SECTION 7 CESSNA
AIRPLANE AND SYSTEM DESCRIPTION MODEL T182T NAV III
GFC 700 AFCS
U.S.
ENGINE (Continued)
IGNITION AND STARTER SYSTEM
Engine ignition is provided by two engine driven magnetos, and two
spark plugs in each cylinder. The left magneto fires the upper left and
lower right spark plugs, and the right magneto fires the lower left and
upper right spark plugs. Normal operation is conducted with both
magnetos due to the more complete burning of the fuel/air mixture with
dual ignition.
Ignition and starter operation is controlled by a rotary-type switch
located on the left switch and control panel. The switch is labeled
clockwise, OFF, R, L, BOTH, and START. The engine should be
operated on both magnetos (BOTH position) except for magneto
checks. The R and L positions are for checking purposes and
emergency use only. When the switch is rotated to the START position,
(with the MASTER switch in the ON position), the starter contactor is
closed and the starter, now energized, will crank the engine. When the
switch is released, it will automatically return to the BOTH position.
AIR INDUCTION SYSTEM
The engine air induction system receives ram air through an intake on
the lower front portion of the engine cowling. The intake is covered by
an air filter which removes dust and other foreign matter from the
induction air. Airflow passing through the filter enters an air box, which
is equipped with a spring-loaded alternate air door. If the air induction
filter should become blocked, suction created by the engine will open
the door and draw unfiltered air from inside the lower cowl area. An
open alternate air door will result in an approximate 10% power loss at
full throttle. After passing through the air box, induction air enters a
compressor then to a fuel/air control unit under the engine, and is then
ducted to the engine cylinders through intake manifold tubes.
(Continued Next Page)
T182TPHBUS-00
7-38
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