DOC AIRBUS | AMM A320FInstallation of the NLG Shock Absorber Assy
TASK 32-21-13-400-001-A
Installation of the NLG Shock Absorber Assy
Self explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
B. Consumable Materials
C. Work Zones and Access Panels
D. Expendable Parts
E. Referenced Information
3. Job Set-up
Subtask 32-21-13-860-052-A
Subtask 32-21-13-110-051-B ** ON A/C NOT FOR ALL
Subtask 32-21-13-860-051-A
[Rev.10 from 2021]
2026.04.01 00:42:06 UTC
Installation of the NLG Shock Absorber Assy
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:
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.
WARNING:
MAKE SURE THAT THE CONTROLS AGREE WITH THE POSITION OF THE ITEMS THEY OPERATE BEFORE YOU PRESSURIZE A HYDRAULIC SYSTEM. UNWANTED MOVEMENT OF HYDRAULICALLY OPERATED ITEMS CAN CAUSE SERIOUS INJURY AND/OR DAMAGE.
WARNING:
PRESSURIZE ONLY THE HYDRAULIC SYSTEM(S) THAT IS (ARE) NECESSARY FOR THE TASK. ISOLATE THE OTHER HYDRAULIC SYSTEM(S) BEFORE YOU SUPPLY HYDRAULIC POWER TO THE AIRCRAFT.
WARNING:
MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT. UNWANTED ELECTRICAL POWER CAN BE DANGEROUS.
WARNING:
BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.
ZONE: 711
1. Reason for the JobSelf explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
| REFERENCE | QTY | DESIGNATION |
|---|---|---|
| No specific | AR | ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE |
| No specific | AR | SAFETY BARRIER(S) |
| No specific | AR | WARNING NOTICE(S) |
| No specific | Torque wrench: range to between 0.35 and 0.25 m.daN (30.97 and 22.12 lbf.in )  | |
| No specific | Torque wrench: range to between 1.25 and 1 m.daN (110.62 and 88.50 lbf.in ) | |
| No specific | Torque wrench: range to between 2 and 1.7 m.daN (14.75 and 12.54 lbf.ft ) | |
| No specific | Torque wrench: range to between 25 and 22 m.daN (184.37 and 162.24 lbf.ft ) | |
| J47564 | 1 | ADAPTOR |
| J47999 | 1 | GUIDE CONE |
| REFERENCE | DESIGNATION |
|---|---|
| (Material No.06ABA1) | Polysulfide Sealant-Fuel Tank Brushable - |
| (Material No.06ABB1) | Polysulfide Sealant-Fuel Tank Fillet - |
| (Material No.06LDG2) | Non Hardening Jointing Putty-High Temp. Area - Structure |
| (Material No.08ABC1) | Aqueous Cleaner-Aircraft Exterior Pressure Spraying - |
| (Material No.08BAA9) | Non Aqueous Cleaner-General - - |
| (Material No.14QFB1) | Wire-Locking Dia: 0.8 mm CRES Nickel Alloy - |
| ZONE/ACCESS | ZONE DESCRIPTION |
|---|---|
| 711 | NOSE GEAR |
| FIG.ITEM | DESIGNATION | IPC-CSN |
|---|---|---|
| 15 | SCRAPER | AIPC 32-21-11-23-230 |
| 13 | RING | AIPC 32-21-11-23-250 |
| 14 | SEAL | AIPC 32-21-11-23-260 |
| 14 | SCRAPER | AIPC 32-21-11-43-230 |
| 15 | SCRAPER | AIPC 32-21-11-43-230 |
| 12 | RING | AIPC 32-21-11-43-250 |
| 13 | RING | AIPC 32-21-11-43-250 |
| 13 | SEAL | AIPC 32-21-11-43-260 |
| 14 | SEAL | AIPC 32-21-11-43-260 |
| 14 | SCRAPER | AIPC 32-21-11-63-230 |
| 12 | RING | AIPC 32-21-11-63-250 |
| 13 | SEAL | AIPC 32-21-11-63-260 |
| 14 | SCRAPER | AIPC 32-21-11-83-230 |
| 12 | RING | AIPC 32-21-11-83-250 |
| 13 | SEAL | AIPC 32-21-11-83-260 |
| 5 | PACKING | AIPC 32-21-13-11-110 |
| 6 | PACKING | AIPC 32-21-13-11-110 |
| 3 | LOCKWASHER | AIPC 32-21-13-11-170 |
| 22 | COTTER PIN | AIPC 32-21-13-12-100 |
| 5 | PACKING | AIPC 32-21-13-21-110 |
| 22 | COTTER PIN | AIPC 32-21-13-22-100 |
| REFERENCE | DESIGNATION |
|---|---|
| TASK 07-11-00-581-001-A | Lifting for Aircraft Maintenance Operations |
| TASK 07-11-00-586-002-A | Lowering of the Aircraft for Maintenance Operations |
| TASK 12-12-32-611-005-A | NLG Shock Absorber Oil Replenishment and Nitrogen Filling (Aircraft on Jacks) |
| TASK 12-22-32-640-002-A | Lubrication of Nose Landing Gear and Doors |
| TASK 32-21-27-400-002-A | Installation of the Torque-Link Center Hinge |
| TASK 32-21-41-400-001-A | Installation of the NLG TOWING attachment |
| TASK 32-22-00-010-001-A | Nose Gear Doors - Ground Doors Opening |
| TASK 32-22-00-410-001-A | Nose Gear Doors - Ground Doors Closing |
| TASK 32-31-00-720-002-A | Functional Test of the Normal Extension and Retraction of the Landing Gear |
| TASK 32-31-00-720-003-A | Functional Test of the Normal Extension and Retraction of the Nose Landing Gear |
| TASK 32-41-12-400-001-A | Installation of the NLG Wheel |
| TASK 32-51-00-720-003-A | Functional Test of the Nose Wheel Steering with the Handwheel |
Nose Gear Torque Links - Center HingeSubtask 32-21-13-860-052-A
A. Aircraft Maintenance Configuration
(1) In the cockpit, on the panel 400VU, make sure that the WARNING NOTICE(S) is (are) in position to tell persons not to operate the landing gear control lever.
