W DOC AIRBUS | TSM A320F

Fuel - ACT Transfer System Flag/Symbol Failure

TASK 28-28-00-810-806-A
Fuel - ACT Transfer System Flag/Symbol Failure

WARNING: OBEY THE FUEL SAFETY PROCEDURES.
1. Possible Causes
  • aircraft wiring
  • ACTUATOR-FUEL TRANSFER VALVE, ACT [6QH]
  • ACTUATOR-FUEL INLET VALVE, ACT1 [5QH1]
  • ACTUATOR-FUEL INLET VALVE, ACT2 [5QH2]
2. Job Set-up Information
 A. Fixtures, Tools, Test and Support Equipment
REFERENCE
QTY
DESIGNATION
No specific
AR
MULTIMETER - STANDARD
 B. Referenced Information
REFERENCE
DESIGNATION
TSM TASK 28-28-00-810-801-A
Fuel Pumps - ACT Manual Transfer Pump 1QH System Malfunction
TSM TASK 28-28-00-810-801-A-01
 Fuel Pumps - ACT Manual Transfer Pump 1QH System Malfunction (802VU ACT Relay Testbox)
TSM TASK 28-28-00-810-802-A
Fuel - ACT 1 Manual Transfer Failure (On The Ground)
TSM TASK 28-28-00-810-802-A-01
 Fuel - ACT 1 Manual Transfer Failure (On The Ground) (802VU ACT Relay Testbox)
TSM TASK 28-28-00-810-804-A
Fuel - ACT Automatic Transfer Failure
TSM TASK 28-28-00-810-804-A-01
Fuel - ACT Automatic Transfer Failure (802VU ACT Relay Testbox)
AMM 28-28-00-710-001
Operational Check of the ACT Manual Transfer System
AMM 28-28-00-710-004
Operational Test of the ACT Automatic Transfer System
ASM 282801
AWM 282802
ASM 282803
AMM 28-28-53-000-001
Removal of the ACT Transfer-Valve Actuator
AMM 28-28-53-400-001
Installation of the ACT Transfer-Valve Actuator
AMM 28-28-54-000-001
Removal of the ACT Fuel Inlet Valve Actuator (5QH)
AMM 28-28-54-400-001
Installation of the ACT Fuel Inlet Valve Actuator (5QH)
AMM 31-36-00-740-008
Access to the Parameter Call-Up Menus
3. Fault Confirmation
Subtask 28-28-00-710-055-A ** ON A/C NOT FOR ALL
A. Test
   (1) Do the Operational Tests of:
     (a) The ACT Manual Transfer System AMM 28-28-00-710-001.
     (b) The ACT Automatic Transfer System AMM 28-28-00-710-004.
   (2) If the ACT transfer system and flag/symbol operate as specified in the tests:
  • no maintenance steps are necessary.
   (3) If the ACT transfer system does not operate as specified in the tests go to the applicable task that follows:
   (4) If the ACT fuel is transferred to the center tank but the ACT flag/symbol fails to operate as specified in the tests:
  • go to Para. 4.
4. Fault Isolation
Subtask 28-28-00-810-055-B ** ON A/C NOT FOR ALL
A. Procedure
   (1) ACT Transfer System Flag/symbol Trouble-shooting For Discrete Inputs To The SDACs
NOTE: The seven discrete input signals required for a two ACT system are shown in the table that follows.
The end column gives the step number for trouble-shooting that signal.

It is not necessary to carry out this trouble-shooting procedure in the order shown in the table.
The order in which the steps are done is best decided locally depending on access availability.
SDAC DISCRETE INPUT SIGNAL DESCRIPTION (FOR BIT STATE = 1)
RELATED SDAC INPUT SIGNAL STATE
TO SDAC OUTPUT BUS EQ/LBL/SDI/BIT
FOR TROUBLE- SHOOTING GO TO THE STEP SHOWN
ACT XFR PUMP P/B ON
28VDC
29/002/00/26
2
ACT XFR PUMP LO PRESS
EARTH
29/002/00/27
3
ACT XFR VALVE OPEN
EARTH
29/002/00/28
4
ACT 1 LOW LEVEL
EARTH
29/002/11/19
5
ACT 1 INLET VALVE NOT OPEN
OPEN CIRCUIT
29/004/01/25
6
ACT 2 LOW LEVEL
EARTH
29/004/00/19
7
ACT 2 INLET VALVE NOT OPEN
OPEN CIRCUIT
29/004/00/25
8
NOTE: OPTIONAL TESTING

With Aircraft Integrated Data System (AIDS)

If the AIDS option is installed in the aircraft the discrete signals can be checked with the minimum of disturbance to the systems by observing the digital data (EQ/LBL/SDI/BIT) shown in column 3 of the table given before.
For access to the AIDS parameter call-up menus AMM 31-36-00-740-008.
For SYS enter 1 or 2 which means system 1 or system 2 respectively.

