Functional Test of the Check Valves of the ACT

TASK 28-28-00-720-006-A
Functional Test of the Check Valves of the ACT

WARNING: OBEY THE FUEL SAFETY PROCEDURES.

FIN: 231QM1 ** ON A/C NOT FOR ALL

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	CAP - BLANKING
No specific	AR	GAGE - ABSOLUTE PRESSURE, DIGITAL, 0.001 BAR ACCURACY
No specific	1	GENERATOR - GROUND PRESSURE MINI. 100 MB
No specific	AR	SAFETY CLIP - CIRCUIT BREAKER
No specific	1	WARNING NOTICE(S)
No specific	Torque wrench: range to between 4.3 and 3.9 m.daN (31.71 and 28.76 lbf.ft )

B. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
152FW, 231JH

C. Referenced Information

REFERENCE	DESIGNATION
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 25-55-11-000-003-A	Removal of the Sidewall Panels in the Aft Cargo Compartment - FR47/FR59
TASK 25-55-11-400-003-A	Installation of the Sidewall Panels in the Aft Cargo Compartment - FR47/FR59
TASK 28-00-00-910-001-A	Fuel Safety Procedures
TASK 28-25-00-650-001-A	Pressure Defuel
TASK 32-12-00-010-001-A	Open the Main Gear Doors for Access
TASK 32-12-00-410-001-A	Close the Main Gear Doors after Access
TASK 53-22-12-000-001-A	Removal of the Cabin Floor Panels
TASK 53-22-12-400-001-A	Installation of the Cabin Floor Panels
Access to the ACT Cavity Drain-Line (Forward ACT)
Access to the ACT Cavity Drain-Line (Aft ACT)
Test Arrangement ACT
Test Arrangement ACT
Pressure Hose of the ACT FWD

3. Job Set-up
Subtask 28-28-00-860-232-A ** ON A/C NOT FOR ALL

A. Aircraft Maintenance Configuration
(1) Obey the fuel safety procedure (Ref. AMM TASK 28-00-00-910-001).
(2) Energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-861-002).
(3) Make sure that the fuel is removed from the ACT(s) (Ref. AMM TASK 28-25-00-650-001).
(4) Put a WARNING NOTICE(S) is(are) in position on these panels, to tell persons not to operate the refuel/defuel system:

Refuel/defuel panel 800VU 801VU,
Fueling panel 40VU,
Fueling panel 28VU.

Subtask 28-28-00-010-119-C ** ON A/C NOT FOR ALL

B. Get Access
(1) Open the right main gear door for access to the drain line of the ACT(s) (Ref. AMM TASK 32-12-00-010-001).
(2) For the test of the check valve (231QM1):
(a) In the aft cargo compartment, at the right side of the cargo door entry, remove sidewall panel 152FW, (Ref. AMM TASK 25-55-11-000-003), for access to the ACT test port T2.
(3) For the test of the check valve (231QM4):
(a) In the forward cabin compartment, remove cabin floor panel 231JH (Ref. AMM TASK 53-22-12-000-001), to get access to the ACT FWD.

Subtask 28-28-00-865-145-A ** ON A/C NOT FOR ALL

C. Open, safety and tag this(these) circuit breaker(s):

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C NOT FOR ALL
121VU	FUEL/ACT/FUEL PUMP/SPLY	25QH	Q29

4. Procedure
Subtask 28-28-00-480-055-D ** ON A/C NOT FOR ALL

A. Install the test tool equipment.

NOTE: The installation of the tool equipment for the test on both check valves is given. If only one tool equipment is available, you can do this test on one check valve first and then the other check valve.

(1) For the test of the check valve (231QM1) in the aft cargo compartment:
(a) In the right main gear bay, connect the test tool equipment to the drain line of the aft ACT(s):
1 Loosen the coupling nuts (6) and remove the elbow pipe (7) from the drain line.
2 Connect a regulated GENERATOR - GROUND PRESSURE MINI. 100 MB with a shutoff valve to the drain line end connection.
3 Put a CAP - BLANKING on the other open line end connection.
(b) On the right side of the aft cargo door entry, connect a GAGE - ABSOLUTE PRESSURE, DIGITAL, 0.001 BAR ACCURACY to test port T2.
(2) For the test of the check valve (231QM4) in the forward cargo compartment:
(a) In the right main gear bay, connect the test tool equipment to the drain line of the forward ACT(s):
1 Loosen the coupling nuts (1), (2) and disconnect the drain line.
2 Connect a regulated GENERATOR - GROUND PRESSURE MINI. 100 MB with a shutoff valve to the drain line end connection.
3 Put a CAP - BLANKING on the other open line end connection.
(b) In the forward cargo compartment, on the check valve (231QM4) of the ACT FWD:
1 Loosen the coupling nut (2) and disconnect the pressure hose (1) from the check valve (3).
2 Put a CAP - BLANKING on the open line end connection of the pressure hose (1).

NOTE: The line end connection of the check valve (231QM4) must be open for the test.

Subtask 28-28-00-720-060-C ** ON A/C NOT FOR ALL

B. Test
(1) In the cockpit, on ACT control panel 28VU:
(a) Turn the mode selector ACT XFR to the OFF position.
(b) Push the MODE SEL pushbutton switch to MAN.

