R 4. Fault Isolation
_______________
R A. If the fault symptom is identified by the CFDS message CTA (51XU2)/ IDG2
R (E2-4000XU)/ GCU2 (1XU2) and the upper ECAM-DU warning GEN 2 FAULT:
R - read the EPGS GROUND REPORT or POST FLIGHT REPORT to see if there is
R one or two of the CFDS messages that follow:
R . IDG2 (E2-4000XU) LOW OIL PRESSURE
R . IDG2 (E2-4000XU) OIL OUT TEMP SENSE / GCU2 (1XU2)
R (1) If one or two of the CFDS messages are given:
R - replace the engine 2 IDG (4000XU) (Ref. AMM TASK 24-21-51-000-040)
R and (Ref. AMM TASK 24-21-51-400-040).
R (2) If these CFDS messages are not given:
R - do a check of the resistance of the Current Transformer (CT)
R (51XU2) (Ref. ASM 24-22/01) between:
R . pins 1 and 4 (10.15 ohms plus or minus 3.45 ohms)
R . pins 2 and 4 (10.15 ohms plus or minus 3.45 ohms)
R . pins 3 and 4 (10.15 ohms plus or minus 3.45 ohms).
R (a) If the resistance values are out of the specified limits:
R - replace the CT (51XU2) (Ref. AMM TASK 24-22-17-000-001) and
R (Ref. AMM TASK 24-22-17-400-001).
R (b) If the resistance values are in the specified limits:
R - do a check of the wiring (Ref. ASM 24-22/01) for a short to
R ground, a short circuit or an open circuit between:
R . pin 1 of the CT and pin A/12B of the GCU 2
R . pin 2 of the CT and pin A/12A of the GCU 2
R . pin 3 of the CT and pin A/11A of the GCU 2
R . pin 4 of the CT and pin A/11B of the GCU 2.
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 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).
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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).
R TASK 24-22-00-810-821
R Failure of the Generator Control Unit 1
R 1. Possible Causes_______________
R - GCU-1 (1XU1)
R 2. Job Set-up Information______________________
R A. Referenced Information
R -------------------------------------------------------------------------------
R REFERENCE DESIGNATION
R -------------------------------------------------------------------------------
R AMM 24-22-34-000-001 Removal of the GCU-1(2) (1XU1, 1XU2)
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