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STRUCTURES
Structures
are of sheet
aluminum
construction
and
are de-
signed to ultimate load factors well in excess
of normal require-
ments.
All components
are completely zinc chromate primed
and
exterior surfaces are coated with acrylic lacquer.
The
main
spars
of the wings
are joined with high
strength
butt
fittings
in the
center
of the fuselage,
making
in effect
a
continuous
main spar. The spars
are attached to the fuselage at
the side of the fuselage and in the center of the structure; wings
are also attached at the rear spar and at an auxiliary front spar.
The
wing
airfoil
section
is
a
laminar
flow
type,
NACA-
642A215,
with
maximum
thickness
about
40%
aft of the
leading
edge.
This
permits
the main spar,
located
at the point of max-
imum
thickness,
to pass
through
the
cabin
under
the
rear seat,
providing
unobstructed
cabin
floor
space
ahead
of
the
seat.
LANDING GEAR
The nose gear is steerable with the rudder pedals through a
40 degree
arc.
During
retraction of the gear, the steering mecha-
nism
is disconnected
automatically
to reduce
rudder pedal
loads
in
flight.
The
nose
gear
is
equipped
with
a hydraulic
shimmy
dampener.
Retraction
of the landing
gear is accomplished
through the
use of an electric motor and gear train, actuating push-pull cables
to each of the main gear and a tube to the nose gear. The landing
gear
motor
is beneath
the center
floor panel and the selector
switch
on the instrument
panel to the
left of the power control
quadrant.
To
guard against
inadvertent
movement
of the landing gear
selector on the ground, the handle must also be pulled aft before
moving it upward. The gear selector has the shape of a wheel to
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