- repair the above wiring.
(2) If the wiring is correct:
- Do an impedance check of the coils of the current transformers 42XU2 and 42XU4 between pin A/4 and successively pins A/1, A/2 and A/3.
NOTE : The normal impedance is 10.15 Ohms plus or minus 3.45 Ohms.
____
(a) If the impedance is out of tolerance:
- replace the defective current transformer (Ref. AMM TASK 24-22-17-000-001) and (Ref. AMM TASK 24-22-17-400-001).
(b) If the impedance is correct:
- Make sure, on current transformers 42XU2 and 42XU4 that the pin A/6 is electrically insulated from pins A/1, A/2, A/3 and A/4.
1_ If not insulated:
- replace the defective current transformer (Ref. AMM TASK 24-
22-17-000-001) and (Ref. AMM TASK 24-22-17-400-001).
2 If insulated:
_
- Do an impedance check of the coil of the IDG 2 current transformer from the pin A/1 to succesively pins A/6, A/7 and A/8.
NOTE : The normal impedance is 26 Ohms plus or minus 2 Ohms at
____ 25.C.
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-2 (1XU2) (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 278
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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 279
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TASK 24-20-00-810-830
Failure of the IDG 2
1. Possible Causes
_______________
- IDG (4000XU)
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 24-41-00-740-002 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
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.
4. Fault Isolation
_______________
CAUTION : BEFORE YOU START THE CHECK OF IDG WIRING THAT INCLUDES CONNECTORS,
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