(2) On the steering handwheel (CAPT and F/O) and on the brake pedals, make sure that the WARNING NOTICE(S) is (are) in position to tell persons not to operate them.
(3) Make sure that the SAFETY BARRIER(S) are in position.
(4) Make sure that the aircraft is lifted with jacks (Ref. AMM TASK 07-11-00-581-001).
(5) Make sure that the doors of the NLG are open (Ref. AMM TASK 32-22-00-010-001).
(6) Make sure that the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE is in position in zone 123.
Subtask 32-21-13-865-051-A (1) In the cockpit, on the panel 400VU, make sure that the WARNING NOTICE(S) is (are) in position to tell persons not to operate the landing gear control lever.
(2) On the steering handwheel (CAPT and F/O) and on the brake pedals, make sure that the WARNING NOTICE(S) is (are) in position to tell persons not to operate them.
(3) Make sure that the SAFETY BARRIER(S) are in position.
(4) Make sure that the aircraft is lifted with jacks (Ref. AMM TASK 07-11-00-581-001).
(5) Make sure that the doors of the NLG are open (Ref. AMM TASK 32-22-00-010-001).
(6) Make sure that the ACCESS PLATFORM 2M (6 FT) - ADJUSTABLE is in position in zone 123.
B. Make sure that this(these) circuit breaker(s) is(are) open, safetied and tagged:
4. Procedure| PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C ALL | |||
| 121VU | HYDRAULIC/BRAKING AND STEERING/SYS2/SPLY | 4GG | M36 |
| 121VU | HYDRAULIC/BRAKING AND STEERING/SYS2/CTL | 3GG | M35 |
| 121VU | HYDRAULIC/BRAKING AND STEERING/SYS1/CTL | 1GG | M34 |
| 121VU | HYDRAULIC/BRAKING AND STEERING/SYS1/IND AND/SPLY | 2GG | M33 |
Subtask 32-21-13-110-051-B ** ON A/C NOT FOR ALL
A. Preparation for Installation
(1) Clean all the removed parts with Aqueous Cleaner-Aircraft Exterior Pressure Spraying - (Material No.08ABC1) and dry them with compressed air.
(2) Make sure that the parts and the chromed surfaces are in the correct condition.
(3) Make sure that the three friction pads (11) are in position in the upper part of the shock strut.
(4) Make sure that the scraper (14) is in the correct condition. Replace the AIPC 32-21-11-43-230 SCRAPER (14) or AIPC 32-21-11-63-230 SCRAPER (14) or AIPC 32-21-11-83-230 SCRAPER (14) if necessary
(5) To prevent damage to the scraper (14) during installation, install it on the shock absorber (10). You will push the scraper (14) in its housing when you engage the shock absorber in the upper bearing.
(6) Systematically replace the AIPC 32-21-11-43-260 SEAL (13) or AIPC 32-21-11-63-260 SEAL (13) or AIPC 32-21-11-83-260 SEAL (13) and the AIPC 32-21-11-43-250 RING (12) or AIPC 32-21-11-63-250 RING (12) or AIPC 32-21-11-83-250 RING (12).
(7) Clean the attachment hardware with Non Aqueous Cleaner-General - - (Material No.08BAA9) and dry them with filtered compressed air.
(8) Apply a light coat of Non Hardening Jointing Putty-High Temp. Area - Structure (Material No.06LDG2) to the threads of all the nuts, screws, bolts and pins.
(9) Apply a light layer of Non Hardening Jointing Putty-High Temp. Area - Structure (Material No.06LDG2) to the threaded parts and the stop plate (4).
(10) Apply a light layer of Non Hardening Jointing Putty-High Temp. Area - Structure (Material No.06LDG2) to the lugs of the shock absorber upper part.
Subtask 32-21-13-420-052-G ** ON A/C NOT FOR ALL (1) Clean all the removed parts with Aqueous Cleaner-Aircraft Exterior Pressure Spraying - (Material No.08ABC1) and dry them with compressed air.
(2) Make sure that the parts and the chromed surfaces are in the correct condition.
