W DOC AIRBUS | AMM A320F

Removal of the Additional Center Tank (ACT)

TASK 28-11-27-000-001-A
Removal 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
1
CAP - BLANKING
No specific
4
CAP - SEALING
No specific
1
CONTAINER 30 L(8 USGAL)
No specific
2
PLIERS - THIN NOSE
No specific
AR
PLUG - BLANKING
No specific
AR
PLUG - DUMMY
No specific
AR
SAFETY CLIP - CIRCUIT BREAKER
No specific
AR
TAPE - ADHESIVE
No specific
1
WARNING NOTICE(S)
No specific
Torque wrench: range to between 0.44 and 0.36 m.daN (38.94 and 31.86 lbf.in ) T
98D28108298000
1
STOWAGE - CONTAINER FUEL, ACT
98D28108299000
1
GUIDE-R I,ADDITIONAL CENTER TANK
98D28108299002
1
GUIDE-R I,ADDITIONAL CENTER TANK
98D28108328000
2
CONTAINER - REST FUEL, ACT
98D28108388000
1
STOWAGE - CONTAINER FUEL, ACT 1 AND 2
98D28108561000
2
EXTRACTOR - WATER DRAIN TUBE
98D28108563000
2
COVER, FUEL VENT-ACT
 B. Consumable Materials
REFERENCE
DESIGNATION
(Material No.03FAB1)
Mineral Oil base Grease-- Vaseline or Petrolatum -
(Material No.14QFB1)
Wire-Locking Dia: 0.8 mm CRES Nickel Alloy -
(Material No.14SBA1)
Textile-Lint free Cotton -
 C. Work Zones and Access Panels
ZONE/ACCESS
ZONE DESCRIPTION
154AZ, 154BR, 154CR, 251KG
153AR, 153BR, 154DR, 251PG
251AG
 D. Expendable Parts
FIG.ITEM
DESIGNATION
IPC-CSN
124
O-RING
AIPC 28-11-04-05-040
129
O-RING
AIPC 28-11-04-05-040
134
O-RING
AIPC 28-11-04-05-040
123
O-RING
AIPC 28-11-04-05-060
133
O-RING
AIPC 28-11-04-05-060
132
O-RING
AIPC 28-11-04-05-120
124
O-RING
AIPC 28-11-84-05-040
129
O-RING
AIPC 28-11-84-05-040
134
O-RING
AIPC 28-11-84-05-040
123
O-RING
AIPC 28-11-84-05-060
133
O-RING
AIPC 28-11-84-05-060
132
O-RING
AIPC 28-11-84-05-120
 E. Referenced Information
REFERENCE
DESIGNATION
TASK 24-42-00-861-001-A
Energize the Ground Service Network from the External Power
TASK 25-52-54-000-001-A
Removal of the Protection Cover
TASK 28-00-00-910-001-A
Fuel Safety Procedures
TASK 28-11-49-000-001-A
Removal of the ACT Integrated Impact Wall
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 52-30-00-860-001-A
Open 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
F Additional Center Tank (ACT) ** ON A/C NOT FOR ALL
F Electrical Connections
F Pressure Hose and Bonding Assembly
F Water Drain Assembly ** ON A/C NOT FOR ALL
F Cavity Drain Assembly ** ON A/C NOT FOR ALL
F Vent Pipe ACT 2 ** ON A/C NOT FOR ALL
F Fuel Pipe ACT 2 ** ON A/C NOT FOR ALL
F ACT Guide - Removal/Installation ** ON A/C NOT FOR ALL
F Roller Track Latches and End Stops ** ON A/C NOT FOR ALL
F Flexible Vent and Fuel-Pipe ** ON A/C NOT FOR ALL
F Vent Pipe ACT 1 ** ON A/C NOT FOR ALL
F Fuel Pipe ACT 1 ** ON A/C NOT FOR ALL
F Additional Center Tank (ACT) ** ON A/C NOT FOR ALL
F Water Drain Assembly ** ON A/C NOT FOR ALL
F Cavity Drain Assembly ** ON A/C NOT FOR ALL
F Vent Pipe Connection ** ON A/C NOT FOR ALL
F Fuel Pipe Connection ** ON A/C NOT FOR ALL
F ACT Guide - Removal/Installation ** ON A/C NOT FOR ALL
F Attachment of the ACT ** ON A/C NOT FOR ALL
F Blanking Flange Caps of the ACT
3. Job Set-up
Subtask 28-11-27-860-050-A ** ON A/C NOT FOR ALL
A. Aircraft Maintenance Configuration
   (1) Obey the fuel safety procedures (Ref. AMM TASK 28-00-00-910-001).
