DOC AIRBUS | TSM A320FFuel Pumps - ACT Manual Transfer Pump, Power Supply - C/B-25QH Tripped
TASK 28-28-00-810-824-A
Fuel Pumps - ACT Manual Transfer Pump, Power Supply - C/B-25QH Tripped
A. Fixtures, Tools, Test and Support Equipment
B. Referenced Information
3. Fault Confirmation
Subtask 28-28-00-865-065-A ** ON A/C NOT FOR ALL
Subtask 28-28-00-810-072-A ** ON A/C NOT FOR ALL
Subtask 28-28-00-942-050-A ** ON A/C NOT FOR ALL
[Rev.8 from Aug 2018]
2026.04.04 04:28:52 UTC
Fuel Pumps - ACT Manual Transfer Pump, Power Supply - C/B-25QH Tripped
WARNING:
OBEY THE FUEL SAFETY PROCEDURES.
WARNING:
DO NOT CLOSE AN OPEN (TRIPPED) CIRCUIT BREAKER RELATED TO A FUEL-PUMP.
IF YOU CLOSE THE CIRCUIT BREAKER, THERE IS A RISK:
- OF FIRE OR OF AN EXPLOSION
- OF DAMAGE TO THE AIRCRAFT WIRING AND STRUCTURE.
WARNING:
WHEN YOU DO WORK ON THE FUEL SYSTEM WIRING, YOU MUST USE TEST EQUIPMENT THAT IS APPROVED (REFER TO INTERNATIONAL OR NATIONAL SPECIFICATIONS FOR INTRINSICALLY SAFE TEST EQUIPMENT: EN50020, UL913 OR EQUIVALENT). TEST EQUIPMENT THAT IS NOT APPROVED CAN CAUSE FIRE OR AN EXPLOSION.
1. Possible Causes- PUMP-FUEL TRANSFER, ACT [1QH]
- C/B-ACT PUMP SUPPLY [25QH]
- CONTACTOR-ACT PUMP SUPPLY [26QH]
- aircraft wiring
A. Fixtures, Tools, Test and Support Equipment
| REFERENCE | QTY | DESIGNATION |
|---|---|---|
| No specific | 1 | MEGOHMMETER 200 MOHMS - 500 VDC, 0.001 A MAX |
| No specific | 1 | MULTIMETER - STANDARD |
| REFERENCE | DESIGNATION |
|---|---|
| TSM TASK 28-13-00-810-801-A | Fuel - Leak Shows at Drain Mast |
| ESPM 2031360 | |
| ESPM 2052210 | |
| ESPM 2052240 | |
| AMM 28-28-00-710-001 | Operational Check of the ACT Manual Transfer System |
| AWM 282801 | |
| AMM 28-28-51-000-001 | Removal of the ACT Fuel-Transfer Pump-Element |
| AMM 28-28-51-400-001 | Installation of the ACT Fuel-Transfer Pump-Element |
| AMM 51-76-12-300-001 | Local Repair of the Fuel Tank Sealant |
| AMM 51-76-12-300-002 | Repair of the Fuel Tank Fillet |
| SRM 530000 | |
| AMM 57-17-11-000-003 | Removal of the Protective Cover of the ACT-Equipment Support Door |
| AMM 57-17-11-400-003 | Installation of the Protective Cover of the ACT-Equipment Support Door |
| AWM 930107 | |
| AWM 930120 | |
| AWM 930121 |
Subtask 28-28-00-865-065-A ** ON A/C NOT FOR ALL
A. Table of the circuit breakers used in this procedure:
Subtask 28-28-00-710-059-A ** ON A/C NOT FOR ALL | PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C NOT FOR ALL | |||
| 121VU | ACT PUMP SUPPLY | 25QH | Q29 |
B. Test
4. Fault IsolationWARNING:
DO NOT CLOSE AN OPEN (TRIPPED) CIRCUIT BREAKER RELATED TO A FUEL-PUMP.
IF YOU CLOSE THE CIRCUIT BREAKER, THERE IS A RISK:
(1) Not applicable. - OF FIRE OR OF AN EXPLOSION
- OF DAMAGE TO THE AIRCRAFT WIRING AND STRUCTURE.
Subtask 28-28-00-810-072-A ** ON A/C NOT FOR ALL
A. Procedure
(1) Do all the steps (2) thru (22) before you close the C/B-25QH in step (23).
