Piper PA-24 Comanche, Руководство по обслуживанию, Страница: 207 / 846

PIPER COMANCHE SERVICE MANUAL
04/01/09 IV - STRUCTURES
1E5
SECTION IV
STRUCTURE
4-1.
Introduction
.
This section covers the removal and installation procedures for the main structural components, for
checking and balancing the control surfaces and minor repairs. No major structural repairs are
recommended. Minor replacement of skins may be made providing there is no internal damage. Minor
repairs such as patching the skin, welding, etc., may be made in accordance with the methods,
techniques and practices set forth in Federal Aviation Administration, Advisory Circular 43.13-1, latest
revision. It may be necessary to cut access holes to make skin repairs in some areas of the aircraft. Refer
to Figure 4-14 for typical access holes.
CAUTION: SKIN REPAIRS MUST RESULT IN A SURFACE WHICH IS AS STRONG AS THE
ORIGINAL SKIN. (REFER TO PARAGRAPH 4-47, STRUCTURAL REPAIRS.)
NOTE: When torquing various assemblies standard torque values are to be used as found in Section II
of this manual or FAA Advisory Circular 43.13-1 latest revision, unless otherwise stated in this
manual.
The disassembly, assembly, and rigging of component parts to the various control surfaces can be found
in Section V.
4-2.
Description.
The structures of the PA-24 are of sheet aluminum, completely primed with zinc chromate and covered
with acrylic lacquer on the exterior surfaces.
The fuselage is an all metal semi-monocoque construction comprised of bulkheads, stringers, stiffeners
and longitudinal beams to which the outer skin is riveted.
Each wing airfoil section is a full cantilever laminar flow type. The full length beam type main spar is
joined with high strength butt fittings in the center of the fuselage, making in effect a continuous main
spar.
The all metal empennage group is a full cantilever design consisting of a vertical fin. rudder, and
stabilator with a trim cab. The stabilator and vertical fin have two channel main spars running full length.
The stabilator is attached to the fuselage by a torque tube supported by bearing blocks.
4-3.
Removal.
4-4.
Removal Of Wing Assembly.
The major sub assemblies of the wing may be removed individually or the wing may be removed as a
unit. To remove the wing, a fuselage supporting cradle is required, also a wing support.
4-5.
Removal Of Wing Tip.
A. Remove the screws holding the wing tip to the wing.
B. Pull the wing tip far enough off to disconnect the navigation light wire at the quick-disconnect
fitting; then remove the wing tip.