Installation of the Fuel Pumps

TASK 28-21-51-400-001-A
Installation of the Fuel Pumps

WARNING: THIS PROCEDURE USES A FUEL SYSTEM ITEM THAT IS IN A CATEGORY KNOWN AS A CRITICAL DESIGN CONFIGURATION CONTROL LIMITATION (CDCCL). CDCCL IDENTIFIES AN ITEM THAT CAN BE THE SOURCE OF A POSSIBLE FUEL TANK IGNITION. YOU MUST KEEP ALL CDCCL ITEMS IN THE APPROVED CONFIGURATION. DAMAGE, WEAR OR CHANGES TO A CDCCL ITEM CAN CAUSE A POSSIBLE FUEL TANK EXPLOSION.

WARNING: BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.

WARNING: MAKE SURE THAT THE FLIGHT CONTROL SAFETY-LOCKS AND THE WARNING NOTICES ARE IN POSITION.

WARNING: MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. THIS WILL PREVENT UNWANTED MOVEMENT OF THE LANDING GEAR, AND THUS POSSIBLE INJURY TO PERSONS AND DAMAGE TO THE AIRCRAFT AND/OR EQUIPMENT.

CAUTION: WHEN YOU REPLACE THE FUEL PUMP(S) 21QA(26QA) OR 25QA(22QA), EXAMINE THE APPLICABLE LANDING LIGHT ASSEMBLY FOR SIGNS OF FUEL CONTAMINATION. IF YOU FIND FUEL CONTAMINATION, EXAMINE THE ITEMS THAT FOLLOW FOR SIGNS OF FUEL LEAKAGE:

THE FUEL PUMP(S) 21QA(26QA) OR 25QA(22QA)
THE WATER DRAIN VALVE 25QM(26QM) DIRECTLY FORWARD OF THE LANDING LIGHT ASSEMBLY.

REFER TO AMM 28-11-00-06 FOR LEAKAGE LIMITS AND REPAIR AS NECESSARY. IF YOU DO NOT REPAIR THE LEAK, NO PERSONS MUST OPERATE THE APPLICABLE LANDING LIGHT UNTIL:

THE LEAK IS REPAIRED
THE LANDING LIGHT ASSEMBLY IS REPLACED.

FIN: 21QA
FIN: 22QA
FIN: 25QA
FIN: 26QA

1. Reason for the Job
Self explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment

REFERENCE	QTY	DESIGNATION
No specific	1	ACCESS PLATFORM 3M (10 FT)
No specific	AR	CAP - BLANKING
No specific	AR	SAFETY BARRIER(S)
No specific	Torque wrench: range to between 110 and 90 lbf.in (1.24 and 1.02 m.daN )
No specific	Torque wrench: range to between 0.25 and 0.20 m.daN (22.12 and 17.70 lbf.in )
No specific	Torque wrench: range to between 0.75 and 0.61 m.daN (66.37 and 53.98 lbf.in )
558-1-05903	1	EXTRACTOR - FUEL PUMP
558-1-05903-002	1	EXTRACTOR - FUEL PUMP

B. Consumable Materials

REFERENCE	DESIGNATION
(Material No.01ABA1)	Turbine Fuel-- Kerosene -
(Material No.03FAB1)	Mineral Oil base Grease-- Vaseline or Petrolatum -
(Material No.06LCG9)	Non Hardening Jointing Putty-Medium Temp. Area - -
(Material No.08BAA9)	Non Aqueous Cleaner-General - -
(Material No.14QFB1)	Wire-Locking Dia: 0.8 mm CRES Nickel Alloy -
(Material No.14SBA1)	Textile-Lint free Cotton -

C. Expendable Parts

FIG.ITEM	DESIGNATION	IPC-CSN
1	O-RING	AIPC 28-21-51-01-010
10	O-RING	AIPC 28-21-51-01-020
11	O-RING	AIPC 28-21-51-01-020
12	O-RING	AIPC 28-21-51-01-020
13	O-RING	AIPC 28-21-51-01-020
11	O-RING	AIPC 28-21-51-01-100
9	O-RING	AIPC 28-21-51-01-100

