Installation of Additional Center Tank No.1 (ACT AFT1)

TASK 28-11-27-400-002-A
Installation of Additional Center Tank No.1 (ACT AFT1)

WARNING: MAKE SURE THE AREA AROUND THE AIRCRAFT IS SAFE BEFORE YOU START THE REFUEL/DEFUEL PROCEDURE. IN THE SAFETY AREA, DO NOT:

SMOKE
MAKE SPARKS OR FIRE
USE ANY EQUIPMENT WHICH IS NOT APPROVED FOR REFUEL/DEFUEL PROCEDURES.

AIRCRAFT FUEL IS FLAMMABLE.

WARNING: OBEY THE FUEL SAFETY PROCEDURES.

WARNING: BEFORE YOU DO WORK IN OR NEAR A FUEL TANK, MAKE SURE THAT YOU OBEY ALL THE SAFETY PROCEDURES. THIS WILL PREVENT INJURY TO PERSONS AND/OR DAMAGE TO THE AIRCRAFT.

WARNING: BE CAREFUL NOT TO GET AIRCRAFT FUEL IN YOUR MOUTH OR IN YOUR EYES. IF YOU GET FUEL ON YOUR SKIN OR ON YOUR CLOTHES, FLUSH IT IMMEDIATELY WITH WATER. IF NECESSARY, GET MEDICAL HELP. AIRCRAFT FUEL IS POISONOUS.

WARNING: DO NOT GET YOUR CLOTHES SOAKED WITH FUEL.

WARNING: MAKE SURE THAT YOU HAVE THE CORRECT FIRE FIGHTING EQUIPMENT AVAILABLE.

WARNING: BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.

WARNING: BE CAREFUL WHEN YOU REMOVE OR INSTALL THIS EQUIPMENT. THIS EQUIPMENT IS HEAVY (MORE THAN 12 KG (26.5 lb)) AND CAN CAUSE INJURY AND/OR DAMAGE.

WARNING: HEAVY WEIGHT. MINIMUM 2 PERSONS OR ASSISTED HANDLING REQUIRED.

ZONE: 150
ZONE: 190
ZONE: 250

1. Reason for the Job
This procedure shows the installation of the Additional Center Tank (ACT) after removal of standard ACT. If you must change the ACT configuration of the aircraft, you must do the ACT installation refer to the applicable Service Bulletin (SB).

NOTE: The weight of this equipment is 335 kg (739 lb).

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

REFERENCE	QTY	DESIGNATION
No specific	AR	ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE
No specific	1	GAGE - FEELER
No specific	1	LOADER - PLATFORM
No specific	AR	TAPE - ADHESIVE
No specific	AR	WARNING NOTICE(S)
No specific	Torque wrench: range to between 0.48 and 0.37 m.daN (42.48 and 32.74 lbf.in )
No specific	Torque wrench: range to between 0.5 and 0.4 m.daN (44.25 and 35.40 lbf.in )
No specific	Torque wrench: range to between 3.39 and 2.79 m.daN (25.00 and 20.58 lbf.ft )
No specific	Torque wrench: range to between 3.3 and 3.0 m.daN (24.34 and 22.12 lbf.ft )
No specific	Torque wrench: range to between 4.3 and 3.9 m.daN (31.71 and 28.76 lbf.ft )
98D28108293002	1	ADAPTER-WATER DRAIN, ADDITIONAL CENTER TANK
98D28108298000	1	STOWAGE - CONTAINER FUEL, ACT
98D28108299002	1	GUIDE-R I,ADDITIONAL CENTER TANK
98D28108388000	1	STOWAGE - CONTAINER FUEL, ACT 1 AND 2

B. Consumable Materials

REFERENCE	DESIGNATION
(Material No.03FAB1)	Mineral Oil base Grease-- Vaseline or Petrolatum -

C. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
150	AFT CARGO COMPARTMENT FWD PRESS BULKHEAD TO AFT BULKHEAD OF AFT CARGO COMPARTMENT
190	BELLY FAIR, AIR CONDITIONING & HYD COMPT
250	AFT PASSENGER COMPARTMENT
192MB, 251KG, 826

