THE NEW PIPER AIRCRAFT, INC.
PA-32-301FT / 301XTC
MAINTENANCE MANUAL
PAGE 4
Jun 1/03
4G20
57-40-00
B. Installation of Wing
(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 trestles.
(3) Prepare the various lines, control cables, etc., for inserting into the wing or fuselage when the
wing is slid into place.
(4) Slide the wing into position on the fuselage.
WARNING: DO NOT DRIVE BOLTS IN OR OUT OF THE MAIN SPAR ATTACHING BOLT
HOLES (C AND D IN FIGURE 1). TAKE EXTRA CARE IN REMOVING AND
REPLACING THESE BOLTS TO PRECLUDE DAMAGING THE BOLT HOLES.
(5) Install the eighteen main spar bolts in accordance with the bolt legend. Do not drive bolts in.
Take care not to damage bolt holes. If reusing bolts, ensure that each bolt goes back into the
same hole that it came out of. Use of new nuts (18) is recommended.
NOTE: When replacing a wing assembly, ascertain the wing butt clearance is maintained
(Refer to Sketch A, Figure 1.)
(6) Install the bolt, washers and nut that attaches the front spar with the fuselage fitting. A
minimum of one washer under the nut and one washer under the head is required. Then add
washers as needed to leave a maximum of one and one-half threads visible or a minimum of
the bolt chamfer exposed.
(7) Insert the number of washers required between the forward face of the wing fitting and aft face
of the fuselage fitting of the rear spar attachment. The maximum number of washers allowed is
one AN960-616L and two AN960-616. It is also acceptable to have the faces of the fittings
against each other. 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.
Use the shortest bolt which will leave 0.580 of an inch minimum from the fitting to the end of
the bolt.
(8) Torque the eighteen main spar bolt nuts or bolt heads to the required torque. Be certain that
the bolts, nuts and washers are installed in accordance with the bolt legend. The forward spar
attachment bolt should be torqued in accordance with the chart of recommended torque
requirements given in 91-00-00.Torque the rear spar attachment bolt as specified in Figure 1.
(9) Install the wing jacks and the tail support to the tail skid with approximately 250 pounds of
ballast on the base of the tail support. Remove the fuselage cradle and wing supports.
(10) If the left wing was removed, it is necessary that the pitot static tube to be connected at the
elbows located within the cockpit at the wing butt line. Replace or install clamps where found
necessary. In the event that a heated pitot is installed, the plus lead must be connected at the
fuselage.
(11) Connect the hydraulic brake line onto the fitting located within the cockpit at the leading edge
of the wing.
(12) Connect the leads to the appropriate posts on the terminal strip and install the washers and
nuts. (For assistance in connecting the electrical lead, refer to the Electrical Schematics in
Chapter 91.) Place the clamps along the electrical harness to secure it in position and install
the terminal strip dust cover.
(13) Remove the cap from the fuel line and connect it at the fitting located forward of the spar at the
wing butt line.
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