W DOC AIRBUS | AMM A320F

Installation of the No.3 Flap Track Beam

TASK 57-51-33-400-003-A
Installation of the No.3 Flap Track Beam

WARNING: BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.
WARNING: MAKE SURE THAT THE FLIGHT CONTROL SAFETY-LOCKS AND THE WARNING NOTICES ARE IN POSITION.
WARNING: MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE IN POSITION ON THE LANDING GEAR. THIS WILL PREVENT UNWANTED MOVEMENT OF THE LANDING GEAR, AND THUS POSSIBLE INJURY TO PERSONS AND DAMAGE TO THE AIRCRAFT AND/OR EQUIPMENT.
CAUTION: BE CAREFUL WHEN YOU DO MAINTENANCE TASKS ON THE WING TRAILING EDGE:
  • DO NOT CAUSE DAMAGE TO THE ELECTRICAL CABLE RACEWAYS.
  • DO NOT CAUSE DAMAGE TO THE ELECTRICAL CABLE INSTALLATIONS.
  • MAKE SURE THAT THE ELECTRICAL CABLES ARE INSTALLED CORRECTLY. INCORRECT INSTALLATION CAN CAUSE DAMAGE.
CAUTION: THIS PART IS A REMOVABLE STRUCTURAL COMPONENT (RSC), WHICH CAN BE MOVED BETWEEN AIRCRAFT. THUS IT CAN HAVE DIFFERENT OPERATION CONDITIONS AND A DIFFERENT LIFE RECORD (FLIGHT HOURS/FLIGHT CYCLES/CALENDAR) FROM THE AIRCRAFT IT IS INSTALLED ON OR REMOVED FROM. THE OPERATOR IS RESPONSIBLE FOR THE SPECIFIC TRACKING AND CONTINUED AIRWORTHINESS OF REMOVABLE STRUCTURAL COMPONENTS. INCORRECT MAINTENANCE OF THESE COMPONENTS CAN CAUSE A RISK FOR THE FLIGHT SAFETY.
1. Reason for the Job
Self explanatory
2. Job Set-up Information
 A. Fixtures, Tools, Test and Support Equipment
REFERENCE
QTY
DESIGNATION
No specific
AR
ACCESS PLATFORM 4M (13 FT)
No specific
AR
SAFETY BARRIER(S)
No specific
AR
WARNING NOTICE(S)
No specific
Torque wrench: range to between 0.4 and 0.35 m.daN (35.40 and 30.97 lbf.in ) T
No specific
Torque wrench: range to between 2.40 and 2.26 m.daN (17.70 and 16.67 lbf.ft ) T
No specific
Torque wrench: range to between 4.0 and 3.7 m.daN (29.50 and 27.29 lbf.ft ) T
No specific
Torque wrench: range to between 9.7 and 9.0 m.daN (71.53 and 66.37 lbf.ft ) T
No specific
Torque wrench: range to between 13.0 and 11.9 m.daN (95.87 and 87.76 lbf.ft ) T
98D27803000000
1
LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION
98D57004037000
1
EXTRACTOR FLAP SPIGOT
 B. Consumable Materials
REFERENCE
DESIGNATION
(Material No.06ABA1)
Polysulfide Sealant-Fuel Tank Brushable -
(Material No.06AEA1)
Polysulfide Sealant-Low Adhesion Brushable -
(Material No.06LCG9)
Non Hardening Jointing Putty-Medium Temp. Area - -
(Material No.08BAA9)
Non Aqueous Cleaner-General - -
(Material No.14QFB1)
Wire-Locking Dia: 0.8 mm CRES Nickel Alloy -
(Material No.14SBA1)
Textile-Lint free Cotton -
 C. Expendable Parts
FIG.ITEM
DESIGNATION
IPC-CSN
2
COTTER PIN
AIPC 57-51-05-76-050
16
COTTER PINS
AIPC 57-51-05-76-080
5
COTTER PINS
AIPC 57-51-05-76-080
2
COTTER PIN
AIPC 57-51-09-22-060
16
COTTER PINS
AIPC 57-51-09-22-090
5
COTTER PINS
AIPC 57-51-09-22-090
23
COTTER PIN
AIPC 57-51-33-03-010
27
COTTER PIN
AIPC 57-51-33-03-240
23
COTTER PIN
AIPC 57-51-33-23-010
27
COTTER PIN
AIPC 57-51-33-23-240
2
COTTER PIN
AIPC 57-51-85-76-060
16
COTTER PINS
AIPC 57-51-85-76-090
5
COTTER PINS
AIPC 57-51-85-76-090
2
COTTER PIN
AIPC 57-51-89-22-060
16
COTTER PINS
AIPC 57-51-89-22-090
5
COTTER PINS
