DOC AIRBUS | TSM A320FFuel - Loss of Power supply to the Center Tank Pump 1(2)
TASK 28-21-00-810-829-A
Fuel - Loss of Power supply to the Center Tank Pump 1(2)
A. Fixtures, Tools, Test and Support Equipment
B. Referenced Information
3. Fault Confirmation
Subtask 28-21-00-865-059-A ** ON A/C NOT FOR ALL
Subtask 28-21-00-810-078-C ** ON A/C NOT FOR ALL
Subtask 28-21-00-942-056-B ** ON A/C NOT FOR ALL
[Rev.8 from Aug 2018]
2026.04.04 04:39:33 UTC
Fuel - Loss of Power supply to the Center Tank Pump 1(2)
WARNING:
OBEY THE FUEL SAFETY PROCEDURES.
WARNING:
DO NOT CLOSE OR RESET:
- AN OPEN (TRIPPED) MECHANICAL CIRCUIT BREAKER
- A TRIPPED GFI
- FIRE OR EXPLOSION
- 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.
CAUTION:
YOU MUST DISCONNECT THE GFI FROM THE AIRCRAFT INSTALLATION BEFORE YOU DO THE INSULATION RESISTANCE TESTS. IF THE GFI IS NOT DISCONNECTED, DAMAGE WILL OCCUR TO THE GFI.
1. Possible Causes- CNTOR-GFI CTR TK PUMP 1 SUPPLY [69QA]
- CNTOR-GFI CTR TK PUMP 2 SUPPLY [70QA]
- PUMP-FUEL NO 1, CTR TK [37QA]
- PUMP-FUEL NO 2, CTR TK [38QA]
- C/B-FUEL/CTR TK/PUMP1 SPLY [29QA]
- C/B-FUEL/CTR TK/PUMP2 SPLY [30QA]
- aircraft wiring
A. Fixtures, Tools, Test and Support Equipment
| REFERENCE | QTY | DESIGNATION |
|---|---|---|
| No specific | 1 | MEGOHMMETER 200 MOHMS - 500 VDC, 0.001 A MAX |
| REFERENCE | DESIGNATION |
|---|---|
| ESPM 2031360 | |
| ESPM 2052210 | |
| ESPM 2052240 | |
| AMM 28-18-00-710-801 | Operational Check of Center-Tank Fuel-Pump GFI |
| AMM 28-21-00-720-001 | Functional Test of the Center-Tank Fuel Control |
| AWM 282105 | |
| AWM 282106 | |
| AMM 28-21-51-000-002 | Removal of the Fuel Pumps |
| AMM 28-21-51-400-002 | Installation of the Fuel Pumps |
| AMM 32-12-00-010-001 | Open the Main Gear Doors for Access |
| AMM 32-12-00-410-001 | Close the Main Gear Doors after Access |
| 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 | |
| AWM 930107 | |
| AWM 930120 | |
| AWM 930121 |
Subtask 28-21-00-865-059-A ** ON A/C NOT FOR ALL
A. Table of the circuit breakers used in this procedure:
Subtask 28-21-00-710-078-B ** ON A/C NOT FOR ALL | PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C NOT FOR ALL | |||
| 121VU | FUEL/CTR TK/PUMP2 SPLY | 30QA | P26 |
| 121VU | FUEL/CTR TK/PUMP1 SPLY | 29QA | P23 |
B. Test
4. Fault IsolationWARNING:
DO NOT CLOSE OR RESET:
(1) Not applicable. - AN OPEN (TRIPPED) MECHANICAL CIRCUIT BREAKER
- A TRIPPED GFI
- FIRE OR EXPLOSION
- DAMAGE TO THE AIRCRAFT WIRING AND STRUCTURE.
Subtask 28-21-00-810-078-C ** ON A/C NOT FOR ALL
A. Procedure
(2) Make sure that the CTR TK/PUMP 1 (2) P/BSW 33QA (34QA) shows OFF (released out).
(3) Open the left (right) main landing gear door for access AMM 32-12-00-010-001.
