W DOC AIRBUS | TSM A320F

Fuel - L(R) Wing Tank Pumps 1, Power Supply (Smoke) - C/B-11QA(12QA) Tripped

TASK 28-21-00-810-830-A
Fuel - L(R) Wing Tank Pumps 1, Power Supply (Smoke) - C/B-11QA(12QA) Tripped

WARNING: OBEY THE FUEL SAFETY PROCEDURES.
1. Possible Causes
  • C/B-L WING TK/PUMP 1/STBY SPLY [11QA]
  • C/B-R WING TK/PUMP 1/STBY SPLY [12QA]
  • CT-AC, 1 [42XU3]
  • CNTOR-L WING TK STBY SPLY, PUMP 1 [53QA]
  • CNTOR-R WING TK STBY SPLY, PUMP 1 [54QA]
  • aircraft wiring (three phase electrical standby supply)
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 28-21-00-810-801-A
Fuel Pumps - Left Wing Tank Fuel Pump No. 1 (Outer) 21QA System Malfunction
TSM TASK 28-21-00-810-802-A
Fuel Pumps - Right Wing Tank Fuel Pump No. 1 (Inner) 22QA System Malfunction
TSM TASK 28-21-00-810-827-A
Fuel - L(R) Wing Tank Pumps 1, Power Supply (Normal) - C/B-1QA(2QA) Tripped
AMM 24-22-17-000-001
Removal of the AC Current Transformers
AMM 24-22-17-400-001
Installation of the AC Current Transformers
AMM 24-41-00-861-002
Energize the Aircraft Electrical Circuits from the External Power
ASM 282101
AMM 28-21-49-400-001
Installation of the Fuel Pump Fairings
AMM 28-21-51-400-001
Installation of the Fuel Pumps
3. Fault Confirmation
Subtask 28-21-00-865-058-A
A. Table of the circuit breakers used in this procedure:
PANELDESIGNATIONFINLOCATION
** ON A/C ALL
121VUFUEL/L WING TK/PUMP1 SPLY1QAN23
121VUFUEL/R WING TK/PUMP1 SPLY2QAQ23
123VUL WING TK/PUMP 1/STBY SPLY11QAAD12
123VUR WING TK/PUMP 1/STBY SPLY12QAAE12
Subtask 28-21-00-710-079-A
B. Test
   (1) Not applicable.
   (2) Do not close (reset) the C/Bs given in the Table.
4. Fault Isolation
Subtask 28-21-00-810-079-B
A. Procedure
   (1) Make sure that the L(R) TK PUMPS 1 P/BSW 13QA(14QA) shows OFF (released out).
   (2) Make sure that the EMER ELEC PWR/GEN 1 LINE P/BSW (13XU) shows OFF (released out).
   (3) Examine these C/Bs:
  • FUEL/L WING TK/PUMP 1 SPLY 1QA (FUEL/R WING TK/PUMP 1 SPLY 2QA)
  • L WING TK/PUMP 1 STBY SPLY 11QA (R WING TK/PUMP 1 STBY SPLY 12QA).
   (4) If the left wing tank fuel pump No. 1 C/Bs 1QA and 11QA have opened (tripped), do these Tasks:
     (a) Fuel Pumps - C/B-FUEL/L(R) WING TK/PUMP 1 SPLY 1QA(2QA) Tripped (Ref. TSM TASK 28-21-00-810-827).
     (b) Fuel Pumps - Left Wing Tank Pump-Fuel No 1 System Failure (Normal Supply) (Ref. TSM TASK 28-21-00-810-801).
   (5) If the right wing tank fuel pump No. 1 C/Bs 2QA and 12QA have opened (tripped), do these Tasks:
     (a) Fuel Pumps - C/B-FUEL/L(R) WING TK/PUMP 1 SPLY 1QA(2QA) Tripped (Ref. TSM TASK 28-21-00-810-827).
     (b) Fuel Pumps - Right Wing Tank Pump-Fuel No 1 System Failure (Normal Supply) (Ref. TSM TASK 28-21-00-810-802).
   (6) If the left(right) wing tank fuel pump No. 1 C/B-11QA(12QA) has opened (tripped):
     (a) Do a check of, and replace if necessary:
       1 The C/B- C/B-L WING TK/PUMP 1/STBY SPLY [11QA] (C/B- C/B-R WING TK/PUMP 1/STBY SPLY [12QA] ).
       2 The CT-AC, 1 [42XU3] AMM 24-22-17-000-001 and AMM 24-22-17-400-001.
       3 The CNTOR-L WING TK STBY SPLY, PUMP 1 [53QA] ( CNTOR-R WING TK STBY SPLY, PUMP 1 [54QA] ).
     (b) Use a MULTIMETER - STANDARD and do an electrical check ASM 282101 of the aircraft wiring (three phase electrical standby supply) between the:
  • C/B-L(R) WING TK/PUMP 1/STBY SPLY 11QA(12QA) and the CNTOR-L(R) WING TK STBY SPLY, PUMP 1 53QA(54QA).
NOTE: The wiring from 11QA and 12QA goes through the same Current Transformer (CT)-Alternating Current (AC) (42XU3), AMM 24-22-17-000-001. It is a three hole CT and contains three toroidal transformers.
One phase line (from each of the fuel pump three phase electrical stand-by supplies) goes through one of the three different toroidal transformers.
Two fuel pump related lines of the same phase, therefore, go through each toroidal transformer in the same direction.
     (c) Repair the unserviceable wiring and connectors.
     (d) Close (set) the C/B-11QA(12QA).
   (7) Energize the Aircraft Electrical Circuits from Engine 1 AMM 24-41-00-861-002.
   (8) If the C/B-11QA(12QA) opens, when the FAULT legend of the GEN 1 pushbutton switch goes off, do the steps in Para. 4.A.(6).
   (9) If the C/B-11QA(12QA) does not open:
     (a) Connect the fuel pump supply cable end connector 21QA-A(22QA-A) to the fuel pump receptacle.
     (b) Do the applicable/related AMM/TSM Task.
5. Close-up
Subtask 28-21-00-942-057-A
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 21QA-A (22QA-A) is connected to the fuel pump electrical receptacle.
   (3) Make sure that the fuel pump cover assembly is installed AMM 28-21-51-400-001.
   (4) Make sure that the fuel pump fairings are installed AMM 28-21-49-400-001.
Make sure that the fuel pump supply cable:
  • is held correctly by the tape hooks (post SB 24-1070)
  • does not get caught under the fairings (this is very important in the area adjacent to the fairing attachment bolts).
   (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 04:28:38 UTC
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