AIPC 57-51-89-22-090
 D. Referenced Information
REFERENCE
DESIGNATION
TASK 20-28-00-912-802-A
Electrical Bonding - General Maintenance Procedure
TASK 27-54-46-000-001-A
Removal of the Nos 2, 3 and 4 Flap Carriages
TASK 27-54-46-400-001-A
Installation of the Nos 2, 3 and 4 Flap Carriages
TASK 27-54-49-400-003-A
Installation of the Flap Track 3 Actuator
TASK 57-55-11-000-001-A
Removal of the Flap Track Fairings Nos. 2, 3 and 4
TASK 57-55-11-000-004-A
Removal of the Flap Track Fairings Nos. 2, 3 and 4
TASK 57-55-11-400-001-A
Installation of the Flap Track Fairings Nos. 2, 3 and 4
TASK 57-55-11-400-004-A
Installation of the Flap Track Fairings Nos. 2, 3 and 4
F No.s 3 and 4 Flap Track Beams ** ON A/C NOT FOR ALL
F Nos. 2, 3 and 4 Flap Track Beams ** ON A/C NOT FOR ALL
3. Job Set-up
Subtask 57-51-33-941-056-A
A. Safety Precautions
   (1) Make sure the WARNING NOTICE(S) are in the cockpit to tell persons not to operate the flaps or slats.
   (2) Make sure that the SAFETY BARRIER(S) are in position.
Subtask 57-51-33-860-052-A ** ON A/C NOT FOR ALL
B. Aircraft Maintenance Configuration
WARNING: MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROLS SURFACES ARE CLEAR. MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.
   (1) Make sure that the fairings of the applicable No.3 flap track have been removed (Ref. AMM TASK 57-55-11-000-001).
   (2) Make sure that the carriage has been removed from the applicable No.3 flap track beam (Ref. AMM TASK 27-54-46-000-001).
   (3) Make sure that the 98D27803000000 LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION is installed on the flap/slat control lever.
   (4) Make sure that the ACCESS PLATFORM 4M (13 FT) is in position below the applicable No.3 flap track beam (1), zone 587 (687).
F No.s 3 and 4 Flap Track Beams ** ON A/C NOT FOR ALL
Subtask 57-51-33-860-052-B ** ON A/C NOT FOR ALL
B. Aircraft Maintenance Configuration
WARNING: MAKE SURE THAT THE TRAVEL RANGES OF THE FLIGHT CONTROLS SURFACES ARE CLEAR. MOVEMENT OF FLIGHT CONTROLS CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.
   (1) Make sure that the fairings of the applicable No.3 flap track have been removed (Ref. AMM TASK 57-55-11-000-004).
   (2) Make sure that the carriage has been removed from the applicable No.3 flap track beam (Ref. AMM TASK 27-54-46-000-001).
   (3) Make sure that the 98D27803000000 LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION is installed on the flap/slat control lever.
   (4) Make sure that the ACCESS PLATFORM 4M (13 FT) is in position below the applicable No.3 flap track beam (1), zone 587 (687).
F Nos. 2, 3 and 4 Flap Track Beams ** ON A/C NOT FOR ALL
Subtask 57-51-33-865-056-A
C. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:
PANELDESIGNATIONFINLOCATION
** ON A/C NOT FOR ALL
49VUFLIGHT CONTROLS/FLP/CTL AND MONG/SYS16CVB07
** ON A/C NOT FOR ALL
49VUFLIGHT CONTROLS/FLP/CTL AND MONG/SYS16CVB02
** ON A/C ALL
121VUFLIGHT CONTROLS/FLP/CTL AND/MONG/SYS28CVQ21
4. Procedure
CAUTION: BE CAREFUL WHEN YOU DO MAINTENANCE TASKS ON THE WING TRAILING EDGE:
  • DO NOT CAUSE DAMAGE TO THE ELECTRICAL CABLE RACEWAYS.
