Functional Check of the Vent/Transfer Pipe Shrouds and ACT Drain Pipe Connectors

TASK 28-28-00-790-004-A
Functional Check of the Vent/Transfer Pipe Shrouds and ACT Drain Pipe Connectors

WARNING: OBEY THE FUEL SAFETY PROCEDURES.

ZONE: 150
ZONE: 151
ZONE: 152

1. Reason for the Job
Refer to the MPD TASK: 282800-18
FUNCTIONAL CHECK OF THE VENT/TRANSFER PIPE SHROUDS AND ACT DRAIN PIPE CONNECTORS
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment

REFERENCE	QTY	DESIGNATION
No specific	1	ACCESS PLATFORM 1M(3 FT)
No specific	2	ADAPTER - EXTENSION, FILLING SYSTEM, DRY AIR
No specific	AR	AIR SOURCE 2 BAR (30 PSI) - REGULATED, FILTERED, DRY
No specific	AR	CAP - BLANKING
No specific	3	GAGE 5 BAR (75 PSI) - PRESSURE
No specific	AR	PLUG - BLANKING
No specific	AR	SAFETY CLIP - CIRCUIT BREAKER
No specific	1	WARNING NOTICE(S)
No specific	Torque wrench: range to between 3.3 and 3.0 m.daN (24.34 and 22.12 lbf.ft )
98D28108562000	AR	ADAPTER, PRESSURE DRAIN - ACT
98D28108658000	2	TOOL-PRESSURE TEST,ACT
99D28108418000	1	ACT VALVE CONTROL BOX

B. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
150	AFT CARGO COMPARTMENT FWD PRESS BULKHEAD TO AFT BULKHEAD OF AFT CARGO COMPARTMENT
151	AFT CARGO COMPARTMENT
152	AFT CARGO COMPARTMENT
153AZ, 192MB, 197PB
151BC, 151CC, 151GC, 154AR, 241EF, 241JF, 251AF, 251AG, 251FF
134AL, 195BB, 197GB, 231JH, 251KG

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 25-55-11-000-002-A	Removal of the Ceiling Panels in the Aft Cargo-Compartment - FR47/FR59
TASK 25-55-11-400-002-A	Installation of the Ceiling Panels in the Aft Cargo-Compartment - FR47/FR59
TASK 28-00-00-910-001-A	Fuel Safety Procedures
TASK 28-11-47-920-001-A	Replacement of the Outer Water Drain-Valve of the ACT
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 28-28-71-000-001-A	Removal of the ACT Isolation-Valve Actuator
TASK 28-28-71-400-001-A	Installation of the ACT Isolation-Valve Actuator
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 31-60-00-860-001-A	EIS Start Procedure
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 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 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 53-42-12-000-001-A	Removal of the Cabin Floor Panels from FR47 thru FR64
TASK 53-42-12-400-001-A	Installation of the Cabin Floor Panels from FR47 thru FR64
Access to Test Points T1 and T2 ** ON A/C NOT FOR ALL
ACT Drain Lines
ACT Cavity Drain Connection ** ON A/C NOT FOR ALL
ACT Vent-Valve-Actuator Position-Indicator 91QH ** ON A/C NOT FOR ALL
ACT Cavity Drain-Connection ** ON A/C NOT FOR ALL
Access to the ACT Cavity Drain-Line (Aft ACT)
Test Arrangement ACT
ACT Valve Control Box ** ON A/C NOT FOR ALL
Test Tool Arrangement ACT ** ON A/C NOT FOR ALL
Access to the ACT Cavity Drain-Line (Forward ACT) ** ON A/C NOT FOR ALL
Test Arrangement ACT ** ON A/C NOT FOR ALL

3. Job Set-up
Subtask 28-28-00-860-148-A ** ON A/C NOT FOR ALL

A. Aircraft Maintenance Configuration
(1) Obey the fuel safety procedures (Ref. AMM TASK 28-00-00-910-001).
(2) Energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-861-002).
(3) Do the EIS start procedure (upper ECAM DU and lower ECAM DU only)
(Ref. AMM TASK 31-60-00-860-001).
(4) In the cockpit, on the ECAM control panel:
(a) Push the FUEL pushbutton switch:

The FUEL page comes into view on the lower ECAM DU.

