(3) Do the steps at 4.A.(1).
R (a) If data is shown, do step 3.B.(2).
(b) Set the MENU MODE and access the FLP ON GROUND FUALTS and check that the ground log is clear.
(4) If the fault does not move.
(a) On the FPPU 27CV, swap the electrical connectors 27CV-A and 27CV-B.
(b) If the fault moves to the other SFCC, go to step 4.A.(5).
(c) If the fault remains in the same circuit do step 4.A.(6).
(5) Replace the 27CV (27CV) (Ref. AMM TASK 27-51-19-000-001) (Ref. AMM TASK 27-51-19-400-001),
(6) Do a check of the aircraft wiring between the SFCC 1 (2) ARINC tray R interface and the flap FPPU electrical connector (Ref. ASM 27-51/06) R (Ref. ASM 27-51/07).
(7) If there is a wiring/interface fault do the repair.
(8) Do the operational test of the flaps system,(Ref. AMM TASK 27-54-00-710-001)
(a) Access the FLP ON GROUND FAULTS and make sure the ground log is clear.
5. Close-up
________
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.
「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 210
Aug 01/98 CES
CSU Fault (51CV) or Fault in Wiring to SFCC 1 (2)
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 TRAVEL RANGES OF THE FLIGHT CONTROL SURFACES ARE
_______
CLEAR BEFORE YOU PRESSURIZE/DEPRESSURIZE A HYDRAULIC SYSTEM.
1. Possible Causes
_______________
- SFCC-1 (21CV)
- SFCC-2 (22CV)
- CSU (51CV)
- aircraft wiring
2. Job Set-up Information
______________________
A. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION
-------------------------------------------------------------------------------
AMM 27-51-17-000-001 Removal of the Command Sensor Unit (CSU) (51CV)
AMM 27-51-17-400-001 Installation of the Command Sensor Unit (CSU) (51CV)
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 27-54-00-710-002 Operational Test of the Flap and Slat Systems
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) Do an operational test of the slats and flaps (Ref. AMM TASK 27-54-00-710-002).
(2) Get access to the SYSTEM REPORT/TEST F/CTL page (Ref. AMM TASK 31-32-00-860-006).
(a) Set the applicable SFCC 1 or SFCC 2, which gave the initial failure message.
「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 211
Feb 01/00R CES
R R R R (b) Access the SYSTEM STATUS page: - If a CSU (51CV) failure message is shown, do the fault isolation procedure in Para. 4.A. - If a different failure message is shown, do the trouble shooting procedure related to the failure message.
NOTE : It is necessary to RETURN to the F/CTL page and set the____ applicable SFCC again, to update the SYSTEM STATUS page.
4. Fault Isolation_______________
A. Procedure
(1) Interchange the SFCC 1 and SFCC 2, (Ref. AMM TASK 27-51-34-000-001) and (Ref. AMM TASK 27-51-34-400-001).
(2) If the fault moves to the other SFCC, replace the defective SFCC-1 (21CV) or SFCC-2 (22CV).
(3) If the fault stays in the same SFCC, get access to the CSU and interchange the electrical connectors 51CV-A and 51CV-B (Ref. AMM TASK 27-51-17-000-001) and (Ref. AMM TASK 27-51-17-400-001).
(4) Do the test in Para. 3.A.
(5) If the fault moves to the other SFCC, replace the CSU (51CV).
(6) If the fault stays in the initial SFCC, do a check and repair the aircraft wiring between the applicable SFCC ARINC tray interface and the applicable electrical connector 51CV-A or 51CV-B, (Ref. ASM 27-51/02) or (Ref. ASM 27-51/03).
中國航空網(wǎng) www.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(86)
