Functional Check for Leakage of the Vent/Transfer Pipe Shrouds, the ACT Tank Casing and the ACT Drain System

TASK 28-28-00-790-804-A
Functional Check for Leakage of the Vent/Transfer Pipe Shrouds, the ACT Tank Casing and the ACT Drain System

WARNING: OBEY THE FUEL SAFETY PROCEDURES.

WARNING: PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU START A TASK ON OR NEAR:

THE FLIGHT CONTROLS
THE FLIGHT CONTROL SURFACES
THE LANDING GEAR AND THE RELATED DOORS
COMPONENTS THAT MOVE.

MOVEMENT OF COMPONENTS CAN KILL OR CAUSE INJURY TO PERSONS AND/OR CAN CAUSE DAMAGE TO THE EQUIPMENT.

ZONE: 130
ZONE: 147
ZONE: 150

1. Reason for the Job
Refer to the MPD TASK: 282800-22
FUNCTIONAL CHECK FOR LEAKAGE OF THE VENT/TRANSFER PIPE SHROUDS, THE ACT TANK CASING AND THE ACT DRAIN SYSTEM.

NOTE: Two persons are necessary for this procedure.

NOTE: This procedure is applicable only when the ACT is installed.

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

REFERENCE	QTY	DESIGNATION
No specific	2	AIR SOURCE 1.5 BAR (21.75 PSI) MAX
No specific	1	CAP - BLANKING
No specific	3	GAGE 5 BAR (75 PSI) - PRESSURE
No specific	AR	SAFETY CLIP - CIRCUIT BREAKER
No specific	AR	WARNING NOTICE(S)
No specific	Torque wrench: range to between 22 and 18 m.N (16.22 and 13.27 lbf.ft )
No specific	Torque wrench: range to between 37 and 30 m.N (27.29 and 22.12 lbf.ft )
98D28108562000	1	ADAPTER, PRESSURE DRAIN - ACT
98D28108658000	1	TOOL-PRESSURE TEST,ACT

B. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
130	FWD CARGO COMPT AFT BULKHEAD OF AVNCS COMPT TO FWD PRESSURE BULKHEAD OF WING CENTER BOX
147	MAIN GEAR WELL AND HYDRAULIC COMPARTMENT
150	AFT CARGO COMPARTMENT FWD PRESS BULKHEAD TO AFT BULKHEAD OF AFT CARGO COMPARTMENT
151NC, 192MB

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 25-54-12-000-002-A	Removal of the Ceiling Panels in the Forward Cargo Compartment
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 28-11-47-000-802-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 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 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
Access To Test Ports T1 and T2
ACT Vent-Valve-Actuator Position-Indicator 91QH
Test-Tool Arrangement ACT
Test-Tool Arrangement ACT
Access to the ACT Cavity Drain-Line (Aft ACT)
Test Arrangement - Forward ACT Cavity-Drain-Line
Test Arrangement - Aft ACT Cavity-Drain-Line
Access to the ACT Cavity Drain-Line (Forward ACT)

3. Job Set-up
Subtask 28-28-00-860-262-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 the Additional Center Tank(s) (ACT(s)) (Ref. AMM TASK 28-25-00-650-001).
(4) Drain the remaining fuel from the applicable ACT(s) (Ref. AMM TASK 28-25-00-650-005).
(5) Open quick-release access door 192MB.
(6) On refuel/defuel control panels 800VU and 801VU, make sure that:

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

(7) Put a WARNING NOTICE(S) in position to tell persons not to operate the refuel/defuel system:

On refuel/defuel control panels 800VU and 801VU.

(8) Close quick-release access door 192MB.
(9) Put the WARNING NOTICE(S) in position on these panels to tell persons not to operate the refuel/defuel system:

Fuel control-panel 40VU.

Subtask 28-28-00-865-185-A ** ON A/C NOT FOR ALL

B. 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

Subtask 28-28-00-010-132-A ** ON A/C NOT FOR ALL

C. Get Access
(1) Open the Main Landing Gear (MLG) doors for access (Ref. AMM TASK 32-12-00-010-001).
(2) Open the aft cargo compartment door (Ref. AMM TASK 52-30-00-860-001).
(3) Remove ceiling panel 151NC to get access to test ports T1 and T2 (Ref. AMM TASK 25-55-11-000-002)

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

(4) On the lower fuselage, to 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.

(a) Remove the applicable cavity-drain service panels.
(5) In the cabin, to get access to the ACT vent/transfer-pipe shroud connectors:
(a) Remove the applicable cabin floor panels and the cargo ceiling panels above the ACT(s):

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

NOTE: To do the leak check of the vent and the fuel-pipe cavity drain between ACT AFT1, ACT AFT2 and the ACT FWD (if installed):

It is necessary to use the access openings in the cabin floor and the cargo ceiling.

