R . pin B/12 of the IDG 2 and pin C/10 of the GCU 2
R . pin B/13 of the IDG 2 and pin C/11 of the GCU 2
R . pin B/14 of the IDG 2 and pin C/9 of the GCU 2
R . pins C/10, C/11, C/9 and C/7 of the GCU 2 (short to shield R of the PMG stator)
R . pin A/9 of the IDG 2 and pin C/12 of the GCU 2
R . pin A/10 of the IDG 2 and pin C/13 of the GCU 2
R . pins C/12, C/13 and pin C/7 of the GCU 2 (short to shield R of the exciter field).
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)
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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Aug 01/05 CES
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 24-21-00-810-828
R Failure of the IDG Cooler 1
R 1. Possible Causes_______________
R - FUEL/OIL HEAT EXCHANGER
R - IDG 1 oil-cooling tubing
R 2. Job Set-up Information______________________
R A. Referenced Information
R -------------------------------------------------------------------------------
R REFERENCE DESIGNATION
R -------------------------------------------------------------------------------
R AMM 24-21-00-612-043
R AMM 24-21-49-000-003
R AMM 24-21-49-400-003
R
R AMM 73-11-60-000-002
R
R AMM 73-11-60-400-002
R R 3. Fault Confirmation
__________________ R A. Test
Servicing of the IDG after Oil Chemical Contamination Removal of the IDG Cooling Oil-in Tubes and Hoses Installation of the IDG Cooling Oil-in Tubes and Hoses Removal of the Integrated Drive Generator (IDG) Oil Cooler Assembly Installation of the Integrated Drive Generator (IDG) Oil Cooler Assembly
R (1) Not applicable, you cannot confirm this fault on the ground.
R 4. Fault Isolation
_______________
R A. If the fault symptom is identified by the CFDS message IDG COOLER 1:
R - smell to make sure there is no fuel in the oil container.
R (1) If you smell fuel in the IDG 1 oil container:
R - replace the FUEL/OIL HEAT EXCHANGER of the IDG 1 (Ref. AMM TASK 73-R 11-60-000-002) and (Ref. AMM TASK 73-11-60-400-002)
R - do the servicing of the IDG 1 after oil chemical contamination
R (Ref. AMM TASK 24-21-00-612-043).
R (2) If there is no sign of fuel in the IDG 1 oil container:
R - replace the FUEL/OIL HEAT EXCHANGER of the IDG 1 (Ref. AMM TASK 73-R 11-60-000-002) and (Ref. AMM TASK 73-11-60-400-002)
R - replace the IDG 1 oil-cooling tubing (Ref. AMM TASK 24-21-49-000-R 003) and (Ref. AMM TASK 24-21-49-400-003)
R - do the servicing of the IDG 1 after oil chemical contamination
R (Ref. AMM TASK 24-21-00-612-043).
「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, ∞∞24-21-00∞∞∞∞∞∞∞∞∞∞Page 270 中國(guó)航空網(wǎng) m.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 2(122)
