「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 : 401-499, ∞∞24-20-00∞∞∞∞∞∞∞∞∞∞Page A269
 Aug 01/05 CES

R B. Do the test given in para. 3.

R TASK 24-20-00-810-872 R Failure of the Auxiliary Status Circuit of the BTC 1 R 1. Possible Causes
_______________
R - GCU-1 (1XU1) R - BTC-1 (11XU1) R - wiring
R 2. Job Set-up Information
______________________
R A. Referenced Information
R -------------------------------------------------------------------------------R REFERENCE DESIGNATION R -------------------------------------------------------------------------------
R AMM 24-22-34-000-001 R AMM 24-22-34-400-001 R AMM 24-22-55-000-001 R AMM 24-22-55-400-002 R R AMM 24-41-00-740-002 R AMM 24-41-00-861-002 R R AMM 24-41-00-862-002 R R AMM 31-60-00-860-001 R AMM 31-60-00-860-002 R AMM 71-00-00-710-003 R AMM 71-00-00-710-028 R ASM 24-22/02
R 3. Fault Confirmation
__________________
R A. Test
R Not applicable.

Removal of the GCU-1(2) (1XU1, 1XU2) Installation of the GCU-1(2) (1XU1, 1XU2) Removal of the Contactors (9XU1, 9XU2, 11XU1, 11XU2) Installation of the Contactors (9XU1, 9XU2, 11XU1, 11XU2) Operational Check of GAPCU via CFDS Energize the Aircraft Electrical Circuits from the External Power De-energize the Aircraft Electrical Circuits Supplied from the External Power EIS Start Procedure EIS Stop Procedure Engine Automatic Start Engine Shutdown
R NOTE : As the GEN 1 was set to OFF because of a true failure, the fault
____ R confirmation is not necessary.

R 4. Fault Isolation
_______________

R A. If the fault symptom is identified by the CFDS message GCU1 (1XU1)/ BTC1
R (11XU1) and the upper ECAM-DU warnings GEN 1 FAULT and AC BUS 1 FAULT:
R - replace the GCU-1 (1XU1) (Ref. AMM TASK 24-22-34-000-001) and (Ref. AMM
R TASK 24-22-34-400-001).

R (1) If the fault continues:
R - do a check of the wiring (Ref. ASM 24-22/02) for a short to 28VDC
R between:

R . pin B/10J of the GCU 1 and pin C/3 of the ELEC/GEN 1 pushbutton R switch (3XU1)

R . pin C/1 of the ELEC/GEN 1 pushbutton switch and pin A/A of the R function relay (20XU)

R . pin A/1 of the function relay (20XU) and pin X/1 of the GLC 1 R auxiliary control relay (4XU1).

R (a) If there is a short to 28VDC:
R - repair or replace as necessary.

R (b) If there is no short to 28VDC:
R - continue the trouble shooting procedure.

R (2) If the fault continues:
R - do a check of the wiring for a short to ground between pin B/29 of
R the BTC 1 and pin A/4C of the GCU 1 (Ref. ASM 24-22/02).

R (a) If there is a short to ground:
R - repair or replace as necessary.

R (b) If there is no short to ground:
R - do a check of the coil return wiring for a short to ground
R between pin B/5 of the BTC 1 and pin A/9A of the GCU 1 (Ref.
R ASM 24-22/02).

R 1_ If there is a short to ground:
R - repair or replace as necessary.

R 2_ If there is no short to ground:
R - do a check of the BTC 1 auxiliary status-contact between pin
R B/29 and pin B/27 (normally open) (Ref. ASM 24-22/02).

R a_ If there is no continuity:
R - replace the BTC-1 (11XU1) (Ref. AMM TASK 24-22-55-000-R 001) and (Ref. AMM TASK 24-22-55-400-002).

R B. Do this operational test to make sure that the system operates correctly.

R (1) Aircraft Maintenance Configuration

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

 「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 : 401-499, ∞∞24-20-00∞∞∞∞∞∞∞∞∞∞Page A272
 Aug 01/05 CES

R  (b) Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) 
R  (Ref. AMM TASK 31-60-00-860-001). 
R  (2) On the ELEC panel 35VU: 
R  - push, release and push again the GEN 1 pushbutton switch (3XU1). 
R  (3) Do the operational test of the GAPCU (Ref. AMM TASK 24-41-00-740-
R  002). 
R  (4) Start the engine 1 (Ref. AMM TASK 71-00-00-710-003). 
R  (5) Do this test: 
R  -------------------------------------------------------------------------------
R  ACTION RESULT 
R  -------------------------------------------------------------------------------
R  On the ECAM control panel: On the lower ECAM DU: 
R  - get the ELEC page. - the correct electrical parameters of 
R  the GEN 1 are shown and the AC1 
R  busbar is supplied by the GEN 1. 
　
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