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AMM 31-60-00-860-001 EIS Start Procedure
AMM 31-60-00-860-002 EIS Stop Procedure
AMM 32-12-00-010-001 Open the Main Gear Doors for Access
AMM 32-12-00-410-001 Close the Main Gear Doors after Access
AWM 28-42-14
AWM 28-42-16
3. Fault Confirmation
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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:
NOTE : The center tank must contain 1500kg (3300lb) of fuel to fully
____
test the ultracomp 50QT.
(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.
_
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.
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(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 C ULTRACOMP 50QT or C ULTRACOMP 50QT/WRG:
(a) Is not shown: 1 First time, maintenance steps are not necessary.
_
2 Second time (intermittent/spurious fault), go to step (14).
_
(b) Is shown, continue as follows:
R (9) Set the MCDU to FQIS INPUT PARAMETERS, Page 1 (Ref. AMM TASK 28-42-R 00-740-003).
(10) Examine the C ULTRACOMP 50QT values:
- permittivity UCMP K (1.893 to 2.361)
- temperature UCMP T (-66.5 to 105.0)
- velocity UCMP V (990.0 to 1665.0).
NOTE : The fuel temperature shown as UCMP T should bear a close
____ relationship to the fuel temperatures shown as TEMP which are derived from the wing tank number 2 probes 54QT1(2). Both
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temperatures have a relationship to the aircrafts recent
transit/local air temperature, and conditions.
(11) Set the MCDU to INPUT PARAMETERS, Page 2 (FQIS PROBE CAPACITANCES).
(12) Examine the C ULTRACOMP 50QT capacitance value (54.45 to 132.45).
(13) If in steps (10) and (12) the values shown are not in the correct range (as shown by the figures in brackets) or not shown, go to Para.
4.A.
(14) If the fault is not shown on the FQIS STATUS (intermittent/spurious), set the MCDU to one of the applicable FUEL options as follows:
- the LAST LEG REPORT
- the PREVIOUS LEGS REPORT.
(a) Press (in) the line function key to the right of the failed LRU.
NOTE : Hexadecimal coded Trouble-shooting Data related to the
____
R original intermittent/spurious failure report is now
R shown. This data can be decoded (Ref. AMM TASK 28-42-00-
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