W DOC AIRBUS | AMM A320F

Detailed Dimensional Check - Free Movement at the Trailing Edge of the Flaps

TASK 27-54-00-200-003-A
Detailed Dimensional Check - Free Movement at the Trailing Edge of the Flaps

WARNING: PUT THE SAFETY DEVICES AND THE WARNING NOTICES IN POSITION BEFORE YOU START A TASK ON OR NEAR:
  • THE FLIGHT CONTROLS
  • THE FLIGHT CONTROL SURFACES
  • THE LANDING GEAR AND THE RELATED DOORS
  • COMPONENTS THAT MOVE.
MOVEMENT OF COMPONENTS CAN KILL OR CAUSE INJURY TO PERSONS AND/OR CAN CAUSE DAMAGE TO THE EQUIPMENT.
1. Reason for the Job
To check for flap backlash
2. Job Set-up Information
 A. Fixtures, Tools, Test and Support Equipment
REFERENCE
QTY
DESIGNATION
No specific
AR
ACCESS PLATFORM 3M (10 FT)
No specific
2
PIN DIA 10 MM (0.394 IN),LENGTH 100 MM (3.937 IN.) ALU
No specific
1
PIN DIA 13 MM (0.512 IN),LENGTH 100 MM (3.937 IN.) ALU
No specific
1
PIN DIA 19 MM (0.748 IN),LENGTH 100 MM (3.937 IN.) ALU
No specific
2
PIN DIA 20 MM (0.787 IN),LENGTH 100 MM (3.937 IN.) ALU
No specific
1
PIN DIA 3 MM (0.118 IN), LENGTH 100 MM (3.937 IN.) ALU
No specific
1
PIN DIA 5 MM (0.197 IN), LENGTH 100 MM (3.937 IN.) ALU
No specific
AR
SAFETY BARRIER(S)
No specific
AR
TAPE - ADHESIVE
No specific
AR
WARNING NOTICE(S)
No specific
Torque wrench: range to between 0.17 and 0.15 m.daN (15.04 and 13.27 lbf.in ) T
No specific
Torque wrench: range to between 0.45 and 0.4 m.daN (39.82 and 35.40 lbf.in ) T
No specific
Torque wrench: range to between 1.4 and 0.8 m.daN (123.89 and 70.80 lbf.in ) T
No specific
Torque wrench: range to between 1 and 0.9 m.daN (88.50 and 79.65 lbf.in ) T
No specific
Torque wrench: range to between 1.8 and 1.2 m.daN (159.29 and 106.19 lbf.in ) T
No specific
Torque wrench: range to between 2.7 and 1.4 m.daN (19.91 and 10.32 lbf.ft ) T
No specific
Torque wrench: range to between 1.8 and 1.6 m.daN (13.27 and 11.80 lbf.ft ) T
No specific
Torque wrench: range to between 2.2 and 1.8 m.daN (16.22 and 13.27 lbf.ft ) T
No specific
Torque wrench: range to between 2.3 and 1.8 m.daN (16.96 and 13.27 lbf.ft ) T
No specific
Torque wrench: range to between 2.2 and 1.95 m.daN (16.22 and 14.38 lbf.ft ) T
No specific
Torque wrench: range to between 2.4 and 2.2 m.daN (17.70 and 16.22 lbf.ft ) T
No specific
Torque wrench: range to between 3.3 and 2.5 m.daN (24.34 and 18.44 lbf.ft ) T
No specific
Torque wrench: range to between 3.6 and 3.1 m.daN (26.55 and 22.86 lbf.ft ) T
No specific
Torque wrench: range to between 6.0 and 5.5 m.daN (44.25 and 40.56 lbf.ft ) T
No specific
Torque wrench: range to between 7.6 and 6.6 m.daN (56.05 and 48.67 lbf.ft ) T
No specific
Torque wrench: range to between 12.0 and 10.0 m.daN (88.50 and 73.75 lbf.ft ) T
98D27504114000
1
DISTANCE GAUGE
98D27504115000
1
GAUGES-DISTANCE
 B. Expendable Parts
FIG.ITEM
DESIGNATION
IPC-CSN
146
COTTER PIN
AIPC 27-54-05-31-030
415
COTTER PIN
AIPC 27-54-05-31-090
405
COTTER PIN
AIPC 27-54-05-31-130
25
COTTER PIN
AIPC 27-54-05-32-040
26
COTTER PIN
AIPC 27-54-05-32-090
35
COTTER PIN
AIPC 27-54-05-32-140
34
COTTER PIN
AIPC 27-54-05-32-190
187
COTTER PIN
AIPC 27-54-05-33-025
15
COTTER PIN
AIPC 27-54-05-33-030
176
COTTER PIN
AIPC 27-54-05-33-035
1
COTTER PIN
AIPC 27-54-05-33-100
6
COTTER PIN
AIPC 27-54-05-33-150
10
COTTER PIN
AIPC 27-54-05-33-200
25
COTTER PIN
AIPC 27-54-05-35-080
416
COTTER PIN
AIPC 27-54-05-35-080
215
COTTER PIN
AIPC 27-54-05-35-130
26
COTTER PIN
AIPC 27-54-05-35-130
44
COTTER PIN
AIPC 27-54-46-22-095
80
COTTER PIN
AIPC 27-54-46-24-095
101
COTTER PIN
AIPC 27-54-46-26-280
1
COTTER PIN
AIPC 27-54-85-32-010
6
COTTER PIN
AIPC 27-54-85-32-050
15
COTTER PIN
AIPC 27-54-85-32-110
10
COTTER PIN
AIPC 27-54-85-32-150
25
COTTER PIN
AIPC 27-54-85-33-110
146
COTTER PIN
AIPC 27-54-85-34-110
415
COTTER PIN
AIPC 27-54-85-34-110
405
COTTER PIN
AIPC 27-54-85-34-220
35
COTTER PIN
AIPC 27-54-85-35-020
25
COTTER PIN
AIPC 27-54-85-35-110
34
COTTER PIN
AIPC 27-54-85-35-210
26
COTTER PIN
AIPC 27-54-85-35-220
30
COTTER PIN
AIPC 57-51-05-89-010
1
COTTER PIN
AIPC 57-52-23-03-270
6
COTTER PIN
AIPC 57-52-23-03-328
 C. Referenced Information
REFERENCE
DESIGNATION
TASK 27-50-00-866-008-A
Extension of the Flaps on the Ground
TASK 27-50-00-866-008-A-01
Extension of the Flaps/Slats on the Ground
TASK 27-50-00-866-009-A
Retraction of the Flaps on the Ground
TASK 27-50-00-866-009-A-01
Retraction of the Flaps/Slats on the Ground
TASK 27-50-00-866-011-A
Manual Extension of the Flaps
TASK 27-50-00-866-012-A
Manual Retraction of the Flaps
TASK 27-51-44-400-001-A
Installation of the Interconnecting Strut
TASK 27-54-46-000-001-A
Removal of the Nos 2, 3 and 4 Flap Carriages
TASK 27-54-46-000-002-A
Removal of Flap Carriage 1
TASK 27-54-46-400-001-A
Installation of the Nos 2, 3 and 4 Flap Carriages
TASK 27-54-46-400-002-A
Installation of Flap Carriage 1
TASK 27-54-49-000-001-A
Removal of the Flap Track 1 Actuator
TASK 27-54-49-000-002-A
Removal of the Flap Track 2 Actuator
TASK 27-54-49-000-003-A
Removal of the Flap Track 3 Actuator
TASK 27-54-49-000-004-A
Removal of the Flap Track 4 Actuator
TASK 27-54-49-400-001-A
Installation of the Flap Track 1 Actuator
TASK 27-54-49-400-002-A
Installation of the Flap Track 2 Actuator
TASK 27-54-49-400-003-A
Installation of the Flap Track 3 Actuator
TASK 27-54-49-400-004-A
Installation of the Flap Track 4 Actuator
TASK 27-54-55-000-001-A
Removal of the Flap-Actuator Lever Assembly - Tracks 1 and 2
TASK 27-54-55-000-002-A
Removal of the Flap-Actuator Lever Assembly - Track 3
TASK 27-54-55-000-003-A
Removal of the Flap-Actuator Lever Assembly - Track 4
TASK 27-54-55-400-001-A
Installation of the Flap-Actuator Lever Assembly - Tracks 1 and 2
TASK 27-54-55-400-002-A
Installation of the Flap-Actuator Lever Assembly - Track 3
TASK 27-54-55-400-003-A
Installation of the Flap-Actuator Lever Assembly - Track 4
TASK 27-54-61-000-001-A
Removal of the Inboard Flap
TASK 27-54-61-000-002-A
Removal of the Flap Kink-Seals and Cushion-Seals
TASK 27-54-61-000-003-A
Removal of the Inboard Double-Slotted Flap
TASK 27-54-61-220-001-A
Dimensional Check of the Joints that Connect the Flap Actuator Levers to the Flap Drive Struts (Tracks 1 and 2)
TASK 27-54-61-400-001-A
Installation of the Inboard Flap
TASK 27-54-61-400-003-A
Installation of the Inboard Double-Slotted Flap
TASK 27-54-61-400-006-A
Installation of the Flap Kink-Seals and Cushion-Seals
TASK 27-54-62-000-001-A
Removal of the Outboard Flap
TASK 27-54-62-000-002-A
Removal of the Outboard Double-Slotted Flap
TASK 27-54-62-220-001-A
Dimensional Check of the Joints that connect the Flap Actuator Levers to the Flap Drive Struts (Tracks 3 and 4)
TASK 27-54-62-400-001-A
Installation of the Outboard Flap
TASK 27-54-62-400-002-A
Installation of the Outboard Double-Slotted Flap
TASK 53-35-11-000-001-A
Removal of the Wing-to-Fuselage Fairings
TASK 57-51-33-000-001-A
Removal of the No.1 Flap Track Beam
TASK 57-51-33-400-001-A
Installation of the No.1 Flap Track Beam
TASK 57-52-00-220-015-A
Detailed Dimensional Check of the Joints that Attach the Flap to the Flap Carriage (Tracks 1 and 2)
TASK 57-53-00-220-023-A
Detailed Dimensional Check of the Joints that Attach the Flap to the Flap Carriage (Tracks 3 and 4)
SRM 57513301
 (for corrective action)
F Details of the Z-Coupling ** ON A/C NOT FOR ALL
F Details of the Hinge 1A Operating Mechanism ** ON A/C NOT FOR ALL
F Details of the Tab Drive Control-Rod (Track 2) ** ON A/C NOT FOR ALL
F Distance Gauges - Location and Detail ** ON A/C NOT FOR ALL
F Details of the Tab Drive Control-Rod (Track 3) ** ON A/C NOT FOR ALL
F Details of the Tab Drive Control-Rod (Track 4) ** ON A/C NOT FOR ALL
F Distance Gauges - Location and Detail ** ON A/C NOT FOR ALL
F Flap to Rotary Actuator Drive Lever - To Disconnect the Inboard Flap ** ON A/C NOT FOR ALL
F Rotary Actuator Drive-Lever - To Measure The Free Play (Track 1) ** ON A/C NOT FOR ALL
F Rotary Actuator Drive-Lever - To Measure the Free Play (Track 2) ** ON A/C NOT FOR ALL
F Flaps Trailing Edge Free Movement - Location and Details of Measurement Positions
F Flap to Rotary Actuator Drive Lever - To Disconnect the Inboard Flap ** ON A/C NOT FOR ALL
F Rotary Actuator Drive-Lever - To Measure The Free Play (Track 1) ** ON A/C NOT FOR ALL
F Rotary Actuator Drive-Lever - To Measure the Free Play (Track 2) ** ON A/C NOT FOR ALL
F Flap to Rotary Actuator Drive Lever - To Disconnect the Inboard Flap ** ON A/C NOT FOR ALL
F Rotary Actuator Drive-Lever - To Measure The Free Play (Track 1) ** ON A/C NOT FOR ALL
F Rotary Actuator Drive-Lever - To Measure the Free Play (Track 2) ** ON A/C NOT FOR ALL
F Flap to Rotary Actuator Drive Lever - To Disconnect the Outboard Flap ** ON A/C NOT FOR ALL
F Rotary Actuator Drive-Lever - To Measure the Free Play (Track 3) ** ON A/C NOT FOR ALL
F Rotary Actuator Drive-Lever - To Measure the Free Play (Track 4) ** ON A/C NOT FOR ALL
F Flap to Rotary Actuator Drive Lever - To Disconnect the Outboard Flap ** ON A/C NOT FOR ALL
F Rotary Actuator Drive-Lever - To Measure the Free Play (Track 3) ** ON A/C NOT FOR ALL
F Rotary Actuator Drive-Lever - To Measure the Free Play (Track 4) ** ON A/C NOT FOR ALL
F Flap to Rotary Actuator Drive Lever - To Disconnect the Outboard Flap ** ON A/C NOT FOR ALL
F Rotary Actuator Drive-Lever - To Measure the Free Play (Track 3) ** ON A/C NOT FOR ALL
F Rotary Actuator Drive-Lever - To Measure the Free Play (Track 4) ** ON A/C NOT FOR ALL
F Flaps Trailing Edge - Flow Chart to do the Free Movement Checks
3. Job Set-up
Subtask 27-54-00-941-059-A
A. Safety Precautions
   (1) As necessary, use the applicable SAFETY BARRIERS, specified by the operator's instructions and your local regulations.
