W DOC AIRBUS | TSM A320F

IDG 2 Manual Disconnect

TASK 24-20-00-810-907-A
IDG 2 Manual Disconnect

1. Possible Causes
2. Job Set-up Information
 A. Referenced Information
REFERENCE
DESIGNATION
AMM 12-13-24-612-041
IDG Servicing - Filling of the IDG with Oil or Addition of Oil after a level Check
AMM 12-13-24-612-803
IDG Servicing - Filling of the IDG with Oil or Addition of Oil after a Level Check
AMM 24-21-00-210-046
Check IDG Oil Level and Differential Pressure Indicator (DPI)
AMM 24-21-00-210-047
Visual Inspection of the IDG for Oil Leaks and Check of the Electrical Circuits
AMM 24-21-00-210-805
Check of the Oil Level and Oil-Filter Differential-Pressure Indicator (DPI)
AMM 24-21-00-210-806
Visual Inspection of the IDG for Oil Leaks and Check of the Electrical Circuits
AMM 24-21-00-210-807
Inspection of the IDG Oil Charge and Scavenge Filter Elements
AMM 24-21-00-710-803
Operational Test of the IDG Disconnect and Reconnect (Reset) Function - Engine Static
AMM 24-21-00-720-041
Operational Test of the IDG Disconnect and Reconnect (Reset) Function - Engine in Operation
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 24-20-00-869-104-A ** ON A/C NOT FOR ALL
A. Test
Not applicable.
NOTE: As the GEN 2 was set to off because of a true fault, the fault confirmation is not necessary.
4. Fault Isolation
Subtask 24-20-00-810-203-B ** ON A/C NOT FOR ALL
A. If the fault symptom is identified by the maintenance message IDG2 (E2-4000XU) MANUAL DISCONNECT and by the upper ECAM-DU warning IDG 2 DISCONNECTED:
NOTE: You can find this message with other CFDS fault messages. First, do the trouble shooting for all the other CFDS fault messages.
   (1) Read the flight log book and the maintenance log book to identify the cause of the IDG disconnect.
   (2) If there is no cause or if the cause is unknown:
  • do a check of the Differential Pressure Indicator (DPI) of the IDG 2 AMM 24-21-00-210-046,
  • do a check of the scavenge filter and charge filter (if installed).
     (a) If the DPI is extended:
     (b) If the DPI is not extended:
       1 If the oil level is not correct:
         a If you find leaks:
  • repair or replace the components as necessary to remove the oil leaks.
         b If you find no leaks:
   (3) 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 and repair the wiring of the IDG 2 disconnect circuit ASM 242101 for a short to 28VDC between:
    . pin B1 of the ELEC/IDG2 pushbutton switch (6XT) and pin B3 of the relay (8XT)
    . pin B2 of the relay (8XT) and pin X1 of the IDG 2 disconnect control relay (4XT)
    . pin B1 of the IDG 2 disconnect control relay and pin A/2J of the GCU 2.
  • do a check and repair the contact of the P/BSW-ELEC/IDG 2 [6XT] for correct operation between pin B1 and pin B3 (normally open) ASM 242101.
Subtask 24-20-00-710-147-F ** 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 24-20-00-810-203-E ** ON A/C NOT FOR ALL
C. If the fault symptom is identified by the maintenance message IDG2 (E2-4000XU) MANUAL DISCONNECT and by the upper ECAM DU warning IDG 2 DISCONNECTED:
NOTE: You can find this message with other CFDS fault messages. First, do the trouble shooting for all the other CFDS fault message.
   (1) Read the flight log book and the maintenance log book to find the cause of the IDG disconnect.
   (2) If you do not find the cause of the fault:
     (a) If the DPI of the IDG2 is extended:
     (b) If the DPI of the IDG2 is not extended:
       1 If the oil level at the sight glass of the IDG2 is not correct:
         a If you find leaks:
  • Repair or replace the components as necessary to remove the oil leaks.
         b If you find no leaks:
  • Add oil in the IDG2 AMM 12-13-24-612-803.
  • Do the operational test of the IDG2 disconnect and reconnect (reset) function (Engine in operation) AMM 24-21-00-710-803.
    . If the oil pressure is correct:
    - Stop the troubleshooting procedure.
       2 If the oil level at the sight glass of the IDG2 is correct:
         a If the BITE test gives the message TEST FAILED:
         b If the BITE test gives the message TEST PASSED:
  • Do a check of the contact of the ELEC/IDG 2 pushbutton switch (6XT) for correct operation between pin B1 and pin B3 (normally open) ASM 242101.
    * If it does not operate correctly:
  • Replace the P/BSW-ELEC/IDG 2 [6XT] .
    * If it operates correctly:
  • Do a check and repair the wiring of the IDG2 disconnect circuit ASM 242101 for a short to 28VDC between:
    . Pin A/B1 of the ELEC/IDG2 pushbutton switch (6XT) and pin A/B3 of the relay (8XT)
    . Pin A/B2 of the relay (8XT) and pin A/X1 of the IDG2 disconnect control relay (4XT)
    . Pin A/B1 of the IDG2 disconnect control relay (4XT) and pin AA/2J of the GCU2.
Subtask 24-20-00-710-147-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 AC 2 busbar.
5. Close-up
Subtask 24-20-00-860-179-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 24-20-00-860-179-F ** 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 04:26:22 UTC
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