_
- replace the engine 1 IDG (4000XU) (Ref. AMM TASK 24-21-51-000-040) and (Ref. AMM TASK 24-21-51-400-040).
B. Test
(1) Aircraft Maintenance Configuration
(a) Energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-861-002).
(b) Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. AMM TASK 31-60-00-860-001).
(2) On the ELEC panel 35VU:
- push, release and push again the GEN 1 pushbutton switch (3XU1).
(3) Do the operational test of the GAPCU (Ref. AMM TASK 24-41-00-740-002).
(4) Start the engine 1 (Ref. AMM TASK 71-00-00-710-003).
(5) Do this test:
-------------------------------------------------------------------------------ACTION RESULT -------------------------------------------------------------------------------
On the ECAM control panel: On the lower ECAM DU:
- get the ELEC page. - the correct electrical parameters of the GEN 1 are shown and the AC1 busbar is supplied by the GEN 1.
5. Close-up
________
A. Put the aircraft back to its initial configuration.
(1) Stop the engine 1 (Ref. AMM TASK 71-00-00-710-028).
(2) Do the EIS stop procedure
(Ref. AMM TASK 31-60-00-860-002).
(3) On the ECAM control panel, set the UPPER DISPLAY and LOWER DISPLAY potentiometers to OFF.
(4) De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002).
TASK 24-20-00-810-950
Failure of the IDG 2 Disconnection Function or the IDG 2 PMG Stator or its
Wiring to the GCU 2
1. Possible Causes
_______________
- IDG (4000XU)
- GCU-2 (1XU2)
- wiring
2. Job Set-up Information
______________________
A. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
AMM 24-21-51-000-040 Removal of the Integrated Drive Generator -IDG 1(2),(4000XU) AMM 24-21-51-400-040 Installation of the Integrated Drive Generator -IDG
1(2),(4000XU)
AMM 24-22-34-000-001 Removal of the GCU-1(2) (1XU1, 1XU2)
AMM 24-22-34-400-001 Installation of the GCU-1(2) (1XU1, 1XU2)
AMM 24-41-00-740-002 Operational Check of GAPCU via CFDS
AMM 24-41-00-861-002 Energize the Aircraft Electrical Circuits from the
External Power AMM 24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied
from the External Power
AMM 31-60-00-860-001 EIS Start Procedure
AMM 31-60-00-860-002 EIS Stop Procedure
AMM 71-00-00-710-003 Engine Automatic Start
AMM 71-00-00-710-028 Engine Shutdown
ASM 24-22/01
3. Fault Confirmation
__________________
A. Test
Not applicable.
NOTE : As the GEN 2 was set to OFF because of a true failure, the fault
____
confirmation is not necessary.
4. Fault Isolation
_______________
CAUTION : BEFORE YOU START THE CHECK OF IDG WIRING THAT INCLUDES CONNECTORS,
_______ EXAMINE EACH CONNECTOR TO MAKE SURE THAT THERE IS NO OIL IN IT. IF YOU FIND OIL, CLEAN THE CONNECTOR AND CONNECT IT AGAIN. IF THE FAILURE CONTINUES, DO THE TROUBLE SHOOTING PROCEDURE AS GIVEN BELOW.
「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 : 106-149, 229-299, 303-399, 401-499, ∞∞24-20-00∞∞∞∞∞∞∞∞∞∞Page C261
Aug 01/05 CES
A. If the fault symptom is identified by the CFDS message IDG DISC/ IDG2 (E2-4000XU) PMG/ GCU2 (1XU2) and the upper ECAM-DU warning GEN 2 FAULT:
NOTE : Before you do the trouble shooting for this fault, do a check of
____ the log book and the CFDS for messages related to IDG 2 thermal or manual disconnection messages.
(1) If there was a thermal or manual disconnection of the IDG 2:
- replace the engine 2 IDG (4000XU) (Ref. AMM TASK 24-21-51-000-040) and (Ref. AMM TASK 24-21-51-400-040).
(2) If there is no sign of thermal or manual disconnection of the IDG: 中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：A320 Trouble Shooting Manual 排故手册 电源 2(86)
