AEROPRAKT 22LS, Pilot Operating Handbook

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AEROPRAKT-22LS Pilot Operating Handbook A22LS-POH-04
8 Airplane and Systems Descriptions
8.1 General
This section provides description and operation of the airplane and its systems. Some
equipment described herein is optional and may not be installed in the airplane. Refer to
Section 9, Supplements, for details of other optional systems and equipment.
8.2 Airframe
Wing: high placed, strut braced, constant chord. Wing section is P-IIIa-15%. Wing primary
structure consists of a single spar, ribs and aft web. Forward of the spar the wing has
2024T3 aluminum alloy skin of 0.020-0.032 in (0.5-0.8 mm) sheet, which together with the
spar web forms the wing torsion box. Aft of the spar the wing is covered with the metal skin
on top and thermoshrinkable fabric on the bottom side. Wing ribs are made of 6061T6
sheet of 0.020-0.032 in (0.5-0.8 mm) thickness. The spar is a riveted structure consisting of
a web, made of 0.032 in (0.8 mm) 6061T6 sheet, and caps, made of an extruded section
(D16chT alloy angle). The wing strut attachment bracket and front attachment bracket of
the wing are fixed to the spar. The rear attachment bracket of the wing is fixed to the aft
web. The flaperon (drooping aileron) hinge brackets are fixed to ribs No. 1, 5, 9 and 13. All
brackets are made of 5 mm 2024T3 sheet.
The primary structure of the flaperon consists of the leading edge skin, spar, trailing edge
section and ribs. The LE skin and spar comprise the torsion box. Flaperon covering is made
of synthetic thermoshrinkable fabric.
The fuselage is an all-metal structure. The mid section is made of the 2024T3 aluminum
alloy bent sheet sections of 0.063 to 0.080 in (1.5 to 2 mm) thickness, which form the edges
of the mid section. The tail boom is a monocoque structure made of 0.032 in (0.8 mm)
2024T3 aluminum alloy sheet.
Engine cowling is made of composites.
The fuselage has 6 frames (bulkheads). Frames No. 1, 2, 4, 5 and 6 are press-formed of an
aluminum alloy sheet; frame No. 3 is made of bent sheet sections. Power plant and nose LG
attachment points are attached to the frame No. 1, the engine mount taking part in
transferring the loads from the nose LG onto the fuselage structure.
The wing and strut attachment brackets as well as the main LG legs attachment brackets
are attached to the frame No. 3. Frames No. 4, 5, 6 are installed in the tail boom.
The fin and ventral fin with the tail wheel are attached to the frames No. 5 and 6.
The bottom and part of the topside of the mid fuselage section are covered with aluminum
alloy sheets of 0.020 in (0.5 mm) thickness.
The doors, cockpit and part of the fuselage have windows of organic glass.
The primary structure of the stabilizer consists of ribs and a spar. The skin is a 2024T3
aluminum alloy sheet of 0.020 in thickness. The stabilizer has brackets of its attachment to
fuselage and 3 elevator hinge brackets.
The fin, structurally similar to the stabilizer, is made as integral part of the fuselage.
Elevator and rudder structures are similar to that of the flaperons.
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