P/N 13772-115 11 of 20
Cirrus Design Section 9
SR22 / SR22T Supplements
Section 7 - System Description
The Ice Protection System can prevent, and in certain conditions,
remove ice accumulation on the flight surfaces by distributing a thin
film of glycol-based fluid on the wing, horizontal stabilizer, and
propeller. The presence of this fluid lowers the freezing temperature
on the flight surface below that of the ambient precipitation preventing
the formation and adhesion of ice.
Ice Protection System - Serials before G3 Wing
The system consists of six porous panels, propeller slinger ring, four
proportioning units, metering pump, filter, outlet strainer, fluid tank,
filler cap, electrical switching, and system plumbing. The system
operates on 28 VDC supplied through the 5-amp ICE PROTECTION
circuit breaker on Main Bus 1.
Storage and Distribution
The deicing fluid tank is serviced through a filler located on the LH side
of the fuselage, just forward of the baggage door. The fluid tank,
located behind the LH rear cabin trim panel, has a total capacity of
2.96 gallons (11.2L). A fine-mesh outlet strainer mounted internal to
the tank protects the metering pump from damage by contaminates.
Upon activation, a two-speed metering pump, mounted below the LH
passenger seat, draws fluid from the tank and provides fluid pressure
to the system at a constant-volume flow rate. Low pump speed
provides the required flow during NORMAL operation and high pump
speed during MAXIMUM operation. The manifold of the Metering
Pump is primed by actuating the gravity-fed Drain Valve located on the
lower fuselage skin.
From the metering pump, deicing fluid is pushed through a filter,
mounted adjacent to the pump, and then carried to the proportioning
units located in the wing, empennage, and cabin floor-forward through
nylon tubing.
• The LH and RH Wing proportioning units distributes fluid to the
Inboard and Outboard wing panels.
• The empennage proportioning unit distributes fluid to the LH
and RH horizontal panels.
Revision 09: 12-17-10
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