(2) Make sure that the P/BSW-FUEL/ACT/AUTO (24QH) is set to AUTO (released out).
(3) Get access to the fuel pump (1QH) installed on the ACT-Equipment Support Door AMM 28-28-51-000-001.
(4) Remove the Protective Cover of the ACT-Equipment Support Door AMM 57-17-11-000-003.
(5) Before you do more steps, make sure that the ACT-Equipment Support Door (panel 147BZ) and adjacent area are not contaminated with fuel from a leak or spillage.
(a) If necessary:
1 Repair all the leaks:
2 Clean the area of the fuel spillage.
(6) If necessary, clean and dry the fuel pump supply cable and the connector 1QH-A.
(7) Disconnect the fuel pump electrical supply cable end connector 1QH-A from the fuel pump receptacle.
(8) Make sure that good lighting is available.
Do a visual inspection and look for distortion (pinched or stretched), damage (chafed or cut), discoloration, overheating (burnt/melted or arcing) liquid contamination or incorrect assembly, of the items that follow:
(a) If a wire is damaged, the complete section (length) of (each) wire (between the fuel pump connector 1QH-A and the connector 7587VC-A that goes through pressure seal 7509VP must be replaced AWM 282801.
This is because the wires are located in a fuel and vapour zone ESPM 2031360.
(b) If the aircraft structure is damaged, refer to the related items - Allowable Damage, P. Block 101, SRM 530000.
(10) Do an insulation test, with an (intrinsically safe) 500VDC insulation tester, of the fuel pump stator windings as follows:
(a) Connect one lead, of the insulation tester, to pin 7 of the fuel pump receptacle.
(b) Connect the pins 1, 2, 4 and 6, of the fuel pump receptacle, together (at the same time).
(c) Connect the other lead, of the insulation tester, to the pins 1, 2, 4 and 6 that were connected together in the previous step.
(11) If the insulation resistance of the fuel pump stator windings:
(a) Is more than 1 Mohm, go to step (12).
(b) Is less than 1 Mohm, replace the PUMP-FUEL TRANSFER, ACT [1QH] AMM 28-28-51-000-001 and AMM 28-28-51-400-001.
(12) In the cockpit (right rear) do a visual inspection as specified in step (8) of the items that follow, replace if necessary:
(a) The C/B-ACT PUMP SUPPLY [25QH] at the C/B panel 121VU AWM 930121.
(b) The connector 2216VC-A and related receptacle at the panel 120VU AWM 930120.
(13) In the forward avionics bay, at the contactor box 107VU AWM 930107 do a visual inspection as specified in step (8) and replace, if necessary:
(a) The CONTACTOR-ACT PUMP SUPPLY [26QH] .
(b) The connectors 1270VC-A and 1274VC-A and the related receptacles.
(14) Do a test, as detailed in the text that follows, of the aircraft wiring (three phase electrical supply) AWM 282801 between the:
The test required is as follows:
(a) Continuity test, with a multimeter, of each three phase wire (from end to end) ESPM 2052210.
(b) Insulation test, with a 500VDC insulation tester, between each phase wire (pole) and ground ESPM 2052240.
(c) Insulation test, with a 500VDC insulation tester, between each phase wire and the other two wires (pole to pole) ESPM 2052240.
(15) Repair/replacement of the unserviceable wiring and connectors.
(16) Continuity test of the aircraft three phase wiring.
The test required is as follows:
(b) Continuity test, with a MULTIMETER - STANDARD, of each three phase wire (from end to end) ESPM 2052210.
(c) Insulation test, with a MEGOHMMETER 200 MOHMS - 500 VDC, 0.001 A MAX, between each phase wire (pole) and ground ESPM 2052240.
(d) Insulation test, with an (intrinsically safe) 500VDC insulation tester, between each phase wire and the other two wires (pole to pole) ESPM 2052240.
(17) Repair/replace the unserviceable wiring and connectors.
(a) If a wire is damaged, the complete section (length) of (each) wire (between the fuel pump connector 1QH-A and the connector 7587VC-A that goes through pressure seal 7509VP must be replaced AWM 282801.
This is because the wires are located in a fuel and vapour zone ESPM 2031360.
