-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
AMM 28-42-15-400-005
AMM 28-42-34-000-001
AMM 28-42-34-400-001
AMM 28-42-43-000-005
AMM 28-42-43-000-008
AMM 28-42-43-400-005
AMM 28-42-43-400-008
AMM 31-32-00-860-001
AMM 31-60-00-860-001
AMM 31-60-00-860-002
Installation of the Fuel-Quantity-Probe (21QT1/2,23QT1/2,25QT1/2,26QT1/2,27QT 1/2,28QT1/2/,29QT1/2,30QT1/2,34QT1/2,54QT1/2,56QT1/2, 59QT1/2,60QT1/2,61QT1/2)Removal of the Fuel Quantity-Indicating Computer (FQIC) (3QT)Installation of the Fuel Quantity-Indicating Computer (FQIC) (3QT)Removal of the Wing Tank Harness 57QT(58QT), 63QT(64QT)Removal of the Wing Tank Fuel Quantity Indicating Probe Fused/Shorting Plug ConnectorsInstallation of the Wing Tank Harness 57QT(58QT), 63QT(64QT)Installation of the Wing Tank Fuel Quantity Indicating Probe Fused/Shorting Plug ConnectorsProcedure to Get Access to the SYSTEM REPORT/TEST Menu PageEIS Start ProcedureEIS Stop Procedure
R AMM 28-42-00 P.Block 001 QUANTITY INDICATING
ASM 28-42/05
ASM 28-42/06
ASM 28-42/07
ASM 28-42/08
AWM 28-42-04
AWM 28-42-05
AWM 28-42-10
AWM 28-42-11
AWM 28-42-12
AWM 28-42-13
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
「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 : 301-399, ∞∞28-42-00∞∞∞∞∞∞∞∞∞∞Page C212
Aug 01/05 CES
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 L(R) wing tank must contain 250kg (550lb) of fuel to fully
____ test the temperature elements of the fuel probe. This is a software requirement related to the temperature measurement but not the fuel gaging.
(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.
(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).
「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 : 301-399, ∞∞28-42-00∞∞∞∞∞∞∞∞∞∞Page C213
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