(b) If the Additional Center Tanks (ACTs) is (are) installed, make sure that the ACT indication is shown on the ECAM FUEL page.
(5) If the ACT(s) is (are) installed, defuel all the ACT(s) (Ref. AMM TASK 28-25-00-650-001).
(6) If the ACT(s) is (are) installed, drain the remaining fuel from the ACT(s) (Ref. AMM TASK 28-25-00-650-005).
(7) Open refuel/defuel control panel-door 192MB.
(8) Open refuel/defuel panels 800VU and 801VU and make sure that:

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

(9) Close refuel/defuel panels 800VU and 801VU.
(10) Close refuel/defuel control panel-door 192MB.
(11) Put the WARNING NOTICE(S) in position on these panels to tell persons not to operate the refuel/defuel system:

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

Subtask 28-28-00-010-095-A ** ON A/C NOT FOR ALL

B. Get Access
(1) If the ACT(s) is (are) installed, open the aft cargo-compartment door (Ref. AMM TASK 52-30-00-860-001):
(a) Get access to the ACT air shutoff-valve and ACT test ports T1 and T2

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

(b) Remove the applicable ceiling panel 151GC or 151CC or 151BC (Ref. AMM TASK 25-55-11-000-002).
(2) Open the main gear doors to get access to: (Ref. AMM TASK 32-12-00-010-001)

The ACT fuel transfer-pump (1QH)
The ACT transfer-valve actuator (6QH)
The ACT cavity drain-line in the Main Landing Gear (MLG) bay.

(3) Put an ACCESS PLATFORM 1M(3 FT) on the left side of the MLG bay.
(4) If the ACT(s) is (are) installed, on the lower fuselage, get access to the ACT cavity drain-line below the ACT(s):
(a) Remove the applicable access panels 154AR, 197PB and 153AZ from the lower fuselage.
(5) If the first step of this leak check can find a possible leak on the pipe shroud connectors, remove the cabin floor panels:
(a) In the cabin, get access to the ACT vent/transfer pipe-shroud-connectors:
1 Remove the applicable cabin floor panels and cargo ceiling panels:

241EF and 241JF (Ref. AMM TASK 53-32-12-000-002)
251AG and/or 251AF and/or 251FF (Ref. AMM TASK 53-42-12-000-001).

Subtask 28-28-00-860-148-B ** ON A/C NOT FOR ALL

C. Aircraft Maintenance Configuration
(1) Obey the fuel safety procedures (Ref. AMM TASK 28-00-00-910-001).
(2) Energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-861-002).
(3) Do the EIS start procedure (upper ECAM DU and lower ECAM DU only)
(Ref. AMM TASK 31-60-00-860-001).
(4) In the cockpit, on the ECAM control panel:
(a) Push the FUEL pushbutton switch:

The FUEL page comes into view on the lower ECAM DU.

(b) If the Additional Center Tanks (ACTs) is (are) installed, make sure that the ACT indication is shown on the ECAM FUEL page.
(5) Open refuel/defuel control panel-door 192MB.
(6) Open refuel/defuel panels 800VU and 801VU and make sure that:

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

(7) Close refuel/defuel panels 800VU and 801VU.
(8) Close refuel/defuel control panel-door 192MB.
(9) Put the WARNING NOTICE(S) in position on these panels to tell persons not to operate the refuel/defuel system:

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

Subtask 28-28-00-010-095-D ** ON A/C NOT FOR ALL

D. Get Access
(1) Open the main gear doors to get access to: (Ref. AMM TASK 32-12-00-010-001)

The ACT fuel transfer-pump (1QH)
The ACT transfer-valve actuator (6QH)
The ACT forward isolation-valve actuator (92QH)
The ACT cavity drain-line in the Main Landing Gear (MLG) bay.