   (2) Energize the ground service network (Ref. AMM TASK 24-42-00-861-001).
   (3) Defuel the Additional Center Tank (ACT) (Ref. AMM TASK 28-25-00-650-001).
   (4) Open the aft cargo-compartment door (Ref. AMM TASK 52-30-00-860-001).
   (5) Put an ACCESS PLATFORM 2M (6 FT) in position at the opening of the aft cargo compartment door.
   (6) On the refuel/defuel control panel 800VU/801VU:
  • put the refuel valve switch in the OPEN position,
  • put the MODE SELECT switch in the REFUEL position.

   (7) Put all switches related to the fuel system to OFF.
   (8) Look on the ECAM Fuel Page and make sure that the ACT-System does not show.
   (9) Put the WARNING NOTICE(S) in position on:
  • the refuel/defuel panel 800VU 801VU,
  • the fueling panel 40VU,
    to tell persons not to operate the refuel/defuel system.
Subtask 28-11-27-865-050-A ** ON A/C NOT FOR ALL
B. Open, safety and tag this(these) circuit breaker(s):
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
121VUACT1/REFUEL & SPLY33QUL29
121VUFUEL/HI/LVL/SPLY1QJL25
121VUFUEL/RFL/DFL/SPLY2QUL24
121VUFUEL/RFL/DFL/XFR/DEFUEL/VALVE1QUL23
121VUACT XFR VALVE MAN CTL30QHN29
121VUACT1/CTL & SPLY9QHP29
121VUACT PUMP SUPPLY25QHQ29
** ON A/C NOT FOR ALL
121VUACT2/REFUEL & SPLY34QUL28
121VUACT2/CTL & SPLY10QHP28
Subtask 28-11-27-220-050-A ** ON A/C NOT FOR ALL
C. Visual Inspection - Before Removal of the ACT.
   (1) Do a check of the leak monitors and look for signs of fuel leakage.
   (2) Look for signs of fuel leakage at the openings of the access panels (16) 154AZ and 154CR.
   (3) If you find signs of leakage, clean it with lint-free cotton cloth Textile-Lint free Cotton - (Material No.14SBA1) .
NOTE: Leaks are not permitted.
   (4) Put a CONTAINER 30 L(8 USGAL) in position below the openings of the access panels (16) 154AZ and 154CR.
Subtask 28-11-27-010-051-A ** ON A/C NOT FOR ALL
D. Get Access
   (1) On the lower center fuselage:
     (a) Remove the panels 154AZ, 154CR, 154BR, to get access to the water drain and cavity drain system of the ACT.
   (2) In the cabin compartment:
     (a) Remove the access panel 251KG from the cabin floor panel 251AG (Ref. AMM TASK 53-42-12-000-001).
     (b) Remove the applicable access panel from the cargo-ceiling, to get access to the line connection of the ACT.
   (3) In the aft cargo-compartment:
     (a) Remove the integrated impact wall from the ACT (Ref. AMM TASK 28-11-49-000-001).
Subtask 28-11-27-220-050-C ** ON A/C NOT FOR ALL
E. Visual Inspection - Before Removal of an Additional Center Tank (ACT1 and ACT2).
   (1) Do a check of the leak monitors and look for signs of fuel leakage.
   (2) For the ACT2:
  • look for signs of fuel leakage at the openings of the access panels 153BR and 154DR.
  • if you find signs of leakage, clean it with lint-free cotton cloth Textile-Lint free Cotton - (Material No.14SBA1) .
NOTE: Leaks are not permitted.
   (3) Put a CONTAINER 30 L(8 USGAL) below the openings of the access panels 153BR and 154DR.
   (4) For the ACT1:
  • look for signs of fuel leakage at the openings of the access panels 153AR and 154BR.
