King Air Series Component Maintenance Manual (Rev C0)

32-20-10 (Rev C0)

90 SERIES NOSE LANDING GEAR - MAINTENANCE PRACTICES

WARNING: To avoid damage to the airplane in case of accidental landing gear retraction anytime maintenance is performed on the landing gear
system, jacks should be placed under all three jack points (one adjacent to the nose gear and one on each side of the fuselage on the
aft spar, inboard of the nacelle).

1. Nose Landing Gear - Disassembly

CAUTION: Prior to LJ-577 and LW-51 unless reworked to Service Instruction No. 0516-200, coat the hinge bolts and bushings (36 and 34,
Figure 202), the drag leg bolts and bushings (1, 9, and 13, Figure 204), and the bolt and bushing (39 and 38, Figure 202) securing
the shimmy damper to the nose gear casting with metal protector (Refer to Chapter 91, Consumable Materials, Chart 1 - Item 8) at
6 month intervals to preclude galvanic reaction between them and the teflon bushings used with them.
A. Place the strut in a vertical position to prevent spilling hydraulic fluid. Remove the cap (3), depress the valve core (4) and release the air pressure from
the strut. Allow the strut to deflate completely (Refer to Figure 202).
CAUTION: Do not remove the filler valve body (1) completely until the strut is entirely deflated. Do not disconnect the torque knees (16
and 17) until all air pressure is released from the strut.
NOTE: Replace the valve core (4) anytime it is removed or loosened.
B. Cut the safety wire and remove the filler valve body (1) and gasket (2). To further disassemble the valve, remove the valve core (4) from the body.
C. To prevent the strut from slipping through the casting when the sleeve assembly (8) is removed, tie the upper shock absorber assembly (29) to the nose
gear shock brace casting (30) with safety wire. Loop the wire through the shimmy damper attaching lug on the casting and around the torque knee
attaching lugs on the upper shock absorber assembly.
NOTE: Note the position and direction of the nose gear straightener bracket (5) to facilitate installation.
D. Remove the nose gear straightener bracket (5) and the nose gear sleeve retainer bar (6) from the strut. Remove the nose gear roller (7) from the
straightener bracket.
E. Lift the sleeve assembly (8) and spacer shim (9) from the strut. Remove the snap ring (10) and separate the sleeve assembly (8) from the support (11).
CAUTION: Make sure the lower shock absorber (22) is butted up firmly against the shoulder of the upper end of the upper shock
absorber (29) when removing the support (11) to prevent the ring (13) from expanding and locking in place in the shock
absorber.
F. Remove the support (11) from the strut, allowing fluid to drain from the support as it is removed.
G. Remove the gasket (12) and ring (13) from the support (11).
H. Drain hydraulic fluid from strut by inverting strut and holding the lower portion of the shock absorber by the axle.
I. Remove the attaching hardware and drive the torque knee pins (15) from the upper and lower torque knees (16 and 17) and remove the knees. The
torque knee bushings (18, 19, and 20), and lubrication fittings (21) should be checked for operation and excessive wear and removed only for
replacement.
CAUTION: Use care when removing the scraper ring (24) since the lip on the ring may become very sharp during normal operation of
the gear.
J. Slide the lower shock absorber (22) from the upper shock absorber (29). Remove the snap ring (23), scraper ring (24), and the wiper ring (25) from the
upper shock absorber assembly (29).
K. Remove the felt lubricating pad (26) from the upper shock absorber assembly (29). With the hook shaped end on a suitable length of music wire, remove
the packing (27) from the brazed bearing in the upper shock absorber assembly (29) (Refer to Figure 201).
L. Remove the shimmy damper arm (28) from the upper shock absorber assembly (29).
M. Remove the safety wire previously tied to secure the upper shock absorber to the shock brace casting and slide the upper shock absorber (29) from the
casting (30).
N. Remove the nose gear travel stop fitting (31) from the attaching lugs on the casting (30). Remove washers (32).
O. Bushings (33 and 34) and bearings (35) in the casting should be replaced if broken, scored or excessively worn.

