Leak Test of the Additional Center Tank (ACT) Fuel/Vent System and Pressurization System

TASK 28-28-00-790-001-A
Leak Test of the Additional Center Tank (ACT) Fuel/Vent System and Pressurization System

WARNING: OBEY THE FUEL SAFETY PROCEDURES.

NOTE: This procedure can test the fuel/vent and pressurization system of some or all installed ACTs. If only a single additional ACT is installed, you can test only the applicable pipes for that ACT. All optional steps are shown in the procedure.

1. Reason for the Job

NOTE: For the New Engine Option (NEO) aircraft with an ACT installed in the forward cargo compartment, the term ACT FWD can also be described as ACT 4.1.

2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment

REFERENCE	QTY	DESIGNATION
No specific	2	ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE
No specific	1	ADAPTER - EXTENSION, FILLING SYSTEM, DRY AIR
No specific	1	AIR SOURCE 0.3 TO 0.7 BAR (5 TO 10 PSI)- FILTERED, DRY
No specific	1	CAP - BLANKING
No specific	AR	GAGE 0 TO 2000 PSI (0 TO 138 BAR) - PRESSURE
No specific	AR	PLUG - BLANKING
No specific	1	WARNING NOTICE(S)
No specific	Torque wrench: range to between 37 and 30 m.N (27.29 and 22.12 lbf.ft )
98D28108562000	2	ADAPTER, PRESSURE DRAIN - ACT
98D28108658000	1	TOOL-PRESSURE TEST,ACT

B. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
152FW, 154AR, 195BB, 197AB, 251AF, 251AG
134AR
826

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 28-11-47-000-802-A	Removal of the Additional Center Tank (ACT) Outer Drain-Valve
TASK 28-11-47-400-802-A	Installation of the Additional Center Tank (ACT) Outer Drain-Valve
TASK 28-25-00-650-001-A	Pressure Defuel
TASK 28-25-00-650-005-A	To Drain the Remaining Fuel from the Additional Center Tank (ACT)
TASK 28-28-72-000-001-A	Removal of the ACT Vent-Valve Actuator
TASK 28-28-72-400-001-A	Installation of the ACT Vent-Valve Actuator
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 33-14-00-710-001-A	Operational Check of the Light Test System
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
TASK 52-42-15-000-001-A	Removal of the Access Panel (134AR,154AR)
TASK 52-42-15-400-001-A	Installation of the Access Panel (134AR,154AR)
TASK 52-42-26-000-801-A	Removal of Access Doors 195BB and 196BB
TASK 52-42-26-400-801-A	Installation of Access Doors 195BB and 196BB
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
TASK 53-32-12-000-002-A	Removal of the Cabin Floor Panels
TASK 53-32-12-400-002-A	Installation of the Cabin Floor Panels
TASK 53-35-13-000-001-A	Removal of the Belly Fairing Access Panels
TASK 53-35-13-400-001-A	Installation of the Belly Fairing Access Panels
ACT Vent-Valve-Actuator Position-Indicator 91QH
Access to the ACT Cavity Drain-Line (Forward ACT) ** ON A/C NOT FOR ALL
Test Arrangement ACT ** ON A/C NOT FOR ALL
Access to Test Ports T1 and T2
Access to the ACT Cavity Drain-Line (Aft ACT) ** ON A/C NOT FOR ALL
Test Arrangement ACT ** ON A/C NOT FOR ALL

3. Job Set-up
Subtask 28-28-00-860-131-C ** 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) Drain the remaining fuel from ACT AFT1 and ACT FWD (if installed) (Ref. AMM TASK 28-25-00-650-005).
(5) Open refuel/defuel panel 800VU 801VU and make sure that:

The "MODE SELECT" switch is in "OFF" position.
All "REFUEL VALVE" switches are in the "NORM" position.

(a) Close refuel/defuel panel 800VU 801VU.

(6) Put a WARNING NOTICE(S) 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 28-28-00-010-074-B ** ON A/C NOT FOR ALL

B. Get Access
(1) Open the Main Landing Gear (MLG) doors (Ref. AMM TASK 32-12-00-010-001).
(2) Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position at the left and right side of the MLG bay.
(3) Open access door 195BB to get access to the ACT vent-valve actuator (91QH) (Ref. AMM TASK 52-42-26-000-801).
(4) Open the forward and aft cargo-compartment doors (Ref. AMM TASK 52-30-00-860-001):
(a) Remove sidewall panel 152FW (Ref. AMM TASK 25-55-11-000-003) to get access to test ports T1 and T2.
(5) On the lower fuselage, get access to the ACT cavity-drain lines below the applicable ACT(s):

NOTE: Removal of the access panel(s) is only necessary if the applicable ACT(s) is(are) installed and to be tested.

