- HARNESS-LEFT WING TANK A (57QT)

 - HARNESS-RIGHT WING TANK A (58QT)

 - PROBE-FQI NO 13, RIB 18-19 L WNG TK GROUP A (61QT1)

 - PROBE-FQI NO 13, RIB 18-19 R WNG TK GROUP A (61QT2)

 - aircraft wiring

 - shorting plug 4041VC-A(4042VC-A)

 2. Job Set-up Information
______________________
 A. Referenced Information
 -------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
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 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 28-42-00-740-009 Interrogation of the (SIMMONDS/GOODRICH) FQIS Trouble R Shooting Data
 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 28-42-15-400-005  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)
 「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 C238
 Aug 01/05 CES -------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------

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 28-42-43-000-008 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 28-42-43-400-008 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 28-42-08 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.
_
 「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 C239
 Aug 01/05 CES

 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.
　
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