W DOC AIRBUS | TSM A320F

Fuel - L(R) Wing Tank Pumps 2, Power Supply - C/B-7QA(8QA) Tripped

TASK 28-21-00-810-828-A
Fuel - L(R) Wing Tank Pumps 2, Power Supply - C/B-7QA(8QA) 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.
1. Possible Causes
  • PUMP-FUEL NO 2, L WING TK [25QA]
  • PUMP-FUEL NO 2, R WING TK [26QA]
  • C/B-FUEL/L WING TK/PUMP2 SPLY [7QA]
  • C/B-FUEL/R WING TK/PUMP2 SPLY [8QA]
  • CNTOR-L WING TK PUMP 2 SPLY [19QA]
  • CNTOR-R WING TK PUMP 2 SPLY [20QA]
  • aircraft wiring
2. Job Set-up Information
 A. Fixtures, Tools, Test and Support Equipment
REFERENCE
QTY
DESIGNATION
No specific
AR
MULTIMETER - STANDARD
No specific
AR
TESTER - INSULATION, 500 V
 B. Referenced Information
REFERENCE
DESIGNATION
ESPM 2052210
ESPM 2052240
ESPM 2053210
AMM 28-21-00-710-001
Operational Test of the Wing-Tank Fuel Control
ASM 282102
AMM 28-21-49-000-001
Removal of the Fuel Pump Fairings
AMM 28-21-49-400-001
Installation of the Fuel Pump Fairings
AMM 28-21-51-000-001
Removal of the Fuel Pumps
AMM 28-21-51-400-001
Installation of the Fuel Pumps
SRM 517612
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 572111
AWM 930107
AWM 930120
AWM 930121
3. Fault Confirmation
Subtask 28-21-00-865-055-A
A. Table of the circuit breakers used in this procedure:
PANELDESIGNATIONFINLOCATION
** ON A/C ALL
121VUFUEL/L WING TK/PUMP2 SPLY7QAN26
121VUFUEL/R WING TK/PUMP2 SPLY8QAQ26
Subtask 28-21-00-710-077-A
B. Test
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.
   (1) Not applicable.
4. Fault Isolation
Subtask 28-21-00-810-077-B
A. Procedure
NOTE: This procedure is written for the C/B-FUEL/L WING TK/PUMP 2 SPLY 7QA with the C/B-FUEL/R WING TK/PUMP 2 SPLY 8QA given in parenthesis, if different.
   (1) Do all the steps (2) thru (20) before you close the C/B-FUEL/L(R) WING TK/PUMP 2 SPLY 7QA(8QA) in step (21).
   (2) Make sure that the L(R) TK PUMPS 2 P/BSW 15QA(16QA) shows OFF (released out).
   (3) Before you do more steps, make sure that the wing area adjacent to the left inner fuel pump 25QA (right outer fuel pump 26QA) fairings and cover are not contaminated with fuel from a fuel leak or spillage.
     (a) If necessary:
       1 Repair all the leaks:
       2 Clean the area of the fuel spillage.
   (4) Remove all the fuel pump 25QA(26QA) fairings AMM 28-21-49-000-001 and cover assembly AMM 28-21-51-000-001.
   (5) Disconnect the supply cable end connector 25QA-A(26QA-A) from the fuel pump receptacle.
   (6) Clean and dry:
  • all the fuel pump fairings
  • the fuel pump cover assembly
  • the fuel pump supply cable and the related end connector
  • the aircraft wing structure adjacent to the route of the supply cable across the wing surface
  • the aircraft wing structure at the rear spar, adjacent to the landing light, where the fuel pump supply cable leaves the conduit and passes through the cable guide (bottom skin).
   (7) 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 electrical receptacle
  • the supply cable end connector 25QA-A(26QA-A)
  • the supply cable
  • the cable guide
  • the fuel pump fairings
  • the aircraft wing structure adjacent to the route of the supply cable (across the wing surface and at the rear spar)
  • junction box (bracket assembly) on the rear spar.
NOTE: Incorrect installation of the fuel pump fairings can damage the supply cable. This can cause electrical arcing and damage to the aircraft structure.
   (8) If any damage (electrical wiring, fairing or structural) is found, tell AIRBUS within 10 days.
   (9) If the aircraft structure is damaged, refer to Skins and Plating - Allowable Damage, P. Block 101 SRM 572111.
   (10) If necessary, replace the damaged fairings with serviceable items.
   (11) If the fuel pump supply cable between the connector 25QA-A(26QA-A) and the related junction box (bracket assembly) on the rear spar is seen to be damaged, repair as follows:
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) If necessary, replace the unserviceable:
  • protective sleeve
  • wire(s)
  • connector.
     (b) Connect the new wire(s) of the fuel pump supply cable where the wiring passes through the junction box (bracket assembly), by a splice(s) ESPM 2053210.
     (c) Make sure that the length of the new supply cable when assembled, between the front face of the connector 25QA-A(26QA-A) and the forward face of the cable guide (that shows outside the wing-skin) is:
  • 1320 mm (51.97 in) for the left (inner) wing tank pump No. 2 - 25QA
  • (1345 mm (52.95 in) for the right (outer) wing tank pump No. 2 - 26QA).
     (d) If necessary, make any final adjustment in the length of the supply cable across the lower surface of the wing during the installation of the rear fairing.
     (e) Feed the surplus cable (small amount only) into the flexible conduit to the junction box (bracket assembly) on the rear spar.
     (f) Make sure that the supply cable is held tight by the P-clip at the cable guide.
NOTE: It is important that the fuel pump supply cable is installed correctly as given in steps (b) thru (f). Incorrect installation of the cable can cause it to get damaged. If the cable is too short it will put tension on the wires and plug. If the cable is too long you will not be able to install the fairings correctly. This is because the unwanted cable (excess length) will become looped and get trapped during the installation of the intermediate and rear fairings.
   (12) Do an insulation test, with a 500VDC insulation tester, of the fuel pump stator windings as follows:
     (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 (13).
       2 Is less than 1 Mohm, replace the PUMP-FUEL NO 2, L WING TK [25QA] ( PUMP-FUEL NO 2, R WING TK [26QA] ) AMM 28-21-51-000-001 and AMM 28-21-51-400-001.
   (13) In the cockpit (right rear) do a visual inspection as specified in step (7) of the items that follow, replace if necessary:
     (a) The C/B-FUEL/L WING TK/PUMP2 SPLY [7QA] ( C/B-FUEL/R WING TK/PUMP2 SPLY [8QA] ) at the C/B panel 121VU AWM 930121.
     (b) The connector 2216VC-A and related receptacle at the panel 120VU AWM 930120.
   (14) In the forward avionics bay, at the contactor box 107VU AWM 930107 do a visual inspection as specified in step (7) and replace, if necessary:
     (a) The CNTOR-L WING TK PUMP 2 SPLY [19QA] ( CNTOR-R WING TK PUMP 2 SPLY [20QA] ).
     (b) The connector 1266VC-A (1262VC-A) and related receptacle.
   (15) Do a test, as detailed in the text that follows, of the aircraft wiring (three phase electrical supply) ASM 282102 between the:
  • C/B-FUEL/L(R) WING TK/PUMP 2 SPLY 7QA(8QA) and the CNTOR-L(R) WING TK PUMP 2 SPLY 19QA(20QA)
  • CNTOR-L(R) WING TK PUMP 2 SPLY 19QA(20QA) and the PUMP-FUEL No. 2, L(R) WING TK connector 25QA-A(26QA-A).

