- HARNESS-CHAN A, L WING TK INR (13QT1)
- HARNESS-CHAN A, R WING TK INR (13QT2)
- PROBE-FUEL QTY NO 3, RIB 2-3 L WNG TK INR GROUP A (23QT1)
- PROBE-FUEL QTY NO 3, RIB 2-3 R WNG TK INR GROUP A (23QT2)
- HARNESS-LEFT WING TANK A (57QT)
- HARNESS-RIGHT WING TANK A (58QT)
- aircraft wiring
- shorting plug 4041VC-A(4042VC-A)
- fused connector 4041VC-A(4042VC-A)
2. Job Set-up Information
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A. Fixtures, Tools, Test and Support Equipment
-------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
No specific multimeter
B. Referenced Information
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ESPM 20-00-00 ESPM 20-52-21 ESPM 20-52-22 AMM 24-41-00-861-002 Energize the Aircraft Electrical Circuits from the
External Power AMM 24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied from the External Power AMM 28-10-00-910-001 Safety Procedures When You Do Work in a Fuel Tank
「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 259
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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 260
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AWM 28-42-07
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
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:
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本文鏈接地址：A320 Trouble Shooting Manual 排故手冊 FUEL 燃油2(133)
