NOTE : As the GEN1 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 1 RESET GEN1 and the upper ECAM DU warning GEN1 FAULT:
- do a check of the status of the ENG1 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 GCU1 and the pin A/C of the ENG/APU FIRE PNL (1WD) . the pin A/3A of the GCU1 and the pin A/B3 of the SENSOR-TDC AC1 (Ref. ASM 24-22/02).
「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 249
201-299, 301-399, Aug 01/05 CES (2) If the pushbutton switch has been pushed:
- do the necessary maintenance procedure and then reset the generator
1.
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 panel 35VU:
- push, release and push again the GEN1 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).
(5) 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 GEN1 are shown and AC1 busbar is supplied by GEN1.
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 250
201-299, 301-399, Aug 01/05 CES
TASK 24-20-00-810-820
Failure of the Generator 1 Feeders
1. Possible Causes
_______________
- SENSOR-TDC AC,1
2. Job Set-up Information
______________________
A. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
AMM 24-22-18-000-001 Removal of the TDC AC Sensor 1(2) (50XU1, 50XU2) AMM 24-22-18-400-001 Installation of the TDC AC Sensor 1(2) (50XU1, 50XU2) 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.
NOTE : As the GEN 1 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,
_______ EXAMINE EACH CONNECTOR TO MAKE SURE THAT THERE IS NO OIL IN IT. IF YOU FIND OIL, CLEAN THE CONNECTOR AND CONNECT IT AGAIN. IF THE FAILURE CONTINUES, DO THE TROUBLE SHOOTING PROCEDURE AS GIVEN BELOW.
「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 251
201-299, 301-399, Aug 01/05 CES
**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 IDG 1 1999VT WIRING and the 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(cè) 電源 1(114)
