W DOC AIRBUS | TSM A320F

Loss of the GEN 1 (Failure of the GLC 1)

TASK 24-20-00-810-824-A
Loss of the GEN 1 (Failure of the GLC 1)

1. Possible Causes
  • Generator 1 contactor-module 30XN1
  • Terminal block 1999VT
  • Terminal block 400VT1
  • Terminal blocks T1, T2, T3 and N of IDG 1
  • Receptacle 400VC1
  • GLC-1 [9XU1]
  • GCU-1 [1XU1]
  • wiring
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 24-22-55-000-001
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 24-20-00-700-110-A ** ON A/C NOT FOR ALL
A. Test
Not applicable.
NOTE: As the GEN1 was set to OFF because of a true failure, the fault confirmation is not necessary.
4. Fault Isolation
Subtask 24-20-00-810-098-A ** ON A/C NOT FOR ALL
A. If the fault symptom is identified by the CFDS message BTC1 OR/AND GLC1 and the warnings GEN1 FAULT and AC BUS1 FAULT on the upper ECAM DU:
   (1) Do a visual inspection and repair or replace as necessary:
  • Generator 1 contactor-module 30XN1
  • Terminal block 1999VT
  • Terminal block 400VT1
  • Terminal blocks T1, T2, T3 and N of IDG 1
  • Receptacle 400VC1 .
   (2) Replace GLC-1 [9XU1] AMM 24-22-55-000-001 and AMM 24-22-55-400-002.
     (a) If the fault continues:
       1 If the fault continues:
  • Do a check and repair the wiring :
    . from the pin B/2D of the GCU1 (1XU1) to the pin B/25 of the GLC1 (9XU1) and to the pin B/10 of the BTC1 (11XU1)
    . from the pin B/23 of the GLC1 (9XU1) and from the pin B/12 of the BTC1 (11XU1) to the pin B/3 of the GLC1 (9XU1), through the relay (4XU1)
    . from the pin B/5 of the GLC1 (9XU1) to the ground
    . from the pin B/12C of the GCU1 (1XU1) to the pin X1 of the relay (4XU1), through the relay (20XU)
    . from the pin X2 of the relay (4XU1) to the ground ASM 242202.
Subtask 24-20-00-710-084-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 1 pushbutton switch (3XU1).
   (3) Do the operational check of the GPCU with the CFDS AMM 24-41-00-740-004.
   (4) Start the engine 1 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 1 come into view
  • the AC 1 busbar is supplied by the GEN 1.
5. Close-up
Subtask 24-20-00-860-112-A ** 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) De-energize the aircraft electrical circuits
AMM 24-41-00-862-002.
[Rev.8 from Aug 2018] 2026.04.04 04:26:12 UTC
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