Removal of the Type A Actuators

TASK 27-84-48-000-001-A
Removal of the Type A Actuators

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.

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.

ZONE: 521
ZONE: 621
FIN: 6013CM
FIN: 6015CM
FIN: 6063CM
FIN: 6065CM

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

REFERENCE	QTY	DESIGNATION
No specific	AR	ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE
No specific	AR	SAFETY BARRIER(S)
No specific	AR	SAFETY CLIP - CIRCUIT BREAKER
No specific	AR	WARNING NOTICE(S)
98D27504030001	2	LOCK-TORQUE SHAFT (FLAPS AND SLATS) WITH CLAMP-PIVOT
98D27803500001	1	LOCKING TOOL ZERO POS
98D27803500002	1	LOCKING TOOL ZERO POS
98D27804006000	AR	TOOL-ALIGNMENT AND LOCKING (SLAT TRACKS 2 AND 3)

B. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
521	INBOARD FIXED L.E STRUCTURE
621	INBOARD FIXED L.E STRUCTURE

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 27-80-00-860-801-A	Readout of the Slat Position Pickoff Unit (PPU) Data
TASK 27-80-00-866-005-A	Retracting the Slats on the Ground
TASK 27-84-45-000-005-A	Removal of the Torque Shaft
TASK 27-84-45-000-006-A	Removal of the Torque Shafts
TASK 27-84-45-000-007-A	Removal of the Torque Shafts
Type A Actuators - Slat Power Transmission ** ON A/C NOT FOR ALL
Type A Actuators - Slat Power Transmission ** ON A/C NOT FOR ALL

3. Job Set-up
Subtask 27-84-48-941-051-A

A. Safety Precautions

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) As necessary, use the applicable SAFETY BARRIERS, specified by the operator's instructions and your local regulations.
(2) Put a WARNING NOTICE(S) in the cockpit to tell persons not to operate the slat controls.

Subtask 27-84-48-860-051-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) Retract the slats fully (Ref. AMM TASK 27-80-00-866-005).
(2) Install the 98D27803500001 LOCKING TOOL ZERO POS or 98D27803500002 LOCKING TOOL ZERO POS on the flap/slat control lever on panel 114VU.

Subtask 27-84-48-740-052-A

C. Readout of the PPU Data
(1) Energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-861-002).
(a) Do the readout of the PPU data (Ref. AMM TASK 27-80-00-860-801).

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 slat transmission system back to the initial condition (without a complete adjustment of the system).

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

Subtask 27-84-48-865-051-A

D. Open, safety and tag this(these) circuit breaker(s):

PANEL	DESIGNATION	FIN	LOCATION
** ON A/C NOT FOR ALL
49VU	FLIGHT CONTROLS/SLT/CTL AND MONG/SYS1	5CV	B06
** ON A/C NOT FOR ALL
49VU	FLIGHT CONTROLS/SLT/CTL AND MONG/SYS1	5CV	B01
** ON A/C ALL
121VU	FLIGHT CONTROLS/SLT/CTL/SYS2	7CV	R21

Subtask 27-84-48-010-050-A

E. Get Access
(1) Put an ACCESS PLATFORM 4M (13 FT)-ADJUSTABLE below the applicable torque shaft.
(2) Remove the applicable torque shaft (1) (Ref. AMM TASK 27-84-45-000-005) and (Ref. AMM TASK 27-84-45-000-007):
(a) FOR [6013CM] (SLAT ACTUATOR TYPE A)
remove the torque shaft FIN 6012CM
(b) FOR [6063CM] (SLAT ACTUATOR TYPE A)
remove the torque shaft FIN 6062CM.
(c) FOR [6015CM] (SLAT ACTUATOR TYPE A)
remove the torque shaft FIN 6016CM.
(d) FOR [6065CM] (SLAT ACTUATOR TYPE A)
remove the torque shaft FIN 6066CM.
(3) Remove the applicable torque shaft (3) (Ref. AMM TASK 27-84-45-000-006):
(a) FOR [6013CM] (SLAT ACTUATOR TYPE A)
remove the torque shaft FIN 6014CM.
(b) FOR [6015CM] (SLAT ACTUATOR TYPE A)
remove the torque shaft FIN 6014CM.
(c) FOR [6063CM] (SLAT ACTUATOR TYPE A)
remove the torque shaft FIN 6064CM.
(d) FOR [6065CM] (SLAT ACTUATOR TYPE A)
remove the torque shaft FIN 6064CM.
(4) Make sure that a 98D27504030001 LOCK-TORQUE SHAFT (FLAPS AND SLATS) WITH CLAMP-PIVOT is installed (Ref. AMM TASK 27-50-00-400-003) as follows :

On the torque shaft inboard of the removed component
On the torque shaft ouboard of the removed component.

4. Procedure
Subtask 27-84-48-020-050-A

A. Removal of the Type A Actuator
(1) Hold the actuator (2) and remove the bolts (4) and washers (5).
(2) Remove the actuator (2).
(3) If you remove the two actuators (2) from the slat, install a 98D27804006000 TOOL-ALIGNMENT AND LOCKING (SLAT TRACKS 2 AND 3) in each pinion after each actuator (2) is removed. This will prevent movement of the slat.

[Rev.10 from 2021] 2026.04.01 07:08:38 UTC