(4) Do the BITE test of the SFCC 1 (2) Ref. Para 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 ∞∞27-51-00∞∞∞∞∞∞∞∞∞∞Page 232
Feb 01/03R
CES FLAP SYSTEM 1 (2) FAULT, No CFDS Message (normal mode)
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
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- VALVE BLOCK-FLAP 1 (23CV)
- VALVE BLOCK-FLAP 2 (24CV)
- RELAY-FLAP 1 FAULT (91CV)
- RELAY-FLAP 2 FAULT (93CV)
- SFCC-1 (21CV)
- SFCC-2 (22CV)
- transient fault
- aircraft wiring
2. Job Set-up Information
______________________
A. Fixtures, Tools, Test and Support Equipment
-------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
No specific multimeter
B. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
27-51-00-810-802 SFCC - FLAP PCU VALVEBLOCK Fault
R 27-51-00-810-805 CSU Fault (51CV) or Fault in Wiring to SFCC 1 (2) 27-51-00-810-841 Wrong Inhibit Sign From Cargo Door Yellow 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
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May 01/04 CES -------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
AMM 31-60-00-860-001 EIS Start Procedure AMM 31-60-00-860-002 EIS Stop Procedure ASM 27-51/02 ASM 27-51/03
3. Fault Confirmation
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A. Fault Analysis
(1) Do a check of the Post Flight Report (PFR):
- if the ECAM Warning message FLAP SYS 1 (2) FAULT is shown without a related CFDS message and the flaps operated correctly, do the next step.
(2) Do the EIS Start Procedure (Ref. AMM TASK 31-60-00-860-001).
(3) At an MCDU, get access to the SYSTEM REPORT/TEST F/CTL page (Ref. AMM TASK 31-32-00-860-006).
(a) Set F/CTL and get access to the SFCC 1 and SFCC 2 menus.
(b) For each SFCC, set LAST LEG REP FLP and do a check for one or more of the messages that follow:
- SYSTEM STOP DUE TO LOW PRESSURE
- DC POWER INTERRUPT
- DC POWER BELOW 16 V
- SINGLE MOTOR OPERATION
- LEVER OUT OF DETENT FOR MORE THAN 10 SEC.
- INHIBIT SIGNAL FROM CARGO DOOR YELLOW SYSTEM.
NOTE : These messages are shown in the Last Leg Report (LLR) to
____ help with trouble shooting when the ECAM Warning message FLAP SYS 1 (2) FAULT is shown because of a transient fault.
(c) From the check of the LLR:
- if one or more of the applicable messages is shown, do the fault isolation procedure in Para. 4.A.
- if none of the applicable messages are shown, do the fault isolation procedure in Para. 4.B.
「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 234
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CES 4. Fault Isolation
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R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 401-499,
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本文鏈接地址：A320 Trouble Shooting Manual 排故手冊 飛行操縱 1(94)