(a) Remove the access panels from the lower fuselage that follow:

For ACT AFT1, remove 197AB (Ref. AMM TASK 53-35-13-000-001)
For ACT AFT2, remove 154AR (Ref. AMM TASK 52-42-15-000-001)
For ACT FWD, remove 134AR (Ref. AMM TASK 52-42-15-000-001).

(6) In the cabin, get access to the ACT vent/transfer-pipe connectors:
(a) Remove the applicable cabin floor panels and cargo ceiling panels installed above the ACT(s) that follow:

NOTE: Removal of the cabin floor panel(s) is only necessary if the applicable ACT(s) is(are) installed and is(are) to be tested.

For the pipe connections of ACT AFT1 and ACT AFT2, remove 251AG and 251AF (Ref. AMM TASK 53-32-12-000-002)
For the pipe connections of ACT FWD, remove 231BMG (Ref. AMM TASK 53-22-12-000-001).

Subtask 28-28-00-860-131-D ** ON A/C NOT FOR ALL

C. 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 the ACT(s) (Ref. AMM TASK 28-25-00-650-001).
(4) Drain the remaining fuel from ACT AFT1 and ACT AFT2 (if installed) (Ref. AMM TASK 28-25-00-650-005).
(5) Open refuel/defuel panels 800VU and 801VU and make sure that:

The MODE SELECT switch is in the OFF position.
All REFUEL VALVE switches are in the NORM position.

(6) Close refuel/defuel panels 800VU and 801VU.
(7) Put the WARNING NOTICE(S) in position on these panels to tell the persons not to operate the refuel/defuel system:

Refuel/defuel panels 800VU and 801VU
HYD/FUEL panel 40VU
ACT control-panel 28VU.

Subtask 28-28-00-010-074-E ** ON A/C NOT FOR ALL

D. Get Access
(1) Open the Main Landing Gear (MLG) doors (Ref. AMM TASK 32-12-00-010-001).
(2) Put the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE in position at the left and right side of the MLG bay.
(3) Open access door 195BB to get access to the ACT vent-valve actuator (91QH) (Ref. AMM TASK 52-42-26-000-801).
(4) Open aft cargo-compartment-door 826 (Ref. AMM TASK 52-30-00-860-001):
(a) Remove sidewall panel 152FW (Ref. AMM TASK 25-55-11-000-003) to get access to test ports T1 and T2.
(5) On the lower fuselage, get access to the ACT cavity-drain lines below the applicable ACT(s):

NOTE: Removal of the access panel(s) is only necessary if the applicable ACT(s) is(are) installed and to be tested.

(a) Remove the access panels from the lower fuselage that follow:

For ACT AFT1, remove 197AB (Ref. AMM TASK 53-35-13-000-001)
For ACT AFT2 (if installed), remove 154AR (Ref. AMM TASK 52-42-15-000-001).

(6) In the cabin, get access to the ACT vent/transfer-pipe connectors:
(a) Remove the applicable cabin floor panels and cargo ceiling panels installed above the ACT(s) that follow:

NOTE: Removal of the cabin floor panel(s) is only necessary if the applicable ACT(s) is(are) installed and is(are) to be tested.

For the pipe connections of ACT AFT1 and ACT AFT2 (if installed), remove 251AG and 251AF (Ref. AMM TASK 53-32-12-000-002).

Subtask 28-28-00-865-093-A ** ON A/C NOT FOR ALL

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

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

4. Procedure
Subtask 28-28-00-860-132-C ** ON A/C NOT FOR ALL

A. Preparation for the Test

NOTE: Steps 3 and 5a can be ignored if there are no FWD ACT(s) installed or to be tested.

NOTE: Step 5b can be ignored if there are no AFT ACT(s) installed or to be tested.

(1) In the cockpit:
(a) Do a operational test of the annunciator light test-system in the cockpit (Ref. AMM TASK 33-14-00-710-001).
1 Make sure that all the lights on ACT control panel 28VU are on during the test.
(b) On ACT control panel 28VU, make sure that the "ACT XFR" rotary switch is in the "OFF" position.
(c) On ACT control panel 28VU, push the "MODE SEL" pushbutton switch.
1 Make sure that the "MAN" legend in the "MODE SEL" pushbutton switch is on.