(4) Get access to the center tank fuel pump No. 1 (2) 37QA (38QA) AMM 28-21-51-000-002.
(5) Before you do more steps make sure that the areas, in the zones 147 (148) and 195 (196), that follow are not contaminated with fuel from a leak or spillage:
1 Repair all the leaks:
2 Clean the area of the fuel spillage.
(6) Clean and dry the fuel pump supply cable and the end connector 37QA-A (38QA-A).
(7) Disconnect the supply cable end connector 37QA-A (38QA-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 37QA-A (38QA-A) and the connector 7612VC-A (7577VC-A) that goes through pressure seal 7611VP (7508VP)) must be replaced AWM 282105 ( AWM 282106).
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:
(b) Connect the pins A, B and C, of the fuel pump receptacle, together (at the same time).
(c) Connect the other lead, of the insulation tester, to the pins A, B and C that were connected together in the previous step.
(d) If the insulation resistance of the fuel pump stator windings:
1 Is more than 1 Mohm, go to step (11).
2 Is less than 1 Mohm, replace the PUMP-FUEL NO 1, CTR TK [37QA] ( PUMP-FUEL NO 2, CTR TK [38QA] ) AMM 28-21-51-000-002 and AMM 28-21-51-400-002.
(11) 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-FUEL/CTR TK/PUMP1 SPLY [29QA] ( C/B-FUEL/CTR TK/PUMP2 SPLY [30QA] ) at the C/B panel 121VU AWM 930121.
(b) The connector 2212VC-A (2204VC-A) and related receptacle at the panel 120VU AWM 930120.
(12) 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 CNTOR-GFI CTR TK PUMP 1 SUPPLY [69QA] ( CNTOR-GFI CTR TK PUMP 2 SUPPLY [70QA] ).
(b) The connectors 1260VC-A (1262VC-A) and 1264VC-A (1266VC-A) and the related receptacles.
(a) Do a test, as detailed in the text that follows, of the aircraft wiring (three phase electrical supply) AWM 282105 ( AWM 282106) between the:
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 an intrinsically safe 500VDC insulation tester, 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.
(14) Repair/replacement of the unserviceable wiring and connectors.
(b) Do step (13).
(a) Do a test, as detailed in the text that follows, of the aircraft wiring (three phase electrical supply) AWM 282105 ( AWM 282106) between the connector 7612VC-A (7577VC-A) and the fuel pump connector 37QA-A (38QA-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.
(16) 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 37QA-A (38QA-A) and the connector 7612VC-A (7577VC-A) that goes through pressure seal 7611VP (7508VP)) must be replaced AWM 282105 ( AWM 282106).
This is because the wires are located in a fuel and vapour zone ESPM 2031360.
(17) Install the serviceable cable on the forward and rear sides of the bulkhead at FR42.
(18) Do not connect the fuel pump supply cable end connector 37QA-A (38QA-A) to the pump receptacle.
(19) Do a wiring test, as detailed in the step (15), of the aircraft wiring (three phase electrical supply) between the connector 7612VC-A (7577VC-A) and the PUMP-FUEL No. 1 (2), CTR TK connector 37QA-A (38QA-A) AWM 282105 ( AWM 282106).
(a) If the test shows that the wiring:
1 Is serviceable, do step (20).
2 Is unserviceable, do steps (8) to (9) and (15) to (19).
(20) Connect the fuel pump supply cable end connector 37QA-A (38QA-A) to the fuel pump receptacle.
(21) Install the CNTOR-GFI CTR TK PUMP 1 SUPPLY [69QA] ( CNTOR-GFI CTR TK PUMP 2 SUPPLY [70QA] ) and make sure that it is not tripped.
(22) Close (reset) the C/B-29QA (30QA).
(23) Do the Operational Check of the Ground Fault Interrupters Test and Reset Function AMM 28-18-00-710-801.
(a) Make sure that the GFI 69QA(70QA) is in the untripped reset condition.
