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SECTION 7
AIRPLANE
&
SYSTEMS DESCRIPTIONS
CESSNA
MODELT210M
provides the suction necessary to operate the attitude indicator and
directional indicator. The system consists of a vacuum pump on the
engine, a vacuum relief valve and vacuum system air filter on the aft side
of the firewall below the instrument panel,
vacuum
operated instruments
on the left side of the instrument panel, and a suction gage on the right side
of the panel.
ATTITUDE INDICATOR
An attitude indicator is available and gives a visual indication of flight
attitude. Bank attitude is presented by a pointer at the top of the indicator
relative to the bank scale which has index marks at 10°, 20°, 30°
,
60°, and 90°
either side of the center mark. Pitch and
roll
attitudes are presented
by
a
miniature airplane in relation to the horizon bar. A knob at the bottom of
the instrument is provided for in-flight adjustment of
the
miniature
airplane to the horizon bar for a more accurate flight attitude indication.
~
,
DIRECTIONAL INDICATOR
A directional indicator is available and displays airplane heading on a
compass card in relation to a fixed simulated airplane image and
index.
The directional indicator will precess slightly over a period of
time.
Therefore, the compass card should be set in accordance with the magnetic
compass just prior to takeoff, and occasionally re-adjusted on extended
flights. A knob on the lower left edge of the instrument is used to adjust the
compass
card to correct for any precession.
SUCTION GAGE
A suction gage is located on the upper right side of the instrument
panel when the airplane is equipped with a vacuum system. Suction
available for operation of the attitude indicator and directional indicator is
shown by this gage, which is calibrated in inches of mercury. The desired
suction range is 4.6 to 5.4 inches of mercury. A suction reading below
this
range may indicate a system malfunction or improper adjustment, and in
this case, the indicators should not be considered reliable:
STALL WARNING SYSTEM
The airplane is equipped with a vane-type stall warning unit in the
leading edge of the left wing. The unit is electrically connected to a dual
warning
unit located above the right cabin door behind the headliner. The
vane in the wing senses the change in airflow over the wing, and operates
the dual warning unit, which produces a continuous tone over the airplane
speaker between 5 and 10 knots above the stall in all
configurations.
7-46
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