Installation of the Flap Track 1 Actuator

TASK 27-54-49-400-001-A
Installation of the Flap Track 1 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:

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.

FIN: 6205CM
FIN: 6255CM

1. Reason for the Job
Self explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment

REFERENCE	QTY	DESIGNATION
No specific	1	ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE
No specific	AR	CLAMPS
No specific	1	PIN DIA 4 MM (0,157 IN) - NON METALLIC
No specific	AR	SAFETY BARRIER(S)
No specific	AR	WARNING NOTICE(S)
No specific	Torque wrench: range to between 0.96 and 0.78 m.daN (84.96 and 69.03 lbf.in )
No specific	Torque wrench: range to between 3.0 and 2.5 m.daN (22.12 and 18.44 lbf.ft )
No specific	Torque wrench: range to between 3.0 and 2.8 m.daN (22.12 and 20.65 lbf.ft )
460005835	1	SLEEVE - GROUND LOCK
98D27504030001	1	LOCK-TORQUE SHAFT (FLAPS AND SLATS) WITH CLAMP-PIVOT
98D27508002000	1	SET-CARRIAGE STOP,FLAP
98D27803000000	1	LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION

B. Consumable Materials

REFERENCE	DESIGNATION
(Material No.03FDB1)	Mineral Oil base Grease-Anti-Fretting Paste -
(Material No.04QAB2)	Coating_- Flexible 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 -

C. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
193AB, 193BB, 194AB, 194BB, 573AB, 573BB, 673AB, 673BB

D. Referenced Information

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 27-54-45-000-002-A	Removal of the Torque Shaft
TASK 27-54-45-000-003-A	Removal of the Torque Shaft
TASK 32-12-00-010-001-A	Open the Main Gear Doors for Access
TASK 32-12-00-410-001-A	Close the Main Gear Doors after Access
TASK 57-51-37-000-002-A	Removal of the Access Panels 571AB(671AB), 573AB(673AB), 573BB(673BB), 573CB(673CB), 573EB(673EB)
TASK 57-51-37-400-002-A	Installation of the Access Panels 571AB(671AB), 573AB(673AB), 573BB(673BB), 573CB(673CB), 573EB(673EB)
Flap Track 1 Actuator ** ON A/C NOT FOR ALL
Flap Track 1 Actuator ** ON A/C NOT FOR ALL
Flap Track 1 Actuator ** ON A/C NOT FOR ALL
Flap Track 1 Actuator ** ON A/C NOT FOR ALL
FOR [6205CM] (FLAP ACTUATOR 1)
TASK 27-54-45-400-002-A	Installation of the Torque Shaft
TASK 27-54-45-400-003-A	Installation of the Torque Shaft
FOR [6255CM] (FLAP ACTUATOR 1)
TASK 27-54-45-400-002-A	Installation of the Torque Shaft
TASK 27-54-45-400-003-A	Installation of the Torque Shaft

3. Job Set-up
Subtask 27-54-49-941-067-A

A. Safety Precautions

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 SAFETY BARRIER(S) are in position.
(2) Make sure that the WARNING NOTICE(S) are in position to tell persons not to operate the flaps.
(3) Make sure that the WARNING NOTICE(S) are in position to tell persons not to operate the landing gear doors.

Subtask 27-54-49-860-054-A

B. Aircraft Maintenance Configuration
(1) Make sure that the flaps are in position 3 (Ref. AMM TASK 27-50-00-866-008).
(2) Make sure the 98D27803000000 LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION is on the flap/slat control lever in the cockpit.
(3) Make sure that the applicable MLG door is open (Ref. AMM TASK 32-12-00-010-001).
(4) Make sure that the 460005835 SLEEVE - GROUND LOCK is on the applicable MLG door actuator.
(5) Make sure that the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE is in position below the applicable access panel.
(6) Make sure that the flap trailing edge is on a support.
(7) Make sure that the 98D27508002000 SET-CARRIAGE STOP,FLAP or the CLAMPS holds the carriage in position.
(8) Make sure that the applicable access panels are removed (Ref. AMM TASK 57-51-37-000-002):
(a) For the LH wing:

193AB, 193BB, 573AB and 573BB.

(b) For the RH wing:

194AB, 194BB, 673AB and 673BB.

