DOC AIRBUS | AMM A320FInstallation of the Flap Track 2 Actuator
TASK 27-54-49-400-002-A
Installation of the Flap Track 2 Actuator
Self explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
B. Consumable Materials
C. Work Zones and Access Panels
D. Referenced Information
3. Job Set-up
Subtask 27-54-49-941-069-A
Subtask 27-54-49-420-081-A ** ON A/C NOT FOR ALL
Subtask 27-54-49-410-054-A
[Rev.10 from 2021]
2026.03.31 23:54:07 UTC
Installation of the Flap Track 2 Actuator
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.
WARNING:
BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.
CAUTION:
BE CAREFUL WHEN YOU DO MAINTENANCE TASKS ON THE WING TRAILING EDGE:
1. Reason for the Job- 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.
Self explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
| REFERENCE | QTY | DESIGNATION |
|---|---|---|
| No specific | AR | ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE |
| No specific | AR | CLAMPS |
| No specific | AR | ROD DIA 4 MM (0,157 IN) |
| No specific | AR | SAFETY BARRIER(S) |
| No specific | AR | WARNING NOTICE(S) |
| No specific | Torque wrench: range to between 3.0 and 2.8 m.daN (22.12 and 20.65 lbf.ft )  | |
| 98D27504030001 | 1 | LOCK-TORQUE SHAFT (FLAPS AND SLATS) WITH CLAMP-PIVOT |
| 98D27508002000 | 1 | SET-CARRIAGE STOP,FLAP |
| 98D27604000000 | 1 | COLLAR-SAFETY, SPOILER |
| 98D27604004000 | 1 | COLLAR SAFETY SPOILER |
| 98D27803000000 | 1 | LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION |
| REFERENCE | DESIGNATION |
|---|---|
| (Material No.03FDB1) | Mineral Oil base Grease-Anti-Fretting Paste - |
| (Material No.06AEA1) | Polysulfide Sealant-Low Adhesion Brushable - |
| (Material No.06AEB2) | Polysulfide Sealant-Low Adhesion Fillet Structure |
| (Material No.08BAA9) | Non Aqueous Cleaner-General - - |
| (Material No.12ACC1) | Corrosion Preventive Compound-Heavy Duty Soft Film - |
| (Material No.14SBA1) | Textile-Lint free Cotton - |
| ZONE/ACCESS | ZONE DESCRIPTION |
|---|---|
| 574 | FALSE SPAR BOX |
| 674 | FALSE SPAR BOX |
| FOR [6211CM] (FLAP ACTUATOR 2) | |
| 573AB, 573BB, 573CB, 575CB | |
| FOR [6261CM] (FLAP ACTUATOR 2) | |
| 673AB, 673BB, 673CB, 675CB | |
| REFERENCE | DESIGNATION |
|---|---|
| TASK 20-28-00-869-002-A | Table of the Maximum Permitted Resistance-Values |
| TASK 20-28-00-912-802-A | Electrical Bonding - General Maintenance Procedure |
| TASK 24-41-00-861-002-A | Energize the Aircraft Electrical Circuits from the External Power |
| TASK 24-41-00-861-002-A-01 | Energize the Aircraft Electrical Circuits from the APU |
| TASK 24-41-00-861-002-A-02 | Energize the Aircraft Electrical Circuits from Engine 1(2) |
| TASK 27-50-00-000-003-A | Removal of the Lock-Torque Shaft - Flaps and Slats (98D27504030001) |
| TASK 27-50-00-400-003-A | Installation of the Lock-Torque Shaft - Flaps and Slats (98D27504030001) |
| TASK 27-50-00-860-801-A | Readout of the Flap Position Pickoff Unit (PPU) Data |
| 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 27-51-44-820-001-A | Adjustment of the Interconnecting Strut |
| TASK 27-54-00-220-007-A | Check of the Flap Drive System |
| TASK 27-54-00-710-001-A | Operational Test of the Flap System |
| TASK 27-54-45-000-005-A | Removal of the Torque Shaft |
| TASK 27-54-45-400-005-A | Installation of the Torque Shaft |
| TASK 27-60-00-866-002-A | Extension-Retraction of the Spoilers for Maintenance |
| FOR [6211CM] (FLAP ACTUATOR 2) | |
| TASK 57-51-37-000-002-A | Removal of the Access Panels 571AB(671AB), 573AB(673AB), 573BB(673BB), 573CB(673CB), 573EB(673EB) |
| TASK 57-51-37-000-004-A | Removal of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) |