(3) Make sure that the three friction pads (11) are in position in the upper part of the shock strut.
(4) Make sure that the scraper (14) is in the correct condition. Replace the AIPC 32-21-11-43-230 SCRAPER (14) or AIPC 32-21-11-63-230 SCRAPER (14) or AIPC 32-21-11-83-230 SCRAPER (14) if necessary
(5) To prevent damage to the scraper (14) during installation, install it on the shock absorber (10). You will push the scraper (14) in its housing when you engage the shock absorber in the upper bearing.
(6) Systematically replace the AIPC 32-21-11-43-260 SEAL (13) or AIPC 32-21-11-63-260 SEAL (13) or AIPC 32-21-11-83-260 SEAL (13) and the AIPC 32-21-11-43-250 RING (12) or AIPC 32-21-11-63-250 RING (12) or AIPC 32-21-11-83-250 RING (12).
(7) Clean the attachment hardware with Non Aqueous Cleaner-General - - (Material No.08BAA9) and dry them with filtered compressed air.
(8) Apply a light coat of Non Hardening Jointing Putty-High Temp. Area - Structure (Material No.06LDG2) to the threads of all the nuts, screws, bolts and pins.
(9) Apply a light layer of Non Hardening Jointing Putty-High Temp. Area - Structure (Material No.06LDG2) to the threaded parts and the stop plate (4).
(10) Apply a light layer of Non Hardening Jointing Putty-High Temp. Area - Structure (Material No.06LDG2) to the lugs of the shock absorber upper part.
B. Installation of the Shock-Absorber Assembly
(2) Install the J47999 GUIDE CONE on the threaded part of the sliding tube.
(3) Release the nitrogen pressure and fully compress the shock absorber (10).
(4) Make sure that the bush (9) is in position on the shock absorber (10).
(5) Slowly engage the shock absorber (10) in the shock strut (7). Make sure you do not cause damage to the friction pads (11) when the shock absorber (10) goes near the upper self-aligning bearing.
(6) Push the scraper (14) in its housing.
(7) Lift the shock absorber (10) to align the lugs of the piston with the slots in the shock strut backplate (8).
(8) Remove the J47999 GUIDE CONE from the threaded part of the sliding tube.
(a) Measure the length of the thread (15) from the top of the bush (9) to the end of the thread (15). When the length is between 18 mm (0.71 in.) and 20 mm (0.79 in.), the shock absorber (10) is correctly installed in the shock strut (7).
(9) Install and TORQUE the nut (6) with the J47564 ADAPTOR to between 25 and 22 m.daN (184.37 and 162.24 lbf.ft ).
(10) Install the charging valve:
(b) Install the valve (1) with a new AIPC 32-21-13-11-110 PACKING (5) or AIPC 32-21-13-21-110 PACKING (5).
(c) TORQUE the valve (1) to between 1.25 and 1 m.daN (110.62 and 88.50 lbf.in ) and safety with 14QFB1 Wire-Locking Dia: 0.8 mm CRES Nickel Alloy -
(d) Install the washer (3) and the screw (2).
(e) TORQUE the screw (2) to between 0.35 and 0.25 m.daN (30.97 and 22.12 lbf.in ).
(11) Remove the TROLLEY - LIFTING.
(12) Do the NLG shock-absorber oil-replenishment and nitrogen filling (Ref. AMM TASK 12-12-32-611-005).
(a) Do not lower the aircraft onto its wheels after the NLG shock-absorber oil-replenishment and nitrogen filling.
(13) With the shock absorber fully extended, make sure that the wheel axle is perpendicular to the aircraft centerline.
(a) Try to turn the NLG shock absorber around its vertical axis.
(b) Make sure that the shock absorber does not turn.
1 If the shock absorber turns, remove it to install the cams in the correct position.
(a) Make sure that there are no hard points when you move the torque links through their full travel.
(16) Connect the center hinge (Ref. AMM TASK 32-21-27-400-002).
Subtask 32-21-13-110-051-H ** ON A/C NOT FOR ALL CAUTION:
WHEN YOU INSTALL THE SHOCK ABSORBER, MAKE SURE THAT YOU ALIGN THE PISTON LUGS WITH THE SLOTS IN THE SHOCK STRUT BACKPLATE. THE SHOCK ABSORBER WILL THUS BE IN THE CORRECT POSITION (THE WHEEL AXLE PERPENDICULAR TO THE AIRCRAFT CENTERLINE). AN INCORRECT INSTALLATION CAN CAUSE IMPORTANT DAMAGE TO THE NLG.
(1) Install the shock absorber (10) on the TROLLEY - LIFTING. (2) Install the J47999 GUIDE CONE on the threaded part of the sliding tube.
(3) Release the nitrogen pressure and fully compress the shock absorber (10).
(4) Make sure that the bush (9) is in position on the shock absorber (10).
(5) Slowly engage the shock absorber (10) in the shock strut (7). Make sure you do not cause damage to the friction pads (11) when the shock absorber (10) goes near the upper self-aligning bearing.
(6) Push the scraper (14) in its housing.
(7) Lift the shock absorber (10) to align the lugs of the piston with the slots in the shock strut backplate (8).
