NOTICE

SECTION 4 CESSNA
NORMAL PROCEDURES MODEL 208B G1000
ENGINE IGNITION PROCEDURES
For most operations, the IGNITION Switch is left in the NORM position.
With the switch in this position, ignition is on only when the starter
switch is in the START position.
NOTE
The use of ignition for extended periods of time will reduce
ignition system component life.
The IGNITION Switch should be turned ON to provide continuous
ignition under the following conditions:
1. Emergency engine starts without starter assist (refer to Section 3,
AIRSTART).
2. Operation on wet or contaminated runways.
3. Flight in heavy precipitation.
4. Flight in moderate or greater turbulence.
5. During inadvertent icing encounters prior to the INERTIAL
SEPARATOR being selected to BYPASS.
6. When near fuel exhaustion as indicated by Red RSVR FUEL
LOW CAS MSG.
Refer to Section 7, Engine Ignition System, for further details regarding
the ignition system.
ENGINE INERTIAL SEPARATOR PROCEDURES
An INERTIAL SEPARATOR system is built into the engine air inlet duct
to prevent ice buildups on the compressor inlet screen. The INERTIAL
SEPARATOR control should be moved to the BYPASS position prior to
running the engine during ground or flight operation in visible moisture
(clouds, rain, snow or ice crystals) with an OAT of 5°C (41°F) or less.
The BYPASS mode can also be used for ground operations or takeoffs
with dusty, sandy field conditions to minimize ingestion of foreign
particles into the compressor. Refer to charts in Section 5 for
performance changes associated with the INERTIAL SEPARATOR in
the BYPASS mode.
The NORMAL mode is used for all other operating conditions, since it
provides substantial inlet ram recovery. This results in more efficient
engine operation and higher critical altitude for a particular power
setting.
Do not return the INERTIAL SEPARATOR to NORMAL until after
engine shutdown and inspection if icing conditions are encountered.
Refer to Section 7, Engine Air Induction System for further details
regarding the INERTIAL SEPARATOR.
4-40
U.S.
FAA APPROVED
208BPHBUS-00