Airframe - Cessna 150 COMMUTER 1976 Pilot Operating Handbook

SECTION 7
AIRPLANE & SYSTEMS DESCRIPTIONS
TABLE OF CONTENTS (Continued)
Over-Voltage Sensor and Warning Light
Circuit Breakers and Fuses . .
Ground Service Plug Receptacle
Lighting Systems
Exterior Lighting. . . . . . .
Interior Lighting . . . . . . .
Cabin Heating, Ventilating and Defrosting System
Pitot-Static System and Instruments
Airspeed Indicator . . .
Rate-of-Climb Indicator
Altimeter . . . . . . .
Vacuum System and Instruments
Attitude Indicator. .
Directional Indicator
Suction Gage. . . .
Stall Warning Sys tern . .
A vionics Support Equipment
Radio Selector Switches .
Static Dischargers . . .
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CESSNA
MODEL 150M
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CESSNA
MODEL 150M
INTRODUCTION
SECTION 7
AIRPLANE & SYSTEMS DESCRIPTIONS
This section provides description and operation of the airplane and
its systems. Some equipment described herein is optional and may not
be installed in the airplane. Refer to Section 9, Supplements, for details
of other optional systems and equipment.
AIRFRAME
The construction of the fuselage is a conventional formed sheet metal
bulkhead, stringer, and skin design referred to as semi-monocoque.
Major items of structure are the front and rear carry-through spars to
which the wings are attached, a bulkhead and forgings for main landing
gear attachment at the base of the rear door posts, and a bulkhead with
attaching plates at the base of the forward door posts for the lower attach-
ment of the wing struts. Four engine mount stringers are also attached
to the forward door posts and extend forward to the firewall.
The externally braced wings, containing the fuel tanks, are construc-
ed of a front and rear spar with formed sheet metal ribs, doublers, and
stringers. The entire structure is covered with aluminum skin. The
front spars are equipped with wing-to-fuselage and wing-to-strut attach
fittings. The aft spars are equipped with wing-to-fuselage attach fittings,
and are partial-span spars. Conventional hinged ailerons and single-slot-
ted flaps are attached to the trailing edge of the wings. The ailerons are
constructed of a forward spar containing a balance weight, formed sheet
metal ribs and "V" type corrugated a luminum skin joined together at the
trailing edge. The flaps are constructed basically the same as the aile-
rons, with the exception of balance weight and the addition of a formed
sheet metal leading edge section.
The empennage (tail assembly) consists of a conventional vertical
stabilizer, rudder, horizontal stabilizer, and elevator. The vertical
stabilizer consists of a spar, formed sheet metal ribs and reinforcements,
a wrap-around skin panel, formed leading edge skin and a dorsal. The
rudder is constructed of a formed leading edge skin containing hinge
halves, a wrap-around skin panel and ribs, and a formed trailing edge
skin with a ground adjustable trim tab at its base. The top of the rudder
incorporates a leading edge extension which contains a balance weight.
The horizontal stabilizer is constructed of a forward spar, main spar,
formed sheet metal ribs and stiffeners, a wrap-around skin panel, and
formed leading edge skins. The horizontal stabilizer also contains the
elevator trim tab actuator. Construction of the elevator consists of a
main spar and bellcrank, left and right wrap-around skin panels, and a
formed trailing edge skin on the left half of the elevator; the entire trail-
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