Cessna 152 - Page 105

CESSNA
MODEL
152
INTRODUCTION
SECTION7
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
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
semimonocoque.
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
attachment
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
construct-
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
fit-
tings.
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
stabiliz-
er
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
1
July
1978
7-3