(a) Put an ACCESS PLATFORM 1M(3 FT) on the left side of the MLG bay.
(2) Open access door 195BB to get access to the ACT vent-valve actuator (91QH).
(3) If the ACT(s) is (are) installed, on the lower fuselage, get access to the ACT cavity drain-lines below the applicable ACT(s):
(a) Remove the access panels from the lower fuselage:

For ACT AFT1, remove panels 197PB and 153AZ
For ACT AFT2, remove panel 197GB
For the ACT FWD (if installed), remove panel 134AL.

(4) In the cabin, get access to the ACT vent/transfer-pipe connectors of ACT AFT1 and the ACT FWD (if installed):

NOTE: It is necessary to remove only the cabin floor panels, the first step of this leak check can find a possible leak on the pipe shroud connectors.

NOTE: The removal of the cabin floor panels is only necessary, if the applicable ACT(s) is(are) installed.

For the pipe connection of the ACT FWD (if installed), remove floor panel 231JH and the applicable cargo ceiling panel (Ref. AMM TASK 53-22-12-000-001).
For the pipe connection of ACT AFT1, remove floor panel 251KG and the applicable cargo ceiling panel (Ref. AMM TASK 53-32-12-000-002).

Subtask 28-28-00-865-100-A ** ON A/C NOT FOR ALL

E. 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 28-28-00-860-149-A ** ON A/C NOT FOR ALL

A. Preparation for the Test

NOTE: The steps (1) and (2) are necessary only if the ACT(s) is (are) installed.

(1) In the cockpit, on fuel control-panel 40VU:
(a) Push the ACT pushbutton switch to open the ACT transfer valve (165QM).
(b) Make sure that the FAULT light and the FWD light in the ACT pushbutton switch are on.
(2) In the MLG bay:
(a) Make sure that the ACT fuel transfer-pump (1QH) is in the off position and you hear no noise from the pump.
(b) Make sure that the ACT transfer-valve actuator (6QH) is shown in the open position.
(3) On the lower fuselage, close the applicable ACT cavity drain-lines on the ACT(s) as follows:

ACT Cavity Drain Connection ** ON A/C NOT FOR ALL

(a) Loosen the nut (1).
(b) Disconnect the hose (3) from the drain fitting (2).
(c) Install a PLUG - BLANKING (4) on the disconnected hose end.
(d) Put a CAP - BLANKING on the drain fitting (2).

Subtask 28-28-00-860-149-C ** ON A/C NOT FOR ALL

A. Preparation for the Test
(1) If the ACT(s) is (are) installed, in the cockpit, on ACT control-panel 28VU:
(a) Push the MODE SEL pushbutton switch to open the ACT transfer valve (165QM).
(b) Make sure that the MAN light in the MODE SEL pushbutton switch is ON.
(2) If the ACT(s) is (are) installed, in the MLG bay:
(a) Make sure that the ACT fuel transfer-pump (1QH) is in the off position and you hear no noise from the pump.
(b) Make sure that the ACT transfer-valve actuator (6QH) is shown in the open position.
(c) Make sure that the ACT forward-isolation-valve actuator (92QH) is shown in the open position:

NOTE: If the ACT FWD is installed in the forward cargo compartment, airbus recommeds you to open the ACT forward isolation-valve.

1 If the ACT forward isolation-valve (236QM) is closed, remove the ACT forward-isolation-valve actuator (92QH) (Ref. AMM TASK 28-28-71-000-001) and open the valve manually.
(3) In the blue hydraulic compartment:
(a) Make sure that the ACT vent-valve actuator (91QH) is shown in the open position.

