(e) If the ECAM warning clears.
(f) Access the FLP ON GROUND FAULTS, and make sure the ground log is clear.
(g) If the ECAM warning and a ground log message is displayed do the fult isolation.
4. Fault Isolation
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A. Procedure
(1) The SFCC flap system has two (2) reported fault coditions.
(2) Access the LAST LEG REPORT and look for the message " SFCC 1". and ""SFCC 2".
(a) Each SFCC is the subject of the system test (BITE) and each fault is identified as a separate subject.
(b) Do the system test (BITE) (Ref. AMM TASK 27-51-00-740-001) on each SFCC in turn.
(c) Refer the applicable fault symptoms to page block 101 and carry out the related TSM procedure.
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.
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Left Flap Interconnecting-Strut Attachment Failure-Detection Sensor 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)
- SENSOR-L FLAP ATTACHMENT FAILURE DETECTION (37CV)
- SENSOR-L FLAP ATTACHMENT FAILURE DETECTION (39CV)
- aircraft wiring
2. Job Set-up Information
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A. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
32-31-00-810-828 Left Flap Disconnect Proximity Sensor (37CV, 39CV) AMM 27-51-00-710-002 Operational Test of the Flap Interconnecting Strut and the Flap-Attachment Failure-Detection Sensors AMM 27-51-15-000-002 Removal of the Proximity-Sensors of the Interconnecting Strut AMM 27-51-15-400-002 Installation of the Proximity-Sensors of the
Interconnecting Strut
AMM 27-51-34-000-001 Removal of the SFCC (21CV,22CV)
AMM 27-51-34-400-001 Installation of the SFCC (21CV,22CV)
R AMM 32-69-00-740-001 BITE Check Landing Gear Control Interface Unit R (LGCIU) using MCDU to Ensure that Continuous BITE is R Operative
ASM 27-51/06
ASM 27-51/07
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May 01/04 CES
3. Fault Confirmation
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A. Test
(1) Do a BITE test with the LGCIU given in the CFDS message (Ref. AMM TASK 32-69-00-740-001).
(2) If the test gives a message that includes the DISC PROX SENSOR (37CV or 39CV), do the fault isolation procedure in (Ref. TASK 32-31-00-810-828).
(3) If the test does not give a message that includes the DISC PROX SENSOR (37CV or 39CV), but the fault continues, do the fault isolation procedure in Para. 4.
4. Fault Isolation
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A. Procedure
(1) Interchange the SFCCs, use (Ref. AMM TASK 27-51-34-000-001) and (Ref. AMM TASK 27-51-34-400-001).
NOTE : This will cause each SFCC to get a new identification.
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(2) Do an operational test of the flap interconnecting strut (Ref. AMM TASK 27-51-00-710-002).
(3) If the test is OK:
(a) Replace the SFCC-1 (21CV) or SFCC-2 (22CV) that was the source of the initial CFDS message.
(4) If the test is not OK (gives the same CFDS message as the initial CFDS message):
(a) Replace the applicable proximity sensor SENSOR-L FLAP ATTACHMENT FAILURE DETECTION (37CV) or SENSOR-L FLAP ATTACHMENT FAILURE DETECTION (39CV), (Ref. AMM TASK 27-51-15-000-002) and (Ref. AMM TASK 27-51-15-400-002).
(5) If the fault continues, do a check and repair as necessary the aircraft wiring between:
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本文链接地址：A320 Trouble Shooting Manual 排故手册 飞行操纵 1(98)
