W DOC AIRBUS | TSM A320F

Low Oil Pressure of the Integrated Drive Generator 2

TASK 24-20-00-810-905-A
Low Oil Pressure of the Integrated Drive Generator 2

1. Possible Causes
2. Job Set-up Information
 A. Referenced Information
REFERENCE
DESIGNATION
AMM 24-21-00-210-047
Visual Inspection of the IDG for Oil Leaks and Check of the Electrical Circuits
AMM 24-21-00-210-806
Visual Inspection of the IDG for Oil Leaks and Check of the Electrical Circuits
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 24-21-51-400-044
Installation of the Integrated Drive Generator - IDG 1(2) (New EPGS)
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 24-20-00-869-089-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 24-20-00-810-156-B ** ON A/C NOT FOR ALL
A. If the fault symptom is identified by the CFDS message IDG2 (E2-4000XU) LOW OIL PRESSURE and the upper ECAM-DU warning IDG 2 OIL LO PR:
CAUTION: AFTER AN IDG OIL LOW PRESSURE (LO PR) OR OVERHEAT (OVHT) CONDITION:
  • DO NOT CONNECT THE DISCONNECTED IDG1(2) AGAIN, AND
  • REPLACE IDG1(2).
IF YOU DO NOT OBEY THESE INSTRUCTIONS, YOU WILL INCREASE THE DAMAGE TO IDG1(2) AT THE NEXT ENGINE START.
   (1) Replace the engine 2 IDG [4000XU] AMM 24-21-51-000-040 and AMM 24-21-51-400-044.
   (2) If the fault continues:
     (a) If the BITE test gives the message TEST FAILED:
  • Push the line key adjacent to the TEST FAILED message.
       1 If the maintenance message GCU2 (1XU2) comes into view:
     (b) If the BITE test gives the message TEST PASSED:
  • Do a check of the wiring for a short to ground between ASM 242101:
    - Pin C/A of the IDG 2 and pin AA/4A of the GCU 2.
       1 If the wiring is not correct:
  • Repair it or replace as necessary.
       2 If the wiring is correct:
  • Do a check of the wirng for an open circuit between ASM 242101:
    - Pin C/B of the IDG 2 and the ground.
         a If the wiring is not correct:
Repair it or replace as necessary.
         b If the wiring is correct:
  • Continue the Trouble shooting.
   (3) If the fault continues:
  • Do a visual inspection of the IDG 2, the external oil-circuit tubing and the fuel/oil heat exchanger for oil leaks AMM 24-21-00-210-047.
     (a) If you find leaks:
  • Repair or replace the components as necessary to remove the oil leaks.
     (b) If you find no leaks:
Subtask 24-20-00-810-156-E ** ON A/C NOT FOR ALL
A. If the fault symptom is identified by the CFDS message IDG2 (E2-4000XU) LOW OIL PRESSURE and the upper ECAM-DU warning IDG 2 OIL LO PR:
CAUTION: AFTER AN IDG OIL LOW PRESSURE (LO PR) OR OVERHEAT (OVHT) CONDITION:
  • DO NOT CONNECT THE DISCONNECTED IDG1(2) AGAIN, AND
  • REPLACE IDG1(2).
IF YOU DO NOT OBEY THESE INSTRUCTIONS, YOU WILL INCREASE THE DAMAGE TO IDG1(2) AT THE NEXT ENGINE START.
   (1) Replace IDG-ENG 2 [4000XU2] AMM 24-21-51-000-803 and AMM 24-21-51-400-803.
   (2) If the fault continues:
     (a) If the BITE test gives the message TEST FAILED:
  • Push the line key adjacent to the TEST FAILED message.
       1 If the maintenance message GCU2 (1XU2) comes into view:
     (b) If the BITE test gives the message TEST PASSED:
  • Do a check of the wiring for a short to ground between ASM 242101:
    - Pin A/12 of the IDG 2 and pin AA/4A of the GCU 2.
       1 If the wiring is not correct:
  • Repair it or replace as necessary.
       2 If the wiring is correct:
  • Do a check of the wiring for an open circuit between ASM 242101:
    - Pin A/3 of the IDG 2 and the ground.
         a If the wiring is not correct:
  • Repair it or replace as necessary.
         b If the wiring is correct:
  • Continue the Trouble shooting.
   (3) If the fault continues:
  • Do a visual inspection of the IDG 2, the external oil-circuit tubing and the fuel/oil heat exchanger for oil leaks AMM 24-21-00-210-806.
     (a) If you find leaks:
  • Repair or replace the components as necessary to remove the oil leaks.
     (b) If you find no leaks:
Subtask 24-20-00-810-251-A ** ON A/C NOT FOR ALL
B. If the fault continues:
   (1) Remove 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 ASM 242101:
- Pin AA/2J of the GCU2 (1XU2) and the pin B/1 of the IDG2 disconnect control-relay (4XT)
- Pin A1 of the IDG2 disconnect control-relay (4XT) and the pin A/12 of the IDG2 (4000XU)
- Pin A/13 of the IDG2 (4000XU) and the ground.
     (a) If the wiring is not correct:
     (b) If the wiring is correct:
  • Install GCU2 AMM 24-22-34-400-001 and the wiring harness from IDG2 connector A.
  • Do a check of the wiring for a short to ground between ASM 242101:
    - Pin B3 of the ELEC/IDG2 pushbutton switch (6XT) and the first branch point
    - Pin B/1 of the ELEC/IDG2 pushbutton switch (6XT) and the pin B/3 of the relay (8XT)
    - Pin B2 of the relay (8XT) and the pin X1 of the IDG1 disconnect control-relay (4XT)
       1 If the wiring is not correct:
  • Repair it.
       2 If the wiring is correct:
  • Do a check and repair the wiring for an open circuit or a short to ground between ASM 242101:
    - Pin B2 of the IDG2 disconnect control-relay (4XT) and the second branch point
    - Pin A2 of the IDG2 disconnect control-relay (4XT) and the first branch point.
    - Pin X2 of the IDG2 disconnect control-relay (4XT) and the ground.
Subtask 24-20-00-710-134-C ** 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) 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 24-20-00-710-134-G ** 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 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 24-20-00-860-159-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 24-20-00-860-159-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 04:39:03 UTC
"AVIABRAIN" 2025