(4) Make sure that the FUEL page shows on the ECAM lower display unit.
(5) Wait 60 seconds.
(6) Continue as follows: NOTE : The FUEL page FQIs will show XXs in amber color, for 35
____ seconds, during the FQIC power up BITE test. A FQIS sensor fault must be sensed by the FQIC for 60 seconds before the applicable LRU identification is transmitted to the CFDS as unserviceable. The fault message is shown on the MCDU
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when set to SYSTEM REPORT/TEST (FUEL) and the FQIS STATUS page.
(a) Do the procedure to get access to the SYSTEM REPORT/TEST menu page (Ref. AMM TASK 31-32-00-860-001).
(b) When the SYSTEM REPORT/TEST menu page comes into view, push the line key adjacent to FUEL.
(c) When the FUEL menu page comes into view, push the line key adjacent to FQIS STATUS.
(7) Examine the FQIS STATUS Page.
(8) If the message L(R) QTY PROBE 28QT1(2) or the L(R) QTY PROBE 28QT1(2)/WRG:
(a) Is not shown, maintenance steps are not necessary.
(b) Is shown, go to Para. 4.A.
R R NOTE : You can get data from the:____ - Description and Operation (D and O) section of the Aircraft Maintenance Manual (AMM), the Fuel Quantity Indicating System (FQIS) (Ref. AMM 28-42-00 P.Block 001) - Trouble-shooting Manual (TSM) - Task Supporting Data (Ref. P. Block 301) - Aircraft Schematic Manual (ASM) (Ref. ASM 28-42/07) ( (Ref. ASM 28-42/08)).
R R NOTE : You can get more Trouble-shooting data from the____ CFDS(FUEL): - Input Parameters Page 2 (Ref. AMM TASK 28-42-00-740-003) - FQIC Trouble Shooting Data (Ref. AMM TASK 28-42-00-740-009).
NOTE : OPTIONAL TESTING:____ If a DC Capacitance Fuel System Tester is available, measurements can be taken before a decision is made to go into or close up a fuel tank. The Tester can be connected to the FQIC rack connector or the related tank wall connector. (Ref. P. Block 301 for the Tank Units DC Capacitance Values).
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**ON A/C ALL
4. Fault Isolation
_______________
R **ON A/C 001-049, 051-061, 101-105, 201-203,
A. Procedure
NOTE : Where applicable, to show the difference between the left and
____ right wing installations, the FINs given in this procedure are written as follows:
- the left wing, no parenthesis, FIN
- the right wing, in parenthesis, (FIN).
(1) Temporarily replace the FQIC 3QT with a serviceable item (Ref. AMM TASK 28-42-34-000-001) and (Ref. AMM TASK 28-42-34-400-001).
NOTE : The step (1) has been included because it is important to make
____ sure that the FQIC is serviceable before you start more steps.
(2) If the message L(R) QTY PROBE 28QT1(2) is not shown:
- complete the installation of the FQIC (3QT) (Ref. AMM TASK 28-42-34-000-001) and (Ref. AMM TASK 28-42-34-400-001).
(3) If the message L(R) QTY PROBE 28QT1(2) is shown:
(a) Remove the temporary installed serviceable FQIC 3QT (Ref. AMM TASK 28-42-34-000-001) and return it to stores.
(b) Get access to the tank wall connector 4040VC1(2)-A and the shorting plug 4043VC-A(4044VC-A) (Ref. AMM TASK 28-42-43-000-008).
1 Disconnect the:
_
- tank wall connector 4040VC1(2)-A
- shorting plug 4043VC-A(4044VC-A).
(c) Do a visual inspection and electrical tests of the aircraft wiring (Ref. AWM 28-42-11) ((Ref. AWM 28-42-10)) and (Ref. AWM 28-42-13) ((Ref. AWM 28-42-12)) between the FQIC rack connector 3QT-A and the tank wall connector 4040VC1-A(4040VC2-A) as follows:
NOTE : Each capacitive fuel probe is supplied with an alternating
____ current drive, of 30 volts at 30 kilo-hertz, from the FQIC. The fuel probes in a tank group (harness) share the drive and drive return (two aircraft wires) between the FQIC rack connector and the connector 4043VC-A (4044VC-A).
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The connector is adjacent to and below its related tank
wall connector.
In the connector:
- the drive wire divides to supply each of the related fuel probes, in parallel 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2(165)