1 Safety your tools with a strip in your hand, to make sure that the tool cannot fall into the cargo compartment.
2 Remove the applicable cabin floor panels above the ACT(s):

For the pipe connections of ACT AFT1 and ACT AFT2, remove the applicable cabin floor panels (Ref. AMM TASK 53-32-12-000-002)
For the pipe connections of the ACT FWD (if installed), remove cabin floor panel 231AMG (Ref. AMM TASK 53-22-12-000-001)
Remove the applicable maintenance panels on the cargo ceiling panels above the ACT(s).

4. Procedure
Subtask 28-28-00-860-263-B ** ON A/C NOT FOR ALL

A. Preparation for the Test
(1) In the cockpit:
(a) Do the operational test of the annunciator light test-system (Ref. AMM TASK 33-14-00-710-001).

Make sure that all the lights on ACT control panel 28VU are ON during the test.

(b) On ACT control panel 28VU:
1 Make sure that the ACT XFR rotary-switch is in the OFF position.
2 Push the MOD SEL pushbutton-switch:

Make sure that the MAN legend in the MOD SEL pushbutton-switch is ON.

NOTE: ACT air-shut-off valve 233QM opens, ACT vent-valve-actuator 91QH closes, ACT fuel-inlet-valve-actuator 94QH1 stays closed, ACT fuel-transfer-valve-actuator 6QH opens and forward-vent isolation-valve-actuator 93QH (if the ACT FWD is installed) is open at this time.

(2) If ACT FWD is installed, make sure that the indication for the forward vent-isolation-valve actuator (93QH) is in the open position.
(3) To do the test of AFT ACT(s):

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

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

Test Arrangement - Forward ACT Cavity-Drain-Line ** ON A/C NOT FOR ALL

(a) Disconnect the APU drain-line from the ACT cavity drain-line as follows:
1 Loosen the coupling nut (3) and disconnect the elbow pipe (4) from the T-connection.
2 Loosen the coupling nut (5) and remove the elbow pipe (4).
3 Put a CAP - BLANKING on the T-connection.
(b) Make sure that each installed ACT is connected with the applicable ACT cavity drain-line.

NOTE: If the provisions for ACT AFT 2 are installed and ACT AFT 2 is not installed, put a CAP - BLANKING on ACT AFT2 cavity-drain connection.

NOTE: Airbus recommends you to use a 98D28108658000 TOOL-PRESSURE TEST,ACT as an alternative and connect it to ACT cavity-drain line.

(d) Connect an AIR SOURCE 1.5 BAR (21.75 PSI) MAX to test port T1 and a GAGE 5 BAR (75 PSI) - PRESSURE to the test port T2.

NOTE: Airbus recommends you to use a 98D28108658000 TOOL-PRESSURE TEST,ACT as an alternative and connect it to test ports T1 and T2.

(4) On the lower fuselage:

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

(a) Remove the ACT outer-water drain-valves from ACT AFT1 (Ref. AMM TASK 28-11-47-000-802).
(b) Connect a 98D28108562000 ADAPTER, PRESSURE DRAIN - ACT to the water drain-valve interface of ACT AFT1.

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

Subtask 28-28-00-790-061-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. Functional Check for Leakage of the Vent/Transfer Pipe Shrouds, the ACT Tank Casing and the ACT Drain System (Aft ACT(s))

NOTE: Access to ACT AFT1 pressurization connection is not possible, if ACT AFT2 is installed.

ACTION	RESULT
1. Make sure that the cavity-drain pressurization tool is in the closed position.
2.In the aft cargo compartment: Pressurize test port T1 to 20 -1 psi or +1 psi (1.3790 -0.0689 bar or +0.0689 bar).	On the pressure gage, at test port T2: The air pressure indication increases to 5 -0 psi or +1.5 psi (0.3447 -0 bar or +0.1034 bar). NOTE: The pressure inside the aft ACTs will be controlled to 5 -0 psi or +1.5 psi (0.3447 -0 bar or +0.1034 bar) by the Pressure Regulation Valve (PRV) and not more than this. NOTE: When the ACTs are pressurized, the pressure in the cavity drain system will increase because of the expanded bladder tank.
3.Stop the pressurization.
4.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 5 -0 psi or +1.5 psi (0.3447 -0 bar or +0.1034 bar).	On the pressure gage, at the aft ACT-cavity drain-line: The air pressure indication is not more than 6.5 psi (0.45 bar).
5.Stop the pressurization.	The pressure stays constant for 15 minutes.
6.If the pressure at the cavity drain line does not stay constant for 15 minutes, find the leak(s): Do a leak check of the cavity drain-line connections of the aft ACT(s) and the vent/transfer pipe shroud-connections of the aft ACT(s). Use a soap solution or a leak detector spray to find leaks.	Make sure that there are no leaks. If there are leaks, do an approved repair and do this test again.
7.Release the pressure from the aft ACT(s) cavity-drain-line: In the MLG bay, on the pressurization tool open the shut off valve.	NOTE: The air pressure in the ACT(s) decreases slowly because of the extension of the bladder tank in the ACT(s). It is not permitted for the air pressure in the ACT(s) to decrease to 0 psi (0 bar). On the pressure gage, at the cavity drain line of the aft ACT(s): The air pressure indication decreases to 0 psi (0 bar).
8.On ACT FUEL control-panel 28VU: 9.Release the MOD SEL pushbutton switch: Make sure that the MAN legend is off.