NOTE: ACT air shutoff Valve (233QM) is open and the ACT inlet valves (228QM1-6) are closed at this time.

(2) Make sure that the forward-vent isolation-valve actuator (93QH) is in the close position if there are no FWD ACTs installed.

(3) In the forward cargo compartment, on the ACT FWD (if installed):

NOTE: You get access to the area behind the ACT FWD from the cabin.

(a) Make sure that the indication for the forward-vent isolation-valve actuator (93QH) shows open position.
(b) If the forward vent isolation-valve (232QM) is close, remove the forward vent-isolation-valve actuator (93QH) (Ref. AMM D/O 28-28-57-00) and open the valve manually.

NOTE: The air pressure in the forward ACT(s) will not decrease after the test procedure when the forward vent isolation-valve (232QM) is close.

(4) In the blue hydraulic compartment:
(a) Make sure that the indication for the ACT vent-valve actuator (91QH) shows the close position

ACT Vent-Valve-Actuator Position-Indicator 91QH ** ON A/C NOT FOR ALL

(b) If the ACT vent valve (234QM) is open, remove the ACT vent-valve actuator (91QH) (Ref. AMM TASK 28-28-72-000-001) and close the ACT vent valve manually.

(5) In the MLG bay, install the test tools on the ACT cavity-drain line.
(a) In the forward area on the right side of the MLG bay:

Access to the ACT Cavity Drain-Line (Forward ACT) ** ON A/C NOT FOR ALL

Test Arrangement ACT ** ON A/C NOT FOR ALL

1 Loosen the nut (1) and disconnect the APU drain line from the ACT cavity-drain line.
2 Put the PLUG-BLANKING in each disconnected line end.
3 Loosen the nut (2) and disconnect the ACT cavity-drain line from the tee.
4 Connect an AIR SOURCE 0.3 TO 0.7 BAR (5 TO 10 PSI)- FILTERED, DRY and a GAGE 0 TO 2000 PSI (0 TO 138 BAR) - PRESSURE with the applicable ADAPTER - EXTENSION, FILLING SYSTEM, DRY AIR to the forward ACT cavity drain-line.

(b) In the aft area on the right side of the MLG bay:
1 Disconnect the elbow nut from the T-connection.
2 Put a CAP - BLANKING on the T-connection.
3 Loosen the nut of the ACT cavity-drain line and remove the elbow.
4 Connect an AIR SOURCE 0.3 TO 0.7 BAR (5 TO 10 PSI)- FILTERED, DRY and a GAGE 0 TO 2000 PSI (0 TO 138 BAR) - PRESSURE with the applicable ADAPTER - EXTENSION, FILLING SYSTEM, DRY AIR to the ACT cavity-drain line.

(6) On the lower fuselage:
(a) Remove the outer ACT water-drain-valves from ACT AFT1 and ACT FWD (if installed) (Ref. AMM TASK 28-11-47-000-802).
(b) Install the 98D28108562000 ADAPTER, PRESSURE DRAIN - ACT on the water drain valve interface of ACT AFT1 and ACT FWD (if installed).

NOTE: This is to monitor the air pressure in the rubber bladder of the applicable ACT(s) in the forward and aft cargo compartment.

(c) Make sure that each installed ACT is connected with the applicable ACT cavity- drain line.
(d) For the removed ACT(s), make sure that the ACT cavity-drain lines are close with the applicable blanking plugs.

(7) In the aft cargo compartment:

Access to Test Ports T1 and T2 ** ON A/C NOT FOR ALL

(a) Install the 98D28108658000 TOOL-PRESSURE TEST,ACT on test port T1 and T2.

Subtask 28-28-00-790-050-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.

B. Leak Test of the ACT vent/transfer pipe shrouds and ACT cavity-drain-line connections

NOTE: In this procedure, steps 9, 10, 11 and 12 can be ignored if no FWD ACT are installed or to be tested.

NOTE: In this procedure, steps 3, 4, 5 and 6 can be ignored if no AFT ACT(s) are installed or to be tested.

