NOTICE

SECTION 7 CESSNA
AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000
AIRFRAME (Continued)
The empennage (tail assembly) consists of a conventional vertical
stabilizer, rudder, horizontal stabilizer, and elevator. The vertical
stabilizer consists of a forward and aft spar, sheet metal ribs and
reinforcements, four skin panels, formed leading edge skins, and a
dorsal fin. 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, four upper and four lower skin
panels, and two left and two right wrap-around skin panels which also
form the leading edges. The horizontal stabilizer also contains dual jack
screw type actuators for the elevator trim tabs. Construction of the
elevator consists of a forward and aft spar, sheet metal ribs, upper and
lower skin panels, and wrap-around skin panels for the leading and
trailing edges. An elevator trim tab is attached to the trailing edge of
each elevator by full length piano-type hinges. Dual pushrods from
each actuator located in the horizontal stabilizer transmit actuator
movement to dual horns on each elevator trim tab to provide tab
movement. Both elevator tip leading edge extensions provide
aerodynamic balance and incorporate balance weights. A row of vortex
generators on the top of the horizontal stabilizer just forward of the
elevator enhances nose down elevator and trim authority.
To assure extended service life of the airplane, the entire airframe is
corrosion proofed. Internally, all assemblies and sub-assemblies are
coated with a chemical film conversion coating and are then epoxy
primed. Steel parts in contact with aluminum structure are given a
chromate dip before assembly. Externally, the complete airframe is
painted with an overall coat of polyurethane paint which enhances
resistance to corrosive elements in the atmosphere. Also, all control
cables for the flight control system are of stainless steel construction.
CARGO POD
The airplane may be equipped with a cargo pod which provides
additional cargo space. The pod attaches to the bottom of the fuselage
with screws and can be removed, if desired, for increased performance
and useful load. The pod is fabricated with a Nomex inner housing, a
layer of Kevlar, and an outer layer of fiberglass. Complete instructions
for removal and installation of the cargo pod are contained in the
Maintenance Manual.
7-8
U.S.
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208BPHBUS-00