(8) Remove the J47999 GUIDE CONE from the threaded part of the sliding tube.
(a) Measure the length of the thread (15) from the top of the bush (9) to the end of the thread (15). When the length is between 18 mm (0.71 in.) and 20 mm (0.79 in.), the shock absorber (10) is correctly installed in the shock strut (7).
(9) Install and TORQUE the nut (6) with the J47564 ADAPTOR to between 25 and 22 m.daN (184.37 and 162.24 lbf.ft )
. (10) Install the charging valve:
WARNING:
USE PROTECTIVE GOGGLES AND GLOVES WHEN YOU REMOVE OR INSTALL LOCKWIRE. EACH TIME YOU CUT LOCKWIRE, REMOVE AND DISCARD IT IMMEDIATELY. LOOSE LOCKWIRE CAN CUT YOU OR MAKE YOU BLIND, AND/OR CAN CAUSE DAMAGE.
(a) Install the stop plate (4). (b) Install the valve (1) with a new AIPC 32-21-13-11-110 PACKING (5) or AIPC 32-21-13-21-110 PACKING (5).
(c) TORQUE the valve (1) to between 1.25 and 1 m.daN (110.62 and 88.50 lbf.in )
and safety with (d) Install the washer (3) and the screw (2).
(e) TORQUE the screw (2) to between 0.35 and 0.25 m.daN (30.97 and 22.12 lbf.in )
. (11) Remove the TROLLEY - LIFTING.
(12) Do the NLG shock-absorber oil-replenishment and nitrogen filling (Ref. AMM TASK 12-12-32-611-005).
(a) Do not lower the aircraft onto its wheels after the NLG shock-absorber oil-replenishment and nitrogen filling.
(13) With the shock absorber fully extended, make sure that the wheel axle is perpendicular to the aircraft centerline.
NOTE: In the fully extended position of the shock absorber, the NLG is automatically aligned to center (the nose wheel steering is in zero position).
(a) Make sure that dimension H of the extended part of the NLG sliding tube between: - The bottom area of the NLG lower bearing and upper surface of the towing fitting lug is 449 mm (17.6772 in.) plus or minus 2 mm (0.0787 in.).
(a) Try to turn the NLG shock absorber around its vertical axis.
(b) Make sure that the shock absorber does not turn.
1 If the shock absorber turns, remove it to install the cams in the correct position.
NOTE: If you can turn the shock absorber, this shows that the anti-rotation lugs are not engaged in the slots. This is because the centering cams are not installed.
(15) Install the stop (64), bolts (66), washers (63) and (65) and nuts (62). Tighten the nuts (62). (a) Make sure that there are no hard points when you move the torque links through their full travel.
(16) Connect the center hinge (Ref. AMM TASK 32-21-27-400-002).
C. Preparation for Installation
(1) Clean all the removed parts with Aqueous Cleaner-Aircraft Exterior Pressure Spraying - (Material No.08ABC1) and dry them with compressed air.
(2) Make sure that the parts and the chromed surfaces are in the correct condition.
(3) Make sure that the three friction pads (12) are in position in the upper part of the shock strut.
(4) Make sure that the scraper (15) is in the correct condition. Replace the AIPC 32-21-11-43-230 SCRAPER (15) or AIPC 32-21-11-23-230 SCRAPER (15) if necessary
(5) To prevent damage to the scraper (15) during installation, install it on the shock absorber (11). You will push the scraper (15) in its housing when you engage the shock absorber in the upper bearing.
(6) Systematically replace the AIPC 32-21-11-43-260 SEAL (14) or AIPC 32-21-11-23-260 SEAL (14) and the AIPC 32-21-11-43-250 RING (13) or AIPC 32-21-11-23-250 RING (13).
(7) Clean the attachment hardware with Non Aqueous Cleaner-General - - (Material No.08BAA9) and dry them with filtered compressed air.
(8) Apply a light coat of Non Hardening Jointing Putty-High Temp. Area - Structure (Material No.06LDG2) to the threads of all the nuts, screws, bolts and pins.
(9) Apply a light layer of Non Hardening Jointing Putty-High Temp. Area - Structure (Material No.06LDG2) to the threaded parts and the stop plates (4) and (5).
(10) Apply a light layer of Non Hardening Jointing Putty-High Temp. Area - Structure (Material No.06LDG2) to the lugs of the shock absorber upper part.
Subtask 32-21-13-420-052-I ** ON A/C NOT FOR ALL (1) Clean all the removed parts with Aqueous Cleaner-Aircraft Exterior Pressure Spraying - (Material No.08ABC1) and dry them with compressed air.
(2) Make sure that the parts and the chromed surfaces are in the correct condition.
(3) Make sure that the three friction pads (12) are in position in the upper part of the shock strut.
(4) Make sure that the scraper (15) is in the correct condition. Replace the AIPC 32-21-11-43-230 SCRAPER (15) or AIPC 32-21-11-23-230 SCRAPER (15) if necessary
(5) To prevent damage to the scraper (15) during installation, install it on the shock absorber (11). You will push the scraper (15) in its housing when you engage the shock absorber in the upper bearing.
