WARNING : PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU
_______
START A TASK ON OR NEAR:
- THE FLIGHT CONTROLS
- THE FLIGHT CONTROL SURFACES
- THE LANDING GEAR AND THE RELATED DOORS
- 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 27-51-34-000-001 Removal of the SFCC (21CV,22CV)
AMM 27-51-34-400-001 Installation of the SFCC (21CV,22CV)
AMM 27-81-00-710-001 Operational Test of the Wing-Tip Brake and the
Pressure-Off Brake
AMM 27-81-00-740-002 Bite Test of the Slat and Flap Control Computers
(Slat System)
AMM 27-84-00-710-001 Operational Test of the Slat 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 ∞∞27-81-00∞∞∞∞∞∞∞∞∞∞Page 270
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 27-81-00-740-002).
(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) or 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 Slat System (Ref. AMM TASK 27-84-00-710-001).
(4) If a fault is detected, swop the SFCC-1 with the SFCC-2.
(5) Do the Operational Test of the Slat 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 27-81-00-710-001).
(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 related 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 ∞∞27-81-00∞∞∞∞∞∞∞∞∞∞Page 271
May 01/05R CES
Slats - 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
-------------------------------------------------------------------------------
AMM 27-51-34-000-001 Removal of the SFCC (21CV,22CV)
AMM 27-51-34-400-001 Installation of the SFCC (21CV,22CV)
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