TROUBLE-SHOOTING
1. General
Use the data below to trouble-shoot the main landing gear.
WARNING: YOU MUST DO A HARD LANDING CHECK AFTER A HARD LANDING.
HARD LANDINGS CAN CAUSE DAMAGE TO THE STRUCTURE AS
WELL AS THE LANDING GEAR.
Complaint Possible Cause Remedy
Strut bent. Hard landing. Do a hard landing check.
Refer to Chapter 05-50.
Replace the strut.
Negative camber. Strut bent, Hard landing. Do a hard landing check.
Refer to Chapter 05-50.
Replace the strut.
Too much tire wear. Incorrect toe-in. Adjust the toe-in.
Refer to Test Adjust The Main
Landing Gear procedure.
Landing Gear
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DA20-C1 AMM
Landing Gear
Doc # DA201-C1
Rev. 14 32-10-00 Page 201
30 Oct 2008
MAINTENANCE PRACTICES
1. General
These maintenance practices tell you how to remove and install components of the main landing
gear and adjust the main landing gear. Refer to the manufacturer for further data.
2. Remove/Install the Main Landing Gear Strut
A. Equipment
Item Quantity Reference
Airplane jacks 2 Commercial
Tail former 1 ?
B. Remove the Main Landing Gear Strut (Refer to Figure 1 - Sheet 1)
Detail Steps/Work Items Key Items
(1) Lift the airplane on jacks. Refer to Chapter 07-10
(2) Remove the wheel fairing:
− Remove the outer bolt.
− Remove 2 screws on the inner side.
If installed
(3) Remove the back-plate from the brake
caliper.
Refer to Chapter 32-40
(4) Remove the wheel. Refer to Chapter 32-40
(5) Release the brake caliper.
(6) Release the brake pipe from the strut. Tie the brake caliper back. Do not stress
the brake pipe.
(7) Remove the 4 bolts which attach the axle.
Remove the axle, torque-plate and fairing
mount.
Only if you will install a different strut.
(8) Disconnect the bonding cable from the strut.
(9) Remove the nut, washers and bolt at the
inner mount attachment-bracket.
(10) Remove the nuts and washers, retaining bar,
inserts and brass strips at the outer mount
attachment-bracket.
Hold the strut!
(11) Remove the strut. Move the strut outboard.
Landing Gear
DA20-C1 AMM
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Rev. 14
C. Install the Main Landing Gear Strut (Refer to Figure 1 - Sheet 1)
Detail Steps/Work Items Key Items
(1) Examine the spar bridge in the area of the
main gear mountings. Look specially for
damage to the GFRP structure
Refer to Chapter 51-10 for GFRP
inspection procedures.
(2) Put the new strut in position. Move it inboard through the fuselage slot.
(3) Put the inserts and brass strips in position
above and below the strut at the outer
mount.
Hold the strut!
Choose inserts to give 0.5mm (0.02 in)
compression when tight.
(4) Apply grease to the brass strips and the
bolts.
Use MIL-G-3545 grease.
(5) Install the retaining bar. Install the washers
and nuts to hold the retaining bar to the outer
mount attachment-bracket
Torque to 20 Nm (14.8 ft.lb.)
(6) Apply grease to the washers and the bolt. Use MIL-G-3545 grease.
(7) Install the bolt, washers and nut at the inner
mount attachment-bracket.
Refer to Figure 1 - Sheet 1. Make sure
that 1 plain washer and the belleville spring
washers are between the top of the strut
and the mounting block.
If necessary, install up to 2 plain washers
between the spring washers and the
mounting block to make the airplane level.
(8) Tighten the nut on the inner bolt. To give a height of the spring washers of
4 +0.5mm -0 (0.16 +0.02 -0 in).
(9) Connect the bonding cable to the strut. If you install a bonding terminal on a new
strut, remove the surface protection where
the terminal will attach. Then varnish the
area with NYCOTE 7-11.
(10) Install the axle, torque-plate and fairing
mount. Install the 4 bolts which attach the
axle.
Only if you install a different strut.
Torque 13.6 - 15.8 Nm (120 - 140 in.lb.).
(11) Attach the brake pipe to the strut.
(12) Install the brake caliper. Refer to Chapter 32-40
(13) Install the wheel. Refer to Chapter 32-40
(14) Install the back-plate to the brake caliper. Refer to Chapter 32-40
(15) Install the wheel fairing:
− Install the outer bolt.
− Install 2 screws on the inner side.
Airplanes with wheel fairing option only.
(16) Lower the airplane with the jacks.
(17) Do a test for correct adjustment of the
landing gear.
See paragraph 3
DA20-C1 AMM
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