(9) Make sure that the 98D27504030001 LOCK-TORQUE SHAFT (FLAPS AND SLATS) WITH CLAMP-PIVOT is installed on the applicable torque shaft (Ref. AMM TASK 27-50-00-400-003).
(10) Make sure that the torque shaft (1) and (4) and the universal joint (3) are removed (Ref. AMM TASK 27-54-45-000-003) and (Ref. AMM TASK 27-54-45-000-002).

Subtask 27-54-49-865-058-A

C. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C NOT FOR ALL
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

4. Procedure

CAUTION: BE CAREFUL WHEN YOU DO MAINTENANCE TASKS ON THE WING TRAILING EDGE:

DO NOT CAUSE DAMAGE TO THE ELECTRICAL CABLE RACEWAYS.
DO NOT CAUSE DAMAGE TO THE ELECTRICAL CABLE INSTALLATIONS.
MAKE SURE THAT THE ELECTRICAL CABLES ARE INSTALLED CORRECTLY. INCORRECT INSTALLATION CAN CAUSE DAMAGE.

Subtask 27-54-49-560-052-A ** ON A/C NOT FOR ALL

A. Preparation for a Replacement Component
(1) The replacement assemblies of the actuator of flap track 1 are given in the Right Hand (RH) configuration. To change the replacement assemblies of the actuator of flap track 1 to the Left Hand (LH) configuration, do as follows:

CAUTION: DO NOT DISENGAGE THE TORQUE LIMITER AND THE ROTARY ACTUATOR FROM THE OFFSET GEARBOX WHEN YOU CHANGE THE CONFIGURATION FROM RIGHT TO LEFT. THESE ITEMS ARE NOT LRU'S AND ARE NOT INTERCHANGEABLE.

(a) Remove the bolts (6) and the washers (5).
(b) Keep the mating surface of the torque limiter attached to the offset gearbox.
(c) Turn the input bevel housing until the arrow (12) is aligned with the LH mark (11).

NOTE: The arrow (12) is on the input bevel housing and the LH mark (11) is on the offset gearbox.

(d) Install the bolts (6) and the washers (5).
(e) TORQUE the bolts (6) to between 0.96 and 0.78 m.daN (84.96 and 69.03 lbf.in )

.
(2) Make sure that the arrow (12) is aligned with the LH mark (11).

NOTE: The arrow and the mark for the LH unit are the same for the RH unit.

(3) Apply a layer of Corrosion Preventive Compound-Heavy Duty Soft Film - (Material No.12ACC1) to the bolts (6) and the washers (5).

Subtask 27-54-49-420-082-A ** ON A/C NOT FOR ALL

B. 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 27-54-49-420-050-A

C. Preparation for Installation
(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 input bevel gearbox and torque limiter
the splines of the universal joint (3) and the plunging joint (2).

(3) Do a visual inspection for the correct condition of:

the internal splines of the flap drive lever
the drive splines of the flap actuator
the internal splines of the input bevel gearbox and the torque limiter
the splines of the universal joint (3) and the plunging joint (2).

(4) Do an inspection of the component interfaces and the adjacent area.
(5) Make sure that the parts retained from the removed component are clean and in the correct condition.
(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 splines of the universal joint (3)
the splines of the plunging joint (2)
the internal splines of the flap drive lever
the drive splines of the actuator.

Subtask 27-54-49-420-054-A ** ON A/C NOT FOR ALL

D. Installation of the Flap Track 1 Actuator 6205CM(6255CM)

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) To align the actuator:
(a) Turn the actuator drive, as necessary, and engage the actuator drive in the flap drive lever.
(2) To install the actuator on the flap track:
(a) Put the plunging joint (2) into the torque limiter.
(b) Turn the plunging joint (2) until you can install the actuator assembly and the bolt holes align correctly.
(c) Remove the plunging joint (2).
(3) Put a countersunk washer (7) onto each of the bolts (8) and (9) with the countersink adjacent to the head of the bolt.
(4) Install one of the bolts (8) in the applicable bonding position (Ref. AMM TASK 20-28-00-912-802):
(a) FOR [6205CM] (FLAP ACTUATOR 1)
in the LH wing bonding position
(b) FOR [6255CM] (FLAP ACTUATOR 1)
in the RH wing bonding position.
(5) Install the remaining bolts (8) and (9) through the actuator and the flap track. Make sure you install the longer bolt (9) through the thickest part of the flap track.
(6) Install the nuts (10).
(7) TORQUE the nuts (10) in a diagonally opposite sequence to between 3.0 and 2.5 m.daN (22.12 and 18.44 lbf.ft )

