SECTION 7
CESSNA
AIRPLANE AND SYSTEMS DESCRIPTION MODEL
2088 (675 SHP)
FUEL
SYSTEM
The airplane fuel system (see Figure 7-12) consists of two vented,
integral fuel tanks with shutoff valves, a fuel selectors off warning
system, a fuel reservoir, an ejectorfuel pump, an electric auxiliary boost
pump, a reservoir manifold assembly, a
firewall shutoff valve, a fuel
filter, an oil-to-fuel heater, an engine-driven fuel pump, a fuel control
unit, a flow divider, dual manifolds, and 14 fuel
nozzle assemblies. A
fuel can and drain is also provided. Refer to Figure 7-13 for fuel
quantity data for the system.
WARNING
UNUSABLE FUEL LEVELS FOR
THIS AIRPLANE WERE
DETERMINED
IN
ACCORDANCE
WITH
FEDERAL
AVIATION REGULATIONS. FAILURE TO OPERATE THE
AIRPLANE IN COMPLIANCE
WITH THE FUEL
LIMITATIONS SPECIFIED IN SECTION
2
MAY FURTHER
REDUCE THE AMOUNT OF FUEL AVAILABLE IN
FLIGHT.
Fuel flows from the tanks throuah the two fuel tank shutoff valves at
each tanks. The fuel tank
snutoff-valves are mechanically controlled by
two fuel selectors. labeled LEFT. ON and OFF, located on the overhead
panel. By manipulating the fuel selectors, the pilot can select either
leff
or right fuel tanks or both at the same time. Normal operation is with
both tanks on. Fuel flows by gravity from the shutoff valves in each tank
to the fuel reservoir. The reservoir is located at the low point in the fuel
system which maintains a head of fuel around the ejector boost pump
and auxiliary boost pump which are contained within the reservoir. This
head of fuel prevents pump cavitation in low-fuel quantity situations,
especially during in-flight maneuvering. Fuel in the reservoir is pumped
by the ejector boost pump or by the electric auxiliary boost pump to the
reservoir manifold assemblv. The eiector boost
oumo. which is driven
by
motlve fuel flow from the'fuel conirol unlt, nornially'prov~des fuel flow
when the
enalne
IS
ooerat~na. In rne event of fallure of the elector boost
pump, the electric boost
iump will automatically turn on, thereby
supplying fuel flow to the engine. The auxiliary boost pump is also used
to supply fuel flow during starting. Fuel in the reservoir manifold then
flows through a fuel shutoff valve located on the aft side of the firewall.
This shutoff valve enables the pilot to cut off all fuel to the engine.
(Continued Next Page)
Revision 23
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