- 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 17QJ1(2) at the tank wall connector 4039VC1(2) between pins <V and EE (Ref. AWM 28-46-02). 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 220
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 28-46-01) and (Ref. AWM 28-46-02) of the aircraft wiring (sensor input line - H) between the FLSCU-1(2) rack connector AB, pin 10A and the tank wall free connector 4039VC1(2)-A, pin <V.
(d) Do a check (Ref. AWM 28-46-01) and (Ref. AWM 28-46-02) of the aircraft wiring (sensor input line - L) between the FLSCU-1(2) rack connector AB, pin 10B and the tank wall free connector 4039VC1(2)-A, pin EE.
(e) Do a check (Ref. AWM 28-46-01) of the aircraft wiring (FLSCU-1 BITE 1 test command line) between the FLSCU-1 rack connector AA, pin 15B and the FQIC rack connector AB, pin 7H, or the (aircraft wiring (FLSCU-2 BITE 1 test command line) between the FLSCU-2 rack connector AA, pin 15B and the FQIC rack connector AB, pin 10H).
(f) Do a check (Ref. AWM 28-46-01) of the aircraft wiring (FLSCU-1 LS3 output line) between the FLSCU-1 rack connector AB, pin 2A and the FQIC rack connector AB, pin 6G, or the (aircraft wiring (FLSCU-2 LS3 output line) between the FLSCU-2 rack connector AB, pin 2A and the FQIC rack connector AB, pin 11H).
(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.B.
(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-GROUP A, L WING TK INR (13QT1) ( HARNESS-GROUP A, R WING TK INR (13QT2)) (Ref. AWM 28-46-02) 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 221
201-299, 401-499, Aug 01/05 CES
(c) If the harness is serviceable, replace the SENSOR-HI LEVEL, LEFT WING TANK INNER CHANNEL A (17QJ1) (SENSOR-HI LEVEL, RIGHT WING TANK INNER CHANNEL A (17QJ2)) (Ref. AMM TASK 28-46-15-000-001) and (Ref. AMM TASK 28-46-15-400-009).
**ON A/C 301-399,
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 57QT(58QT)) (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 17QJ1(2) at the tank wall connector 4039VC1(2) between pins <V and EE (Ref. AWM 28-46-02). Make sure the resistance is between 330 and 480 ohms. If there is:
- continuity as specified above, go to Step (6) 中國航空網 www.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：A320 Trouble Shooting Manual 排故手冊 FUEL 燃油4(47)
