graduations on the pitch
scale.
With failure of both radio altimeters, this indication goes out of
view.

(2) Decision height display (DH) (Item 1)

The pilot sets the DH on the MCDU. The DH data are shown on the R top
corner of the PFD (3 mm high digits) as soon as the radio altimeter
operates.
When the height is lower than the DH, a DH amber warning message
comes into view at the bottom of the attitude sphere (Item 5).

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 Radio Altimeter - Data and Warning Displays
R Figure 006

R
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 D. Warnings
R (Ref. Fig. 005, 006)
The warnings related to the radio altimeter are :
- local warning on the instruments that use the radio altimeter data
- MASTER CAUT lights on the CAPT and F/O glareshield panels
- aural warning : single chime
- warning message shown on the upper ECAM display unit.
R

4. Power
____________
Supply
R (Ref. Fig. 004)
Energization of each system is through 115VAC, 400 Hz normal buses :
- 115VAC BUS1 101XP via circuit breaker 1SA1 for system 1
- 115VAC BUS2 202XP via circuit breaker 1SA2 for system 2.
R

5. _____________________
Component Description

A. Transceiver

(1) External description

R (Ref. Fig. 007)
The face of the transceiver is fitted with a handle, two attaching
parts, a TEST pushbutton switch, a connector (TEST CONN) to connect
test set for system test and three LEDs.
The name, color and function of the three LEDs are as follows:
- LRU STATUS: green indicates no fault detected during the self-test
sequence and red indicates that a fault is detected during the
self-test sequence
- XMIT ANT FAIL: red indicates a fault in the antenna circuit
- REC ANT FAIL: red indicates a fault in the antenna circuit.
The back is equipped with one ARINC 600 electrical receptacle and a
slot for the test connector.
R

(2) Internal description

R (Ref. Fig. 003)

(a) Layout
The transceiver LRA-900 consists of an interconnect assembly, an
RF assembly, a modulator/IF assembly, an instrumentation assembly
(processor) and a power supply assembly.
The transceiver is a radio altimeter using a wideband frequency
modulated continuous wave (FM/CW) technique to measure the
distance between the aircraft and the terrain below.

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 Radio Altimeter - Transceiver
R Figure 007

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 (b) Modulator assembly
The function of the modulator is to provide the transmitter with
a 100 Hz triangular wave corrected for transmitter non
linearities and also to maintain the transmitter deviation limits
at 4250 MHz and 4350 MHz.
The modulator assembly also contains the high and low altitude
IF<s, and two major circuits.
The first is a closed loop circuit which controls the rate at
which the transmitter<s output frequency changes.
The other major circuit controls the transmitter bandwidth within
the 4250 to 4350 MHz normal band of operation.

(c) Instrumentation assembly

The instrumentation assembly consists of the altitude processor,
the monitor processor, a system monitor and AFCS bus driver power
switch.

1
_ Altitude processor
The beat and reference frequencies from the IF circuit board
are converted to a binary number in the counter array and the
microprocessor calculates the radio altitude based on the
counter array data.
The altitude information is converted to ARINC 429 ternary
data by being formatted and sent by the UART through the
driver circuits to the FMGCs and PFDs once every 35 or 40
milliseconds depending on aircraft altitude.

2
_ Monitor processor
The monitor processor counts and computes altitude, in the
same manner as the altitude processor. Instead of transmitting
ternary data, however, the monitor processor receives it and
compares it with its own previously computed altitude. Any
altitude disparity (outside of a fixed error window determined
by software) generates a failure indication.
An incorrect word or altitude also causes the monitor
processor to inhibit transmission of this data to the
autopilot if the optional AFCS interrupt mode is selected.
This is accomplished by disabling the AFCS power supply during
periods of incorrect data transmission and thereby shutting
down the ALT bus No.1 ARINC 429 transmitter.

(d) RF assembly
The RF assembly contains all of the 4300 MHz functions. It is
comprised of the transmitter and receiver microstrip circuitry.
R

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 (3) Digital outputs
This table contains all the output parameters in the digital form.
They are sorted as per the numerical order of their output label.
The following table gives :
- EQ.SYS.LAB.SDI: (SDAC, FWC, DMC...) output label for which the
parameter is available
- PARAMETER DEFINITION: parameter name
- WORD RANGE OPER RANGE RESOLUTION ACCURACY: measurement range.
Maximum value transmitted. When the digital value changes, the
change step is equal to the accuracy
- UNIT: unit in which the digital value is transmitted
- SIG BIT: indicates whether a sign bit is available
- BITS: number of bits used by the parameter in the label
- XMSN/INTV: output transmission interval. The refresh rate is given
in milliseconds
- CODE :
BNR: binary data word
BCD: binary coded decimal data word
ISO: data word coded in ISO5 code
DIS: discrete data word
HEX: hexadecimal coded
HYB: mixed code
- ALPHA CODE: indicates the parameter mnemonic code
- SOURCE ORIGIN: parameter source computer or system.

-------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
| 164 |RADIO | 8192 | FT | 29 | 16 | 35 |BNR |RALT | |
| |HEIGHT | 0.125 | | | | or | | | |
| | | | | | | 40 | | | |
-------------------------------------------------------------------------------

B. Antennas
R
(Ref. Fig. 008)
R
The transmission and reception antennas are identical. The small -
thickness antenna is installed on the skin of the aircraft.

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 Radio Altimeter - Antennas
R Figure 008

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 Each antenna is supplied through a coaxial connector linked to the
transceiver. The operating range of the antenna according to the attitude
of the aircraft is limited to + or - 30⁰ for roll and pitch.

C. Fans
The six-blade fan is integral with a removable base plate attached under
the transceiver mount. It is contained in a square aluminum alloy case.
It is supplied with 115VAC through a connector and associated wiring
connecting it to the transceiver. Interference is suppressed by a
capacitor mounted on the fan case.

6. Operation
_________

A. Control
In normal operation, system 1 automatically provides the height data for
the CAPT PFD and system 2 for the F/O PFD.
With failure of one system, the valid system is automatically switched to
both CAPT and F/O PFDs.
With failure of the two systems, the digits go out of view from the PFD :
in place of the digits, a red RA warning message flashes during three
seconds then remains on.
For information : the pilot sets the DH on the MCDU. The Flight Warning
Computer (FWC) generates the DH warning message.
With loss of DH information, the DH data are not shown.

B. Reconfiguration Switching
In normal utilization, the radio altimeter data are shown on the CAPT PFD
and F/O PFD through the Display Management Computers 1 and 2 (DMC).
With failure of the radio altimeter transceiver 1, the DMC 1 and 2
automatically switch over to the transceiver 2.
With failure of the DMC 1 (2), it is possible to switch over to the DMC 3
with the EIS DMC selector switch.
This selector switch is located on panel 8VU on the center pedestal.
In this case the DMC 3 totally replaces the DMC 1 (2) through the stage
of the output switching relay of the failed DMC.
With failure of the PFD, there is an automatic transfer of the PFD image
onto the Navigation Display (ND).
When you set the PFD potentiometer to OFF on panel 301VU (500VU), this
causes :
- deactivation of the PFD
- transfer of the PFD image onto the ND.
R

R
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 7. ____
Test
R (Ref. Fig. 009)

A. Access to Radio Altimeter Sub-menu Functions

It is possible to select the maintenance functions of the radio altimeter
transceiver 1(2) by pressing the line key adjacent to the SYSTEM
REPORT/TEST indication on the CFDS menu, and then selecting the relevant
RA on the NAV menu.
After these actions the RA 1(2) provides its own menu page and the
sub-menu functions can then be chosen by the operator.

NOTE : The test can be performed on the ground only. It is inhibited (the
____
EIU1 (EIU2) sends a ground discrete to the RA1 (RA2)) as soon as
N2 rating (high pressure compressor rotational speed) is greater
than minimum idle rating.

B. Activation of the Test Function

(1) SYSTEM TEST

The RA SYSTEM TEST function can be activated by pressing the line key
adjacent to the corresponding indication on the RA 1(2) maintenance
sub-menu.
The following sequence occurs :
- on the PFD :
* the bottom sector line moves down from the horizon line.
* the radio altimeter is 40 ft.
- on the MCDU, at the end of the test, the TEST OK message comes into
view.

NOTE : During the test :

____
- You can hear auto call-out announcements 40, 41 or 42
- You must open the RA1 circuit breaker to hear auto call-out
announcements during the RA2 SYSTEM TEST.

(2) RAMP TEST

The RAMP TEST function can be activated from the MCDU by pressing the
line key adjacent to the SYSTEM REPORT/TEST indication on the CFDS
menu then selecting the RA1 (RA2) on the NAV menu and then selecting
the RAMP TEST page.
The RA then begins simulating a ramp starting from 500 ft. down to 0
ft. (with a slope of 11 ft/s from 500 ft. to 50 ft. and approximately
3 ft/s from 50 ft. to 0 ft.).

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R **ON A/C 001-004,

C. Power-up Tests Initialization and Cockpit Repercussions

(1) Conditions of power-up tests initialization

- How long the computer must be de-energized: 2 s.
- A/C configuration:
- whatever the A/C configuration on ground

(2) Progress of power-up tests

- Duration: 3 s.
- Cockpit repercussions directly linked to power-up test
accomplishment (some other repercussions may occur depending on the
A/C configuration but these can be disregarded):
- MASTER CAUT light on

(3) Results of power-up tests

(cockpit repercussions, if any, in case of tests pass/tests failed).
- Tests pass:
- MASTER CAUT light off
- Tests failed:
- MASTER CAUT light on
- ECAM warning
NAV RA 1 or 2 FAULT
- ECAM STATUS
RA 1 or 2 INOP

R **ON A/C ALL

D. CFDIU Interface
(Ref. Fig. 009)

(1) BITE description

The BITE facilitates maintenance on in-service aircraft. It detects
and identifies a failure related to the RA system. The BITE of the
radio altimeter is connected to the CFDIU (Ref. 31-32-00).
The BITE:
- transmits permanently RA system status and its identification
message to the CFDIU
- memorizes the failures which occurred during the last 63 flight
legs
- monitors data inputs from the various peripherals
- transmits to the CFDIU the result of the tests performed and
selt-tests
- can communicate with the CFDIU through the menus.
The BITE can operate in two modes:
- the normal mode
- the menu mode.

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 Radio Altimeter - Maintenance Test Procedure
R Figure 009 (SHEET 1)

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 Radio Altimeter - Maintenance Test Procedure
R Figure 009 (SHEET 2)

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 Radio Altimeter - Maintenance Test Procedure
R Figure 009 (SHEET 3)

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 Radio Altimeter - Maintenance Test Procedure
R Figure 009 (SHEET 4)

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 Radio Altimeter - Maintenance Test Procedure
R Figure 009 (SHEET 5)

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 (a) Normal mode
During the normal mode the BITE monitors cyclically the status of
the RA system. It transmits its information to the CFDIU during
the concerned flight.
In case of fault detection the BITE stores the information in the
fault memories.
These items of information are transmitted to the CFDIU by an
ARINC 429 message with label 356.

(b) Menu mode

The menu mode can only be activated on the ground.
This mode enables communication between the CFDIU and the RA BITE
by means of the MCDU.
All the information displayed on the MCDU during the BITE Test
configuration can be printed by the printer (Ref. 31-35-00).
The RA menu mode is composed of:
- LAST LEG REPORT
This menu contains the fault messages (class 1 and 2, internal
and external) detected during the last flight.
- PREVIOUS LEGS REPORT
This report contains the fault messages related to the external
or internal failures (class 1 and 2) recorded during the previous
63 flight legs.
- LRU IDENTIFICATION
Allows to display the P/N of the equipment.
- TROUBLE SHOOTING DATA
Provides correlation parameters and snapshot data concerning the
failure displayed in the LAST LEG REPORT and PREVIOUS LEGS
REPORT.
- GROUND REPORT.
Allows to present the class 1, 2 or 3 internal failures detected
on ground.
- SYSTEM TEST.
Allows a check of the correct operation of the RA transceiver on
the ground.
- RAMP TEST.
Allows to verify that auto call out altitudes are correctly
announced.

(2) List of components

All the components are listed in the Para. 2. Component Location.

R
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 RADIO ALTIMETER - ADJUSTMENT/TEST
_________________________________

TASK 34-42-00-740-002

BITE Test of the Radio Altimeter

WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE
_______
YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
31-32-00-860-010 Procedure to Get Access to the SYSTEM REPORT/TEST NAV
Page
31-60-00-860-001 EIS Start Procedure
31-60-00-860-002 EIS Stop Procedure
34-10-00-860-002 ADIRS Start Procedure
34-10-00-860-005 ADIRS Stop Procedure

3. __________
Job Set-up

Subtask 34-42-00-860-054

A. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits

(Ref. TASK 24-41-00-861-002).

(2) Do the EIS start procedure (PFDs only) (Ref. TASK 31-60-00-860-001).

(3) Do the ADIRS Start Procedure (Ref. TASK 34-10-00-860-002).

(4) On the center pedestral, on one MCDU, get the SYSTEM REPORT/TEST/NAV
page (Ref. TASK 31-32-00-860-010).

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 Subtask 34-42-00-865-056

B. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
121VU COM NAV/RAD ALTM/2 1SA2 K12
121VU COM NAV/RAD ALTM/1 1SA1 K11

4. Procedure
_________

Subtask 34-42-00-740-051-A

A. BITE Test

NOTE : - During the test, you can hear auto call out announcements 40 or
____
41 or 42.
- You must open the RA1 circuit breaker to hear auto call out
announcements during the RA2 SYSTEM TEST.

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the MCDU:

- get the RA1 (RA2) page then On the CAPT (F/O PFD):
push the line key adjacent to - the bottom sector line moves down
the SYSTEM TEST indication. from the horizon line.
- the radio altitude indication is 40
ft.

- push the line key adjacent to the TEST OK message comes into view.
the YES indication.

- push the line key adjacent to On the CAPT (F/O PFD):

the RETURN indication. - the bottom sector line moves up to
the horizon line.
- the radio altitude indication is O
ft.
On the MCDU, the RA1 (RA2) page comes
into view.

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R

5. Close-up
________

Subtask 34-42-00-860-055

A. Put the aircraft back to its initial configuration.

(1) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005).

(2) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002).

(3) On the center pedestal, on the MCDU, push the line key adjacent to
the RETURN indication until the MCDU MENU page comes into view.

(4) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

(5) Make sure that the work area is clean and clear of tool(s) and other
items.

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 TASK 34-42-00-750-001

R Detailed Inspection and Operational Check of the Radio Altimeter Fan

WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE
_______
YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.

1. __________________
Reason for the Job

Refer to the MPD TASK: 344200-01

Operational Test of Radio Altimeter Fan.

2. ______________________
Job Set-up Information

R A. Fixtures, Tools, Test and Support Equipment

R -------------------------------------------------------------------------------
R REFERENCE QTY DESIGNATION
R -------------------------------------------------------------------------------

R No specific air blower

R No specific soft brush
R No specific access platform 2 m (6 ft. 7 in.)

R B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

R 22-97-00-710-001 Operational Test of the LAND CAT III Capability

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the
External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
R 34-42-00-740-002 BITE Test of the Radio Altimeter
R 34-42-33-000-001 Removal of the Radio Altimeter Transceiver 2SA1 and
R 2SA2
R 34-42-33-400-001 Installation of the Radio Altimeter Transceiver 2SA1
R and 2SA2
R 34-42-45-000-001 Removal of the Radio Altimeter-Transceiver Fan 3SA1
R (3SA2)
R 34-42-45-400-001 Installation of the Radio Altimeter-Transceiver Fan
R 3SA1 (3SA2)
R 52-30-00-860-001 Open the FWD or AFT Cargo-Compartment Door with the
R Yellow Electric Pump

R
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 -------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

R 52-30-00-860-002 Close the FWD or AFT Cargo-Compartment Door with the

R Yellow Electric Pump

3. __________
Job Set-up

Subtask 34-42-00-860-056

A. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits

(Ref. TASK 24-41-00-861-002).

R Subtask 34-42-00-010-050

R B. Get Access

R (1) Put an access platform in position at the aft cargo door 826.

R (2) Open the aft cargo door 826 (Ref. TASK 52-30-00-860-001).

R (3) Remove the sidewall panel 152GW.

Subtask 34-42-00-865-055

R C. Make sure that this(these) circuit breaker(s) is(are) open, safetied and
R tagged

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
121VU COM NAV/RAD ALTM/2 1SA2 K12
121VU COM NAV/RAD ALTM/1 1SA1 K11

4. Procedure
_________

R Subtask 34-42-00-020-050

R A. Remove the two Radio Altimeter Transceivers (Ref. TASK 34-42-33-000-001).

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R Subtask 34-42-00-210-051

R B. Detailed Inspection of the two RA transceiver Fans

R (1) Do a detailed visual inspection of the two RA transceiver fans and of

R the fan housing.

R (2) Remove the RA transceiver fans (Ref. TASK 34-42-45-000-001).

R (3) Make sure that the fan and the fan housing are blocked.

R NOTE : Cleaning with an air blower can cause excessive fan

____
R rotation-speed and thus fan failure.

R (4) Clean the RA transceiver fans and their housing with a soft brush
R and/or an air blower.

R (5) Install the RA transceiver fans (Ref. TASK 34-42-45-400-001).

R (6) Close the circuit breakers 1SA1 and 1SA2 on the panel 121VU.

Subtask 34-42-00-720-053

R C. Functional Test

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

R 1. On the rear circuit breaker panel In the aft cargo compartment (zone 152,
R 121VU: door 826), below the transceiver mount:
R

R - open the circuit breaker 1SA1 - make sure that the RA transceiver fan
R (1SA2). 3SA1 (3SA2) does not blow.

R - close the circuit breaker 1SA1 - make sure that the RA transceiver fan
R (1SA2). 3SA1 (3SA2) blows air up.

R Subtask 34-42-00-420-050

R D. Install the two Radio Altimeter Transceivers (Ref. TASK 34-42-33-400-

R 001).

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R Subtask 34-42-00-740-052

R E. Do the BITE test of the radio altimeter (Ref. TASK 34-42-00-740-002).

R NOTE : If the airline operates the aircraft in CAT III conditions, you
____
R must also do the LAND CAT III capability test (Ref. TASK 22-97-00-
R 710-001).

5. Close-up
________

R Subtask 34-42-00-410-050

R A. Close Access

R (1) Install the sidewall panel 152GW.

R (2) Close the aft cargo door 826 (Ref. TASK 52-30-00-860-002).

R (3) Remove the access platform(s).

R Subtask 34-42-00-865-059

R B. Make sure that this(these) circuit breaker(s) is(are) closed:

R 1SA1, 1SA2

Subtask 34-42-00-860-057

R C. Put the aircraft back to its initial configuration.

(1) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

(2) Make sure that the work area is clean and clear of tool(s) and other
items.

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 TASK 34-42-00-730-002

Ramp Test of the Radio Altimeter

WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE
_______
YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.

1. __________________
Reason for the Job

Test of the automatic simulation of a change in altitude.

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

R
No specific access platform 2 m (6 ft. 7 in.)
R DRA707B1 1 TEST SET - DIGITAL RADIO ALTIMETER

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

31-60-00-860-001 EIS Start Procedure

31-60-00-860-002 EIS Stop Procedure

3. __________
Job Set-up

Subtask 34-42-00-860-052

A. Aircraft Maintenance Configuration

(1) Put the access platform in position at the AFT cargo door 826.

(2) Open the AFT cargo door 826.

(3) Remove the access panel 152HW.

R (4) Connect the TEST SET - DIGITAL RADIO ALTIMETER (DRA707B1) to the face
of the transceiver.

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 (5) Do the EIS start procedure (PFDs only) (Ref. TASK 31-60-00-860-001).

(6) On the overhead panel, on the ADIRS CDU, set the OFF/NAV/ATT selector
switches to NAV.

Subtask 34-42-00-865-057

B. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
121VU COM NAV/RAD ALTM/2 1SA2 K12
121VU COM NAV/RAD ALTM/1 1SA1 K11

Subtask 34-42-00-865-058

C. Make sure that this(these) circuit breaker(s) is(are) open, safetied and
tagged

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
121VU EIS/GPWS/115VAC 3WZ P07

4. Procedure
_________

Subtask 34-42-00-730-050-A

A. RAMP Test Simulation of the Radio Altimeter

NOTE : This test is for the RA1. For the RA2, use the indications between
____
parentheses.

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the MCDU: On the MCDU:

- push the line key adjacent to - the RA1 (RA2) RAMP TEST page comes
the RA1 (RA2) indication. Then into view with these indications:
push the line key adjacent to TWO SUCCESSIVES RAMPS:
the RAMP TEST indication. RAMP1: 500-50FT (11FT/S)
RAMP2: 50-0FT (3FT/S)
MAKE SURE THAT AUTO
CALL OUT ALTITUDES ARE
CORRECTLY ANNOUNCED

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
On the CAPT (F/O) PFD:
- the ramp test starts. The speed scale
moves down from 500 to 0 ft. and
stops after approximately 1 minute.
- when the altitude is between 500 and
0 ft., the red ribbon adjacent to the
altitude scale moves up.

On the MCDU:
- at the end of the test, the TEST OK
page comes into view.

- push the line key adjacent to - the RA1 (RA2) page comes into view.
the RETURN indication.

5. Close-up
________

Subtask 34-42-00-860-053

A. Put the aircraft back to its initial configuration.

(1) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002).

(2) On the overhead panel, on the ADIRS CDU, set the OFF/NAV/ATT selector
switches to OFF.

(3) Disconnect the RA simulator.

(4) Install the access panel 152HW.

(5) Close the AFT cargo door 826.

(6) Remove the access platform(s).

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 TASK 34-42-00-710-001

Warning Test of the Radio Altimeter

WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE
_______
YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.

1. __________________
Reason for the Job

Test of the operation of the RA warning.

2. ______________________
Job Set-up Information

A. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
27-80-00-866-004 Extending the Slats on the Ground
27-80-00-866-005 Retracting the Slats on the Ground
31-60-00-860-001 EIS Start Procedure
31-60-00-860-002 EIS Stop Procedure

3. __________
Job Set-up

Subtask 34-42-00-860-050

A. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits

(Ref. TASK 24-41-00-861-002).

(2) Do the EIS start procedure (Ref. TASK 31-60-00-860-001).

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 Subtask 34-42-00-865-051

B. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
121VU COM NAV/RAD ALTM/2 1SA2 K12
121VU COM NAV/RAD ALTM/1 1SA1 K11

4. Procedure
_________

Subtask 34-42-00-710-051

A. Test of the Operation of the RA Warning

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the center pedestal:

- move the slat/flap control The slats extend to the full position.
lever to the position 1
(Ref. TASK 27-80-00-866-004).

2. On the rear circuit breaker panel

121VU:

- open the circuit breaker 1SA1. On the CAPT and F/O PFDs:
- the altitude 0 ft. stays in view.
On the upper ECAM display unit:
- the NAV RA1 FAULT indication comes
into view.
On the CAPT and F/O glareshield panels:
- the MASTER CAUT lights come on.
In the loud speakers:
- you can hear the single chime.

- open the circuit breaker 1SA2. On the CAPT and F/O PFDs:
- the altitude 0 ft. goes out of view.
- the RA warning comes into view.
On the upper ECAM display unit:
- the NAV RA1 FAULT indication stays in
view.
- the NAV RA2 FAULT indication comes
into view.

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
On the CAPT and F/O glareshield panels:
- the MASTER CAUT lights stay on.
In the loud speakers:
- you can hear the single chime.

3. On the rear circuit breaker panel

121VU:

- close the circuit breakers 1SA1 On the CAPT and F/O PFDs:
and 1SA2. - the RA warning goes out of view after
15 seconds.
- the altitude 0 ft. comes into view.
On the upper ECAM display unit:
- the NAV RA1 FAULT and NAV RA2 FAULT
indications go out of view.

5. Close-up
________

Subtask 34-42-00-860-051

A. Put the aircraft back to its initial configuration.

(1) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002).

(2) Put the aircraft in clean configuration (Ref. TASK 27-80-00-866-005).

(3) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

(4) Make sure that the work area is clean and clear of tool(s) and other
items.

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 ANTENNA - RADIO ALTIMETER (5SA1,5SA2,6SA1,6SA2) - REMOVAL/INSTALLATION
______________________________________________________________________

TASK 34-42-11-000-001

Removal of the Radio Altimeter Antennas 5SA1, 5SA2, 6SA1, 6SA2

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific blanking caps

No specific circuit breaker(s) safety clip(s)
No specific nonmetallic scraper

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-42-00-861-001 Energize the Ground Service Network from the External

Power
34-42-11-991-001-A Fig. 401
R 34-42-11-991-003 Fig. 402

3. __________
Job Set-up

Subtask 34-42-11-861-050

A. Energize the ground service network

(Ref. TASK 24-42-00-861-001).

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 Subtask 34-42-11-865-050

B. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
FOR 5SA1(6SA1)
121VU COM NAV/RAD ALTM/1 1SA1 K11
FOR 5SA2(6SA2)
121VU COM NAV/RAD ALTM/2 1SA2 K12

4. Procedure
_________

R (Ref. Fig. 401/TASK 34-42-11-991-001-A, 402/TASK 34-42-11-991-003)

Subtask 34-42-11-020-051-A

A. Removal of the Radio Altimeter Antenna

(Ref. Fig. 401/TASK 34-42-11-991-001-A)

WARNING : CUT, REMOVE AND DISCARD THE LOCKWIRE AS YOU DO THE TASK. LOOSE
_______
LOCKWIRE CAN CUT OR BLIND YOU.

NOTE : The procedure is the same for the radio altimeter antennas 5SA1,
____
5SA2, 6SA1, 6SA2.

(1) Remove the sealant from the heads of the screws (5) with a
nonmetallic scraper.

(2) Remove the attachment screws (5) from the antenna (4).

(3) Pull the antenna (4) carefully away until you can see the coaxial
connector (2).

(4) Remove and discard the lockwire from the coaxial connector (2), if
installed.

(5) Disconnect the coaxial connector (2) from the antenna connector (3).

(6) Remove the antenna (4).

(7) Put blanking caps on the disconnected electrical connectors.

(8) Remove and discard the packing - preformed (6), if installed.

(9) Remove the teflon gasket (8).

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R Radio Altimeter Antennas
Figure 401/TASK 34-42-11-991-001-A

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R Radio Altimeter Antennas (Alternative)
Figure 402/TASK 34-42-11-991-003

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R Subtask 34-42-11-020-054

R B. Removal of the Radio Altimeter Antenna (Alternative)

R (Ref. Fig. 402/TASK 34-42-11-991-003)

R WARNING : CUT, REMOVE AND DISCARD THE LOCKWIRE AS YOU DO THE TASK. LOOSE
_______
R LOCKWIRE CAN CUT OR BLIND YOU.

R NOTE : The procedure is the same for the radio altimeter antennas 5SA1,
____
R 5SA2, 6SA1, 6SA2.

R (1) Remove the sealant from the heads of the screws (5) with a
R nonmetallic scraper.

R (2) Remove the attachment screws (5) from the antenna (4).

R (3) Pull the antenna (4) carefully away until you can see the coaxial
R connector (2).

R (4) Remove and discard the lockwire from the coaxial connector (2), if
R installed.

R (5) Disconnect the coaxial connector (2) from the antenna connector (3).

R (6) Remove the antenna (4).

R (7) Put blanking caps on the disconnected electrical connectors.

R (8) Remove and discard the packing - preformed (6), if installed.

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 TASK 34-42-11-400-001

Installation of the Radio Altimeter Antennas 5SA1, 5SA2, 6SA1, 6SA2

WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS

_______
ONLY WITH A GOOD SUPPLY OF AIR.
OBEY THE MANUFACTURERS INSTRUCTIONS.
PUT ON PROTECTIVE CLOTHING.
DO NOT GET THEM IN YOUR MOUTH.
DO NOT SMOKE.
DO NOT BREATHE THE GAS.
THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT.
GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED.

WARNING : DO NOT GET THE COMPOUND ON YOUR SKIN.

_______
IF YOU DO:
- RUB IT OFF IMMEDIATELY WITH A CLEAN CLOTH
- WASH THE SKIN WITH SOAP AND RINSE WITH CLEAN WATER.

WARNING : IF YOU GET THE FLUID ON YOUR SKIN OR IN YOUR EYES:

_______
- FLUSH IT AWAY WITH CLEAN WATER
- GET MEDICAL AID.

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific lint free cloth

No specific nonmetallic scraper
No specific Torque Wrench : range 0.20 to 3.60 m.daN
(2.00 to 26.00 lbf.ft)

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 B. Consumable Materials

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

Material No. 05-013 D TV-53-3507/73

RELEASE AGENT (OBSOLETE USE 05-013A) (Ref. 20-31-00)
Material No. 07-001
ELECTRICAL BONDING COATING (BLUE COLOR)
(Ref. 20-31-00)
Material No. 08-048 D DA-2-657-4
ADHESIVE (Ref. 20-31-00)
R Material No. 09-016 USA MIL-PRF-81733D TYPE II CLASS B
CORROSION INHIBITING FILLET CONSISTENCY
(Ref. 20-31-00)
Material No. 09-019 USA AMS 3267/3
LOW ADHESION CORROSION INHIBITING SEALANT
(Ref. 20-31-00)
Material No. 11-010 USA TT-I-735 GRADE A
ISOPROPYL ALCOHOL (Ref. 20-31-00)
Material No. 16-003 F ASNB70720
COATING (OBSOLETE USE 16-021) (Ref. 20-31-00)
Material No. 19-009 USA AMS 5687
LOCKWIRE STAINLESS STEEL ANNEALED 0.5MM DIA
(Ref. 20-31-00)

C. Expendable Parts

-------------------------------------------------------------------------------
FIG.ITEM |DESIGNATION |IPC-CSN
-------------------------------------------------------------------------------

R 6 packing-preformed 34-42-11 07 -010

8 teflon-gasket 34-42-04 05B-035

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 D. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

20-28-00-912-005 Electrical Bonding of Antennas With Conductive Bolts.

24-42-00-861-001 Energize the Ground Service Network from the External
Power
24-42-00-862-001 De-energize the Ground Service Network Supplied from
the External Power
34-42-00-740-002 BITE Test of the Radio Altimeter
34-42-11-991-001-A Fig. 401
R 34-42-11-991-003 Fig. 402

3. __________
Job Set-up

Subtask 34-42-11-860-050

A. Aircraft Maintenance Configuration

(1) Make sure that the ground service network is energized

(Ref. TASK 24-42-00-861-001).

(2) Make sure that the aircraft is in the same configuration as for the
removal task.

(3) Make sure that the parts retained from the removed component are
clean and in the correct condition.

Subtask 34-42-11-865-051

B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and
tagged

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
FOR 5SA1(6SA1)
121VU COM NAV/RAD ALTM/1 1SA1 K11
FOR 5SA2(6SA2)
121VU COM NAV/RAD ALTM/2 1SA2 K12

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 4. Procedure
_________

R (Ref. Fig. 401/TASK 34-42-11-991-001-A, 402/TASK 34-42-11-991-003)

WARNING : OBEY THE MANUFACTURER<S INSTRUCTIONS WHEN YOU USE THE SPECIAL
_______
MATERIAL.
THIS MATERIAL IS DANGEROUS.

Subtask 34-42-11-140-050-A

A. Preparation for Installation

(1) Remove the used sealant from the fuselage structure (1) with a
nonmetallic scraper.

R (2) Clean the component interface and/or the adjacent area with CLEANING
R AGENTS (Material No. 11-010) and the lint free cloth.

(3) Do an inspection of the component interface and/or the adjacent area.

NOTE : Make sure that the antenna-attachment screw-head recesses have

____
no signs of paint, corrosion or sealant because the antenna
electrical bonding is made through the attachment screws.

R Subtask 34-42-11-140-051

R B. Preparation for Installation (Alternative)

R (1) Remove the used sealant from the fuselage structure (1) with a
R nonmetallic scraper.

R (2) Clean the component interface and/or the adjacent area with CLEANING
R AGENTS (Material No. 11-010) and the lint free cloth.

R (3) Do an inspection of the component interface and/or the adjacent area.

R NOTE : Make sure that the antenna-attachment screw-head recesses have

____
R no signs of paint, corrosion or sealant because the antenna
R electrical bonding is made through the attachment screws.

R (4) Apply masking tape to the structure (1), the edge of the antenna (4),
R the screw holes and the hole for the antenna connector (3).

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 Subtask 34-42-11-420-050-A

R C. Installation of the Radio Altimeter Antenna

(Ref. Fig. 401/TASK 34-42-11-991-001-A)

NOTE : Use the old Teflon-Gasket unless it is damaged.

____

(1) Install the teflon-gasket (8) to the antenna (4).

(2) Remove the blanking caps from the electrical connectors.

(3) Install the new packing-preformed (6) packing - preformed (6), if

removed.

(4) Make sure that the electrical connectors are clean and in the correct
condition.

(5) Connect the coaxial connector (2) to the antenna connector (3).

(6) TORQUE the coaxial connector (2) to 0.265 m.daN (23.45 lbf.in) and
R safety it with MISCELLANEOUS (Material No. 19-009) or safety it with
one drop of BONDING AND ADHESIVE COMPOUNDS (Material No. 08-048) and
identification with safety-paint.

(7) Put the antenna (4) in position and install the screws (5) to the
fuselage structure.

NOTE : Make sure that the FWD sign or the datum mark on the antenna
____
points in the direction of flight.

(8) TORQUE the screws (5) to between 0.3 and 0.35 m.daN (26.54 and 30.97
lbf.in) diagonally opposite.

NOTE : The antenna mounting screws (5) give the electrical bonding
____
between the antenna (4) and the fuselage structure (1)
(Ref. TASK 20-28-00-912-005).

(9) Remove the unwanted sealant with a nonmetallic scraper.

(10) Remove the remaining masking tape.

(11) Make sure that the bonding contact resistance between the antenna (4)
and the fuselage structure (1) is not higher than 5 milliohms
(Ref. TASK 20-28-00-912-005).

(12) Make a sealing bead with SEALANTS (Material No. 09-016) around the
antenna (4).

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 (13) Apply SEALANTS (Material No. 09-016) to the heads of the screws (5).

(14) Make the contour of the sealant on the screws (5) and around the
antenna (4) smooth.

(15) Let the sealant cure.

(16) Apply STRUCTURE PAINTS (Material No. 16-003) to the sealant around
the base of the antenna (4).

R (17) Apply PAINTS FOR DETAIL (INTERNAL AND EXTERN AL) (Material No. 07-
R 001) to the sealant on the head of the screws (5).

R Subtask 34-42-11-420-054

R D. Installation of the Radio Altimeter Antenna (Alternative)

R (Ref. Fig. 402/TASK 34-42-11-991-003)

R (1) Apply the SPECIAL MATERIALS (Material No. 05-013) to the bottom of
R the antenna (4).

R (2) Apply the SEALANTS (Material No. 09-019) to the area of the fuselage
R that makes an interface with the antenna (4).

R (3) Remove the masking tape from the screw holes and the hole for the
R antenna connector.

R (4) Remove the blanking caps from the electrical connectors.

R (5) Install the new packing-preformed (6), if removed.

R (6) Make sure that the electrical connectors are clean and in the correct
R condition.

R (7) Connect the coaxial connector (2) to the antenna connector (3).

R (8) TORQUE the coaxial connector (2) to 0.265 m.daN (23.45 lbf.in) and
R safety it with MISCELLANEOUS (Material No. 19-009) (7) or safety it
R with one drop of BONDING AND ADHESIVE COMPOUNDS (Material No. 08-048)
R and identification with safety-paint.

R (9) Put the antenna (4) in position and install the screws (5) to the
R fuselage structure.

R NOTE : Make sure that the FWD sign or the datum mark on the antenna
____
R points in the direction of flight.

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R (10) TORQUE the screws (5) to between 0.3 and 0.35 m.daN (26.54 and 30.97
R lbf.in) diagonally opposite.

R NOTE : The antenna mounting screws (5) give the electrical bonding
____
R between the antenna (4) and the fuselage structure (1)
R (Ref. TASK 20-28-00-912-005).

R (11) Remove the unwanted sealant with a nonmetallic scraper.

R (12) Remove the remaining masking tape.

R (13) Make sure that the bonding contact resistance between the antenna (4)
R and the fuselage structure (1) is not higher than 5 milliohms
R (Ref. TASK 20-28-00-912-005).

R (14) Make a sealing bead with SEALANTS (Material No. 09-016) around the
R antenna (4).

R (15) Apply SEALANTS (Material No. 09-016) to the heads of the screws (5).

R (16) Make the contour of the sealant on the screws (5) and around the
R antenna (4) smooth.

R (17) Let the sealant cure.

R (18) Apply STRUCTURE PAINTS (Material No. 16-003) to the sealant around
R the base of the antenna (4).

R (19) Apply PAINTS FOR DETAIL (INTERNAL AND EXTERN AL) (Material No. 07-
R 001) to the sealant on the head of the screws (5).

Subtask 34-42-11-865-052

R E. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
FOR 5SA1(6SA1)
1SA1
FOR 5SA2(6SA2)
1SA2

Subtask 34-42-11-740-050

R F. Do the BITE test of the radio altimeter system (Ref. TASK 34-42-00-740-
002).

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 5. Close-up
________

Subtask 34-42-11-862-050

A. De-energize the ground service network

(Ref. TASK 24-42-00-862-001).

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 TRANSCEIVER - RADIO ALTIMETER (2SA1,2SA2) - REMOVAL/INSTALLATION
________________________________________________________________

TASK 34-42-33-000-001

Removal of the Radio Altimeter Transceiver 2SA1 and 2SA2

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific blanking caps

No specific circuit breaker(s) safety clip(s)
No specific access platform 2 m (6 ft. 7 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-42-00-861-001 Energize the Ground Service Network from the External

Power
52-30-00-860-001 Open the FWD or AFT Cargo-Compartment Door with the
Yellow Electric Pump
34-42-33-991-001 Fig. 401

3. __________
Job Set-up

Subtask 34-42-33-861-050

A. Energize the ground service network

(Ref. TASK 24-42-00-861-001)

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 Subtask 34-42-33-865-050

B. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
FOR 2SA1
121VU COM NAV/RAD ALTM/1 1SA1 K11
FOR 2SA2
121VU COM NAV/RAD ALTM/2 1SA2 K12

Subtask 34-42-33-010-050

C. Get Access

(1) Open the AFT Cargo Door 826. (Ref. TASK 52-30-00-860-001)

(2) Put the access platform at the aft cargo door 826.

R (3) Remove the access panel 152GW.

4. Procedure
_________

(Ref. Fig. 401/TASK 34-42-33-991-001)

Subtask 34-42-33-020-051

A. Removal of Radio Altimeter Transceiver

NOTE : The removal procedure is the same for the radio altimeter
____
transceiver 2SA1 and 2SA2.

(1) Loosen the knurled nuts (3) and lower the fasteners.

R (2) Carefully remove the transceiver (1) from the rack (2).

R NOTE : Make sure that you do not damage the electrical connector
____
R pins.

(3) Put blanking caps on the disconnected electrical connectors.

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R Radio Altimeter Transceiver
Figure 401/TASK 34-42-33-991-001

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 TASK 34-42-33-400-001

Installation of the Radio Altimeter Transceiver 2SA1 and 2SA2

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific access platform 2 m (6 ft. 7 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

22-97-00-710-001 Operational Test of the LAND CAT III Capability

24-42-00-861-001 Energize the Ground Service Network from the External
Power
24-42-00-862-001 De-energize the Ground Service Network Supplied from
the External Power
34-42-00-740-002 BITE Test of the Radio Altimeter
52-30-00-860-001 Open the FWD or AFT Cargo-Compartment Door with the
Yellow Electric Pump
52-30-00-860-002 Close the FWD or AFT Cargo-Compartment Door with the
Yellow Electric Pump
34-42-33-991-001 Fig. 401

3. __________
Job Set-up

Subtask 34-42-33-860-050

A. Aircraft Maintenance Configuration

(1) Make sure that the ground service network is energized

(Ref. TASK 24-42-00-861-001)

(2) Make sure that the AFT cargo-compartment door (Ref. TASK 52-30-00-
860-001) is open.

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R (3) Make sure that the access panel 152GW is removed.

(4) Make sure that the access platform is in position at the Aft cargo
door 826.

Subtask 34-42-33-865-051

B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and
tagged

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
FOR 2SA1
121VU COM NAV/RAD ALTM/1 1SA1 K11
FOR 2SA2
121VU COM NAV/RAD ALTM/2 1SA2 K12

4. Procedure
_________

(Ref. Fig. 401/TASK 34-42-33-991-001)

Subtask 34-42-33-420-050

A. Installation of the Radio Altimeter Transceiver

NOTE : The installation procedure is the same for the radio altimeter
____
transceiver 2SA1 and 2SA2.

(1) Clean the component interface and/or the adjacent area.

(2) Do an inspection of the component interface and/or the adjacent area.

(3) Remove the blanking caps from the electrical connectors.

(4) Make sure that the electrical connectors are clean and in the correct
condition.

(5) Carefully install the transceiver (1) into the rack (2).

NOTE : Make sure that the transceiver is correctly aligned to prevent

____
damage to the electrical connectors (4).

(6) Lift the fasteners and tighten the knurled nuts (3) until the
transceiver (1) is correctly attached.

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 Subtask 34-42-33-865-052

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
FOR 2SA1
1SA1
FOR 2SA2
1SA2

Subtask 34-42-33-740-050

C. Do the BITE test of the radio altimeter (Ref. TASK 34-42-00-740-002).

NOTE : If the aircraft is operated in actual CAT 3 conditions, you must

____
also do the LAND CAT III capability test: (Ref. TASK 22-97-00-710-
001).

5. Close-up
________

Subtask 34-42-33-860-051

A. Aircraft Maintenance Configuration

R (1) On the FTL CTL panel 23VU, push the FAC1 pushbutton switch (the OFF
R legend goes off.

R (2) On the FTL CTL panel 24VU, push the ELAC2 pushbutton switch (the OFF
R legend goes off.

Subtask 34-42-33-410-052

B. Close Access

(1) Make sure that the work area is clean and clear of tool(s) and other
items.

(2) Install the access panel 152GW.

(3) Remove the access platform(s).

(4) Close the AFT Cargo Door 826 (Ref. TASK 52-30-00-860-002).

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 Subtask 34-42-33-862-050

C. De-energize the ground service network

(Ref. TASK 24-42-00-862-001)

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 FAN - RADIO ALTIMETER TRANSCEIVER (3SA1,3SA2) - REMOVAL/INSTALLATION
____________________________________________________________________

TASK 34-42-45-000-001

Removal of the Radio Altimeter-Transceiver Fan 3SA1 (3SA2)

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific blanking caps

No specific circuit breaker(s) safety clip(s)
No specific access platform 2 m (6 ft. 7 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-42-00-861-001 Energize the Ground Service Network from the External

Power
52-30-00-860-001 Open the FWD or AFT Cargo-Compartment Door with the
Yellow Electric Pump
34-42-45-991-001 Fig. 401

3. __________
Job Set-up

Subtask 34-42-45-861-050

A. Energize the ground service network

(Ref. TASK 24-42-00-861-001)

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 Subtask 34-42-45-865-050

B. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
FOR 3SA1
121VU COM NAV/RAD ALTM/1 1SA1 K11
FOR 3SA2
121VU COM NAV/RAD ALTM/2 1SA2 K12

Subtask 34-42-45-010-050

C. Get Access
R

R (1) Open the AFT Cargo Door 826 (Ref. TASK 52-30-00-860-001).

R (2) Put the access platform at the aft cargo door 826.

(3) Remove the access panel 152HW.

4. Procedure
_________

(Ref. Fig. 401/TASK 34-42-45-991-001)

Subtask 34-42-45-020-052

A. Removal of the Radio Altimeter Transceiver Fan

NOTE : The procedure is the same for the radio altimeter-transceiver fans
____
3SA1 and 3SA2.

(1) Disconnect the electrical connector (8).

(2) Remove the screws (2), the washers (3) and remove the fan assembly
(1).

(3) Remove the nuts (6), the washers (5), the bolts (4), and remove the
cover (7).

(4) Disconnect the electrical connections (13).

(5) Put blanking caps on the disconnected electrical connectors.

(6) Remove the nuts (11), the washers (10) and the bolts (9).

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 Radio Altimeter-Transceiver Fan.
Figure 401/TASK 34-42-45-991-001

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 (7) Remove the blower (12).

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 TASK 34-42-45-400-001

Installation of the Radio Altimeter-Transceiver Fan 3SA1 (3SA2)

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific access platform 2 m (6 ft. 7 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-42-00-861-001 Energize the Ground Service Network from the External

Power
24-42-00-862-001 De-energize the Ground Service Network Supplied from
the External Power
R 34-42-00-750-001 Detailed Inspection and Operational Check of the
R Radio Altimeter Fan
52-30-00-860-001 Open the FWD or AFT Cargo-Compartment Door with the
Yellow Electric Pump
52-30-00-860-002 Close the FWD or AFT Cargo-Compartment Door with the
Yellow Electric Pump

3. __________
Job Set-up

Subtask 34-42-45-860-050

A. Aircraft Maintenance Configuration

(1) Make sure that the ground service network is energized

(Ref. TASK 24-42-00-861-001)

(2) Make sure that the Aft cargo-compartment door (Ref. TASK 52-30-00-
860-001) is open.

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 (3) Make sure that the access panel 152HW is removed.

(4) Make sure that the access platform is in position at the Aft cargo
door 826.

Subtask 34-42-45-865-051

B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and
tagged

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
FOR 3SA1
121VU COM NAV/RAD ALTM/1 1SA1 K11
FOR 3SA2
121VU COM NAV/RAD ALTM/2 1SA2 K12

4. Procedure
_________

Subtask 34-42-45-420-050

A. Installation of the Radio Altimeter Transceiver Fan

(1) Clean the component interface and/or the adjacent area.

(2) Do an inspection of the component interface and/or the adjacent area.

(3) Remove the blanking caps from the electrical connectors.

(4) Make sure that the electrical connectors are clean and in the correct
condition.

(5) Install the blower (12) with the bolts (9), the washers (10) and the
nuts (11).

(6) Connect the electrical connections (13).

(7) Install the cover (7) with the bolts (4), the washers (5) and the
nuts (6).

(8) Install the fan assembly (1) with the screws (2) and the washers (3).

(9) Connect the electrical connector (8).

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 Subtask 34-42-45-865-052

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
FOR 3SA1
1SA1
FOR 3SA2
1SA2

Subtask 34-42-45-750-050

C. Do the fan test of the radio altimeter system (Ref. TASK 34-42-00-750-
001).

5. Close-up
________

Subtask 34-42-45-410-050

A. Close Access

(1) Make sure that the work area is clean and clear of tool(s) and other
items.

(2) Install the access panel 152HW.

R (3) Remove the access platform(s).

R (4) Close the AFT Cargo Door 826 (Ref. TASK 52-30-00-860-002).
R

Subtask 34-42-45-862-050

B. De-energize the ground service network

(Ref. TASK 24-42-00-862-001)

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 FAN - RADIO ALTIMETER TRANSCEIVER (3SA1,3SA2) - CLEANING/PAINTING
_________________________________________________________________

TASK 34-42-45-100-001

Cleaning of the Radio Altimeter Transceiver Fan

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific air blower

No specific circuit breaker(s) safety clip(s)
No specific soft brush
No specific access platform 2 m (6 ft. 7 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

22-97-00-710-001 Operational Test of the LAND CAT III Capability

24-42-00-861-001 Energize the Ground Service Network from the External
Power
24-42-00-862-001 De-energize the Ground Service Network Supplied from
the External Power
34-42-00-740-002 BITE Test of the Radio Altimeter
34-42-00-750-001 Detailed Inspection and Operational Check of the
Radio Altimeter Fan
34-42-33-000-001 Removal of the Radio Altimeter Transceiver 2SA1 and
2SA2
34-42-33-400-001 Installation of the Radio Altimeter Transceiver 2SA1
and 2SA2
34-42-45-000-001 Removal of the Radio Altimeter-Transceiver Fan 3SA1
(3SA2)
34-42-45-400-001 Installation of the Radio Altimeter-Transceiver Fan
3SA1 (3SA2)
52-30-00-860-001 Open the FWD or AFT Cargo-Compartment Door with the
Yellow Electric Pump

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 -------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

52-30-00-860-002 Close the FWD or AFT Cargo-Compartment Door with the

Yellow Electric Pump

3. __________
Job Set-up

Subtask 34-42-45-861-051

A. Energize the ground service network

(Ref. TASK 24-42-00-861-001)

Subtask 34-42-45-865-053

B. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
FOR 3SA1
121VU COM NAV/RAD ALTM/1 1SA1 K11
FOR 3SA2
121VU COM NAV/RAD ALTM/2 1SA2 K12

Subtask 34-42-45-010-051

C. Get Access

(1) Open the AFT Cargo Door 826 (Ref. TASK 52-30-00-860-001).

(2) Put the access platform at the aft cargo door 826.

(3) Remove the access panel 152HW.

4. Procedure
_________

Subtask 34-42-45-020-053

A. Remove the radio altimeter units

(1) Remove the radio altimeter transceiver (Ref. TASK 34-42-33-000-001).

(2) Remove the radio altimeter transceiver fan (Ref. TASK 34-42-45-000-
001).

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 Subtask 34-42-45-100-052

B. Cleaning

(1) Use a soft brush and/or an air blower to clean the fan or the fan
housing.

NOTE : Make sure that the fan and the fan housing are blocked when
____
you use an air blower. Cleaning with an air blower can cause
exessive fan rotation speed and thus fan failure.

Subtask 34-42-45-420-051

C. Install the radio altimeter units

(1) Install the radio altimeter transceiver fan (Ref. TASK 34-42-45-400-
001).

(2) Install the radio altimeter transceiver (Ref. TASK 34-42-33-400-001).

Subtask 34-42-45-865-054

D. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
FOR 3SA1
1SA1
FOR 3SA2
1SA2

Subtask 34-42-45-710-051

E. Do the test

(1) Do the fan test of the radio altimeter system (Ref. TASK 34-42-00-
750-001).

(2) Do the Bite test of the radio altimeter (Ref. TASK 34-42-00-740-002).

NOTE : If the aircraft is operated in actual CAT 3 conditions, you

____
must also do the LAND CAT III capabillity test (Ref. TASK 22-
97-00-710-001).

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 5. Close-up
________

Subtask 34-42-45-410-052

A. Close Access

(1) Make sure that the work area is clean and clear of tool(s) and other
items.

(2) Install the access panel 152HW.

(3) Remove the access platform(s).

(4) Close the AFT Cargo Door 826 (Ref. TASK 52-30-00-860-002).

Subtask 34-42-45-862-051

B. De-energize the ground service network

(Ref. TASK 24-42-00-862-001)

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 TCAS (TRAFFIC COLLISION AVOIDANCE SYSTEM) - DESCRIPTION AND OPERATION
_____________________________________________________________________

R **ON A/C 001-004,

1. General
_______

A. Presentation
The TCAS II (Traffic Collision Avoidance System) is an optional system
whose function is to detect and display aircraft in the immediate
vicinity and to provide the flight crew with indications to avoid these
intruders by changing the flight path in the vertical plane only.
The TCAS periodically interrogates their transponders, computes their
trajectories and constantly determines their potential threat. The
acquisition of their signals is achieved by means of two transmit/receive
antennas, one located on the underside of the fuselage and the other on
the top.
The system can establish individualized communications with each aircraft
through ATC/Mode S transponders, thus permitting operation in dense
traffic areas while avoiding an overload of radio-electric transmissions
that would result from a general all-intruder response.
The TCAS II system is designed to provide the air traffic control system
with an additional possibility. It usually operates independently but may
be controlled from ground stations.
The TCAS has the capability to communicate with ATCRBS (Air Traffic
Control Radar Beacon System) ground stations equipped with the Mode S
system to indicate to them the vertical maneuver orders presented to the
aircraft pilot. This information can facilitate the task of the ground
station controller who, in turn, can modify the TCAS operating mode and
cancel the avoidance orders if he deems it necessary for safety.
The current surveillance envelope covers an area of plus or minus 2700 ft
in altitude and 14 NM minimum in range, but display range is authorized
up to 30 NM in range and plus or minus 1200 ft in altitude.
The system maintains surveillance within a sphere determined by the
transmit power and receiver sensitivity of the TCAS computer. The area in
which a threat is imminent depends on the speed and path of the own A/C
and the threat A/C.
There is an area defined as TAU within the surveillance arc which
represents the minimum time the flight crew needs to discern a collision
threat and take evasive action.
The TCAS detection capability covers an area of 30 NM in range and plus
or minus 9900 ft in altitude but display range is authorized up to plus
or minus 1200 ft in altitude.
(Ref. Fig. 001)

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 TCAS - Surveillance and Display
Figure 001

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R **ON A/C ALL

R Post SB 34-1179 For A/C 001-004,

1. General
_______

A. Presentation
The TCAS II (Traffic Collision Avoidance System) is an optional system
whose function is to detect and display aircraft in the immediate
vicinity and to provide the flight crew with indications to avoid these
intruders by changing the flight path in the vertical plane only.
The TCAS periodically interrogates their transponders, computes their
trajectories and constantly determines their potential threat. The
acquisition of their signals is achieved by means of two transmit/receive
antennas, one located on the underside of the fuselage and the other on
the top.
The system can establish individualized communications with each aircraft
through ATC/Mode S transponders, thus permitting operation in dense
traffic areas while avoiding an overload of radio-electric transmissions
that would result from a general all-intruder response.
The TCAS II system is designed to provide the air traffic control system
with an additional possibility. It usually operates independently but may
be controlled from ground stations.
The TCAS has the capability to communicate with ATCRBS (Air Traffic
Control Radar Beacon System) ground stations equipped with the Mode S
system to indicate to them the vertical maneuver orders presented to the
aircraft pilot. This information can facilitate the task of the ground
station controller who, in turn, can modify the TCAS operating mode and
cancel the avoidance orders if he deems it necessary for safety.
The system maintains surveillance within a sphere determined by the
transmit power and receiver sensitivity of the TCAS computer. The area in
which a threat is imminent depends on the speed and path of the own A/C
and the threat A/C.
There is an area defined as TAU within the surveillance arc which
represents the minimum time the flight crew needs to discern a collision
threat and take evasive action.
The TCAS detection capability covers an area of 30 NM in range and plus
or minus 9900 ft in altitude but display range is authorized up to plus
or minus 2700 ft in altitude.
(Ref. Fig. 001A)

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 TCAS - Surveillance and Display
Figure 001A

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R **ON A/C ALL

B. Principle
When an aircraft is airborne, its TCAS periodically transmits
interrogation signals for all ATCRBS and Mode S transponder-equipped
aircraft in the vicinity. These interrogations are received by the ATCRBS
ground stations and by the transponders of the other aircraft.
In response to these interrogations, the transponders of nearby aircraft
return signals containing their altitude value. The TCAS computes the
range between the two aircraft by measuring the elapsed time between
transmission of the interrogation and reception of the reply.
The altitude, altitude rate, range and range rate are determined by a
periodic tracking of these exchanges and the data are used for intruder
threat assessment.
Each threat is treated individually but the TCAS determines the best
collision avoidance possibility with respect to all aircraft in its
vicinity, while establishing maneuver coordination with the other
TCAS-equipped aircraft. The optimum maneuver is the one that ensures an
adequate separation of trajectories with a minimum vertical trend
variation.

C. Advisories
Visual and aural advisories are supplied by the TCAS computer whenever
assessment of the relative position of two aircraft reveals a potential
collision hazard.
The Traffic Advisories (TA) indicate the position of nearby aircraft
which are or may become a threat. Their display alerts the flight crew to
the presence of intruders and facilitates their visual acquisition.
The Resolution Advisories (RA) may be divided into two categories:
- Corrective Advisories that instruct the pilot to deviate from current
vertical rate
- Preventive Advisories that instruct the pilot to avoid certain
maneuvers.

D. Display
Visual indications are presented on the Electronic Flight Instrument
System (EFIS).
The Navigation Display (ND) is used to indicate the situation in the
nearby traffic area: a symbol is displayed for each intruder on the image
in the ARC or ROSE mode.
The avoidance maneuver indications, if any, are displayed on the vertical
speed scale of the Primary Flight Display (PFD) by means of a band of
colored sectors showing the vertical speed value to be adopted in order
to avoid any risk of collision.

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 E. Coordination
The avoidance maneuvers initiated by the TCAS could create a conflict
situation if directed at another TCAS-equipped aircraft as this aircraft
may also take similar evasive action, resulting in an unchanged
situation.
To avoid this situation, a communication link between the two aircraft is
established via the transponders, exchanging coordination messages.
The first aircraft to detect the other one initiates the communication
procedure, indicates the maneuvers it intends to perform and communicates
orders to the other aircraft requesting it to maintain its trajectory.
This necessarily involves the use of Mode S transponders, the only
equipment of this type possessing the LINK function required for data
exchange.
The Mode S transponders provide the capability to transmit a unique
address (24 bits) assigned to each aircraft, permitting them to reply
individually to other TCAS-equipped aircraft. It can respond to ground
station interrogations in Mode A and Mode C and also in Mode S if the
stations are suitably equipped.
With respect to aircraft equipped with Mode A transponders only, the TCAS
cannot generate resolution advisories as these transponders do not
communicate aircraft altitude. The aircraft are however displayed on the
ND, enabling their location in range and bearing, but with no altitude
indications.
The ground stations can modify the TCAS operating mode via the
transponder link so as to inhibit resolution advisories in certain
conditions.

2. Component
__________________
Location
(Ref. Fig. 002, 003)

-------------------------------------------------------------------------------
FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA
| | | | DOOR | REF.
-------------------------------------------------------------------------------
3SH CTL UNIT-ATC/TCAS 11VU 211 831 34-52-12
1SG CMPTR-TCAS 82VU 128 824 34-43-34
7SG1 ANTENNA-TCAS, TOP 230 34-43-11
7SG2 ANTENNA-TCAS, BOTTOM 130 34-43-11

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 TCAS - Component Location
Figure 002

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 INTENTIONALLY BLANK

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R TCAS Block Diagram - Data Acquisition
R Figure 003

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 3. System
__________________
Description
R (Ref. Fig. 003, 004)
The TCAS environment is composed of items closely associated with its
operation, such as the transponders and the EFIS display units and
peripherals supplying parameters or with maintenance functions.

A. TCAS Computer
The TCAS computer is the heart of the TCAS II system.
It ensures two main functions:
- a radio-electric transmission reception function in the L-band
frequency for intruder acquisition
- a processing function ensuring total operation control: digital,
discrete and analog-type interfaces, intruder trajectory computation
and tracking, visual and aural alert commands.

B. Directional Antennas
The TCAS has two antennas, one located on the top of the aircraft and the
other on the underside of the fuselage. These antennas, of the
transmit/receive type, provide azimuth information on aircraft located
within the TCAS surveillance range. They consist of four independent
elements. In reception, the amplitude of the signals received by each
element depends on the direction of the signal source, which permits the
relative bearing of the transmitting aircraft to be determined.

C. ATC/TCAS Control Unit

The ATC/TCAS control unit common to the ATC transponders and the TCAS,
enables the operating modes of these two items of equipment to be
selected. Information intended for the TCAS is transmitted via an ARINC
429 bus to the transponders which in turn transmit it to the TCAS
computer.
R

R D. Associated Items

R (1) ATC/Mode S transponders

R Two ATC/Mode S transponders, one active and the other on standby, are
R used with their antennas. Each transponder is linked to the TCAS by
R one high-speed ARINC 429 bus for transmission and another one for
R reception.
R Apart from the specific transponder functions (response to ATC ground
R station interrogations) they permit communication between the TCAS
R and a TCAS-equipped detected aircraft.

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R TCAS Block Diagram - Maintenance and Display
R Figure 004

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R (2) Displays
R Advisories are displayed by the Electronic Instrument System (EIS) by
R high speed transmission of ARINC 429 messages on the buses linking
R the TCAS to the DMCs 1 on one hand and to the DMC2 on the other hand.
R Depending on the EFIS DMC selection, the DMC 3 receives either the
R TA/RA display bus 1 (CAPT3/NORM positions) or the TA/RA display bus 2
R (FO3 position). The FWCs connected in parallel on these buses monitor
R the validity of the information.
R The NDs provide indications on the location of intruders in the
R traffic area. The PFDs provide the flight crew with vertical speed
R correction information to avoid them.
R The ECAM system also presents warning messages.

R E. Peripherals
R The TCAS receives information from the following equipment:

R (1) Radio altimeter

R The radio altitude is an essential parameter for the TCAS. In the 0
R to 2500 ft range it permits modulation of system sensitivity and
R triggering of inhibit orders. For this reason, two radio altimeters,
R one active and the other in standby, are linked to the TCAS via the
R low speed ARINC 429 bus.

R (2) Air data system

R Barometric altitude information fulfils the same functions as radio
R altitude information but for the range over 2500 ft. The ADIRU, which
R is not directly linked to the TCAS computer, transmits this
R information to the computer across the transponders via the ARINC 429
R buses.

R (3) Inertial reference system

R The TCAS is linked by a high speed ARINC 429 bus to the aircraft
R ADIRU1 which supplies it with magnetic heading and pitch and roll
R attitude information.

R (4) Landing Gear Control and Interface Unit (LGCIU)

R The LGCIU provides the TCAS with the following discrete signals:
R - ground/flight signal
R - landing gear extended signal.

R (5) Centralized Fault Display Interface Unit (CFDIU)

R The TCAS computer communicates with the Centralized Fault Display
R System (CFDS) via two low speed ARINC 429 buses.

R
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 (6) Data loader
It is possible to load software data into the TCAS computer by means
of a mobile data loader with remote loading capability linked by two
low speed ARINC 429 buses to a dedicated connector in the aircraft.

(7) Flight Data Interface Unit (FDIU)

The FDIU receives TCAS data from the DMC.
The following parameters are recorded by the FDIU:
- RA related information (label 270):
* advisory rate to maintain
* combined control
* vertical control
* up advisory
* down advisory
- manual sensitivity level (SL 0, 1, 2)
- TA issued or not.

(8) Various discrete signals

Discretes are used for the inhibition of certain advisories by
equipment with higher priority than the TCAS:
- advisory inhibit by the windshear signal
- advisory inhibit by the stall warning
- advisory inhibits by the ground proximity warning.

(9) Pin programming

Discrete pin program inputs are used:
- audio level to set the audio level of the synthetic voice output
- all traffic/threat traffic display at Threat Traffic indicates that
intruders are only displayed if a TA or RA is presented
- ground display mode: specifies that the display mode, when the
aircraft is on the ground, is the TA mode only
- display intruder limit: indicates the maximum number of intruders
that can be displayed (8)
- aircraft altitude limit, configured at 48,000 ft informs the TCAS
computer that it must inhibit climb orders above this altitude.

4. Power
____________
Supply
The TCAS is supplied with 115VAC, 100 watt power rating. The ATC/TCAS
control unit, common to the transponders and the TCAS, is also supplied with
115VAC:
- the 115VAC BUS1 101XP supplies the TCAS via circuit breaker 4SG
- the 115VAC SHED ESS BUS 801XP supplies the ATC1 system via circuit breaker
5SH1
- the 115VAC BUS2 204XP supplies the ATC2 system via circuit breaker 5SH2.
The ATC/TCAS control unit is energized through the two circuit breakers
5SH1 and 5SH2.
The system is supplied through these circuit breakers:

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 -------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV/ATC/1 5SH1 G11
121VU COM NAV/ATC/2 5SH2 K07

R **ON A/C 005-099,

121VU COM NAV/TCAS 4SG K10

**ON A/C ALL

5. _____________________
Component Description

A. TCAS Computer

(Ref. Fig. 005, 006)

(1) Introduction
The TCAS computer is divided into four major sections:
- Radio Frequency section (RF Assembly A6)
- Signal Processor (A4)
- Central Processing Unit (CPU A3)
- Input/Output Processor (I/O A2)

(2) Radio frequency section

(a) General
The RF section consists of receiver, transmitter and RF switch
portions.
The receiver processes the raw ATCRBS or Mode S intruder reply
data received from either the top or bottom antenna. The
transmitter portion of the RF section interrogates intruders once
per second, also using either antenna.
The RF switch portion selects the antenna (top or bottom) for the
transmission and reception of the TCAS signals.
For ATCRBS intruders, interrrogations are accomplished by
controlling a Wwhisper shoutW attenuation system which provides
successive responses, starting with the nearest aircraft and
continuing progressively to those farther away so as to avoid
saturating the radio-electric space and resulting interference.

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 TCAS Computer
R Figure 005

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 TCAS Computer - Block Diagram
R Figure 006

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 (b) Description

1
_ Transmitter
The transmitter is a solid-state circuit that develops 1030
MHz outputs. The TCAS transmitter/receiver has a
transmit/listen cycle of approximately 1 s intervals. A series
of increasing power mode C interrogations is first
transmitted. This is the whisper-shout sequence (4-pulse group
repeated with increasing power to 20 dB at 1 ms intervals).
Immediately following is a mode S interrogation modulated in
DPSK (Data Phase Shift Keyed) format. The remainder of the
1s-cycle is spent in listen mode.
After the whisper shout attenuator, the signal is fed through
diplexers, beam-steering networks and top/bottom antenna
switch. The beam-steering network generates and controls the
phase relationships of the four RF outputs from the
transmitter. These outputs are connected to the four elements
of the TCAS antenna.