(18) Install the serviceable cable on the rear side of the bulkhead at FR42 (tank wall).
(19) Do not connect the fuel pump supply cable end connector 1QH-A to the pump receptacle.
(20) Do a wiring test as detailed in the step (16), of the aircraft wiring, after the repair and installation.
(21) If the test shows that the wiring:
(a) Is serviceable, do step (22).
(b) Is unserviceable, do steps (2) thru (20) again.
(22) Connect the fuel pump supply cable connector 1QH-A to the fuel pump receptacle.
(23) Close (reset) the C/B-25QH.
(24) Do a check of the three leak monitors (Ref. TSM TASK 28-13-00-810-801).
(25) If you find fuel in a leak monitor, do the related trouble-shooting (Ref. TSM TASK 28-13-00-810-801).
5. Close-up(1) Do all the steps (2) thru (22) before you close the C/B-25QH in step (23).
(2) Make sure that the P/BSW-FUEL/ACT/AUTO (24QH) is set to AUTO (released out).
(3) Get access to the fuel pump (1QH) installed on the ACT-Equipment Support Door AMM 28-28-51-000-001.
(4) Remove the Protective Cover of the ACT-Equipment Support Door AMM 57-17-11-000-003.
(5) Before you do more steps, make sure that the ACT-Equipment Support Door (panel 147BZ) and adjacent area are not contaminated with fuel from a leak or spillage.
(a) If necessary:
1 Repair all the leaks:
2 Clean the area of the fuel spillage.
(6) If necessary, clean and dry the fuel pump supply cable and the connector 1QH-A.
(7) Disconnect the fuel pump electrical supply cable end connector 1QH-A from the fuel pump receptacle.
(8) Make sure that good lighting is available.
Do a visual inspection and look for distortion (pinched or stretched), damage (chafed or cut), discoloration, overheating (burnt/melted or arcing) liquid contamination or incorrect assembly, of the items that follow:
- the fuel pump electrical receptacle
- the supply cable connector 1QH-A
- the supply cable (part of the harness 5675VB) between the end connector 1QH-A and pressure seal feedthrough 7509VP on the roof of the left Main Landing Gear (MLG) bay
- the aircraft structure adjacent to the route of the supply cable in the left MLG bay.
NOTE: Damage to the fuel pump supply cable insulation can cause electrical arcing and damage to the aircraft structure.
(9) Repair, replace or make serviceable items found unserviceable in step (8). (a) If a wire is damaged, the complete section (length) of (each) wire (between the fuel pump connector 1QH-A and the connector 7587VC-A that goes through pressure seal 7509VP must be replaced AWM 282801.
This is because the wires are located in a fuel and vapour zone ESPM 2031360.
(b) If the aircraft structure is damaged, refer to the related items - Allowable Damage, P. Block 101, SRM 530000.
(10) Do an insulation test, with an (intrinsically safe) 500VDC insulation tester, of the fuel pump stator windings as follows:
(a) Connect one lead, of the insulation tester, to pin 7 of the fuel pump receptacle.
(b) Connect the pins 1, 2, 4 and 6, of the fuel pump receptacle, together (at the same time).
(c) Connect the other lead, of the insulation tester, to the pins 1, 2, 4 and 6 that were connected together in the previous step.
(11) If the insulation resistance of the fuel pump stator windings:
(a) Is more than 1 Mohm, go to step (12).
(b) Is less than 1 Mohm, replace the PUMP-FUEL TRANSFER, ACT [1QH] AMM 28-28-51-000-001 and AMM 28-28-51-400-001.
(12) In the cockpit (right rear) do a visual inspection as specified in step (8) of the items that follow, replace if necessary:
(a) The C/B-ACT PUMP SUPPLY [25QH] at the C/B panel 121VU AWM 930121.
(b) The connector 2216VC-A and related receptacle at the panel 120VU AWM 930120.
(13) In the forward avionics bay, at the contactor box 107VU AWM 930107 do a visual inspection as specified in step (8) and replace, if necessary:
(a) The CONTACTOR-ACT PUMP SUPPLY [26QH] .
(b) The connectors 1270VC-A and 1274VC-A and the related receptacles.
