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CESSNA
MODELT210M
INTRODUCTION
SECTION 7
AIRPLANE
&
SYSTEMS DESCRIPTIONS
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.
AIRFRAME
The airplane is an
all-metal,
six-place,
high-wing,
single-engine
airplane equipped with
retra
ctable tricycle landing
gear,
and
designed for
g
eneral utility
purposes.
The construction of the fuselage is a conventional formed sheet metal
bulkhead and skin design referred to as semimonocoque. Incorporated into
the fuselage structure are two large cabin door openings and a baggage
door
opening.
Major items of structure include a forward carry-through
spar and a forged aluminum main carry-through spar to which the wings
are
a
ttached. The lower aft portion of the fuselage center section contains
the forgings and structure for the retractable main landing gear.
The full cantilever wings have
integral
fuel tanks and are constructed
of
a
forward
spar,
main
spar,
conventional formed sheet metal ribs and
aluminum
skin. The
integral
fuel tanks are formed by the forward spar,
two sealing ribs, and
an
aft fuel tank spar forward of the main spar. The
Frise-type ailerons and single-slot type flaps are of conventional formed
sheet metal ribs and smooth aluminum skin
construction.
The ailerons are
•
equipped with ground adjustable trim tabs on the inboard end of the
trailing
edge, and balance weights in the leading
edges.
The empennage
(t
ail assembly) consists of a conventional vertical
stabilizer, rudder, horizontal stabilizer, and elevator. The vertical stabiliz-
er
consists
of a forward and aft
spar,
formed sheet metal ribs and
reinforcements, four skin panels, formed leading edge skins
,
and
a
dorsal.
The rudder is constructed of a forward and aft
spar,
formed sheet metal ribs
and reinforcements, and a wrap-around skin panel. The top of the rudder
incorporates a leading edge extension which contains a balance weight.
The horizontal stabilizer is constructed of a forward and
aft
spar, ribs and
stiffeners, center upper skin panel, and two left and two right wrap-around
skin panels which also form the leading edges. The horizontal stabilizer
also contains the elevator trim tab actuator. Construction of the elevator
consists of a forward
and
.
aft spar, ribs, torque tube and bellcrank, left
upper
and
lower skin panels, a formed onecpiece left trailing edge, right
upper and lower skin panels, and right inboard and outboard formed
trailing
edges.
The elevator trim tab consists of a bracket
assembly,
hinge
7-3
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