W DOC AIRBUS | TSM A320F

Loss of the GEN2 (Failure of the GLC 2)

TASK 24-20-00-810-832-A
Loss of the GEN2 (Failure of the GLC 2)

1. Possible Causes
2. Job Set-up Information
 A. Referenced Information
REFERENCE
DESIGNATION
ASM 242203
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 24-22-55-000-001
Removal of the Contactors
AMM 24-22-55-400-002
Installation of the Contactors
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 31-60-00-860-002
EIS Stop Procedure
AMM 71-00-00-710-003
Engine Automatic Start
AMM 71-00-00-710-028
Engine Shutdown
3. Fault Confirmation
Subtask 24-20-00-700-111-A ** ON A/C NOT FOR ALL
A. Test
Not applicable.
NOTE: As the GEN2 was set to OFF because of a true failure, the fault confirmation is not necessary.
4. Fault Isolation
Subtask 24-20-00-810-099-A ** ON A/C NOT FOR ALL
A. If the fault symptom is identified by the CFDS message BTC2 OR/AND GLC2 and the warnings GEN2 FAULT and AC BUS2 FAULT on the upper ECAM DU:
   (1) If the fault continues:
     (a) If the fault continues:
  • do a check and repair the wiring :
    . from the pin B/2D of the GCU2 (1XU2) to the pin B/25 of the GLC2 (9XU2) and to the pin B/10 of the BTC2 (11XU2)
    . from the pin B/23 of the GLC2 (9XU2) and from the pin B/12 of the BTC2 (11XU2) to the pin B/3 of the GLC2 (9XU2), through the relay (4XU2)
    . from the pin B/5 of the GLC2 (9XU2) to the ground
    . from the pin B/12C of the GCU2 (1XU2) to the pin A/X1 of the relay (4XU2)
    . from the pin A/X2 of the relay (4XU2) to the ground ASM 242203.
Subtask 24-20-00-710-085-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 (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.
   (5) Do this test:
ACTION
RESULT
On the ECAM control panel:
  • push the ELEC key to get the ELEC page.
On the lower ECAM display unit:
  • the correct electrical parameters of GEN 2 come into view
  • the AC 2 busbar is supplied by the GEN 2.
5. Close-up
Subtask 24-20-00-860-113-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) Do the EIS stop procedure AMM 31-60-00-860-002.
   (3) De-energize the aircraft electrical circuits
AMM 24-41-00-862-002.
[Rev.8 from Aug 2018] 2026.04.04 04:26:13 UTC
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