Installation of the Additional Center Tank (ACT)

TASK 28-11-27-400-001-A
Installation of the Additional Center Tank (ACT)

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: 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 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.

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 2M (6 FT)
No specific	AR	PLIERS - THIN NOSE
No specific	1	WARNING NOTICE(S)
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 3.4 and 2.8 m.daN (25.07 and 20.65 lbf.ft )
98D28108293001	1	ADAPTER-WATER DRAIN, ADDITIONAL CENTER TANK
98D28108298000	1	STOWAGE - CONTAINER FUEL, ACT
98D28108299000	1	GUIDE-R I,ADDITIONAL CENTER TANK
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
154AZ, 154BR, 154CR, 251KG
153AR, 153BR, 154DR, 251PG

D. Expendable Parts

FIG.ITEM	DESIGNATION	IPC-CSN
22	O-RING	AIPC 28-11-04-01-050
24	O-RING	AIPC 28-11-04-01-050
22	O-RING	AIPC 28-11-04-01-060
24	O-RING	AIPC 28-11-04-01-060
49	O-RING	AIPC 28-11-04-02-120
56	O-RING	AIPC 28-11-04-02-120
50	O-RING	AIPC 28-11-04-02-130
55	O-RING	AIPC 28-11-04-02-130
14	RETAINING RING	AIPC 28-11-04-03-060
11	O-RING	AIPC 28-11-04-03-100
9	O-RING	AIPC 28-11-04-03-100
155	O-RING	AIPC 28-11-04-17-020
161	O-RING	AIPC 28-11-04-17-020
24	O-RING	AIPC 28-11-04-17-090
22	O-RING	AIPC 28-11-04-17-100
154	O-RING	AIPC 28-11-04-17-140
162	O-RING	AIPC 28-11-04-17-140
14	RETAINING RING	AIPC 28-11-04-18-060
11	O-RING	AIPC 28-11-04-18-100
9	O-RING	AIPC 28-11-04-18-100
103	SHIM PLATES	AIPC 28-11-27-01-030
22	ORING	AIPC 28-11-84-01-050
24	ORING	AIPC 28-11-84-01-050
22	ORING	AIPC 28-11-84-01-060
24	ORING	AIPC 28-11-84-01-060
49	ORING	AIPC 28-11-84-02-120
56	ORING	AIPC 28-11-84-02-120
50	ORING	AIPC 28-11-84-02-130
55	ORING	AIPC 28-11-84-02-130
14	RING	AIPC 28-11-84-03-060
11	ORING	AIPC 28-11-84-03-100
9	ORING	AIPC 28-11-84-03-100

E. Referenced Information

REFERENCE	DESIGNATION
TASK 20-28-00-912-802-A	Electrical Bonding - General Maintenance Procedure
TASK 24-42-00-861-001-A	Energize the Ground Service Network from the External Power
TASK 24-42-00-862-001-A	De-energize the Ground Service Network Supplied from the External Power
TASK 25-52-54-400-001-A	Installation of the Protection Cover
TASK 28-00-00-910-001-A	Fuel Safety Procedures
TASK 28-11-49-400-001-A	Installation of the ACT Integrated Impact Wall
TASK 28-25-00-650-005-A	To Drain the Remaining Fuel from the Additional Center Tank (ACT)
TASK 28-28-00-200-003-A	Operational Check of the Leak Monitor for the Indication of Fuel Leakage
TASK 28-28-00-710-001-A	Operational Check of the ACT Manual Transfer System
TASK 28-28-00-710-004-A	Operational Test of the ACT Automatic Transfer System
TASK 28-28-00-790-004-A	Functional Check of the Vent/Transfer Pipe Shrouds and ACT Drain Pipe Connectors
TASK 28-28-00-790-005-A	Leak Test of ACT Vent/Transfer Pipe-Shrouds and Cavity Drain Lines
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 53-42-12-000-001-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 Guide - Removal/Installation ** ON A/C NOT FOR ALL
ACT Guide - Removal/Installation ** ON A/C NOT FOR ALL
Blanking Flange Caps of the ACT
Pressure Hose and Bonding Assembly
ACT 1 Adjustment ** ON A/C NOT FOR ALL
Roller Track Latches and End Stops ** ON A/C NOT FOR ALL
Latch Adjustment ** ON A/C NOT FOR ALL
Attachment of the ACT ** ON A/C NOT FOR ALL
ACT Adjustment ** ON A/C NOT FOR ALL
ACT Latch Adjustment ** ON A/C NOT FOR ALL
Electrical Connections
Water Drain Assembly ** ON A/C NOT FOR ALL
Cavity Drain Assembly ** ON A/C NOT FOR ALL
Vent Pipe ACT 1 ** ON A/C NOT FOR ALL
Fuel Pipe ACT 1 ** ON A/C NOT FOR ALL
Flexible Vent and Fuel-Pipe ** ON A/C NOT FOR ALL
Water Drain Assembly ** ON A/C NOT FOR ALL
Cavity Drain Assembly ** ON A/C NOT FOR ALL
Vent Pipe Connection ** ON A/C NOT FOR ALL
Fuel Pipe Connection ** ON A/C NOT FOR ALL
ACT 2 Adjustment ** ON A/C NOT FOR ALL
Vent Pipe ACT 2 ** ON A/C NOT FOR ALL
Fuel Pipe ACT 2 ** ON A/C NOT FOR ALL

3. Job Set-up
Subtask 28-11-27-869-050-A ** ON A/C NOT FOR ALL

A. Safety Precautions
(1) You must obey the safety procedures when you work on a fuel tank (Ref. AMM TASK 28-00-00-910-001).
(2) Make sure that the ACT is completely drained (Ref. AMM TASK 28-25-00-650-005).
(3) Make sure that the WARNING NOTICE(S) are in position on:

the refuel/defuel panel 800VU/801VU,
the fueling panel 40VU,
to tell persons not to operate the refuel/defuel system.

