W DOC AIRBUS | TSM A320F

Fuel Pumps - Right Wing Tank Fuel Pump No. 2 (Outer) 26QA System Malfunction

TASK 28-21-00-810-804-A
Fuel Pumps - Right Wing Tank Fuel Pump No. 2 (Outer) 26QA System Malfunction

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 NO 2, R WING TK [26QA]
  • C/B-FUEL/R WING TK/PUMP2 SPLY [8QA]
  • CNTOR-R WING TK PUMP 2 SPLY [20QA]
  • aircraft wiring
  • PRESS SW-FUEL PUMP NO 2, R WING TK [28QA]
  • pressure switch sealing valve
  • pressure switch plug (banjo adaptor attachment bolt)
  • pressure switch fuel supply pipe-line between the fuel pump canister 4QM and the pressure switch 28QA
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
99A28404000000
1
ADAPTOR-SEQUENCE VALVE
 B. Referenced Information
REFERENCE
DESIGNATION
TSM TASK 28-21-00-810-828-A
Fuel - L(R) Wing Tank Pumps 2, Power Supply - C/B-7QA(8QA) Tripped
ESPM 2052210
ESPM 2052240
ESPM 2053210
ASM 245805
AMM 28-21-00-710-007
Operational Test of the Main Fuel-Pump System with Fuel Flow by Transfer
ASM 282102
AWM 282104
AMM 28-21-15-000-003
Removal of the Fuel-Pump Pressure-Switch
AMM 28-21-15-400-001
Installation of the Fuel-Pump Pressure-Switch
AMM 28-21-45-400-003
Installation of the Sequence Valve
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 28-21-00-865-053-A
A. Table of the circuit breakers referred to in this procedure:
PANELDESIGNATIONFINLOCATION
** ON A/C ALL
121VUFUEL/R WING TK/PUMP2 SPLY8QAQ26
Subtask 28-21-00-710-053-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) Examine the C/B-FUEL/R WING TK/PUMP 2 SPLY (8QA).
   (2) If the C/B-8QA:
     (a) Is open (tripped), do Fuel - L(R) Wing Tank Pumps 2, Power Supply - C/B-7QA(8QA) Tripped (Ref. TSM TASK 28-21-00-810-828).
     (b) Is closed (set), do the Fault Isolation.
4. Fault Isolation
Subtask 28-21-00-810-053-D ** ON A/C NOT FOR ALL
A. Procedure
   (1) If a fuel low pressure indication is shown for the right wing tank fuel pump No. 2 (26QA):
  • do a fuel transfer AMM 28-21-00-710-007 use the right wing tank fuel pump No. 2 to do the fuel transfer.
   (2) If the fuel starts to transfer go to step (3). If the fuel does not start to transfer:
     (a) Set the R TK PUMPS 2 P/BSW (16QA) to OFF (release out). This will de-energize the contactor 20QA.
     (b) Before you do more steps, make sure that the wing area adjacent to the right outer fuel pump 26QA fairings and cover is not contaminated with fuel from a fuel leak or spillage.
       1 If necessary:
         a Repair all the leaks:
         b Clean the area of the fuel spillage.
     (c) Remove all the fuel pump 26QA cable fairings AMM 28-21-49-000-001 and cover assembly AMM 28-21-51-000-001.
     (d) Disconnect the supply cable end connector 26QA-A from the fuel pump receptacle.
     (e) If, in step (c) or (d), any damage can be seen on the supply cable or the aircraft structure, go to step (j) 1_.
     (f) Set the R TK PUMPS 2 P/BSW (16QA) to ON (push in). This will energize the contactor 20QA and the 115VAC three phases will be supplied to the fuel pump connector 26QA-A.
     (g) Use a MULTIMETER - STANDARD to do a test, to make sure that each of the 115VAC three phases are available at the connector 26QA-A ASM 282102.
     (h) Set the R TK PUMPS 2 P/BSW (16QA) to OFF (release out). This will de-energize the contactor 20QA.
       1 Use a multimeter to do a test, to make sure that each of the 115VAC three phases are not available at the connector 26QA-A.
NOTE: This is to make sure that the contactor 20QA does not stay in the on position (stuck/held on).
     (i) If the 115VAC three phase supply voltage measured in step (g) is correct:
       1 Replace the PUMP-FUEL NO 2, R WING TK [26QA] AMM 28-21-51-000-001 and AMM 28-21-51-400-001.
     (j) If the 115VAC three phase supply voltage measured in step (g) is not correct (no voltage, incorrect voltage or a phase is missing), do all the sub-steps that follow:
       1 Clean and dry:
  • all the fuel pump cable 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).
