Apitot tube, mounted on the lower surface of the left wing,
picks up airspeed indicator ram air. Anoptional heated
pitot
prevents pitot tube icing when flying in moisture- laden
air.
Static ports on each side of the tail cone supply static air
pressure for the altimeter, the airspeed indicator, and the
vertical speed indicator. An optional alternate static pres-
sure source valve may be installed.
A
stall warning horn, triggered by a sensing vane on the
left wing leading edge, will sound when 'airspeed drops to
near stall speed. Landing gear position lights on the panel
will show red when the gear
is
retracted. Reducing power
below
10
inches manifold pressure when the gear
is
not
in
the down- and- locked position will cause the gear warning
horn to sound.
FLlGHT
CONTROLS
\
PRIMARY
FLIGHT CONTROLS
)I
'.
Push-pull tubes withself-aligning rodend bearings actuate
the primary flight control surfaces. Beveled aileron trail-
ing edges help
reduce pilot control forces requiredfor flight
maneuvering.
A
spring-loaded interconnect device indirect-
ly joins the aileron and rudder controlsystems
to
assist in
lateral stability during flight maneuvers. Control surface
gap strips minimize airflow spoilage at the hinge slots and
reduce drag.
POSITIVE CONTROL
The Mooney Positive Control (P.C.) system provides
a
high
degree of roll and yaw stability, thereby enhancing the in-
herent wings- level flight characteristics of the aircraft.
Positive Control
will
hold an average heading over
a
long
periodof time when the aircraft
is
trimmed properly. How-
ever, without the installation of
a
magnetic heading lock,
P,C. will not maintain an absolute preselected heading.
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