- NO WTB POWER
- LH WTB SOLENOID S/C (or O/C)
- RH WTB SOLENOID S/C (or O/C)
- LH APPU FAULT
- FPPU FAULT
- RH APPU FAULT
4. Fault Isolation
_______________
A. Procedure
(1) At the MCDU access the CFDS MENU then LAST LEG REPORT to see if a related fault message was given during normal system operation. The table that follows shows the relationship between the messages given during the SFCC TEST and normal mode, it also gives the related trouble shooting task. Do Para. 4.A. of the applicable task.
NOTE : A fault message given during normal mode will make sure that
____ the fault identified during the SFCC TEST is correct. It will also give the FIN of the defective component.
「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 275
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CES
----------------------------------------------------------------------------
SFCC TEST CFDS LAST LEG REPORT TS TASK IN
MESSAGE ------------------- MESSAGE -------------------------------------- 27-81-00-------------------
OTHER SFCC SLT 1 (2) NO SFCC 2 (1) DATA 826
ARM SIGNAL
NOT TESTED
NO WTB POWER SLT 1 (2) C/B 9CV (11CV) 821
LH WTB SOLENOID SLT LH WTB BLU (GRN) SOLENOID 822
S/C (or O/C) 35CV OR WIRING TO SLT 1 (2)
RH WTB SOLENOID SLT RH WTB BLU (GRN) SOLENOID 823
S/C (or O/C) 36CV OR WIRING TO SLT 1 (2)
LH APPU FAULT LH SLT APPU 31CV OR WIRING TO 807
SLT 1 (2)
FPPU FAULT SLT FPPU 28CV OR WIRING TO 806
SLT 1 (2)
RH APPU FAULT RH SLT APPU 32CV OR WIRING TO 807
SLT 1 (2)
----------------------------------------------------------------------------NOTE : The LAST LEG REPORT messages shown are for SFCC1, the items in
____ ( ) are for SFCC 2.
「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 276
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CES Slats - SFCC 1 and SFCC 2 Show PCU Valveblock Fault Message (25CV, 26CV)
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 GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING
_______
GEAR.
1. Possible Causes
_______________
- flaps (and slats) control lever is out of detent
2. Job Set-up Information
______________________
A. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
AMM 27-81-00-740-002 Bite Test of the Slat and Flap Control Computers (Slat System)
3. Fault Confirmation
__________________
A. Test
(1) At the ECAM Control Panel, push the STS P/BSW to show the status page on the lower ECAM DU:
- if a SLATS status message is not shown, there is no slats fault
- if a SLATS status message is shown, do the fault isolation procedure given in Para. 4.
4. Fault Isolation
_______________
A. Procedure
R (1) Make sure that the flaps (and slats) control lever is in the correct R detent and reset it if necessary:
- if the SLATS status message has gone, there is no fault
- if the SLATS status message stays, do the next step.
NOTE : When the flaps (and slats) control lever is out of detent,
____ SFCC1 and SFCC2 will find that the lever position and the slats position (signal from the Valveblock PPU) disagree. The SLT 1 (2) PCU VALVEBLOCK 25CV (26CV) message will then be
「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 277
May 01/05 CES
given by each SFCC and the ECAM message SLATS FAULT will be shown. This flight control configuration error can be cleared by a reset of the flaps (and slats) control lever.
R R (2) Do a BITE test of the SFCC1 and SFCC2 slats system (Ref. AMM TASK 27-81-00-740-002): - If the test gives a fault message, do the trouble shooting procedure related to this message.
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本文链接地址：A320 Trouble Shooting Manual 排故手册 飞行操纵 2(82)
