Cessna R182 - Hydraulic System

CESSNA
MODEL N,182
SECTION
7
AIRPLANE
&
SYSTEMS
DESCRIPTIONS
(
the wings
are not level.
The
fuel system
is
equipped
witb
drain
valves
to
provide
a means
for
the examination of
fuel in the
system
for
contamination and
grade.
The
system
should
be examined before the first flight
of every day
and
after
each
refueling,
by using the sampler cup
provided
to drain fuel
from
the
wing
tank sumps,
and by utilizing
the
fuel strainer drain under a,n &ccess
panel
on the
left side of tho engine cowling. The fuel tanks
should
be
filled
after
each
flight to
prevent
condensation.
HYDRAULIC SYSTEM
Hydraulic
power (soe
figure
7-7)
is supplied
by
an
electrically-driven
hydraulic
power pack
located behind the firewall
between the
pilot's
and
copilot's rudder
pedals.
The
power pack's
only function is
to supply
hydraulic
power
for operation
of the retractable
landing
gear.
This
is
accomplished by applying
hydraulic
pressure
to actuator
cylinders
which
extend
or
retract the
gear.
The bydraulic
systemnorrnally
operates
at 1000
PSI
to 1500 FSI,
and is
protected
by relief
valves which
prevent
high
pressure
damage to
the
pump
and
other components in
the system.
The
electrical
portion
of the
power pack
is
protected.by
a 30-amp
push-pull
type
circuit breaker
switch,
labeled
GEAR PIIMP, on the left
switch
and
control
panel.
The hydraulic
power pack
is turned
on by a
pressure
switch
on
the
power
pack
when the landing
gear
lever is
placed
in
eitber the
GEAR,
UP or
GEAR DOWN
position.
When
the
lever
is
placed
in
the GEAR UP or GEAR
DOWN
position,
it
mechanically
rotates
a selector valve which applies
hydraulic
pressure
in the direction selected.
As soon as the landing
gear
reaches
the selected
po6ition,
a series of electrical
switches will
illuminate
one of two indicator
lights on the instrument
panel
to show
gear
position
and
completion
of the cycle.
After indicator
light illumination,
hydraulic
pressure
will continue to build
until the
power pack
pressure
switch
turns
the
power pack
off.
The
hydraulic
systom includes a,n emergency
hand
pump
to
permit
manual
extension,of
the landing
gear
in
the event
of
hydraulic
power pack
failure.
The hand
pump
is located on the cabin floor
between the front seats.
During
normal
operations, the landing
gear
should require
from
5 to 7
seconds to fully extend or
retract. For
malfunctions
of the
hydraulic
and
landing
gear
systems,
refer to
Section 3 of this
handbook.
7-27