Pitot-Static System And Instruments - Cessna SKYLANE RG R182 Pilot Operating Handbook

CESSNA
MODEL R182
SECTION 7
AIRPLANE
&
SYSTEMS DESCRIPTIONS
NOTE
For improved partial heating on mild days, pull out the
CABIN AIR knob slightly when the CABIN HEAT knob is
out. This action increases the airflow through the system,
increasing efficiency, and blends cool outside air with the
exhaust manifold heated air, thus eliminating the possibil-
ity of overheating the system ducting.
Front cabin heat and ventilating air is supplied by outlet holes spaced
across a cabin manifold just forward of the pilot's and copilot's feet. Rear
cabin heat and air is supplied by two ducts from the manifold, one
extending down each side of the cabin to an outlet at the front door post at
floor level. Windshield defrost air is also supplied by a duct leading from
the cabin manifold to an outlet on top of the antiglare shield. Defrost air
flow is controlled by a rotary type knob labeled DEFROST.
For cabin ventilation, pull the CABIN AIR knob out, with the CABIN
HEA T knob pushed full in. To raise the air temperature, pull the CABIN
HEAT knob out until the desired temperature is attained. Additional heat
is available by pulling the knob out farther; maximum heat is available
with the CABIN HEAT knob pulled out and the CABIN AIR knob pushed
full in.
Separate adjustable ventilators supply additional ventilation air to
the cabin. One near each upper corner of the windshield supplies air for the
pilot and copilot, and two ventilators are available for the rear cabin area
to supply air to the rear seat passengers. Each rear ventilator outlet can be
adjusted in any desired direction by moving the entire outlet to direct the
airflow up or down, and by moving a tab protruding from the center of the
outlet left or right to obtain left or right airflow. Ventilation airflow may be
closed off completely, or partially closed according to the amount of
airflow desired, by rotating an adjustment wheel adjacent to the outlet.
PITOT-STATIC SYSTEM AND INSTRUMENTS
The pitot-static system supplies ram air pressure to the airspeed
indicator and static pressure to the airspeed indicator, rate-of-climb
indicator and altimeter. The system is composed of either an unheated or
heated pitot tube mounted on the lower surface of the left wing, two
external static ports on the left and right sides of the forward fuselage, and
the associated pI umbing necessary to connect the instrumen ts to the
sources.
The heated pitot system consists of a heating element in the pitot tube.
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