  • if you find signs of leakage, clean it with lint-free cotton cloth Textile-Lint free Cotton - (Material No.14SBA1) .
NOTE: Leaks are not permitted.
   (5) Put a CONTAINER 30 L(8 USGAL) in position below the openings of the access panels 153AR and 154BR.
Subtask 28-11-27-010-051-C ** ON A/C NOT FOR ALL
F. Get Access
   (1) On the lower center fuselage:
     (a) Remove the access panels:
  • 153BR and 154DR to get access to the water drain system of ACT2
  • 153AR to get access to the cavity drain system of ACT2
  • 154AZ and 154BR to get access to the water drain system of ACT1
  • 154CR to get access to the cavity drain system of ACT1.
   (2) In the cabin compartment:
     (a) Remove cabin floor panel 251PG and the applicable cargo ceiling panel, to get access to the line connection of ACT2.
     (b) Remove cabin floor panel 251KG and the applicable cargo ceiling panel, to get access to the line connection of ACT1 (Ref. AMM TASK 53-42-12-000-001).
   (3) In the aft cargo compartment:
     (a) If installed, remove the protection covers from the roller tracks (Ref. AMM TASK 25-52-54-000-001).
     (b) Remove the integrated impact wall from the ACT (Ref. AMM TASK 28-11-49-000-001).
Subtask 28-11-27-680-050-A ** ON A/C NOT FOR ALL
G. Drain the remaining fuel from the ACT (Ref. AMM TASK 28-25-00-650-005).
4. Procedure
Subtask 28-11-27-020-052-B ** ON A/C NOT FOR ALL
A. Removal of ACT2
F Additional Center Tank (ACT) ** ON A/C NOT FOR ALL
   (1) Disconnect the electrical harness of ACT2 as follows:
F Electrical Connections ** ON A/C NOT FOR ALL
     (a) On the cargo ceiling, disconnect electrical connectors 7617VC-A (81), 7618VC-A (85) and 7619VC-A (88) from the electrical ports (89), (86) and (87).
     (b) Put a PLUG - DUMMY on the electrical ports (89), (86) and (87).
     (c) Connect the electrical connectors (81), (85) and (88) to the stowage ports (77), (78) and (79) on ACT2 (1).
   (2) Disconnect the bonding straps of ACT2 from the aircraft structure as follows:
F Pressure Hose and Bonding Assembly ** ON A/C NOT FOR ALL
     (a) Remove the screws (33) from the anchor nuts (38).
     (b) Disconnect the bonding straps (34) from the aircraft structure (31).
     (c) Attach the bonding straps (34) to ACT2 (1) with an TAPE - ADHESIVE.
   (3) Disconnect the air hose assembly from the ACT pressure line as follows:
F Pressure Hose and Bonding Assembly ** ON A/C NOT FOR ALL
     (a) Loosen the union nut (36).
     (b) Disconnect the air hose assembly (39) from the elbow union (35).
     (c) Attach the air hose assembly (39) to ACT2 (1) with the TAPE - ADHESIVE.
NOTE: You can remove the air hose assembly from ACT2 after the removal of ACT2 from the cargo compartment.
   (4) Remove the water drain tubes from ACT2 as follows:
F Water Drain Assembly ** ON A/C NOT FOR ALL
     (a) Put the removed parts in the 98D28108388000 STOWAGE - CONTAINER FUEL, ACT 1 AND 2.
     (b) Remove the screw (18) and the washer (17) from the bonding strap (15).
     (c) Disconnect the bonding strap (15) from the aircraft structure.
     (d) Remove the retaining ring (14) from the flange (13).
NOTE: You can use a PLIERS - THIN NOSE to remove the retaining ring.
     (e) Remove the flange (13) and the compression spring (12) from the drain tube (10).
     (f) Put an 98D28108561000 EXTRACTOR - WATER DRAIN TUBE in the drain tube (10).
     (g) Turn the 98D28108561000 EXTRACTOR - WATER DRAIN TUBE 90 deg (90 deg) until it hangs in the drain tube (10).
     (h) Pull the 98D28108561000 EXTRACTOR - WATER DRAIN TUBE down and remove the drain tube (10) from the access hole.