2
_ Receiver
The receiver has four individual RF and IF sections, one for
each directional antenna segment. The receive frequency is
1090 MHz. The signal received from each antenna element is
passed through one of the four parallel top/bottom antenna
switches, beam-steering networks, transmit/receive switches,
then to four identical receiver RF circuits. These four
signals are further applied to mixer circuits to develop IF
signals (the local oscillator frequency used by the mixers is
1030 MHz from the transmitter sub-assembly). These IF signals
are amplified, filtered and applied to splitters for output to
the video processor.

3
_ Video processor
One output from each of the four signal splitters is
recombined and output as a video signal. This signal is used
to detect mode C and mode S data pulses. These items of
information are checked and invalid pulses eliminated so the
outputs of the video processor are mode C and mode S data. The
output from each signal splitter is applied to the bearing
detector.

4
_ Bearing detector
One of the IF signals is applied to one limiter as a reference
signal. Outputs of two other limiters are mixed with the
reference signal for phase detection. The resulting phase
detector outputs are dc signals whose levels are directly

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 proportional to the angle of arrival of the RF signal at the
antenna.

(3) Signal processor (A4)

The signal processor serves as an interface between the RF assembly
and the system software. It receives the three signal outputs from
the RF assembly: bearing information, mode S and mode C data.
The bearing data are converted into digital signals and applied to
the RAM. The mode S and C video signals are formatted, checked for
errors and applied to the RAM. Data from range counters are also
stored in the RAM. So in linking mode S and C data with bearing data,
the CPU is able to estimate the target aircraft range and bearing.
Additional tasks of the signal processor are: management of system
interface, buffer configuration, test, monitoring and fault
isolation, mode S and C interrogation/reply management.

(4) CPU card (A3)

The CPU is the computational center of the TCAS. The CPU is made up
of three microprocessors and associated circuits. It contains the
programs for analyzing data developed as a result of signals from
other transponders, and generates the traffic and resolution
advisories for the cockpit display. Intruder range, altitude and
bearing are calculated from received data. For TCAS equipped
intruders, a data link is established to coordinate resolution of the
threat condition.

(5) Input/output card (A2)

The input/output interface circuits handle the A/D, D/A, ARINC,
discrete and analog signal conversions required for communication
with external TCAS equipment.

(6) Data loader

A plug is installed next to the computer for the loading of the
operational program and I/O configuration data into the TCAS computer
via 2 ARINC 429 low speed buses, by means of a data loader.

B. ATC/TCAS Control Unit

For detailed description, Ref. 34-52-00, Para. 5.B.

C. TCAS Antennas

R (Ref. Fig. 007)

The directional antenna is composed of four passive vertically-polarized
elements. This high-strength composite antenna is provided with a curved
base (110 in), eight fuselage mounting screws and four color-coded
connectors used to coaxially connect the four antenna elements to the
TCAS computer.

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 TCAS Antenna
R Figure 007

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 A teflon gasket is located between the fuselage and the base of the
antenna, in order to facilitate the removal of the antenna.
An O-ring is provided to seal the antenna to the fuselage. The antenna is
used to receive and provide directional information for 1090 MHz Mode S
squitters, Mode S and Air Traffic Control Radar Beacon System (ATCRBS)
replies. Proper phasing of the four antenna elements enables omni or
directional transmission of 1030 MHz broadcast or coordination messages
and ATCRBS or Mode S interrogations.

6. Operation
_________

R (Ref. Fig. 008)

A. Intruder Detection
The TCAS detects A/C equipped with Mode S transponders by listening for
squitter transmissions. Mode S transponders announce their presence by
transmitting squitter messages once every second. The TCAS also detects
A/C equipped with transponders that do not reply to Mode S interrogations
but do reply to Mode C interrogations. The TCAS must actively search for
Mode C equipped intruder aircraft because Mode C transponders do not
transmit squitter messages. Once the presence of a Mode C intruder is
confirmed, it is tracked by the TCAS. The TCAS is capable of tracking up
to a combined total of 30 Mode S and Mode C intruders.
Tracking is performed by repetitive TCAS interrogations in Mode S and
Mode C format.

(1) Interrogation of aircraft equipped with Mode A or Mode C transponders

With respect to aircraft equipped with Mode A or Mode C transponders,
the TCAS is active and transmits Mode C only all-call interrogations
(P1, P3 and P4 pulses). The code is similar to the one used by the
Mode A and Mode C ground stations. The P4 pulse informs those Mode S
transponders that this interrogation is not addressed to them.
R (Ref. Fig. 009)
The nominal time interval between two interrogations is one second.
But, to limit radio-electric interference in dense traffic areas,
each interrogation consists of a series of interrogations of
increasing strength to reach more remote aircraft (whisper-shout)
with 1 ms time periods inside the series.
R (Ref. Fig. 010)
The first transmission consists of relatively low power P1, P3 and P4
pulses only.
Therefore, only the nearest aircraft will receive and reply to these
interrogations.

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 TCAS - Operation/Control and Indicating
R Figure 008

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 TCAS - Mode C Only All-Call Interrogation
R Figure 009

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 TCAS - Whisper-Shout Transmitter Sequence
R Figure 010

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 Then an S1 pulse is also transmitted. This pulse is at a lower
amplitude, causing the close-in aircraft to interpret this as a side
lobe from the transmitting station, requiring no reply. The purpose
of the whisper-shout sequence is to reduce the number of aircraft
replying to any one interrogation, thus limiting interference.

(2) Replies of aircraft equipped with Mode A or Mode C transponders

Aircraft equipped with Mode C transponders reply by transmitting
their altitude, octal encoded in four digits ABCD, with a value of
100 ft for the LSB in the ATCRBS format.
Aircraft equipped with Mode A transponders reply by transmitting
their Mode A identification code. In this case, intruder presentation
on the ND is limited to a display of its position in range and
bearing.
R (Ref. Fig. 011)

(3) Interrogation of aircraft equipped with Mode S transponders

(a) Transmission coding

The TCAS uses the Mode S function for certain identification of
intruders as a 24-bit address is definitively assigned to each
aircraft by air traffic control.
The interrogation comprises three pulses: P1, P2 and P6. P2 level
is equal to or greater than the P1 level, which is the no-reply
condition for the aircraft equipped with Mode A or C
transponders. Therefore, only Mode S transponders reply to the
interrogation.
The useful information is contained in P6 divided into 56 or 112
chips.
A chip is an unmodulated interval of 0.25 microseconds, preceded
by possible phase reversals.
The message formats contain a number of bits permitting a more
complete and diversified information exchange than in Mode C.
There are two distinct message formats:
- all Mode S interrogations (UPLINK format) are binary
differential phase shift keying (DPSK) signals
- Mode S replies (DOWNLINK format) are formed by pulse position
modulation (PPM) encoding the reply data.
R (Ref. Fig. 012)
The Mode S reply is preceded by a preamble containing four
pulses of specific duration and intervals intended to guarantee
received message validity. Any messages whose preamble is not
in complete conformity with the model are rejected by the TCAS.
This information is encoded in PPM mode with, for each bit, a
logic level one if the first half of the interval is at 1 and a
logic level zero if it is at zero.

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 TCAS - Mode C Reply
R Figure 011

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 TCAS - Mode S - Interrogation and Reply
R Figure 012

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 (b) Squitters
The Mode S transponder participates actively in its own detection
by transmitting signals, at one second intervals, intended to
inform nearby aircraft of its presence.
This transmission, called squitter transmission, consists of a
Format DF = 11 message, containing the Mode S 24-bit address
assigned to the aircraft, whereas all the bits of the message PI
field at zero indicates a squitter.

(c) Mode S communication messages

The Mode S ATC communications system supporting personalized
exchanges between ATC ground stations and Mode S
transponder-equipped aircraft comprises:
- a set of 25 standard messages for station-aircraft uplinks
(Uplink format) identified UFxx
- another set of 25 standard messages for downlinks (Downlink
format) identified DFxx.
The message may be long or short and contain either 56 or 112
bits.
Each message consists of specific fields with bit combinations
that have specific meanings. Two fields, however, have an
identical definition for all messages:
- the Wmessage-typeW field consisting of bits 1 to 5 whose coding
translates the format decimal value into binary
- the address field containing the last 24 bits of the message
(bits 33 to 56 or bits 89 to 112 depending on whether the
message is short or long). These 24 bits contain the Mode S
address of the transmitter.
The TCAS uses this bidirectional link capability to communicate
with other TCAS equipped aircraft to coordinate avoidance
maneuvers. It may also dialog with ground stations: these
stations have the possibility of monitoring and modifying its
action.
In the Mode S message set, the TCAS uses only six UF-type
messages and seven DF-type messages. These messages are:
- UF0, UF4, UF5, UF16, UF20, UF21
- DF0, DF4, DF5, DF11, DF16, DF20, DF21.
The following two figures give the list of messages used by the
TCAS for communications with other aircraft and with ground
stations.
They are followed by the definition of the fields used in the
messages.

NOTE : The TCAS only uses short messages (56 bits).

____

R (Ref. Fig. 013, 014)

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 TCAS - Message Uplink Format
R Figure 013

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 TCAS - Message Downlink Format
R Figure 014

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 DEFINITION OF UPLINK FORMAT MESSAGE FIELDS

-------------------------------------------------------------------------------
| DESIGNATOR | FIELD | INDICATION |
|-------------|----------------|----------------------------------------------|
| AP | ADDRESS PARITY | Coded address with parity check |
| AQ | ACQUISITION | Indicates if it is an interrogation message; |
| | | 1 = interrogation |
| DI | DESIGNATOR | Specifies type of information contained in SD|
| | IDENT | field |
| MA | MESSAGE | Used by ground station to transmit a TCAS SL |
| | Comm-A | command to a TCAS-equipped aircraft |
| MU | MESSAGE | Used by TCAS to transmit to other aircraft RA|
| | Comm-U | coordination information (under fields UDS, |
| | | MTB, CVC, VRC, CHC, HRC, HSB, VSB) |
| PC | PROTOCOL | Operating commands to the transponder |
| RL | REPLY LENGTH | Indicates if message is short (0) or long (1)|
| RR | REPLY REQUEST | Length and content of reply information |
| | | requested by the interrogator |
| SD | SPECIAL | Contains control codes affecting the |
| | DESIGNATOR | transponder protocol |
-------------------------------------------------------------------------------

DEFINITION OF DOWNLINK FORMAT MESSAGE FIELDS

-------------------------------------------------------------------------------
| DESIGNATOR | FIELD | INDICATION |
|-------------|----------------|----------------------------------------------|
| AA | ADDRESS | Mode S address in the clear in 24 bits |
| | ANNOUNCED | |
| AC | ALTITUDE CODE | Information indicating aircraft altitude |
| AP | ADDRESS PARITY | Coded address with parity check |
| CA | CAPABILITY | Transponder capability |
| DR | DOWNLINK | Requests extraction of downlink message by |
| | REQUEST | the interrogator (existing RA) |
| FS | FLIGHT STATUS | Flight status of the aircraft: ground, |
| | | flight, alert, SPI |
| ID | IDENTIFICATION | Contains the Mode A identification code |
| | CODE | |
| MB | MESSAGE | Indicates Advisory content to the ground |
| | Comm-B | station |
| MV | MESSAGE | Contains ARA, RAC, VDS subfields used for |
| | Comm-V | coordination |
| RI | REPLY | Type of reply and airspeed capability |
| | INFORMATION | |
| SL | SENSITIVITY | TCAS current sensitivity level |
| | LEVEL | |

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 -------------------------------------------------------------------------------
| DESIGNATOR | FIELD | INDICATION |
|-------------|----------------|----------------------------------------------|
| AA | ADDRESS | Mode S address in the clear in 24 bits |
| UM | UTILITY MESSAGE| Transponder status readouts |
| VS | VERTICAL STATUS| Aircraft status: 0 = airborne, 1 = ground |
-------------------------------------------------------------------------------

B. Measurement of Intruder Parameters

(1) Principle

(a) Determination of relative altitude

Upon confirmed transponder reception, the TCAS starts to
interrogate the intruder. Its altitude is transmitted directly in
the reply (standard barometric altitude) and this information is
used to determine the relative altitude of the two aircraft, by
calculating the barometric altitude difference.
This computation is, however, only possible with respect to Mode
C or Mode S transponder-equipped aircraft.
R (Ref. Fig. 015)

(b) Range measurement

The range is calculated by measuring the elapsed time between
transmission of the interrogation signal and return of the reply
transmitted by the intruder. Aircraft are detected from a minimum
range of 14 NM.

(c) Determination of Azimuth

There are several methods for calculating the angle of reception
of a radio-electric signal with respect to a reference direction
such as the aircraft centerline.
The TCAS utilizes a four-element antenna and a form of phase
interferometry to derive bearing from the received signal.
The interferometry principle is based on a comparison of signal
phases received by four independent elements of the directional
antenna.
For any given direction of reception, three antenna elements and
their corresponding receiver channels are used. The elements
which are used are the one physically positioned in the center of
the quadrant being interrogated and the elements adjacent to it.

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 TCAS - Relative Altitude Calculation Principle
R Figure 015

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 Two phase measurements are performed: one corresponding to the
difference in phase between the center element and the element on
its right, and one corresponding to the phase difference between
the center element and the element on its left. These two signals
are converted from analog to digital information and stored. The
bearing is calculated by reading the phase detector outputs,
taking the ratio of the phase detector outputs with respect to
each other, and performing a table lookup which relates the ratio
to the phase difference from beam center.

(d) Tracking
Once identified, the intruders are tracked by a series of
interrogation-replies in Mode C only all-call for Mode C
transponder-equipped aircraft, and in Mode S for Mode S
transponder-equipped aircraft.
These exchanges permit the TCAS to periodically update the
altitude, range and bearing data for each intruder and to compute
the range rate and altitude rate variations. These data are then
used to determine the time separating the two aircraft from their
closest point of approach.

(e) Broadcast messages

Every ten seconds, the TCAS transmits a broadcast message
intended to inform nearby aircraft, themselves equipped with a
TCAS, of the presence of a TCAS-equipped aircraft in their
traffic area.
These messages, received by the Mode S transponders, are
communicated to the TCAS computer to enable it to know the number
of TCAS-equipped aircraft in its detection envelope. This
information is then used in the interference limitation formulas
whose results modulate the Mode S interrogation output power
level in inverse proportion to the number of aircraft. This
reduces the number of non-elicited replies received by ground ATC
stations.
The messages transmitted are of the uplink format type UF = 16
with the Mode S 24 bit address of the interrogating TCAS included
in the MID field (bits 65 to 88) with the UDS field (bits 33 to
40) containing the code F50. No response is expected for this
type of message.

(f) Communications frequencies

Communications between two aircraft are always crossed between
transponder and TCAS. The TCAS transmits at a frequency of 1030
MHz to the transponder of the other aircraft, whose reply signals
are at a frequency of 1090 MHz to the TCAS receiver. This choice
allows system compatibility with ground station-transponder links
as the ground stations use the same frequencies as the TCAS.

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R (Ref. Fig. 016)

C. Coordination
Two TCAS-equipped aircraft must coordinate their maneuvers to avoid the
flight path corrections ordered by each TCAS resulting in a hazardous
situation.

(1) Coordination principle

In most cases of encounters between two TCAS-equipped aircraft,
mutual identification is almost but not quite simultaneous, with
sufficient time lag to establish the priority necessary for the
coordination process.
The first aircraft to detect a potentially dangerous configuration
computes a deviation maneuver sense and communicates it to the other
aircraft.
This aircraft takes the information into account and in turn computes
a correction.
If two aircraft detect each other at exactly the same time and
simultaneously transmit coordination messages containing incompatible
deviation senses it is, by convention, the aircraft that has the
highest Mode S address that cancels its trajectory correction. A time
delay in the display of orders on the display units avoids opposing
orders.

(2) Communications protocol

Communications between two aircraft comprises three phases:

(a) Detection phase

The TCAS receives squitter messages transmitted by the
transponder of the intruder aircraft. These are DF11-type
messages transmitted periodically at one second intervals and
intended to enable its detection and identification.
This message essentially uses two fields:
- an AA (Address Announced) field containing the Mode S address
which must be acknowledged
- A PI (parity interrogator Identity) field which is the result
of a parity encoding using a method of polynominal
multiplication. On reception, the Address Announced field is
multiplied by the same polynominal and the result is compared
with the received value.

(b) Surveillance phase

After detection, a surveillance phase starts. This phase is
composed of an acquisition part and a tracking part.

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 TCAS - Communication Principle
R Figure 016

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 INTENTIONALLY BLANK

R
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 INTENTIONALLY BLANK

R
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 1
_ Acquisition interrogation
When the TCAS receives a squitter and acquires the Mode S
address of the intruder it enters into contact by transmitting
a UFO-type message (Short special surveillance interrogation)
with the following specific fields:
- bit 9, RL = 0: reply message length requested short (56
bits)
- bit 14, AQ = 1: acquisition-type message indication.

2
_ Acquisition reply
The intruder<s transponder replies to this request by a DFO
message containing the following information:
- bit 6, VS :Vertical Status, = 1 if the aircraft is on the
ground, = 0 if the aircraft is airborne
- bits 9 to 11, SL :Sensitivity level indicates in which
sensitivity level its TCAS is operating
- bits 14 to 17, RI :combinations of bits, from values 8 to
15, specify the maximum speed the aircraft can reach. The
other combinations are not used
- bits 20 to 32, AC :aircraft altitude code indicating the
barometric altitude.

3
_ Tracking interrogation
After its acquisition, the intruder is tracked by UFO-type
interrogations with the following field values:
- RL = 0: reply message length requested short
- AQ = 0: not an acquisition message.

4
_ Tracking reply
The intruder<s transponder replies with a DFO message
indicating altitude and TCAS sensitivity level by a
combination of fields SL and RI:
- SL: bits 9 to 11
- RI: bits 14 to 17, combination values 0 to 7. Values 8 to 15
are not used
- AC: bits 20 to 32, aircraft altitude code.

(c) Coordination phase

If the intruder becomes a threat, the TCAS programs a deviation
maneuver to avoid a risk of collision. A coordination procedure
is initiated between the two aircraft with an exchange of the
following messages:

1
_ Coordination interrogation
The TCAS transmits a UF16 Long Special Surveillance message
whose fields contain the following indications:

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 ---------------------------------------------------------------------
| BITS | FIELD | INDICATION |
|-------|-------|---------------------------------------------------|
| 9 | RL | = 1: reply message length requested long |
| 14 | AQ | = 0: non-acquisition type interrogation |
| 33-40 | UDS | U Definition Subfield - defines the other data |
| | | in the MU field (Comm-U), composed of bits 42 |
| | | to 88 |
| 42 | MTB | Indicates multiple threat processing |
| 43-44 | CVC | Cancel Vertical resolution advisory Complement - |
| | | used to cancel an RA complement sent earlier to |
| | | an intruder |
| 45-46 | VRC | Vertical Resolution advisory Complement - used to|
| | | transmit an RA vertical complement to the intru- |
| | | der requesting it not to modify its trajectory |
| | | (don<t climb, don<t descend) |
| 47-49 | CHC | Cancel Horizontal resolution advisory Complement-|
| | | not used in TCAS II |
| 50-52 | HRC | Horizontal Resolution advisory Complement - not |
| | | used in TCAS II |
| 53-55 | | not used |
| 56-60 | HSB | Encoded Sense bits for Horizontal resolution |
| | | advisory complement - not used in TCAS II |
| 61-64 | VSB | Encoded Sense Bits for Vertical resolution advi- |
| | | sory complement - parity code to protect the 4 |
| | | vertical command bits (43-46) |
| 65-88 | MID | Interrogator TCAS-equipped aircraft Mode S |
| | | address. |
---------------------------------------------------------------------

2
_ Coordination reply
After acquisition of this message, the intruder<s transponder
replies with a Long Special Surveillance DF 16 type message,
containing the information previously transmitted to it by its
own TCAS:

---------------------------------------------------------------------
| BITS | FIELD | INDICATION |
|-------|--------|--------------------------------------------------|
| 6 | VS | Vertical Status - indicates whether aircraft is |
| | | on ground or airborne |
| 9-11 | SL | With RI, SL indicates the sensitivity level at |
| | | which the interrogated aircraft<s TCAS is |
| | | operating |
| 14-17 | RI | Reply Information |
| 20-32 | AC | Altitude Code - contains aircraft altitude |
| | | encoded in 100 ft increments if bit 28 equals 0, |

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 ---------------------------------------------------------------------
| BITS | FIELD | INDICATION |
|-------|--------|--------------------------------------------------|
| | | and in 25 ft increments if bit 28 equals 1 |
| 33-40 | VDS | V Definition Subfield defines the contents of the|
| | | data and coding in the field MV (Comm V) composed|
| | | of bits 41 to 88 |
| 41-54 | ARA | Active Resolution Advisory - indicates the RA |
| | | type currently generated by the TCAS |
| 55-58 | RAC | Resolution Advisory Complement - Indicates the RA|
| | | complement type currently received from other |
| | | TCAS-equipped aircraft |
| 59-88 | | Not used |
--------------------------------------------------------------------

(d) Correspondence of radio messages with ARINC 429 words

The coordination information exchanged between two aircraft
transits via ARINC 429 buses linking the transponder to the TCAS.
The following table gives the correspondence between the two
types of link:

---------------------------------------------------
| 1 - TRANSPONDER TO TCAS |
|-------------------------------------------------|
| | RADIO MESSAGE | ARINC MESSAGE |
|---------|-------------------|-------------------|
| FIELD | MESSAGE | BITS | LABEL | BITS |
|---------|---------|---------|---------|---------|
| MTB | UF16 | 42 | 271 | 09 |
| CVC | | 43-44 | | 10-11 |
| VRC | | 45-46 | | 12-13 |
| CHC | | 47-49 | | 14-16 |
| HRC | | 50-52 | | 17-19 |
| HSB | | 56-60 | | 20-24 |
| VSB | | 61-64 | | 25-28 |
---------------------------------------------------

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 ---------------------------------------------------
| 2 - TCAS TO TRANSPONDER |
|-------------------------------------------------|
| | RADIO MESSAGE | ARINC MESSAGE |
|---------|-------------------|-------------------|
| FIELD | MESSAGE | BITS | LABEL | BITS |
|---------|---------|---------|---------|---------|
| SL | DF16 | 09-11 | 274 | 23-25 |
| RI | | 14-17 | | 26-29 |
| ARA | | 41-54 | 273 | 12-25 |
| RAC | | 55-58 | | 26-29 |
---------------------------------------------------

D. Principles of Computation
In the TCAS, target aircraft are categorized depending on specific
criteria varying in function of altitude.
The TCAS essentially uses two types of information to perform this
classification:
- the relative altitude between two aircraft, known by the difference of
their barometric altitudes
- the distance or range separating them.
R (Ref. Fig. 017)
Acquisition of these two parameters at regular intervals (tracking)
enables their variations to be calculated:
- altitude rate
- range rate.
Assessment of the potential threat represented by an intruder depends
on two criteria determined with respect to a point in the traffic area
called Closest Point of Approach (CPA).
This is the point of minimum distance between the two aircraft,
assuming that their trajectories do not deviate.
The two criteria are:
- vertical separation at CPA
- time left before reaching CPA.

(1) Projected vertical separation

The threat is evaluated by calculating the vertical separation
between the two aircraft at the closest point of approach.
R (Ref. Fig. 018)
The TCAS computer processes the current altitude and altitude rate of
the intruder to predict whether it will be within limits considered
dangerous at the closest point of approach.
Intruder 1 penetrates the altitude zone delimited by the upper and
lower thresholds but when it reaches CPA, it will be outside this
zone.
Therefore no advisory will be issued.

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 TCAS - Definition of Main Parameters
R Figure 017

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 TCAS - Threat Evaluation
R Figure 018

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 However, when intruder 2 reaches CPA it is still inside this zone and
therefore an advisory will be issued.

(2) Time to intercept (TAU)

The TCAS does not need to locate the CPA in space, but rather it
needs to know the time to intercept for two aircraft. For example, if
two aircraft are approaching on the same axis on a collision course,
this time is the ratio of distance between them to the sum of their
speeds.
D
T = ---------
V1 + V2
More generally, the TCAS uses range and range rate measurement to
compute this time:
RANGE R(NM)
TAU = ------------ i.e. TAU(s) = 3600 --------
RANGE RATE RR (Kts)
With the risk of collision being in inverse proportion to this time,
trajectory correction orders are initiated by crossing predetermined
time thresholds whose values depend on the altitude layer in which
the aircraft is located.
This method of calculation avoids the initiation of corrections if,
from a certain distance, the TAU trend is inverted even though the
distance separating the two aircraft decreases. For example, in the
case of two aircraft moving on parallel axes but in the opposite
direction.
R (Ref. Fig. 019, 020)
The curve represents the TAU variation before the closest point of
approach.
R (Ref. Fig. 020)
This time decreases as the range decreases, reaches a minimum when
the intruder<s relative bearing is 45 deg. and then increases
rapidly. If the time corresponding to a predetermined threshold has
not been reached before the minimum TAU value, a trajectory
correction will not be initiated.
Certain conditions exist, however, in which this formula may prove
insufficient. This may arise for example when two aircraft fly in the
same direction with a very low closure rate. In this case, the
range/range rate ratio gives a high TAU value whereas in fact, the
two aircraft could be very near.
The TCAS uses a slightly different formula to preclude this
situation:
range - X (DMOD) to the power two
TAU = ---------- with X = ---------
range rate range

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 TCAS - TAU Minimum Configuration
R Figure 019

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 TCAS - TAU Curve
R Figure 020

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 This formula represents an estimate of the time the aircraft would
take to penetrate a sphere around the intruder with a radius equal to
(DMOD)expnt2/range. The DMOD coefficients are in function of
altitude, ranging from 0.20 NM for 1000-2350ft, to 1.1 NM above
20,000 ft as shown below:
Altitude DMOD
(ft) (NM)
0-1000
1000-2350 0.20
2350-5000 0.35
5000-10000 0.55
10000-20000 0.80
more than 20000 1.10

R **ON A/C 001-004,

E. Definition of Target Aircraft

Target aircraft are divided into four categories: OTHER - PROXIMATE -
TRAFFIC ADVISORY (TA) - RESOLUTION ADVISORY (RA).

(1) Other aircraft

Depending on the Above/Below selection, targets are defined as other
intruders if their:
- altitude is between 2700 ft and 7000 ft above or below the TCAS
equipped aircraft
- distance is more than 14 NM.
Their presentation on the ND is permanent (TFC function selected =
full time display function activated) or conditioned by the
presence of a TA/RA intruder (TA or TA/RA function selected).
Depending on their trajectory, they may:
- conserve this status and move away without an advisory being
declared.
In this case the pilot is informed of their presence on the ND by a
white outlined diamond symbol and can monitor their progress, or
- have a trajectory liable to lead to a conflict situation and in
this case they require a new category and a symbol change.

(2) Proximate aircraft

Targets are defined as proximate traffic if the difference between
their altitude and that of the TCAS aircraft is less than 1200 ft and
if their range is within 6 NM.
Their presentation on the ND is permanent (TFC function selected =
full time display function activated) or conditioned by the presence
of a TA/RA intruder (TA or TA/RA function selected).
Generally aircraft not in the immediate vicinity enter into this
category.

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 Depending on their trajectory, they may:
- conserve this status and move away without an advisory being
declared.
In this case the pilot is informed of their presence on the ND by a
white filled diamond symbol and can monitor their progress, or
- have a trajectory liable to lead to a conflict situation and in
this case they require a traffic advisory and their symbol changes.

(3) Traffic advisory aircraft

R (Ref. Fig. 021)

When an intruder is relatively near but does not represent an
immediate threat the TCAS issues a traffic advisory. Its presence is
displayed on the ND by an amber filled circle. Its display is
accompanied by an aural alert:
WTraffic TrafficW.
The pilot is therefore aware of its presence and knows its range and
relative bearing. Its display is linked to vertical separation and
time TAU before CPA values.
Depending on its trajectory, an intruder may conserve this status and
move away, or it may become a collision threat. In this case
avoidance maneuvers are suggested to the pilot via a resolution
advisory.

(4) Resolution advisory aircraft

R (Ref. Fig. 021)

In resolution displays, the intruder is represented on the ND by a
red filled square and corrective orders are issued on the vertical
speed scale of the PFD. Crossing into resolution advisory occurs for
a TAU time threshold 10 to 15 seconds lower than a traffic advisory
threshold.
Vertical separation between the two aircraft is also taken into
account for this category. There are two types of resolution
advisory, in function of the vertical separation value:
- Preventive Advisories
- Corrective Advisories.

(a) Preventive Advisory

In this case the vertical separation is less than a threshold S1
and greater than a threshold S2. The advisory instructs the pilot
to avoid certain deviations from current vertical rate, this
measure being sufficient to avoid a risk of collision. On the PFD
speed scale, the forbidden values are indicated by red sectors.

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 TCAS - Threat Threshold Scale
R Figure 021

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 (b) Corrective advisory
In this case, the vertical separation is lower than the threshold
S2.
On the vertical speed scale of the PFD, colored sectors depict
avoidance maneuvers to be performed:
- red sector = forbidden vertical speeds
- green Wfly toW sector = a vertical speed range to be respected.

(Ref. Fig. 021)

R **ON A/C ALL

R Post SB 34-1179 For A/C 001-004,

E. Definition of Target Aircraft

Target aircraft are divided into four categories: OTHER - PROXIMATE -
TRAFFIC ADVISORY (TA) RESOLUTION ADVISORY (RA).

(1) Other aircraft

Depending on the Above/Below selection, targets are defined as other
intruders if their:
- altitude is between 1200 ft and 9900 ft above or below the TCAS
equipped aircraft
- distance is more than 14 NM.
Their presentation on the ND is permanent (TFC function selected =
full time display function activated) or conditioned by the
presence of a TA/RA intruder (TA or TA/RA function selected).
Depending on their trajectory, they may:
- conserve this status and move away without an advisory being
declared.
In this case the pilot is informed of their presence on the ND by a
white outlined diamond symbol and can monitor their progress, or
- have a trajectory liable to lead to a conflict situation and in
this case they require a new category and a symbol change.

(2) Proximate aircraft

Targets are defined as proximate traffic if the difference between
their altitude and that of the TCAS aircraft is less than 1200 ft and
if their range is within 6 NM.
Their presentation on the ND is permanent (TFC function selected =
full time display activated) or conditioned by the presence of a
TA/RA intruder (TA or TA/RA function selected)
Generally aircraft not in the immediate vicinity enter into this
category.
Depending on their trajectory, they may:
- conserve this status and move away without an advisory being
declared.

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 In this case the pilot is informed of their presence on the ND by a
white filled diamond symbol and can monitor their progress, or
- have a trajectory liable to lead to a conflict situation and in
this case they require a traffic advisory and their symbol changes.

(3) Traffic advisory aircraft

(Ref. Fig. 021)

When an intruder is relatively near but does not represent an
immediate threat the TCAS issues a traffic advisory. Its presence is
displayed on the ND by an amber filled circle. Its display is
accompanied by an aural alert:
WTraffic TrafficW.
The pilot is therefore aware of its presence and knows its range and
relative bearing. Its display is linked to vertical separation and
time TAU before CPA values.
Depending on its trajectory, an intruder may conserve this status and
move away, or it may become a collision threat. In this case
avoidance maneuvers are suggested to the pilot via a resolution
advisory.

(4) Resolution advisory aircraft

(Ref. Fig. 021)

In resolution displays, the intruder is represented on the ND by a
red filled square and corrective orders are issued on the vertical
speed scale of the PFD. Crossing into resolution advisory occurs for
a TAU time threshold 10 to 15 seconds lower than a traffic advisory
threshold.
Vertical separation between the two aircraft is also taken into
account for this category. There are two types of resolution
advisory, in function of the vertical separation value:
- Preventive Advisories
- Corrective Advisories.

(a) Preventive Advisory

In this case the vertical separation is less than a threshold S1
and greater than a threshold S2. The advisory instructs the pilot
to avoid certain deviations from current vertical rate, this
measure being sufficient to avoid a risk of collision. On the PFD
speed scale, the forbidden values are indicated by red sectors.

(b) Corrective advisory

In this case, the vertical separation is lower than the threshold
S2.
On the vertical speed scale of the PFD, colored sectors depict
avoidance maneuvers to be performed:

R
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 - red sector = forbidden vertical speeds
- green Wfly toW sector = a vertical speed range to be respected.

R (Ref. Fig. 021)

**ON A/C 001-004,

(c) Aural alerts

Trajectory correction or holding visual orders are accompanied by
synthesized voice announcements whose level cannot be adjusted by
the pilot. These announcements are generated by the TCAS computer
and broadcast via the cockpit loud speakers. These messages and
their meanings are described below:
- WCLIMB, CLIMB, CLIMBW.
Climb at the rate shown by the green sector on the PFD (1500
ft/mn),
- WCLIMB, CROSSING CLIMB, CLIMB, CROSSING CLIMBW.
As above except that it further indicates that own flight path
will cross through that of the intruder,
- WREDUCE CLIMB, REDUCE CLIMBW.
Reduce vertical speed to that shown by the green sector on the
PFD,
- WINCREASE CLIMB, INCREASE CLIMBW
Follows a WclimbW advisory. The vertical speed of the aircraft
should be increased (2500 ft/mn),
- WCLIMB, CLIMB NOW, CLIMB, CLIMB NOWW.
Follows a WdescendW advisory when a reversal in sense is
required to achieve safe vertical separation from a maneuvering
intruder,
- WDESCEND, DESCEND, DESCENDW
Descend at the rate indicated by the green sector on the PFD
(-1500 ft/mn),
- WDESCEND, CROSSING DESCEND, DESCEND, CROSSING DESCENDW
As above except that it further indicates that own flight path
will cross through that of the intruder,
- WREDUCE DESCENT, REDUCE DESCENTW
Reduce vertical speed to that shown by the green sector on the
PFD,
- WINCREASE DESCENT, INCREASE DESCENTW
Follows a WdescendW advisory. The vertical speed of the descent
should be increased (-2500 ft/mn),
- WDESCEND, DESCEND NOW, DESCEND, DESCEND NOWW
Follows a WclimbW advisory when a reversal in sense is required
to achieve safe vertical separation from a maneuvering
intruder.
Two other aural advisories are also generated:

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 - WMONITOR VERTICAL SPEED, MONITOR VERTICAL SPEEDW
Indicates that a forbidden vertical speed range exists (red
sector) and that pilot must monitor vertical speed so as not to
enter this range (Preventive Advisory).
This message is spoken only once if softening from a previous
corrective advisory,
- WCLEAR OF CONFLICTW
Indicates that separation has been achieved and range has
started to increase.
R

R **ON A/C ALL

R Post SB 34-1179 For A/C 001-004,

(c) Aural alerts

Trajectory correction or holding visual orders are accompanied by
synthesized voice announcements whose level cannot be adjusted by
the pilot. These announcements are generated by the TCAS computer
and broadcast via the cockpit loud speakers. These messages and
their meanings are described below:

- WCLIMB, CLIMBW:
Climb at the rate shown by the green sector on the PFD (1500
ft/min),

- WCLIMB, CROSSING CLIMB, CLIMB, CROSSING CLIMBW:

As above except that it further indicates that own flight path
will cross through that of the intruder,

- WINCREASE CLIMB, INCREASE CLIMBW:

Follows a WclimbW advisory. The vertical speed of the aircraft
should be increased (2500 ft/min),

- WCLIMB, CLIMB NOW, CLIMB, CLIMB NOWW:

Follows a WdescendW advisory when a reversal in sense is
required to achieve safe vertical separation from a maneuvering
intruder,

- WDESCEND, DESCENDW:
Descend at the rate indicated by the green sector on the PFD
(-1500 ft/min),

- WDESCEND, CROSSING DESCEND, DESCEND, CROSSING DESCENDW:

As above except that it further indicates that own flight path
will cross through that of the intruder,

R
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 - WINCREASE DESCENT, INCREASE DESCENTW:
Follows a WdescendW advisory. The vertical speed of the descent
should be increased (-2500 ft/min),

- WDESCEND, DESCEND NOW, DESCEND, DESCEND NOWW:

Follows a WclimbW advisory when a reversal in sense is required
to achieve safe vertical separation from a maneuvering
intruder,

- WADJUST VERTICAL SPEED, ADJUSTW:

Reduce vertical speed to that shown by the green sector on the
PFD.
It can correspond to a corrective reduce climb or reduce
descent.
It can also represent a weakening of corrective RA.

Four other aural advisories are also generated:

- WMONITOR VERTICAL SPEEDW:

Indicates that a forbidden vertical speed range exists (red
sector) and that pilot must monitor vertical speed so as not to
enter this range (Preventive Advisory).

- WMAINTAIN VERTICAL SPEED, MAINTAINW:

Indicates a non-crossing advisory type, maintains rate RA<s
(corrective).

- WMAINTAIN VERTICAL SPEED, CROSSING MAINTAINW:

Indicates an altitude crossing advisory type, maintains rate
RA<s (corrective).

These messages are spoken only once if softening from a

previous corrective advisory,

- WCLEAR OF CONFLICTW:
Indicates that separation has been achieved and range has
started to increase.

R **ON A/C 001-004,

R (5) Advisory inhibit conditions

R In certain particular conditions, certain advisories are not
R generated as they could lead to the pilot adopting flight conditions
R that are hazardous or outside the aircraft<s performance capability.

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R (a) Low altitude inhibitions
R Ground proximity leads to the inhibition of those advisories
R liable to cause a hazardous situation at this level. In
R decreasing altitude, these are:
R - below 1450 ft above ground level (AGL) inhibition of WIncrease
R DescendW resolution advisories (RA)
R - below 1200 ft AGL at take-off and 1000 ft AGL in approach,
R inhibition of WDescendW resolution advisories (RA)
R - below 1100 ft AGL at take-off and 900 ft AGL in approach,
R inhibition of all aural traffic advisories (TA) and all
R resolution advisories (RA).

R (b) High altitude inhibition

R Above 48,000 ft, further climb orders are inapplicable as the
R aircraft performance capability does not permit them to be taken
R into account.
R WClimbW advisories are therefore inhibited above this altitude.

R (c) Advisory inhibit discretes

R Three discretes are used to manage priority between:
R - windshear/stall
R - GPWS - G/S
R - and the TCAS computer.
R The environmental alert priorities are: windshear/stall, GPWS -
R G/S and then TCAS II.
R When TCAS II is inhibited, the TA ONLY mode is selected and the
R voice announcements are cancelled.

R (d) Rejection of signals from aircraft on ground

R (Ref. Fig. 022)
R Aircraft on the ground may reply to TCAS interrogations,
R producing an unnecessary overload in the processing and display
R of information. The ground logic Waircraft declared on the
R groundW is enabled when the own aircraft descends below 1650 ft
R AGL and when it climbs up to 1750 ft AGL.
R All on-ground intruders are displayed as non-threat traffic white
R unfilled diamond.
R Intruders are declared to be on-ground if they are within 380 ft
R from the ground when descending, and if they are within 400 ft
R from the ground when climbing.
R Intruders declared to be on-ground can never cause proximate,
R traffic or resolution advisory.
R But, as the altitude transmitted by the intruder is a barometric
R altitude with respect to sea level, the TCAS shall process this
R value to convert it into height above ground level in order to
R compare it with the 380 ft (+ or - 20 ft) threshold.

R
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 TCAS - Inhibition Condition
Figure 022

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R (e) Rejection of non altitude reporting aircraft by the own aircraft
R The TCAS does not display Wnon altitude reporting aircraftW above
R 15,500 ft MSL.

R **ON A/C 005-099,

(5) Advisory inhibit conditions

In certain particular conditions, certain advisories are not
generated as they could lead to the pilot adopting flight conditions
that are hazardous or outside the aircraft<s performance capability.

(a) Low altitude inhibitions

Ground proximity leads to the inhibition of those advisories
liable to cause a hazardous situation at this level. In
decreasing altitude, these are:
- below 1550 plus or minus 100 ft above ground level (AGL),
inhibition of WIncrease DescendW resolution advisories (RA),
- below 1100 plus or minus 100 ft AGL, inhibition of WDescendW
resolution advisories (RA),
- below 500 plus or minus 100 ft (600 ft in climb, 400 ft in
descent), inhibition of all resolution advisories (RA) and
inhibitions of aural traffic advisories (TA).

(b) High altitude inhibition

Above 48,000 ft, further climb orders are inapplicable as the
aircraft performance capability does not permit them to be taken
into account.
WClimbW advisories are therefore inhibited above this altitude.

(c) Advisory inhibit discretes

Four discretes are used to manage priority between:
- windshear/stall,
- predictive windshear,
- GPWS - G/S,
- and the TCAS computer.
The environmental alert priorities are: windshear/stall,
predictive windshear, GPWS - G/S and then TCAS II.
When TCAS II is inhibited, the TA ONLY mode is selected and the
voice announcements are cancelled.

(d) Rejection of signals from aircraft on ground

(Ref. Fig. 022)
Aircraft on the ground may reply to TCAS interrogations,
producing an unnecessary overload in the processing and display
of information. The ground logic Waircraft declared on the

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 groundW is enabled when the own aircraft descends below 1650 ft
AGL and when it climbs up to 1750 ft AGL.
All on-ground intruders are displayed as non-threat traffic white
unfilled diamond.
Intruders are declared to be on-ground if they are within 380 ft
from the ground when descending, and if they are within 400 ft
from the ground when climbing.
Intruders declared to be on-ground can never cause proximate,
traffic or resolution advisory.
But, as the altitude transmitted by the intruder is a barometric
altitude with respect to sea level, the TCAS shall process this
value to convert it into height above ground level in order to
compare it with the 380 ft (plus or minus 20 ft) threshold.

(e) Rejection of non altitude reporting aircraft by the own aircraft

The TCAS does not display Wnon altitude reporting aircraftW above
15,500 ft MSL.

R **ON A/C 001-004,

R Post SB 34-1179 For A/C 001-004,

R (5) Advisory inhibit conditions

R In certain particular conditions, certain advisories are not
R generated as they could lead to the pilot adopting flight conditions
R that are hazardous or outside the aircraft<s performance capability.

R (a) Low altitude inhibitions

R Ground proximity leads to the inhibition of those advisories
R liable to cause a hazardous situation at this level. In
R decreasing altitude, these are:
R - below 1550 plus or minus 100 ft above ground level (AGL),
R inhibition of WIncrease DescendW Resolution Advisories (RA),
R - below 1100 plus or minus 100 ft AGL, inhibition of WDescendW
R RA,
R - below 500 plus or minus 100 ft (600 ft in climb, 400 ft in
R descent), inhibition of all RA and inhibitions of aural Traffic
R Advisories (TA).

R (b) High altitude inhibition

R Above 48,000 ft, further climb orders are inapplicable as the
R aircraft performance capability does not permit them to be taken
R into account.
R WClimbW advisories are therefore inhibited above this altitude.

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R (c) Advisory inhibit discretes
R Three discretes are used to manage priority between:
R - windshear/stall,
R - GPWS - G/S,
R - and the TCAS computer.
R The environmental alert priorities are: windshear/stall, GPWS -
R G/S and then TCAS II.
R When TCAS II is inhibited, the TA ONLY mode is selected and the
R voice announcements are cancelled.

R (d) Rejection of signals from aircraft on ground

R (Ref. Fig. 022)
R Aircraft on the ground may reply to TCAS interrogations,
R producing an unnecessary overload in the processing and display
R of information. The ground logic Waircraft declared on the
R groundW is enabled when the own aircraft descends below 1650 ft
R AGL and when it climbs up to 1750 ft AGL.
R All on-ground intruders are displayed as non-threat traffic white
R unfilled diamond.
R Intruders are declared to be on-ground if they are within 380 ft
R from the ground when descending, and if they are within 400 ft
R from the ground when climbing.
R Intruders declared to be on-ground can never cause proximate,
R traffic or resolution advisory.
R But, as the altitude transmitted by the intruder is a barometric
R altitude with respect to sea level, the TCAS shall process this
R value to convert it into height above ground level in order to
R compare it with the 380 ft (plus or minus 20 ft) threshold.

R (e) Rejection of non altitude reporting aircraft by the own aircraft

R The TCAS does not display Wnon altitude reporting aircraftW above
R 15,500 ft MSL.

**ON A/C 001-004,

F. Sensitivity Level
The notion of sensitivity level is very important in the TCAS as many of
the operating modes depend on it.
The TCAS separates the surrounding airspace into altitude layers. A
different Sensitivity Level (SL) threshold for issuing advisories is
applied to each altitude layer.
The sensitivity level is decreased at low altitude to prevent unnecessary
advisories in higher traffic densities such as terminal areas.
Generally, the level is determined automatically by the TCAS in function
of:
- altitude values from the radio altimeter up to 2500 ft AGL

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 - barometric altitude values in the 2500 ft to 48,000 ft range. TAU
values corresponding to each sensitivity level indicate the TA and RA
thresholds. The vertical separation thresholds at CPA also vary in
function of the sensitivity level for the different types of advisory.
The following table summarizes these data:

----------------------------------------------------------------------
| | TAU thresholds | Vertical separation |
| | | thresholds |
|----------------------------|-----------------|---------------------|
| Source | Altitude | SL TA RA | S0 S1 S2 |
| Altitude | | | TA RA RA |
| | | | prev cor |
| | | (sec) (sec) | (ft) (ft) (ft) |
|------------|---------------|-----------------|---------------------|
| Radio Alt |less than 1000 | 2 20 | 850 |
| Radio Alt | 1000-2350 | 3 25 15 | 850 600 300 |
| Baro | 2350-5000 | 4 30 20 | 850 600 300 |
| Baro | 5000-10000 | 5 40 25 | 850 600 350 |
| Baro | 10000-20000 | 6 45 30 | 850 600 400 |
| Baro | 20000-30000 | 7 48 35 | 850 700 600 |
| Baro |more than 30000| 7 48 35 | 1200 800 700 |
----------------------------------------------------------------------

NOTE : Level 1 corresponds to Standby Mode in which no advisory is

____
generated.

NOTE : This table indicates the threshold based on own aircraft altitude.
____
Each aircraft altitude depends on an hysteresis:
- 1000 + or - 100 ft
- 2350 + or - 200 ft
- 5000 + or - 500 ft
- 10000 + or - 500 ft
- 20000 + or - 500 ft
- 30000 + or - 500 ft
For example, to switch from sensitivity level 3 to sensitivity
level 2, the altitude must fall below 900 ft.
However, to switch from sensitivity level 2 to sensitivity level
3, the altitude value must go above 1100 ft.
(Ref. Fig. 023)
There are two other means of modifying the sensitivity level:
- selecting TA only mode on the ATC/TCAS control unit forces level
2. In this case, intruders of all types are displayed but are
not transformed into RA symbols and no vertical speed
modification indications are issued.

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 TCAS - Separation into Altitude Layers
Figure 023

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 - the ATC/Mode S-equipped ground stations may modify the
sensitivity level of the aircraft TCAS via the uplink without,
however, having the capability to force the Standby Mode. If
several ground stations command sensitivity levels, the TCAS
logic selects the lowest level.
Definition of priority logic:
First a sensitivity level based on altitude is selected. Level 2
is selected if the radio altimeter altitude is less than 1000
ft. Level 2 is also selected if own aircraft is configured such
that both CLIMB and DESCEND RAs are inhibited. Level 3 is
selected if the aircraft is above 1000 ft and below 2350 ft AGL.
If the aircraft is above 2350 ft AGL, barometric altitude is
used to select either level 4 (below 5000 ft), 5 (from 5000 to
10,000 ft), 6 (from 10,000 to 20,000 ft), and 7 (above 20,000
ft).
ATC/TCAS control unit input is read by the TCAS computer. If the
pilot has selected Automatic Mode (TA/RA), then the
altitude-based sensivity level is used in comparisons to
determine the final level.
From all sensitivity level commands, if any, received from
ground stations, the lowest is selected.
If the TA ONLY mode is selected, either manually via the control
unit or by a ground station, the altitude-based sensitivity
level is used for TA thresholds and the RAs are inhibited.
Otherwise, the lowest of all inputs is chosen.

R **ON A/C ALL

R Post SB 34-1179 For A/C 001-004,

F. Sensitivity Level
The notion of Sensitivity Level (SL) is very important in the TCAS as
many of the operating modes depend on it.
The TCAS separates the surrounding airspace into altitude layers. A
different sensitivity level threshold for issuing advisories is applied
to each altitude layer.
The sensitivity level is decreased at low altitude to prevent unnecessary
advisories in higher traffic densities such as terminal areas.
Generally, the level is determined automatically by the TCAS in function
of:
- altitude values from the radio altimeter up to 2500 ft AGL
- barometric altitude values in the 2500 ft to 48,000 ft range. TAU
values corresponding to each sensitivity level indicate the TA and RA
thresholds. The vertical separation thresholds at CPA also vary in
function of the sensitivity level for the different types of advisory.
The following table summarizes these data:

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 ----------------------------------------------------------------------
| | TAU thresholds | Vertical separation |
| | | thresholds |
|-----------------------------|----------------|---------------------|
| Source | Altitude | SL TA RA | S0 S1 S2 |
| Altitude | | | TA RA RA |
| | | | prev cor |
| | | (sec) (sec) | (ft) (ft) (ft) |
|------------|----------------|----------------|---------------------|
| Radio Alt |less than 1000 | 2 20 | 850 |
| Radio Alt | 1000-2350 | 3 25 15 | 850 600 300 |
| Baro | 2350-5000 | 4 30 20 | 850 600 300 |
| Baro | 5000-10,000 | 5 40 25 | 850 600 350 |
| Baro | 10,000-20,000 | 6 45 30 | 850 600 400 |
| Baro | 20,000-42,000 | 7 48 35 | 850 700 600 |
| Baro |more than 42,000| 7 48 35 | 1200 800 700 |
----------------------------------------------------------------------

NOTE : Level 1 corresponds to Standby Mode in which no advisory is

____
generated.

NOTE : This table indicates the threshold based on own aircraft altitude.
____
Each aircraft altitude depends on an hysteresis:
- 1000 plus or minus 100 ft
- 2350 plus or minus 200 ft
- 5000 plus or minus 500 ft
- 10,000 plus or minus 500 ft
- 20,000 plus or minus 500 ft
- 42,000 plus or minus 500 ft
For example, to switch from sensitivity level 3 to sensitivity
level 2, the altitude must fall below 900 ft.
However, to switch from sensitivity level 2 to sensitivity level
3, the altitude value must go above 1100 ft.
(Ref. Fig. 023A)
There are two other means of modifying the sensitivity level:
- selecting TA only mode on the ATC/TCAS control unit forces level
2. In this case, intruders of all types are displayed but are
not transformed into RA symbols and no vertical speed
modification indications are issued.
- the ATC/Mode S-equipped ground stations may modify the
sensitivity level of the aircraft TCAS via the uplink without,
however, having the capability to force the Standby Mode. If
several ground stations command sensitivity levels, the TCAS
logic selects the lowest level.
Definition of priority logic:

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 TCAS - Separation into Altitude Layers
Figure 023A

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 First a sensitivity level based on altitude is selected. Level 2
is selected if the radio altimeter altitude is less than 1000
ft. Level 2 is also selected if own aircraft is configured such
that both CLIMB and DESCEND RAs are inhibited. Level 3 is
selected if the aircraft is above 1000 ft and below 2350 ft AGL.
If the aircraft is above 2350 ft AGL, barometric altitude is
used to select either level 4 (below 5000 ft), 5 (from 5000 to
10,000 ft), 6 (from 10,000 to 20,000 ft), and 7 (above 20,000
ft).
ATC/TCAS control unit input is read by the TCAS computer. If the
pilot has selected Automatic Mode (TA/RA), then the
altitude-based sensivity level is used in comparisons to
determine the final level.
From all sensitivity level commands, if any, received from
ground stations, the lowest is selected.
If the TA ONLY mode is selected, either manually via the control
unit or by a ground station, the altitude-based sensitivity
level is used for TA thresholds and the RAs are inhibited.
Otherwise, the lowest of all inputs is chosen.

**ON A/C ALL

G. Information Display
The TCAS information is presented on the CAPT and F/O NDs of the EFIS
system. Additional messages can also be presented on the display units of
the ECAM system.

(1) Traffic information on the ND

Target aircraft are presented on the ND in ROSE or ARC mode but not
in PLAN mode.
These traffic indications show the situation in the surveillance
zone.
The aircraft present in this zone are represented by symbols whose
shape and color correspond to the type of intruders defined in the
TCAS.
The symbols are positioned on the ND so as to depict their relative
bearing and range. Data tags are associated with intruders.
These tags consist of:
- two digits indicating their relative altitude in hundreds of feet
- a symbol indicating whether the intruder is above (+) or below (-)
the aircraft.
An arrow to the right of the symbol indicates the vertical trend of
the aircraft.
Targets are symbolized according to their type:
- OTHER TRAFFIC: white outlined diamond, height 7 mm
- PROXIMATE TRAFFIC: white filled diamond, height 7 mm

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 - TRAFFIC ADVISORY: amber filled circle, diameter 5 mm
- RESOLUTION ADVISORY: red filled square, side 5 mm.
The display only presents the eight most threatening intruders
(number determined through program pins on the TCAS computer).
The own aircraft is represented by the aircraft symbol at the
center of the dial in ROSE mode and at the lower quarter and at the
center of the image in ARC mode.
A white range ring with markings at each of the twelve clock
positions is placed around the own aircraft symbol at a radius of
2.5 NM.
The following figure shows an example of the display on the ND:

(Ref. Fig. 024)

These indications are only presented for the 10, 20 and 40 NM range
selections. If a TA or RA type intruder is detected and the display
range is at a higher scale, the following message comes into view
at the center of the display, in red for RA and in amber for TA:
REDUCE RANGE
If a TA or RA type intruder is detected and the ND mode is
inadequate for display, the following message comes into view at
the center of the display in the same colors as above:
CHANGE MODE
The TCAS can detect an intruder without acquiring its bearing (for
instance, multipath problem). In this case its range, relative
altitude and an arrow are displayed in the TCAS area (at the bottom
of the ND).
The color of the display is the same as the color of the intruder
symbol.
(Ref. Fig. 025)
OFF SCALE intruder: if only a half of a symbol is displayed, the
target is defined as an off scale intruder. This calls for
increasing the range selection on the ND.

(2) Aircraft control information on the PFD

Resolution advisories are represented on the vertical speed scale of
the PFD by indications given in the form of a band made up of colored
sectors:
- a red sector represents a forbidden vertical speed range
- a green sector indicates the vertical speed range the aircraft
should fly in to avoid a collision threat represented by one or
more intruders.

(3) Corrective advisory display

Corrective resolution advisories are displayed to advise the crew to
perform an avoidance maneuver in the vertical sense.
This maneuver may take different forms:
- climb or descent if the aircraft is in level flight

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 TCAS - ND Data Display
Figure 024

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 TCAS - Display of Intruders on ND
Figure 025

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 - reducing or increasing rate of climb or reversing to descent if the
aircraft is in climb
- reducing or increasing rate of descent or reversing to climb if the
aircraft is in descent.
When resolution advisories are displayed, the vertical speed scale
surface changes from trapezoidal to rectangular.
The grey background is replaced by green and red sectors defining
the optimum vertical speed values.
The pilot<s task is to maneuver the aircraft to keep the needle out
of the red sectors and place it in the adjacent green WFly-toW
sector.
The vertical speed information needle and digits are colored in red
when the vertical speed is in the forbidden area. It becomes green
when the vertical speed is in the authorized area.
(Ref. Fig. 026)

(4) Preventive advisory display

Preventive resolution advisories advise the pilot to avoid vertical
speeds that could lead to a hazardous situation.
They are represented by one or two red sectors on the vertical speed
scale.
The pilot must keep the vertical speed of his aircraft outside these
zones.
For example, if own and intruder<s flight paths are horizontal and
cross through each other, the intruder being at a higher flight
level, if the vertical separation is sufficient, it is not necessary
to modify the aircraft flight path. The positive vertical speed
sector is in red to indicate that the aircraft may remain at its
present level or may descend but must not climb.
(Ref. Fig. 026)
If intruders are detected above and below, two red sectors are
displayed leaving an uncolored zone around the zero value on the
vertical speed scale advising the pilot to maintain the aircraft at
its current level.
The following figure shows several examples of corrective and
preventive advisories.
(Ref. Fig. 027)

(5) Messages annunciated on the ND

As well as intruder information, the ND also displays operating mode
messages or fault data. This information is presented in the lower
section of the ND (message zone):
- TA ONLY - white - for the TA mode (automatic or manual switching)
- TCAS - red - to indicate a TCAS computer failure
(Ref. Fig. 028)

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 TCAS - PFD Data Display
Figure 026

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 TCAS - Sector Displays on Vertical Speed Scale
Figure 027

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 TCAS - Messages Displayed on ND
Figure 028

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 (6) Display on the PFD
A red TCAS flag appears to the left of the vertical speed scale on
the PFD if the TCAS cannot deliver RA data
(Ref. Fig. 029)

(7) Display on the upper ECAM DU

- If a TCAS fault is detected, the amber warning message NAV TCAS
FAULT is displayed on the upper ECAM DU.
- Selection of the TCAS STBY mode on the ATC/TCAS control unit
results in the display of the TCAS STBY message (green) in the memo
section of the upper ECAM DU.
(Ref. Fig. 029)

H. ATC/TCAS Control Unit Operational Use

The TCAS is a cooperative system whose operating mode is very close to
the ATC/Mode S transponder associated to it.
The main controls are thus grouped on the ATC/TCAS control unit and the
traffic and conflict resolution information is presented on the EFIS
displays.

NOTE : - operation of the ATC/Mode S transponder is described in 34-52.

____
- the EFIS components are also described in 31-64 for the PFD
and 31-65 for the ND.

The manual operating modes of the TCAS are selected via the ATC/TCAS
control unit.

(Ref. Fig. 030)

(1) TCAS modes of operation

The TCAS mode of operation is selected by means of a switch with six
positions INOP/STBY/XPDR/TA/TA-RA/TFC.

(a) STBY mode

In the Standby Mode, the advisory generation and surveillance
functions are inhibited. No TCAS information can be displayed on
the PFDs and NDs.
The aircraft symbol and the range ring remain on the ND and
vertical speed information is not displayed on the PFD.
The green TCAS STBY message is displayed in the memo section of
the upper ECAM DU.
If the mode selector is set to XPDR, the TCAS also operates in
standby mode.

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 TCAS - Messages Displayed on PFD and ECAM
Figure 029

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 TCAS - ATC/TCAS Control Unit
Figure 030

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 (b) TA mode
In this mode, intruders are displayed on the ND according to
their position in the airspace. The TCAS performs surveillance
functions but does not generate any resolution advisories.
The TA ONLY message is displayed in white on the NDs in the left
corner of the TCAS message area.

(c) TA/RA mode

The TCAS performs all TA mode functions and also issues
preventive or corrective resolution advisories, represented in
the form of colored sectors along the vertical speed scale on the
PFD.
The sensitivity level is determined automatically in function of
altitude.

NOTE : The final mode of operation is a combination taking into

____
account the aircraft altitude and any instructions
received from ATC Mode S ground stations. For further
information refer to the priority logic definition (Ref.
Para. 6.F.).

(d) TFC mode

In this mode, four types of symbols can be displayed permanently
on the NDs. The number of the targets simultaneously displayed is
limited to eight by pin-programming.

(2) TCAS Surveillance envelope

(a) ABOVE/N/BELOW mode (CAPT/FO selection)

In the ABOVE mode, the TCAS surveillance envelope expands from
-2700 ft to +9900 ft above the TCAS equipped aircraft
In the BELOW mode, the TCAS surveillance envelope expands from
+2700 ft to -9900 ft below the TCAS equipped aircraft
In the NORMAL mode, the TCAS surveillance envelope is equal above
or below the TCAS equipped aircraft.

(3) INOP placards

These functions (TEST and ABSolute/RELative altitude selection) are
reserved for a future use.

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 (4) ATC mode of operation
The mode of operation of the transponder is selected by a switch with
six positions INOP/STBY/XPDR/TA/TA-RA/TFC

(a) STBY mode

When the transponder is in standby mode, it does not transmit
either squitters or replies to ground station or other aircraft
interrogations.

(b) XPDR mode

In flight, all ATC modes are active.
When the aircraft touches down, the landing gear ground/flight
relay disables the Mode A and C replies of the selected
transponder from ground station interrogations.
The Mode S transponder operates permanently, both in flight and
on the ground. It periodically transmits squitters (at 1 second
intervals) to be detected by other aircraft and replies to their
interrogations and those from ground stations.
This function permits, on ground, to override the inhibition of
replies from interrogations in Mode A or C. It is used by the air
traffic controller to check the correct operation of the aircraft
Mode A or C transponder prior to takeoff.

(c) TA/TA-RA/TFC modes

The ATC system continues to operate normally in mode A, C and S.
These functions are reserved for TCAS use.

(5) Selection of active transponder 1 or 2

The 1/2 switch permits selection of the active transponder. The
non-selected transponder is placed in standby mode.

(6) Identification code in Mode A

The Mode S transponder also replies to Mode A interrogations from
ground stations. A concentric knob permits the pilot to set the Mode
A octal code assigned to the aircraft by the ATC ground station
controller and included in the transmitted replies. A window on the
control unit displays this code permanently as long as the content of
the digital output message complies with the displayed data.

(7) IDENT pushbutton switch

On ground station request, an addition pulse must be included in the
Mode A and Mode C replies transmitted by the transponder to enable a
more precise location. This operation is performed by pressing the
IDENT pushbutton switch on the control unit.

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 7. Test
____

A. Self-Test
A quick check of the correct operation of the TCAS installation can be
performed by activating the TEST function:
- either by pressing the pushbutton switch on the front of the TCAS
computer
- or through the CFDIU by applying the procedure TCAS functional test on
the MCDU.
The self-test sequence checks the main functions of the computer and
transmits to the displays:
- resolution advisory characteristics (0 ft/mn advisory, up corrective
advisory, don<t descend, don<t climb > 2000 ft/mn, rate to maintain) on
label 270
- label frames 130, 131, 132 containing the data for each of the four
intruders according to the following table:

--------------------------------------------------------------------------
| INTRUDER | TYPE | RANGE | REL ALT | BEARING | VERTICAL RATE |
| | | (NM) | (FEET) | (DEG) | |
|------------|--------|---------|-----------|-----------|----------------|
| 1 | RA | 2.00 | +200 | +90 |no vertical rate|
| 2 | TA | 2.00 | -200 | -90 |climbing |
| 3 | PROX | 3.625 | -1000 | +33.75 |descending |
| 4 | OTHER | 3.625 | +1000 | -33.75 |no vertical rate|
--------------------------------------------------------------------------

(1) ND image
The ND must display the images corresponding to the four types of
intruders: Other, Proximate, TA and RA.
The shapes and colors of the traffic symbols are:
- white outlined diamond for Other traffic
- white diamond for Proximate traffic
- yellow circle for TA traffic
- red square for RA traffic
(Ref. Fig. 031)

(2) PFD image

At the beginning of the test sequence, green and red sectors must
appear sequentially on the vertical speed scale of the PFD. Then a
resolution advisory display is shown.
(Ref. Fig. 031)

(3) Fault indication

At the end of the test sequence, the system generates a synthesized
voice message:

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 TCAS - Test Display
Figure 031

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 TCAS SYSTEM TEST OK
if the system operates correctly or:
TCAS SYSTEM TEST FAIL
if an anomaly has been detected.
In this case the NDs, the PFDs and the ECAM show the fault messages
described in Para. 6.G.(5), (6) and (7).
In addition, two windows on the front of the TCAS computer display a
code identifying the failed component according to the table below:

-------------------------------------------------------------------------------
| CONTROL/ | LOCATION | FUNCTION |
| INDICATING | | |
|------------------|-------------|--------------------------------------------|
| TTR PASS | Front panel | Comes on to indicate TTR has passed self- |
|(indicator light) | | test |
| TTR FAIL | Front panel | Comes on to indicate TTR has failed self- |
|(indicator light) | | test |
| XPNDR | Front panel | Comes on to indicate transponder or data |
|(indicator light) | | link interface failure |
| UPPER ANT | Front panel | Comes on to indicate upper TCAS antenna |
|(indicator light) | | failure |
| LOWER ANT | Front panel | Comes on to indicate lower TCAS antenna |
|(indicator light) | | failure |
| RAD ALT | Front panel | Comes on to indicate lack of radio |
|(indicator light) | | altimeter data |
| HDNG | Front panel | Comes on to indicate lack of heading data |
|(indicator light) | | |
| R/A | Front panel | Comes on to indicate RA indicator failure |
|(indicator light) | | |
| T/A | Front panel | Comes on to indicate TA indicator failure |
|(indicator light) | | |
| TEST (pushbutton | Front panel | Initiates self-test when pressed |
| switch) | | |
-------------------------------------------------------------------------------

B. CFDS

(1) Introduction
The CFDS permits to present the TCAS computer faults on the
Multipurpose Control and Display Units (MCDU) and on the printer.
The TCAS computer which is classified Type 1 system in the CFDS also
delivers data related to fault diagnoses required for its
maintenance.
It communicates with the CFDS through two ARINC 429 low speed buses.
The CFDS is characterized by two operating modes:
- MENU mode
- NORMAL mode.

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 (2) Menu Mode

(a) SYSTEM REPORT/TEST function

This function enables access to all the electronic systems and to
the TCAS computer.
The display of the SYSTEM REPORT/TEST page for the NAV components
on which the TCAS is accessible is shown on the following figure.
When the line key adjacent to the TCAS indication is pressed, the
CFDIU establishes the dialog and provides access to one of the
eight following items:
- LAST LEG REPORT
- PREVIOUS LEGS REPORT
- LRU IDENTIFICATION
- GROUND SCANNING
- TROUBLE SHOOTING DATA
- CLASS 3 FAULTS
- GROUND REPORT
- TEST.
The procedure used to get the page for selection of an item is
shown in the figure
(Ref. Fig. 032)

(b) LAST LEG REPORT

This report contains the computer class 1 internal and external
faults recorded during the last flight.
The following tables give the lists of the fault messages which
can be reported and indicate the fault class assigned to them as
defined by the CFDS standard.