(4) Make sure that on the control panel 800VU:

the refuel valve switch is in the OPEN position,
the MODE SELECT switch is in the REFUEL position.

Subtask 28-11-27-860-051-A ** ON A/C NOT FOR ALL

B. Aircraft Maintenance Configuration

NOTE: Use the 98D28108298000 STOWAGE - CONTAINER FUEL, ACT for this procedure.

(1) Make sure that the ground service network is energized (Ref. AMM TASK 24-42-00-861-001).
(2) On the lower center fuselage, make sure that access panels to the water drain and cavity drain of the ACT 154AZ, 154CR, 154BR are removed.
(3) In the cabin compartment, make sure that the cabin floor panel 251KG is removed. (Ref. AMM TASK 53-42-12-000-001).
(a) Make sure that the applicable access panel is removed from the cargo-ceiling.
(4) Make sure the aft cargo-compartment door is open (Ref. AMM TASK 52-30-00-860-001).
(5) Make sure that the ACCESS PLATFORM 2M (6 FT) is in position at the opening of the aft cargo-compartment door.
(6) In the aft cargo-compartment:
(a) Remove the protective blank flange caps from the vent and fuel-pipe ends.
(b) Make sure that the 98D28108299000 GUIDE-R I,ADDITIONAL CENTER TANK is installed on the cargo floor.

ACT Guide - Removal/Installation ** ON A/C NOT FOR ALL

(7) Make sure that all bolts and nuts of the vent and fuel-pipe flanges of the ACT are in a good condition.

Subtask 28-11-27-860-051-C ** ON A/C NOT FOR ALL

B. Aircraft Maintenance Configuration

NOTE: Use the 98D28108388000 STOWAGE - CONTAINER FUEL, ACT 1 AND 2 for this procedure.

(1) Make sure that the ground service network is energized (Ref. AMM TASK 24-42-00-861-001).
(2) On the lower center fuselage:
(a) Make sure that access panels 153BR, 154DR, 153AR are removed, for access to the water drain and cavity drain system of the ACT2.
(b) Make sure that access panels 154AZ, 154BR, 154CR are removed, for access to the water drain and cavity drain of the ACT1.
(3) In the cabin compartment:
(a) Make sure that the cabin floor panels 251PG and 251KG are removed (Ref. AMM TASK 53-42-12-000-001).
(b) Make sure that all applicable access panels are removed from the cargo-ceiling.
(4) Make sure the aft cargo-compartment door is open (Ref. AMM TASK 52-30-00-860-001).
(5) Make sure that the ACCESS PLATFORM 2M (6 FT) is in position at the opening of the aft cargo-compartment door.
(6) In the aft cargo-compartment:
(a) Remove the protective blank flange caps from the vent and fuel-pipe ends.
(b) Make sure that the 98D28108299002 GUIDE-R I,ADDITIONAL CENTER TANK is installed on the cargo floor.

ACT Guide - Removal/Installation ** ON A/C NOT FOR ALL

(7) Make sure that all bolts and nuts of the vent and fuel-pipe flanges of the ACT are in a good condition.

Subtask 28-11-27-865-051-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	ACT1/REFUEL & SPLY	33QU	L29
121VU	FUEL/HI/LVL/SPLY	1QJ	L25
121VU	FUEL/RFL/DFL/SPLY	2QU	L24
121VU	FUEL/RFL/DFL/XFR/DEFUEL/VALVE	1QU	L23
121VU	ACT XFR VALVE MAN CTL	30QH	N29
121VU	ACT1/CTL & SPLY	9QH	P29
121VU	ACT PUMP SUPPLY	25QH	Q29
** ON A/C NOT FOR ALL
121VU	ACT2/REFUEL & SPLY	34QU	L28
121VU	ACT2/CTL & SPLY	10QH	P28

4. Procedure
Subtask 28-11-27-410-050-A ** ON A/C NOT FOR ALL

A. Preparation for Installation
(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 the ACT.

(2) Make sure that all bonding points of the ACT are in the correct condition (Ref. AMM TASK 20-28-00-912-802).
(3) Clean the component interfaces and the adjacent area.
(4) Do an inspection of the component interfaces and the adjacent area.

NOTE: A new ACT or a replacement ACT has blanking plates installed on all openings.

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

Blanking Flange Caps of the ACT ** ON A/C NOT FOR ALL

(a) Remove the nuts (127) from the studs (121).
(b) Remove the outer blanking flange (128) and the O-ring (129) from the inner blanking flange (130).
(c) Discard the O-ring (129).
(d) Remove and discard the lockwire from the pressure relief screw (126).
(e) Loosen the pressure relief screw (126) to release the air pressure from the ACT (1).
(f) Remove the nuts (125) from the studs (122).
(g) Remove the inner blanking flange (130) and the O-rings (124), (123) from the ACT (1).
(h) Discard the O-rings (124), (123).
(i) Remove the nuts (136) from the studs (137).
(j) Remove the blanking flange (135) and the O-rings (134), (133) from the ACT
(k) Discard the O-rings (134), (133).
(6) Remove the blanking plug from the cavity drain port of the ACT:
(a) Turn the cavity-drain plug (131) 60 deg. clockwise and remove it from the ACT (1).
(b) Discard the O-ring (132).
(7) Connect the air hose assembly to the check valve of the ACT.