(6) Systematically replace the AIPC 32-21-11-43-260 SEAL (14) or AIPC 32-21-11-23-260 SEAL (14) and the AIPC 32-21-11-43-250 RING (13) or AIPC 32-21-11-23-250 RING (13).
(7) Clean the attachment hardware with Non Aqueous Cleaner-General - - (Material No.08BAA9) and dry them with filtered compressed air.
(8) Apply a light coat of Non Hardening Jointing Putty-High Temp. Area - Structure (Material No.06LDG2) to the threads of all the nuts, screws, bolts and pins.
(9) Apply a light layer of Non Hardening Jointing Putty-High Temp. Area - Structure (Material No.06LDG2) to the threaded parts and the stop plates (4) and (5).
(10) Apply a light layer of Non Hardening Jointing Putty-High Temp. Area - Structure (Material No.06LDG2) to the lugs of the shock absorber upper part.
D. Installation of the Shock Absorber Assy
(2) Install the J47999 GUIDE CONE on the threaded part of the sliding tube.
(3) Release the nitrogen pressure and fully compress the shock absorber (11).
(4) Make sure that the bush (10) is in position on the shock absorber (11).
(5) Slowly engage the shock absorber (11) in the shock strut (8). Be careful not to cause damage to the friction pads (12) when the shock absorber goes near the upper self-aligning bearing.
(6) Push the scraper (15) in its housing.
(7) Lift the shock absorber (11) to align the lugs of the piston with the slots in the shock-strut backplate (9).
(8) Remove the J47999 GUIDE CONE from the threaded part of the sliding tube.
(a) Measure the length of the thread (16) from the top of the bush (10) to the end of the thread (16). When the length is between 18 mm (0.71 in.) and 20 mm (0.79 in.), the shock absorber (11) is correctly installed in the shock strut (8).
(9) Install and TORQUE the nut (7) with the J47564 ADAPTOR to between 25 and 22 m.daN (184.37 and 162.24 lbf.ft ).
(10) Install the charging valve:
(a) Install the stop plate (5).
(b) Install the valve (1) with a new AIPC 32-21-13-11-110 PACKING (6).
(c) TORQUE the valve (1) to between 1.25 and 1 m.daN (110.62 and 88.50 lbf.in ).
(d) Install the stop plate (4), align it with a hole of the plate (5) and the related thread of the nut (7).
(e) Install the new lockwasher (3) and the screw (2).
(f) TORQUE the screw (2) to between 0.35 and 0.25 m.daN (30.97 and 22.12 lbf.in ) and safety with the AIPC 32-21-13-11-170 LOCKWASHER (3).
(11) Remove the TROLLEY - LIFTING.
(12) Do the NLG shock-absorber oil-replenishment and nitrogen filling (Ref. AMM TASK 12-12-32-611-005).
(a) Do not lower the aircraft onto the its wheels after the NLG shock-absorber oil-replenishment and nitrogen filling.
(13) With the shock absorber fully extended, make sure that the wheel axle is perpendicular to the aircraft centerline.
(a) Try to turn the NLG shock absorber around its vertical axis.
(b) Make sure that the shock absorber does not turn.
1 If the shock abosorber turns, remove it to install the cams in the correct position.
(16) Connect the center hinge (Ref. AMM TASK 32-21-27-400-002).
Subtask 32-21-13-110-051-Q ** ON A/C NOT FOR ALL CAUTION:
WHEN YOU INSTALL THE SHOCK ABSORBER, MAKE SURE THAT YOU ALIGN THE PISTON LUGS WITH THE SLOTS IN THE SHOCK STRUT BACKPLATE. THE SHOCK ABSORBER WILL THUS BE IN THE CORRECT POSITION (THE WHEEL AXLE PERPENDICULAR TO THE AIRCRAFT CENTERLINE). AN INCORRECT INSTALLATION CAN CAUSE IMPORTANT DAMAGE TO THE NLG.
(1) Install the shock absorber (11) on the TROLLEY - LIFTING. (2) Install the J47999 GUIDE CONE on the threaded part of the sliding tube.
(3) Release the nitrogen pressure and fully compress the shock absorber (11).
(4) Make sure that the bush (10) is in position on the shock absorber (11).
(5) Slowly engage the shock absorber (11) in the shock strut (8). Be careful not to cause damage to the friction pads (12) when the shock absorber goes near the upper self-aligning bearing.
(6) Push the scraper (15) in its housing.
(7) Lift the shock absorber (11) to align the lugs of the piston with the slots in the shock-strut backplate (9).
(8) Remove the J47999 GUIDE CONE from the threaded part of the sliding tube.
(a) Measure the length of the thread (16) from the top of the bush (10) to the end of the thread (16). When the length is between 18 mm (0.71 in.) and 20 mm (0.79 in.), the shock absorber (11) is correctly installed in the shock strut (8).
(9) Install and TORQUE the nut (7) with the J47564 ADAPTOR to between 25 and 22 m.daN (184.37 and 162.24 lbf.ft )
. (10) Install the charging valve:
(a) Install the stop plate (5).