  • DO NOT CAUSE DAMAGE TO THE ELECTRICAL CABLE INSTALLATIONS.
  • MAKE SURE THAT THE ELECTRICAL CABLES ARE INSTALLED CORRECTLY. INCORRECT INSTALLATION CAN CAUSE DAMAGE.
Subtask 57-51-33-560-051-B ** ON A/C NOT FOR ALL
A. Preparation of a Replacement Component
F No.s 3 and 4 Flap Track Beams ** ON A/C NOT FOR ALL
   (1) Make sure that the parts retained from the removed component are clean and in the correct condition.
   (2) Apply a layer of Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) to the shims (12).
   (3) Put all the shims (12) and the bearing pads (11) in position.
   (4) Install the bolts (9) and the nuts (13).
   (5) Install the studs (8), the washers (14) and the nuts (15).
   (6) TORQUE the nuts (15) to between 2.4 and 2.26 m.daN (17.70 and 16.67 lbf.ft ) T.
   (7) Install the new AIPC 57-51-05-76-080 COTTER PINS (16) or AIPC 57-51-85-76-090 COTTER PINS (16).
Subtask 57-51-33-560-051-C ** ON A/C NOT FOR ALL
A. Preparation of a Replacement Component
F Nos. 2, 3 and 4 Flap Track Beams ** ON A/C NOT FOR ALL
   (1) Make sure that the parts retained from the removed component are clean and in the correct condition.
   (2) Apply a layer of Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) to the shims (12).
   (3) Put the set of shims (12) and the bearing pads (11) in the positions that they were removed from (do one side at a time).
   (4) Install the bolts (9) and the nuts (13).
   (5) Install the studs (8), the washers (14) and the nuts (15).
   (6) TORQUE the nuts (15) to between 2.4 and 2.26 m.daN (17.70 and 16.67 lbf.ft ) T.
   (7) Install the new AIPC 57-51-09-22-090 COTTER PINS (16) or AIPC 57-51-89-22-090 COTTER PINS (16).
Subtask 57-51-33-420-069-A
B. Preparation for Installation
   (1) Clean the component interfaces and the adjacent areas with a Textile-Lint free Cotton - (Material No.14SBA1) made moist with Non Aqueous Cleaner-General - - (Material No.08BAA9) .
   (2) Do an inspection of the component interfaces and the adjacent area.
   (3) Make sure that the parts retained from the removed component are clean and in the correct condition.
Subtask 57-51-33-420-056-C ** ON A/C NOT FOR ALL
WARNING: SUPPORT THE UNIT/ASSEMBLY. THE UNIT/ASSEMBLY IS HEAVY. IF YOU DO NOT SUPPORT IT, IT WILL FALL. THIS CAN CAUSE INJURY TO PERSONS, AND/OR DAMAGE TO EQUIPMENT.
C. Installation of the Flap Track Beam
NOTE: The weight of the flap track beam (1) is 36 kg (79.4 lb).
F No.s 3 and 4 Flap Track Beams ** ON A/C NOT FOR ALL
   (1) Lift and hold the flap track beam (1).
NOTE: Steps 2,3 and 4 must be completed carefully and as one continuous procedure. Unsatisfactory work will result in damage to the spigot chrome protection and/or the top flange of the beam. in the recess in the wing.
   (2) Lift the rear end of the flap track beam (1). Engage the failsafe spigot (10) through the bush in the bottom skin plate.
   (3) At the rear mounting:
     (a) Apply Non Hardening Jointing Putty-Medium Temp. Area - - (Material No.06LCG9) to the aft spigot pin (17), but not to the thread.
     (b) Install the spherical washer (4).
     (c) Fill the space between the spherical washer (4) and the aft spigot pin (17), as shown, with Non Hardening Jointing Putty-Medium Temp. Area - - (Material No.06LCG9) .
     (d) Loosely assemble the nut (3) on the aft spigot pin (17).