2. Nose Landing Gear Cleaning and Parts Replacement

A. Clean all parts with solvent (Refer to Chapter 91, Consumable Materials, Chart 1 - Item 6). Check castings for cracks and pitting and finished surfaces
for scoring, pitting, nicks, cracks, distortions, or worn surfaces. Chart 1 lists manufacturing tolerances and wear limits to aid in determining the extent of
wear. Replace all damaged or excessively worn parts.
B. Replace all strut packings, gaskets, and the valve core whenever the strut is disassembled. At maintenance periods, replace the felt lubricating pads.
C. Prior to assembly, soak all packings and all parts coming into contact with hydraulic fluid in clean hydraulic fluid (Refer to Chapter 91, Consumable
Materials, Chart 1 - Item 9). Use lubricating oil (Refer to Chapter 91, Consumable Materials, Chart 1 - Item 11) to saturate the felt pads. After assembly,
use lubricating grease (Refer to Chapter 91, Consumable Materials, Chart 1 - Item 22) to lubricate the torque knee bushings. Use lubricant (Refer to
Chapter 91, Consumable Materials, Chart 1 - Item 25) to lubricate the nose gear shock brace casting bearings (35).

3. Nose Landing Gear Assembly

NOTE: Any time landing gear components are removed, all parts must be inspected for corrosion before installation.
A. Install any replacement lubrication fittings or bushings which were removed. Make sure that lubricating holes have been drilled through the replacement
bushings if such holes are required.
NOTE: Add a maximum of two washers to each side of the stop to maintain a clearance of 0.001 to 0.006 inch between the stop and the
casting.
B. Replace the nose gear travel stop fitting (31) and washers (32) as required to eliminate looseness in the stop (Refer to Figure 202).
C. With the outer surface of the upper shock absorber assembly (29) lubricated with hydraulic fluid (Refer to Chapter 91, Consumable Materials, Chart 1 -

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 King Air Series Component Maintenance Manual (Rev C0)
32-20-10 (Rev C0)

