Adjustment Of Main Landing Gear - Piper Navajo PA-31 Service Manual

PIPER NAVAJO SERVICE MANUAL
5. Position the lower link (35) between the upper drag link ends, install bolt assembly and
tighten to allow the link to turn free with no side play.
6.
Attach the lower drag link (35) to the landing gear housing (40), secure and safety. Move
the gear in and out of the downlock position several times to determine that there is no binding.
f.
Position the downlock switch bracket (33) between the forward and aft upper drag links and bolt
in place.
g. The downlock hook (34) may be installed on the drag link assembly by the following procedure:
1. Place the "U" end of the downlock spring (68) over the back of the hook (34) with the
loops also toward the back.
2.
Spread the spring and fit the loops over the bushing that goes through the hook.
3.
Insert the ends of the spring into holes located in the downlock switch bracket (33) on each
side of the drag link assembly. Push the hook down between the two upper drag links until the bolt holes in
the links align with the bushing hole of the hook.
4. Insert the pivot bolt and on each side of the bushing install spacer washers to maintain a
minimum amount of side play. Secure bolt and safety.
h. The downlock cable or rod (23) may be installed by bolting the proper end of the rod or cable to the
downlock hook and the other end to the upper drag link arm, at the same time attaching the landing gear
actuating cylinder (15). also install anti-rotation clip. (See Sketch B of Figure 7-7 )
i.
Lubricate the landing gear assembly. (Refer to Lubrication, Section II.)
j. Check the main gear adjustment, operation and alignment.
7-24. ADJUSTMENT OF MAIN LANDING GEAR. (Refer to Figure 7-7.)
a. With the airplane on jacks and the gear extended, disconnect the inboard and outboard gear door
operating rods and secure doors in the open position.
b. Disconnect the downlock operating rod or cable (23) from the downlock hook (34).
c. With the gear in the downlocked position and both stop surfaces of the side brace links touching,
ascertain that the linkage is .063 to .156 inch through center. If one side of the stop surfaces does not
touch, and filing will not let the link exceed the .156 inch through travel, then this may be done. If filing
will bring it beyond the .156 inch through travel, then a link or links must be replaced.
NOTE
A fabricated tool may be constructed to check through center
travel of the side brace link assembly while the links are installed.
(Refer to Figure 7-22.)
1. To use the fabricated tool to check through travel of the side brace link assembly, ascertain
that the gear is in the down locked position with no hydraulic pressure on the system. The airplane may be
either on or off jacks.
Revised: 3/2/84
LANDING GEAR AND BRAKE SYSTEM
2F9