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NAI Pushbutton-Switch-Command Discrete-Signal Failure on Channel A

TASK 30-21-00-810-831-A
NAI Pushbutton-Switch-Command Discrete-Signal Failure on Channel A

1. Possible Causes
  • wiring
  • HARNESS-FAN, WF02 [4218KS]
  • P/BSW-ANTI ICE/ENG 1 [2DN1]
  • [4000KS]
  • P/BSW-ANTI ICE/ENG 2 [2DN2]
2. Job Set-up Information
 A. Fixtures, Tools, Test and Support Equipment
REFERENCE
QTY
DESIGNATION
FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENG 1)
No specific
1
PLIERS - JAWED, SOFT
FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENG 2)
No specific
1
PLIERS - JAWED, SOFT
 B. Referenced Information
REFERENCE
DESIGNATION
TSM TASK 71-00-00-810-835-A
Component and Harness Intermittent Troubleshooting Procedure for Guidance Troubleshooting Intermittent Faults
AMM 24-41-00-861-002
Energize the Aircraft Electrical Circuits from the External Power
AMM 31-32-00-860-012
Procedure to Get Access to the SYSTEM REPORT/TEST/ENG Page
AMM 31-60-00-860-001
EIS Start Procedure
FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENG 1)
ESPM 204511
ASM 302101
AWM 302101
AMM 31-14-25-400-001
Installation of the 25VU
AMM 31-14-25-860-002
Emergency-Lighting Inhibition With Removal of the Overhead Panel 25VU
AWM 715135
AMM 73-21-01-000-801
Removal of the Electronic Engine Control (EEC)
AMM 73-21-01-400-801
Installation of the Electronic Engine Control (EEC)
AMM 73-21-62-000-802
Removal of the EEC Wiring Harness (WF02)
AMM 73-21-62-400-802
Installation of the EEC Wiring Harness (WF02)
FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENG 2)
ESPM 204511
ASM 302101
AWM 302102
AMM 31-14-25-400-001
Installation of the 25VU
AMM 31-14-25-860-002
Emergency-Lighting Inhibition With Removal of the Overhead Panel 25VU
AWM 715135
AMM 73-21-01-000-801
Removal of the Electronic Engine Control (EEC)
AMM 73-21-01-400-801
Installation of the Electronic Engine Control (EEC)
AMM 73-21-62-000-802
Removal of the EEC Wiring Harness (WF02)
AMM 73-21-62-400-802
Installation of the EEC Wiring Harness (WF02)
3. Fault Confirmation
Subtask 30-21-00-730-073-A ** ON A/C NOT FOR ALL
A. Test
   (1) Energize the aircraft electrical circuits
AMM 24-41-00-861-002.
   (2) Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) AMM 31-60-00-860-001.
   (3) In the cockpit, on the overhead control and indicator panel, on the ANTI ICE section, push the ENG1(2) pushbutton switch (the ON legend comes on).
   (4) Wait three seconds.
   (5) On the overhead control and indicator panel, on the ANTI ICE section, elease the ENG1(2) pushbutton switch (the ON legend goes off).
   (6) On the MCDU screen, get access to the SYSTEM REPORT/TEST/ENG menu page AMM 31-32-00-860-012.
     (a) On the SYSTEM REPORT/TEST/ENG menu page, push the line key adjacent to the FADEC 1(2) A indication.
The EEC 1(2) CHAN A page come into view.
     (b) Push the line key adjacent to the GND SCANNING indication, the GROUND SCANNING menu page comes into view.
       1 If there is a maintenance message, go to the Para. Fault Isolation.
       2 If the maintenance message does not come into view again, do the component and harness intermittent for guidance troubleshooting intermittent faults (Ref. TSM TASK 71-00-00-810-835).
         a If you find no fault, send the engine back to service. Monitor the engine to make sure that the maintenance message does not come into view again.
4. Fault Isolation
WARNING: BE CAREFUL WHEN YOU DO WORK ON THE ENGINE AFTER SHUTDOWN. THE ENGINE CAN STAY HOT FOR A LONG TIME. IF YOU DO NOT OBEY THIS WARNING, INJURY CAN OCCUR.
CAUTION: MAKE SURE YOU REMOVE ELECTRICAL POWER FROM THE EEC BEFORE YOU REMOVE THE ELECTRICAL CONNECTORS. IF YOU DO NOT OBEY THIS INSTRUCTION, DAMAGE TO THE EEC CAN OCCUR.
Subtask 30-21-00-810-085-A ** ON A/C NOT FOR ALL
A. If there is confirmation of the fault:
   (1) FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENG 1)
. Pin A/D3 of the anti-ice pushbutton switch of engine 1 (2DN1) and pin P1/p of the EEC
. Pin A/D1 of the anti-ice pushbutton switch of engine 1 (2DN1) and pin P1/q of the EEC.
     (a) If there is no continuity:
  • Repair the wiring.
  • Install the overhead control and indicating panel 25VU AMM 31-14-25-400-001.
  • Do the test given in Para. 3.
     (b) If there is continuity:
  • Do a continuity check of the wiring AWM 302101 and AWM 715135 between:
    . Pin A/D3 of the anti-ice pushbutton switch of engine 1 (2DN1) and pin 6 of 402VC1.
    . Pin A/D1 of the anti-ice pushbutton switch of engine 1 (2DN1) and pin 5 of 402VC1.
       1 If there is no continuity:
  • Repair the wiring.
  • Install the overhead control and indicating panel 25VU AMM 31-14-25-400-001.
  • Do the test given in Para. 3.
       2 If there is continuity:
   (2) FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENG 2)
  • Remove the overhead control and indicating panel 25VU AMM 31-14-25-860-002.
  • Do a continuity check of the wiring ASM 302101 between:
    . Pin A/D3 of the anti-ice pushbutton switch of engine 2 (2DN2) and pin P1/p of the EEC
    . Pin A/D1 of the anti-ice pushbutton switch of engine 2 (2DN2) and pin P1/q of the EEC.
     (a) If there is no continuity:
  • Repair the wiring.
  • Install the overhead control and indicating panel 25VU AMM 31-14-25-400-001.
  • Do the test given in Para. 3.
     (b) If there is continuity:
  • Do a continuity check of the wiring , AWM 302102 and AWM 715135 between:
    . Pin A/D3 of the anti-ice pushbutton switch of engine 2 (2DN2) and pin 6 of 402VC2.
    . Pin A/D1 of the anti-ice pushbutton switch of engine 2 (2DN2) and pin 5 of 402VC2.
       1 If there is no continuity:
  • Repair the wiring.
  • Install the overhead control and indicating panel 25VU AMM 31-14-25-400-001.
  • Do the test given in Para. 3.
       2 If there is continuity:
5. Close-up
Subtask 30-21-00-942-077-A ** ON A/C NOT FOR ALL
A. Put the aircraft back to its initial configuration.
   (1) Make sure that the work area is clean and clear of tools and other items.
[Rev.8 from Aug 2018] 2026.04.04 04:40:00 UTC
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