   (2) Put the WARNING NOTICE(S) in position to tell persons not to pressurize the hydraulic systems.
   (3) Put a WARNING NOTICE(S) in position to tell persons not to operate the flight controls.
   (4) Put the ACCESS PLATFORM 3M (10 FT) in position below the applicable flap.
Subtask 27-54-00-860-062-A ** ON A/C NOT FOR ALL
B. Aircraft Maintenance Configuration
   (1) Extend the flaps to position 1 (Ref. AMM TASK 27-50-00-866-008).
   (2) Remove the flap kink-seals (Ref. AMM TASK 27-54-61-000-002).
   (3) Remove the applicable wing to fuselage panels (Ref. AMM TASK 53-35-11-000-001):
  • for the LH flap, remove 193AB
  • for the RH flap, remove 194AB.
   (4) Fully retract the flaps (Ref. AMM TASK 27-50-00-866-009).
Subtask 27-54-00-860-062-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) Extend the flaps to position 1 (Ref. AMM TASK 27-50-00-866-008).
   (2) Remove the flap kink-seals (Ref. AMM TASK 27-54-61-000-002).
   (3) Disconnect the Z-Coupling:
F Details of the Z-Coupling ** ON A/C NOT FOR ALL
     (a) Remove and discard the cotter pin (1).
     (b) Remove the nut (2) and the washer (3).
     (c) Remove and discard the cotter pin (6).
     (d) Remove the nut (7), the washer (8) and the spacer(s) (9).
     (e) Retract the flaps fully (Ref. AMM TASK 27-50-00-866-009).
     (f) Remove the bolt (10).
     (g) Remove the lever (4) and the remaining spacer(s) (9).
NOTE: Record the position of the remaining spacer(s) (9) when you remove them. This is to make sure the spacers are installed in the same position.
     (h) Temporarily install the spacer(s) (9), the washer (8) and the nut (7) on the lever (4).
     (i) Temporarily install the lever (4) on the attachment bracket (11) with the bolt (10), the washer (3) and the nut (2).
     (j) Turn the lever (4) forward as far as possible and hold it in this position with TAPE - ADHESIVE.
     (k) Turn the lever (5) forward as far as possible and hold it in this position with adhesive tape.
   (4) Remove the applicable wing to fuselage panels (Ref. AMM TASK 53-35-11-000-001):
  • for the LH flap, remove 193AB
  • for the RH flap, remove 194AB.
   (5) Extend the flaps fully (Ref. AMM TASK 27-50-00-866-008).
   (6) For the inboard flap:
     (a) Disconnect the upper tab-drive control-rod (22) from the shroud box assembly attachment-bracket (26).
F Details of the Hinge 1A Operating Mechanism ** ON A/C NOT FOR ALL
       1 Remove and discard the cotter pin (30).
       2 Remove the nut (29), the washer (28) and the bolt (27).
       3 Hold the tab drive control-rod (22) to the flap with adhesive tape.
     (b) Disconnect the tab drive control-rod (46) from the track 2 carriage (41).
F Details of the Tab Drive Control-Rod (Track 2) ** ON A/C NOT FOR ALL
       1 Remove and discard the cotter pin (44).
       2 Remove the nut (45), the washer (43), the bolt (47) and the loose bush (42).
     (c) Install the distance gages:
F Distance Gauges - Location and Detail ** ON A/C NOT FOR ALL
CAUTION: MAKE SURE THAT THE DISCONNECTED PARTS DO NOT TOUCH AND/OR CATCH THE ADJACENT STRUCTURE WHEN YOU MOVE THE FLAP. THIS WILL PREVENT DAMAGE TO THE WING.
       1 Manually push the tab forward and install the 98D27504114000 DISTANCE GAUGE (60) and (64).
         a At the hinge 1A position, put the distance gage (60) in position:
  • install the rear pin (61)
  • install the forward pin (58) and lock it with the knurled screw (59).
         b At the track 2 position, put the distance gage (64) in position:
  • install the forward pin (62) and lock it with the knurled screw (63)
  • install the rear pin (65) and lock it with the knurled screw (66).
   (7) For the outboard flap:
     (a) Disconnect the tab drive control-rod (82) from the track 3 carriage (77).
F Details of the Tab Drive Control-Rod (Track 3) ** ON A/C NOT FOR ALL
       1 Remove and discard the cotter pin (80).
       2 Remove the nut (81), the washer (79), the bolt (83) and the loose bush (78).
     (b) Disconnect the tab drive control-rod (97) from the track 4 carriage (94).
F Details of the Tab Drive Control-Rod (Track 4) ** ON A/C NOT FOR ALL
       1 Remove and discard the cotter pin (101).
       2 Remove the nut (100), the washer (99) and the loose bush (98).
       3 Remove the hinge pin (96) sufficiently to let you remove the tab drive control-rod (97). Do not fully remove the hinge pin (96).
NOTE: If you fully remove the hinge pin (96) from the carriage (94), the roller bearing block (95) will fall out of alignment.
       4 Fully install the hinge pin (96) and temporarily install the nut (100).
     (c) Install the distance gages:
F Distance Gauges - Location and Detail ** ON A/C NOT FOR ALL
CAUTION: MAKE SURE THAT THE DISCONNECTED PARTS DO NOT TOUCH AND/OR CATCH THE ADJACENT STRUCTURE WHEN YOU MOVE THE FLAP. THIS WILL PREVENT DAMAGE TO THE WING.
       1 Manually push the tab forward and install the 98D27504115000 GAUGES-DISTANCE (112) and (115) at the track 3 and the track 4 positions.
       2 At the track 3 position, put the distance gage (112) in position and install the pins (113) and (114).
       3 At the track 4 position, put the distance gage (115) in position and install the pin (116).
   (8) Fully retract the flaps (Ref. AMM TASK 27-50-00-866-009).
4. Procedure
Subtask 27-54-00-220-050-B ** ON A/C NOT FOR ALL
A. Detailed Dimensional Check - Free Movement at the Trailing Edge of the Inboard Flap
F Flap to Rotary Actuator Drive Lever - To Disconnect the Inboard Flap ** ON A/C NOT FOR ALL
F Rotary Actuator Drive-Lever - To Measure The Free Play (Track 1) ** ON A/C NOT FOR ALL
F Rotary Actuator Drive-Lever - To Measure the Free Play (Track 2) ** ON A/C NOT FOR ALL
F Flaps Trailing Edge Free Movement - Location and Details of Measurement Positions ** ON A/C NOT FOR ALL
   (1) At the track 1 position, disconnect the flap drive-arm from the rotary actuator lever-arm:
     (a) Remove and discard the cotter pin (146).
     (b) Remove the nut (145) and the washer (144).
     (c) Remove the bolt (141) and install the PIN DIA 13 MM (0.512 IN),LENGTH 100 MM (3.937 IN.) ALU.
NOTE: The diameter of the aluminium pin is approximately 6.0 mm (0.2362 in.) less than the bolt (141) it replaces. The pin is 100 mm (3.9370 in.) long and is made locally from material LN 1798 3.1354T3511. The pin temporary and has two functions:
  • it keeps the joint together when you extend/retract the flaps
  • it is easy to remove the pin to disconnect the joint when the flaps are extended.
     (d) Extend the flaps fully (Ref. AMM TASK 27-50-00-866-008).
     (e) Remove the aluminium pin.
   (2) At the track 2 position, measure the total free movement of the flap trailing edge:
     (a) Make sure that the flaps are fully extended, and that the travel ranges are clear.
     (b) Apply a down force (by hand) to the trailing edge of the flap. Apply sufficient force to make the flap move through possible free movement in the flap system mechanism and joints.
NOTE: Do not apply too much force to cause the system components, mechanism or the aircraft fixed structure to move or bend.
     (c) Hold the flap in this position, then measure and record the dimension Z.
