W DOC AIRBUS | TSM A320F

Low Oil Pressure of IDG 2

TASK 24-20-00-810-848-A
Low Oil Pressure of IDG 2

1. Possible Causes
2. Job Set-up Information
 A. Referenced Information
REFERENCE
DESIGNATION
ASM 242101
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)
AMM 24-22-33-000-001
Removal of the EGIU-1(2)
AMM 24-22-33-400-002
Installation of the EGIU-1(2)
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 24-20-00-700-097-A ** ON A/C NOT FOR ALL
A. Test
Not applicable.
NOTE: As GEN 2 was set to OFF because of a true failure, the fault confirmation is not necessary.
4. Fault Isolation
Subtask 24-20-00-810-086-B ** ON A/C NOT FOR ALL
A. If the fault symptom is identified by the CFDS message IDG 2 LOW OIL PRESSURE and the upper ECAM DU warning IDG 2 OIL LO PR:
   (1) Remove GCU2 AMM 24-22-34-000-001.
   (2) Remove EGIU2 AMM 24-22-33-000-001.
   (3) Disconnect connector C from IDG2, and do a check for a short to ground at pin AA/15D of GCU-2 (1XU2) ASM 242101.
     (a) If there is a short to ground:
     (b) If there is no short to ground:
       1 If the fault continues:
       2 If the fault continues:
Subtask 24-20-00-810-249-A ** ON A/C NOT FOR ALL
B. If the fault continues:
   (1) Remove EGIU-2 AMM 24-22-33-000-001, GCU2 AMM 24-22-34-000-001 and the wiring harness from IDG2 connector A.
   (2) Do a check of the wiring for an open circuit or a short to ground between:
- Pin AA/4B of EGCIU-2 (22XU2) and pin B1 of the IDG1 disconnect control-relay (4XT) ASM 242101
- Pin AA/3B of GCU2 (1XU2) and pin A/12 of the IDG2 wiring harness ASM 242101
- Pin A1 of the IDG2 disconnect control-relay (4XT) and the first branch point ASM 242101
- Pin A/13 of IDG2 (4000XU) and the ground ASM 242101.
     (a) If the wiring is not correct:
  • Repair it.
     (b) If the wiring is correct:
  • Install EGIU-2 AMM 24-22-33-400-002 and GCU2 AMM 24-22-34-400-001.
  • Do a check of the wiring for an open circuit or a short to ground between:
    - Pin B3 of the ELEC/IDG2 pushbutton switch (6XT) and the first branch point ASM 242101
    - Pin B/1 of the ELEC/IDG2 pushbutton switch (6XT) and pin B/3 of the relay (8XT) ASM 242101
    - Pin B2 of the relay (8XT) and pin X1 of the IDG1 disconnect control-relay (4XT) ASM 242101
    - Pin B2 of the IDG2 disconnect control-relay (4XT) and the ground ASM 242101
    - Pin X2 of the IDG2 disconnect control-relay (4XT) and the first branch point ASM 242101.
       1 If the wiring is not correct:
  • Repair it.
       2 If the wiring is correct:
  • Remove EGIU-2 (22XU2) AMM 24-22-33-000-001.
  • Disonnect connector A of IDG2.
  • Do a check and repair the wiring for a short to ground between pin AA/6B of EGIU-2 (22XU2) and pin A/14 of IDG2 (4000XU) ASM 242101.
  • Install EGIU-2 (22XU2) AMM 24-22-33-400-002.
Subtask 24-20-00-860-100-A ** ON A/C NOT FOR ALL
C. 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 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 engine 2 AMM 71-00-00-710-003.
Subtask 24-20-00-710-075-A ** ON A/C NOT FOR ALL
D. 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 are shown and the AC 2 busbar is supplied by GEN 2.
5. Close-up
Subtask 24-20-00-860-101-A ** ON A/C NOT FOR ALL
A. Put the aircraft back to its initial configuration.
   (1) Stop 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 04:26:14 UTC
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