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

(b) If the ACT vent valve (234QM) is closed, remove the ACT vent-valve actuator (91QH) (Ref. AMM TASK 28-28-72-000-001) and open the valve manually.
(4) If the ACT(s) is (are) installed, on the lower fuselage, close the applicable ACT cavity drain-lines on the ACT(s) as follows:

ACT Cavity Drain-Connection ** ON A/C NOT FOR ALL

(a) Loosen the nut (2).
(b) Disconnect the hose (3) from the drain fitting (1).
(c) Install a PLUG - BLANKING (4) on the disconnected hose end (3).
(d) Put a CAP - BLANKING on the drain fitting (1).

Subtask 28-28-00-480-050-A ** ON A/C NOT FOR ALL

B. Installation of the Test Tool

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) On the right side of the MLG bay, install a 98D28108658000 TOOL-PRESSURE TEST,ACT on the ACT cavity drain-line:
(a) Loosen the nut (5) and disconnect the elbow (7) from the T-connection.
(b) Put a CAP - BLANKING on the T-connection.
(c) Loosen the nut (6) of the aft ACT cavity-drain-line and remove the elbow (7).
(d) Connect the 98D28108658000 TOOL-PRESSURE TEST,ACT to the cavity drain line.

NOTE: If the 98D28108658000 TOOL-PRESSURE TEST,ACT is not available, you can use AIR SOURCE 2 BAR (30 PSI) - REGULATED, FILTERED, DRY as an alternative and a GAGE 5 BAR (75 PSI) - PRESSURE with the applicable ADAPTER - EXTENSION, FILLING SYSTEM, DRY AIR.

Subtask 28-28-00-790-053-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.

C. Leak Test of the ACT Vent/Transfer Pipe Shrouds and Drain-Pipe Connectors of the ACT(s) in the Aft Cargo-Compartment

ACTION	RESULT
1.In the MLG bay, at the ACT cavity-drain-line connection: Start the ground pressure generator Carefully pressurize the drain line to 1.4 bar (20 psi).	On the ground-pressure-generator pressure gage: The air pressure in the drain line increases to 1.4 bar (20 psi).
2.In the MLG bay, at the ACT cavity-drain-line connection: Close the ground-pressure generator shutoff-valve Stop the ground pressure generator.	On the ground-pressure-generator pressure gage: Make sure that an air pressure of 1.4 bar (20 psi) is stable for approximately 15 minutes.
3.If the air pressure is not stable, continue the test: Remove the applicable cabin floor panels to get access to the ACT vent/transfer pipe-shrouds Do a leak check on the ACT vent/transfer pipe-shrouds Do a leak check on the ACT cavity drain-lines Use a soap solution or a leak detector spray to find the leak.	On the ACT vent/transfer pipe-shrouds and the ACT cavity drain-lines: Make sure that there are no leaks. NOTE: Leaks are not permitted. If you find a leak, do an approved repair and do the test again.
4.In the MLG bay, at the ACT cavity-drain-line connection: Carefully release the air pressure from the drain line.	On the ground-pressure-generator pressure gage: The air pressure decreases to 0 bar (0 psi).

Subtask 28-28-00-790-053-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.

