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clean, lint-free cloth. Isopropyl Alcohol may be used to remove oil or
grease.
Revision 07: 05-13-08
P/N 13772-115 15 of 16
Cirrus Design Section 9
SR22 Supplements
System Priming - Serials before G3 Wing only
If allowed to run dry, the metering pump may fail to prime because of
air trapped in the system. If no de-icing fluid is evident during the Pre-
Flight Inspection, perform the following procedure:
1. Locate de-icing fluid drain on LH side of fuselage belly just forward
of fluid tank.
• Caution •
Use a dedicated de-icing fluid sample cup for the following
step.
Do not use the fuel sampling cup.
2. Sample de-icing fluid until fluid streams shows no evidence of air
bubbles for at least three seconds.
3. Perform Pre-Flight Inspection verifying evidence of de-icing fluid
from porous panels and slinger ring.
4. If necessary, repeat steps 2 and 3.
5. If after the above procedure no de-icing fluid is evident, the ice
protection system must be purged in accordance with the Airplane
Maintenance Manual by an appropriately certified technician.
System Priming - Serials with G3 Wing
1. If no de-icing fluid is evident during the Pre-Flight Inspection, the
ice protection system must be purged in accordance with the
Airplane Maintenance Manual by an appropriately certified
technician.
Revision 07: 05-13-08
16 of 16 P/N 13772-115
Section 9 Cirrus Design
Supplements SR22
Section 10 – Safety Information
The Ice Protection System is not intended to remove ice from the
aircraft on the ground. Do not attempt to take off with frost, ice, or
snow on flying surfaces.
Flight into known icing is prohibited. The Ice Protection System has
not been evaluated in known icing conditions. Therefore, the affects of
known icing on the system is unknown. Its purpose is to provide some
protection from the effects of ice, should an unexpected encounter
with icing conditions occur. At the first indication of icing, the most
expeditious and safest course of exiting the icing conditions should be
taken. The decision should be based on weather briefings, recent pilot
reports, ATC observations, and may include course changes or
altitude changes.
During simulated icing encounters, stall speed increases of
approximately 12 knots in the clean configuration and 3 knots in the
landing configuration were observed. In addition, cruise speed was
reduced by at least 20 KCAS and the airplanes rate of climb
diminished by at least 20%.
Even with the protected flight surfaces totally clear of ice, performance
degradation will occur due to ice on unprotected regions. The amount
of the degradation cannot be accurately predicted and it is therefore,
depending on circumstances, advisable to increase approach and
landing speeds while using the Ice Protection System. Use extreme
caution during approach and landing, being alert to the first signs of
pre-stall buffet and an impending stall.
Revision 07: 05-13-08
P/N 13772-121 1 of 12
Cirrus Design Section 9
SR22 Supplements
Pilot’s Operating Handbook and
FAA Approved Airplane Flight Manual
Supplement
for
Honeywell KGP 560 Terrain
Awareness/Warning System
When the Honeywell KGP 560 Terrain Awareness and Warning
System is installed in the Cirrus Design SR22, this 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 Revision dated Revision 01: 12-15-07
supersedes and replaces the original release of this supplement dated
Original: 07-03-04.
Revision 01: 12-15-07
2 of 12 P/N 13772-121
Section 9 Cirrus Design
Supplements SR22
Section 1 - General
The airplane is equipped with an Honeywell KGP 560 Terrain
Awareness and Warning System that performs the functions of a
Class C Terrain Awareness and Warning System (TAWS) in
accordance with TSO C151b.
Incorporating much of the technology found in TAWS for air transport
aircraft, the KPG 560 supports:
• Alerting for premature descent.
• Alerting for excessive rate of climb/descent.
• Altitude callout (500 ft) and alerting within 5 nm of 2000 ft public
runways.
• Look-ahead algorithms and integrated terrain/obstacle
database.
The system consists of the 560 GA-EGPWS Processor mounted on
　
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