1. Possible Causes
_______________
- flaps control lever is out of detent
2. Job Set-up Information
______________________
A. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
AMM 27-51-00-740-002 Bite Test of the Slat and Flap Control Computers (Flap System)
3. Fault Confirmation
__________________
A. Test
(1) At the ECAM Control Panel, push the STS P/BSW to show the status page on the lower ECAM DU:
- if a FLAPS status message is not shown, there is no flaps fault
- if a FLAPS status message is shown, do the fault isolation procedure given in Para. 4.
4. Fault Isolation
_______________
A. Procedure
R (1) Make sure that the flaps control lever is in the correct detent and R reset it if necessary:
- if the FLAPS status message has gone, there is no fault
- if the FLAPS status message stays, do the next step.
NOTE : When the flaps control lever is out of detent, SFCC1 and SFCC2
____ will find that the lever position and the flap position (signal from the Valveblock PPU) disagree. The FLP 1 (2) PCU VALVEBLOCK 23CV (24CV) message will then be given by each SFCC
「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 A208
May 01/05 CES
and the ECAM message FLAPS FAULT will be shown. This flight control configuration error can be cleared by a reset of the flaps control lever.
R R (2) Do a BITE test of the SFCC1 and SFCC2 flaps system (Ref. AMM TASK 27-51-00-740-002): - if the test gives a fault message, do the trouble shooting procedure related to this message.
Flaps - SFCC 1 (2) Gives PCU Valveblock 23CV (24CV) Valve Sensor Message
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 GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING
_______
GEAR.
1. Possible Causes
_______________
- SFCC-1 (21CV)
- SFCC-2 (22CV)
- VALVE BLOCK-FLAP 1 (23CV)
- VALVE BLOCK-FLAP 2 (24CV)
- valve sensor
- 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)
AMM 27-54-53-000-001 Removal of the Valve Blocks 23CV, 24CV of the Power
Control Unit (Flap) AMM 27-54-53-400-001 Installation of the Valve Blocks 23CV, 24CV of the Power Control Unit (Flap) AMM 31-32-00-860-006 Procedure to Get Access to the SYSTEM REPORT/TEST
F/CTL Page
ASM 27-51/02
ASM 27-51/03
3. Fault Confirmation
__________________
A. Test
(1) At the MCDU, access the SYSTEM REPORT / TEST page and select F/CTL> (Ref. AMM TASK 31-32-00-860-006).
(2) Select <SFCCX (where X is the No. of the applicable SFCC).
「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 A210
May 01/05R CES
(3) Select <SFCC/TEST, to do the SFCC BITE test:
- if the fault message FLP1 (2) PCU VALVEBLOCK 23CV (24CV) VALVE SENSOR 27-54-53 is shown, do the Fault Isolation Procedure given in Para. 4.
NOTE : This message is not a CFDS Normal Mode message and is only
____
shown in SFCC reports.
4. Fault Isolation
_______________
A. Procedure
(1) Interchange the SFCC1 and SFCC2 (Ref. AMM TASK 27-51-34-000-001) and (Ref. AMM TASK 27-51-34-400-001).
(2) Do the test given in Para. 3.A:
(a) If the fault goes, replace the initial SFCC-1 (21CV) or SFCC-2 (22CV), (Ref. AMM TASK 27-51-34-000-001) and (Ref. AMM TASK 27-51-34-400-001). 中國航空網 m.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：A320 Trouble Shooting Manual 排故手冊 飛行操縱 2(17)
