W DOC AIRBUS | TSM A320F

Failure of the Generator Control Unit 1

TASK 24-20-00-810-801-A
Failure of the Generator Control Unit 1

1. Possible Causes
  • GCU-1 [1XU1]
  • sockets of the 400VC1
2. Job Set-up Information
 A. Fixtures, Tools, Test and Support Equipment
REFERENCE
QTY
DESIGNATION
No specific
1
DYNAMOMETER 15 DAN (33 LBF) - PULL
 B. Referenced Information
REFERENCE
DESIGNATION
ESPM 2048230
AWM 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 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 24-20-00-700-050-A ** ON A/C NOT FOR ALL
A. Test
Not applicable.
NOTE: As the GEN 1 was set to OFF because of a true failure, the fault confirmation is not necessary.
4. Fault Isolation
Subtask 24-20-00-810-050-A ** ON A/C NOT FOR ALL
A. If the fault symptom is identified by the CFDS message GCU 1 and the upper ECAM DU warning GEN 1 FAULT:
   (1) If the fault continues:
  • do a pin retention check ESPM 2048230 of the sockets of the 400VC1 AWM 242201. Use a DYNAMOMETER 15 DAN (33 LBF) - PULL, the CANNON value is 1.2 daN (2.7 lbf) minimum and the SOURIAU value is 2.8 daN (6.3 lbf) minimum, in relation to pin/socket type used.
Subtask 24-20-00-860-050-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 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.
Subtask 24-20-00-710-050-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 1 are shown and AC 1 busbar is supplied by GEN 1.
5. Close-up
Subtask 24-20-00-860-051-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 04:26:10 UTC
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