Cooling System; Propeller; Fuel System - Cessna 172 P Pilot Operating Handbook

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CO O L I N G S YS TE M
Ram air for engine cooling enters
through two intake openings in
the front of the engine cowling.
The cooling air is directed around
PRO PE L L E R
The airplane is equipped with a
two-bladed, fixed-pitch, one-piece
F UE L S YS TE M
The airplane may be equipped
with a standard fuel system or
either of two long range systems.
Each system consists of two
vented fuel tanks (one tank each
wing), a four-position selector
valve, fuel strainer, manual
primer, and carburetor. The 68-
gallon long-range system utilizes
integral tanks and the other two
systems employ removable
aluminium tanks. Fuel flows by
gravity from the two wing tanks
to a four-position selector valve
labelled BOTH, LEFT, RIGHT and
fuel quantity
tansmitter filler cap
left fuel tank
drain
vent with
valve
check valve
strainer
to engine
engine
primer
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the cylinders and other areas of
the engine by baffling, and is then
exhausted through an opening at
the bottom aft edge of the
forged aluminium alloy propeller
wich is anodized to retard
FUEL TANKS
STANDARD
LONG RANGE
LONG RANGE
(INTEGRAL)
OFF. With the selector valve in
either the BOTH, LEFT or RIGHT
position, fuel flows through a
strainer to the carburetor. From
the carburetor, mixed fuel and
air flows to the cylinders through
vented filler cap
right fuel tank
selector
valve
drain
valve
selector valve
drain plug
fuel
fuel
strainer
crain
control
carburetor
to
engine
AIRPLANE & SYSTEMS DESCRIPTION
cowling. No manual cooling
system control is provided.
corrosion. The propeller is 75
inches in diameter.
FUEL TOTAL FUEL
LEVEL
FULL 43
FULL 54
FULL 68
intake manifold tubes. The
manual primer draws its fue from
the fuel strainer and injects it
into the cylinder intake ports.
Fuel system venting is essential
to system operation. Blockage
of the system will result in
decreasing fuel flow and eventual
fuel quantity
engine stoppage. Venting is
tansmitter
a c c o m l i s h e d
interconnecting line from the
right fuel tank to the left fuel
tank. The left fuel tank is vented
overboard through a vent line,
equipped with a check valve,
which protrudes from the bottom
surface of the left wing near the
wing strut. The right fuel tank
filler cap is also vented.
When long range integral tanks
are installed, the airplane may be
serviced to a reduced capacity to
permit heavier cabin loadings.
This is accomplished by filling
each tank to the bottom edge of
throttle
the fuel filler collar, thus giving
control
a reduced fuelload of 24 gallons
in each tank.
Fuel Quantity is measured by two
mixture
f l o a t - t y p e
control
transmitters and indicated by two
elictrically-operated fuel quantity
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TOTAL TOTAL
UNUSABLE USABLE
3 40
4 50
6 62
b y a n
f u e l q u a n t i t y