ACTION	RESULT
1.In the aft cargo compartment, on the ACT PRESSURE TEST-TOOL: Pressurize test port T1 to 1.00 bar (14.5038 psi). NOTE: All ACT(s) in the forward and aft cargo compartment will be pressurized at this time.	On the pressure gage at test port T2: The air pressure indication increases to between 0.345 bar (5.0038 psi) and 0.448 bar (6.4977 psi). On the pressure gage at ACT AFT1 and ACT FWD (if installed) water-drain-valve interface: The air pressure indication increases to between 0.345 bar (5.0038 psi) and 0.448 bar (6.4977 psi)0.195 bar (2.8282 psi). NOTE: If the air pressure becomes too high: The ACT pressure holding-valves will open at 0.664 bar (9.6305 psi) The burst discs of the ACT vent system will break at 1.1 -0.27 bar or +0.0 bar (15.9541 -3.9160 psi or +0 psi).
2.Stop the pressurization.
3.In the MLG bay, on the pressure gage at the aft ACT cavity-drain-line: Monitor the air pressure indication. If necessary, pressurize the aft ACT cavity-drain-line to between 0.345 bar (5.0038 psi) and 0.448 bar (6.4977 psi)0.195 bar (2.8282 psi) with the ground pressure generator.	On the pressure gage at the aft ACT cavity-drain-line: The air pressure indication increases to between 0.345 bar (5.0038 psi) and 0.448 bar (6.4977 psi)0.195 bar (2.8282 psi).
4.Stop the pressurization.
5.If the air pressure is not stable, do the leak test: Do a leak check of the cavity-drain-line connections of the ACT(s) in the aft cargo compartment as necessary. Do a leak check of the vent/transfer-pipe shroud connections of the ACT(s) in the aft cargo compartment as necessary. Use a soap solution or a leak detector spray to find leaks.	There are no leaks. If there are leaks, do an approved repair and do this test again.
6.In the MLG bay, on the ground pressure generator: Release the air pressure from the aft ACT cavity-drain-line.	On the pressure gage at the aft ACT cavity-drain-line: The air pressure indication decreases to 0.0 bar (0.0000 psi). On the pressure gage at ACT AFT1 and ACT FWD water-drain-valve interface: The air pressure indication decreases to approximately 0.1 +0.05 bar or -0.05 bar (1.4504 +0.7252 psi or -0.7252 psi). NOTE: The air pressure in the ACT(s) decreases slowly because of the extension of the rubber bladder in the ACT(s). It is not permitted for the air pressure in the ACT(s) to decrease to 0.0 bar (0.0000 psi).
7.In the aft cargo compartment: On the pressure gage at test port T2, make sure that the air pressure is between 0.345 bar (5.0038 psi) and 0.448 bar (6.4977 psi)0.195 bar (2.8282 psi) If necessary, adjust the pressure on test port T1 with the ACT PRESSURE-TEST TOOL.	On the pressure gage at test port T2: The indicator shows the air pressure between 0.345 bar (5.0038 psi) and 0.448 bar (6.4977 psi)0.195 bar (2.8282 psi). On the pressure gage at ACT AFT1 and ACT FWD (if installed) water-drain-valve interface: The air pressure indication increases to between 0.345 bar (5.0038 psi) and 0.448 bar (6.4977 psi)0.195 bar (2.8282 psi).
8.Stop the pressurization.
9.In the MLG Bay, on the pressure gage at the forward ACT cavity-drain-line: Monitor the air pressure indication. If necessary, pressurize the forward ACT cavity-drain-line to between 0.345 bar (5.0038 psi) and 0.448 bar (6.4977 psi)0.195 bar (2.8282 psi) with the ground pressure generator.	On the pressure gage at the forward ACT cavity-drain-line: The air pressure indication increases to between 0.345 bar (5.0038 psi) and 0.448 bar (6.4977 psi)0.195 bar (2.8282 psi).
10.Stop the pressurization.
11.If the air pressure is not stable, do the leak test: Do a leak check of the cavity-drain-line connections of the ACT(s) in the forward cargo compartment as necessary. Do a leak check of the vent/transfer pipe shroud of the ACT(s) in the forward cargo compartment as necessary. Use a soap solution or a leak detector spray to find leaks.	There are no leaks. If there are leaks, do an approved repair and do this test again.
12.In the MLG bay, on the ground pressure generator: Release the air pressure from the forward ACT cavity-drain-line.	On the pressure gage at the forward ACT cavity-drain-line: The air pressure indication decreases to 0.0 bar (0.0000 psi). On the pressure gage at ACT AFT1 and ACT FWD water-drain-valve interface: The air pressure indication decreases to approximately 0.1 +0.05 bar or -0.05 bar (1.4504 +0.7252 psi or -0.7252 psi). NOTE: The air pressure in the ACT(s) decreases slowly because of the extension of the rubber bladder in the ACT(s).It is not permitted for the air pressure in the ACT(s) to decrease to 0.0 bar (0.0000 psi).
13.In the aft cargo compartment, on the ACT PRESSURE TEST-TOOL: Release the air pressure from test port T1. In the blue hydraulic compartment: Open the ACT vent valve (234QM) manually with a screwdriver.	On the pressure gage at test port T2: The air pressure indication decreases to 0 bar (0.0000 psi). On the pressure gage at the interface of ACT AFT1 and ACT FWD (if installed) water-drain-valve: The air pressure indication decreases to 0 bar (0.0000 psi).

