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 2 pushbutton switch (3XU2).
(3) Do the operational test of the GPCU (Ref. AMM TASK 24-41-00-740-002).
(4) Start the engine 2 (Ref. AMM TASK 71-00-00-710-003).
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 2 are shown and AC 2 busbar is supplied by GEN 2.
5. Close-up
________
A. Put the aircraft back to its initial configuration.
(1) Stop the engine 2 (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 281
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TASK 24-20-00-810-831
Loss of the GEN 2 (Failure of the Electrical Wiring between the GCU 2 and GLC 2)
1. Possible Causes
_______________
- EGIU-2 (22XU2)
- GLC-2 (9XU2)
- GCU-2 (1XU2)
- wiring
- RELAY-GLC2 AUX CTL (4XU2)
2. Job Set-up Information
______________________
A. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
24-20-00-810-812 Loss of the GEN 2 (Failure of the Electrical Wiring
between the GLC 2 and GCU 2) AMM 24-22-33-000-001 Removal of the EGIU-1(2) (22XU1, 22XU2) AMM 24-22-33-400-002 Installation of the EGIU-1(2) (22XU1, 22XU2) 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 24-22-55-000-001 Removal of the Contactors (9XU1, 9XU2, 11XU1, 11XU2) AMM 24-22-55-400-002 Installation of the Contactors (9XU1, 9XU2, 11XU1,
11XU2) 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 24-22/02
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.
「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 282
201-299, 301-399, Aug 01/05 CES
4. Fault Isolation
_______________
A. If the fault symptom is identified by the CFDS message CHECK GLC 2 AND/OR CONTROL CKT and the upper ECAM DU warning GEN 2 FAULT:
- do a check of the status of the GCU 2 circuit breaker.
(1) If the circuit breaker is open:
- refer to (Ref. TASK 24-20-00-810-812). 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 1(126)
