NOTE : The sensor status (wet or dry) and fuel/air temperature will
____
have an effect on the resistance value.
(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).
「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 230
Aug 01/05 CES
R (7) If the fault continues:
R (a) Get access to the tank wall connector 4040VC1(2)-A (for the wing R tank harness 63QT(64QT) (Ref. AMM TASK 28-42-43-000-008).
R (b) Disconnect the free connector 4040VC1(2)-A from the receptacle R 4040VC1(2).
R (c) Do a check (Ref. AWM 28-46-05) of the aircraft wiring (sensor input line - H) between the FLSCU-2(1) rack connector AB, pin 9A and the tank wall free connector 4040VC1(2)-A, pin <U.
R (d) Do a check (Ref. AWM 28-46-05) of the aircraft wiring (sensor input line - L) between the FLSCU-2(1) rack connector AB, pin 9B and the tank wall free connector 4040VC1(2)-A, pin <T.
R (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 13F, or the (aircraft wiring (FLSCU-1 BITE 3 test command line) between the FLSCU-1 rack connector AA, pin 15C and the FQIC rack connector AB, pin 15F).
R (f) Do a check (Ref. AWM 28-46-06) of the aircraft wiring (FLSCU-2 LS2 output line) between the FLSCU-2 rack connector AB, pin 5A and the FQIC rack connector AC, pin 1B, or the (aircraft wiring (FLSCU-1 LS2 output line) between the FLSCU-1 rack connector AB, pin 5A and the FQIC rack connector AC, pin 4C).
R (g) Repair all the unserviceable wiring and connectors (Ref. ESPM 20-R 00-00).
R (h) Connect the free connector 4040VC1(2)-A to the receptacle R 4040VC1(2).
R (i) Do the test in Para. 3.A.
R (8) If the fault continues or if there is no continuity in Step (5):
R (a) Drain, open and vent the applicable wing tank (Ref. AMM TASK 28-R 10-00-910-001) and (Ref. AMM TASK 28-10-00-910-002).
R (b) Do a wiring check of the HARNESS-LEFT WING TANK B (63QT) ( R HARNESS-RIGHT WING TANK B (64QT)) (Ref. AWM 28-46-05) and R replace, if necessary (Ref. AMM TASK 28-42-43-000-005) and R R (Ref. AMM TASK 28-42-43-400-005).
R (c) If the harness is serviceable, replace the SENSOR-LOW LVL R (750KG), L WING TANK CHANNEL A (39QJ1) (SENSOR-LOW LVL (750KG), R R WING TANK CHANNEL A (39QJ2)) (Ref. AMM TASK 28-46-15-000-001) and R (Ref. AMM TASK 28-46-15-400-009).
「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 : 301-399, ∞∞28-46-00∞∞∞∞∞∞∞∞∞∞Page 231
May 01/05 CES
R
「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 232
May 01/05 CES
**ON A/C ALL
TASK 28-46-00-810-805
Center Tank High Level Sensor 20QJ
WARNING : OBEY THE FUEL SAFETY PROCEDURES.
_______
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.
1. Possible Causes
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- FLSCU-1 (7QJ)
- HARNESS-CHAN A, CTR TK (17QT)
- SENSOR-HIGH LEVEL, CENTER TANK (20QJ)
- aircraft wiring
- fused adaptor at 7509VC
2. Job Set-up Information
______________________
A. Fixtures, Tools, Test and Support Equipment
-------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
No specific multimeter
B. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
28-46-00-810-818
R ESPM 20-00-00
AMM 28-10-00-910-001
R AMM 28-10-00-910-002
AMM 28-42-00-740-003
AMM 28-42-44-000-001
AMM 28-42-44-400-001
AMM 28-46-00-740-001
AMM 28-46-15-000-004
AMM 28-46-15-400-012
AMM 28-46-34-000-001
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本文鏈接地址：A320 Trouble Shooting Manual 排故手冊 FUEL 燃油4(51)
