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12000 104 816 773 726 676 804
14000 103 675 627 576 523 670
16000 102 532 480 425 368 536
Revision 02: 08-26-09
P/N 13772-129 7 of 8
Cirrus Design Section 9
SR22 Supplements
Section 6 - Weight & Balance
Installation of the subject propeller adds the following optional (Sym =
O) equipment at the weight and arm shown in the following table.
Section 7 - Systems Description
The airplane employs a 3 blade, constant speed, non-feathering
propeller. The composite blades are mounted in an aluminum hub
which contains the pitch changing mechanism consisting of a piston/
cylinder, piston rod, and blade actuating components. Refer to the
basic POH for additional information on the propeller system.
ATA /
Item Description Sym Part Number Unit
Wt Arm
61-01 Propeller Installation without Ice
Protection
O 13599-007 67.2 48.0
61-02 Propeller Installation with
Ice Protection
O 15319-00x 68.0 48.0
61-03 Lightweight Hub Propeller
Installation without Ice Protection
O 13599-010 62.4 48.0
61-04 Lightweight Hub Propeller
Installation with Ice Protection
O 15319-013 63.2 48.0
Revision 02: 08-26-09
8 of 8 P/N 13772-129
Section 9 Cirrus Design
Supplements SR22
Section 8 - Handling, Servicing & Maintenance
Propeller Servicing
The spinner and backing plate should be cleaned and inspected for
cracks frequently. Before each flight the propeller should be inspected
for nicks, scratches, and gouges. If found, they should be repaired as
soon as possible by a rated mechanic, since a nick or scratch causes
an area of increased stress which can lead to serious cracks or the
loss of a propeller tip.
Propeller blades are painted with a durable specialized coating that is
resistant to abrasion. If this coating becomes eroded, it is necessary to
repaint the blades to provide proper erosion protection. Painting
should be performed by an authorized propeller repair station.
It is permissible to perform a blade touch-up with aerosol paint in
accordance with Hartzell Propeller Owner’s Manual, p/n 145, revision
1 or later.
Section 10 - Safety Information
No Change.
Revision 02: 08-26-09
13772-130 1 of 58
Cirrus Design Section 9
SR22 Supplements
Pilot’s Operating Handbook and
FAA Approved Airplane Flight Manual
Supplement
for
SR22 Airplanes Equipped with the
“G3 Wing”
When the G3 Wing is installed on the Cirrus Design SR22 serials
2334, 2420, 2438 and subsequent, this POH Supplement is applicable
and must be inserted in the Supplements Section (Section 9) of the
Cirrus Design SR22 Pilot’s Operating Handbook. This document must
be carried in the airplane at all times. Information in this supplement
adds to, supersedes, or deletes information in the basic SR22 Pilot’s
Operating Handbook.
• Note •
This POH Supplement Change, dated Revision 02: 08-26-09,
supersedes and replaces the original release of this POH
Supplement dated 11-11-07.
Revision 02: 08-26-09
2 of 58 13772-130
Section 9 Cirrus Design
Supplements SR22
Revision 02: 08-26-09
Intentionally Left Blank
13772-130 3 of 58
Cirrus Design Section 9
SR22 Supplements
Section 1 - General
The G3 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.
G3 Wing geometry is slightly changed with an 1° increase in dihedral
which allows for the elimination of the aileron-rudder interconnect
system.
The CG Envelope (Center of Gravity Envelope) is expanded to allow
for slightly more forward loading at higher gross weights.
The main landing gear is moved slightly inboard and the strut angle
increased to achieve an increase in airplane height of 1.5 inches.
The ice protection system’s glycol tank is moved from the fuselage to
an integral tank on the left wing and the porous panels are lengthened
to cover the entire leading edge of the wing.
Other G3 Wing updates include:
　
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