C. Leak Test of the ACT Vent/Transfer Pipe Shrouds and Drain-Pipe Connectors of ACT AFT1 in the Aft Cargo-Compartment

ACTION	RESULT
1.In the MLG bay, at the ACT cavity-drain-line connection: Start the ground pressure generator Carefully pressurize the drain line to 1.4 bar (20 psi).	On the ground-pressure-generator pressure gage: The air pressure in the drain-line increases to 1.4 bar (20 psi).
2.In the MLG bay, at the ACT cavity-drain-line connection: Close the ground-pressure generator shutoff-valve Stop the ground pressure generator.	On the ground-pressure-generator pressure gage: Make sure that an air pressure of 1.4 bar (20 psi) is stable for approximately 15 minutes.
3.If the air pressure is not stable, continue the test: Remove the applicable cabin floor panels to get access to the ACT vent/transfer pipe-shrouds Do a leak check on the ACT vent/transfer pipe-shrouds Do a leak check on the ACT cavity drain-lines Use a soap solution or a leak detector spray to find the leak.	On the ACT vent/transfer pipe shrouds and the ACT cavity drain-lines: Make sure there are no leaks. NOTE: Leaks are not permitted. If you find a leak, do an approved repair and do the test again.
4.In the MLG bay, at the ACT cavity-drain-line connection: Carefully release the air pressure from the drain line.	On the ground-pressure-generator pressure gage: The air pressure decreases to 0 bar (0 psi).

Subtask 28-28-00-080-050-B ** ON A/C NOT FOR ALL

D. Removal of the Test Tool

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

(1) In the MLG bay, remove the 98D28108658000 TOOL-PRESSURE TEST,ACT from the ACT cavity drain-line:
(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.
(2) Assemble the ACT cavity drain-line:
(a) Connect the elbow (7) to the ACT cavity drain-line and tighten the nut (6).
(b) Connect the elbow (7) to T-connection and tighten the nut (5).

Subtask 28-28-00-480-051-A ** ON A/C NOT FOR ALL

E. Installation of the Test Tool

NOTE: The steps that follow are necessary only if the ACT(s) is (are) installed.

(1) In the aft cargo compartment:
(a) Install an 99D28108418000 ACT VALVE CONTROL BOX on the ACT air-shutoff-valve actuator (3QH):

ACT Valve Control Box ** ON A/C NOT FOR ALL

1 Disconnect connector 3QH-A from the ACT air-shutoff-valve actuator (3QH).
2 Connect the 99D28108418000 ACT VALVE CONTROL BOX to the ACT air-shutoff-valve actuator (3QH).
3 Connect the second connector of the 99D28108418000 ACT VALVE CONTROL BOX to connection plug 3QH-A.
4 Open the ACT air shutoff-valve (168QM) with the 99D28108418000 ACT VALVE CONTROL BOX.
5 Make sure that the indication for the ACT air-shutoff-valve actuator (3QH) is in the OPEN position.
6 Close the ACT vent valve(s) (167QM1 and 167QM2) of the ACT(s) installed on the aircraft with the 99D28108418000 ACT VALVE CONTROL BOX:

NOTE: The ACT vent valve(s) (167QM1 and 167QM2) are installed on the ACT(s). You can see the position of the valves only on the indication for the applicable ACT vent-valve actuator (4QH):

For the ACT vent-valve actuator (4QH1) in the cabin, when you remove the applicable cabin floor panel and the cargo ceiling panel above ACT1
For the ACT vent-valve actuator (4QH2) in the aft cargo compartment, when you remove the right impact wall.

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

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

(2) Remove the outer ACT water-drain-valve(s) from the ACT(s) (Ref. AMM TASK 28-11-47-920-001):
(a) Install an 98D28108562000 ADAPTER, PRESSURE DRAIN - ACT on the ACT water-drain-valve interface.

NOTE: This is to monitor the air pressure in the ACT(s).

Subtask 28-28-00-480-051-B ** ON A/C NOT FOR ALL

E. Installation of the Test Tool

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) On the right side of the MLG bay, install the 98D28108658000 TOOL-PRESSURE TEST,ACT on the forward ACT cavity-drain-line:
(a) Disconnect the elbow nut (2) from the T-connection.
(b) Put the PLUG-BLANKING in each disconnected line end.
(c) Connect AIR SOURCE 2 BAR (30 PSI) - REGULATED, FILTERED, DRY and a GAGE 5 BAR (75 PSI) - PRESSURE with the applicable ADAPTER - EXTENSION, FILLING SYSTEM, DRY AIR to the forward ACT cavity-drain-line.