| TASK 57-51-37-400-002-A | Installation of the Access Panels 571AB(671AB), 573AB(673AB), 573BB(673BB), 573CB(673CB), 573EB(673EB) |
| TASK 57-51-37-400-004-A | Installation of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) |
| FOR [6261CM] (FLAP ACTUATOR 2) | |
| TASK 57-51-37-000-002-A | Removal of the Access Panels 571AB(671AB), 573AB(673AB), 573BB(673BB), 573CB(673CB), 573EB(673EB) |
| TASK 57-51-37-000-004-A | Removal of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) |
| TASK 57-51-37-400-002-A | Installation of the Access Panels 571AB(671AB), 573AB(673AB), 573BB(673BB), 573CB(673CB), 573EB(673EB) |
| TASK 57-51-37-400-004-A | Installation of the Access Panels 575AB(675AB), 575BB(675BB), 575CB(675CB), 575DB(675DB), 575EB(675EB), 575FB(675FB), 575GB(675GB), 575HB(675HB) |
Flap Track 2 ActuatorSubtask 27-54-49-941-069-A
A. Safety Precautions
(2) Make sure that the WARNING NOTICE(S) is in position to tell persons not to operate the flight controls.
Subtask 27-54-49-860-056-A WARNING:
BEFORE YOU START WORK, YOU MUST PUT ON A SAFETY HARNESS AND ATTACH IT TO THE ACCESS PLATFORM. WITHOUT A SAFETY HARNESS, YOU CAN FALL. THIS CAN KILL YOU OR CAUSE YOU INJURY.
(1) Make sure that the SAFETY BARRIER(S) are in position. (2) Make sure that the WARNING NOTICE(S) is in position to tell persons not to operate the flight controls.
B. Aircraft Maintenance Configuration
(2) Make sure that the 98D27803000000 LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION is on the flap/slat control lever in the cockpit.
(3) Make sure that the No. 1 spoiler is extended (Ref. AMM TASK 27-60-00-866-002).
(4) Make sure that the 98D27604000000 COLLAR-SAFETY, SPOILER or the 98D27604004000 COLLAR SAFETY SPOILER is on the piston rod of the servo-control.
(5) Make sure that the trailing edge of the flap is on a support.
(6) Make sure that the 98D27508002000 SET-CARRIAGE STOP,FLAP or the CLAMPS holds the carriage in position.
(7) Make sure that the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE is in position below the applicable access panel.
(8) Make sure that the applicable access panels are removed:
(a) FOR [6211CM] (FLAP ACTUATOR 2)
(b) FOR [6261CM] (FLAP ACTUATOR 2)
(9) Make sure that the 98D27504030001 LOCK-TORQUE SHAFT (FLAPS AND SLATS) WITH CLAMP-PIVOT are installed on the torque shafts (1) and (6) (Ref. AMM TASK 27-50-00-400-003).
(10) Make sure that the torque shaft (4) and the universal joint (3) are removed (Ref. AMM TASK 27-54-45-000-005).
Subtask 27-54-49-865-060-A 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 flaps are in position 3 (Ref. AMM TASK 27-50-00-866-008). (2) Make sure that the 98D27803000000 LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION is on the flap/slat control lever in the cockpit.
(3) Make sure that the No. 1 spoiler is extended (Ref. AMM TASK 27-60-00-866-002).
(4) Make sure that the 98D27604000000 COLLAR-SAFETY, SPOILER or the 98D27604004000 COLLAR SAFETY SPOILER is on the piston rod of the servo-control.
(5) Make sure that the trailing edge of the flap is on a support.
(6) Make sure that the 98D27508002000 SET-CARRIAGE STOP,FLAP or the CLAMPS holds the carriage in position.
(7) Make sure that the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE is in position below the applicable access panel.
(8) Make sure that the applicable access panels are removed:
(a) FOR [6211CM] (FLAP ACTUATOR 2)
(b) FOR [6261CM] (FLAP ACTUATOR 2)
(9) Make sure that the 98D27504030001 LOCK-TORQUE SHAFT (FLAPS AND SLATS) WITH CLAMP-PIVOT are installed on the torque shafts (1) and (6) (Ref. AMM TASK 27-50-00-400-003).