D. Expendable Parts

FIG.ITEM	DESIGNATION	IPC-CSN
35	0-RING	AIPC 28-11-84-01-050
33	O-RING	AIPC 28-11-84-01-060
76	O-RING	AIPC 28-11-84-02-120
82	O-RING	AIPC 28-11-84-02-120
75	O-RING	AIPC 28-11-84-02-130
83	O-RING	AIPC 28-11-84-02-130
22	O-RING	AIPC 28-11-84-18-090
24	O-RING	AIPC 28-11-84-18-100

E. Referenced Information

REFERENCE	DESIGNATION
TASK 20-28-00-912-802-A	Electrical Bonding - General Maintenance Procedure
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 28-10-00-910-001-A	Safety Procedures When You Do Work in a Fuel Tank
TASK 28-11-27-000-003-A	Removal of the Additional Center Tank No.2 (ACT AFT2)
TASK 28-11-27-400-003-A	Installation of the Additional Center Tank No.2 (ACT AFT2)
TASK 28-28-00-710-005-A	Operational Test of the Additional Center Tank (ACT) Automatic Transfer System
TASK 28-28-00-710-008-A	Operational Check of the ACT Manual Transfer System (AFT Cargo-Compartment)
TASK 28-28-00-790-005-A	Leak Test of ACT Vent/Transfer Pipe-Shrouds and Cavity Drain Lines
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
TASK 28-51-00-740-801-A	Power Up Test and Cold Start Procedure
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 53-32-12-000-002-A	Removal of the Cabin Floor Panels
TASK 53-32-12-400-002-A	Installation of the Cabin Floor Panels
ACT Guide
Protective Blank Flange Caps (ACT AFT1)
Pressure Hose and Bonding Assembly (ACT AFT1)
Adjustment of the ACT AFT1
Fuel Hose (ACT AFT1)
Vent Hose (ACT AFT1)
Roller Track Latches and End Stops (ACT AFT1)
Cavity Drain Assembly (ACT AFT1)
Water Drain Assembly (ACT AFT1)
Electrical Connections (ACT AFT1)
ACT Water-Drain Adaptors

3. Job Set-up
Subtask 28-11-27-869-051-A ** ON A/C NOT FOR ALL

A. Safety Precautions
(1) Obey the fuel safety procedures (Ref. AMM TASK 28-00-00-910-001).
(2) Obey the safety procedures when you do work in a fuel tank (Ref. AMM TASK 28-10-00-910-001).
(3) On the right side of the belly fairing, open quick-release access door 192MB.
(4) On refuel/defuel control-panels 800VU and 801VU, make sure that:

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

(5) Make sure that the WARNING NOTICE(S) is (are) on refuel/defuel control-panels 800VU and 801VU to tell persons not to operate the fuel system.
(6) On the right side of the belly fairing, close quick-release access door 192MB.
(7) In the cockpit, put the WARNING NOTICE(S) on the panels that follow, to tell persons not to operate the fuel system:

Fuel control-panel 40VU
ACT control-panel 28VU.

Subtask 28-11-27-860-053-D ** ON A/C NOT FOR ALL

B. Aircraft Maintenance Configuration
(1) Make sure that the aircraft electrical circuits are energized (Ref. AMM TASK 24-41-00-861-002).
(2) Make sure that aft cargo-compartment-door 826 is open (Ref. AMM TASK 52-30-00-860-001).
(3) Make sure that ACT AFT2 is removed from the aft cargo compartment (Ref. AMM TASK 28-11-27-000-003).
(4) Make sure that an ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE is in position at aft cargo-compartment-door 826.
(5) Make sure that a 98D28108299002 GUIDE-R I,ADDITIONAL CENTER TANK is installed on the cargo floor in the aft cargo-compartment-door 826.