With an ARINC Reader

Alternatively if an ARINC Reader (high speed bus) is available the SDACs acquisition of the discrete signals can be checked with the minimum of disturbance to the systems by observing the digital data (LBL/SDI/BIT) shown in column 3 of the table given before.
To check the bus outputs connect the ARINC Reader as follows:
  • SDAC-1 (1WV1) - test connector 199VC, located at 187VU127
  • SDAC-2 (1WV2) - test connector 198VC, located at 188VU128.
   (2) Do the Act Transfer Pump Pushbutton On/Off Discrete Signal Trouble-shooting as follows:
     (a) Do a check of the aircraft wiring AWM 282802 between the P/BSW-FUEL/ACT/AUTO (24QH) terminal C1, and the SDAC-1(2) 1WV1(1WV2) connector AD, pin 7E.
     (b) Repair all the unserviceable wiring and connectors.
     (c) Do the test given in Para. 3.A.
   (3) Do the Act Pump Low Pressure Discrete Signal Trouble-shooting as follows:
     (a) Do a check of the aircraft wiring AWM 282802 between the RELAY-PANEL (802VU) free connector 4065VC-A, pin Z and the SDAC-1(2) 1WV1(1WV2) connector AD, pin 8E.
     (b) Repair all the unserviceable wiring and connectors.
     (c) Do the test given in Para. 3.A.
   (4) Do the Act Transfer Valve Open/Close Discrete Signal Trouble-shooting as follows:
     (a) Make sure the P/BSW-FUEL/ACT/AUTO (24QH) is released (out) (ACT manual transfer set to off).
     (b) Make sure the ACTUATOR-FUEL XFR VALVE, ACT (6QH) see/feel indicator is in the closed position.
     (c) Disconnect the free connector 6QH-A from the ACTUATOR-FUEL XFR VALVE, ACT (6QH) receptacle.
     (d) With a MULTIMETER - STANDARD do a continuity check at the receptacle 6QH-A between the pins D and E ASM 282803.
     (e) Make sure the multimeter shows an open circuit.
     (f) Connect the free connector 6QH-A to the ACTUATOR-FUEL XFR VALVE, ACT (6QH) receptacle.
     (g) Push (in) the P/BSW-FUEL/ACT/AUTO (24QH) (ACT manual transfer set to on).
     (h) Make sure the ACTUATOR-FUEL XFR VALVE, ACT (6QH) see/feel indicator is in the open position.
     (i) Disconnect the free connector 6QH-A from the ACTUATOR-FUEL XFR VALVE, ACT (6QH) receptacle.
     (j) With a multimeter do a continuity check at the receptacle 6QH-A between the pins D and E ASM 282803.
     (k) Make sure the multimeter shows a low resistance.
     (l) If the actuator position micro-switch continuity checks are not as specified in steps (e) and (k):
     (m) Do a check of the aircraft wiring ASM 282803 between the actuator fuel transfer valve free connector 6QH-A, pin D and the SDAC-1(2) 1WV1(1WV2) connector AD, pin 7F.
     (n) Repair all the unserviceable wiring and connectors.
     (o) Do the test given in Para. 3.A.
   (5) Do the Act 1 Low Level Discrete Signal Trouble-shooting as follows:
     (a) Disconnect the free connector 4065VC-A from the RELAY-PANEL (802VU).
     (b) Do a check of the aircraft wiring ASM 282803 between:
  • the FLSCU-3 (47QJ) connector AA, pin 9B and the SDAC-1(2) 1WV1(1WV2) connector AA, pin 6G
  • the RELAY-PANEL (802VU) free connector 4065VC-A, pin <A and the SDAC-1(2) 1WV1(1WV2) connector AA, pin 6G.
     (c) Repair all the unserviceable wiring and connectors.
     (d) Do the test given in Para. 3.A.
   (6) Do the Act 1 Inlet Valve Open/Close Discrete Signal Trouble-shooting as follows:
     (a) At the REFUEL PANEL (800VU):
  • make sure the SW-MODE SELECT/REFUEL/OFF/DEFUEL/XFR (3QU) is set to OFF
  • make sure all the main tank REFUEL VALVE switches are at NORMAL.
     (b) At the ACT REFUEL PANEL (801VU):
  • make sure the ACT REFUEL VALVE switch is at NORMAL.
     (c) Make sure the P/BSW-FUEL/ACT/AUTO (24QH) is released (out) (ACT manual transfer set to off).
     (d) Open, safety and tag the C/B-ACT2/XFR VLV/AUTO CTL (10QH) located at 121VU, location 28P.
NOTE: This is to make sure that only the ACT 1, inlet valve (5QH1) can open during the operations in this step and the ACT 2, inlet valve (5QH2) is kept closed.
     (e) Make sure the ACTUATOR-FUEL INLET VALVE, ACT 1 (5QH1) see/feel indicator is in the closed position.
     (f) Disconnect the free connector 5QH1-A from the ACTUATOR-FUEL INLET VALVE, ACT 1 (5QH1) receptacle.
     (g) With a multimeter do a continuity check at the receptacle 5QH1-A between the pins A and C ASM 282801.
     (h) Make sure the multimeter shows an open circuit.
