DOC AIRBUS | AMM A320FInstallation of the Torque Shaft
TASK 27-84-45-400-012-A
Installation of the Torque Shaft
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 27-84-45-941-068-A
Subtask 27-84-45-420-083-A
Subtask 27-84-45-865-089-A
[Rev.10 from 2021]
2026.03.31 23:57:26 UTC
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.
1. Reason for the JobSelf 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 | SAFETY CLIP - CIRCUIT BREAKER |
| 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 |
| 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 - |
| ZONE/ACCESS | ZONE DESCRIPTION |
|---|---|
| FOR [6032CM] (SLAT XMSN TORQUE SHAFT) | |
| 522FB | |
| FOR [6082CM] (SLAT XMSN TORQUE SHAFT) | |
| 622FB | |
| 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 27-84-44-000-006-A | Removal of the Steady Bearing |
| TASK 27-84-44-400-004-A | Installation of the Steady Bearing |
| TASK 27-84-44-400-006-A | Installation of the Steady Bearing |
Torque shafts - Slat Power TransmissionSubtask 27-84-45-941-068-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 27-84-45-860-061-A (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.
B. Aircraft Maintenance Configuration
(1) Make sure that the access platform is in position below the applicable access panel 522FB(622FB).
(2) Make sure that the applicable access panel 522FB(622FB) is removed.
(3) Make sure that the applicable steady bearing has been removed (Ref. AMM TASK 27-84-44-000-006).
(4) Make sure that the slats are retracted fully (Ref. AMM TASK 27-80-00-866-005).
(5) 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.
(6) Make sure that a 98D27504030001 LOCK-TORQUE SHAFT (FLAPS AND SLATS) WITH CLAMP-PIVOT is installed (Ref. AMM TASK 27-50-00-400-003):
Subtask 27-84-45-865-088-A (1) Make sure that the access platform is in position below the applicable access panel 522FB(622FB).
(2) Make sure that the applicable access panel 522FB(622FB) is removed.
(3) Make sure that the applicable steady bearing has been removed (Ref. AMM TASK 27-84-44-000-006).
(4) Make sure that the slats are retracted fully (Ref. AMM TASK 27-80-00-866-005).
(5) 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.
(6) 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 removed component
- on the torque shaft, outboard of the removed component.
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/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 27-84-45-420-083-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 27-84-45-420-084-A (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.
B. Installation of the Torque Shaft 6032CM(6082CM)
(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:
(a) FOR [6032CM] (SLAT XMSN TORQUE SHAFT)
install the steady bearing 6031CM
(b) FOR [6082CM] (SLAT XMSN TORQUE SHAFT)
install the steady bearing 6081CM.
(7) Make sure that:
Subtask 27-84-45-865-103-A (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).
(a) FOR [6032CM] (SLAT XMSN TORQUE SHAFT)
install the steady bearing 6031CM
(b) FOR [6082CM] (SLAT XMSN TORQUE SHAFT)
install the steady bearing 6081CM.
(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.
- from the torque shaft, inboard of the applicable components
- from the torque shaft, outboard of the applicable components.
C. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):
Subtask 27-84-45-710-061-A | 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 |
D. Test
(1) The operational test of the slat power transmission system is contained in the installation of the steady bearing (Ref. AMM TASK 27-84-44-400-004).
5. Close-up(1) The operational test of the slat power transmission system is contained in the installation of the steady bearing (Ref. AMM TASK 27-84-44-400-004).
Subtask 27-84-45-865-089-A
A. Open, safety and tag this(these) circuit breaker(s):
Subtask 27-84-45-410-058-A | 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 |
B. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Install the applicable access panel:
(a) FOR [6032CM] (SLAT XMSN TORQUE SHAFT)
install 522FB
(b) FOR [6082CM] (SLAT XMSN TORQUE SHAFT)
install 622FB.
Subtask 27-84-45-865-090-A (1) Make sure that the work area is clean and clear of tools and other items.
(2) Install the applicable access panel:
(a) FOR [6032CM] (SLAT XMSN TORQUE SHAFT)
install 522FB
(b) FOR [6082CM] (SLAT XMSN TORQUE SHAFT)
install 622FB.
C. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):
Subtask 27-84-45-942-060-A | 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 |
D. Removal of Equipment
(1) Remove the safety barriers.
(2) Remove the WARNING NOTICE(S).
(3) Remove the access platform(s).
(4) 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 access platform(s).
(4) Remove the ground support and maintenance equipment, the special and standard tools and all other items.