Operational Check of ACT(S) Inward Relief Valve

TASK 28-28-00-720-002-A
Operational Check of ACT(S) Inward Relief Valve

WARNING: OBEY THE FUEL SAFETY PROCEDURES.

ZONE: 150

1. Reason for the Job
Refer to the MPD TASK: 282800-08
OPERATIONAL CHECK OF ACT(S) INWARD RELIEF VALVE
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment

REFERENCE	QTY	DESIGNATION
No specific	1	AIR SOURCE 0.3 TO 0.7 BAR (5 TO 10 PSI)- FILTERED, DRY
No specific	1	CAP - BLANKING
No specific	1	GAGE 0,1 BAR (1,45 PSI) - PRESSURE, DIGITAL
No specific	1	LOCALLY MANUFACTURED - ADAPTER
No specific	AR	SAFETY CLIP - CIRCUIT BREAKER
No specific	1	WARNING NOTICE(S)

B. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
150	AFT CARGO COMPARTMENT FWD PRESS BULKHEAD TO AFT BULKHEAD OF AFT CARGO COMPARTMENT
153AZ, 197PB
154AR

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 28-00-00-910-001-A	Fuel Safety Procedures
TASK 28-11-49-000-001-A	Removal of the ACT Integrated Impact Wall
TASK 28-11-49-000-002-A	Removal of the Additional Center Tank (ACT) Integrated Impact Wall
TASK 28-11-49-400-001-A	Installation of the ACT Integrated Impact Wall
TASK 28-25-00-650-001-A	Pressure Defuel
TASK 52-30-00-860-001-A	Open the FWD or Aft Cargo-Compartment Door with the Yellow Electric Pump
TASK 52-30-00-860-002-A	Close the FWD or Aft Cargo-Compartment Door with the Yellow Electric Pump
Test Connection to the Cavity Drain Port of the ACT
Test Equipment Diagram
Visual Indicator Position of ACT Vent-Valve ** ON A/C NOT FOR ALL
Visual Indicator Position of ACT Vent-Valve ** ON A/C NOT FOR ALL
Visual Indicator Position of ACT Vent-Valve ** ON A/C NOT FOR ALL

3. Job Set-up
Subtask 28-28-00-860-063-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) Defuel all Additional Center Tanks ACT(s) (Ref. AMM TASK 28-25-00-650-001).
(4) Put WARNING NOTICE(S) in position on these panels, to tell persons not to operate the refuel/defuel system:

Refuel/defuel panel 800VU and 801VU
Fuel panel 40VU
Fuel panel 28VU.

Subtask 28-28-00-010-050-A ** ON A/C NOT FOR ALL

B. Get Access
(1) Get access to the aft cargo-compartment (Ref. AMM TASK 52-30-00-860-001).
(2) Remove the right side of the ACT Integrated Impact Wall (Ref. AMM TASK 28-11-49-000-001), to get access to the actuator of the ACT vent-valve (4QH).
(3) On the lower fuselage, get access to the ACT cavity drain connection:
(a) Remove the panels 197PB and 153AZ from the lower fuselage.

Subtask 28-28-00-010-050-B ** ON A/C NOT FOR ALL

B. Get Access
(1) Get access to the aft cargo-compartment (Ref. AMM TASK 52-30-00-860-001).
(2) Remove the right side of the ACT Integrated Impact Wall (Ref. AMM TASK 28-11-49-000-001), to get access to the actuator of the ACT2 vent-valve (4QH2).
(3) On the lower fuselage, get access to the ACT1 and ACT2 cavity drain connection:
(a) Remove the access panels 197PB, 153AZ and 154AR from the lower fuselage.

Subtask 28-28-00-010-050-C ** ON A/C NOT FOR ALL

B. Get Access
(1) Get access to the aft cargo-compartment door (Ref. AMM TASK 52-30-00-860-001).
(2) Remove the right side of the ACT integrated impact wall, to get access to the ACT inward relief valves (229QM1) and (229QM2) (Ref. AMM TASK 28-11-49-000-002).
(3) On the lower fuselage, get access to ACT AFT1 and ACT AFT2 cavity drain connection:
(a) Remove access panels 197PB and 153AZ from the lower fuselage.

Subtask 28-28-00-865-056-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	ACT PUMP SUPPLY	25QH	Q29
** ON A/C NOT FOR ALL
121VU	FUEL/ACT/FUEL PUMP/SPLY	25QH	Q29

4. Procedure
Subtask 28-28-00-860-064-A ** ON A/C NOT FOR ALL

A. Preparation for the Test
(1) On the lower fuselage, connect the test tool equipment to the line end of the ACT cavity drain:
(a) Loosen the coupling nut (1) and disconnect the hose (6) from the ACT cavity drain (2).
(b) Put a CAP - BLANKING on the coupling nut (1).
(c) Connect the LOCALLY MANUFACTURED - ADAPTER together with the GAGE 0,1 BAR (1,45 PSI) - PRESSURE, DIGITAL to the line end of the ACT cavity drain (2).

