Installation & Operation Manual
O-360 and IO-360 Series Engines
1 Chapter 3 • Aircraft / Engine
© March 2004 Superior Air Parts Inc. Integration Considerations
CHAPTER 3
Aircraft / Engine Integration Considerations
1. GENERAL
The following sections in this chapter include a
discussion of design practices to be considered
during the integration of a Superior Vantage
engine with an airframe and propeller. These
discussions should be used IN ADDITION TO
the applicable requirements of the FARs.
Superior requires that proper functioning of the
system designs outlined in this chapter be
proven prior to activation of the warranty.
Proper functioning of the installation design shall
be proven by technical data such as test data,
photographs, drawings and engineering
calculations. Superior Air Parts Engineering
Department will provide guidance regarding the
specifics of these requirements as appropriate to
the installation and on a case-by-case basis.
Throughout this chapter reference is made to
data contained in the Model Specification Data.
These documents are engine series specific and
are contained in Appendices of this manual.
Refer to the appropriate Model Specification
Data for your engine model when consulting this
data.
2. INDUCTION SYSTEM
The induction system design can significantly
effect both performance and longevity of an
aircraft engine installation. In addition to more
obvious issues such as air filtration, seemingly
insignificant design features can cause
restrictions or other airflow disturbances
resulting in flow loss or improper function of the
fuel metering system. Induction systems which
yield excessive intake air temperatures can
promote engine detonation.
A. General Induction System Design
It is important that the induction system of
naturally aspirated engines such as the Superior
Vantage Series be capable of supplying clean,
filtered, cool intake air to the engine at the
maximum required flowrate and with maximum
attainable pressure. The term “maximum
attainable pressure” as used here refers to an
air source that provides maximum intake air
pressure, (including ram air effects) while
minimizing restrictions and flow losses. A
reduction in flowrate or total pressure, or
increased temperature can cause power loss,
reduced service ceiling and increased possibility
of detonation during high power requirements.
Properly engineered intake systems for naturally
aspirated engines should result in total intake air
pressures that are greater than ambient air
pressure. For example, air pressure in the intake
system can be raised by
directing the face of the air pickup into the
relative wind of the aircraft. Further, by locating
the air pickup within the propeller diameter, ram
air effects can be increased. Care should be
taken to position the air pickup as far as possible
away from the propeller axis (but within the
“propeller envelope”) so as to take advantage of
the increased air velocities at the outer areas of
the prop. Care should also be given to prevent
“blanking” of the intake air pickup by the prop
blade. Increasing the size of the air pickup,
particularly in the direction perpendicular to the
blade axis, can help reduce this potential. Care
should also be given to designing an air pickup
that maintains maximum frontal area during
periods of high aircraft angle of attack.
Typically, maximum power is required during
flight conditions having high angle of attack and
reductions in airflow will restrict maximum power
capability.
The intake air system should be designed to
minimize pressure and flow losses. Sharp
elbows and abrupt duct expansions or
contractions all contribute to system losses.
Changes in duct sizing should be accompanied
by tapered transitions to minimize these losses.
Duct losses are a function of air velocity and can
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