Item 9), slide it into the shock brace casting (30). The torque knee Iugs should be on the forward side of the casting.
D. Install and safety the shimmy damper arm (28).
E. Tie the upper shock absorber to the shock brace casting with wire similar to the procedure used in disassembly.
F. Install packing (27) and use two dowel rods to work it into position. (Refer to Figure 201).
G. Saturate the felt lubricating pad (26) with lubricating oil (Refer to Chapter 91, Consumable Materials, Chart 1 - Item 11), press out the excess oil. Trim
the pad as necessary to insure a proper fit.
H. Install the felt lubricating pad (26).
CAUTION: Make sure the lower shock absorber (22) is butted up firmly against the shoulder in the upper end of the upper shock
absorber (29) when installing the support (11) to prevent the ring (13) from expanding and locking in place in the shock
absorber.
I. Install gasket (12) and ring (13) on the support (11). Install the ring (13) with the narrow part of the chamfer facing the axle.
J. File the ends of ring (13) as necessary to obtain a 0.005 to 0.015 inch gap with the support (11) installed in the lower shock absorber assembly (22).
K. Assemble snap ring (23), scraper ring (24), and wiper ring (25) on the lower shock absorber (22). The wiper ring should be installed with the grooved
edge facing the axle and the beveled edge up. The cone of the scraper ring should face the axle.
L. Insert the lower shock absorber assembly (22) into the upper shock absorber assembly (29) and secure the wiper, scraper, and snap rings.
M. Install the upper and lower torque knees (16 and 17) and the torque knee pins (15).
N. Replace bushing (14) and fasten the two torque knees together.
O. Install the support (11) into the upper (29) and lower (22) shock absorbers with the filler plug opening toward the front of the strut, use the sleeve
retaining bar (6) to align the support assembly (11).
P. Install snap ring (10) in the upper shock absorber (29).
Q. Fill the strut, using the following procedure:
(1) Place the strut in the fully compressed position.
(2) Fill the strut with hydraulic fluid (Refer to Chapter 91, Consumable Materials, Chart 1 - Item 9) to the bottom of the gauge tube. Lubricate bearings
(35) with lubricant (Refer to Chapter 91, Consumable Materials, Chart 1 - Item 25).
(3) Work the strut slightly to eliminate any trapped air.
(4) Refill the strut to the correct level.
R. Install the filler valve gasket (2) and filler valve body (1) in the support (11). If the air valve core (4) has been removed, install a new core.
CAUTION: Make sure the torque knees are connected before inflating the strut.
S. Inflate the strut to 65 psi air pressure.
T. Apply a soap and water solution around the upper portion of the strut, especially around the brazed joint. Check the area for leaks. Release air pressure
before installing landing gear on airplane. Wipe off the soap and water and install valve cap.
U. Install the spacer shim (9) over the top of the upper shock absorber, place the sleeve assembly (8) on top of the shim, and install the sleeve retainer bar
(6) on the sleeve.
NOTE: On LJ-502 and after and on LW-1 and after, the clearance between the top side of the snap ring (10) and the snap ring groove in
the upper shock absorber (29) must not exceed 0.003 inch. If necessary, peel laminations from the shim (40) under the retainer bar
(6) until the clearance is within the allowable limits.
CAUTION: Verify position and direction of the nose gear straightener bracket (5) as noted during removal procedure. It is possible to
install the straightener bracket backwards (180°). Improper installation may cause the nose wheel to missalign with the
wheel well during retraction resulting in damage to the airplane.
V. Install the nose gear roller (7) in the nose gear straightener bracket (5), and secure the straightener bracket (5) over the sleeve retainer bar (6).
W. Measure the distance between the nose gear sleeve assembly (8) and the shock brace casting upper bearing (35) or between the shock brace casting
lower bearing (35) and the lower part of the upper shock absorber assembly (29). A maximum gap of 0.015 inch is permissible. Part of spacer shim (9)
may be added or removed to obtain the desired clearance.
X. Remove the safety wire tied between the upper shock absorber assembly and the casting.
Y. On LJ-577 and after, LW-51 and after and prior airplanes in compliance with Service Instructions No 0516-200 or subsequent, lubricate the torque knee
joints with grease (Refer to Chapter 91, Consumable Materials, Chart 1 - Item 10).
Nose Landing Gear Manufacturing and Wear Tolerances(Continued)
Chart 1
Nose Landing gear Manufacturing and Wear Tolerances
NOTE: All dimensions are given in inches (Refer to Figure 202). Wear limits noted below may vary additionally as long as total joint
looseness does not exceed 0.025 inch.
Item I.D. O.D. Remarks
Top Brace Assembly (30)
Bearings (35) 3.504 to 3.502 3.631 to 3.629
Bushings (37) 0.6265 to 0.6245 0.7210 I.D. = 0.6265 maximum wear tolerance. Replace if worn.
(I.D. dimension is after line reaming.)
Bushings (34) 0.5010 to 0.5000 0.6240 to 0.6230

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 King Air Series Component Maintenance Manual (Rev C0)
32-20-10 (Rev C0)