ACT Guide ** ON A/C NOT FOR ALL

(6) On the lower fuselage, below ACT AFT1:
(a) Make sure that the water drain-valve service-panel is removed to get access to the water to the water drain valve of ACT AFT1.
(b) Make sure that the cavity drain service-panel is removed to get access to the cavity drain port of ACT AFT1.
(7) Make sure that the floor panel 251KG on the ceiling panel is removed from the aft cargo compartment (Ref. AMM TASK 53-32-12-000-002).
(8) Make sure that all bolts and anchor nuts of the fuel and vent pipe flanges of the ACT are in good condition.

Subtask 28-11-27-865-054-A ** ON A/C NOT FOR ALL

C. 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 RFL/VLV/SPLY & CTL	43QU	J21
121VU	FUEL/ACT AIR SOV/MAN/SPLY	64QH	J20
121VU	FUEL/ACT AIR SOV/AUTO/SPLY	63QH	J19
121VU	FUEL/ACT XFR VLV/MOT2	66QH	J18
121VU	FUEL/ACT XFR VLV/MOT1	65QH	J17
121VU	FUEL/RFL/DFL INLET VLV/AFT 1 & 2	53QU	J15
121VU	FUEL/INLET VLV MOT2 AUTO SP AFT 2	44QH2	K16
121VU	FUEL/INLET VLV MOT2 AUTO SP AFT 1	44QH1	K15
121VU	FUEL/INLET VLV/MOT1/AFT 2	84QH	L29
121VU	FUEL/INLET VLV/MOT1/MAN SPLY/AFT 1	46QH	L28
121VU	FUEL/RFL/DFL CTL/AFT 1 & 2	49QU	L26
121VU	FUEL/HI/LVL/SPLY	1QJ	L24
121VU	FUEL/RFL/DFL/SPLY	2QU	L23
121VU	FUEL/RFL/DFL/XFR/DEFUEL/VALVE	1QU	L22
121VU	FUEL/ACT VENT VLV/MAN/SPLY	62QH	L21
121VU	FUEL/ACT VENT VLV/AUTO/SPLY	61QH	L20
121VU	FUEL/INLET VLV MAN CTL SPLY AFT 2	81QH	L16
121VU	FUEL/INLET VLV MAN CTL SPLY AFT 1	45QH	L15
121VU	FUEL/ACT/FUEL PUMP/SPLY	25QH	Q29

4. Procedure
Subtask 28-11-27-410-053-B ** ON A/C NOT FOR ALL

A. Preparation for the Installation

NOTE: Airbus recommends you to use the 98D28108298000 STOWAGE - CONTAINER FUEL, ACT or 98D28108388000 STOWAGE - CONTAINER FUEL, ACT 1 AND 2 for this procedure.

NOTE: A new ACT has blanking caps installed on all openings.

NOTE: Airbus recommends you to use a box to keep all removed caps and blanks is available.

(1) Do the leak test of ACT vent/transfer pipe-shrouds and cavity drain lines (Ref. AMM TASK 28-28-00-790-005).

NOTE: The leak test will make sure that the pipe shrouds and cavity drain lines have no leaks before the installation of ACT AFT1.

(2) Remove the protective blank flange-caps from the fuel line and the vent line ends of ACT AFT1:

Protective Blank Flange Caps (ACT AFT1) ** ON A/C NOT FOR ALL

NOTE: Airbus recommends you to remove the aft blanking flanges of ACT AFT1 when ACT AFT2 is installed in the aircraft.

(a) Remove the nuts (147) from the studs (141).
(b) Remove the outer blanking flange (148) and the O-ring (149) from the inner blanking flange (150).
(c) Discard the O-ring (149).

WARNING: USE PROTECTIVE GOGGLES AND GLOVES WHEN YOU REMOVE OR INSTALL LOCKWIRE. EACH TIME YOU CUT LOCKWIRE, REMOVE AND DISCARD IT IMMEDIATELY. LOOSE LOCKWIRE CAN CUT YOU OR MAKE YOU BLIND, AND/OR CAN CAUSE DAMAGE.

