Removal of the Flap Track 1 Actuator

TASK 27-54-49-000-001-A
Removal of the Flap Track 1 Actuator

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.

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.

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	AR	SAFETY BARRIER(S)
No specific	AR	SAFETY CLIP - CIRCUIT BREAKER
No specific	AR	WARNING NOTICE(S)
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. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
734, 744
FOR [6205CM] (FLAP ACTUATOR 1)
193AB, 193BB, 573AB, 573BB
FOR [6255CM] (FLAP ACTUATOR 1)
194AB, 194BB, 673AB, 673BB

C. Referenced Information

REFERENCE	DESIGNATION
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 24-41-00-862-002-A	De-energize the Aircraft Electrical Circuits Supplied from the External Power
TASK 24-41-00-862-002-A-01	De-energize the Aircraft Electrical Circuits Supplied from the APU
TASK 24-41-00-862-002-A-02	De-energize the Aircraft Electrical Circuits Supplied from the Engine 1(2)
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 27-54-45-000-002-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
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 57-51-37-000-002-A	Removal of the Access Panels 571AB(671AB), 573AB(673AB), 573BB(673BB), 573CB(673CB), 573EB(673EB)
FOR [6255CM] (FLAP ACTUATOR 1)
TASK 57-51-37-000-002-A	Removal of the Access Panels 571AB(671AB), 573AB(673AB), 573BB(673BB), 573CB(673CB), 573EB(673EB)

3. Job Set-up
Subtask 27-54-49-941-050-A

A. Safety Precautions
(1) As necessary, use the applicable SAFETY BARRIERS, specified by the operator's instructions and your local regulations.
(2) Put a WARNING NOTICE(S) in position to tell persons not to operate the landing gear doors.

Subtask 27-54-49-860-050-A

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 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) Put the WARNING NOTICE(S) in position to tell persons not to operate the flaps.

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 27-54-49-480-050-A

A. Installation of Support Equipment
(1) Install the 98D27504030001 LOCK-TORQUE SHAFT (FLAPS AND SLATS) WITH CLAMP-PIVOT on the applicable torque shaft (Ref. AMM TASK 27-50-00-400-003).

Subtask 27-54-49-860-067-A

B. Readout of the PPU Data
(1) Energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-861-002).
(2) Do the readout of the PPU data (Ref. AMM TASK 27-50-00-860-801).

NOTE: Airbus recommends to do the readout and recording of the PPU angles before the maintenance action.
In case of a loss of the torque shaft fixture you can put the flap transmission system back to the initial condition (without a complete adjustment of the system).

(3) De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002).

Subtask 27-54-49-740-078-A

DELETED

Subtask 27-54-49-865-090-A

D. Open, safety and tag 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 27-54-49-010-067-A

E. Get Access
(1) Open the applicable MLG door (Ref. AMM TASK 32-12-00-010-001):
- for FIN 6205CM open 734
- for FIN 6255CM open 744.
(2) Put the ACCESS PLATFORM 3M (10 FT)- ADJUSTABLE in position below the applicable access panel.
(3) Remove the applicable access panels:
(a) FOR [6205CM] (FLAP ACTUATOR 1)
remove 193AB 193BB
remove 573AB 573BB (Ref. AMM TASK 57-51-37-000-002).
(b) FOR [6255CM] (FLAP ACTUATOR 1)
remove 194AB 194BB
remove 673AB 673BB (Ref. AMM TASK 57-51-37-000-002).

Subtask 27-54-49-020-057-A

F. Preparation for Removal of the Flap Track 1 Actuator
(1) Hold the trailing edge of the flap on a support.
(2) Use the 98D27508002000 SET-CARRIAGE STOP,FLAP or the CLAMPS to hold the carriage in position.

NOTE: This will make sure that the carriage does not move.

(3) Remove the torque shaft (1) (Ref. AMM TASK 27-54-45-000-003). Do not remove the plunging joint (2) from the actuator.
(4) Remove the torque shaft (4) and the universal joint (3) (Ref. AMM TASK 27-54-45-000-002).

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

Subtask 27-54-49-020-064-A ** ON A/C NOT FOR ALL

G. Removal 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.

(1) Remove the nuts (10), the bolts (8) and (9) and the countersunk washers (7).
(2) Turn the plunging joint (2) until the input bevel housing moves out of the hole in the sloping frame.
(3) Remove the plunging joint (2).
(4) Remove the actuator assembly from the flap drive lever and the aircraft.
(5) Prevent damage to the component interfaces and the adjacent area.

Subtask 27-54-49-020-064-B ** ON A/C NOT FOR ALL

G. Removal 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.

(1) Remove the nuts (9) the bolts (8) and the countersunk washers (7).
(2) Turn the plunging joint (2) until the input bevel housing moves out of the hole in the sloping frame.
(3) Remove the plunging joint (2).
(4) Remove the actuator assembly from the flap drive lever and the aircraft.
(5) Prevent damage to the component interfaces and the adjacent area.

Subtask 27-54-49-020-064-D ** ON A/C NOT FOR ALL

G. Removal 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.

Subtask 27-54-49-020-064-E ** ON A/C NOT FOR ALL

G. Removal 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.

(1) Remove the nuts (8) and the washers (7).
(2) Remove the bolts (5) and the countersunk washers (6).
(3) Turn the plunging joint (2) until the input bevel housing moves out of the hole in the sloping frame.
(4) Remove the plunging joint (2).
(5) Remove the actuator assembly from the flap drive lever and the aircraft.
(6) Prevent damage to the component interfaces and the adjacent area.

[Rev.10 from 2021] 2026.03.31 23:54:04 UTC