Cessna R182 - Page 157

'(
CESSNA
MODEL R182
SECTION
7
AIRPLANE
& SYSTEMS
DESCF,IPTIONS
NOTE
For
improved
partial
heating on
mild
days,
pull
out
the
CABIN
AIR
knob slightlywhen
the
CABINHEATknob
is
out.
This action
increases the airllow through the
system,
increasing
efficiency, and blends cool outside
air with the
exlraust
manifold
beated air,
thus
eliminating
the
possibil-
ity of
overheating
tbe system ducting.
Front ca,bin
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 t5rpe
knob labeled DEFROST.
For
cabin
ventilation,
pull
the CABIN
AIR knob out, with the
CABIN
HEAT
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; maximuim 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 reat
cabin area
io
suppty
aii
to the
rear seat
passengers.
Each rear ventilator outlet
can
be
adjusted
in
an5z
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
a,nd
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 forwajrd fuselage, and
the associated
plumbing necessary
to
connect
the instruments to the
sources.
The
heated
pitot
system consists
of a heating element
in the
pitot
tube,
7-37