Airframe; Fuselage; Wings - Cirrus DESIGN SR22T Pilot Operating Handbook

Section 7 Cirrus Design
Airplane and Systems Description SR22T

Airframe

Fuselage

The airplane's monocoque fuselage is constructed primarily of
composite materials and is designed to be aerodynamically efficient.
The cabin area is bounded on the forward side by the firewall at
fuselage station 100, and on the rear by the aft baggage compartment
bulkhead at fuselage station 222. Comfortable seating is provided for
four adults. A composite roll cage within the fuselage structure
provides roll protection for the cabin occupants. The cabin and
baggage compartment floors are constructed of a foam core
composite with access to under-floor components.
All flight and static loads are transferred to the fuselage structure from
the wings and control surfaces through four wing attach points in two
locations under the front seats and two locations on the sidewall just
aft of the rear seats.
The lower firewall employes a 20° bevel to improve crashworthiness.
In addition, an avionics bay is located aft of bulkhead 222 and
accessible through an access panel installed on the RH side of the aft
fuselage.

Wings

The wing structure is constructed of composite materials producing
wing surfaces that are smooth and seamless. The wing cross section
is a blend of several high performance airfoils. A high aspect ratio
results in low drag. Each wing provides attach structure for the main
landing gear and contains a 47.25-gallon fuel tank.
The wing is constructed in a conventional spar, rib, and shear section
arrangement. The upper and lower skins are bonded to the spar, ribs,
and aft shear web forming a torsion box that carries all of the wing
bending and torsion loads. The rear shear webs are similar in
construction but do not carry through the fuselage. The main spar is
laminated epoxy/carbon fiber in a C-section, and is continuous from
wing tip to wing tip. The wing spar passes under the fuselage below
the two front seats and is attached to the fuselage in two locations. Lift
and landing loads are carried by the single carry-through spar, plus a
pair of rear shear webs (one on each wing) attached to the fuselage.
7-6 P/N 13772-003
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