     (i) Remove and discard the O-rings (11).
   (5) Remove the cavity drain assembly from ACT2 as follows:
F Cavity Drain Assembly ** ON A/C NOT FOR ALL
     (a) Make sure that the access panel (30) is removed from the fuselage.
     (b) Disconnect the union nuts (27) from the drain fitting (26) and the pipe fitting (29).
     (c) Make sure that you do not twist the hose (28) when you loosen the nuts (27).
     (d) Remove the hose (28) from the aircraft.
     (e) Push and turn the cavity drain assembly (25) clockwise approximately to 60 deg (60 deg).
     (f) Make sure that the locking plate (23) of the cavity drain assembly (25) is disengaged from ACT2.
     (g) Remove the cavity drain assembly (25) from the cavity drain port.
     (h) Remove and discard the O-rings (22) and (24).
     (i) Put the PLUG-BLANKING in each disconnected line end.
   (6) Disconnect the flexible vent pipe from ACT2 as follows:
F Vent Pipe ACT 2 ** ON A/C NOT FOR ALL
NOTE: You can use the access openings in the cabin floor and the cargo ceiling, to disconnect the vent and fuel pipe from ACT2.
     (a) Remove the nuts (151) from the studs (156).
     (b) Disconnect the vent pipe flange (152) from the ACT flange (153).
     (c) Discard the O-rings (154) and (155):
       1 Do not remove the nuts in the top and bottom positions of the ACT flange.
   (7) Disconnect the flexible fuel pipe from ACT2 as follows:
F Fuel Pipe ACT 2 ** ON A/C NOT FOR ALL
     (a) Put a 98D28108328000 CONTAINER - REST FUEL, ACT below the flexible fuel pipe (166) to catch the remaining fuel in the pipe.
     (b) Remove the nuts (165) from the studs (160).
     (c) Disconnect the fuel pipe flange (164) from the ACT flange (163).
     (d) Discard the O-rings (161) and (162):
       1 Do not remove the nuts in the top and bottom positions of the ACT flange.
   (8) Prepare for removal of ACT2 as follows:
F ACT Guide - Removal/Installation ** ON A/C NOT FOR ALL
     (a) Put an applicable platform at the cargo door opening to removal ACT2 from the cargo compartment.
     (b) Put the 98D28108299002 GUIDE-R I,ADDITIONAL CENTER TANK in the correct position in the aft cargo compartment.
     (c) Assemble and safety the 98D28108299002 GUIDE-R I,ADDITIONAL CENTER TANK with the rigging pins (111).
     (d) Safety the ACT guide (116) in the door sill area with the fasteners (112) and (113) in the mounting bracket (114) and the seat track (115).
   (9) Remove the latches from the roller tracks as follows:
F Roller Track Latches and End Stops ** ON A/C NOT FOR ALL
     (a) Make match marks on the components that you disconnect/remove to record their connections/positions. This is important for the subsequent installation procedure.
     (b) Remove the bolts (91), (92) and (93) and the washers (96), (97) and (100) from the latches (94) and (95).
     (c) Remove the latches (94) and (95) from the roller tracks (99).
   (10) Remove ACT2 from the aft cargo compartment as follows:
     (a) Carefully move the ACT2 (1) away from the flexible vent pipe (150) and the flexible fuel pipe (166).
F Vent Pipe ACT 2 ** ON A/C NOT FOR ALL
F Fuel Pipe ACT 2 ** ON A/C NOT FOR ALL
     (b) Put a CAP - SEALING on the end of the flexible vent pipe (150) and the flexible fuel pipe (166).
     (c) Move ACT2 (1) out of the cargo compartment.
NOTE: The ACT weighs approximately 335 kg (738.5484 lb).
Subtask 28-11-27-020-051-A ** ON A/C NOT FOR ALL
B. Removal of ACT1
NOTE: Airbus recommends you to do the subsequent procedure, if it is necessary to remove ACT1 from the aft cargo compartment.
   (1) Remove the aft flexible vent and fuel pipe from ACT1 as follows:
F Flexible Vent and Fuel-Pipe ** ON A/C NOT FOR ALL
NOTE: You must remove the aft flexible pipes from ACT1, before you remove ACT1 from the cargo compartment.
