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

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PIPER CHEROKEE SERVICE MANUAL
01/31/08 VIIA - LANDING GEAR AND BRAKE SYSTEM
(PA-28R)
2H15
c. The drag links (32 and 35) and gear tension spring arm (53) may be installed by the following
procedure:
1.
Ascertain that the upper and lower links (32 and 35) are assembled with the downlock hook
attached, and the through travel of the links checked according to paragraph 7A-10.
2. Position the link assembly to allow the bolt holes in the links to align with the bolt holes in the
gear housing and the engine mount. Install the link attachment bolts.
3. Install nuts and washers on the upper link (35) attachment bolts. Tighten the nuts to allow the
links to rotate freely and safety.
4. Check alignment of the downlock hook to determine if it grips the roller bearing so as not to
contact the bolt head, the bearing attachment block or washer. If the downlock hook is inboard,
or it contacts the bolt head, shim between the bearing and the bearing attachment block with
washer AN960-10L, not to exceed three. The bearing must be free to rotate, therefore, it may
be necessary to replace the bearing retaining bolt with longer bolt, AN23-36A, depending on
the number of washers used. Should the downlock hook be onboard, or in contact with the
bearing attachment block, add one washer, P/N 62833-40 of P/N 62833-41 between the engine
mount (55) and upper drag link (35). Washer, P/N 6283341, is to be tried first.
5. Install the gear tension spring arm (53) on the drag link bolt (29) on the right side of the gear
oleo housing (54), secure and safety. A washer is installed on the bolt between the lower drag
link and the arm.
d. Retract and extend the landing gear several times to ascertain smoothness of operation. Also check
that the drag link assembly falls into the through center-locked position.
e. Retract the gear and connect the gear downlock spring (42) between the downlock hook (43) and
the upper drag link (35).
f. Extend the gear and connect the two gear tension springs (15 and 17) between the attachment point
on the oleo housing (54) and the spring arm (53).
g. Ascertain that the landing gear is lubricated per Lubrication Chart, Section II.
h. Check adjustment of the gear per paragraph 7A-12, 7A-13, or 7A-13a.
i. Install engine cowling. (The cowl support jacks located at each forward side of the nose gear door
hinges are adjusted down to contact the cowl surface after attaching screws are secure.)
j. Retract landing gear and check door operation as per paragraph 7A-18.
k. Check the alignment of the nose gear per paragraph 7A-14.
1. Remove the airplane from jacks.
7A-12. ADJUSTMENT OF NOSE LANDING GEAR (Without Gear Up Stop). (Refer. to Figure 7A-3.)
a. Place the airplane on jacks. (Refer to Jacking, Section II. )
b. With the gear extended, disconnect the nose gear door retraction rods from each door by removing
the rod attaching bolts. If desired, the lower engine cowl may be removed to facilitate easier access
for adjustments.
c. Retract the landing gear hydro-electrically by turning the master switch on, raising the emergency
gear extension lever and moving the gear selector handle to the up position. Retain the emergency
extension lever in the up override position.
d. Clearance between the strut housing (10) and the cross-over tube (2) where the steering bellcrank
(1) attaches should be 0.015 ± 0.003 of an inch with the piston of the actuator cylinder bottomed.
Should this dimension be incorrect and it will require more than 0.010 of an inch to bring the
housing to the correct clearance, then block the gear in the up position, disconnect the piston rod
end bearing from the downlock by removing the attaching bolt, loosen the jam nut on the end
bearing to obtain correct adjustment. Reinstall attaching bolt and safety.