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. 
R  5. Close-up________ 
R  A. Put the aircraft back to its initial configuration. 
R  (1) Stop the engine 1 (Ref. AMM TASK 71-00-00-710-028). 
R  (2) Do the EIS stop procedure 
R  (Ref. AMM TASK 31-60-00-860-002). 
R  (3) On the ECAM control panel, set the UPPER DISPLAY and LOWER DISPLAY 
R  potentiometers to OFF. 
R  (4) De-energize the aircraft electrical circuits 
R  (Ref. AMM TASK 24-41-00-862-002).

R TASK 24-20-00-810-893

R Failure of the GLC 2 Control Circuit R 1. Possible Causes
_______________
R - GCU-2 (1XU2)
R - RELAY-GLC 2 AUX CTL (4XU2)
R - GLC-2 (9XU2)
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 24-22/03
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 2 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 GLC AUX RLY
R (4XU2)/ GLC2 (9XU2)/ GCU2 (1XU2) and the upper ECAM-DU warning GEN 2
R FAULT:

R (1) If the CFDS message comes into view associated with the fault code 19
R (GLC CONTROL CKT keyword):
R - replace the GCU-2 (1XU2) (Ref. AMM TASK 24-22-34-000-001) and (Ref.
R AMM TASK 24-22-34-400-001).

R (2) If the CFDS message comes into view associated with the fault codes
R 180 (PR SSR OC ACTIVE keyword) or 183 (GLC CONTROL CKT keyword):
R - do a check of the wiring of the GLC 2 control circuit (Ref. ASM 24-R 22/03) for a short to ground or a short circuit condition between:

R . pin B/10J of the GCU 2 and pin A/C3 of the ELEC/GEN 2 pushbutton R switch (3XU2)

R . pin A/C1 of the ELEC/GEN 2 pushbutton switch and pin A/X1 of the R GLC 2 auxiliary control relay (4XU2)

R . pin B/10J of the GCU 2 and pin A/23 of the diode module 2422VD

R . pin A/8 of the diode module 2422VD and pin B/25 of the GLC 2

R . pin A/8 of the diode module 2422VD and pin B/10 of the BTC 2 R (11XU2)

R . pin B/23 of the GLC 2 and pin A/D2 of the GLC 2 auxiliary control R relay

R . pin B/12 of the BTC 2 and pin A/D2 of the GLC 2 auxiliary control R relay

R . pin A/D1 of the GLC 2 auxiliary control relay and pin B/3 of the R GLC 2.

R (a) If the wiring is not correct:
R - repair or replace as necessary.

R (b) If the wiring is correct:
R - replace the GCU-2 (1XU2) (Ref. AMM TASK 24-22-34-000-001) and
R (Ref. AMM TASK 24-22-34-400-001).

R 1_ If the fault continues:
R - replace the RELAY-GLC 2 AUX CTL (4XU2).

R a_ If the fault continues:
R - replace the GLC-2 (9XU2) (Ref. AMM TASK 24-22-55-000-001)
R and (Ref. AMM TASK 24-22-55-400-002).

R B. Do this operational test to make sure that the system operates correctly.
　
中國航空網 m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：A320 Trouble Shooting Manual 排故手冊 電源 2(34)