1
_ Internal faults

-------------------------------------------------------------------------------
| LIST OF INTERNAL FAULT MESSAGES |
|-----------------------------------------------------------------------------|
| ATA | CLASS | MESSAGE |
|-----------------------------------------------------------------------------|
| 344334 | 1 | TCAS (1SG) |
| 344311 | 1 | TCAS TOP ANTENNA (7SG1) |
| 344311 | 1 | TCAS TOP ANTENNA (7SG1) |
| | | COAXIAL J1 |
| 344311 | 1 | TCAS TOP ANTENNA (7SG1) |
| | | COAXIAL J2 |
| 344311 | 1 | TCAS TOP ANTENNA (7SG1) |
| | | COAXIAL J3 |
| 344311 | 1 | TCAS TOP ANTENNA (7SG1) |
| | | COAXIAL J4 |
| 344311 | 1 | TCAS BOT ANTENNA (7SG2) |

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 TCAS - Maintenance Test Procedure
Figure 032

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 -------------------------------------------------------------------------------
| LIST OF INTERNAL FAULT MESSAGES |
|-----------------------------------------------------------------------------|
| ATA | CLASS | MESSAGE |
|-----------------------------------------------------------------------------|
| 344311 | 1 | TCAS BOT ANTENNA (7SG2) |
| | | COAXIAL J1 |
| 344311 | 1 | TCAS BOT ANTENNA (7SG2) |
| | | COAXIAL J2 |
| 344311 | 1 | TCAS BOT ANTENNA (7SG2) |
| | | COAXIAL J3 |
| 344311 | 1 | TCAS BOT ANTENNA (7SG2) |
| | | COAXIAL J4 |
-------------------------------------------------------------------------------

The following figure shows the sequence of menus to display

these messages.
(Ref. Fig. 033)

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 TCAS - Internal Fault Messages
Figure 033

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 2
_ External faults
External faults and associated messages are listed in the
table below:

-------------------------------------------------------------------------------
| LIST OF EXTERNAL FAULT MESSAGES |
|-----------------------------------------------------------------------------|
| ATA | CLASS | MESSAGE |
|-----------------------------------------------------------------------------|
| 344233 | 3 | RA1 (2SA1)/TCAS (1SG) |
| 344233 | 3 | RA2 (2SA2)/TCAS (1SG) |
| 344233 | 1 | RA1 (2SA1)+RA2 (2SA2)/TCAS (1SG) |
| 345233 | 3 | ATC 1(1SH1)/TCAS (1SG) |
| 345233 | 3 | ATC 2(1SH2)/TCAS (1SG) |
| 345233 | 1 | ATC1 (1SH1)+ATC2 (1SH2)/TCAS (1SG) |
| 341234 | 3 | ADIRU1 (1FP1)/TCAS (1SG) |
| 240000 | 1 | POWER SUPPLY INTERRUPT |
| 355212 | 1 | ATC - TCAS CTL PNL (3SH)/TCAS (1SG) |
| 313234 | 3 | CFDIU (1TW)/TCAS (1SG) |
-------------------------------------------------------------------------------

NOTE : Fault of one ATC is a class 3 fault.

____
Fault of both ATCs is a class 1 fault.

NOTE : Fault of one radio altimeter is a class 3 fault whereas

____
it becomes a class 1 fault when two radio altimeters
are faulty.

The class 3 recorded external faults are displayed through the

CLASS 3 FAULTS menu sequence as shown in the following figure.
(Ref. Fig. 034)

(3) PREVIOUS LEGS REPORT

The messages are identical to those shown in the Para. above but
concern the last 63 flights if faults have occurred during these
flights.
(Ref. Fig. 035)

(4) LRU IDENTIFICATION

**ON A/C 001-004,

(Ref. Fig. 036)

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 TCAS - External Fault Messages
Figure 034

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 TCAS - PREVIOUS LEGS REPORT
Figure 035

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 TCAS - LRU IDENTIFICATION
Figure 036

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R **ON A/C ALL

R Post SB 34-1179 For A/C 001-004,

(Ref. Fig. 036A)

**ON A/C ALL

(5) GROUND SCANNING

This function enables consultation of the TCAS computer fault
recordings as defined by the Component Manufacturer.
The TCAS peripheral monitoring and internal cyclic tests are used in
order to detect transient faults.
(Ref. Fig. 037)

(6) TROUBLE SHOOTING DATA

This function allows to analyze the snapshot of the recorded fault to
detect any software bug.
Two types of data are displayed:
- some correlation parameters which are the date and the UTC hour
displayed in clear english,
- some snapshot data delivered in hexadecimal code or in clear
message.
(Ref. Fig. 038)

(7) GROUND REPORT

This function is used to present class 1, 2 or 3 internal faults when
they are detected on ground. These faults differ from those displayed
on the LAST LEG REPORT page.
The following figure shows examples of internal faults recorded on
ground by the TCAS system.
The relevant trouble shooting data are displayed by pressing the line
key adjacent to the fault indication.
(Ref. Fig. 039)

(8) TCAS functional test

A TCAS built-in functional test can be initiated by pressing the line
key adjacent to the TEST indication on the TCAS maintenance sub-menu.
The following sequence is then generated.
(Ref. Fig. 040, 041)
- the test ends with the display of the following message on the
MCDU:
TEST OK or TEST FAIL
- at the end of the functional test the TCAS computer generates a
complete sequence of synthesized voice messages.

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 TCAS - LRU IDENTIFICATION
Figure 036A

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 TCAS - GROUND SCANNING
Figure 037

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 TCAS - TROUBLE SHOOTING DATA
Figure 038

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 TCAS - GROUND REPORT
Figure 039

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 TCAS - Functional Test (Sheet 1/2)
Figure 040

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 TCAS - Functional Test (Sheet 2/2)
Figure 041

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 When all the tests are completed and no fault has been detected the
computer reports TCAS SYSTEM TEST OK.
If one of the test criteria has not been met, the synthesized voice
message TCAS SYSTEM TEST FAIL is announced.
Remarks:
- this short test permits to check rapidly, on ground, the
functionality of the TCAS and particularly that of the PFD/NDs via
the DMC.
In addition it enables to check correct operation of the
synthesized voice message system.

(9) Software configuration follow-up

The TCAS has the DATA BASE loading capacity from a portable data
loader or an airborne data loader (MDDU) in compliance with ARINC 615
characteristics.
Consequently it must be possible to check correct downloading by
using the CFDS/MCDU interface.
The LRU IDENTIFICATION item displays the downloaded software version
reference (line SW/N).

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 TCAS (TRAFFIC COLLISION AVOIDANCE SYSTEM) - SERVICING
_____________________________________________________

**ON A/C 001-004,

TASK 34-43-00-610-001

Uploading Procedure with Portable Data Loader (SFIM) to Load the Operational
Software of the TCAS

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific circuit breaker(s) safety clip(s)

No specific access platform 1.6 m (5 ft. 3 in.)
YV68A110 1 PORTABLE DATA LOADER

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
31-32-00-860-010 Procedure to Get Access to the SYSTEM REPORT/TEST NAV
Page
R 52-41-00-410-002 Close the Avionics Compartment Doors after Access
34-43-00-991-001 Fig. 301

3. __________
Job Set-up

Subtask 34-43-00-861-051

A. Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002).

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 Subtask 34-43-00-860-071

B. On the PORTABLE DATA LOADER (YV68A110), make sure that the ON/OFF switch
is at OFF.

Subtask 34-43-00-010-052

C. Get Access

(1) Put the access platform in position at the access door 824 in zone
128.

(2) Open the access door 824.

Subtask 34-43-00-865-067

D. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------

C/B NOT APPLICABLE

Subtask 34-43-00-860-072

E. Aircraft Maintenance Configuration

(1) On the panel 188VU

(Ref. Fig. 301/TASK 34-43-00-991-001)

(a) Remove the blanking cap from the DATA LOADER connector 194VC.

(b) Connect the cable of the portable data loader to the DATA LOADER
connector 194VC.

(2) Make sure that the aircraft is in ground configuration.

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R Data Loader Connector
R Figure 301/TASK 34-43-00-991-001

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 Subtask 34-43-00-865-068

F. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------

C/B NOT APPLICABLE

Subtask 34-43-00-865-069

G. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
C/B NOT APPLICABLE.

4. Procedure
_________

Subtask 34-43-00-970-052

A. Loading of the Operational Software

NOTE : After the uploading operations, you must do a check on the MCDU,
____
of the reference of the data loaded in the computer.

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the portable data loader: On the portable data loader:

- set the ON/OFF switch to ON. - the < < MDDU READY > > indication
comes into view.

- put the disk into the disk - the READY indication comes into view
drive, the label in the forward - then, the WAIT RESPONSE indication
direction. comes into view
- then, the TRANSF IN PROG indication
comes into view.

NOTE : If more than one disk is

____
necessary, the EJECT DISK and
INSERT NEXT DISK indications
come into view one after the
other. They tell you to put a
new disk in the portable data
loader.

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
- when all the data are in the
computer, the TRANSF COMPLETE
indication comes into view.

- eject the disk from the disk - the < < MDDU READY > > indication
drive. comes into view.

Subtask 34-43-00-280-055

B. On the MCDU Check of the Reference of the Data Loaded in the TCAS

(1) On the center pedestal, on one MCDU, get the SYSTEM REPORT/TEST/NAV
page (Ref. TASK 31-32-00-860-010).

(2) Do a check of the identification of the loaded disk.

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the MCDU: On the MCDU:

- push the line key adjacent to - the TCAS page comes into view.
the TCAS indication.

- push the line key adjacent to - the LRU IDENTIFICATION page comes
the LRU IDENT indication. into view.

NOTE : Make sure that the SW/N

____
indication shown is the same as
the SW/N indication read on the
disk.

5. Close-up
________

Subtask 34-43-00-860-073

A. Put the aircraft back to its initial configuration.

(1) On the MCDU, push the line key adjacent to the RETURN indication
until the CFDS menu page comes into view.

(2) On the portable data loader, set the ON/OFF switch to OFF.

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 Subtask 34-43-00-865-070

B. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------

C/B NOT APPLICABLE

Subtask 34-43-00-860-074

C. Aircraft Maintenance Configuration

(1) On the panel 188VU, disconnect the cable of the portable data loader
from the DATA LOADER connector

(2) install the blanking cap on the DATA LOADER connector.

Subtask 34-43-00-865-071

D. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
C/B NOT APPLICABLE.

Subtask 34-43-00-862-051

E. De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-

002).

Subtask 34-43-00-410-052

F. Close Access

R (1) Close the access door 824 (Ref. TASK 52-41-00-410-002).

(2) Remove the access platform(s).

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 TCAS (TRAFFIC COLLISION AVOIDANCE SYSTEM) - DEACTIVATION/REACTIVATION
_____________________________________________________________________

TASK 34-43-00-040-001

Deactivation of the TCAS

1. __________________
Reason for the Job

Refer to the MMEL TASK: 34-43-01

NAVIGATION
TCAS
(FAA Only)

2. ______________________
Job Set-up Information

A. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
31-60-00-860-001 EIS Start Procedure
31-60-00-860-002 EIS Stop Procedure
34-10-00-860-004 IR Alignment Procedure

3. __________
Job Set-up

Subtask 34-43-00-860-067

A. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits

(Ref. TASK 24-41-00-861-002).

(2) Do the EIS start procedure (PFDs and NDs only) (Ref. TASK 31-60-00-
860-001).

(3) Do the IR alignment procedure (Ref. TASK 34-10-00-860-004).

(4) On the EFIS control sections of the FCU:

- set the mode selector switches to ROSE.
- set the scale selector switches to 10.

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 Subtask 34-43-00-865-063

B. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV/ATC/1 5SH1 G11
121VU COM NAV/ATC/2 5SH2 K07

R **ON A/C 005-099,

121VU COM NAV/TCAS 4SG K10

**ON A/C ALL

4. Procedure
_________

Subtask 34-43-00-040-050

A. Deactivation of the TCAS

(1) Open, safety and tag the circuit breaker 4SG of the TCAS (ignore the
related warnings).

5. Close-up
________

Subtask 34-43-00-860-068

A. Put the aircraft back to its initial configuration.

(1) On the ADIRS CDU, set the OFF/NAV/ATT selector switches to OFF.

(2) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002).

(3) Make an entry in the log book.

(4) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

(5) Make sure that the work area is clean and clear of tool(s) and other
items.

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 TASK 34-43-00-440-001

Reactivation of the TCAS

1. __________________
Reason for the Job

Refer to the MMEL TASK: 34-43-01

NAVIGATION
TCAS
(FAA Only)

2. ______________________
Job Set-up Information

A. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
TSM 34PB101 (for corrective action)

3. __________
Job Set-up

Subtask 34-43-00-860-069

A. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits

(Ref. TASK 24-41-00-861-002).

4. Procedure
_________

Subtask 34-43-00-440-050

A. Do the Trouble Shooting of the TCAS (Ref. TSM 34PB101).

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 5. Close-up
________

Subtask 34-43-00-860-070

A. Put the aircraft back to its initial configuration.

(1) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

(2) Make sure that the work area is clean and clear of tool(s) and other
items.

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 TCAS (TRAFFIC COLLISION AVOIDANCE SYSTEM) - ADJUSTMENT/TEST
___________________________________________________________

TASK 34-43-00-740-001

BITE Test of the TCAS

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
31-32-00-860-010 Procedure to Get Access to the SYSTEM REPORT/TEST NAV
Page
31-60-00-860-001 EIS Start Procedure
31-60-00-860-002 EIS Stop Procedure
34-10-00-860-004 IR Alignment Procedure

3. __________
Job Set-up

Subtask 34-43-00-860-050

A. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits

(Ref. TASK 24-41-00-861-002).

(2) Do the EIS start procedure (PFDs and NDs only) (Ref. TASK 31-60-00-
860-001).

(3) Do the IR alignment procedure (Ref. TASK 34-10-00-860-004).

(4) On the EFIS control sections of the FCU:

- set the mode selector switches to ROSE
- set the scale selector switches to 10.

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 (5) On the center pedestal, if the ATC/TCAS control unit has the ALTITUDE
REPORTING function , set the ALT RPTG (or ALT RPT) switch to ON.

(6) Do the procedure to get access to the SYSTEM REPORT/TEST NAV page on
one MCDU (Ref. TASK 31-32-00-860-010):
- push the NEXT PAGE function key (two times) until the TCAS menu
page comes into view.

Subtask 34-43-00-865-050

B. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV/ATC/1 5SH1 G11
121VU COM NAV/ATC/2 5SH2 K07

R **ON A/C 005-099,

121VU COM NAV/TCAS 4SG K10

**ON A/C ALL

4. Procedure
_________

Subtask 34-43-00-740-050

A. BITE Test of the TCAS

NOTE : During the test, obey the instructions shown on the MCDU used.
____

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

On the MCDU: On the MCDU:

- push the line key adjacent to the - the subsequent TCAS TEST page with
TEST indication. instructions comes into view.

- push the line key adjacent to the - the TEST IN PROGRESS 12 S indication
START TEST indication. comes into view.
- this sequence starts:

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
R - in the loudspeakers:
R * you can hear the TCAS TEST message.
R - on the CAPT and F/O NDs, these
R symbols come into view:
R * a white diamond with a + 10
R indication.
R * a white diamond with a down arrow
R and a - 10 indication.
R * an amber circle with an up arrow
R and a - 0.2 indication.
R * a red square with a + 0.2
R indication.
R - on the CAPT and F/O PFDs:
R * a sequence of RA advisories (grey
R and red sectors) comes into view on
R the V/S scale.
R * at the end of this sequence, the
R V/S scale goes back to the normal
R configuration.
R - in the loudspeakers:
R * you can hear the TCAS SYSTEM TEST
R OK message.

R - push the line key adjacent to the - on the MCDU, the TEST OK indication
R TCAS SYSTEM TEST OK indication. comes into view.

R - push the line key adjacent to the - on the MCDU, the TCAS menu page comes
R RETURN indication. into view.

5. Close-up
________

Subtask 34-43-00-860-051

A. Put the aircraft back to its initial configuration.

(1) On the ADIRS CDU, set the OFF/NAV/ATT selector switches to OFF.

(2) On the center pedestal, on the MCDU, push the line key adjacent to
the RETURN indication until the MCDU MENU page comes into view.

(3) Do the EIS stop procedure (Ref. TASK 31-60-00-860-002).

(4) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

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 (5) Make sure that the work area is clean and clear of tool(s) and other
items.

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 TASK 34-43-00-720-001

Functional Test of the TCAS Antennas

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific access platform

No specific aluminum adhesive tape
No specific TIC T-49 ATC/TCAS test set (version 4.0.1) or
equivalent

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
32-69-00-860-001 Simulation of Flight, with the Aircraft on the Ground
34-10-00-860-004 IR Alignment Procedure

3. __________
Job Set-up

Subtask 34-43-00-480-050

A. Put an aluminum adhesive tape on the Radio Altimeter transmission antenna

1 (6SA1).

NOTE : Do this step only for the test of the TCAS bottom antenna.
____

Subtask 34-43-00-860-079

B. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits

(Ref. TASK 24-41-00-861-002).

(2) Do the ADIRS alignment procedure (Ref. TASK 34-10-00-860-004).

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 (3) On the panel 13VU, on the CAPT and F/O EFIS control sections of the
FCU:
- set the mode selector switch to ROSE/NAV
- set the scale selector switch to 10.

Subtask 34-43-00-865-079

C. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV/ATC/1 5SH1 G11
121VU COM NAV/RAD ALTM/2 1SA2 K12
121VU COM NAV/RAD ALTM/1 1SA1 K11
121VU COM NAV/ATC/2 5SH2 K07

R **ON A/C 005-099,

121VU COM NAV/TCAS 4SG K10

**ON A/C ALL

Subtask 34-43-00-860-080

D. Aircraft Maintenance Configuration

NOTE : Ignore all the warnings.

____

(1) For the test of the TCAS bottom antenna, on the MCDU:
- do a simulation of flight with the aircraft on the ground, with the
LGCIU 1 for the left main landing gear only (Ref. TASK 32-69-00-
860-001).

(2) On the center pedestal, on the ATC/TCAS control unit, set:

- the ATC 1 system on
- code 5555 to keep the traffic interference to a minimum
- the ABOVE/N/BELOW switches to N
- the TEST/STBY/XPDR/TA/TA/RA/TFC switch to TA/RA.

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R Subtask 34-43-00-480-051

R E. Put the TIC T-49 ATC/TCAS test set (version 4.0.1) or equivalent in
R position.

R NOTE : For the test of the TCAS top antenna, put the ATC/TCAS test set on
____
R an access platform.

R (1) Put the ATC/TCAS test set in position on the right side of the
R aircraft at 40 ft. (12.19 m) from the bottom (top) antenna and at the
R same level as the antenna.

R (2) Connect the test antenna to the ATC/TCAS test set.

R (3) Make sure that the test antenna is in the line of sight of the TCAS
R bottom (top) antenna.

R (4) On the ATC/TCAS test set, push the INTERROGATE pushbutton switch to
R energize the test set.

R 4. Procedure
_________

R Subtask 34-43-00-720-050

R A. Functional Test of the TCAS Antennas

R NOTE : This test is for the TCAS bottom antenna. For the TCAS top
____
R antenna, use the indications between the parentheses.

R -------------------------------------------------------------------------------
R ACTION RESULT
R -------------------------------------------------------------------------------

R 1. On the ATC/TCAS test set:

R - set the ATCRBS/MODE S/TCAS/XPDR
R TEST selector switch to TCAS
R - set the TCAS INTRUDER TYPE
R scenario selector switch to 0
R KTS/+1000/-1000
R - set the +1000/-1000 switch to
R -1000 (+1000)

R - push the INTERROGATE pushbutton On the ATC/TCAS test set, the scenario
R switch starts.
R On the ND, make sure that:

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
R - a white diamond with a -10 (+10)
R indication is shown in the right part
R of the display
R - the position of this diamond agrees
R with the position of the test set.

R 2. Put the ATC/TCAS test set in

R position on the left side of the
R aircraft.

R 3. On the ATC/TCAS test set, push On the ATC/TCAS test set, the scenario
R the INTERROGATE pushbutton switch starts.
R On the ND, make sure that:
R - a white diamond with a -10 (+10)
R indication is shown in the left part
R of the display
R - the position of this diamond agrees
R with the position of the test set.

R 5. Close-up
________

R Subtask 34-43-00-860-081

R A. Put the aircraft back to its initial configuration.

R (1) On the center pedestal, put the ATC/TCAS control unit back to its
R initial configuration (standby/off mode).

R (2) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-

R 002).

R Subtask 34-43-00-080-052

R B. Remove the ground support and maintenance equipment, the special and
R standard tools and all other items.

R (1) Remove the aluminum adhesive tape from the Radio Altimeter
R transmission Antenna 1.

R (2) Remove the ATC/TCAS test set and the test antenna.

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R Subtask 34-43-00-410-053

R C. Close Access

R (1) Remove the access platform(s).

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 ANTENNA - TCAS (7SG1,7SG2) - REMOVAL/INSTALLATION
_________________________________________________

TASK 34-43-11-000-001

Removal of the TCAS Antenna (7SG1, 7SG2)

WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS

_______
ONLY WITH A GOOD SUPPLY OF AIR.
OBEY THE MANUFACTURERS INSTRUCTIONS.
PUT ON PROTECTIVE CLOTHING.
DO NOT GET THEM IN YOUR MOUTH.
DO NOT SMOKE.
DO NOT BREATHE THE GAS.
THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT.
GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED.

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific blanking caps

No specific circuit breaker(s) safety clip(s)
No specific nonmetallic scraper
No specific access platform 6.0 m (19 ft. 8 in.)

B. Consumable Materials

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

Material No. 11-003 USA TT-M-261

METHYL-ETHYL-KETONE (Ref. 20-31-00)

C. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

34-43-11-991-001 Fig. 401

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 3. __________
Job Set-up

Subtask 34-43-11-865-050

A. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------

R **ON A/C 005-099,

121VU COM NAV/TCAS 4SG K10

**ON A/C ALL

Subtask 34-43-11-010-050

B. Get Access

(1) Put the access platform in position at zone 230 to get access to the
TCAS top antenna 7SG1.

4. Procedure
_________

Subtask 34-43-11-020-050

A. Removal of the TCAS Antenna

(Ref. Fig. 401/TASK 34-43-11-991-001)

(1) Remove the sealant from the screw heads and around the antenna base.

(2) Remove the screws (9) and the washers (8).

(3) Pull the antenna (6) away from the fuselage structure (1).

(4) Disconnect the four coaxial connectors (2).

NOTE : For the antenna 7SG1, the coaxial connectors (2) must not go
____
into the fuselage.

(5) FOR 7SG1

Remove the foam washer (5).

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R TCAS Antenna
Figure 401/TASK 34-43-11-991-001

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 (6) Remove and discard the O-ring (4) and the gasket (3).

(7) Remove the antenna (6).

(8) Put blanking caps on the disconnected coaxial connectors (2) and (7).

(9) FOR 7SG1

Put masking tape around the coaxial cables (2) and attach them to the
fuselage.

(10) Remove the sealant with a nonmetallic scraper and clean the fuselage
structure with CLEANING AGENTS (Material No. 11-003).

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 TASK 34-43-11-400-001

Installation of the TCAS Antenna (7SG1, 7SG2)

WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS

_______
ONLY WITH A GOOD SUPPLY OF AIR.
OBEY THE MANUFACTURERS INSTRUCTIONS.
PUT ON PROTECTIVE CLOTHING.
DO NOT GET THEM IN YOUR MOUTH.
DO NOT SMOKE.
DO NOT BREATHE THE GAS.
THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT.
GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED.

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific lint-free cloth

No specific nonmetallic scraper
No specific access platform 6.0 m (19 ft. 8 in.)
R No specific Torque Wrench : range 0.12 to 0.16 m.daN
R (10.61 to 14.15 lbf.in)
R No specific Torque Wrench : range 0.20 to 3.60 m.daN
R (2.00 to 26.00 lbf.ft)

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 B. Consumable Materials

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

No specific corrosion-resistant-steel lockwire 0.4 mm (0.016

in.) dia.
Material No. 07-001B
ELECTRICAL BONDING COATING (BLUE COLOR)
(Ref. 20-31-00)
R Material No. 09-016 USA MIL-PRF-81733D TYPE II CLASS B
CORROSION INHIBITING FILLET CONSISTENCY
(Ref. 20-31-00)
Material No. 11-003 USA TT-M-261
METHYL-ETHYL-KETONE (Ref. 20-31-00)
Material No. 11-004 USA MIL-T-81533
1.1.1TRICHLOROETHANE (METHYL CHLOROFORM)
(Ref. 20-31-00)
Material No. 16-003 F ASNB70720
COATING (OBSOLETE USE 16-021) (Ref. 20-31-00)
Material No. 19-002 USA MIL-T-713
SYNTHETIC FIBRE CORD (NYLON) 2.5MM DIA.
(Ref. 20-31-00)

C. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

20-28-00-912-005 Electrical Bonding of Antennas With Conductive Bolts.

34-43-00-740-001 BITE Test of the TCAS
34-43-11-991-001 Fig. 401

3. __________
Job Set-up

Subtask 34-43-11-860-050

A. Get Access

(1) Make sure that the access platform is in position at zone 230 to get
access to the TCAS top antenna 7SG1.

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 Subtask 34-43-11-865-051

B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and
tagged

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------

R **ON A/C 005-099,

121VU COM NAV/TCAS 4SG K10

**ON A/C ALL

4. Procedure
_________

WARNING : DO NOT GET THE COMPOUND ON YOUR SKIN.

_______
IF YOU DO:
- RUB IT OFF IMMEDIATELY WITH A CLEAN CLOTH
- WASH THE SKIN WITH SOAP AND RINSE WITH CLEAN WATER.

WARNING : IF YOU GET THE FLUID ON YOUR SKIN OR IN YOUR EYES:

_______
- FLUSH IT AWAY WITH CLEAN WATER
- GET MEDICAL AID.

Subtask 34-43-11-420-050

A. Installation of the TCAS Antenna

(Ref. Fig. 401/TASK 34-43-11-991-001)

WARNING : OBEY THE COLOR CODES WHEN YOU CONNECT THE ELECTRICAL CONNECTORS
_______
(THIS WILL PREVENT CROSS-CONNECTIONS).
MAKE SURE THAT YOU INSTALL THE ANTENNA IN THE CORRECT
DIRECTION. IF THE ANTENNA DOES NOT POINT IN THE CORRECT
DIRECTION, THE TCAS WILL ONLY SENSE TRAFFIC BEHIND THE
AIRCRAFT.

(1) Remove the used sealant from the fuselage structure (1) with a
nonmetallic scraper.

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 (2) Clean the component interface and/or the adjacent area with CLEANING
AGENTS (Material No. 11-004) and a lint-free cloth.

NOTE : If you install the same antenna it is necessary to clean it

____
with CLEANING AGENTS (Material No. 11-003).

(3) Do an inspection of the component interface and/or the adjacent area.

(4) Put the new O-ring (4) in the correct position on the antenna (6).

NOTE : If the O-ring has a flat face, make sure that this face is
____
against the antenna and not against the a/c surface.

(5) FOR 7SG1

Install the foam washer (5).

(6) Align the new gasket (3) with the screw holes.

(7) Remove the blanking caps from the coaxial connectors (2) and (7).

(8) Make sure that the electrical connectors are clean and in the correct
condition.

(9) Remove the masking tape from the coaxial cables and connect each
connector (2) to the related connector (7) (see color code).

(10) Safety the coaxial connectors (2) and (7) with corrosion-resistant-
steel lockwire 0.4 mm (0.016 in.) dia..

(11) Install the antenna (6) on the fuselage structure (1) with the screws
(9) and the washers (8) and then tighten:
- TORQUE the four outer screws to between 0.23 and 0.33 m.daN (20.35
and 29.20 lbf.in)
- TORQUE the four inner screws to between 0.12 and 0.16 m.daN (10.61
and 14.15 lbf.in)

(12) Make sure that the bonding contact resistance between the antenna (6)
and the fuselage structure (1) is not higher than 5 milliohms
(Ref. TASK 20-28-00-912-005).

(13) Install the MISCELLANEOUS (Material No. 19-002) (10) on the screw
heads with the SEALANTS (Material No. 09-016). This is necessary for
the subsequent removal of the antenna. (see detail on section B-B).

(14) Put a bead of SEALANTS (Material No. 09-016) around the antenna (6).

(15) Let the sealant become dry.

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 (16) Apply STRUCTURE PAINTS (Material No. 16-003) to the sealant around
the antenna and the screw heads.

(17) Apply PAINTS FOR DETAIL (INTERNAL AND EXTERN AL) (Material No. 07-
001B) to the sealant of the head of the screws (9).

Subtask 34-43-11-865-052

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
R 4SG

Subtask 34-43-11-740-050

C. Do the BITE test of the TCAS (Ref. TASK 34-43-00-740-001)

5. Close-up
________

Subtask 34-43-11-410-050

A. Close Access

(1) Make sure that the work area is clean and clear of tool(s) and other
items.

(2) For 7SG1 only.

Remove the access platform(s).

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 COMPUTER - TCAS (1SG) - REMOVAL/INSTALLATION
____________________________________________

TASK 34-43-34-000-001

Removal of the TCAS Computer (1SG)

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific blanking caps

No specific circuit breaker(s) safety clip(s)
No specific access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

34-43-34-991-001 Fig. 401

3. __________
Job Set-up

Subtask 34-43-34-865-050

A. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------

R **ON A/C 005-099,

121VU COM NAV/TCAS 4SG K10

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R **ON A/C ALL

Subtask 34-43-34-010-050

B. Get Access

(1) Put the access platform in position at the access door 824 in zone
128.

(2) Open the access door 824.

4. Procedure
_________

Subtask 34-43-34-020-050

A. Removal of the TCAS Computer

(Ref. Fig. 401/TASK 34-43-34-991-001)

(1) Loosen the nuts (4).

(2) Lower the nuts (4).

(3) Pull the TCAS computer (1) on its rack (3) to disconnect the
electrical connectors (2).

(4) Remove the TCAS computer (1) from its rack (3).

(5) Put blanking caps on the disconnected electrical connectors (2).

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 TCAS Computer
Figure 401/TASK 34-43-34-991-001

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 TASK 34-43-34-400-001

Installation of the TCAS Computer (1SG)

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

34-43-00-740-001 BITE Test of the TCAS

R 52-41-00-410-002 Close the Avionics Compartment Doors after Access
34-43-34-991-001 Fig. 401

3. __________
Job Set-up

Subtask 34-43-34-860-050

A. Aircraft Maintenance Configuration

(1) Make sure that the access platform is in position at the access door
824 in zone 128.

(2) Make sure that the access door 824 is open.

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 Subtask 34-43-34-865-051

B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and
tagged

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------

R **ON A/C 005-099,

121VU COM NAV/TCAS 4SG K10

**ON A/C ALL

4. Procedure
_________

Subtask 34-43-34-420-050

A. Installation of the TCAS Computer

(Ref. Fig. 401/TASK 34-43-34-991-001)

(1) Clean the component interface and/or the adjacent area.

(2) Do an inspection of the component interface and/or the adjacent area.

(3) Remove the blanking caps from the electrical connectors (2).

(4) Make sure that the electrical connectors are clean and in the correct
condition.

(5) Install the TCAS computer (1) on its rack (3) to connect the
electrical connectors (2).

(6) Engage the nuts (4) on the lugs (5) and tighten.

Subtask 34-43-34-865-052

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
4SG

Subtask 34-43-34-740-050

C. Do the BITE test of the TCAS (Ref. TASK 34-43-00-740-001).

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 5. Close-up
________

Subtask 34-43-34-860-051

A. Put the aircraft back to its initial configuration.

(1) Make sure that the work area is clean and clear of tool(s) and other
items.

Subtask 34-43-34-410-050

B. Close Access

R (1) Close the access door 824 (Ref. TASK 52-41-00-410-002).

(2) Remove the access platform(s).

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 ENHANCED GROUND PROXIMITY WARNING SYSTEM (GPWS) - DESCRIPTION AND OPERATION
___________________________________________________________________________

R 1. _______
General
R (Ref. Fig. 001)
R The purpose of the Enhanced Ground Proximity Warning System (Enhanced GPWS)
R is to alert the flight crew of potentially hazardous conditions with respect
R to the terrain.
R The system achieves this objective by accepting a variety of aircraft
R parameters as inputs, applying alerting algorithms, and providing the flight
R crew with aural alert messages and visual annunciations and displays in the
R event that the boundaries of any alerting envelope are exceeded.
R Enhanced features have been added to existing basic Ground Proximity Warning
R Modes 1 to 5 which are the backbone of the system.
R
Several main alerting functional areas are integrated into the Enhanced
GPWC, which is a single Line Replaceable Unit (LRU). Except for basic GPWS,
each function is pin selectable.
The functional areas are:
- basic Ground Proximity Warning System (GPWS) (Modes 1 to 5),
- Terrain Clearance Floor function (TCF),
- Terrain Awareness and Display (TAD) function.

A. Basic GPWS Modes

The basic GPWS modes generate aural and visual warnings if the aircraft
adopts a potentially hazardous condition with respect to:
Mode 1 - Excessive rate of descent.
Mode 2 - Excessive closure rate with terrain.
Mode 3 - Descent after takeoff and minimum terrain clearance.
Mode 4 - Unsafe terrain clearance.
Mode 5 - Descent below glide slope.

B. Enhanced Features
The Enhanced GPWC includes enhanced features which complete the basic
GPWS modes.

(1) Terrain Clearance Floor (TCF) function

The Terrain Clearance Floor (TCF) function adds an additional element
of protection to the basic GPWS modes. It creates an increasing
terrain clearance envelope around the intended airport runway
directly related to the distance from the runway. TCF alerts are
based on current aircraft location, nearest runway center point
position and radio altitude. TCF is active during takeoff, cruise and
final approach. This alert mode complements existing Mode 4
protection by providing an alert based on insufficient terrain
clearance even when in landing configuration. TCF function generates
aural and visual alert.

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 Enhanced GPWS - Enhanced Ground Proximity Warning System
Figure 001

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 (2) Terrain Awareness alerting and Display (TAD) function
A major new feature of the Enhanced GPWS is the incorporation of the
terrain awareness alerting and display functions. These functions use
aircraft geographic position, aircraft altitude and a terrain data
base to predict potential conflicts between the aircraft flight path
and the terrain, and to provide graphic displays of the conflicting
terrain, as illustrated by the block diagram.
(Ref. Fig. 002)
The terrain awareness alerting algorithms continuously compute
terrain clearance envelopes ahead of the aircraft. If the boundaries
of these envelopes conflict with terrain elevation data in the
terrain database, then alerts are issued.

2. Component
__________________
Location
(Ref. Fig. 003)

-------------------------------------------------------------------------------
FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA
| | | | DOOR | REF.
-------------------------------------------------------------------------------
1WZ GPWC 88VU 128 824 34-48-34
4WZ P/BSW-GPWS/G/S 500VU 212 831 34-48-00
5WZ P/BSW-GPWS/G/S 301VU 211 831 34-48-00
7WZ P/BSW-GPWS/FLAP MODE 21VU 211 831 34-48-00
9WZ P/BSW-GPWS/SYS 21VU 211 831 34-48-00
11WZ P/BSW-GPWS/G/S MODE 21VU 211 831 34-48-00
13WZ P/BSW-GPWS/LDG FLAP 3 21VU 211 831 34-48-00
30WZ1 P/BSW-TERR ON ND,CAPT 403VU 211 831 34-48-00
30WZ2 P/BSW-TERR ON ND,F/O 402VU 212 831 34-48-00
31WZ P/BSW-GPWS/TERR 21VU 211 831 34-48-00
32WZ RELAY-TERRAIN/WEATHER RADAR 1 DATA 187VU 127 824 34-48-00
SWITCHING, F/O
33WZ RELAY-TERRAIN/WEATHER RADAR 1 DATA 187VU 127 824 34-48-00
SWITCHING, CAPT

3. __________________
System Description

A. General
The Enhanced GPWS monitors data inputs from the navigation sensors. This
information is used to provide suitable aural and visual warnings to
alert the crew of a hazardous situation with respect to the terrain.

B. Warnings
Warnings are generated by the Enhanced GPWC which is installed on the
shelf 88VU, in the aft electronics rack 80VU.
Aural warnings are broadcast from the cockpit loud speakers.

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 Enhanced GPWS - Terrain Awareness Functions
Figure 002

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 Enhanced GPWS - Component Location
Figure 003

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R **ON A/C 001-004,

C. Digital Data Inputs

(Ref. Fig. 004)
The Enhanced GPWC receives serial digital data inputs from:
- radio altimeter transceiver 1 (radio altitude),
- Air Data/Inertial Reference Unit 1 (ADIRU),
- ADR portion (barometric altitude, barometric altitude rate, computed
airspeed),
- IR portion (latitude, longitude, magnetic heading),
- ILS receiver 1 (glide slope deviation, localizer deviation, selected
runway heading),
- Flight Management and Guidance Computer (FMGC) (latitude, longitude,
track, navigation modes),
- Centralized Fault Display Interface Unit (CFDIU) (command word, date,
flight number, UTC),
- Flight Control Unit (FCU) 1 and 2 (CAPT and F/O ranges),
- Weather Radar 1 (hazard bus).

**ON A/C ALL

R Post SB 34-1147 For A/C 001-004,

C. Digital Data Inputs

(Ref. Fig. 004A)
The Enhanced GPWC receives serial digital data inputs from:
- radio altimeter transceiver 1 (radio altitude),
- Air Data/Inertial Reference Unit 1 (ADIRU),
- ADR portion (barometric altitude, barometric altitude rate, computed
airspeed),
- IR portion (latitude, longitude, magnetic heading),
- Multi-Mode Receiver 1 (MMR) (glide slope deviation, localizer
deviation, selected runway heading),
- Flight Management and Guidance Computer (FMGC) (latitude, longitude,
track, navigation modes),
- Centralized Fault Display Interface Unit (CFDIU) (command word, date,
flight number, UTC),
- Flight Control Unit (FCU) 1 and 2 (CAPT and F/O ranges),
- Weather Radar 1 (hazard bus).

**ON A/C ALL

D. Discrete Data Inputs

(Ref. Fig. 005)
Discrete data inputs are received from the following:
- Slat Flap Control Computer 1 (SFCC) (3 and FULL flap position),
- Flight Warning Computer 1 and 2 (FWC) (all audio inhibition),

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 Enhanced GPWC - Inputs and Outputs (Buses)
Figure 004

R
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R Enhanced GPWC - Inputs and Outputs (Buses)
R Figure 004A

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R Enhanced GPWC - Inputs (Discretes)
R Figure 005

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 - Landing Gear Control and Interface Unit (LGCIU) (main landing gear
retracted or extended),
- ECAM control panel (audio suppression),
- GPWS/FLAP MODE pushbutton switch which, when pressed (in) (white OFF
legend on), overrides a flap abnormal condition input,
- GPWS/SYS pushbutton switch which, when pressed (in) (white OFF legend
on), inhibits Modes 1 to 5 warnings,
- GPWS/G/S MODE pushbutton switch which, when pressed (in) (white OFF
legend on), overrides the glide slope mode,
- GPWS/G/S pushbutton switch which, when pressed (in), enables the
Enhanced GPWC to perform test,
- GPWS/TERR pusbutton switch which, when pressed (in) (white OFF legend
on), inhibits TAD and TCF functions,
- TERR ON ND (CAPT or F/O) pushbutton switches allow the crew to select
or deselect terrain display on ND<s,
- Weather Radar control unit.

E. Warning Outputs
(Ref. Fig. 006)
- two discrete outputs from the Enhanced GPWC control the GPWS/G/S
pushbutton switches located on Captain and First Officer main
instrument panels.
Each pushbutton switch is a momentary-action pushbutton switch with an
illuminated split legend cap. The upper legend identified GPWS,
controlled by the first output, comes on red when a ground proximity
warning is generated by the Enhanced GPWC for Modes 1 to 4 or TAD and
TCF warnings.
The lower legend identified G/S, controlled by the second output, comes
on amber when a glide slope (Mode 5) caution alert is generated by the
Enhanced GPWC.
The pushbutton switch provides a facility to cancel a glide slope
warning, if in progress, or to initiate an Enhanced GPWS self-test.
- both discrete outputs are also used to inhibit TCAS and automatic call
out when the GPWS or G/S warnings are in progress.
- both discrete outputs are also used for the Digital Flight Data
Recorder (DFDR).

-------------------------------------------------------------------------------
NAME ELECTRICAL LEVEL TO SIGNAL STATUS
-------------------------------------------------------------------------------
FAULT LEGEND GND/OC SYS P/BSW/SDACs GND = VALID
G/S VISUAL ALERT GND/OC FWCs GND = VALID
GPWS LEGEND GND/OC FWCs GND = VALID
-------------------------------------------------------------------------------

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 Enhanced GPWC - Outputs
Figure 006

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 F. Monitor Outputs
There are two monitor outputs:
- GPWS monitor output controls the FAULT legend of the SYS pushbutton
switch and indicates a failure of Modes 1 to 5,
- TERR monitor output controls the FAULT legend of the TERR pushbutton
switch and indicates a failure of TAD and TCF functions.

-------------------------------------------------------------------------------
NAME ELECTRICAL LEVEL TO SIGNAL STATUS
-------------------------------------------------------------------------------
GPWS MONITOR OUTPUT GND/OC BOARD-ANN LT GND=FAULT
TEST and INTFC
SDAC1
SDAC2
TERR MONITOR OUTPUT GND/OC BOARD-ANN LT GND=FAULT
TEST and INTFC
SDAC1
SDAC2
-------------------------------------------------------------------------------

G. Bus Output
The bus output is used by the Aircraft Integrated Data System (AIDS),
Data Management Unit (DMU) and by the Centralized Fault Display Interface
Unit (CFDIU) for test causes.

H. Audio Output
The audio output is used by the cockpit loud speakers for aural warning
messages.

4. Power
____________
Supply
(Ref. Fig. 006)
The Enhanced GPWC power supply circuits receive 115VAC, 400 Hz, single phase
(22 W max.) supply from the aircraft AC power.

5. Interface
_________

A. Digital Outputs
This table contains all the output parameters in digital form.
They are sorted as per the numerical order of their output label.
The following table gives:
- EQ.SYS.LAB.SDI: output label for which the parameter is available,
- PARAMETER DEFINITION: parameter name,
- WORD RANGE/OPER RANGE/RESOLUTION ACCURACY: measurement range. Maximum
value transmitted. When the digital value changes, the change step is
equal to the accuracy,
- UNIT: unit in which the digital value is transmitted,
- SIG BIT: indicates whether a sign bit is available,

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 - BITS: number of bits used by the parameter in the label,
- XMSN/INTV: output transmission interval. The refresh rate is given in
milliseconds,
- CODE:
BNR: binary data word
BCD: binary coded decimal data word
ISO: data word coded in ISO5 code
DIS: discrete data word
HEX: hexadecimal coded
HYB: mixed code
- ALPHA CODE: indicates the parameter mnemonic code,
- SOURCE ORIGIN: parameter source computer or system.

-------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
| 1.270.00 |ENH. GPWS |(1=voice on)| | | | 50 |DIS | | |
| |ALER DSCRT| | | | | to | | | |
| |WORD 1 | | | | |100 | | | |
| | | | | | | | | | |
| |SINKRATE- |bit status 1| | | 11 | | | | |
| |PAUSE- | | | | | | | | |
| |SINKRATE | | | | | | | | |
| | | | | | | | | | |
| |PULL UP |bit status 1| | | 12 | | | | |
| | | | | | | | | | |
| |TERRAIN |bit status 1| | | 13 | | | | |
| | | | | | | | | | |
| |DON<T SINK|bit status 1| | | 14 | | | | |
| |-PAUSE- | | | | | | | | |
| |DON<T SINK| | | | | | | | |
| | | | | | | | | | |
| |TOO LOW |bit status 1| | | 15 | | | | |
| |GEAR | | | | | | | | |
| | | | | | | | | | |
| |TOO LOW |bit status 1| | | 16 | | | | |
| |FLAPS | | | | | | | | |
| | | | | | | | | | |
| |TOO LOW |bit status 1| | | 17 | | | | |
| |TERRAIN | | | | | | | | |
| | | | | | | | | | |

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 -------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
| |GLIDESLOPE|bit status 1| | | 18 | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 19 | | | | |
| | | | | | | | | | |
| |TERRAIN |bit status 1| | | 20 | | | | |
| |PULL UP | | | | | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 21 | | | | |
| | | | | | | | | | |
| |TERRAIN |bit status 1| | | 22 | | | | |
| |AHEAD PULL| | | | | | | | |
| |UP | | | | | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 23 | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 24 | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 25 | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 26 | | | | |
| | | | | | | | | | |
| |TERRAIN |bit status 1| | | 27 | | | | |
| |AHEAD | | | | | | | | |
| | | | | | | | | | |
| |SPARE | | | | 28 | | | | |
| | | | | | | | | | |
| |Reserved | | | | 29 | | | | |
| |for obsta.| | | | | | | | |
| |voice | | | | | | | | |
| 1.274.00 |ENH. GPWS |(W1W= on) | | | | 50 |DIS | | |
| |ALER DSCRT| | | | | to | | | |
| |WORD 2 | | | | |100 | | | |
| | | | | | | | | | |
| |G/S CANCEL|bit status 1| | | 11 | | | | |
| | | | | | | | | | |
| |GPWS ALERT|bit status 1| | | 12 | | | | |
| | | | | | | | | | |
| |GPWS |bit status 1| | | 13 | | | | |

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 -------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
| |WARNING | | | | | | | | |
| | | | | | | | | | |
| |GPWS INOP |bit status 1| | | 14 | | | | |
| | | | | | | | | | |
| |WINDSHEAR |bit status 1| | | 15 | | | | |
| |WARNING | | | | | | | | |
| |(IF WR/PWS| | | | | | | | |
| |INSTALLED)| | | | | | | | |
| | | | | | | | | | |
| |AUDIO ON |bit status 1| | | 16 | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 17 | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 18 | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 19 | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 20 | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 21 | | | | |
| | | | | | | | | | |
| |TERRAIN |bit status 1| | | 22 | | | | |
| |AWARENESS | | | | | | | | |
| |WARNING | | | | | | | | |
| | | | | | | | | | |
| |TERRAIN |bit status 1| | | 23 | | | | |
| |AWARENESS | | | | | | | | |
| |CAUTION | | | | | | | | |
| | | | | | | | | | |
| |TERRAIN |bit status 1| | | 24 | | | | |
| |AWARENESS | | | | | | | | |
| |INOP | | | | | | | | |
| | | | | | | | | | |
| |EXTERNAL |bit status 1| | | 25 | | | | |
| |FAULT | | | | | | | | |
| | | | | | | | | | |
| |COMPUTER |bit status 1| | | 26 | | | | |
| |FAIL | | | | | | | | |

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 -------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
| | | | | | | | | | |
| |TERRAIN |bit status 1| | | 27 | | | | |
| |AWARENESS | | | | | | | | |
| |NOT AVAIL.| | | | | | | | |
| | | | | | | | | | |
| |TERRAIN |bit status 1| | | 28 | | | | |
| |DISPLAY | | | | | | | | |
| |DSCRT 1 | | | | | | | | |
| | | | | | | | | | |
| |TERRAIN |bit status 1| | | 29 | | | | |
| |DISPLAY | | | | | | | | |
| |DSCRT 2 | | | | | | | | |
| | | | | | | | | | |
| 1.271.00 |ENH. GPWS |(W1W= warn. | | | |100 |DIS | | |
| |LOGIC DSCR|in progress)| | | | to | | | |
| | | | | | |200 | | | |
| | | | | | | | | | |
| |NOT USED | | | | 11 | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 12 | | | | |
| | | | | | | | | | |
| |TERRAIN |bit status 1| | | 13 | | | | |
| |CLEARANCE | | | | | | | | |
| |FLOOR ALER| | | | | | | | |
| | | | | | | | | | |
| |ENV.MOD IN|bit status 1| | | 14 | | | | |
| |PROGRESS | | | | | | | | |
| | | | | | | | | | |
| |ENV.MOD |bit status 1| | | 15 | | | | |
| |SNAPSHOT | | | | | | | | |
| |LATCH SET | | | | | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 16 | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 17 | | | | |
| | | | | | | | | | |
| |TAKE OFF |bit status 1| | | 18 | | | | |
| |MODE | | | | | | | | |

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 -------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
| | | | | | | | | | |
| |MODE 1 |bit status 1| | | 19 | | | | |
| |SINKRATE | | | | | | | | |
| | | | | | | | | | |
| |MODE 1 |bit status 1| | | 20 | | | | |
| |PULL UP | | | | | | | | |
| | | | | | | | | | |
| |MODE 2 |bit status 1| | | 21 | | | | |
| |TERRAIN | | | | | | | | |
| | | | | | | | | | |
| |MODE 2 |bit status 1| | | 22 | | | | |
| |PULL UP | | | | | | | | |
| | | | | | | | | | |
| |MODE 3 |bit status 1| | | 23 | | | | |
| |VISUAL | | | | | | | | |
| | | | | | | | | | |
| |MODE 4 |bit status 1| | | 24 | | | | |
| |VISUAL | | | | | | | | |
| | | | | | | | | | |
| |MODE 5 |bit status 1| | | 25 | | | | |
| |VISUAL | | | | | | | | |
| | | | | | | | | | |
| |MODE 7 |bit status 1| | | 26 | | | | |
| |VISUAL | | | | | | | | |
| |ALERT | | | | | | | | |
| | | | | | | | | | |
| |TERRAIN |bit status 1| | | 27 | | | | |
| |AWARENESS | | | | | | | | |
| |CAUTION | | | | | | | | |
| | | | | | | | | | |
| |TERRAIN |bit status 1| | | 28 | | | | |
| |AWARENESS | | | | | | | | |
| |WARNING | | | | | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 29 | | | | |
| | | | | | | | | | |
| 1.300.00 |ENH. GPWC | | | | | 50 |DIS | | |
| |ALERT DSCR| | | | | to | | | |

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 -------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
| |WORD3 | | | | |100 | | | |
| | | | | | | | | | |
| |MODES 1 TO| | | | 11 | | | | |
| |4 INOP | | | | | | | | |
| | | | | | | | | | |
| |MODE 5 | | | | 12 | | | | |
| |INOP | | | | | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 13 | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 14 | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 15 | | | | |
| | | | | | | | | | |
| |TERR CLEA.| | | | 16 | | | | |
| |FLOOR INOP| | | | | | | | |
| | | | | | | | | | |
| |TERR AWAR.| | | | 17 | | | | |
| |INOP | | | | | | | | |
| | | | | | | | | | |
| |ENV. MODU.| | | | 18 | | | | |
| |INOP | | | | | | | | |
| | | | | | | | | | |
| |SPARE | | | | 19 | | | | |
| | | | | | | | | | |
| |SPARE | | | | 20 | | | | |
| | | | | | | | | | |
| |SPARE | | | | 21 | | | | |
| | | | | | | | | | |
| |SPARE | | | | 22 | | | | |
| | | | | | | | | | |
| |SPARE | | | | 23 | | | | |
| | | | | | | | | | |
| |SPARE | | | | 24 | | | | |
| | | | | | | | | | |
| |SPARE | | | | 25 | | | | |
| | | | | | | | | | |
| |SPARE | | | | 26 | | | | |

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 -------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
| | | | | | | | | | |
| |SPARE | | | | 27 | | | | |
| | | | | | | | | | |
| |SPARE | | | | 28 | | | | |
| | | | | | | | | | |
| |SPARE | | | | 29 | | | | |
| | | | | | | | | | |
| 1.275.00 |PROGRAM |(W1W=Open | | | |100 |DIS | | |
| |PIN STATUS|W0W=Ground) | | | | to | | | |
| |WORD 1 | | | | |200 | | | |
| | | | | | | | | | |
| |NOT USED | | | | 11 | | | | |
| | | | | | | | | | |
| |CFDS |bit status 1| | | 12 | | | | |
| |ENABLE | | | | | | | | |
| | | | | | | | | | |
| |AIRCRAFT | | | | 13 | | | | |
| |SELECT 6 | | | | | | | | |
| | | | | | | | | | |
| |AIRCRAFT | | | | 14 | | | | |
| |SELECT 1 | | | | | | | | |
| | | | | | | | | | |
| |AIRCRAFT | | | | 15 | | | | |
| |SELECT 2 | | | | | | | | |
| | | | | | | | | | |
| |AIRCRAFT | | | | 16 | | | | |
| |SELECT 3 | | | | | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 17 | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 18 | | | | |
| | | | | | | | | | |
| |AUDIO |bit status 0| | | 19 | | | | |
| |DECLUTTER | | | | | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 20 | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 21 | | | | |

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 -------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
| | | | | | | | | | |
| |AIRCRAFT | | | | 22 | | | | |
| |SELECT 7 | | | | | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 23 | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 24 | | | | |
| | | | | | | | | | |
| |AIRCRAFT | | | | 25 | | | | |
| |SELECT 5 | | | | | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 26 | | | | |
| | | | | | | | | | |
| |AIRCRAFT | | | | 27 | | | | |
| |SELECT 4 | | | | | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 28 | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 29 | | | | |
| | | | | | | | | | |
| 1.276.00 |PROGRAM |(W1W=Open | | | |100 |DIS | | |
| |PIN STATUS|W0W=Ground) | | | | to | | | |
| |WORD 2 | | | | |200 | | | |
| | | | | | | | | | |
| |VOICE | | | | 11 | | | | |
| |SELECT 1 | | | | | | | | |
| | | | | | | | | | |
| |VOICE | | | | 12 | | | | |
| |SELECT 2 | | | | | | | | |
| | | | | | | | | | |
| |VOICE | | | | 13 | | | | |
| |SELECT 3 | | | | | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 14 | | | | |
| | | | | | | | | | |
| |AUDIO |bit status 1| | | 15 | | | | |
| |SUPPRESS | | | | | | | | |
| | | | | | | | | | |

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 -------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
| |ATERNATE |bit status 1| | | 16 | | | | |
| |MODE 4 | | | | | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 17 | | | | |
| | | | | | | | | | |
| |FMGC |bit status 1| | | 18 | | | | |
| |SELECT | | | | | | | | |
| | | | | | | | | | |
| |ALTERN. |bit status 1| | | 19 | | | | |
| |G/S CANCEL| | | | | | | | |
| | | | | | | | | | |
| |LAMP |bit status 1| | | 20 | | | | |
| |FORMAT | | | | | | | | |
| | | | | | | | | | |
| |QFE/QNH |bit status 1| | | 21 | | | | |
| |SELECT |=QFE SELECT | | | | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 22 | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 23 | | | | |
| | | | | | | | | | |
| |G/S |bit status 1| | | 24 | | | | |
| |INHIBIT | | | | | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 25 | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 26 | | | | |
| | | | | | | | | | |
| |AIRCRAFT | | | | 27 | | | | |
| |SELECT 8 | | | | | | | | |
| | | | | | | | | | |
| |AIRCRAFT | | | | 28 | | | | |
| |SELECT 9 | | | | | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 29 | | | | |
| | | | | | | | | | |
| 1.277.00 |PROGRAM |(W1W=Open | | | |100 |DIS | | |
| |PIN STATUS|W0W=Ground) | | | | to | | | |

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 -------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
| |WORD 3 | | | | |200 | | | |
| | | | | | | | | | |
| |ALTER.VOL.|bit status 1| | | 11 | | | | |
| |SELECTED | | | | | | | | |
| | | | | | | | | | |
| |SPARE | | | | 12 | | | | |
| | | | | | | | | | |
| |SPARE | | | | 13 | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 14 | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 15 | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 16 | | | | |
| | | | | | | | | | |
| |TCF |bit status 1| | | 17 | | | | |
| |DISABLE | | | | | | | | |
| | | | | | | | | | |
| |TAD |bit status 1| | | 18 | | | | |
| |DISABLE | | | | | | | | |
| | | | | | | | | | |
| |SPARE | | | | 19 | | | | |
| | | | | | | | | | |
| |SPARE | | | | 20 | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 21 | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 22 | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 23 | | | | |
| | | | | | | | | | |
| |SPARE | | | | 24 | | | | |
| | | | | | | | | | |
| |SPARE | | | | 25 | | | | |
| | | | | | | | | | |
| |SPARE | | | | 26 | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 27 | | | | |

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 -------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
| | | | | | | | | | |
| |NOT USED | | | | 28 | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 29 | | | | |
| | | | | | | | | | |
| 1.350.00 |FAULT |(W1W=Failed)| | | |100 |DIS | | |
| |DIAGNOSTIC| | | | | to | | | |
| |WORD 1 | | | | |200 | | | |
| | | | | | | | | | |
| |ARINC 429 | | | | 11 | | | | |
| |IR1 INPUT | | | | | | | | |
| |INACTIVE | | | | | | | | |
| | | | | | | | | | |
| |ARINC 429 | | | | 12 | | | | |
| |FMGC1 | | | | | | | | |
| |INPUT | | | | | | | | |
| |INACTIVE | | | | | | | | |
| | | | | | | | | | |
| |ARINC 429 | | | | 13 | | | | |
| |ADR1 INPUT| | | | | | | | |
| |INACTIVE | | | | | | | | |
| | | | | | | | | | |
| |ARINC 429 | | | | 14 | | | | |
| |FCU BUS 1 | | | | | | | | |
| |INPUT | | | | | | | | |
| |INACTIVE | | | | | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 15 | | | | |
| | | | | | | | | | |
| |ARINC 429 | | | | 16 | | | | |
| |ILS1 INPUT| | | | | | | | |
| |INACTIVE | | | | | | | | |
| | | | | | | | | | |
| |ARINC 429 | | | | 17 | | | | |
| |FMGC1(Nav | | | | | | | | |
| |Modes) IN.| | | | | | | | |
| |INACTIVE | | | | | | | | |
| | | | | | | | | | |

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 -------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
| |ARINC 429 | | | | 18 | | | | |
| |RA1 INPUT | | | | | | | | |
| |INACTIVE | | | | | | | | |
| | | | | | | | | | |
| |ARINC 429 | | | | 19 | | | | |
| |FCU BUS 2 | | | | | | | | |
| |INPUT | | | | | | | | |
| |INACTIVE | | | | | | | | |
| | | | | | | | | | |
| |ARINC 429 | | | | 20 | | | | |
| |CFDIU | | | | | | | | |
| |INPUT | | | | | | | | |
| |INACTIVE | | | | | | | | |
| | | | | | | | | | |
| |ARINC 429 | | | | 21 | | | | |
| |WXR HZD | | | | | | | | |
| |BUS1 INPUT| | | | | | | | |
| |INACTIVE | | | | | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 22 | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 23 | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 24 | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 25 | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 26 | | | | |
| | | | | | | | | | |
| |PROGRAM | | | | 27 | | | | |
| |PIN FAULT | | | | | | | | |
| | | | | | | | | | |
| |FLAP | | | | 28 | | | | |
| |INPUT FAI.| | | | | | | | |
| | | | | | | | | | |
| |GEAR | | | | 29 | | | | |
| |INPUT FAI.| | | | | | | | |
| | | | | | | | | | |

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 -------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
| 1.351.00 |FAULT |(W1W=Failed)| | | |100 |DIS | | |
| |DIAGNOSTIC| | | | | to | | | |
| |WORD 2 | | | | |200 | | | |
| | | | | | | | | | |
| |G/S CANCEL| | | | 11 | | | | |
| |DSCR. FAI.| | | | | | | | |
| | | | | | | | | | |
| |MOMENTARY | | | | 12 | | | | |
| |AUDIO SUPP| | | | | | | | |
| |DSCR. FAI.| | | | | | | | |
| | | | | | | | | | |
| |AUDIO | | | | 13 | | | | |
| |INHIBIT | | | | | | | | |
| |DSCR. FAI.| | | | | | | | |
| | | | | | | | | | |
| |SELF-TEST | | | | 14 | | | | |
| |DSCR INPUT| | | | | | | | |
| |FAILED | | | | | | | | |
| | | | | | | | | | |
| |SUPPORT | | | | 15 | | | | |
| |TASK FAULT| | | | | | | | |
| | | | | | | | | | |
| |NVM FAULT | | | | 16 | | | | |
| | | | | | | | | | |
| |WATCHDOG | | | | 17 | | | | |
| |TIMER FAUL| | | | | | | | |
| | | | | | | | | | |
| |A/D FAIL | | | | 18 | | | | |
| | | | | | | | | | |
| |VOICE FAIL| | | | 19 | | | | |
| | | | | | | | | | |
| |DITS | | | | 20 | | | | |
| |OUTPUT FAI| | | | | | | | |
| | | | | | | | | | |
| |TERRAIN | | | | 21 | | | | |
| |DATABASE | | | | | | | | |
| |FAULT | | | | | | | | |
| | | | | | | | | | |

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 -------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
| |FLASH FILE| | | | 22 | | | | |
| |SYSTEM | | | | | | | | |
| |WRITE | | | | | | | | |
| |FAULT | | | | | | | | |
| | | | | | | | | | |
| |DITS INPUT| | | | 23 | | | | |
| |FAIL | | | | | | | | |
| | | | | | | | | | |
| |VOICE | | | | 24 | | | | |
| |FAULT | | | | | | | | |
| | | | | | | | | | |
| |SYSTEM OR | | | | 25 | | | | |
| |MODE TASK | | | | | | | | |
| |FAULT | | | | | | | | |
| | | | | | | | | | |
| |ENV. MOD. | | | | 26 | | | | |
| |DATABASE | | | | | | | | |
| |FAULT | | | | | | | | |
| | | | | | | | | | |
| |WATCHDOG | | | | 27 | | | | |
| |FAIL COUNT| | | | | | | | |
| | | | | | | | | | |
| |AIRCRAFT | | | | 28 | | | | |
| |DATABASE | | | | | | | | |
| |FAULT WORW| | | | | | | | |
| |CRC FAULT | | | | | | | | |
| | | | | | | | | | |
| |IMAGE DSP | | | | 29 | | | | |
| |FAULT | | | | | | | | |
| | | | | | | | | | |
| 1.355.00 |FAULT |(W1W=Failed)| | | |100 |DIS | | |
| |DIAGNOSTIC| | | | | to | | | |
| |WORD 3 | | | | |200 | | | |
| | | | | | | | | | |
| |NOT USED | | | | 11 | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 12 | | | | |
| | | | | | | | | | |

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 -------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
| |NOT USED | | | | 13 | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 14 | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 15 | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 17 | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 18 | | | | |
| | | | | | | | | | |
| |SPARE | | | | 19 | | | | |
| | | | | | | | | | |
| |SPARE | | | | 20 | | | | |
| | | | | | | | | | |
| |SPARE | | | | 21 | | | | |
| | | | | | | | | | |
| |SPARE | | | | 22 | | | | |
| | | | | | | | | | |
| |SPARE | | | | 23 | | | | |
| | | | | | | | | | |
| |SPARE | | | | 24 | | | | |
| | | | | | | | | | |
| |SPARE | | | | 25 | | | | |
| | | | | | | | | | |
| |SPARE | | | | 26 | | | | |
| | | | | | | | | | |
| |SPARE | | | | 27 | | | | |
| | | | | | | | | | |
| |SPARE | | | | 28 | | | | |
| | | | | | | | | | |
| |SPARE | | | | 29 | | | | |
| | | | | | | | | | |
| 1.357.00 |INPUT | | | | |100 |DIS | | |
| |DSCRT STAT| | | | | to | | | |
| |WORD 1 | | | | |200 | | | |
| | | | | | | | | | |
| |NOT USED | | | | 11 | | | | |
| | | | | | | | | | |

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 -------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
| |G/S |(W1W= | | | 12 | | | | |
| |INHIBIT |inhibit) | | | | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 13 | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 14 | | | | |
| | | | | | | | | | |
| |GPWS MODES|(W1W= | | | 15 | | | | |
| |1 TO 5 |inhibit) | | | | | | | |
| |INHIBIT | | | | | | | | |
| |(AUDIO AND| | | | | | | | |
| |VISUAL) | | | | | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 16 | | | | |
| | | | | | | | | | |
| |MOMENTARY |(W1W= | | | 17 | | | | |
| |AUDIO SUPP|suppress) | | | | | | | |
| | | | | | | | | | |
| |SELF-TEST | | | | 18 | | | | |
| | | | | | | | | | |
| |LANDING |(W1W= down) | | | 19 | | | | |
| |GEAR | | | | | | | | |
| | | | | | | | | | |
| |LANDING |(W1W= | | | 20 | | | | |
| |FLAPS |extended) | | | | | | | |
| | | | | | | | | | |
| |G/S CANCEL|(W1W= | | | 21 | | | | |
| | |cancelled) | | | | | | | |
| | | | | | | | | | |
| |WXR 1 |(W1W= ON) | | | 22 | | | | |
| |ON/OFF | | | | | | | | |
| | | | | | | | | | |
| |TAD AND |(W1W= | | | 23 | | | | |
| |TCF |inhibit) | | | | | | | |
| |INHIBIT | | | | | | | | |
| | | | | | | | | | |
| |TERR ON ND| | | | 25 | | | | |
| |CAPT INPUT| | | | | | | | |

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 -------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
| | | | | | | | | | |
| |TERR ON ND| | | | 26 | | | | |
| |F/O INPUT | | | | | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 27 | | | | |
| | | | | | | | | | |
| |NOT USED | | | | 28 | | | | |
| | | | | | | | | | |
| |ALL AUDIO |(W1W= | | | 29 | | | | |
| |INHIBIT |inhibit) | | | | | | | |
-------------------------------------------------------------------------------

6. _____________________
Component Description

A. Enhanced GPWC

(1) External descrition

(Ref. Fig. 007)
The Enhanced GPWC is packaged in a 2 MCU ARINC 600-6 form factor
enclosure.
The enclosure of the unit is painted with a blue semi-gloss coating,
except for the bottom, which is unpainted.
The computer is composed of the following subassemblies:
- rear panel assembly,
- front panel assembly,
- chassis,
- PCMCIA interface,
- front connector.

