Installation & Operation Manual
O-360 and IO-360 Series Engines
26 Chapter 3 • Aircraft / Engine
© March 2004 Superior Air Parts Inc. Integration Considerations
Note: The location of the center of gravity in Figure 3-7 is based from the crankcase
backplane and can be modified to describe the mounting gage point specific to a given
mount style as described in Figures 3-4 through 3-6 above.
Figure 3-7 • Limit and Ultimate Engine Forces
D. Engine Mount Vibration
The use of isolators in the design of the engine
mount reduces the magnitude of vibratory loads
and Superior has designed the Vantage Engine
for state of the art isolation systems. However,
no isolation system is perfect and some loads
are transmitted from the engine / propeller
system to the airframe. It is important during the
installation design to consider these loads and
ensure that natural frequencies of the airframe
do not match these forcing functions during
prolonged operation. Although these loads will
vary depending upon choices of mount style,
propeller and accessories Superior has
measured the transmitted vibratory loads for a
typical installation. Figures 3-8 and 3-9
illustrate forcing functions produced by the
engine on the engine on a typical engine mount
design. Data is presented for startup and
shutdown sequences in Figure 3-8 and steady
state power settings in Figure 3-9. Proper
installation design requires that testing be
performed to verify that vibratory loads are
acceptable for the specific airframe, isolator
style, engine, propeller and accessories.
Further, the stresses introduced to the engine
mount must be verified to assure proper function
and resistance to fatigue. This is separate from
the issue of propeller limitations based on strain
gauge testing of the engine crankshaft.
-10000
-8000
-6000
-4000
-2000
0
2000
4000
6000
8.00
8.50
9.00
9.50
10.00
10.50
11.00
11.50
12.00
Longitudinal C.G. Location (In)
V
e
rt
ical
F
o
rce
(L
b
f)
Limit
Ultimate
Ultimate
Limit
