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R R R R R  (4) If the message 284617 L(R) TEMP SENSOR 29QJ1(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 28-46/04). You can get more Trouble-shooting data from the CFDS(FUEL): - Input Parameters Page 3 (Ref. P. Block 301), used with the Fuel Temperature 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.

 「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 A202
 May 01/05 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 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 29QJ1(2) at the tank wall connector 4039VC1(2) between pins <H and <X (Ref. AWM 28-46-11) ( (Ref. AWM 28-46-12)). 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 A203
 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 28-46-11), and (Ref. AWM 28-46-12) of the aircraft wiring (sensor input line - H) between the FLSCU-1(2) rack connector AB, pin 8D and the tank wall free connector 4039VC1(2)-A, pin <H.

 (d) Do a check (Ref. AWM 28-46-11), and (Ref. AWM 28-46-12) of the aircraft wiring (sensor input line - L) between the FLSCU-1(2) rack connector AB, pin 8C and the tank wall free connector 4039VC1(2)-A, pin <X.

 (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, 7K 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, 9H).

 (f) Do a check (Ref. AWM 28-46-11) of the aircraft wiring (FLSCU-1 T1 output line) between the FLSCU-1 rack connector AB, pin 4C and the FQIC rack connector AB, 5J or ((Ref. AWM 28-46-12) of the aircraft wiring (FLSCU-2 T1 output line) between the FLSCU-2 rack connector AB, pin 4C and the FQIC rack connector AB, 15J).

 (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.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-CHAN A, L WING TK INR (13QT1) ( HARNESS-CHAN A, R WING TK INR (13QT2)) (Ref. AWM 28-46-11) ((Ref. AWM 28-46-12)) and replace, if necessary (Ref. AMM TASK 28-42-43-000-006) and (Ref. AMM TASK 28-42-43-400-006).
　
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