     (d) Apply an up force (by hand) to the trailing edge of the flap. Apply sufficient force to make the flap move through possible free movement in the flap system mechanism and joints.
NOTE: Do not apply too much force to cause the system components, mechanism or the aircraft fixed structure to move or bend.
     (e) Hold the flap in this position, measure and record the dimension Y and then release the flap.
     (f) To find the total free movement, subtract the dimension Z from the dimension Y.
   (3) At the track 1 position, measure the total free movement of the actuator lever (dimension X):
     (a) Apply a down force (by hand) to the actuator lever. Apply sufficient force to make the actuator lever move through possible free movement in the flap system mechanism and joints.
     (b) Hold the actuator lever in this position, then measure and record the dimension T.
     (c) Apply an up force (by hand) to the actuator lever. Apply sufficient force to make the actuator lever move through possible free movement in the flap system mechanism and joints.
     (d) Hold the actuator lever in this position, then measure and record the dimension S.
     (e) To find the total free movement (dimension X), subtract dimension S from dimension T.
   (4) Install the aluminium pin through the joint where you removed the bolt (141).
   (5) Retract the flaps fully (Ref. AMM TASK 27-50-00-866-009).
   (6) Remove the aluminium pin.
   (7) At the track 1 position, temporarily connect the flap drive arm to the rotary actuator drive-lever as follows:
     (a) Install the bolt (141), the washer (144) and the nut (145).
     (b) Hand tighten the nut (145).
   (8) At the track 2 position, disconnect the flap drive arm from the rotary actuator drive-lever:
     (a) For the attachment with one bolt only:
       1 Remove and discard the cotter pin (146).
       2 Remove the nut (145) and the washer (144).
       3 Remove the bolt (141) and install the PIN DIA 20 MM (0.787 IN),LENGTH 100 MM (3.937 IN.) ALU.
     (b) For the attachment with one bolt which is safetied with the locking plate:
       1 Remove and discard the cotter pins (405) and (415).
       2 Remove the nuts (404) and (414) and the washers (403) and (413).
       3 Remove the bolts (401) and (411) and install the PIN DIA 20 MM (0.787 IN),LENGTH 100 MM (3.937 IN.) ALU.
     (c) Extend the flaps fully (Ref. AMM TASK 27-50-00-866-008).
     (d) Remove the aluminium pin.
   (9) At the inboard edge of the flap, measure the total free movement of the flap trailing edge:
     (a) Make sure that the flaps are fully extended, and that the travel ranges are clear.
     (b) Apply a down force (by hand) to the trailing edge of the flap. Apply sufficient force to make the flap move through possible free movement in the flap system mechanism and joints.
NOTE: Do not apply too much force to cause the system components, mechanism or the aircraft fixed structure to move or bend.
     (c) Hold the flap in this position, then measure and record the dimension Z.
     (d) Apply an up force (by hand) to the trailing edge of the flap. Apply sufficient force to make the flap move through possible free movement in the flap system mechanism and joints.
NOTE: Do not apply too much force to cause the system components, mechanism or the aircraft fixed structure to move or bend.
     (e) Hold the flap in position, measure and record the dimension Y and then release the flap.
     (f) To find the total free movement, subtract the dimension Z from the dimension Y.
   (10) At the track 2 position, measure the total free movement of the actuator lever (dimension X):
     (a) Apply a down force (by hand) to the actuator lever. Apply sufficient force to make the actuator lever move through possible free movement in the flap system mechanism and joints.
     (b) Hold the actuator lever in this position, then measure and record the dimension T.
     (c) Apply an up force (by hand) to the actuator lever. Apply sufficient force to make the actuator lever move through possible free movement in the flap system mechanism and joints.
     (d) Hold the actuator lever in this position, then measure and record the dimension S.
     (e) To find the total free movement (dimension X), subtract dimension S from dimension T.
   (11) Install the aluminium pin through the joint where you removed the bolt (128).
   (12) Retract the flaps fully (Ref. AMM TASK 27-50-00-866-009).
   (13) Remove the aluminium pin.
   (14) At the track 2 position, temporarily connect the flap drive arm to the rotary actuator drive-lever as follows:
     (a) For the attachment with one bolt only:
       1 Install the bolt (141), the washer (144) and the nut (145).
       2 Hand tighten the nut (141).
     (b) For the attachment with one bolt which is safetied with the locking plate:
       1 Install the bolt (401), the washer (403) and the nut (404).
       2 Hand tighten the nut (404).
       3 Install the locking plate (402), the bolt (411), washer (413) and the nut (414).
       4 Hand tighten the nut (414).
   (15) Compare the measured free movement dimensions:
  • the maximum acceptable value of free movement of the flap trailing edge at tracks 1 and 2 is 10.0 mm (0.3937 in.)
  • for the maximum acceptable value of dimension X (free movement of the lever arm) refer to the table 601.
Subtask 27-54-00-220-050-D ** ON A/C NOT FOR ALL
A. Detailed Dimensional Check - Free Movement at the Trailing Edge of the Inboard Flap
F Flap to Rotary Actuator Drive Lever - To Disconnect the Inboard Flap ** ON A/C NOT FOR ALL
F Rotary Actuator Drive-Lever - To Measure The Free Play (Track 1) ** ON A/C NOT FOR ALL
F Rotary Actuator Drive-Lever - To Measure the Free Play (Track 2) ** ON A/C NOT FOR ALL
F Flaps Trailing Edge Free Movement - Location and Details of Measurement Positions ** ON A/C NOT FOR ALL
   (1) At the track 1 position, disconnect the flap drive arm from the rotary actuator lever-arm:
     (a) Remove and discard the cotter pin (176).
     (b) Remove the nut (177) and the washer (178).
     (c) Remove the bolts (183), the washers (182) and the indicator plate (181).
     (d) Remove the indicator pin (180).
     (e) Remove the shearbolt (179) and install the PIN DIA 3 MM (0.118 IN), LENGTH 100 MM (3.937 IN.) ALU.
NOTE: The diameter of the aluminium pin is approximately 6.0 mm (0.2362 in.) less than the shearbolt (179) it replaces. The pin is 100 mm (3.9370 in.) long and is made locally from LN 1798 3.1354T3511. The pin is temporary and has two functions:
  • it keeps the joint together when you extend/retract the flaps
  • it is easy to remove the pin to disconnect the joint when the flaps are extended.
     (f) Extend the flaps manually (Ref. AMM TASK 27-50-00-866-011) as follows:
       1 Slowly extend the flaps until the dimension T at track 2 is approximately 6.0 mm (0.2362 in.).
       2 Dimension T can be +/- 1.0 mm (0.0394 in.) but it must be set during the flap extension procedure. Do not retract the flaps in small amounts to set the dimension T.
     (g) Remove the aluminium pin.
   (2) At the track 2 position, measure the total free movement of the flap trailing edge:
     (a) Refer to step 4.A.(1)(f) and make sure the flaps are extended correctly.
     (b) Make sure that the travel ranges are clear.
     (c) Apply a down force (by hand) to the trailing edge of the flap. Apply sufficient force to make the flap move through possible free movement in the flap system mechanism and joints.
NOTE: Do not apply too much force to cause the system components, mechanism or the aircraft fixed structure to move or bend.
     (d) Hold the flap in this position, measure and record the dimension Z and then release the flap.
     (e) Apply an up force (by hand) to the trailing edge of the flap. Apply sufficient force to make the flap move through possible free movement in the flap system mechanism and joints.
NOTE: Do not apply too much force to cause the system components, mechanism or the aircraft fixed structure to move or bend.
     (f) Hold the flap in this position, measure and record the dimension Y and then release the flap.
     (g) To find the total free movement, subtract the dimension Z from the dimension Y.
   (3) At the track 1 position, measure the total free movement of the actuator lever (dimension X):
     (a) Apply a down force (by hand) to the actuator lever. Apply sufficient force to make the actuator lever move through possible free movement in the flap system mechanism and joints.
     (b) Hold the actuator lever in this position, then measure and record the dimension T.
     (c) Apply an up force (by hand) to the actuator lever. Apply sufficient force to make the actuator lever move through possible free movement in the flap system mechanism and joints.
     (d) Hold the actuator lever in this position, then measure and record the dimension S.
     (e) To find the total free movement (dimension X), subtract the dimension S from the dimension T.
   (4) Install the aluminium pin through the joint where you removed the shearbolt (179).
   (5) Manually retract the flaps fully and connect the drive system (Ref. AMM TASK 27-50-00-866-012).
   (6) Remove the aluminium pin.
   (7) At the track 1 position, temporarily connect the flap drive arm to the rotary actuator drive-lever as follows:
     (a) Install the shearbolt (179), the washer (178) and the nut (177).
     (b) Hand tighten the nut (177).
     (c) Install the indicator pin (180), the indicator plate (181), the washers (182) and the bolts (183).
     (d) Hand tighten the bolts (183).
   (8) At the track 2 position, disconnect the flap drive arm from the rotary actuator lever-arm:
     (a) Remove and discard the cotter pin (187).
     (b) Remove the nut (186) and the washer (185).
     (c) Remove the bolt (184) and install the PIN DIA 10 MM (0.394 IN),LENGTH 100 MM (3.937 IN.) ALU.
     (d) Extend the flaps fully (Ref. AMM TASK 27-50-00-866-008).
     (e) Remove the aluminium pin.
   (9) At the inboard end of the flap, measure the total free movement of the flap trailing edge:
     (a) Make sure that the flaps are fully extended, and that the travel ranges are clear.
     (b) Apply a down force (by hand) to the trailing edge of the flap. Apply sufficient force to make the flap move through possible free movement in the flap system mechanism and joints.
NOTE: Do not apply too much force to cause the system components, mechanism or the aircraft fixed structure to move or bend.
     (c) Hold the flap in this position, measure and record the dimension Z and then release the flap.
     (d) Apply an up force (by hand) to the trailing edge of the flap. Apply sufficient force to make the flap move through possible free movement in the flap system mechanism and joints.
NOTE: Do not apply too much force to cause the system components, mechanism or the aircraft fixed structure to move or bend.
     (e) Hold the flap in this position, measure and record the dimension Y and then release the flap.
     (f) To find the total free movement, subtract the dimension Z from the dimension Y.
   (10) At the track 2 position, measure the total free movement of the actuator lever (dimension X):
     (a) Apply a down force (by hand) to the actuator lever. Apply sufficient force to make the actuator lever move through possible free movement in the flap system mechanism and joints.
     (b) Hold the actuator lever in this position, then measure and record the dimension T.
     (c) Apply an up force (by hand) to the actuator lever. Apply sufficient force to make the actuator lever move through possible free movement in the flap system mechanism and joints.
