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

CESSNA
MODEL 208B 867 SHP
GARMIN G1000

INERTIAL SEPARATOR SYSTEM

An inertial separator system in the engine air inlet duct prevents
moisture particles from entering the compressor air inlet plenum when
in bypass mode. The inertial separator consists of two movable vanes
and a fixed airfoil which, during normal operation, route the inlet air
through a gentle turn into the compressor air inlet plenum. When
separation of moisture particles is desired, the vanes are positioned so
that the inlet air is forced to execute a sharp turn in order to enter the
inlet plenum. This sharp turn causes any moisture particles to separate
from the inlet air and discharge overboard through the inertial separator
outlet in the left side of the cowling.
Inertial separator operation is controlled by a T-handle located on the
lower instrument panel. The T-handle is labeled BYPASS-PULL,
NORMAL-PUSH. 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, ice crystals) with an
OAT of 5°C (41°F) or less. It may also be used for ground operations or
takeoffs from dusty, sandy field conditions to minimize ingestion of
foreign particles into the compressor. The NORMAL position is used for
all other operations.
The T-handle locks in the NORMAL position by rotating the handle
clockwise 1/4 turn to its vertical position. To unlock, push forward
slightly and rotate the handle 90° counterclockwise. The handle can
then be pulled into the BYPASS position. Once moved to the BYPASS
position, air loads on the movable vanes hold them in this position.
Do not return the INERTIAL SEPARATOR to NORMAL
until after engine shutdown and inspection if icing
conditions are encountered.
When moving the inertial separator control from BYPASS to
NORMAL position during flight, reduction of engine power
will reduce the control forces.
208BPHCUS-00
AIRPLANE AND SYSTEMS DESCRIPTION
CAUTION
NOTE
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SECTION 7
7-63
U.S.