(a) Rear panel assembly

The rear panel assembly contains a 2 MCU ARINC 600-6 form
aircraft interface connector. The top and middle shells contain
all interface signals. Power interface is in the bottom shell,
isolated from interface signals. Connector index pin coding is
orientation W08W or W10W in accordance with ARINC 723-1
recommendations for GPWS.

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 Enhanced GPWC
Figure 007

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 The rear panel assembly also contains the interconnection between
the aircraft interface connector and the internal interface
Circuit Card Assembly (CCA), A5, and the Backplane CCA, A4, which
provide all internal electrical interconnects between CCAs and
other circuitry.
The Enhanced GPWC pins are listed in the table below (N/U means
Not Used):

---------------------------------------------------------
|LRU Con |Pin| Description |
---------------------------------------------------------
| MIDDLE | 6A| 429 INPUT 1(A) ADIRU1 BUS IR (A) |
| MIDDLE | 6B| 429 INPUT 1(B) ADIRU1 BUS IR (B) |
| TOP | 9A| 429 INPUT 10(A) CFDIU (A) |
| TOP | 9B| 429 INPUT 10(B) CFDIU (B) |
| TOP | 8A| 429 INPUT 11(A) WXR1 HZD BUS (A) |
| TOP | 8B| 429 INPUT 11(B) WXR1 HZD BUS (B) |
| TOP | 8C| 429 INPUT 12(A) N/U |
| TOP | 8D| 429 INPUT 12(B) N/U |
| TOP | 5A| 429 INPUT 13(A) N/U |
| TOP | 6A| 429 INPUT 13(B) N/U |
| TOP | 1C| 429 INPUT 14(A) N/U |
| TOP | 1D| 429 INPUT 14(B) N/U |
| TOP | 4A| 429 INPUT 15(A) N/U |
| TOP | 4B| 429 INPUT 15(B) N/U |
| MIDDLE |10C| 429 INPUT 2(A) FMGC1 (A) |
| MIDDLE |10D| 429 INPUT 2(B) FMGC1 (B) |
| MIDDLE |11A| 429 INPUT 3(A) ADIRU 1 BUS ADR (A) |
| MIDDLE |11B| 429 INPUT 3(B) ADIRU 1 BUS ADR (B) |
| MIDDLE |12A| 429 INPUT 4(A) FCU 1 (A) |
| MIDDLE |12B| 429 INPUT 4(B) FCU 1 (B) |
| MIDDLE |10A| 429 INPUT 5(A) N/U |
| MIDDLE |10B| 429 INPUT 5(B) N/U |
| MIDDLE |11C| 429 INPUT 6(A) ILS 1 (A) |
| MIDDLE |11D| 429 INPUT 6(B) ILS 1 (B) |
| MIDDLE |12C| 429 INPUT 7(A) FMGC 1 DISCWORD (A) |
| MIDDLE |12D| 429 INPUT 7(B) FMGC 1 DISCWORD (B) |
| MIDDLE |13A| 429 INPUT 8(A) RA 1 (A) |
| MIDDLE |13B| 429 INPUT 8(B) RA 1 (B) |
| TOP | 9C| 429 INPUT 9(A) FCU 2 (A) |
| TOP | 9D| 429 INPUT 9(B) FCU 2 (B) |
| MIDDLE | 1C| 429 OUTPUT 1(A) CFDIU (A) |
| MIDDLE | 1D| 429 OUTPUT 1(B) CFDIU (B) |
| TOP | 2A| 429 OUTPUT 2(A) N/U |
| TOP | 2B| 429 OUTPUT 2(B) N/U |
| TOP | 5C| 429 INPUT 16(A) N/U |
| TOP | 5D| 429 INPUT 16(B) N/U |

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 ---------------------------------------------------------
|LRU Con |Pin| Description |
---------------------------------------------------------
| TOP |11C| 429 INPUT 17(A) N/U |
| TOP |11D| 429 INPUT 17(B) N/U |
| TOP | 3A| 453 OUTPUT 1(A) TERR DATA R1 (A) |
| TOP | 3B| 453 OUTPUT 1(B) TERR DATA R1 (B) |
| TOP | 3C| 453 OUTPUT 2(A) TERR DATA R2 (A) |
| TOP | 3D| 453 OUTPUT 2(B) TERR DATA R2 (B) |
| TOP |13A| DC ANALOG INPUT 1 (+) N/U |
| TOP |13B| DC ANALOG INPUT 1 (-) N/U |
| TOP |14A| DC ANALOG INPUT 2 (+) N/U |
| TOP |14B| DC ANALOG INPUT 2 (-) N/U |
| TOP |13C| DC ANALOG INPUT 3 (+) N/U |
| TOP |13D| DC ANALOG INPUT 3 (-) N/U |
| TOP |14C| DC ANALOG INPUT 4 (+) N/U |
| TOP |14D| DC ANALOG INPUT 4 (-) N/U |
| MIDDLE |13D| 600 OHM AUDIO OUTPUT (C) |
| MIDDLE |13C| 600 OHM AUDIO OUTPUT (H) |
| MIDDLE | 3C| HIGH LEVEL 8 OHM AUDIO OUTPUT (C) N/U |
| MIDDLE | 3B| HIGH LEVEL 8 OHM AUDIO OUTPUT (H) N/U |
| BOTTOM | 1| Optional GPS COAX CONNECTION |
| MIDDLE | 3A| PROGRAM PIN COMMON |
| TOP |15A| 28 VDC DISCRETE INPUT 1 N/U |
| TOP |15B| 28 VDC DISCRETE INPUT 2 N/U |
| TOP |15C| 28 VDC DISCRETE INPUT 3 N/U |
| TOP |15D| 28 VDC DISCRETE INPUT 4 N/U |
| TOP | 7A| 28 VDC DISCRETE INPUT 5 N/U |
| TOP | 7B| 28 VDC DISCRETE INPUT 6 N/U |
| TOP | 7C| 28 VDC DISCRETE INPUT 7 N/U |
| TOP | 7D| 28 VDC DISCRETE INPUT 8 N/U |
| MIDDLE |1A | GND DISCRETE INPUT 1 N/U |
| MIDDLE |9C | GND DISCRETE INPUT 10 LDG FLAP |
| MIDDLE |9D | GND DISCRETE INPUT 11 G/S MANUAL |
| MIDDLE |14A| GND DISCRETE INPUT 12 WXR1 ON/OFF |
| MIDDLE |14B| GND DISCRETE INPUT 13 TAD and TCF INHIBIT|
| TOP | 1A| GND DISCRETE INPUT 15 F/O TERR SELECTION |
| TOP | 1B| GND DISCRETE INPUT 16 CAPT TERR SELECTION|
| MIDDLE | 2B| GND DISCRETE INPUT 17 N/U |
| TOP | 4C| GND DISCRETE INPUT 18 N/U |
| MIDDLE | 5D| GND DISCRETE INPUT 19 ALL AUDIO INHIBIT |
| MIDDLE | 1B| GND DISCRETE INPUT 2 G/S INHIBIT |
| MIDDLE | 7A| GND DISCRETE INPUT 20 N/U |
| MIDDLE | 2A| GND DISCRETE INPUT 3 N/U |
| MIDDLE | 5C| GND DISCRETE INPUT 4 N/U |
| MIDDLE | 7D| GND DISCRETE INPUT 5 INHIBIT MODES 1 TO 5|
| | | (AUDIO AND VISUAL) |

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 ---------------------------------------------------------
|LRU Con |Pin| Description |
---------------------------------------------------------
| MIDDLE | 8C| GND DISCRETE INPUT 6 N/U |
| MIDDLE | 8D| GND DISCRETE INPUT 7 AUDIO SUPPRESS |
| | | (MOMENTARY) |
| MIDDLE | 9A| GND DISCRETE INPUT 8 SELF TEST |
| MIDDLE | 9B| GND DISCRETE INPUT 9 LDG GEAR |
| MIDDLE |15D| GND DISCRETE OUTPUT 1 |
| MIDDLE | 3D| GND DISCRETE OUTPUT 2 G/S ALERT OUTPUT |
| MIDDLE | 7B| GND DISCRETE OUTPUT 3 WARNING OUTPUT |
| TOP |12C| GND DISCRETE OUTPUT 4 |
| TOP |12A| GND DISCRETE OUTPUT 5 |
| TOP |12B| GND DISCRETE OUTPUT 6 |
| TOP | 4D| GND DISCRETE OUTPUT 7 |
| TOP |10D| GND DISCRETE OUTPUT 8 CAPT POP-UP OUTPUT |
| MIDDLE |14C| GND DISCRETE OUTPUT 9 F/O POP-UP OUTPUT |
| TOP |11A| GND DISCRETE OUTPUT 10 |
| MIDDLE | 7C| DISCRETE MONITOR OUTPUT 1 GPWS MONITOR |
| | | OUTPUT |
| TOP |12D| DISCRETE MONITOR OUTPUT 2 TERR NOT AVAIL |
| | | OUTPUT |
| TOP |11B| DISCRETE MONITOR OUTPUT 3 TERRAIN MONITOR|
| | | OUTPUT |
| BOTTOM | 4 | CHASSIS GND |
| BOTTOM | 2 | PRIMARY PWR (H) |
| BOTTOM | 3 | PRIMARY PWR (L) |
| TOP |10A| PROGRAM PIN 1 |
| MIDDLE | 4A| PROGRAM PIN 10 |
| MIDDLE | 4C| PROGRAM PIN 11 |
| TOP | 5B| PROGRAM PIN 12 |
| MIDDLE | 5B| PROGRAM PIN 13 |
| TOP | 2C| PROGRAM PIN 14 |
| MIDDLE |15C| PROGRAM PIN 15 |
| MIDDLE | 8B| PROGRAM PIN 16 |
| TOP | 6D| PROGRAM PIN 17 |
| TOP |10B| PROGRAM PIN 2 |
| TOP |10C| PROGRAM PIN 3 |
| MIDDLE | 4D| PROGRAM PIN 4 |
| MIDDLE | 4B| PROGRAM PIN 5 |
| MIDDLE | 8A| PROGRAM PIN 6 |
| MIDDLE |14D| PROGRAM PIN 7 |
| MIDDLE | 5A| PROGRAM PIN 8 |
| MIDDLE | 2C| PROGRAM PIN 9 |
| TOP | 2D| OUTPUT REF 10.00 VDC |
| TOP | 6C| RS232 RECEIVE |
| TOP | 6B| RS232 TRANSMIT |

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 ---------------------------------------------------------
|LRU Con |Pin| Description |
---------------------------------------------------------
| BOTTOM | 5 | Spare |
| MIDDLE |15A| Spare |
| MIDDLE |15B| Spare |
---------------------------------------------------------

(b) Front panel assembly

The front panel assembly contains identification and modification
status labels, status LEDs, a latched door for access to a
SELF-TEST pushbutton switch, a HEADPHONE jack, a RS232 test
connector (P1), and a Personal Computing Memory Card Interface
Adapter (PCMCIA) interface and status LEDs. There is also a
handle for ease of carrying and installation/removal, and a
hold-down hook for securing at installation.

(c) Chassis
The chassis is welded aluminum, composed of a top and bottom and
two sides. It provides slots for CCA and space for the front and
rear panel assemblies.

(d) PCMCIA interface

The standard Type II PCMCIA interface provided at the front panel
allows for both the uploading and downloading of internal
Enhanced GPWC information. Control of the upload/download process
is accomplished by insertion of the PCMCIA card into the front
panel access. Four LEDs are provided for PCMCIA interface
operation.
The PCMCIA card does not remain installed during normal Enhanced
GPWC operation, and is not intended as an on-line/inflight
storage medium.

(e) Front connector

A 15-pin (double density, D-Sub) test connector is located on the
front panel, which provides for connection to either a CRT
terminal or a PC.
This connector provides the following interfaces:

1
_ Three-wire serial interface, compatible with RS232
This port can be used to access internal data from the
Enhanced GPWC for both bench simulation and aircraft testing.
Unit configuration and flight history can also be accessed.
This port can also be used to upload software and data bases.

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 2
_ ARINC 429/422/423 data loader interface
This port can be used to upload software and data bases.
System power is provided on two of the pins for data loader
use.
The Enhanced GPWC front connector pins are listed in the table
below (N/U means Not Used):

---------------------------------------------------------
|LRU Con |Pin| Description |
---------------------------------------------------------
| FRONT | 8 | 429 INPUT 20(A)/422 INPUT 2(A) |
| FRONT |13 | 429 INPUT 20(B)/422 INPUT 2(B) |
| FRONT | 9 | 429 OUTPUT 5(A)/422 OUTPUT 2(A) |
| FRONT |14 | 429 OUTPUT 5(B)/422 OUTPUT 2(B) |
| FRONT | 2 | RESERVED FOR BOOT CODE LOAD N/U |
| FRONT | 6 | PCMCIA BOOT ENABLE N/U |
| FRONT | 11| RS422 SELECT N/U |
| FRONT | 1| Ground |
| FRONT | 10| POWER PIN ISOLATOR |
| FRONT | 15| 115 VAC-C (OR 28 VDC-) |
| FRONT | 5| 115 VAC-H (OR 28 VDC+) |
| FRONT | 3| RS232 RECEIVE |
| FRONT | 4| RS232 TRANSMIT |
| FRONT | 7| Spare |
| FRONT | 12| Spare |
|FRT JACK| 1 | 600 OHM AUDIO OUTPUT (C) |
|FRT JACK| 2 | 600 OHM AUDIO OUTPUT (H) |
---------------------------------------------------------

(2) Internal Description

(Ref. Fig. 008)

(a) The hardware consists of three main circuit card assemblies:

- the controller card,
- the accessory card,
- the analog acquisition card.

1
_ The controller card contains the main processor
(microprocessor 486DX4), the Digital Information Transfer
System (DITS) handler microcontroller and the image generator
DSP.

2
_ The accessory card contains the power supply and the voice
generator DSP.

3
_ The analog acquisition card contains the analog acquisition
microcontroller.

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 Enhanced GPWC - Block Diagram
Figure 008

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 (b) The Enhanced GPWC contains the following five processors:
- main processor (486DX4) that runs the Enhanced GPWC Application
software and the Boot Loader Software,
- DITS handler microcontroller that runs the DITS Handler
software,
- image generator DPS that runs the image generator software,
which is a part of the Application software,
- voice generator DSP that runs the voice generator software,
which is part of the Application software,
- analog acquisition microcontroller that runs the Analog
Acquisition software.

B. Pushbutton Switches
(Ref. Fig. 003)

(1) GPWS/LDG FLAP 3 pushbutton switch 13WZ

To avoid nuisance warnings during approach, the Enhanced GPWC needs
to know at which flap position the crew intends to land.
This pushbutton switch (item 5), when pressed (in) (white ON legend
on), indicates to the Enhanced GPWC that the pilot intends to land in
flap 3 position. When released (out), the pushbutton switch indicates
to the Enhanced GPWC that the pilot intends to land in flap FULL
position.
The GPWS FLAP message is permanently displayed in green on the MEMO
of the ECAM display unit if no warning is in progress.

(2) GPWS/FLAP MODE pushbutton switch 7WZ

This pushbutton switch (item 4), when pressed (in) (white OFF legend
on), overrides flap abnormal condition input and generates the GPWS
FLAP MODE OFF message (green) in the memo area of the upper ECAM
display unit.

(3) GPWS/G/S MODE pushbutton switch 11WZ

This pushbutton switch (item 3), when pressed (in) (white OFF legend
on), inhibits the glide slope mode.

(4) GPWS/SYS pushbutton switch 9WZ

When this pushbutton switch (item 2) is pressed (white OFF legend
on), all ground proximity alerts (Mode 1 to 5) are inhibited (visual
and audio) and no Enhanced GPWC self-test is possible.
- This pushbutton switch provides a FAULT warning indicating that a
failure in Modes 1 to 5 has been detected by the Enhanced GPWC.
When the FAULT legend comes on, the following messages are
displayed:
. on the upper ECAM display unit if they are not inhibited by the
FWC:

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 NAV - GPWS FAULT (amber)
GPWS ........OFF (cyan)
(associated with action requested)
. in the INOP SYS item, on the STATUS page of the lower ECAM
display unit:
GPWS (amber)
A fault message is sent to the CFDIU.
(Ref. Fig. 009)

(5) GPWS/TERR pushbutton switch 31WZ

- When this pushbutton switch (item 1) is pressed (white OFF legend
on), the TAD and TCF functions are inhibited (visual display and
audio inhibition).
- The pushbutton switch provides a FAULT warning indicating that a
failure of TAD and/or TCF functions has been detected by the
Enhanced GPWC.
When the FAULT legend comes on, the following messages are
displayed:
. on the upper ECAM display unit if they are not inhibited by the
FWC:
NAV - GPWS TERR DET FAULT (amber)
GPWS TERR.............OFF (cyan)
. in the INOP SYS item, on the STATUS page of the lower ECAM
display unit:
GPWS TERR (amber)
A fault message is sent to the CFDIU.

(6) CAPT and F/O GPWS/G/S pushbutton switches 5WZ and 4WZ
These pushbutton switches, located on panels 301VU and 500VU, have
two functions when pressed (in):
- they cancel the glide slope alert, or
- they initiate the self-test sequence if the aircraft is on ground
or above 2000 ft. Above Ground Level (AGL).

(7) CAPT and F/O TERR ON ND pushbutton switches 30WZ1 and 30WZ2
These pushbutton switches (items 6 and 7) allow the crew to select or
deselect terrain display on ND.
The ON legends indicate that terrain data is displayed on ND
(following manual or automatic pop up selection).

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 Enhanced GPWS - Messages Displayed on Upper and Lower ECAM DU
Figure 009

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 7. Operation
_________

A. General

(1) Warning modes

The serial digital data and discrete data inputs are interfaced and
used in different combinations to monitor aircraft situation
awareness with respect to the terrain. The following functions are
implemented within the Enhanced GPWS:
Mode 1 - Excessive rate of descent
Mode 2 - Excessive closure rate with terrain
Mode 3 - Descent after takeoff and minimum terrain clearance
Mode 4 - Unsafe terrain clearance
Mode 5 - Descent below glide slope
Terrain Awareness and Display (TAD)
Terrain Clearance Floor (TCF)

(2) Aural alert messages

Each mode computes and compares aircraft behaviour with a
corresponding alert envelope. If the alert envelope is penetrated,
visual and aural alerts are generated. The aural message is broadcast
through the cockpit loud speakers.
The messages are as follows:
MODE AURAL ALERTS VISUAL ALERTS
1 SINK RATE GPWS
1 PULL UP GPWS
2 TERRAIN GPWS
2 TERRAIN TERRAIN GPWS
2 PULL UP GPWS
3 DON<T SINK GPWS
4 TOO LOW TERRAIN GPWS
4 TOO LOW GEAR GPWS
4 TOO LOW FLAPS GPWS
5 GLIDE SLOPE G/S
TAD TERRAIN AHEAD GPWS
TAD TERRAIN AHEAD PULL UP GPWS
TCF TOO LOW TERRAIN GPWS
Each of these alerts inhibits the automatic call out.

(3) Inhibitions
(Ref. Fig. 009)
Alerts may be cancelled by:

(a) Pressing the EMER CANC key on the ECAM control panel (aural alert
only).

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 (b) Pressing the GPWS/G/S pushbutton switch on the main instrument
panel for Mode 5 (glide slope) visual and aural alert. This
inhibition is temporary and the mode is automatically reactivated
for a new envelope penetration.

(c) Pressing the G/S MODE pushbutton switch on the overhead panel for
Mode 5 (glide slope) visual and aural alert (permanent
inhibition).

(d) Pressing the SYS pushbutton switch on the overhead panel for
inhibition of GPWS Modes 1 to 5 (visual and aural alerts).

(e) Pressing the TERR pushbutton switch on the overhead panel for
inhibition of TAD and TCF functions (visual and aural alerts).

(f) All aural messages are inhibited if a stall or a windshear (if

WR/PWS is installed) is in progress.

(4) Faults which prevent normal Enhanced GPWC operation are stored in the
BITE memory. They can be read on the MCDU.

B. Detailed Operation - Modes 1 through 5

This section describes the five warning modes of the Enhanced GPWC and
describes the operation of each of the modes.

(1) Mode 1 - Excessive rate of descent

(Ref. Fig. 010)

(a) Mode 1 provides the pilot with an alert/warning for high descent
rates into terrain. The pilot also receives a timely alert for
rapidly building sink rates near the runway when landing. The
figure shows the outer and inner boundaries whose penetration
triggers the alert/warnings.

(b) The outer boundary is a straight line which has an equation of:

H warn (ft.) = - 572 ft. - 0.6035 X Altitude rate.

NOTE : The descent rate is considered negative during the

____
descent. The formulas provide theoretical target values
only.

(c) The outer warning boundary is biased to the right as a function

of glide slope deviation above (Fly Down) the beam in order to
prevent unwanted warnings while re-positioning from above the
beam.

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 Enhanced GPWS - Excessive Rate of Descent
Figure 010

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 (d) The penetration of this outer boundary activates the GPWS legends
and produces the voice warning SINK RATE repeated twice, then
remains silent unless the excessive descent rate condition
degrades by approximately 20 per cent.

(e) Further penetration of the first boundary reaches the inner

boundary where the voice warning changes from SINK RATE to PULL
UP. This inner boundary is composed of two straight lines. The
equation which describes the lower line is:

H warn (ft.) = - 1620 ft. - 1.1133 X Altitude rate.

The equation which describes the upper line is:

H warn (ft.) = - 400 ft. - 0.400 X Altitude rate.

(f) Both boundaries are cut off at the top by a radio altitude of
2450 ft. The lower is cut off at 10 ft. A delay equivalent to 0.8
seconds is included in the upper function to minimize the
warnings caused by the momentary boundary penetration.

(g) Both boundaries can be biased to the right at certain airports

through envelope modulation to minimize nuisance warnings.

(2) Mode 2 - Excessive closure rate with terrain

(Ref. Fig. 011)

(a) Mode 2 provides a warning based on the radio altitude between the
aircraft and the ground and on how rapidly the radio altitude
decreases.
The barometric altitude of the aircraft is not important for the
initiation of this warning.

(b) The altitude rate is complemented in the filter to provide lead

information. The increase of the altitude descent rate tends to
speed up the warning occurrence. The reduction of the altitude
descent rate or the initiation of a climb tends to delay the
warning occurrence or reduce the time the warning is on.

(c) This mode has two areas of application that are generally
referred to as Mode 2A and Mode 2B. Mode 2A is applied when the
landing flaps are not down and the aircraft is not in the glide
slope beam. Mode 2B requires that the landing flaps be down or
that the aircraft be in the glide slope beam within +/- 2 dots of
deviation during an ILS approach. The figure shows the warning
boundary for Mode 2A (landing flaps up). The closure rate is the
computed change in the radio altitude between the aircraft and

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 Enhanced GPWS - Terrain Closure Rate - Mode
Figure 011

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 the ground. It is considered positive when the altitude
decreases.
The lower sloped line has an equation of:

H warn (ft.) = - 1579 ft. + 0.7895 X closure rate (FPM).

The upper sloped line has an equation of:

H warn (ft.) = 522 ft. + 0.1968 X closure rate (FPM).

(d) The normal upper limit of the boundary is horizontal at 1650 ft.
radio altitude due to a computed maximum closure rate limit of
5733 FPM. As the airspeed increases from 220 Kts up to 310 Kts,
the maximum rate limit is linearly increased to 9800 FPM. This
allows the upper boundary to also linearly increase up to 2450
ft.
The upper boundary is limited at certain airports to reduce the
warning sensitivity and minimize the nuisance warnings.

(e) Upon penetration of the boundary, either on the slope or from the
top, the GPWS legends come on and the voice message is TERRAIN
TERRAIN.
If the boundary penetration lasts beyond these two TERRAIN
messages, approximately 1 second, then the warning switches to
PULL UP repeated continuously until the boundary is departed.
When the Mode 2A envelope is exited, after having been violated
for more than 3 seconds, an altitude gain feature is
automatically activated. First the altitude at this instant is
sampled and stored. The GPWS legends remain on and the voice
message is TERRAIN. After three hundred feet of altitude are
gained from the stored value, or 45 seconds have elapsed from the
point where the PULL UP envelope was exited, the GPWS legends and
voice stop. If another boundary penetration occurs during this
altitude gain time, and it lasts long enough to restart the PULL
UP warning plus 3 seconds, then the whole process begins again
with a new reference altitude for the 300 ft. after boundary
separation.
In this manner the aircraft is directed up and over the terrain
to a safer altitude.

(f) Lowering the flaps to the landing position automatically switches

the GPWS to Mode 2B. The static boundary for Mode 2B is the same
as the Mode 2A boundary except the upper limit has been lowered
to 789 ft. at a maximum closure rate of 3000 FPM. The lower part
of the Mode 2B boundary is controlled as a function of radio
altitude and altitude rate when flaps are in full landing
configuration.

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 (g) Mode 2B is also selected when the aircraft is performing an ILS
approach and the glide slope and localizer deviations are less
than +/- 2 dots. However, the warning envelope is slightly
different from the flaps down case in that the lower boundary is
controlled only as a function of radio altitude, having a
constant lower cutoff of 30 ft. above ground level. When the
flaps are selected to landing configuration in the ILS beams, the
lower boundary is activated, (Mode 2B inhibit).

(h) When the envelope boundary conditions for Mode 2B are violated,
the GPWS legends come on, and the voice message is repeated until
the boundary is exited. If the gear or the flaps are up, then the
message is TERRAIN TERRAIN followed by PULL UP if the condition
persists. If both gear and flaps are in the landing
configuration, the message is TERRAIN.

(3) Mode 3 - Insufficient climb performance after takeoff

(Ref. Fig. 012)

(a) Mode 3 provides a warning for excessive altitude loss after

takeoff.
Mode 3 is based primarily on radio altitude, altitude (IR
inertial altitude, internally computed inertial altitude, or
barometric altitude), and altitude rate (IVS, internally computed
inertial altitude rate, or barometric altitude rate).

(b) Penetration of the Mode 3 alert/boundary results in the message

DON<T SINK and is based on altitude loss and radio altitude. This
alert/warning is only provided during takeoff when the aircraft
looses a predetermined amount of altitude.
(Ref. Fig. 012)
The sloped portion of the static warning envelope depicted is
defined by the following equation:

ALTITUDE LOSS (FT.) = 5.4 + 0.092 (RADIO ALTITUDE (FT.))

(c) Inertially compensated air data signals are used when possible.
IVS is used when valid data is available and barometric altitude
rate is used only when valid IVS is not available and the
internal computed inertial data is not valid. The Mode 3 warning
envelopes are inhibited close to the ground.

(d) The descent required for a warning varies as a function of flight

profile and time. Once a descent begins during the takeoff phase
of flight, as determined by the polarity of the altitude rate
signal and takeoff/approach mode logic, the Enhanced GPWC stores
the existing value of altitude. Subsequent samples of altitude,

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 Enhanced GPWS - Descent After Takeoff
Figure 012

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 altitude rate, and radio altitude are examined for warning
conditions. The original stored value of altitude indicating
where the descent began is retained until the aircraft ascends
above the stored altitude value. When the polarity of the
altitude rate signal indicates ascent rather than descent, the
warning is cut off to indicate recovery is being initiated. A
subsequent return to descent prior to regaining the altitude lost
enables the warning. The altitude loss required to resume the
message and legend activation is based on the initially stored
altitude value. In this manner, the possibility of stair stepping
down without Mode 3 warning indication is eliminated.

(e) Mode 3 is biased or desensitized under certain conditions. This

is accomplished by sampling radio altitude and altitude at
takeoff or go-around, and combining these signals to establish
the field elevation (or ground elevation) at takeoff or at the
point of go-around. Subsequent altitude information is then
compared to this value to determine the altitude gained since
takeoff or go-around.

(f) A delay equivalent to 0.8 second is added to the warning output

to prevent the possibility of nuisance warnings caused by static
pressure disturbances during gear retraction.

(4) Mode 4 - Unsafe terrain clearance

(Ref. Fig. 013)

(a) Mode 4 generates three types of voice warnings based on the radio
altitude, computed airspeed, and aircraft configuration, commonly
referred to as Modes 4A, 4B and 4C. The standard upper boundary
is at 500 ft. radio altitude. If the aircraft penetrates this
boundary with the landing gear still up, the voice message is TOO
LOW GEAR. Above 190 Kts airspeed, the upper boundary increases
linearly with airspeed to a maximum of 1000 ft. radio altitude at
250 Kts or more. Penetrating this boundary produces a repetitive
TOO LOW TERRAIN message. Other maximums are used at certain
airports to minimize the nuisance warnings.
The Mode 4 maximum altitude is lowered from 1000 to 800 ft. of
radio altitude when an overflight is detected. An overflight can
be detected by sensing the sudden change in radio altitude. The
800 ft. limit is maintained for 60 seconds after an overflight to
ensure that a nuisance warning is not issued.

(b) When the landing gear or flaps are lowered, the upper boundary
decreases to 245 ft. To maintain the same airspeed expansion
function up to 1000 ft. nominal at 250 Kts, the lower level
corner is at 159 Kts.

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 INTENTIONALLY BLANK

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 Enhanced GPWS - Unsafe Terrain Clearance - Mode
Figure 013 (SHEET 1)

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 Enhanced GPWS - Unsafe Terrain Clearance - Mode
Figure 013 (SHEET 2)

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 Penetration below 159 Kts results in TOO LOW GEAR messages with
gear up or TOO LOW FLAPS message with gear down and flaps not in
landing configuration, while above 159 Kts the message is TOO LOW
TERRAIN.

(c) The equation for the sloped portion of the warning curve is:

H warn (ft.) = - 1083 ft. + 8.333 X Computed Airspeed (Kts)

(d) The basic audio de-clutter feature applies a ratched function to

the Mode 4 voice warning which is similar to the Mode 3
ratcheting voice message. Once the message is given, the envelope
is biased down by 20 per cent and further warnings are held off
until this additional 20 per cent radio altitude is lost. The
lamp is not affected and remains on until the radio altitude
becomes greater than indicated on the curves.
(Ref. Fig. 013)
Mode 4 also provides a warning based on minimum radio altitude
clearance during takeoff. This warning is similar to the Mode 4A
warning that is active during the cruise and approach phases of
flight, only in this case, the minimum terrain clearance is a
function of the radio altitude of the aircraft. The sloped
portion of the envelope boundary is described by the equation:

MIN TERRAIN CLEARANCE (FT.) = 0.75 (RADIO ALTITUDE (FT.))

Mode 4C is based on a minimum terrain clearance, or floor, that

increases with radio altitude during takeoff. A value equal to 75
per cent of the current radio altitude is accumulated in a long
term filter that is only allowed to increase in value. If the
radio altitude later decreases, the filter stores its maximum
attained value. Further decrease of radio altitude below the
stored filter value with gear or flaps up results in the warning
TOO LOW TERRAIN (or equivalent).
A simplified example illustrates this operation. First assume the
radio altitude increases rapidly from 0 ft. to 400 ft. The filter
begins charging to 75 per cent of 400 ft., or 300 ft. In 20
seconds, the filter has charged up to approximately 220 ft. Now
if the radio altitude decreases so that 75 per cent of this value
results in something less than 220 ft. (i.e., approximately 295
ft. or less), the filter remains at a value of 220 ft. Further
reductions in radio altitude below 220 ft. result in the TOO LOW
TERRAIN warning.
This warning is provided to prevent inadvertent controlled flight
into the ground during takeoff climb into terrain that produces
insufficient closure rate for a Mode 2 warning. After takeoff,

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 and mode change over from Takeoff to Cruise or Approach, then
Mode 4A and 4B provide this protection.
The basic audio de-clutter feature applies a ratchet function to
the Mode 4C voice warning which is equivalent to the ratcheting
voice message described above. Once the message is given, the
envelope is biased down by 20 per cent and further warnings are
held off until this additional 20 per cent radio altitude is
lost. The lamp is not affected and remains on until the terrain
clearance problem is rectified.

(5) Mode 5 - Descent below glide slope

(Ref. Fig. 014)

(a) Mode 5 provides two levels of warning when the aircraft flight
path descends below the glide slope beam on front course ILS
approaches.
The upper limit of 1000 ft. nominal allows the capture of the
beam before enabling this mode. Higher upper limits are used at
certain airports to increase the warning envelope. The deviation
boundaries are shown in dots below the beam where one dot equals
0.0875 DDM = 0,36 degree. The first warning occurs whenever the
aircraft is more than 1.3 dots below the beam. It is called a
soft glide slope warning because the volume level of the GLIDE
SLOPE warning is approximately one half (- 6 db) that of the
other warnings.
A second warning boundary occurs below 300 ft. radio altitude and
more than 2 dots below the beam. It is called loud glide slope
because the volume level is increased to that of the other
warnings.

(b) Both boundaries allow additional deviation below 150 ft. of radio
altitude to allow for normal beam variations near the threshold.

(c) The basic audio de-clutter feature provides GLIDE SLOPE message
logic which suppresses the aural alert after one message has been
given. Follow-on alerts are only allowed when the aircraft
descends lower on the glide slope beam by approximately 20 per
cent. The alert lamp remains on until the excessive FLY UP
condition has been corrected. The aural alerts are provided
continuously once the aircraft exceeds 2 dots FLY UP. Below 300
ft. AGL the messages speed up as altitude is lowered or deviation
is increased. Actual time between GLIDE SLOPE messages for these
conditions is controlled by the equation:

RADIO ALTITUDE (FT.)

PAUSE(SEC) = --------------------------------- X 0.0067
GLIDE SLOPE DEVIATION (DOTS FLY UP)

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 Enhanced GPWS - Descent Below Glide Slope
Figure 014

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 Additionally, the audio de-clutter feature allows for Mode 5
GLIDE SLOPE alerts to occur during penetration of the Mode 1
outer envelope while the Mode 1 SINKRATE audio is suppressed.

(d) The GLIDE SLOPE warning can be manually cancelled by the crew.
This can be done any time below 2000 ft. nominal radio altitude.
Cancel can be reset by ascending above 2000 ft. nominal, or
descending below 30 ft.

(e) The change from constant deviation to a slope below 150 ft. radio
altitude is shown along with the constant separation 0.7 dot
between the two boundaries. A delay of approximately 0.8 second
is inserted between the warning output and the enabling logic
during a warning condition. The delay also turns off the warning
output when two successive samples show a loss of the enabling
logic. The repetition rate of the GLIDE SLOPE message is
controlled by the radio altitude and the glide slope deviation as
shown in the equation above.

(f) The gear-down logic requirement for Mode 5 is deleted at certain

airports.

R **ON A/C 001-004,

C. Envelope Modulation

(1) Background
During the past 20 years, experience with GPWS has shown that normal
approaches to certain airports can be incompatible with the normal
warning envelopes and signal filtering.
The envelope modulation feature provides improved alert/warning
protection at some key locations throughout the world, while
improving nuisance margins at others. This is made possible with the
use of navigational signals from modern inertially based navigation
equipment. This feature utilizes updated flight management system
navigational signals.
A number of enhancements to the envelopes and filters have been
developed during this time in an attempt to accommodate these few
airports, without compromising the overall GPWS effectiveness for all
the other airport WnormalW approaches. However, there remains a
limited number of cases which are still not satisfactory persist
despite these efforts.
All of the noticeable cases have been due to nuisance warnings for
approaches and departures at particular airports. The majority of
nuisance warnings involves Mode 2 closure rate due to terrain under
the approach path or rising terrain just before the runway threshold.

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 Others involve Mode 4 terrain clearance warnings during initial
approach. A few Mode 1 warnings are the results of steeper than
normal approaches over terrain which slopes down to the runway at
some airports.
A different type of case is the inadequate warning protection during
ILS approaches because Mode 5 is limited to less than 1000 ft. radio
altitude. There are airports located at a significantly higher
altitude than the surrounding terrain. In some instances this
difference is over 1000 ft., thus requiring the aircraft to be below
the runway elevation before a Mode 5 warning is possible during most
of the approach.
Until recently there has been no reasonable way to accomodate these
few special cases without compromising the Enhanced GPWC at all other
airports.
What is needed is the ability to recognize when the aircraft is
approaching one of these airports and then adjust the warning
criteria to suit the particular approach.
The availability of accurate, low drift, latitude and longitude
information from the latest generation inertial navigation equipment
now makes individual airport recognition possible. After recognizing
the approach to or departure from one of these airports, it is also
important to verify the aircraft is at a reasonable altitude before
desensitizing any warning criteria. If the aircraft is already low,
further warning reduction is not desirable. This requires the use of
corrected altitude signals.

(2) Functional description

Furthermore, in order to prevent inadvertent activation of envelope
modulation, cross checks must be made which validate the navigational
and altitude information. This requires a cross check to other ground
based navigational aids.
Corrected altitude information from the ADIRU is used. This data can
be either QNH or QFE corrected (selectable via program pin). This
altitude information is verified in one of two ways:
- For ILS approaches, the glide slope deviation is used to establish
that adequate terrain clearance exists (i.e. a WnormalW approach).
Consequently, errors in altitude data do not enable envelope
modulation during an unsafe condition,
- When ILS information is not available, stored terrain elevation
data is matched against computed elevation data (i.e. corrected
altitude - radio altitude) to verify altitude. This is done for a
WsnapshotW location immediately prior to the envelope modulation
area.
The following input data are used for airport recognition:
- latitude position from the FMGC or the ADIRU,
- longitude position from the FMGC or the ADIRU,
- glide slope deviation from the ILS,

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 - localizer deviation from the ILS,
- aircraft magnetic track angle from the FMGC or the ADIRU,
- runway course from the ILS,
- corrected barometric altitude from the ADIRU,
- QNH or QFE mode of baro altitude correction via program pin. QNH
mode is baro altitude correction to sea level. QFE mode is selected
with a program pin for baro altitude correction to the airport
field elevation,
- radio altitude.
Latitude and longitude data are continuously monitored for the
airport locations. Additional data processing for envelope modulation
is not required until the aircraft approaches one of the envelope
modulation areas. Then the other data inputs are checked for a
WnormalW approach before any warning envelopes are modulated.
The FMGC is the preferred source for latitude and longitude data
because these data were corrected for the normal drift of the ADIRU
basic latitude and longitude data. If the FMGC data are invalid, or
missing, then the Enhanced GPWC automatically switches back to the
ADIRU data.

(3) Types of envelope modulation - There are currently four types of

envelope modulation required for particular airport approaches.
- bias the Mode 1 warning boundaries for SINK RATE and PULL UP to the
right to allow greater altitude descent rates before a warning is
generated.
(Ref. Fig. 010)
- lower the maximum upper limit for Mode 2A and Mode 2B.
This limits the maximum radio altitude, or the minimum terrain
clearance required to generate a warning.
(Ref. Fig. 011)
- lower the maximum upper limit for Mode 4 to allow less minimum
terrain clearance before a warning is generated.
(Ref. Fig. 013)
- expand the maximum Mode 5 radio altitude level where a warning can
begin. This allows GLIDE SLOPE warnings for higher radio altitudes.
The gear down requirement is also removed during warning expansion,
to allow gear up warnings.
The actual data for each of the established areas is in tables stored
in the Enhanced GPWC non-volatile memory. This data can be for either
a WsnapshotW area or an envelope modulation area. In fact, these
areas can actually overlap since the envelope modulation is not
performed until the WsnapshotW conditions have been verified. Every
WsnapshotW has an associated envelope modulation area, but not every
envelope modulation area has an associated WsnapshotW area. This is
because some locations use glide slope instead of the WsnapshotW
feature as a cross check on corrected altitude data. All of the data

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 extracted for each location is used to form a unique key which
establishes the aircraft position, orientation and altitude.
Stored data for latitude, longitude, terrain elevation, expected
elevation tolerance, minimum expected radio altitude, heading (track)
and maximum allowable time to reach the envelope modulation area are
compared to real time computed values for these parameters in order
to set WsnapshotW latch. This latch is intentionally stored in
volatile RAM memory and cleared during power loss recovery. The
associated signal validities are used to establish signal integrity
prior to setting the WsnapshotW latch. The maximum time term is used
to clear the WsnapshotW latch once this time has expired unless the
envelope modulation conditions are satisfied first.
Logic is required to satisfy one or more of the envelope modulation
WkeysW. In each case, if the WkeyW is required, the associated
conditions are monitored.
The following is a summary of the envelope modulation, and snapshot
keys:
ENVELOPE MODULATION KEYS

-----------------------------------------------------------------------------
| SELECTED KEY | DESCRIPTION |
|------------------|--------------------------------------------------------|
| ENVELOPE | REQUIRES VALID LATITUDE AND LONGITUDE TO BE WITHIN |
| MODULATION AREA | DEFINED AREA |
|------------------|--------------------------------------------------------|
| G/S SELECTED | REQUIRES VALID GLIDE SLOPE WITHIN +/- 2 DOTS |
|------------------|--------------------------------------------------------|
| LOC SELECTED | REQUIRES VALID LOCALIZER WITHIN +/- 2 DOTS |
|------------------|--------------------------------------------------------|
| HDG SELECTED | REQUIRES VALID HEADING WITHIN +/- 30 DEG OF SELECTED |
| | VALUE |
|------------------|--------------------------------------------------------|
| CRS SELECTED | REQUIRES VALID RUNWAY COURSE WITHIN +/- 10 DEG OF |
| | SELECTED VALUE |
| | If the aircraft installation does not provide runway |
| | course (or selected heading) then this key is not |
| | required. |
|------------------|--------------------------------------------------------|
| MIN ALTITUDE | REQUIRES VALID CORRECTED ALTITUDE (QFE OR QNH) TO BE |
| SELECTED | GREATER THAN SELECTED VALUE |
|------------------|--------------------------------------------------------|
| SNAPSHOT SELECTED| REQUIRES SNAPSHOT DETECTED |
-----------------------------------------------------------------------------

SNAPSHOT KEYS

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 -----------------------------------------------------------------------------
| SELECTED KEY | DESCRIPTION |
|------------------|--------------------------------------------------------|
| SNAPSHOT AREA | REQUIRES VALID LATITUDE AND LONGITUDE TO BE WITHIN |
| | DEFINED AREA |
|------------------|--------------------------------------------------------|
| HDG SELECTED | REQUIRES VALID HEADING WITHIN +/- 30 DEG OF SELECTED |
| | VALUE |
|------------------|--------------------------------------------------------|
| MINIMUM RADIO | REQUIRES VALID RADIO ALTITUDE TO BE GREATER THAN |
| ALTITUDE | SELECTED VALUE |
|------------------|--------------------------------------------------------|
| TERRAIN ELEVATION| REQUIRES TERRAIN ELEVATION (QFE OR QNH) TO BE WITHIN |
| | A SPECIFIC TOLERANCE OF THE SELECTED VALUE |
|------------------|--------------------------------------------------------|
| MAXIMUM TIME | MAXIMUM TIME PERMITTED TO SATISFY ALL ENVELOPE |
| | MODULATION KEYS AFTER LEAVING THE SNAPSHOT |
|__________________|________________________________________________________|

All of the WkeysW, either by virtue of not being selected, or by

being selected and satisfied, are required to enable envelope
modulation. Envelope modulation parameters are either within the
selected values if the WkeysW fit, or defaulted to normal values if
the WkeysW do not fit. These parameters are used as inputs to the
warning modes and thereby provide the mechanism for envelope
modulation.

**ON A/C ALL

R Post SB 34-1147 For A/C 001-004,

C. Envelope Modulation

(1) Background
During the past 20 years, experience with GPWS has shown that normal
approaches to certain airports can be incompatible with the normal
warning envelopes and signal filtering.
The envelope modulation feature provides improved alert/warning
protection at some key locations throughout the world, while
improving nuisance margins at others. This is made possible with the
use of navigational signals from modern inertially based navigation
equipment. This feature utilizes updated flight management system
navigational signals.
A number of enhancements to the envelopes and filters have been
developed during this time in an attempt to accommodate these few
airports, without compromising the overall GPWS effectiveness for all
the other airport WnormalW approaches. However, there remains a

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R limited number of cases which are still not satisfactory and which
R persist despite these efforts.
R All of the noticeable cases have been due to nuisance warnings for
R approaches and departures at particular airports. The majority of
R nuisance warnings involves Mode 2 closure rate due to terrain under
R the approach path or rising terrain just before the runway threshold.
R Others involve Mode 4 terrain clearance warnings during initial
R approach. A few Mode 1 warnings are the results of steeper than
R normal approaches over terrain which slopes down to the runway at
R some airports.
R A different type of case is the inadequate warning protection during
R ILS approaches because Mode 5 is limited to less than 1000 ft. radio
R altitude. There are airports located at a significantly higher
R altitude than the surrounding terrain. In some instances this
R difference is over 1000 ft., thus requiring the aircraft to be below
R the runway elevation before a Mode 5 warning is possible during most
R of the approach.
R Until recently there has been no reasonable way to accomodate these
R few special cases without compromising the Enhanced GPWC at all other
R airports.
R What is needed is the ability to recognize when the aircraft is
R approaching one of these airports and then adjust the warning
R criteria to suit the particular approach.
R The availability of accurate, low drift, latitude and longitude
R information from the latest generation inertial navigation equipment
R now makes individual airport recognition possible. After recognizing
R the approach to or departure from one of these airports, it is also
R important to verify the aircraft is at a reasonable altitude before
R desensitizing any warning criteria. If the aircraft is already low,
R further warning reduction is not desirable. This requires the use of
R corrected altitude signals.

R (2) Functional description

R Furthermore, in order to prevent inadvertent activation of envelope
R modulation, cross checks must be made which validate the navigational
R and altitude information. This requires a cross check to other ground
R based navigational aids.
R Corrected altitude information from the ADIRU is used. This data can
R be either QNH or QFE corrected (selectable via program pin). This
R altitude information is verified in one of two ways:
R - For ILS approaches, the glide slope deviation is used to establish
R that adequate terrain clearance exists (i.e. a WnormalW approach).
R Consequently, errors in altitude data do not enable envelope
R modulation during an unsafe condition,
R - When ILS information is not available, stored terrain elevation
R data is matched against computed elevation data (i.e. corrected
R altitude - radio altitude) to verify altitude. This is done for a

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R WsnapshotW location immediately prior to the envelope modulation
R area.
R The following input data are used for airport recognition:
R - latitude position from the FMGC or the ADIRU,
R - longitude position from the FMGC or the ADIRU,
R - glide slope deviation from the ILS portion of the MMR,
R - localizer deviation from the ILS portion of the MMR,
R - aircraft magnetic track angle from the FMGC or the ADIRU,
R - runway course from the ILS portion of the MMR,
R - corrected barometric altitude from the ADIRU,
R - QNH or QFE mode of baro altitude correction via program pin. QNH
R mode is the baro altitude correction to sea level. QFE mode is
R selected with a program pin for baro altitude correction to the
R airport field elevation,
R - radio altitude.
R Latitude and longitude data are continuously monitored for the
R airport locations. Additional data processing for envelope modulation
R is not required until the aircraft approaches one of the envelope
R modulation areas. Then the other data inputs are checked for a
R WnormalW approach before any warning envelopes are modulated.
R The FMGC is the preferred source for latitude and longitude data
R because these data were corrected for the normal drift of the ADIRU
R basic latitude and longitude data. If the FMGC data are invalid, or
R missing, then the Enhanced GPWC automatically switches back to the
R ADIRU data.

R (3) Types of envelope modulation - There are currently four types of

R envelope modulation required for particular airport approaches.
R - bias the Mode 1 warning boundaries for SINK RATE and PULL UP to the
R right to allow greater altitude descent rates before a warning is
R generated.
R (Ref. Fig. 010)
R - lower the maximum upper limit for Mode 2A and Mode 2B.
R This limits the maximum radio altitude, or the minimum terrain
R clearance required to generate a warning.
R (Ref. Fig. 011)
R - lower the maximum upper limit for Mode 4 to allow less minimum
R terrain clearance before a warning is generated.
R (Ref. Fig. 013)
R - expand the maximum Mode 5 radio altitude level where a warning can
R begin. This allows GLIDE SLOPE warnings for higher radio altitudes.
R The gear down requirement is also removed during warning expansion,
R to allow gear up warnings.
R The actual data for each of the established areas is in tables stored
R in the Enhanced GPWC non-volatile memory. This data can be for either
R a WsnapshotW area or an envelope modulation area. In fact, these
R areas can actually overlap since the envelope modulation is not

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R performed until the WsnapshotW conditions have been verified. Every
R WsnapshotW has an associated envelope modulation area, but not every
R envelope modulation area has an associated WsnapshotW area. This is
R because some locations use glide slope instead of the WsnapshotW
R feature as a cross check on corrected altitude data. All of the data
R extracted for each location is used to form a unique key which
R establishes the aircraft position, orientation and altitude.
R Stored data for latitude, longitude, terrain elevation, expected
R elevation tolerance, minimum expected radio altitude, heading (track)
R and maximum allowable time to reach the envelope modulation area are
R compared to real time computed values for these parameters in order
R to set WsnapshotW latch. This latch is intentionally stored in
R volatile RAM memory and cleared during power loss recovery. The
R associated signal validities are used to establish signal integrity
R prior to setting the WsnapshotW latch. The maximum time term is used
R to clear the WsnapshotW latch once this time has expired unless the
R envelope modulation conditions are satisfied first.
R Logic is required to satisfy one or more of the envelope modulation
R WkeysW. In each case, if the WkeyW is required, the associated
R conditions are monitored.
R The following is a summary of the envelope modulation, and snapshot
R keys:
R ENVELOPE MODULATION KEYS

R -----------------------------------------------------------------------------
R | SELECTED KEY | DESCRIPTION |
R |------------------|--------------------------------------------------------|
R | ENVELOPE | REQUIRES VALID LATITUDE AND LONGITUDE TO BE WITHIN |
R | MODULATION AREA | DEFINED AREA |
R |------------------|--------------------------------------------------------|
R | G/S SELECTED | REQUIRES VALID GLIDE SLOPE WITHIN +/- 2 DOTS |
R |------------------|--------------------------------------------------------|
R | LOC SELECTED | REQUIRES VALID LOCALIZER WITHIN +/- 2 DOTS |
R |------------------|--------------------------------------------------------|
R | HDG SELECTED | REQUIRES VALID HEADING WITHIN +/- 30 DEG OF SELECTED |
R | | VALUE |
R |------------------|--------------------------------------------------------|
R | CRS SELECTED | REQUIRES VALID RUNWAY COURSE WITHIN +/- 10 DEG OF |
R | | SELECTED VALUE |
R | | If the aircraft installation does not provide runway |
R | | course (or selected heading) then this key is not |
R | | required. |
R |------------------|--------------------------------------------------------|
R | MIN ALTITUDE | REQUIRES VALID CORRECTED ALTITUDE (QFE OR QNH) TO BE |
R | SELECTED | GREATER THAN SELECTED VALUE |
R |------------------|--------------------------------------------------------|
R | SNAPSHOT SELECTED| REQUIRES SNAPSHOT DETECTED |

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 -----------------------------------------------------------------------------
| SELECTED KEY | DESCRIPTION |
|------------------|--------------------------------------------------------|
-----------------------------------------------------------------------------

SNAPSHOT KEYS

-----------------------------------------------------------------------------
| SELECTED KEY | DESCRIPTION |
|------------------|--------------------------------------------------------|
| SNAPSHOT AREA | REQUIRES VALID LATITUDE AND LONGITUDE TO BE WITHIN |
| | DEFINED AREA |
|------------------|--------------------------------------------------------|
| HDG SELECTED | REQUIRES VALID HEADING WITHIN +/- 30 DEG OF SELECTED |
| | VALUE |
|------------------|--------------------------------------------------------|
| MINIMUM RADIO | REQUIRES VALID RADIO ALTITUDE TO BE GREATER THAN |
| ALTITUDE | SELECTED VALUE |
|------------------|--------------------------------------------------------|
| TERRAIN ELEVATION| REQUIRES TERRAIN ELEVATION (QFE OR QNH) TO BE WITHIN |
| | A SPECIFIC TOLERANCE OF THE SELECTED VALUE |
|------------------|--------------------------------------------------------|
| MAXIMUM TIME | MAXIMUM TIME PERMITTED TO SATISFY ALL ENVELOPE |
| | MODULATION KEYS AFTER LEAVING THE SNAPSHOT |
|__________________|________________________________________________________|

All of the WkeysW, either by virtue of not being selected, or by

being selected and satisfied, are required to enable envelope
modulation. Envelope modulation parameters are either within the
selected values if the WkeysW fit, or defaulted to normal values if
the WkeysW do not fit. These parameters are used as inputs to the
warning modes and thereby provide the mechanism for envelope
modulation.

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R **ON A/C 001-004,

D. Enhanced Features

(1) Terrain Awareness alerting and Display (TAD) functions

The terrain awareness component of the Enhanced GPWS is divided into
functional blocks with an interface to Navigation Display.
(Ref. Fig. 015)
The highlighted blocks monitor aircraft position with respect to
local terrain data base and provide rapid audio and visual alerts
when a terrain threat is detected. Terrain threats are recognized and
annunciated when terrain violates specific computed envelope
boundaries forward of the aircraft path. Provision has been included
for a future obstacle data base providing similar annunciation when
cataloged obstacles violate the same envelope boundaries.
The terrain awareness alert lamps and audio outputs behave in the
same manner as the standard GPWS mode alerts. A terrain caution alert
or terrain warning alert initiates a specific audio alert phrase
(Ref. para.D.(1)(d)2_ and D.(1)(d)3_).
Complementing the terrain threat alerts, the Enhanced GPWS also
maintains a synthetic image of local terrain forward of the aircraft
for display on EFIS Navigation Displays (ND).
The Enhanced GPWS is configured to automatically de-select the
weather display and pop-up a display of the terrain threats when they
occur. The logic used provides an external input for predictive
windshear alerts that can override a terrain display and revert to
the weather display with the corresponding windshear data (if WR/PWS
installed).
The Enhanced GPWS provides two external display outputs, each with
independent range-scaling control in the same fashion as a weather
radar on both NDs. Changes of range scaling to one ND do not affect
the other display. Each of these two independent outputs may be used
to drive more than one display.

(a) Enhanced GPWS Input Processing and Signal Selection

(Ref. Fig. 015)
The Enhanced GPWS Input Processing and Signal Selection function
conditions and formats aircraft data into proper form for use by
the Enhanced GPWS while insulating the Enhanced GPWS from
variations in aircraft type and configuration.

R
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 Enhanced GPWS - Terrain Awareness Functions
Figure 015

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 1
_ Aircraft Data Inputs
Aircraft position latitude and longitude are required for
terrain awareness operation and are received from the Flight
Management System (FMS). The terrain threat detection and
display processing are automatically disabled in some
particular conditions. This is indicated to the flight crew by
an ECAM memo (TERR STBY).
(Ref. Fig. 009)
Additionally, aircraft ground track and ground speed data are
received from the IR portion of the ADIRU 1 (IRS). The
aircraft altitude MSL is received from the air data portion of
the ADIRU 1.
Other aircraft inputs include aircraft heading (from the IR),
roll attitude (from IR) and flight path angle (Gamma, derived
by the Enhanced GPWC).

2
_ Control Inputs
Installations provide discrete terrain display select
pushbutton switches (TERR ON ND) in the cockpit for each
display. These are momentary-action pushbutton switches that
are processed by the Enhanced GPWS input processing and signal
selection block as input to display control logic.
Additionally, for aircraft with predictive windshear radar
capability (if WR/PWS installed), a windshear override boolean
is computed using alert level bits from label 077 on WXR
hazard bus for the display control logic.
(Ref. Fig. 004)

R **ON A/C 001-004,

R Post SB 34-1147 For A/C 001-004,

(Ref. Fig. 004A)

R **ON A/C 001-004,

This boolean allows the Enhanced GPWC to manage priority

between Enhanced GPWC alerts and PWS alerts. The installation
requires input of cockpit-selected range scales provided by
the FCU for each ND.

(b) Local Terrain Processing

The local terrain processing block extracts and formats local
topographic data and terrain features from the related data bases
creating a set of digital elevation matrix overlays for use by
the terrain threat detection and display processing functions.

R
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 Additionally, data for the nearest runway are also extracted for
use by the terrain threat detection and display processing
functions. Processing for each topographic data base and the
runway data base are described in the following sub-sections.

1
_ Terrain Surface Data
Local terrain processing of topographic surface data updates a
set of digital elevation matrix overlays that are positioned
with respect to aircraft position. Each matrix element
contains the highest terrain altitude with respect to mean sea
level in that element area. Elements where terrain data are
not available are marked invalid. These unknown data are
displayed in magenta low density on ND whatever the altitude.

2
_ Obstacle Data
In addition to terrain surface data, provisions are made for
future use of an obstacle data base providing obstacle data in
the vicinity of major airports. Local terrain processing will
update a dedicated overlay within the digital elevation matrix
overlays with local obstacle altitude data.

3
_ Nearest Runway Data
Data for the nearest runway are extracted and processed for
use by the terrain threat detection and display processing
functions. Data are extracted from the same airport data base
used by the Terrain Clearance Floor functions (Ref. para.
D.(2)). This data base contains data on all hard-surface
runways 3500 ft. or more in length with published coordinates.
The contents of the data base are processed by the local
terrain processing into nearest runway center position,
nearest runway threshold position, and nearest runway altitude
for use by the Enhanced GPWS. These data are updated when the
terrain threat detection and display processing functions are
performed.

(c) Terrain Threat Detection

The terrain threat detection and display processing block
performs the threat analysis on the terrain data within computed
caution and warning envelope boundaries below and forward of the
aircraft path. Results of these threat assessments are combined
with background terrain data and data for the nearest runway and
formatted into a terrain display image which can be displayed on
Navigation Display in place of the weather image. In the event of
terrain caution or warning conditions, a specific audio alert is
triggered and the terrain display image is enhanced to highlight
each of the types of terrain threats.

R
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 1
_ Terrain Caution and Warning Envelopes
(Ref. Fig. 016)

a
_ Caution Altitude Floor
The caution altitude floor (or terrain floor) is computed
as a function of aircraft altitude with respect to nearest
runway altitude and range to the nearest runway threshold
position. This parameter represents a distance below the
aircraft. The relationship to the nearest runway threshold
location prevents undesired alerts when the aircraft is
taking off or landing at an airport. The system is
compatible with terrain clearances allowed for by
regulatory approach and departure design criteria.

b
_ Caution Look Ahead Distance
The caution look ahead distance is computed from aircraft
ground speed and turn rate to provide an advanced caution
with adequate time for the crew to react safely. Depending
on the situation this distance roughly corresponds to
between 40 and 60 seconds for advance alerting.

c
_ Warning Altitude Floor
The warning altitude floor is set to a fraction of the
caution altitude floor, as illustrated in the upper part of
this illustration.
(Ref. Fig. 016)
The warning altitude floor is computed as a function of
aircraft altitude with respect to nearest runway altitude
and range to the nearest runway threshold position. This
parameter represents a distance below the aircraft. The
relationship to the nearest runway threshold location
prevents undesired alerts when the aircraft is taking off
or landing at an airport.

d
_ Warning Look Ahead Distance
The warning look ahead distance is a fraction of the
caution look ahead distance (computed from aircraft ground
speed and turn rate) to provide an advanced warning with
adequate time for the crew to react safely.

R
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 Enhanced GPWS - Terrain Detection Envelope
Figure 016

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 **ON A/C ALL

R Post SB 34-1193 For A/C 001-004,

D. Enhanced Features

(1) Terrain Awareness alerting and Display (TAD) functions

The terrain awareness component of the Enhanced GPWS is divided into
functional blocks with an interface to Navigation Display.
(Ref. Fig. 015)
The highlighted blocks monitor aircraft position with respect to
local terrain data base and provide rapid audio and visual alerts
when a terrain threat is detected. Terrain threats are recognized and
annunciated when terrain violates specific computed envelope
boundaries forward of the aircraft path. Provision has been included
for a future obstacle data base providing similar annunciation when
cataloged obstacles violate the same envelope boundaries.
The terrain awareness alert lamps and audio outputs behave in the
same manner as the standard GPWS mode alerts. A terrain caution alert
or terrain warning alert initiates a specific audio alert phrase
(Ref. para.D.(1)(d)2_ and D.(1)(d)3_).
Complementing the terrain threat alerts, the Enhanced GPWS also
maintains a synthetic image of local terrain forward of the aircraft
for display on EFIS Navigation Displays (ND).
The Enhanced GPWS is configured to automatically de-select the
weather display and pop-up a display of the terrain threats when they
occur. The logic used provides an external input for predictive
windshear alerts that can override a terrain display and revert to
the weather display with the corresponding windshear data (if WR/PWS
installed).
The Enhanced GPWS provides two external display outputs, each with
independent range-scaling control in the same fashion as a weather
radar on both NDs. Changes of range scaling to one ND do not affect
the other display. Each of these two independent outputs may be used
to drive more than one display.

(a) Enhanced GPWS Input Processing and Signal Selection

(Ref. Fig. 015)
The Enhanced GPWS Input Processing and Signal Selection function
conditions and formats aircraft data into proper form for use by
the Enhanced GPWS while insulating the Enhanced GPWS from
variations in aircraft type and configuration.

1
_ Aircraft Data Inputs
Aircraft position latitude and longitude are required for
terrain awareness operation and are received from the Flight
Management System (FMS). The terrain threat detection and

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 display processing are automatically disabled in some
particular conditions. This is indicated to the flight crew by
an ECAM memo (TERR STBY).
(Ref. Fig. 009)
Additionally, aircraft ground track and ground speed data are
received from the IR portion of the ADIRU 1 (IRS). The
aircraft altitude MSL is received from the air data portion of
the ADIRU 1.
When QNH baro setting is selected on FCU, baro correction
altitude (label 204) from ADIRU 1 is used.
When STD baro setting is selected on FCU, standard altitude
(label 203) from ADIRU 1 is used.
When QFE baro setting is selected on FCU (assuming QFE option
activated), the altitude is computed:
- during take off, using standard altitude (label 203) from
ADIRU 1 and landing elevation,
- during approach, using standard altitude (label 203) from
ADIRU 1 and QNH baro correction entered by the crew via the
MCDU. On the MCDU, a prompt comes into view adjacent to the
line key related to QNH information for input when < 180 NM
from destination.
(Ref. Fig. 017)
Other aircraft inputs include aircraft heading (from the
IR), roll attitude (from IR) and flight path angle (Gamma,
derived by the Enhanced GPWC).

2
_ Control Inputs
Installations provide discrete terrain display select
pushbutton switches (TERR ON ND) in the cockpit for each
display. These are momentary-action pushbutton switches that
are processed by the Enhanced GPWS input processing and signal
selection block as input to display control logic.
Additionally, for aircraft with predictive windshear radar
capability (if WR/PWS installed), a windshear override boolean
is computed using alert level bits from label 077 on WXR
hazard bus for the display control logic.

R **ON A/C 001-004,

R Post SB 34-1193 For A/C 001-004,

(Ref. Fig. 004)

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R Enhanced GPWC - Discrete Data Inputs
R Figure 017

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 **ON A/C ALL

R Post SB 34-1147 For A/C 001-004,

R Post SB 34-1193 For A/C 001-004,

(Ref. Fig. 004A)

**ON A/C ALL

R Post SB 34-1193 For A/C 001-004,

This boolean allows the Enhanced GPWC to manage priority

between Enhanced GPWC alerts and PWS alerts. The installation
requires input of cockpit-selected range scales provided by
the FCU for each ND.

(b) Local Terrain Processing

The local terrain processing block extracts and formats local
topographic data and terrain features from the related data bases
creating a set of digital elevation matrix overlays for use by
the terrain threat detection and display processing functions.
Additionally, data for the nearest runway are also extracted for
use by the terrain threat detection and display processing
functions. Processing for each topographic data base and the
runway data base are described in the following sub-sections.

1
_ Terrain Surface Data
Local terrain processing of topographic surface data updates a
set of digital elevation matrix overlays that are positioned
with respect to aircraft position. Each matrix element
contains the highest terrain altitude with respect to mean sea
level in that element area. Elements where terrain data are
not available are marked invalid. These unknown data are
displayed in magenta low density on ND whatever the altitude.

2
_ Obstacle Data
In addition to terrain surface data, provisions are made for
future use of an obstacle data base providing obstacle data in
the vicinity of major airports. Local terrain processing will
update a dedicated overlay within the digital elevation matrix
overlays with local obstacle altitude data.

3
_ Nearest Runway Data
Data for the nearest runway are extracted and processed for
use by the terrain threat detection and display processing
functions. Data are extracted from the same airport data base
used by the Terrain Clearance Floor functions (Ref. para.
D.(2)). This data base contains data on all hard-surface
runways 3500 ft. or more in length with published coordinates.
The contents of the data base are processed by the local
terrain processing into nearest runway center position,
nearest runway threshold position, and nearest runway altitude

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 for use by the Enhanced GPWS. These data are updated when the
terrain threat detection and display processing functions are
performed.

