W DOC AIRBUS | TSM A320F

Loss of the GEN 2 (Failure of the Electrical Wiring between the IDG 2 and the GCU 2, Voltage Regulation Function)

TASK 24-20-00-810-816-A
Loss of the GEN 2 (Failure of the Electrical Wiring between the IDG 2 and the GCU 2, Voltage Regulation Function)

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
F IDG 1(2) Exciter Field Resistance Versus Temperature
3. Fault Confirmation
Subtask 24-20-00-700-061-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
CAUTION: BEFORE YOU START THE CHECK OF IDG WIRING THAT INCLUDES CONNECTORS, EXAMINE EACH CONNECTOR TO MAKE SURE THAT THERE IS NO CONTAMINATION IN IT. IF YOU FIND CONTAMINATION, CLEAN THE CONNECTOR AND CONNECT IT AGAIN. IF THE FAILURE CONTINUES, DO THE TROUBLE SHOOTING PROCEDURE AS GIVEN BELOW.
Subtask 24-20-00-810-061-B ** ON A/C NOT FOR ALL
A. If the fault symptom is identified by the CFDS message CHECK GCU 2 PIN C1,C5/ IDG 2 PIN A9 A10 WIRING and the upper ECAM DU warning GEN 2 FAULT:
  • Do a check of the wiring for open circuit or short to ground between respectively the GCU 2 pins C/1, C/5 and the IDG 2 pins A/9 and A/10 ASM 242201.
   (1) If the wiring is not correct:
  • Repair it.
   (2) If the wiring is correct:
     (a) If the resistance is out of tolerance:
     (b) If the resistance is correct:
   (3) If the fault continues:
  • Do a check of the wiring for open circuit or short to ground between respectively the IDG 2 pins B/12, B/13, B/14 and the GCU 2 pins C/2, C/3, C/4 ASM 242201.
Subtask 24-20-00-860-072-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 24-20-00-710-061-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 24-20-00-860-073-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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