1 If necessary, replace the CNTOR-GFI CTR TK PUMP 1 SUPPLY [69QA] ( CNTOR-GFI CTR TK PUMP 2 SUPPLY [70QA] ).
(24) Do the Functional Test of the Center-Tank Fuel Control (Manual Mode) AMM 28-21-00-720-001.
5. Close-upNOTE: This procedure is written for C/B-FUEL/CTR TK/PUMP 2 SPLY 29QA and GFI CTR TK PUMP 1 SUPPLY 69QA, with the C/B-FUEL/CTR TK/PUMP 2 SPLY 30QA and GFI CTR TK PUMP 2 SUPPLY 70QA given in parenthesis, if different.
(1) Do all the steps (2) thru (20) before you close the C/B-FUEL/CTR TK/PUMP 1 (2) SPLY 29QA (30QA) and CNTOR-GFI CTR TK PUMP 1 SUPPLY [69QA] ( CNTOR-GFI CTR TK PUMP 2 SUPPLY [70QA] ) in step (21). (2) Make sure that the CTR TK/PUMP 1 (2) P/BSW 33QA (34QA) shows OFF (released out).
(3) Open the left (right) main landing gear door for access AMM 32-12-00-010-001.
(4) Get access to the center tank fuel pump No. 1 (2) 37QA (38QA) AMM 28-21-51-000-002.
(5) Before you do more steps make sure that the areas, in the zones 147 (148) and 195 (196), that follow are not contaminated with fuel from a leak or spillage:
- the center tank bottom skin adjacent to the left (right) fuel pump 37QA (38QA)
- the hydraulic compartment below the wing box (center tank) and forward side of the rear bulkhead at FR42
- the rear wall (spar) of the center tank in the left (right) main landing gear bay
- the rear side of the bulkhead at FR 42 below the center tank.
1 Repair all the leaks:
2 Clean the area of the fuel spillage.
(6) Clean and dry the fuel pump supply cable and the end connector 37QA-A (38QA-A).
(7) Disconnect the supply cable end connector 37QA-A (38QA-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 receptacle
- the supply cable end connector 37QA-A (38QA-A)
- the supply cable
- the forward and rear sides of the structure of bulkhead FR42 adjacent to the route of the supply cable.
(a) If a wire is damaged, the complete section (length) of (each) wire (between the fuel pump connector 37QA-A (38QA-A) and the connector 7612VC-A (7577VC-A) that goes through pressure seal 7611VP (7508VP)) must be replaced AWM 282105 ( AWM 282106).
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:
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) Connect one lead, of the insulation tester, to pin D of the fuel pump receptacle. (b) Connect the pins A, B and C, of the fuel pump receptacle, together (at the same time).
(c) Connect the other lead, of the insulation tester, to the pins A, B and C that were connected together in the previous step.
(d) If the insulation resistance of the fuel pump stator windings:
1 Is more than 1 Mohm, go to step (11).
2 Is less than 1 Mohm, replace the PUMP-FUEL NO 1, CTR TK [37QA] ( PUMP-FUEL NO 2, CTR TK [38QA] ) AMM 28-21-51-000-002 and AMM 28-21-51-400-002.
(11) 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-FUEL/CTR TK/PUMP1 SPLY [29QA] ( C/B-FUEL/CTR TK/PUMP2 SPLY [30QA] ) at the C/B panel 121VU AWM 930121.
(b) The connector 2212VC-A (2204VC-A) and related receptacle at the panel 120VU AWM 930120.
(12) 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 CNTOR-GFI CTR TK PUMP 1 SUPPLY [69QA] ( CNTOR-GFI CTR TK PUMP 2 SUPPLY [70QA] ).
(b) The connectors 1260VC-A (1262VC-A) and 1264VC-A (1266VC-A) and the related receptacles.
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.
CAUTION:
YOU MUST DISCONNECT THE GFI FROM THE AIRCRAFT INSTALLATION BEFORE YOU DO THE INSULATION RESISTANCE TESTS. IF THE GFI IS NOT DISCONNECTED, DAMAGE WILL OCCUR TO THE GFI.
