B. Do this operational test to make sure that the system operates correctly.
(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 GPCU (Ref. AMM TASK 24-41-00-740-002).
(4) Start the engine 1 (Ref. AMM TASK 71-00-00-710-003).
「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1R EFF : 001-049, 051-099, 101-149, 151-199, ∞∞24-20-00∞∞∞∞∞∞∞∞∞∞Page 208
201-299, 301-399, Aug 01/05 CES
C. Do this test:
-------------------------------------------------------------------------------ACTION RESULT -------------------------------------------------------------------------------
On the ECAM control panel: On the lower ECAM display unit:
- get the ELEC page. - the correct electrical parameters of GEN 1 are shown and AC 1 busbar is supplied by 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) On the ECAM control panel, set the UPPER DISPLAY and LOWER DISPLAY potentiometers to OFF.
(3) De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002).
「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1R EFF : 001-049, 051-099, 101-149, 151-199, ∞∞24-20-00∞∞∞∞∞∞∞∞∞∞Page 209
201-299, 301-399, Aug 01/05 CES
TASK 24-20-00-810-805
Loss of the GEN 1 (Failure of the IDG 1 Feeder)
1. Possible Causes
_______________
- GCU-1 (1XU1)
- aircraft wiring
2. Job Set-up Information
______________________
A. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION
-------------------------------------------------------------------------------
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 Test of the Ground power Control Unit
(GPCU) AMM 24-41-00-861-002 Energize the Aircraft Electrical Circuits from Engine 1(2) 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 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 1 was set to OFF because of a true failure, the fault
____
confirmation is not necessary.
4. Fault Isolation
_______________
**ON A/C 001-049, 051-062, 101-105, 151-152, 201-205,
A. If the fault symptom is identified by the CFDS message CHECK IDG 1 FEEDER PIN T1, T2, T3 SHORT TO GROUND and the upper ECAM DU warning GEN 1 FAULT:
- do a check of the aircraft wiring for short to ground between respectively the IDG 1 pins A/T1, B/T2, C/T3 and the GLC 1 pins D, E, F (Ref. ASM 24-22/01).
(1) If the wiring is not correct:
- repair it.
「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1R EFF : 001-049, 051-099, 101-149, 151-199, ∞∞24-20-00∞∞∞∞∞∞∞∞∞∞Page 210
201-299, 301-399, Aug 01/05 CES (2) If the wiring is correct:
- replace the GCU-1 (1XU1) (Ref. AMM TASK 24-22-34-000-001) and (Ref. AMM TASK 24-22-34-400-001).
**ON A/C 063-099, 106-149, 153-199, 206-299, 301-399,
A. If the fault symptom is identified by the CFDS message CHECK IDG 1 FEEDER PIN T1, T2, T3 SHORT TO GROUND and the upper ECAM DU warning GEN 1 FAULT:
- do a check of the aircraft wiring for short to ground between respectively the IDG 1 pins A/T1, B/T2, C/T3 and the module 30XN1 pins 1, 2, 3 (Ref. ASM 24-22/01).
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本文鏈接地址：A320 Trouble Shooting Manual 排故手冊 電源 1(99)