Subtask 28-28-00-480-056-A ** ON A/C NOT FOR ALL

F. Installation of the Test Tool

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) On the right side of the MLG bay, install the 98D28108658000 TOOL-PRESSURE TEST,ACT on the ACT cavity drain-line:
(a) Loosen the nut (5) and disconnect the elbow (7) from the T-connection.
(b) Put a CAP - BLANKING on the T-connection.
(c) Loosen the nut (6) of the aft ACT cavity-drain-line and remove the elbow (7).
(d) Connect the 98D28108658000 TOOL-PRESSURE TEST,ACT to the cavity drain line.

NOTE: If the 98D28108658000 TOOL-PRESSURE TEST,ACT is not available, you can use an AIR SOURCE 2 BAR (30 PSI) - REGULATED, FILTERED, DRY as an alternative with a GAGE 5 BAR (75 PSI) - PRESSURE and the applicable ADAPTER - EXTENSION, FILLING SYSTEM, DRY AIR.

Subtask 28-28-00-860-277-A ** ON A/C NOT FOR ALL

G. Put the system back to the serviceable condition.

ACT Cavity Drain Connection ** ON A/C NOT FOR ALL

(1) If the ACT(s) is (are) installed, on the lower fuselage, at the ACT cavity drain:
(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 ACT cavity drain-line to the ACT.
(e) Install the hose (3) on the drain fitting (2).
(f) Do not twist the hose (3) when you tighten the nut (1).

Subtask 28-28-00-790-054-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.

H. Leak Test of the ACT Vent/Transfer Pipe-Shrouds between ACT1 and ACT2 or the Blank Flanges of ACT1

NOTE: The steps that follow are necessary only if the ACT(s) is (are) installed.

ACTION	RESULT
1.In the aft cargo compartment, on the 98D28108658000 TOOL-PRESSURE TEST,ACT: Pressurize test port T1 to 1.00 bar (15 psi).	On the pressure gage at test port T2: The air pressure indication increases to 0.195 bar (3 psi). On the pressure gage at the ACT water-drain-valve interface: The air pressure indication increases to 0.195 bar (3 psi). NOTE: It takes approximately 15 minutes to pressurize all the ACT(s). NOTE: The ACT pressure holding-valve opens at approximately 0.20 bar (3 psi), if the air pressure in the ACT becomes too high. NOTE: The burst discs of the ACT vent system breaks at approximately 1.1 +0.0 bar or -0.1 bar (16 +0 psi or -1 psi), if the ACT pressure holding-valve does not open.
2.In the MLG bay, on the pressure gage at the ACT cavity drain-line: Start the ground pressure generator Carefully pressurize the ACT cavity drain-line to 0.20 bar (3 psi) Monitor the air pressure indication.	On the pressure gage at the ACT cavity drain-line: The air pressure indication increases to 0.20 bar (3 psi) and is stable for the test.
3.If the air pressure does not increase, continue the test: A.With ACT1 and ACT2 installed: Remove the applicable cabin floor panels to get access to the ACT vent/transfer pipe-shrouds between ACT1 and ACT2 Do a leak check on the pipe shroud connections between ACT1 and ACT2 Do a leak check on the ACT cavity-drain-line connections. B.With ACT1 installed: Remove the applicable cabin floor panels to get access to the vent/transfer pipe blank-flanges installed on ACT1 Do a leak check on the blank flanges interfaces with ACT1 Do a leak check on the ACT cavity-drain-line connections Use a soap solution or a leak detector spray to find the leak.	Make sure that there are no leaks. If you find a leak, do an approved repair and do the test again.
4.In the MLG bay, on the ground pressure generator at the ACT cavity drain-line: Release the air pressure from the ACT cavity drain-line.	On the pressure gage at the ACT cavity drain-line: The air pressure indication decreases to 0 bar (0 psi).
5.In the aft cargo compartment: On the 98D28108658000 TOOL-PRESSURE TEST,ACT, release the air pressure from test port T1 On the 99D28108418000 ACT VALVE CONTROL BOX, open the ACT vent valves.	On the pressure gage at test port T2: The air pressure indication decreases to 0 bar (0 psi). On the pressure gage at the interface of the ACT water-drain valve: The air pressure indication decreases to 0 bar (0 psi).

