R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 301-399,
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).
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 206
201-299, 301-399, Aug 01/05 CES
TASK 24-20-00-810-804
Loss of the GEN 1 (Failure of the Electrical Wiring between the GLC 1 and GCU 1)
1. Possible Causes
_______________
- EGIU-1 (22XU1)
- GCU-1 (1XU1)
- wiring
2. Job Set-up Information
______________________
A. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION
-------------------------------------------------------------------------------
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 24-41-00-740-002 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 1 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 207
201-299, 301-399, Aug 01/05 CES
4. Fault Isolation
_______________
A. If the fault symptom is identified by the CFDS message CHECK GLC 1 GCU 1 PIN B2D WIRING and the upper ECAM DU warning GEN 1 FAULT:
- reset the circuit breaker on the front of the GCU 1.
(1) If the circuit breaker trips:
- Do a check of the wiring for short to ground between: . the GCU 1 pin B/2D and successively the GLC 1 pin B/3, GCU 1 pin A/5B, EGIU 1 pin A/12D, and EGIU 1 pin A/12A . the GCU 1 pin A/12C and the GLC 1 AUX RELAY pin X1 . the GCU 1 A/12D and the EGIU 1 pin A/13A (Ref. ASM 24-22/02).
(a) If the wiring is not correct:
- repair it.
(b) If the wiring is correct:
- do a check for short to ground of the internal wiring of the EGIU 1 between the pin A/12A and the pin A/13A.
1_ If the wiring is shorted:
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本文鏈接地址：A320 Trouble Shooting Manual 排故手冊 電源 1(98)