Subtask 28-28-00-860-188-C ** ON A/C NOT FOR ALL

C. Put the system back to the serviceable condition.
(1) In the cockpit:
(a) On ACT control panel 28VU, push to release the "MODE SEL" pushbutton switch.
(b) Make sure that the "MAN" legend in the "MODE SEL" pushbutton switch is off.

(2) In the forward cargo compartment, on the ACT FWD (if installed):
(a) If removed for the test, install the forward-vent isolation-valve actuator (93QH) (Ref. AMM D/O 28-28-57-40).

(3) In the blue hydraulic compartment:
(a) If removed for the test, install the ACT vent-valve actuator (91QH) (Ref. AMM TASK 28-28-72-400-001).

(4) In the MLG bay:
(a) Remove the test-tools from the forward and aft ACT cavity-drain-line.
(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) Assemble the forward and aft ACT cavity-drain-lines.

(5) On the lower fuselage:
(a) Remove the PRESSURE - DRAIN ADAPTER ACT from the ACT water-drain valve interface.
(b) Install the outer ACT water-drain valves on the ACT FWD and ACT AFT1 (Ref. AMM TASK 28-11-47-400-802).

(6) In the aft cargo compartment:
(a) Remove the ACT PRESSURE-TEST TOOL from test port T1 and T2.

Subtask 28-28-00-860-132-D ** ON A/C NOT FOR ALL

D. Preparation for the Test

NOTE: In this procedure, you can ignore step (3) (a) if no AFT ACT(s) is (are) installed or if no test is necessary.

(1) In the cockpit:
(a) Do the operational test of the annunciator light test-system in the cockpit (Ref. AMM TASK 33-14-00-710-001):
1 Make sure that all the lights on ACT control-panel 28VU come on during the test.
(b) On ACT control-panel 28VU, make sure that the ACT XFR rotary switch is in the OFF position.
(c) On ACT control-panel 28VU, push the MODE SEL pushbutton switch:
1 Make sure that the MAN legend in the MODE SEL pushbutton switch comes on.

NOTE: ACT air shutoff-valve (233QM) is open and the ACT inlet valves (228QM1 and 228QM2) are closed at this time.

(2) In the blue hydraulic compartment:
(a) Make sure that the indication for the ACT vent-valve actuator (91QH) shows the close position.

ACT Vent-Valve-Actuator Position-Indicator 91QH ** ON A/C NOT FOR ALL

(b) If the ACT vent valve (234QM) is open, remove the ACT vent-valve actuator (91QH) (Ref. AMM TASK 28-28-72-000-001) and close the ACT vent valve manually.
(3) In the MLG bay, install the test tools on the ACT cavity-drain line:
(a) In the aft area of the MLG bay:

Access to the ACT Cavity Drain-Line (Aft ACT) ** ON A/C NOT FOR ALL

Test Arrangement ACT ** ON A/C NOT FOR ALL

1 Loosen the coupling nut (5) and disconnect the elbow pipe (7) from the T-connection.
2 Loosen the coupling nut (6) of the ACT cavity-drain line and remove the elbow pipe (7).
3 Put the CAP - BLANKING on the T-connection.
4 Connect the AIR SOURCE 0.3 TO 0.7 BAR (5 TO 10 PSI)- FILTERED, DRY and GAGE 0 TO 2000 PSI (0 TO 138 BAR) - PRESSURE with the applicable ADAPTER - EXTENSION, FILLING SYSTEM, DRY AIR to the ACT cavity-drain line.
(4) On the lower fuselage:
(a) Remove the outer ACT water-drain-valves from ACT AFT1 and ACT AFT2 (if installed) (Ref. AMM TASK 28-11-47-000-802).
(b) Install the 98D28108562000 ADAPTER, PRESSURE DRAIN - ACT on the water drain-valve interface of ACT AFT1 and ACT AFT2 (if installed).