Chart 1
Nose Landing gear Manufacturing and Wear Tolerances
NOTE: All dimensions are given in inches (Refer to Figure 202). Wear limits noted below may vary additionally as long as total joint
looseness does not exceed 0.025 inch.
Item I.D. O.D. Remarks
Bolt (36) 0.4995 to 0.4985 Replace if worn.
Bushings (41) 0.6245 to 0.6250 0.7500 to 0.7490 Not installed on airplanes prior to LW-51 and LJ-577.
Bushing (33) 0.4990 to 0.4980 0.5941 to 0.5934
Bushing (38) 0.3780 to 0.3750 0.4980 to 0.4950
Aluminum Top Brace Assembly (30) Installed on airplanes LJ-1073 and after, and earlier
airplanes with Kit P/N 101-8021 installed.
Bearings (35) 3.500 to 3.502 3.631to 3.629
Bushings (37) 0.6265 to 0.6245 0.8768 to 0.8763 I.D. = 0.6265 maximum wear tolerance. Replace if worn.
(I.D. dimension is after line reaming.)
Bushings (34) 0.5010 to 0.5000 0.6240 to 0.6230
Bolt (36) 0.4995 to 0.4985 Replace if worn.
Bushing (33) 0.4990 to 0.4980 0.5941 to 0.5934
Bushing (38) 0.3780 to 0.3750 0.4980 to 0.4950
Upper Shock Absorber Assembly (29)
Tube (29) 3.497 to 3.494
Internal and Lower Brazed Bearings 2.753 to 2.751 2.755 maximum wear tolerance.
Lower Shock Absorber (22)
Piston 2.465 to 2.461 2.749 to 2.747 O.D. = 2.746 maximum wear tolerance. Inspect O.D. for
nicks and scoring.
Restrictor Support (11)
Lower End 2.428 to 2.425 0.005 maximum wear on a side.
Upper and Lower Torque Knees (16
and 17)
Pins (15) 0.6240 to 0.6230 0.6210 maximum wear tolerance.
Bushings (18) 0.6250 to 0.6220
Bushing (14) (used with 50-810032-8 0.3755 to 0.3745 0.4975 to 0.4960 I.D. = 0.380 maximum wear tolerance. +O.D. = 0.491
upper knee assembly) maximum wear tolerance.
Bushing (20)
P/N 105740X-YN0625 (used with 50- 0.5005 to 0.4995 0.6275 to 0.6260 I.D. = 0.505 maximum wear tolerance.
810032-8 aluminum upper knee assembly)
P/N 105740X-YA0630 (used with 50- 0.3755 to 0.3745 0.4975 to 0.4960 I.D. = 0.380 maximum wear tolerance.
810032-12 steel upper knee assembly)
Bushings (19) 0.3755 to 0.3745 0.5020 to 0.5010 I.D. = 0.380 maximum wear tolerance.
Bolt (42) 0.3740 to 0.3710 Replace if worn.

Chart 2
Nose Landing Gear Actuator Clevis Manufacturing and Wear Tolerances
NOTE: All dimensions are given in inches (Refer to Figure 203).
Item I.D. O.D. Remarks
Actuator
Clevis Attach Holes (1) Nose Gear 0.250 to 0.254 0.257 maximum wear tolerance.
(Mechanical)

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 King Air Series Component Maintenance Manual (Rev C0)
32-20-10 (Rev C0)

Chart 2
Nose Landing Gear Actuator Clevis Manufacturing and Wear Tolerances
NOTE: All dimensions are given in inches (Refer to Figure 203).
Item I.D. O.D. Remarks
Clevis Attach Holes (1) Nose Gear 0.3120 to 0.3160 0.3260 maximum wear tolerance.
(Hydraulic)

4. Nose Landing Gear Actuator Disassembly

A. Remove the pin attaching clevis (1) to the nut assembly (9), and remove the clevis (1), spring (2), and retainer (3) (Refer to Figure 203).
B. Remove the four bolts attaching covers (4 and 5) to housing (18). Remove the lower cover (5) and any shims between it and the housing. Remove
packing (7) from the cover.
C. Remove screw assembly (8), nut assembly (9), cover (4), and upper bearing (10) from the housing.
D. Remove the screw assembly (8) from the nut assembly (9).
E. Press the cover (4) and upper bearing (10) off the screw assembly (8).
F. Press the grease seal (11) out of the cover.
G. Remove the lower bearing (12).
H. Remove the plug (13).
I. Remove snap ring (14), then remove pinion gear (15) from the housing by driving on the shaft end. Remove bearings (16 and 17).

