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REFERENCE DESIGNATION -------------------------------------------------------------------------------
AMM 28-10-00-910-002 Access to the Fuel Tanks and the Work Areas
AMM 28-42-00-740-003 Interrogation of the FQIS Input Parameters Pages
R AMM 28-42-00-740-007 Interrogation of the (SMITHS INDUSTRIES) FQIS Trouble
R Shooting Data
R AMM 28-42-00-740-009 Interrogation of the (SIMMONDS/GOODRICH) FQIS Trouble
R Shooting Data AMM 28-42-15-000-001 Removal of the Wing Tank Fuel-Quantity-Probe (21QT1/2,22QT1/2,23QT1/2,24QT1/2,2 5QT1/2,26QT1/2,27QT1/2,28QT1/2,29QT1/2,30QT1/2,31QT1/ 2,32QT1/2,33QT1/2,34QT1/2) AMM 28-42-15-000-005 Removal of the Wing Tank Fuel-Quantity Probe (21QT1/2,23QT1/2,25QT1/2,26QT1/2,2 7QT1/2,28QT1/2,29QT1/2,30QT1/2,34QT1/2,54QT1/2,56QT1/ 2,59QT1/2,60QT1/2,61QT1/2) AMM 28-42-15-400-001 Installation of the Fuel-Quantity-Probe (21QT1/2,22QT1/2,23QT1/2,24QT1/2,25QT1/ 2,26QT1/2,27QT1/2,28QT1/2,29QT1/2,30QT1/2,31QT1/2,32Q T1/2,33QT1/2,34QT1/2) AMM 28-42-15-400-005 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) AMM 28-42-34-000-001 Removal of the Fuel Quantity-Indicating Computer (FQIC) (3QT) AMM 28-42-34-400-001 Installation of the Fuel Quantity-Indicating Computer (FQIC) (3QT) AMM 28-42-43-000-005 Removal of the Wing Tank Harness 57QT(58QT), 63QT(64QT) AMM 28-42-43-000-006 Removal of the Wing-Tank Inner-Cell Group A Harness 13QT1(13QT2) AMM 28-42-43-000-008 Removal of the Wing Tank Fuel Quantity Indicating Probe Fused/Shorting Plug Connectors AMM 28-42-43-400-005 Installation of the Wing Tank Harness 57QT(58QT), 63QT(64QT) AMM 28-42-43-400-006 Installation of the Wing-Tank Inner-Cell Group A Harness 13QT1(13QT2) AMM 28-42-43-400-008 Installation of the Wing Tank Fuel Quantity Indicating Probe Fused/Shorting Plug Connectors AMM 31-32-00-860-001 Procedure to Get Access to the SYSTEM REPORT/TEST Menu Page AMM 31-60-00-860-001 EIS Start Procedure AMM 31-60-00-860-002 EIS Stop Procedure
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 28-42-06
「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 ∞∞28-42-00∞∞∞∞∞∞∞∞∞∞Page 284
Aug 01/05 CES
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
AWM 28-42-07
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
R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 401-499,
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.
_
2 Wait 5 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 5 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).
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