NOTE: The pressure gage must have a fine scale with steps of 0.01 bar (0.15 psi).

(d) Connect a regulated AIR SOURCE 0.3 TO 0.7 BAR (5 TO 10 PSI)- FILTERED, DRY with a shut off valves to the coupling adapter of the PRESSURE GAGE DIGITAL 0.1 BAR (1.45 PSI).

NOTE: The pressure gage of the regulated air source must have a scale with steps of 0.1 bar (1.45 psi).

(2) In the aft cargo-compartment, on the actuator of the ACT vent-valve (4QH):
(a) Make sure that the visual indicator of the actuator is in the open position.

Visual Indicator Position of ACT Vent-Valve ** ON A/C NOT FOR ALL

Subtask 28-28-00-720-051-A ** ON A/C NOT FOR ALL

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.

B. Test

ACTION	RESULT
1.On the regulated air source: make sure that the regulator of the air source is set to 0 bar (0 psi), make sure that the air shut off valves of the air source are closed, start the regulated air source, carefully set the regulated air source to a maximum of 0.1 bar (1.45 psi), to get sufficient air flow for the test. NOTE: Be careful when you pressurize the ACT cavity drain. The rubber bladder of the ACT can be damage, if the air pressure becomes too high and the inward relief-valve does not work as specified.
stop the pressurization each time after 10 seconds and start it again.	On the pressure gage at the ACT cavity drain: the air pressure increases to 0.01 bar (0.15 psi), the air pressure is stable at approximately 0.01 bar (0.15 psi). NOTE: The Inward Relief Valve must open at approximately 0.01 bar (0.15 psi) to prevent damage on the Bladder Tank of the ACT.
2.On the regulated air source: stop the regulated air source and open the air shut off valves of the air source.	On the pressure gage at the ACT cavity drain: the air pressure decreases to 0 bar (0 psi).

Subtask 28-28-00-860-064-B ** ON A/C NOT FOR ALL

C. Preparation for the Test
(1) On the lower fuselage, connect the test tool equipment to the line end of the cavity drain of the ACT1 and/or ACT2:

NOTE: You can install the test tool equipment on the cavity drain of the ACT2 first and do the test on the ACT2.
Then after install the test tool equipment on the cavity drain of the ACT1 and and do the test on the ACT1.

(a) Loosen the coupling nut (1) and disconnect the hose (6) from the ACT cavity drain (2).
(b) Put a CAP - BLANKING on the coupling nut (1).
(c) Connect the LOCALLY MANUFACTURED - ADAPTER together with the GAGE 0,1 BAR (1,45 PSI) - PRESSURE, DIGITAL to the line end of the ACT cavity drain (2).

NOTE: The pressure gage must have a fine scale with steps of 0.01 bar (0.15 psi).

(d) Connect a regulated AIR SOURCE 0.3 TO 0.7 BAR (5 TO 10 PSI)- FILTERED, DRY with a shut off valves to the coupling adapter of the PRESSURE GAGE DIGITAL 0.1 BAR (1.45 PSI).

NOTE: The pressure gage of the regulated air source must have a scale with steps of 0.1 bar (1.45 psi).

(2) In the aft cargo-compartment, on the actuator of the ACT2 vent-valve (4QH2):
(a) Make sure that the visual indicator of the actuator is in the open position.

Visual Indicator Position of ACT Vent-Valve ** ON A/C NOT FOR ALL

NOTE: The vent-valves of the ACT2 and ACT1 are open and closed at the same time.

Subtask 28-28-00-720-051-B ** ON A/C NOT FOR ALL

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.

D. Test

NOTE: You can do this test on the ACT2 first, then do this test on the ACT1.

ACTION	RESULT
1.On the regulated air source: make sure that the regulator of the air source is set to 0 bar (0 psi), make sure that the air shut off valves of the air source are closed, start the regulated air source, carefully set the regulated air source to a maximum of 0.1 bar (1.45 psi), to get sufficient air flow for the test. NOTE: Be careful when you pressurize the ACT cavity drain. The rubber bladder of the ACT can be damage, if the air pressure becomes too high and the inward relief-valve does not work as specified.
stop the pressurization each time after 10 seconds and start it again.	On the pressure gage at the ACT cavity drain: the air pressure increases to 0.01 bar (0.15 psi), the air pressure is stable at approximately 0.01 bar (0.15 psi). NOTE: The Inward Relief Valve must open at approximately 0.01 bar (0.15 psi) to prevent damage on the Bladder Tank of the ACT.
2.On the regulated air source: stop the regulated air source and open the air shut off valves of the air source.	On the pressure gage at the ACT cavity drain: the air pressure decreases to 0 bar (0 psi).

