R  1_  If the fault does not continue:
R  - open the circuit breakers 8XA and 1XA 
R  - replace the diode module 1162VD (Ref. IPC 25710104) 
R  - install the GCU 1 (1XU1) (Ref. AMM TASK 24-22-34-400-001) 
R  - close the circuit breakers 8XA and 1XA. 
R  2_  If the fault continues:
R  - open the circuit breakers 8XA and 1XA 
R  - do a check and repair the wiring between the pin A/14 of the 
R  diode module 1162VD and the pin AA/6G of the GCU 1 (1XU1) 
R  - connect the connector of the diode module 1162VD (Ref. IPC 
R  25710104) 
R  - install the GCU 1 (1XU1) (Ref. AMM TASK 24-22-34-400-001) 
R  - close the circuit breakers 8XA and 1XA. 
R  **ON A/C ALL
 C. Do the test given in Para. 3.
 5. Close-up________
 A. Put the aircraft back to its initial configuration.
 (1) Stop the engine 1 (Ref. AMM TASK 71-00-00-710-028).
 (2) Put the aircraft back to its initial configuration.
 (3) De-energize the aircraft electrical circuits
 (Ref. AMM TASK 24-41-00-862-002).

 TASK 24-22-00-810-816

 Failure of the ELEC/GALLEY Pushbutton Switch Circuit after GEN2 Load Shedding
 1. Possible Causes
_______________
 - P/BSW-ELEC/GALLEY (2XA)

 - GCU-2 (1XU2)

 - EGIU-2 (22XU2)

 - diode module 1162VD

 - wiring

 2. Job Set-up Information
______________________
 A. Referenced Information
 -------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
IPC 25710104
 AMM 24-22-33-000-001 Removal of the EGIU-1(2) (22XU1, 22XU2)
 AMM 24-22-33-400-002 Installation of the EGIU-1(2) (22XU1, 22XU2)
 AMM 24-22-34-000-001 Removal of the GCU-1(2) (1XU1, 1XU2)
 AMM 24-22-34-400-001 Installation of the GCU-1(2) (1XU1, 1XU2)
 AMM 24-41-00-861-002 Energize the Aircraft Electrical Circuits from Engine
 1(2)
 AMM 24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
 from the Engine 1(2)
 AMM 31-60-00-860-001 EIS Start Procedure
 AMM 33-10-00-000-002 Removal of the Bulbs and the Body of a Pushbutton
 Switch in the Cockpit
 AMM 33-10-00-400-002 Installation of the Bulbs and the Body of a
 Pushbutton Switch in the Cockpit
 AMM 71-00-00-710-003 Engine Automatic Start
 AMM 71-00-00-710-028 Engine Shutdown
 3. Fault Confirmation
__________________
 A. Job Set-up
 (1) Push the ELEC/GEN 1 pushbutton switch (3XU1).

 (2) Aircraft Maintenance Configuration

 (a) Energize the aircraft electrical circuits
 (Ref. AMM TASK 24-41-00-861-002).

 (b) Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. AMM TASK 31-60-00-860-001).

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

 「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1 EFF : ALL ∞∞24-22-00∞∞∞∞∞∞∞∞∞∞Page 248
 Aug 01/05 CES

 **ON A/C 001-049, 051-060, 101-102, 201-201,

 B. Test
 -------------------------------------------------------------------------------ACTION RESULT -------------------------------------------------------------------------------
1. On the ECAM control panel: - push the ELEC key to get the ELEC page.  On the upper ECAM DU:- the GEN 2 OVERLOAD message comes intoview.
 2. On the ELEC panel 35VU: - release the GALLEY pushbutton switch (2XA).  If on the upper ECAM DU:- the GEN 2 OVERLOAD message goes outof view, stop the trouble shooting. If on the upper ECAM DU: - the GEN 2 OVERLOAD message stays in view, continue the trouble shooting (refer to the fault isolation which follows). 

R **ON A/C 061-099, 103-149, 151-199, 202-299, 301-399, 401-499,
 B. Test
 -------------------------------------------------------------------------------ACTION RESULT -------------------------------------------------------------------------------
1. On the ECAM control panel: - push the ELEC key to get the ELEC page.  On the upper ECAM DU:- the GEN 2 OVERLOAD message comes intoview.
 2. On the ELEC panel 35VU: - release the GALY & CAB pushbutton switch (2XA).  If on the upper ECAM DU:- the GEN 2 OVERLOAD message goes outof view, stop the trouble shooting. If on the upper ECAM DU: - the GEN 2 OVERLOAD message stays in view, continue the trouble shooting (refer to the fault isolation which follows).
　
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