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aircraft heading system (gyro slaving amplifier), and a speed switch
plumbed into the pitot system. Electrical power for system operation is
28 vdc supplied through the 5-amp SKYWATCH Circuit Breaker on the
Avionics Non-Essential bus.
• Note •
Refer to the L-3 Avionics Systems SkyWatch Pilot’s Guide (P/
N 009-10801-001) for a description of the SkyWatch System.
Refer to the GARMIN Addendum for “Display Interface for
Traffic and Weather Data” P/N 190-001140-10 for additional
operational information and a display description.
Revision 02: 03-27-07
P/N 13772-115 1 of 16
Cirrus Design Section 9
SR22 Supplements
Pilot’s Operating Handbook and
FAA Approved Airplane Flight Manual
Supplement
for
Ice Protection System
When the Ice Protection System is installed on the Cirrus Design
SR22, 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 •
Noted effectivity “Serials with G3 Wing” indicates Serials
2334, 2420, 2438 and subsequent.
Noted effectivity “Serials before G3 Wing” indicates Serials
0334 thru 2333, 2335 thru 2419, 2421 thru 2437 unless
otherwise noted.
This POH Supplement Change, dated Revision 05: 03-27-07,
supersedes and replaces revision 4 of this POH Supplement
dated 07-03-04.
Revision 05: 03-27-07
2 of 16 P/N 13772-115
Section 9 Cirrus Design
Supplements SR22
Section 1 - General
The airplane is equipped with an Ice Protection System. This system
allows a pilot who inadvertently enters icing conditions, to initiate deicing
fluid flow along the wing, horizontal stabilizer, and propeller
blades.
Section 2 - Limitations
1. Flight into known icing is prohibited.
2. De-icing fluids meeting DTD 406B:
• AVL (DTD 406B) - Aviation Laboratories
• AL-5 (DTD 406B) - Canyon Industries
• Dimax 80 (TKS-80) - Canyon Industries
• TKS-Fluid (DTD 406B) - D.W. Davies & Co
• Note •
The Ice Protection System is certified only as “No Hazard” to
normal operations, therefore, no determination has been
made as to the capability of this system to remove or prevent
ice accumulation
Revision 05: 03-27-07
P/N 13772-115 3 of 16
Cirrus Design Section 9
SR22 Supplements
Placards
Serials 2334, 2420, 2438 & subs; Left wing, above de-icing fluid filler cap:
DE-ICING FLUID
REFER TO AFM FOR APPROVED
DE-ICING FLUIDS
L EU F O N
L EU F ON
L EU F ON
Serials 0334 thru 2333, 2335 thru 2419, 2421 thru 2437;
LH Fuselage, above de-icing fluid filler cap:
SR22_FM09_2592
Figure - 1
Required Placards
Revision 05: 03-27-07
4 of 16 P/N 13772-115
Section 9 Cirrus Design
Supplements SR22
Section 3 - Emergency Procedures
Inadvertent Icing Encounter
Flight into known icing conditions is prohibited. However, if icing is
inadvertently encountered, determine the most appropriate operating
mode:
NORMAL mode is selected when icing conditions are encountered
and prior to ice accretion. The maximum system operating time while
in NORMAL mode is approximately, Serials before G3 Wing, 1 hour or,
Serials with G3 Wing, 90 minutes.
MAXIMUM mode is selected if ice has accreted to flight surfaces. The
maximum system operating time while in MAXIMUM mode is
approximately Serials before G3 Wing, 30 minutes or, Serials with G3
Wing, 45 minutes.
• Caution •
Prolonged operation of the system in clear air, at very high
altitudes, and very cold temperatures can result in “flash”
evaporation of water and alcohol from the de-icing fluid. This
evaporation results in a glycol rich fluid that could become
“gel” like on the wing surface until the aircraft enters cloud or
descends to warmer temperatures.
• WARNING •
The Ice Protection System may not remove significant
accumulations of ice if accretions are permitted to form with
the Ice Protection System off.
Ensure system start time and system mode is noted while
exiting icing conditions to aid in estimating de-icing fluid
reserve.
1. Ice Protection Switch ..................................................As Required
2. Pitot Heat .................................................................................. ON
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AIRPLANE INFORMATION MANUAL for the CIRRUS DESIGN SR22(124)
