Installation & Operation Manual
O-360 and IO-360 Series Engines
25 Chapter 3 • Aircraft / Engine
© March 2004 Superior Air Parts Inc. Integration Considerations
The installation of an engine per 14CFR Part 23
(FAR 23) includes the use of several Factors of
Safety. When performing the engine installation
design for a Superior Vantage Engine, the
weight and location for the center of gravity of
the engine, propeller and all engine mounted
accessories must be considered together with
the appropriate Factors of Safety from FAR 23
for the flight category desired. The resulting
positive and negative maneuvering loads for the
installation must be within the limits shown in
Table 3-3. For convenience, Figure 3-7
illustrates the above load limits (Table 3-3) in
terms of vertical forces as a function of the
longitudinal center of gravity. The term “engine
torque” in Table 3-3 relates to the average
output torque of the engine at maximum rated
speed plus design factors as required by 14CFR
Part 33. When performing the engine
installation design for a Superior
Vantage Engine it is required that the average
output torque at maximum rated speed and
power be below these values. The limit load
engine torque of 1634 Ft-Lb
f
corresponds to a
power output of approximately 210 Hp at 2700
RPM including design factors.
Note: Positive maneuvering moment values result in a downward force
on the engine and negative values result in an upward force.
Table 3-3 • Limit and Ultimate Engine Mount Loads
Load Limit
Positive
Negative
Maneuvering Moment
-4361 Ft-Lb
f
2181 Ft-Lb
f
Limit
Load
Engine Torque
1634 Ft-Lb
f
1634 Ft-Lb
f
Maneuvering Moment
-6542 Ft-Lb
f
3271 Ft-Lb
f
Ultimate
Load
Engine Torque
2451 Ft-Lb
f
2451 Ft-Lb
f