(7) If the fault continues:
(a) Get access to the tank wall connector 4040VC1(2)-A (for the wing tank harness 14QT1(2)) (Ref. AMM TASK 28-42-43-000-008).
(b) Disconnect the free connector 4040VC1(2)-A from the receptacle 4040VC1(2).
(c) Do a check (Ref. AWM 28-46-05) of the aircraft wiring (sensor input line - H) between the FLSCU-2 rack connector AB, pin 8A and the tank wall free connector 4040VC1-A, pin <G, or the (aircraft wiring (sensor input line - H) between the FLSCU-2 rack connector AB, pin 15A and the tank wall free connector 4040VC2-A, pin <G).
(d) Do a check (Ref. AWM 28-46-05) of the aircraft wiring (sensor input line - L) between the FLSCU-2 rack connector AB, pin 8B and the tank wall free connector 4040VC1-A, pin <W, or the (aircraft wiring (sensor input line - L) between the FLSCU-2 rack connector AB, pin 15B and the tank wall free connector 4040VC2-A, pin <W).
(e) Do a check (Ref. AWM 28-46-06) of the aircraft wiring (FLSCU-2 BITE 3 test command line) between the FLSCU-2 rack connector AA, pin 15C and the FQIC rack connector AB, pin 9J, or the (aircraft wiring (FLSCU-2 BITE 2 test command line) between the FLSCU-2 rack connector AA, pin 15A and the FQIC rack connector AB, pin 8K).
(f) Do a check (Ref. AWM 28-46-06) of the aircraft wiring (FLSCU-2 LS5 output line) between the FLSCU-2 rack connector AB, pin 5B and the FQIC rack connector AB, pin 11J, or the (aircraft wiring (FLSCU-2 LS1 output line) between the FLSCU-2 rack connector AB, pin 1A and the FQIC rack connector AB, pin 9K).
(g) Repair all the unserviceable wiring and connectors (Ref. ESPM 20-00-00).
(h) Connect the free connector 4040VC1(2)-A to the receptacle 4040VC1(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-GROUP B, L WING TK INR (14QT1) ( HARNESS-GROUP B, R WING TK INR (14QT2)) (Ref. AWM 28-46-05) and replace, if necessary (Ref. AMM TASK 28-42-43-000-007) and (Ref. AMM TASK 28-42-43-400-007).
「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1R EFF : 001-049, 051-099, 101-149, 151-199, ∞∞28-46-00∞∞∞∞∞∞∞∞∞∞Page 205
201-299, 401-499, Aug 01/05 CES
(c) If the harness is serviceable, replace the SENSOR-LOW LEVEL (1500KG), L WNG TK INR FWD CHANNEL B (15QJ1) (SENSOR-LOW LEVEL (1500KG), R WNG TK INR FWD CHANNEL B (15QJ2)) (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 4040VC1(2)-A (for the wing tank harness 63QT(64QT) (Ref. AMM TASK 28-42-43-000-008).
(4) Disconnect the free connector 4040VC1(2)-A from the receptacle 4040VC1(2).
(5) Do a resistance check of the sensor 15QJ1(2) at the tank wall connector 4040VC1(2) between pins <G and <W (Ref. AWM 28-46-05). 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.
「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1 EFF : ALL ∞∞28-46-00∞∞∞∞∞∞∞∞∞∞Page 206
Aug 01/05R
CES
R (6) Replace the FLSCU-2 (9QJ) (FLSCU-1 (7QJ)), (Ref. AMM TASK 28-46-34-000-001) and (Ref. AMM TASK 28-46-34-400-001).
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本文鏈接地址：A320 Trouble Shooting Manual 排故手冊(cè) FUEL 燃油4(41)
