Cessna 152 1979 Pilot Operating Handbook page 103

CESSNA SECTION 7
MODEL 152 AIRPLANE & SYSTEMS
DESCRIPTIONS
INTRODUCTION
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.
AIRFRAME
The airplane is an all-metal, two-place, high-wing, single-engine airplane equipped with tricycle
landing gear and designed for general utility purposes.
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 doorposts, and a bulkhead with attaching plates at the
base of the forward door posts for the lower attachment of the wing struts. Four engine mount
stringers are also attached to the forward doorposts and extend forward to the firewall.
The externally braced wings, containing the fuel tanks, are constructed 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-slotted flaps are attached to the trailing edge
of the wings. The ailerons are constructed of a forward spar containing balance weights,
formed sheet metal ribs and "V" type corrugated aluminum skin joined together at the trailing
edge. The flaps are constructed basically the same as the ailerons, with the exception of the
balance weights 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 wraparound skin panel, formed leading edge skin and a dorsal. The rudder
is constructed of a formed leading edge skin containing hinge halves, a wraparound 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 trailing 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.
1 July 1978 7-3