(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 28-46-07) ( (Ref. AWM 28-46-08) 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 265
201-299, 401-499, Aug 01/05 CES
(c) If the harness is serviceable, replace the SENSOR-UNDERFULL, L WNG TK INR 1 CHANNEL B (24QJ1) (SENSOR-UNDERFULL, R WNG TK INR 1 CHANNEL B (24QJ2)) (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 24QJ1(2) at the tank wall connector 4040VC1(2) between pins <B and F (Ref. AWM 28-46-07) ((Ref. AWM 28-46-08)). 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 266
Aug 01/05R CES
(7) If the fault continues:
(a) 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).
(b) Disconnect the free connector 4040VC1(2)-A from the receptacle 4040VC1(2).
(c) Do a check (Ref. AWM 28-46-07), and (Ref. AWM 28-46-08) of the aircraft wiring (sensor input line - H) between the FLSCU-1(2) rack connector AB, pin 12D and the tank wall free connector 4040VC1(2)-A, pin <B.
(d) Do a check (Ref. AWM 28-46-07), and (Ref. AWM 28-46-08) of the aircraft wiring (sensor input line - L) between the FLSCU-1(2) rack connector AB, pin 12C and the tank wall free connector 4040VC1(2)-A, pin F.
(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 15E 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 13E.
(f) Do a check (Ref. AWM 28-46-10) of the aircraft wiring (FLSCU-1 LS13 output line) between the FLSCU-1 rack connector AB, pin 1D and the FQIC rack connector AB, pin 3G or the (aircraft wiring (FLSCU-2 LS13 output line) between the FLSCU-2 rack connector AB, pin 1D and the FQIC rack connector AB, pin 1F).
(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 (63QT) ( HARNESS - GROUP B, R WING TK (64QT)) (Ref. AWM 28-46-07) ((Ref. AWM 28-46-08) and replace, if necessary (Ref. AMM TASK 28-42-43-000-005) and (Ref. AMM TASK 28-42-43-400-005). 中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：A320 Trouble Shooting Manual 排故手册 FUEL 燃油4(65)