WARNING: WHEN YOU USE COMPRESSED AIR:

USE THE CORRECT PROTECTION (FACE SHIELD OR GOGGLES)
DO NOT POINT THE AIRFLOW AT YOURSELF OR OTHER PERSONS.

LOOSE PARTICLES AND/OR HIGH PRESSURE AIR CAN CAUSE INJURY.

NOTE: This is necessary to close the vent valve (234QM) for the test.

ACTION	RESULT
Test of the aft ACT(s) check valve (231QM1): 1.On the regulated air source, at the drain line of the aft ACT(s): Start the regulated air source, Carefully set the regulated air source to a maximum of 0.1 bar (1.4504 psi), to get sufficient air flow for the test. Be careful when you pressurize the cavity of the ACT(s). If the air pressure becomes too high, then the rubber bladder of the ACT(s) in the aft cargo compartment can be damaged.
Stop the pressurization of the aft ACT(s) cavity each time after 10 seconds and start it again.	On the pressure gage, at the test port T2: Examine the pressure gage, Make sure that the air pressure stays zero.
Stop the pressurization at approximately 0.1 bar (1.4504 psi).	On the pressure gage, at the drain line of the aft ACT(s): Make sure that the air pressure is approximately 0.1 bar (1.4504 psi).
	On the pressure gage, at test port T2: Examine the pressure gage, No air pressure must be indicated. NOTE: Air pressure on test port T2 is not permitted.
2.On the regulated air source, at the drain line of the aft ACT(s): Stop the regulated air source and release the air pressure.	On the pressure gage, at the drain line of the aft ACT(s): The air pressure decreases to 0 bar (0.0000 psi).
Test of the ACT FWD check valve (231QM4): 3.On the regulated air source, at the drain line of the ACT FWD: Start the regulated air source Carefully set the regulated air source to a maximum of 0.1 bar (1.4504 psi), to get sufficient air flow for the test. Be careful when you pressurize the cavity of the ACT. If the air pressure becomes too high, then the rubber bladder of the ACT in the forward cargo compartment can be damaged.
Stop the pressurization of the forward ACT(s) cavity each time after 10 seconds and start it again.
Stop the pressurization at approximately 0.1 bar (1.4504 psi).	On the pressure gage, at the drain line of the forward ACT(s): Make sure that the air pressure is approximately 0.1 bar (1.4504 psi).
4.In the forward cargo compartment, on the check valve (231QM4) of the ACT FWD: Apply air leak detector spray on the line end connection of the check valve.	On the check valve (231QM4) of the ACT FWD: Make sure that the check valve has no leaks. NOTE: Leaks are not permitted.
5.On the regulated air source, at the drain line of the forward ACT(s): Stop the regulated air source and release the air pressure.	On the pressure gage, at the drain line of the forward ACT(s): The air pressure decreases to 0 bar (0.0000 psi).

(2) In the cockpit, on ACT control panel 28VU:
(a) Push to release the MODE SEL pushbutton switch.
(b) Make sure that the MAN legend in the pushbutton goes off.

Subtask 28-28-00-080-055-D ** ON A/C NOT FOR ALL

C. Remove the test equipment.
(1) In the right main gear bay, on the forward and aft ACT(s) drain line connections:
(a) Remove the ground support and maintenance equipment, the special and standard tools and all other items.
(b) Remove the PLUG-BLANKING from each disconnected line end.
(c) Clean the component interfaces and the adjacent area.
(d) Do an inspection of the component interfaces and the adjacent area.
(e) Connect the forward drain lines and tighten the coupling nuts (1) and (2).
(f) Connect the aft drain lines with the elbow pipe (7) and tighten the coupling nuts (6).
(2) On the right side of the cargo door entry, disconnect the pressure gage from test port T2.
(3) In the forward cargo compartment, on the ACT FWD:
(a) Remove the PLUG-BLANKING from each disconnected line end.
(b) Clean the component interfaces and the adjacent area.
(c) Do an inspection of the component interfaces and the adjacent area.
(d) Connect the pressure hose (1) to the check valve (3) and install the coupling nut (2).

CAUTION: MAKE SURE THAT THE FLEXIBLE HOSES ARE NOT TWISTED OR PULLED TIGHT. IF THE HOSES ARE TWISTED OR PULLED TIGHT, THE CONNECTIONS WILL BREAK AND CAUSE A LEAK.

(e) TORQUE the coupling nut (2) to between 4.3 and 3.9 m.daN (31.71 and 28.76 lbf.ft )

5. Close-up
Subtask 28-28-00-865-146-A ** ON A/C NOT FOR ALL

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

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C NOT FOR ALL
121VU	FUEL/ACT/FUEL PUMP/SPLY	25QH	Q29

Subtask 28-28-00-410-081-A ** ON A/C NOT FOR ALL

B. Close Access
(1) On the right side of the cargo door entry, install sidewall panel 152FW (Ref. AMM TASK 25-55-11-400-003).
(2) Close the right main-gear door (Ref. AMM TASK 32-12-00-410-001).
(3) In the forward cabin compartment, install cabin floor panel 231JH (Ref. AMM TASK 53-22-12-400-001).

Subtask 28-28-00-860-233-A ** ON A/C NOT FOR ALL

C. Put the aircraft back to its initial configuration.
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Remove the WARNING NOTICE(S).
(3) De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002).

[Rev.10 from 2021] 2026.04.02 07:03:42 UTC