NOTE: This is to monitor the air pressure in the rubber bladder of the applicable ACT(s) in the aft cargo compartment.

(c) Make sure that each installed ACT is connected with the applicable ACT cavity-drain line.
(d) For the removed ACT(s), make sure that the ACT cavity-drain line(s) are closed with the applicable blanking plug(s).
(5) In the aft cargo compartment:

Access to Test Ports T1 and T2 ** ON A/C NOT FOR ALL

(a) Install the 98D28108658000 TOOL-PRESSURE TEST,ACT on test ports T1 and T2.

Subtask 28-28-00-790-050-D ** 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.

E. Leak Test of the ACT vent/transfer pipe shrouds and ACT cavity-drain-line connections

NOTE: In this procedure, you can ignore steps 3 to 6 if no AFT ACT(s) is (are) installed or if no test is necessary.

ACTION	RESULT
1.In the aft cargo compartment, on the ACT pressure-test tool: Pressurize test port T1 to 1 bar (14.50 psi). NOTE: All ACT(s) in the aft cargo compartment will be pressurized at this time.	On the pressure gauge at test port T2: The air pressure indication increases between 0.345 bar (5.00 psi) and 0.448 bar (6.50 psi). On the pressure gauge at ACT AFT1 water-drain-valve interface: The air pressure indication increases between 0.345 bar (5.00 psi) and 0.448 bar (6.50 psi) 0.195 bar (2.83 psi). NOTE: If the air pressure becomes too high: The ACT pressure holding-valves will open at 0.664 bar (9.63 psi) The burst discs of the ACT vent system will break at 1.1 -0.27 bar or +0.0 bar (15.95 -3.92 psi or +0 psi).
2.Stop the pressurization.
3.In the MLG bay, on the pressure gauge at the aft ACT cavity-drain-line: Monitor the air pressure indication. If necessary, pressurize the aft ACT cavity-drain-line between 0.345 bar (5.00 psi) and 0.448 bar (6.50 psi) 0.195 bar (2.83 psi) with the ground pressure generator.	On the pressure gauge at the aft ACT cavity-drain-line: The air pressure indication increases between 0.345 bar (5.00 psi) and 0.448 bar (6.50 psi) 0.195 bar (2.83 psi).
4.Stop the pressurization.
5.If the air pressure is not stable, do the leak test: Do a leak check of the cavity drain-line connections of the ACT(s) in the aft cargo compartment as necessary. Do a leak check of the vent/transfer-pipe shroud connections of the ACT(s) in the aft cargo compartment as necessary. Use a soap solution or a leak detector spray to find the leaks.	Make sure that there are no leaks. If there are leaks, do an approved repair and do this test again.
6.In the MLG bay, on the ground pressure generator: Release the air pressure from the aft ACT cavity-drain-line.	On the pressure gauge at the aft ACT cavity-drain-line: The air pressure indication decreases to 0.0 bar (0 psi). On the pressure gage at ACT AFT1 water-drain-valve interface: The air pressure indication decreases to approximately 0.1 -0.05 bar or +0.05 bar (1.45 -0.73 psi or +0.73 psi). NOTE: The air pressure in the ACT(s) decreases slowly because of the extension of the rubber bladder in the ACT(s). It is not permitted for the air pressure in the ACT(s) to decrease to 0.0 bar (0 psi).
7.In the aft cargo compartment: On the pressure gauge at test port T2, make sure that the air pressure is between 0.345 bar (5.00 psi) and 0.448 bar (6.50 psi) 0.195 bar (2.83 psi) If necessary, adjust the pressure on test port T1 with the ACT PRESSURE-TEST TOOL.	On the pressure gauge at test port T2: The indicator shows the air pressure between 0.345 bar (5.00 psi) and 0.448 bar (6.50 psi) 0.195 bar (2.83 psi). On the pressure gauge at ACT AFT1 water-drain-valve interface: The air pressure indication increases between 0.345 bar (5.00 psi) and 0.448 bar (6.50 psi) 0.195 bar (2.83 psi).
8.Stop the pressurization.
9.In the aft cargo compartment, on the ACT pressure-test tool: Release the air pressure from test port T1. In the blue hydraulic compartment: Open the ACT vent valve (234QM) manually with a screwdriver.	On the pressure gauge at test port T2: The air pressure indication decreases to 0.0 bar (0 psi). On the pressure gauge at the interface of ACT AFT1 water-drain-valve: The air pressure indication decreases to 0.0 bar (0 psi).