(c) Terrain Threat Detection

The terrain threat detection and display processing block
performs the threat analysis on the terrain data within computed
caution and warning envelope boundaries below and forward of the
aircraft path. Results of these threat assessments are combined
with background terrain data and data for the nearest runway and
formatted into a terrain display image which can be displayed on
Navigation Display in place of the weather image. In the event of
terrain caution or warning conditions, a specific audio alert is
triggered and the terrain display image is enhanced to highlight
each of the types of terrain threats.

1
_ Terrain Caution and Warning Envelopes
(Ref. Fig. 016)

a
_ Caution Altitude Floor
The caution altitude floor (or terrain floor) is computed
as a function of aircraft altitude with respect to nearest
runway altitude and range to the nearest runway threshold
position. This parameter represents a distance below the
aircraft. The relationship to the nearest runway threshold
location prevents undesired alerts when the aircraft is
taking off or landing at an airport. The system is
compatible with terrain clearances allowed for by
regulatory approach and departure design criteria.

b
_ Caution Look Ahead Distance
The caution look ahead distance is computed from aircraft
ground speed and turn rate to provide an advanced caution
with adequate time for the crew to react safely. Depending
on the situation this distance roughly corresponds to
between 40 and 60 seconds for advance alerting.

c
_ Warning Altitude Floor
The warning altitude floor is set to a fraction of the
caution altitude floor, as illustrated in the upper part of
this illustration.
(Ref. Fig. 016)
The warning altitude floor is computed as a function of
aircraft altitude with respect to nearest runway altitude
and range to the nearest runway threshold position. This
parameter represents a distance below the aircraft. The
relationship to the nearest runway threshold location

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R prevents undesired alerts when the aircraft is taking off
R or landing at an airport.

R d
_ Warning Look Ahead Distance
R The warning look ahead distance is a fraction of the
R caution look ahead distance (computed from aircraft ground
R speed and turn rate) to provide an advanced warning with
R adequate time for the crew to react safely.

R **ON A/C ALL

(d) Terrain Displays and Alerts

R (Ref. Fig. 018, 019)
The terrain awareness alerting and display function maintains a
background display of local terrain forward of the aircraft for
cockpit display. In the event of terrain caution or warning
conditions, an aural alert and lamp outputs are triggered. The
background image is then enhanced to highlight related terrain
threats forward of the aircraft.
The background terrain is depicted as variable density dot
patterns in green, yellow or red. The density and color being a
function of how close the terrain is relative to aircraft
altitude. Terrain alerts are depicted by painting the threatening
terrain as solid yellow or red.
The set of digital elevation matrix overlays is processed by the
terrain display algorithms into a matching set of display matrix
overlays and passed to the radar display output processor. The
display matrix overlays hold display attributes rather than
altitude for each matrix element. These attributes are computed
for the background and terrain threat areas and kept small (one
byte) to reduce memory requirements and transfer time to the
radar display output processor. The aircraft position and
aircraft heading are used at the radar display output processor
to extract a specific sweeping image ahead of the aircraft from
the display overlays.
Each element of the output display matrix overlays holds a single
display attribute byte with fields for the colors, patterns, and
symbols shown in the following table:

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 Enhanced GPWS - Terrain Background Display Legend
R Figure 018

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 Enhanced GPWS - Terrain Background Display on ND
R Figure 019

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 -------------------------------------------------------------------------------
| Color | Threat |
-------------------------------------------------------------------------------
| Solid Red | Warning terrain (approximately 30 seconds from |
| | impact) |
|---------------------|-------------------------------------------------------|
| Solid Yellow | Caution terrain (approximately 60 seconds from |
| | impact) |
|---------------------|-------------------------------------------------------|
| High Density Red | Terrain that is more than 2000 ft. above aircraft |
| | altitude |
|---------------------|-------------------------------------------------------|
| High Density | Terrain that is between 1000 and 2000 ft. above |
| Yellow | aircraft altitude |
|---------------------|-------------------------------------------------------|
| Medium Density | Terrain that is 500 (250 with gear down) ft. below |
| Yellow | to 1000 ft. above aircraft altitude |
|---------------------|-------------------------------------------------------|
| Medium Density | Terrain that is 500 (250 with gear down) ft. below |
| Green | to 1000 ft. below aircraft altitude |
|---------------------|-------------------------------------------------------|
| Light Density Green | Terrain that is 1000 to 2000 ft. below aircraft |
| | altitude |
|---------------------|-------------------------------------------------------|
| Black | No close terrain (Ref. NOTE in para. D.(1)(d)1_) |
|---------------------|-------------------------------------------------------|
| Light Density | Unknown terrain |
| Magenta | |
-------------------------------------------------------------------------------

1
_ Background Display
R (Ref. Fig. 019)
The background display is computed from the aircraft altitude
with respect to the terrain data in the digital elevation
matrix overlays. Where terrain data are available and
sufficiently close to the aircraft altitude, they are
presented in background color dot patterns reflecting the
projected separations shown in this illustration.
R (Ref. Fig. 018)
Different dot density patterns and colors are used to
represent terrain altitude bands with respect to the aircraft.
Areas with no terrain data available are painted with the low
density magenta. Known terrain sufficiently below the aircraft
altitude is black.

NOTE : Terrain is not shown if more than 2000 ft. below

____
reference altitude

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 AND/OR
Terrain is not shown if terrain elevation is within 400
ft. of runway elevation nearest the aircraft.

2
_ Terrain Caution Alert
R (Ref. Fig. 020)
When the conditions have been met to generate a terrain
caution alert, a specific audio alert and light output is
triggered and the background image is enhanced to highlight
the terrain caution threats.
At the start of a terrain caution alert, the terrain awareness
function triggers the caution audio alert phrase TERRAIN
AHEAD. The phrase is repeated after seven seconds if still
within the terrain caution envelope.
During a terrain caution alert, the GPWS legend of pushbutton
switches 4WZ and 5WZ is on.
During a terrain caution alert, areas where terrain violates
the terrain caution envelope along the aircraft track, and
within plus or minus 90 deg. of the aircraft track, are
painted with the caution color 100 per cent yellow.

3
_ Terrain Warning Alert
R (Ref. Fig. 020)
When the conditions have been met to generate a terrain
warning alert, a specific audio alert and light output is
triggered and the background image is enhanced to highlight
the terrain caution and warning threats.
At the start of a terrain warning alert, the terrain awareness
function triggers the warning audio alert phrase TERRAIN
AHEAD, PULL UP. The phrase is repeated continuously while
within the terrain warning envelope.
During a terrain warning alert, the GPWS legend of pushbutton
switches 4WZ and 5WZ is on.
During a terrain warning alert, areas where terrain violates
the terrain warning envelope along the aircraft track, and
within plus or minus 90 deg. of the aircraft track, are
painted with the warning color 100 per cent red.

NOTE : -Terrain may only be displayed on ND<s when FCU mode

____
ARC or ROSE is selected.
-When an alert occurs (caution or warning) and the FCU
mode is not in a correct mode (ARC or ROSE), the
message TERR. CHANGE MODE is displayed on ND<s.
-When an alert occurs (caution or warning) and the FCU
range selected is 160 or 320Nm the message TERR. REDUCE
RANGE is displayed on ND<s.

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 Enhanced GPWS - Warning and Caution Display on ND
R Figure 020

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 (e) Terrain Data Base
(Ref. Fig. 015)
Local terrain processing extracts and formats local topographic
terrain data from the Enhanced GPWS terrain data base for use by
the terrain threat detection and display processing functions.
This terrain data base divides the earth surface into grid sets
referenced horizontally on the geographic (latitude/longitude)
coordinate system of the WGS-84. Elements of the grid sets record
the highest terrain altitude (above MSL) in that element
respective area. Grid sets vary in resolution depending on
geographic location. Higher resolution grids are used around
airports. Lower resolution grids are used outside of airport
areas where aircraft altitude enroute makes hazardous conditions
unlikely and for which detailed terrain features are not
important to the flight crew.
Digital Elevation Models (DEM) are available for most of the
airports around the world today. In cases where the data are not
currently available, DEMs are generated in-house from available
topographic maps, sectional charts, and airline approach plates.
The process of acquiring, generating, assembling, and updating
the data base is governed by strict configuration controls to
ensure the highest level of data integrity. DEMs from external
sources are inputs to this process and are checked and formatted
for generation of the Enhanced GPWS terrain data base.
The global Enhanced GPWS terrain data base is organized in a
flexible manner. Using digital compression techniques, the
complete data base is stored in non-volatile memory within the
LRU. Updates and additions are easily accomplished by inserting a
single PCMCIA card in the card slot on the LRU front panel.
Status LEDs on the LRU front panel allow the operator to monitor
the data base load progress and completion.

(f) Obstacle Data Base

Provisions are also made for future use of an obstacle data base
providing obstacle data in the vicinity of major airports. This
data base will provide altitude for man-made obstacles or groups
of obstacles that protrude above the Enhanced GPWS terrain
protection floors.

(2) Terrain Clearance Floor (TCF)

The Terrain Clearance Floor (TCF) alert function adds an additional
element of protection to the standard GPWS. It creates an increasing
terrain clearance envelope around the airport runway to provide
protection against Controlled Flight Into Terrain (CFIT) situations
beyond that which is currently provided. TCF alerts are based on
current aircraft location, nearest runway center point position and
radio altitude. TCF is active during takeoff, cruise and final

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 approach. This alert mode complements the existing Mode 4 protection
by providing an alert based on insufficient terrain clearance even
when in landing configuration. Alerts for TCF illuminate GPWS cockpit
lamps and produce aural messages.

(a) System inputs

The following table lists the inputs required to allow
implementation of the TCF function:

-------------------------------------------------------------------------------
| Input | Source |
-------------------------------------------------------------------------------
| Radio Altitude | External: Radio Altimeter |
|----------------------------------|------------------------------------------|
| Latitude | External: FMS |
|----------------------------------|------------------------------------------|
| Longitude | External: FMS |
|----------------------------------|------------------------------------------|
| Runway Center Latitude | Internal: data base |
|----------------------------------|------------------------------------------|
| Runway Center Longitude | Internal: data base |
|----------------------------------|------------------------------------------|
| Navigation mode | FMS |
|----------------------------------|------------------------------------------|
| Alert Envelope Parameters | Internal: data base |
|----------------------------------|------------------------------------------|
| 1/2 Runway Length | Internal: data base |
|----------------------------------|------------------------------------------|
| System Error Factor | Internal: data base |
-------------------------------------------------------------------------------

(b) Runway Data Base

The TCF runway data base consists of data records containing the
position of airport runway center points along with 1/2 the
runway length. The data base includes all hard surface runways in
the world greater than or equal to 3500 ft. in length. The
process of generating this data base is certified and includes an
end check that validates that the data was not corrupted in the
translation process. This data base can be updated without
affecting the customer certified system part number.
The design of the data base and related software is such that
additional runway records can be added in the future without
altering the code. The data base provides a means of accessing
the runway record of the runway closest to the current aircraft
position.

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 (c) Alert Envelope
The TCF alert envelope is a circular band centered over the
nearest runway.
R (Ref. Fig. 021)
The distance from the runway center to the inner envelope edge is
equal to 1/2 the runway length plus the envelope bias factor.
Thus the inner and outer radius of the envelope are modulated
based on the runway length and envelope bias factor. Runway
length varies from one runway to the next, and the envelope bias
factor is typically 1/2 NM to 2 NM and varies with position
accuracy.
The outer alert envelope boundary extends to infinity, or until
it meets the outer alert envelope boundary of another runway. The
alert is inhibited below radio altitude of 30 ft. This cutoff
value was chosen to match the current Mode 4 lower cutoff value.

(d) System Outputs

When an aircraft penetrates the TCF alert envelope the following
aural message occurs: TOO LOW TERRAIN.
This aural message occurs once when initial envelope penetration
occurs, and one time thereafter for each 20 per cent degradation
in radio altitude. At the same time the GPWS legend of pushbutton
switches 4WZ and 5WZ comes on. The legends remain on until the
alert envelope is exited.

R
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 Enhanced GPWS - TCF Alert Envelope
R Figure 021

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 E. Warning Generation and Inhibition

(1) Audio Output

Alert outputs result in an audio voice warning unless inputs are
invalid or one of the audio suppression discretes is active. The
actual output message, or intended message during audio suppression,
is sent to the warning lamp logic for proper output activation.
The audio outputs consist of a transformer isolated 600 Ohm output.
Aural warnings and their priority rate are as follows:

------------------------------------------------------------------------
| RELATIVE | WARNING | POSSIBLE | LEGEND |
| PRIORITY | CONDITION | MESSAGES | |
|----------------------------------------------------------------------|
| HIGHEST | Mode 1 Pull Up | PULL UP | GPWS |
|----------|--------------------------|-------------------|------------|
| | Mode 2 Pull Up | PULL UP | GPWS |
|----------|--------------------------|-------------------|------------|
| | Mode 2 Pull Up Preface | TERRAIN TERRAIN | GPWS |
|----------|--------------------------|-------------------|------------|
| | Terrain Awareness Preface| TERRAIN AHEAD | GPWS |
|----------|--------------------------|-------------------|------------|
| | Terrain Awareness Pull Up| TERRAIN AHEAD | GPWS |
| | | PULL UP | |
|----------|--------------------------|-------------------|------------|
| | Mode 2 Terrain | TERRAIN | GPWS |
|----------|--------------------------|-------------------|------------|
| * | Terrain Awareness Caution| TERRAIN AHEAD | GPWS |
|----------|--------------------------|-------------------|------------|
| * | Mode 4 Too Low Terrain | TOO LOW TERRAIN | GPWS |
|----------|--------------------------|-------------------|------------|
| | TCF Too Low Terrain | TOO LOW TERRAIN | GPWS |
|----------|--------------------------|-------------------|------------|
| * | Mode 4 Too Low Gear | TOO LOW GEAR | GPWS |
|----------|--------------------------|-------------------|------------|
| * | Mode 4 Too Low Flaps | TOO LOW FLAPS | GPWS |
|----------|--------------------------|-------------------|------------|
| * | Mode 1 Sinkrate | SINKRATE | GPWS |
|----------|--------------------------|-------------------|------------|
| * | Mode 3 Don<t Sink | DON<T SINK | GPWS |
|----------|--------------------------|-------------------|------------|
| LOWEST * | Mode 5 Glide slope | GLIDE SLOPE | G/S |
------------------------------------------------------------------------

* Allows interleaving of multiple alerts.

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 The voice warning circuits also contain logic elements which ensure
that:
- only one message at a time is output,
- higher priority messages interrupt lower priority messages except
if interleaving is allowed (Ref. table above),
- a triggered message is completed even when warning condition
ceases,
- a 0.75 second pause exists between warning messages.

(2) Alert Discrete Outputs

Mode 5 GLIDE SLOPE message activates the alert lamp output (which
illuminates G/S amber legend).
All other messages activate the warning lamp output (which
illuminates GPWS red legend).
(Ref. Fig. 003)

R (3) Control and Indicating

R (Ref. Fig. 022)

R (4) Inhibitions

(a) All audio inhibition:

- The INHIBIT ALL AUDIO discrete input
(Ref. Fig. 005)
controls the audio outputs as follows. When grounded, all
voices are inhibited (not interrupted, all aural messages once
started are finished). Visual and display indications are not
affected. This input is used to manage the audio priority with
other systems (FWS, PWS, TCAS).

(b) Modes 1 to 5 inhibitions:

- The INHIBIT MODES 1 TO 5 discrete
(Ref. Fig. 005)
input controls the audio and visual outputs as follows. When
grounded,this input always inhibits all GPWS aural and visual
indications with the exception of Terrain Clearance Floor
Alerts and Terrain Awareness caution and warnings. This input
is wired to SYS pushbutton switch to manually inhibit GPWS
Modes 1 to 5.

(c) TAD and TCF inhibitions:

- The TERRAIN AWARENESS INHIBIT discrete input
(Ref. Fig. 005)
controls the audio, visual and display outputs as follows. When
grounded, this input always inhibits TAD and TCF aural, visual
and display indications. This input is wired to the TERR

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 push-button switch to manually inhibit the TAD and TCF
functions.
- When the automatic deselection option actived TAD and TCF
functions may also be inhibit automatically when the FMS
aircraft position accuracy is not accurate enough. This is
indicated to the crew by the automatic deselection of terrain
display and the illumation of the TERR STBY memo on the ECAM
display unit.

F. Enhanced GPWC Maintenance Output

A maintenance output signal (label 270 octal) is provided by the ARINC
429 transmitter. The transmitter converts the microprocessor parallel
data to standard serial data for the DMU of the AIDS.

**ON A/C 001-004,

8. Test
____

A. Self-Tests

(1) On the ground only, the Enhanced GPWC provides self-test capability,
providing an indication of the ability of the Enhanced GPWC to
perform its intended function.

(2) The Enhanced GPWC self-test is initiated by momentarily pressing

GPWS/G/S pushbutton switches or activated via the MCDU on the ground.
When activated by pressing the GPWS/G/S pushbutton switches, the
self-test is enunciated, via the same audio system as the Enhanced
GPWS alerts. This self-test can also be accessed via the headphone
jack on the front panel of the Enhanced GPWC and it has been divided
into six different levels to help with Enhanced GPWC testing and
troubleshooting.

(a) Level 1
Level 1, functional testing, provides an overview of the current
operational functions selected and provides an indication of
their operational status.
A long level 1 self-test sequence is initiated when the GPWS/G/S
pushbutton switch is not released while self-test voices start.
Level 1 self-test sequence:
- the FAULT legend of the GPWS/SYS pushbutton switch is on,
- the FAULT legend of the GPWS/TERR pushbutton switch is on,
- G/S legends of both GPWS/G/S pushbutton switches are on,
- GLIDE SLOPE audio phase is broadcast,
- G/S legends of both GPWS/G/S pushbutton switches go off,
- GPWS legends of both GPWS/G/S pushbutton switches are on,

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 Enhanced GPWS - Control and Indicating
R Figure 022 (SHEET 1)

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 Enhanced GPWS - Control and Indicating
R Figure 022 (SHEET 2)

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 Enhanced GPWS - Control and Indicating
R Figure 022 (SHEET 3)

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 Enhanced GPWS - Control and Indicating
R Figure 022 (SHEET 4)

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 - PULL UP audio phase is broadcast,
- TERRAIN AHEAD PULL UP audio phase is broadcast,
- GPWS legends of both GPWS/G/S pushbutton switches go off,
- ON legends of both TERR ON ND pushbutton switches are on,
- terrain self-test pattern is displayed on both NDs,
(Ref. Fig. 023)
- vocabulary sequence when long self-test initiated:

SINK RATE
PULL UP
TERRAIN
PULL UP
DON<T SINK
DON<T SINK
TOO LOW TERRAIN
TOO LOW GEAR
TOO LOW FLAPS
TOO LOW TERRAIN
GLIDE SLOPE
MINIMUMS MINIMUMS
TOO LOW TERRAIN
TERRAIN AHEAD
TERRAIN AHEAD
TERRAIN AHEAD PULL UP

- terrain self-test pattern turns off,

- ON legends of both TERR ON ND pushbutton switches and the
images displayed on both NDs revert to the configuration
selected before the test,
- the FAULT legend of the GPWS/SYS pushbutton switch goes off,
- the FAULT legend of the GPWS/TERR pushbutton switch goes off.

(b) Level 2
Level 2, current faults, provides a listing of the internal and
external faults currently detected by the Enhanced GPWC.
Level 2 self-test is initiated by pressing the GPWS/G/S
pushbutton switch within 3 seconds after the end of level 1
self-test.

(c) Level 3
Level 3, Enhanced GPWS configuration, indicates the current
configuration by listing the current hardware, software, data
bases and program pin inputs detected by the Enhanced GPWC.
This level is initiated by pressing the GPWS/G/S pushbutton
switch when PRESS TO CONTINUE message is enunciated.

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 Enhanced GPWS - Test Pattern
R Figure 023

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 (d) Level 4
Level 4, fault history, provides a historical record of both
internal and external faults detected by the Enhanced GPWC.
This level is initiated by pressing the GPWS/G/S pushbutton
switch when PRESS TO CONTINUE message is enunciated.

(e) Level 5
Level 5, warning history, provides a historical record of the
warnings and cautions given by the Enhanced GPWC.
This level is initiated by pressing the GPWS/G/S pushbutton
switch when PRESS TO CONTINUE message is enunciated.

(f) Level 6
Level 6, discrete test, provides annunciation of discrete input
transitions to be used for maintenance support.
This level is initiated by pressing the GPWS/G/S pushbutton
switch when PRESS TO CONTINUE message is enunciated.

(3) To speed up the navigation of self-test levels and information two

types of cancel sequences are supported. Pressing and holding the
GPWS/G/S pushbutton switch for less than 2 seconds is considered to
be a short cancel. Pressing and holding the cockpit GPWS/G/S
pushbutton switch for more than 2 seconds is considered to be a long
cancel.

B. CFDS Interface

R (1) Interactive function

To gain access to the BITE, it is necessary to use one MCDU (Ref.
22-82-00).
All information displayed on the MCDU during the BITE TEST
configuration can be printed by the printer (Ref. 31-35-00).

(2) BITE description

The BITE facilitates maintenance on in-service aircraft. It detects
and identifies faults related to the Enhanced GPWS. The BITE of the
Enhanced GPWC is connected to the CFDIU.
The BITE:
- continuously transmits Enhanced GPWS status and its identification
message to the CFDIU,
- memorizes the faults which occurred during the last 63 flight
segments,
- monitors data inputs from the various peripherals (FMGC, RA
transceiver, ILS receiver, ADIRU, SFCC, LGCIU, ECAM control panel
and CFDIU),
- transmits to the CFDIU the result of the tests performed,
- can communicate with the CFDIU through the menus.

R
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 The BITE can operate in two modes:
- normal mode
- menu mode.

(a) Normal mode

During normal mode, the BITE monitors cyclically the status of
the Enhanced GPWS. It transmits its information to the CFDIU
during the given flight.
In case of fault detection, the BITE stores the information in
the fault memories.
These items of information are transmitted to the CFDIU every 100
ms by an ARINC 429 message with label 356.

(b) Menu mode

The menu mode can only be activated on the ground.
This mode enables communication between the CFDIU and the
Enhanced GPWC BITE by means of the MCDU.
The Enhanced GPWS menu mode is composed of:
- LAST LEG REPORT
(Ref. Fig. 024)
- PREVIOUS LEGS REPORT
(Ref. Fig. 024)
- LRU IDENTIFICATION
(Ref. Fig. 024)
- GROUND SCANNING
(Ref. Fig. 025)
- TROUBLE SHOOTING DATA
(Ref. Fig. 026)
- CLASS 3 FAULTS
(Ref. Fig. 024)
- GROUND REPORT
(Ref. Fig. 025)
- TEST
(Ref. Fig. 026)

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 Maintenance Test Procedure - Sub-Menu Function
Figure 024

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R Maintenance Test Procedure - Sub-Menu Function
R Figure 024A

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 Maintenance Test Procedure - Sub-Menu Function
Figure 025

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R Maintenance Test Procedure - Sub-Menu Function
R Figure 025A

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 Maintenance Test Procedure - Sub-Menu Function
Figure 026

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 (3) Failure condition

-------------------------------------------------------------------------------
| FAULT | EXAMPLE | REASON |
|-----------------------------------------------------------------------------|
| ARINC 429 | IRS BUS INACTIVE | No expected input labels received |
| Bus Fault | | for more than 4 s. |
|-----------------------------------------------------------------------------|
| ARINC 429 | FMGC LATITUDE | The SSM of the input data indicates|
| Signal Fault | FAILURE | Failure/Warning or the input label |
| | | is not meeting the required update |
| | | rate. |
|-----------------------------------------------------------------------------|
| Discrete | Flaps stuck down | For at least 60 s: |
| Input Faults | | - FLAPS are in landing configura- |
| | | tion through SFFC1 (GROUND |
| | | signal at GPWC FLAPS discrete |
| | | input) or FLAP MODE pushbutton |
| | | switch is selected OFF and |
| | | - AIRSPEED > 250 Kts and |
| | | - IN AIR and |
| | | - RADIO ALT VALID and |
| | | - AIRSPEED VALID. |
| |--------------------------------------------------------------|
| | Flaps stuck up | For at least 2 s: |
| | | - FLAPS are not in landing configu-|
| | | ration and FLAP MODE pushbutton |
| | | switch is in normal position |
| | | (not OFF) and |
| | | - RADIO ALT < = 100 ft. and |
| | | - MODE 4 TOO LOW FLAPS alert is |
| | | on. |
| |--------------------------------------------------------------|
| | Gear stuck down | For at least 60 s: |
| | | - GEAR is down through LGCIU1 and |
| | | - AIRSPEED > 290 Kts and |
| | | - IN AIR and |
| | | - RADIO ALT VALID and |
| | | - AIRSPEED VALID. |
| |--------------------------------------------------------------|
| | Gear stuck up | For at least 2 s: |
| | | - GEAR not down and |
| | | - RADIO ALT < = 100 ft. and |
| | | - MODE 4 TOO LOW GEAR alert is |
| | | on. |
| |--------------------------------------------------------------|
| | AUDIO CANCEL INVALID | Discrete grounded for > 30 s. |

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 -------------------------------------------------------------------------------
| FAULT | EXAMPLE | REASON |
|-----------------------------------------------------------------------------|
| |--------------------------------------------------------------|
| | GPWS TERR INHIBIT | Discrete grounded for > 60 s. |
| | INVALID | |
| |--------------------------------------------------------------|
| | GPWS INHIBIT INVALID | Discrete grounded for > 60 s. |
| |--------------------------------------------------------------|
| | ALL AUDIO SUPPRESS | Discrete grounded for > 60 s. |
| | INVALID | |
| |--------------------------------------------------------------|
| | GLIDE SLOPE CANCEL | Discrete grounded for > 15 s. |
| | INVALID | |
| |--------------------------------------------------------------|
| | RANGE FAULT | No valid range provided > 5 s. |
| |--------------------------------------------------------------|
| | SELF TEST INVALID | Discrete selected for > 60 s. |
| |--------------------------------------------------------------|
| | MOMENTARY TERRAIN | Selected for > 15 s. |
| | SELECT 1 (or2) INVALID | |
-------------------------------------------------------------------------------

**ON A/C ALL

R Post SB 34-1193 For A/C 001-004,

8. Test
____

A. Self-Tests

(1) On the ground only, the Enhanced GPWC provides self-test capability,
providing an indication of the ability of the Enhanced GPWC to
perform its intended function.

(2) The Enhanced GPWC self-test is initiated by momentarily pressing

GPWS/G/S pushbutton switches or activated via the MCDU on the ground.
When activated by pressing the GPWS/G/S pushbutton switches, the
self-test is enunciated, via the same audio system as the Enhanced
GPWS alerts. This self-test can also be accessed via the headphone
jack on the front panel of the Enhanced GPWC and it has been divided
into six different levels to help with Enhanced GPWC testing and
troubleshooting.

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R (a) Level 1
R Level 1, functional testing, provides an overview of the current
R operational functions selected and provides an indication of
R their operational status.
R A long level 1 self-test sequence is initiated when the GPWS/G/S
R pushbutton switch is not released while self-test voices start.
R Level 1 self-test sequence:
R - the FAULT legend of the GPWS/SYS pushbutton switch is on,
R - the FAULT legend of the GPWS/TERR pushbutton switch is on,
R - G/S legends of both GPWS/G/S pushbutton switches are on,
R - GLIDE SLOPE audio phase is broadcast,
R - G/S legends of both GPWS/G/S pushbutton switches go off,
R - GPWS legends of both GPWS/G/S pushbutton switches are on,
R - PULL UP audio phase is broadcast,
R - TERRAIN AHEAD PULL UP audio phase is broadcast,
R - GPWS legends of both GPWS/G/S pushbutton switches go off,
R - ON legends of both TERR ON ND pushbutton switches are on,
R - terrain self-test pattern is displayed on both NDs,
R (Ref. Fig. 023)
R - vocabulary sequence when long self-test initiated:
R
R SINK RATE
R PULL UP
R TERRAIN
R PULL UP
R DON<T SINK
R DON<T SINK
R TOO LOW TERRAIN
R TOO LOW GEAR
R TOO LOW FLAPS
R TOO LOW TERRAIN
R GLIDE SLOPE
R TOO LOW TERRAIN
R TERRAIN AHEAD
R TERRAIN AHEAD
R TERRAIN AHEAD PULL UP
R
R - terrain self-test pattern turns off,
R - ON legends of both TERR ON ND pushbutton switches and the
R images displayed on both NDs revert to the configuration
R selected before the test,
R - the FAULT legend of the GPWS/SYS pushbutton switch goes off,
R - the FAULT legend of the GPWS/TERR pushbutton switch goes off.

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 (b) Level 2
Level 2, current faults, provides a listing of the internal and
external faults currently detected by the Enhanced GPWC.
Level 2 self-test is initiated by pressing the GPWS/G/S
pushbutton switch within 3 seconds after the end of level 1
self-test.

(c) Level 3
Level 3, Enhanced GPWS configuration, indicates the current
configuration by listing the current hardware, software, data
bases and program pin inputs detected by the Enhanced GPWC.
This level is initiated by pressing the GPWS/G/S pushbutton
switch when PRESS TO CONTINUE message is enunciated.

(d) Level 4
Level 4, fault history, provides a historical record of both
internal and external faults detected by the Enhanced GPWC.
This level is initiated by pressing the GPWS/G/S pushbutton
switch when PRESS TO CONTINUE message is enunciated.

(e) Level 5
Level 5, warning history, provides a historical record of the
warnings and cautions given by the Enhanced GPWC.
This level is initiated by pressing the GPWS/G/S pushbutton
switch when PRESS TO CONTINUE message is enunciated.

(f) Level 6
Level 6, discrete test, provides annunciation of discrete input
transitions to be used for maintenance support.
This level is initiated by pressing the GPWS/G/S pushbutton
switch when PRESS TO CONTINUE message is enunciated.

(3) To speed up the navigation of self-test levels and information two

types of cancel sequences are supported. Pressing and holding the
GPWS/G/S pushbutton switch for less than 2 seconds is considered to
be a short cancel. Pressing and holding the cockpit GPWS/G/S
pushbutton switch for more than 2 seconds is considered to be a long
cancel.

B. CFDS Interface

R (1) Interactive function

To gain access to the BITE, it is necessary to use one MCDU (Ref.
22-82-00).
All information displayed on the MCDU during the BITE TEST
configuration can be printed by the printer (Ref. 31-35-00).

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R (2) BITE description
R The BITE facilitates maintenance on in-service aircraft. It detects
R and identifies faults related to the Enhanced GPWS. The BITE of the
R Enhanced GPWC is connected to the CFDIU.
R The BITE:
R - continuously transmits Enhanced GPWS status and its identification
R message to the CFDIU,
R - memorizes the faults which occurred during the last 63 flight
R segments,
R - monitors data inputs from the various peripherals (FMGC, RA
R transceiver, ILS receiver, ADIRU, SFCC, LGCIU, ECAM control panel
R and CFDIU),
R - transmits to the CFDIU the result of the tests performed,
R - can communicate with the CFDIU through the menus.
R The BITE can operate in two modes:
R - normal mode
R - menu mode.

R (a) Normal mode

R During normal mode, the BITE monitors cyclically the status of
R the Enhanced GPWS. It transmits its information to the CFDIU
R during the given flight.
R In case of fault detection, the BITE stores the information in
R the fault memories.
R These items of information are transmitted to the CFDIU every 100
R ms by an ARINC 429 message with label 356.

R (b) Menu mode

R The menu mode can only be activated on the ground.
R This mode enables communication between the CFDIU and the
R Enhanced GPWC BITE by means of the MCDU.
R The Enhanced GPWS menu mode is composed of:
R - LAST LEG REPORT
R (Ref. Fig. 024A)
R - PREVIOUS LEGS REPORT
R (Ref. Fig. 024A)
R - LRU IDENTIFICATION
R (Ref. Fig. 024A)
R - GROUND SCANNING
R (Ref. Fig. 025A)
R - TROUBLE SHOOTING DATA
R (Ref. Fig. 026A)
R - CLASS 3 FAULTS
R (Ref. Fig. 024A)
R - GROUND REPORT
R (Ref. Fig. 025A)
R - CURRENT STATUS

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R Maintenance Test Procedure - Sub-Menu Function
R Figure 026A

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R (Ref. Fig. 026A)
R - TEST
R (Ref. Fig. 027)

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R Maintenance Test Procedure - Sub-Menu Function
R Figure 027

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R (3) Failure condition

R -------------------------------------------------------------------------------
R | FAULT | EXAMPLE | REASON |
R |-----------------------------------------------------------------------------|
R | ARINC 429 | IRS BUS INACTIVE | No expected input labels received |
R | Bus Fault | | for more than 4 s. |
R |-----------------------------------------------------------------------------|
R | ARINC 429 | FMGC LATITUDE | The SSM of the input data indicates|
R | Signal Fault | FAILURE | Failure/Warning or the input label |
R | | | is not meeting the required update |
R | | | rate. |
R |-----------------------------------------------------------------------------|
R | Discrete | Flaps stuck down | For at least 60 s: |
R | Input Faults | | - FLAPS are in landing configura- |
R | | | tion through SFFC1 (GROUND |
R | | | signal at GPWC FLAPS discrete |
R | | | input) or FLAP MODE pushbutton |
R | | | switch is selected OFF and |
R | | | - AIRSPEED > 250 Kts and |
R | | | - IN AIR and |
R | | | - RADIO ALT VALID and |
R | | | - AIRSPEED VALID. |
R | |--------------------------------------------------------------|
R | | Flaps stuck up | For at least 2 s: |
R | | | - FLAPS are not in landing configu-|
R | | | ration and FLAP MODE pushbutton |
R | | | switch is in normal position |
R | | | (not OFF) and |
R | | | - RADIO ALT < = 100 ft. and |
R | | | - MODE 4 TOO LOW FLAPS alert is |
R | | | on. |
R | |--------------------------------------------------------------|
R | | Gear stuck down | For at least 60 s: |
R | | | - GEAR is down through LGCIU1 and |
R | | | - AIRSPEED > 290 Kts and |
R | | | - IN AIR and |
R | | | - RADIO ALT VALID and |
R | | | - AIRSPEED VALID. |
R | |--------------------------------------------------------------|
R | | Gear stuck up | For at least 2 s: |
R | | | - GEAR not down and |
R | | | - RADIO ALT < = 100 ft. and |
R | | | - MODE 4 TOO LOW GEAR alert is |
R | | | on. |
R -------------------------------------------------------------------------------

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R **ON A/C ALL

(4) Reporting function

(a) Internal failures

---------------------------------------------------------------------------
| Reported Internal Failures |
|-------------------------------------------------------------------------|
| MESSAGE | CLASS | ATA |
|-------------------------------------------------------------------------|
| GPWC (1WZ) | 1 | 34-48-34 |
| GPWC (1WZ) | 3 | 34-48-34 |
| WRG:PIN PROG/GPWC (1WZ) | 1 | 34-48-34 |
| CAPT/FO GPWS GS PB SW (4WZ/5WZ)/GPWC(1WZ) | 1 | 34-48-34 |
| FO GPWS GS PB SW (5WZ)/GPWC(1WZ) | 1 | 34-48-08 |
| ECP(6WT)/GPWC(1WZ) | 1 | 31-61-12 |
| GPWS SYS PB SW (9WZ)/GPWC (1WZ) | 1 | 34-48-08 |
| GPWS TERR PB SW (31WZ)/GPWC(1WZ) | 1 | 34-48-08 |
| GPWC(1WZ)/FWC1/2(1WW1/2)/WXR1/2(1SQ1/2) | 1 | 34-48-34 |
| CAPT TERR ON ND PB SW (30WZ1)/GPWC (1WZ) | 1 | 34-48-08 |
| FO TERR ON ND PB SW (30WZ2)/GPWC (1WZ) | 1 | 34-48-08 |
---------------------------------------------------------------------------

(b) External failures

---------------------------------------------------------------------------
| Reported External Failures |
|-------------------------------------------------------------------------|
| MESSAGE | CLASS | ATA |
|-------------------------------------------------------------------------|
| GPWS FLP MODE PB SW (7WZ)/SFCC1(21CV)/GPWC(1WZ) | 1 | 34-48-08 |
| LGCIU1 (5GA1)/GPWC (1WZ) | 1 | 32-31-71 |
| CFDIU (1TW)/GPWC (1WZ) | 3 | 31-32-34 |
| RA1 (2SA1)/GPWC (1WZ) | 1 | 34-42-33 |
| ADIRU1 (1FP1)/GPWC (1WZ) | 1 | 34-12-34 |
| ADIRU1 (1FP1)/GPWC (1WZ) | 3 | 34-12-34 |
| ILS1 (2RT1)/GPWC (1WZ) | 1 | 34-36-31 |
| ILS1 (2RT1)/GPWC (1WZ) | 3 | 34-36-31 |
| FMGC1 (1CA1)/GPWC (1WZ) | 1 | 22-83-34 |
| FMGC1 (1CA1)/GPWC (1WZ) | 3 | 22-83-34 |
| FCU (3CA) BUS CP-L/GPWC (1WZ) | 1 | 22-81-12 |
| FCU (3CA) BUS CP-R/GPWC (1WZ) | 1 | 22-81-12 |
| WXR1 (1SQ1) BUS HAZARD/GPWC (1WZ) | 1 | 34-41-33 |
| WXR1 (1SQ1)/GPWC (1WZ) | 1 | 34-41-33 |
---------------------------------------------------------------------------

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 C. BITE Implementation
The BITE capability is implemented primarily in software. Most of the
tests run continuously, while the remainder run only as the result of
certain events (e.g. power-up). Failures are indicated by monitor output
discretes, the ARINC 429 outputs, the Enhanced GPWC audio output, and on
the MCDU (interactive mode).
These failures are saved in the flight history memory if they occurred
during flight. Some BITE failures inhibit alerts and warnings. In these
cases, the self-test is inhibited.
Internal test processing:

------------------------------------------------------------------------------
| TEST | TESTED INTERNAL COMPONENTS | DURATION | ACTIVATION |
| DESIGNATION | | | CONDITIONS |
|----------------------------------------------------------------------------|
| MCDU system | - CPU | 30 s | Relevant MCDU |
| test | - RAM | | menu line key |
| | - EPROM | | selection |
| | - Wait state | | |
| | - Non Envelope modulation NVM | | |
| | - Watchdog timer | | |
| | - A/D converter | | |
| | - Voice generator | | |
| | - ARINC 429 transmitter | | |
| | - Software configuration data | | |
| | base monitor | | |
| | - ARINC 429 parity | | |
| | - Software operating system | | |
| | monitor | | |
| | - Software watchdog monitor | | |
| | - Envelope modulation NVM | | |
| | - ARINC 429 receiver | | |
|----------------------------------------------------------------------------|
| Cockpit | Ref. para. 8. A. | | Ref. para. 8. A.|
| Self-test | | | |
------------------------------------------------------------------------------

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 GROUND PROXIMITY WARNING SYSTEM (GPWS) - SERVICING
__________________________________________________

TASK 34-48-00-610-001

Uploading of the Enhanced GPWC Data Base

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
34-48-00-740-002 BITE Test of the Enhanced GPWC
R 52-41-00-410-002 Close the Avionics Compartment Doors after Access
34-48-00-991-002 Fig. 301

3. __________
Job Set-up

Subtask 34-48-00-861-055

A. Energize the aircraft electrical circuits

(Ref. TASK 24-41-00-861-002).

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 Subtask 34-48-00-010-053

B. Get Access

(1) Put the access platform in position at the access door 824 in zone
128.

(2) Open the access door 824.

Subtask 34-48-00-865-066

C. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
121VU EIS/GPWS/115VAC 3WZ P07

4. Procedure
_________

(Ref. Fig. 301/TASK 34-48-00-991-002)

Subtask 34-48-00-970-050

A. Loading of the PCMCIA Card Software

NOTE : Before you load the software make sure that the version of the
____
terrain data base is correct.

(1) Make sure that the COMPUTER OK LED on the face of the Enhanced GPWC,
is on.

(2) Open the door on the face of the Enhanced GPWC.

(3) Put the PCMCIA card into the PCMCIA card slot.

(4) During software loading, the IN PROG LED stays on and the COMPUTER OK
LED is off.

(5) When the loading is completed, the XFER COMP LED comes on.

(6) Remove the PCMCIA card from the Enhanced GPWC.

(7) After approximately 15 seconds, the COMPUTER OK LED comes on to tell

the operator that the loading of the PCMCIA card contents is
completed.

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 Enhanced GPWC Face
Figure 301/TASK 34-48-00-991-002

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 (8) Close the door on the face of the Enhanced GPWC.

Subtask 34-48-00-740-053

B. Do the BITE Test of the Enhanced GPWC (Ref. TASK 34-48-00-740-002).

5. Close-up
________

Subtask 34-48-00-410-053

A. Close Access

(1) Make sure that the work area is clean and clear of tool(s) and other
items.

R (2) Close the access door 824 (Ref. TASK 52-41-00-410-002).

(3) Remove the access platform(s).

Subtask 34-48-00-862-054

B. De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

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 GROUND PROXIMITY WARNING SYSTEM (GPWS) - ADJUSTMENT/TEST
________________________________________________________

TASK 34-48-00-710-001

Operational Test of Enhanced GPWS Ground Self-test Function

WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE
_______
YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.

1. __________________
Reason for the Job

Refer to the MPD TASK: 344800-01

Operational test of GPWS ground self-test function

2. ______________________
Job Set-up Information

A. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
34-10-00-860-002 ADIRS Start Procedure

**ON A/C ALL

R Post SB 34-1193 For A/C 001-004,

34-48-00-991-001 Fig. 501

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 **ON A/C ALL

3. __________
Job Set-up

Subtask 34-48-00-860-059

A. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits

(Ref. TASK 24-41-00-861-002).

(2) On the overhead panel, on the ADIRS CDU, set the OFF/NAV/ATT selector
switch related to the ADIRU1 to NAV (Ref. TASK 34-10-00-860-002).

(3) On the overhead control and indicating panel 21VU, on the GPWS
section, make sure that the five GPWS pushbutton switches are
released (legends off).

(4) On the panels 301VU and 500VU set the ND POTENTIOMETER to BRT
position.

Subtask 34-48-00-865-057

B. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
121VU EIS/GPWS/115VAC 3WZ P07
121VU EIS/GPWS/28VDC 2WZ P06

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 4. Procedure
_________

R **ON A/C 001-004,

Subtask 34-48-00-710-056

A. Operational Test of Enhanced GPWS Ground Self-test Function

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

On the CAPT (F/O) LIGHTING/LOUD

SPEAKER control panel 301VU (500VU):

- push the GPWS/G/S pushbutton On the panel 21VU:

switch and hold it for five - the FAULT legend of the GPWS/SYS
seconds after the first aural pushbutton switch comes on.
warning. - the FAULT legend of the GPWS/TERR
pushbutton switch comes on.

On the panels 301VU and 500VU:

- the G/S legends come on.

In the loudspeakers:
- the GLIDESLOPE aural warning operates
then stops.

On the panels 301VU and 500VU:

- the G/S legends go off.
- the GPWS legends come on.

In the loudspeakers:
- the PULL UP aural warning operates
then stops.
- the TERRAIN AHEAD PULL UP aural
warning operates then stops.

On the panels 301VU and 500VU:

- the GPWS legends go off.

On the LANDING GEAR control and

indicating panel 402VU, and on the TERR
ON ND panel 403VU:
- the ON legends of the TERR ON ND
pushbutton switches come on.

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
On the CAPT (F/O) NDs:
- the test pattern is shown and the
TERR TST amber message comes into
view.
(Ref. Fig. 501/TASK 34-48-00-991-001)

The above warnings operate, then all

these warnings, one after the other:
- GLIDE SLOPE,
- PULL UP,
- TERRAIN AHEAD,
- PULL UP,
- SINK RATE,
- PULL UP,
- TERRAIN,
- PULL UP,
- DON<T SINK,
- DON<T SINK,
- TOO LOW TERRAIN,
- TOO LOW GEAR,
- TOO LOW FLAPS,
- TOO LOW TERRAIN,
- GLIDE SLOPE,
- MINIMUMS MINIMUMS,
- TOO LOW TERRAIN,
- TERRAIN AHEAD,
- TERRAIN AHEAD,
- TERRAIN AHEAD PULL UP.

On the LANDING GEAR control and

indicating panel 402VU, and on the TERR
ON ND panel 403VU:
- the ON legends of the TERR ON ND
pushbutton switches go off.

On the CAPT (F/O) NDs:

- the TERR TST amber message goes off.

On the panel 21VU:

- the FAULT legend of the GPWS/SYS
pushbutton switch goes off.
- the FAULT legend of the GPWS/TERR
pushbutton switch goes off.

R
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 Enhanced GPWS Test Pattern
Figure 501/TASK 34-48-00-991-001

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
On the CAPT (F/O) ND<s:
- the TEST PATTERN turns off.

**ON A/C ALL

R Post SB 34-1193 For A/C 001-004,

Subtask 34-48-00-710-056-A

A. Operational Test of Enhanced GPWS Ground Self-test Function

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

On the CAPT (F/O) LIGHTING/LOUD

SPEAKER control panel 301VU (500VU):

- push the GPWS/G/S pushbutton On the panel 21VU:

switch and hold it for five - the FAULT legend of the GPWS/SYS
seconds after the first aural pushbutton switch comes on.
warning. - the FAULT legend of the GPWS/TERR
pushbutton switch comes on.

On the panels 301VU and 500VU:

- the G/S legends come on.

In the loudspeakers:
- the GLIDESLOPE aural warning operates
then stops.

On the panels 301VU and 500VU:

- the G/S legends go off.
- the GPWS legends come on.

In the loudspeakers:
- the PULL UP aural warning operates
then stops.
- the TERRAIN AHEAD PULL UP aural
warning operates then stops.

On the panels 301VU and 500VU:

- the GPWS legends go off.

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
On the LANDING GEAR control and
indicating panel 402VU, and on the TERR
ON ND panel 403VU:
- the ON legends of the TERR ON ND
pushbutton switches come on.

On the CAPT (F/O) NDs:

- the test pattern is shown and the
TERR TST amber message comes into
view.
(Ref. Fig. 501/TASK 34-48-00-991-001)

The above warnings operate, then all

these warnings, one after the other:
- GLIDE SLOPE,
- PULL UP,
- TERRAIN AHEAD,
- PULL UP,
- SINK RATE,
- PULL UP,
- TERRAIN,
- PULL UP,
- DON<T SINK,
- DON<T SINK,
- TOO LOW TERRAIN,
- TOO LOW GEAR,
- TOO LOW FLAPS,
- TOO LOW TERRAIN,
- GLIDE SLOPE,
- TOO LOW TERRAIN,
- TERRAIN AHEAD,
- TERRAIN AHEAD,
- TERRAIN AHEAD PULL UP.

On the LANDING GEAR control and

indicating panel 402VU, and on the TERR
ON ND panel 403VU:
- the ON legends of the TERR ON ND
pushbutton switches go off.

On the CAPT (F/O) NDs:

- the TERR TST amber message goes off.

On the panel 21VU:

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
- the FAULT legend of the GPWS/SYS
pushbutton switch goes off.
- the FAULT legend of the GPWS/TERR
pushbutton switch goes off.

On the CAPT (F/O) ND<s:

- the TEST PATTERN turns off.

**ON A/C ALL

5. Close-up
________

Subtask 34-48-00-860-060

A. Put the aircraft back to its initial configuration.

(1) On the overhead panel, on the ADIRS CDU, set the OFF/NAV/ATT selector
switch related to the ADIRU1 to OFF.

(2) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

(3) Make sure that the work area is clean and clear of tool(s) and other
items.

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 TASK 34-48-00-710-002

Operational Test of the Enhanced GPWS with Stall Warning Test and Activation of
the GPWS/SYS Pushbutton Switch and EMER CANC Key

WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE
_______
YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
31-32-00-860-010 Procedure to Get Access to the SYSTEM REPORT/TEST NAV
Page
34-10-00-860-002 ADIRS Start Procedure

3. __________
Job Set-up

Subtask 34-48-00-860-061

A. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits

(Ref. TASK 24-41-00-861-002).

(2) On the overhead control and indicating panel 21VU, on the GPWS
section, make sure that the five GPWS pushbutton switches are
released (legends off).

(3) On the center pedestal, on one MCDU, get the SYSTEM REPORT/TEST/NAV
page
(Ref. TASK 31-32-00-860-010).

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 (4) On the overhead panel, on the the ADIRS CDU, set the OFF/NAV/ATT
selector switch related to the ADIRU1 to NAV (Ref. TASK 34-10-00-860-
002).

Subtask 34-48-00-865-058

B. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU FWS/FWC1/SPLY 3WW F01
121VU EIS/GPWS/115VAC 3WZ P07
121VU EIS/GPWS/28VDC 2WZ P06
121VU EIS/FWC2/SPLY 2WW Q07

4. Procedure
_________

R Subtask 34-48-00-710-057-A

R A. Operational Test of the Enhanced GPWS with Stall Warning Test and
R Activation of the GPWS/SYS Pushbutton Switch and EMER CANC Key

R -------------------------------------------------------------------------------
R ACTION RESULT
R -------------------------------------------------------------------------------

R 1. On the MCDU, on the NAV page:

R - push the line key adjacent to On the MCDU:

R the ADR1 indication. - the ADIRS ADR1 1/2 menu page comes
R into view.

R - push the NEXT PAGE function - the ADIRS ADR1 2/2 menu page comes
R key. into view.

R - push the line key adjacent to - these indications come into view:
R the AOA SENSOR TEST indication. AOA SENSOR COMMANDED TO FIXED
R POSITION CHECK STALL WARNING.

R - push the line key adjacent to On the panel 21VU:

R the TEST START indication. - the FAULT legend of the GPWS/SYS and
R GPWS/TERR pushbutton switches comes
R on after a time between 4 and 60
R seconds.

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
R On the CAPT and F/O glareshield panels
R 130VU and 131VU:
R - the MASTER WARN lights flash.

R In the loudspeakers:
R - you can hear the cricket aural
R warning and the stall voice.

R - push the line key adjacent to On the panel 21VU:

R the RETURN indication. - the FAULT legend of the GPWS/SYS and
R GPWS/TERR pusbutton switches goes
R off.

R On the CAPT and F/O glareshield panels

R 130VU and 131VU:
R - the MASTER WARN lights go off.

R In the loudspeakers:
R - the aural warnings stop.

R 2. On the center pedestal, on the

R ECAM control panel:

R - push and hold the EMER CANC On the panel 21VU:

R key. - the FAULT legend of the GPWS/SYS
R pushbutton switch comes on after
R approximately 35 seconds.

R 3. On the panel 21VU: - the FAULT legend goes off.

R - push the GPWS/SYS pushbutton - the OFF legend comes on.
R switch

R - release the GPWS/SYS pushbutton - the FAULT legend comes on.

R switch. - the OFF legend goes off.

R 4. On the center pedestal, on the

R ECAM control panel:

R - release the EMER CANC key. On the overhead panel 21VU:

R - the FAULT legend of the GPWS/SYS
R pushbutton switch goes off.

R 5. On the overhead circuit breaker

R panel 49VU:

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
R - open the circuit breaker 3WW.

R On the rear circuit breaker panel

R 121VU:
R - open the circuit breaker 2WW.

R 6. Close the circuit breakers 2WW

R and 3WW.

5. Close-up
________

Subtask 34-48-00-860-062

A. Put the aircraft back to its initial configuration.

(1) On the center pedestal, on the MCDU, push the line key adjacent to
the RETURN indication until the MCDU MENU page comes into view.

(2) On the overhead panel, on the ADIRS CDU, set the OFF/NAV/ATT selector
switch related to the ADIRU1 to OFF.

(3) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

(4) Make sure that the work area is clean and clear of tool(s) and other
items.

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 TASK 34-48-00-740-002

BITE Test of the Enhanced GPWC

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
31-32-00-860-010 Procedure to Get Access to the SYSTEM REPORT/TEST NAV
Page
34-10-00-860-002 ADIRS Start Procedure
34-10-00-860-005 ADIRS Stop Procedure

3. __________
Job Set-up

Subtask 34-48-00-860-063

A. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits

(Ref. TASK 24-41-00-861-002).

(2) On the overhead control and indicating panel 21VU, on the GPWS
section, make sure that the five GPWS pushbutton switches are
released (legends off).

(3) On the center pedestal, on one MCDU, get the SYSTEM REPORT/TEST/NAV
page then push the NEXT PAGE function key until the GPWC indication
comes into view.
(Ref. TASK 31-32-00-860-010).

(4) On the overhead panel, on the ADIRS CDU, set the OFF/NAV/ATT selector
switch related to the ADIRU1 to NAV (Ref. TASK 34-10-00-860-002).

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 Subtask 34-48-00-865-059

B. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
121VU EIS/GPWS/115VAC 3WZ P07
121VU EIS/GPWS/28VDC 2WZ P06

4. Procedure
_________

R **ON A/C 001-004,

Subtask 34-48-00-740-051

A. BITE Test of the Enhanced GPWC

NOTE : The actions and the results of this procedure occur on the MCDU
____
used.

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

On the MCDU, on the NAV page: On the MCDU:

- push the line key adjacent to the - the GPWC page comes into view.
GPWC indication.

- push the line key adjacent to the On the GPWC TEST page:
TEST indication. - the TEST IN PROGRESS indication comes
into view
- at the end of the test, the TEST OK
indication comes into view.

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R **ON A/C ALL

R Post SB 34-1193 For A/C 001-004,

R Subtask 34-48-00-740-051-A

R A. BITE Test of the Enhanced GPWC

R NOTE : The actions and the results of this procedure occur on the MCDU
____
R used.

R -------------------------------------------------------------------------------
R ACTION RESULT
R -------------------------------------------------------------------------------

R On the MCDU, on the NAV page: On the MCDU:

R - push the line key adjacent to the - the GPWC page comes into view.
R GPWC indication.

R - push the line key adjacent to the - the subsequent GPWC TEST pages with
R TEST indication. instructions come into view.

R - push the line key adjacent to the - the TEST IN PROGRESS 20S indication
R START TEST indication, comes into VIEW.
R - after 20s obey the instructions that
R are shown on the subsequent pages
R until the TEST OK indication comes
R into view.

R **ON A/C ALL

5. Close-up
________

Subtask 34-48-00-860-064

A. Put the aircraft back to its initial configuration.

(1) On the center pedestal, on the MCDU, push the line key adjacent to
the RETURN indication until the MCDU MENU page comes into view.

(2) On the overhead panel, on the ADIRS CDU, set the OFF/NAV/ATT selector
switch related to the ADIRU1 to OFF (Ref. TASK 34-10-00-860-005).

(3) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

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 (4) Make sure that the work area is clean and clear of tool(s) and other
items.

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 COMPUTER - GROUND PROXIMITY WARNING (GPWC) (1WZ) - REMOVAL/INSTALLATION
_______________________________________________________________________

TASK 34-48-34-000-001

Removal of the GPWC (1WZ)

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific blanking caps

No specific circuit breaker(s) safety clip(s)
No specific access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

34-48-34-991-001 Fig. 401

3. __________
Job Set-up

Subtask 34-48-34-865-050

A. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
121VU EIS/GPWS/115VAC 3WZ P07
121VU EIS/GPWS/28VDC 2WZ P06

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 Subtask 34-48-34-010-050

B. Get Access

(1) Put the access platform in position at the access door 824 in zone
128.

(2) Open the access door 824.

4. Procedure
_________

(Ref. Fig. 401/TASK 34-48-34-991-001)

Subtask 34-48-34-020-050

A. Removal of the GPWC

(1) Loosen the nut (4).

(2) Lower the nut (4).

(3) Pull the GPWC (1) on its rack (3) to disconnect the electrical
connectors (2).

(4) Remove the GPWC (1) from its rack (3).

(5) Put blanking caps on the disconnected electrical connectors (2).

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 GPWC
Figure 401/TASK 34-48-34-991-001

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 TASK 34-48-34-400-001

Installation of the GPWC (1WZ)

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

34-48-00-610-001 Uploading of the Enhanced GPWC Data Base

34-48-00-710-001 Operational Test of Enhanced GPWS Ground Self-test
Function
R 52-41-00-410-002 Close the Avionics Compartment Doors after Access
34-48-34-991-001 Fig. 401

3. __________
Job Set-up

Subtask 34-48-34-860-050

A. Aircraft Maintenance Configuration

(1) Make sure that the access platform is in position at the access door
824 in zone 128.

(2) Make sure that the access door 824 is open.

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 Subtask 34-48-34-865-051

B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and
tagged

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
121VU EIS/GPWS/115VAC 3WZ P07
121VU EIS/GPWS/28VDC 2WZ P06

4. Procedure
_________

(Ref. Fig. 401/TASK 34-48-34-991-001)

Subtask 34-48-34-420-050

A. Installation of the GPWC

(1) Clean the component interface and/or the adjacent area.

(2) Do an inspection of the component interface and/or the adjacent area.

(3) Remove the blanking caps from the electrical connectors (2).

(4) Make sure that the electrical connectors (2) are clean and in the
correct condition.

(5) Install the GPWC (1) on its rack (3).

(6) Push the GPWC (1) on its rack (3) to connect the electrical
connectors (2).

(7) Engage the nut (4) on the lug (5) and tighten.

Subtask 34-48-34-865-052

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
3WZ, 2WZ

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 Subtask 34-48-34-710-050-A

C. Do the operational test of the Enhanced GPWS (Ref. TASK 34-48-00-710-

001).

NOTE : Make sure that the version of the terrain data base which is
____
loaded in the Enhanced GPWC is the correct one.

Subtask 34-48-34-610-050

D. If the Enhanced GPWS has not the last updated database (loaded in shop or
at th e vendor), do the loading of the Enhanced GPWC Data Base (Ref. TASK
34-48-00-610-001).

5. Close-up
________

Subtask 34-48-34-860-051

A. Make sure that the work area is clean and clear of tool(s) and other
items.

Subtask 34-48-34-410-050

B. Close Access

R (1) Close the access door 824 (Ref. TASK 52-41-00-410-002).

(2) Remove the access platform(s).

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 DME - DESCRIPTION AND OPERATION
_______________________________

1. _______
General
The Distance Measuring Equipment (DME) is a radio aid to medium range
navigation which provides the crew with :
- a digital readout of the slant range distance of the aircraft from a
selected ground station
- audio signals which identify the selected ground station.
The DME uses the frequency band from 962 MHz to 1213 MHz for reception and
transmission.

2. Component
__________________
Location
(Ref. Fig. 001)

-------------------------------------------------------------------------------
FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA
| | | | DOOR | REF.
-------------------------------------------------------------------------------
2SD1 INTRG-DME, 1 81VU 127 824 34-51-33
2SD2 INTRG-DME, 2 82VU 128 824 34-51-33
3SD1 ANTENNA-DME, 1 121 NONE 34-51-11
3SD2 ANTENNA-DME, 2 NONE 127 NONE 34-51-11

3. __________________
System Description

A. Principle
- The principle of the DME navigation is based on the measurement of the
transmission time. Paired interrogation pulses go from an onboard
interrogator to a selected ground station. After 50 microseconds, the
station transmits the reply pulses to the aircraft.
- The measurement of time between transmitting the interrogation pulses
and receiving the reply pulses is a function of the slant range
distance of the aircraft to the ground station.
The measurement value is converted into nautical miles and shown to the
crew.
- The interrogation frequencies vary from 1041 to 1150 MHz. The reply
frequencies vary from 962 to 1213 MHz.
- Furthermore, the ground station provides a Morse identification.

B. System Architecture
(Ref. Fig. 002)
The DME comprises two independent systems. Each system consists of :
- one DME interrogator 2SD1 (2SD2)
- one DME antenna 3SD1 (3SD2)
- one dual VOR/DME Radio Magnetic Indicator (VOR/DME RMI) 11FN.
The components given after can control the DME system:
(Ref. Fig. 003)

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 DME - Component Location
Figure 001

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 DME - Block Diagram
Figure 002

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 INTENTIONALLY BLANK

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 DME - Control and Indicating
Figure 003

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 - the CAPT (F/O) Audio Control Panel (ACP) 2RN1 (2RN2) and the Audio
Management Unit (AMU) 1RN for audio controls
- the Multipurpose Control and Display Unit 1(2) (MCDU) 3CA1 (3CA2), the
Radio Management Panel 1(2) (RMP) 1RG1 (1RG2), and the Flight
Management and Guidance Computer 1(2) (FMGC) 1CA1 (1CA2) for
frequency/course selection
- The MCDU and the Centralized Fault-Display Interface-Unit (CFDIU) 1TW
for test causes.
The DME data are shown on :
- the CAPT and F/O Primary Flight Displays (PFD)
- the CAPT and F/O Navigation Displays (ND)
- the VOR/DME RMI
- the MCDU(s) (maintenance data).

C. Utilization Technical Data

(1) Data display

(Ref. Fig. 004)

(a) On the PFDs

With ILS/DME collocated stations, the ILS/DME distance is shown
in magenta in the L lower corner of the PFD (Item 1). These data
come into view when you push the ILS pushbutton switch located on
the EFIS control section of the Flight Control Unit (FCU).

(b) On the NDs

The VOR/DME distance is shown in green in the L lower corner of
the ND for DME system 1 (Item 2), and in the R lower corner of
the ND for DME system 2 (Item 3) when :
- you set the mode selector switch on the EFIS control section of
the FCU to ROSE (ILS, VOR, NAV) or ARC
- you set the ADF/VOR/OFF switch to VOR.
In addition, when you push the VOR-D pushbutton switch on the
EFIS control section of the FCU, this causes :
Display of the VOR/DME and DME ground stations which are not
already included in the flight plan, with the mode selector
switch in ROSE NAV and ARC positions :
- a circle for the DME station
- circle plus cross symbol for the VOR/DME station.

(c) On the VOR/DME RMI

Two windows are available for indication of both distances from
the DME 1 and DME 2 (Item 4) when the VOR/DME stations are
collocated.
When the DME or RMI monitoring circuits detect a fault, the
corresponding display window (Item 5) is blanked.

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 DME - Data and Fault Displays
Figure 004

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 In case of No Computed Data (NCD) (out-of-range station) the
windows show white horizontal dashed lines (Item 6).
In addition, the LEDs on the face of the DME interrogator
indicate the status of the DME system.

(2) Audio control

The DME interrogator applies its audio output to the audio
integrating system. This system controls and directs the output to
the headsets and/or the loud speakers. The pilot can control the DME
audio signals by pressing the VOR pushbutton switch on the ACP and
adjusting the related potentiometer to the correct audio level.
In case of collocated ILS/DME ground stations and when the ILS
pushbutton switch is pressed on the EFIS control section of the FCU,
the pilot can control the DME audio signal through the ILS pushbutton
switch on the ACP.

4. Power
____________
Supply
(Ref. Fig. 002)
Energization of each system is through 115VAC 400 Hz buses :
- 115VAC SHED ESS BUS 801XP via circuit breaker 1SD1 for system 1
- 115VAC BUS2 BUS 204XP via circuit breaker 1SD2 for system 2.
The 115VAC ESS BUS 401XP energizes the VOR/DME RMI via circuit breaker 12FN.

5. _____________________
Component Description

A. DME Interrogator

(1) Description
(Ref. Fig. 005)
The face of the interrogator is fitted with a handle, two lugs, a
TEST pushbutton switch and two LEDs.
The name, color and function of the two LEDs are as follows:
- CONTROL FAIL (red) indicates invalid frequency input tuning words
- LRU STATUS (green) indicates that no faults are detected during the
test sequence
- LRU STATUS (red) indicates that a fault is detected during the test
sequence.
The back is equipped with two ARINC 600 size one connectors which
include three plugs:
- Top Plug (TP): connection with the automatic test circuit
- Middle Plug (MP): connection with the antenna and peripheral
circuits
- Bottom Plug (BP): connection with the power supply circuit and
suppressor.

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 DME - Interrogator
Figure 005

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 (2) Operation
(Ref. Fig. 006)

(a) Interrogation
When the frequency for a DME ground station is selected on the
RMP or by the FMGC, a serial digital tuning word is transmitted
along an ARINC 429 data bus to the range processor in the
interrogator. The range processor uses the frequency data to
provide a tuning word for the synthesizer. In the synthesizer the
Voltage Controlled Oscillator (VCO), which operates in the L-band
range of 1025 to 1150 MHz, generates the transmitter signal which
after amplification is applied to the driver.
The transmitter part of the interrogator consists of a VCO with a
quartz-stabilized, phase-locked-loop frequency synthesizer and a
power amplifier. The synthesizer is controlled by the 8OC/86 CPU.
The power amplifier is energized only during the pulse
transmission and the transmitted energy goes to the antenna
through a circulator. The receiver part consists of a
preselecting filter, an RF amplifier, a mixer and an IF amplifier
centered on 63 MHz. The IF amplifier output pulses are then
detected.

(b) Reply signal processing

Reply pulses from a DME ground station are received by the
antenna and applied through the circulator to the receiver.
In the receiver the reply pulses are filtered, amplified and
mixed with the local oscillation from the driver to produce a 63
MHz IF signal. After further amplification and filtering, a
second mixer combines the 63 MHz signal with a local 52.3 MHz
oscillation to produce a 10.7 MHz IF signal which is applied to
the video processor through a video detector.
In the video processor the signal is applied to a threshold
detector and a pulse pair decoder. The threshold detector
determines the range measurement timing. The video processor
verifies that a valid pulse is received and applies the valid
video pulse to the range processor module. An audio
identification algorithm executed by the processor board decodes
and synthesizes a 1350 Hz audio signal which reproduces the
source identification signal transmitted by the DME ground
station and provides an output to the audio integrating system in
the aircraft.

