TASK 24-20-00-810-815

 Accidental Disconnection of the IDG2
 1. Possible Causes
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 - RELAY-IDG2 DISC CTL (4XT)

 - wiring

 - P/BSW-ELEC/IDG2 (6XT)

 2. Job Set-up Information
______________________
 A. Referenced Information
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REFERENCE DESIGNATION
 -------------------------------------------------------------------------------
AMM 24-21-00-710-040 Operational Test of the IDG Disconnect and Reconnect (Reset) Function - Engine Static AMM 24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
 from the External Power
 AMM 71-00-00-710-003 Engine Automatic Start
 AMM 71-00-00-710-028 Engine Shutdown
 ASM 24-21/01

 3. Fault Confirmation
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 A. Test
 Not applicable, you cannot confirm this fault on the ground.

 4. Fault Isolation
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 A. If the fault symptom is identified by the CFDS message IDG2 DISCONNECTED and the warning ELEC GEN2 FAULT on the upper ECAM display unit:
 (1) If the IDG2 has been disconnected intentionally, that is if this CFDS message is found with other CFDS messages such as: . IDG2 LOW OIL PRESSURE . IDG2 (OVERTEMP) . IDG2 HIGH DELTA TEMP . IDG2 BULB TOLERANCE . other messages.

 - no trouble shooting is necessary.

 (2) If the IDG2 has not been disconnected intentionally:

 - reconnect the IDG2: for this, reset the disconnect system (Ref. AMM TASK 24-21-00-710-040) (the warning ELEC GEN2 FAULT is no longer shown of the upper ECAM display unit and the DISC indication is no longer shown on the lower ECAM display unit).
 「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1R EFF : 001-049, 051-099, 101-149, 151-199, ∞∞24-20-00∞∞∞∞∞∞∞∞∞∞Page 236
 201-299, 301-399, Aug 01/05 CES

 (a) If the IDG2 disconnects again (the warning GEN2 FAULT is shown again on the upper ECAM display unit and the DISC indication is shown again on the lower ECAM display unit):
 - replace the RELAY-IDG2 DISC CTL (4XT).
 1 If the fault continues:
_
 - do a check and repair the wiring for abnormal 28VDC between the pin A/A1 of the relay (4XT) and the pin A/12 of the IDG2 (Ref. ASM 24-21/01).
 (b) If the IDG2 does not disconnect:
 - on the circuit breaker panel 122VU, open, safety and tag the circuit breaker ELEC/GCU/2 (2XU2).
 1 If the IDG2 disconnects (the warning GEN2 FAULT is shown on
_ the upper ECAM display unit and the DISC indication is shown on the lower ECAM display unit).
 - replace the P/BSW-ELEC/IDG2 (6XT).
 a If the fault continues:
_
 - do a check and repair the wiring for abnormal 28VDC between the pin A/B1 of the pushbutton switch (6XT) and the pin A/X1 of the relay (4XT) (Ref. ASM 24-21/01).
 2 If the IDG2 does not disconnect:
_
 - stop the trouble shooting and on the circuit breaker panel 122VU, remove the safety clip and tag and close the circuit breaker (2XU2).
 B. Do this test to make sure that the system operates correctly:
 (1) Make sure that the circuit breaker 2XU2 is closed.

 (2) On the overhead panel, on the ELEC panel 35VU:

 - push, release and push again the ELEC/GEN2 pushbutton switch (3XU2).

 (3) Start the engine 2 (Ref. AMM TASK 71-00-00-710-003).

 (4) Do this test:

 -------------------------------------------------------------------------------ACTION RESULT -------------------------------------------------------------------------------
On the ECAM control panel:  On the lower ECAM display unit:
 - push the ELEC key to get the ELEC  - the correct electrical parameters of
 page.  the GEN2 are shown and the AC2 busbar is supplied by the GEN2.
 「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1R EFF : 001-049, 051-099, 101-149, 151-199, ∞∞24-20-00∞∞∞∞∞∞∞∞∞∞Page 237
 201-299, 301-399, Aug 01/05 CES 5. Close-up

________
 A. Put the aircraft back to its initial configuration.
 (1) Stop the engine 2 (Ref. AMM TASK 71-00-00-710-028).

 (2) On the ECAM control panel, set the UPPER DISPLAY and LOWER DISPLAY potentiometers to OFF.

 (3) De-energize the aircraft electrical circuits
 (Ref. AMM TASK 24-41-00-862-002).