W DOC AIRBUS | TSM A320F

Loss of the GEN 2 (Failure of the Electrical Wiring between the IDG 2, GLC 2 and GCU 2)

TASK 24-20-00-810-811-A
Loss of the GEN 2 (Failure of the Electrical Wiring between the IDG 2, GLC 2 and GCU 2)

1. Possible Causes
2. Job Set-up Information
 A. Referenced Information
REFERENCE
DESIGNATION
AMM 24-21-51-000-040
Removal of the Integrated Drive Generator - IDG 1(2)
AMM 24-21-51-400-040
Installation of the Integrated Drive Generator - IDG 1(2)
ASM 242201
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 24-41-00-740-004
Operational Check of the GPCU 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 71-00-00-710-003
Engine Automatic Start
AMM 71-00-00-710-028
Engine Shutdown
3. Fault Confirmation
Subtask 24-20-00-700-058-A ** ON A/C NOT FOR ALL
A. Test
Not applicable.
NOTE: As the GEN 2 was set to OFF because of a true failure, the fault confirmation is not necessary.
4. Fault Isolation
Subtask 24-20-00-810-058-B ** ON A/C NOT FOR ALL
A. If the fault symptom is identified by the CFDS message CHECK IDG 2 PHASE SEQ and the upper ECAM DU warning GEN 2 FAULT.
  • Do a check of the wiring for phase inversion on the feeders between respectively:
    . the IDG 2 pins T1, T2, T3 and the GLC 2 pins D, E, F,
    . the GLC 2 pins D, E, F and the GCU 2 pins B/1A, B/2B, C/3A ASM 242201.
   (1) If the wiring is not correct:
  • repair it.
   (2) If the wiring is correct:
     (a) If the fault continues:
Subtask 24-20-00-810-058-D ** ON A/C NOT FOR ALL
A. If the fault symptom is identified by the CFDS message CHECK IDG 2 PHASE SEQ and the upper ECAM DU warning GEN 2 FAULT.
  • Do a check of the wiring for phase inversion on the feeders between respectively:
    . the IDG 2 pins T1, T2, T3 and the generator 2 contactor module (30XN2) pins 1, 2, 3,
    . the generator 2 contactor module (30XN2) pins 1, 2, 3 and the GCU 2 pins B/1A, B/2B, C/3A ASM 242201.
   (1) If the wiring is not correct:
  • repair it.
   (2) If the wiring is correct:
     (a) If the fault continues:
Subtask 24-20-00-860-066-A ** ON A/C NOT FOR ALL
B. 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 2 pushbutton switch (3XU2).
   (3) Do the operational check of the GPCU with the CFDS AMM 24-41-00-740-004.
   (4) Start the engine 2 AMM 71-00-00-710-003.
Subtask 24-20-00-710-058-A ** ON A/C NOT FOR ALL
C. Do this test:
ACTION
RESULT
On the ECAM control panel:
  • get the ELEC page.
On the lower ECAM display unit:
  • the correct electrical parameters of GEN 2 are shown and AC 2 busbar is supplied by GEN 2.
5. Close-up
Subtask 24-20-00-860-067-A ** ON A/C NOT FOR ALL
A. Put the aircraft back to its initial configuration.
   (1) Stop the engine 2 AMM 71-00-00-710-028.
   (2) On the ECAM control panel, set the UPPER DISPLAY and LOWER DISPLAY potentiometers to OFF.
   (3) De-energize the aircraft electrical circuits
AMM 24-41-00-862-002.
[Rev.8 from Aug 2018] 2026.04.04 04:26:10 UTC
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