(d) Remove and discard the lockwire from the pressure relief screw (146).
(e) Loosen the pressure relief screw (146) to release the air pressure from ACT AFT1.
(f) Remove the nuts (145) from the studs (142).
(g) Remove the inner blanking flange (150) and the O-rings (143) and (144) from ACT AFT1.
(h) Discard the O-rings (143) and (144).
(i) Remove the nuts (152) from the studs (154).
(j) Remove the blanking flange (153) and the O-rings (156) and (157) from ACT AFT1.
(k) Discard the O-rings (156) and (157).
(3) Remove the blanking plug from the cavity drain port of ACT AFT1:
(a) Turn the cavity drain plug (151) 60 deg (60 deg) clockwise and remove it from ACT AFT1.
(b) Remove and discard the O-ring (155).
(4) Connect the air hose assembly (7) to the check valve (9) as follows:

Pressure Hose and Bonding Assembly (ACT AFT1) ** ON A/C NOT FOR ALL

(a) Remove the PLUG-BLANKING from each disconnected line end.
(b) Do an inspection of the component interfaces and the adjacent area.
(c) Make sure that the parts retained from the removed component are clean and in the correct condition.
(d) Connect the union nut (8) of the air hose assembly (7) to the check valve (9).

CAUTION: USE TWO WRENCHES TO REMOVE OR INSTALL THE HOSE NUTS. USE ONE WRENCH TO HOLD THE FITTING AND ONE WRENCH TO LOOSEN OR TIGHTEN THE HOSE NUT. IF YOU DO NOT DO THIS, DAMAGE TO THE COMPONENTS CAN OCCUR.

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.

(e) TORQUE the union nut (8) to between 4.3 and 3.9 m.daN (31.71 and 28.76 lbf.ft )

.
(f) Attach the air hose (7) to ACT AFT1 with a TAPE - ADHESIVE.
(5) Make sure that the components that follow are in correct condition:

The check valves
The shut-off valve
The pressure reducing valve
The air filter
The self-sealing couplings T1 and T2.

(6) If installed, remove the blanking caps from the vent hose and the fuel hose ends.
(7) Examine the vent hose and the fuel hose for the corrosion, the damage or the signs of leakage.
(8) Make sure that all components of the ACT system are correctly attached to the aircraft structure.

Subtask 28-11-27-820-071-C ** ON A/C NOT FOR ALL

B. Adjustment of ACT AFT1
(1) Make sure that a LOADER - PLATFORM is installed at the aft cargo door-opening.
(2) Move ACT AFT1 to the aft cargo compartment.
(3)

Adjustment of the ACT AFT1 ** ON A/C NOT FOR ALL

NOTE: Too much putty can have an effect on the measurement of the thickness of the putty. Airbus recommends you to apply a cherry stone size of putty on the left and right sides of the crash stoppers (1).

(4) Install the O-rings on the flexible fuel hose (87) as follows:

Fuel Hose (ACT AFT1) ** ON A/C NOT FOR ALL

(a) Apply a thin layer of Mineral Oil base Grease-- Vaseline or Petrolatum - (Material No.03FAB1) on the new AIPC 28-11-84-02-130 O-RING (83) and the new AIPC 28-11-84-02-120 O-RING (82).
(b) Put the O-rings (82) and (83) in position on the flange (85) of the flexible fuel hose (87).
(5) Install the O-rings on the flexible vent hose (71) as follows:

Vent Hose (ACT AFT1) ** ON A/C NOT FOR ALL

(a) Apply a thin layer of Mineral Oil base Grease-- Vaseline or Petrolatum - (Material No.03FAB1) on the new AIPC 28-11-84-02-130 O-RING (75) and the new AIPC 28-11-84-02-120 O-RING (76).
(b) Put the O-rings (75) and (76) in position on the flange (73) of the flexible vent hose (71).
(6) Move ACT AFT1 to the forward position in the aft cargo compartment.
(7) Make sure that the flexible vent hose and fuel hose are correctly aligned with the flanges of ACT AFT1.
(8) Move ACT AFT1 to the forward position until it touches the end stops at FR 47.2.
(9) Do the check of the adjustment on the crash stoppers (1) as follows:

Adjustment of the ACT AFT1 ** ON A/C NOT FOR ALL

(a) Make sure that ACT AFT1 is in the most forward position to measure the clearance of the crash stoppers.
(b) Install the latch elements (123) at FR47.5 to lock ACT AFT1 in position:

Roller Track Latches and End Stops (ACT AFT1) ** ON A/C NOT FOR ALL

NOTE: This makes an imprint on the putty.