   (4) At the forward mounting:
     (a) Apply a thin layer of Non Hardening Jointing Putty-Medium Temp. Area - - (Material No.06LCG9) to the forward spigot pin (24).
     (b) Use the 98D57004037000 EXTRACTOR FLAP SPIGOT to install the forward spigot pin (24):
  • through the spherical bearing (19)
  • into the flap track beam (1).
     (c) Apply a thin layer of Non Hardening Jointing Putty-Medium Temp. Area - - (Material No.06LCG9) to the bolt (20).
     (d) Align the hole in the forward spigot pin (24) and install the bolt (20), the washer (29) and the nut (28).
     (e) TORQUE the nut (28) to between 0.4 and 0.35 m.daN (35.40 and 30.97 lbf.in ) T.
     (f) Install the new AIPC 57-51-33-03-240 COTTER PIN (27).
   (5) At the rear mounting:
     (a) TORQUE the nut (3) to between 9.7 and 9.0 m.daN (71.53 and 66.37 lbf.ft ) T.
     (b) If the flap track beam has a new aft spigot pin (17) installed:
  • drill a 3.25 mm (0.1280 in.) hole in the aft spigot pin (17) for the cotter pin (2).
     (c) Install the new AIPC 57-51-05-76-050 COTTER PIN (2) or AIPC 57-51-85-76-060 COTTER PIN (2).
   (6) At the forward mounting:
     (a) Apply a thin layer of Polysulfide Sealant-Low Adhesion Brushable - (Material No.06AEA1) to the failsafe pin (26) and the anti-chafe collar (21).
     (b) Install the failsafe pin (26), the anti-chafe collar (21), the pin (18), the collar (22) and the new AIPC 57-51-33-03-010 COTTER PIN (23).
     (c) Install the bonding strap (30) with the bolt (31) and the nut (25) (Ref. AMM TASK 20-28-00-912-802).
   (7) At the rear mounting:
     (a) Install the flanged nuts (7) on the studs (8).
     (b) Adjust the flanged nuts (7) until the dimension Z is between 0.7 mm (0.0276 in.) to 0.8 mm (0.0315 in.).
     (c) Hold the flanged nuts (7) and install the nuts (6).
     (d) TORQUE the nuts (6) to between 2.40 and 2.26 m.daN (17.70 and 16.67 lbf.ft ) T.
     (e) Install the new AIPC 57-51-05-76-080 COTTER PINS (5) or AIPC 57-51-85-76-090 COTTER PINS (5) then safety the nuts (6) and (7) with 14QFB1Wire-Locking Dia: 0.8 mm CRES Nickel Alloy -.
   (8) Remove the support from the flap track beam (1).
   (9) Measure the dimension Z again.
Subtask 57-51-33-420-056-D ** ON A/C NOT FOR ALL
WARNING: SUPPORT THE UNIT/ASSEMBLY. THE UNIT/ASSEMBLY IS HEAVY. IF YOU DO NOT SUPPORT IT, IT WILL FALL. THIS CAN CAUSE INJURY TO PERSONS, AND/OR DAMAGE TO EQUIPMENT.
C. Installation of the Flap Track Beam
NOTE: The weight of the flap track beam (1) is 57 kg (125.7 lb).
F Nos. 2, 3 and 4 Flap Track Beams ** ON A/C NOT FOR ALL
   (1) Lift and hold the flap track beam (1).
NOTE: Steps 2,3 and 4 must be completed carefully and as one continuous procedure. Unsatisfactory work will result in damage to the spigot chrome protection and/or the top flange of the beam. in the recess in the wing.
   (2) Lift the rear end of the flap track beam (1). Engage the failsafe spigot (10) through the bush in the bottom skin plate.
   (3) At the rear mounting:
     (a) Apply Non Hardening Jointing Putty-Medium Temp. Area - - (Material No.06LCG9) to the aft spigot pin (17), but not to the thread.
     (b) Install the spherical washer (4).
     (c) Fill the space between the spherical washer (4) and the aft spigot pin (17), as shown, with Non Hardening Jointing Putty-Medium Temp. Area - - (Material No.06LCG9) .
