Cessna TURBO CENTURION T210M 1978 Pilot Operating Handbook page 159

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CESSNA
MODELT210M
SECTION 7
AIRPLANE
&
SYSTEMS DESCRIPTIONS
compressed. The pressurized air is then ducted through a fuel/ air control
unit and induction manifold to the cylinders.
EXHAUST SYSTEM
Exhaust gas from each cylinder passes through riser assemblies into
an exhaust manifold which discharges the gas into the turbine section of
the turbocharger. After the exhaust gas has passed through the turbine, it
is vented overboard through a tailpipe. A waste gate is incorporated into
the exhaust manifold, and controls the amount of exhaust gas to the turbine
by venting excess gas to the tailpipe through a bypass. A shroud, attached
to the left side of the exhaust manifold, forms a heating chamber for cabin
heater and windshield defrost air.
FUEL INJECTION SYSTEM
The engine is equipped with a fuel injection system. The system is
comprised of an engine-driven fuel pump, fuel/ air control unit, fuel
manifold, fuel flow indicator, and air-bleed type injector nozzles.
Fuel is delivered by the engine-driven fuel pump to the fuel/ air control
unit behind the engine. The fuel/ air control unit correctly proportions the
fuel flow to the induction air flow. After passing through the control unit,
induction air is delivered to the cylinders through intake manifold tubes,
and metered fuel is delivered to a fuel manifold. The fuel manifold, through
spring tension on a diaphragm and valve, evenly distributes the fuel to an
air-bleed type injector nozzle in the intake valve chamber of each cylinder.
A pressure line is also attached to the fuel manifold, and is connected to a
fuel flow indicator on the instrument panel.
COOLING SYSTEM
Ram air for engine cooling enters through two intake openings in the
front of the engine cowling. The cooling air is directed around the cylinders
and other areas of the engine by baffling, and is then exhausted through
cowl flaps on the lower aft edge of the cowling. The cowl flaps are
mechanically operated from the cabin by means of a cowl flap lever on the
right side of the control pedestal. The pedestal is labeled COWL FLAP,
OPEN, CLOSED. During takeoff and high power operation, the cowl flap
lever should be placed in the OPEN position for maximum cooling. This is
accomplished by moving the lever to the right to clear a detent, then
moving the lever up to the OPEN position. Anytime the lever is repositi-
oned, it must first be moved to the right. While in cruise flight, cowl flaps
should be adjusted to keep the cylinder head temperature at approximately
two-thirds of the normal operating range (green arc). During extended let-
downs, it may be necessary to completely close the cowl flaps by pushing
the cowl flap lever down to the CLOSED position.
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