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 DME Interrogator - Simplifed Block Diagram
Figure 006

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 (c) Distance measurement
A range counter in the range processor module, which generates
the driver and power amplifier trigger pulses, measures the time
interval between the first interrogation pulse and the reception
of the first valid video pulse. The time delay of the reply pulse
is converted to a distance value and stored in memory. During an
interrogation cycle, additional reply pulse delay measurements
are made and processed to produce an accurate range distance.
The range distance data is transmitted through ARINC 429 data
ports to the DMC, the RMI and the FMGC.

(d) Suppression
A suppression coaxial connects all these units: the DME
interrogators and ATC/ TCAS system. This prevents transmission
from one system while the other is in reception mode. This is
necessary because all these systems operate on the same frequency
range.

(e) Modes
The DME system has three basic modes : standby, directed and free
scan.
- Standby mode: in this mode no distance data is computed, the
NCD indication appears in the RMI, and the NCD signal is also
transmitted to the FMGC. The DME reverts to the standby mode
when it is not communicating with a ground station.
- Directed mode: in this mode up to five foreground stations are
designated by the FMGC to the DME interrogator.
- Free scanning mode: in this mode any or all of five stations
can be designated by the FMGC. If less than five stations are
designated, the DME fills the empty slots with the closest
stations.
The DME scans the background loop, consisting of the other 247
stations, searching for station pulses.

(3) Manual self-test and automatic monitoring

(a) Purpose
The fault monitor of the DME interrogator periodically checks the
circuits and operation of the interrogator while the unit is
installed in the aircraft. The fault monitor uses Built-In Test
Equipment (BITE) to gather operating parameters relating to the
fault and stores historical fault data relating to the failure in
the maintenance fault memory. If a failure is detected, the crew
and/or the FMCS is alerted that the unit does not operate
correctly. The stored fault data can be used by the shop
technician as an aid in trouble shooting the faulty LRU.

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 (b) Operation
The fault monitor self-test periodically interrupts normal DME
operation and uses BITE to monitor a number of parameters
selected to determine the status of functionally replaceable
modules. Under normal conditions, the self-test is performed
every 60 s. If a failure is detected, the self-test is performed
every 5 s.
Safety related failures detected while the aircraft is in the air
cause DME service to be denied to the crew and/or the FMCS. A
detected failure causes the DME to output ARINC data words
containing failure and No Computed Data indications. Safety
related failures include wrong distance, wrong channel, etc. If
the failure is not safety related (low RF power, poor receiver
sensitivity, etc.), the DME continues to attempt to operate
normally until the aircraft is on the ground.
If any failure is detected while the aircraft is on the ground,
DME service is denied to the crew and/or the FMCS. The DME
outputs ARINC data words containing failure and No Computed Data
indications.
Data relating to any failure detected when the aircraft is in the
air is stored in Non-Volatile Memory on processor card A7. The
Non-Volatile Memory can be accessed by the shop technician as an
aid to fault isolation.
The DME self-test procedure can be manually initiated by either
the ARINC 429 input control word or the DME functional test rear
connector discrete. When the self-test procedure is initiated in
one of these ways, the ARINC output data words indicate a failure
for 2 seconds, No Computed Data for 2 seconds, and then a
continuous self-test indication. The DME stays in self-test until
released.
While the self-test procedure is being performed, the DME
continues to calculate distance, except when the fault monitor
test is initiated.

B. DME Antenna
(Ref. Fig. 007)
The L-band antenna is an airborne antenna for the DME interrogator. It is
a blade type with a radiating cavity driven by capacitive coupling.
This antenna is designed for installation on fast aircraft and operation
within the L-band from 960 to 1250 MHz.

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 DME - Antenna
Figure 007

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 6. _________
Operation
(Ref. Fig. 002)

A. Control
- Each DME interrogator is connected to one RMP. The DME interrogator 1
is connected to the RMP 1 (DME interrogator 2 to RMP 2). The RMP 1 also
receives the management bus from the FMGC 1 (RMP 2 from FMGC 2).
- In normal operation the FMGC 1(2) tunes the DME interrogator 1(2)
either automatically or manually by means of the MCDU 1(2).
In this case the RMP 1(2) operates as a relay which sends the frequency
information from the FMGC 1(2) to the DME interrogator 1(2).
- By a second port, the DME interrogator 1(2) receives a second
management bus directly from the FMGC 2(1). The interrogator selects
one of the two port functions by a discrete signal coming from the FMGC
1(2) through the RMP 1(2).
- In case of one FMGC fault, the other FMGC can control the two DME
interrogators, one directly, the other through its RMP.
- In case of the RMP 1(2)fault, the concerned RMP is transparent to data
and discrete coming from the FMGC.
- In manual operation (at any time or with failure of the two FMGCs), the
RMP 1 can control the DME interrogator 1 after ON NAV mode selection.
Same possibility for the RMP 2 (DME interrogator 2).
(Ref. Fig. 008)
- In addition, a suppressor coaxial connects the ATC transponders to the
DME interrogators. This prevents transmission from one system while the
other is in reception mode.
This is necessary because the DME and the ATC systems operate on the
same frequency range.

B. Reconfiguration Switching
In normal utilization, the DME 1 and 2 data are shown on both CAPT and
F/O NDs through the Display Management Computer (DMC 1(2)). ILS/DME data
are shown on both CAPT and F/O PFDs.
In caes of DMC 1(2) fault, it is possible to switch over to the DMC 3
with the EIS DMC selector switch.
This selector switch is located on panel 8VU on the center pedestal.
In this case, the DMC 3 totally replaces the DMC 1(2) through the stage
of the output switching relay of the failed DMC.
In case of PFD fault, there is an automatic transfer of the PFD image
onto the ND.
In case of ND fault: you obtain the transfer of the ND image onto the PFD
when you push the PFD/ND XFR pushbutton switch on panel 301VU (501VU).
When you set the PFD potentiometer to OFF on panel 301VU (501VU), this
causes :
- deactivation of the PFD
- transfer of the PFD image onto the ND.

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 DME - Frequency Selection in Emergency Mode
Figure 008

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 7. BITE
_____________
Function
(Ref. Fig. 009)

A. Access to DME Sub-menu Functions

It is possible to select the maintenance functions of the DME
interrogator 1(2) by pressing the line key adjacent to the SYSTEM
REPORT/TEST indication on the CFDS menu, and then selecting the relevant
DME on the NAV menu.
After these actions the DME 1(2) provides its own menu page and the
sub-menu functions can then be chosen by the operator.

B. Activation of the Test Function

The DME 1(2) test function can be activated in ground conditions only by
pressing the line key adjacent to the TEST indication on the DME 1(2)
maintenance sub-menu or by pressing the pushbutton switch on the face of
the interrogator.

C. CFDIU Interface

(1) BITE description

The BITE facilitates maintenance on in-service aircraft. It detects
and identifies a failure related to the DME system. The BITE of the
DME interrogator is connected to the CFDIU (Ref. 31-32-00).
The BITE:
- transmits permanently DME system status and its identification
message to the CFDIU
- memorizes the failures which occurred during the last 63 flight
segments
- monitors data inputs from the various peripherals (FMGC, RMP and
CFDIU)
- transmits to the CFDIU the result of the tests performed and
self-tests
- can communicate with the CFDIU through the menus.
The BITE can operate in two modes:
- the normal mode
- the menu mode

(a) Normal mode

During the normal mode the BITE monitors cyclically the status of
the DME system. It transmits its information to the CFDIU during
the concerned flight.
In case of fault detection the BITE stores the information in the
fault memories.
These items of information are transmitted to the CFDIU every 167
ms by an ARINC 429 message with label 356.

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 DME - Maintenance Test Procedure
Figure 009

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 (b) Menu mode
The menu mode can only be activated on the ground.
This mode enables communication between the CFDIU and the DME
interrogator BITE by means of the MCDU.
The DME menu mode is composed of:
- LAST LEG REPORT
- PREVIOUS LEGS REPORT
- LRU IDENTIFICATION
- GND SCANNING
- TROUBLE SHOOTING DATA
- CLASS 3 FAULTS
- GROUND REPORT
- TEST.

(2) Interactive function

The interactive mode can be activated on the ground only, using the
line key adjacent to the DME 1 (or 2) indication on the SYSTEM
REPORT/TEST page of any MCDU (Ref. 22-82-00).
This mode enables communication between the CFDIU and the BITE of the
DME interrogator by means of the MCDU.
(Ref. Fig. 009)
The interactive mode is composed of:
- LAST LEG REPORT
(Ref. Fig. 010)
This menu contains the fault messages (class 1 and 2, internal and
external) detected during the last flight.
- PREVIOUS LEGS REPORT
(Ref. Fig. 010)
This report contains the fault messages related to the external or
internal failures (class 1 and 2) recorded during the previous 63
flight legs.
- LRU IDENTIFICATION
(Ref. Fig. 010)
Allows to display the P/N and the S/N of the equipment.
- GND SCANNING
(Ref. Fig. 011)
Based on the monitoring and fault analysis during flight, provides
information of the failures detected while using this function.
- TROUBLE SHOOTING DATA
(Ref. Fig. 011)
Provides correlation parameters and snapshot data concerning the
failure displayed in the LAST LEG REPORT and PREVIOUS LEGS REPORT.
- CLASS 3 FAULTS
(Ref. Fig. 012)
Allows to display the class 3 faults recorded during the last
flight leg.
- GROUND REPORT

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 DME - Maintenance Test Procedure - DME Menu (sheet 1/5)
Figure 010

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R DME - Maintenance Test Procedure - DME Menu (sheet 2/5)
Figure 011

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R DME - Maintenance Test Procedure - DME Menu (sheet 3/5)
Figure 012

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 (Ref. Fig. 012)
Allows to present the class 1, 2 or 3 internal failures detected on
ground.
- TEST.
(Ref. Fig. 013, 014)
allows a check of the correct operation of the DME interrogator.

(3) List of components

All the components are listed in the Para. 2. Component Location.

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 DME - Maintenance Test Procedure - DME Menu (sheet 4/5)
Figure 013

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R DME - Maintenance Test Procedure - DME Menu (sheet 5/5)
Figure 014

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 (4) Reporting function
The tables below give the list of internal/external failures:

-------------------------------------------------------------------------------
| REPORTED INTERNAL FAILURES |
|-----------------------------------------------------------------------------|
| MESSAGE (i = 1 or 2) | CLASS | ATA |
|----------------------------------------------------------|-------|----------|
| DME i (2SDi) | 1 | 34-51-33 |
| DME i ANTENNA (3SDi) | 1 | 34-51-11 |
-------------------------------------------------------------------------------

-------------------------------------------------------------------------------
| REPORTED EXTERNAL FAILURES |
|-----------------------------------------------------------------------------|
| MESSAGE (i = 1 or 2) | CLASS | ATA |
|----------------------------------------------------------|-------|----------|
| FMGCi(1CA1)/RMPi(1RGi)/DMEi(2SDi) | 3 | 22-83-34 |
| CFDIU(1TW)/DMEi(2SDi) | 3 | 31-32-34 |
| POWER SUPPLY INTERRUPT | 1 | 24-00-00 |
| DMC1/2(1WT1/2)/DDRMI(1FN)/DME1(2SD1) | 1 | 31-62-34 |
| DMC2/1(1WT2/1)/DDRMI(1FN)/DME2(2SD2) | 1 | 31-62-34 |
| LGCIU(5GAi)/DMEi(2SDi) | 3 | 32-31-71 |
-------------------------------------------------------------------------------

D. BITE Implementation

(1) Internal test processing

---------------------------------------------------------------------------
| TEST | TESTED INTERNAL COMPONENTS | DURATION | ACTIVATION |
| DESIGNATION | | | CONDITIONS |
|----------------|----------------------------|----------|----------------|
| Power-up | Power supply module | | Power interrupt|
| test | | | > 200ms |
|----------------|----------------------------|----------|----------------|
| MCDU system | - processor board | | Relevant MCDU |
| test | - receiver | | menu line key |
| | - synthesizer | | selection |
| | - power amplifier | | |
| | - driver | | |
| | - AGC circuitry | | |
|----------------|----------------------------|----------|----------------|
| FACE TEST | ditto | | Relevant P/BSW |
| | | | activated on |
| | | | the receiver |
| | | | face |

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 ---------------------------------------------------------------------------
| TEST | TESTED INTERNAL COMPONENTS | DURATION | ACTIVATION |
| DESIGNATION | | | CONDITIONS |
|----------------|----------------------------|----------|----------------|
---------------------------------------------------------------------------

(2) Activation of the test on the indicators

The DME 1(2) test function can be activated only by pressing the
pushbutton switch on the face of the interrogator.
The following sequence is then generated on the output of the
equipment:

---------------------------------------------------------------------------
| DURATION | MESSAGE | RMI DISPLAY |
|---------------------|-------------------------|-------------------------|
| 2 s approx. | FAILURE | Blanked window |
| 2 s approx. | NCD | Dashed lines |
| Duration of test | TEST | 0.0 |
---------------------------------------------------------------------------

During the first 2 s, the green LRU STATUS and the red CONTROL FAIL
LEDs on the face of the interrogator are on.
During the next 2 s, the red LRU STATUS and the red CONTROL FAIL LEDs
are on.
During the next 2 s, all LEDs go off.
The green LRU STATUS remains on for 30 s or until the pushbutton
switch on the face of the interrogator is pressed and the sequence
starts again.

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 DME - ADJUSTMENT/TEST
_____________________

TASK 34-51-00-740-002

BITE Test of the DME

WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE
_______
YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
31-32-00-860-010 Procedure to Get Access to the SYSTEM REPORT/TEST NAV
Page
34-10-00-860-002 ADIRS Start Procedure
34-10-00-860-004 IR Alignment Procedure
34-10-00-860-005 ADIRS Stop Procedure
34-51-00-991-001 Fig. 501

3. __________
Job Set-up

Subtask 34-51-00-860-054

A. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits(Ref. TASK 24-41-00-861-

002).

(2) On the EFIS control sections of the FCU:

- set the mode selector switches to ROSE or ARC
- set the ADF/VOR selector switches to VOR
- push the ILS pushbutton switches.

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 (3) On the center pedestal, on the RMP1 and RMP2:
- set the ON/OFF switches to ON
- set a non local frequency of a VOR/DME1 and VOR/DME2.
(Ref. Fig. 501/TASK 34-51-00-991-001)

(4) On the center pedestal, on one MCDU, get the SYSTEM REPORT/TEST/NAV
page
(Ref. TASK 31-32-00-860-010).

(5) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002).

(6) Do the IR alignment procedure

(Ref. TASK 34-10-00-860-004).

Subtask 34-51-00-865-056

B. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV/VOR/DME/RMI 12FN F13
49VU NAV/DME/1 1SD1 G14
121VU COM NAV/DME/2 1SD2 K06

4. Procedure
_________

Subtask 34-51-00-740-051

A. BITE Test of the DME

NOTE : The DME and the VOR/DME data come into view on the ND. The ILS/DME
____
data come into view on the PFD.

NOTE : During the BITE TEST (DME1 or 2) by the MCDU, the indications
____
related to the two receivers (CAPT and F/O) are shown at the same
time. This has no effect on the test or component operation.

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 VOR/DME - Frequency Selection
Figure 501/TASK 34-51-00-991-001

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the MCDU: On the MCDU:

- push the line key adjacent to - the DME1 (DME2) page comes into view.
the DME1 (DME2) indication.

- push the line key adjacent to - the INITIAL CONDITIONS are shown
the TEST indication. (page 1 to 2).

- push the line key adjacent to - the TEST IN PROGRESS 10s indication
the START TEST indication. comes into view.

From 0 to 4s:
- on the CAPT and F/O NDs and PFDs:
. the DME1(DME2) red warning flag
comes into view at the bottom and on
the left (right) side then it goes
out of view.
- on the VOR/DME RMI:
. the left (right) window is blanked.

From 4 to 7s:
- on the CAPT and F/O NDs:
. two green dashes come into view at
the bottom and on the left (right)
side of the heading dial instead of
the distance value.
- on the VOR/DME RMI:
. the left (right) window shows white
horizontal dashes.

From 7 to 10s:
- on the CAPT and F/O NDs and on the
VOR/DME RMI:
. the distance of 0.0 comes into
view.

- push the line key adjacent to On the MCDU:

the YES indication. - the TEST OK indication comes into
view.

- push the line key adjacent to The test procedure stops.

the RETURN indication.

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 5. Close-up
________

Subtask 34-51-00-860-055

A. Put the aircraft back to its initial configuration.

(1) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005).

(2) On the center pedestal, on the MCDU, push the line key adjacent to
the RETURN indication until the MCDU MENU page comes into view.

(3) On the RMP, set the ON/OFF switch to OFF.

(4) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

(5) Make sure that the work area is clean and clear of tool(s) and other
items.

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 TASK 34-51-00-710-001

Operational Test of the DME

WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE
_______
YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.

1. __________________
Reason for the Job

Reception Test of the DME beacon.

2. ______________________
Job Set-up Information

A. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
34-10-00-860-002 ADIRS Start Procedure
34-10-00-860-004 IR Alignment Procedure
34-10-00-860-005 ADIRS Stop Procedure
34-51-00-991-001 Fig. 501

3. __________
Job Set-up

Subtask 34-51-00-860-050

A. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits. (Ref. TASK 24-41-00-861-

002)

(2) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002).

(3) Do the IR alignment procedure

(Ref. TASK 34-10-00-860-004).

(4) On the EFIS control sections of the FCU:

- set the mode selector switches to ROSE or ARC
- set the ADF/VOR selector switches to VOR.

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 (5) On the center pedestal, on the RMP1 and RMP2, set the ON/OFF switches
to ON.

Subtask 34-51-00-865-051

B. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV/DME/1 1SD1 G14
121VU COM NAV/DME/2 1SD2 K06

4. Procedure
_________

Subtask 34-51-00-710-055

A. Operational Test of the DME

NOTE : The DME and the VOR/DME data come into view on the ND. The ILS/DME
____
data come into view on the PFD.

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the RMP1 (RMP2):

- set the local frequency of a On the CAPT or F/O ND, the range
VOR/DME1 (DME2) station between the aircraft and the station
(Ref. Fig. 501/TASK 34-51-00-
991-001)
comes into view at the bottom. On the
RMI, the range between the aircraft and
the station is also in view.

2. On the center pedestal, on the

ACP:

- push the VOR1 (VOR2) or ILS In the loudspeakers, you can hear the
pushbutton switch. Morse code signal from the station set.

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 5. Close-up
________

Subtask 34-51-00-860-051

A. Put the aircraft back to its initial configuration.

(1) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005).

(2) On the RMP, set the ON/OFF switch to OFF.

(3) On the ACP, release the VOR1 (VOR2) or ILS pushbutton switch.

(4) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

(5) Make sure that the work area is clean and clear of tool(s) and other
items.

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 TASK 34-51-00-720-001

Functional Test of the DME

WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE
_______
YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.

1. __________________
Reason for the Job

Make sure that the system operates correctly.

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific DME ground test unit

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
34-10-00-860-002 ADIRS Start Procedure
34-10-00-860-004 IR Alignment Procedure
34-10-00-860-005 ADIRS Stop Procedure
34-51-00-991-001 Fig. 501

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 3. __________
Job Set-up

Subtask 34-51-00-860-052

A. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-

002).

(2) Install the DME ground test unit near the DME1 (DME2) antenna. To do
this, obey the operating instructions. Set the VOR/DME ground test
unit to ON.

(3) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002).

(4) Do the IR alignment procedure

(Ref. TASK 34-10-00-860-004).

(5) On the EFIS control sections of the FCU, set the mode selector
switches to ROSE or ARC.

(6) On the FCU, set the ADF/VOR selector switches to VOR.

(7) On the center pedestal, on the RMP1 and RMP2, set the ON/OFF selector
switches to ON.

Subtask 34-51-00-865-054

B. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV/VOR/DME/RMI 12FN F13

Subtask 34-51-00-865-055

C. Make sure that this(these) circuit breaker(s) is(are) open, safetied and
tagged

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV/DME/1 1SD1 G14
121VU COM NAV/DME/2 1SD2 K06

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 4. Procedure
_________

Subtask 34-51-00-720-050

A. DME Reception and Identification Test

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the RMP1 (RMP2):

R - set the VOR/DME1 (VOR/DME2)
R test frequency of the ground
R test unit.
(Ref. Fig. 501/TASK 34-51-00-
991-001)

2. On the panel 49VU (121VU) :

- close the circuit breaker 1SD1 On the CAPT and F/O NDs, on the left
(1SD2). (right) side:
- the DME1 (DME2) flag goes out of view
R - the horizontal dashs come into view.

On the VOR/DME RMI, in the left (right)

window:
R - the horizontal dashs come into view.

R 3. On the ground test unit, set the

R IDENT signal on

R 4. On the center pedestal, on one

R ACP:

- push the VOR1 (VOR2) pushbutton You can hear the identification signal
switch in the loudspeaker.

- adjust the volume to the volume Do the adjustment slowly and

you need. continuously .There is no unwanted
noise.

- push the ON VOICE pushbutton The audio signal in the loudspeaker

switch. stops.

R 5. On the ground test unit:

R - set the IDENT signal off.

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
- set a DME1 (DME2) range of 5 On the left (right) side of the CAPT
NM. and F/O NDs:
R - the range 5.0 comes into view.

On the VOR/DME RMI, in the left (right)

window:
R - the range 5.0 comes into view.

- set a range of 270 NM. On the ND and the VOR/DME RMI :

R - the range 270.0 comes into view.

R 6. On the ground test unit, set the

R IDENT signal on

R 7. On the center pedestal, on the

ACP:

- release the ON VOICE pushbutton You can hear the audio signal in the
switch. loudspeaker.

R 8. On the center pedestal, on the

ATC control unit:

- set the AUTO/ON/STBY switch to On the CAPT and F/O NDs and the VOR/DME
ON. RMI:
- the DME1 (DME2) indication does not
change.

In the loudspeaker :
- the audio signal does not change.

- set the AUTO/ON/STBY switch to

STBY.

R 9. On the ground test unit, set the

R IDENT signal off.

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 5. Close-up
________

Subtask 34-51-00-860-053

A. Put the aircraft back to its initial configuration.

(1) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005).

(2) On the center pedestal, on the RMP, set the ON/OFF switch to OFF.

(3) De-energize the DME ground test unit.

(4) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

(5) Make sure that the work area is clean and clear of tool(s) and other
items.

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 ANTENNA - DME (3SD1,3SD2) - REMOVAL/INSTALLATION
________________________________________________

TASK 34-51-11-000-002

Removal of the DME Antenna (3SD1, 3SD2)

WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS

_______
ONLY WITH A GOOD SUPPLY OF AIR.
OBEY THE MANUFACTURERS INSTRUCTIONS.
PUT ON PROTECTIVE CLOTHING.
DO NOT GET THEM IN YOUR MOUTH.
DO NOT SMOKE.
DO NOT BREATHE THE GAS.
THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT.
GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED.

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific blanking caps

No specific circuit breaker(s) safety clip(s)
No specific nonmetallic scraper

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

34-51-11-991-002 Fig. 401

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 3. __________
Job Set-up

Subtask 34-51-11-865-052

A. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
FOR 3SD1
49VU NAV/DME/1 1SD1 G14
FOR 3SD2
121VU COM NAV/DME/2 1SD2 K06

4. Procedure
_________

(Ref. Fig. 401/TASK 34-51-11-991-002)

Subtask 34-51-11-020-050

A. Removal of the DME Antenna

(1) Remove the sealant from the heads of the screws (5) with a
nonmetallic scraper.

(2) Remove the screws (5).

(3) Put the antenna (4) away from the fuselage (1).

(4) Disconnect the coaxial connector (2).

(5) Remove the antenna (4).

(6) Put blanking caps on the disconnected coaxial connectors (2) and (3).

(7) Remove and discard the O-ring seal (6).

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 DME Antenna
Figure 401/TASK 34-51-11-991-002

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 TASK 34-51-11-400-002

Installation of the DME Antenna (3SD1, 3SD2)

WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS

_______
ONLY WITH A GOOD SUPPLY OF AIR.
OBEY THE MANUFACTURERS INSTRUCTIONS.
PUT ON PROTECTIVE CLOTHING.
DO NOT GET THEM IN YOUR MOUTH.
DO NOT SMOKE.
DO NOT BREATHE THE GAS.
THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT.
GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED.

WARNING : DO NOT GET THE COMPOUND ON YOUR SKIN.

_______
IF YOU DO:
- RUB IT OFF IMMEDIATELY WITH A CLEAN CLOTH
- WASH THE SKIN WITH SOAP AND RINSE WITH CLEAN WATER.

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific lint-free cloth

No specific masking tape
No specific nonmetallic scraper

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 B. Consumable Materials

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

Material No. 05-013 D TV-53-3507/73

RELEASE AGENT (OBSOLETE USE 05-013A) (Ref. 20-31-00)
Material No. 07-001B
ELECTRICAL BONDING COATING (BLUE COLOR)
(Ref. 20-31-00)
R Material No. 09-016 USA MIL-PRF-81733D TYPE II CLASS B
CORROSION INHIBITING FILLET CONSISTENCY
(Ref. 20-31-00)
Material No. 09-019 USA AMS 3267/3
LOW ADHESION CORROSION INHIBITING SEALANT
(Ref. 20-31-00)
Material No. 11-003 USA TT-M-261
METHYL-ETHYL-KETONE (Ref. 20-31-00)
Material No. 16-003 F ASNB70720
COATING (OBSOLETE USE 16-021) (Ref. 20-31-00)

C. Expendable Parts

-------------------------------------------------------------------------------
FIG.ITEM |DESIGNATION |IPC-CSN
-------------------------------------------------------------------------------

6 O-ring seal 34-51-11 01 -010

D. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

20-28-00-912-005 Electrical Bonding of Antennas With Conductive Bolts.

34-51-00-710-001 Operational Test of the DME
34-51-00-720-001 Functional Test of the DME
51-76-11-300-001 Repair of the Sealing
34-51-11-991-002 Fig. 401

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 3. __________
Job Set-up

Subtask 34-51-11-865-053

A. Make sure that this(these) circuit breaker(s) is(are) open, safetied and
tagged

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
FOR 3SD1
49VU NAV/DME/1 1SD1 G14
FOR 3SD2
121VU COM NAV/DME/2 1SD2 K06

4. Procedure
_________

(Ref. Fig. 401/TASK 34-51-11-991-002)

WARNING : IF YOU GET THE FLUID ON YOUR SKIN OR IN YOUR EYES:

_______
- FLUSH IT AWAY WITH CLEAN WATER
- GET MEDICAL AID.

WARNING : OBEY THE MANUFACTURER<S INSTRUCTIONS WHEN YOU USE THE SPECIAL
_______
MATERIAL.
THIS MATERIAL IS DANGEROUS.

Subtask 34-51-11-420-050

A. Installation of the DME Antenna

(1) Remove the used sealant from the fuselage with CLEANING AGENTS
(Material No. 11-003) and a nonmetallic scraper.

NOTE : If you install the same antenna it is necessary to clean it

____
with a lint-free cloth.

(2) Do an inspection of the component interface and/or the adjacent area.

NOTE : Make sure that the antenna attachment screw-head recesses have
____
no signs of paint, corrosion or sealant because the antenna
electrical bonding is made through the attachment screws.

(3) Apply masking tape to the structure (1), the edge of the antenna (4),
the screw holes and the hole for the antenna connector.

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 (4) Apply SPECIAL MATERIALS (Material No. 05-013) on the antenna (4)
mount and on the fuselage (1).

(5) Apply SEALANTS (Material No. 09-019) on the antenna (4) mount and on
the fuselage (1) (Ref. TASK 51-76-11-300-001).

NOTE : Make sure that there is no sealant in the screw holes.

____

(6) Remove the blanking caps from the coaxial connectors (2) and (3).

(7) Install the new O-ring seal (6).

(8) Connect the coaxial connector (2) to the antenna (4).

(9) Put the antenna (4) in position on the fuselage (1).

(10) Attach the antenna (4) with the screws (5).

(11) Remove the sealant which is not necessary with a nonmetallic scraper.

(12) Make sure that the bonding contact resistance between the antenna (4)
and the fuselage structure (1) is not higher than 5 milliohms
(Ref. TASK 20-28-00-912-005).

(13) Apply a sealing bead with SEALANTS (Material No. 09-016) around the
antenna (4) (Ref. TASK 51-76-11-300-001).

(14) Apply SEALANTS (Material No. 09-016) on the heads of the screws (5).

(15) Make the contour of the screws (5) and the antenna (4) smooth.

(16) Apply STRUCTURE PAINTS (Material No. 16-003) to the sealant around
the base of the antenna (4).

R (17) Apply PAINTS FOR DETAIL (INTERNAL AND EXTERN AL) (Material No. 07-
R 001B) to the sealant on the head of the screws (5).

Subtask 34-51-11-865-054

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
FOR 3SD1
1SD1
FOR 3SD2
1SD2

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 Subtask 34-51-11-720-050

C. Do the functional test of the DME with tool (Ref. TASK 34-51-00-720-001)
or the operational test of the DME without tool (Ref. TASK 34-51-00-710-
001).

5. Close-up
________

Subtask 34-51-11-410-050

A. Make sure that the work area is clean and clear of tool(s) and other
items.

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 INTERROGATOR - DME (2SD1,2SD2) - REMOVAL/INSTALLATION
_____________________________________________________

TASK 34-51-33-000-001

Removal of the DME Interrogator (2SD1,2SD2)

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific blanking caps

No specific circuit breaker(s) safety clip(s)
No specific access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

34-51-33-991-001 Fig. 401

3. __________
Job Set-up

Subtask 34-51-33-865-050

A. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
FOR 2SD1
49VU NAV/DME/1 1SD1 G14
FOR 2SD2
121VU COM NAV/DME/2 1SD2 K06

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 Subtask 34-51-33-010-050

B. Get Access

R (1) Put the access platform in position at the access door 824 in zone
128.

(2) Open the access door 824.

4. Procedure
_________

(Ref. Fig. 401/TASK 34-51-33-991-001)

Subtask 34-51-33-020-050

A. Removal of the DME Interrogator

(1) Loosen the nuts (4).

(2) Lower the nuts (4).

(3) Pull the DME interrogator (1) on its rack (3) to disconnect the
electrical connectors (2).

(4) Remove the DME interrogator (1) from its rack (3).

(5) Put blanking caps on the disconnected electrical connectors (2).

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R DME Interrogator
Figure 401/TASK 34-51-33-991-001

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 TASK 34-51-33-400-001

Installation of the DME Interrogator (2SD1,2SD2)

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

34-51-00-710-001 Operational Test of the DME

R 52-41-00-410-002 Close the Avionics Compartment Doors after Access
34-51-33-991-001 Fig. 401

3. __________
Job Set-up

Subtask 34-51-33-860-050

A. Aircraft Maintenance Configuration

(1) Make sure that the access platform is in position at the access door
824 in zone 128.

(2) Make sure that the access door 824 is open.

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 Subtask 34-51-33-865-051

B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and
tagged

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
FOR 2SD1
49VU NAV/DME/1 1SD1 G14
FOR 2SD2
121VU COM NAV/DME/2 1SD2 K06

4. Procedure
_________

(Ref. Fig. 401/TASK 34-51-33-991-001)

Subtask 34-51-33-420-050

A. Installation of the DME Interrogator

(1) Clean the component interface and/or the adjacent area.

(2) Do an inspection of the component interface and/or the adjacent area.

(3) Remove the blanking caps from the electrical connectors (2).

(4) Make sure that the electrical connectors (2) are clean and in the
correct condition.

(5) Install the DME interrogator (1) on its rack (3).

(6) Push the DME interrogator (1) on its rack (3) to connect the
electrical connectors (2).

(7) Engage the nuts (4) on the lugs (5) and tighten.

Subtask 34-51-33-865-052

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
FOR 2SD1
1SD1
FOR 2SD2
1SD2

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 Subtask 34-51-33-710-050

C. Do the operational test of the DME (Ref. TASK 34-51-00-710-001).

5. Close-up
________

Subtask 34-51-33-860-051

A. Make sure that the work area is clean and clear of tool(s) and other
items.

Subtask 34-51-33-410-050

B. Close Access

R (1) Close the access door 824 (Ref. TASK 52-41-00-410-002).

(2) Remove the access platform(s).

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 ATC/MODE S (SELECT) - DESCRIPTION AND OPERATION
_______________________________________________

1. _______
General
The Air Traffic Control (ATC) system is based on the replies provided by the
airborne transponders in response to interrogations from the ATC secondary
radar.
The ground ATC secondary radar uses technics which provide the air traffic
control with information that cannot be acquired by the primary radar.
This system enables to distinguish between aircraft and to maintain
effective ground surveillance of the air traffic.
The system provides the air traffic controllers with :
- Mode A : transmission of aircraft identification or,
- Mode C : transmission of aircraft barometric altitude or,
- Mode S : aircraft selection and transmission of flight data for the ground
surveillance.
The mode S is fully compatible with the other modes, A and C.
The mode S bas been designed as an evolutionary addition to the ATC system
to provide the enhanced surveillance and communication capability required
for air traffic control automation.

NOTE : The ATC/mode S will be able to provide the Traffic Collision

____
Avoidance System (TCAS) with the aircraft address.

2. Component
__________________
Location
R (Ref. Fig. 001, 002)
R

-------------------------------------------------------------------------------
FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA
| | | | DOOR | REF.
-------------------------------------------------------------------------------
1SH1 XPDR-ATC/MODE S, 1 81VU 127 824 34-52-33
1SH2 XPDR-ATC/MODE S, 2 82VU 128 824 34-52-33
7SH1 ANTENNA-ATC BOTTOM, 1 127 34-52-11
7SH2 ANTENNA-ATC BOTTOM, 2 128 34-52-11
7SH3 ANTENNA-ATC TOP, 1 224 34-52-11
7SH4 ANTENNA-ATC TOP, 2 223 34-52-11
3SH CTL UNIT-ATC/TCAS 11VU 211 831 34-52-12

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 ATC - Component Location
Figure 001

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 ATC - Control and Indicating
Figure 002

R
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 3. __________________
System Description

A. Principle
(Ref. Fig. 003)
An airborne transponder provides coded reply signals in response to
interrogation signals from the ground secondary radar and from aircraft
which will be eventually equipped with the TCAS.
This ground interrogation is transmitted in the form of pair of pulses P1
and P3 for the mode A or C and in the form of pulses P1, P3 and P4 for
the mode S.
The decoding of the time between the interrogation pulses determines the
operating mode of the transponder :
- mode A (identification)
- mode C (altitude range)
- mode S (flight data)
The interrogation frequency is 1030 MHz.
The reply frequency is 1090 MHz.
The system is provided with four antennas :
- two antennas are located at the upper part of the fuselage
- two antennas are located at the lower part of the fuselage.
According to the aircraft configuration, the transponder selects the
antennas (lower or upper) which receive the best transmission signal
from the ground ATC secondary radar.

B. System Architecture
(Ref. Fig. 004)
The ATC comprises two independent systems. Each system consists of:
- one transponder 1SH1 (1SH2),
- two antennas 7SH1,7SH3 (7SH2,7SH4),
- one ATC/TCAS control unit 3SH common to the two systems.
In addition, the Centralized Fault-Display Interface-Unit (CFDIU) 1TW
enables access to the maintenance part of the ATC system through one
Multipurpose Control and Display Unit (MCDU) 3CA1 (3CA2).
R
(Ref. Fig. 002)
R

C. Warning
R
(Ref. Fig. 002)
R
The warning related to the ATC is only the FAULT or FAIL indicator light
of the ATC control unit : when the system is faulty, the amber FAULT or
FAIL indicator light comes on.

R
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 ATC - Principle
Figure 003

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 ATC - Block Diagram
Figure 004

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 4. Power
____________
Supply
Energization of each system is through :
- 115VAC ESS BUS SHEDDABLE 801XP via circuit breaker 5SH1 for system 1.
- 115VAC BUS 2 204XP via circuit breaker 5SH2 for system 2.
Energization of the ATC control unit is through the two circuit breakers
5SH1 and 5SH2.

5. _____________________
Component Description

A. ATC Transponder

(1) External description

(Ref. Fig. 005)
The face of the transponder is fitted with a handle, two attaching
parts, a TEST pushbutton switch and five LEDs.
The name, color and function of the five LEDs are as follows:
- LRU STATUS (green) indicates that no faults are detected during the
BITE self-test
- LRU STATUS (red) indicates that a fault(s) is detected during the
BITE self-test
- ANTENNA TOP FAIL (red) indicates that the upper antennas are
incorrectly connected or are failed (comes on during BITE
self-test)
- ANTENNA BOT FAIL (red) indicates that the lower antennas are
incorrectly connected or are failed (comes on during BITE
self-test)
- ALTITUDE FAIL (red) indicates that the altitude data is not in
correct format or that the internal data receiver circuit is faulty
(comes on during BITE self-test)
- CONTROL FAIL (red) indicates that the control input is not in
correct format or that the internal data receiver circuit is faulty
(comes on during BITE self-test).
The back of the transponder contains an ARINC 600, shell size
connector to provide electrical connections to the aircraft wiring
via mount.
Contact grouping is as follows :
- Top contact set - ATE interface
- Center contact set - System interconnections
- Bottom contact set - Power supply and bonding.

(2) Principle of operation

(Ref. Fig. 004)
Each ground interrogator transmits its interrogations at the
frequency of 1030 MHz in the form of a series of two pulses.
Depending on the pulse intervals and numbers, they define four
different interrogation modes:
- Mode A interrogations

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R ATC - Transponder
Figure 005

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 - Mode C interrogations
- Mode S all call interrogations
- Mode S interrogations.
R After receiving these pulses, the transponder identifies and
R decodes the interrogations. Depending on the detected interrogation
R mode, the transponder transmits the identification of the aircraft
or its barometric altitude. The transponder is provided with the
Mode S Data Link capability. The transmission of the replies to the
R ground takes place on a carrier frequency of 1090 MHz.

(a) Interrogations
(Ref. Fig. 003)
Four classes of interrogations are transmitted by the ground
interrogator, they are:

1
_ Mode A or C interrogations
A mode A or C interrogation consists of two pulses labelled P1
and P3. These pulses are transmitted by the directional
antenna of the Secondary Surveillance Radar (SSR) and spaced
according to the SSR mode of operation. A control pulse P2 is
radiated by the omnidirectional antenna of the SSR two
microseconds after the pulse P1 is transmitted from the
directional antenna of the SSR.
Amplitude of pulses P1 and P3 varies according to the position
of the directional antenna. P1 and P3 are at higher amplitude
than P2 when the aircraft flies in the antenna main beam.
Amplitude of the pulse P2, also called side lobe suppression
pulse, is constant whichever the position of the
omnidirectional antenna.
The aircraft receives the P1 pulse at a higher amplitude than
P2. The aircraft transponder detects this amplitude difference
and determines the interrogation to be a valid interrogation.
When the transponder detects that P2 is within 6 dB of P1, in
amplitude, it determines that the interrogation is not valid.

2
_ Mode S all call interrogation
(Ref. Fig. 006)
A mode S all call interrogation consists of three pulses
labelled P1, P3 and P4. They are transmitted by a directional
antenna. A control pulse P2 (Side Lobe Suppression Pulse) is
transmitted following P1 by an omnidirectional antenna.
The detection of pulse P1, P2 and P3 is the same as for mode A
or C interrogation.

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 ATC - Mode S All Call Pulse Characteristics
Figure 006

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 The transponder initiates a reply until the presence of the
pulse P4 is detected. Upon detection of the pulse P4, the
reply is terminated. If the width of the pulse P4 is 0.8
microseconds (mode A or mode C only all-call), no reply is
transmitted. If the width of the pulse is 1.6 microseconds
(mode S all-call), a mode S reply is generated 128
microseconds after the leading edge of the pulse P4.

3
_ Mode S interrogation
(Ref. Fig. 007)
A mode S interrogation consists of a preamble followed by a
data block.
The preamble consists of two equal transmitted pulses labelled
P1 and P2 and spaced by two microseconds.
The data block consists of a single pulse P6 with a synchro
phase reversal modulation.
Pulse P6 duration : short 15.5 microseconds,
long 29.5 microseconds,
Data block : 56 or 112 bits.
The pulse P5, which is radiated by the omnidirectional antenna
may be overlaid on P6 by the ground interrogator as a Side
Lobe Suppression (SLS) signal in any mode S interrogation. The
pulse P5 is spaced 0.4 microsecond from the synchro phase
reversal.

(b) Encoded reply

1
_ Mode A or C reply
A mode A or C reply consists of two framing pulses F1 and F2,
separated by a 20.3 microseconds time interval. The encoding
of the reply is done by means of the presence (1) or absence
(0) of 13 reply pulses (12 pulses plus X pulse).

2
_ Mode S all call reply
A mode S all call reply consists of a four-bit preamble
followed by a data block.
The data block contains 56 position modulated pulses.

3
_ Mode S reply
A mode S reply occurs after a mode S interrogation or a mode S
all call interrogation (P4 duration 1.6 microseconds).
A mode S reply consists of a four-bit preamble followed by a
data block. The data block contains 56 (short) or 112 (long)
position modulated pulses.

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 ATC - Mode S Pulse Characteristics
Figure 007

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 4
_ Mode S message content
The minimum data link transponder supports all surveillance
functions, in addition to bidirectional air-to-air data
exchange, ground-to-air data uplink (Comm A), air-to-ground
data downlink (Comm B), and multisite message protocol. In
addition, the transponder is capable of receiving Extended
Length Messages (ELMs) from the ground. ELMS are received in
the Comm C format. ELM transmittals to the ground use the Comm
R D format (Note: Comm C and Comm D are future applications;
R Comm D is not available with this transponder). All discrete
R Mode S interrogations and replies (except the all-call reply)
R contain the 24-bit discrete address of the Mode S transponder
upon which 24 error detection parity check bits are overlaid.
In the all-call reply, the 24 parity check bits are overlaid
on the Mode S interrogation address and the transponders<
R discrete address is included in the text of the reply.
The main function of Mode S is surveillance. To accomplish
this function, the Mode S transponder uses the 56-bit
transmissions (in each direction). In the 56-bit
transmissions, the aircraft reports its altitude or ATCRBS
4096 code, and the flight status (airborne, on-ground, alert,
Special Position Identification (SPI), etc.
The discrete addressing and digital encoding of Mode S
transmissions permit their use as a digital data link. The
interrogation and reply formats of the Mode S system contain
sufficient coding space to permit the transmission of data.
These data transmissions may be used for air traffic control
purposes, air-to-air data interchange for collision avoidance,
or to provide flight advisory services such as weather
reports, or Automated Terminal Information System (ATIS).
Most Mode S data link transmissions will be handled as one
56-bit message included as part of a long 112-bit
interrogation or reply.
These transmissions include the message in addition to the
surveillance data.
Longer messages are transmitted using the Extended Length
Message (ELM) capability. The ELM is capable of transmitting
up to sixteen 80-bit message segments, either ground-to-air or
air-to-ground. The ELM can be acknowledged with a single reply
or interrogation. ELMs uplinked need not be replied to
individually, but can be acknowledged in a reply containing a
summary of the received interrogations.
ELMs do not contain surveillance data.
The following table gives the definition of uplink format
message fields:

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 -------------------------------------------------------------------------------
| DESIGNATOR | FIELD | INDICATION |
-------------------------------------------------------------------------------
| AP | address parity | 24-bit address and parity overlaid |
| | | |
| AQ | acquisition | differentiates acquisition from non-acquisi- |
| | | tion interrogations |
| | | |
| DI | designator | identifies the coding contained in the SD |
| | identification | field |
| | | |
| II | interrogator | identifies the interrogator |
| | identification | |
| | | |
| MA | message | 56-bit MA field contains messages directed |
| | Comm A | to the A/C |
| | | |
| MC | message | 80-bit MC field contains one segment of a |
| | Comm C | sequence of segments transmitted in ELM mode. |
| | | |
| MU | message | 56-bit MU messages contain information used |
| | Comm U | in air-to-air exchanges |
| | | |
| NC | number of C | number of segments transmitted in ELM mode |
| | segments | |
| | | |
| PC | protocol | operating commands of the transponder |
| | | |
| PR | probability | contains commands to the transponder to |
| | of reply | specify the reply probability to the mode S |
| | | only all-call interrogations (Allows |
| | | operators to acquire closely spaced A/C). |
| | | |
| RC | reply | designates the transmitted segment as initial,|
| | control | intermediate or final |
| | | |
| RL | reply | indicates if message is short or long |
| | length | |
| | | |
| RR | reply | length and content of the reply information |
| | request | requested by the interrogator |
| | | |
| SD | special | contains control codes affecting the link |
| | designator | protocol |
-------------------------------------------------------------------------------

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 The table below gives the definition of downlink format
message fields:

-------------------------------------------------------------------------------
| DESIGNATOR | FIELD | INDICATION |
-------------------------------------------------------------------------------
| AA | address | contains the A/C mode S address |
| | announced | |
| | | |
| AC | altitude | information containing the A/C altitude |
| | code | |
| | | |
| AP | address | 24-bit address and parity overlaid |
| | parity | |
| | | |
| CA | transponder | reports transponder capability |
| | capability | |
| | | |
| DR | downlink | requests extraction of downlink messages from |
| | request | the transponder by the interrogator |
| | | |
| FS | flight | flight status |
| | status | |
| | | |
| ID | identification | contains the Mode A identification code |
| | | |
| MB | message | 56-bit MB field contains the message |
| | Comm B | transmitted to the interrogator |
| | | |
| MD | message | 80-bit MD field contains one segment of a |
| | Comm D | sequence of segments in the ELM Mode |
-------------------------------------------------------------------------------

(3) Operation
(Ref. Fig. 008)

(a) Introduction
R The transponder is capable of operating with ATC Radar Beacon
R System interrogators, as well as mode S interrogators and is also
R designed to accept two antenna inputs for diversity operation.
R Diversity operation in a Mode S transponder is an added feature
to improve air to air surveillance as part of a collision
R avoidance system.
An additional feature of a Mode S transponder is the ability to
send and receive data link messages via the reply and
interrogation mode S message formats.

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 ATC Transponder - Simplified Block Diagram
Figure 008

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 (b) Simplified theory
The transponder consists of four principal assemblies: the
transmitter, the receiver, the I/O and processor circuit card and
the power supply.
Input signals (1030 MHz interrogations/uplinks) are received at
one or both of the antennas. Each received antenna signal is
pulse demodulated and sent to the processing circuits, where the
diversity selection is made. The diversity selection determines
which receiver provides the stronger (or first) signal. The
selected received signal is then applied through a demodulator
circuit to the processing circuits. The processing circuits
determine if the interrogation is an ATC Radar Beacon System
interrogation, a mode S interrogation addressed to the particular
aircraft, or a mode S interrogation addressed to another
aircraft. Depending upon the type of the interrogation, the
processing circuits determine the proper reply (if one is
required) and send the appropriate reply through a message
processing circuit to the diversity switching circuits. The
diversity switching circuits select the antenna that the reply
will be transmitted through. The reply message is transmitted
through the same antenna from which the selected received signal
originated.
- The I/O circuit is an interface circuit to receive serial ARINC
429 data, the 24 bit address input, the code altitude input and
various discretes. The CPU provides the link between the I/O
and the signal processing circuits.
- The signal processing cicuits consist of a video processor, a
PAM decoder and a message processor. The video processor
analyzes the received signals ( pulses and pulse amplitude). If
the received signal is valid, the PAM decoder determines the
type of interrogation. Then the decoder ouput is sent to the
message processor where appropriate reply format is generated.
- The message processor output is amplified and the resultant
1090 MHz transmit signal is applied to the antennas through a
diplexer/diversity switch.
- The received signals from the antennas are sent to the receiver
stage. The 60 MHz IF output is used to drive the video
processor and the message processor (DSPK function). The input
of the receiver stage is filtered to reduce the susceptibility
to HIRF signals.
- The power supply is a pulse-width modulated switching
regulator. It supplies all the necessary DC voltages required
by the internal circuitry. An integrated monitoring function
gives protection to the power supply circuits and reset signals
to the CPUs each time primary power is applied.

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 (c) Outputs
The discrete output from transponder is :

-------------------------------------------------------------------------------
NAME ELECTRICAL LEVEL TO SIGNAL STATUS
-------------------------------------------------------------------------------
R XPNDR FAIL OC/5VDC CTL UNIT - ATC 5VDC = FAULT
-------------------------------------------------------------------------------

B. Control Unit
(Ref. Fig. 009)
The processor based unit conforms to the ARINC 718 specification. The
face is integrally lit by clear 5V lamps and features:
- a liquid crystal display window, in which the identification code is
displayed
- an ATC FAIL indicator light
- an IDENT pushbutton switch which is used to generate additional
identification pulses in the reply signal
- a control knob to select the four-digit transmit code from 0000 to
7777.
- a 1/2 switch which enables the selection of the ATC 1 or ATC 2 system
- two ABOVE/N/BELOW switches which :
* in ABOVE position, enable a TCAS traffic surveillance from 2700 ft
below to 9900 ft above the TCAS-equipped aircraft
* in N position, enable the normal TCAS traffic surveillance from 2700
ft below to 2700 ft above the TCAS-equipped aircraft
* in BELOW position, enable a TCAS traffic surveillance from 9900 ft
below to 2700 ft above the TCAS-equipped aircraft
- two ABS/REL switches which :
* in ABS position, enable the display of the absolute altitude of TA/RA
intruders
* in REL position, enable the display of the relative altitude of TA/RA
intruders

NOTE : At the present time, these functions are inoperative and reserved
____
for a future use.

- a TEST/STBY/XPDR/TA/TA-RA/TFC switch which :

* in STBY position, inhibits the replies of the selected transponder
and the TCAS surveillance and advisory generation
* in XPDR position, transmits the replies of the selected transponder
when the aircraft is in flight or on the ground. TCAS advisory
generation and surveillance functions are inhibited.

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 INTENTIONALLY BLANK

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 INTENTIONALLY BLANK

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 ATC/TCAS - Control Unit
Figure 009

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 * in TA position, enables the ATC/TCAS operation, but only in TA mode.
No resolution advisories are generated. TA intruders are displayed on
the NDs.
* in RA/TA position, enables all ATC/TCAS modes of operation. TA and RA
intruders are displayed on the NDs. Preventive/corrective vertical
resolution advisories are displayed on the PFDs. Aural messages are
heard on the cockpit loudspeakers.
* in TFC position, enables all ATC/TCAS modes of operation. Other,
Proximate, TA and RA intruders are displayed on the NDs.
Preventive/corrective vertical resolution advisories are displayed on
the PFDs. Aural messages are heard on the cockpit loudspeakers.

NOTE : The display of other/proximate intruders is permanent if the

____
switch is set to TFC. If the switch is set to TA or TA/RA
position, the display of other/proximate intruders is conditioned
by the presence of a TA/RA target.

NOTE : At the present time, the TEST position is not used and therefore,
____
inoperative.

The processor controls the function of the unit and:

- converts the identification code selected into ARINC 429 format
transmission to the selected transponder
- provides selected code data to drive the liquid crystal display
- activates the appropriate light when a fault signal is received from
the selected transponder.
R

C. Antenna
(Ref. Fig. 010)
The L-band antenna is a short stub, all aluminum blade type which is
completely sealed to prevent failure from moisture incursion.
It is vertically polarized, has an impedance of 50 ohms, a Voltage
Standing Wave Ratio (VSWR) of 1,5 : 1 and operates in the 960 MHz to 1220
MHz frequency band. Lightning protection is provided to prevent damage to
the antenna and the transponder.
Four antennas must be provided on the aircraft. The desire for improved
upper hemisphere coverage usually leads to a choice of upper and lower
mounting locations for the transponder antennas on the aircraft.

6. Operation
_________

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 ATC - Antenna
Figure 010

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R

A. Control
(Ref. Fig. 002)

(1) In normal operation, you select the ATC 1(2) through the 1/2 selector
switch on the control unit in either position 1 or 2.
A switch INOP/STBY/XPDR/TA/TA-RA/TFC enables the functions given
below :
- in STBY position : the answers of the two transponders are
inhibited
- in XPDR position : the selected transponder answers are valid when
the aircraft is in flight or on the ground.
- in TA or TA-RA or TFC positions : the selection of the TCAS modes.

(2) Upon energization of the aircraft or modification of system

selection, the last ATC code selected is displayed before the new
code selection. This code comes into view on the display window of
the control unit.

(3) When you push the IDENT pushbutton switch (ON configuration), this
generates an additional identification pulse in the reply signal.

(4) With failure of the ATC control unit, the transponder continues to
transmit the last displayed code. No new code selection is possible.

(5) In addition, a suppressor coaxial connects the ATC tranponders to the

Distance Measuring Equipment (DME) interrogators and the TCAS
computer. This prevents transmission from one system while the others
are in reception mode. This is necessary because the ATC, the DME and
the TCAS systems operate on the same frequency range.

B. Reconfiguration Switching
In normal configuration, each ATC receives the altitude information from
its corresponding Air Data/Inertial Reference Unit (ATC1 from ADIRU1,
ATC2 from ADIRU2).
With failure of the ADIRU corresponding to the serviceable transponder,
the pilot can select the altitude information from the ADIRU 3. This
selection is through the AIR DATA selector switch installed on panel 8VU
on the center pedestal.
R

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R 7. Test
____

R A. CFDIU Interface

R (1) BITE description

R The BITE facilitates maintenance on in-service aircraft. It detects
R and identifies a failure related to the ATC system.
R The BITE of the ATC transponder is connected to the CFDIU.
R The unit tested is the ATC transponder.
R The BITE:
R - transmits permanently ATC system status and its identification
R message to the CFDIU
R - memorizes the faults which occurred during the last 63 flight legs
R - monitors data inputs from the various peripherals (FMGC, ADIRU, ATC
R CTL UNIT and CFDIU)
R - transmits to the CFDIU the result of the tests performed and
R self-tests
R - can communicate with the CFDIU through the menus.
R The BITE can operate in two modes:
R - the normal mode
R - the interactive mode.

R (a) Normal mode

R During the normal mode the BITE monitors cyclically the status of
R the ATC system. It transmits its information to the CFDIU during
R the flight concerned.
R In case of fault detection, the BITE stores the information in
R the fault memories.
R These items of information are transmitted to the CFDIU every 100
R ms by an ARINC 429 message with label 350.

R (b) Interactive mode:

R The interactive mode can only be activated on the ground.
R This mode enables communication between the CFDIU and the ATC
R transponder BITE by means of the MCDU.
R (Ref. Fig. 011)
R The ATC interactive mode is composed of:
R (Ref. Fig. 012, 013, 014, 015)
R - LAST LEG REPORT
R The purpose of this item is to present the fault messages
R (class 1 and 2, internal and external) that appeared during the
R last flight.
R - PREVIOUS LEGS REPORT
R The purpose of this item is to present the fault messages
R (class 1 and 2, internal and external) that appeared during the
R previous flights.

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R ATC Maintenance Test Procedure - ATC Menu (sheet 1/5)
R Figure 011

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R ATC Maintenance Test Procedure - ATC Menu (sheet 2/5)
Figure 012

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R ATC Maintenance Test Procedure - ATC Menu (sheet 3/5)
R Figure 013

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R ATC Maintenance Test Procedure - ATC Menu (sheet 4/5)
R Figure 014

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R ATC Maintenance Test Procedure - ATC Menu (sheet 5/5)
R Figure 015

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R When no fault has been detected during the last 63 flights, the
R NO FAULT DETECTED message is displayed.
R - LRU IDENTIFICATION
R The purpose of this item is to present the part number (P/N)
R and the software number (SW/N) of the component.
R - GROUND SCANNING
R This item is based on the monitoring and fault analysis used
R during the flight.
R The system peripherals monitoring and system internal cyclic
R tests are used to detect transient anomalies.
R - TROUBLE SHOOTING DATA
R This item allows to analyze the snapshot of the recorded
R failure to detect the software bugs.
R - CLASS 3 FAULTS
R The purpose of this item is to present the class 3 fault
R messages that appeared during the last flight.
R There is no date and no failure classification.
R - GROUND REPORT
R The purpose of this item is to present the class 1, 2 or 3
R internal failures when they are detected on ground.
R - DISCRETE STATUS
R This item includes display of all input discretes, display of
R instrumentation port data blocks or any other information that
R may be helpful in system trouble-shooting or any other
R application.
R - TEST
R The activation of this manual test shall only be allowed on the
R ground. The results of the test are transmitted to the CFDS but
R are not memorized.

R (2) Reporting functions

R --------------------------------------------------------------------------
R | REPORTED INTERNAL FAILURES |
R |------------------------------------------------------------------------|
R | MESSAGE (i = 1 or 2) | CLASS | ATA |
R |---------------------------------------------|---------|----------------|
R | ATCi (1SHi) | 1 | 34-52-33 |
R | ATC1 TOP ANTENNA (7SH3) | 1 | 34-52-11 |
R | ATC1 BOT ANTENNA (7SH1) | 1 | 34-52-11 |
R | ATC2 TOP ANTENNA (7SH4) | 1 | 34-52-11 |
R | ATC2 BOT ANTENNA (7SH2) | 1 | 34-52-11 |
R | WRG : MODE S ADRESS/ATCi (1SHi) | 1 | 34-52-33 |
R --------------------------------------------------------------------------

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R --------------------------------------------------------------------------
R | REPORTED EXTERNAL FAILURES |
R |------------------------------------------------------------------------|
R | MESSAGE (i = 1 or 2) | CLASS | ATA |
R |---------------------------------------------|---------|----------------|
R | ATC CTL PNL (3SH)/ATCi (1SHi) | 1 | 34-52-12 |
R | ADIRU i/3(1FPi/3)/ATCi (1SHi) | 1 | 34-12-34 |
R | TCAS(1SG)/ATCi(1SHi) | 3 | 34-43-34 |
R | CFDIU(1TW)/ATCi(1SHi) | 3 | 31-32-34 |
R | FMGCi(1CAi)/ATCi(1SHi) | 3 | 22-83-34 |
R | POWER SUPPLY INTERRUPT | 1 | 24-00-00 |
R | LGCIUi(5GAi)/ATCi(1SHi) | 3 | 32-31-71 |
R --------------------------------------------------------------------------

R B. BITE Implementation

R (1) Internal test processing

R ----------------------------------------------------------------------------
R | TEST | TESTED INTERNAL COMPONENTS | DURATION | ACTIVATION |
R | DESIGNATION | | | CONDITIONS |
R ----------------------------------------------------------------------------
R | Power-up test | Power supply module | 3 s | Power interrupt|
R | | ROM - RAM | | > 200 ms |
R |---------------|------------------------------|----------|----------------|
R | MCDU system | - NAV receiver | | Relevant MCDU |
R | test | - BITE circuitry | | menu and line |
R | | - SYS failure LED indication | | key selection |
R | | on the ATC control unit | | |
R |---------------|------------------------------|----------|----------------|
R | Face test | - ROM, RAM check | | Relevant P/BSW |
R | | - Antenna integrity | | activated on |
R | | - Receiver (top/bottom) | | XPDR face. |
R | | - Transmitter | | |
R | | - Reply format | | |
R | | - Power supply monitor | | |
R | | - I/O bus check | | |
R | | - Non-Volatile Memory | | |
R ----------------------------------------------------------------------------

R (2) Activation of the test on the indicators

R The ATC 1(2) test function can be activated in ground conditions only
R by pressing the TEST key on the ATC 1(2) maintenance sub-menu or by
R pressing the pushbutton switch on the face of the transponder.
R The following sequence is then generated on the output of the
R equipment:

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R -------------------------------------------------------------------------
R | DURATION | MESSAGE | ATC CONTROL UNIT AND FACE OF ATC TRANSPONDER |
R -------------------------------------------------------------------------
R | FOR 1 s | Failure | - Failure light comes on on control unit |
R | | | - all LEDs come on on transponder face |
R | AFTER 1 s | | - All indicator lights go off |
R | FOR 10 s | | - The indicator lights associated with the |
R | | | self-test results come on. Afterwards, all |
R | | | indicator lights go off. |
R -------------------------------------------------------------------------

R When the selected system on the ATC control unit is different from
R the system under test, this causes illumination of a message on the
R MCDU after the TEST selection. This message is: PLEASE CHECK IF THE
R CONTROL PANEL SWITCH IS ON SYSTEM (1 OR 2) AND PRESS TEST KEY.
R Reminder: The TEST pushbutton switch is used to initiate the LED test
R and transponder self-test. When this pushbutton switch is pressed for
R more than five seconds, the transponder reads the Non-Volatile Memory
R fault data for last four legs and the applicable fault indicator
R lights come on.

R C. Power-up Tests Initialization and Cockpit Repercussions

R (1) Conditions of power-up tests initialization

R - How long the computer must be de-energized: 1 s.
R - A/C configuration: whatever the A/C configuration on ground

R (2) Duration of power-up tests: 3 s approx.

R (3) Results of power-up tests

R (cockpit repercussions, if any, in case of tests pass/tests failed).
R - Tests pass: none
R - Tests failed: on the ATC control unit, FAULT or FAIL indicator
R light comes on or F indication appears on the display (depending on
R the type of the control unit).

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 ATC - ADJUSTMENT/TEST
_____________________

TASK 34-52-00-740-004

BITE Test of the ATC

WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE
_______
YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
31-32-00-860-010 Procedure to Get Access to the SYSTEM REPORT/TEST NAV
Page
34-10-00-860-002 ADIRS Start Procedure

3. __________
Job Set-up

Subtask 34-52-00-860-078-A

A. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-

002).

(2) On the overhead panel, on the ADIRS CDU, set the OFF/NAV/ATT selector
switches to NAV (Ref. TASK 34-10-00-860-002).

(3) On the center pedestal, on the ATC/TCAS control unit, set:

- the ATC system 1(2) on.
- the INOP/STBY/XPDR/TA/TA-RA/INOP switch to XPDR.
R

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 Subtask 34-52-00-860-086

B. On the center pedestal, on one MCDU, get the SYSTEM REPORT/TEST/NAV page
then push the NEXT PAGE function key.
(Ref. TASK 31-32-00-860-010)

Subtask 34-52-00-865-055

C. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV/ATC/1 5SH1 G11
121VU COM NAV/ATC/2 5SH2 K07

4. Procedure
_________

Subtask 34-52-00-740-052-A

A. BITE Test of the ATC

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

On the MCDU: On the MCDU:

- on the NAV page, push the line key - the ATC page comes into view.
adjacent to the ATC1 (ATC2)
indication.

- push the line key adjacent to the On the ATC/TCAS control unit:
TEST indication. - the ATC FAULT or FAIL indicator light
comes on during 2 seconds approx.

At the end of the test, on the MCDU,

the TEST OK indication comes into view.

On the ATC/TCAS control unit:

- set the
INOP/STBY/XPDR/TA/TA-RA/INOP
switch to STBY.

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 5. Close-up
________

Subtask 34-52-00-860-079

A. Put the aircraft back to its initial configuration.

(1) On the overhead panel, on the ADIRS CDU, set the OFF/NAV/ATT selector
switches to OFF.

(2) On the center pedestal, on the MCDU, push the line key adjacent to
the RETURN indication until the MCDU MENU page comes into view.

(3) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

(4) Make sure that the work area is clean and clear of tool(s) and other
items.

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 TASK 34-52-00-710-003

Operational Test of the ATC

WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE
_______
YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

R A. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
34-10-00-860-002 ADIRS Start Procedure
34-10-00-860-005 ADIRS Stop Procedure
R

3. __________
Job Set-up

Subtask 34-52-00-860-080-A

A. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-

002).

(2) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002).

(3) On the center pedestal, on the ATC/TCAS control unit, set:

- the ATC system 1(2) on.
- the INOP/STBY/XPDR/TA/TA-RA/INOP switch to XPDR.

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 Subtask 34-52-00-865-054

B. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV/ATC/1 5SH1 G11
121VU COM NAV/ATC/2 5SH2 K07

4. Procedure
_________

Subtask 34-52-00-710-055

A. Transmission Test

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

On the ATC/TCAS control unit:

- set the On the ATC/TCAS control unit:

INOP/STBY/XPDR/TA/TA-RA/INOP - the ATC FAULT or FAIL indicator light
switch to XPDR. stays off.

- set the On the ATC/TCAS control unit:

INOP/STBY/XPDR/TA/TA-RA/INOP - the display stays on.
switch to STBY.

5. Close-up
________

Subtask 34-52-00-860-062

A. Put the aircraft back to its initial configuration.

(1) Do the ADIRS Stop Procedure (Ref. TASK 34-10-00-860-005).

(2) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

(3) Make sure that the work area is clean and clear of tool(s) and other
items.

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 INTENTIONALLY BLANK

R
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 TASK 34-52-00-720-004

Functional Test of the Altitude Reporting Function

NOTE : You must do this test very quickly to prevent interference with air
____
traffic, specially if the aircraft is in the open air. If the test is
long you must tell the nearest airport of this test.

1. __________________
Reason for the Job

Functional Test of the Altitude Reporting Function.

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

R No specific Air Data Generator

No specific ATC ground test unit

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
R 32-69-00-860-001 Simulation of Flight, with the Aircraft on the Ground
34-10-00-860-002 ADIRS Start Procedure
34-10-00-860-005 ADIRS Stop Procedure
R 34-13-00-790-002 Leak Test of the Principal Static and Total Air Data
R System

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 3. __________
Job Set-up

R Subtask 34-52-00-860-088

R A. Aircraft Maintenance Configuration

R (1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-

R 002).