D. Referenced Information

REFERENCE	DESIGNATION
TASK 12-11-28-650-003-A	Pressure Refuel with Automatic Control
TASK 20-28-00-720-006-A	Check of the Electrical Bonding of the Fluid Systems
TASK 24-41-00-861-002-A	Energize the Aircraft Electrical Circuits from the External Power
TASK 24-41-00-861-002-A-01	Energize the Aircraft Electrical Circuits from the APU
TASK 24-41-00-861-002-A-02	Energize the Aircraft Electrical Circuits from Engine 1(2)
TASK 24-41-00-862-002-A	De-energize the Aircraft Electrical Circuits Supplied from the External Power
TASK 24-41-00-862-002-A-01	De-energize the Aircraft Electrical Circuits Supplied from the APU
TASK 24-41-00-862-002-A-02	De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)
TASK 28-00-00-910-001-A	Fuel Safety Procedures
TASK 28-25-00-650-001-A	Pressure Defuel
TASK 28-25-00-869-001-A	Fuel Transfer
TASK 33-42-11-000-001-A	Removal of the Landing Light
ESPM 205120
SRM 517300	(for corrective action)
Fuel Pump 21QA(26QA) and 25QA(22QA) ** ON A/C NOT FOR ALL
Fuel Pump Extractor
Fuel Pump 21QA(26QA) and 25QA(22QA) ** ON A/C NOT FOR ALL

3. Job Set-up
Subtask 28-21-51-941-059-A

A. Safety Precautions

WARNING: OBEY THE FUEL SAFETY PROCEDURES.

(1) You must obey the fuel safety procedures when you do work on the fuel system (Ref. AMM TASK 28-00-00-910-001).
(2) As necessary, use the applicable SAFETY BARRIERS, specified by the operator's instructions and your local regulations.
(3) Make sure that the ACCESS PLATFORM 3M (10 FT) is below the applicable zone 540(640).

Subtask 28-21-51-865-102-A

B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C ALL
FOR FIN: 25QA (PUMPFUEL NO 2, L WING TK) FOR FIN: 21QA (PUMPFUEL NO 1, L WING TK)
121VU	FUEL/L WING TK/PUMP2 SPLY	7QA	N26
121VU	FUEL/L WING TK/PUMP1 SPLY	1QA	N23
122VU	LIGHTING/LANDING LT/L/CTL	3LB	T05
122VU	LIGHTING/LANDING LT/L/SPLY	1LB	T04
123VU	L WING TK/PUMP 1/STBY SPLY	11QA	AD12
FOR FIN: 26QA (PUMPFUEL NO 2, R WING TK) FOR FIN: 22QA (PUMPFUEL NO 1, R WING TK)
121VU	FUEL/R WING TK/PUMP2 SPLY	8QA	Q26
121VU	FUEL/R WING TK/PUMP1 SPLY	2QA	Q23
122VU	LIGHTING/LANDING LT/R/CTL	4LB	T07
122VU	LIGHTING/LANDING LT/R/SPLY	2LB	T06
123VU	R WING TK/PUMP 1/STBY SPLY	12QA	AE12

4. Procedure

WARNING: WHEN YOU OPERATE THE FUEL PUMPS DURING A MAINTENANCE PROCEDURE, A MAINTENANCE PERSON MUST BE IN THE COCKPIT. THIS PERSON MUST STOP THE PUMPS WHEN THE LOW PRESSURE FAULT LIGHT(S) (ON PANEL 40VU) COME ON, TO PREVENT OPERATION OF THE PUMPS(S) WITHOUT FUEL ('DRY RUNNING'). OPERATION OF THE PUMPS WITHOUT FUEL CAN CAUSE A FIRE.

Subtask 28-21-51-420-053-A ** ON A/C NOT FOR ALL

A. Preparation for Installation
(1) Clean the component interfaces and the adjacent areas with a clean Textile-Lint free Cotton - (Material No.14SBA1) made moist with Non Aqueous Cleaner-General - - (Material No.08BAA9) .
(2) Make sure that the parts retained from the removed component are clean and in the correct condition.
(3) Do an inspection of the component interfaces and the adjacent area.
(4) Lubricate the new parts that follow with Turbine Fuel-- Kerosene - (Material No.01ABA1) or Mineral Oil base Grease-- Vaseline or Petrolatum - (Material No.03FAB1) :

(5) Install the new O-rings (10), (11) and (1) on the fuel pump (2).
(6) If you install the fuel pump (2) that you removed:
(a) Install the new O-ring (9) on the drain bolt (8).
(b) Install the drain bolt (8).
(c) TORQUE the drain bolt (8):
1 For the part number 568-2-27275-000, TORQUE the drain bolt (8) to between 0.25 and 0.20 m.daN (22.12 and 17.70 lbf.in )

WARNING: USE PROTECTIVE GOGGLES AND GLOVES WHEN YOU REMOVE OR INSTALL LOCKWIRE. EACH TIME YOU CUT LOCKWIRE, REMOVE AND DISCARD IT IMMEDIATELY. LOOSE LOCKWIRE CAN CUT YOU OR MAKE YOU BLIND, AND/OR CAN CAUSE DAMAGE.