Pressure Hose and Bonding Assembly ** ON A/C NOT FOR ALL

(a) Remove the PLUG-BLANKING from each disconnected line end.
(b) Make sure that the parts retained from the removed component are clean and in the correct condition.
(c) Connect the union nut (40) of the air hose (39) to the check valve (32)
(d) Do not fully tighten the union nut (40) at this time.
(8) In the aft cargo-compartment, make sure that all floor-latches are lowered.
(a) Make sure that:

the check valves,
the shut-off valve,
the pressure reducing valve,
the air filter,
the self-sealing couplings T1 and T2,
are in the correct condition.

(b) Remove the blanking caps from the vent-pipe and the fuel-pipe ends, if installed.
(c) Examine the vent-pipe and fuel-pipe for corrosion, damage or signs of leakage.
(d) Make sure that all components of the ACT system are correctly attached to the aircraft structure.

Subtask 28-11-27-820-051-B ** ON A/C NOT FOR ALL

B. Adjustment of ACT1
(1) Do the adjustment of the crash stoppers as follows:

ACT 1 Adjustment ** ON A/C NOT FOR ALL

Roller Track Latches and End Stops ** ON A/C NOT FOR ALL

NOTE: Airbus recommends you to do the subsequent procedure to get the dimension of the gap "a":

If initial ACT1 is installed in the aft cargo compartment
If new ACT1 is to be installed in the aft cargo compartment
If new crash rods are installed in the aft cargo compartment.

NOTE: The gap "c" is the distance between the forward directed surface of the crash rods (102) and the crash stoppers (101) without the shim plates (103).

(a) Remove the shim plates (103) from ACT1 (1).
(b) Apply a piece of putty on the surface of the crash stoppers (101).
(c) Move ACT1 (1) into the aft cargo compartment.
(d) Move ACT1 (1) to the forward position in the aft cargo compartment, until it is in contact with the end stops (98).
(e) Make sure that the flexible pipes are correctly attached to the vent and fuel line ends of ACT1 (1) to prevent the damage on the pipes.

NOTE: You can use the openings in the cabin floor and the cargo ceiling to get access to the flexible pipes.

(f) Make sure that the ACT is in contact with a minimum of two end stops (98).
(g) Install the latch elements (94) on the cargo floor to lock ACT1 (1) in the end position:

NOTE: This makes an imprint on the putty.

1 Put the latch elements (94) in position on the roller tracks (99).
2 Install the washers (96) and the bolts (91).
(h) Remove the latch elements (94) to release ACT1 (1):
1 Remove the bolts (91) and the washers (96).
2 Remove the latch elements (94).
(i) Move ACT1 (1) away from the end stops (98) until you can measure the thickness of the putty imprint to get the dimension of the gap "c".
(j) Subtract the thickness of the shim plates "b" from the thickness of the putty "c" to get the result of the gap "a".
(k) Make sure that the dimension of the gap "a" is 4.5 +0.5 mm or -0.5 mm (0.1772 +0.0197 in. or -0.0197 in.).
(l) Replace the AIPC 28-11-27-01-030 SHIM PLATES (103) and do the measurement again until the dimension of the gap "a" is correct.
(2) Do the adjustment of the latch elements as follows:

Latch Adjustment ** ON A/C NOT FOR ALL

(a) Move ACT1 (1) to the forward position until ACT1 (1) has contact with the end stops (98).
(b) Install the latch elements (94) on the cargo floor to lock ACT1 (1) in the end position.
(c) Make sure that ACT1 (1) has contact with a minimum of two end stops (98) when you do the measurement.
(d) Measure the dimension of the gap "x".
(e) Make sure that ACT1 (1) is in contact with a minimum of two end stops (98) when you do the measurement.
(f) Make sure that dimension of the gap "x" is 2.3 +1 mm or -1 mm (0.0906 +0.0394 in. or -0.0394 in.).
(3) Install the latches on the roller tracks as follows:

Roller Track Latches and End Stops ** ON A/C NOT FOR ALL

(a) Make sure that the latches (94) and (95) are in the correct installation positions on the roller tracks (99).
(b) Install the washers (96), (97) and (100) and the bolts (91), (92) and (93).
(c) TORQUE the bolts (91) and (92) to between 3.4 and 2.8 m.daN (25.07 and 20.65 lbf.ft )

.
(4) Remove the forward part of the 98D28108299002 GUIDE-R I,ADDITIONAL CENTER TANK from the cargo floor, to make sure that you can install ACT2 in the aft cargo compartment.

ACT Guide - Removal/Installation ** ON A/C NOT FOR ALL

Subtask 28-11-27-420-052-B ** ON A/C NOT FOR ALL

C. Installation of ACT1

NOTE: Airbus recommends you to do the subsequent procedure only if ACT1 was removed.

