R (a) If there is no continuity:
R - repair or replace as necessary.
R (b) If there is continuity:
R - replace the GCU-1 (1XU1) (Ref. AMM TASK 24-22-34-000-001) and
R (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 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).
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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 24-00-00-810-815
R Failure of the Oil Temperature Sensors of the IDG 2 R 1. Possible Causes
_______________
R - IDG (4000XU) R - GCU-2 (1XU2) R - wiring
R 2. Job Set-up Information
______________________
R A. Referenced Information
R -------------------------------------------------------------------------------R REFERENCE DESIGNATION R -------------------------------------------------------------------------------
R AMM 24-21-51-000-040 R R AMM 24-21-51-400-040 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 24-21/01
R 3. Fault Confirmation
__________________
R A. Test
R Not applicable.
Removal of the Integrated Drive Generator -IDG 1(2),(4000XU) Installation of the Integrated Drive Generator -IDG 1(2),(4000XU) 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 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 CAUTION : BEFORE YOU START THE CHECK OF IDG WIRING THAT INCLUDES CONNECTORS,
_______ R EXAMINE EACH CONNECTOR TO MAKE SURE THAT THERE IS NO OIL IN IT. R IF YOU FIND OIL, CLEAN THE CONNECTOR AND CONNECT IT AGAIN. R IF THE FAILURE CONTINUES, DO THE TROUBLE SHOOTING PROCEDURE AS R GIVEN BELOW.
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R A. If the fault symptom is identified by the CFDS message IDG2 (E2-4000XU) R TEMP SENSE/ GCU2 (1XU2):
R NOTE : The CMS message IDG2 (E2-4000XU) TEMP SENSE/ GCU2 (1XU2) can come
____ R into view if the electrical connector B is disconnected from the R IDG and the 28VDC backup power supplies the related GCU. Before R you do the trouble shooting procedure for this CMS message, make R sure that the electrical connector B is not disconnected.
R - do an electrical resistance test of the inlet and outlet oil R temperature-sensors of the IDG 2 (Ref. ASM 24-21/01) between:
R . pin B/7 and pin B/8 (100 ohms plus or minus 10 ohms at the ambient R temperature of the IDG case)
R . pin B/8 and pin B/9 (100 ohms plus or minus 10 ohms at the ambient R temperature of the IDG case). 中國(guó)航空網(wǎng) www.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：A320 Trouble Shooting Manual 排故手冊(cè) 電源 1(83)
