W DOC AIRBUS | TSM A320F

Failure of the Oil Temperature Sensors of the IDG 2

TASK 24-00-00-810-815-A
Failure of the Oil Temperature Sensors of the 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 24-21-51-000-803
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)
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 24-00-00-869-051-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 24-00-00-810-062-B ** ON A/C NOT FOR ALL
A. If the fault symptom is identified by the CFDS message IDG2 (E2-4000XU) TEMP SENSE/ GCU2 (1XU2):
NOTE: The CMS message IDG2 (E2-4000XU) TEMP SENSE/ GCU2 (1XU2) can come into view if the electrical connector B is disconnected from the IDG and the 28VDC backup power supplies the related GCU. Before you do the trouble shooting procedure for this CMS message, make sure that the electrical connector B is not disconnected.
  • do an electrical resistance test of the inlet and outlet oil temperature-sensors of the IDG 2 ASM 242101 between:
    . pin B/7 and pin B/8 (100 ohms plus or minus 10 ohms at the ambient temperature of the IDG case)
    . pin B/8 and pin B/9 (100 ohms plus or minus 10 ohms at the ambient temperature of the IDG case).
   (1) If the resistance values are out of the specified limits:
   (2) If the resistance values are in the specified limits:
  • do a check of the wiring of the inlet and outlet oil temperature-sensors ASM 242101 for an open circuit condition between:
    . pin B/7 of the IDG 2 and pin A/9C of the GCU 2
    . pin B/8 of the IDG 2 and pin A/9D of the GCU 2
    . pin B/9 of the IDG 2 and pin A/10C of the GCU 2.
     (a) If there is no continuity:
  • repair or replace as necessary.
     (b) If there is continuity:
Subtask 24-00-00-710-056-G ** 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 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.
Subtask 24-00-00-810-062-E ** ON A/C NOT FOR ALL
C. If the fault symptom is identified by the CFDS message IDG2 (E2-4000XU) TEMP SENSE/ GCU2 (1XU2):
NOTE: The CMS message IDG2 (E2-4000XU) TEMP SENSE/ GCU2 (1XU2) can come into view if the electrical connector B is disconnected from the IDG and the 28VDC backup power supplies the related GCU. Before you do the trouble shooting procedure for this CMS message, make sure that the electrical connector B is not disconnected.
  • Do a check of the resistance of the oil inlet and outlet temperature-sensors of the IDG 2 ASM 242101 between:
    . Pin B/7 and pin B/8 (100 ohms plus or minus 10 ohms at the ambient temperature of the IDG case)
    . Pin B/8 and pin B/9 (100 ohms plus or minus 10 ohms at the ambient temperature of the IDG case).
   (1) If the resistance values are out of the specified limits:
   (2) If the resistance values are in the specified limits:
  • Do a check of the wiring of the oil inlet and outlet temperature-sensors ASM 242101 for an open circuit condition between:
    . Pin B/7 of the IDG 2 and pin A/9C of the GCU 2
    . Pin B/8 of the IDG 2 and pin A/9D of the GCU 2
    . Pin B/9 of the IDG 2 and pin A/10C of the GCU 2.
     (a) If there is no continuity:
  • Repair or replace as necessary.
     (b) If there is continuity:
Subtask 24-00-00-710-056-C ** ON A/C NOT FOR ALL
D. 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.
5. Close-up
Subtask 24-00-00-860-051-C ** 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 24-00-00-860-051-G ** 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 04:26:07 UTC
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