(10) Make sure that the torque shaft (4) and the universal joint (3) are removed (Ref. AMM TASK 27-54-45-000-005).
C. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:
4. Procedure| PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C NOT FOR ALL | |||
| 49VU | FLIGHT CONTROLS/FLP/CTL AND MONG/SYS1 | 6CV | B07 |
| ** ON A/C NOT FOR ALL | |||
| 49VU | FLIGHT CONTROLS/FLP/CTL AND MONG/SYS1 | 6CV | B02 |
| ** ON A/C ALL | |||
| 121VU | FLIGHT CONTROLS/FLP/CTL AND/MONG/SYS2 | 8CV | Q21 |
Subtask 27-54-49-420-081-A ** ON A/C NOT FOR ALL
A. General
(1) The flap actuator has an off-set gearbox and a rotary actuator. The rotary actuator is a vented unit filled with grease.
(2) It is normal for this grease to have some oil separation. The external surfaces of the rotary actuator may be moist with this separated oil as it is not a hermetically sealed unit. However, separated oil in the unit that touches the grease will be changed back during operation. The oil separation will decrease during in-service operation until the lubricant is in a condition that is stable. This is normal and will not cause damage to the unit.
Subtask 27-54-49-420-057-A (1) The flap actuator has an off-set gearbox and a rotary actuator. The rotary actuator is a vented unit filled with grease.
(2) It is normal for this grease to have some oil separation. The external surfaces of the rotary actuator may be moist with this separated oil as it is not a hermetically sealed unit. However, separated oil in the unit that touches the grease will be changed back during operation. The oil separation will decrease during in-service operation until the lubricant is in a condition that is stable. This is normal and will not cause damage to the unit.
B. Preparation for Installation
(2) Clean these items with a Textile-Lint free Cotton - (Material No.14SBA1) made moist with Non Aqueous Cleaner-General - - (Material No.08BAA9) :
(5) Make sure that the parts retained from the removed component are clean and in the correct condition.
Subtask 27-54-49-420-068-A ** ON A/C NOT FOR ALL CAUTION:
DO NOT APPLY MORE THAN ONE TYPE OF LUBRICANT.
GREASE AND ASSEMBLY PASTE DO NOT MIX.
(1) Clean the component interfaces and the adjacent area with a Textile-Lint free Cotton - (Material No.14SBA1) made moist with Non Aqueous Cleaner-General - - (Material No.08BAA9) . (2) Clean these items with a Textile-Lint free Cotton - (Material No.14SBA1) made moist with Non Aqueous Cleaner-General - - (Material No.08BAA9) :
- the internal splines of the flap drive lever
- the drive splines of the flap actuator
- the internal splines of the torque limiter
- the splines of the torque shaft (2)
- the splines of the universal joint (3).
- internal splines of the flap drive lever
- drive splines of the flap actuator
- internal splines of the torque limiter
- splines of the torque shaft (2)
- splines of the universal joint (3).
(5) Make sure that the parts retained from the removed component are clean and in the correct condition.
CAUTION:
DO NOT APPLY MORE THAN ONE TYPE OF LUBRICANT.
GREASE AND ASSEMBLY PASTE DO NOT MIX.
(6) Make sure that the surfaces of the items that follow are fully covered with a thin layer of Mineral Oil base Grease-Anti-Fretting Paste - (Material No.03FDB1) : - the drive splines of the actuator
- the internal splines of the flap drive lever
- the internal splines of the torque limiter.
C. Installation of the Flap Track 2 Actuator 6211CM(6261CM)
(a) Move the torque limiter away from the torque shaft (2).
(b) Put the universal joint (3) into the torque limiter.
(c) Turn the universal joint (3) until the bolt holes are aligned.
(d) Install the torque limiter on the torque shaft (2).
(e) Remove the universal joint (3).
(3) Put a countersunk washer (10) on a bolt (9), with the countersink adjacent to the head of the bolt.
(4) Install the bolt (9) with the countersunk washer (10), one or two (as applicable) of the washers (7) and one of the nuts (8) in the applicable hole (Ref. AMM TASK 20-28-00-912-802):
(a) FOR [6211CM] (FLAP ACTUATOR 2)
in the LH wing bonding position
(b) FOR [6261CM] (FLAP ACTUATOR 2)
in the RH wing bonding position.
