(b) If the fault continues, replace the applicable VALVE BLOCK-FLAP 1 (23CV) or VALVE BLOCK-FLAP 2 (24CV), (Ref. AMM TASK 27-54-53-000-001) and (Ref. AMM TASK 27-54-53-400-001).
NOTE : The valve sensor is not a Line Replaceable Unit (LRU) and
____ it is necessary to replace the valve block.
(3) If the fault continues:
(a) Do a check of the aircraft wiring and repair as necessary (Ref. ASM 27-51/02) or (Ref. ASM 27-51/03).
(b) Do the test given in Para. 3.A.
「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 A211
May 01/05R
CES Flap Attachment ECAM Warning (FLT/CTL - FLAP ATTACH SENSOR)
1. Possible Causes
_______________
- SFCC-1 (21CV)
- SFCC-2 (22CV)
- LGCIU-1 (5GA1)
- LGCIU-2 (5GA2)
- SENSOR-L FLAP ATTACHMENT FAILURE DETECTION (37CV)
- SENSOR-L FLAP ATTACHMENT FAILURE DETECTION (39CV)
- SENSOR-R FLAP ATTACHMENT FAILURE DETECTION (38CV)
- SENSOR-R FLAP ATTACHMENT FAILURE DETECTION (40CV)
2. Job Set-up Information
______________________
A. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
27-51-00-810-806 Data Fault Between SFCC 1 and SFCC 2. Loss of
Cross-computer Link or Faulty Data. 27-51-00-810-831 SFCC 1 No LGCIU 1 Data or SFCC 2 No LGCIU 2 Data. 32-31-00-810-828 Left Flap Disconnect Proximity Sensor (37CV, 39CV) 32-31-00-810-829 Right Flap Disconnect Proximity Sensor (38CV, 40CV) AMM 27-51-00-740-002 Bite Test of the Slat and Flap Control Computers
(Flap System) AMM 32-69-00-740-001 BITE Check Landing Gear Control Interface Unit
(LGCIU) using MCDU to Ensure that Continuous BITE is
Operative
3. Fault Confirmation
__________________
A. Test
(1) Do a BITE test of the SFCC-1 (21CV) or SFCC-2 (22CV), identified on the Post Flight Report (PFR) (Ref. AMM TASK 27-51-00-740-002) and record each fault related to the flap attachment, for example:
- SFCC 1 (2) 21CV (22CV) (SFCC fault)
- NO LGCIU 1 (2) DATA / CHECK WIRING TO FLP 1 (2) (ARINC 429 Input fault)
- FLP 1 (2) NO SFCC 2 (1) DATA / CHECK WIRING & SFCC 2 (1) (ARINC 429 X-computer data link fault).
「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 A212
May 01/05R
CES
(2) Do a BITE test of the LGCIU-1 (5GA1) or LGCIU-2 (5GA2) identified on the PFR (Ref. AMM TASK 32-69-00-740-001) and record each fault related to the flap attachment, for example:
- L FLP DISC PROX SNSR SENSOR-L FLAP ATTACHMENT FAILURE DETECTION (37CV) or SENSOR-L FLAP ATTACHMENT FAILURE DETECTION (39CV) (LH flap attachment sensor 1 or 2 fault)
- R FLP DISC PROX SNSR SENSOR-R FLAP ATTACHMENT FAILURE DETECTION (38CV) or SENSOR-R FLAP ATTACHMENT FAILURE DETECTION (40CV) (RH flap attachment sensor 1 or 2 fault)
(3) Do the fault isolation procedure given in Para. 4.
NOTE : The ECAM Warning message "FLT/CTL - FLAP ATTACH SENSOR" is
____ only shown when there are two faults in the flap attachment monitoring system. One fault in System 1 and one fault in System 2. The ECAM warning is not shown if the two faults are a failure of Sensor 1 and Sensor 2 on the same interconnecting strut. This condition is a MISADJUSTMENT fault which does not give an ECAM warning.
4. Fault Isolation_______________
A. Procedure
(1) For SFCC faults do the TSM Task (Ref. TASK 27-51-00-810-806).
(2) For LGCIU faults do the TSM Task (Ref. TASK 27-51-00-810-831).
(3) For LH flap attachment sensor faults do the TSM Task (Ref. TASK 32-31-00-810-828).
(4) For RH flap attachment sensor faults do the TSM Task (Ref. TASK 32-31-00-810-829).
「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 A213
May 01/05R
CES Flaps - SFCC TEST Gives the Message PERFORMED WITH FAULT
1. Possible Causes
_______________
- SFCC-1 (21CV)
- SFCC-2 (22CV)
2. Job Set-up Information
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本文链接地址：A320 Trouble Shooting Manual 排故手册 飞行操纵 2(18)
