Piper PA-28-161, Maintenance Manual

Page: 802 / 1104

PIPER AIRCRAFT, INC.
PA-28-161, WARRIOR III
MAINTENANCE MANUAL
PAGE 4
Nov 30/06
4H8
57-40-00
WARNING: DO NOT DRIVE OUT SPAR TO FUSELAGE ATTACH BOLTS. TAKE EXTREME
CARE NOT TO DAMAGE BOLTS OR BOLT HOLES. NUMBER BOLTS AND
BOLT HOLES TO ENSURE THAT, IF REUSED, THE SAME BOLTS ARE
REINSTALLED IN THE SAME HOLES.
(18) For the wing(s) being removed, remove the eighteen (18) main spar to fuselage (i.e. - spar
carrythrough) attachment bolts. Discard nuts.
(19) Slowly remove the wing being cer tain that all electrical leads, cables and lines are
disconnected. Ensure that no undue up or down pressure is exerted on the inboard spar within
the spar carrythrough.
B. Installation
NOTE: Whenever a wing is removed and reinstalled, conduct Wing Spar Inspection, 57-10-00, and
make an appropriate aircraft logbook entry documenting the inspection for that wing.
NOTE: When installing a “replacement” wing, perform Stall Warning Flight Test Procedure, 27-30-00,
upon completion of wing installation.
NOTE: If a factory replacement wing is being installed, the wing aft spar fitting must have a .3745 / .3765
diameter hole installed in line with the existing hole in the fuselage fitting, using suitable tooling to
ensure alignment of the holes.
(1) Ascertain that the fuselage is positioned solidly on a support cradle.
(2) Place the wing in position for installation, with the spar end a few inches from the side of the
fuselage and set on supports.
(3) Prepare the various lines, control cables, etc., for inserting into the wing or fuselage when the
wing is slid into place. Insure that the bushing is in place in the fuselage forward wing attach
fitting. (See View A-A, Sketch A.)
(4) Slide the wing into position in the fuselage. Ensure that the lines, cable, and electrical leads
are carefully fed into place.
WARNING: DO NOT DRIVE SPAR TO FUSELAGE ATTACH BOLTS IN. TAKE EXTREME
CARE NOT TO DAMAGE BOLTS OR BOLT HOLES. IF REUSING BOLTS,
ENSURE THE SAME BOLTS ARE REINSTALLED IN THE SAME HOLES.
(5) Install the eighteen (18) main spar to fuselage (i.e. - spar carrythrough) attachment bolts in
accordance with the bolt legend in Figure 1. Use eighteen (18) new nuts (see bolt legend,
Figure 1).
(6) Install the bolt, washers, and nut that secures the front wing spar to fuselage attach fittings. A
minimum of one washer is required under the nut and head of bolt, then add washers as
needed to leave a maximum of one and on-half threads visible or a minimum of the bolt
chamfer exposed.
(7) Insert the number of washers required at the rear wing spar between the forward face of the
wing fitting and aft face of the fuselage fitting, as specified in Sketch B, Figure 1, to fill the gap. A
true “no-gap” condition with the faces of the fittings against each other is also acceptable. After
the required washers are inserted between the plates, install the bolt and check to insure that
no threads are bearing on the forward plate prior to installing the nut. Add washers, as specified
in Sketch B, Figure 1, as required (minimum of one), to leave a maximum of one and one-half
usable threads exposed.