(13) Continuity and insulation resistance test of internal three phase wiring. (a) Do a test, as detailed in the text that follows, of the aircraft wiring (three phase electrical supply) AWM 282105 ( AWM 282106) between the:
- C/B-FUEL/CTR TK/PUMP1(2) SPLY 29QA(30QA) and the CNTOR-GFI CTR TK PUMP 1 SUPPLY [69QA] ( CNTOR-GFI CTR TK PUMP 2 SUPPLY [70QA] )
- CNTOR-GFI CTR TK PUMP 1 SUPPLY [69QA] ( CNTOR-GFI CTR TK PUMP 2 SUPPLY [70QA] ) and the connector 7612VC (7577VC).
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 an intrinsically safe 500VDC insulation tester, 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.
(14) 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. (b) Do step (13).
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.
CAUTION:
YOU MUST DISCONNECT THE GFI FROM THE AIRCRAFT INSTALLATION BEFORE YOU DO THE INSULATION RESISTANCE TESTS. IF THE GFI IS NOT DISCONNECTED, DAMAGE WILL OCCUR TO THE GFI.
(15) Continuity and insulation resistance test of external three phase wiring. (a) Do a test, as detailed in the text that follows, of the aircraft wiring (three phase electrical supply) AWM 282105 ( AWM 282106) between the connector 7612VC-A (7577VC-A) and the fuel pump connector 37QA-A (38QA-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.
(16) 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 37QA-A (38QA-A) and the connector 7612VC-A (7577VC-A) that goes through pressure seal 7611VP (7508VP)) must be replaced AWM 282105 ( AWM 282106).
This is because the wires are located in a fuel and vapour zone ESPM 2031360.
(17) Install the serviceable cable on the forward and rear sides of the bulkhead at FR42.
(18) Do not connect the fuel pump supply cable end connector 37QA-A (38QA-A) to the pump receptacle.
(19) Do a wiring test, as detailed in the step (15), of the aircraft wiring (three phase electrical supply) between the connector 7612VC-A (7577VC-A) and the PUMP-FUEL No. 1 (2), CTR TK connector 37QA-A (38QA-A) AWM 282105 ( AWM 282106).
(a) If the test shows that the wiring:
1 Is serviceable, do step (20).
2 Is unserviceable, do steps (8) to (9) and (15) to (19).
(20) Connect the fuel pump supply cable end connector 37QA-A (38QA-A) to the fuel pump receptacle.
(21) Install the CNTOR-GFI CTR TK PUMP 1 SUPPLY [69QA] ( CNTOR-GFI CTR TK PUMP 2 SUPPLY [70QA] ) and make sure that it is not tripped.
(22) Close (reset) the C/B-29QA (30QA).
(23) Do the Operational Check of the Ground Fault Interrupters Test and Reset Function AMM 28-18-00-710-801.
(a) Make sure that the GFI 69QA(70QA) is in the untripped reset condition.
1 If necessary, replace the CNTOR-GFI CTR TK PUMP 1 SUPPLY [69QA] ( CNTOR-GFI CTR TK PUMP 2 SUPPLY [70QA] ).
(24) Do the Functional Test of the Center-Tank Fuel Control (Manual Mode) AMM 28-21-00-720-001.
Subtask 28-21-00-942-056-B ** ON A/C NOT FOR ALL
A. Procedure
(1) Make sure that the fuel pump is installed correctly and the bolts that attach the pump have been torque tightened AMM 28-21-51-400-002.
(2) Close the left (right) main landing gear door AMM 32-12-00-410-001.
(3) Close the access panel 195AB (196AB).
(4) 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 and the bolts that attach the pump have been torque tightened AMM 28-21-51-400-002.
(2) Close the left (right) main landing gear door AMM 32-12-00-410-001.
(3) Close the access panel 195AB (196AB).
(4) Remove the ground support and maintenance equipment, the special and standard tools and all other items.