Ignition System - Textron Cessna Grand Caravan Ex 208B Pilot's Operating Handbook And Faa Approved Airplane Flight Manual

CESSNA SECTION 7
MODEL 208B 867 SHP AIRPLANE AND SYSTEMS DESCRIPTION
GARMIN G1000

IGNITION SYSTEM

The ignition system consists of two igniters, an ignition exciter, two
high-tension leads, an ignition monitor light, an IGNITION switch, and a
STARTER switch. Engine ignition is provided by two igniters in the
engine combustion chamber. The igniters are energized by the ignition
exciter mounted on the engine mount on the right side of the engine
compartment. Electrical energy from the ignition exciter is transmitted
through two high-tension leads to the igniters in the engine. The ignition
system is normally energized only during engine start.
Ignition is controlled by an IGNITION switch and a STARTER switch
located on the left sidewall switch and circuit breaker panel. The
IGNITION switch has two positions, ON and NORM. The NORM
position of the switch arms the ignition system so that ignition will be
obtained when the STARTER switch is placed in the START position.
The NORM position is used during all ground starts and during air
starts with starter assist. The ON position of the switch provides
continuous ignition regardless of the position of the STARTER switch.
This position is used for operation on water-covered runways, during
flight in heavy precipitation, during inadvertent icing encounters until
the inertial separator has been in bypass for 5 minutes, and when near
fuel exhaustion as indicated by illumination of the red RSVR FUEL
LOW annunciator.
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208BPHCUS-01 7-61
U.S.