Ignition System; Fuel System - Continental Motors GTSIO-520 SERIES Operator's Manual

Aircraft engines
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6.
IGNITION SYSTEM
High voltage current is generated and distributed to the upper right
and lower left spark plugs by a magneto mounted on the front side
of the right crankcase accessory pad. The magneto on the left
crankcase pad, in addition to supplying high voltage current to the
upper left and lower right spark plugs, is also equipped with a double
breaker. The double breaker magneto serves a dual purpose. When
cranking the engine the retard breaker is in effect, causing a shower
of high voltage sparks to start -the engine. As the engine is started and
the cranking motor is disengaged the retard breaker is no longer
transmitting spark and the engine is running on the advance breakers
from both magnetos. Spark is transmitted to the spark plug through
high tension cables which pass through flexible, braided, shielded
conduit assemblies.
7.
FUEL SYSTEM
The fuel injection system is of the multi-nozzle continuous flow type
which controls fuel flow to match engine air flow. Any change in air
throttle position, engine speed, or a combination of both, causes
changes in fuel flow in correct relation to engine air flow. A manual
mixture control and a pressure gauge indicating metered fuel flow are
provided for precise leaning at any combination of altitude and
power settings. As fuel flow is directly proportioned to the metered
fuel pressure, settings can be predetermined and fuel consumption
can be accurately predicted.
The continuous flow system permits the use of a typical rotary vane
pump with integral relief valve in place of a much more complex and
expensive plunger type pump. The relief valve maintains maximum
fuel flow under full power conditions. The fuel pump also
incorporates a variable orifice and a centrifugal rotor for separation
of vapor formed between the tank and engine at high altitudes.
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