2 For the part number AN814-3JL, TORQUE the drain bolt (8) to between 0.75 and 0.61 m.daN (66.37 and 53.98 lbf.in )

Safety the drain bolt (8) with 14QFB1Wire-Locking Dia: 0.8 mm CRES Nickel Alloy -.

(7) Lubricate the fuel pump (2), the slide valve and the pump canister with Turbine Fuel-- Kerosene - (Material No.01ABA1) .

Subtask 28-21-51-420-054-A ** ON A/C NOT FOR ALL

B. Installation of the Fuel Pumps 21QA(26QA) and 25QA(22QA)

CAUTION: MAKE SURE THAT THE RETAINER BAULK ARM STAYS IN THE UNLOCKED (OPEN) POSITION. THIS WILL PREVENT ACCIDENTAL MOVEMENT OF THE SLIDE-VALVE WHICH CAN CAUSE LEAKAGE OF FUEL FROM THE FUEL TANK.

(1) Make sure that the baulk-arm (13) (on the retaining pin and spring assembly) is in the unlocked (open) position. This gives clearance for the fuel pump (2) to be installed into the slide valve.
(2) Make sure that the electrical receptacle (14) is in the same position that you wrote down.
(3) Install the 558-1-05903-002 EXTRACTOR - FUEL PUMP or the 558-1-05903 EXTRACTOR - FUEL PUMP on the applicable fuel pump (2) as follows:
(a) Install the threaded rods (22) through the tooling holes (12) (in the pump flange) and fully into the threaded holes in the slide valve.
(4) Align and install the fuel pump (2) into the slide valve.
(5) Use the 558-1-05903-002 EXTRACTOR - FUEL PUMP to turn the fuel pump (2) and the slide valve clockwise. Align the stop pin in the slide valve flange with the stop pin locating hole in the canister.
(6) Make sure that the slot in the flange of the fuel pump (2) engages with the retaining pin and spring assembly.
(7) Turn the baulk-arm (13) on the retaining pin and spring assembly to the locked (closed) position.
(8) Remove the 558-1-05903-002 EXTRACTOR - FUEL PUMP from the fuel pump (2) and the slide valve.
(9) Push the fuel pump (2) and the slide-valve up and fully into the fuel pump canister.
(10) Install the bolts (3).
(11) TORQUE the bolts (3) to between 110 and 90 lbf.in (1.24 and 1.02 m.daN )

.
(12) Do the steps that follow:
(a) Do a visual inspection of the electrical harness you can see, for signs of wear and electrical arcing. If you find damage, replace the electrical harness.
(b) Do a visual inspection of the aircraft structure (in the area adjacent to the electrical harness), for signs of damage caused by arcing. If you find damage refer to the SRM 517300 for the correct repair procedure.
(13) Remove the blanking caps from the electrical connector and receptacle (14).
(14) Connect the electrical connector to the electrical receptacle (14).

WARNING: THIS INSTRUCTION IS APPLICABLE TO A CRITICAL DESIGN CONFIGURATION CONTROL LIMITATION (CDCCL) ITEM. CAREFULLY OBEY ALL GIVEN INSTRUCTIONS WHEN YOU DO THIS STEP. IF YOU DO NOT OBEY THESE INSTRUCTIONS, A DANGEROUS CONDITION CAN OCCUR THAT CAN CAUSE A POSSIBLE FUEL TANK EXPLOSION.

(a) Do a check of the electrical bonding between the fuel pump (2) and the wing structure (Ref. AMM TASK 20-28-00-720-006).
(15) Apply sealant on the bolts (3) ESPM 205120.

Subtask 28-21-51-420-053-B ** ON A/C NOT FOR ALL

C. Preparation for Installation
(1) Clean the component interfaces and the adjacent areas with a clean Textile-Lint free Cotton - (Material No.14SBA1) made moist with Non Aqueous Cleaner-General - - (Material No.08BAA9) .
(2) Make sure that the parts retained from the removed component are clean and in the correct condition.
(3) Do an inspection of the component interfaces and the adjacent area.
(4) Lubricate the new parts that follow with Turbine Fuel-- Kerosene - (Material No.01ABA1) or Mineral Oil base Grease-- Vaseline or Petrolatum - (Material No.03FAB1) :