1 Put the latch elements (123) in the correct installation position on the roller tracks (125).
2 Install the washers (122) and the bolts (121) on the latch elements (123).
(c) Remove the latch elements (123) at FR47.5 to release ACT AFT1:

Roller Track Latches and End Stops (ACT AFT1) ** ON A/C NOT FOR ALL

1 Remove the bolts (121) and the washers (122) from the latch elements (123).
2 Remove the latch elements (123).
(d) Move ACT AFT1 away from the end stops until you can measure the thickness of the putty imprint.
(e) Subtract the thickness of shim plates "B" from the thickness of putty "C" to get the result of clearance "A".
(f) Make sure that the dimension of clearance "A" is 2 -0.5 mm or +0.5 mm (0.079 -0.020 in. or +0.020 in.).
(g) If necessary, adjust the clearance with the shim plates on the crash stoppers (1):
1 Make sure that the clearance are in the permitted tolerance.
(10) Install the latch elements (123) at FR 47.5 to lock ACT AFT1 in position as follows:

NOTE: Airbus recommends you to install the latch elements (123) in the marked position on the roller tracks (125).

(a) Put the latch elements (123) in the correct installation position on the roller tracks (125).
(b) Install the washers (122) and the bolts (121) on the latch elements (123).
(11) Do a check of adjustment on the latch elements (123) as follows:

Adjustment of the ACT AFT1 ** ON A/C NOT FOR ALL

Roller Track Latches and End Stops (ACT AFT1) ** ON A/C NOT FOR ALL

(a) Measure the clearance when ACT AFT1 touches the end stops (124) at FR 47.2.
(b) Use a GAGE - FEELER and make sure that the clearances are in the permitted tolerance:

Make sure that the latch elements (2) have a horizontal clearance of 2.3 -1 mm or +1 mm (0.091 -0.039 in. or +0.039 in.)
Make sure that the latch elements (2) have a vertical clearance of 1.5 -1 mm or +1 mm (0.059 -0.039 in. or +0.039 in.).

Roller Track Latches and End Stops (ACT AFT1) ** ON A/C NOT FOR ALL

1 Replace the adapter plates (126) below the latch to adjust the clearance on the latch elements (123).

NOTE: The thickness of these plates is 0.2 mm (0.0079 in.).

(12) Install the latches (123) on the roller tracks (125) as follows:

Roller Track Latches and End Stops (ACT AFT1) ** ON A/C NOT FOR ALL

NOTE: Refer to the marks made on the roller tracks (125) to install the latch elements (123).

(a) Install the washers (122) and the bolts (121) on the latch elements (123).
(b) TORQUE the bolts (121) to between 3.39 and 2.79 m.daN (25.00 and 20.58 lbf.ft )

Subtask 28-11-27-420-054-C ** ON A/C NOT FOR ALL

C. Installation of ACT AFT1

NOTE: Airbus recommends you to use the access openings in the cabin floor and the cargo ceiling to connect the fuel and vent hoses to the ACT.