     (d) Hold the actuator lever in this position, then measure and record the dimension S.
     (e) To find the total free movement (dimension X), subtract the dimension S from the dimension T.
   (11) Install the aluminium pin through the joint where you removed the bolt (184).
   (12) Retract the flaps fully (Ref. AMM TASK 27-50-00-866-009).
   (13) Remove the aluminium pin.
   (14) At the track 2 position, temporarily connect the flap drive arm to the rotary actuator drive-lever as follows:
     (a) Install the bolt (184), the washer (185) and the nut (186).
     (b) Hand tighten the nut (186).
   (15) Compare the measured free movement dimensions:
  • the maximum acceptable value of free movement at the inboard flap trailing edge at tracks 1 and 2 is 10.0 mm (0.3937 in.)
  • for the maximum acceptable value of dimension X (free movement of the lever arm) refer to the table 601.
Subtask 27-54-00-220-050-H ** ON A/C NOT FOR ALL
A. Detailed Dimensional Check - Free Movement at the Trailing Edge of the Inboard Flap
F Flap to Rotary Actuator Drive Lever - To Disconnect the Inboard Flap ** ON A/C NOT FOR ALL
F Rotary Actuator Drive-Lever - To Measure The Free Play (Track 1) ** ON A/C NOT FOR ALL
F Rotary Actuator Drive-Lever - To Measure The Free Play (Track 1) ** ON A/C NOT FOR ALL
F Rotary Actuator Drive-Lever - To Measure the Free Play (Track 2) ** ON A/C NOT FOR ALL
F Rotary Actuator Drive-Lever - To Measure the Free Play (Track 2) ** ON A/C NOT FOR ALL
F Flaps Trailing Edge Free Movement - Location and Details of Measurement Positions ** ON A/C NOT FOR ALL
   (1) At the track 1 position, disconnect the flap drive arm from the rotary actuator lever-arm:
     (a) Remove and discard the cotter pins (1) and (6).
     (b) Remove the nut (2) and the washer (3).
     (c) Remove the bolt (5) and the locking plate (4).
     (d) Remove the nut (7) and the washer (8).
     (e) Remove the bolt (9) and install the PIN DIA 5 MM (0.197 IN), LENGTH 100 MM (3.937 IN.) ALU.
NOTE: The diameter of the aluminium pin is approximately 6.0 mm (0.2362 in.) less than the bolt (9) it replaces. The pin is 100 mm (3.9370 in.) long and is made locally from LN 1798 3.1354T3511. The pin is temporary and has two functions:
  • it keeps the joint together when you extend/retract the flaps
  • it is easy to remove the pin to disconnect the joint when the flaps are extended.
     (f) Extend the flaps manually (Ref. AMM TASK 27-50-00-866-011) as follows:
       1 Slowly extend the flaps until the dimension T at track 2 is approximately 6.0 mm (0.2362 in.).
       2 Dimension T can be +/- 1.0 mm (0.0394 in.) but it must be set during the flap extension procedure. Do not retract the flaps in small amounts to set the dimension T.
     (g) Remove the aluminium pin.
   (2) At the track 2 position, measure the total free movement of the flap trailing edge:
     (a) Refer to step 4.A.(1)(f) and make sure the flaps are extended correctly.
     (b) Make sure that the travel ranges are clear.
     (c) Apply a down force (by hand) to the trailing edge of the flap. Apply sufficient force to make the flap move through possible free movement in the flap system mechanism and joints.
NOTE: Do not apply too much force to cause the system components, mechanism or the aircraft fixed structure to move or bend.
     (d) Hold the flap in this position, measure and record the dimension Z and then release the flap.
     (e) Apply an up force (by hand) to the trailing edge of the flap. Apply sufficient force to make the flap move through possible free movement in the flap system mechanism and joints.
NOTE: Do not apply too much force to cause the system components, mechanism or the aircraft fixed structure to move or bend.
     (f) Hold the flap in this position, measure and record the dimension Y and then release the flap.
     (g) To find the total free movement, subtract the dimension Z from the dimension Y.
   (3) At the track 1 position, measure the total free movement of the actuator lever (dimension X):
     (a) Apply a down force (by hand) to the actuator lever. Apply sufficient force to make the actuator lever move through possible free movement in the flap system mechanism and joints.
     (b) Hold the actuator lever in this position, then measure and record the dimension T.
     (c) Apply an up force (by hand) to the actuator lever. Apply sufficient force to make the actuator lever move through possible free movement in the flap system mechanism and joints.
     (d) Hold the actuator lever in this position, then measure and record the dimension S.
     (e) To find the total free movement (dimension X), subtract the dimension S from the dimension T.
   (4) Install the aluminium pin through the joint where you removed the bolt (9).
   (5) Manually retract the flaps fully and connect the drive system (Ref. AMM TASK 27-50-00-866-012).
   (6) Remove the aluminium pin.
   (7) At the track 1 position, temporarily connect the flap drive arm to the rotary actuator drive-lever as follows:
     (a) Install the bolt (9), the washer (8) and the nut (7).
     (b) Hand tighten the nut (7).
     (c) Install the bolt (5), the locking plate (4), the washer (3) and the nut (2).
     (d) Hand tighten the nut (2).
   (8) At the track 2 position, disconnect the flap drive arm from the rotary actuator lever-arm:
     (a) Remove and discard the cotter pins (10) and (15).
     (b) Remove the nut (11) and the washer (12).
     (c) Remove the bolt (14) and the locking plate (13).
     (d) Remove the nut (16) and the washer (17).
     (e) Remove the bolt (18) and install the PIN DIA 10 MM (0.394 IN),LENGTH 100 MM (3.937 IN.) ALU.
     (f) Extend the flaps fully (Ref. AMM TASK 27-50-00-866-008).
     (g) Remove the aluminium pin.
   (9) At the inboard end of the flap, measure the total free movement of the flap trailing edge:
     (a) Make sure that the flaps are fully extended, and that the travel ranges are clear.
     (b) Apply a down force (by hand) to the trailing edge of the flap. Apply sufficient force to make the flap move through possible free movement in the flap system mechanism and joints.
NOTE: Do not apply too much force to cause the system components, mechanism or the aircraft fixed structure to move or bend.
     (c) Hold the flap in this position, measure and record the dimension Z and then release the flap.
     (d) Apply an up force (by hand) to the trailing edge of the flap. Apply sufficient force to make the flap move through possible free movement in the flap system mechanism and joints.
NOTE: Do not apply too much force to cause the system components, mechanism or the aircraft fixed structure to move or bend.
     (e) Hold the flap in this position, measure and record the dimension Y and then release the flap.
     (f) To find the total free movement, subtract the dimension Z from the dimension Y.
   (10) At the track 2 position, measure the total free movement of the actuator lever (dimension X):
     (a) Apply a down force (by hand) to the actuator lever. Apply sufficient force to make the actuator lever move through possible free movement in the flap system mechanism and joints.
     (b) Hold the actuator lever in this position, then measure and record the dimension T.
     (c) Apply an up force (by hand) to the actuator lever. Apply sufficient force to make the actuator lever move through possible free movement in the flap system mechanism and joints.
     (d) Hold the actuator lever in this position, then measure and record the dimension S.
     (e) To find the total free movement (dimension X), subtract the dimension S from the dimension T.
   (11) Install the aluminium pin through the joint where you removed the bolt (18).
   (12) Retract the flaps fully (Ref. AMM TASK 27-50-00-866-009).
   (13) Remove the aluminium pin.
   (14) At the track 2 position, temporarily connect the flap drive arm to the rotary actuator drive-lever as follows:
     (a) Install the bolt (18), the washer (17) and the nut (16).
     (b) Hand tighten the nut (16).
     (c) Install the bolt (14), the locking plate (13), the washer (12) and the nut (11).
     (d) Hand tighten the nut (11).
   (15) Compare the measured free movement dimensions:
  • the maximum acceptable value of free movement at the inboard flap trailing edge at tracks 1 and 2 is 10.0 mm (0.3937 in.)
  • for the maximum acceptable value of dimension X (free movement of the lever arm) refer to the table 601.
Subtask 27-54-00-220-069-C ** ON A/C NOT FOR ALL
B. Detailed Dimensional Check - Free Movement at the Trailing Edge of the Outboard Flap
F Flap to Rotary Actuator Drive Lever - To Disconnect the Outboard Flap ** ON A/C NOT FOR ALL
F Rotary Actuator Drive-Lever - To Measure the Free Play (Track 3) ** ON A/C NOT FOR ALL
F Rotary Actuator Drive-Lever - To Measure the Free Play (Track 4) ** ON A/C NOT FOR ALL
F Flaps Trailing Edge Free Movement - Location and Details of Measurement Positions ** ON A/C NOT FOR ALL
   (1) At the track 3 position, disconnect the outboard flap drive-arm from the rotary actuator lever-arm:
     (a) Remove and discard the cotter pins (215) and (416).
     (b) Remove the nut (214) and the washer (213).
     (c) Remove the nut (415), the washer (414), the bolt (412) and the locking plate (413).
     (d) Remove the bolt (212) and install the PIN DIA 20 MM (0.787 IN),LENGTH 100 MM (3.937 IN.) ALU.
NOTE: The diameter of the aluminium pin is approximately 6.0 mm (0.2362 in.) less than the bolt (212) it replaces. The pin is 100 mm (3.9370 in.) long and is made locally from material LN 1798 3.1354T3511. The pin is temporary and has two functions:
  • it keeps the joint together when you extend/retract the flaps
  • it is easy to remove the pin to disconnect the joint when the flaps are extended.
     (e) Extend the flaps fully (Ref. AMM TASK 27-50-00-866-008).
     (f) Remove the aluminium pin.
   (2) At the track 4 position, measure the total free movement of the flap trailing edge:
     (a) Make sure that the flaps are fully extended, and that the travel ranges are clear.
     (b) Apply a down force (by hand) to the trailing edge of the flap. Apply sufficient force to make the flap move through possible free movement in the flap system mechanism and joints.
NOTE: Do not apply too much force to cause the system components, mechanism or the aircraft fixed structure to move or bend.
     (c) Hold the flap in this position, then measure and record the dimension Z.
     (d) Apply an up force (by hand) to the trailing edge of the flap. Apply sufficient force to make the flap move through possible free movement in the flap system mechanism and joints.
NOTE: Do not apply too much force to cause the system components, mechanism or the aircraft fixed structure to move or bend.
     (e) Hold the flap in this position, measure and record the dimension Y and then release the flap.
     (f) To find the total free movement, subtract the dimension Z from the dimension Y.
