(a) Swop the SFCC's and repeat the test in Para. 3.A. on SFCC-1 (21CV) and SFCC-2 (22CV).
(2) If the fault has moved to the other SFCC position, swop the SFCC's back and replace the SFCC that has the fault (Ref. AMM TASK 27-51-34-000-001) and (Ref. AMM TASK 27-51-34-400-001).
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(3) If the fault did not move to the other SFCC position, swop the SFCC's back Ref. Para. (2).
(a) Make sure that there are no landing gear system faults (Ref. ATA 32-31-00)
NOTE : Main landing gear shock absorber proximity sensor faults
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will cause this failure.
- For SFCC 1 PROX SNSR R L/G EXT 20GA and PROX SNSR L L/G EXT 21GA
- For SFCC 2 PROX SNSR R L/G EXT 22GA and PROX SNSR L L/G EXT 23GA
(4) If there were any landing gear faults, do the test in Para. 3.A.
(5) If the fault continues:
(a) Swop the RELAY-A/C ON GND (94CV) with RELAY-A/C ON GND (96CV).
(b) Do the test in Para. 3.A. on the SFCC 1 and SFCC 2.
(c) If the fault moves to the other system, replace the relay in the system that now has the fault.
(d) Do the test in Para. 3.A.
(6) If the fault does not move to the other system, do a check of the aircraft wiring:
- for SFCC 1 from C/B 5CV to the LGCIU 1 and from the RELAY A/C ON GND 94CV to SFCC 1 (Ref. ASM 27-81/02).
- for SFCC 2 from C/B 7CV to the LGCIU 2 and from the RELAY A/C ON GND 96CV to SFCC 2 (Ref. ASM 27-81/03).
(a) Repair any defect found.
(b) Do the test 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 ∞∞27-81-00∞∞∞∞∞∞∞∞∞∞Page 236
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CES Slat System Asymmetry 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.
1. Possible Causes
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- slat transmission assembly
2. Job Set-up Information
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A. Referenced Information
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REFERENCE DESIGNATION
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AMM 27-80-00-869-004 Reset of the Wing Tip Brake (WTB) of the Slat System on the Ground AMM 27-81-00-740-002 Bite Test of the Slat and Flap Control Computers (Slat System) AMM 27-81-18-000-001 Removal of the Asymmetry-Position Pick-Off Unit 31CV (32CV) AMM 27-81-18-400-001 Installation of the Asymmetry-Position Pick-Off Unit 31CV (32CV) AMM 27-84-00-200-001 Detailed Visual Inspection of the Slat Transmission System AMM 27-84-00-710-001 Operational Test of the Slat System
3. Fault Confirmation
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A. Procedure
(1) For the fault message, SLT 1 ASYMMETRY LH/RH. CHECK SLT MECH DRIVE. Access the MENU Mode and set it to SFCC 1.
(a) Go to submenu SYSTEM DATA SLAT.
(b) Press the line key 1L to set the PPU page.
(c) The SFCC transmits the LH and RH APPU data page(s) to the CFDS.
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(d) The selected page is transmitted again every 5 seconds with refreshed data.
(e) Refer to page block 301 table 2. The LH APPU and RH APPU Synchro Angles are shown as a decimal value.
(f) If there is a difference between the LH and RH values, do the fault isolation.
1 A difference of more than 5.2 deg. generates an asymmetry
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fault message.
(2) For the fault message, SLT 2 ASYMMETRY LH/RH. CHECK SLT MECH DRIVE. Do the step 3.A.(1) but substitute SFCC 2. 中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：A320 Trouble Shooting Manual 排故手册 飞行操纵 2(68)