Subtask 28-28-00-860-064-C ** ON A/C NOT FOR ALL

E. Preparation for the Test
(1) On the lower fuselage, connect the test tool equipment to the line end of the ACT cavity drain:
(a) Loosen the coupling nut (1) and disconnect the hose (6) from the ACT cavity drain (2).
(b) Put a CAP - BLANKING on the coupling nut (1).

NOTE: The pressure gage has a scale of 0.01 bar (0.15 psi).

(c) Connect a regulated AIR SOURCE 0.3 TO 0.7 BAR (5 TO 10 PSI)- FILTERED, DRY with a shutoff valve to the coupling adapter of the PRESSURE GAGE DIGITAL 0.1 BAR (1.45 PSI) (5) with the nut (3) and the air supply hose (4).

NOTE: The pressure gage of the regulated air source has a scale of 0.1 bar (1.45 psi).

(2) In the aft cargo-compartment, on the actuator of the ACT inward relief valves (229QM1) and ACT (229QM2):
(a) Make sure that the visual indicator of the actuator is in the open position.

Visual Indicator Position of ACT Vent-Valve ** ON A/C NOT FOR ALL

Subtask 28-28-00-720-051-C ** ON A/C NOT FOR ALL

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.

CAUTION: BE CAREFUL WHEN YOU PRESSURIZE THE ACT CAVITY DRAIN. IF THE AIR PRESSURE BECOMES TOO HIGH AND THE INWARD RELIEF-VALVE DOES NOT OPERATE CORRECTLY, DAMAGE TO THE ACT RUBBER BLADDER CAN OCCUR.

F. Test

ACTION	RESULT
1.On the regulated air source: Make sure that the regulator of the air source is set to 0 bar (0 psi) Make sure that the air shutoff valves of the air source are closed Start the regulated air source Carefully set the regulated air source to a maximum of 0.1 bar (1.45 psi), to get sufficient air flow for the test.
Stop the pressurization each time after 10 seconds and start it again.	On the pressure gage at the ACT cavity drain: The air pressure increases to 0.007 bar (0.10 psi) The air pressure is stable at approximately 1000 ltr/min The inward relief valve must open at approximately 0.007 bar (0.10 psi) to prevent damage to the bladder tank of the ACT.
2.On the regulated air source: Stop the regulated air source and open the air shutoff valves of the air source.	On the pressure gage at the ACT cavity drain: The air pressure decreases to 0 bar (0 psi).

Subtask 28-28-00-860-125-A ** ON A/C NOT FOR ALL

G. Put the system back to the serviceable condition.
(1) On the lower fuselage, at the ACT cavity drain:
(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 hose (6) to the ACT cavity drain (2) and tighten the coupling nut (1).

NOTE: Make sure that you do not twist the hose when you tighten coupling nut.

5. Close-up
Subtask 28-28-00-410-051-A ** ON A/C NOT FOR ALL

A. Close Access
(1) In the aft cargo-compartment:
(a) Make sure that the work area is clean and clear of tools and other items.
(b) Install the ACT Integrated Impact Wall (Ref. AMM TASK 28-11-49-400-001).
(2) Remove the access platform(s).
(3) Close the aft cargo-compartment door (Ref. AMM TASK 52-30-00-860-002).
(4) On the lower fuselage, close the access to the ACT cavity drain:
(a) Install the panels 197PB and 153AZ on the lower fuselage.

Subtask 28-28-00-410-051-B ** ON A/C NOT FOR ALL

A. Close Access
(1) In the aft cargo-compartment:
(a) Make sure that the work area is clean and clear of tools and other items.
(b) Install the ACT Integrated Impact Wall (Ref. AMM TASK 28-11-49-400-001).
(2) Remove the access platform(s).
(3) Close the aft cargo-compartment door (Ref. AMM TASK 52-30-00-860-002).
(4) On the lower fuselage, close the access to the ACT1 and ACT2 cavity drain:
(a) Install the panels 197PB, 153AZ and 154AR on the lower fuselage.

Subtask 28-28-00-865-057-A ** ON A/C NOT FOR ALL

B. 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	ACT PUMP SUPPLY	25QH	Q29
** ON A/C NOT FOR ALL
121VU	FUEL/ACT/FUEL PUMP/SPLY	25QH	Q29

Subtask 28-28-00-860-065-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 06:17:51 UTC