(c) Do the test in para 3.A. with the L/G simulated to shock absorbers extended (Ref. AMM TASK 32-69-00-860-001).
(2) If the test in para. 3.A. is not OK:
(a) Do a check to see if the circuit breaker (2DL) is open, if it is open, do (Ref. TASK 30-11-00-810-809).
(3) If the circuit breaker (2DL) is closed:
(a) On the P/BSW (3DL) connector do a check for 28VDC on the pin D1 (Ref. ASM 30-11/01).
(b) If there is no 28VDC, replace the C/B-ANTI-ICE/WING/CTL 2DL.
(c) Do the test in Para. 3.A.
(4) If there is 28VDC:
(a) With the P/BSW 3DL connected, and set to on, do a check for 28VDC at the relay anti-ice valve control, connector pin X (Ref. ASM 30-11/01).
(b) If there is no 28VDC, replace the P/BSW ANTI ICE/WING 3DL.
(c) Do the test in para. 3.A.
(5) If there is 28VDC:
(a) Replace the RELAY ANTI ICE VALVE CONTROL 5DL
(b) Do the test in Para. 3.A.
(6) If the fault continues:
(a) Replace the RELAY GROUND TEST (4DL).
(b) Do the test in Para. 3.A.
(7) If the fault continues:
(a) Do a check of the aircraft wiring (Ref. ASM 30-11/01) between:
- the circuit breaker (2DL) and the P/BSW (3DL)
- relay (3DL) and relay (5DL)
- relay (5DL) and relay (4DL)
- relay (4DL) connector pin A3 and pin X2 for ground
(b) Repair all the unserviceable wiring and connectors.
(c) 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 ∞∞30-11-00∞∞∞∞∞∞∞∞∞∞Page 210
Aug 01/05R CES
Wing Anti-Ice - Spurious Fault Indications.
1. Possible Causes_______________
- Wing Anti-Ice System
2. Job Set-up Information______________________ Not Applicable
3. Fault Confirmation__________________
A. Test
(1) Examine the ECAM display for the Wing Anti-Ice System fault warning.
4. Fault Isolation_______________
A. Procedure
(1) If the ECAM shows the Wing Anti-Ice System warning, do the trouble shooting procedure related to the maintenance message.
(2) If the ECAM shows no Wing Anti-Ice System warning, the CFDS message can be regarded as spurious and requires no further action.
「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 ∞∞30-11-00∞∞∞∞∞∞∞∞∞∞Page 211
Aug 01/05R
CES Wing Anti-Ice Control-Valves Stay Open After Ground Test
WARNING : DO NOT TOUCH THE ANTI-ICE DUCTS UNTIL THEY ARE COOL. THE TEMPERATURE
_______
OF THE DUCTS STAYS HIGH FOR SOME TIME AFTER THE ENGINE STOPS.
1. Possible Causes
_______________
- RELAY-GROUND TEST (4DL)
- LGCIU-1 (5GA1)
- LGCIU-2 (5GA2)
- PROX SNSR-L L/G EXT, SYS 1 (21GA)
- PROX SNSR-R L/G EXT, SYS 2 (22GA)
- RELAY-FAULT MONITOR C/O (6DL)
- aircraft wiring
2. Job Set-up Information
______________________
A. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION
-------------------------------------------------------------------------------
AMM 30-11-00-710-001 Operational Test of the Wing Ice-Protection System
AMM 32-31-71-000-001 Removal of the LGCIU (5GA1, 5GA2)
AMM 32-31-71-400-001 Installation of the LGCIU (5GA1, 5GA2)
AMM 32-31-73-000-001 Removal of the Proximity-Sensors 9GA(8GA),
11GA(10GA), 27GA(26GA), 29GA(28GA), 15GA(14GA), 17GA(16GA), 21GA(20GA), 23GA(22GA), 33GA(32GA), 35GA(34GA)
AMM 32-31-73-400-001 Installation of the Proximity-Sensors 9GA(8GA), 11GA(10GA), 27GA(26GA), 29GA(28GA), 15GA(14GA), 17GA(16GA), 21GA(20GA), 23GA(22GA), 33GA(32GA)...
AMM 32-31-73-820-002 Adjustment of the MLG Extension Proximity Sensors 20GA, 21GA, 22GA, 23GA ASM 30-11/01
3. Fault Confirmation
__________________
A. Procedure
CAUTION : MAKE SURE THAT YOU SET THE WING ANTI-ICE SYSTEM P/BSW TO OFF
_______ AFTER 30 SECONDS. THIS WILL PREVENT DAMAGE TO THE SLATS.
NOTE : When the Wing Anti-Ice System Ground Test is OK, the system will
____ automatically switch off after 30 seconds. If after 35 seconds the anti-ice symbols on the BLEED page, on the lower ECAM DU, do not go off, the ANTI ICE WING P/BSW must be released (out) manually.
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