W DOC AIRBUS | TSM A320F

Failure of the Phase B of the IDG 2

TASK 24-20-00-810-956-A
Failure of the Phase B of the IDG 2

1. Possible Causes
  • Generator 2 contactor module 30XN2
  • Terminal block 1998VT
  • Terminal block 400VT2
  • Terminal block T1, T2, T3, N of IDG 2
  • Terminal block 440VT2
  • IDG-ENG 2 [4000XU2]
  • feeder
  • GCU-2 [1XU2]
  • Receptacle 400VC2
  • IDG [4000XU]
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 24-21-51-000-803
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 24-21-51-400-803
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 24-41-00-740-002
Operational Check of the GAPCU 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
AMM 71-00-00-860-814
Shutdown of the Engine
AMM 71-00-00-860-823
Start the Engine (Normal Automatic Start)
3. Fault Confirmation
Subtask 24-20-00-869-118-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
Subtask 24-20-00-810-229-B ** ON A/C NOT FOR ALL
A. If the fault symptom is identified by the CFDS message WRG: GEN2 FEEDER PHASE B/ IDG2 (E2-4000XU) and the upper ECAM-DU warning GEN 2 FAULT:
   (1) Do a visual inspection and repair or replace if necessary:
  • Generator 2 contactor module 30XN2
  • Terminal block 1998VT
  • Terminal block 400VT2
  • Terminal block T1, T2, T3, N of IDG 2
  • Terminal block 440VT2 .
   (2) If the fault continues, do a check of the resistance of the main stator windings of IDG 2 ASM 242201 between:
  • Terminal T1 and N (7 milliohms plus or minus 1 milliohm)
  • Terminal T2 and N (7 milliohms plus or minus 1 milliohm)
  • Terminal T3 and N (7 milliohms plus or minus 1 milliohm).
     (a) If the resistance values are out of the specified limits:
     (b) If the resistance values are in the specified limits:
  • Do a check of the feeder ASM 242201 for an open circuit condition or a high resistance between terminals T1, T2, T3 of IDG 2 and pins 1, 2, 3 of the generator 2 contactor module (30XN2).
       1 If the feeder is not correct:
  • Repair or replace the feeder as necessary.
       2 If the feeder is correct:
         a If the fault continues:
Subtask 24-20-00-710-167-B ** 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) In the cockpit, on the ELEC panel 35VU:
  • Push, release and push again the GEN 2 pushbutton switch (3XU2).
   (3) Do the BITE test of the GAPCU AMM 24-41-00-740-002.
   (4) Start engine 2 AMM 71-00-00-860-823.
   (5) Do this test:
ACTION
RESULT
On the ECAM control panel:
  • Push the ELEC key to get the ELEC page.
On the lower ECAM DU:
  • The correct electrical parameters of GEN 2 are shown and GEN 2 supplies the AC2 busbar.
Subtask 24-20-00-810-229-E ** ON A/C NOT FOR ALL
C. If the fault symptom is identified by the CFDS message WRG: GEN2 FEEDER PHASE B/ IDG2 (E2-4000XU) and the upper ECAM-DU warning GEN 2 FAULT:
   (1) Do a visual inspection and repair or replace if necessary:
  • Generator 2 contactor module 30XN2
  • Terminal block 1998VT
  • Terminal block 400VT2
  • Terminal block T1, T2, T3, N of IDG 2
  • Receptacle 400VC2 .
   (2) If the fault continues, do a check of the resistance of the main stator windings of IDG 2 ASM 242201 between:
  • Terminal T1 and N (7 milliohms plus or minus 1 milliohm)
  • Terminal T2 and N (7 milliohms plus or minus 1 milliohm)
  • Terminal T3 and N (7 milliohms plus or minus 1 milliohm).
     (a) If the resistance values are out of the specified limits:
     (b) If the resistance values are in the specified limits:
  • Do a check of the feeder ASM 242201 for an open circuit condition or a high resistance between terminals T1, T2, T3 of IDG 2 and pins 1, 2, 3 of the generator 2 contactor module (30XN2).
       1 If the feeder is not correct:
  • Repair or replace the feeder as necessary.
       2 If the feeder is correct:
         a If the fault continues:
Subtask 24-20-00-710-167-E ** ON A/C NOT FOR ALL
D. Test
   (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 test of the GAPCU AMM 24-41-00-740-002.
   (4) Start the engine 2 AMM 71-00-00-710-003.
   (5) Do this test:
ACTION
RESULT
On the ECAM control panel:
  • get the ELEC page.
On the lower ECAM DU:
  • the correct electrical parameters of the GEN 2 are shown and the AC2 busbar is supplied by the GEN 2.
5. Close-up
Subtask 24-20-00-860-204-B ** ON A/C NOT FOR ALL
A. Put the aircraft back to its initial configuration.
   (1) Stop engine 2 AMM 71-00-00-860-814.
   (2) Do the EIS stop procedure
AMM 31-60-00-860-002.
   (3) On the ECAM control panel, set the UPPER DISPLAY and LOWER DISPLAY potentiometers to OFF.
   (4) De-energize the aircraft electrical circuits
AMM 24-41-00-862-002.
Subtask 24-20-00-860-204-E ** 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) On the ECAM control panel, set the UPPER DISPLAY and LOWER DISPLAY potentiometers to OFF.
   (4) De-energize the aircraft electrical circuits
AMM 24-41-00-862-002.
[Rev.8 from Aug 2018] 2026.04.04 04:26:27 UTC
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