(1) Connect the air hose to the ACT pressure line as follows:

Pressure Hose and Bonding Assembly ** 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 connection of the elbow union (35) is tight.
(d) Connect the union nut (36) of the air hose (39) to the elbow union (35).
(e) Tighten the union nuts (40) and (36).
(f) Make sure that the air hose (39) is not twisted when you tighten the nuts (40) and (36).

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.

(2) Connect the bonding straps of ACT1 to the aircraft structure as follows:

Pressure Hose and Bonding Assembly ** ON A/C NOT FOR ALL

(a) Remove the TAPE - ADHESIVE from the bonding straps (34).
(b) Make sure that the bonding straps (34) are correctly installed on the left and right sides of ACT1 (1).
(c) Connect the bonding straps (34) to the aircraft structure (31).
(d) Install the screws (33) on the anchor nuts (38).
(3) Do the electrical bonding on ACT1 (Ref. AMM TASK 20-28-00-912-802).
(4) Connect the electrical harness of ACT1 as follows:

Electrical Connections ** ON A/C NOT FOR ALL

(a) Remove the PLUG - DUMMY from the electrical ports (86), (87) and (89) on the cargo ceiling.
(b) Disconnect the electrical connector (88) from the stowage port (77) on ACT1 (1).
(c) Make sure that electrical harness 7619VC (83) is not damaged and correctly connected to the actuators of the ACT vent valve and the ACT fuel inlet-valve.
(d) Connect the electrical connector (88) to the port (87) on the cargo ceiling.
(e) Disconnect the electrical connectors (81) and (85) from the stowage ports (78) and (79) on ACT1 (1).
(f) Make sure that electrical harnesses 7617VC (82) and 7618VC (84) are not damaged and correctly connected to the ACT probes.
(g) Connect the electrical connectors (81) and (85) of the ACT probes to the ports (86) and (89) on the cargo ceiling.
(5) Install the water drain tubes on ACT1:

Water Drain Assembly ** ON A/C NOT FOR ALL

(d) Put the O-rings (9) and (11) in position on the drain tube (10).
(e) Push the drain tube (10) into the access hole (8) of the ACT water drain-valve.
(f) Make sure the drain tube (10) is correctly attached to the ACT water drain-port (7).
(g) Put the compression spring (12) and the flange (13) in position on the drain tube (10).
(h) Install the AIPC 28-11-04-03-060 RETAINING RING (14) or AIPC 28-11-84-03-060 RING (14) on the flange (13).

NOTE: You can use a PLIERS - THIN NOSE to install the retaining ring.

(i) Connect the bonding strap (15) to the aircraft structure.
(j) Install the washer (17) and the screw (18) on the bonding strap (15).
(6) Do the electrical bonding on the ACT water drain-tubes (Ref. AMM TASK 20-28-00-912-802).
(7) Do an operational check on the ACT water drain-valves (174QM and 175QM):
(a) Put the 98D28108293001 ADAPTER-WATER DRAIN, ADDITIONAL CENTER TANK on the ACT water drain-port.
(b) Push the ACT water drain-valve with the rod.
(c) Make sure that the ACT water drain-valve moves smoothly.
(d) Remove the 98D28108293001 ADAPTER-WATER DRAIN, ADDITIONAL CENTER TANK from the ACT water drain-port.
(e) Make sure that the ACT water drain-valve is fully closed.
(f) Do the same work step on the other ACT water drain-valve.
(8) Install the cavity drain assembly on ACT1 as follows:

Cavity Drain Assembly ** 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 O-rings that follow:

(b) Put the O-rings (22) and (24) in position on the cavity drain assembly (25).
(c) Put the cavity drain assembly (25) in the cavity drain port.
(d) Push and turn the cavity drain assembly (25) counter clockwise approximately to 60 deg (60 deg).
(e) Make sure that the locking plate (23) of the cavity drain assembly (25) is fully engaged in ACT1.
(f) Connect the union nuts (27) of the hose (28) to the drain fitting (26) and pipe fitting (29).
(g) Make sure that the hose (28) is not twisted when you tighten the union nuts (27).
(9) Connect the flexible vent pipe to ACT1 as follows:

Vent Pipe ACT 1 ** ON A/C NOT FOR ALL

NOTE: You can use the access openings in the cabin floor and the cargo ceiling to connect the vent and fuel pipe.

(a) Safety your tools with a strip at your hand, to make sure that the tool can not fall into the cargo compartment.
(b) Apply a thin layer of Mineral Oil base Grease-- Vaseline or Petrolatum - (Material No.03FAB1) on the new O-rings that follows:

(c) Put the O-rings (49) and (50) in position on the flange (47) of the flexible vent pipe (45).
(d) Align the holes of the vent pipe flange (47) with the studs (51).
(e) Connect the vent pipe flange (47) to the ACT flange (48).
(f) Install the nuts (46) on the studs (51).
(g) Torque the nuts (46) opposite to each other to between 0.5 and 0.4 m.daN (44.25 and 35.40 lbf.in )

.
(10) Connect the flexible fuel pipe to ACT1 as follows:

Fuel Pipe ACT 1 ** 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 O-rings that follow:

(b) Put the O-rings (55) and (56) in position on the flange (58) of the flexible fuel pipe (60).
(c) Align the holes of the fuel pipe flange (58) with the studs (54).
(d) Connect the fuel pipe flange (58) to the ACT flange (57).
(e) Install the nuts (59) on the studs (54).
(f) Torque the nuts (59) opposite to each other to between 0.5 and 0.4 m.daN (44.25 and 35.40 lbf.in )

.
(11) Install the aft flexible vent-pipe and fuel-pipe on ACT1 as follows:

Flexible Vent and Fuel-Pipe ** ON A/C NOT FOR ALL

NOTE: The flexible vent pipe and fuel pipe connect ACT1 with ACT2.

