W DOC AIRBUS | TSM A320F

Loss of the Generator 2 (Pins D, E, F, R, P, N of BTC 2 Shorted to Ground)

TASK 24-20-00-810-814-A
Loss of the Generator 2 (Pins D, E, F, R, P, N of BTC 2 Shorted to Ground)

1. Possible Causes
  • feeder
  • IDG2 feeders
  • IDG [4000XU]
  • wiring
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 242202
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 24-20-00-700-105-A ** ON A/C NOT FOR ALL
A. Test
   (1) Read the Class 1 Faults of the GCU or GPCU from the CFDS.
NOTE: As the GEN2 was set to OFF because a true failure, the fault confirmation is not necessary.
4. Fault Isolation
Subtask 24-20-00-810-094-A ** ON A/C NOT FOR ALL
A. If the fault symptom is identified by the maintenance message CHECK BTC2 PIN D, E, F, R, P,N SHORT TO GROUND and by the upper ECAM DU warning GEN2 FAULT:
  • do a check of the feeder for short to ground between respectively:
    . the pins A/R, A/P, A/N of the GLC2 and the main bus,
    . the pins A/M, A/L, A/K of the GLC2 and the pins A/D, A/E, A/F of the BTC2,
    . the pins A/G, A/H, A/J of the BTC2 and the pins A/J, A/H, A/G of the APU GLC ASM 242202.
   (1) If the wiring is not correct:
  • repair it.
   (2) If the wiring is correct:
  • do a check of the IDG2 feeders for intermittent short to ground between respectively the pins A/T1, B/T2, C/T3 of the IDG2 and the pins A/D, A/E, A/F of the GLC2.
   (3) If the wiring is not correct:
  • repair it.
   (4) If the wiring is correct:
   (5) If the fault continues:
  • do a check and repair the wiring between respectively the pins A1, A6, A7, A8 of the IDG2 and the pins B/13D, B/13A, B/13B, B/13C of the GCU2.
Subtask 24-20-00-810-094-B ** ON A/C NOT FOR ALL
A. If the fault symptom is identified by the maintenance message CHECK BTC2 PIN D, E, F, R, P,N SHORT TO GROUND and by the upper ECAM DU warning GEN2 FAULT:
  • do a check of the feeder for short to ground between respectively:
    . the pins 4, 5, 6 of the generator 2 contactor module (30XN2) and the main bus,
    . the pins 10, 11, 12 of the generator 2 contactor module (30XN2) and the pins 10, 11, 12 of the APU/EXT power contactor module (29XN) ASM 242202.
   (1) If the wiring is not correct:
  • repair it.
   (2) If the wiring is correct:
  • do a check of the IDG2 feeders for intermittent short to ground between respectively the pins A/T1, B/T2, C/T3 of the IDG2 and the pins 1, 2, 3 of the generator 2 contactor module (30XN2).
   (3) If the wiring is not correct:
  • repair it.
   (4) If the wiring is correct:
   (5) If the fault continues:
  • do a check and repair the wiring between respectively the pins A1, A6, A7, A8 of the IDG2 and the pins B/13D, B/13A, B/13B, B/13C of the GCU2.
Subtask 24-20-00-710-081-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 panel 35VU:
  • push, release and push again the GEN2 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.
   (5) 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 GEN2 are shown and AC2 busbar is supplied by GEN2.
5. Close-up
Subtask 24-20-00-860-109-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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