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SECTION 7 CESSNA
AIRPLANE AND SYSTEMS DESCRIPTION MODEL
2088
(675 SHP)
FUEL SYSTEM
(Continued)
AUXILIARY BOOST PUMP SWITCH
An auxiliary boost pump switch, located on the left sidewall switch and
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circuit breaker panel, is labeled FUEL BOOST and has OFF, NORM,
,
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and ON positions. When the switch is in the OFF position, the auxiliary
boost pump is inoperative. When the switch is in the NORM position,
,
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the auxiliary boost pump is armed and will operate when fuel pressure
in the fuel manifold assembly drops below 4.75 psi. This switch position
,?
is used for all normal engine operation where main fuel flow is provided
by the ejector boost pump and the auxiliary boost pump is used as a
standby. When the auxiliary boost pump switch is placed in the ON
position, the auxiliary boost pump will operate continuously. This
position is used for engine start and any other time that the auxiliary
boost pump cycles on and off with the switch in the NORM position,
and for all operations utilizing aviation gasoline.
FUEL FLOW INDICATOR
A fuel flow indicator, located at the top of the instrument panel,
indicates the fuel consumption of the engine in pounds per hour based
on Jet A fuel. The indicator measures the flow of fuel downstream of
the fuel control unit just before being routed into the flow divider. When
power is removed from the indicator, the needle will stow below zero in
the OFF band. The fuel flow indicator receives power from a "pull-off'
type circuit breaker labeled FUEL FLOW, on the left sidewall switch and
circuit breaker panel.
U.S.
(Continued Next Page)
Revision
23
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