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
Summary of Contents for Arrow IV
Page 18: ...CHAPTER AIRWORTHINESS LIMITATIONS 1A18...
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Page 22: ...CHAPTER TIME LIMITS MAINT CHECKS 1A22...
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Page 40: ...CHAPTER DIMENSIONS AND AREAS 1B16...
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Page 53: ...CHAPTER LIFTING AND SHORING 1C5...
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Page 57: ...CHAPTER LEVELING AND WEIGHING 1C9...
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Page 62: ...CHAPTER TOWING AND TAXIING 1C14...
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Page 66: ...CHAPTER PARKING AND MOORING 1C18...
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Page 70: ...CHAPTER REQUIRED PLACARDS 1C22...
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Page 77: ...CHAPTER SERVICING 1D5...
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Page 110: ...CHAPTER STANDARD PRACTICES AIRFRAME 1E14...
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Page 117: ...CHAPTER ENVIRONMENTAL SYSTEM 1E21...
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Page 169: ...CHAPTER AUTO FLIGHT 1H1...
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Page 176: ...CHAPTER COMMUNICATIONS 1H8...
Page 185: ...CHAPTER ELECTRICAL POWER 1H17...
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Page 233: ...CHAPTER FLIGHT CONTROLS 1J17...
Page 297: ...CHAPTER FUEL 2A18...
Page 320: ...CHAPTER HYDRAULIC POWER 2B17...
Page 355: ...CHAPTER LANDING GEAR 2D4...
Page 418: ...CHAPTER LIGHTS 2F19...
Page 430: ...CHAPTER NAVIGATION AND PITOT STATIC 2G7...
Page 444: ...CHAPTER OXYGEN SYSTEM 2G21...
Page 464: ...CHAPTER VACUUM SYSTEM 2H17...
Page 473: ...CHAPTER ELECTRICAL ELECTRONIC PANELS AND MULTI PURPOSE PARTS 2I2...
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Page 477: ...CHAPTER STRUCTURES 2I6...
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Page 496: ...CHAPTER DOORS 2J1...
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Page 505: ...CHAPTER STABILIZERS 2J10...
Page 514: ...CHAPTER WINDOWS 2J19...
Page 519: ...CHAPTER WINGS 2J24...
Page 550: ...CHAPTER PROPELLER 3A18...
Page 565: ...CHAPTER STANDARD PRACTICES ENGINE 3B9...
Page 568: ...CHAPTER POWER PLANT 3B12...
Page 592: ...CHAPTER ENGINE FUEL AND CONTROL 3C12...
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Page 611: ...CHAPTER IGNITION 3D7...
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Page 655: ...CHAPTER ENGINE INDICATING 3F16...
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Page 664: ...CHAPTER EXHAUST 3G1...
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Page 669: ...CHAPTER OIL SYSTEM 3G6...
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Page 673: ...CHAPTER STARTING 3G10...
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Page 688: ...CHAPTER TURBINES 3H1...
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Page 694: ...CHAPTER 91 CHARTS AND WIRING DIAGRAMS 3H7...
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