(5) Install the new O-rings (12), (13) and (1) on the fuel pump (2).
(6) If you install the fuel pump (2) that you removed:
(a) Install the new O-ring (11) on the drain bolt (10).
(b) Install the drain bolt (10).
(c) TORQUE the drain bolt (10):
1 For the part number 568-2-27275-000, TORQUE the drain bolt (10) to between 0.25 and 0.20 m.daN (22.12 and 17.70 lbf.in )

.
2 For the part number AN814-3JL, TORQUE the drain bolt (10) to between 0.75 and 0.61 m.daN (66.37 and 53.98 lbf.in )

(d) Safety the drain bolt (10) with 14QFB1Wire-Locking Dia: 0.8 mm CRES Nickel Alloy -.
(7) Lubricate the fuel pump (2), the slide valve and the pump canister with Turbine Fuel-- Kerosene - (Material No.01ABA1) .

Subtask 28-21-51-420-054-C ** ON A/C NOT FOR ALL

D. Installation of the Fuel Pumps 21QA (26QA) and 25QA (22QA)

CAUTION: MAKE SURE THAT THE RETAINER BAULK ARM STAYS IN THE UNLOCKED (OPEN) POSITION. THIS WILL PREVENT ACCIDENTAL MOVEMENT OF THE SLIDE-VALVE WHICH CAN CAUSE LEAKAGE OF FUEL FROM THE FUEL TANK.

(1) Make sure that the baulk-arm (14) (on the retaining pin and spring assembly) is in the unlocked (open) position:

This gives clearance for the fuel pump (2) to be installed into the slide valve.

(2) Make sure that the electrical receptacle (15) is in the same position that you recorded.
(3) Install the 558-1-05903-002 EXTRACTOR - FUEL PUMP or the 558-1-05903 EXTRACTOR - FUEL PUMP on the applicable fuel pump (2) as follows:
(a) Install the threaded rods (22) through the tooling holes (3) (in the pump flange) and fully into the threaded holes in the slide valve.
(4) Align and install the fuel pump (2) into the slide valve.
(5) Use the 558-1-05903-002 EXTRACTOR - FUEL PUMP to turn the fuel pump (2) and the slide valve clockwise:

Align the stop pin in the slide valve flange with the stop pin locating hole in the canister.

(6) Make sure that the slot in the flange of the fuel pump (2) engages with the retaining pin and spring assembly.
(7) Turn the baulk-arm (14) on the retaining pin and spring assembly to the locked (closed) position.
(8) Remove the 558-1-05903-002 EXTRACTOR - FUEL PUMP from the fuel pump (2) and the slide valve.
(9) Push the fuel pump (2) and the slide-valve up and fully into the fuel pump canister.
(10) Install the bolts (4).
(11) TORQUE the bolts (4) to between 110 and 90 lbf.in (1.24 and 1.02 m.daN )

.
(12) Do the steps that follow:
(a) Do a visual inspection of the electrical harness you can see, for signs of wear and electrical arcing:

If you find damage, replace the electrical harness.

(b) Do a visual inspection of the aircraft structure (in the area adjacent to the electrical harness), for signs of damage caused by arcing:

If you find damage, refer to the SRM 517300 for the correct repair procedure.

(13) Remove the CAP - BLANKING from the electrical connector and receptacle (15).
(14) Connect the electrical connector to the electrical receptacle (15).

(a) Do a check of the electrical bonding between the fuel pump (2) and the wing structure (Ref. AMM TASK 20-28-00-720-006).
(15) Apply sealant on the bolts (4) ESPM 205120.

Subtask 28-21-51-860-050-A

E. Aircraft Maintenance Configuration
(1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002).
(2) Refuel the applicable wing tank to a minimum of 1000 kg (2204.6220 lb), (Ref. AMM TASK 12-11-28-650-003).

Subtask 28-21-51-790-054-A

F. Leak Test
(1) Examine the fuel pump (2), the slide valve and the fuel pump canister for fuel leaks.
(2) If signs of fuel leakage are found, examine the applicable landing light assembly for fuel contamination (Ref. AMM TASK 33-42-11-000-001).