Subtask 28-28-00-080-051-A ** ON A/C NOT FOR ALL

I. Removal of Test Tool

NOTE: The steps that follow are necessary only if the ACT(s) is (are) installed.

(1) On the lower fuselage:
(a) Remove the 98D28108562000 ADAPTER, PRESSURE DRAIN - ACT from the ACT water-drain-valve interface.
(b) Install the outer ACT water-drain-valves on the ACT(s) (Ref. AMM TASK 28-11-47-920-001).

(2) In the aft cargo-compartment:
(a) Remove the 98D28108658000 TOOL-PRESSURE TEST,ACT from the test ports T1 and T2.
(b) Disconnect the 99D28108418000 ACT VALVE CONTROL BOX from the connector-plug 3QH-A and the ACT air-shutoff-valve actuator (3QH).
(c) Connect the connector 3QH-A to the ACT air shut-off-valve actuator (3QH).

Subtask 28-28-00-790-054-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.

J. Leak Test of the ACT Vent/Transfer Pipe Shrouds and Drain-Pipe Connectors of ACT FWD in the Forward Cargo-Compartment

ACTION	RESULT
1.In the MLG bay, on the forward ACT cavity-drain-line: Start the ground pressure generator Carefully pressurize the ACT cavity drain-line to 1.4 bar (20 psi).	On the ground-pressure-generator pressure gage: The air pressure in the ACT cavity drain-line increases to 1.4 bar (20 psi).
2.Close the ground-pressure generator shutoff-valve.	On the ground-pressure-generator pressure gage: Make sure that an air pressure of 1.4 bar (20 psi) is stable for approximately 15 minutes.
3.If the air pressure is not stable, continue the test: Remove the applicable cabin floor panels to get access to the ACT vent/transfer pipe-shrouds Do a leak check on the forward ACT-pipe shroud-connections Do a leak check on the forward ACT-cavity drain-line connections Use a soap solution or a leak detector spray to find the leak.	Make sure that there are no leaks. NOTE: Leaks are not permitted. If you find a leak, do an approved repair and do the test again.
4.In the MLG bay, on the forward ACT cavity-drain-line: Stop the ground pressure generator Carefully release the air pressure from the ACT cavity drain-line.	On the ground-pressure-generator pressure gage: The air pressure in the drain-line decreases to 0 bar (0 psi).

Subtask 28-28-00-080-051-B ** ON A/C NOT FOR ALL

K. Removal of the Test Tool

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

(1) In the MLG bay, remove the 98D28108658000 TOOL-PRESSURE TEST,ACT from the forward ACT cavity drain-line:
(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 ACT cavity drain-line to T-connection and tighten the nuts (1) and (2).

Subtask 28-28-00-080-056-A ** ON A/C NOT FOR ALL

L. Removal of the Test Tool

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

(1) If the ACT(s) is(are) installed, in the MLG bay, remove the 98D28108658000 TOOL-PRESSURE TEST,ACT from the ACT cavity drain-line:
(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.
(2) If the ACT(s) is(are) installed, assemble the ACT cavity drain-line as follows:
(a) Connect the elbow (7) to the ACT cavity drain-line and tighten the nut (6).
(b) Connect the elbow (7) to the T-connection and tighten the nut (5).

Subtask 28-28-00-860-185-A ** ON A/C NOT FOR ALL

M. Put the system back to the serviceable condition.

ACT Cavity Drain Connection ** ON A/C NOT FOR ALL

NOTE: The steps (2) and (3) are necessary only if the ACT(s) is (are) installed.

