「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1R EFF : 301-399, ∞∞28-46-00∞∞∞∞∞∞∞∞∞∞Page A214
May 01/05 CES
**ON A/C ALL
4. Fault Isolation
_______________ R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 401-499,
A. Procedure
(1) Do the steps applicable to the test equipment available.
(2) Test Equipment. WARNING : WHEN YOU DO WORK ON THE FUEL SYSTEM WIRING, YOU MUST USE
_______ TEST EQUIPMENT THAT IS APPROVED (REFER TO INTERNATIONAL OR NATIONAL SPECIFICATIONS FOR INTRINSICALLY SAFE TEST EQUIPMENT, E.G. EN50-020, UL913 OR EQUIVALENT). TEST EQUIPMENT THAT IS NOT APPROVED CAN CAUSE FIRE OR AN EXPLOSION.
(a) If there is:
- approved test equipment available, go to Step (3)
- no approved test equipment available, go to Step (6).
(3) Get access to the tank wall connector 4039VC1(2)-A (for the wing tank harness 13QT1(2)) (Ref. AMM TASK 28-42-43-000-008).
(4) Disconnect the free connector 4039VC1(2)-A from the receptacle 4039VC1(2).
(5) Do a resistance check of the sensor 38QJ1(2) at the tank wall connector 4039VC1(2) between pins <U and <T (Ref. AWM 28-46-11) ( (Ref. AWM 28-46-12)). Make sure the resistance is between 330 and 480 ohms. If there is:
- continuity as specified above, go to Step (6)
- no continuity as specified above (resistance check out of range), go to Step (8).
NOTE : The sensor status (wet or dry) and fuel/air temperature will
____ have an effect on the resistance value.
(6) Replace the FLSCU-1 (7QJ) (FLSCU-2 (9QJ)) (Ref. AMM TASK 28-46-34-000-001) and (Ref. AMM TASK 28-46-34-400-001).
「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 ∞∞28-46-00∞∞∞∞∞∞∞∞∞∞Page A215
Aug 01/05 CES
(7) If the fault continues:
(a) Get access to the tank wall connector 4039VC1(2)-A (for the wing tank harness 13QT1(2)) (Ref. AMM TASK 28-42-43-000-008).
(b) Disconnect the free connector 4039VC1(2)-A from the receptacle 4039VC1(2).
(c) Do a check (Ref. AWM 28-46-11), and (Ref. AWM 28-46-12) of the aircraft wiring (sensor input line - H) between the FLSCU-1(2) rack connector AB, pin 9D and the tank wall free connector 4039VC1(2)-A, pin <U.
(d) Do a check (Ref. AWM 28-46-11), and (Ref. AWM 28-46-12) of the aircraft wiring (sensor input line - L) between the FLSCU-1(2) rack connector AB, pin 9C and the tank wall free connector 4039VC1(2)-A, pin <T.
(e) Do a check (Ref. AWM 28-46-11) of the aircraft wiring (FLSCU-1 BITE 4 test command line) between the FLSCU-1 rack connector AA, pin 15D and the FQIC rack connector AB, pin 7K or ((Ref. AWM 28-46-12) of the aircraft wiring (FLSCU-2 BITE 4 test command line) between the FLSCU-2 rack connector AA, pin 15D and the FQIC rack connector AB, pin 9H).
(f) Do a check (Ref. AWM 28-46-11) of the aircraft wiring (FLSCU-1 LS10 output line) between the FLSCU-1 rack connector AB, pin 1C and the FQIC rack connector AB, pin 3K or ((Ref. AWM 28-46-12) of the aircraft wiring (FLSCU-2 LS10 output line) between the FLSCU-2 rack connector AB, pin 1C and the FQIC rack connector AB, pin 12J).
(g) Repair all the unserviceable wiring and connectors (Ref. ESPM 20-00-00).
(h) Connect the free connector 4039VC1(2)-A to the receptacle
4039VC1(2).
(i) Do the test in Para. 3.A.
(8) If the fault continues or if there is no continuity in Step (5):
(a) Drain, open and vent the tank (Ref. AMM TASK 28-10-00-910-001) and (Ref. AMM TASK 28-10-00-910-002).
(b) Do a wiring check of the HARNESS-CHAN A, L WING TK INR (13QT1) ( HARNESS-CHAN A, R WING TK INR (13QT2)) , (Ref. AWM 28-46-11) ( (Ref. AWM 28-46-12)) and replace, if necessary (Ref. AMM TASK 28-42-43-000-006) and (Ref. AMM TASK 28-42-43-400-006).
「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1R EFF : 001-049, 051-099, 101-149, 151-199, ∞∞28-46-00∞∞∞∞∞∞∞∞∞∞Page A216
201-299, 401-499, Aug 01/05 CES
(c) If the harness is serviceable, replace the SENSOR-LOW LEVEL, LEFT WING TK INNER CHANNEL A (38QJ1) (SENSOR-LOW LEVEL, RIGHT WING TK INNER CHANNEL A (38QJ2)) (Ref. AMM TASK 28-46-19-000-001) and (Ref. AMM TASK 28-46-19-400-001).
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本文鏈接地址：A320 Trouble Shooting Manual 排故手冊(cè) FUEL 燃油4(84)