       2 Make sure that good lighting is available.
Do a visual inspection and look for distortion (pinched or streched) damage (chafed or cut), discoloration, overheating (burnt/melted or arcing) liquid contamination, loose electrical connection or incorrect assembly, of the items that follow:
  • the electrical receptacle
  • the supply cable end connector 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.
       3 If any damage (electrical wiring, fairing or structural) is found, tell AIRBUS within 10 days.
       4 If the aircraft structure is damaged, refer to Skins and Plating - Allowable Damage, P. Block 101, SRM 572111.
       5 If necessary, replace the damaged fairings with serviceable items.
       6 If the fuel pump supply cable between the connector 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 26QA-A and the forward face of the cable guide (that shows outside the wing-skin) is 1345 mm (52.9528 in.).
         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) back up 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.
       7 In the cockpit (right rear) do a visual inspection as specified in step (j)2_ of the items that follow, replace if necessary:
         a The 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.
       8 Release the front face of the C/B panel 121VU and lower to the open (horizontal) position.
       9 Use a multimeter and make sure that each of the 115VAC three phases are available at the C/B-8QA input and output terminals ASM 282102.
       10 If the 115VAC supply to the C/B-8QA, is not available at terminals A1, B1 and C1 trouble shoot the AC supply ASM 245805.
       11 If, with the C/B-8QA closed, the 115VAC supply is not available at the terminals A2, B2 and C2, replace the C/B-FUEL/R WING TK/PUMP2 SPLY [8QA] .
       12 Raise the front face of the C/B panel 121VU to the closed (vertical) position and secure.
       13 In the forward avionics bay remove the front cover of the contactor box 107VU AWM 930107.
       14 Do a visual inspection as specified in step (j)2_ and replace, if necessary:
         a The CNTOR-R WING TK PUMP 2 SPLY [20QA] .
         b The connector 1262VC-A and related receptacle.
       15 Remove the contactor 20QA.
       16 Use a multimeter and make sure that each of the 115VAC three phases are available at the contactor base input sockets (8, 6 and 2) ASM 282102.
       17 If the 115VAC supply to the contactor 20QA is not available, do a test of the aircraft wiring (three phase supply) between the C/B-FUEL/R WING TK/PUMP 2 SPLY (8QA) and the CNTOR-R WING TK PUMP 2 SPLY (20QA) ASM 282102.
Do the test as follows:
         a Continuity test, with a multimeter, 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.
         d Repair/replace the unserviceable wiring and connectors.
         e Install the contactor 20QA.
         f Install the the front cover of the contactor box 107VU.
       18 If the 115VAC supply is available, replace the CNTOR-R WING TK PUMP 2 SPLY [20QA] with a serviceable item.
       19 Set the R TK PUMPS 2 P/BSW (16QA) to ON (push in). This will energize the contactor 20QA and the 115VAC three phases will be supplied to the fuel pump connector 26QA-A.
       20 Use a MULTIMETER - STANDARD to do a test, to make sure that each of the 115VAC three phases are available at the connector 26QA-A ASM 282102.
       21 Set the R TK PUMPS 2 P/BSW (16QA) to OFF (release out). This will de-energize the contactor 20QA.
       22 If the 115VAC is available at the end connector 26QA-A:
         a Install the front cover of the contactor box 107VU.
         b Connect the end connector 26QA-A to the fuel pump receptacle.
         c Do the test given in Para. 3.B.(2)(b).
       23 If the 115VAC is not available at the end connector 26QA-A, do a test of the aircraft wiring (three phase supply) between the CNTOR-R WING TK PUMP 2 SPLY (20QA) and the PUMP-FUEL No. 2, R WING TK (26QA) free connector (26QA-A) ASM 282102.
NOTE: If necessary, you can divide the supply cable between the contactor 20QA and the connector 26QA-A into two sections at the connector 4010VC AWM 282104.
Do the test as follows:
         a Continuity test, with a multimeter, 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.
         d If during the wiring test in step 23_ the wiring is unserviceable, repair/replace the unserviceable wiring and connectors.
         e If the fuel pump supply cable is found to be unserviceable (where it is routed across the lower surface of the wing) 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).
         f If necessary, replace the unserviceable:
  • protective sleeve
  • wire(s)
  • connector 26QA-A.
         g 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.
         h Make sure that the length of the new supply cable when assembled, between the front face of the connector 26QA-A and the forward face of the cable guide (that shows outside the wing-skin) is 1345 mm (52.9528 in.).
         i If necessary, make a final adjustment in the length of the supply cable across the lower surface of the wing during the installation of the rear fairing.
         j Feed the surplus cable (small amount only) back up the flexible conduit to the junction box (bracket assembly) on the rear spar.
         k 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 g_ thru k_. 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.
         l Install the front cover of the contactor box 107VU.
         m Connect the connector 26QA-A to the fuel pump receptacle.
         n Do the test given in Para. 3.A.(2)(b).