(a) Make sure that the blanking caps are removed from the vent and fuel line ends of ACT1.
(b) Clean the component interfaces and the adjacent area.
(c) Do an inspection of the component interfaces and the adjacent area.

NOTE: The installation of the flexible vent pipe and fuel pipe is the same.

(d) Apply a thin layer of Mineral Oil base Grease-- Vaseline or Petrolatum - (Material No.03FAB1) on the new AIPC 28-11-04-17-140 O-RING (154) and AIPC 28-11-04-17-020 O-RING (155).
(e) Put the O-rings (154) and (155) in position on the flange (152) of the flexible pipe (150).
(f) Align the holes of the flange (152) with the studs (156).
(g) Connect the flange (152) of the flexible pipe (150) to the ACT flange (153).
(h) Install the nuts (151) on the studs (156).
(i) Torque the nuts (151) opposite to each other to between 0.5 and 0.4 m.daN (44.25 and 35.40 lbf.in )

Subtask 28-11-27-820-051-C ** ON A/C NOT FOR ALL

D. Adjustment of the ACT

Attachment of the ACT ** ON A/C NOT FOR ALL

(1) Do the adjustment of the crash stoppers as follows:

ACT Adjustment ** ON A/C NOT FOR ALL

NOTE: Airbus recommends you to do the subsequent procedure to get the dimension of the gap "a":

If the initial ACT is installed in the aft cargo compartment
If a new ACT is to be installed in the aft cargo compartment
If new crash rods are installed in the aft cargo compartment.

NOTE: The gap "c" is the distance between the forward directed surface of the crash rods (102) and the crash stoppers (101) without the shim plates (103).

(a) Remove the shim plates (103) from the ACT (1).
(b) Apply a piece of putty to the surface of the crash stoppers (101).
(c) Move the ACT (1) into the aft cargo compartment.
(d) Move the ACT (1) to the forward position in the aft cargo compartment, until the ACT (1) has contact with the end stops (98).
(e) Make sure that the flexible pipes are correctly attached to the vent and fuel line ends of the ACT (1) to prevent damage on the pipes.

NOTE: You can use the openings in the cabin floor and the cargo ceiling, to get access to the flexible pipes.

(f) Make sure that the ACT has contact with a minimum of two end stops (98).
(g) Raise the latch elements (94) to lock the ACT (1) in position.

NOTE: This makes an imprint on the putty.

(h) Lower the latch elements (94) to release the ACT (1).
(i) Move the ACT (1) away from the end stops (98) until you can measure the thickness of the putty imprint to get the dimension of the gap "c".
(j) Subtract the thickness of the shim plates "b" from the thickness of the putty "c" to get the result of the gap "a".
(k) Make sure that the dimension of the gap "a" is 4.5 +0.5 mm or -0.5 mm (0.1772 +0.0197 in. or -0.0197 in.).
(l) Replace the AIPC 28-11-27-01-030 SHIM PLATES (103) and do the measurement again until the dimension of the gap "a" is correct.
(2) Do the adjustment of the latch elements as follows:

ACT Latch Adjustment ** ON A/C NOT FOR ALL

(a) Move the ACT (1) to the forward position until the ACT (1) has contact with the end stops (98).
(b) Raise the latch elements (94) to lock the ACT (1) in position.
(c) Measure the dimension of the gap "x". Make sure that ACT (1) has contact with a minimum of two end stops (98) when you do the measurement.
(d) Make sure that dimension of the gap "x" is 2.3 +1 mm or -1 mm (0.0906 +0.0394 in. or -0.0394 in.).
(e) If necessary, remove the ACT from the cargo compartment and adjust the gap with the adjustment bolt of the end stops (98).
(3) Make sure that all the latch elements (94) are correctly locked.
(4) Put the locking plates (93) in position on the latch elements (94).
(5) Install the washers (92) and the screws (91) on the locking plates (93).

Subtask 28-11-27-420-052-C ** ON A/C NOT FOR ALL

E. Installation of the ACT
(1) Connect the air hose to the ACT pressure line as follows:

Pressure Hose and Bonding Assembly ** ON A/C NOT FOR ALL

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.

(2) Connect the bonding straps of the ACT to the aircraft structure as follows:

Pressure Hose and Bonding Assembly ** ON A/C NOT FOR ALL

(a) Remove the TAPE - ADHESIVE from the bonding straps (34).
(b) Make sure that the bonding straps (34) are correctly installed on the left and right side of the ACT (1).
(c) Connect the bonding straps (34) to the aircraft structure (31).
(d) Install the screws (33) on the anchor nuts (38).
(3) Do the electrical bonding on the ACT (Ref. AMM TASK 20-28-00-912-802).
(4) Connect the electrical harness of the ACT as follows:

Electrical Connections ** ON A/C NOT FOR ALL

(a) Remove the PLUG - DUMMY from the electrical ports (86), (87) and (89) on the cargo ceiling.
(b) Disconnect the electrical connector (88) from the stowage port (77) on the ACT.
(c) Make sure that electrical harness 7619VC (83) is not damaged and correctly connected to the actuators of the ACT vent valve and the ACT fuel inlet-valve.
(d) Connect the electrical connector (88) to the port (87) on the cargo ceiling.
(e) Disconnect the electrical connectors (81) and (85) from the stowage ports (78) and (79) on the ACT.
(f) Make sure that electrical harnesses 7617VC (82) and 7618VC (84) are not damaged and correctly connected to the ACT probes.
(g) Connect the electrical connectors (81) and (85) of the ACT probes to the ports (86) and (89) on the cargo ceiling.
(5) Install the water drain tubes on the ACT as follows:

Water Drain Assembly ** ON A/C NOT FOR ALL

NOTE: You can use a PLIERS - THIN NOSE to install the retaining ring.