     (a) Remove the nuts (151) from the studs (156).
     (b) Remove the flexible pipe (150) from the ACT flange (153).
     (c) Remove and discard the O-rings (154) and (155).
   (2) Disconnect the electrical harness of ACT1 as follows:
F Electrical Connections ** ON A/C NOT FOR ALL
     (a) On the cargo ceiling, disconnect electrical connectors 7617VC-A (81), 7618VC-A (85) and 7619VC-A (88) from the electrical ports (89), (86) and (87).
     (b) Put a PLUG - DUMMY on the electrical ports (89), (86) and (87).
     (c) Connect the electrical connectors (81), (85) and (88) to the stowage ports (77), (78) and (79) on ACT1 (1).
   (3) Disconnect the bonding straps of ACT1 from the aircraft structure as follows:
F Pressure Hose and Bonding Assembly ** ON A/C NOT FOR ALL
     (a) Remove the screws (33) from the anchor nuts (38).
     (b) Disconnect the bonding straps (34) from the aircraft structure (31).
     (c) Attach the bonding straps (34) to ACT2 (1) with an TAPE - ADHESIVE.
   (4) Disconnect the air hose assembly from the ACT pressure line as follows:
     (a) Loosen the union nut (36).
     (b) Disconnect the air hose assembly (39) from the elbow union (35).
     (c) Attach the air hose assembly (39) to ACT1 (1) with the TAPE - ADHESIVE.
   (5) Remove the water drain tubes from ACT1 as follows:
F Water Drain Assembly ** ON A/C NOT FOR ALL
     (a) Remove the screw (18) and the washer (17) from the bonding strap (15).
     (b) Disconnect the bonding strap (15) from the aircraft structure.
     (c) Remove the retaining ring (14) from the flange (13).
NOTE: You can use a PLIERS - THIN NOSE to remove the retaining ring.
     (d) Remove the flange (13) and the compression spring (12) from the drain tube (10).
     (e) Put an 98D28108561000 EXTRACTOR - WATER DRAIN TUBE into the drain tube (10).
     (f) Turn the 98D28108561000 EXTRACTOR - WATER DRAIN TUBE 90 deg (90 deg) until it hangs in the drain tube (10).
     (g) Pull the 98D28108561000 EXTRACTOR - WATER DRAIN TUBE down and remove drain tube (10) from the access hole.
     (h) Remove and discard the O-rings (11).
   (6) Remove the cavity drain assembly from ACT1 as follows:
F Cavity Drain Assembly ** ON A/C NOT FOR ALL
     (a) Make sure that the access panel (30) is removed from the fuselage.
     (b) Disconnect the union nuts (27) from the drain fitting (26) and the pipe fitting (29).
     (c) Make sure that you do not twist the hose (28) when you loosen the nuts (27).
     (d) Remove the hose (28) from the aircraft.
     (e) Push and turn the cavity drain assembly (25) clockwise approximately to 60 deg (60 deg).
     (f) Make sure that the locking plate (23) of the cavity drain assembly (25) is disengaged from ACT2.
     (g) Remove the cavity drain assembly (25) from the cavity drain port.
     (h) Remove and discard the O-rings (22) and (24).
     (i) Put the PLUG-BLANKING in each disconnected line end.
   (7) Disconnect the forward flexible vent-pipe from ACT1 as follows:
F 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 disconnect the vent and fuel pipe from ACT1.
     (a) Remove the nuts (46) from the studs (51).
     (b) Disconnect the flexible vent pipe (45) from the ACT flange (48).
     (c) Remove and discard the O-rings (49) and (50).
   (8) Disconnect the forward flexible fuel-pipe from ACT1 as follows:
F Fuel Pipe ACT 1 ** ON A/C NOT FOR ALL
     (a) Put a 98D28108328000 CONTAINER - REST FUEL, ACT below the flexible fuel pipe (60) to catch the remaining fuel in the pipe.
     (b) Remove the nuts (59) from the studs (54).
     (c) Disconnect the flexible fuel pipe (60) from the ACT flange (57).
     (d) Remove and discard the O-rings (55) and (56).