(1) On the lower fuselage, at the ACT cavity drain:
(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 ACT cavity drain-line to the ACT.
(e) Install the hose (3) on the drain fitting (2) with the nut (1).

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.

(f) TORQUE the nut (1) to between 3.3 and 3.0 m.daN (24.34 and 22.12 lbf.ft )

.
(2) In the cockpit, on fuel conrol-panel 40VU:
(a) Push and release the ACT pushbutton switch.
(b) Make sure that the FAULT light and the FWD light in the ACT pushbutton switch are off.
(3) In the MLG bay:
(a) Make sure that the ACT transfer-valve actuator (6QH) is shown in the closed position.

Subtask 28-28-00-860-185-C ** ON A/C NOT FOR ALL

M. Put the system back to the serviceable condition.

ACT Cavity Drain-Connection ** ON A/C NOT FOR ALL

(1) If the ACT(s) is (are) installed, on the lower fuselage, at the ACT cavity drain:
(a) Remove the PLUG-BLANKING from each disconnected line end.
(b) Remove the CAP - BLANKING from the drain fitting (1).
(c) Clean the component interfaces and the adjacent area.
(d) Do an inspection of the component interfaces and the adjacent area.
(e) Connect the ACT cavity drain-lines to the ACT(s).
(f) Install the hose (3) on the drain fitting (1) with 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.

(g) TORQUE the nut (2) to between 3.3 and 3.0 m.daN (24.34 and 22.12 lbf.ft )

.
(2) If the ACT(s) is (are) installed, in the cockpit, on ACT control-panel 28VU:
(a) Push and release the MODE SEL pushbutton switch.
(b) Make sure that the "FAULT" light and the "MAN" light of the MODE SEL pushbutton switches are OFF.
(c) If the ACT(s) is (are) installed, in the MLG bay:
1 Make sure that the indicator for the ACT transfer-valve actuator (6QH) shows the closed position.
(3) Install the ACT forward-isolation valve-actuator (92QH) (Ref. AMM TASK 28-28-71-400-001).
(4) Install the ACT vent-valve actuator (91QH) (Ref. AMM TASK 28-28-72-400-001).

5. Close-up
Subtask 28-28-00-410-075-A ** ON A/C NOT FOR ALL

A. Close Access
(1) In the aft cargo-compartment, install the applicable ceiling panels (Ref. AMM TASK 25-55-11-400-002).
(2) Remove the access platform(s).
(3) Close the aft cargo-compartment door (Ref. AMM TASK 52-30-00-860-002).
(4) Close the MLG doors after the access (Ref. AMM TASK 32-12-00-410-001).
(5) If the ACT(s) is (are) installed, on the lower fuselage:
(a) Install the applicable access panels of the ACT cavity-drain.

(6) In the cabin:
(a) Install the applicable cargo ceiling panels and the cabin floor panels (Ref. AMM TASK 53-32-12-400-002) (Ref. AMM TASK 53-42-12-400-001).

Subtask 28-28-00-410-075-D ** ON A/C NOT FOR ALL

A. Close Access
(1) Remove the access platform(s).
(2) Close access door 195BB.
(3) Close the MLG doors after the access (Ref. AMM TASK 32-12-00-410-001).
(4) If the ACT(s) is (are) installed, on the lower fuselage:
(a) Install the applicable access panels to the ACT cavity-drain:

For ACT AFT1, install panels 153AZ and 197PB
For ACT AFT2, install panel 197GB
For the ACT FWD (if installed), install panel 134AL.

(5) In the cabin:
(a) Install the applicable cargo ceiling panels and the cabin floor panels (Ref. AMM TASK 53-22-12-400-001) (Ref. AMM TASK 53-32-12-400-002).

Subtask 28-28-00-865-122-A ** ON A/C NOT FOR ALL

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

NOTE: This procedure is applicable only if the ACT(s) is (are) installed.

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 28-28-00-860-150-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] 2026.04.01 07:22:20 UTC