DOC AIRBUS | AMM A320FInstallation of the Torque Shaft
TASK 27-84-45-400-006-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 27-84-45-941-062-A
Subtask 27-84-45-420-072-A
Subtask 27-84-45-865-070-A
[Rev.10 from 2021]
2026.04.01 07:06:19 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 [6012CM] (SLAT XMSN TORQUE SHAFT) | |
| 191BT, 521AB, 521BB, 521CB | |
| FOR [6062CM] (SLAT XMSN TORQUE SHAFT) | |
| 192BT, 621AB, 621BB, 621CB | |
| 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 27-84-00-710-001-A | Operational Test of the Slat System |
| FOR [6062CM] (SLAT XMSN TORQUE SHAFT) | |
| TASK 53-35-11-000-001-A | Removal of the Wing-to-Fuselage Fairings |
| TASK 53-35-11-400-001-A | Installation of the Wing-to-Fuselage Fairings |
| TASK 57-41-37-000-004-A | Removal of the Pressure Relief Panels |
| TASK 57-41-37-000-005-A | Removal of the NACA Duct Panel |
| TASK 57-41-37-400-002-A | Installation of the Pressure Relief Panels |
| TASK 57-41-37-400-005-A | Installation of the NACA Duct Panel |
Torque shafts - Slat Power TransmissionSubtask 27-84-45-941-062-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 27-84-45-860-055-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 slats are retracted fully (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):
(5) Make sure that the applicable access panels have been removed:
(a) FOR [6012CM] (SLAT XMSN TORQUE SHAFT)
panels 521AB, 521CB and 521BB, 191BT
(b) FOR [6062CM] (SLAT XMSN TORQUE SHAFT)
panels 621AB, 621CB and 621BB, 192BT
(Ref. AMM TASK 57-41-37-000-004), (Ref. AMM TASK 57-41-37-000-005) and (Ref. AMM TASK 53-35-11-000-001).
Subtask 27-84-45-865-068-A (1) Make sure that the slats are retracted fully (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.
(5) Make sure that the applicable access panels have been removed:
(a) FOR [6012CM] (SLAT XMSN TORQUE SHAFT)
panels 521AB, 521CB and 521BB, 191BT
(b) FOR [6062CM] (SLAT XMSN TORQUE SHAFT)
panels 621AB, 621CB and 621BB, 192BT
(Ref. AMM TASK 57-41-37-000-004), (Ref. AMM TASK 57-41-37-000-005) and (Ref. AMM TASK 53-35-11-000-001).
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 27-84-45-420-072-A
A. Preparation for Installation
(1) Clean the component interface and/or the adjacent area with 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 27-84-45-420-054-A (1) Clean the component interface and/or the adjacent area with 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 6012CM(6062CM)
(1) Put the retaining ring (34) in position over the shaft (29).
(2) Install the universal joint (35) and attach it with the pin (33) and the retaining ring (34).
(3) Install the universal joint (28) so that it is against the shoulder of the gear box.
(4) Attach the shaft (29) to the universal joint (28) with the bolts (39) and the nuts (38).
(5) Install the shaft (30) and attach it to the shaft (29) with the bolts (37) and the nuts (36).
Subtask 27-84-45-220-053-A (1) Put the retaining ring (34) in position over the shaft (29).
(2) Install the universal joint (35) and attach it with the pin (33) and the retaining ring (34).
(3) Install the universal joint (28) so that it is against the shoulder of the gear box.
(4) Attach the shaft (29) to the universal joint (28) with the bolts (39) and the nuts (38).
(5) Install the shaft (30) and attach it to the shaft (29) with the bolts (37) and the nuts (36).
C. Dimensional Checks
(1) Measure the dimension between the flanges of the shaft (30) and the universal joint (35):
(a) If the dimension is less than 6.5 mm (0.2559 in.) or more than 23.5 mm (0.9252 in.), tell the Design Authority.
(b) If the dimension is between 6.6 mm (0.2598 in.) and 13.25 mm (0.5217 in.), do not install a spacer.
(c) If the dimension is between 13.26 mm (0.5220 in.) and 16.75 mm (0.6594 in.), install a spacer 3.5 mm (0.1378 in.) thick between the flanges of the shaft (30) and the universal joint (35).
