R  AMM 28-42-00 P.Block 001 QUANTITY INDICATING ASM 28-42/05 ASM 28-42/06 AWM 28-42-04 AWM 28-42-05 AWM 28-42-08 AWM 28-42-09
 3. Fault Confirmation
__________________
 A. Table of the circuit breakers used in this procedure:
 -------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION -------------------------------------------------------------------------------49VU FUEL/FQI/CHAN/1 1QT A13 121VU FUEL/FQI/CHAN/2 2QT M27
 B. Test
 (1) To keep the number of computer replacements (with no fault found) to a minimum, do the power on BITE test of the FQIS as follows:
 (a) If the FQIS is not energized:
 1  Close the C/Bs 1QT and 2QT.
_
 2  Energize the Aircraft Electrical Circuits from the External
_ Power (Ref. AMM TASK 24-41-00-861-002).
 (b) If the FQIS is energized, reset the FQIC as follows:
 1  Open the C/Bs 1QT and 2QT.
_
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 2 Wait 10 seconds.
_
 3 Close the C/Bs 1QT and 2QT.
_ NOTE : For the FQIC to do a (new) power up BITE test, a power
____ supply interrupt (interval) of more than 10 seconds is necessary. This gives the current status of the FQIS components.
 (2) Do the EIS Start Procedure (ECAM only) (Ref. AMM TASK 31-60-00-860-001).

 (3) On the ECAM control panel, push (in) the FUEL P/BSW.

 (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 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 59QT1(2) or the L(R) QTY PROBE 59QT1(2)/WRG:

 (a) Is not shown, maintenance steps are not necessary.

 (b) Is shown, go to Para. 4.A.

 NOTE : You can get data from the:
____
 - Description and Operation (D and O) section of the R Aircraft Maintenance Manual (AMM), the Fuel Quantity R Indicating System (FQIS) (Ref. AMM 28-42-00 P.Block 001)
 - Trouble-shooting Manual (TSM) - Task Supporting Data (Ref. P. Block 301)
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 - Aircraft Schematic Manual (ASM) (Ref. ASM 28-42/05) ( (Ref. ASM 28-42/06)).
 NOTE : You can get more Trouble-shooting data from the
____
 CFDS(FUEL):

 - Input Parameters Page 2 (Ref. AMM TASK 28-42-00-740-003) R - FQIC Trouble Shooting Data (Ref. AMM TASK 28-42-00-740-R 009).
 NOTE : OPTIONAL TESTING:
____ If a DC Capacitance Fuel System Tester is available, measurements can be taken before a decision is made to enter 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).
 4. Fault Isolation
_______________
 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 59QT1(2) or L(R) QTY PROBE 59QT1(2)/WRG is not shown: