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follows:
− Apply thread locker on stud
− Install stud into shock absorber rod. If
the stud and shock absorber rod does
not have a hole for spring pin
installation, drill a hole.
− Apply thread locker on spring pin
− Insert spring pin into holes of shock
absorber rod and stud
− Install nut into rod end bearing and
install rod bearing with nut into shock
absorber rod
− Install shock absorber plate, 10-rubber
dampers, and 9-shock absorber
washers
− Install shock absorber retainer, rubber
damper, washer, and secure with self
locking nut.
Use Loctite 243.
Use a clamping fixture. Touch up with
alodine after drilling.
Use Loctite 680.
Wipe thread locker excess.
The distance between the center of the rod
end bearing and the center of the shock
absorber retainer must be 245 mm (9.65
in).
(2) Install the shock absorber assembly to the
nose landing gear strut as follows:
− Apply a light corrosion protection on
strut pins and clip retainers
− Install the shock absorber assembly
using the strut pins
− Install the clip retainers and secure
with rivets.
Refer to Figure 2
Use Mastinox (6856K).
Clean corrosion excess
Use vinyl hammer to secure strut pins.
Landing Gear
DA20-C1 AMM
Page 206
30 Apr 2009 32-40-00 Doc # DA201-C1
Rev. 15
Detail Steps/Work Items Key Items
(3) Connect the shock absorber assembly to the
engine mount as follows.
− Apply corrosion protection to bolt
shank
− Install the bolt, washer, and nut
− Connect the lockwire.
Use LPS-3.
Clean corrosion inhibitor from the threads
(4) Remove the trestle from the front fuselage.
(5) Lower the nose wheel to the floor. Remove the weights from the rear
fuselage.
(6) Install the engine cowling. Refer to Chapter 71-10
4. Replace the Shock Absorber Assembly ElementsYou must replace cracked rubber damper.
Detail Steps/Work Items Key Items
(1) Remove the shock absorber assembly from
the airplane.
Refer to paragraph 3.A and 3.B.
WARNING: DO NOT STAND IN THE LINE OF THE SHOCK ABSORBER
ASSEMBLY WHEN YOU REMOVE THE NUT. THE ASSEMBLY
MAY EXPAND WITH A LOT OF FORCE.
(1) Remove the adjusting nut from the shock
absorber assembly.
(2) Remove the defective rubber damper.
(3) Install the new rubber damper.
(4) Install the adjusting nut. Refer to Figure 2.
The distance between the center of the
rod-end bearing and the center of the
shock absorber retainer must be 245 mm
(9.65 in). Measurement for new elements
and any play found when installed should
be adjusted out
(5) Install the shock absorber assembly in the
airplane.
Refer to paragraph 3.C.
DA20-C1 AMM
Landing Gear
Doc # DA201-C1
Rev. 15 32-20-00 Page 207
30 Apr 2009
Intentionally left blank
Landing Gear
DA20-C1 AMM
Page 208
30 Apr 2009 32-40-00 Doc # DA201-C1
Rev. 15
Figure 3: Adjust the Nose Wheel Steering Friction
DA20-C1 AMM
Landing Gear
Doc # DA201-C1
Rev. 15 32-20-00 Page 209
30 Apr 2009
5. Adjust the Nose Wheel Steering Friction
Steering friction prevents nose-wheel shimmy.
A. Equipment
Item Quantity Reference
Padded trestle 1 Commercial
Weight and strap 1 Commercial
Spring balance 1 Commercial
B. Procedure
Detail Steps/Work Items Key Items
(1) Use weights to hold the rear fuselage down
with the nose wheel clear of the ground.
Use a strap around the rear fuselage.
(2) Put a padded trestle under the front fuselage
just aft of the nose gear mounting.
(3) Remove the nose-wheel fairing.
(4) Adjust the nose-wheel fork pivot nut:
− Remove the cotter pin.
− Adjust the nut.
− Install a new cotter pin.
The nose-wheel must just caster when you
apply a force of 30 - 50 N (6.75 - 11.25 lb)
acting in the direction of the nose-wheel
axle. If the cotter pin hole does not align,
tighten the nut to the next slot.
Refer to Figure: 3.
(5) Apply corrosion protection to the stud, nut
and washers only.
Use CRC corrosion shell.
Do not get CRC corrosion shell on the tire
or fiberglass.
(6) Install the nose-wheel fairing.
(7) Remove the trestle from the front fuselage.
(8) Lower the nose wheel to the floor. Remove the weights from the rear
fuselage.
6. Nose Wheel Balancing
Always have a new nose-wheel balanced before installation.
Landing Gear
DA20-C1 AMM
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钻石20系列AMM 2(5)