   (3) At the track 3 position, measure the total free movement of the actuator lever (dimension X):
     (a) Apply a down force (by hand) to the actuator lever. Apply sufficient force to make the actuator lever move through possible free movement in the flap system mechanism and joints.
     (b) Hold the actuator lever in this position, then measure and record the dimension T.
     (c) Apply an up force (by hand) to the actuator lever. Apply sufficient force to make the actuator lever move through possible free movement in the flap system mechanism and joints.
     (d) Hold the actuator lever in this position, then measure and record the dimension S.
     (e) To find the total free movement (dimension X), subtract the dimension S from the dimension T.
   (4) Install the aluminium pin through the joint where you removed the bolt (212).
   (5) Retract the flaps fully (Ref. AMM TASK 27-50-00-866-009).
   (6) Remove the aluminium pin.
   (7) At the track 3 position, temporarily connect the flap drive arm to the rotary actuator drive-lever as follows:
     (a) Install the bolt (212), the washer (213) and the nut (214).
     (b) Hand tighten the nut (214).
     (c) Install the locking plate (413), the bolt (412), the washer (414) and the nut (415).
     (d) Hand tighten the nut (415).
   (8) At the track 4 position, disconnect the outboard flap drive-arm from the rotary actuator drive-lever:
     (a) Remove and discard the cotter pins (215) and (416).
     (b) Remove the nut (214) and the washer (213)
     (c) Remove the nut (415), the washer (414), the bolt (412) and the locking plate (413).
     (d) Remove the bolt (212) and install the PIN DIA 10 MM (0.394 IN),LENGTH 100 MM (3.937 IN.) ALU.
     (e) Extend the flaps fully (Ref. AMM TASK 27-50-00-866-008).
     (f) Remove the aluminium pin.
   (9) At the track 3 position, measure the total free movement of the flap trailing edge:
     (a) Make sure that the flaps are fully extended, and that the travel ranges are clear.
     (b) Apply a down force (by hand) to the trailing edge of the flap. Apply sufficient force to make the flap move through possible free movement in the flap system mechanism and joints.
NOTE: Do not apply too much force to cause the system components, mechanism or the aircraft fixed structure to move or bend.
     (c) Hold the flap in this position, then measure and record the dimension Z.
     (d) Apply an up force (by hand) to the trailing edge of the flap. Apply sufficient force to make the flap move through possible free movement in the flap system mechanism and joints.
NOTE: Do not apply too much force to cause the system components, mechanism or the aircraft fixed structure to move or bend.
     (e) Hold the flap in this position, measure and record the dimension Y and then release the flap.
     (f) To find the total free movement, subtract the dimension Z from the dimension Y.
   (10) At the track 4 position, measure the total free movement of the actuator lever (dimension X):
     (a) Apply a down force (by hand) to the actuator lever. Apply sufficient force to make the actuator lever move through possible free movement in the flap system mechanism and joints.
     (b) Hold the actuator lever in this position, then measure and record the dimension T.
     (c) Apply an up force (by hand) to the actuator lever. Apply sufficient force to make the actuator lever move through possible free movement in the flap system mechanism and joints.
     (d) Hold the actuator lever in this position, then measure and record the dimension S.
     (e) To find the total free movement (dimension X), subtract the dimension S from the dimension T.
   (11) Install the aluminium pin through the joint where you removed the bolt (212).
   (12) Retract the flaps fully (Ref. AMM TASK 27-50-00-866-009).
   (13) Remove the aluminium pin.
   (14) At the track 4 position, temporarily connect the flap drive arm to the rotary actuator drive-lever as follows:
     (a) Install the bolt (212), the washer (213) and the nut (214).
     (b) Hand tighten the nut (214).
     (c) Install the locking plate (413), the bolt (412), the washer (414) and the nut (415).
     (d) Hand tighten the nut (415).
   (15) Compare the measured free movement dimensions:
  • the maximum acceptable value of free movement at the outboard flap trailing edge at tracks 3 and 4 is 11.0 mm (0.4331 in.)
  • for the maximum acceptable value of dimension X (free movement of the lever arm) refer to the table 601.
Subtask 27-54-00-220-069-D ** ON A/C NOT FOR ALL
B. Detailed Dimensional Check - Free Movement at the Trailing Edge of the Outboard Flap
F Flap to Rotary Actuator Drive Lever - To Disconnect the Outboard Flap ** ON A/C NOT FOR ALL
F Rotary Actuator Drive-Lever - To Measure the Free Play (Track 3) ** ON A/C NOT FOR ALL
F Rotary Actuator Drive-Lever - To Measure the Free Play (Track 4) ** ON A/C NOT FOR ALL
F Flaps Trailing Edge Free Movement - Location and Details of Measurement Positions ** ON A/C NOT FOR ALL
   (1) At the track 3 position, disconnect the outboard flap drive-arm from the rotary actuator lever-arm:
     (a) Remove and discard the cotter pins (25) and (26).
     (b) Remove the nut (24) and the washer (23).
     (c) Remove the bolt (21) and the locking plate (22).
     (d) Remove the nut (27) and the washer (28).
     (e) Remove the bolt (20) and install the PIN DIA 19 MM (0.748 IN),LENGTH 100 MM (3.937 IN.) ALU.
NOTE: The diameter of the aluminium pin is approximately 6.0 mm (0.2362 in.) less than the bolt (20) it replaces. The installation of the pin is temporary and has two functions:
  • It keeps the joint together when you extend/retract the flaps
  • It is easy to remove the pin to disconnect the joint when the flaps are extended.
     (f) Extend the flaps fully (Ref. AMM TASK 27-50-00-866-008).
     (g) Remove the aluminium pin.
   (2) At the track 4 position, measure the total free movement of the flap trailing edge:
     (a) Make sure that the flaps are fully extended, and that the travel ranges are clear.
     (b) Apply a down force (by hand) to the trailing edge of the flap. Apply sufficient force to make the flap move through possible free movement in the flap system mechanism and joints.
NOTE: Do not apply too much force to cause the system components, mechanism or the aircraft fixed structure to move or bend.
     (c) Hold the flap in this position, then measure and record the dimension Z.
     (d) Apply an up force (by hand) to the trailing edge of the flap. Apply sufficient force to make the flap move through possible free movement in the flap system mechanism and joints.
NOTE: Do not apply too much force to cause the system components, mechanism or the aircraft fixed structure to move or bend.
     (e) Hold the flap in this position, measure and record the dimension Y and then release the flap.
     (f) To find the total free movement, subtract the dimension Z from the dimension Y.
   (3) At the track 3 position, measure the total free movement of the actuator lever (dimension X):
     (a) Apply a down force (by hand) to the actuator lever. Apply sufficient force to make the actuator lever move through possible free movement in the flap system mechanism and joints.
     (b) Hold the actuator lever in this position, then measure and record the dimension T.
     (c) Apply an up force (by hand) to the actuator lever. Apply sufficient force to make the actuator lever move through possible free movement in the flap system mechanism and joints.
     (d) Hold the actuator lever in this position, then measure and record the dimension S.
     (e) To find the total free movement (dimension X), subtract the dimension S from the dimension T.
   (4) Install the aluminium pin through the joint where you removed the bolt (20).
   (5) Retract the flaps fully (Ref. AMM TASK 27-50-00-866-009).
   (6) Remove the aluminium pin.
   (7) At the track 3 position, temporarily connect the flap drive arm to the rotary actuator drive-lever as follows:
     (a) Install the bolt (20), the washer (28) and the nut (27).
     (b) Hand tighten the nut (27).
     (c) Install the bolt (21), the locking plate (22), the washer (23) and the nut (24).
     (d) Hand tighten the nut (24).
   (8) At the track 4 position, disconnect the outboard flap drive-arm from the rotary actuator drive-lever:
     (a) Remove and discard the cotter pins (35) and (34).
     (b) Remove the nut (36) and the washer (37).
     (c) Remove the bolt (30) and the locking plate (31).
     (d) Remove the nut (33) and the washer (32).
     (e) Remove the bolt (29) and install the PIN DIA 10 MM (0.394 IN),LENGTH 100 MM (3.937 IN.) ALU.
     (f) Extend the flaps fully (Ref. AMM TASK 27-50-00-866-008).
     (g) Remove the aluminium pin.
   (9) At the track 3 position, measure the total free movement of the flap trailing edge:
     (a) Make sure that the flaps are fully extended, and that the travel ranges are clear.
     (b) Apply a down force (by hand) to the trailing edge of the flap. Apply sufficient force to make the flap move through possible free movement in the flap system mechanism and joints.
NOTE: Do not apply too much force to cause the system components, mechanism or the aircraft fixed structure to move or bend.
     (c) Hold the flap in this position, then measure and record the dimension Z.
     (d) Apply an up force (by hand) to the trailing edge of the flap. Apply sufficient force to make the flap move through possible free movement in the flap system mechanism and joints.
NOTE: Do not apply too much force to cause the system components, mechanism or the aircraft fixed structure to move or bend.
     (e) Hold the flap in this position, measure and record the dimension Y and then release the flap.
     (f) To find the total free movement, subtract the dimension Z from the dimension Y.
   (10) At the track 4 position, measure the total free movement of the actuator lever (dimension X):
     (a) Apply a down force (by hand) to the actuator lever. Apply sufficient force to make the actuator lever move through possible free movement in the flap system mechanism and joints.
     (b) Hold the actuator lever in this position, then measure and record the dimension T.
     (c) Apply an up force (by hand) to the actuator lever. Apply sufficient force to make the actuator lever move through possible free movement in the flap system mechanism and joints.
     (d) Hold the actuator lever in this position, then measure and record the dimension S.
     (e) To find the total free movement (dimension X), subtract the dimension S from the dimension T.
   (11) Install the aluminium pin through the joint where you removed the bolt (20).
   (12) Retract the flaps fully (Ref. AMM TASK 27-50-00-866-009).
   (13) Remove the aluminium pin.
   (14) At the track 4 position, temporarily connect the flap drive arm to the rotary actuator drive-lever as follows:
     (a) Install the bolt (29), the washer (32) and the nut (33).
     (b) Hand tighten the nut (33).
     (c) Install the bolt (30), the locking plate (31), the washer (37) and the nut (36).
     (d) Hand tighten the nut (36).
   (15) Compare the measured free movement dimensions:
  • the maximum acceptable value of free movement at the outboard flap trailing edge at tracks 3 and 4 is 11.0 mm (0.4331 in.)
  • for the maximum acceptable value of dimension X (free movement of the lever arm) refer to the table 601.