     (i) Connect the free connector 5QH1-A to the ACTUATOR-FUEL INLET VALVE, ACT 1 (5QH1) receptacle.
     (j) Push (in) the P/BSW-FUEL/ACT/AUTO (24QH) (ACT manual transfer set to on).
     (k) Make sure the ACTUATOR-FUEL INLET VALVE, ACT 1 (5QH1) see/feel indicator is in the open position.
     (l) Disconnect the free connector 5QH1-A from the ACTUATOR-FUEL INLET VALVE, ACT 1 (5QH1) receptacle.
     (m) With a multimeter do a continuity check at the receptacle 5QH1-A between the pins A and C ASM 282801.
     (n) Make sure the multimeter shows a low resistance.
     (o) If the actuator position micro-switch continuity checks are not as specified in Step (h) and (n):
NOTE: The inlet valve actuator position mirco-switch can be checked remotely at the aircraft to ACT 1 free connector 7619VC1-A, between the pins 15 and 16.
     (p) Do a check of the aircraft wiring ASM 282801 between:
  • the ACT 1 actuator fuel inlet valve free connector 5QH1-A, pin C and the aircraft to ACT 1 free connector 7619VC1-A, pin 16
  • the aircraft to ACT 1 connector 7619VC1, pin 16 and the SDAC-1(2) 1WV1(1WV2) connector AB, pin 1B.
     (q) Repair all the unserviceable wiring and connectors.
     (r) Remove the tag, and close the C/B-ACT2/XFR VLV/AUTO CTL (10QH) located at 121VU, location 28P.
     (s) Do the test given in Para. 3.A.
   (7) Do the Act 2 Low Level Discrete Signal Trouble-shooting as follows:
     (a) Disconnect the free connector 4065VC-A from the RELAY-PANEL (802VU).
     (b) Do a check of the aircraft wiring ASM 282803 between:
  • the FLSCU-3 (47QJ) connector AA, pin 4C and the SDAC-1(2) 1WV1(1WV2) connector AA, pin 14E
  • the RELAY-PANEL (802VU) free connector 4065VC-A, pin D and the SDAC-1(2) 1WV1(1WV2) connector AA, pin 14E.
     (c) Repair all the unserviceable wiring and connectors.
     (d) Do the test given in Para. 3.A.
   (8) Do the Act 2 Inlet Valve Open/Close Discrete Signal Trouble-shooting as follows:
     (a) At the REFUEL PANEL (800VU):
  • make sure the SW-MODE SELECT/REFUEL/OFF/DEFUEL/XFR (3QU) is set to OFF
  • make sure all the main tank REFUEL VALVE switches are at NORMAL.
     (b) At the ACT REFUEL PANEL (801VU):
  • make sure the ACT REFUEL VALVE switch is at NORMAL.
     (c) Make sure the P/BSW-FUEL/ACT/AUTO (24QH) is released (out) (ACT manual transfer set to off).
     (d) Make sure the ACTUATOR-FUEL INLET VALVE, ACT 2 (5QH2) see/feel indicator is in the closed position.
     (e) Disconnect the free connector 5QH2-A from the ACTUATOR-FUEL INLET VALVE, ACT 2 (5QH2) receptacle.
     (f) With a multimeter do a continuity check at the receptacle 5QH2-A between the pins A and C ASM 282801.
     (g) Make sure the multimeter shows an open circuit.
     (h) Connect the free connector 5QH2-A to the ACTUATOR-FUEL INLET VALVE, ACT 2 (5QH2) receptacle.
     (i) Push (in) the P/BSW-FUEL/ACT/AUTO (24QH) (ACT manual transfer set to on).
     (j) Make sure the ACTUATOR-FUEL INLET VALVE, ACT 2 (5QH1) see/feel indicator is in the open position.
     (k) Disconnect the free connector 5QH2-A from the ACTUATOR-FUEL INLET VALVE, ACT 2 (5QH2) receptacle.
     (l) With a multimeter do a continuity check at the receptacle 5QH2-A between the pins A and C ASM 282801.
     (m) Make sure the multimeter shows a low resistance.
     (n) If the actuator position micro-switch continuity checks are not as specified in Step (g) and (m):
NOTE: The inlet valve actuator position micro-switch can be checked remotely at the aircraft to ACT 2 free connector 7619VC2-A, between the pins 15 and 16.
     (o) Do a check of the aircraft wiring ASM 282801 between:
  • the ACT 2 actuator fuel inlet valve free connector 5QH2-A, pin C and the aircraft to ACT 2 free connector 7619VC2-A, pin 16
  • the aircraft to ACT 2 connector 7619VC2, pin 16 and the SDAC-1(2) 1WV1(1WV2) connector AB, pin 1D
  • the aircraft to ACT 2 connector 7619VC2, pin 16 and the RELAY-PANEL (802VU) FREE CONNECTOR 4065VC, pin M.
     (p) Repair all the unserviceable wiring and connectors.
     (q) Do the test given in Para. 3.A.
   (9) If the fault continues on the completion of all the steps in this procedure trouble-shoot the SDAC - Acquisition/Interface, Chap. 31-54-00.
[Rev.8 from Aug 2018] 2026.04.04 04:39:44 UTC
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