5. Nose Landing Gear Actuator Cleaning and Parts Replacement

A. Wash all parts with solvent (Refer to Chapter 91, Consumable Materials, Chart 1 - Item 6) and inspect for damage and wear. Replace bearings (12) at
overhaul (Refer to Figure 203).
NOTE: When replacing bearings (10, 12, 16, and 17), use only the proper replacement bearings as specified in the Parts Catalog.

6. Nose Landing Gear Actuator Assembly

A. Fill the nut assembly (9) 1/2 full with lubricating grease (Refer to Chapter 91, Consumable Materials, Chart 1 - Item 4) (Refer to Figure 203).
B. Screw nut assembly (9) into screw assembly (8). Run the threads completely in and out to make sure they do not bind.
C. Slide bearing (10) over screw assembly (8) and insert the entire assembly into housing (18). The face of the bearing race containing the part number
must be out.
D. Slide lower bearing (12) over nut assembly (9), position any shims which were between the housing and lower cover (5), install packing (7) in the lower
cover (5), and install the lower cover (5) on the housing.
E. Install top cover (4) on the housing.
CAUTION: The adjustment is critical for proper operation of the actuator. It must be made with the pinion gear removed.
F. After all bolts have been tightened, check the end play of the screw assembly. Add or remove shims between housing (18) and lower cover (5) until
there is a maximum end play of 0.004 inch and a minimum of 0.000 inch. If necessary, use a press on the actuator to confine end play within the proper
limits.
G. Remove screw assembly (8) and nut assembly (9) from the housing (18).
H. Install bearing (16) on the pinion gear (15) with the “X” out, and place the shaft in housing (18).
I. Install bearing (17) and snap ring (14).
J. Repeat Steps C. through F.. Check meshing of the screw assembly gear with the pinion gear to make sure they rotate freely.
NOTE: If the 50-820145 pinion is replaced by a 50-820243 pinion on airplanes prior to LJ-116, the 50-820225 housing must also be replaced
by a 50-820245 housing. The 50-820225 housing is identified by a yellow band on the base of the actuator housing encircling the
nut assembly, while the 50-820245 housing is identifiable by a green band in the same location. Once the original pinion gear and
screw housing set have been replaced, either part may be replaced separately.
K. Place retainer (3) and spring (2) over clevis (1), insert the clevis into the nut assembly, and install the retaining pin.
L. Apply sealant (Refer to Chapter 91, Consumable Materials, Chart 1 - Item 15) to grease seal (11), the top cover (4), and slide grease seal (11) over the
screw assembly (8) and press into place.
M. Fill the housing 1/2 full with grease (Refer to Chapter 91, Consumable Materials, Chart 1 - Item 4) and install plug (13).

7. Nose Landing Gear Actuator End Play

A. Nose Landing Gear Actuator end play limits between screw (8) and nut (9) are as follows:
B. If less than 0.012 inch, actuator may be continued in service subject to normal maintenance procedures (Refer to Figure 203).

8. Nose Landing Gear Actuator Proof Test and Break-In

NOTE: All loads are to be applied to the clevis (1) and in the direction of travel shown by the arrow in Figure 203.

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 King Air Series Component Maintenance Manual (Rev C0)
32-20-10 (Rev C0)

A. Apply 550 ± 25 pounds tension load to clevis. The pinion gear (15) should have backlash of 0.002 inch and must not bind.
B. Apply 200 ± 25 pounds compression load to clevis. Run a minimum of 5 cycles through retraction and extension. Cool the actuator for 5 minutes after
each 3 cycles. Measure and record the end play between the actuator nut and screw.
C. Apply 500 ± 50 lbs. tension load through three full cycles then three full cycles compression load. Actuator shall not bind, squeal or bottom out at full
travel.
D. Remove the 500 ± 50 lbs. compression load and recheck the end play between the actuator nut and screw. There should be no increase in the actuator
end play between the nut and screw.
E. The actuator end play, measured from the nut to the housing, may be a maximum of 0.005 to 0.010 inch.