(1) Connect the flexible fuel hose to ACT AFT1:

Fuel Hose (ACT AFT1) ** ON A/C NOT FOR ALL

(a) Align the holes of the flange (85) with the studs (81).
(b) Connect the flexible fuel hose (87) to the ACT flange (84).
(c) Install the nuts (86) on the studs (81).
(d) Torque the nuts (86) opposite to each other to between 0.5 and 0.4 m.daN (44.25 and 35.40 lbf.in )

.
(2) Connect the flexible vent hose to ACT AFT1:

Vent Hose (ACT AFT1) ** ON A/C NOT FOR ALL

(a) Align the holes of the flange (73) with the studs (77).
(b) Connect the flexible vent hose (71) to the ACT flange (74).
(c) Install the nuts (72) on the studs (77).
(d) Torque the nuts (72) opposite to each other to between 0.5 and 0.4 m.daN (44.25 and 35.40 lbf.in )

.
(3) Install the cavity drain assembly (36) on ACT AFT1:

Cavity Drain Assembly (ACT AFT1) ** ON A/C NOT FOR ALL

(a) Apply a thin layer of Mineral Oil base Grease-- Vaseline or Petrolatum - (Material No.03FAB1) on the new AIPC 28-11-84-01-050 0-RING (35) and the new AIPC 28-11-84-01-060 O-RING (33).
(b) Put the O-rings (33) and (35) in position on the cavity drain assembly (36).
(c) Put the cavity drain assembly (36) in the cavity drain port (31).
(d) Push and turn the cavity drain assembly (36) counterclockwise, approximately to 60 deg (60 deg).
(e) Make sure that the locking plate (34) of the cavity drain assembly (36) fully engaged in ACT AFT1.

(f) Connect the union nuts (38) of the hose (39) to the drain fitting (37) and pipe fitting (40).

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 union nuts (38) to between 3.3 and 3.0 m.daN (24.34 and 22.12 lbf.ft )

.
(4) Install the water drain tube on ACT AFT1 as follows:

Water Drain Assembly (ACT AFT1) ** ON A/C NOT FOR ALL

(a) Do an inspection of the component interfaces and the adjacent area.
(b) Make sure that the area around the drain opening has no corrosion and is not damaged.
(c) Apply a thin layer of Mineral Oil base Grease-- Vaseline or Petrolatum - (Material No.03FAB1) on the new AIPC 28-11-84-18-090 O-RING (22) and the new AIPC 28-11-84-18-100 O-RING (24).
(d) Put the O-rings (22) and (24) in position on the drain tube (23).
(e) Push the drain tube (23) into the access hole of the ACT water-drain valve.
(f) Make sure that the drain tube (23) is correctly attached to the ACT water-drain port (21).

WARNING: BE CAREFUL WHEN YOU REMOVE OR INSTALL THE SPRING. THE TENSION IN THE SPRING CAN CAUSE INJURY TO PERSONS.

(g) Put the compression spring (25) and the flange (26) in position on the drain tube (23).
(h) Install the retaining ring (27) with a PLIERS - THIN NOSE.
(i) Prepare equipment for electrical bonding (Ref. AMM TASK 20-28-00-912-802).
(j) Connect the screw (30), washer (29), bonding strap (28) and spacer (31) to the aircraft structure.
(k) TORQUE the screw (30) to between 0.48 and 0.37 m.daN (42.48 and 32.74 lbf.in )

.
(l) Do the electrical bonding on ACT AFT1 water drain tube (Ref. AMM TASK 20-28-00-912-802).
(5) Connect the air hose assembly (7) to the ACT pressure line as follows:

Pressure Hose and Bonding Assembly (ACT AFT1) ** ON A/C NOT FOR ALL

(a) Remove the PLUG-BLANKING from each disconnected line end.
(b) Do an inspection of the component interfaces and the adjacent area.
(c) Make sure that the elbow union (10) of the ACT pressure line is tight.
(d) Connect the union nut (6) of the air hose assembly (7) to the elbow union (10).

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.

(e) TORQUE the union nut (6) to between 4.3 and 3.9 m.daN (31.71 and 28.76 lbf.ft )

NOTE: The fuel transfer from the ACT to the center tank will not work if the air hose is not correctly connected to the ACT pressurization system.