The test required is as follows:
     (a) Continuity test, with a MULTIMETER - STANDARD, of each three phase wire (from end to end) ESPM 2052210.
     (b) Insulation test, with a TESTER - INSULATION, 500 V, 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.
   (16) Repair/replace 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) If the fuel pump supply cable between the connector 25QA-A(26QA-A) and the related junction box (bracket assembly) on the rear spar is seen to be damaged, repair as follows:
       1 If necessary, replace the unserviceable:
  • protective sleeve
  • wire(s)
  • connector.
       2 Connect the new wire(s) of the fuel pump supply cable where the wiring passes through the junction box (bracket assembly), by a splice(s) ESPM 2053210.
       3 Make sure that the length of the new supply cable when assembled, between the front face of the connector 25QA-A(26QA-A) and the forward face of the cable guide (that shows outside the wing-skin) is:
  • 1320 mm (51.97 in) for the left (inner) wing tank pump No. 2 - 25QA
  • (1345 mm (52.95 in) for the right (outer) wing tank pump No. 2 - 26QA).
       4 If necessary, make any final adjustment in the length of the supply cable across the lower surface of the wing during the installation of the rear fairing.
       5 Feed the surplus cable (small amount only) into the flexible conduit to the junction box (bracket assembly) on the rear spar.
       6 Make sure that the supply cable is held tight by the P-clip at the cable guide.
NOTE: It is important that the fuel pump supply cable is installed correctly as given in steps 2_ thru 6_. Incorrect installation of the cable can cause it to get damaged. If the cable is too short it will put tension on the wires and plug. If the cable is too long you will not be able to install the fairings correctly. This is because the unwanted cable (excess length) will become looped and get trapped during the installation of the intermediate and rear fairings.
   (17) The fuel pump supply cable end connector 25QA-A(26QA-A) must stay disconnected.
   (18) Install the fuel pump, rear and intermediate, fairings AMM 28-21-49-400-001. Make sure that the fuel pump supply cable does not get caught under the fairings.
   (19) Do a wiring test, as detailed in the step (15), of the aircraft wiring (three phase electrical supply) ASM 282102 between the CNTOR-L(R) WING TK PUMP 2 SPLY 19QA(20QA) and the PUMP-FUEL No. 2, L(R) WING TK connector 25QA-A(26QA-A).
     (a) If the wiring test:
       1 Is serviceable, do step (20).
       2 Is unserviceable, do steps (15) thru (19) again.
   (20) Connect the fuel pump supply cable end connector 25QA-A(26QA-A) to the fuel pump receptacle.
   (21) Close (reset) the C/B-7QA(8QA).
   (22) Do the Operational Test of the Wing-Tanks Fuel Control AMM 28-21-00-710-001.
5. Close-up
Subtask 28-21-00-942-055-A
A. Procedure
   (1) Make sure that the fuel pump is installed correctly and the two bolts that attach the pump have been torque tightened AMM 28-21-51-400-001.
   (2) Install the fuel pump cover plate and the front fairing AMM 28-21-51-400-001.
   (3) Remove the ground support and maintenance equipment, the special and standard tools and all other items.
[Rev.8 from Aug 2018] 2026.04.04 04:28:37 UTC
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