(7) Install the longer bolt (12) through the lever stop (11), the structure and the actuator assembly.
(8) Install the washer(s) (7) and the nut (8) on the longer bolt (12). Do not tighten in this step.
(10) Install two of the washers (7) and a nut (8) on each of the bolts (9). Do not tighten in this step.
(11) TORQUE all the nuts (8) in a diagonally opposite sequence to between 3.0 and 2.8 m.daN (22.12 and 20.65 lbf.ft ).
(12) Do an electrical bonding check between the structure and the applicable bolt (Ref. AMM TASK 20-28-00-869-002):
(a) FOR [6211CM] (FLAP ACTUATOR 2)
in the LH wing bonding position
(b) FOR [6261CM] (FLAP ACTUATOR 2)
in the RH wing bonding position.
(13) Seal the bolt (9), the countersunk washer (10), the washer(s) (7) and the nut (8) installed in the applicable hole (Ref. AMM TASK 20-28-00-912-802):
(a) FOR [6211CM] (FLAP ACTUATOR 2)
in the LH wing bonding position
(b) FOR [6261CM] (FLAP ACTUATOR 2)
in the RH wing bonding position.
(14) Apply a layer of Corrosion Preventive Compound-Heavy Duty Soft Film - (Material No.12ACC1) to these remaining items:
(16) Put the ROD DIA 4 MM (0,157 IN) through the vent into each hole of the bearing to make sure the holes are not blocked.
(17) Close the bottom vent cover (13).
(18) Install the universal joint (3) and the torque shaft (4) (Ref. AMM TASK 27-54-45-400-005):
(a) FOR [6211CM] (FLAP ACTUATOR 2)
install 6210CM
(b) FOR [6261CM] (FLAP ACTUATOR 2)
install 6260CM.
Subtask 27-54-49-420-068-E ** ON A/C NOT FOR ALL CAUTION:
SUPPORT THE ACTUATOR, WHICH CAN WEIGH UP TO 10.5kg (23.2lbs). THIS WILL PREVENT DAMAGE TO THE RELATED STRUCTURE AND EQUIPMENT.
CAUTION:
DO A CHECK OF THE FLAP DRIVE SYSTEM AND/OR THE INTERCONNECTING STRUT AFTER YOU INSTALL A FLAP ROTARY ACTUATOR. INCORRECT ALIGNMENT CAN CAUSE A FLAP TO BECOME LOCKED.
(1) Do these steps together: - turn the actuator drive, as necessary, and engage the actuator drive into the flap drive lever
- install the torque limiter on the torque shaft (2).
(a) Move the torque limiter away from the torque shaft (2).
(b) Put the universal joint (3) into the torque limiter.
(c) Turn the universal joint (3) until the bolt holes are aligned.
(d) Install the torque limiter on the torque shaft (2).
(e) Remove the universal joint (3).
(3) Put a countersunk washer (10) on a bolt (9), with the countersink adjacent to the head of the bolt.
(4) Install the bolt (9) with the countersunk washer (10), one or two (as applicable) of the washers (7) and one of the nuts (8) in the applicable hole (Ref. AMM TASK 20-28-00-912-802):
(a) FOR [6211CM] (FLAP ACTUATOR 2)
in the LH wing bonding position
(b) FOR [6261CM] (FLAP ACTUATOR 2)
in the RH wing bonding position.
NOTE: Do not tighten in this step. Do not apply sealant.
(5) Apply a layer of Polysulfide Sealant-Low Adhesion Brushable - (Material No.06AEA1) or Polysulfide Sealant-Low Adhesion Fillet Structure (Material No.06AEB2) to these remaining items: - the shanks of the bolts (9) and (12).
(7) Install the longer bolt (12) through the lever stop (11), the structure and the actuator assembly.
(8) Install the washer(s) (7) and the nut (8) on the longer bolt (12). Do not tighten in this step.
NOTE: You must install the same number of washers (7) that you removed.
(9) Install the remaining bolts (9) through the actuator assembly and the structure. (10) Install two of the washers (7) and a nut (8) on each of the bolts (9). Do not tighten in this step.
