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Engine Description
2-2.1. Crankcase Breather Ventilation
The aircraft manufacturer is required to provide a means to vent crankcase pressure
overboard. The crankcase breather line must not have low points or "sumps" as to prevent
the accumulation of water and ice. The exit point should be designed as to not create a
suction on the line. A fitting for a 0.625 inch ID hose is provided in the crankcase above
the fuel pump mounting pad on the 1-3 side of the crankcase.
2-2.2. Engine Cooling
Inter-cylinder baffles are provided as a part of the engine design. The aircraft
manufacturer is responsible for additional baffling to provide adequate engine and
accessory cooling during all aircraft maneuvers and engine power settings. The aircraft
manufacturer must demonstrate adequate engine cooling so that the maximum engine and
component temperatures are not exceeded and that recommended temperatures are
maintained during any flight condition.
If cooling problems exist, CM recommends measurements be taken with independent
pressure rakes on the cylinders and oil cooler.
2-2.3. Induction System
The aircraft manufacturer is required to provide the induction system interface between
the engine intake at the throttle and control assembly and the aircraft air filter and the
alternate air system in compliance with the applicable regulations.
The engine induction air system consists of individual tubes connected between the
cylinder intake ports and a common manifold above the carburetor.
2-2.3.1. Mass Flow
Refer to Section 2-4.2, "Induction" in "Engine Specifications" for details.
2-2.3.2. Air Filtration
CAUTION: Pressure drop across the air filter will affect engine
performance.
Two optional air intake systems are available, including air filters, or the aircraft
manufacturer may provide their own compliant interface. Operation under severe dust
conditions will require additional filtration capacity and more frequent filter change
intervals to ensure satisfactory engine life.
2-2.3.3. Alternate Air System
A suitable alternate air system must be incorporated in the engine installation in
accordance with applicable aircraft regulations. Alternate air systems which extract
induction air from a heated area such as the engine compartment will cause engine
horsepower to decrease approximately 1% for each 10°F increase in manifold inlet air
temperature. The aircraft manufacturer must ensure aircraft performance remains within
the applicable Title 14 CFR regulations during alternate air door operation. Alternate air
systems tend to accumulate dust and debris. The alternate air system design should
minimize any accumulation of dust or debris and provide a tight seal when not open to
avoid engine contamination during normal operation.
2-4
O-200-D & X Series Engine Installation and Operation Manual
3 January 2017
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