(b) Install the valve (1) with a new AIPC 32-21-13-11-110 PACKING (6).
(c) TORQUE the valve (1) to between 1.25 and 1 m.daN (110.62 and 88.50 lbf.in )
. (d) Install the stop plate (4), align it with a hole of the plate (5) and the related thread of the nut (7).
(e) Install the new lockwasher (3) and the screw (2).
(f) TORQUE the screw (2) to between 0.35 and 0.25 m.daN (30.97 and 22.12 lbf.in )
and safety with the AIPC 32-21-13-11-170 LOCKWASHER (3). (11) Remove the TROLLEY - LIFTING.
(12) Do the NLG shock-absorber oil-replenishment and nitrogen filling (Ref. AMM TASK 12-12-32-611-005).
(a) Do not lower the aircraft onto the its wheels after the NLG shock-absorber oil-replenishment and nitrogen filling.
(13) With the shock absorber fully extended, make sure that the wheel axle is perpendicular to the aircraft centerline.
NOTE: In the fully extended position of the shock absorber, the NLG is automatically aligned to center (the nose wheel steering is in zero position).
(a) Make sure that the dimension H of the extended part of the NLG sliding tube between: - The lower area of the NLG lower bearing and upper surface of the towing fitting lug is 449 mm (17.6772 in.) plus or minus 2 mm (0.0787 in.).
(a) Try to turn the NLG shock absorber around its vertical axis.
(b) Make sure that the shock absorber does not turn.
1 If the shock abosorber turns, remove it to install the cams in the correct position.
NOTE: If you can turn the shock absorber, this shows that the anti-roation lugs are not not engaged in the slots. This is because the centering cams are not correctly installed.
(15) Install the stop (64), the bolts (66), the washers (63) and (65) and the nuts (62). Tighten the nuts (62). (16) Connect the center hinge (Ref. AMM TASK 32-21-27-400-002).
E. Preparation for Installation
(1) Clean all the removed parts with Aqueous Cleaner-Aircraft Exterior Pressure Spraying - (Material No.08ABC1) and dry them with compressed air.
(2) Make sure that the parts and the chromed surfaces are in the correct condition.
(3) Make sure that the three friction pads (12) are in position in the upper part of the shock strut.
(4) Make sure that the scraper (15) is in the correct condition. Replace the AIPC 32-21-11-23-230 SCRAPER (15) if necessary
(5) To prevent damage to the scraper (15) during installation, install it on the shock absorber (11). You will push the scraper (15) in its housing when you engage the shock absorber in the upper bearing.
(6) Systematically replace the AIPC 32-21-11-23-260 SEAL (14) and the AIPC 32-21-11-23-250 RING (13).
(7) Clean the attachment hardware with Non Aqueous Cleaner-General - - (Material No.08BAA9) and dry them with filtered compressed air.
(8) Apply a light coat of Non Hardening Jointing Putty-High Temp. Area - Structure (Material No.06LDG2) to the threads of all the nuts, screws, bolts and pins.
(9) Apply a light layer of Non Hardening Jointing Putty-High Temp. Area - Structure (Material No.06LDG2) to the threaded parts and the stop plates (4) and (5).
(10) Apply a light layer of Non Hardening Jointing Putty-High Temp. Area - Structure (Material No.06LDG2) to the lugs of the shock absorber upper part.
Subtask 32-21-13-420-052-E ** ON A/C NOT FOR ALL (1) Clean all the removed parts with Aqueous Cleaner-Aircraft Exterior Pressure Spraying - (Material No.08ABC1) and dry them with compressed air.
(2) Make sure that the parts and the chromed surfaces are in the correct condition.
(3) Make sure that the three friction pads (12) are in position in the upper part of the shock strut.
(4) Make sure that the scraper (15) is in the correct condition. Replace the AIPC 32-21-11-23-230 SCRAPER (15) if necessary
(5) To prevent damage to the scraper (15) during installation, install it on the shock absorber (11). You will push the scraper (15) in its housing when you engage the shock absorber in the upper bearing.
(6) Systematically replace the AIPC 32-21-11-23-260 SEAL (14) and the AIPC 32-21-11-23-250 RING (13).
(7) Clean the attachment hardware with Non Aqueous Cleaner-General - - (Material No.08BAA9) and dry them with filtered compressed air.
(8) Apply a light coat of Non Hardening Jointing Putty-High Temp. Area - Structure (Material No.06LDG2) to the threads of all the nuts, screws, bolts and pins.
(9) Apply a light layer of Non Hardening Jointing Putty-High Temp. Area - Structure (Material No.06LDG2) to the threaded parts and the stop plates (4) and (5).
(10) Apply a light layer of Non Hardening Jointing Putty-High Temp. Area - Structure (Material No.06LDG2) to the lugs of the shock absorber upper part.
F. Installation of the Shock Absorber Assy
(2) Install the J47999 GUIDE CONE on the threaded part of the sliding tube.
(3) Release the nitrogen pressure and fully compress the shock absorber (10).
(4) Make sure that the bush (9) is in position on the shock absorber (10).
(5) Slowly engage the shock absorber (10) in the shock strut. Be careful not to cause damage to the friction pads (11) when the shock absorber goes near the upper self-aligning bearing.
