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continues to a tee that splits the flow between the forward and aft
portions of the system.
The forward line runs to a five-port proportioning unit which divides the
flow into specific volumetric requirements for each porous panel and to
the propeller slinger ring.
The aft line runs to a test port assembly then to a second five-port
proportioning unit, dividing the flow into the specific volumetric
requirements of the horizontal, vertical, and elevator horn panels. To
monitor the performance of the empennage leading edge panels, four
low pressure switches are integrated with the aft proportioning unit to
provide the annuciations system with low pressure faults.
The windshield pump, located adjacent to the main metering pumps,
supplies the windshield nozzles with fluid and also acts as a priming
pump for the main metering pumps.
Revision 02: 11-17-09
44 of 44 P/N 13772-134
Section 9 Cirrus Design
Supplements SR22
Section 8 – Handling, Service, & Maintenance
Storage
• Caution •
During long periods of non-use, the porous panel membranes
may dry out which could cause uneven fluid flow during
subsequent operation. Perform the Pre-Flight Inspection every
30 days to keep porous panel membranes wetted.
To prepare the Anti-Ice System for flyable storage, fill the anti-ice fluid
reservoir and operate the system on MAX to ensure all air is
completely purged from components and plumbing. Re-fill the anti-ice
fluid reservoir after purging.
Servicing
• Caution •
Use only approved anti-ice fluid. See Section 2, Limitations.
Certain solvents may damage the panel membrane. Use only
soap and water, isopropyl alcohol, or ethyl alcohol to clean
panels. Do not wax leading edge porous panels.
Anti-Ice Fluid Reservoir
The anti-ice fluid reservoirs are serviced through filler caps in the
upper wing skins. Each reservoir is individually drained and vented by
lock-open/lock-close drain valves and vents in the lower wing skins.
Porous Panels
Periodically clean porous panels with soap and water using a clean,
lint-free cloth. Isopropyl alcohol may be used to remove oil or grease.
System Priming
In the event of a loss of prime, the windshield pump may be activated
to purge the system of any air between the main metering pumps and
the fluid tank. It is unlikely that the system will experience a loss of
prime except when the fluid tanks are intentionally run dry. If, after
multiple purging attempts, insufficient anti-ice 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 02: 11-17-09
P/N 13772-135 1 of 16
Cirrus Design Section 9
SR22 Supplements
Pilot’s Operating Handbook and
FAA Approved Airplane Flight Manual
Supplement
for
GFC 700 Automatic Flight Control
System
When the GFC 700 Automatic Flight Control System is installed on the
aircraft, this POH Supplement is applicable and must be inserted in
the Supplements Section (Section 9) of the basic 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 Pilot’s Operating Handbook.
• Note •
This POH Supplement Change, dated Revision 01: 08-26-09,
supersedes and replaces the original release of this POH
Supplement dated 05-13-08.
Revision 01: 08-26-09
2 of 16 P/N 13772-135
Section 9 Cirrus Design
Supplements SR22
Section 1 - General
The aircraft is equipped with a Garmin GFC 700 digital Automatic
Flight Control System (AFCS) which is fully integrated within the Cirrus
Perspective Integrated Avionics System architecture. Refer to Section
7 - System Description and the Cirrus Perspective Pilot’s Guide for
additional description of the Automatic Flight Control System and
operating procedures.
Section 2 - Limitations
1. The Cirrus Perspective by Garmin Integrated Avionics System
Pilot’s Guide for the SR22, P/N 190-00820-00, Revision A or later
must be immediately available to the pilot during flight. The
software status stated in the pilot's guide must match that
displayed on the equipment.
2. Minimum Autopilot Speed ..................................................80 KIAS
3. Maximum Autopilot Speed ...............................................185 KIAS
4. Autopilot Minimum-Use-Height:
a. Takeoff, and Climb ............................................... 400 feet AGL
　
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