(6) Do a check of the A/C wiring between SFCC 2 ARINC tray interface and the electrical connector (Ref. ASM 27-51/07) 34CVB (GREEN solenoid)
(7) If there is no continuity repair the wiring/interface.
(8) If the A/C wiring is satisfactory, do a check of the circuit
resistance and circuit isolation of the fault indicated solenoid
valve.
(9) On the RH WTB, use a Multimeter and do a check of the resistance
between
(a) For SFCC1 - 34CVA - RH Blue Solenoid Pins A and B. (Ref. ASM 27-51/06)
(b) For SFCC2 - 34CVB - RH Green Solenoid Pins A and B (Ref. ASM 27-51/07)
(c) The resistance for the solenoid valve 667C0000-02 must be between 71 ohms and 84 ohms
(d) The resistance for the solenoid valves 903A0000-01; 1106A0000-01 and 1111A0000-01 must be between 53 ohms and 60 ohms
(10) On the RH WTB BLUE solenoid do a check for circuit isolation.
(a) For the BLUE solenoid connect the pins A & B together.
(b) Connect one test lead of the 45Vdc Isolation Tester to the pins AB for the BLUE solenoid and the other test lead to pin C.
(c) Supply a test signal for 5 seconds and read the shown resistance value
(d) the resistance value must be greater than 100Megohms.
(e) For the GREEN soleniod do the same operation as in 4.A.(9) and (10).
(11) If the BRAKE-R WING TIP (34CV) fails one of the two tests at Para 4.A.(9) and (10) replace the WTB solenoid valve, (Ref. AMM TASK 27-51-51-000-002) (Ref. AMM TASK 27-51-51-400-002).
(12) Do the system BITE test as given in Para 3.A.(1).
(13) Set the MCDU to MENU MODE and access the FLP ON GROUND FAULTS page and make sure that the ground log is clear.
「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 283
May 01/05R
CES
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 284
May 01/05R
CES EFCS Identifies a Loss of Data from the SFCC-1 (2).
1. Possible Causes
_______________
- SFCC-1 (21CV)
- SFCC-2 (22CV) R - aircraft wiring between:
2. Job Set-up Information
______________________
A. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
AWM 275123W01
AWM 275124W01 R AWM 278123W01 R AWM 278124W01
AMM 27-51-34-000-001 Removal of the SFCC (21CV,22CV)
AMM 27-51-34-400-001 Installation of the SFCC (21CV,22CV)
3. Fault Confirmation
__________________
A. Select MCDU MENU mode, set the CFDS then A/C CURRENT STATUS or AVIONICS STATUS.
(1) Do a check of the STATUS report and look for a SFCC-1 (2) fault on the SDAC, CFDIU, ELAC, FAC and SEC.
(2) If these systems identify an SFCC-1 (2) fault, do the fault isolation.
4. Fault Isolation
_______________
R A. This fault isolation procedure is for a fault (loss of data) not
R identified withthe SFCC-1 (2) but identified with the related systems.
R (1) Interchange the SFCC-1 (2) with SFCC-2 (1) (Ref. AMM TASK 27-51-34-R 000-001), (Ref. AMM TASK 27-51-34-400-001),
(2) Do the procedure at Para. 3.A.(1). R (3) If the fault does not continue, the fault is in the SFCC-1 (2).
(a) Install the serviceable SFCC-2 (1) in its initial location and replace the unserviceable SFCC-1 (21CV) (SFCC-2 (22CV)), Refer to Para. 4.A.(1).
「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 285
Aug 01/05 CES
(b) Do the procedure at Para. 3.A.(1).
R (4) If the fault continues in the SFCC-1 (2) circuit, do a check of the
R aircraft wiring between:
R - The SFCC-1 (2) FLAP ARINC connector tray and the BUS connector to
R 1853VT (SFFC 1 (Ref. AWM 275123W01)) (SFFC 2 (Ref. AWM 275124W01)).
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本文鏈接地址：A320 Trouble Shooting Manual 排故手冊 飛行操縱 2(9)