.
(8) Do an electrical bonding check between the flap track 1 and the applicable bolt (Ref. AMM TASK 20-28-00-869-002):
(a) FOR [6205CM] (FLAP ACTUATOR 1)
in the LH wing bonding position
(b) FOR [6255CM] (FLAP ACTUATOR 1)
in the RH wing bonding position.
(9) Seal the applicable bolt (8), the countersunk washer (7) and the nut (10) in the bonding position (Ref. AMM TASK 20-28-00-912-802):
(a) FOR [6205CM] (FLAP ACTUATOR 1)
in the LH wing bonding position
(b) FOR [6255CM] (FLAP ACTUATOR 1)
in the RH wing bonding position.
(10) Apply a thin layer of Coating_- Flexible Structure (Material No.04QAB2) when the sealant you applied before is cured.
(11) Apply a layer of Corrosion Preventive Compound-Heavy Duty Soft Film - (Material No.12ACC1) to the remaining bolts (8) and (9), the countersunk washers (7) and the nuts (10).
(12) Install the plunging joint (2) and the universal joint (3) so that the flanges align with the torque shafts (1) and (4).
(13) Install the torque shafts (1) and (4):
(a) FOR [6205CM] (FLAP ACTUATOR 1)
install 6206CM (Ref. AMM TASK 27-54-45-400-003) and 6204CM (Ref. AMM TASK 27-54-45-400-002)
(b) FOR [6255CM] (FLAP ACTUATOR 1)
install 6256CM (Ref. AMM TASK 27-54-45-400-003) and 6254CM (Ref. AMM TASK 27-54-45-400-002).

NOTE: If you install the related torque shafts, it is not necessary to extend the flaps fully. The flaps can stay in position 3.

(14) Open the bottom of the two vent covers (12).
(15) Put the PIN DIA 4 MM (0,157 IN) - NON METALLIC through the vent into each hole of the bearing to make sure the holes are not blocked.
(16) Close the bottom vent cover (12).

Subtask 27-54-49-420-054-B ** ON A/C NOT FOR ALL

D. Installation of the Flap Track 1 Actuator 6205CM(6255CM)

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) To align the actuator:
(a) Turn the actuator drive, as necessary, and engage the actuator drive in the flap drive lever.
(2) To install the actuator on the flap track:
(a) Put the plunging joint (2) into the torque limiter.
(b) Turn the plunging joint (2) until you can install the actuator assembly and the bolt holes align correctly.
(c) Remove the plunging joint (2).
(3) Put a countersunk washer (7) onto each of the bolts (8). Make sure that the countersink is adjacent to the head of the bolt.
(4) Install one of the bolts (8) in the applicable bonding position (Ref. AMM TASK 20-28-00-912-802):
(a) FOR [6205CM] (FLAP ACTUATOR 1)
in the LH wing bonding position
(b) FOR [6255CM] (FLAP ACTUATOR 1)
in the RH wing bonding position.
(5) Install the remaining bolts (8) through the actuator and the flap track.
(6) Install the nuts (9).
(7) TORQUE the nuts (9) in a diagonally opposite sequence to between 3.0 and 2.5 m.daN (22.12 and 18.44 lbf.ft )

.
(8) Do an electrical bonding check between the flap track 1 and the applicable bolt (Ref. AMM TASK 20-28-00-869-002):
(a) FOR [6205CM] (FLAP ACTUATOR 1)
in the LH wing bonding position
(b) FOR [6255CM] (FLAP ACTUATOR 1)
in the RH wing bonding position.
(9) Seal the applicable bolt (8), the countersunk washer (7) and the nut (9) in the bonding position (Ref. AMM TASK 20-28-00-912-802):
(a) FOR [6205CM] (FLAP ACTUATOR 1)
in the LH wing bonding position
(b) FOR [6255CM] (FLAP ACTUATOR 1)
in the RH wing bonding position.
(10) Apply a thin layer of Coating_- Flexible Structure (Material No.04QAB2) when the sealant you applied before is cured.
(11) Apply a layer of Corrosion Preventive Compound-Heavy Duty Soft Film - (Material No.12ACC1) to the remaining bolts (8), the countersunk washers (7) and the nuts (9).
(12) Install the plunging joint (2) and the universal joint (3) so that the flanges align with the torque shafts (1) and (4).
(13) Install the torque shafts (1) and (4):
(a) FOR [6205CM] (FLAP ACTUATOR 1)
install 6206CM (Ref. AMM TASK 27-54-45-400-003) and 6204CM (Ref. AMM TASK 27-54-45-400-002)
(b) FOR [6255CM] (FLAP ACTUATOR 1)
install 6256CM (Ref. AMM TASK 27-54-45-400-003) and 6254CM (Ref. AMM TASK 27-54-45-400-002).

