(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 241
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TASK 24-20-00-810-817
Loss of the GEN 1 (Failure of the IDG 1 Feeder or GCU 1 POR Wiring)
1. Possible Causes
_______________
- IDG (4000XU)
- GCU-1 (1XU1)
- wiring
- sockets of the 400VC1
2. Job Set-up Information
______________________
A. Fixtures, Tools, Test and Support Equipment
-------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
No specific dynamometer
B. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
R ESPM 204823 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 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
R AWM 24-22-01
「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 242
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3. Fault Confirmation
__________________
A. Test
Not applicable.
NOTE : As the GEN 1 was set to OFF because of a true fault, 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 GLC 1 PIN D, E, F GCU 1 PIN B1A, B2A, B3A and upper ECAM DU warning GEN 1 FAULT:
- do a check of the voltage of each phase.
(1) If the voltage on each phase is correct:
- do a check of the wiring between respectively the GCU 1 pins B/1A, B/2B, B/3A and the GLC 1 pins D, E and F (Ref. ASM 24-22/01).
(a) If there is no continuity:
- repair the above wiring.
(b) If there is continuity:
- do a check of the wiring between respectively the IDG 1 pins A/T1, B/T2, C/T3 and the GLC 1 terminals D, E and F.
1 If there is no continuity:
_ - repair the above wiring.
2 If there is continuity:
_
- do an impedance check between the IDG 1 terminals and the neutral.
NOTE : . impedance between each terminal and neutral must be
____ 0.0105 Ohm plus or minus 0.001 Ohm at 25 deg.C. . the maximum difference allowed between the values read is 0.03 Ohm.
a If the impedance is out of tolerance:
_
- replace the IDG (4000XU) (Ref. AMM TASK 24-21-51-000-040) and (Ref. AMM TASK 24-21-51-400-040).
b If the impedance is correct:
_
- replace the GCU-1 (1XU1) (Ref. AMM TASK 24-22-34-000-001) and (Ref. AMM TASK 24-22-34-400-001).
「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 243
201-299, 301-399, Aug 01/05 CES
(2) If the voltage on one phase is not correct:
R - do a pin retention check (Ref. ESPM 204823) of the sockets of the 400VC1 (Ref. AWM 24-22-01). Use a dynamometer, the CANNON value is
1.2 daN (2.7 lbf) minimum and the SOURIAU value is 2.8 daN (6.3 lbf) minimum, in relation to pin/socket type used.
**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 GLC 1 PIN D, E, F GCU 1 PIN B1A, B2A, B3A and upper ECAM DU warning GEN 1 FAULT:
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本文鏈接地址：A320 Trouble Shooting Manual 排故手冊 電源 1(111)
