R Data Fault Between SFCC 1 and SFCC 2. Loss of Cross-computer Link or Faulty R Data.
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)
- aircraft wiring
2. Job Set-up Information
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A. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION
-------------------------------------------------------------------------------
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 27-54-00-710-001 Operational Test of the Flap System
AMM 31-32-00-860-006 Procedure to Get Access to the SYSTEM REPORT/TEST
F/CTL Page
ASM 27-51/08
3. Fault Confirmation
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A. Table of the circuit breakers used in this procedure:
-------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION -------------------------------------------------------------------------------49VU FLIGHT CONTROLS/FLP/CTL AND MONG/SYS1 6CV B07 121VU FLIGHT CONTROLS/FLP/CTL AND/MONG/SYS2 8CV Q21
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R B. Reset and Intialization.
R (1) At the circuit breakers:
(a) Open the circuit breakers.
(b) Wait for 3 seconds and close the circuit breakers.
(c) Wait for 60 seconds and do the next step.
(2) At the MCDU set the SYSTEM REPORT/TEST FLT CTL page (Ref. AMM TASK 31-32-00-860-006):
(a) Set the SFCC related to the flap channel which reported the loss of data.
(b) At the applicable SFCC1 (or SFCC2) SYSTEM STATUS FLAP page: R - If the message FLP1 NO SFCC2 DATA (or FLP2 NO SFCC1 DATA) is R shown, do the fault isolation procedure given in Para. 4.A. R - If a different message is shown, do the trouble shooting R procedure related to the message. R - If no message is shown, no further maintenance action is R necessary.
4. Fault Isolation
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A. Procedure
(1) Interchange SFCC1 with SFCC2 (Ref. AMM TASK 27-51-34-000-001) and (Ref. AMM TASK 27-51-34-400-001).
(2) Do the test given in Para. 3.B.(2):
- if the message stays the same, do step (5)
- if the message goes, do the next step.
(3) Replace the SFCC-1 (21CV) or SFCC-2 (22CV) in the flap channel which reported the loss of data (Ref. AMM TASK 27-51-34-000-001) and (Ref. AMM TASK 27-51-34-400-001):
- if the fault continues, do the next step.
(4) Replace the opposite SFCC to that replaced in step (3):
- if the fault continues, do the next step.
「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 214
May 01/05 CES
(5) Do a check and repair the aircraft wiring between SFCC1 and SFCC2 (Ref. ASM 27-51/08).
(6) Do the operational test of the flaps system (Ref. AMM TASK 27-54-00-710-001).
「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 215
May 01/00R
CES R Loss of SFCC 1 (2) Because of an A/C Pin Program Fault
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
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