NOTE: If you install the related torque shafts, it is not necessary to extend the flaps fully. The flaps can stay in position 3.

(14) Open the bottom vent cover (11).
(15) Put the PIN DIA 4 MM (0,157 IN) - NON METALLIC through the vent into each hole of the bearing to make sure the holes are not blocked.
(16) Close the bottom vent cover (11).

Subtask 27-54-49-420-054-D ** ON A/C NOT FOR ALL

D. Installation of the Flap Track 1 Actuator 6205CM(6255CM)

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) To align the actuator:
(a) Turn the actuator drive, as necessary, and engage the actuator drive in the flap drive lever.
(2) To install the actuator on the flap track:
(a) Put the plunging joint (2) into the torque limiter.
(b) Turn the plunging joint (2) until you can install the actuator assembly and the bolt holes align correctly.
(c) Remove the plunging joint (2).
(3) Put a countersunk washer (7) onto each of the four bolts (8). Make sure that the countersink is adjacent to the head of the bolt.
(4) Install one of the bolts (8) in the applicable bonding position (Ref. AMM TASK 20-28-00-912-802):
(a) FOR [6205CM] (FLAP ACTUATOR 1)
in the LH wing bonding position
(b) FOR [6255CM] (FLAP ACTUATOR 1)
in the RH wing bonding position.
(5) Install the remaining bolts (8) through the actuator and the flap track.
(6) Install the nuts (9).
(7) TORQUE the nuts (9) in a diagonally opposite sequence to between 3.0 and 2.5 m.daN (22.12 and 18.44 lbf.ft )

.
(8) Do an electrical bonding check between the flap track 1 and the applicable bolt (Ref. AMM TASK 20-28-00-869-002):
(a) FOR [6205CM] (FLAP ACTUATOR 1)
in the LH wing bonding position
(b) FOR [6255CM] (FLAP ACTUATOR 1)
in the RH wing bonding position.
(9) Seal the applicable bolt (8), the countersunk washer (7) and the nut (9) in the bonding position (Ref. AMM TASK 20-28-00-912-802):
(a) FOR [6205CM] (FLAP ACTUATOR 1)
in the LH wing bonding position
(b) FOR [6255CM] (FLAP ACTUATOR 1)
in the RH wing bonding position.
(10) Apply a thin layer of Coating_- Flexible Structure (Material No.04QAB2) when the sealant you applied before is cured.
(11) Apply a layer of Corrosion Preventive Compound-Heavy Duty Soft Film - (Material No.12ACC1) to the remaining bolts (8) the countersunk washers (7) and the nuts (9).
(12) Install the plunging joint (2) and the universal joint (3) so that the flanges align with the torque shafts (1) and (4).
(13) Install the torque shafts (1) and (4):
(a) FOR [6205CM] (FLAP ACTUATOR 1)
install 6206CM (Ref. AMM TASK 27-54-45-400-003) and 6204CM (Ref. AMM TASK 27-54-45-400-002)
(b) FOR [6255CM] (FLAP ACTUATOR 1)
install 6256CM (Ref. AMM TASK 27-54-45-400-003) and 6254CM (Ref. AMM TASK 27-54-45-400-002).

NOTE: If you install the related torque shafts, it is not necessary to extend the flaps fully. The flaps can stay in position 3.

