Fuel, Main Transfer System - Control Valve 1 (Left) Does Not Close

TASK 28-26-00-810-804-A
Fuel, Main Transfer System - Control Valve 1 (Left) Does Not Close

WARNING: OBEY THE FUEL SAFETY PROCEDURES.

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

ACTUATOR-JET PUMP 1 CTL VALVE,CTR TK or ACTUATOR-JET PUMP 1 CTL VALVE, CTR TK [11QL]
FUEL CONTROL VALVE-JET PUMP, L WING TK [153QM]
RELAY-AUTO CTL No1 CTR (7QL)
P/BSW-FUEL/CTR TK/L XFR (5QL)
aircraft wiring
P/BSW-IND, CTR TK XFR CTL [4QL]

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
ESPM 2045110
ESPM 2052210
ESPM 2052220
ESPM 2053210
AMM 28-26-00-710-001	Operational Test of the Main Transfer System
ASM 282601
AWM 282601
ASM 282602
AIPC 28260802
AMM 28-26-43-000-001	Removal of the Jet Pump Fuel Control Valve
AMM 28-26-43-400-001	Installation of the Jet Pump Fuel Control Valve
AMM 28-26-51-000-001	Removal of the Fuel Control-Valve Actuator
AMM 28-26-51-400-001	Installation of the Fuel Control-Valve Actuator
AMM 28-46-34-000-001	Removal of the Fuel-Level Sensing Control-Unit (FLSCU)
AWM 930040
AWM 930092

3. Fault Confirmation
Subtask 28-26-00-710-053-A ** ON A/C NOT FOR ALL

A. Test
(1) Do the Operational Test of the Main Transfer System (for the left wing and the center-tank left side) AMM 28-26-00-710-001.
(a) At the panel 40VU, make sure that:
1 The P/BSW-FUEL/CTR TK/MODE SELECT/AUTO (4QL) is set to MAN (released out).
2 The P/BSW-FUEL/CTR TK/L XFR (5QL) is set to OFF (released out) to close the transfer valve.
(b) At the lower ECAM DU (FUEL system display page), make sure the actuator 11QL symbol shows crossline - amber.

NOTE: This shows the transfer valve position disagrees with the switch position (closed).

(c) Get access to the actuator 11QL AMM 28-26-51-000-001.
1 Make sure the actuator 11QL see/feel indicator (on the actuator body) shows in the (incorrect) open position.
(2) If (during the operational test and as given above) the actuator 11QL:

is found to be closed, no more troubleshooting work steps are necessary
does not go to the closed position, do Para. 4.A.

4. Fault Isolation
Subtask 28-26-00-810-053-A ** ON A/C NOT FOR ALL

A. Procedure
(1) At the actuator 11QL, disconnect the connector 11QL-A.
(2) Do a voltage check, with a MULTIMETER - STANDARD, to see if 28VDC is available between pin B (+ve) and pin E (ground) of the connector 11QL-A ASM 282601.
(a) If the 28VDC:

is available, do step (3)
is not available, do step (4).

(3) Replace the ACTUATOR-JET PUMP 1 CTL VALVE,CTR TK or ACTUATOR-JET PUMP 1 CTL VALVE, CTR TK [11QL] as follows:
(a) Remove the actuator 11QL AMM 28-26-51-000-001.
(b) Do a check of the (ball) valve and drive shaft assembly 153QM as follows:
1 Make sure that the shaft turns:

freely (with no more than 20 lbf.in (0.23 m.daN) of torque necessary to turn the shaft in each direction)
through a complete 90 degrees of movement in each direction.

NOTE: If the shaft does not turn freely the high torque load is applied to the electrically operated actuator 11QL. This can cause the actuator 11QL to become unserviceable again and again (prematurely and repeatedly). Thus it is important that the checks given in this step are fully done and that the valve and drive shaft assembly 153QM are serviceable.

2 If necessary, replace the FUEL CONTROL VALVE-JET PUMP, L WING TK [153QM] AMM 28-26-43-000-001 and AMM 28-26-43-400-001.
(c) Install a serviceable actuator 11QL AMM 28-26-51-400-001.
(d) Do the test given in Para. 3.A.
(4) If the 28VDC is not available at pin B of the actuator connector 11QL-A:
(a) Get access to panel shelf - 92VU AMM 28-46-34-000-001 AIPC 28260802 AWM 930092.
(b) Interchange the relay-7QL with the adjacent relay-8QL (which is an item of the right-side main transfer circuit QL).
(c) Do all of the operational test given in Para. 3.A. (test the transfer systems on each side of the aircraft).
1 If the (initial) fault symptom:

stays the same, do step (5)
changes from the left to the right side, replace the initial RELAY-AUTO CTL No1 CTR (7QL) ESPM 2053210.

(d) Do the test given in Para. 3.A.
(5) If the fault continues:
(a) Get access to the cockpit overhead panel 40VU AWM 930040.
(b) Do a check of ASM 282601 and replace, if necessary, the items that follow ESPM 2053210:
1 The P/BSW-FUEL/CTR TK/L XFR (5QL).
2 The diode between terminals 13 and 28 that is part of the diode module 2408VD.
(c) Do the test given in Para. 3.A.
(6) If the fault continues:
(a) Do a wiring check of the aircraft wiring ASM 282601 between:

the pin B, of the cable connector 11QL-A and the terminal B1, of the relay-7QL
the pin B, of the cable connector 11QL-A and the terminal 13, of the diode 2408VD
the terminal B2, of the relay-7QL and the terminal B1, of the P/BSW-5QL
the terminal B3, of the P/BSW-5QL and the C/B-1QL
the terminal 28, of the diode 2408VD and the terminal B2, of the P/BSW-5QL
the terminal B2, of the P/BSW-5QL and the terminal 15E, of the SDAC-1 (2) rack connector 1WV1-AA (1WV2-AA)
the pin E, of the cable connector 11QL-A and the ground point 6743VN AWM 282601.

NOTE: A wiring check means that you test the wire(s) specified as follows:

for continuity ESPM 2052210
for a short circuit to ground ESPM 2052220
for a short circuit to adjacent wires ESPM 2052220.

(b) Repair all the unserviceable wiring and connectors ESPM 2053210.
(c) Do the test given in Para. 3.A.
(7) If the fault continues:
(a) Get access to the cockpit overhead panel 40VU AWM 930040.
(b) Do a check of the P/BSW-IND, CTR TK XFR CTL [4QL] ASM 282602 and, if necessary, replace it ESPM 2045110.
(c) Do the test given in Para. 3.A.

[Rev.8 from Aug 2018] 2026.04.04 04:39:40 UTC