- COMPONENTS THAT MOVE.
WARNING : MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROL SURFACES ARE
_______
CLEAR BEFORE YOU PRESSURIZE/DEPRESSURIZE A HYDRAULIC SYSTEM.
1. Possible Causes
_______________
- SFCC-1 (21CV)
- SFCC-2 (22CV)
2. Job Set-up Information
______________________
A. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
AMM 27-51-00-710-001 Operational Test of the Wing Tip Brake and the Pressure Off Brake AMM 27-51-00-740-002 Bite Test of the Slat and Flap Control Computers
(Flap System) AMM 27-51-34-000-001 Removal of the SFCC (21CV,22CV) AMM 27-51-34-400-001 Installation of the SFCC (21CV,22CV) AMM 27-54-00-710-001 Operational Test of the Flap System AMM 31-32-00-860-006 Procedure to Get Access to the SYSTEM REPORT/TEST
F/CTL Page
3. Fault Confirmation
__________________
A. Fault monitor action.
(1) Possible causes of the SFCC 1 (2) reported fault are as follows:
(a) The non-validity of the synchro-excitation power generation.
(b) The SFCC primary/secondary internal power supply fault.
(c) Automatic integrity test detected fault conditions:
- processor checks
- ROM and RAM tests
- processor I/O tests
- consolidation logic tests.
「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1 EFF : ALL ∞∞27-51-00∞∞∞∞∞∞∞∞∞∞Page 297
May 01/05R CES
(d) A cross lane monitoring fault.
B. Procedure
(1) Set the MCDU to the MENU MODE and access the LAST LEG REPORT for a list of fault messages (Ref. AMM TASK 31-32-00-860-006).
(2) Do a BITE test with the applicable SFCC (Ref. AMM TASK 27-51-00-740-002).
(3) If the MCDU shows a failure message, do the Fault Isolation procedure.
4. Fault Isolation
_______________
A. Procedure
(1) Swop the SFCC-1 with the SFCC-2 (Ref. AMM TASK 27-51-34-000-001) and (Ref. AMM TASK 27-51-34-400-001).
(2) If the failure moves with the SFCC, replace the applicable SFCC-1 (21CV) and SFCC-2 (22CV).
(3) If the failure does not move with the SFCC or there is no fault detected, do the Operational Test of the Flap System (Ref. AMM TASK 27-54-00-710-001).
(4) If a fault is detected, swop the SFCC-1 with the SFCC-2.
(5) Do the Operational Test of the Flap System again.
(6) If the fault moves with the SFCC, replace the applicable SFCC-1 (21CV) or SFCC-2 (22CV).
(7) If the fault does not move with the SFCC, refer to P. Block 101 for the related system trouble-shooting procedure.
(8) If there is no fault detected, do the Operational Test of the Wing-Tip Brake and the Pressure-Off Brake (Ref. AMM TASK 27-51-00-710-001).
(9) If a fault is detected, swop the SFCC-1 with the SFCC-2.
(10) Do the Operational Test of the Wing-Tip Brake and the Pressure-Off Brake again.
(11) If the fault moves with the SFCC, replace the applicable SFCC-1 (21CV) or SFCC-2 (22CV).
(12) If the fault does not move with the SFCC, refer to P. Block 101 for the system trouble-shooting procedure.
「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1 EFF : ALL ∞∞27-51-00∞∞∞∞∞∞∞∞∞∞Page 298
May 01/05R CES
Flap Pin Program Disagree Installation Fault
1. Possible Causes
_______________
- SFCC-1 (21CV)
- SFCC-2 (22CV)
- aircraft wiring
2. Job Set-up Information
______________________
A. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
27-81-00-810-833 Slats - Pin Program Disagree Installation Fault ASM 275108S01 AMM 27-51-34-000-001 Removal of the SFCC (21CV,22CV) AMM 27-51-34-400-001 Installation of the SFCC (21CV,22CV) AMM 31-32-00-860-006 Procedure to Get Access to the SYSTEM REPORT/TEST
F/CTL Page
3. Fault Confirmation
__________________
A. Test
(1) Get access to the SYSTEM REPORT/TEST F/CTL page, (Ref. AMM TASK 31-32-00-860-006), press the line key for the applicable SFCC menu, and press the line key for FLP class 3 faults.
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本文鏈接地址：A320 Trouble Shooting Manual 排故手冊 飛行操縱 2(13)