(6) Push the scraper (14) in its housing.
(7) Lift the shock absorber (10) to align the lugs of the piston with the slots in the shock-strut backplate (8).
(8) Remove the J47999 GUIDE CONE from the threaded part of the sliding tube.
(a) Measure the length of the thread (15) from the top of the bush (9) to the end of the thread (15). When the length is between 18 mm (0.71 in.) and 20 mm (0.79 in.), the shock absorber (10) is correctly installed in the shock strut (7).
(9) Install the nut (6).
(10) Use the J47564 ADAPTOR and TORQUE the nut (6) to between 25 and 22 m.daN (184.37 and 162.24 lbf.ft ).
(11) Install the valve (1) as follows:
(a) Install the stop plate (4).
(b) Install the valve (1) with a new AIPC 32-21-13-11-110 PACKING (5) or the new AIPC 32-21-13-21-110 PACKING (5).
(c) TORQUE the valve (1) to between 1.25 and 1 m.daN (110.62 and 88.50 lbf.in ).
(d) Safety with the valve (1)14QFB1 Wire-Locking Dia: 0.8 mm CRES Nickel Alloy -
(e) Install the washer (3) and the screw (2).
(f) TORQUE the screw (2) to between 0.35 and 0.25 m.daN (30.97 and 22.12 lbf.in ) .
(12) Remove the TROLLEY - LIFTING.
(13) Do the NLG shock-absorber oil-replenishment and nitrogen filling (Ref. AMM TASK 12-12-32-611-005).
(a) Do not lower the aircraft onto its wheels after the NLG shock-absorber oil-replenishment and nitrogen filling.
(14) With the shock absorber fully extended, make sure that the wheel axle is perpendicular to the aircraft centerline.
(a) Try to turn the NLG shock absorber around its vertical axis.
(b) Make sure that the shock absorber does not turn.
1 If the shock absorber turns, remove it to install the cams in the correct position.
(17) Install the washers (66), the bolts (67), the washers (64) and the nuts (63).
(a) Make sure that there are no hard points when you moved the torque links through their full travel.
(18) Tighten the nuts (63).
(19) Connect the center hinge (Ref. AMM TASK 32-21-27-400-002).
Subtask 32-21-13-420-051-G WARNING:
USE PROTECTIVE GOGGLES AND GLOVES WHEN YOU REMOVE OR INSTALL LOCKWIRE. EACH TIME YOU CUT LOCKWIRE, REMOVE AND DISCARD IT IMMEDIATELY. LOOSE LOCKWIRE CAN CUT YOU OR MAKE YOU BLIND, AND/OR CAN CAUSE DAMAGE.
CAUTION:
WHEN YOU INSTALL THE SHOCK ABSORBER, MAKE SURE THAT YOU ALIGN THE PISTON LUGS WITH THE SLOTS IN THE SHOCK STRUT BACKPLATE. THE SHOCK ABSORBER WILL THUS BE IN THE CORRECT POSITION (THE WHEEL AXLE PERPENDICULAR TO THE AIRCRAFT CENTERLINE). AN INCORRECT INSTALLATION CAN CAUSE IMPORTANT DAMAGE TO THE NLG.
(1) Install the shock absorber (10) on the TROLLEY - LIFTING. (2) Install the J47999 GUIDE CONE on the threaded part of the sliding tube.
(3) Release the nitrogen pressure and fully compress the shock absorber (10).
(4) Make sure that the bush (9) is in position on the shock absorber (10).
(5) Slowly engage the shock absorber (10) in the shock strut. Be careful not to cause damage to the friction pads (11) when the shock absorber goes near the upper self-aligning bearing.
(6) Push the scraper (14) in its housing.
(7) Lift the shock absorber (10) to align the lugs of the piston with the slots in the shock-strut backplate (8).
(8) Remove the J47999 GUIDE CONE from the threaded part of the sliding tube.
(a) Measure the length of the thread (15) from the top of the bush (9) to the end of the thread (15). When the length is between 18 mm (0.71 in.) and 20 mm (0.79 in.), the shock absorber (10) is correctly installed in the shock strut (7).
(9) Install the nut (6).
(10) Use the J47564 ADAPTOR and TORQUE the nut (6) to between 25 and 22 m.daN (184.37 and 162.24 lbf.ft )
.(11) Install the valve (1) as follows:
(a) Install the stop plate (4).
(b) Install the valve (1) with a new AIPC 32-21-13-11-110 PACKING (5) or the new AIPC 32-21-13-21-110 PACKING (5).
(c) TORQUE the valve (1) to between 1.25 and 1 m.daN (110.62 and 88.50 lbf.in )
. (d) Safety with the valve (1)
(e) Install the washer (3) and the screw (2).
(f) TORQUE the screw (2) to between 0.35 and 0.25 m.daN (30.97 and 22.12 lbf.in )
. (12) Remove the TROLLEY - LIFTING.
(13) Do the NLG shock-absorber oil-replenishment and nitrogen filling (Ref. AMM TASK 12-12-32-611-005).
