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CESSNA
MODELT210M
SECTION 7
AIRPLANE
&
SYSTEMS DESCRIPTIONS
panel on the left side of the engine cowling. Quick-drain valves
are also
provided for the fuel reservoir tanks. The valves are located under plug
buttons in the belly skin of the airplane, and are used to facilitate purging
of the fuel system in the event water is discovered during the preflight fuel
system inspection. The fuel tanks should be filled after each flight to
prevent condensation.
HYDRAULIC SYSTEM
Hydraulic power (see figure
7-8)
is supplied by
an
electrically-driven
hydraulic power pack located behind the control pedestal. 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 open and close the wheel well doors,
operate the gear up and down locks, and extend or retract the gear. The
electrical portion of the power pack is protected by a 30-amp push-pull
type circuit breaker switch on the circuit breaker panel.
The hydraulic power pack is turned on, and the direction of actuation is
selected by the landing gear lever when it is placed in either the gear-up or
gear-down position. When the gear has fully extended or retracted
and
locked, a series of electrical switches will illuminate one of two indicator
lights on the instrument panel to show gear position. Hydraulic pressure
is then switched from the gear actuators to the door actuators to close the
gear doors. As soon as the doors reach the closed position, a hydraulic
pressure switch in the door closing system will automatically turn off the
power pack.
The hydraulic system includes an emergency hand pump to permit
manual extension of the landing gear in the event of hydraulic power pack
or electrical system failure. The hand pump is
located
on the cabin floor
between the front seats.
,,----.,_ _
During normal operations, the landing gear should require from 10 to
12 seconds to fully extend or retract. For malfunctions of the hydraulic and
landing gear systems, refer to Section 3 of this handbook.
BRAKE SYSTEM
The airplane has a single-disc, hydraulically-actuated brake on each
main landing gear wheel. Each brake is connected, by a hydraulic line, to a
master cylinder attached to each of the pilot's rudder pedals. The brakes
are operated by applying pressure to the top of either the left (pilot's) or
right (copilot's) set of rudder pedals, which are interconnected. When the
airplane is parked, both main wheel brakes may be set by utilizing
the
7-33
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