Cessna T182 Series User Manual

MODEL
182
& T182
SERIES
SERVICE
MANUAL
b. Remove
drain
tube,
safety wire,
nut and
wash-
c. Remove
fuel
lines from
pump,
observing
precautions
er at
bottom
of filter
bowl
and remove
bowl.
cautions
in
paragraph
12-3.
c. Carefully
unscrew
standpipe
and remove.
d. Disconnect
wire
at connector.
d.
Remove
filter
screen
and gasket.
Wash
filter
e. Remove
two mount
bolts,
retaining
hardware
for
screen and
bowl with
solvent
(Federal
Specification
installation.
P-S-661,
or equivalent)
and
dry
with
compressed
air.
f.
Reverse
preceding
steps
for
installation,
and check
e.
Using
a new
gasket
between
filter
screen
and
check
pump
operation
when
repair
is completed.
top assembly,
install
screen and
standpipe.
Tighten
standpipe only
finger tight.
12-40A. PRIMING
SYSTEM (T182 OPTIONAL).
f. Using all
new O-rings, install
bowl. Note that
step-washer at bottom of bowl is installed
so that 12-40B. DESCRIPTION. The
optional electric pri-
step
seats against
O-ring. Connect
drain tube.
mer
consists of a
solenoid valve,
switch, circuit
g. With
selector valve in "ON"
position, check for
breaker, and necessary
plumbing. The
solenoid
leaks and
proper operation
of quick-drain
valve.
valve is mounted
on a tee
attached to the
outlet side
h. Safety wire
bottom nut
to top assembly.
Wire
of the auxiliary
fuel pump. A line
to the engine
driven
must have right hand wrap, at least 45 degrees.
pump is attached to the other
side of the tee. The
primer functions in
conjunction with the
auxiliary
12-35. PRIMING SYSTEM.
electric fuel pump.
With the auxiliary electric fuel
pump
on, and
the primer
switch depressed,
the
12-36.
DESCRIPTION.
The priming
system is
solenoid
valve opens allowing
fuel to
flow to the
comprised
of a plunger-type manually-operated
cylinders.
primer,
which
draws fuel
from the
strainer and
forces
it through a tee fitting
to the aft end
of each 12-41.
INTEGRAL FUEL
BAY.
intake manifold.
Injecting the fuel
into each mani-
fold
primes both
banks of cylinders.
12-41A. DESCRIPTION.
Beginning
Serial
18266591. The integral
fuel bay is
a sealed
12-37. REMOVAL
AND INSTALLATION.
portion
of the inboard wing
structure between
a. With selector valve in "OFF" position,
drain the front and rear wing
spars, extending ap-
fuel from strainer and
lines with quick-drain control. proximately
five feet into each wing. This
b. Disconnect and cap or plug all fuel lines at type construction reduces overall weight as
primer (Observe
precautions in
paragraph 12-3.)
well as increasing
the strength of the
wing.
c. Unscrew
knurled nut and
remove plunger from
pump
body.
12-42. FUEL LEAK CLASSIFICATION.
Fuel
d. Remove pump body from instrument panel. leaks which do not constitute a night hazard are
stains, seeps and
heavy seeps NOT
in an enclosed
NOTE
area.
However,
they should
be repaired
when the
aircraft
is grounded for
other maintenance.
Fuel
Visually
inspect primer
lines for crushed,
leaks which
constitute a
fight hazard are
running
kinked
or broken condition.
Ensure proper
leaks in any area,
seeps, heavy seeps, or
stains in
clamping
to prevent fatigue
due to vibration
an enclosed
area, such as the
wing leading
edge, the
and chafing.
sections of wing inboard
and outboard of the
fuel bay
and the area between
the rear fuel spar
and the main
e. Prior to installing a primer, check for proper spar. These leaks must be repaired before that bay
pumping action
and positive
fuel shut-off in
the
is used for another
flight. The
wet or stained
spot
pumping action
and positive fuel shut-off
in the
locked position.
on the wing
in the area of the bay is an indication of
f. Reverse the preceding
steps for installation. the intensity
of the leak. Fuel leak classifications
With selector valve in "BOTH" position, check for are shown in figure 12-10.
leaks
and
proper
pumping
action.
NOTE
12-38.
AUXILIARY
ELECTRIC
FUEL
PUMP
- T182.
Stains
and
seeps that
are
not considered
a
flight hazard must be inspected after each
12-39.
DESCRIPTION.
On
turbocharged
aircraft
an
night to
insure that
they have
not grown
in
auxiliary
electric
fuel pump
is used
to ensure
adequate
intensity
to the
point
of causing
a flight
fuel flow.
See figure
12-9.
hazard.
12-40. REMOVAL AND INSTALLATION.
a. Place
fuel selector valve
in OFF position.
b. Make sure that Master Switch and Auxiliary Fuel
Pump Switch are OFF.
12-23

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)