Textron Cessna Grand Caravan Ex 208B Pilot's Operating Handbook And Faa Approved Airplane Flight Manual page 710

SECTION 9 - SUPPLEMENTS CESSNA
SUPPLEMENT 1 MODEL 208B 867 SHP
GARMIN G1000
AIRPLANE SYSTEMS AND DESCRIPTIONS
SYSTEM DESCRIPTION
The TKS Ice Protection System includes laser-drilled titanium porous
panels for the leading edges of the wings, horizontal and vertical
stabilizers, lift struts, propeller fluid slinger ring and windshield fluid
spray bar. Refer to Figures S1-5 and S1-6 for system installation and
fluid schematic.
The outer skin of the ice protection panels are manufactured with
titanium, which provides excellent strength, durability, light weight, and
corrosion resistance.
The panel skin is perforated by laser drilling holes, 0.0025 inches in
diameter, 800 per square inch. The porous areas of the titanium panels
are designed to assure fluid coverage from best rate of climb speed to
maximum operating speed.
The back plates of the panels are also manufactured out of titanium
and are formed to create reservoirs for the ice protection fluid, allowing
fluid supply to the entire porous area. A porous membrane between the
outer skin and the reservoir assure even flow and distribution through
the entire porous area of the panel.
The porous panels are bonded or attached as a cuff over a leading
edge. Panels are bonded to the airframe with a two-part, flexible
adhesive.
Fluid is supplied to the panels and propeller by two positive
displacement, constant volume metering pumps. The pumps provide
various flow rates to the panels and propeller. Single pump operation, a
combined mode, and timed pumping provide a range of flow rates for
different icing conditions.
Fluid for the windshield spray bar system is provided by an on-demand
gear pump. The spray bar may be activated as needed to clear forward
vision through the windshield.
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FAA APPROVED
208BPHCUS-S1-00
S1-58 U.S.