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not selectable.
The vertical speed display is the only Altitude Selector / Alerter
function available in the ‘operate’ mode. Therefore, vertical speed
changes can be commanded by rotating the selector input knob.
Vertical speeds can also be entered in the data (DTA) entry (ENT)
mode by pressing the VS button and using the selector input knob to
enter a new vertical speed. The DTA button must be pressed again to
accept the new vertical speed and enter the ‘operate’ mode.
The Altitude Selector / Alerter VS mode can be disabled by pressing
the Altitude Selector / Alerter MAN button.
MAN (Manual) – Vertical Speed selection can be completely
decoupled from the autopilot system by depressing the Altitude
Selector / Alerter MAN button.
Revision 05: 08-15-07
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
Basic 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 07: 05-13-08,
supersedes and replaces revision 6 of this POH Supplement
dated 08-15-07.
Revision 07: 05-13-08
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 07: 05-13-08
P/N 13772-115 3 of 16
Cirrus Design Section 9
SR22 Supplements
Placards
Serials 22-2334, 22-2420, 22-2438 & 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 22-0334 thru 22-2333, 22-2335 thru 22-2419, 22-2421 thru 22-2437;
LH Fuselage, above de-icing fluid filler cap:
SR22_FM09_2592A
Figure - 1
Required Placards
Revision 07: 05-13-08
4 of 16 P/N 13772-115
Section 9 Cirrus Design
Supplements SR22
Section 3 - Emergency Procedures
Inadvertent Icing Encounter
• 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.
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, 60 minutes.
Serials with G3 Wing, 80 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.
Serials with G3 Wing, 40 minutes.
1. Ice Protection Switch ................................................... As required
2. Pitot Heat .................................................................................. ON
3. Airspeed................................................................... 100-139 KIAS
4. Time ................................................................................... NOTED
　
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