   (3) If the fuel transfers:
     (a) During the fuel transfer, disconnect the free connector 28QA-A from the PRESS SW-FUEL PUMP No. 2, R WING TK (28QA) AMM 28-21-15-000-003.
     (b) If the P/BSW-FUEL/R TK PUMPS/2 (16QA) FAULT legend stays on go to step (d). If the P/BSW-FUEL/R TK PUMPS/2 (16QA) FAULT legend goes off:
NOTE: The fuel-pump fuel pressure can be measured at the sealing valve outlet using an 99A28404000000 ADAPTOR-SEQUENCE VALVE. This can be installed in place of the pressure switch 28QA AMM 28-21-45-400-003.
     (c) If the fault continues, or if no fuel pressure is shown on the gage of the ADAPTOR - SEQUENCE VALVE, make sure that these components are in the correct condition:
  • the pressure switch sealing valve
  • the pressure switch plug (banjo adaptor attachment bolt)
  • the pressure switch fuel supply pipe-line between the fuel pump canister 4QM and the pressure switch 28QA .
NOTE: The pressure switch 28QA fuel supply pipe-line is also connected to the CHECK VALVE-FUEL PUMP, R WING TK OUTR (36QM).
The check valve 36QM is in one of the primary fuel supply pipe-lines to the right wing scavenge jet pumps 68QM and 69QM.
       1 Repair/replace the components that are unserviceable.
       2 Do the test given in Para. 3.B.(2)(b).
     (d) If the P/BSW-FUEL/R TK PUMPS/2 (16QA) FAULT legend stays on, do a check of the aircraft wiring (low pressure lines) ASM 282102 between the:
  • pressure switch connector 28QA-A, pin C and the FLSCU-2 rack connector 9QJ-AA, terminal 13D
  • pressure switch connector 28QA-A, pin C and the SDAC-1 rack connector 1WV1-AD, terminal 2K
  • pressure switch connector 28QA-A, pin C and the SDAC-2 rack connector 1WV2-AD, terminal 2K
  • pressure switch connector 28QA-A, pin C and the BOARD-ANN LT TEST & INTFC connector 20LP-A, terminal 14
  • BOARD-ANN LT TEST & INTFC connector 20LP-A, terminal 13 and the P/BSW-FUEL/R TK PUMPS/2 connector 16QA-A, terminal 7.
NOTE: A short circuit to ground on one of these lines can cause:
  • a false LO PR warning to be generated within the FWC
  • the FAULT legend/lamp to come on incorrectly.
It is possible that a short circuit to ground on one of these lines can come from one of the LRUs as follows:
  • BOARD-ANN LT TEST & INTFC (20LP)
  • FLSCU-2 (9QJ)
  • SDAC-1 (1WV1)/SDAC-2 (1WV2).
     (e) Repair the unserviceable wiring and connectors.
     (f) Do the test given in Para. 3.B.(2)(b).
Subtask 28-21-00-810-053-E ** ON A/C NOT FOR ALL
A. Procedure
   (1) If a fuel low pressure indication is shown for the right wing tank fuel pump No. 2 (26QA):
  • do a fuel transfer AMM 28-21-00-710-007 use the right wing tank fuel pump No. 2 to do the fuel transfer.
   (2) If the fuel starts to transfer go to step (3). If the fuel does not start to transfer:
     (a) Set the R TK PUMPS 2 P/BSW (16QA) to OFF (release out). This will de-energize the contactor 20QA.
     (b) Before you do more steps, make sure that the wing area adjacent to the right outer fuel pump 26QA fairings and cover is not contaminated with fuel from a fuel leak or spillage.
       1 If necessary:
         a Repair all the leaks:
         b Clean the area of the fuel spillage.
     (c) Remove all the fuel pump 26QA cable fairings AMM 28-21-49-000-001 and cover assembly AMM 28-21-51-000-001.
     (d) Disconnect the supply cable end connector 26QA-A from the fuel pump receptacle.
     (e) If, in step (c) or (d), any damage can be seen on the supply cable or the aircraft structure, go to step (j) 1_.
     (f) Set the R TK PUMPS 2 P/BSW (16QA) to ON (push in). This will energize the contactor 20QA and the 115VAC three phases will be supplied to the fuel pump connector 26QA-A.
