AEROPRAKT-32 Pilot Operating Handbook
A32-214-POH
26
7
Airplane and Systems Descriptions
7.1 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.
7.2 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" 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" thickness. The spar is a riveted structure consisting of a web, made of 0.032" 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 semi monocoque structure. The frames are made of 6061T6
aluminum alloy sheets of 0.063" to 0.080" thickness. The fuselage skin is made of 2024T3
aluminum alloy sheets of 0.02" to 0.04" thickness.
Engine cowling is made of composites.
The doors, cockpit and part of the fuselage have windows of organic glass.
The primary structure of the all-flying horizontal tail (AFHT) of ribs and a spar. The leading
edge skin is made of a 2024T3 aluminum alloy sheets of 0.020" thickness. Aft of the spar
AFHT is covered with fabric. The AFHT has 2 hinge brackets of its attachment to fuselage.
The fin is made as integral part of the fuselage. It consists of a spar, ribs and 2024T3
aluminum alloy skin of 0.020" thickness.
7.3 Landing gear
Airplane landing gear is of tricycle type with steerable nose wheel. The main LG is of the
cantilever spring type. The main LG leg is made of aluminum alloy. It is attached to the lower
boom of the frame No. 3 at two points: upper and lower supports. The support brackets are
machined of aluminum alloy. The main LG wheels are fitted with hydraulic disk brakes.
The nose LG leg is steerable, of trailing link type. The steering is ensured using the rudder
pedals via pushrods, connecting the left and right side pedals with bellcrank on the strut.
The leg consists of a strut and a trailing link in form of nose wheel fork. The trailing link is
connected to the strut with a shock absorber/damper.
The nose leg is attached to the frame No. 1 at two points
– at upper and lower supports.
The upper support is made of 5 mm 2024T3 aluminum alloy sheet and the lower one is
build-up. The supports are fitted with bronze bushings.
Each wheel is fitted with a wheel spat (fairing) or mud screens (in case of the low-profile
tires and 6.00×6 wheels).
