Piper Arrow IV, Руководство по обслуживанию

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3. The landing gear housing with components may be removed by the following procedure:
A. Disconnect the brake line at its upper end in the wheel well.
B. Disconnect the gear door actuating rod at the gear housing.
C. Remove the access plate located on the underside of the wing, aft of landing gear.
D. If not previously disconnected, disconnect the lower side brace link from the gear housing.
E. Disconnect the forward support fitting of the housing from the web of the main spar by removing
the fitting attachment bolts.
F. Remove the retainer tube in the aft support fitting that supports the aft arm of the housing by
reaching through the access opening on the underside of the wing, through the hole in the web and
removing the bolt that secures the tube in the housing. Insert a hook through the bolt hole in the
tube, and slide it aft from the support fitting. Remove the tube from the wing. Note the number of
spacer washers between the arm and support fitting.
G. Allow the gear to drop down removing it from the wing.
H. The aft support fitting may be removed by holding the nuts, reaching through the access opening,
and removing the fitting attachment bolts.
I. The forward support fitting may be removed from the arm of the housing by removing the bolt and
washer from the base side of the fitting. Slide the fitting from the arm. Remove the washer from
the arm.
4. Either bearing installed in the support fittings may be removed by removing the snap rings that hold
the bearing in the housing. Push the bearing from the housing.
CLEANING, INSPECTION AND REPAIR OF MAIN LANDING GEAR.
1. Clean all parts with a suitable dry type cleaning solvent.
2. Inspect the gear components for the following unfavorable conditions:
A. Bolts, bearing and bushings for excess wear, corrosion and damage.
B. Gear housing, side brace links, torque links and attachment plates for cracks, bends or
misalignment.
C. Downlock hook for excessive wear of the bearing surfaces.
3. Inspect the gear downlock spring for the following:
A. Excessive wear or corrosion, expecially around the hook portion of the spring. A spring should be
rejected if wear or corrosion exceeds one-quarter the diameter of the spring. Clean away all
corrosion and repaint.
B. Check the spring for load tensions below minimum allowable tolerance. The minimum tension of
the spring is 63 pounds pull at 7.9 inches. Measurement is taken from the inner side of each hook.
4. Check the general condition of each limit switch and its actuator, and wiring for fraying, poor
connections or conditions that may lead to failures.
5. Check side brace link through center travel by attaching the upper and lower links, setting them on a
surface table, and ascertaining that when the stop surfaces of the two links touch, linkage is not less than .062
nor more than .125 of an inch through center. Should the distance exceed the required through center travel and
bolt and bushings are tight, replace one or both links.
6. With the side brace links assembled and checked, ascertain that when the stop surfaces of the two links
contact, the clearance between each downlock hook and the flat of the downlock pin is not less than 0.010 of
an inch. Should clearance be less than that required, the hook only may be filed not to exceed a gap of more
than 0.025 of an inch. The maximum allowable clearance between each hook and the downlock pin that are
service worn is 0.055 of an inch. Should clearance be more than 0.055 of an inch, replace the pin, check
clearance and then if still beyond tolerance, replace hooks. The gap between each hook should be equal.
7. Repair of the landing gear is limited to reconditioning of parts such as replacing components, bearings
and bushings, smoothing out minor nicks and scratches and repainting areas where paint has chipped or peeled.
32-10-05
Page 32-16
December l, 1978
2D23
PIPER AIRCRAFT
PA-28RT-201 / 201T
MAINTENANCE MANUAL