   (9) Remove the latches from the roller tracks as follows:
F Roller Track Latches and End Stops ** ON A/C NOT FOR ALL
     (a) Make match marks on the components that you disconnect/remove to record their connections/positions. This is important for the subsequent installation procedure.
     (b) Remove the bolts (91), (92) and (93) and the washers (96), (97) and (100) from the latches (94) and (95).
     (c) Remove the latches (94) and (95) from the roller tracks (99).
   (10) Remove ACT1 from the aft cargo compartment as follows:
     (a) Make sure that the 98D28108299002 GUIDE-R I,ADDITIONAL CENTER TANK is correctly installed in the cargo compartment to support the removal of ACT1.
     (b) Carefully move ACT1 away from the flexible vent pipe (45) and the flexible fuel pipe (60).
     (c) Move ACT1 out of the cargo compartment.
NOTE: The ACT weighs approximately 374 kg (824.5286 lb).
   (11) Support the flexible vent pipe (45) and the flexible fuel pipe (60) at FR. 47 as follows:
     (a) Put a CAP - SEALING on the end of the flexible vent pipe (45) and the flexible fuel pipe (60).
Subtask 28-11-27-020-051-B ** ON A/C NOT FOR ALL
B. Removal of the ACT
F Additional Center Tank (ACT) ** ON A/C NOT FOR ALL
   (1) Disconnect the electrical harness of the ACT as follows:
F Electrical Connections ** ON A/C NOT FOR ALL
     (a) On the cargo ceiling, disconnect electrical connectors 7617VC-A (81), 7618VC-A (85) and 7619VC-A (88) from the electrical ports (89), (86) and (87).
     (b) Put a PLUG - DUMMY on the electrical ports (89), (86) and (87).
     (c) Connect the electrical connectors (81), (85) and (88) to the stowage ports (77), (78) and (79) on the ACT (1).
   (2) Disconnect the bonding straps of the ACT from the aircraft structure as follows:
F Pressure Hose and Bonding Assembly ** ON A/C NOT FOR ALL
     (a) Remove the screws (33) from the anchor nuts (38).
     (b) Disconnect the bonding straps (34) from the aircraft structure (31).
     (c) Attach the bonding straps (34) to the ACT (1) with an TAPE - ADHESIVE.
   (3) Disconnect the air hose assembly from the ACT pressure line as follows:
     (a) Loosen the union nut (36).
     (b) Disconnect the air hose assembly (39) from the elbow union (35).
     (c) Attach the air hose assembly (39) to the ACT (1) with the TAPE - ADHESIVE.
NOTE: You can remove the air hose assembly from the ACT after the removal of the ACT from the cargo compartment.
   (4) Remove the water drain tubes from the ACT as follows:
F Water Drain Assembly ** ON A/C NOT FOR ALL
     (a) Put the removed parts in the 98D28108298000 STOWAGE - CONTAINER FUEL, ACT.
     (b) Remove the screw (18) and the washer (17) from the bonding strap (15).
     (c) Disconnect the bonding strap (15) from the aircraft structure.
     (d) Remove the retaining ring (14) from the flange (13).
NOTE: You can use a PLIERS - THIN NOSE to remove the retaining ring.
     (e) Remove the flange (13) and the compression spring (12) from the drain tube (10).
     (f) Put an 98D28108561000 EXTRACTOR - WATER DRAIN TUBE into the drain tube (10).
     (g) Turn the 98D28108561000 EXTRACTOR - WATER DRAIN TUBE 90 deg (90 deg) until it hangs in the drain tube (10).
     (h) Pull the 98D28108561000 EXTRACTOR - WATER DRAIN TUBE down and remove the drain tube (10) from the access hole.
     (i) Remove and discard the O-rings (11).
   (5) Remove the cavity drain assembly from the ACT as follows:
F Cavity Drain Assembly ** ON A/C NOT FOR ALL
     (a) Make sure that the access panel (30) is removed from the fuselage.
     (b) Disconnect the union nuts (27) from the drain fitting (26) and the pipe fitting (29).
     (c) Make sure that you do not twist the hose (28) when you loosen the nuts (27).
     (d) Remove the hose (28) from the aircraft.