(14) Do a test, as detailed in the text that follows, of the aircraft wiring (three phase electrical supply) AWM 282801 between the:
- C/B-ACT PUMP SPLY (25QH) and the CONTACTOR-ACT PUMP SUPPLY (26QH)
- CONTACTOR-ACT PUMP SUPPLY (26QH) and the connector 7587VC.
The test required is as follows:
(a) Continuity test, with a multimeter, of each three phase wire (from end to end) ESPM 2052210.
(b) Insulation test, with a 500VDC insulation tester, between each phase wire (pole) and ground ESPM 2052240.
(c) Insulation test, with a 500VDC insulation tester, between each phase wire and the other two wires (pole to pole) ESPM 2052240.
(15) Repair/replacement of the unserviceable wiring and connectors.
CAUTION:
DO NOT USE IN-LINE SPLICES TO REPAIR SECTIONS OF ELECTRICAL CABLE THAT ARE BEHIND A FAIRING OR IN A CONDUIT.
THIS WILL MAKE SURE THAT IT IS POSSIBLE TO SEE THE REPAIR FOR AN INSPECTION (REF. ESPM 20-53-29).
(a) Repair/replace the unserviceable wiring and connectors. (16) Continuity test of the aircraft three phase wiring.
WARNING:
WHEN YOU DO WORK ON THE FUEL SYSTEM WIRING, YOU MUST USE TEST EQUIPMENT THAT IS APPROVED (REFER TO INTERNATIONAL OR NATIONAL SPECIFICATIONS FOR INTRINSICALLY SAFE TEST EQUIPMENT: EN50020, UL913 OR EQUIVALENT). TEST EQUIPMENT THAT IS NOT APPROVED CAN CAUSE FIRE OR AN EXPLOSION.
(a) Do a test, as detailed in the text that follows, of the aircraft wiring (three phase electrical supply) AWM 282801 between the connector 7587VC-A and the (ACT/transfer) fuel pump connector 1QH-A. The test required is as follows:
(b) Continuity test, with a MULTIMETER - STANDARD, of each three phase wire (from end to end) ESPM 2052210.
(c) Insulation test, with a MEGOHMMETER 200 MOHMS - 500 VDC, 0.001 A MAX, between each phase wire (pole) and ground ESPM 2052240.
(d) Insulation test, with an (intrinsically safe) 500VDC insulation tester, between each phase wire and the other two wires (pole to pole) ESPM 2052240.
(17) Repair/replace the unserviceable wiring and connectors.
(a) If a wire is damaged, the complete section (length) of (each) wire (between the fuel pump connector 1QH-A and the connector 7587VC-A that goes through pressure seal 7509VP must be replaced AWM 282801.
This is because the wires are located in a fuel and vapour zone ESPM 2031360.
(18) Install the serviceable cable on the rear side of the bulkhead at FR42 (tank wall).
(19) Do not connect the fuel pump supply cable end connector 1QH-A to the pump receptacle.
(20) Do a wiring test as detailed in the step (16), of the aircraft wiring, after the repair and installation.
(21) If the test shows that the wiring:
(a) Is serviceable, do step (22).
(b) Is unserviceable, do steps (2) thru (20) again.
(22) Connect the fuel pump supply cable connector 1QH-A to the fuel pump receptacle.
(23) Close (reset) the C/B-25QH.
(24) Do a check of the three leak monitors (Ref. TSM TASK 28-13-00-810-801).
(25) If you find fuel in a leak monitor, do the related trouble-shooting (Ref. TSM TASK 28-13-00-810-801).
NOTE: It is important to make sure that there are no fuel leaks in the ACT system assemblies before you do the test that follows.
(26) Do the Operational Test of the ACT Manual Transfer System AMM 28-28-00-710-001. Subtask 28-28-00-942-050-A ** ON A/C NOT FOR ALL
A. Close Access
(1) Make sure that the fuel pump is installed correctly with the two mounting bars and the four bolts have been torque tightened AMM 28-28-51-400-001.
(2) Install the fuel pump cover assembly AMM 57-17-11-400-003.
(3) Remove the ground support and maintenance equipment, the special and standard tools and all other items.
(1) Make sure that the fuel pump is installed correctly with the two mounting bars and the four bolts have been torque tightened AMM 28-28-51-400-001.
(2) Install the fuel pump cover assembly AMM 57-17-11-400-003.
(3) Remove the ground support and maintenance equipment, the special and standard tools and all other items.