9. Nose Landing Gear Drag Brace Disassembly

A. Remove the cotter pin, nut, washer, bushings (3) and stop bolt (2) securing the yoke (4) to the upper drag leg (7) (Refer to Figure 204).
B. Remove the cotter pin, washers, nut and hinge bolt (1) securing the upper drag leg (7) to the lower drag legs (11) Remove the bushings (9 and 10).
C. Remove the bolts and washers securing the bracket (12) to the lower drag leg (11).
D. Remove the downlock indicator switch (8) from the upper drag leg (7).
E. Remove the bushings (9 and 10) from the lower drag leg (11).

10. Nose Landing Gear Drag Brace Cleaning and Parts Replacement

A. Wash all parts in solvent (Refer to Chapter 91, Consumable Materials, Chart 1 - Item 6) and dry with filtered, compressed air. Inspect the drag brace for
nicks, cracks, and distortion, especially at the bushings and pivot points. Check for excessive wear in accordance with the manufacturing tolerances
and wear limits in Chart 3. Replace all damaged or excessively worn parts.

11. Nose Landing Gear Drag Brace Assembly

CAUTION: Prior to LJ-577 and LW-51 unless reworked to Service Instruction No.0516-200, coat the drag leg bolts and bushings (1, 9, and 13
of Figure 204) with metal protector (Refer to Chapter 91, Consumable Materials, Chart 1 - Item 8) at 6 month intervals to preclude
galvanic reaction between them and the teflon bushing used with them.
A. Install the bushings (9 and 10) in the lower drag leg (11) (Refer to Figure 204).
B. Attach the yoke (4) to the upper drag leg (7) with the stop bolt (2), bushings (3), washers, nut, and cotter pin. Coat the stop bolt lightly with grease
(Refer to Chapter 91, Consumable Materials, Chart 1 - Item 22) prior to insertion into the bushings.
C. Attach the lower drag leg (11) to the upper drag leg (7) with the hinge bolt (1), bushings (9 and 10), washers, nut, and cotter pin. Torque the hinge bolt
(1) from 200 to 400 in.-lbs.
D. Secure the bracket (12) to the lower drag leg (11) with the attaching bolts, and washers, then safety the bolts.
E. Install the downlock indicator switch (8) on the upper drag leg (7).

12. Shimmy Damper Disassembly

A. Remove the snap ring (1), scraper ring (2) and end bearing (4) from the aft end of the barrel (Refer to Figure 205).
B. Remove the packings (3 and 5) from the end bearing.
C. Remove the fitting (16), nut (17), and lubrication fitting (18) from the piston rod (15).
D. Remove the snap ring (1), scraper ring (2), and end bearing (4) from the forward end of the barrel.
E. Remove the packings (3 and 5) from the forward end bearing (4).
F. Remove the piston rod assembly (15) from the barrel and remove the packing (12) from the damper piston.
CAUTION: The piston spring (9) is compressed. Remove the snap ring (7) and washer (8) carefully.
G. Remove the snap ring (7), washer (8), and aft piston spring (9) from the piston rod.
H. Remove the aft floating piston (10) from the piston rod (15) by screwing a long bolt with a 10-32 thread into the piston and pulling it out. Remove the
packing (11) from the floating piston.
I. Insert the 10-32 bolt into the aft end of the piston rod. Apply pressure on the forward floating piston (10) to compress the forward piston spring (9), and
drive out the retaining pin (13) holding the damper piston (14).
J. Slowly release the pressure on the floating piston, then push it out the aft end of the piston rod and remove the packing from the piston.
K. Remove the forward spring (9) and slide the damper piston (14) off the rod.
Chart 3
Nose Landing Gear Drag Brace manufacturing and Wear Tolerance
NOTE: All dimensions are given in inches (Refer to Figure 204).
Item I.D. O.D. Remarks
Upper Drag Leg (7)
Forward Attachment Holes 0.629 to 0.625