     (e) Push and turn the cavity drain assembly (25) clockwise approximately to 60 deg (60 deg).
     (f) Make sure that the locking plate (23) of the cavity drain assembly (25) is disengaged from the ACT.
     (g) Remove the cavity drain assembly (25) from the cavity drain port.
     (h) Remove and discard the O-rings (22) and (24).
   (6) Disconnect the flexible vent pipe from the ACT as follows:
F 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 disconnect the vent and fuel pipe from the ACT.
     (a) Remove the nuts (46) from the studs (51).
     (b) Disconnect the flexible vent pipe (45) from the ACT flange (48).
     (c) Remove and discard the O-rings (49) and (50).
   (7) Disconnect the flexible fuel pipe from the ACT as follows:
F Fuel Pipe Connection ** ON A/C NOT FOR ALL
     (a) Put a 98D28108328000 CONTAINER - REST FUEL, ACT below the flexible fuel pipe (60) to catch the remaining fuel in the pipe.
     (b) Remove the nuts (59) from the studs (54).
     (c) Disconnect the flexible fuel pipe (60) from the ACT flange (57).
     (d) Remove and discard the O-rings (55) and (56).
   (8) Prepare for removal of the ACT as follows:
F ACT Guide - Removal/Installation ** ON A/C NOT FOR ALL
     (a) Put an applicable platform at the cargo door opening to remove the ACT.
     (b) Put the 98D28108299000 GUIDE-R I,ADDITIONAL CENTER TANK in the correct position in the aft cargo compartment.
     (c) Assemble and safety the 98D28108299000 GUIDE-R I,ADDITIONAL CENTER TANK with the rigging pins (111).
NOTE: If there is a cargo loading system installed in the aft cargo compartment, the 98D28108299000 GUIDE-R I,ADDITIONAL CENTER TANK is not necessary.
     (d) Safety the ACT guide (116) in the door sill area with the fasteners (112) and (113) in the mounting bracket (114) and the seat track (115).
   (9) Remove the ACT from the aft cargo compartment as follows:
F Attachment of the ACT ** ON A/C NOT FOR ALL
     (a) Remove the screws (91), the washers (92) and the locking plates (93) from the latch elements (94).
     (b) Install the screws (91) and the washers (92) in the latch elements (94).
     (c) Lower the latches (94) to release the ACT (1).
     (d) Carefully move the ACT (1) away from the flexible vent pipe (45) and the flexible fuel pipe (60).
F Vent Pipe Connection ** ON A/C NOT FOR ALL
F Fuel Pipe Connection ** ON A/C NOT FOR ALL
     (e) Move the ACT (1) out of the cargo compartment.
NOTE: The ACT weighs approximately 374 kg (824.5286 lb).
   (10) Support the flexible vent pipe (45) and the flexible fuel pipe (60) as follows:
     (a) Put a CAP - SEALING on the end of the flexible vent pipe (45) and the flexible fuel pipe (60).
5. Close-up
Subtask 28-11-27-551-050-A ** ON A/C NOT FOR ALL
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.
A. Preparation for Storage
NOTE: The subsequent procedure is the same for each ACT. Therefore only one ACT is given.
   (1) If the ACT is not to be reinstalled within twenty days, you must do the following:
     (a) Do the storage procedure in the workshop.
NOTE: Because of the possibility that the bladder tank can be damaged, the storage procedure must be done in the workshop only.
Subtask 28-11-27-010-052-A ** ON A/C NOT FOR ALL
B. Remove the air hose assembly
F Pressure Hose and Bonding Assembly ** ON A/C NOT FOR ALL
   (1) Loosen the union nut (40) and remove it from the ACT pressurization check valve (32).
   (2) Remove the air hose assembly (39).
   (3) Put blanking caps on the port of the check valve (32) and on the elbow union (35).
   (4) Put a CAP - BLANKING on each end of the air hose assembly (39).
   (5) Remove the ACT guide from the aft cargo compartment.
     (a) Loosen and remove the fasteners (112) and (113) from the mounting bracket (114).
     (b) Remove the rigging pins (111) from the guide.
     (c) Remove the ACT guide from the aft cargo compartment.
