4. Fault Isolation
_______________
A. Procedure
(1) Swop the SFCC 1 with SFCC 2 (Ref. AMM TASK 27-51-34-000-001) and (Ref. AMM TASK 27-51-34-400-001).
(2) If the fault moves with the SFCC:
- replace the applicable SFCC-1 (21CV) or SFCC-2 (22CV).
(3) If the fault does not move with the applicable SFCC:
(a) Replace the applicable APPU-L SLAT (31CV) APPU-R SLAT (32CV) (Ref. AMM TASK 27-81-18-000-001) (Ref. AMM TASK 27-81-18-400-001).
(4) If the fault continues:
(a) Do a check of the aircraft wiring between the applicable SFCC and the related APPU (Ref. ASM 27-81/06).
(b) Do the repair.
(c) Do the test given in Para. 3.A.(1).
「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 220
Nov 01/00R
CES R SFCC 1 (2) or SLT PPU Power Fault. SFCC Generated SLT Power Fault.
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.
WARNING : MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING
_______
GEAR.
1. Possible Causes
_______________
- SFCC-1 (21CV)
- SFCC-2 (22CV)
- A/C wiring/interface between SFCC 1 (2) and all PPU.
2. Job Set-up Information
______________________
A. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
ASM 275101S01
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 27-81-00-740-002 Bite Test of the Slat and Flap Control Computers
(Slat System)
3. Fault Confirmation
__________________
A. SFCC System Exitation Power Test.
(1) Do a BITE test on the SFCC 1 (2) (Ref. AMM TASK 27-81-00-740-002). The fault data" PPU excitation power short circuit" is displayed.
(2) Do the fault isolation.
4. Fault Isolation
_______________
A. Procedure
(1) 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 SLT ON GROUND FAULTS and do a check of the ground log.
(2) If the fault moves with SFCC 1(2).
(3) Return the SFCC 1 (2) to their initial locations.
(4) Replace the unserviceable SFCC-1 (21CV) (SFCC-2 (22CV)) Ref. Para.4.A.(1)>
(5) Do the BITE test of the SFCC 1 (2) Ref. Step 3.A.(1).
(6) If the fault continues, do a check of the A/C wiring/interface between SFCC 1 (2) and all PPU. (Ref. ASM 275101S01) (Ref. ASM 275108S01)
(7) If there is a wiring/interface fault, do the repair.
(8) Do the BITE Test.Ref 3.A.(1).
5. Close-up
________
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 ∞∞27-81-00∞∞∞∞∞∞∞∞∞∞Page 222
Aug 01/98R
CES Slat System Jam.
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
_______________
- POWER CONTROL UNIT (6001CM)
- BRAKE-L WING TIP (35CV)
- BRAKE-R WING TIP (36CV)
- Rotary Actuators
- Transmission Assembly
- Slat Track Rollers 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 2(62)