(6) Do the leak test of the ACT fuel/vent system and pressurization system (Ref. AMM TASK 28-28-00-790-804).
(7) Connect the bonding straps (4) of ACT AFT1 to the aircraft structure:

Pressure Hose and Bonding Assembly (ACT AFT1) ** ON A/C NOT FOR ALL

(a) Remove and discard the tie wraps from the bonding straps (4).
(b) Make sure that the bonding straps (4) are correctly installed on the left and right side of ACT AFT1.
(c) Prepare equipment for electrical bonding (Ref. AMM TASK 20-28-00-912-802).
(d) Connect the bonding straps (4) to the aircraft structure (2).
(e) Install the screws (3) and the washers (5) on the anchor nuts (1).
(f) TORQUE the screws (3) to between 0.48 and 0.37 m.daN (42.48 and 32.74 lbf.in )

.
(g) Do a electrical bonding on ACT AFT1 (Ref. AMM TASK 20-28-00-912-802).
(8) Connect the electrical harness of ACT AFT1:

Electrical Connections (ACT AFT1) ** ON A/C NOT FOR ALL

CAUTION: DO NOT TOUCH THE CONNECTOR PINS OR OTHER CONDUCTORS ON THE COMPONENT DURING THE PROCEDURE. IF YOU TOUCH THESE CONDUCTORS, ELECTROSTATIC DISCHARGE CAN CAUSE DAMAGE TO COMPONENT.

(a) Make sure that the electrical harness is not damaged and correctly connected to the actuators of the ACT vent valve and the fuel inlet valve.
(b) Remove the CAP - BLANKING from the receptacles above ACT AFT1.
(c) Remove the electrical connectors (11), (12), (13) and (14) from their stowage positions (15), (16), (17) and (18) on ACT AFT1.

CAUTION: MAKE SURE THAT THE BONDING STRAP(S) IS(ARE) CONNECTED BEFORE YOU CONNECT THE ELECTRICAL CONNECTOR(S).

CAUTION: WHEN YOU CONNECT THE ELECTRICAL CONNECTORS, MAKE SURE THAT YOU CONNECT EACH PLUG TO THE CORRECT RECEPTACLE (USE THE IDENTIFICATION MARKS).

CAUTION: MAKE SURE THAT THE ELECTRICAL CONNECTORS ARE CLEAN BEFORE YOU DISCONNECT OR CONNECT THEM. CONTAMINATION ON THE ELECTRICAL CONNECTORS CAN CAUSE DAMAGE TO EQUIPMENT.

(d) In the aft cargo compartment, connect the electrical connectors (11), (12), (13) and (14) to the related receptacles above ACT AFT1.
(9) Remove the LABEL - ADHESIVE, INOP from ACT FUEL panel 28VU for ACT AFT1.

Subtask 28-11-27-410-054-D ** ON A/C NOT FOR ALL

D. Put the system back to the serviceable condition.
(1) Install the ACT AFT2 in the aft cargo-compartment (Ref. AMM TASK 28-11-27-400-003).

Subtask 28-11-27-865-055-A ** ON A/C NOT FOR ALL

E. 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 RFL/VLV/SPLY & CTL	43QU	J21
121VU	FUEL/ACT AIR SOV/MAN/SPLY	64QH	J20
121VU	FUEL/ACT AIR SOV/AUTO/SPLY	63QH	J19
121VU	FUEL/ACT XFR VLV/MOT2	66QH	J18
121VU	FUEL/ACT XFR VLV/MOT1	65QH	J17
121VU	FUEL/RFL/DFL INLET VLV/AFT 1 & 2	53QU	J15
121VU	FUEL/INLET VLV MOT2 AUTO SP AFT 2	44QH2	K16
121VU	FUEL/INLET VLV MOT2 AUTO SP AFT 1	44QH1	K15
121VU	FUEL/INLET VLV/MOT1/AFT 2	84QH	L29
121VU	FUEL/INLET VLV/MOT1/MAN SPLY/AFT 1	46QH	L28
121VU	FUEL/RFL/DFL CTL/AFT 1 & 2	49QU	L26
121VU	FUEL/HI/LVL/SPLY	1QJ	L24
121VU	FUEL/RFL/DFL/SPLY	2QU	L23
121VU	FUEL/RFL/DFL/XFR/DEFUEL/VALVE	1QU	L22
121VU	FUEL/ACT VENT VLV/MAN/SPLY	62QH	L21
121VU	FUEL/ACT VENT VLV/AUTO/SPLY	61QH	L20
121VU	FUEL/INLET VLV MAN CTL SPLY AFT 2	81QH	L16
121VU	FUEL/INLET VLV MAN CTL SPLY AFT 1	45QH	L15
121VU	FUEL/ACT/FUEL PUMP/SPLY	25QH	Q29

