- 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 module 30XN1 pins 1, 2, 3.
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).
(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.
「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 244
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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) 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 245
201-299, 301-399, Aug 01/05 CES
TASK 24-20-00-810-818
Loss of the GEN 1 (Failure of the IDG 1 PMG)
1. Possible Causes
_______________
- IDG (4000XU)
- GCU-1 (1XU1)
- 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 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.
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本文链接地址：A320 Trouble Shooting Manual 排故手册 电源 1(112)
