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FQIS - ACT 1 Pin Programming Fault

TASK 28-42-00-810-857-A
FQIS - ACT 1 Pin Programming Fault

WARNING: OBEY THE FUEL SAFETY PROCEDURES.
1. Possible Causes
  • ACT wiring
  • aircraft wiring
  • FQIC [3QT]
2. Job Set-up Information
 A. Referenced Information
REFERENCE
DESIGNATION
AMM 24-41-00-861-002
Energize the Aircraft Electrical Circuits from the External Power
AMM 28-11-27-000-001
Removal of the Additional Center Tank (ACT)
AMM 28-42-00-740-003
Interrogation of the FQIS Input Parameters Pages
ASM 284209
AMM 28-42-34-000-001
Removal of the Fuel Quantity-Indicating Computer (FQIC)
AMM 28-42-34-400-001
Installation of the Fuel Quantity-Indicating Computer (FQIC)
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
3. Fault Confirmation
Subtask 28-42-00-865-091-A ** ON A/C NOT FOR ALL
A. Table of the circuit breakers used in this procedure:
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
49VUFUEL/FQI/CHAN/11QTA13
121VUFUEL/FQI/CHAN/22QTM27
Subtask 28-42-00-710-106-A ** ON A/C NOT FOR ALL
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 AMM 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) AMM 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 AMM 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 WRG ACT1 PPROG DISAGREE:
     (a) Is not shown, maintenance steps are not necessary.
     (b) Is shown, go to Para. 4.A.
NOTE: You can get data from the:
  • Description and Operation (D and O) section of the Aircraft Maintenance Manual (AMM), Chap. 28-42-00, the Fuel Quantity Indicating System (FQIS)
  • Trouble-shooting Manual (TSM) - Task Supporting Data (Ref. P. Block 301)
  • Aircraft Schematic Manual (ASM) ASM 284209.
NOTE: You can get more Trouble-shooting data from the CFDS(FUEL):
  • Input Parameters Page 3 (ACT PROBE CAPACITANCES) and Page 4 (FQIS DISCRETE INPUTS) AMM 28-42-00-740-003
  • FQIC Trouble Shooting Data (Ref. P. Block 301).
4. Fault Isolation
Subtask 28-42-00-810-106-A ** ON A/C NOT FOR ALL
A. Procedure
   (1) Do the Interrogation of the Input Parameters Pages AMM 28-42-00-740-003.
   (2) Set the MCDU to INPUT PARAMETERS, Page 4.
   (3) Monitor the bit location A1:
  • make sure that it shows a 1.
   (4) Monitor the bit location E1:
  • make sure that it shows a 1.

Table of the ACT 1/FQIC pin programming connections
Bit position
Signal discription
FQIC Pin allocation
Signal level
Aircraft to ACT connector and service
A1
ACT1 Installed
AC, pin 6D
Ground
7618VC1, FQI probe No. 2
E1
ACT1 Installed
AC, pin 5F
Ground
7619VC1, valve actuators
   (5) If in step (3) and (4) the two bits are set to a 1 (correct), go to step (8).
   (6) If in step (3) bit A1 shows a 0 (not correct):
     (a) Disconnect the aircraft to ACT connector 7618VC1-A AMM 28-11-27-000-001.
     (b) Do a check of the ACT wiring ASM 284209 between:
  • the connector 7618VC1-A, pins 1 and 2.
     (c) Do a check of the aircraft wiring ASM 284209 between:
  • the connector 7618VC1, pin 2 and the ground point DC2
  • the connector 7618VC1, pin 1 and the FQIC rack connector AC, pin 6D.
     (d) Repair all the unserviceable wiring and connectors.
     (e) Reconnect the connector 7618VC1-A.
     (f) Do the:
       1 Steps (1) thru (3).
       2 Test given in Para. 3.B.
   (7) If in step (4) bit E1 shows a 0 (not correct):
     (a) Disconnect the aircraft to ACT connector 7619VC1-A AMM 28-11-27-000-001.
     (b) Do a check of the ACT wiring ASM 284209 between:
  • the connector 7619VC1-A, pins 1 and 2.
     (c) Do a check of the aircraft wiring ASM 284209 between:
  • the connector 7619VC1, pin 1 and the ground point DC1
  • the connector 7619VC1, pin 2 and the FQIC rack connector AC, pin 5F.
     (d) Repair all the unserviceable wiring and connectors.
     (e) Reconnect the connector 7619VC1-A.
     (f) Do the:
       1 Steps (1) (2) and (4).
       2 Test given in Para. 3.B.
   (8) If the fault continues, replace the FQIC [3QT] AMM 28-42-34-000-001 and AMM 28-42-34-400-001.
NOTE: Make sure that the FQIC to be installed is of the same type as that removed (Simmons Precision - Sextant Avionique).
[Rev.8 from Aug 2018] 2026.04.04 04:29:08 UTC
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