     (d) Loosely assemble the nut (3) on the aft spigot pin (17).
   (4) At the forward mounting:
     (a) Apply a thin layer of Non Hardening Jointing Putty-Medium Temp. Area - - (Material No.06LCG9) to the forward spigot pin (24).
     (b) Use the 98D57004037000 EXTRACTOR FLAP SPIGOT to install the forward spigot pin (24):
  • through the spherical bearing (19)
  • into the flap track beam (1).
     (c) Apply a thin layer of Non Hardening Jointing Putty-Medium Temp. Area - - (Material No.06LCG9) to the bolt (20).
     (d) Align the hole in the forward spigot pin (24) and install the bolt (20), the washer (29) and the nut (28).
     (e) TORQUE the nut (28) to between 0.4 and 0.35 m.daN (35.40 and 30.97 lbf.in ) T.
     (f) Install the new AIPC 57-51-33-23-240 COTTER PIN (27).
   (5) At the rear mounting:
     (a) TORQUE the nut (3) to between 13.0 and 11.9 m.daN (95.87 and 87.76 lbf.ft ) T.
     (b) If the flap track beam has a new aft spigot pin (17) installed:
  • drill a 3.25 mm (0.1280 in.) hole in the aft spigot pin (17) for the cotter pin (2).
     (c) Install the new AIPC 57-51-09-22-060 COTTER PIN (2) or AIPC 57-51-89-22-060 COTTER PIN (2).
   (6) At the forward mounting:
     (a) Apply a thin layer of Polysulfide Sealant-Low Adhesion Brushable - (Material No.06AEA1) to the failsafe pin (26) and the anti-chafe collar (21).
     (b) Install the failsafe pin (26), the anti-chafe collar (21), the pin (18), the collar (22) and the new AIPC 57-51-33-23-010 COTTER PIN (23).
     (c) Install the bonding strap (30) with the bolt (31) and the nut (25) (Ref. AMM TASK 20-28-00-912-802).
   (7) At the rear mounting:
     (a) Install the flanged nuts (7) on the studs (8).
     (b) Adjust the flanged nuts (7) until the dimension Z is between 0.7 mm (0.0276 in.) to 0.8 mm (0.0315 in.).
     (c) Hold the flanged nuts (7) and install the nuts (6).
     (d) TORQUE the nuts (6) to between 4.0 and 3.7 m.daN (29.50 and 27.29 lbf.ft ) T.
     (e) Install the new AIPC 57-51-09-22-090 COTTER PINS (5) or AIPC 57-51-89-22-090 COTTER PINS (5) then safety the nuts (6) and (7) with 14QFB1Wire-Locking Dia: 0.8 mm CRES Nickel Alloy -.
   (8) Remove the support from the flap track beam (1).
   (9) Measure the dimension Z again.
5. Close-up
Subtask 57-51-33-410-052-A ** ON A/C NOT FOR ALL
A. Close Access
   (1) If necessary, install the No.3 flap track actuator (Ref. AMM TASK 27-54-49-400-003).
   (2) Install the carriage on the applicable No.3 flap track beam (Ref. AMM TASK 27-54-46-400-001).
   (3) Install the fairings of the No.3 flap track (Ref. AMM TASK 57-55-11-400-001).
Subtask 57-51-33-410-052-B ** ON A/C NOT FOR ALL
A. Close Access
   (1) If necessary, install the No.3 flap track actuator (Ref. AMM TASK 27-54-49-400-003).
   (2) Install the carriage on the applicable No.3 flap track beam (Ref. AMM TASK 27-54-46-400-001).
   (3) Install the fairings of the No.3 flap track (Ref. AMM TASK 57-55-11-400-004).
Subtask 57-51-33-942-052-A
B. Removal of Equipment
   (1) Make sure that the work area is clean and clear of tools and other items.
   (2) Remove the 98D27803000000 LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION from the flap/slat control lever.
   (3) Remove the WARNING NOTICE(S).
   (4) Remove the access platform(s).
   (5) Remove the safety barriers.
   (6) Remove the ground support and maintenance equipment, the special and standard tools and all other items.
[Rev.10 from 2021] 2026.04.02 06:31:13 UTC
"WTRUIB" 2025