Subtask 27-54-49-420-054-F ** ON A/C NOT FOR ALL

D. Installation of the Flap Track 1 Actuator 6205CM(6255CM)

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) To align the actuator:
(a) Turn the actuator drive, as necessary, and engage the actuator drive in the flap drive lever.
(2) To install the actuator on the flap track:
(a) Put the plunging joint (2) into the torque limiter.
(b) Turn the plunging joint (2) until you can install the actuator assembly and the bolt holes align correctly.
(c) Remove the plunging joint (2).
(3) Put a countersunk washer (6) onto each of the five bolts (5).
(a) Make sure that the countersink is adjacent to the head of the bolt (5).
(4) Install one of the bolts (5) in the applicable bonding position (Ref. AMM TASK 20-28-00-912-802):
(a) FOR [6205CM] (FLAP ACTUATOR 1)
in the LH wing bonding position
(b) FOR [6255CM] (FLAP ACTUATOR 1)
in the RH wing bonding position.
(5) Install the remaining bolts (5) through the actuator and the flap track.
(6) Install the washers (7) and the nuts (8) on the bolts (5).
(7) TORQUE the nuts (8) in a diagonally opposite sequence to between 3.0 and 2.8 m.daN (22.12 and 20.65 lbf.ft )

.
(8) Do a check of the electrical bonding between the flap track 1 and the applicable bolt (Ref. AMM TASK 20-28-00-869-002):
(a) FOR [6205CM] (FLAP ACTUATOR 1)
in the LH wing bonding position
(b) FOR [6255CM] (FLAP ACTUATOR 1)
in the RH wing bonding position.
(9) Seal the applicable bolt (5), the countersunk washer (6), the washer (7) and the nut (8) in the bonding position (Ref. AMM TASK 20-28-00-912-802):
(a) FOR [6205CM] (FLAP ACTUATOR 1)
in the LH wing bonding position
(b) FOR [6255CM] (FLAP ACTUATOR 1)
in the RH wing bonding position.
(10) Apply a thin layer of Coating_- Flexible Structure (Material No.04QAB2) when the sealant you applied before is cured.
(11) Apply a layer of Corrosion Preventive Compound-Heavy Duty Soft Film - (Material No.12ACC1) to the remaining bolts (5), the countersunk washers (6), the washers (7) and the nuts (8).
(12) Install the plunging joint (2) and the universal joint (3) so that the flanges align with the torque shafts (1) and (4).
(13) Install the torque shafts (1) and (4):
(a) FOR [6205CM] (FLAP ACTUATOR 1)
install 6206CM (Ref. AMM TASK 27-54-45-400-003) and 6204CM (Ref. AMM TASK 27-54-45-400-002)
(b) FOR [6255CM] (FLAP ACTUATOR 1)
install 6256CM (Ref. AMM TASK 27-54-45-400-003) and 6254CM (Ref. AMM TASK 27-54-45-400-002).

NOTE: If you install the related torque shafts, it is not necessary to extend the flaps fully. The flaps can stay in position 3.

Subtask 27-54-49-080-050-A

E. Removal of Support Equipment
(1) Remove the 98D27504030001 LOCK-TORQUE SHAFT (FLAPS AND SLATS) WITH CLAMP-PIVOT from the applicable torque shaft (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 27-54-49-740-074-A

F. Check of the Flap Drive System and/or 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 27-54-49-740-063-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).

NOTE: The flaps can stay in position 1.

Subtask 27-54-49-820-060-A

H. 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 27-54-49-860-059-A

I. Aircraft Maintenance Configuration
(1) Remove the 98D27803000000 LOCKING TOOL-FLAP SLAT LEVER,INT. POSITION from the flap/slat control lever in the cockpit.
(2) Make sure that the work area is clean and clear of tools and other items.
(3) Remove the access platform(s).

Subtask 27-54-49-865-059-A

J. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C NOT FOR ALL
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 27-54-49-710-050-A

K. Test
(1) Fully retract the flaps (Ref. AMM TASK 27-50-00-866-009).
(2) Do an operational test of the flaps (Ref. AMM TASK 27-54-00-710-001).

5. Close-up
Subtask 27-54-49-410-051-A

A. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Install the applicable access panels:
(a) For the LH wing, install

(b) For the RH wing, install

(3) Close the applicable MLG door (Ref. AMM TASK 32-12-00-410-001).

Subtask 27-54-49-942-051-A

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.

[Rev.10 from 2021] 2026.03.31 23:54:05 UTC