(a) The BITE gives a "WTBs set in this channel"
(2) Do the detailed inspection of the PCU (Ref. AMM TASK 27-54-00-200-001)).
(a) During the inspection at Para 4.A.(2).
- refer to (Ref. AMM TASK 27-51-19-000-001) Figure 402 and identify the FPPU:
- do a check of the FPPU zero datum mark.
- if the zero datum marks are NOT aligned. Do (Ref. AMM TASK 27-51-00-820-001).
- if the zero datum is set
- do the reset of the wing tip brakes (Ref. AMM TASK 27-50-00-869-006)
(3) Do the operational test of the flap system, (Ref. AMM TASK 27-54-00-710-001).
(4) Access the FLP ON GROUND FAULTS and check that the ground log is clear.
5. Close-up
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A. 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 253
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CES Right Flap Interconnecting-Strut Attachment Failure-Detection Sensor Fault
WARNING : MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING
_______
GEAR.
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 : 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.
1. Possible Causes
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- SFCC-1 (21CV)
- SFCC-2 (22CV)
- SENSOR-R FLAP ATTACHMENT FAILURE DETECTION (38CV)
- SENSOR-R FLAP ATTACHMENT FAILURE DETECTION (40CV)
- aircraft wiring
2. Job Set-up Information
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A. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
32-31-00-810-829 Right Flap Disconnect Proximity Sensor (38CV, 40CV) 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
「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 254
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 (38CV or 40CV), do the fault isolation procedure in (Ref. TASK 32-31-00-810-829).
(3) If the test does not give a message that includes the DISC PROX SENSOR (38CV or 40CV), 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-R FLAP ATTACHMENT FAILURE DETECTION (38CV) or SENSOR-R FLAP ATTACHMENT FAILURE DETECTION (40CV), (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:
- the applicable proximity sensor and the related LGCIU, (Ref. ASM 27-51/06) or (Ref. ASM 27-51/07)
- the applicable LGCIU and the related SFCC, (Ref. ASM 27-51/06) or (Ref. ASM 27-51/07). 中國航空網(wǎng) 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 1(102)
