**ON A/C 301-399,
A. Test
(1) Do the BITE test of the FLSS (Ref. AMM TASK 28-46-00-740-001).
(2) Examine the FLSS STATUS page on the MCDU.
(3) If the page shows messages for one or more of the other sensors and/or the FLSCU-1(2), do (Ref. TASK 28-46-00-810-818).
(4) If the message 284615 L(R) FULL SENSOR 27QJ1(2):
- is shown, do Para. 4.A.
- is not shown, no work steps are necessary.
NOTE : You can get more data from the:
____
- Aircraft Maintenance Manual (AMM) Chap. 28-46-00, the Fuel Level Sensing System, Description and Operation (D and O)
- Trouble Shooting Manual (TSM) - Task Supporting Data (Ref.
P. Block 301)
- Aircraft Schematic Manual (ASM) (Ref. ASM 28-46/03). You can get more Trouble-shooting data from the CFDS(FUEL):
- Input Parameters Page 3 (Ref. P. Block 301), used with the Fuel Level Sensors Operating (Changeover) Values (Ref. P. Block 301)
- Trouble-shooting Data (Ref. P. Block 301).
NOTE : OPTIONAL TESTING:
____ Where a PSDA321-1 Test Set is available, a check can be made before a decision is made to go into or close up a fuel tank. The Test Set enables a GO/NOGO check to be made of the tank mounted components and wiring from the tank wall connectors.
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Aug 01/05R
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 4040VC1(2)-A (for the wing tank harness 14QT1(2)) (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 27QJ1(2) at the tank wall connector 4040VC1(2) between pins <E 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).
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Aug 01/05 CES
(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 28-46-07), and (Ref. AWM 28-46-08) of the aircraft wiring (sensor input line - H) between the FLSCU-1(2) rack connector AB, pin 13D and the tank wall free connector 4040VC1(2)-A, pin <E.
(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 13C 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 7K or ((Ref. AWM 28-46-12) of the aircraft wiring (FLSCU-2 BITE 4 test command line) between the FLSCU-2 rackconn ector AA, pin 15D and the FQIC rack connector AB, pin 9H).
(f) Do a check (Ref. AWM 28-46-10) of the aircraft wiring (FLSCU-1 LS12 output line) between the FLSCU-1 rack connector AB, pin 3C and the FQIC rack connector AB, pin 4H or the (aircraft wiring (FLSCU-2 LS12 output line) between the FLSCU-2 rack connector AB, pin 3C and the FQIC rack connector AB, pin 13H). 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(73)