Subtask 27-54-00-220-069-E ** ON A/C NOT FOR ALL
B. Detailed Dimensional Check - Free Movement at the Trailing Edge of the Outboard Flap
F Flap to Rotary Actuator Drive Lever - To Disconnect the Outboard Flap ** ON A/C NOT FOR ALL
F Rotary Actuator Drive-Lever - To Measure the Free Play (Track 3) ** ON A/C NOT FOR ALL
F Rotary Actuator Drive-Lever - To Measure the Free Play (Track 3) ** ON A/C NOT FOR ALL
F Rotary Actuator Drive-Lever - To Measure the Free Play (Track 4) ** ON A/C NOT FOR ALL
F Rotary Actuator Drive-Lever - To Measure the Free Play (Track 4) ** ON A/C NOT FOR ALL
F Flaps Trailing Edge Free Movement - Location and Details of Measurement Positions ** ON A/C NOT FOR ALL
   (1) At the track 3 position, disconnect the outboard flap drive-arm from the rotary actuator lever-arm:
     (a) Remove and discard the cotter pins (25) and (26).
     (b) Remove the nut (24) and the washer (23).
     (c) Remove the bolt (21) and the locking plate (22).
     (d) Remove the nut (27) and the washer (28).
     (e) Remove the bolt (20) and install the PIN DIA 10 MM (0.394 IN),LENGTH 100 MM (3.937 IN.) ALU.
NOTE: The diameter of the aluminium pin is approximately 6.0 mm (0.2362 in.) less than the bolt (20) it replaces. The installation of the pin is temporary and has two functions:
  • It keeps the joint together when you extend/retract the flaps
  • It is easy to remove the pin to disconnect the joint when the flaps are extended.
     (f) Extend the flaps fully (Ref. AMM TASK 27-50-00-866-008).
     (g) Remove the aluminium pin.
   (2) At the track 4 position, measure the total free movement of the flap trailing edge:
     (a) Make sure that the flaps are fully extended, and that the travel ranges are clear.
     (b) Apply a down force (by hand) to the trailing edge of the flap. Apply sufficient force to make the flap move through possible free movement in the flap system mechanism and joints.
NOTE: Do not apply too much force to cause the system components, mechanism or the aircraft fixed structure to move or bend.
     (c) Hold the flap in this position, then measure and record the dimension Z.
     (d) Apply an up force (by hand) to the trailing edge of the flap. Apply sufficient force to make the flap move through possible free movement in the flap system mechanism and joints.
NOTE: Do not apply too much force to cause the system components, mechanism or the aircraft fixed structure to move or bend.
     (e) Hold the flap in this position, measure and record the dimension Y and then release the flap.
     (f) To find the total free movement, subtract the dimension Z from the dimension Y.
   (3) At the track 3 position, measure the total free movement of the actuator lever (dimension X):
     (a) Apply a down force (by hand) to the actuator lever. Apply sufficient force to make the actuator lever move through possible free movement in the flap system mechanism and joints.
     (b) Hold the actuator lever in this position, then measure and record the dimension T.
     (c) Apply an up force (by hand) to the actuator lever. Apply sufficient force to make the actuator lever move through possible free movement in the flap system mechanism and joints.
     (d) Hold the actuator lever in this position, then measure and record the dimension S.
     (e) To find the total free movement (dimension X), subtract the dimension S from the dimension T.
   (4) Install the aluminium pin through the joint where you removed the bolt (20).
   (5) Retract the flaps fully (Ref. AMM TASK 27-50-00-866-009).
   (6) Remove the aluminium pin.
   (7) At the track 3 position, temporarily connect the flap drive arm to the rotary actuator drive-lever as follows:
     (a) Install the bolt (20), the washer (28) and the nut (27).
     (b) Hand tighten the nut (27).
     (c) Install the bolt (21), the locking plate (22), the washer (23) and the nut (24).
     (d) Hand tighten the nut (24).
   (8) At the track 4 position, disconnect the outboard flap drive-arm from the rotary actuator drive-lever:
     (a) Remove and discard the cotter pins (25) and (26).
     (b) Remove the nut (24) and the washer (23).
     (c) Remove the bolt (21) and the locking plate (22).
     (d) Remove the nut (27) and the washer (28).
     (e) Remove the bolt (20) and install the PIN DIA 10 MM (0.394 IN),LENGTH 100 MM (3.937 IN.) ALU.
     (f) Extend the flaps fully (Ref. AMM TASK 27-50-00-866-008).
     (g) Remove the aluminium pin.
   (9) At the track 3 position, measure the total free movement of the flap trailing edge:
     (a) Make sure that the flaps are fully extended, and that the travel ranges are clear.
     (b) Apply a down force (by hand) to the trailing edge of the flap. Apply sufficient force to make the flap move through possible free movement in the flap system mechanism and joints.
NOTE: Do not apply too much force to cause the system components, mechanism or the aircraft fixed structure to move or bend.
     (c) Hold the flap in this position, then measure and record the dimension Z.
     (d) Apply an up force (by hand) to the trailing edge of the flap. Apply sufficient force to make the flap move through possible free movement in the flap system mechanism and joints.
NOTE: Do not apply too much force to cause the system components, mechanism or the aircraft fixed structure to move or bend.
     (e) Hold the flap in this position, measure and record the dimension Y and then release the flap.
     (f) To find the total free movement, subtract the dimension Z from the dimension Y.
   (10) At the track 4 position, measure the total free movement of the actuator lever (dimension X):
     (a) Apply a down force (by hand) to the actuator lever. Apply sufficient force to make the actuator lever move through possible free movement in the flap system mechanism and joints.
     (b) Hold the actuator lever in this position, then measure and record the dimension T.
     (c) Apply an up force (by hand) to the actuator lever. Apply sufficient force to make the actuator lever move through possible free movement in the flap system mechanism and joints.
     (d) Hold the actuator lever in this position, then measure and record the dimension S.
     (e) To find the total free movement (dimension X), subtract the dimension S from the dimension T.
   (11) Install the aluminium pin through the joint where you removed the bolt (20).
   (12) Retract the flaps fully (Ref. AMM TASK 27-50-00-866-009).
   (13) Remove the aluminium pin.
   (14) At the track 4 position, temporarily connect the flap drive arm to the rotary actuator drive-lever as follows:
     (a) Install the bolt (20), the washer (28) and the nut (27).
     (b) Hand tighten the nut (27).
     (c) Install the bolt (21), the locking plate (22), the washer (23) and the nut (24).
     (d) Hand tighten the nut (24).
   (15) Compare the measured free movement dimensions:
  • the maximum acceptable value of free movement at the outboard flap trailing edge at tracks 3 and 4 is 11.0 mm (0.4331 in.)
  • for the maximum acceptable value of dimension X (free movement of the lever arm) refer to the table 601.
Subtask 27-54-00-220-058-A ** ON A/C NOT FOR ALL
C. Table 601 shows the maximum values for dimension X.

Track Number
Dimension X (maximum)
1
4.00 mm (0.157 in.)
2
1.81 mm (0.071 in.)
3
1.70 mm (0.067 in.)
4
1.42 mm (0.056 in.)
Table 601
Subtask 27-54-00-220-058-B ** ON A/C NOT FOR ALL
C. Table 601 shows the maximum values for dimension X.

Track Number
Dimension X (maximum)
1
4.00 mm (0.157 in.)
2
1.51 mm (0.060 in.)
3
1.79 mm (0.070 in.)
4
1.37 mm (0.054 in.)
Table 601
Subtask 27-54-00-220-058-C ** ON A/C NOT FOR ALL
C. Table 601 shows the maximum values for dimension X.

Track Number
Dimension X (maximum)
1
2.77 mm (0.109 in.)
2
1.64 mm (0.065 in.)
3
1.77 mm (0.070 in.)
4
1.24 mm (0.049 in.)
Table 601
Subtask 27-54-00-220-056-A ** ON A/C NOT FOR ALL
D. Checks to Identify and Correct too much Free Movement at the Trailing Edge of the Flaps
F Flaps Trailing Edge - Flow Chart to do the Free Movement Checks ** ON A/C NOT FOR ALL
   (1) General
     (a) The flow chart shows the process to find and correct too much free movement. Use the flow chart as a guide. Each time you make a correction, do a free movement check until the free movement is in limits.
     (b) When the free movement value is too much, do the checks that follow to identify the cause. Start at the inboard flap track 2 and then track 1. Subsequently, do the checks at the outboard flap track 3 and then track 4.
     (c) When you look for backlash, move the flap up and down 4 or 5 times to help you see the backlash or wear.
   (2) Do the steps that follow only when they are applicable:
     (a) Do a general visual inspection:
       1 Visually inspect the connection joints for backlash or wear between the flap actuator and the flap track beam and carriage. Some of the possible causes of too much backlash in the connection joints are:
  • a bearing that has moved to an incorrect position or a bearing that cannot move
  • a loose bush
  • a damaged or missing spherical bearing liner
  • worn bushes and bolts.
       2 An indication that the backlash is too much is when a connection shows more radial or axial movement than an equivalent adjacent component.
       3 Make sure that all components are installed correctly.
       4 Replace components that are unserviceable.
     (b) If the free movement of the lever arm (dimension X) is too much, remove the unserviceable actuator and install a serviceable actuator:
       1 for the flap track 1 actuator (Ref. AMM TASK 27-54-49-000-001) and (Ref. AMM TASK 27-54-49-400-001).
       2 for the flap track 2 actuator (Ref. AMM TASK 27-54-49-000-002) and (Ref. AMM TASK 27-54-49-400-002).
       3 for the flap track 3 actuator (Ref. AMM TASK 27-54-49-000-003) and (Ref. AMM TASK 27-54-49-400-003).
       4 for the flap track 4 actuator (Ref. AMM TASK 27-54-49-000-004) and (Ref. AMM TASK 27-54-49-400-004).
     (c) If you have installed a new flap actuator and the free movement of the lever arm (dimension X) is too much, do a check of the actuator lever splines:
       1 Remove the applicable lever:
       2 Do a check for wear of the actuator lever splines.
       3 Install a serviceable lever:
     (d) Do a detailed dimensional check of the connection of the joint between the flap drive arm and the rotary actuator lever-arm:
       1 Remove the flap sufficiently to allow the flap drive arm to be disconnected from the rotary actuator lever arm:
       2 Do the detailed dimensional check:
     (e) Do a detailed dimensional check of the flap attachments:
       1 Remove the applicable flap:
       2 Do a detailed dimensional check of the inboard flap attachments (Ref. AMM TASK 57-52-00-220-015).
       3 Do a detailed dimensional check of the outboard flap attachments (Ref. AMM TASK 57-53-00-220-023).
     (f) Make sure the free play between the flap track and the top roller is in limits.