(11) TORQUE all the nuts (8) in a diagonally opposite sequence to between 3.0 and 2.8 m.daN (22.12 and 20.65 lbf.ft )
. (12) Do an electrical bonding check between the structure and the applicable bolt (Ref. AMM TASK 20-28-00-869-002):
(a) FOR [6211CM] (FLAP ACTUATOR 2)
in the LH wing bonding position
(b) FOR [6261CM] (FLAP ACTUATOR 2)
in the RH wing bonding position.
(13) Seal the bolt (9), the countersunk washer (10), the washer(s) (7) and the nut (8) installed in the applicable hole (Ref. AMM TASK 20-28-00-912-802):
(a) FOR [6211CM] (FLAP ACTUATOR 2)
in the LH wing bonding position
(b) FOR [6261CM] (FLAP ACTUATOR 2)
in the RH wing bonding position.
(14) Apply a layer of Corrosion Preventive Compound-Heavy Duty Soft Film - (Material No.12ACC1) to these remaining items:
- the bolts (9) and (12)
- the washers (7) and (10)
- the nuts (8).
(16) Put the ROD DIA 4 MM (0,157 IN) through the vent into each hole of the bearing to make sure the holes are not blocked.
(17) Close the bottom vent cover (13).
(18) Install the universal joint (3) and the torque shaft (4) (Ref. AMM TASK 27-54-45-400-005):
(a) FOR [6211CM] (FLAP ACTUATOR 2)
install 6210CM
(b) FOR [6261CM] (FLAP ACTUATOR 2)
install 6260CM.
NOTE: If you install the related torque shaft, it is not necessary to extend the flaps fully. The flaps can stay in position 3.
C. Installation of the Flap Track 2 Actuator 6211CM(6261CM)
(a) Turn the actuator drive, as necessary, and engage the actuator drive into the flap drive lever.
(b) Install the torque limiter on the torque shaft (2).
(2) Do these steps if the bolt holes of the actuator assembly and the structure do not align:
(a) Move the torque limiter away from the torque shaft (2).
(b) Put the universal joint (3) into the torque limiter.
(c) Turn the universal joint (3) until the bolt holes are aligned.
(d) Install the torque limiter on the torque shaft (2).
(e) Remove the universal joint (3).
(3) Put a countersunk washer (10) on a bolt (9), with the countersink adjacent to the head of the bolt.
(4) Install the bolt (9), with the countersunk washer (10), washer (12) and nut (13) in the applicable hole (Ref. AMM TASK 20-28-00-912-802):
(a) FOR [6211CM] (FLAP ACTUATOR 2)
in the LH wing bonding position
(b) FOR [6261CM] (FLAP ACTUATOR 2)
in the RH wing bonding position.
(7) Install the longer bolt (14) through the lever stop (11), the structure and the actuator assembly.
(8) Install the washer (7) and the nut (8) on the longer bolt (14). Do not tighten in this step.
(9) Install the remaining bolts (9) through the actuator assembly and the structure.
(10) Install a washer (12) and a nut (13) on each of the bolts (9).
(11) TORQUE all the nuts (8) and (13) in a diagonally opposite sequence to between 3.0 and 2.8 m.daN (22.12 and 20.65 lbf.ft ).
(12) Do an electrical bonding check between the structure and the applicable bolt (Ref. AMM TASK 20-28-00-869-002):
(a) FOR [6211CM] (FLAP ACTUATOR 2)
in the LH wing bonding position
(b) FOR [6261CM] (FLAP ACTUATOR 2)
in the RH wing bonding position.
(13) Seal the bolt (9), the countersunk washer (10), washer (12) and nut (13) installed in the applicable hole (Ref. AMM TASK 20-28-00-912-802):
(a) FOR [6211CM] (FLAP ACTUATOR 2)
in the LH wing bonding position
(b) FOR [6261CM] (FLAP ACTUATOR 2)
in the RH wing bonding position.
(14) Apply a layer of Corrosion Preventive Compound-Heavy Duty Soft Film - (Material No.12ACC1) to these remaining items:
(a) FOR [6211CM] (FLAP ACTUATOR 2)
install 6210CM.
(b) FOR [6261CM] (FLAP ACTUATOR 2)
install 6260CM.