Subtask 28-21-51-865-118-A

G. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C ALL
FOR FIN: 25QA (PUMPFUEL NO 2, L WING TK) FOR FIN: 21QA (PUMPFUEL NO 1, L WING TK)
121VU	FUEL/L WING TK/PUMP2 SPLY	7QA	N26
121VU	FUEL/L WING TK/PUMP1 SPLY	1QA	N23
123VU	L WING TK/PUMP 1/STBY SPLY	11QA	AD12
FOR FIN: 26QA (PUMPFUEL NO 2, R WING TK) FOR FIN: 22QA (PUMPFUEL NO 1, R WING TK)
121VU	FUEL/R WING TK/PUMP2 SPLY	8QA	Q26
121VU	FUEL/R WING TK/PUMP1 SPLY	2QA	Q23
123VU	R WING TK/PUMP 1/STBY SPLY	12QA	AE12

Subtask 28-21-51-710-051-A

H. Operational Test
(1) Do this test:

ACTION	RESULT
On panel 40VU:	On panel 40VU:
1.Start the applicable fuel pump:
for 21QA, push (in) the L TK PUMPS 1 pushbutton switch (P/BSW)	the P/BSW OFF light goes off the L TK PUMPS 1 P/BSW FAULT light comes on momentarily
for 25QA, push in the L TK PUMPS 2 P/BSW	the P/BSW OFF light goes off the L TK PUMPS 2 P/BSW FAULT light comes on momentarily
for 22QA, push in the R TK PUMPS 1 P/BSW	the P/BSW OFF light goes off the R TK PUMPS 1 P/BSW FAULT light comes on momentarily
for 26QA, push in the R TK PUMPS 2 P/BSW.	the P/BSW OFF light goes off the R TK PUMPS 2 P/BSW FAULT light comes on momentarily.
2.Stop the applicable main fuel pump:
for 21QA, release (out) the L TK PUMPS 1 P/BSW	the P/BSW OFF light comes on
for 25QA, release (out) the L TK PUMPS 2 P/BSW	the P/BSW OFF light comes on
for 22QA, release (out) the R TK PUMPS 1 P/BSW	the P/BSW OFF light comes on
for 26QA, release (out) the R TK PUMPS 2 P/BSW.	the P/BSW OFF light comes on.

Subtask 28-21-51-420-055-A ** ON A/C NOT FOR ALL

I. Installation of the Fuel Pump (Completion)
(1) If applicable, use a clean Textile-Lint free Cotton - (Material No.14SBA1) made moist with Non Aqueous Cleaner-General - - (Material No.08BAA9) to clean all the remaining sealant from

The front fairing (7)
The under-wing skin interface.

(2) Install the front fairing (7) and the cover-plate (5) assembly as follows:

NOTE: Sealant is not used between the front fairing (7) and the under-wing skin.

(a) Install the front fairing (7) and the cover-plate (5) assembly. Make sure that the fuel pump cables are not caught.
(b) Hold the front fairing (7) and the cover-plate (5) assembly in position and install it with bolts (6).
(c) TORQUE tighten the bolts (6) to between 110 and 90 lbf.in (1.24 and 1.02 m.daN )

Subtask 28-21-51-420-055-B ** ON A/C NOT FOR ALL

The front fairing (9)
The under-wing skin interface.

(2) Install the front fairing (9) and the cover-plate (6) assembly as follows:

NOTE: Sealant is not used between the front fairing (9) and the under-wing skin.

(a) Install the front fairing (9) and the cover-plate (6) assembly.
(b) Make sure that the fuel pump cables are not caught.
(c) Hold the front fairing (9) and the cover-plate (6) assembly in position.
(d) Apply Non Hardening Jointing Putty-Medium Temp. Area - - (Material No.06LCG9) to:

The mating surface of the special washers (8) and the cover-plate (6) assembly
The bores in the cover-plate (6) assembly
Below the head of the bolts (7)
The plain shanks of the bolts (7).

(e) Install the bolts (7) and the special washers (8).
(f) TORQUE the bolts (7) to between 110 and 90 lbf.in (1.24 and 1.02 m.daN )

5. Close-up
Subtask 28-21-51-860-051-A

A. Aircraft Maintenance Configuration
(1) Refuel, defuel or transfer fuel as necessary (Ref. AMM TASK 12-11-28-650-003), (Ref. AMM TASK 28-25-00-650-001) or (Ref. AMM TASK 28-25-00-869-001).
(2) De-energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-862-002).

Subtask 28-21-51-865-142-A

B. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C ALL
122VU	LIGHTING/LANDING LT/R/CTL	4LB	T07
122VU	LIGHTING/LANDING LT/R/SPLY	2LB	T06
122VU	LIGHTING/LANDING LT/L/CTL	3LB	T05
122VU	LIGHTING/LANDING LT/L/SPLY	1LB	T04

Subtask 28-21-51-942-051-A

C. Removal of Equipment
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Remove the safety barriers.
(3) Remove the access platform(s).
(4) Remove the WARNING NOTICE(S).
(5) Remove the ground support and maintenance equipment, the special and standard tools and all other items.

[Rev.10 from 2021] 2026.04.02 07:02:46 UTC