     (g) Do a detailed dimensional check of the flap carriage main rollers, the upper rollers and the pivot pins of lubrication blocks:
       1 Remove the applicable flap carriage:
       2 Do a detailed dimensional check of the No 1 to 4 flap carriages in the workshop.
       3 Install the applicable serviceable flap carriage:
     (h) Do a detailed dimensional check of the Nos. 2, 3 and 4 flap track beams SRM 57513301.
     (i) Do a detailed dimensional check of the No. 1 flap track beam:
       1 Remove the No. 1 flap track beam (Ref. AMM TASK 57-51-33-000-001).
       2 Do a detailed dimensional check of the No 1. flap track beam in the workshop.
       3 Install a serviceable No.1 flap track beam (Ref. AMM TASK 57-51-33-400-001).
     (j) Install a serviceable flap:
Subtask 27-54-00-220-056-B ** ON A/C NOT FOR ALL
D. Checks to Identify and Correct too much Free Movement at the Trailing Edge of the Flaps
F Flaps Trailing Edge - Flow Chart to do the Free Movement Checks ** ON A/C NOT FOR ALL
   (1) General
     (a) The flow chart shows the process to find and correct too much free movement. Use the flow chart as a guide. Each time you make a correction, do a free movement check until the free movement is in limits.
     (b) When the free movement value is too much, do the checks that follow to identify the cause. Start at the inboard flap track 2 and then track 1. Subsequently, do the checks at the outboard flap track 3 and then track 4.
     (c) When you look for backlash, move the flap up and down 4 or 5 times to help you see the backlash or wear.
   (2) Do the steps that follow only when they are applicable:
     (a) Do a general visual inspection:
       1 Visually inspect the connection joints for backlash or wear between the flap actuator and the flap track beam and carriage. Some of the possible causes of too much backlash in the connection joints are:
  • a bearing that has moved to an incorrect position or a bearing that cannot move
  • a loose bush
  • a damaged or missing spherical bearing liner
  • worn bushes and bolts.
       2 An indication that the backlash is too much is when a connection shows more radial or axial movement than an equivalent adjacent component.
       3 Make sure that all components are installed correctly.
       4 Replace components that are unserviceable.
     (b) If the free movement of the lever arm (dimension X) is too much, remove the unserviceable actuator and install a serviceable actuator:
       1 for the flap track 1 actuator (Ref. AMM TASK 27-54-49-000-001) and (Ref. AMM TASK 27-54-49-400-001).
       2 for the flap track 2 actuator (Ref. AMM TASK 27-54-49-000-002) and (Ref. AMM TASK 27-54-49-400-002).
       3 for the flap track 3 actuator (Ref. AMM TASK 27-54-49-000-003) and (Ref. AMM TASK 27-54-49-400-003).
       4 for the flap track 4 actuator (Ref. AMM TASK 27-54-49-000-004) and (Ref. AMM TASK 27-54-49-400-004).
     (c) If you have installed a new flap actuator and the free movement of the lever arm (dimension X) is too much, do a check of the actuator lever splines:
       1 Remove the applicable lever:
       2 Do a check for wear of the actuator splines.
       3 Install a serviceable actuator lever:
     (d) Do a detailed dimensional check of the connection of the joint between the flap drive arm and the rotary actuator lever-arm:
       1 Remove the flap sufficiently to disconnect the applicable flap connections.
       2 Do the detailed dimensional check:
     (e) Do a detailed dimensional check of the flap attachments:
       1 Remove the applicable flap:
       2 Do a detailed dimensional check of the inboard flap attachments (Ref. AMM TASK 57-52-00-220-015).
       3 Do a detailed dimensional check of the outboard flap attachments (Ref. AMM TASK 57-53-00-220-023).
     (f) Do a detailed dimensional check of the flap carriage main rollers, the upper rollers and the pivot pins of lubrication blocks:
       1 Remove the applicable flap carriage:
       2 Do a detailed dimensional check of the No. 1 to 4 flap carriages in the workshop.
       3 Install the applicable serviceable flap carriage:
     (g) Do a detailed dimensional check of the Nos. 2, 3 and 4 flap track beams SRM 57513301.
     (h) Do a detailed dimensional check of the No. 1 flap track beam:
       1 Remove the No. 1 flap track beam (Ref. AMM TASK 57-51-33-000-001).
       2 Do a detailed dimensional check of the No. 1 flap track beam in the workshop.
       3 Install a serviceable No.1 flap track beam (Ref. AMM TASK 57-51-33-400-001).
     (i) Install a serviceable flap:
Subtask 27-54-00-420-050-D ** ON A/C NOT FOR ALL
E. Connect the Flap Drive Arms
F Flap to Rotary Actuator Drive Lever - To Disconnect the Inboard Flap ** ON A/C NOT FOR ALL
   (1) At the track 1 position:
     (a) Connect the flap drive arm to the rotary actuator drive-lever with the shearbolt (179), the washer (178) and the nut (177).
     (b) TORQUE the nut (177) to between 1.8 and 1.6 m.daN (13.27 and 11.80 lbf.ft ) T and safety with the new AIPC 27-54-05-33-035 COTTER PIN (176).
     (c) Install the indicator pin (180), the indicator plate (181), the washers (182) and the bolts (183).
     (d) TORQUE the bolts (183) to between 0.17 and 0.15 m.daN (15.04 and 13.27 lbf.in ) T.
   (2) At the track 2 position:
     (a) Connect the flap drive arm to the rotary actuator drive-lever with the bolt (184), the washer (185) and the nut (186).
     (b) TORQUE the nut (186) to between 1.8 and 1.2 m.daN (159.29 and 106.19 lbf.in ) T and safety with a new AIPC 27-54-05-33-025 COTTER PIN (187).
Subtask 27-54-00-420-050-E ** ON A/C NOT FOR ALL
E. Connect the Flap Drive Arms
F Flap to Rotary Actuator Drive Lever - To Disconnect the Inboard Flap ** ON A/C NOT FOR ALL
   (1) At the track 1 position:
     (a) Connect the flap drive arm to the rotary actuator drive-lever with the bolt (9), the washer (8) and the nut (7).
     (b) TORQUE the nut (7) to between 1.8 and 1.2 m.daN (159.29 and 106.19 lbf.in ) T and safety with the new AIPC 27-54-05-33-150 COTTER PIN (6).
     (c) Install the locking plate (4), the bolt (5), the washer (3) and the nut (2).
     (d) TORQUE the nut (2) to between 0.45 and 0.4 m.daN (39.82 and 35.40 lbf.in ) T and safety with the new AIPC 27-54-05-33-100 COTTER PIN (1).
   (2) At the track 2 position:
     (a) Connect the flap drive arm to the rotary actuator drive-lever with the bolt (18), the washer (17) and the nut (16).
     (b) TORQUE the nut (16) to between 1.8 and 1.2 m.daN (159.29 and 106.19 lbf.in ) T and safety with a new AIPC 27-54-05-33-030 COTTER PIN (15).
     (c) Install the locking plate (13), the bolt (14), the washer (12) and the nut (11).
     (d) TORQUE the nut (11) to between 0.45 and 0.4 m.daN (39.82 and 35.40 lbf.in ) T and safety with the new AIPC 27-54-05-33-200 COTTER PIN (10).
Subtask 27-54-00-420-050-F ** ON A/C NOT FOR ALL
E. Connect the Flap Drive Arms
F Flap to Rotary Actuator Drive Lever - To Disconnect the Inboard Flap ** ON A/C NOT FOR ALL
   (1) At the track 1 position:
     (a) Connect the flap drive arm to the rotary actuator drive-lever with the bolt (9), the washer (8) and the nut (7).
     (b) TORQUE the nut (7) to between 1.8 and 1.2 m.daN (159.29 and 106.19 lbf.in ) T and safety with the new AIPC 27-54-05-33-150 COTTER PIN (6) or AIPC 27-54-85-32-050 COTTER PIN (6).
     (c) Install the locking plate (4), the bolt (5), the washer (3) and the nut (2).
     (d) TORQUE the nut (2) to between 0.45 and 0.4 m.daN (39.82 and 35.40 lbf.in ) T and safety with the new AIPC 27-54-05-33-100 COTTER PIN (1) or AIPC 27-54-85-32-010 COTTER PIN (1).
   (2) At the track 2 position:
     (a) Connect the flap drive arm to the rotary actuator drive-lever with the bolt (18), the washer (17) and the nut (16).
     (b) TORQUE the nut (16) to between 2.3 and 1.8 m.daN (16.96 and 13.27 lbf.ft ) T and safety with a new AIPC 27-54-05-33-030 COTTER PIN (15) or AIPC 27-54-85-32-110 COTTER PIN (15).
     (c) Install the locking plate (13), the bolt (14), the washer (12) and the nut (11).
     (d) TORQUE the nut (11) to between 0.45 and 0.4 m.daN (39.82 and 35.40 lbf.in ) T and safety with the new AIPC 27-54-05-33-200 COTTER PIN (10) or AIPC 27-54-85-32-150 COTTER PIN (10).
Subtask 27-54-00-420-050-G ** ON A/C NOT FOR ALL
E. Connect the Flap Drive Arms
F Flap to Rotary Actuator Drive Lever - To Disconnect the Inboard Flap ** ON A/C NOT FOR ALL
   (1) At the track 1 position:
     (a) Connect the flap drive arm to the rotary actuator drive-lever with the bolt (141), the washer (144) and the nut (145).
     (b) TORQUE the nut (145) to between 6.0 and 5.5 m.daN (44.25 and 40.56 lbf.ft ) T and safety with the new AIPC 27-54-05-31-030 COTTER PIN (146) or AIPC 27-54-85-34-110 COTTER PIN (146).
   (2) At the track 2 position:
     (a) Connect the flap drive arm to the rotary actuator drive-lever with the bolt (401), the washer (403) and the nut (404).
     (b) TORQUE the nut (404) to between 12.0 and 10.0 m.daN (88.50 and 73.75 lbf.ft ) T and safety with a new AIPC 27-54-05-31-130 COTTER PIN (405) or AIPC 27-54-85-34-220 COTTER PIN (405).
     (c) Install the locking plate (402), the bolt (411), the washer (413) and the nut (414).
     (d) Tighten the nut (414) and safety with the new AIPC 27-54-05-31-090 COTTER PIN (415) or AIPC 27-54-85-34-110 COTTER PIN (415).
Subtask 27-54-00-420-053-C ** ON A/C NOT FOR ALL
F. Connect the Flap Drive Arms
F Flap to Rotary Actuator Drive Lever - To Disconnect the Outboard Flap ** ON A/C NOT FOR ALL
   (1) At the track 3 and track 4 positions:
     (a) Connect the flap drive arm to the rotary actuator drive-lever with the bolt (212), the washer (213) and the nut (214).
