NOTICE

SECTION 7 CESSNA
AIRPLANE AND SYSTEMS DESCRIPTION MODEL 208B G1000
ENGINE LUBRICATION SYSTEM (Continued)
Breather air from the engine bearing compartments and from the
accessory and reduction gearboxes is vented overboard through a
centrifugal breather installed in the accessory gearbox. The bearing
compartments are connected to the accessory gearbox by cored
passages and existing scavenge oil return lines. A bypass valve,
immediately upstream of the front element of the internal scavenge
pump, vents the accessory gearbox when the engine is operating at
high power.
An oil dipstick/filler cap is located at the rear of the engine on the left
side and is accessible when the left side of the upper cowling is raised.
Markings which indicate U.S. quarts low if the oil is hot are provided on
the dipstick to facilitate oil servicing. The oil tank capacity is 9.5 U.S.
quarts and total system capacity is 14 U.S. quarts. For engine oil type
and brand, refer to Section 8.
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 NORMAL. The NORMAL 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 NORMAL
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
air starts without starter assist, 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 CAS MSG.
7-50
U.S.
(Continued Next Page)
208BPHBUS-00