(i) Connect the bonding strap (15) to the aircraft structure.
(j) Install the washer (17) and the screw (18) on the bonding strap (15).
(6) Do the electrical bonding on the ACT water drain tubes (Ref. AMM TASK 20-28-00-912-802).
(7) Do an operational check on the ACT water drain-valves (174QM and 175QM) as follows:
(a) Put the 98D28108293001 ADAPTER-WATER DRAIN, ADDITIONAL CENTER TANK on the ACT water drain-port.
(b) Push the ACT water drain-valve with the rod.
(c) Make sure that the ACT water drain-valve moves smoothly.
(d) Remove the 98D28108293001 ADAPTER-WATER DRAIN, ADDITIONAL CENTER TANK from the ACT water drain-port.
(e) Make sure that the ACT water drain-valve is fully closed.
(f) Do the same work step on the other ACT water drain-valve.
(g) Install access panel 154AZ and 154CR (16) on the fuselage.
(8) Install the cavity drain assembly on the ACT as follows:

Cavity Drain Assembly ** 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 O-rings that follow:

(b) Put the O-rings (22) and (24) in position on the cavity drain assembly (25).
(c) Put the cavity drain assembly (25) in the cavity drain port.
(d) Push and turn the cavity drain assembly (25) counter clockwise approximately to 60 deg (60 deg).
(e) Make sure that the locking plate (23) of the cavity drain assembly (25) is fully engaged in the ACT.
(f) Connect the union nuts (27) of the hose (28) to the drain fitting (26) and the pipe fitting (29).
(g) Make sure that the hose (28) is not twisted when you tighten the union nuts (27).
(h) Install access panel 154BR (30) on the fuselage.
(9) Connect the flexible vent pipe to the ACT as follows:

Vent Pipe Connection ** ON A/C NOT FOR ALL

NOTE: You can use the access openings in the cabin floor and the cargo ceiling to connect the vent and fuel pipe.

.
(10) Connect the flexible fuel pipe to the ACT:

Fuel Pipe Connection ** 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 O-rings that follow:

Subtask 28-11-27-820-052-A ** ON A/C NOT FOR ALL

F. Adjustment of ACT2
(1) Make sure that ACT1 is fully installed in the aft cargo compartment.
(2) Adjustment of the crash stoppers as follows:

ACT 2 Adjustment ** ON A/C NOT FOR ALL

Roller Track Latches and End Stops ** ON A/C NOT FOR ALL

NOTE: Airbus recommends you to do the subsequent procedure to get the dimension of the gap "a":

If the initial ACT2 is to be installed in the aft cargo compartment,
If a new ACT2 is to be installed in the aft cargo compartment,

(a) Remove the shim plates (103) from ACT2.
(b) Apply a piece of putty to the surface of the crash stoppers (101).
(c) Move ACT2 into the aft cargo compartment.
(d) Move ACT2 to the forward position in the aft cargo compartment, until the ACT2 has contact with the end stops of the ACT1.
(e) Make sure that the flexible pipes of ACT1 are correctly attached to vent and fuel line ends of ACT2 to prevent damage on the pipes.

NOTE: You can use the openings in the cabin floor and the cargo ceiling, to get access to flexible pipes.

(f) Make sure that ACT2 has contact with a minimum of two end stops of the ACT1.
(g) Install the latch elements (94) and (95) on the cargo floor to lock ACT2 in the end position as follows:

NOTE: This makes an imprint on the putty.

1 Put the latch elements (94) and (95) in position on the roller tracks (99).
2 Install the washers (97) and (100) and the bolts (92) and (93).
(h) Remove the latch elements (94) and (95) to release ACT2 as follows:
1 Remove the bolts (92) (93) and the washers (97) (100).
2 Remove the latch elements (94) (95).
(i) Move ACT2 away from the end stops of ACT1 until you can measure the thickness of the putty imprint to get the dimension of the gap "c".
(j) Subtract the thickness of the shim plates "b" from the thickness of the putty "c" to get the result of the gap "a".
(k) Make sure that the dimension of the gap "a" is 4.5 +0.5 mm or -0.5 mm (0.1772 +0.0197 in. or -0.0197 in.).
(l) Replace the AIPC 28-11-27-01-030 SHIM PLATES (103) and do the measurement again until the dimension of the gap "a" is correct.
(3) Adjustment of the latch elements as follows:

