Piper Aircraft Corporation Cherokee 140 PA-28-140, Service Manual

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PIPER CHEROKEE SERVICE MANUAL
VIIA - LANDING GEAR AND BRAKE SYSTEM 01/31/08
(PA-28R)
2I8
7A-25. INSTALLATION OF MAIN LANDING GEAR. (Refer to Figure 7A-9.)
NOTE: When assembling components of the landing gear, lubricate bearings, bushings and friction
surfaces with proper lubricant as described in Section II.
a. Insert a gear support bearing (53 or 54) in each support fitting (1 or 16) and secure with snap rings
(2). Check bearing (53) for excess end play, shim as necessary with shim washers (49) (P/N 62833-
44).
b. The gear housing may be installed in the wheel well of the wing by the following procedure:
1. Place a spacer washer (52) and then the forward support fitting (16) on the forward arm of the
housing. Ascertain that the barrel nut (55) is positioned in the arm and insert the attachment
bolt through washer (51) and the fitting into the arm. Tighten bolt and ascertain that the
bearing is free to rotate.
2. Position the aft support fitting (1) at its attachment point in the wheel well and secure with
bolts, washers and nuts. Install the nuts and washers by reaching through the access hole on the
underside of the wing.
3. With the retainer tube (4) for the aft arm of the housing in hand, reach up through the access
opening and insert the tube into the support fitting (1) through the hole in the web.
4. Position the gear housing up in the wheel well and install the forward support fitting (16) bolts
and washers. (One each AN960-416 and AN960-416L washer per bolt.)
5. Push the retainer tube into the arm of the housing and secure with bolt.
6. Check that the gear rotates freely in its support fittings and recheck thrust.
7. Connect the brake line to its mating line in the wheel well and bleed brakes as given in
paragraph 7A-73.
c. The gear side brace link assembly may be installed by the following procedure:
1. Position the link support bracket (27) with swivel stud (26) installed at its attachment point on
the web of the spar and secure with bolts and washers.
NOTE: When installing a new wing, it will be necessary to back drill two (2) holes 0.250 inch
and countersink 100° x .499 through the spar cap. (Screw head should be flush with
spar). Use hole in the support bracket as a guide in the drilling.
2. Ascertain that the upper and lower links (28 and 33) are assembled with downlock hook (30),
retraction fitting (21), etc. attached, and the through travel of the links and downlock hook
clearance checked according to paragraph 7A-24.
3. Attach the upper link to the swivel stud of the support fitting and secure with bolt, bushing,
washer, nut and cotter pin.
4. The actuating cylinder rod end bearing (46) and lower side brace link (33) may be attached
respectively to the retraction fitting (21) and gear housing during the adjustment of the landing
gear.
d. Ascertain that the landing gear is lubricated per Lubrication Chart.
e. Check adjustment of the landing gear per paragraph 7A-26.
f. Check alignment of the wheel per paragraph 7A-27.
g. Install the access plate on the underside of the wing and remove the airplane from jacks.