Subtask 28-28-00-860-188-D ** ON A/C NOT FOR ALL

F. Put the system back to the serviceable condition.
(1) In the cockpit:
(a) On ACT control-panel 28VU, push to release the MODE SEL pushbutton switch.
(b) Make sure that the MAN legend in the MODE SEL pushbutton switch goes off.
(2) In the blue hydraulic compartment:
(a) If removed for the test, install the ACT vent-valve actuator (91QH) (Ref. AMM TASK 28-28-72-400-001).
(3) In the MLG bay:
(a) Remove the test tools from the aft ACT cavity-drain line.
(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) Install the elbow pipe (7) on the ACT cavity-drain line.
(f) TORQUE the coupling nut (6) to between 37 and 30 m.N (27.29 and 22.12 lbf.ft )

.
(g) Connect the elbow pipe (7) to the T-connection.
(h) TORQUE the coupling nut (5) to between 37 and 30 m.N (27.29 and 22.12 lbf.ft )

.
(4) On the lower fuselage:
(a) Remove the ACT pressure drain-valve-adapter from the ACT water-drain-valve interface.
(b) Install the outer ACT water-drain-valves on the ACT AFT1 and ACT AFT2 (if installed) (Ref. AMM TASK 28-11-47-400-802).
(5) In the aft cargo compartment:
(a) Remove the ACT pressure-test tool from test ports T1 and T2.

5. Close-up
Subtask 28-28-00-410-067-B ** ON A/C NOT FOR ALL

A. Close Access
(1) In the cabin:
(a) Install the applicable cargo ceiling panels and cabin floor panels that follow:

For the pipe connections of ACT AFT1 and ACT AFT2, install 251AG and 251AF (Ref. AMM TASK 53-32-12-400-002)
For the pipe connections of ACT FWD, install 231BMG (Ref. AMM TASK 53-22-12-400-001).

(2) On the lower fuselage:
(a) Install the applicable access panels of the ACT cavity-drain line on the fuselage that follow:

For ACT AFT1, install 197AB (Ref. AMM TASK 53-35-13-400-001)
For ACT AFT2, install 154AR (Ref. AMM TASK 52-42-15-400-001)
For ACT FWD, install 134AR (Ref. AMM TASK 52-42-15-400-001).

(3) In the aft cargo compartment, install cargo sidewall-panel 152FW (Ref. AMM TASK 25-55-11-400-003).
(4) Close the forward and aft cargo-compartment doors (Ref. AMM TASK 52-30-00-860-002).
(5) Close access door 195BB (Ref. AMM TASK 52-42-26-400-801).
(6) Remove the access platform(s).
(7) Close the MLG doors (Ref. AMM TASK 32-12-00-410-001).

Subtask 28-28-00-410-067-E ** ON A/C NOT FOR ALL

A. Close Access
(1) In the cabin:
(a) Install the applicable cargo ceiling panels and cabin floor panels 251AG and 251AF (Ref. AMM TASK 53-22-12-400-001).
(2) On the lower fuselage:
(a) Install the applicable access panels of the ACT cavity-drain line on the fuselage that follow:

For ACT AFT1, install 197AB (Ref. AMM TASK 53-35-13-400-001)
For ACT AFT2 (if installed), install 154AR (Ref. AMM TASK 52-42-15-400-001).

(3) In the aft cargo compartment, install cargo sidewall-panel 152FW (Ref. AMM TASK 25-55-11-400-003).
(4) Close aft cargo-compartment-door 826 (Ref. AMM TASK 52-30-00-860-002).
(5) Close access door 195BB (Ref. AMM TASK 52-42-26-400-801).
(6) Remove the access platform(s).
(7) Close the MLG doors (Ref. AMM TASK 32-12-00-410-001).

Subtask 28-28-00-865-094-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	FUEL/ACT/FUEL PUMP/SPLY	25QH	Q29

Subtask 28-28-00-860-133-A ** ON A/C NOT FOR ALL

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

[Rev.10 from 2021] 2026.04.02 06:17:52 UTC