Latch Adjustment ** ON A/C NOT FOR ALL

(a) Move ACT2 to the forward position until ACT2 has contact with the end stops of ACT1.
(b) Install the latch elements (94) and (95) on the cargo floor to lock ACT2 in the end position.
(c) Measure the dimension of the gap "x". Make sure that ACT2 has contact with a minimum of two end stops of ACT1 when you do the measurement.
(d) Make sure that dimension of the gap "x" is 2.3 +1 mm or -1 mm (0.0906 +0.0394 in. or -0.0394 in.).
(4) Install the latches on the roller tracks as follows:

Roller Track Latches and End Stops ** ON A/C NOT FOR ALL

(a) Make sure that the latches (94) and (95) are in the correct installation position on the roller tracks (99).
(b) Install the washers (96), (97) and (100) and the bolts (91), (92) and (93).
(c) TORQUE the bolts (91) and (92) to between 3.4 and 2.8 m.daN (25.07 and 20.65 lbf.ft )

Subtask 28-11-27-420-053-B ** ON A/C NOT FOR ALL

G. Installation of the ACT2
(1) Connect the air hose to the ACT pressure line:

Pressure Hose and Bonding Assembly ** ON A/C NOT FOR ALL

NOTE: The fuel transfer from the ACT2 to the ACT1 will not work if the air hose is not correctly connected to the ACT pressurization system.

(2) Connect the bonding straps of the ACT2 to the aircraft structure:

Pressure Hose and Bonding Assembly ** ON A/C NOT FOR ALL

(a) Remove the adhesive tape from the bonding straps (34).
(b) Make sure that the bonding straps (34) are correctly installed at the left and right side of the ACT2 (1).
(c) Connect the bonding straps (34) to the aircraft structure (31).
(d) Install the screws (33) on the anchor nuts (38).
(3) Do the electrical bonding on the ACT2 (Ref. AMM TASK 20-28-00-912-802).
(4) Connect the electrical harness of the ACT2:

Electrical Connections ** ON A/C NOT FOR ALL

(a) Remove the dummy plugs from the electrical ports (86), (87), (89) on the cargo-ceiling.
(b) Disconnect the electrical connector (88) from the stowage port (77) on the ACT2.
(c) Make sure that the electrical harness 7619VC (83) is not damaged and correctly connected to the actuators of the ACT2 vent valve and ACT2 fuel inlet valve.
(d) Connect the electrical connector (88) to the port (87) on the cargo-ceiling.
(e) Disconnect the electrical connectors (81), (85) from the stowage ports (78), (79) on the ACT2.
(f) Make sure that the electrical harnesses 7617VC (82) and 7618VC (84) are not damaged and correctly connected to the ACT2 probes.
(g) Connect the electrical connectors (81), (85) of the ACT2 probes to the ports (86), (89) on the cargo-ceiling.
(5) Install the water drain tubes on the ACT2:

Water Drain Assembly ** 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 28-11-04-18-100 O-RING (9), AIPC 28-11-04-18-100 O-RING (11).
(d) Put the O-rings (9), (11) in position on the drain tube (10).
(e) Push the drain tube (10) into the access hole (8) of the ACT water drain valve.
(f) Make sure the drain tube (10) is correctly attached to the ACT water drain port (7).
(g) Put the compression spring (12) and the flange (13) in position on the drain tube (10).
(h) Install the AIPC 28-11-04-18-060 RETAINING RING (14) on the flange (13).

NOTE: Use a PLIERS - THIN NOSE to install the retaining ring.

(i) Connect the bonding strap (15) to the aircraft structure.
(j) Install the washer (17) and the screw (18) on the bonding strap (15).
(6) Do the electrical bonding on the water drain tubes of the ACT2 (Ref. AMM TASK 20-28-00-912-802).
(7) Do an operational check on the water drain valves of the ACT2:
(a) Put the 98D28108293001 ADAPTER-WATER DRAIN, ADDITIONAL CENTER TANK on the ACT water drain port.
(b) Push the ACT water drain valve with the rod.
(c) Make sure that the ACT water drain valve moves smoothly.
(d) Remove the 98D28108293001 ADAPTER-WATER DRAIN, ADDITIONAL CENTER TANK from the ACT water drain port.
(e) Make sure that the ACT water drain valve is fully closed.
(f) Do the same work step on the other water drain valve.
(8) Install the cavity drain assembly on the ACT2:

Cavity Drain Assembly ** 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 28-11-04-17-100 O-RING (22), AIPC 28-11-04-17-090 O-RING (24).
(b) Put the O-rings (22), (24) in position on the cavity drain assembly (25).
(c) Put the cavity drain assembly (25) in the cavity drain port.
(d) Push and turn the cavity drain assembly (25) counter clockwise approximately 60 degrees.
(e) Make sure that the locking plate (23) of the cavity drain assembly (25) is fully engaged in the ACT2.
(f) Connect the union nuts (27) of the hose (28) to the drain fitting (26) and pipe fitting (29).
(g) Make sure that the hose (28) is not twisted when you tighten the union nuts (27).
(9) Connect the flexible vent-pipe to the ACT2:

Vent Pipe ACT 2 ** ON A/C NOT FOR ALL

NOTE: To connect the vent and fuel-pipe between the ACT1 and ACT2, you must use the access openings in the cabin floor and cargo ceiling.

NOTE: Safety your tools with a strip at your hand, to make sure that the tool can not fall into the cargo-compartment.