     (b) TORQUE the nut (214) to between 3.3 and 2.5 m.daN (24.34 and 18.44 lbf.ft ) T and safety with a new AIPC 27-54-05-35-130 COTTER PIN (215).
     (c) Install the locking plate (413), the bolt (412), the washer (414) and the nut (415).
     (d) TORQUE the nut (415) to between 0.45 and 0.4 m.daN (39.82 and 35.40 lbf.in ) T and safety with the new AIPC 27-54-05-35-080 COTTER PIN (416).
Subtask 27-54-00-420-053-D ** ON A/C NOT FOR ALL
F. Connect the Flap Drive Arms
F Flap to Rotary Actuator Drive Lever - To Disconnect the Outboard Flap ** ON A/C NOT FOR ALL
   (1) At the track 3 position:
     (a) Connect the flap drive arm to the rotary actuator drive-lever with the bolt (20), the washer (28) and the nut (27).
     (b) TORQUE the nut (27) to between 7.6 and 6.6 m.daN (56.05 and 48.67 lbf.ft ) T and safety with the new AIPC 27-54-05-32-090 COTTER PIN (26) or AIPC 27-54-85-35-220 COTTER PIN (26).
     (c) Install the locking plate (22), the bolt (21), the washer (23) and the nut (24).
     (d) Tighten the nut (24) and safety with the new AIPC 27-54-05-32-040 COTTER PIN (25) or AIPC 27-54-85-35-110 COTTER PIN (25).
   (2) At the track 4 position:
     (a) Connect the flap drive arm to the rotary actuator drive-lever with the bolt (29), the washer (32) and the nut (33).
     (b) TORQUE the nut (33) to between 2.2 and 1.95 m.daN (16.22 and 14.38 lbf.ft ) T and safety with the new AIPC 27-54-05-32-190 COTTER PIN (34) or AIPC 27-54-85-35-210 COTTER PIN (34).
     (c) Install the locking plate (31), the bolt (30), the washer (37) and the nut (36).
     (d) Tighten the nut (36) and safety with the new AIPC 27-54-05-32-140 COTTER PIN (35) or AIPC 27-54-85-35-020 COTTER PIN (35).
Subtask 27-54-00-420-053-E ** ON A/C NOT FOR ALL
F. Connect the Flap Drive Arms
F Flap to Rotary Actuator Drive Lever - To Disconnect the Outboard Flap ** ON A/C NOT FOR ALL
   (1) At the track 3 position:
     (a) Connect the flap drive arm to the rotary actuator drive-lever with the bolt (20), the washer (28) and the nut (27).
     (b) TORQUE the nut (27) to between 2.2 and 1.8 m.daN (16.22 and 13.27 lbf.ft ) T and safety with the new AIPC 27-54-05-35-130 COTTER PIN (26).
     (c) Install the locking plate (22), the bolt (21), the washer (23) and the nut (24).
     (d) TORQUE the nut (24) to between 0.45 and 0.4 m.daN (39.82 and 35.40 lbf.in ) T and safety with the new AIPC 27-54-05-35-080 COTTER PIN (25) or AIPC 27-54-85-33-110 COTTER PIN (25).
   (2) At the track 4 position:
     (a) Connect the flap drive arm to the rotary actuator drive-lever with the bolt (20), the washer (28) and the nut (27).
     (b) TORQUE the nut (27) to between 2.2 and 1.8 m.daN (16.22 and 13.27 lbf.ft ) T and safety with the new AIPC 27-54-05-35-130 COTTER PIN (26).
     (c) Install the locking plate (22), the bolt (21), the washer (23) and the nut (24).
     (d) TORQUE the nut (24) to between 0.45 and 0.4 m.daN (39.82 and 35.40 lbf.in ) T and safety with the new AIPC 27-54-05-35-080 COTTER PIN (25) or AIPC 27-54-85-33-110 COTTER PIN (25).
5. Close-up
Subtask 27-54-00-860-061-A ** ON A/C NOT FOR ALL
A. Aircraft 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) If applicable, connect the interconnecting strut (Ref. AMM TASK 27-51-44-400-001).
   (2) If applicable, install the flap kink seals (Ref. AMM TASK 27-54-61-400-006).
   (3) If applicable, retract the flaps fully (Ref. AMM TASK 27-50-00-866-009).
Subtask 27-54-00-860-061-B ** ON A/C NOT FOR ALL
A. Aircraft 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) Remove the 98D27504114000 DISTANCE GAUGE (60) and (64) and extend the flap tab by hand:
F Distance Gauges - Location and Detail ** ON A/C NOT FOR ALL
     (a) At the hinge 1A position:
       1 Remove the knurled screw (59) and the forward pin (58).
       2 Remove the rear pin (61) and the distance gage (60).
     (b) At the track 2 position:
       1 Remove the knurled screw (66) and the forward pin (65).
       2 Remove the knurled screw (63), the rear pin (62) and remove the distance gage (64).
   (2) If applicable, attach the tab-drive control-rod (46) to the track 2 carriage (41) (inboard flap):
F Details of the Tab Drive Control-Rod (Track 2) ** ON A/C NOT FOR ALL
     (a) Install the loose bush (42).
     (b) Move the tab sufficiently to install the tab drive control-rod (46) with the bolt (47).
     (c) Install the washer (43) and the nut (45).
     (d) TORQUE the nut (45) to between 1.4 and 0.8 m.daN (123.89 and 70.80 lbf.in ) T.
     (e) Safety the nut (45) with the new AIPC 27-54-46-22-095 COTTER PIN (44).
   (3) If applicable, install the tab drive control-rod (22) at the hinge 1A position (inboard flap):
F Details of the Hinge 1A Operating Mechanism ** ON A/C NOT FOR ALL
CAUTION: MAKE SURE THAT THE DISCONNECTED PARTS DO NOT TOUCH AND/OR CATCH THE ADJACENT STRUCTURE WHEN YOU MOVE THE FLAP. THIS WILL PREVENT DAMAGE TO THE WING.
     (a) Push the tab forward (at the inboard end) until the upper tab drive control-rod (22) is aligned with the bracket (26).
     (b) Install the bolt (27), the washer (28) and the nut (29).
     (c) TORQUE the nut (29) to between 2.4 and 2.2 m.daN (17.70 and 16.22 lbf.ft ) T.
     (d) Safety the nut (29) with the new AIPC 57-51-05-89-010 COTTER PIN (30).
   (4) For the outboard flap, remove the 98D27504115000 GAUGES-DISTANCE (115) and (112) and extend the flap tab by hand:
F Distance Gauges - Location and Detail ** ON A/C NOT FOR ALL
     (a) At the track 3 position, release the pins (113) and (114) and remove the distance gage (112).
     (b) At the track 4 position, release the pin (116) and remove the distance gage (115).
   (5) If applicable, connect the tab drive control-rod (82) at the track 3 position (outboard flap):
F Details of the Tab Drive Control-Rod (Track 3) ** ON A/C NOT FOR ALL
     (a) Install the loose bush (78).
     (b) Connect the control-rod (82) with the bolt (83).
     (c) Install the washer (79) and the nut (81).
     (d) TORQUE the nut (81) to between 2.7 and 1.4 m.daN (19.91 and 10.32 lbf.ft ) T.
     (e) Safety the nut (81) with the new AIPC 27-54-46-24-095 COTTER PIN (80).
   (6) If applicable, connect the tab drive control-rod (97) at the track 4 position (outboard flap):
F Details of the Tab Drive Control-Rod (Track 4) ** ON A/C NOT FOR ALL
     (a) Remove the nut (100) temporarily installed when you disconnected the tab drive control-rod (97).
     (b) Remove the hinge pin (96) sufficiently to let you connect the tab drive control-rod (97). Do not fully remove the hinge pin (96).
NOTE: If you fully remove the hinge pin (96) from the carriage (94), the roller bearing block (95) will fall out of alignment.
     (c) Install the loose bush (98).
     (d) Connect the tab drive control-rod (97) to the track 4 carriage with the hinge pin (96).
     (e) Install the washer (99) and the nut (100).
     (f) TORQUE the nut (100) to between 2.7 and 1.4 m.daN (19.91 and 10.32 lbf.ft ) T.
     (g) Safety the nut (100) with the new AIPC 27-54-46-26-280 COTTER PIN (101).
   (7) If applicable, install the Z-coupling:
F Details of the Z-Coupling ** ON A/C NOT FOR ALL
     (a) Retract the flaps to position 1 (Ref. AMM TASK 27-50-00-866-009).
     (b) Remove the Z-coupling lever (4) from the inboard flap attachment-bracket (5):
       1 Remove the nut (2), the washer (3), the bolt (10) and the lever (4).
       2 Remove the nut (7), the washer (8) and the spacer(s) (9).
     (c) Retract the flaps fully (Ref. AMM TASK 27-50-00-866-009).
     (d) Install the lever (4) with the same number of spacers (9) you removed between the levers (4) and (5).
     (e) Install the bolt (10).
     (f) Extend the flaps to the position 1 (Ref. AMM TASK 27-50-00-866-009).
     (g) Install the washer (3) and the nut (2).
     (h) TORQUE the nut (2) to between 1 and 0.9 m.daN (88.50 and 79.65 lbf.in ) T.
     (i) Safety the nut (2) with a new AIPC 57-52-23-03-270 COTTER PIN (1).
     (j) Retract the flaps to the O position (Ref. AMM TASK 27-50-00-866-009).
     (k) Install the remaining spacer(s) (9), the washer (8) and the nut (7).
     (l) TORQUE the nut (7) to between 3.6 and 3.1 m.daN (26.55 and 22.86 lbf.ft ) T.
     (m) Safety the nut (7) with a new AIPC 57-52-23-03-328 COTTER PIN (6).
   (8) If applicable, connect the interconnecting strut (Ref. AMM TASK 27-51-44-400-001).
   (9) If applicable, install the flap kink seals (Ref. AMM TASK 27-54-61-400-006).
   (10) If applicable, retract the flaps fully (Ref. AMM TASK 27-50-00-866-009).
Subtask 27-54-00-942-065-A
B. Removal of Equipment
   (1) Make sure that the work area is clean and clear of tools and other items.
   (2) Remove the safety barriers.
   (3) Remove the WARNING NOTICE(S).
   (4) Remove the access platform(s).
   (5) Remove the ground support and maintenance equipment, the special and standard tools and all other items.
[Rev.10 from 2021] 2026.03.31 23:53:07 UTC
"Aviabrain" 2025