INSTALLATION OF WING (figure 57-1)
1. Ensure that fuselage is positioned solidly on a support cradle.
2. Place wing in position for installation, with spar end a few inches from side of fuselage and set on
trestles.
3. Prepare the various lines, control cables, etc., for inserting into wing or fuselage when wing is slid into
place. Ensure that bushing is in place in forward wing fitting.
—NOTE—
The aft wing fitting on a new service wing assembly is not drilled.
It is necessary to drill fitting to proper diameter (0.3745 to 03765
in.) prior to installation. It is suggested that wing be placed into
position on fuselage. With wing held in position by forward wing
fitting bolt and main spar bolts, mark aft wing fitting using aft
fuselage fitting as a guide. Remove wing from fuselage, drill a
pilot hole in aft wing fitting followed by drilling of hole to the
correct size (0.3745 to 0.3765 in.). If fuselage fitting hole is
0.3135 it is permissible to enlarge the hole per figure 57-1, B-II.
4. Slide wing into position on fuselage.
5. Install eighteen main spar bolts in accordance with bolt legend.
—NOTE—
When replacing a wing assembly, ensure wing butt clearance is
maintained. (Refer to sketch A, figure 57-1.)
6. Install bolt, washers, and nut that attach front spar with fuselage fitting. A minimum of one washer is
required under nut. Add washers as needed to leave a maximum of one and one-half threads visible or
a minimum of bolt chamfer exposed.
7. Insert number of washers required between forward face of wing fitting and aft face of fuselage fitting.
—NOTE—
When installing new service wing requiring 3/8 in. rear spar
attachment bolt, refer to step b.
a. PA-28-236 aircraft with S/N: 28-7911001 to 28-8011137—Maximum number of washers(AN960-
516) allowed is two. It is also acceptable to have faces of fittings against each other. After required
washers are inserted between plates, install bolt and check to ensure that no threads are bearing on
forward plate prior to installing nut. Use shortest bolt which will leave 0.580 of an inch minimum
from fitting to end of bolt. Add washers (AN960-516) as required (minimum of one) to leave a
maximum of one and one-half visible thread, or minimum of bolt chamfer exposed after nut is
tightened.
b. PA-28-236 aircraft with S/N: 28-8011138 and up—Maximum gap between forward face of wing
fitting and aft face of fuselage fitting is 0.15. Use any combination of AN960-616L and AN960-
616 washers required. Use AN960-616 or AN960-616L washers under nuts as required to leave a
minimum of one and one-half usable threads on bolt-exposed.
57 - 41 - 00
Page - 57-06
Reissued: August 1, 1986
2G19
PIPER AIRCRAFT
PA-28-236
MAINTENANCE MANUAL
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