Cessna 208B - Engine Lubrication System

CESSNA SECTION 7
MODEL
208B (675 SHP) AIRPLANE AND SYSTEMS DESCRIPTION
ENGINE LUBRICATION SYSTEM
The lubrication system consists of a pressure system, a scavenge
svstem and a breather svstem. The main components of the lubrication
system ~nclude an integral oil tank at the back of the englne, an oil
pressure pump at the
botlom of the oil tank, an external double-element
scavenge pump located on the back of the accessory case, an internal
double-element scavenge pump located
ins~de the accessory gearbox.
an oil-to-fuel heater located on'the top rear of the
accessoj case, an
oil filter located internally on the right side of the oil tank, and an oil
cooler located on the right side of the nose cowl.
A large capacity oil
cooler is installed in modified early serial airplanes and all later serial
airplanes to increase the hot day outside air temperature limits for flight
operations. The large oil cooler has
25% more airflow area than a
standard cooler.
Oil is drawn from the bottom of the oil tank through a filter screen where
it passes through a pressure relief valve for regulation of oil pressure.
The pressure oil is then delivered from the main oil pump to the oil filter
where extraneous matter is removed from the oil and precluded from
further circulation. Pressure oil is then routed through passageways to
the engine bearings, reduction gears, accessory drives, torquemeter,
and propeller governor. Also, pressure oil is routed to the oil-to-fuel
heater where it then returns to the oil tank
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U.S. 7-55