Kodiak 100 Series User Manual

Pilot’s Operating Handbook
7-5
DO NOT USE FOR FLIGHT OPERATIONS
Section 7
AIRPLANE & SYSTEMS DESCRIPTIONS
100 SERIES
Systems
7-1 GENERAL
This section of the Pilot’s Operating Handbook provides basic descriptions
and operation procedures for the standard airplane and its systems. Optional
equipment described within this section is identied as “optional” or “if
equipped.”
7-2 AIRFRAME
FUSELAGE
The KODIAK’s semi-monocoque fuselage is constructed of aluminum
bulkheads, stringers, and skins. It is designed to be lightweight, rugged,
aerodynamically efcient, and capable of hauling 9 passengers and/or cargo
into remote locations. The fuselage contains forward and aft carry-through
spars which provide connection ttings for the wings, landing gear, and wing
struts.
WINGS
The externally braced wing structure is constructed of aluminum front and
rear spars, ribs, doublers, and stringers. The wing cross section is a blend
of several high performance airfoils. The outboard cross section of each
wing is designed with a lower angle of incidence to improve roll control near
stall. This design also incorporates a discontinuous leading edge which acts
as a stall fence to help maintain aileron control near stall. The wings contain
integral fuel bays, each providing a capacity of 160 gallons. The integral fuel
bays are formed by the forward and aft spars, upper and lower skins, and
the inboard and outboard closeout ribs. The forward spar provides wing to
fuselage attach ttings and wing to strut attach ttings. The aft spar provides
a wing to fuselage attach tting.
EMPENNAGE
The empennage consists of a horizontal stabilizer, elevator, vertical tail, and
a rudder. All of the empennage components are of conventional construction
containing aluminum spars, ribs, and skins. A dorsal n is attached to the
forward spar of the vertical stabilizer and the upper structure of the fuselage.
The rudder is attached to the vertical stabilizer at three hinge points. The
elevator is constructed as two pieces, connected with a torque tube and
attached to the aft spar of the horizontal stabilizer at seven hinge points.
NOTE: Some optional equipment, primarily avionics, may not be
described in this section. For descriptions and operation procedures for
equipment not provided in this section, refer to “Section 9” of this manual.
Uncontrolled if printed

Kodiak 100 Series Specifications

General

Manufacturer	Daher
Engine	Pratt & Whitney Canada PT6A-34
Service Ceiling	25, 000 feet
Seating Capacity	10
Crew	1-2
Range	1, 132 nautical miles
Type	Utility aircraft
Length	34 feet 2 inches
Wingspan	45 feet
Max takeoff weight	7, 255 pounds
Power Output	750 shp
Cabin Width	4 feet 6 inches