Subtask 28-11-27-710-051-B ** ON A/C NOT FOR ALL

F. Test(s)
(1) Do the power up test and cold start procedure (Ref. AMM TASK 28-51-00-740-801).
(2) Do the leak test of the ACT fuel/vent system and pressurization system (Ref. AMM TASK 28-28-00-790-804).
(3) Do the operational test of the ACT manual transfer-system (Ref. AMM TASK 28-28-00-710-008).
(4) Do the operational test of the ACT automatic-transfer system (Ref. AMM TASK 28-28-00-710-005).
(5) Do an operational check of ACT AFT1 water-drain-valve as follows:

ACT Water-Drain Adaptors ** ON A/C NOT FOR ALL

(a) Install a 98D28108293002 ADAPTER-WATER DRAIN, ADDITIONAL CENTER TANK on the ACT water-drain port (1).
(b) Put the thrust rod (3) into the sleeve (2).
(c) Install the sleeve (2) in the water drain-valve tube.
(d) Hold the sleeve (2) and turn the nut (5) clockwise against the nut (4) to hold the water drain adaptor in position.
(e) Push the ACT water-drain valve with the thrust rod (3).
(f) Make sure that the ACT water-drain valve moves smoothly.
(g) To release the water drain adaptor from the water drain-valve tube:

Hold the sleeve (2) and turn the nut (5) counterclockwise from the nut (4).

(h) Remove the thrust rod (3) from the sleeve (2).
(i) Remove the 98D28108293002 ADAPTER-WATER DRAIN, ADDITIONAL CENTER TANK from the ACT water drain-port (1).
(j) Make sure that the ACT water drain-valve is fully closed.

5. Close-up
Subtask 28-11-27-860-072-B ** ON A/C NOT FOR ALL

A. Close Access
(1) Remove the 98D28108299002 GUIDE-R I,ADDITIONAL CENTER TANK from the cargo floor in the aft cargo compartment as follows:

ACT Guide ** ON A/C NOT FOR ALL

(a) Remove the ball lock pins (223) and (224) that attach the stop (208).
(b) Remove the stop (208).
(c) Remove the ball lock pins (214) that attach the stop (213).
(d) Remove the stop (213).
(e) Remove the pins (215) and (222) that attach the connection rails (207).
(f) Remove the connection rails (207).
(g) Remove the pin (221) that attach the rail (209).
(h) Remove the rail (209).
(i) Loosen the nut (210) and remove it.
(j) Remove the connection parts (211) and (212) from the support (219).
(k) Remove the pin (220) that attach the rail (206).
(l) Remove the rail (206).
(m) Remove the bolts (216) and the fasteners (218) from the seat track (217).
(2) Make sure that the work area is clean and clear of tools and other items.
(3) On the lower fuselage, below ACT AFT1:
(a) Install the water drain-valve service-panel on the water drain valve.
(b) Install the cavity drain service-panel on the cavity drain port.
(4) Install removed floor-panel 251KG on the cargo ceiling panel of the aft cargo compartment (Ref. AMM TASK 53-32-12-400-002).

Subtask 28-11-27-942-051-C ** ON A/C NOT FOR ALL

B. Put the aircraft back to the serviceable condition.
(1) Remove the ground support and maintenance equipment, the special and standard tools and all other items.
(2) Remove the WARNING NOTICE(S).
(3) Remove the access platform(s).
(4) Close the aft cargo-compartment door (Ref. AMM TASK 52-30-00-860-002).
(5) De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002).

[Rev.10 from 2021] 2026.04.01 00:01:14 UTC