R (2) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002).

R (3) Install the ATC ground test unit in the cockpit.

R Put the antenna of the ATC ground test unit at 50 cm (approx. 2ft)
R from the ATC antennas.
R Connect the antenna to the ATC ground test unit.

R (4) On the SWITCHING panel 8VU, make sure that the AIR DATA selector
R switch is at NORM.

R (5) On the center pedestal, on the ATC/TCAS control unit:

R - set the ATC system 1(2) on.
R - set the TEST/STBY/XPDR/TA/TA-RA/TFC switch to XPDR.
R - make sure that the display does not show an emergency code: 7500,
R 7600 or 7700.

R (6) On the panel 13VU, on the CAPT and F/O EFIS control sections of the
R FCU, make sure that the baro displays show STD.

R (7) Connect the Air Data Generator to the pitot/static system (Ref. TASK
R 34-13-00-790-002).

R (8) On the center pedestal, on one MCDU, get the LGCIU 1 (2) page and
R simulate a flight condition (Ref. TASK 32-69-00-860-001).

R (9) Start the Air Data Generator and set the ATC ground test unit so that
R it can process ATC mode C replies.

Subtask 34-52-00-865-056

B. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV/ATC/1 5SH1 G11
121VU COM NAV/ATC/2 5SH2 K07

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R 4. Procedure
_________

R Subtask 34-52-00-720-061

R A. Functional Test of the Altitude Reporting Function

R -------------------------------------------------------------------------------
R ACTION RESULT
R -------------------------------------------------------------------------------

R 1. On the air data generator:

R - set a static pressure of 402
R hPa (23,458 ft).
R - set an impact pressure of 153.5
R hPa (300 kts).

R 2. On the ATC/TCAS control unit: On the ATC/TCAS control unit:

R - set the - the display shows the last code set.
R TEST/STBY/XPDR/TA/TA-RA/TFC - the ATC FAULT or FAIL indicator light
R switch to XPDR. stays off.

R On the ATC ground test unit, a display

R shows:
R - the last selected code.
R - a standard altitude of approx. 23,458
R ft or equivalent.

R The difference between the altitude

R shown on CAPT and F/O PFDs and that
R shown on the ATC ground test unit must
R not be more than 125 ft.

R - set the On the ATC/TCAS control unit:

R TEST/STBY/XPDR/TA/TA-RA/TFC - the display stays on.
R switch to STBY.

R 3. On the air data generator: The rate of descent must not be more
R - slowly decrease pitot and than 6,000 ft.
R static pressures until you get
R atmospheric values.

R 4. Stop and disconnect the air data

R generator.

R 5. On the MCDU: The flight condition is no longer

R - push the line key adjacent to simulated.

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
R the RETURN indication until you
R get the CFDS menu page.

5. Close-up
________

Subtask 34-52-00-860-059

A. Put the aircraft back to its initial configuration.

(1) Disconnect the ATC ground test unit.

(2) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005).

(3) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

(4) Make sure that the work area is clean and clear of tool(s) and other
items.

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 TASK 34-52-00-720-005

Functional Test of the ATC/Mode S Transponder

NOTE : You must do this test very quickly to prevent interference with air
____
traffic, specially if the aircraft is in the open air. If the test is
long, you must tell the nearest airport of this test.

NOTE : For best test results, buildings, vehicles and other aircraft must not
____
be in the area of the main antenna lobe (approx 30 ft.).

1. __________________
Reason for the Job

NOTE : There are alternative methods for this procedure. This task gives one
____
of the methods. For the other method with a different Ground Test
Unit, refer to the other task in this page block.

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific access platform

No specific circuit breaker(s) safety clip(s)
No specific telescopic pole
No specific T49 - ATC GROUND TEST UNIT (or equivalent)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
32-00-00-860-001 Flight Configuration Precautions
32-00-00-860-002 Ground Configuration after Flight Configuration
34-10-00-860-002 ADIRS Start Procedure
34-10-00-860-005 ADIRS Stop Procedure

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 3. __________
Job Set-up

Subtask 34-52-00-860-083

A. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits

(Ref. TASK 24-41-00-861-002).

(2) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002).

(3) On the center pedestal:

(a) On the ATC/TCAS control unit, set:

- the ATC system 1(2) on.
- the ATC code 5555 to keep the traffic interference to a
minimum.
- the STBY/XPDR/TA/TA/RA/TFC switch to XPDR.

(b) On the SWITCHING panel 8VU:

- make sure that the AIR DATA selector switch is at NORM.
R

Subtask 34-52-00-865-057

B. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV/ATC/1 5SH1 G11
121VU COM NAV/ATC/2 5SH2 K07

Subtask 34-52-00-480-050

C. Install the T49 - ATC GROUND TEST UNIT (or equivalent) in the cockpit.

(1) Connect the test antenna to the test unit.

(2) Put the test antenna near the ATC antenna for which you do the test
(approx. 2 ft.).

NOTE : Use an access platform or a telescopic pole to put the test

____
antenna near the ATC bottom antenna.

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 Subtask 34-52-00-860-073

D. Obey the applicable safety precautions before you open the LGCIU circuit
breakers (Ref. TASK 32-00-00-860-001).

Subtask 34-52-00-865-061

E. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU L/G/LGCIU/SYS1/NORM 1GA C09
121VU HYDRAULIC/LGCIU/SYS2 2GA Q35
121VU HYDRAULIC/LGCIU/SYS1/GRND SPLY 52GA Q34

4. Procedure
_________

Subtask 34-52-00-720-051-A

A. Functional Test of the ATC/Mode S Transponder

NOTE : Do the test of the ATC bottom antenna 1(2) first.

____
Then, do the test of the ATC top antenna 1(2).

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the ATC ground test unit: On the ATC ground test unit:

- set the ATCRBS/MODE S/TCAS/XPDR

TEST switch to XPDR TEST.

- push the TEST pushbutton switch - the data display shows:

to start the operation of the MODE S XPDR COM A/B
test set. INTERROGATE TO TEST.

NOTE : You can also start the

____
same test procedure if you
push the INTERROGATE
pushbutton switch. At the
end of this test
procedure, a test message
shows the system status
but all the results given
below are not shown.

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
- push the TEST pushbutton - the data display shows:
switch. ATCRBS/A
TESTING
and then,
ATCRBS/A
5555 XX% REPLY
(XX is a number which indicates the
local conditions of reception).

NOTE : You must do the steps that

____
follow in a fast sequence
to keep incorrect traffic
alarms to a minimum.

2. On the ATC/TCAS control unit:

- set the
TEST/STBY/XPDR/TA/TA-RA/TFC
selector switch to XPDR.

3. On the test unit: On the test unit:

- push the TEST pushbutton - the data display shows:
switch. ATCRBS/C
TESTING
and then,
ATCRBS/C
Z,ZZZ ft XX% REPLY
(Z,ZZZ is a number which shows,
approximately, the local field
elevation).

- push the TEST pushbutton - the data display shows:

switch. ATCRBS/A MODE S ALL
TESTING
and then,
ATCRBS/A MODE S ALL
AIRCRAFT CODE XX% REPLY
(the aircraft code is on 6 digits).

- push the TEST pushbutton - the data display shows:

switch. ATCRBS/C MODE S ALL
TESTING
and then,
ATCRBS/C MODE S ALL
AIRCRAFT CODE XX% REPLY.

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
- push the TEST pushbutton - the data display shows:
switch. ATCRBS/A ONLY
TESTING
and then,
ATCRBS/A ONLY
NO REPLY FROM XPDR.

- push the TEST pushbutton - the data display shows:

switch. ATCRBS/C ONLY
TESTING
and then,
ATCRBS/C ONLY
NO REPLY FROM XPDR.

- push the TEST pushbutton - the data display shows:

switch. MODE S SURV IDENTITY
TESTING
MODE S SURV ALTITUDE
TESTING
MODE S SURV SHORT
TESTING
and then:
MODE S SURV XX% REPLY
AIRCRAFT CODE (Make sure that the
code display agrees with the code WSW
given to that aircraft - 6 digits)
APPROXIMATE LOCAL FIELD-ELEVATION.

- push the TEST pushbutton - the data display shows:

switch. UNDESIRED REPLIES
TESTING
and after a short time during which
the display flashes:
UNDESIRED REPLIES
NO REPLIES.

- push the TEST pushbutton - the data display shows:

switch. SQUITTER
TESTING
and then,
SQUITTER
PASS.

R - push the TEST pushbutton - the data display shows:

R switch. DIVERSITY
R PASS

R - push the TEST pushbutton - the data display shows:

R switch. MAX TRUE AIRSPEED

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
R GT 300 LE 600KTS

R - push the TEST pushbutton - the data display shows:

R switch. FLIGHT NO.
R TESTING
R and then,
R FLIGHT NO.
R 12345678

R - push the TEST pushbutton - the data display shows:

R switch. PWR. RCVR. FREQ
R TESTING
R and then,
R 1090.2 MHZ
R 250W -75DBM

R - At the end of the test, set the - the display goes off.
R LIGHTS/OFF switch to OFF.

5. Close-up
________

Subtask 34-52-00-860-051

A. Put the aircraft back to its initial configuration.

(1) On the center pedestal, on the ATC/TCAS control unit, set the
STBY/XPDR/TA/TA/RA/TFC switch to STBY.

(2) Do the ADIRS Stop Procedure(Ref. TASK 34-10-00-860-005).

(3) On the test unit, set the OFF/LIGHTS switch to OFF.

(4) Remove the test antenna and the test unit.

(5) De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-

002).

Subtask 34-52-00-865-062

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
1GA, 2GA, 52GA

Subtask 34-52-00-860-074

C. Do the ground configuration after the flight configuration (Ref. TASK 32-
00-00-860-002).

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 TASK 34-52-00-720-005- 01

Functional Test of the ATC/Mode S Transponder

NOTE : You must do this test very quickly to prevent interference with air
____
traffic. If the test is long, you must tell the nearest airport of this
test.

NOTE : For best test results, buildings, vehicles and other aircraft must not
____
be in the area of the main antenna lobe (approx. 30 ft.).

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific antenna shield

R No specific ATC-601 test set (version 2.22) or equivalent

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
R 32-69-00-860-001 Simulation of Flight, with the Aircraft on the Ground
34-10-00-860-002 ADIRS Start Procedure
34-10-00-860-005 ADIRS Stop Procedure

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 3. __________
Job Set-up

Subtask 34-52-00-860-084

A. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits

(Ref. TASK 24-41-00-861-002).

(2) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002).

R (3) On the center pedestal, on one MCDU, get the LGCIU 1 (2) page and
R simulate a flight condition (Ref. TASK 32-69-00-860-001).

R (4) On the center pedestal:

(a) On the ATC/TCAS control unit, set:

- the ATC system 1(2) on.
- the ATC code 5555 to keep the traffic interference to a
minimum.
- the STBY/XPDR/TA/TA/RA/TFC switch to XPDR.

(b) On the SWITCHING panel 8VU:

- make sure that the AIR DATA selector switch is at NORM.

Subtask 34-52-00-865-058

B. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV/ATC/1 5SH1 G11
121VU COM NAV/ATC/2 5SH2 K07

Subtask 34-52-00-480-051-A

R C. Install the ATC-601 test set (version 2.22) or equivalent

(1) Make sure that the test set and the test antenna are in the correct
position:
- for the test of the bottom antenna:
10 ft. (3 m) approximately from this antenna,
- for the test of the top antenna:
in the line of sight of this antenna, at less than 200 ft. (60.95
m).

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 (2) Connect the test antenna to the test set with the coaxial cable.

(3) Put an antenna shield on the bottom antenna during the test of the
top antenna.

(4) On the test set:

- push the POWER key,
- push the SELF TEST key,
- push the RUN/STOP key and make sure that the test is satisfactory,
- push the SETUP key to record the antenna setup data in the SETUP
MENU:
. RANGE, HEIGHT, SELECTED antenna and GAIN read on the test
antenna.

4. Procedure
_________

Subtask 34-52-00-720-052

A. Functional Test of the ATC/Mode S Transponder.

NOTE : Do the test of the ATC top antenna 1(2) first with the antenna
____
shield on the bottom antenna.
Then, do the test of the ATC bottom antenna 1(2) without the
antenna shield.
Ignore the indications VS, RI, FS, DR, UM, CA, PI, MV, MB, because
they are not related to this test.

NOTE : For the AIRCRAFT CODE, make sure that the code display agree with
____
the code WSW given to that aircraft - 6 digits.

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the test set:

- push the AUTO TEST key.

- push the RUN/STOP key to start The data display shows the TEST RUNNING
the operation of the test set. indication and asterisks on the bottom
line.
At the end of the test, the AUTO TEST -
PASSED, comes into view with these
indications:
MODE TESTED - A, C, S FREQ: 1090 (+/-
3) MHZ
MODE PASSED - A, C, S ERP: 54 (+/- 4)
dBm

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
MODE FAILED - . . . . MTL: -73 (+/-
4)dBm
DIVERSITY ISOLATION: more than or equal
to 20 dBm
Press RUN to start

2. To know the 19 available, push

the SELECT keys and push the
RUN/STOP key to start the test.

- push the right SELECT key until On the REPLY DELAY TEST - PASSED page,
the REPLY DELAY TEST menu page the results of the test come into view:
comes into view. MODE S: 128.00 (+/- 0.25) microseconds
ITM A: 128.00 (+/- 0.25) microseconds
C: 128.00 (+/- 0.25) microseconds
ATC A: 3.00 (+/- 0.5) microseconds C:
3.00 (+/- 0.5) microseconds
Press run to start.

- push the right SELECT key. On the REPLY JITTER TEST - PASSED page,
the results of the test come into view:
MODE S: XXX (less than or equal to
0.08) microseconds
ITM A: XXX (less than or equal to 0.1)
microseconds C: XXX (less than or equal
to 0.1) microseconds
ATC A: XXX (less than or equal to 0.1)
microseconds C: XXX (less than or equal
to 0.1) microseconds
Press run to start.

- push the right SELECT key. On the ATCRBS REPLY TEST - PASSED page,
the results of the test come into view:
F1 TO F2 SPACING A: 20.3 (+/- 0.10)
microseconds C: 20.3 (+/- 0.10)
microseconds
F1 PULSE WIDTH A: 0.45 (+/- 0.10)
microseconds C: 0.45 (+/- 0.10)
microseconds
F2 PULSE WIDTH A: 0.45 (+/- 0.10)
microseconds C: 0.45 (+/- 0.10)
microseconds
CODE= 5555 ALT= XX XXX FT
Press run to start.

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
- push the right SELECT key. On the SLS LEVEL TEST - PASSED page,
the results of the test come into view:
-9dB: REPLY
0dB: NO REPLY
Press run to start.

- push the right SELECT key. On the ATC ONLY ALL-CALL TEST - PASSED
page, the indication PASSED TEST comes
into view
Press run to start.

- push the right SELECT key. On the MODE S ALL-CALL TEST - PASSED
page, the indication ALL-CALL ADDRESS =
XXXXXX comes into view
Press run to start.

- push the right SELECT key. On the INVALID ADDRESS TEST - PASSED
page, the indication PASSED TEST comes
into view
Press run to start.

- push the right SELECT key. On the SPR ON/OFF TEST - PASSED page,
the results of the test come into view:
SPR ON : REPLY
SPR OFF : NO REPLY
Press run to start.

- push the right SELECT key. On the MODE S UF0 TEST - PASSED page,
these indications come into view:
DF 0 VS=X RI=X AC=XXXXX FT
ADDRESS=XXXXXX
Press run to start.

- push the right SELECT key. On the MODE S UF4 TEST - PASSED page,
these indications come into view:
DF 4 FS=X DR=XX UM=XX AC=XXXXX FT
ADDRESS=XXXXXX
Press run to start.

- push the right SELECT key. On the MODE S UF5 TEST - PASSED page,
these indications come into view:
DF 5 FS=X DR=XX UM=XX ID=5555
ADDRESS=XXXXXX
Press run to start.

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
- push the right SELECT key. On the MODE S UF11 TEST - PASSED page,
these indications come into view:
DF 11 CA=X AA=XXXXXX PI=XXXXXX
Press run to start.

- push the right SELECT key. On the MODE S UF16 TEST - PASSED page,
these indications come into view:
DF 16 VS=X RI=X AC=XX XXX FT
MV=XXXXXXXXXXXXXX ADDRESS=XXXXXX
R (If TCAS is not installed or is in
R standby mode, the only NO REPLY
R indication comes into view).
Press run to start.

- push the right SELECT key. On the MODE S UF20 TEST - PASSED page,
ignore the results.

- push the right SELECT key. On the MODE S UF21 TEST - PASSED page,
ignore the results.

- push the right SELECT key. On the SQUITTER TEST - PASSED page,
these indications come into view:
PERIOD = X.XX SECONDS (PERIOD is 0.8 s
to 2.4 s)
TAIL NUMBER = XXXXXX
SQUITTER ADDRESS=XXXXXX
Press run to start.

- push the right SELECT key. On the FREQUENCY TEST - PASSED page,
the indication FREQUENCY = 1090 (plus
or minus 3) MHz comes into view
Press run to start.

- push the right SELECT key. On the DIVERSITY TEST - PASSED page,
the indication DIVERSITY ISOLATION: XX
(more than or equal to 20) dB comes
into view
Press run to start.
You must do this test at a distance of
less than 50 ft. (15.24 m) of the
antenna).

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
- push the right SELECT key. On the MTL DIFFERENCE TEST - PASSED
page, the indication MODE A MTL - MODE
C MTL = X.X (less than or equal to 1)
dB comes into view with the indication
Press run to start.

R 3. On the test set:

R - push the POWER TEST key The results of the last power test are
R displayed:
R
R ** POWER TEST **
R .................ERP..MTL
R .TOP AVG (dBm) = XX.X -XX.X
R .BOT AVG (dBm) = XX.X -XX.X
R INSTANTANEOUS =
R Press RUN to start

R - push the left or right SELECT The dot in front of TOP or BOT
R key to select the top (bottom) indicates which set of antennas has
R antenna. been selected.

R Hold the directional flat test

R set antenna at arm<s length over
R your head, aim it and on its
R handle:
R
R - push the pushbutton switch to
R start the test.

R - move the antenna downward from After a short while the display shows:
R the top position within
R approximately 2 seconds to near - for the top antenna:
R the level of your ankles. ** POWER TEST **
R .................ERP..MTL
R .TOP AVG (dBm) =
R .BOT AVG (dBm) = NOT RUN
R INSTANTANEOUS = XX.X -XX.X
R Press RUN to start
R
R - for the bottom antenna:
R ** POWER TEST **
R .................ERP..MTL
R .TOP AVG (dBm) = NOT RUN

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
R .BOT AVG (dBm) =
R INSTANTANEOUS = XX.X -XX.X
R Press RUN to start
R

R NOTE : The indicated values in the

____
R places of XX.X represent the
R specific data measured
R presently.

R On the handle of the directional

R flat test set antenna:

R - push the pushbutton switch to The display shows:

R stop the power test.
R - for the top antenna:
R ** POWER TEST **
R .................ERP..MTL
R .TOP AVG (dBm) = XX.X -XX.X
R .BOT AVG (dBm) = NOT RUN
R INSTANTANEOUS =
R Press RUN to start
R
R - for the bottom antenna:
R ** POWER TEST **
R .................ERP..MTL
R .TOP AVG (dBm) = NOT RUN
R .BOT AVG (dBm) = XX.X -XX.X
R INSTANTANEOUS =
R Press RUN to start
R

R NOTE : The indicated values should be:

____
R - ERP: less than 57.0 dBm
R and more than 48.5 dBm
R - MTL: -73.0 (plus/minus 4.0)
R dBm.

R 4. At the end of the test, push the The display goes off.
POWER key.

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 5. Close-up
________

Subtask 34-52-00-860-053

A. Put the aircraft back to its initial configuration.

(1) On the center pedestal, on the ATC/TCAS control unit, set the
STBY/XPDR/TA/TA/RA/TFC switch to STBY.

R (2) On the MCDU, push the line key adjacent to the RETURN indication
R until you get the CFDS menu page.

R (3) Do the ADIRS Stop Procedure(Ref. TASK 34-10-00-860-005).

R (4) Remove the test antenna and the test set.

Subtask 34-52-00-862-054

B. De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-

002).

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 TASK 34-52-00-720-006

Functional Test of the ATC Antennas

1. __________________
Reason for the Job

Refer to the MPD TASK: 345200-02

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific access platform

No specific telescopic pole
No specific ATC grount test unit

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
32-69-00-860-001 Simulation of Flight, with the Aircraft on the Ground

3. __________
Job Set-up

Subtask 34-52-00-861-055

A. Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-002).

Subtask 34-52-00-865-059

B. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV/ATC/1 5SH1 G11
121VU COM NAV/ATC/2 5SH2 K07

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 Subtask 34-52-00-480-052

C. Install the ATC grount test unit in the cockpit.

(1) Put the antenna of the ATC ground test unit at 50cm (approx 2 ft.)
from the ATC antennas.

NOTE : Use an access platform or a telescopic pole to put the test

____
antenna near the ATC bottom antenna.

(2) Connect the antenna to the ATC ground test unit.

(3) Set the ATC ground test unit to ON.

Subtask 34-52-00-860-085-A

D. Aircraft Maintenance Configuration

(1) On the center pedestal, on the ATC/TCAS control unit, set:

- the ATC system 1(2) on.
- the ATC code 5555 to keep the traffic interference to a minimum.
- the TEST/STBY/XPDR/TA/TA-RA/TFC switch to STBY.

(2) On the center pedestal, on one MCDU, get the LGCIU 1 (2) menu page
and simulate a flight condition (Ref. TASK 32-69-00-860-001).

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 4. Procedure
_________

Subtask 34-52-00-720-059-A

A. Functional Test of the Antennas

NOTE : Do the test of the ATC bottom antenna 1(2) first.

____
Then, do the test of the ATC top antenna 1(2).

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

On the ATC/TCAS control unit: On the ATC ground test unit,

- set the the data display shows the code 5555.
TEST/STBY/XPDR/TA/TA-RA/TFC switch
to XPDR.

On the ATC/TCAS control unit:

- set the
TEST/STBY/XPDR/TA/TA-RA/TFC switch
to STBY.

5. Close-up
________

Subtask 34-52-00-860-087

A. Put the aircraft back to its initial configuration.

(1) Set the ATC ground test unit to OFF.

(2) Remove the test antenna and the ground test unit.

Subtask 34-52-00-862-055

B. De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-

002).

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 ANTENNA - ATC (7SH1,7SH2,7SH3,7SH4) - REMOVAL/INSTALLATION
__________________________________________________________

TASK 34-52-11-000-001

Removal of the ATC Antenna (7SH1,7SH2,7SH3,7SH4)

WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS

_______
ONLY WITH A GOOD SUPPLY OF AIR.
OBEY THE MANUFACTURERS INSTRUCTIONS.
PUT ON PROTECTIVE CLOTHING.
DO NOT GET THEM IN YOUR MOUTH.
DO NOT SMOKE.
DO NOT BREATHE THE GAS.
THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT.
GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED.

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific blanking caps

No specific circuit breaker(s) safety clip(s)
No specific nonmetallic scraper
FOR FIN 7SH3, 7SH4
No specific access platform 6.0 m (19 ft. 8 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

34-52-11-991-001 Fig. 401

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 3. __________
Job Set-up

Subtask 34-52-11-865-050

A. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
FOR 7SH1, 7SH3
49VU NAV/ATC/1 5SH1 G11
FOR 7SH2, 7SH4
121VU COM NAV/ATC/2 5SH2 K07

Subtask 34-52-11-010-050

B. Get Access

(1) FOR 7SH1, 7SH2

Find the ATC bottom antenna 1 7SH1 at zone 127 or ATC bottom antenna
2 7SH2 at zone 128.

(2) FOR 7SH3, 7SH4

Put the access platform in position at zone 224 (ATC top antenna 1
7SH3) or at zone 223 (ATC top antenna 2 7SH4)

4. Procedure
_________

(Ref. Fig. 401/TASK 34-52-11-991-001)

Subtask 34-52-11-020-050

A. Removal of the ATC Antenna

NOTE : The procedure is the same for the ATC antennas 7SH1, 7SH2, 7SH3
____
and 7SH4.

(1) Remove the sealant from the heads of the screws (5) with anonmetallic
scraper.

(2) Remove the screws (5).

(3) Pull the antenna (4) away from the fuselage (1).

(4) Disconnect the coaxial connector (2) from the ATC antenna connector
(3).

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 ATC Antenna
Figure 401/TASK 34-52-11-991-001

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 (5) Remove the antenna (4).

(6) Put blanking caps on the disconnected coaxial connectors (2) and (3).

(7) Remove and discard the O-ring seal (6).

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 TASK 34-52-11-400-001

Installation of the ATC Antenna (7SH1,7SH2,7SH3,7SH4)

WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS

_______
ONLY WITH A GOOD SUPPLY OF AIR.
OBEY THE MANUFACTURERS INSTRUCTIONS.
PUT ON PROTECTIVE CLOTHING.
DO NOT GET THEM IN YOUR MOUTH.
DO NOT SMOKE.
DO NOT BREATHE THE GAS.
THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT.
GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED.

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific lint-free cloth

No specific masking tape
No specific nonmetallic scraper
FOR FIN 7SH3, 7SH4
No specific access platform 6.0 m (19 ft. 8 in.)

B. Consumable Materials

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

Material No. 05-013 D TV-53-3507/73

RELEASE AGENT (OBSOLETE USE 05-013A) (Ref. 20-31-00)
Material No. 07-001B
ELECTRICAL BONDING COATING (BLUE COLOR)
(Ref. 20-31-00)
R Material No. 09-016 USA MIL-PRF-81733D TYPE II CLASS B
CORROSION INHIBITING FILLET CONSISTENCY
(Ref. 20-31-00)

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 -------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

Material No. 09-019 USA AMS 3267/3

LOW ADHESION CORROSION INHIBITING SEALANT
(Ref. 20-31-00)
Material No. 11-003 USA TT-M-261
METHYL-ETHYL-KETONE (Ref. 20-31-00)
R Material No. 16-003 F ASNB70720
COATING (OBSOLETE USE 16-021) (Ref. 20-31-00)

C. Expendable Parts

-------------------------------------------------------------------------------
FIG.ITEM |DESIGNATION |IPC-CSN
-------------------------------------------------------------------------------

6 O-ring seal 34-52-11 01 -010

D. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

20-28-00-912-005 Electrical Bonding of Antennas With Conductive Bolts.

34-52-00-710-003 Operational Test of the ATC
51-76-11-300-001 Repair of the Sealing
34-52-11-991-001 Fig. 401

3. __________
Job Set-up

Subtask 34-52-11-860-050

A. Aircraft Maintenance Configuration

(1) FOR 7SH1, 7SH2

Find the ATC bottom antenna 1 7SH1 at zone 127 or ATC bottom antenna
2 7SH2 at zone 128.

(2) FOR 7SH3, 7SH4

Make sure that the access platform is in position at zone 224 (ATC
top antenna 1 7SH3) or at zone 223 (ATC top antenna 2 7SH4).

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 Subtask 34-52-11-865-051

B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and
tagged

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
FOR 7SH1, 7SH3
49VU NAV/ATC/1 5SH1 G11
FOR 7SH2, 7SH4
121VU COM NAV/ATC/2 5SH2 K07

4. Procedure
_________

(Ref. Fig. 401/TASK 34-52-11-991-001)

WARNING : DO NOT GET THE COMPOUND ON YOUR SKIN.

_______
IF YOU DO:
- RUB IT OFF IMMEDIATELY WITH A CLEAN CLOTH
- WASH THE SKIN WITH SOAP AND RINSE WITH CLEAN WATER.

WARNING : IF YOU GET THE FLUID ON YOUR SKIN OR IN YOUR EYES:

_______
- FLUSH IT AWAY WITH CLEAN WATER
- GET MEDICAL AID.

WARNING : OBEY THE MANUFACTURER<S INSTRUCTIONS WHEN YOU USE THE SPECIAL
_______
MATERIAL.
THIS MATERIAL IS DANGEROUS.

Subtask 34-52-11-420-050

A. Installation of the ATC Antenna

NOTE : The procedure is the same for the ATC antennas 7SH1, 7SH2, 7SH3
____
and 7SH4.

(1) Remove the sealant from the fuselage with CLEANING AGENTS (Material
No. 11-003) and a nonmetallic scraper

NOTE : If you install the same antenna it is necessary to clean it

____
with a lint-free cloth.

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 (2) Do an inspection of the component interface and/or the adjacent area.

NOTE : Make sure that the antenna-attachment screw-head recesses have

____
no signs of paint, corrosion or sealant because the antenna
electrical bonding is made through the attachment screws.

(3) Apply masking tape to the structure (1), the edge of the antenna (4),
the screw holes and the hole for the antenna connector.

(4) Apply SPECIAL MATERIALS (Material No. 05-013) on the mount of the
antenna (4) and on the fuselage (1).

(5) Apply SEALANTS (Material No. 09-019) on the mount of the antenna (4)
and on the fuselage (1) (Ref. TASK 51-76-11-300-001).

NOTE : Make sure that there is no sealant in the screw holes.

____

(6) Remove the blanking caps from the coaxial connectors (2) and (3).

(7) Install the new O-ring seal (6).

(8) Connect the coaxial connector (2) to the antenna connector (3).

(9) Put the antenna (4) in position on the fuselage (1) and install the
screws (5).

(10) Tighten the screws (5).

(11) Remove the sealant which is not necessary.

(12) Make sure that the bonding contact resistance between the antenna (4)
and the fuselage structure (1) is not higher than 5 milliohms
(Ref. TASK 20-28-00-912-005).

(13) Apply a sealing bead with SEALANTS (Material No. 09-016) around the
antenna (4) (Ref. TASK 51-76-11-300-001).

(14) Apply SEALANTS (Material No. 09-016) on the heads of the screws (5).

(15) Make the contour of the screws (5) and the antenna (4) smooth.

(16) Apply STRUCTURE PAINTS (Material No. 16-003) to the sealant around
the base of the antenna (4).

R (17) Apply PAINTS FOR DETAIL (INTERNAL AND EXTERN AL) (Material No. 07-
R 001B) to the sealant on the heads of the screws (5).

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 Subtask 34-52-11-865-052

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
FOR 7SH1, 7SH3
5SH1
FOR 7SH2, 7SH4
5SH2

Subtask 34-52-11-710-050

C. Do the operational test of the ATC (para. ATC DME simultaneous test)
(Ref. TASK 34-52-00-710-003).

5. Close-up
________

Subtask 34-52-11-410-050

A. Close Access

(1) Make sure that the work area is clean and clear of tool(s) and other
items.

(2) Remove the access platform(s).

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 CONTROL UNIT - ATC/TCAS (3SH) - REMOVAL/INSTALLATION
____________________________________________________

TASK 34-52-12-000-001

Removal of the ATC/TCAS Control Unit (3SH)

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific blanking caps

No specific circuit breaker(s) safety clip(s)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

34-52-12-991-001 Fig. 401

3. __________
Job Set-up

Subtask 34-52-12-865-050

A. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV/ATC/1 5SH1 G11
121VU COM NAV/ATC/2 5SH2 K07

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 4. Procedure
_________

(Ref. Fig. 401/TASK 34-52-12-991-001)

Subtask 34-52-12-020-050

A. Removal of the ATC/TCAS Control Unit (3SH)

R NOTE : If your ATC/TCAS control unit has an INOP label(s) on its face and
____
R if you must use this (these) label(s) for the new ATC/TCAS control
R unit:
R - remove this (these) label(s) carefully
R - keep them for installation on the new ATC/TCAS control unit.

(1) Loosen the four quarter-turn fasteners (1).

(2) Disengage the ATC/TCAS control unit (2) from its housing (5).

(3) Disconnect the electrical connectors (4) and hold them away from the
panel.

(4) Remove the ATC/TCAS control unit (2).

(5) Put blanking caps on the disconnected electrical connectors (3) and
(4).

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 ATC/TCAS Control Unit
Figure 401/TASK 34-52-12-991-001

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 TASK 34-52-12-400-001

Installation of the ATC/TCAS Control Unit (3SH)

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

34-52-00-740-004 BITE Test of the ATC

34-52-12-991-001 Fig. 401

3. __________
Job Set-up

Subtask 34-52-12-865-051

A. Make sure that this(these) circuit breaker(s) is(are) open, safetied and
tagged

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV/ATC/1 5SH1 G11
121VU COM NAV/ATC/2 5SH2 K07

4. Procedure
_________

(Ref. Fig. 401/TASK 34-52-12-991-001)

Subtask 34-52-12-420-050

A. Installation of the ATC/TCAS Control Unit (3SH)

R NOTE : If the new ATC/TCAS control unit has some inoperative

____
R functions/modes, install the INOP labels that were on the removed
R ATC/TCAS control unit.

(1) Clean the component interface and/or the adjacent area.

(2) Do an inspection of the component interface and/or the adjacent area.

(3) Remove the blanking caps from the electrical connectors (3) and (4).

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 (4) Make sure that the electrical connectors are clean and in the correct
condition.

(5) Connect the electrical connectors (4) to the ATC/TCAS Control Unit
(2).

(6) Install the ATC/TCAS Control Unit (2) in its housing (5).

(7) Tighten the four quarter-turn fasteners (1).

Subtask 34-52-12-865-052

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
5SH1, 5SH2

Subtask 34-52-12-740-050

C. Do the BITE test of the ATC (Ref. TASK 34-52-00-740-004).

5. Close-up
________

Subtask 34-52-12-860-050

A. Make sure that the work area is clean and clear of tool(s) and other
items.

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 TRANSPONDER - ATC/MODE S (1SH1,1SH2) - REMOVAL/INSTALLATION
___________________________________________________________

TASK 34-52-33-000-001

Removal of the ATC/Mode S Transponder (1SH1, 1SH2)

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific blanking caps

No specific circuit breaker(s) safety clip(s)
No specific access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

34-52-33-991-001 Fig. 401

3. __________
Job Set-up

Subtask 34-52-33-865-050

A. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
FOR 1SH1
49VU NAV/ATC/1 5SH1 G11
FOR 1SH2
121VU COM NAV/ATC/2 5SH2 K07

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 Subtask 34-52-33-010-050

B. Get Access

(1) Put the access platform in position at the access door 824 in zone
128.

(2) Open the access door 824.

4. Procedure
_________

(Ref. Fig. 401/TASK 34-52-33-991-001)

Subtask 34-52-33-020-050

R A. Removal of the ATC/Mode S Transponder

(1) Loosen the nuts (4).

(2) Lower the nuts (4).

(3) Pull the ATC/Mode S transponder, on its rack (3) to disconnect the
electrical connectors (2).

(4) Remove the ATC/Mode S transponder (1) from its rack (3).

(5) Put blanking caps on the disconnected electrical connectors (2).

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 ATC/Mode S Transponder
Figure 401/TASK 34-52-33-991-001

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 TASK 34-52-33-400-001

Installation of the ATC/Mode S Transponder (1SH1,1SH2)

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

34-52-00-740-004 BITE Test of the ATC

R 52-41-00-410-002 Close the Avionics Compartment Doors after Access
34-52-33-991-001 Fig. 401

3. __________
Job Set-up

Subtask 34-52-33-860-050

A. Aircraft Maintenance Configuration

(1) Make sure that the access platform is in position at the access door
824 in zone 128.

(2) Make sure that the access door 824 is open.

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 Subtask 34-52-33-865-051

B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and
tagged

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
FOR 1SH1
49VU NAV/ATC/1 5SH1 G11
FOR 1SH2
121VU COM NAV/ATC/2 5SH2 K07

4. Procedure
_________

(Ref. Fig. 401/TASK 34-52-33-991-001)

Subtask 34-52-33-420-050

A. Installation of the ATC/Mode S Transponder.

(1) Clean the component interface and/or the adjacent area.

(2) Do an inspection of the component interface and/or the adjacent area.

(3) Remove the blanking caps from the electrical connectors (2).

(4) Make sure that the electrical connectors (2) are clean and in the
correct condition.

(5) Install the ATC/Mode S transponder (1) on its rack (3).

(6) Push the ATC/Mode S transponder (1) on its rack (3) to connect the
electrical connectors (2).

(7) Engage the nuts (4) on the lugs (5) and tighten.

Subtask 34-52-33-865-052

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
FOR 1SH1
5SH1
FOR 1SH2
5SH2

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 Subtask 34-52-33-740-050

C. Do the BITE test of the ATC (Ref. TASK 34-52-00-740-004).

5. Close-up
________

Subtask 34-52-33-860-051

A. Make sure that the work area is clean and clear of tool(s) and other
items.

Subtask 34-52-33-410-050

B. Close Access

R (1) Close the access door 824 (Ref. TASK 52-41-00-410-002).

(2) Remove the access platform(s).

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 ADF - DESCRIPTION AND OPERATION
_______________________________

1. _______
General
The Automatic Direction Finder (ADF) is a radio navigation aid which
provides :
- an indication of the relative bearing of the aircraft to a selected ground
station (150 to 1799 KHz)
- aural identification of the ground station.
The frequency range includes :
- the standard commercial broadcast AM stations (550 to 1610 KHz) located at
known co-ordinates around the world
- the Non-Directional Beacons (NDB) (190 to 550 KHz).

2. Component
__________________
Location
(Ref. Fig. 001)

-------------------------------------------------------------------------------
FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA
| | | | DOOR | REF.
-------------------------------------------------------------------------------
2RP1 RECEIVER-ADF, 1 81VU 127 824 34-53-31
2RP2 RECEIVER-ADF, 2 82VU 128 824 34-53-31
3RP1 ANTENNA-ADF LOOP AND SENSE, 1 244 34-53-11
3RP2 ANTENNA-ADF LOOP AND SENSE, 2 253 34-53-11

3. __________________
System Description

A. Principle
The principle of the ADF navigation is to determine the relative bearing
of a selected ground station.
This is obtained by the combination of :
- the signals from two loop and sense antennas positioned 90 deg. apart
with
- the signal from an omni-directional sense antenna. This signal is not
affected by the relative bearing.
An external 96Hz signal modulates the composite signal which is processed
in order to deliver the relative bearing.
An additional Morse signal is provided to identify the selected ground
station.

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 ADF - Component Location
Figure 001

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 B. System Architecture

R **ON A/C 001-004,

(Ref. Fig. 002)

**ON A/C ALL

R Post SB 34-1147 For A/C 001-004,

(Ref. Fig. 002A)

**ON A/C ALL

The ADF comprises two independent systems. Each system consists of :

- one receiver 2RP1 (2RP2)
- one loop and sense antenna 3RP1 (3RP2)
In addition, the components given after control the system :
(Ref. Fig. 003)
- the Radio Management Panel 1(2) (RMP) 1RG1 (1RG2)
- the CAPT (F/O) Audio Control Panel (ACP) 2RN1 (2RN2)
- the Multipurpose Control and Display Unit 1(2) (MCDU) 3CA1 (3CA2)
- the Flight Management and Guidance Computer 1(2) (FMGC) 1CA1 (1CA2)
- the Centralized Fault-Display Interface-Unit (CFDIU) 1TW
- the Audio Management Unit (AMU) 1RN.
The Navigation Displays (ND) show the ADF1 and ADF2 data.

C. Utilisation Technical Data

(1) Data Display

(Ref. Fig. 004)

(a) In ROSE and ARC modes

If you set the ADF/VOR/OFF switches on the EFIS control section
of the FCU to ADF, this causes : display of the characteristics
of the ADF 1 and/or 2 stations in the L and/or R lower corner of
the ND (item 3) :
- type of station
- shape of the associated bearing display
- station identification or frequency
- tuning mode (nothing : automatically tuned, M : manually tuned
and R : if tuned by the RMP).
A single pointer on the heading dial shows the bearing of the ADF
1, a double pointer that of the ADF 2 (item 2).
All these data are shown in green except the tuning mode which is
shown in white.

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 ADF - Block Diagram
Figure 002

R
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R ADF - Block Diagram
R Figure 002A

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 ADF - Control and Indicating
Figure 003

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 ADF - Data and Warning Displays
Figure 004

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 (b) In ROSE NAV and ARC modes
If you push the NDB pushbutton switch on the EFIS control section
of the FCU, triangle symbols show the ADF stations (item 1).

(c) In case of NCD, the station characteristics and associated

pointer(s) go out of view.

(d) In case of ADF 1 (2) fault, a red ADF warning message is shown in
place of the station characteristics.

(2) Audio control

(a) The ADF receiver applies its audio output to the audio
integrating system. This system controls and directs the output
to the headsets and/or the loud speakers.
The AMU controls the audio level through the ACP.
On the ACP, the pilot must push the ADF1 (ADF2) pushbutton switch
and adjust the related potentiometer to the correct audio level.

R (b) Only with NDB stations modulated in A1 mode (in automatic or

R manual mode) it is necessary to select the BFO function on the
MCDU in order to hear clearly its Morse identification signal.

(c) In emergency mode, the BFO function is selected on the RMP when :
- you push the STBY NAV/ADF pushbutton switch
- you push the STBY NAV/BFO pushbutton switch.

(d) It is possible to select the broadcast station on the RMP and the
MCDU (manual mode only). In this case, the BFO selection is not
necessary.

(e) With the ATIS message trasmission by the NDB station, with the
BFO active : it is necessary to push the ON VOICE pushbutton
switch on one ACP in order to hear clearly this information
without Morse signal.

D. Warning
(Ref. Fig. 004)
The warnings related to the ADF are only the local warnings shown on the
NDs.
The warnings are detected by the BITE function of the receiver.

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 4. ____________
Power Supply

R **ON A/C 001-004,

(Ref. Fig. 002)

**ON A/C ALL

R Post SB 34-1147 For A/C 001-004,

(Ref. Fig. 002A)

**ON A/C ALL

Energization of the system is through 115VAC 400 Hz buses :

- 115VAC SHED ESS BUS 801XP via circuit breaker 1RP1
- 115VAC BUS 2 202XP via circuit breaker 1RP2

5. _____________________
Component Description

A. ADF Receiver

(1) Characteristics
- Frequency range : 190 to 1799 KHz in 0.5 KHz steps
- Electrical power supply: 115VAC, 400 Hz, 45 VA
- Tuning accuracy: selected frequency plus or minus 250 Hz
- ADF accuracy: plus or minus 2 deg.
- Sensivity: 30 % modulation
- ADF mode: 50 microV/m field strength at 400 Hz for 6 dB signal to
noise ratio.

(2) External description

The ADF receiver conforms with the ARINC specification 600.
The case size is 2MCU.

(a) Receiver face

(Ref. Fig. 005)
The face of the receiver is fitted with a handle, one lug, a TEST
pushbutton switch and two LEDs.
The name, color and function of the two LEDs are as follows:
- LRU STATUS (red): indicates that a malfunction is detected
during the self test of the ADF receiver.
- LRU STATUS (green): indicates that no faults are detected
during the self test of the ADF receiver.
- CONTROL FAIL (red): indicates that an ARINC input data is
faulty.
The back is equipped with one ARINC 600 size one connector which
includes three plugs:
- Top Plug (TP): connection with the automatic test circuit

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 ADF - Receiver
Figure 005

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 - Middle Plug (MP): connection with the antenna and peripheral
circuits
- Bottom Plug (BP): connection with the power supply circuit.
Index pin code is 05.

(3) Internal description

The receiver determines the relative bearing to any selected
transmitter operating between 190 and 1799 KHz. This bearing data is
converted into ARINC 429 format and transmitted through ARINC buses
to the NDs via the DMCs. In addition the AM modulation of the carrier
wave is detected and applied to the audio integrating system. The
receiver is housed in an ARINC 2MCU case and consists of the
following interconnected assemblies:

(a) An ARINC interconnect assembly which provides filtering against

HIRF and noise entry or exit.

(b) A digital instrumentation assembly which contains the system

processor and signal processor:

1
_ The function of the system processor is to:
- format the ADF data from the signal processor into an ARINC
429 bearing word
- provide frequency tuning for the ADF receiver
- perform functional test and self-test functions
- provide diagnostic data to the maintenance processor
- transmit data generated by the system processor and
maintenance processor
- store calibration constants (as received from the signal
processor) in the system processor Non-Volatile Memory
during the calibration mode
- monitor the power-down warning signal from the power supply
to provide warm start capability
- monitor system voltages and discretes for fault conditions.

2
_ The function of the signal processor is to:
- compute and output, to the system processor, the ADF bearing
derived from the ADF detector
- determine the presence of the ADF detector signal and flag
the bearing data accordingly
- detect the presence of a 400Hz or 1020Hz identification tone
(or BFO mode) and output a Wtone presentW discrete to the
maintenance processor
- monitor ADF signal level status and output maintenance data
to the system processor
- output sin mode and cosine mode to the loop modulators via
their respective D/A converters

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 - process the ADF detector signal to provide filtered and
amplitude controlled audio information to the aircraft audio
system.

(c) A maintenance processor assembly the primary function of which is

the logging of maintenance information and secondarily, decoding
the morse binary data stream into ASCII characters.

(d) A power supply assembly which provides +12VDC, -12VDC and -5VDC
from 115VAC at 400Hz.

(e) A tuner/synthesizer assembly

1
_ The tuner combines the sense and loop signals from the
antenna, amplifies and filters them and then provides the
detected audio information to the signal processor.

2
_ The synthesizer receives frequency information from the system
processor and provides fixed and variable oscillator signals
for the mixers in the tuner.

(4) Operation
(Ref. Fig. 006)
The operation of the receiver is initiated when the desired frequency
is selected by the FMGCs or RMPs.
Frequency and function data are received via an interface.
This data is used to activate the desired function, set the receive
band and tune a Voltage Controlled Oscillator (VCO) for converting
the received signal to the IF.
Sense and loop signals from the antenna are applied to the loop
modulators where they are modulated with 95Hz control signals from
the signal processor. The summed output of the loops is corrected for
the antenna loop gain and phase and then summed with the sense
channel.
The composite output of the summing circuit is passed through a band
select filter, which output feeds the first mixer.

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 ADF Receiver - Simplified Block Diagram
Figure 006

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 The VCO is mixed with the input to generate a first IF of 15MHz. The
signal is filtered and amplified and then applied to the second mixer
where 18.6MHz mixes it down to a second IF of 3.6Mhz. It is once
again filtered and amplified before application to a coherent
detector. The output of the coherent detector is used to derive the
AGC control for the IF. The composite audio is sampled and processed
by audio and bearing algorithms in a Digital Signal Processor (DSP)
in the signal processor area. The DSP filters the audio, and sets the
output level and returns it to an audio amplifier stage, and then to
the aircraft audio system. The DSP also applies a separate narrow
audio filter and then detects the audio tone for MORSE ident. This
binary data stream is sent to the maintenance processor for decoding
into ASCII characters.
The bearing is determined in the null-seeking algorithm by the DSP
continuously adjusting the ratio of the 95Hz loop modulation applied
to the sine and cosine modulators. When the ratio is properly
adjusted, the amount of 95Hz present in the coherent detector output
is minimized. The ratio of the loop modulation is then directly
proportional to the raw bearing. The raw bearing is corrected for
Quandrantal Error and calibration factors.
The signal processor then converts this corrected bearing to ARINC
word format and relays it to the system processor for transmission on
the ARINC bus.
In addition to its receiver control functions, the system processor
continuously monitors receiver health and passes radio health
information to the maintenance processor. It also initiates
functional tests when conditions allow it.
The maintenance processor processes commands from the CFDIU and
stores faults detected by the system processor. It also decodes the
MORSE ident data stream passed by the signal processor.

(5) Digital outputs

This table contains all the output parameters in the digital form.
They are sorted as per the numerical order of their output label.
The following table gives :
- EQ.SYS.LAB.SDI: (SDAC, FWC, DMC...) output label for which the
parameter is available
- PARAMETER DEFINITION: parameter name
- WORD RANGE OPER RANGE RESOLUTION ACCURACY: measurement range.
Maximum value transmitted. When the digital value changes, the
change step is equal to the accuracy
- UNIT: unit in which the digital value is transmitted
- SIG BIT: indicates whether a sign bit is available
- BITS: number of bits used by the parameter in the label
- XMSN/INTV: output transmission interval. The refresh rate is given
in milliseconds
- CODE :

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 BNR: binary data word
BCD: binary coded decimal data word
ISO: data word coded in ISO5 code
DIS: discrete data word
HEX: hexadecimal coded
HYB: mixed code
- ALPHA CODE: indicates the parameter mnemonic code
- SOURCE ORIGIN: parameter source computer or system.

-------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
| .032. |ADF 1 |FROM 190 |KHZ | | | 200|BCD | | |
| |FREQUENCY |TO 1799 | | | | | | | |
| | | | | | | | | | |
| |ADF 2 | | | | | | | | |
| |FREQUENCY | | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| .162. |ADF 1 |-180 TO |DEG | | |62.5|BNR | | |
| |BEARING |+180 | | | | | | | |
| | | | | | | | | | |
| |ADF 2 | | | | | | | | |
| |BEARING | | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| .254. |ADF 1 | | | | |250 |HYB | | |
| |IDENTIFIER| | | | | | | | |
| |WORD 1 | | | | | | | | |
| | | | | | | | | | |
| .254. |ADF 2 | | | | |250 |HYB | | |
| |IDENTIFIER| | | | | | | | |
| |WORD 1 | | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| .255. |ADF 1 | | | | |250 |HYB | | |
| |IDENTIFIER| | | | | | | | |
| |WORD 2 | | | | | | | | |
| | | | | | | | | | |
| .255. |ADF 2 | | | | |250 |HYB | | |
| |IDENTIFIER| | | | | | | | |
| |WORD 2 | | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| .377. |EQUIPMENT | | | | |1000|BCD | | |

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 -------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
| |IDENTIFIER| | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| .356. |MAINTENAN-| | | | | 250|ISO | | |
| |CE STATUS | | | | | | | | |
| |WORD 2 | | | | | | | | |
-------------------------------------------------------------------------------

B. Loop and Sense Antenna

(Ref. Fig. 007)
The combined loop and sense antenna operates in the 190 to 1750 kHz
frequency range and consists of the following components enclosed in a
fiberglass housing:
- a vertically polarized sense antenna which is omnidirectional in the
horizontal plane
- two horizontally polarized orthogonal loop antennas which are
directional in the horizontal plane
- a test loop which enables a self-test of the antenna
- a printed circuit board which contains three pre-amplifiers used to
amplify the loop and sense antennas signals. The pre-amplifiers are
energized by plus or minus 12VDC form the ADF receiver.
The output impedance of the antenna is 78 Ohms and the Voltage Standing
Wave Ratio (VSWR) 1.2:1.

6. Operation
_________

R **ON A/C 001-004,

(Ref. Fig. 002)

**ON A/C ALL

R Post SB 34-1147 For A/C 001-004,

(Ref. Fig. 002A)

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 ADF - Antenna
Figure 007

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 **ON A/C ALL

NOTE : The two ADF systems are independent. The operating mode is identical
____
for ADF 1 and ADF 2.
- The FMGC 1 sends a management bus to the ADF receiver 1 through the
RMP1.
- In normal operation, the FMGC 1 tunes the ADF receiver 1 either
automatically or manually by means of the MCDU. In this case, the
RMP 1 operates as a relay which sends the frequency information
from the FMGC 1 to the ADF receiver 1.
- By a second port, the ADF receiver 1 receives a second management
bus directly from the FMGC 2. The FMGC 2 becomes active when the
ADF receiver 1 receives a failure signal from the FMGC 1.
- With RMP 1 internal failures the RMP 1 is transparent to data and
discrete from the FMGC 1.
- In emergency configuration (failure of the FMGC 1 and 2), the RMP 1
can control the ADF receiver 1 after ON NAV mode selection.
- In emergency configuration (failure of the FMGC 1 and 2), the RMP 2
can control the ADF receiver 2 after on NAV mode selection.
(Ref. Fig. 008)

7. Test
____

A. Maintenance Test
(Ref. Fig. 009)
It is possible to do the maintenance tests with the Centralized Fault
Display System (CFDS).
The primary components of the CFDS are :
- the MCDU
- the CFDIU
- the Built-In Test Equipment (BITE) internal to the ADF receiver.
It is possible to perform these tests on the ground only.
The access to the ADF 1 (2) menu is through :
- selection of the SYSTEM REPORT/TEST item on the CFDS menu
- then, selection of the relevant ADF on the NAV menu.
The test sequence starts when you push the line key adjacent to the TEST
indication on the ADF1(2) menu.

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 ADF - Frequency Selection in Emergency Mode
Figure 008

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 ADF - Maintenance Test Procedure
Figure 009

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R **ON A/C 001-004,

B. Power-up Tests Initialization and Cockpit Repercussions

(1) Conditions of power-up tests initialization

- How long the computer must be de-energized: 2 s.
- A/C configuration:
- whatever the A/C configuration on ground

(2) Progress of power-up tests

(a) Duration: 2 s.

(b) Cockpit repercussions directly linked to power-up test

accomplishment (some other repercussions may occur depending on
the A/C configuration but these can be disregarded):
- if ADF selected on FCU
- ND
ADF 1 or 2 in red
- if ADF RMI option available
- ADF RMI display
ADF flag during 2 s.

(3) Results of power-up tests

(cockpit repercussions, if any, in case of tests pass/tests failed).

(a) Tests pass:

- if ADF selected on FCU
- ND
ADF 1 or 2 in green
- if ADF RMI option available
- ADF RMI display
ADF flag no longer displayed

(b) Tests failed:

- if ADF selected on FCU
- ND
ADF 1 or 2 red indications flash
- if ADF RMI option available
- ADF RMI display
ADF flag

R **ON A/C ALL

C. CFDIU Interface

R **ON A/C 001-004,

(Ref. Fig. 002)

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 **ON A/C ALL

R Post SB 34-1147 For A/C 001-004,

(Ref. Fig. 002A)

**ON A/C ALL

(1) BITE description

The BITE facilitates maintenance on in-service aircraft.
It detects and identifies a failure related to the ADF system.
The BITE of the ADF receiver is connected to the CFDIU (Ref.
31-32-00).
The unit tested is the ADF receiver.
The BITE:
- transmits continuously ADF system status and its identification
message to the CFDIU
- memorizes the failures which occurred during the last 63 flight
segments
- monitors data inputs from the various peripherals (RMP and CFDIU)
- transmits to the CFDIU the result of the tests performed and
self-tests
- can communicate with the CFDIU through the menus.
The BITE can operate in two modes:
- the normal mode
- the menu mode.

(a) Normal mode

During the normal mode the BITE monitors cyclically the status of
the ADF system. It transmits its information to the CFDIU during
the concerned flight.
In case of fault detection the BITE stores the information in the
fault memories.
These items of information are transmitted to the CFDIU every 50
- 250 ms by an ARINC 429 message with label 356.

(b) Menu mode:

The menu mode can only be activated on the ground.
This mode enables communication between the CFDIU and the ADF
receiver BITE by means of the MCDU.
The ADF menu mode is composed of:
- LAST LEG REPORT
- PREVIOUS LEGS REPORT
- LRU IDENTIFICATION
- GROUND SCANNING
- TROUBLE SHOOTING DATA
- CLASS 3 FAULTS
- GROUND REPORT
- TEST.

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 (2) Interactive function
The interactive mode can be activated on the ground only, using the
line key adjacent to the ADF 1 (or 2) indication on the SYSTEM
REPORT/TEST page of any MCDU (Ref. 22-82-00).
This mode enables communication between the CFDIU and the BITE of the
ADF receiver by means of the MCDU.
(Ref. Fig. 009)
The interactive mode is composed of:
- LAST LEG REPORT:
This report contains the fault messages related to the external or
internal failures (class 1 and 2) recorded during the last flight
leg.
(Ref. Fig. 010)
- PREVIOUS LEGS REPORT:
This report contains the fault messages related to the external or
internal failures (class 1 and 2) recorded during the previous 63
flight legs.
(Ref. Fig. 010)
- LRU IDENTIFICATION:
Allows to display the P/N and the S/N of the equipment.
(Ref. Fig. 010)
- GROUND SCANNING:
(Ref. Fig. 011)
Based on the monitoring and fault analysis during flight, provides
information of the failures detected while using this function.
By pressing the line key adjacent to the failure message, the
operator is allowed to the corresponding Trouble Shooting Data. The
peripheral monitoring and ADF internal cyclic tests are used to
detect transient failures.
- TROUBLE SHOOTING DATA
(Ref. Fig. 011)
Provides correlation parameters and snapshot data concerning the
failure displayed in the LAST LEG REPORT and PREVIOUS LEGS REPORT.
- CLASS 3 FAULTS
(Ref. Fig. 012)
Allows to display the class 3 faults recorded during the last
flight leg.
- GROUND REPORT
(Ref. Fig. 012)
Allows to present the class 1, 2 or 3 internal failures detected on
ground.
These failures differ from those displayed on the LAST LEG REPORT
and CLASS 3 FAULTS.
By pressing the line key adjacent to the failure message, the
operator is allowed to access to the corresponding Trouble Shooting
Data.
- TEST

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 ADF - Last Leg Report, Previous Legs Report and LRU IDENT
Figure 010

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 ADF - GROUND SCANNING and Trouble Shooting Data
Figure 011

R
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 ADF - CLASS 3 FAULTS and Ground Report
Figure 012

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 (Ref. Fig. 013)
Allows a check of the correct operation of the ADF on the ground.
This test can be performed by:
- either selecting the test function on the face of the ADF receiver
by pressing the TEST pushbutton switch
- or through the Centralized Fault Display System (CFDS) by
selecting, on the MCDU, the test function on the ADF 1 (or 2) main
menu page.
All the information displayed on the MCDU during the BITE TEST
configuration can be printed by the printer (Ref. 31-35-00).

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 ADF - TEST
Figure 013 (SHEET 1)

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 ADF - TEST
Figure 013 (SHEET 2)

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 ADF - ADJUSTMENT/TEST
_____________________

TASK 34-53-00-740-003

BITE Test of the ADF

WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE
_______
YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
31-32-00-860-010 Procedure to Get Access to the SYSTEM REPORT/TEST NAV
Page
34-10-00-860-002 ADIRS Start Procedure
34-10-00-860-004 IR Alignment Procedure
34-10-00-860-005 ADIRS Stop Procedure
34-53-00-991-002 Fig. 501

3. __________
Job Set-up

Subtask 34-53-00-860-053

A. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-

002).

(2) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002).

(3) Do the IR alignment procedure

(Ref. TASK 34-10-00-860-004).

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 (4) On the EFIS control sections of the FCU:
- set the ADF/VOR selector switches to ADF
- set the mode selector switches to ROSE/NAV.

(5) On the center pedestal, on the MCDU:

- get the SYSTEM REPORT/TEST/NAV page
(Ref. TASK 31-32-00-860-010)
- push the NEXT PAGE function key.

(6) On the center pedestal, on the RMP1 (RMP2):

- set the ON/OFF switch to ON
- push the NAV pushbutton switch (the green LED on this pushbutton
switch comes on)
- set a non local ADF1 and ADF2 station (greater than 750 KHz).
(Ref. Fig. 501/TASK 34-53-00-991-002)

Subtask 34-53-00-865-055

B. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV/VOR/DME/RMI 12FN F13
49VU NAV/ADF/1 1RP1 H14
R
121VU COM NAV/ADF/2 1RP2 K02

4. Procedure
_________

Subtask 34-53-00-740-050-A

A. BITE Test of the ADF

NOTE : During the BITE TEST (ADF1 or 2) by the MCDU, the indications
____
related to the two receivers (Capt and F/O) are shown at the same
time.This has no effect on the test or component.

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 ADF-Frequency Selection
Figure 501/TASK 34-53-00-991-002

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R -------------------------------------------------------------------------------
R ACTION RESULT
R -------------------------------------------------------------------------------

R 1. On the MCDU: On the MCDU:

R - push the line key adjacent to - the ADF1 (ADF2) page comes into view.
R the ADF1 (ADF2) indication.

R - push the line key adjacent to - the INITIAL CONDITIONS are shown
R the TEST indication. (page 1 to 3).

R - push the line key adjacent to - the TEST IN PROGRESS 4S indication

R the START TEST indication. comes into view.

R From 0 to 6s:
R - On the CAPT and F/O NDs:
R * the ADF1 (ADF2) pointer dissapears.
R * the RED ADF1 (ADF2) warning message
R comes into view.

R From 6 to 13s:
R - On the CAPT and F/O NDs:
R * the ADF1 (ADF2) pointer comes into
R view, moves to a relative bearing of
R 135⁰.

R On the MCDU: On the MCDU:

R - push the line key adjacent to the TEST OK indication comes into view.
R the YES indication.

R - push the line key adjacent to The test procedure stops.

R the RETURN indication.

5. Close-up
________

Subtask 34-53-00-860-054

A. Put the aircraft back to its initial configuration.

(1) On the EFIS control sections of the FCU, set the ADF/VOR selector
switches to OFF.

(2) Do the ADIRS STOP procedure (Ref. TASK 34-10-00-860-005)

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 (3) On the center pedestal, on the RMP:
- push the NAV pushbutton switch (the green LED on this pushbutton
switch goes off).
- set the ON/OFF switch to OFF.

(4) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

(5) Make sure that the work area is clean and clear of tool(s) and other
items.

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 TASK 34-53-00-710-002

Operational Test of the ADF

WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE
_______
YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.

1. __________________
Reason for the Job

Test of ADF Identification and Reception

2. ______________________
Job Set-up Information

A. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
34-10-00-860-002 ADIRS Start Procedure
34-10-00-860-004 IR Alignment Procedure
34-10-00-860-005 ADIRS Stop Procedure
34-53-00-991-002 Fig. 501

3. __________
Job Set-up

Subtask 34-53-00-860-051

A. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-

002).

(2) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002).

(3) Do the IR alignment procedure

(Ref. TASK 34-10-00-860-004).

(4) On the EFIS control sections of the FCU:

- set the ADF/VOR selector switches to ADF
- set the mode selector switches to ROSE/NAV.

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 (5) On the center pedestal, on the RMP1 (RMP2):
- set the ON/OFF switch to ON.
- push the NAV pushbutton switch (the green LED on this pushbutton
switch comes on).

Subtask 34-53-00-865-054

B. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV/ADF/1 1RP1 H14

4. Procedure
_________

Subtask 34-53-00-710-056

A. Operational Test of the ADF

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the center pedestal, on one

ACP:
- push the ADF1 (ADF2) pushbutton
switch.

2. On the RMP1 (RMP2):

- set the ON/OFF selector switch
to ON

- set an ADF local frequency . On the CAPT and F/O NDs:

(Ref. Fig. 501/TASK 34-53-00-
991-002)
- the ADF1 (ADF2) pointer moves and
shows the station direction.
- the station identification or
frequency comes into view in the left
lower corner.
R

In the loudspeakers:
- if the station set is a A1 station,
you cannot hear the identification
signal. Do step 3

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
- if the station set is a A2 station,
you can hear the identification
signal. Go to step 4
R

R 3. On the RMP1 (RMP2):

- set the BF0 function. In the loudspeakers, you can hear the
(Ref. Fig. 501/TASK 34-53-00-
991-002)
identification signal but it is weaker.
R

R 4. On the RMP1 (RMP2):

- set a non local ADF station. On the CAPT and F/O NDs, the ADF1
(Ref. Fig. 501/TASK 34-53-00-
991-002)
(ADF2) pointer goes out of view.

In the loudspeakers, no signal is

heard.

5. Close-up
________

Subtask 34-53-00-860-052

A. Put the aircraft back to its initial configuration.

(1) On the EFIS control sections of the FCU, set the ADF/VOR selector
switches to OFF.

(2) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005).

(3) On the center pedestal, on the RMP:

- push the NAV pushbutton switch (the green LED on this pushbutton
switch goes off)
- set the ON/OFF switch to OFF.

(4) On the center pedestal, on the ACP, release the ADF1 (ADF2)
pushbutton switch.

(5) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002).

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 (6) Make sure that the work area is clean and clear of tool(s) and other
items.

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 ANTENNA - ADF LOOP AND SENSE (3RP1,3RP2) - REMOVAL/INSTALLATION
_______________________________________________________________

TASK 34-53-11-000-001

Removal of the ADF Loop and Sense Antenna

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific blanking caps

No specific circuit breaker(s) safety clip(s)
No specific masking tape
No specific nonmetallic scraper
No specific access platform 6.0 m (19 ft. 8 in.)

B. Consumable Materials

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

Material No. 11-010 USA TT-I-735 GRADE A

ISOPROPYL ALCOHOL (Ref. 20-31-00)

C. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-42-00-861-001 Energize the Ground Service Network from the External

Power
34-53-11-991-001 Fig. 401

3. __________
Job Set-up

Subtask 34-53-11-861-050

A. Energize the ground service network

(Ref. TASK 24-42-00-861-001).

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 Subtask 34-53-11-865-050

B. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV/ADF/1 1RP1 H14
R
121VU COM NAV/ADF/2 1RP2 K02

4. Procedure
_________

(Ref. Fig. 401/TASK 34-53-11-991-001)

Subtask 34-53-11-010-050

A. Get Access

(1) Put the access platform in position.

(2) Safety Precautions

WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL

_______
MATERIALS ONLY WITH A GOOD SUPPLY OF AIR.
OBEY THE MANUFACTURERS INSTRUCTIONS.
PUT ON PROTECTIVE CLOTHING.
DO NOT GET THEM IN YOUR MOUTH.
DO NOT SMOKE.
DO NOT BREATHE THE GAS.
THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT.
GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED.

Subtask 34-53-11-020-051

B. Removal of the ADF Loop and Sense Antenna

(1) Remove the bolts (1) from the antenna (2).

