(g) If no difference is found go to Para.4.A.(2).
(2) Swap the SFCC 1 and SFCC 2.(Ref. AMM TASK 27-51-34-000-001) for (Ref. AMM TASK 27-51-34-400-001)do a check of the ground log.
(a) Access the FLP ON GROUND FAULTS and do a check of the ground log.
(b) If the fault moves with SFCC 1 (2).
(c) Replace SFCC-1 (21CV) (SFCC-2 (22CV)) Ref. Para.4.A.(2)(a).
(3) Move the slats and flaps control lever from and to a valid position.
(a) Examine the ECAM EWD and the SD FLT/CTL page and check if the fault clears.
(b) If the fault message clears, access the FLP ON GROUND FAULTS page and make sure the ground log is clear.
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(4) If the fault continues, do a check of the aircraft wiring between the SFCC 1(2) and the CSU (Ref. ASM 27-51/02).
(a) If there is a circuit/interface fault do the repair.
(b) Move the flaps (Ref. AMM TASK 27-50-00-866-008) (Ref. AMM TASK 27-50-00-866-009)
(c) Access the FLP ON GROUND FAULTS page and make sure the ground log is clear.
5. Close-up
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A. Remove the ground support and maintenance equipment, the special and standard tools and all other items.
B. Put the aircraft back to its initial configuration.
「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 230
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CES R SFCC 1 (2) OR FLP PPU POWER SFCC Generated FLAP PPU Power Fault.
WARNING : PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU
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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
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CLEAR BEFORE YOU PRESSURIZE/DEPRESSURIZE A HYDRAULIC SYSTEM.
WARNING : MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING
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GEAR.
1. Possible Causes
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- SFCC-1 (21CV)
- SFCC-2 (22CV)
- A/C wiring/interface between SFCC 1 (2) and the PPUs'.
2. Job Set-up Information
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A. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
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)
ASM 27-51/01
ASM 27-51/08
3. Fault Confirmation
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A. SFCC system exitation power test.
(1) Do the SYSTEM TEST (BITE) on the SFCC 1 (2) (Ref. AMM TASK 27-51-00-740-002). The fault data" PPU excitation power short circuit" is displayed. Page block 301 table 7 gives the SFCC test menu selections details.
(2) Do the fault isolation.
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4. Fault Isolation
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A. Procedure
(1) Make sure that there is no SFCC to PPU external circuit/interface short circuit fault, before troubleshooting the SFCC 1 (2).
(a) Do a check of the A/C wiring/interface between SFCC 1 (2) and the PPUs'. (Ref. ASM 27-51/01) (Ref. ASM 27-51/08)
(2) If there is a wiring/interface fault, do the repair.
(a) Do the BITE test of the SFCC 1 (2).
(b) If the same fault message is shown and there are no circuit/interface faults.
(3) Swap the SFCC 1 and SFCC 2.(Ref. AMM TASK 27-51-34-000-001) for (Ref. AMM TASK 27-51-34-400-001) do Para.2,3 and 4 only.
(a) Access the FLP ON GROUND FAULTS and do a check of the ground log.
(b) If the fault moves with SFCC 1(2).
(c) Return the SFCC 1 (2) to their initial locations.
(d) Replace the unserviceable SFCC-1 (21CV) (SFCC-2 (22CV)) Ref. Para.4.A.(1). 中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：A320 Trouble Shooting Manual 排故手册 飞行操纵 1(93)
