SECTION 7 CESSNA
AIRPLANE AND SYSTEM DESCRIPTION MODEL T182T NAV III
GFC 700 AFCS
U.S.
AIRFRAME (Continued)
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 and lower skin panels 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 formed leading edge skins, a
forward spar, ribs, torque tube and bellcrank, left upper and lower V
type corrugated skins, and right upper and lower V type corrugated
skins incorporating a trailing edge cut-out for the trim tab. Both elevator
tip leading edge extensions incorporate balance weights. The elevator
trim tab consists of a spar, rib, and upper and lower V type corrugated
skins.
FLIGHT CONTROLS
The airplane's flight control system (Refer to Figure 7-1) consists of
conventional aileron, rudder, and elevator control surfaces. The control
surfaces are manually operated through mechanical linkage using a
control wheel for the ailerons and elevator, and rudder/brake pedals for
the rudder. The elevator control system is equipped with downsprings
which provide improved stability in flight.
(Continued Next Page)
T182TPHBUS-00
7-6
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