Leak Check of the Additional Center Tank (ACT)-Vent/Transfer Pipe-Shrouds and the ACT Drain-Pipe Connectors

TASK 28-11-00-790-013-A
Leak Check of the Additional Center Tank (ACT)-Vent/Transfer Pipe-Shrouds and the ACT Drain-Pipe Connectors

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: 150

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	ACCESS PLATFORM 1M(3 FT)
No specific	AR	ADAPTER - EXTENSION, FILLING SYSTEM, DRY AIR
No specific	AR	AIR SOURCE 2 BAR (30 PSI) - REGULATED, FILTERED, DRY
No specific	2	CAP - BLANKING
No specific	AR	GAGE 0 TO 2000 PSI (0 TO 138 BAR) - PRESSURE
No specific	1	GROUND PRESSURE GENERATOR - 0 TO 2 BAR (0 TO 30 PSI)
No specific	AR	SAFETY BARRIER(S)
No specific	AR	SAFETY CLIP - CIRCUIT BREAKER
No specific	AR	WARNING NOTICE(S)
No specific	AR	WATER - SOAPY SOLUTION
98D28108658000	1	TOOL-PRESSURE TEST,ACT

B. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
150	AFT CARGO COMPARTMENT FWD PRESS BULKHEAD TO AFT BULKHEAD OF AFT CARGO COMPARTMENT
241EF, 241JF, 251AF, 251AG, 251FF

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 31-60-00-860-001-A	EIS Start Procedure
TASK 31-60-00-860-002-A	EIS Stop Procedure
TASK 32-00-00-481-001-A	Installation of the Safety Devices on the Landing Gears
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 53-32-12-000-002-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
ACT Cavity-Drain Connection
Access to the ACT Cavity Drain-Line (AFT ACT)
ACT Test Arrangement (TEST-PRESSURE TEST, ACT)

3. Job Set-up
Subtask 28-11-00-941-117-A ** ON A/C NOT FOR ALL

A. Safety Precautions

WARNING: OBEY THE FUEL SAFETY PROCEDURES.

(1) You must obey the fuel safety procedures when you do work on the fuel system (Ref. AMM TASK 28-00-00-910-001).
(2) Make sure that the ground safety locks are installed on the landing gears (Ref. AMM TASK 32-00-00-481-001).
(3) Put the WARNING NOTICE(S) in position to tell persons not to operate the Main Landing Gear (MLG) doors.
(4) As necessary, use the applicable SAFETY BARRIERS, specified by the operator's instructions and your local regulations.

Subtask 28-11-00-860-119-A ** ON A/C NOT FOR ALL

B. Aircraft Maintenance Configuration
(1) Energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-861-002).
(2) Do the EIS start procedure (upper ECAM DU and lower ECAM DU only)
(Ref. AMM TASK 31-60-00-860-001).
(3) In the cockpit, on the ECAM control panel:
(a) Push (in) the FUEL P/BSW.
(b) The FUEL page comes into view on the lower ECAM DU.
(c) Make sure that the ACT indication is shown on the ECAM FUEL page.
(4) On the refuel/defuel control panels 800VU and 801VU, make sure that:

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

(5) Put the WARNING NOTICE(S) in position on these panels to tell persons not to operate the refuel/defuel system:

The refuel/defuel control panels 800VU and 801VU
The HYD/FUEL panel 40VU
The FUEL panel 28VU.

Subtask 28-11-00-010-090-A ** ON A/C NOT FOR ALL

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

To the ACT fuel transfer-pump 1QH
To the ACT transfer-valve actuator 6QH
To the ACT cavity drain-line in the MLG bay.

(2) Put an ACCESS PLATFORM 1M(3 FT) on the LH side of the MLG bay.
(3) On the lower fuselage zone 150, get access to the ACT cavity drain-line below the ACT as follows:
(a) Remove the access panels 197PB and 153AZ from the lower fuselage.
(4) In the cabin, get access to the ACT-vent/transfer pipe-shroud connectors as follows:
(a) Remove the cabin floor panels 241EF and 241JF (Ref. AMM TASK 53-32-12-000-002).
(b) Remove the cargo ceiling panels 251AG, 251AF and 251FF (Ref. AMM TASK 53-42-12-000-001).

Subtask 28-11-00-865-133-A ** ON A/C NOT FOR ALL

D. 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

4. Procedure
Subtask 28-11-00-860-120-A ** ON A/C NOT FOR ALL

A. Preparation for the Test
(1) In the cockpit, on the HYD/FUEL panel 40VU:
(a) Push (in) the ACT P/BSW to open the ACT transfer-valve 165QM.
(b) Make sure that the FAULT light and the FWD light on the ACT P/BSWs are on.
(2) In the MLG bay:
(a) Make sure that the ACT fuel transfer-pump 1QH is off and you hear no sound from the pump.
(b) Make sure that the indicator on the ACT transfer-valve actuator 6QH is in the open position.
(3) On the lower fuselage, close the applicable ACT cavity drain-lines on the ACT as follows:

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

(a) Remove the nut (2) and disconnect the hose (3) from the drain fitting (1).
(b) Install the TEST PLUG (MS 21913-8) (4) on the disconnected hose end.
(c) Put a CAP - BLANKING on the drain fitting (1).