     (g) Use a MULTIMETER - STANDARD to do a test, to make sure that each of the 115VAC three phases are available at the connector 26QA-A ASM 282102.
     (h) Set the R TK PUMPS 2 P/BSW (16QA) to OFF (release out). This will de-energize the contactor 20QA.
       1 Use a multimeter to do a test, to make sure that each of the 115VAC three phases are not available at the connector 26QA-A.
NOTE: This is to make sure that the contactor 20QA does not stay in the on position (stuck/held on).
     (i) If the 115VAC three phase supply voltage measured in step (g) is correct, replace the PUMP-FUEL NO 2, R WING TK [26QA] AMM 28-21-51-000-001 and AMM 28-21-51-400-001.
     (j) If the 115VAC three phase supply voltage measured in step (g) is not correct (no voltage, incorrect voltage or a phase is missing), do all the sub-steps that follow:
       1 Clean and dry:
  • all the fuel pump cable 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).
       2 Make sure that good lighting is available.
Do a visual inspection and look for distortion (pinched or streched) damage (chafed or cut), discoloration, overheating (burnt/melted or arcing) liquid contamination, loose electrical connection or incorrect assembly, of the items that follow:
  • the electrical receptacle
  • the supply cable end connector 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.
       3 If any damage (electrical wiring, fairing or structural) is found, tell AIRBUS within 10 days.
       4 If the aircraft structure is damaged, refer to Skins and Plating - Allowable Damage, P. Block 101, SRM 572111.
       5 If necessary, replace the damaged fairings with serviceable items.
       6 If the fuel pump supply cable between the connector 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 26QA-A and the forward face of the cable guide (that shows outside the wing-skin) is 1345 mm (52.9528 in.).
         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) back up 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.
       7 In the cockpit (right rear) do a visual inspection as specified in step (j)2_ of the items that follow, replace if necessary:
         a The 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.
       8 Release the front face of the C/B panel 121VU and lower to the open (horizontal) position.
       9 Use a multimeter and make sure that each of the 115VAC three phases are available at the C/B-8QA input and output terminals ASM 282102.
       10 If the 115VAC supply to the C/B-8QA, is not available at terminals A1, B1 and C1 trouble shoot the AC supply ASM 245805.
       11 If, with the C/B-8QA closed, the 115VAC supply is not available at the terminals A2, B2 and C2, replace the C/B-FUEL/R WING TK/PUMP2 SPLY [8QA] .
       12 Raise the front face of the C/B panel 121VU to the closed (vertical) position and secure.
       13 In the forward avionics bay remove the front cover of the contactor box 107VU AWM 930107.
       14 Do a visual inspection as specified in step (j)2_ and replace, if necessary:
         a The CNTOR-R WING TK PUMP 2 SPLY [20QA] .
         b The connector 1262VC-A and related receptacle.
       15 Remove the contactor 20QA.
       16 Use a multimeter and make sure that each of the 115VAC three phases are available at the contactor base input sockets (8, 6 and 2) ASM 282102.
       17 If the 115VAC supply to the contactor 20QA is not available, do a test of the aircraft wiring (three phase supply) between the C/B-FUEL/R WING TK/PUMP 2 SPLY (8QA) and the CNTOR-R WING TK PUMP 2 SPLY (20QA) ASM 282102.
Do the test as follows:
         a Continuity test, with a multimeter, 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.
         d Repair/replace the unserviceable wiring and connectors.
         e Install the contactor 20QA.
         f Install the the front cover of the contactor box 107VU.
       18 If the 115VAC supply is available, replace the CNTOR-R WING TK PUMP 2 SPLY [20QA] with a serviceable item.
       19 Set the R TK PUMPS 2 P/BSW (16QA) to ON (push in). This will energize the contactor 20QA and the 115VAC three phases will be supplied to the fuel pump connector 26QA-A.
       20 Use a MULTIMETER - STANDARD to do a test, to make sure that each of the 115VAC three phases are available at the connector 26QA-A ASM 282102.
       21 Set the R TK PUMPS 2 P/BSW (16QA) to OFF (release out). This will de-energize the contactor 20QA.
       22 If the 115VAC is available at the end connector 26QA-A:
         a Install the front cover of the contactor box 107VU.
         b Connect the end connector 26QA-A to the fuel pump receptacle.
         c Do the test given in Para. 3.B.(2)(b).
       23 If the 115VAC is not available at the end connector 26QA-A, do a test of the aircraft wiring (three phase supply) between the CNTOR-R WING TK PUMP 2 SPLY (20QA) and the PUMP-FUEL No. 2, R WING TK (26QA) free connector (26QA-A) ASM 282102.
