Introduction; Airframe; Fuselage; Wings - Cirrus SR22 Pilot Operating Handbook

C D
IRRUS ESIGN
SR22

Introduction

This section provides a basic description and operation of the standard
airplane and its systems. Optional equipment described within this section
is identified as optional.
Some optional equipment may not be described in this section.
For description and operation of optional equipment not
described in this section, refer to

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 the pilot and up to four passengers. 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 compo-
nents.
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 employs 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
P/N 13772-006
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