Cessna T182 Series User Manual

MODEL
182
& T182
SERIES
SERVICE
MANUAL
11A-1.
ENGINE
COWLING.
d.
Reverse
the
preceding
steps
for
reinstallation.
Rig cowl
flaps, if necessary.
in accordance
with
11A-2.
DESCRIPTION.
The
engine
cowling
is
divid-
paragraph
11A-9.
ed
into
major
removable
segments.
The
upper
RH
segment
has
an oil
dipstick
and remote
fuel
strainer
11A-9.
RIGGING.
(See
figure
11A-1.)
drain control
access
door.
The
upper
center
cowl
a.
Disconnect
cowl
flap
control
clevises
(6) from
skin
has the
oil filler
neck
access
door,
and the
cowl
flap
shock-mounts
(7).
lower
LH panel
contains
the turbocharger
access
b.
Check
to make
shure
that flexible
controls
reach
door.
Controllable
cowl
flaps
are
integral
with
the
their
internal
stops
in
each
direction.
Mark
controls
lower
trailing
edge
of cowl
skin.
They
are
hinged
at
so that
full
travel
can be
readily
checked
and
main-
the front
edge,
and controlled
manually
to
maintain
tained
during
remaining
rigging
procedures.
efficient
engine
operating
temperature.
The
upper
c.
Place
cowl flap
control
lever
(11)
in CLOSED
pos-
center
and lower
cowl segments
are screw
fastened
ition.
If the
control
lever
cannot
be placed
in closed
at
the nose
cap, but
RH and
LH segments
use quick
position,
adjust
controls
at upper
clevis
(10) to
position
release
fasteners
all around
for
easy access.
Land-
control
lever
in bottom
hole
of position
bracket
(9).
ing
and taxi
lights are
mounted
in the nose
cap lower
d. With
control
lever in
CLOSED position,
hold one
cowling.
cowl
flap closed,
streamlined
with
trailing
edge
of lower
cowl.
Loosen jam
nut and adjust
clevis
(6) on the con-
11A-3.
REMOVAL
AND
INSTALLATION.
trol
to hold
cowl
flap in
this position.
Retighten
jam
a. Remove
screws
securing
upper
center
and lower
nut and
install
bolt through
clevis
and
shock-mount.
cowling
segments
to the nose cap.
b. Release
the
quick-release
fasteners
attaching
NOTE
the cowling
to
the fuselage
and
at the
parting
surfaces
of the
center and
lower
segments.
Be shure
threads
are visible
in clevis
inspec-
c.
Disconnect
the
landing
and
taxi
light
wires
at
the
tion
holes.
quick-disconnects
and carefully
remove
cowling.
d. Reverse
the preceding
steps
for
reinstallation.
e. Repeat
preceding
step
for the
opposit
cowl flap.
Ensure
the
baffle seals
are turned
in the
correct
f. Check
that
all clamps
and jam
nuts are
tight.
direction
to confine
and direct
air flow
around the
g. Check
for ease
of operation.
engine.
The
vertical
installed
seals
must
fold
for-
ward
and the
side seals
must
fold upwards.
11A-10.
ENGINE.
11A-4.
CLEANING
AND
INSPECTION.
Wipe
the
11A-11.
DESCRIPTION.
An
air
cooled,
wet-sump,
inner
surfaces
of
the cowling
segments
with
a clean
six-cylinder,
horizontally-opposed,
direct-drive,
cloth
saturated
with
cleaning
solvent
(Stoddard
or
carbureted,
Turbocharged
Avco
Lycoming
0-540-
equivalent).
If
the
inside
surface
of
the
cowling
is
L3C5D
engine,
driving
a constant-speed
propeller,
coated
heavily
with
oil
or
dirt,
allow
solvent
to
soak
is
used
to power
the
aircraft
The
cylinders,
num-
until
foreign
material
can be
removed.
Wash
painted
bered
from
front
to rear,
are staggered
to
permit
a
surfaces
of the
cowling
with
a solution
of mild
soap
separate
throw
on the
crankshaft
for
each
connecting
and
water
and
rinse
thoroughly.
After
washing,
a
rod.
The
right
front
cylinder
is
number
1 and
cylin-
coat
of wax
may
be applied
to the
painted
surfaces
to
ders
on
the right
side
are
identified
by
odd
numbers
prolong
paint
life.
After
cleaning,
inspect
cowling
1,
3 and
5. The
left
front
cylinder
is
number
2 and
for dents,
cracks,
loose
rivets
and
spot welds.
Re-
the cylinders
on
the left
side are
identified
as number
pair
all defects
to
prevent
spread
of damage.
2, 4
and 6.
Refer
to paragraph
11A-12
for
engine
data. For
repair and
overhaul
of the engine
turbo-
11A-5.
REPAIR.
(Refer
to Section
17.)
charger,
accessories
and
propeller,
refer
to the
appropriate
publications
issued
by
their manufacturers.
11A-6.
COWL
FLAPS.
These
publications
are
available
from
the
Cessna
Supply
Division.
11A-7.
DESCRIPTION.
Cowl
flaps
are provided
to
aid
in controlling
engine
temperature.
Two
cowl
11A-12.
TIME
BETWEEN
OVERHAUL
(TBO).
Avco
flaps,
operated
by
a single
control
in the
cabin,
are
Lycoming
recommends
engine
overhaul
at
2000
hours
located
at the
aft
edge
of the
lower
cowl
segment.
operating
time
for
the 0-540-L3C5D
series
engines.
Refer
to Avco
Lycoming
Service Instruction
1009,
NOTE
and
to
any
superseding
Instructions,
revisions
or
supplements
thereto,
for
further recommendations.
Refer
to Section
2 for
cowl
flap
hinge
inspec-
At
the
time
of overhaul,
engine
accessories
should
be
tion frequency.
overhauled.
Refer
to Section
13
for propeller
and
governor
overhaul periods.
11A-8.
REMOVAL
AND
INSTALLATION.
(Refer
to
figure
11A-1.)
11A-13.
OVERSPEED
LIMITATIONS.
The
engine
a.
Place
cowl
flap control
lever
(11) in
the
OPEN
must
not
be operated
above
specified
maximum
con-
position.
tinuous
RPM.
However,
should
inadvertent
overspeed
b.
Disconnect
cowl
flap
control
clevises
(6) from
occur,
refer
to
Avco Lycoming
Service
Bulletin
369F,
cowl flap
shock-mounts
(7).
and
to any
superseding
bulletins,
revisions
or supple-
c.
Remove
safety
wire
securing
hinge
pins
to
cowl
ments
thereto,
for further
recommendations.
flaps, pull pins and remove flaps.
11A-2
Revision
1

Cessna T182 Series Specifications

General

Engine Type	Lycoming IO-540-AB1A5
Horsepower	230 hp
Seating Capacity	4
Service Ceiling	18, 100 feet
Takeoff Distance	1, 600 feet
Landing Distance	1, 350 ft
Type	Single-engine
Max Takeoff Weight	3, 100 lb
Wingspan	36 ft
Length	29 ft
Height	9 feet 3 inches
Fuel Capacity	92 US gal (348 L)