(a) Apply a thin layer of Mineral Oil base Grease-- Vaseline or Petrolatum - (Material No.03FAB1) on the new AIPC 28-11-04-17-140 O-RING (154), AIPC 28-11-04-17-020 O-RING (155).
(b) Put the O-rings (154), (155) in position on the flange (152) of the flexible vent-pipe (150).
(c) Align the holes of the flange (152) with the studs (156).
(d) Connect the vent-pipe flange (152) to the ACT2 flange (153).
(e) Install the nuts (151) on the studs (156).
(f) Torque the nuts (151) opposite to one another to between 0.5 and 0.4 m.daN (44.25 and 35.40 lbf.in )

.
(10) Connect the flexible fuel-pipe to the ACT2:

Fuel Pipe ACT 2 ** 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 28-11-04-17-140 O-RING (162), AIPC 28-11-04-17-020 O-RING (161).
(b) Put the O-rings (161), (162) in position on the flange (164) of the flexible fuel-pipe (166).
(c) Align the holes of the flange (164) with the studs (160).
(d) Connect the fuel-pipe flange (164) to the ACT2 flange (163).
(e) Install the nuts (165) on the studs (160).
(f) Torque the nuts (165) opposite to one another to between 0.5 and 0.4 m.daN (44.25 and 35.40 lbf.in )

Subtask 28-11-27-710-050-A ** ON A/C NOT FOR ALL

H. Test
(1) Do the Functional Check of the Vent/Transfer Pipe Shrouds and ACT Drain Pipe Connectors (Ref. AMM TASK 28-28-00-790-004).
(2) Do the Operational Test of the ACT Manual Transfer System (Ref. AMM TASK 28-28-00-710-001).
(3) Do the Operational Test of the ACT Automatic Transfer System (Ref. AMM TASK 28-28-00-710-004).
(4) Do a visual inspection on the ACT Fuel/Vent-Line connections.
(a) Make sure that there are no leaks.

NOTE: Leaks are not permitted.

(5) Do the Leak Check of the Leak Monitor for Evidence of Fuel Leakage (Ref. AMM TASK 28-28-00-200-003).

NOTE: After the leak check, it is possible that small signs of fuel still can remain in the cavity drain line of the ACT.

5. Close-up
Subtask 28-11-27-410-051-A ** ON A/C NOT FOR ALL

A. Close Access
(1) Remove the 98D28108299000 GUIDE-R I,ADDITIONAL CENTER TANK from the cargo floor:

ACT Guide - Removal/Installation ** ON A/C NOT FOR ALL

(a) Remove the fasteners (112), (113) from the mounting bracket (114).
(b) Remove the rigging pins (111) from the guide (116).
(c) Remove the 98D28108299000 GUIDE-R I,ADDITIONAL CENTER TANK (116) from the aft cargo-compartment.
(2) Install the integrated impact wall in the aft cargo-compartment (Ref. AMM TASK 28-11-49-400-001).
(3) Close the aft cargo-compartment door (Ref. AMM TASK 52-30-00-860-002).
(4) On the lower center fuselage, install the access panels 154AZ, 154CR, 154BR.
(5) In the cabin-compartment: x
(a) Install the applicable access panel on the cargo-ceiling.
(b) Install the cabin floor panel 251KG (Ref. AMM TASK 53-42-12-400-001).
(6) Make sure that the work area is clean and clear of tools and other items.

Subtask 28-11-27-410-051-C ** ON A/C NOT FOR ALL

A. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Remove the 98D28108299002 GUIDE-R I,ADDITIONAL CENTER TANK from the cargo floor:

ACT Guide - Removal/Installation ** ON A/C NOT FOR ALL

(a) Remove the fasteners (112) and (113) from the mounting bracket (114).
(b) Remove the rigging pins (111) from the guide (116).
(c) Remove the 98D28108299002 GUIDE-R I,ADDITIONAL CENTER TANK (116) from the aft cargo compartment.
(3) Install the integrated impact wall in the aft cargo compartment (Ref. AMM TASK 28-11-49-400-001).
(4) If removed, install the protection covers on the roller tracks (Ref. AMM TASK 25-52-54-400-001).
(5) Close the aft cargo-compartment door (Ref. AMM TASK 52-30-00-860-002).
(6) On the lower center fuselage, install access panels 153BR, 154DR, 153AR, 154AZ, 154BR, 154CR.
(7) In the cabin compartment:
(a) Install the applicable access panels on the cargo ceiling.
(b) Install cabin floor panel 251PG and 251KG (Ref. AMM TASK 53-42-12-400-001).

Subtask 28-11-27-865-052-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	ACT1/REFUEL & SPLY	33QU	L29
121VU	FUEL/HI/LVL/SPLY	1QJ	L25
121VU	FUEL/RFL/DFL/SPLY	2QU	L24
121VU	FUEL/RFL/DFL/XFR/DEFUEL/VALVE	1QU	L23
121VU	ACT XFR VALVE MAN CTL	30QH	N29
121VU	ACT1/CTL & SPLY	9QH	P29
121VU	ACT PUMP SUPPLY	25QH	Q29

Subtask 28-11-27-942-050-A ** ON A/C NOT FOR ALL

C. Close up
(1) Remove the WARNING NOTICE(S).
(2) Remove the access platform(s).
(3) De-energize the ground service network
(Ref. AMM TASK 24-42-00-862-001).
(4) Remove the ground support and maintenance equipment, the special and standard tools and all other items.
(5) Put the aircraft back to the serviceable condition.

[Rev.10 from 2021] 2026.04.01 03:47:02 UTC