Subtask 27-54-49-080-053-A CAUTION:
SUPPORT THE ACTUATOR, WHICH CAN WEIGH UP TO 10.5kg (23.2lbs). THIS WILL PREVENT DAMAGE TO THE RELATED STRUCTURE AND EQUIPMENT.
CAUTION:
DO A CHECK OF THE FLAP DRIVE SYSTEM AND/OR THE INTERCONNECTING STRUT AFTER YOU INSTALL A FLAP ROTARY ACTUATOR. INCORRECT ALIGNMENT CAN CAUSE A FLAP TO BECOME LOCKED.
(1) Do these steps together: (a) Turn the actuator drive, as necessary, and engage the actuator drive into the flap drive lever.
(b) Install the torque limiter on the torque shaft (2).
(2) Do these steps if the bolt holes of the actuator assembly and the structure do not align:
(a) Move the torque limiter away from the torque shaft (2).
(b) Put the universal joint (3) into the torque limiter.
(c) Turn the universal joint (3) until the bolt holes are aligned.
(d) Install the torque limiter on the torque shaft (2).
(e) Remove the universal joint (3).
(3) Put a countersunk washer (10) on a bolt (9), with the countersink adjacent to the head of the bolt.
(4) Install the bolt (9), with the countersunk washer (10), washer (12) and nut (13) in the applicable hole (Ref. AMM TASK 20-28-00-912-802):
(a) FOR [6211CM] (FLAP ACTUATOR 2)
in the LH wing bonding position
(b) FOR [6261CM] (FLAP ACTUATOR 2)
in the RH wing bonding position.
NOTE: Do not tighten in this step. Do not apply sealant.
(5) Apply a layer of Polysulfide Sealant-Low Adhesion Brushable - (Material No.06AEA1) or Polysulfide Sealant-Low Adhesion Fillet Structure (Material No.06AEB2) to these remaining items: - the shanks of the bolts (9) and (14).
(7) Install the longer bolt (14) through the lever stop (11), the structure and the actuator assembly.
(8) Install the washer (7) and the nut (8) on the longer bolt (14). Do not tighten in this step.
(9) Install the remaining bolts (9) through the actuator assembly and the structure.
(10) Install a washer (12) and a nut (13) on each of the bolts (9).
(11) TORQUE all the nuts (8) and (13) in a diagonally opposite sequence to between 3.0 and 2.8 m.daN (22.12 and 20.65 lbf.ft )
. (12) Do an electrical bonding check between the structure and the applicable bolt (Ref. AMM TASK 20-28-00-869-002):
(a) FOR [6211CM] (FLAP ACTUATOR 2)
in the LH wing bonding position
(b) FOR [6261CM] (FLAP ACTUATOR 2)
in the RH wing bonding position.
(13) Seal the bolt (9), the countersunk washer (10), washer (12) and nut (13) installed in the applicable hole (Ref. AMM TASK 20-28-00-912-802):
(a) FOR [6211CM] (FLAP ACTUATOR 2)
in the LH wing bonding position
(b) FOR [6261CM] (FLAP ACTUATOR 2)
in the RH wing bonding position.
(14) Apply a layer of Corrosion Preventive Compound-Heavy Duty Soft Film - (Material No.12ACC1) to these remaining items:
- the bolts (9) and (14)
- the washers (7), (10), (12) and (15)
- the nuts (8) and (13).
(a) FOR [6211CM] (FLAP ACTUATOR 2)
install 6210CM.
(b) FOR [6261CM] (FLAP ACTUATOR 2)
install 6260CM.
NOTE: If you install the related torque shaft, it is not necessary to extend the flaps fully. The flaps can stay in position 3.
D. Removal of Support Equipment
(1) Remove the 98D27504030001 LOCK-TORQUE SHAFT (FLAPS AND SLATS) WITH CLAMP-PIVOT from the torque shafts (1) and (6) (Ref. AMM TASK 27-50-00-000-003).
(2) Remove the 98D27508002000 SET-CARRIAGE STOP,FLAP or the CLAMPS that holds the carriage in position.
(3) Remove the support from the flap trailing edge.
Subtask 27-54-49-740-075-A (1) Remove the 98D27504030001 LOCK-TORQUE SHAFT (FLAPS AND SLATS) WITH CLAMP-PIVOT from the torque shafts (1) and (6) (Ref. AMM TASK 27-50-00-000-003).