Subtask 28-11-27-010-052-C ** ON A/C NOT FOR ALL
B. Remove the air hose assembly (39)
F Pressure Hose and Bonding Assembly ** ON A/C NOT FOR ALL
F Water Drain Assembly ** ON A/C NOT FOR ALL
NOTE: The subsequent procedure is the same for each ACT. Therefore only one ACT is given. Differences between each ACT are given where applicable.
   (1) Remove the O-ring (9) from the water drain port in the base of the ACT (1).
   (2) Loosen the union nut (40) and remove it from the ACT pressurization check valve (32).
   (3) Remove the air hose assembly (39).
   (4) Put blanking caps on the port of the check valve (32) and on the elbow union (35).
   (5) Put a CAP - BLANKING on each end of the air hose assembly (39).
   (6) Remove the ACT guide from the aft cargo compartment.
F ACT Guide - Removal/Installation ** ON A/C NOT FOR ALL
     (a) Loosen and remove the fasteners (112) and (113) from the mounting bracket (114).
     (b) Remove the rigging pins (111) from the guide.
Subtask 28-11-27-420-051-A ** ON A/C NOT FOR ALL
C. Install protective blank flange caps on the ACT
F Blanking Flange Caps of the ACT ** ON A/C NOT FOR ALL
NOTE: The openings of the ACT must be closed when the ACT is removed from the aircraft and the ACT must be put into storage.
   (1) Install the cavity-drain blanking plug on the ACT:
     (a) Apply a thin layer of Mineral Oil base Grease-- Vaseline or Petrolatum - (Material No.03FAB1) on the new AIPC 28-11-04-05-120 O-RING (132)AIPC 28-11-84-05-120 O-RING (132).
     (b) Put the O-ring (132) on the cavity-drain plug (131).
     (c) Put the cavity-drain plug (131) into the opening of the ACT (1).
     (d) Turn the cavity-drain plug (131) 60 deg. counterclockwise to seal the port.
     (e) Make sure that cavity-drain plug (131) is fully engaged.
   (2) Install the protective blank flange caps on the fuel-line and vent-line ends of the ACT:
     (a) Apply a thin layer of Mineral Oil base Grease-- Vaseline or Petrolatum - (Material No.03FAB1) on the new AIPC 28-11-04-05-060 O-RING (123)AIPC 28-11-84-05-060 O-RING (123), AIPC 28-11-04-05-040 O-RING (124)AIPC 28-11-84-05-040 O-RING (124), AIPC 28-11-04-05-040 O-RING (129)AIPC 28-11-84-05-040 O-RING (129), AIPC 28-11-04-05-060 O-RING (133)AIPC 28-11-84-05-060 O-RING (133), AIPC 28-11-04-05-040 O-RING (134)AIPC 28-11-84-05-040 O-RING (134).
     (b) Put the O-rings (123), (124) and the inner blanking flange (130) on the end of the ACT vent-line.
     (c) Install the nuts (125) on the studs (122).
     (d) Torque the nuts (125) opposite to one another to between 0.44 and 0.36 m.daN (38.94 and 31.86 lbf.in ) T.
     (e) Make sure that the pressure relief screw (126) is installed on the inner blanking flange (130).
     (f) Safety the pressure relief screw (126) with 14QFB1Wire-Locking Dia: 0.8 mm CRES Nickel Alloy -.
     (g) Put the O-ring (129) and the outer blanking flange (128) on the inner blanking flange (130).
     (h) Install the nuts (127) on the studs (121).
     (i) Torque the nuts (127) opposite to one another to between 0.44 and 0.36 m.daN (38.94 and 31.86 lbf.in ) T.
     (j) Put the O-rings (133), (134) and the blanking flange (135) on the end of the ACT fuel-line.
     (k) Install the nuts (136) on the studs (137).
     (l) Torque the nuts (136) opposite to one another to between 0.44 and 0.36 m.daN (38.94 and 31.86 lbf.in ) T.
   (3) In the aft cargo-compartment, put the 98D28108563000 COVER, FUEL VENT-ACT on the vent- and fuel pipe ends.
NOTE: This makes sure that no fuel vapor can enter the cargo-compartment.
[Rev.10 from 2021] 2026.04.01 00:01:11 UTC
"Aviabrain" 2025