(d) If the dimension is between 16.76 mm (0.6598 in.) and 23.5 mm (0.9252 in.), remove the nuts (36), the bolts (37) and the shaft (30).
(e) Install two spacers, each one 3.5 mm (0.1378 in.) thick:
Subtask 27-84-45-420-073-A (1) Measure the dimension between the flanges of the shaft (30) and the universal joint (35):
(a) If the dimension is less than 6.5 mm (0.2559 in.) or more than 23.5 mm (0.9252 in.), tell the Design Authority.
(b) If the dimension is between 6.6 mm (0.2598 in.) and 13.25 mm (0.5217 in.), do not install a spacer.
(c) If the dimension is between 13.26 mm (0.5220 in.) and 16.75 mm (0.6594 in.), install a spacer 3.5 mm (0.1378 in.) thick between the flanges of the shaft (30) and the universal joint (35).
(d) If the dimension is between 16.76 mm (0.6598 in.) and 23.5 mm (0.9252 in.), remove the nuts (36), the bolts (37) and the shaft (30).
(e) Install two spacers, each one 3.5 mm (0.1378 in.) thick:
- one between the flanges of the shaft (30) and the universal joint (35)
- one between the flanges of the shaft (29) and the shaft (30).
D. Continue with the Installation Procedure
(1) Install the shaft (30) and attach it to the shaft (29) with the bolts (37) and the nuts (36).
(2) Attach the shaft (30) to the universal joint (35) with the bolts (31) and the nuts (32).
(3) TORQUE the nuts (32), (36) and (38) to between 1.24 and 1.02 m.daN (109.73 and 90.27 lbf.in ).
(4) Apply a layer of Corrosion Preventive Compound-Heavy Duty Soft Film - (Material No.12ACC1) to the:
Subtask 27-84-45-210-061-A (1) Install the shaft (30) and attach it to the shaft (29) with the bolts (37) and the nuts (36).
(2) Attach the shaft (30) to the universal joint (35) with the bolts (31) and the nuts (32).
(3) TORQUE the nuts (32), (36) and (38) to between 1.24 and 1.02 m.daN (109.73 and 90.27 lbf.in )
. (4) Apply a layer of Corrosion Preventive Compound-Heavy Duty Soft Film - (Material No.12ACC1) to the:
- nuts (32), (36) and (38)
- bolts (31), (37) and (39)
- flanges of the universal joints (28) and (35)
- flanges of the shafts (29) and (30).
- from the torque shaft, inboard of the applicable component
- from the torque shaft, outboard of the removed component.
E. Dimensional/Visual Checks
(1) Make sure that:
Subtask 27-84-45-865-069-A (1) 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.
F. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):
Subtask 27-84-45-710-053-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 |
G. Test
(1) Do an operational test of the slat power-transmission system (Ref. AMM TASK 27-84-00-710-001). Make sure that the rotation of the torque shafts does not cause damage.
5. Close-up(1) Do an operational test of the slat power-transmission system (Ref. AMM TASK 27-84-00-710-001). Make sure that the rotation of the torque shafts does not cause damage.
Subtask 27-84-45-865-070-A
A. Open, safety and tag this(these) circuit breaker(s):
Subtask 27-84-45-410-053-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 panels:
(a) FOR [6012CM] (SLAT XMSN TORQUE SHAFT)
install 521AB 521BB 521CB and 191BT
(b) FOR [6062CM] (SLAT XMSN TORQUE SHAFT)
install 621AB 621BB 621CB and 192BT
(Ref. AMM TASK 57-41-37-400-002), (Ref. AMM TASK 57-41-37-400-005) and (Ref. AMM TASK 53-35-11-400-001).
Subtask 27-84-45-865-071-A (1) Make sure that the work area is clean and clear of tools and other items.
(2) Install the applicable access panels:
(a) FOR [6012CM] (SLAT XMSN TORQUE SHAFT)
install 521AB 521BB 521CB and 191BT
(b) FOR [6062CM] (SLAT XMSN TORQUE SHAFT)
install 621AB 621BB 621CB and 192BT
(Ref. AMM TASK 57-41-37-400-002), (Ref. AMM TASK 57-41-37-400-005) and (Ref. AMM TASK 53-35-11-400-001).
C. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):
Subtask 27-84-45-942-054-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.