Section II
DESCRIPTION AND OPERATING DETAILS
The following paragraphs describe the systems and equipment
whose function and operation is not obvious when sitting in the
airplane. This section also covers in somewhat greater detail some
of the items listed in Check List form in Section I that require
further explanation.
FUEL SYSTEM.
Fuel is supplied to the engine from two integral fuel bays, one
in each wing. Usable fuel in each bay, for all flight conditions, is
25.0 gallons when completely filled (a 22 gallon marker, in the
form of a series of small holes just inside the filler neck, is
provided to facilitate fueling to reduced fuel loads). With full
cabin loading, it may be necessary to reduce the fuel load to keep
the aircraft within the approved weight limits. (Refer to Section
IV for weight and balance control procedures.)
Fuel from each wing fuel bay flows through a reservoir tank,
auxiliary fuel pump with by-pass, and fuel shutoff valve to the
fuel strainer. From there, it is routed to an engine-driven fuel
pump which delivers the fuel under pressure to the fuel injection
unit. The continuous flow type fuel injector meters the fuel in
proportion to consumed air flow, through a vented nozzle at each
cylinder intake port. Manual mixture control and idle cut-off
functions are provided.
The auxiliary fuel pump is used primarily for priming the
engine before starting. Priming is accomplished through the
regular injection system.
If the auxiliary fuel pump switch is accidentally turned "ON"
(with master switch "ON" and mixture rich) with the engine
stopped, the intake manifolds will be flooded.
The auxiliary fuel pump is also used for vapor suppression in
hot weather. Normally, momentary use will be sufficient for vapor
2-1
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