NOTE: If necessary, you can divide the supply cable between the contactor 20QA and the connector 26QA-A into two sections at the connector 4010VC AWM 282104.
Do the test as follows:
         a Continuity test, with a multimeter, 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.
         d If during the wiring test in step 23_ the wiring is unserviceable, repair/replace the unserviceable wiring and connectors.
         e If the fuel pump supply cable is found to be unserviceable (where it is routed across the lower surface of the wing) 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).
         f If necessary, replace the unserviceable:
  • protective sleeve
  • wire(s)
  • connector 26QA-A.
         g 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.
         h Make sure that the length of the new supply cable when assembled, between the front face of the connector 26QA-A and the forward face of the cable guide (that shows outside the wing-skin) is 1345 mm (52.9528 in.).
         i If necessary, make a final adjustment in the length of the supply cable across the lower surface of the wing during the installation of the rear fairing.
         j Feed the surplus cable (small amount only) back up the flexible conduit to the junction box (bracket assembly) on the rear spar.
         k 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 g_ thru k_. 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.
         l Install the front cover of the contactor box 107VU.
         m Connect the connector 26QA-A to the fuel pump receptacle.
         n Do the test given in Para. 3.A.(2)(b).
   (3) If the fuel transfers:
     (a) During the fuel transfer, disconnect the electrical free connector 28QA-A from the PRESS SW-FUEL PUMP No. 2, R WING TK (28QA) AMM 28-21-15-000-003.
     (b) If the P/BSW-FUEL/R TK PUMPS/2 (16QA) FAULT legend stays on go to step (d). If the P/BSW-FUEL/R TK PUMPS/2 (16QA) FAULT legend goes off:
NOTE: If an ADAPTOR - SEQUENCE VALVE (99A28404000000) is available, the fuel-pump fuel pressure can be measured at the sealing valve outlet. This can be installed in place of the pressure switch 28QA.
     (c) If the fault continues, or if no fuel pressure is shown on the gage of the ADAPTOR - SEQUENCE VALVE, make sure that these components are in the correct condition:
  • the pressure switch sealing valve
  • the pressure switch plug (banjo adaptor attachment bolt)
  • the pressure switch fuel supply pipe-line between the fuel pump canister 4QM and the pressure switch 28QA .
NOTE: The pressure switch 28QA fuel supply pipe-line is also connected to the CHECK VALVE (225QM).
The check valve 225QM is in one of the fuel supply pipe-lines that go to the right wing Integrated Drive Generator (IDG) cooling system. The fuel in this pipe-line is at ambient temperature.
       1 Repair/replace the components that are unserviceable.
       2 Do the test given in Para. 3.B.(2)(b).
     (d) If the P/BSW-FUEL/R TK PUMPS/2 (16QA) FAULT legend stays on, do a check of the aircraft wiring (low pressure lines) ASM 282102 between the:
  • pressure switch connector 28QA-A, pin C and the FLSCU-2 rack connector 9QJ-AA, terminal 13D
  • pressure switch connector 28QA-A, pin C and the SDAC-1 rack connector 1WV1-AD, terminal 2K
  • pressure switch connector 28QA-A, pin C and the SDAC-2 rack connector 1WV2-AD, terminal 2K
  • pressure switch connector 28QA-A, pin C and the BOARD-ANN LT TEST & INTFC connector 20LP-A, terminal 14
  • BOARD-ANN LT TEST & INTFC connector 20LP-A, terminal 13 and the P/BSW-FUEL/R TK PUMPS/2 connector 16QA-A, terminal 7.
NOTE: A short circuit to ground on one of these lines can cause:
  • a false LO PR warning to be generated within the FWC
  • the FAULT legend/lamp to come on incorrectly.
It is possible that a short circuit to ground on one of these lines can come from one of the LRUs as follows:
  • BOARD-ANN LT TEST & INTFC (20LP)
  • FLSCU-2 (9QJ)
  • SDAC-1 (1WV1)/SDAC-2 (1WV2).
     (e) Repair the unserviceable wiring and connectors.
     (f) Do the test given in Para. 3.B.(2)(b).
5. Close-up
Subtask 28-21-00-942-053-B
A. Close Access
   (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) Make sure that the fuel pump supply cable end connector 26QA-A is connected to the fuel pump electrical receptacle.
   (3) Install the fuel pump cover assembly AMM 28-21-51-400-001.
   (4) Install the fuel pump fairings AMM 28-21-49-400-001. Make sure that the fuel pump supply cable does not get caught under the fairings.
   (5) Remove the ground support and maintenance equipment, the special and standard tools and all other items.
[Rev.8 from Aug 2018] 2026.04.04 04:28:34 UTC
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