Subtask 28-28-00-020-055-A ** ON A/C NOT FOR ALL

C. Removal of the Test Tools from Aft ACT(s) Cavity-Drain-Line

Test Arrangement - Aft ACT Cavity-Drain-Line ** ON A/C NOT FOR ALL

(1) Disconnect the AIR SOURCE 1.5 BAR (21.75 PSI) MAX and the GAGE 5 BAR (75 PSI) - PRESSURE from the aft ACT(s) cavity-drain-line.
(2) If you install the 98D28108658000 TOOL-PRESSURE TEST,ACT as an alternative, then disconnect it from the ACT cavity drain-line.

Subtask 28-28-00-860-264-B ** ON A/C NOT FOR ALL

D. Put the system back to the serviceable condition.
(1) Remove the PLUG-BLANKING from each disconnected line end.
(2) Clean the component interfaces and the adjacent area.
(3) Do an inspection of the component interfaces and the adjacent area.
(4) In the aft cargo compartment:
(a) Disconnect the AIR SOURCE 1.5 BAR (21.75 PSI) MAX and the GAGE 5 BAR (75 PSI) - PRESSURE from test ports T1 and T2.
(b) If you install the 98D28108658000 TOOL-PRESSURE TEST,ACT as an alternative, then disconnect it from test ports T1 and T2.
(5) On the lower fuselage:

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

(a) Disconnect the 98D28108562000 ADAPTER, PRESSURE DRAIN - ACT from the applicable water drain-valve interface.
(b) Install the ACT outer water-drain-valves on the ACT FWD (if installed) and ACT AFT1 (Ref. AMM TASK 28-11-47-400-802).
(6) For the aft ACT(s) cavity drain-line:

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

(a) Remove the PLUG-BLANKING from each disconnected line end.
(b) Install the elbow pipe (4) on the ACT cavity-drain line.
(c) TORQUE the coupling nut (5) to between 37 and 30 m.N (27.29 and 22.12 lbf.ft )

.
(d) Connect the elbow pipe (4) to the T-connection.
(e) TORQUE the coupling nut (3) to between 37 and 30 m.N (27.29 and 22.12 lbf.ft )

.
(7) For the forward ACT cavity-drain-line (if installed):

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

Test Arrangement - Forward ACT Cavity-Drain-Line ** ON A/C NOT FOR ALL

(a) Disconnect the AIR SOURCE 1.5 BAR (21.75 PSI) MAX and the GAGE 5 BAR (75 PSI) - PRESSURE from the forward ACT cavity-drain-line.
(b) If you install the 98D28108658000 TOOL-PRESSURE TEST,ACT as an alternative, then disconnect it from the ACT cavity drain-line.
(c) Remove the PLUG-BLANKING from each disconnected line end.
(d) Install the tee to the ACT cavity-drain line.
(e) TORQUE the coupling nut (2) to between 37 and 30 m.N (27.29 and 22.12 lbf.ft )

.
(f) Connect the APU drain line to the tee.
(g) TORQUE the coupling nut (1) to between 22 and 18 m.N (16.22 and 13.27 lbf.ft )

5. Close-up
Subtask 28-28-00-410-093-A ** ON A/C NOT FOR ALL

A. Close Access
(1) If removed, install the applicable maintenance panels on the cargo ceiling panels (Ref. AMM TASK 25-54-12-000-002) and/or (Ref. AMM TASK 25-55-11-000-002).
(2) If removed, install the applicable cabin floor panels above the ACT(s):

For the pipe connections of ACT AFT1 and ACT AFT2, install applicable cabin floor panels (Ref. AMM TASK 53-32-12-400-002)
For the pipe connections of the ACT FWD (if installed), install cabin floor panel 231AMG (Ref. AMM TASK 53-22-12-400-001).

(3) On the lower fuselage, install the applicable cavity-drain service panels.
(4) Install access panel 151NC to close access to test ports T1 and T2 (Ref. AMM TASK 25-55-11-400-002).
(5) Close the aft cargo-compartment door (Ref. AMM TASK 52-30-00-860-002).
(6) Close the MLG doors (Ref. AMM TASK 32-12-00-410-001).

Subtask 28-28-00-865-186-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 28-28-00-860-265-A ** ON A/C NOT FOR ALL

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

[Rev.10 from 2021] 2026.04.02 07:01:53 UTC