7-2
Airframe
7-2-1
General
The aircraft construction is conventional semimonocoque, primarily incorporating aluminum
alloy, but composite structures are used in certain areas. Flush riveting is used where
appropriate to minimize drag. Access panels are installed to facilitate inspection and
maintenance. The complete airframe is electrically bonded to eliminate electromagnetic
interference and static discharge wicks are used to reduce static charges while in flight.
7-2-2
Fuselage
The fuselage consists of the engine area, nose gear assembly, cockpit, cabin, and aft
fuselage. The engine area contains the powerplant and associated accessories. The engine
cowling is constructed from a carbon/nomex honeycomb material and is covered by a copper
foil for lightning protection. The engine mount is welded steel tubing and bolted to the firewall
in four places. The firewall is titanium and protected by insulation material.
A left and a right windshield, two side windows, and a Direct Vision (DV) window provide
cockpit visibility. The windshield is made of two glass layers with an interlayer, while the two
side windows and the DV window are made of two stretched acrylic layers with an interlayer.
All windows are made of two ply laminated design.
The cabin area is aft of the cockpit to the aft pressure bulkhead and contains the passenger
door, the cargo door, and an emergency overwing exit. The nine cabin windows are two ply
laminated monolithic stretched acrylic and incorporate dry neoprene seals. Airplane avionics
are mounted under the cabin floor, running the length of the center cabin, and are accessible
through quick release panels. The cabin carry-through spar attachment fittings are one-piece
machined aluminum. Fuselage fairings are constructed from either carbon/nomex or aramid/
nomex honeycomb material.
A safety net is installed aft of the rear pressure bulkhead to protect the bulkhead from damage
during maintenance.
7-2-3
Empennage
The empennage is a T-tail design with the horizontal stabilizer mounted on top of the vertical
stabilizer. The vertical and horizontal stabilizer assemblies are conventional aluminum
construction. The horizontal stabilizer is a trimmable structure. The dorsal fin is made of glass
fiber honeycomb and the ventral fin is made of kevlar honeycomb material.
7-2-4
Wings
The wings are of conventional construction incorporating front and rear spars, ribs, and skin.
The front and rear spars are mainly from machined aluminum alloy plate. Both spars include
fuselage and integral landing gear attachment points, while the rear spar also integrates flap
actuator attachment points. Main load carrying ribs are machined from aluminum alloy plate.
All other ribs are formed sheet metal. The ribs incorporate lightening holes to reduce weight
and integral beads for stiffening. The wing skin is stiffened clad aluminum alloy sheet riveted to
the spars and ribs. Access panels are in the wing bottom only.
Each wing is attached to the fuselage using three titanium shear bolts and, at the aft upper
fitting, one steel tension bolt.
Section 7 - Airplane and Systems Description
Airframe
Pilot's Operating Handbook
Report No: 02406
Issue date: Mar 06, 2020
Page 7-2-1
12-C-A15-00-0702-00A-043A-A
FOR
GENERAL
AND
FAMILIARIZATION
PURPOSES
ONLY
