Adjustment Of Main Landing Gear - Piper Cheyenne IIIA Airplane Maintenance Manual

PIPER AIRCRAFT
PA-42-720 (Advanced Trainer)
MAINTENANCE MANUAL
A. Main Gear and Doors (continued)
3. Installation of Main Landing Gear (refer to 32-10-00 Figure 401) (continued)
(f) Position down lock switch bracket between forward and aft upper drag links and bolt in place.
(g) The down lock hook is installed on the drag link assembly as follows:
(1.) Place U end of down lock spring over the back of the hook with the loops toward the back.
(2.) Spread the spring and fit loops over bushing extending through hook.
(3.) Insert ends of spring into holes located in down lock switch bracket on each side of drag
link assembly. Push hook down between two upper drag links until bolt holes in the links
align with bushing hole of the hook.
(4.) Insert pivot bolt and on each side of the bushing, install spacer washers to maintain a
minimum amount of side play. Secure bolt and safety it.
(h) The down lock cable is installed by bolting the sliding end of cable to the down lock hook and
the other end of the upper drag link arm while attaching the landing gear actuating cylinder.
Check lubrication of sliding end of down lock cable.
(i) Lubricate landing gear assembly. (refer to 12-20-00 Chart 2 and Figure 301.)
(j) Check main gear adjustment, operation, and alignment.
4. Adjustment of Main Landing Gear
(a) With the airplane on jacks and gear extended, disconnect inboard and outboard gear door
operating rods, keeping doors in the open position.
(b) Disconnect down lock operating rod or cable from down lock hook.
(c) The through-center adjustment of the side brace links is as follows:
(1.) Maintain gear in down locked position with stop surfaces of the side brace links touching.
(2.) Check that the linkage is 0.219 to 0.281 of an inch through center.
(3.) If one side of the stop surfaces does not touch, file it to obtain desired through travel.
CAUTION: DO NOT FILE PIN OR LET LINKAGE EXCEED 0.281 INCH THROUGH
CENTER.
NOTE: A fabricated tool can be constructed to check through-center travel of the side
brace link assembly while the links are installed. (refer to 32-10-00 Figure 501.))
(d) Use the fabricated tool in the following procedure:
(1.) The gear must be down and locked with no hydraulic pressure on system.
NOTE: The airplane can either be on or off jacks.
(2.) Remove cotter pins which safety the nuts securing both upper side brace links to
attachment plates.
NOTE: On right gear only, remove pin at the nut that securing the lower link to the gear
housing. Do not remove the nuts.
(3.) Place tool tube through elongated hole in tool plate. Place tube over and between upper
link attachment nuts.
EFFECTIVITY:
040-999
32-10-00Jan
10/90
Jan 10/90