Subtask 28-11-00-480-066-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

ACT Test Arrangement (TEST-PRESSURE TEST, ACT) ** ON A/C NOT FOR ALL

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

NOTE: If the 98D28108658000 TOOL-PRESSURE TEST,ACT is not available, you can use the alternative test tools that follow:

An AIR SOURCE 2 BAR (30 PSI) - REGULATED, FILTERED, DRY
A GAGE 0 TO 2000 PSI (0 TO 138 BAR) - PRESSURE
An applicable ADAPTER - EXTENSION, FILLING SYSTEM, DRY AIR.

Subtask 28-11-00-790-092-A ** ON A/C NOT FOR ALL

C. Leak Test of the ACT-Vent/Transfer Pipe-Shrouds and Drain-Pipe Connectors of the ACT1 in the Aft Cargo-Compartment

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.

(1) Do this test:

ACTION	RESULT
1.In the MLG bay, on the ACT cavity drain-line: Start the GROUND PRESSURE GENERATOR - 0 TO 2 BAR (0 TO 30 PSI) Carefully pressurize the ACT cavity drain-line to 1.4 bar (20 psi).	On the GROUND PRESSURE GENERATOR - 0 TO 2 BAR (0 TO 30 PSI) pressure-gage: The air pressure in the ACT cavity drain-line increases to 1.4 bar (20 psi).
2.Close the GROUND PRESSURE GENERATOR - 0 TO 2 BAR (0 TO 30 PSI) shut-off valve.	On the GROUND PRESSURE GENERATOR - 0 TO 2 BAR (0 TO 30 PSI) pressure gage: Make sure that the air pressure in the ACT cavity drain-line is stable at 1.4 bar (20 psi) for 15 minutes.
3.In the MLG bay, on the ACT cavity drain-line: Stop the GROUND PRESSURE GENERATOR - 0 TO 2 BAR (0 TO 30 PSI) Carefully release the air pressure from the ACT cavity drain-line.	On the GROUND PRESSURE GENERATOR - 0 TO 2 BAR (0 TO 30 PSI) pressure gage: The air pressure in the ACT cavity drain-line decreases to 0 bar (0 psi).

(2) Leaks are not permitted. If the pressure decreases during the 15 minutes, then:
(a) Do a leak check of the ACT cavity drain-line and vent/transfer pipe-shroud connections as follows:
1 Use the GROUND PRESSURE GENERATOR - 0 TO 2 BAR (0 TO 30 PSI) to maintain the test pressure in the ACT cavity drain-line.
2 Use a WATER - SOAPY SOLUTION or a leak detector spray to find leak(s).
3 When you find the leak(s), stop the GROUND PRESSURE GENERATOR - 0 TO 2 BAR (0 TO 30 PSI).
4 Carefully release the air pressure from the ACT cavity drain-line.
5 Repair or replace as necessary.
(3) Do the test again.

Subtask 28-11-00-080-066-A ** ON A/C NOT FOR ALL

D. Removal of the Test Tool
(1) In the MLG bay, remove the 98D28108658000 TOOL-PRESSURE TEST,ACT from the ACT cavity drain-line as follows:
(a) Remove the CAP - BLANKING from the T-connection.
(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 as follows:
(a) Connect the elbow (6) to the T-connection and tighten the nuts (5) and (7).
(3) On the lower fuselage, at the ACT cavity drain-line:
(a) Remove the TEST PLUG (MS 21913-8) (4) from the disconnected hose 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) Install the hose (3) on the drain fitting (1).
(f) Do not twist the hose (3) when you tighten the nut (2).
(4) Close the ACT transfer-valve 165QM as follows:
(a) In the cockpit, on the HYD/FUEL panel 40VU release (out) the ACT P/BSW.
(b) Make sure that the FAULT light and the FWD light on the ACT P/BSWs are off.
(c) In the MLG bay, make sure that the indicator on the ACT transfer-valve actuator 6QH is in the closed position.

5. Close-up
Subtask 28-11-00-410-089-A ** ON A/C NOT FOR ALL

A. Close Access
(1) Remove the access platform(s).
(2) Close the MLG doors after access (Ref. AMM TASK 32-12-00-410-001).
(3) On the lower fuselage zone 150, install the access panels 197PB and 153AZ.
(4) In the cabin:
(a) Install the applicable cabin floor panels 241EF and 241JF (Ref. AMM TASK 53-32-12-400-002).
(b) Install the applicable cargo ceiling panels 251AG, 251AF and 251FF (Ref. AMM TASK 53-42-12-400-001).

Subtask 28-11-00-865-134-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

Subtask 28-11-00-860-122-A ** ON A/C NOT FOR ALL

C. Put the aircraft back to its initial configuration.
(1) Do the EIS stop procedure
(Ref. AMM TASK 31-60-00-860-002).
(2) De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002).

Subtask 28-11-00-942-121-A ** ON A/C NOT FOR ALL

D. Removal Of the Equipment
(1) Remove the safety barriers.
(2) Remove the WARNING NOTICE(S).
(3) Remove the ground support and maintenance equipment, the special and standard tools and all other items.
(4) Make sure that the work area is clean and clear of tools and other items.

[Rev.10 from 2021] 2026.04.02 06:17:01 UTC