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 King Air Series Component Maintenance Manual (Rev C0)
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Chart 3
Nose Landing Gear Drag Brace manufacturing and Wear Tolerance
NOTE: All dimensions are given in inches (Refer to Figure 204).
Item I.D. O.D. Remarks
Pin (6) 0.624 to 0.623
Yoke Bore (4) 0.3790 to 0.3750 0.385 maximum wear tolerance.
Lower Drag Legs (11) In the area where the stop bolt on the upper drag leg
contacts the lower drag leg with the landing gear in the
down and locked position, the portion of the lower drag leg
perpendicular to the bolt is limited to a minimum
thickness of 0.40 inch
Attachment Holes 0.8755 to 0.8747
Bushing (9) 0.7500 to 0.7400 0.7515 maximum wear tolerance.
Bushing (10) 0.6255 to 0.6245 0.7480 to 0.7490 0.747 maximum wear tolerance.
Bolts (1 and 13) 0.6240 (maximum after Replace if worn.
cad plating)

13. Shimmy Damper Cleaning and Parts Replacement

A. Repairs on the shimmy damper should be confined to replacing worn or leaking packings or replacing the complete assembly. When disassembled,
clean with solvent (Refer to Chapter 91, Consumable Materials, Chart 1 - Item 6) and lubricate the parts with hydraulic fluid (Refer to Chapter 91,
Consumable Materials, Chart 1 - Item 9

14. Shimmy Damper Assembly

A. Replace the packing (11) on one floating piston, then insert one piston spring and the piston into the piston rod (15). With a long 10-32 bolt, push the
piston forward to compress the spring until the damper piston retaining pin can be inserted (Refer to Figure 205).
B. Place the damper piston (14) on the piston rod (15) and insert the retaining pin (13). Replace the packing (12) on the damper piston.
CAUTION: If the piston is installed in the wrong direction, the mounting lug will break off the strut.
C. Insert the piston rod assembly into the barrel. Make sure the threaded end of the rod is at the forward end of the barrel. The attachment holes in the
barrel are closer to the front than to the rear.
D. Replace the packings in one end bearing (4), insert the bearing and scraper ring (2) in the forward end of the barrel, and secure with snap ring (1).
E. Clamp the damper in a vise with the open end up and fill the barrel and piston rod with clean hydraulic fluid (Refer to Chapter 91, Consumable Materials,
Chart 1 - Item 9). Work the piston rod up and down until bubbles stop appearing in the fluid, then refill the barrel and the piston rod.
F. Replace the packings in the other end bearing (4), insert the bearing and the scraper ring (2) into the barrel, and secure with snap ring (1).
G. Engage the forward floating piston (10) with the 10-32 bolt and pull forward. At the same time, insert the aft floating piston (10) and spring (9) and push
down. The piston will follow the fluid down and prevent the entry of air into the rod assembly. Secure the spring and piston with the washer (8) and snap
ring (7).
H. To check the level of the fluid in the piston rod, measure the distance of both floating piston races from the ends of the rod. The distance may be
checked with a wire. The forward piston should be 2.63 to 2.88 inches from the forward end of the shaft and the rear piston should be 2.13 to 2.38
inches from the opposite end. Add or remove hydraulic fluid if the pistons are not properly positioned.

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Figure 201 : Sheet 1 : Packing Removal and Installation

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Figure 202 : Sheet 1 : Nose Landing Gear Assembly

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Figure 203 : Sheet 1 : Nose Landing Gear Actuator

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Figure 204 : Sheet 1 : Nose Landing Gear Drag Brace

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 King Air Series Component Maintenance Manual (Rev C0)
32-20-10 (Rev C0)

Figure 205 : Sheet 1 : Nose Landing Gear Shimmy Damper

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Retain printed data for historical reference only. For future maintenance, use only current data. Print Date: Thu Apr 10 15:02:58 CDT 2025