W DOC AIRBUS | TSM A320F

Failure of the FAULT Light of the ELEC/GEN 1 Pushbutton Switch

TASK 24-20-00-810-886-A
Failure of the FAULT Light of the ELEC/GEN 1 Pushbutton Switch

1. Possible Causes
  • GCU-1 [1XU1]
  • wiring
  • BOARD-ANN LT TEST & INTFC [10LP]
2. Job Set-up Information
 A. Referenced Information
REFERENCE
DESIGNATION
ASM 242202
AMM 24-22-34-000-001
Removal of the GCU-1(2)
AMM 24-22-34-400-001
Installation of the GCU-1(2)
AMM 24-41-00-740-002
Operational Check of the GAPCU via the CFDS
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 31-60-00-860-001
EIS Start Procedure
AMM 31-60-00-860-002
EIS Stop Procedure
AMM 33-14-33-000-001
Removal of the Annunciator-Light Test and Interface-Board
AMM 33-14-33-400-001
Installation of the Annunciator-Light Test and Interface-Board
AMM 71-00-00-710-003
Engine Automatic Start
AMM 71-00-00-710-028
Engine Shutdown
AMM 71-00-00-860-814
Shutdown of the Engine
AMM 71-00-00-860-823
Start the Engine (Normal Automatic Start)
3. Fault Confirmation
Subtask 24-20-00-860-184-A ** ON A/C NOT FOR ALL
A. Job Set-up
   (1) Energize the aircraft electrical circuits from the external power AMM 24-41-00-861-002.
Subtask 24-20-00-710-152-A ** ON A/C NOT FOR ALL
B. Test
   (1) If on the ELEC panel 35VU, the AVAIL legend of the ELEC/GEN 1 pushbutton switch (3XU1) is on:
  • do the trouble shooting given in Para.4.A.
   (2) If on the ELEC panel 35VU, the AVAIL legend of the ELEC/GEN 1 pushbutton switch (3XU1) is off:
  • do the trouble shooting given in Para.4.B.
4. Fault Isolation
Subtask 24-20-00-810-211-A ** ON A/C NOT FOR ALL
A. If the test confirms the fault:
Subtask 24-20-00-810-212-A ** ON A/C NOT FOR ALL
B. If the test confirms the fault:
  • do a check of the wiring ASM 242202 for a short to ground between:
    . pin A/5G of the GCU 1 and pin A/4 of the annunciator light test and interface board (10LP)
    . pin A/3 of the annunciator light test and interface board (10LP) and pin A/7 of the diode module 2422VD
    . pin A/22 of the diode module 2422VD and pin A/14 of the diode module 2420VD.
   (1) If there is a short to ground:
  • repair or replace as necessary.
   (2) If there is no short to ground:
   (3) If the fault continues:
Subtask 24-20-00-710-150-C ** ON A/C NOT FOR ALL
C. Do this operational test to make sure that the system operates correctly.
   (1) Aircraft Maintenance Configuration
     (a) Energize the aircraft electrical circuits
AMM 24-41-00-861-002.
     (b) Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only)
AMM 31-60-00-860-001.
   (2) In the cockpit, on the ELEC panel 35VU:
  • Push, release and push again the GEN 1 pushbutton switch (3XU1).
   (3) Do the BITE test of the GAPCU AMM 24-41-00-740-002.
   (4) Start engine 1 AMM 71-00-00-860-823.
   (5) Do this test:
ACTION
RESULT
On the ECAM control panel:
  • Push the ELEC key to get the ELEC page.
On the lower ECAM DU:
  • The correct electrical parameters of GEN 1 are shown and GEN 1 supplies the AC1 busbar.
Subtask 24-20-00-710-150-F ** ON A/C NOT FOR ALL
C. Do this operational test to make sure that the system operates correctly.
   (1) Aircraft Maintenance Configuration
     (a) Energize the aircraft electrical circuits
AMM 24-41-00-861-002.
     (b) Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only)
AMM 31-60-00-860-001.
   (2) On the ELEC panel 35VU:
  • push, release and push again the GEN 1 pushbutton switch (3XU1).
   (3) Do the operational test of the GAPCU AMM 24-41-00-740-002.
   (4) Start the engine 1 AMM 71-00-00-710-003.
   (5) Do this test:
ACTION
RESULT
On the ECAM control panel:
  • get the ELEC page.
On the lower ECAM DU:
  • the correct electrical parameters of the GEN 1 are shown and the AC1 busbar is supplied by the GEN 1.
5. Close-up
Subtask 24-20-00-860-185-C ** ON A/C NOT FOR ALL
A. Put the aircraft back to its initial configuration.
   (1) Stop engine 1 AMM 71-00-00-860-814.
   (2) Do the EIS stop procedure
AMM 31-60-00-860-002.
   (3) On the ECAM control panel, set the UPPER DISPLAY and LOWER DISPLAY potentiometers to OFF.
   (4) De-energize the aircraft electrical circuits
AMM 24-41-00-862-002.
Subtask 24-20-00-860-185-F ** ON A/C NOT FOR ALL
A. Put the aircraft back to its initial configuration.
   (1) Stop the engine 1 AMM 71-00-00-710-028.
   (2) Do the EIS stop procedure
AMM 31-60-00-860-002.
   (3) On the ECAM control panel, set the UPPER DISPLAY and LOWER DISPLAY potentiometers to OFF.
   (4) De-energize the aircraft electrical circuits
AMM 24-41-00-862-002.
[Rev.8 from Aug 2018] 2026.04.04 04:26:18 UTC
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