Flight Controls; Instrument Panel; Ground Control; Wing Flap System - Cessna 150 COMMUTER 1976 Pilot Operating Handbook

SECTION 7
AIRPLANE & SYSTEMS DESCRIPTIONS
CESSNA
MODEL 150M
ing edge of the right half is hinged and forms the elevator trim tab. The
leading edge of both left and right elevator tips incorporate extensions
which contain balance weights.
FLIGHT CONTROLS
The airplane's flight control system consists of conventional aileron,
rudder, and elevator control surfaces (see figure 7-1). The control sur-
faces are manually operated through mechanical linkage using a control
wheel for the ailerons and elevator, and rudder/brake pedals for the rud-
der.
TRIM SYSTEM
A manually-operated eleva,tor trim tab is provided. Elevator trim-
ming is accomplished through the elevator trim tab by utilizing the verti-
cally mounted trim control wheel. Upward rotation of the trim wheel will
trim nose-down; conversely, downward rotation will trim nose-up.
INSTRUMENT PANEL
The instrument panel (see figure 7 -2) is designed to place the primary
flight instruments directly in front of the pilot. The gyro-operated flight
instruments are arranged one above the other, slightly to the left of the
control column. To the left of these instruments are t e airspeed indica-
tor, turn coordinator, and suction gage. On the rig . side are the clock,
altimeter, rate-of-climb indicator, and navigation instruments. Avionics
equipment is stacked approximately on the centerline of the panel, with
space for additional equipment on the lower right side of the instrument
panel. The right side of the panel also contains the tachometer, ammeter,
over-voltage light, and additional optional instruments such as a flight
hour recorder. A subpanel, under the primary instrument panel, contains •
the fuel quantity indicators and engine instruments positioned below the
pilot's control wheel. The electrical switches, primer, and parking
brake control are located around these instruments. The engine controls,
wing flap switch, and cabin air and heat control knobs are to the right of
the pilot, along the upper edge of the subpanel. Directly below these con-
trols are the elevator trim control wheel, trim position indicator, micro-
phone, circuit breakers, and a cigar lighter. A map compartment is on
the extreme right side of the subpanel.
For details concerning the instruments, switches, circuit breakers,
and controls on this panel, refer in this section to the description of the
systems to which these items are related.
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CESSNA
MODEL 150M
SECTION 7
AIRPLANE & SYSTEMS DESCRIPTIONS
GROUND CONTROL
Effective ground control while taxiing is accomplished through nose
wheel steering by using the rudder pedals; left rudder pedal to steer left
and right rudder pedal to steer right. When a rudder pedal is depressed,
a spring-loaded steering bungee (which is connected to the nose gear and
to the rudder bars) will turn the nose wheel through an arc of approximate-
ly 8. 5° each side of center. By applying either left or right brake, the de-
gree of turn may be increased up to 30° each side of center.
Moving the airplane by hand is most easily accomplished by attaching
a tow bar to the nose gear strut. If a tow bar is not available, or pushing
is required, use the wing struts as push points. Do not use the vertical
or horizontal surfaces to move the airplane.
If
the airplane is to be towed
by vehicle, never turn the nose wheel more than 30° either side of center
or structural damage to the nose gear could result.
The minimum turning radius of the airplane, using differential brak-
ing and nose wheel steering during taxi, is approximately 24 feet 8 inches.
To obtain a minimum radius turn during ground handling, the airplane
may be rotated around either main landing gear by pressing down on the
tailcone just forward of the dorsal to raise the nose wheel off the ground.
WING FLAP, SYSTEM
The wing flaps
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of the single-slot type (see figure 7-3) and are
lectrically operated by a motor located in the right wing. Flap position
is controlled by a switch, labeled WING FLAPS, on the lower center por-
I
ion of the insfrument panel. Flap position is mechanically indicated by a
pC,linter housed in the left front doorpost.
To extend the wing flaps, the flap switch, which is spring-loaded to
I
he center, or off, position, must be depressed and held in the DOWN
I
sition until the desired degree of extension is reached. Normal full
fla p extension in flight will require approximately 9 seconds. After the
flaps reach maximum extension or retraction, limit switches will auto-
matically shut off the flap motor.
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To retract the flaps, place the flap switch in the UP position. The
witch will remain in the UP position without manual assistance due to a
rI te nt in the switch. Full flap retraction in flight requires approximately
; s econds. More gradual flap retraction can be accomplished by intermit-
t nt operation of the flap switch to the UP position. After full retraction,
I
h switch should be returned to the center off position .
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