R 1_ If the wiring is not correct:
R - repair or replace as necessary.
R 2_ If the wiring is correct:
R - replace the GCU-2 (1XU2) (Ref. AMM TASK 24-22-34-000-001)
R and (Ref. AMM TASK 24-22-34-400-001).
R a_ If the fault continues:
R - replace the engine 2 IDG (4000XU) (Ref. AMM TASK 24-21-R 51-000-040) and (Ref. AMM TASK 24-21-51-400-040).
R (2) If the CFDS message comes into view with the fault code 189 (PMG SHT
R TO CHAS 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 (a) If the fault continues:
R - do a check of the wiring of the IDG 2 PMG stator (Ref. ASM 24-R 22/01) for a short circuit, an open circuit, a short to ground
R or a short to shield between:
R . pins C/10 and C/7 of the GCU 2
R . pins C/11 and C/7 of the GCU 2
R . pins C/9 and C/7 of the GCU 2.
R 1_ If the wiring is not correct:
R - repair or replace as necessary.
「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 : 401-499, ∞∞24-20-00∞∞∞∞∞∞∞∞∞∞Page B275
Aug 01/05 CES
R 2 If the wiring is correct:_
R - replace the engine 2 IDG (4000XU) (Ref. AMM TASK 24-21-51-
R 000-040) and (Ref. AMM TASK 24-21-51-400-040).
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).
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 2 pushbutton switch (3XU2).
R (3) Do the operational test of the GAPCU (Ref. AMM TASK 24-41-00-740-
R 002).
R (4) Start the engine 2 (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 2 are shown and the AC2
R busbar is supplied by the GEN 2.
R 5. Close-up________
R A. Put the aircraft back to its initial configuration.
R (1) Stop the engine 2 (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).
「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 : 401-499, ∞∞24-20-00∞∞∞∞∞∞∞∞∞∞Page B276
Aug 01/05 CES
R TASK 24-20-00-810-912
R Failure of the Bus between the ECU 1 and the GCU 1 R 1. Possible Causes
_______________
R - GCU-1 (1XU1) 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 24-41-00-740-002 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 24-22/01
R 3. Fault Confirmation
__________________
R A. Test
R Not applicable.
R 4. Fault Isolation
_______________ Removal of the GCU-1(2) (1XU1, 1XU2) Installation of the GCU-1(2) (1XU1, 1XU2) 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 A. If the fault symptom is identified by the maintenance message ECU
R (E1-4000KS)/ GCU1 (1XU1) and by the upper ECAM-DU warning GEN 1 FAULT:
R NOTE : You can find this message with other CFDS fault messages. First,
____ R do the trouble shooting for all the other CFDS fault messages. 中國航空網 www.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(55)