(a) Do not lower the aircraft onto its wheels after the NLG shock-absorber oil-replenishment and nitrogen filling.
(14) With the shock absorber fully extended, make sure that the wheel axle is perpendicular to the aircraft centerline.
NOTE: In the fully extended position of the shock absorber, the NLG is automatically aligned to center (the nose wheel steering is in zero position).
(a) Make sure that dimension H of the extended part of the NLG sliding tube between: - The lower area of the NLG lower bearing and upper surface of the towing fitting lug is 449 mm (17.6772 in.) plus or minus 2 mm (0.0787 in.).
(a) Try to turn the NLG shock absorber around its vertical axis.
(b) Make sure that the shock absorber does not turn.
1 If the shock absorber turns, remove it to install the cams in the correct position.
NOTE: If you can turn the shock absorber, this shows that the anti-roation lugs are not not engaged in the slots. This is because the centering cams are not correctly installed.
(16) Put the stop (65) in position.(17) Install the washers (66), the bolts (67), the washers (64) and the nuts (63).
(a) Make sure that there are no hard points when you moved the torque links through their full travel.
(18) Tighten the nuts (63).
(19) Connect the center hinge (Ref. AMM TASK 32-21-27-400-002).
G. End of the Installation
(1) Install the support (21).
(2) Install the bolt (20) with its head up and install the nut (23).
(3) TORQUE the nut (23) to between 2 and 1.7 m.daN (14.75 and 12.54 lbf.ft ) and safety it with a AIPC 32-21-13-12-100 COTTER PIN (22) or AIPC 32-21-13-22-100 COTTER PIN (22).
(4) Install the wheels on the nose landing gear (Ref. AMM TASK 32-41-12-400-001).
Subtask 32-21-13-865-053-A (1) Install the support (21).
(2) Install the bolt (20) with its head up and install the nut (23).
(3) TORQUE the nut (23) to between 2 and 1.7 m.daN (14.75 and 12.54 lbf.ft )
and safety it with a AIPC 32-21-13-12-100 COTTER PIN (22) or AIPC 32-21-13-22-100 COTTER PIN (22). (4) Install the wheels on the nose landing gear (Ref. AMM TASK 32-41-12-400-001).
NOTE: Lower the aircraft to make the installation of the wheels easier.
(5) Install the towing fitting (Ref. AMM TASK 32-21-41-400-001). H. Remove the safety clip(s) and the tag(s) and close this(these) circuit breaker(s):
Subtask 32-21-13-941-053-A | PANEL | DESIGNATION | FIN | LOCATION |
|---|---|---|---|
| ** ON A/C ALL | |||
| 121VU | HYDRAULIC/BRAKING AND STEERING/SYS2/SPLY | 4GG | M36 |
| 121VU | HYDRAULIC/BRAKING AND STEERING/SYS2/CTL | 3GG | M35 |
| 121VU | HYDRAULIC/BRAKING AND STEERING/SYS1/CTL | 1GG | M34 |
| 121VU | HYDRAULIC/BRAKING AND STEERING/SYS1/IND AND/SPLY | 2GG | M33 |
I. Preparation for the Test
(1) Lubricate the nose landing gear (Ref. AMM TASK 12-22-32-640-002).
(2) Apply a layer of Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) in areas E.
(3) Apply a layer of Polysulfide Sealant-Fuel Tank Fillet - (Material No.06ABB1) in areas F.
(4) Remove the access platform(s).
Subtask 32-21-13-720-051-C (1) Lubricate the nose landing gear (Ref. AMM TASK 12-22-32-640-002).
(2) Apply a layer of Polysulfide Sealant-Fuel Tank Brushable - (Material No.06ABA1) in areas E.
(3) Apply a layer of Polysulfide Sealant-Fuel Tank Fillet - (Material No.06ABB1) in areas F.
(4) Remove the access platform(s).
J. Test(s)
(1) Do the functional test of the NLG normal extension and retraction (Ref. AMM TASK 32-31-00-720-003) or (Ref. AMM TASK 32-31-00-720-002).
(2) Do the functional test of the nose wheel steering with the handwheel (Ref. AMM TASK 32-51-00-720-003).
5. Close-up(1) Do the functional test of the NLG normal extension and retraction (Ref. AMM TASK 32-31-00-720-003) or (Ref. AMM TASK 32-31-00-720-002).
(2) Do the functional test of the nose wheel steering with the handwheel (Ref. AMM TASK 32-51-00-720-003).
NOTE: You can do the functional test of the nose wheel steering with or without the aircraft on wheels configuration.
Subtask 32-21-13-860-051-A
A. Put the aircraft back to its initial configuration.
(1) Lower the aircraft on its wheels (Ref. AMM TASK 07-11-00-586-002).
(2) Remove the safety barriers.
(3) Remove the WARNING NOTICE(S).
(4) Make sure that the work area is clean and clear of tools and other items.
Subtask 32-21-13-410-051-A (1) Lower the aircraft on its wheels (Ref. AMM TASK 07-11-00-586-002).
(2) Remove the safety barriers.
(3) Remove the WARNING NOTICE(S).
(4) Make sure that the work area is clean and clear of tools and other items.