A. If the fault symptom is identified by the CFDS message CHECK GCU 2 PIN C2 TO C4 IDG 2 PIN B12 TO B14 and the upper ECAM DU warning GEN 2 FAULT:
- do a check of the wiring for open circuit or short to ground between respectively the IDG 2 pins B/12, B/13, B/14 and the GCU 2 pins C/2, C/3, C/4 (Ref. ASM 24-22/01).
(1) If the wiring is not correct:
- repair it.
(2) If the wiring is correct:
- do a check of the resistance of the IDG 2 PMG stator between successively 2 pins among the 3.
NOTE : . the resistance between two pins must be between 1.33 and
____ 1.84 Ohms at 25.C . the maximum permitted difference between the values read is
0.04 Ohm.
(a) If the resistance 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 resistance is correct:
- replace the GCU-2 (1XU2) (Ref. AMM TASK 24-22-34-000-001) and (Ref. AMM TASK 24-22-34-400-001).
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).
「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 270
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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 271
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TASK 24-20-00-810-827
Failure of the ENG2 FIRE Pushbutton Switch or its Wiring to the GCU2
1. Possible Causes
_______________
- wiring
2. Job Set-up Information
______________________
A. Referenced Information
-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------
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 24-22/03
3. Fault Confirmation
__________________
A. Test
Not applicable.
NOTE : As the GEN2 was set to OFF because of a true failure, the test
____
configuration is not necessary.
4. Fault Isolation
_______________
A. If the fault symptom is identified by the CFDS message CHECK FIRE HANDLE 2 RESET GEN2 and the upper ECAM DU warning GEN2 FAULT:
- do a check of the status of the ENG2 FIRE pushbutton switch on the FIRE panel (1WD).
(1) If the pushbutton switch has not been pushed:
- do a check for intermittent +28VDC and repair the wiring between respectively: . the pin A/3A of the GCU2 and the pin C/V of the ENG/APU FIRE PNL (1WD) . the pin A/3A of the GCU2 and the pin A/B3 of the SENSOR-TDC AC2 (Ref. ASM 24-22/03).
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