Installation of the Torque Shaft

TASK 27-84-45-400-004-A
Installation of the Torque Shaft

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.

FIN: 6008CM
FIN: 6058CM

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	SAFETY BARRIER(S)
No specific	AR	WARNING NOTICE(S)
No specific	Torque wrench: range to between 1.24 and 1.02 m.daN (109.73 and 90.27 lbf.in )
98D27504030001	2	LOCK-TORQUE SHAFT (FLAPS AND SLATS) WITH CLAMP-PIVOT

B. Consumable Materials

REFERENCE	DESIGNATION
(Material No.03FDB1)	Mineral Oil base Grease-Anti-Fretting Paste -
(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
191BB, 192FB

D. Referenced Information

REFERENCE	DESIGNATION
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 27-80-00-866-005-A	Retracting the Slats on the Ground
TASK 27-84-44-000-001-A	Removal of the Steady Bearing
TASK 27-84-44-400-001-A	Installation of the Steady Bearing
TASK 53-35-13-000-002-A	Removal of the Quick-Release Access Panels from the Belly Fairing Structure
TASK 53-35-13-400-002-A	Installation of the Quick-Release Access Panels on the Belly Fairing Structure
Torque shafts - Slat Power Transmission
Torque Shafts - Slat Power Transmission

3. Job Set-up
Subtask 27-84-45-941-060-A

A. Safety Precautions
(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 slat controls.

Subtask 27-84-45-860-053-A

B. Aircraft Maintenance Configuration
(1) Make sure that the slats are fully retracted (Ref. AMM TASK 27-80-00-866-005).
(2) Make sure that the 98D27803500001 LOCKING TOOL ZERO POS or 98D27803500002 LOCKING TOOL ZERO POS is installed on the flap/slat control lever on panel 114VU.
(3) Make sure that a 98D27504030001 LOCK-TORQUE SHAFT (FLAPS AND SLATS) WITH CLAMP-PIVOT is installed (Ref. AMM TASK 27-50-00-400-003):

on the torque shaft, inboard of the applicable component
on the torque shaft, outboard of the applicable component.

(4) Make sure that the applicable steady bearing (15) is removed (Ref. AMM TASK 27-84-44-000-001).
(5) Make sure that the applicable access panel 191BB, 192FB is removed (Ref. AMM TASK 53-35-13-000-002).

Subtask 27-84-45-865-063-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/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

4. Procedure
Subtask 27-84-45-420-068-A

A. Preparation for Installation
(1) Clean the component interface and/or the adjacent area with a Textile-Lint free Cotton - (Material No.14SBA1) made moist with Non Aqueous Cleaner-General - - (Material No.08BAA9) .
(2) Do an inspection of the component interfaces and the adjacent area.
(3) Make sure that the parts retained from the removed component are clean and in the correct condition.
(4) Apply a thin layer of Mineral Oil base Grease-Anti-Fretting Paste - (Material No.03FDB1) to the torque shaft splines.

Subtask 27-84-45-420-069-A

B. Installation of the Torque Shaft 6008CM(6058CM)
(1) Put the retaining ring (18) in position over the shaft (14).
(2) Install the universal joint (13) and attach it with the pin (12) and the retaining ring (18).
(3) Install the shaft (14) and attach it with the bolts (17) and the nuts (16).
(4) TORQUE the nuts (16) to between 1.24 and 1.02 m.daN (109.73 and 90.27 lbf.in )

.
(5) Apply a layer of Corrosion Preventive Compound-Heavy Duty Soft Film - (Material No.12ACC1) to the:

nuts (16)
bolts (17)
flange of the universal joint (13)
flange of the shaft (14).

(6) Install the applicable steady bearing (15) (Ref. AMM TASK 27-84-44-400-001):
(a) FOR [6008CM] (SLAT XMSN TORQUE SHAFT)
install the steady bearing 6007CM
(b) FOR [6058CM] (SLAT XMSN TORQUE SHAFT)
install the steady bearing 6057CM.
(7) Make sure that:

you cannot see the spline engagement groove at the movable joint
the dimension A is a minimum of 6.5 mm (0.2559 in.) at the movable joint.

(8) Remove the 98D27504030001 LOCK-TORQUE SHAFT (FLAPS AND SLATS) WITH CLAMP-PIVOT (Ref. AMM TASK 27-50-00-000-003):

from the torque shaft inboard of the applicable component
from the torque shaft outboard of the applicable component.

Subtask 27-84-45-865-098-A

C. 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/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 27-84-45-710-058-A

D. Test
(1) The operational test of the slat power-transmission system is contained in the installation of the steady bearing (Ref. AMM TASK 27-84-44-400-001).

5. Close-up
Subtask 27-84-45-410-060-A

A. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Install the access panels 191BB 192FB (Ref. AMM TASK 53-35-13-400-002).

Subtask 27-84-45-942-052-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] 2026.04.01 07:07:45 UTC