(2) Remove the 98D27508002000 SET-CARRIAGE STOP,FLAP or the CLAMPS that holds the carriage in position.
(3) Remove the support from the flap trailing edge.
E. Check of the Flap Drive System and of the Interconnecting Strut
(1) Do a check of the flap drive system (Ref. AMM TASK 27-54-00-220-007).
(2) Do the adjustment of the interconnecting strut (Ref. AMM TASK 27-51-44-820-001).
Subtask 27-54-49-865-084-A (1) Do a check of the flap drive system (Ref. AMM TASK 27-54-00-220-007).
(2) Do the adjustment of the interconnecting strut (Ref. AMM TASK 27-51-44-820-001).
DELETED
Subtask 27-54-49-740-062-A G. Check of the PPU Data
(1) Energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-861-002).
(2) Do the readout and check of the PPU data (Ref. AMM TASK 27-50-00-860-801).
Subtask 27-54-49-865-085-A (1) Energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-861-002).
(2) Do the readout and check of the PPU data (Ref. AMM TASK 27-50-00-860-801).
NOTE: The flaps can stay in position 1.
DELETED
Subtask 27-54-49-820-063-A I. Adjustment after Check of the PPU Data
(1) If the PPU data are not in the specified limits, do these steps:
(a) Disconnect the APPU and adjust the APPU input shaft.
(b) Do step (1)(a) again until the PPU data are in the specified limits.
Subtask 27-54-49-860-055-A (1) If the PPU data are not in the specified limits, do these steps:
(a) Disconnect the APPU and adjust the APPU input shaft.
(b) Do step (1)(a) again until the PPU data are in the specified limits.
J. Aircraft Maintenance Configuration
(2) Make sure that the applicable spoiler servo-control is in the 'O' (Operation) condition.
(3) Remove the 98D27803000000 LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION from the flap/slat control lever in the cockpit.
(4) Remove the 98D27604000000 COLLAR-SAFETY, SPOILER or 98D27604004000 COLLAR SAFETY SPOILER from the piston rod of the servo-control.
(5) Fully retract the flaps (Ref. AMM TASK 27-50-00-866-009).
(6) Make sure that the work area is clean and clear of tools and other items.
(7) Remove the access platform(s).
Subtask 27-54-49-865-061-A 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) Retract the No. 1 spoiler (Ref. AMM TASK 27-60-00-866-002). (2) Make sure that the applicable spoiler servo-control is in the 'O' (Operation) condition.
(3) Remove the 98D27803000000 LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION from the flap/slat control lever in the cockpit.
(4) Remove the 98D27604000000 COLLAR-SAFETY, SPOILER or 98D27604004000 COLLAR SAFETY SPOILER from the piston rod of the servo-control.
(5) Fully retract the flaps (Ref. AMM TASK 27-50-00-866-009).
(6) Make sure that the work area is clean and clear of tools and other items.
(7) Remove the access platform(s).
K. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):
Subtask 27-54-49-710-051-A 5. Close-up| PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C NOT FOR ALL | |||
| 49VU | FLIGHT CONTROLS/FLP/CTL AND MONG/SYS1 | 6CV | B07 |
| ** ON A/C NOT FOR ALL | |||
| 49VU | FLIGHT CONTROLS/FLP/CTL AND MONG/SYS1 | 6CV | B02 |
| ** ON A/C ALL | |||
| 121VU | FLIGHT CONTROLS/FLP/CTL AND/MONG/SYS2 | 8CV | Q21 |
Subtask 27-54-49-410-054-A
A. Close Access
(1) Install the applicable access panels:
(a) FOR [6211CM] (FLAP ACTUATOR 2)
install:
(b) FOR [6261CM] (FLAP ACTUATOR 2)
install:
Subtask 27-54-49-942-053-A (1) Install the applicable access panels:
(a) FOR [6211CM] (FLAP ACTUATOR 2)
install:
(b) FOR [6261CM] (FLAP ACTUATOR 2)
install:
B. Removal of Equipment
(1) Remove the safety barriers.
(2) Remove the WARNING NOTICE(S).
(3) Remove the ground support and maintenance equipment, the special and standard tools and all other items.
(1) Remove the safety barriers.
(2) Remove the WARNING NOTICE(S).
(3) Remove the ground support and maintenance equipment, the special and standard tools and all other items.