(2) Lift the antenna (2) until you can see the coaxial cable connector
(5).

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 ADF Loop and Sense Antennas.
Figure 401/TASK 34-53-11-991-001

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 (3) Disconnect the coaxial cable connector (5) from the antenna
connector.

NOTE : The coaxial cable (6) must not go into the fuselage.
____

(4) Remove and discard the O-ring (3).

(5) Remove the antenna (2) and the gasket (4).

(6) Put blanking caps on the disconnected electrical connectors.

(7) Put masking tape around the coaxial cable (6) and attach it to the
fuselage.

(8) Remove the sealant with a nonmetallic scraper and clean the fuselage
R structure with the CLEANING AGENTS (Material No. 11-010).

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 TASK 34-53-11-400-001

Installation of the ADF Loop and Sense Antenna

WARNING : IF YOU GET THE FLUID ON YOUR SKIN OR IN YOUR EYES:

_______
- FLUSH IT AWAY WITH CLEAN WATER
- GET MEDICAL AID.

WARNING : DO NOT GET THE COMPOUND ON YOUR SKIN.

_______
IF YOU DO:
- RUB IT OFF IMMEDIATELY WITH A CLEAN CLOTH
- WASH THE SKIN WITH SOAP AND RINSE WITH CLEAN WATER.

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific lint free cloth

No specific access platform 6.0 m (19 ft. 8 in.)

B. Consumable Materials

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

Material No. 07-001

ELECTRICAL BONDING COATING (BLUE COLOR)
(Ref. 20-31-00)
Material No. 09-008 USA MIL-S-8802 CLASS A
EARLY QUICK REPAIR FUEL TANK SEALANT (Ref. 20-31-00)
R Material No. 09-016 USA MIL-PRF-81733D TYPE II CLASS B
CORROSION INHIBITING FILLET CONSISTENCY
(Ref. 20-31-00)
Material No. 11-004 USA MIL-T-81533
1.1.1TRICHLOROETHANE (METHYL CHLOROFORM)
(Ref. 20-31-00)
Material No. 16-021 F ASNB70720
FLEXIBLE POLYURETHANE (Ref. 20-31-00)

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 -------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

Material No. 19-002 USA MIL-T-713

SYNTHETIC FIBRE CORD (NYLON) 2.5MM DIA.
(Ref. 20-31-00)

C. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

20-28-00-912-005 Electrical Bonding of Antennas With Conductive Bolts.

24-42-00-861-001 Energize the Ground Service Network from the External
Power
24-42-00-862-001 De-energize the Ground Service Network Supplied from
the External Power
34-53-00-710-002 Operational Test of the ADF
R 51-76-11-300-001 Repair of the Sealing
34-53-11-991-001 Fig. 401

3. __________
Job Set-up

Subtask 34-53-11-860-050

A. Aircraft Maintenance Configuration

(1) Make sure that the ground service network is energized

(Ref. TASK 24-42-00-861-001).

(2) Make sure that the access platform is in position.

(3) Make sure that the aircraft is in the same configuration as for the
removal task.

(4) Make sure that the parts retained from the removed component are
clean and in the correct condition.

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 4. Procedure
_________

(Ref. Fig. 401/TASK 34-53-11-991-001)

Subtask 34-53-11-420-051

A. Installation of the ADF Loop and Sense Antenna

WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL

_______
MATERIALS ONLY WITH A GOOD SUPPLY OF AIR.
OBEY THE MANUFACTURERS INSTRUCTIONS.
PUT ON PROTECTIVE CLOTHING.
DO NOT GET THEM IN YOUR MOUTH.
DO NOT SMOKE.
DO NOT BREATHE THE GAS.
THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT.
GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED.

WARNING : OBEY THE MANUFACTURER<S INSTRUCTIONS WHEN YOU USE THE SPECIAL
_______
MATERIAL.
THIS MATERIAL IS DANGEROUS.

(1) Clean the component interface and/or the adjacent area with CLEANING
AGENTS (Material No. 11-004) and lint free cloth.

(2) Do an inspection of the component interface and/or the adjacent area.

(3) Remove the blanking caps from the electrical connectors.

(4) Make sure that the electrical connectors are clean and in the correct
condition.

(5) Put the new o-ring (3) in the correct position on the antenna.

(6) Put the new gasket (4) on the fuselage and align the bolts hole.

(7) Remove the masking tape from the coaxial cable (6) and connect the
cable connector (5) to the antenna connector.

(8) Install the antenna (2) ) to the fuselage structure with the bolts
(1).
R

NOTE : Make sure that the bolts (1) are tightened in sequence.
____

NOTE : The antenna mounting bolts (1) and the holes (8) provide the
____
electrical bonding.

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 (9) Make sure that the bonding contact resistance between the antenna (2)
and the fuselage structure is not higher than 5 milliohms (Ref. TASK
20-28-00-912-005).

R (10) Apply a bead of SEALANTS (Material No. 09-016) (7) or use as an

R alternative SEALANTS (Material No. 09-008) around the antenna (2)
R (Ref. TASK 51-76-11-300-001) and the fuselage.
R

R (11) Fill the recess of the bolts (1) with MISCELLANEOUS (Material No. 19-
R 002) and SEALANTS (Material No. 09-016) or as an alternative SEALANTS
R (Material No. 09-008).
R

R (12) Make the contour of the sealant on the bolts (1) and around the
R antenna (2) smooth.

R (13) Let the sealant cure.

R (14) Apply STRUCTURE PAINTS (Material No. 16-021) to the sealant around
R the base of the antenna (2).

R (15) Apply PAINTS FOR DETAIL (INTERNAL AND EXTERN AL) (Material No. 07-
R 001) to the sealant on the head of the bolts (1).

Subtask 34-53-11-865-052

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
1RP1, 1RP2

Subtask 34-53-11-710-050

C. Do the operational test of the ADF system (Ref. TASK 34-53-00-710-002).

5. Close-up
________

Subtask 34-53-11-410-052

A. Close Access

(1) Make sure that the work area is clean and clear of tool(s) and other
items.

(2) Remove the access platform(s).

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 Subtask 34-53-11-862-050

B. De-energize the ground service network

(Ref. TASK 24-42-00-862-001).

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 RECEIVER - ADF (2RP1,2RP2) - REMOVAL/INSTALLATION
_________________________________________________

TASK 34-53-31-000-002

Removal of the ADF Receiver (2RP1, 2RP2)

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific blanking caps

No specific circuit breaker(s) safety clip(s)
No specific access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

34-53-31-991-001 Fig. 401

3. __________
Job Set-up

Subtask 34-53-31-865-052

A. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV/ADF/1 1RP1 H14
R
121VU COM NAV/ADF/2 1RP2 K02

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R

Subtask 34-53-31-010-050

B. Get Access

(1) Put the access platform in position at the access door 824 in zone
128.

(2) Open the access door 824.

4. Procedure
_________

(Ref. Fig. 401/TASK 34-53-31-991-001)

Subtask 34-53-31-020-050

A. Removal of the ADF Receiver

(1) Loosen the nut (4).

(2) Lower the nut (4).

(3) Pull the ADF receiver (1) on its rack (3) to disconnect the
electrical connectors (2).

(4) Remove the ADF receiver (1) from its rack (3).

(5) Put blanking caps on the disconnected electrical connectors (2).

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 ADF Receivers
Figure 401/TASK 34-53-31-991-001

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 TASK 34-53-31-400-002

Installation of the ADF Receiver (2RP1, 2RP2)

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

34-53-00-740-003 BITE Test of the ADF

R 52-41-00-410-002 Close the Avionics Compartment Doors after Access
34-53-31-991-001 Fig. 401

3. __________
Job Set-up

Subtask 34-53-31-860-050

A. Aircraft Maintenance Configuration

(1) Make sure that the access platform is in position at the access door
824 in zone 128.

(2) Make sure that the access door 824 is open.

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 Subtask 34-53-31-865-053

B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and
tagged

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV/ADF/1 1RP1 H14
R
121VU COM NAV/ADF/2 1RP2 K02

4. Procedure
_________

Subtask 34-53-31-420-050

A. Installation of the ADF Receiver

(1) Clean the component interface and/or the adjacent area.

(2) Do an inspection of the component interface and/or the adjacent area.

(3) Remove the blanking caps from the electrical connectors (2).

(4) Make sure that the electrical connectors (2) are clean and in the
correct condition.

(5) Install the ADF Receiver (1) on its rack (3).

(6) Push the ADF Receiver (1) on its rack (3) to connect the electrical
connectors (2).

(7) Engage the nut (4) and the lug (5) and tighten.

Subtask 34-53-31-865-054

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
1RP1, 1RP2

Subtask 34-53-31-740-050

C. Do the BITE test of the ADF (Ref. TASK 34-53-00-740-003).

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 5. Close-up
________

(Ref. Fig. 401/TASK 34-53-31-991-001)

Subtask 34-53-31-410-050

A. Close Access

(1) Make sure that the work area is clean and clear of tool(s) and other
items.

(2) Close the access door 824 (Ref. TASK 52-41-00-410-002).

(3) Remove the access platform(s).

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 VOR/MARKER - DESCRIPTION AND OPERATION
______________________________________

R **ON A/C 001-004,

1. General
_______

A. Foreword
The VOR/MARKER comprises two independent systems in a same receiver :
- a VOR system for the radio navigation phase
- a MARKER (MKR) system for the landing approach phase.
The two VOR/MKR receivers are interchangeable but only one marker system
is installed on the aircraft.

B. VOR System
The VOR system is a radio aid to medium-range navigation.
The aircraft is equipped with two VOR systems which can accept ground
station signals in the frequency range of 108 MHz to 117.95 MHz.
These signals are processed and conditioned to provide the crew with :
- identification of a selected ground station
- indication of the aircraft position with respect to the station
(bearing information)
- indication of the aircraft angular deviation from a selected course.

C. MARKER System
The marker system is a radio navigation aid. It is normally used together
with the Instrument Landing System (ILS) during an ILS approach. The
system determines the distance between the aircraft and the runway
threshold. The marker system also marks particular airway and holding
points.
The system provides visual and aural indications of the passage of the
aircraft over the marker transmitters located on the ground.

**ON A/C ALL

R Post SB 34-1147 For A/C 001-004,

1. General
_______

A. Foreword
The VOR/MARKER comprises two independent systems in a same receiver:
- a VOR system for the radio navigation phase,
- a MARKER (MKR) system for the landing approach phase.
The two VOR/MKR receivers are interchangeable but only one marker system
is installed on the aircraft.

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R B. VOR System
R The VOR system is a radio aid to medium-range navigation.
R The aircraft is equipped with two VOR systems which can accept ground
R station signals in the frequency range of 108 MHz to 117.95 MHz.
R These signals are processed and conditioned to provide the crew with:
R - identification of a selected ground station,
R - indication of the aircraft position with respect to the station
R (bearing information),
R - indication of the aircraft angular deviation from a selected course.

R C. MARKER System
R The marker system is a radio navigation aid. It is normally used together
R with the Instrument Landing System (ILS) portion of the Multi-Mode
R Receiver (MMR) during an ILS approach. The system determines the distance
R between the aircraft and the runway threshold. The marker system also
R marks particular airway and holding points.
R The system provides visual and aural indications of the passage of the
R aircraft over the marker transmitters located on the ground.

R **ON A/C ALL

2. Component
__________________
Location
(Ref. Fig. 001)

-------------------------------------------------------------------------------
FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA
| | | | DOOR | REF.
-------------------------------------------------------------------------------
1RS ANTENNA-MARKER 133 34-55-18
3RS1 RECEIVER-VOR/MKR, 1 81VU 127 824 34-55-31
3RS2 RECEIVER-VOR/MKR, 2 82VU 128 824 34-55-31
4RS ANTENNA-VOR 1/2 324 324AT 34-55-11

3. __________________
System Description

A. Principle

(1) VOR system

The principle of the VOR navigation is a comparison between a
reference phase signal and a variable phase signal. The ground
station generates these two signals. The phase difference between the
reference and the variable phase is a function of the position of the
aircraft with respect to the ground station.
Furthermore, the ground station provides a Morse identification.

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 VOR/Marker - Component Location
Figure 001

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 (2) Marker system
There are three marker transmitters positioned on the ground at known
distances from the runway threshold :
- the outer marker at approx. 4 N miles
- the middle marker at 0.6 N miles
- the inner marker at the runway threshold.
The markers transmit a modulated 75 MHz signal to provide a marker
position.
When the aircraft passes through the beam of a marker, the modulating
frequency is detected. Then, the system provides aural and visual
indications to the flight crew.

B. System Architecture
(Ref. Fig. 002)

(1) VOR system

The VOR system comprises two independent systems. Each system
consists of :
- one VOR/MKR receiver 1(2) 3RS1 (3RS2)
- one VOR 1/2 antenna 4RS
- one VOR/DME Radio Magnetic Indicator (VOR/DME RMI) 11FN.
The components given after control the VOR system:
(Ref. Fig. 003)
- the CAPT (F/O) Audio Control Panel (ACP) 2RN1 (2RN2) and the Audio
Management Unit (AMU) 1RN for audio control
- the Multipurpose Control and Display Unit 1(2) (MCDU) 3CA1 (3CA2),
the Radio Management Panel 1(2) (RMP) 1RG1 (1RG2) and the Flight
Management and Guidance Computer 1(2) (FMGC) 1CA1 (1CA2) for
frequency/course selection
- the MCDU 1(2) and the Centralized Fault-Display Interface-Unit
(CFDIU) 1TW for test purposes.

(2) Marker system

The marker system consists of one system only. The receiver is part
of the VOR/MKR receiver 1.
The system comprises :
- one VOR/MKR receiver 1 3RS1
- one marker antenna 1RS.
All the data are shown on the CAPT and F/O Primary Flight Displays
(PFD).

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 VOR/Marker - Block Diagram
Figure 002

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 INTENTIONALLY BLANK

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 VOR/Marker - Control and Indicating
Figure 003

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 C. Utilization Technical Data

(1) Data display

(Ref. Fig. 004)

(a) VOR system

1
_ On the Navigation Display (ND)
In ROSE and ARC modes.
If you set the ADF/VOR/OFF switch on the EFIS control section
of the Flight Control Unit (FCU) to VOR, this causes : display
of the characteristics of the VOR 1 and/or VOR 2 stations in
the L and/or R lower corner of the ND (item 7) :
- type of station (VOR 1, VOR 2)
- shape of the associated bearing display
- station identification
- mode of tuning :
nothing : automatically tuned by the FMGC
M : manually tuned through the MCDU
R : tuned through the RMP.
A single pointer on the heading dial shows the bearing of
the VOR 1 (item 5), a double pointer that of the VOR 2 (item
1).
All these data are shown in white.
In case of VOR system fault, all the corresponding data go
out of view and the VOR indication turns to red.
In ROSE VOR mode, the data below are shown :
- a dagger-shaped pointer points to the selected VOR course
(cyan) (item 6)
- the lateral deviation bar which represents the VOR deviation
is shown with an arrow for the TO FROM indication (cyan)
(item 2)
- in the R top corner, the VOR characteristics come into view:
VOR 1 or 2, frequency, selected course (item 4),
identification (cyan).
In case of VOR system fault ,all these data go out of view and
the VOR 1 or 2 indication turns to red.
If the VOR approach is selected, the VOR APP message comes
into view in the center top section of the ND (item 3).
In ROSE NAV and ARC modes, the characteristics and location of
the VOR stations which are not already included in the flight
plan, can be shown when you push the VOR-D pushbutton switch
on the EFIS control section of the FCU :
- cross symbol for the VOR station (item 8)
- circle plus cross symbol for the VOR/DME station (item 9).

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 VOR/Marker - Data and Warning Displays
Figure 004

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 2
_ On the VOR/DME RMI
The RMI indicates the VOR bearings :
- a single pointer indicates the VOR 1 bearing (item 11)
- a double pointer indicates the VOR 2 bearing.
A warning flag comes into view to indicate system malfunction
(item 12). In this case, the corresponding pointer is in the 3
o<clock position (item 13).
In case of No Computed Data (NCD), no warning flag appears but
the corresponding pointer remains in the 3 o<clock position.

(b) Marker system

The MKR data are shown on the PFD, in approach at the
intersection of the G/S and LOC scales (item 14).
When the aircraft overflies the corresponding marker, the data
given after come into view on the PFD :
- OM for the outer marker (blue)
- MM for the middle marker (amber)
- AWY for the inner marker (white).

(2) Audio control

(a) VOR system

1
_ The VOR/MKR receivers apply their VOR audio output to the
audio integrating system. This system controls and directs the
output to the headsets and/or the loud speakers. The AMU
controls the audio level through the ACP. On the ACP, the
pilot must push the VOR 1 (2) pushbutton switch and adjust the
related potentiometer to the correct audio level.

2
_ In case of ATIS message transmission by the VOR station :
- it is necessary to push the ON VOICE pushbutton switch on
one ACP in order to hear clearly this information without
Morse signal.

(b) Marker system

The VOR/MKR receiver 1 applies its marker audio output to the
audio integrating system. This system controls and directs the
output to the headsets and/or the loud speakers. The AMU controls
the audio level through the ACP. On the ACP, the pilot must push
the MKR pushbutton switch and adjust the related potentiometer to
the correct audio level.

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 D. Warning
(Ref. Fig. 004)
The warning related to the VOR is the local warning shown on the VOR/DME
RMI.
In case of VOR fault, a corresponding VOR flag comes into view on the
VOR/DME RMI.

4. Power
____________
Supply
(Ref. Fig. 002)
Energization of each system is through 115VAC 400Hz buses :
- 115VAC ESS BUS 401XP via circuit breaker 2RS1 for system 1
- 115VAC BUS 2 204XP via circuit breaker 2RS2 for system 2.
The 115VAC ESS BUS 401XP energizes the VOR/DME RMI via circuit breaker 12FN.

5. _____________________
Component Description

A. VOR/MKR Receiver

(1) External description

(Ref. Fig. 005)
The face of the receiver is fitted with a handle, two lugs, a TEST
pushbutton switch and test LEDs.
The name, color and function of the LEDs are as follows:
- CONTROL FAIL (red) indicates that the control input data are faulty
- LRU STATUS (green) indicates that no faults are detected during the
self-test sequence
- LRU STATUS (red) indicates that a fault is detected during the
self-test sequence.
The back of the VOR /MKR receiver contains an ARINC 600, shell size
connector to provide electrical connections to the aircraft wiring
via mount.
Contact grouping is as follows:
- Top plug (TP): connection with the automatic test circuit
- Middle plug (MP): connection with the peripheral circuits
- Bottom plug (BP): connection with the power supply circuit and the
antennas.

(2) Internal description

(Ref. Fig. 006)
The microprocessor-based receiver processes and conditions signals
within the frequency range of 108 MHz to 117.95 MHz, to produce
digital bearing and identification word outputs and an audio output.
The receiver comprises:

(a) A VOR RF receiver module which converts, conditions, filters and

amplifies the received VOR signal.

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 VOR/MKR Receiver
Figure 005

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 VOR/MKR Receiver - General Architecture
Figure 006

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 (b) A marker beacon receiver module which converts, conditions,
filters and amplifies the received marker beacon signal.

(c) A digital instrumentation module which processes VOR and marker

beacon detector signals into ARINC-711 NAV receiver outputs.
This module contains a signal processor and system processor. The
signal processor is used in computing VOR bearing information.
The system processor is used in interfacing with the aircraft and
also communicates with the maintenance processor.

(d) A maintenance processor module which monitors the health of the

VOR and marker beacon receivers, power supply and signal and
system processor faults.

(e) A power supply module which converts aircraft 115VAC, 400 Hz

power to supplies used by the internal circuits.

(3) Operation

(a) VOR operation

(Ref. Fig. 007)
The antenna applies the composite signal transmitted by the
ground station to an RF receiver. In the receiver, the signal
passes through a low-pass filter, a bandpass filter (preselector)
and an RF switch to an RF amplifier. The output of the amplifier
passes through one of two bandpass filters, depending on the RF
frequency of the station being received, to the first mixer. The
mixer combines the RF signal with a Local Oscillator (LO) to
produce a first Intermediate Frequency (IF) of 20.05 MHz. The
first LO injects a frequency 20.05 MHz below the desired RF
frequency. The mixer output is filtered by a crystal filter and
passed through a two-stage IF amplifier. Following the IF
amplifier, the signal is mixed with a 20.505 MHz second LO to
produce a second IF of 455 MHz. The second IF signal is
demodulated using a precision AM peak detector. The VOR detector
signal is processed by the signal processor on the
instrumentation module. The filtered VOR detector signal is
output to the rear interconnect module where it is amplified and
output to the aircraft.

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 VOR Receiver - Simplified Block Diagram
Figure 007

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 (b) MARKER operation
(Ref. Fig. 008)
The RF signal is filtered through a low-pass and a 75 MHz
bandpass filter. Following the bandpass filter, the signal passes
through an RF switch. This switch selects the incoming signal or
the functional test signal. After the switch, an RF amplifier
provides 12 dB of gain. Following the RF amplifier, the signal is
further filtered by another 75 MHz bandpass filter. The output of
the second filter goes to a mixer, where it is mixed with an
85.700 MHz Local Oscillator signal to produce an IF of 10.7 MHz.
This IF signal is filtered, amplified and demodulated. The
detector output is applied to three tone filters. The filter
outputs are rectified and checked against a reference level by a
comparator. Each comparator output is sent to the instrumentation
module.
The marker beacon receiver module also contains the functional
test generator circuits. These circuits generate the 75 MHz test
signal for the marker beacon receiver and VOR test signal for the
VOR receiver.

(c) Instrumentation
The instrumentation module contains two processors. The signal
processor, takes the VOR detector signal and separates the two 30
Hz signals (variable and reference). From these two signals, the
signal processor computes the station bearing. The second
processor on the module, the system processor, is used to
communicate the bearing information to the aircraft. The system
processor handles the signal interface with the aircraft.

(d) LRU monitoring

The maintenance processor, monitors the health of the VOR and
marker beacon receivers. The maintenance processor provides all
the BITE functions for the LRU. BITE information is transferred
to the system processor for communications to the aircraft.
Maintenance functions include:

1
_ Receive data from the ARINC maintenance bus and store the
time, data, aircraft IDENT, aircraft configuration and process
the maintenance control word.

2
_ Process data received from the system processor for storage in
the Non-Volatile fault Memory (NVM).

3
_ Monitor discrete inputs.

4
_ Determine the validity of the maintenance input control word.

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 MARKER Receiver - Simplified Block Diagram
Figure 008

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 5
_ Format the fault summary word and transfer it to the system
processor.

6
_ Transfer all OMS interactive mode data and normal mode data
words to the system processor.

7
_ Provide maintenance menus in the aircraft.

8
_ Provide extended interactive mode support for troubleshooting
when the LRU is in the maintenance mode.

(4) Digital outputs

This table contains all the output parameters in the digital form.
They are sorted as per the numerical order of their output label.
The following table gives :
- EQ.SYS.LAB.SDI: (SDAC,FWC,DMC...) output label for which the
parameter is available
- PARAMETER DEFINITION: parameter name
- WORD RANGE OPER RANGE RESOLUTION ACCURACY: measurement range.
Maximum value transmitted. When the digital value changes, the
change step is equal to the accuracy
- UNIT: unit in which the digital value is transmitted
- SIG BIT: indicates whether a sign bit is available
- BITS: number of bits used by the parameter in the label
- XMSN/INTV: output transmission interval. The refresh rate is given
in milliseconds
- CODE :
BNR: binary data word
BCD: binary coded decimal data word
ISO: data word coded in ISO5 code
DIS: discrete data word
HEX: hexadecimal coded
HYB: mixed code
- ALPHA CODE: indicates the parameter mnemonic code
- SOURCE ORIGIN: parameter source computer or system.

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 -------------------------------------------------------------------------------
| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |
-------------------------------------------------------------------------------
|EQ.SYS.LAB.SDI|PARAMETER | WORD RANGE |UNIT|SIG |BITS|XMSN|CODE|ALPHA|SOURCE |
| |DEFINITION| OPER RANGE | |BIT | |INTV| |CODE |ORIGIN |
| |(*=REMARK)| RESOLUTION | | | | | | |BUS No.|
| |(X=NOTE) | ACCURACY | | | | | | |ATA REF|
| | | | | | | | | |CONV |
-------------------------------------------------------------------------------
| .034. |VOR 1 FREQ| 108/117.95 |MHZ | | 4 |2560|BCD | | |
| | | 0.01 | | | | | | | |
| |VOR 2 FREQ| | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| .100. |SEL | 180 |DEG | | 12 | |BNR | | |
| |COURSE 1 | 0.0439 | | | | | | | |
| | | | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| .222. |OMNI | 180 |DEG | | 12 | |HYB | | |
| |BEARING | 0.0439 | | | | | | | |
| | | | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| .242. |VOR 1 | | | | | |HYB | | |
| |IDENT | | | | | | | | |
| |WORD 1 | | | | | | | | |
| | | | | | | | | | |
| |VOR 2 | | | | | | | | |
| |IDENT | | | | | | | | |
| |WORD 1 | | | | | | | | |
|--------------|----------|------------|----|----|----|----|----|-----|-------|
| .244. |VOR 1 | | | | | |HYB | | |
| |IDENT | | | | | | | | |
| |WORD 2 | | | | | | | | |
| | | | | | | | | | |
| |VOR 2 | | | | | | | | |
| |IDENT | | | | | | | | |
| |WORD 2 | | | | | | | | |
-------------------------------------------------------------------------------

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 B. Antennas

(1) MARKER antenna

(Ref. Fig. 009)
A low-drag, lightweight antenna, located in the longitudinal axis of
the aircraft below the fuselage, is provided for the reception of the
75 MHz marker signals. The dielectric, foam-filled, white polyester
fiberglass housing, fitted with a metal leading edge, protects
against moisture and erosion. The antenna is horizontally polarized,
has an impedance of 50 ohms.

(2) VOR antenna

(Ref. Fig. 010)
The VOR antenna is an airborne antenna sunk into the fin and used to
receive VOR signals in the 108-118 MHz range. It is a small-sized
half-wave folded dipole type.
The antenna has two independent RF connectors used to feed two items
of equipment. The antenna is horizontally polarized, has an impedance
of 50 ohms.

6. _________
Operation
(Ref. Fig. 002)

A. Control

(1) VOR system

- Each VOR/MKR receiver is connected to one RMP. The VOR/MKR receiver
1 is connected to the RMP 1, (the VOR/MKR receiver 2 to the RMP 2).
The RMP 1 also receives the management bus from the FMGC 1 (the RMP
2 from the FMGC 2).
- In normal operation, the FMGC 1(2) tunes the VOR/MKR receiver 1(2)
either automatically or manually by means of the MCDU 1(2). In this
case the RMP 1(2) operates as a relay which sends the frequency and
course information from the FMGC 1(2) to the VOR/MKR receiver 1(2).
- By a second port, the VOR/MKR receiver 1(2) receives a second
management bus directly from the FMGC 2(1). The receiver selects
one of the two port functions by a discrete signal from the FMGC
1(2) through the RMP 1(2).
- In case of one FMGC fault, the other FMGC can control the two
VOR/MKR receivers, one directly, the other through its RMP.
- In case of the RMP 1(2) or two RMPs fault, the concerned RMP is
transparent to data and discrete from the FMGC.
- In emergency configuration (in case of two FMGCs fault) the RMP 1
can control the VOR/MKR receiver 1 after ON NAV mode selection.
Same possibility for the RMP 2 (VOR/MKR receiver 2).
(Ref. Fig. 011)

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 MARKER - Antenna
Figure 009

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 VOR - Antenna
Figure 010

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 VOR - Frequency Selection in Emergency Mode
Figure 011

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 (2) Marker system
The marker receiver is contained in the VOR/MKR receiver.
In normal operation, the VOR/MKR receiver receives a signal when the
aircraft overflies the corresponding marker.

B. Reconfiguration Switching
In normal utilization, both VOR 1 and 2 data are shown on the CAPT (F/O)
ND through their respective Display Management Computer (DMC 1(2)). The
marker data are shown on the CAPT (F/O) PFD through the DMC 1(2).
In case of the DMC 1(2) fault, it is possible to switch over to the DMC 3
with the EIS DMC selector switch. This selector switch is located on
panel 8VU on the center pedestal. In this case the DMC 3 totally replaces
the DMC 1(2) through the stage of the output switching relay of the
failed DMC. In case of PFD fault, there is an automatic transfer of the
PFD image into the ND.
In case of ND fault:
- you obtain the transfer of the ND image onto the PFD when you push the
PFD/ND XFR pushbutton switch on panel 301VU (501VU).
When you set the PFD potentiometer to OFF on panel 301VU (501VU), this
causes :
- deactivation of the PFD
- transfer of the PFD image onto the ND.

7. BITE
_____________
Function
(Ref. Fig. 012)

A. Access to the VOR/MKR Sub-menu Functions

It is possible to select the maintenance functions of the VOR/MKR
receiver 1 (2) on the MCDU1 (2) by pressing the line key adjacent to the
SYSTEM REPORT/TEST indication on the CFDS menu, and then selecting the
relevant VOR on the NAV menu.
After these actions, the VOR 1 (2) provides its own menu page and the
sub-menu functions can then be chosen by the operator.

B. Activation of the Test Function

The test function can be activated in ground conditions only.

(1) Marker test

The marker test can be activated by pressing the line key adjacent to
the TEST indication on the VOR 1 maintenance sub-menu or by pressing
the pushbutton switch on the face of the receiver.

(2) VOR test

The VOR test can be activated by pressing the line key adjacent to
the TEST indication on the VOR 1(2) maintenance sub-menu or by
pressing the pushbutton switch on the face of the receiver.

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 VOR/Marker - Maintenance Test Procedure
Figure 012

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 8. _________
BITE Test

A. CFDIU Interface

(1) BITE description

The BITE facilitates maintenance on in-service aircraft. It detects
and identifies a failure related to the VOR system.
The BITE of the VOR receiver is connected to the CFDIU (Ref.
31-32-00).
The unit tested is the VOR receiver.
The BITE:
- transmits permanently VOR system status and its identification
message to the CFDIU
- memorizes the failures which occurred during the last 63 flight
segments
- monitors data inputs from the various peripherals (FMGC, RMP and
CFDIU)
- transmits to the CFDIU the result of the tests performed and
self-tests
- can communicate with the CFDIU through the menus.
The BITE can operate in two modes:
- the normal mode
- the menu mode.

(a) Normal mode

During the normal mode the BITE monitors cyclically the status of
the VOR system. It transmits its information to the CFDIU during
the concerned flight.
In case of fault detection the BITE stores the information in the
fault memories.
These items of information are transmitted to the CFDIU every 50
to 250 ms by an ARINC 429 message with label 356.

(b) Menu mode:

The menu mode can only be activated on the ground.
This mode enables communication between the CFDIU and the VOR
receiver BITE by means of the MCDU.
The VOR menu mode is composed of:
- LAST LEG REPORT
(Ref. Fig. 013)
This menu permits to display two failures per page. These may
be any combination of class 1 and /or class 2 faults.
- PREVIOUS LEGS REPORT
(Ref. Fig. 013)
This report contains the fault messages related to the external
or internal failures (class 1 and 2) recorded during the
previous 63 flight legs.

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 VOR - Maintenance Test Procedure - VOR Menu (Sheet 1/6)
Figure 013

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 - LRU IDENTIFICATION
(Ref. Fig. 013)
Allows to display the P/N and S/N of the equipment.
- GROUND SCANNING
(Ref. Fig. 014)
Based on the monitoring and fault analysis during flight,
provides information of the failures detected while using this
function.
- TROUBLE SHOOTING DATA
(Ref. Fig. 014)
Provides correlation parameters and snapshot data concerning
the failure displayed in the LAST LEG REPORT and PREVIOUS LEG
REPORT.
- CLASS 3 FAULT
(Ref. Fig. 015)
Allows to display the class 3 faults recorded during the last
flight leg.
- GROUND REPORT
(Ref. Fig. 015)
Allows to present the class 1, 2 or 3 internal failures
detected on ground.
These failures differ from those displayed on the LAST LEG
REPORT and CLASS 3 FAULTS.
- TEST
(Ref. Fig. 016, 017, 018)
Allows a check of the correct operation of the VOR/MKR on
ground.

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 VOR - Maintenance Test Procedure - VOR Menu (Sheet 2/6)
Figure 014

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 VOR - Maintenance Test Procedure - VOR Menu (Sheet 3/6)
Figure 015

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R VOR - Maintenance Test Procedure - VOR Menu (Sheet 4/6)
Figure 016

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 VOR - Maintenance Test Procedure - VOR Menu (Sheet 5/6)
Figure 017

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 VOR - Maintenance Test Procedure - VOR Menu (Sheet 6/6)
Figure 018

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 VOR/MARKER - ADJUSTMENT/TEST
____________________________

TASK 34-55-00-740-002

BITE Test of the VOR/MKR

WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE
_______
YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
31-32-00-860-010 Procedure to Get Access to the SYSTEM REPORT/TEST NAV
Page
34-10-00-860-002 ADIRS Start Procedure
34-10-00-860-004 IR Alignment Procedure
34-10-00-860-005 ADIRS Stop Procedure
34-55-00-991-001 Fig. 501

3. __________
Job Set-up

Subtask 34-55-00-860-054

A. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits

(Ref. TASK 24-41-00-861-002).

(2) Do the ADIRS Start procedure (Ref. TASK 34-10-00-860-002)

(3) Do the IR alignment procedure (Ref. TASK 34-10-00-860-004)

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 (4) On the EFIS control sections of the FCU:
- set the ADF/VOR selector switches to VOR
- set the mode selector switches to ROSE/VOR.
- push the ILS pushbutton switches.

R (5) On the center pedestal, on one MCDU:

- get the SYSTEM REPORT/TEST/NAV page (Ref. TASK 31-32-00-860-010).
- push the NEXT PAGE function key.

(6) On the center pedestal, on the RMP1 (RMP2):

- set the ON/OFF switch to ON
- push the NAV and VOR pushbutton switches (the green LED on these
pushbutton switches comes on)
- set the non local VOR1 and VOR2 stations and a course of 190⁰.
(Ref. Fig. 501/TASK 34-55-00-991-001)

Subtask 34-55-00-865-054

B. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV/VOR/DME/RMI 12FN F13
49VU NAV/VOR/1 2RS1 G13
121VU COM NAV/VOR/2 2RS2 K08

4. Procedure
_________

Subtask 34-55-00-740-051

A. BITE Test of the VOR/MARKER

NOTE : During the BITE TEST (VOR1 or 2) by the MCDU, the indications
____
related to the two receivers (CAPT and F/O) are shown at the same
time. This has no effect on the test or component operation.

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 VOR-Frequency and Course Selection
Figure 501/TASK 34-55-00-991-001

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the MCDU: On the MCDU:

- push the line key adjacent to - the VOR1 (VOR2) page comes into view.
the VOR1 (VOR2) indication.

- push the line key adjacent to - the INITIAL CONDITIONS are shown
the TEST indication. (pages 1 to 3).

- push the line key adjacent to - the TEST IN PROGRESS 11 S indication

the START TEST indication. comes into view

On the CAPT and F/O PFDs (for the VOR1

test only):
- the OM indication comes into view
until the end of the test.

R From 0 to 3S:
- on the CAPT and F/O NDs:
. the VOR1 (VOR2) warning flags come
into view.
- on the VOR/DME RMI:
. the VOR1 (VOR2) warning flag comes
into view.

R From 3 to 6s:
- on the CAPT and F/O NDs:
. the VOR1 (VOR2) pointer is not
shown.
- on the VOR/DME RMI:
R . the VOR pointers stay at the last
R valid position.

R From 6 to 11s:
- on the CAPT and F/O NDs:
. the VOR1 (VOR2) pointer comes into
view and shows 180 deg.
- on the VOR/DME RMI:
. the VOR1 (VOR2) pointer shows 180
deg.
- on the CAPT and F/O PFDs (for the
VOR1 test only):
. the OM indication is shown.

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
NOTE : Do not reject the VOR/DME RMI if
____
the pointers do not show the
test values.This is because of
the pointer slaving time.

- push the line key adjacent to On the MCDU:

the YES indication (for the - the MARKER AURAL TONE OK indication
VOR1 test only). comes into view (for the VOR1 test
only).

- push the line key adjacent to - the TEST OK indication comes into
the YES indication. view.

- push the line key adjacent to The test procedure stops.

the RETURN indication.

5. Close-up
________

Subtask 34-55-00-860-055

A. Put the aircraft back to its initial configuration.

(1) On the MCDU, push the line key adjacent to the RETURN indication
until the CFDS menu page comes into view.

(2) On the EFIS control sections of the FCU:

- set the ADF/VOR selector switches to OFF.
- release the ILS pushbutton switches.

(3) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005).

(4) On the center pedestal, on the RMP:

- push the NAV and VOR pushbutton switches (the green LED on these
pushbutton switches goes off).
- set the ON/OFF switch to OFF.

(5) De-energize the aircraft electrical circuits

(Ref. TASK 24-41-00-862-002)

(6) Make sure that the work area is clean and clear of tool(s) and other
items.

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 TASK 34-55-00-710-001

Operational Test of the VOR/MKR

WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE
_______
YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.

1. __________________
Reason for the Job

Reception Test of the VOR beacon.

2. ______________________
Job Set-up Information

A. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
34-55-00-991-001 Fig. 501

3. __________
Job Set-up

Subtask 34-55-00-860-050

A. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-

002)

(2) On the center pedestal, on the RMP1 (RMP2), set the ON/OFF switches
to ON.

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 Subtask 34-55-00-865-051

B. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV/VOR/DME/RMI 12FN F13
49VU NAV/VOR/1 2RS1 G13
121VU COM NAV/VOR/2 2RS2 K08

4. Procedure
_________

Subtask 34-55-00-710-055

A. Operational Test of the VOR/MKR

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the RMP1 (RMP2):

- push the NAV pushbutton switch. On the RMP, the green LED on this
pushbutton switch comes on.

- set the frequency of the VOR1 The frequency comes into view in the
(2) local station left window of the RMP
(Ref. Fig. 501/TASK 34-55-00-
991-001)

2. On the center pedestal, on one

ACP :

- set the VOR1 reception. In the loud speakers, you must hear the
Morse signal of the set station.

3. On the RMP1 (RMP2):

- push the NAV pushbutton switch. The green LED on this pushbutton switch
goes off.

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 5. Close-up
________

Subtask 34-55-00-860-051

A. Put the aircraft back to its initial configuration.

(1) On the center pedestal, on the RMP, set the ON/OFF switch to OFF.

(2) On the center pedestal, on the ACP, release the VOR1 pushbutton
switch.

(3) De-energize the aircraft electrical circuits.

(Ref. TASK 24-41-00-862-002)

(4) Make sure that the work area is clean and clear of tool(s) and other
items.

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 TASK 34-55-00-720-001

Functional Test of the VOR/MKR

WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE
_______
YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.

R NOTE : You can do the MKR test only at the end of the VOR1 test.
____

1. __________________
Reason for the Job

To make sure that the VOR and MKR systems operate correctly.

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific ground test unit

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-41-00-861-002 Energize the Aircraft Electrical Circuits from the

External Power
24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
34-10-00-860-002 ADIRS Start Procedure
34-10-00-860-004 IR Alignment Procedure
34-10-00-860-005 ADIRS Stop Procedure
34-55-00-991-001 Fig. 501

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 3. __________
Job Set-up

Subtask 34-55-00-865-053

A. Make sure that this(these) circuit breaker(s) is(are) closed:

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV/VOR/DME/RMI 12FN F13
49VU NAV/VOR/1 2RS1 G13
121VU COM NAV/VOR/2 2RS2 K08

Subtask 34-55-00-860-052

B. Aircraft Maintenance Configuration

(1) Energize the aircraft electrical circuits (Ref. TASK 24-41-00-861-

002)

(2) Install the ground test unit near the VOR or MKR antenna as shown in
the installation instructions.

(3) Do the ADIRS start procedure (Ref. TASK 34-10-00-860-002).

(4) Do the IR alignment procedure (Ref. TASK 34-10-00-860-004).

R (5) On the EFIS control sections of the FCU:

R - set the ADF/VOR selector switches to VOR and the mode selector
R switches to ROSE/VOR.
R - push the ILS pushbutton switches.

(6) On the center pedestal, on one ACP, set the VOR1 (2) or MKR
reception.

(7) On the center pedestal, on the RMP1 and RMP2:

- set the ON/OFF selector switch to ON.

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 4. Procedure
_________

Subtask 34-55-00-720-050

A. Test of the VOR Reception and Identification

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the test unit:

- set the frequency of the VOR

test unit and then set a
bearing of 0⁰.

2. On the RMP1 (RMP2):

- push the NAV pushbutton switch. On the RMP, the green LED on this
pushbutton switch comes on.

- push the VOR pushbutton switch. On the RMP, the green LED on this
pushbutton switch comes on.

- set the VOR1 (VOR2) frequency On the RMP1 (RMP2):

of the VOR test unit and then - the frequency comes into view in the
set a course of C000 . left window.
(Ref. Fig. 501/TASK 34-55-00-
991-001)
- the course comes into view in the
right window.
On the CAPT and F/O NDs:
- the VOR1 (VOR2) frequency and the CRS
000 indications come into view in the
top right corner.
- the VOR1 (VOR2) indication and the
VOR1 (VOR2) frequency come into view
in the left (right) lower corner.
- the outline of the pointer comes into
view in the left (right) lower
corner.
- the dagger shaped pointer (course
pointer) shows 0⁰.
- the VOR1 (VOR2) pointer comes into
view and shows 0⁰.
- the lateral deviation bar and the
arrow that shows the TO indication

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
come into view and are on the same
axis as the dagger shaped pointer
(course pointer).
On the VOR/DME RMI:
- the VOR1 (VOR2) pointer shows 0⁰.

- set a course of C005 . On the CAPT and F/O NDs the dagger
shaped (course pointer) shows 5⁰ and
R the lateral deviation bar moves to the
R left and stops on the first dot.

- set a course of C010 . On the CAPT and F/O NDs the dagger
shaped (course pointer) shows 10⁰ and
R the lateral deviation bar moves to the
R left and stops on the second dot.

- set a course of C355 . On the CAPT and F/O NDs the dagger
shaped (course pointer) shows 355⁰ and
R the lateral deviation bar moves to the
R right and stops on the first dot.

- set a course of C350 . On the CAPT and F/O NDs the dagger
shaped (course pointer) shows 350⁰ and
R the lateral deviation bar moves to the
R right and stops on the second dot.

3. On the test unit:

- set a bearing of 135⁰. On the CAPT and F/O NDs:

- the VOR1 (VOR2) pointer shows 135⁰.
- the lateral deviation bar moves to
the right and the arrow indicates
FROM.
On the VOR/DME RMI:
- the VOR1 (VOR2) pointer shows 135⁰.

4. On the RMP1 (RMP2):

- set a course of C135. On the CAPT and F/O NDs:

- the CRS 135⁰ indication comes into
view in the top right corner.

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
- the set dagger shaped pointer (course
pointer) shows 135⁰.
- the lateral deviation bar moves to
the center and the arrow indicates
TO.

- set a course of C315. On the CAPT and F/O NDs:

- the CRS 315⁰ indication comes into
view in the top right corner.
- the set dagger shaped pointer (course
pointer) shows 315⁰.
- the lateral deviation bar moves and
then returns to the center and the
arrow indicates FROM.

5. On the test unit: On the CAPT ND:

- set the test unit in the OFF - the VOR1 (VOR2) pointer goes out of
position view
- the lateral deviation bar and the
arrow that indicates FROM/TO go out
of view.

On the F/O ND:

- the VOR1 (VOR2) pointer goes out of
view

On the VOR/DME RMI:

R - the VOR1 (VOR2) pointer goes to the 3
R o<clock position.

6. On the test unit:

- set the test unit on the ON In the loudspeaker, you can hear the
position and set the audio signal.
transmission of the
identification signal.

7. On the ACP:

- adjust the volume until you get The adjustment is continuous and no
the required level. unwanted noise is heard.

8. On the test unit:

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
- cancel the transmission of the You cannot hear the signal.
audio signal.

R 9. On the RMP1 (RMP2):

- push the NAV pushbutton switch. On the RMP, the green LED on this
pushbutton switch goes off.

Subtask 34-55-00-720-051

B. Test of the MKR Reception and Identification

-------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------

1. On the test unit:

- set a frequency of 75 MHz with On the CAPT and F/O PFDs:

a signal modulation of 400Hz - the OM indication comes into view on
(OM signal). the right.
In the loudspeaker, you can hear the
audio signal.

2. On the ACP:

- adjust the volume until you get In the loudspeaker, the adjustment is
the required level. continuous and no unwanted noise can be
heard.

3. On the test unit:

- modulate the signal to 1300Hz On the CAPT and F/O PFDs:

(MM signal). - the MM indication comes into view on
the right.
In the loudspeaker, you can hear the
audio signal.

- modulate the signal to 3000Hz On the CAPT and F/O PFDs:

(AWY signal). - the AWY indication comes into view on
the right.
In the loudspeaker, you can hear the
audio signal.

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 -------------------------------------------------------------------------------
ACTION RESULT
-------------------------------------------------------------------------------
- cancel the 75MHz frequency. On the CAPT and F/O PFDs:
the last MKR indication goes out of
view.
In the loudspeaker, you cannot hear the
transmission of the audio signal.

5. Close-up
________

Subtask 34-55-00-860-053

A. Put the aircraft back to its initial configuration.

R (1) On the EFIS control sections of the FCU:

R - set the ADF/VOR selector switches to OFF.
R
R - release the ILS pushbutton switches.

(2) Do the ADIRS stop procedure (Ref. TASK 34-10-00-860-005).

(3) On the center pedestal, on the RMP, set the ON/OFF switch to OFF.

(4) On the center pedestal, on the ACP, release the VOR1 (2) or MKR
pushbutton switch.

(5) Stop the test unit.

(6) De-energize the aircraft electrical circuits.

(Ref. TASK 24-41-00-862-002)

(7) Make sure that the work area is clean and clear of tool(s) and other
items.

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 ANTENNA - VOR (4RS) - REMOVAL/INSTALLATION
__________________________________________

TASK 34-55-11-000-001

Removal of the VOR Antenna 4RS

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific blanking caps

No specific circuit breaker(s) safety clip(s)
No specific nonmetallic scraper
No specific warning notice
No specific access platform 12 m (39 ft. 4 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

24-42-00-861-001 Energize the Ground Service Network from the External

Power
55-34-11-000-001 Removal of the Vertical Stabilizer Tip 324AT
34-55-11-991-001 Fig. 401

3. __________
Job Set-up

Subtask 34-55-11-861-050

A. Energize the ground service network

(Ref. TASK 24-42-00-861-001)

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 Subtask 34-55-11-865-050

B. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV/VOR/1 2RS1 G13
121VU COM NAV/VOR/2 2RS2 K08

Subtask 34-55-11-010-050

C. Get Access

(1) Put the warning notice in the cockpit to tell persons not to operate
the flight controls.

(2) Put the access platform in position at Zone 324.

(3) Remove the vertical stabilizer tip 324AT (Ref. TASK 55-34-11-000-001)

4. Procedure
_________

(Ref. Fig. 401/TASK 34-55-11-991-001)

Subtask 34-55-11-020-051

A. Removal of the VOR Antenna

(1) Solution 1 (VOR antenna S/N 001-331):

- disconnect the coaxial cable connectors (2) from the antenna
connectors (6).
- remove sealant from the head of the screws (3) with a nonmetallic
scraper.
- remove the screws (3), the washers (5) and the antenna (1).

(2) Solution 2 (VOR antenna S/N 332 and subsequent):

- disconnect the coaxial cable connectors (2) from the antenna
connectors (6).
- remove the sealant from the head of the screws (3) with a
nonmetallic scraper.
- remove the screws (3), the washers (5), the isolation washers (7)
and the antenna (1).

NOTE : The isolation washers have a tendancy to stick to the bottom

____
of the VOR antenna. They must be removed.

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 VOR Antenna 4RS.
Solution 1 (S/N 001-331) / Solution 2 (S/N 332 and subsequent).
Figure 401/TASK 34-55-11-991-001

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 (3) Put blanking caps on the disconnected electrical connectors.

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 TASK 34-55-11-400-001

Installation of the VOR Antenna 4RS

WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS

_______
ONLY WITH A GOOD SUPPLY OF AIR.
OBEY THE MANUFACTURERS INSTRUCTIONS.
PUT ON PROTECTIVE CLOTHING.
DO NOT GET THEM IN YOUR MOUTH.
DO NOT SMOKE.
DO NOT BREATHE THE GAS.
THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT.
GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED.

WARNING : DO NOT GET THE COMPOUND ON YOUR SKIN.

_______
IF YOU DO:
- RUB IT OFF IMMEDIATELY WITH A CLEAN CLOTH
- WASH THE SKIN WITH SOAP AND RINSE WITH CLEAN WATER.

WARNING : IF YOU GET THE FLUID ON YOUR SKIN OR IN YOUR EYES:

_______
- FLUSH IT AWAY WITH CLEAN WATER
- GET MEDICAL AID.

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific nonmetallic scraper

No specific Lint-free cloth
No specific Torque Wrench : range 0.20 to 3.60 m.daN
(2.00 to 26.00 lbf.ft)

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 B. Consumable Materials

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

Material No. 07-001

ELECTRICAL BONDING COATING (BLUE COLOR)
(Ref. 20-31-00)
R Material No. 09-016 USA MIL-PRF-81733D TYPE II CLASS B
CORROSION INHIBITING FILLET CONSISTENCY
(Ref. 20-31-00)
Material No. 11-010 USA TT-I-735 GRADE A
ISOPROPYL ALCOHOL (Ref. 20-31-00)
Material No. 16-003 F ASNB70720
COATING (OBSOLETE USE 16-021) (Ref. 20-31-00)

C. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

20-28-00-912-005 Electrical Bonding of Antennas With Conductive Bolts.

24-42-00-861-001 Energize the Ground Service Network from the External
Power
24-42-00-862-001 De-energize the Ground Service Network Supplied from
the External Power
34-55-00-720-001 Functional Test of the VOR/MKR
55-34-11-000-001 Removal of the Vertical Stabilizer Tip 324AT
55-34-11-400-001 Installation of the Vertical Stabilizer Tip 324AT
34-55-11-991-001 Fig. 401

3. __________
Job Set-up

Subtask 34-55-11-860-050

A. Aircraft Maintenance Configuration

Make sure that the ground service network is energized
(Ref. TASK 24-42-00-861-001)

(1) Make sure that the warning notices are in position in the cockpit to
tell persons not to operate the flight controls.

(2) Make sure that the access platform is in position at Zone 324.

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 (3) Make sure that the vertical stabilizer 324AT (Ref. TASK 55-34-11-000-
001) is removed.

Subtask 34-55-11-865-051

B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and
tagged

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV/VOR/1 2RS1 G13
121VU COM NAV/VOR/2 2RS2 K08

4. Procedure
_________

(Ref. Fig. 401/TASK 34-55-11-991-001)

WARNING : OBEY THE MANUFACTURER<S INSTRUCTIONS WHEN YOU USE THE SPECIAL
_______
MATERIAL.
THIS MATERIAL IS DANGEROUS.

Subtask 34-55-11-140-050

A. Preparation for Installation

(1) Remove the used sealant from the antenna support with a nonmetallic
scraper.

R (2) Clean the component interface and/or the adjacent area with CLEANING
R AGENTS (Material No. 11-010) and a Lint-free cloth.

(3) Do an inspection of the component interface and/or the adjacent area.

NOTE : Make sure that the antenna-attachment points have no signs of

____
paint, corrosion or sealant.

Subtask 34-55-11-420-050

B. Installation of the VOR Antenna

(1) Solution 1 ( VOR antenna S/N 001-331):

- put the antenna (1) in position and install the screws (3) and the
washers (5).
- TORQUE the screws (3) to between 0.35 and 0.45 m.daN (30.97 and
39.82 lbf.in).
- connect the cable connector (2) to the antenna connector (6).

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 (2) Solution 2 ( VOR antenna S/N 332 and subsequent):
- put the antenna (1) in position and install the isolation washers
(7), the
- screws (3) and the washers (5).
- TORQUE the screws (3) to between 0.35 and 0.45 m.daN (30.97 and
39.82 lbf.in).

(3) Remove the blanking caps from the electrical connectors.

(4) Make sure that the electrical connectors are clean and in the correct
condition.

(5) Connect the cable connector (2) to the antenna connector (6).

(6) Make sure that the bonding contact resistance between the antenna (1)
and the fuselage structure is not higher than 5 milliohms (Ref. TASK
20-28-00-912-005).

(7) Apply SEALANTS (Material No. 09-016) around the antenna electrical
bonding points and the screws (3).

(8) Let the sealant cure.

(9) Apply STRUCTURE PAINTS (Material No. 16-003) to the sealant around
the electrical bonding points.

R (10) Apply PAINTS FOR DETAIL (INTERNAL AND EXTERN AL) (Material No. 07-
R 001) to the sealant on the head of the screws (3).

Subtask 34-55-11-865-052

C. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
2RS1, 2RS2

Subtask 34-55-11-720-050

D. Do the functional test of the VOR system (Ref. TASK 34-55-00-720-001).

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 5. Close-up
________

Subtask 34-55-11-410-052

A. Close Access

(1) Make sure that the work area is clean and clear of tool(s) and other
items.

(2) Install the vertical stabilizer tip 324AT (Ref. TASK 55-34-11-400-
001).

(3) Remove the access platform(s).

(4) Remove the warning notice(s).

Subtask 34-55-11-862-050

B. De-energize the ground service network

(Ref. TASK 24-42-00-862-001)

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 ANTENNA - MARKER (1RS) - REMOVAL/INSTALLATION
_____________________________________________

TASK 34-55-18-000-001

Removal of the Marker Antenna (1RS)

WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS

_______
ONLY WITH A GOOD SUPPLY OF AIR.
OBEY THE MANUFACTURERS INSTRUCTIONS.
PUT ON PROTECTIVE CLOTHING.
DO NOT GET THEM IN YOUR MOUTH.
DO NOT SMOKE.
DO NOT BREATHE THE GAS.
THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT.
GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED.

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific blanking caps

No specific circuit breaker(s) safety clip(s)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

34-55-18-991-001 Fig. 401

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 3. __________
Job Set-up

Subtask 34-55-18-865-050

A. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV/VOR/1 2RS1 G13

4. Procedure
_________

(Ref. Fig. 401/TASK 34-55-18-991-001)

Subtask 34-55-18-020-050

A. Removal of the Marker Antenna

(1) Remove the sealant from the heads of the screws (4).

(2) Remove the screws (4).

(3) Put the antenna (3) away from the fuselage (2).

(4) Disconnect the coaxial connector (1).

(5) Remove and discard the seal (6).

(6) Remove the antenna (3).

(7) Put blanking caps on the disconnected coaxial connectors (1) and (5).

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 Marker Antenna
Figure 401/TASK 34-55-18-991-001

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 TASK 34-55-18-400-001

Installation of the Marker Antenna (1RS)

WARNING : USE SOLVENTS/CLEANING AGENTS, SEALANTS AND OTHER SPECIAL MATERIALS

_______
ONLY WITH A GOOD SUPPLY OF AIR.
OBEY THE MANUFACTURERS INSTRUCTIONS.
PUT ON PROTECTIVE CLOTHING.
DO NOT GET THEM IN YOUR MOUTH.
DO NOT SMOKE.
DO NOT BREATHE THE GAS.
THESE MATERIALS ARE POISONOUS, FLAMMABLE AND SKIN IRRITANT.
GET MEDICAL HELP IF YOUR SKIN OR EYES BECOME IRRITATED.

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Consumable Materials

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

Material No. 05-013 D TV-53-3507/73

RELEASE AGENT (OBSOLETE USE 05-013A) (Ref. 20-31-00)
R Material No. 09-016 USA MIL-PRF-81733D TYPE II CLASS B
CORROSION INHIBITING FILLET CONSISTENCY
(Ref. 20-31-00)
Material No. 09-019 USA AMS 3267/3
LOW ADHESION CORROSION INHIBITING SEALANT
(Ref. 20-31-00)
Material No. 11-003 USA TT-M-261
METHYL-ETHYL-KETONE (Ref. 20-31-00)

B. Expendable Parts

-------------------------------------------------------------------------------
FIG.ITEM |DESIGNATION |IPC-CSN
-------------------------------------------------------------------------------

6 seal 34-55-18 01 -010

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 C. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

34-55-00-720-001 Functional Test of the VOR/MKR

34-55-18-991-001 Fig. 401

3. __________
Job Set-up

Subtask 34-55-18-865-051

A. Make sure that this(these) circuit breaker(s) is(are) open, safetied and
tagged

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV/VOR/1 2RS1 G13

4. Procedure
_________

(Ref. Fig. 401/TASK 34-55-18-991-001)

Subtask 34-55-18-420-050

A. Installation of the Marker Antenna

WARNING : IF YOU GET THE FLUID ON YOUR SKIN OR IN YOUR EYES:

_______
- FLUSH IT AWAY WITH CLEAN WATER
- GET MEDICAL AID.

NOTE : If you install the same antenna it is necessary to clean it with

____
CLEANING AGENTS (Material No. 11-003)

(1) Remove the used sealant from the fuselage with CLEANING AGENTS
(Material No. 11-003).

(2) Apply SPECIAL MATERIALS (Material No. 05-013) on the antenna (3)
mount and on the fuselage (2).

(3) Apply SEALANTS (Material No. 09-019) on the antenna (3) mount and on
the fuselage (2).

NOTE : Make sure that there is no sealant in the screw holes.

____

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 (4) Remove the blanking caps from the coaxial connectors (1) and (5).

(5) Install a new seal (6).

(6) Connect the coaxial connector (1) to the antenna (3).

(7) Put the antenna (3) in position on the fuselage (2).

(8) Attach the antenna (3) with the screws (4).

(9) Remove the sealant which is not necessary.

(10) Apply a sealing bead with SEALANTS (Material No. 09-016) around the
antenna (3).

(11) Apply SEALANTS (Material No. 09-016) on the screw (4) heads.

(12) Make the contour of the screws (4) and the antenna (3) smooth.

Subtask 34-55-18-865-052

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
2RS1

Subtask 34-55-18-720-050

C. Do the functional test of the VOR/MKR (para. MKR Identification and

Reception test) (Ref. TASK 34-55-00-720-001).

5. Close-up
________

Subtask 34-55-18-860-050

A. Make sure that the work area is clean and clear of tool(s) and other
items.

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 RECEIVER - VOR/MARKER (3RS1,3RS2) - REMOVAL/INSTALLATION
________________________________________________________

TASK 34-55-31-000-001

Removal of the VOR/MKR Receiver (3RS1, 3RS2)

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific blanking caps

No specific circuit breaker(s) safety clip(s)
No specific access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

34-55-31-991-001 Fig. 401

3. __________
Job Set-up

Subtask 34-55-31-865-050

A. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
FOR 3RS1
49VU NAV/VOR/1 2RS1 G13
FOR 3RS2
121VU COM NAV/VOR/2 2RS2 K08

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 Subtask 34-55-31-010-050

B. Get Access

(1) Put the access platform in position at the access door 824 in zone
128.

(2) Open the access door 824.

4. Procedure
_________

(Ref. Fig. 401/TASK 34-55-31-991-001)

Subtask 34-55-31-020-050

A. Removal of the VOR/MKR Receiver

R (1) Loosen the nuts (4).

(2) Lower the nuts (4).

(3) Pull the VOR/MKR receiver (1) on its rack (3) to disconnect the
electrical connectors (2).

(4) Remove the VOR/MKR receiver (1) from its rack (3).

(5) Put blanking caps on the disconnected electrical connectors (2).

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R VOR/MKR Receiver
Figure 401/TASK 34-55-31-991-001

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 TASK 34-55-31-400-001

Installation of the VOR/MKR Receiver (3RS1, 3RS2)

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific access platform 1.6 m (5 ft. 3 in.)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

34-55-00-740-002 BITE Test of the VOR/MKR

R 52-41-00-410-002 Close the Avionics Compartment Doors after Access
34-55-31-991-001 Fig. 401

3. __________
Job Set-up

Subtask 34-55-31-860-050

A. Aircraft Maintenance Configuration

(1) Make sure that the access platform is in position at the access door
824 in zone 128.

(2) Make sure that the access door 824 is open.

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 Subtask 34-55-31-865-051

B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and
tagged

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
FOR 3RS1
49VU NAV/VOR/1 2RS1 G13
FOR 3RS2
121VU COM NAV/VOR/2 2RS2 K08

4. Procedure
_________

(Ref. Fig. 401/TASK 34-55-31-991-001)

Subtask 34-55-31-420-050

R A. Installation of the VOR/MKR Receiver

(1) Clean the component interface and/or the adjacent area.

(2) Do an inspection of the component interface and/or the adjacent area.

(3) Remove the blanking caps from the electrical connectors (2).

(4) Make sure that the electrical connectors (2) are clean and in the
correct condition.

(5) Install the VOR/MKR receiver (1) on its rack (3).

(6) Push the VOR/MKR receiver (1) on its rack (3) to connect the
electrical connectors (2).

(7) Engage the nuts (4) on the lugs (5) and tighten.

Subtask 34-55-31-865-052

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
FOR 3RS1
2RS1
FOR 3RS2
2RS2

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 Subtask 34-55-31-710-050-A

C. Do the BITE test of the VOR/MKR (Ref. TASK 34-55-00-740-002).

5. Close-up
________

Subtask 34-55-31-860-051

A. Make sure that the work area is clean and clear of tool(s) and other
items.

Subtask 34-55-31-410-050

B. Close Access

R (1) Close the access door 824 (Ref. TASK 52-41-00-410-002).

(2) Remove the access platform(s).

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 RMI - VOR/DME (11FN) - REMOVAL/INSTALLATION
___________________________________________

TASK 34-57-22-000-001

Removal of the VOR/DME RMI (11FN)

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Fixtures, Tools, Test and Support Equipment

-------------------------------------------------------------------------------
REFERENCE QTY DESIGNATION
-------------------------------------------------------------------------------

No specific blanking caps

No specific circuit breaker(s) safety clip(s)

B. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

34-57-22-991-001 Fig. 401

3. __________
Job Set-up

Subtask 34-57-22-865-050

A. Open, safety and tag this(these) circuit breaker(s):

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV/VOR/DME/RMI 12FN F13
R 49VU NAV PROBES/ADIRU3/PWR/SWTG 8FP F09
R 122VU LIGHTING/INSTL LT/MAIN INST/PNL AND/PED 4LF Y04

Subtask 34-57-22-010-050

B. Remove the thermoformed cover from the center instrument panel.

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 4. Procedure
_________

(Ref. Fig. 401/TASK 34-57-22-991-001)

Subtask 34-57-22-020-050

A. Removal of the VOR/DME RMI

(1) Loosen the screws (1), do not remove them.

(2) Disengage the VOR/DME RMI (2) from its housing.

(3) Disconnect the electrical connector (4).

(4) Remove the VOR/DME RMI (2).

(5) Put blanking caps on the disconnected electrical connectors (3) and
(4).

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 VOR/DME RMI
Figure 401/TASK 34-57-22-991-001

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 TASK 34-57-22-400-001

Installation of the VOR/DME RMI (11FN)

1. __________________
Reason for the Job

Self Explanatory

2. ______________________
Job Set-up Information

A. Referenced Information

-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------

33-13-00-710-001 Operational Test of the Instrument and Panel Integral

Lighting
34-14-00-740-001 Interface Test of the IR

3. __________
Job Set-up

Subtask 34-57-22-865-051

A. Make sure that this(these) circuit breaker(s) is(are) open, safetied and
tagged

-------------------------------------------------------------------------------
PANEL DESIGNATION IDENT. LOCATION
-------------------------------------------------------------------------------
49VU NAV/VOR/DME/RMI 12FN F13
R 49VU NAV PROBES/ADIRU3/PWR/SWTG 8FP F09
R 122VU LIGHTING/INSTL LT/MAIN INST/PNL AND/PED 4LF Y04

4. Procedure
_________

Subtask 34-57-22-420-050

A. Installation of the VOR/DME RMI

(1) Clean the component interface and/or the adjacent area.

(2) Do an inspection of the component interface and/or the adjacent area.

(3) Remove the blanking caps from the electrical connectors (3) and (4).

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 (4) Make sure that the electrical connectors are clean and in the correct
condition.

(5) Connect the electrical connector (4) to the VOR/DME RMI (2).

(6) Install the VOR/DME RMI (2) in its housing.

(7) Tighten the screws (1).

Subtask 34-57-22-865-052

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit
breaker(s):
12FN, 8FP, 4LF

Subtask 34-57-22-710-050

C. Test of the VOR/DME RMI

(1) Do the BITE test of the IR system (but read only the heading value on
the RMI).
(Ref. TASK 34-14-00-740-001)

(2) Do the operational test of the instrument and panel integral lighting
(Ref. TASK 33-13-00-710-001).

5. Close-up
________

Subtask 34-57-22-410-050

A. Put the aircraft back to its initial configuration.

(1) Install the thermoformed cover on the center instrument panel.

(2) Make sure that the work area is clean and clear of tool(s) and other
items.

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 **ON A/C ALL

Post SB 34-1147 For A/C 001-004,

SATELLITE NAVIGATION - DESCRIPTION AND OPERATION

________________________________________________

1. _______
General
Not applicable.
The GPS function is included in the Multi-Mode Receiver (MMR).
The GPS is described in AMM 34-36-00 ILS/MMR.

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