CESSNA SECTION 5
MODEL 208B 867 SHP PERFORMANCE
GARMIN G1000
U.S.
FAA APPROVED
SAMPLE PROBLEM (Continued)
CRUISE
The cruising altitude should be selected based on a consideration of
trip length, winds aloft, and the airplane’s performance. A cruising
altitude and the expected wind enroute have been given for this sample
problem. However, the power setting selection for cruise must be
determined based on several considerations.
These include the cruise performance characteristics presented in the
Cruise Performance, Cruise Maximum Torque charts, Fuel and Time
Required, and the Range and Endurance Profile charts.
The Range Profile chart shows range at maximum cruise power and
also at maximum range power. For this sample problem, maximum
cruise power and 1900 RPM will be used.
The Cruise Performance chart for 12,000 feet pressure altitude is
entered using 10°C temperature. These values most nearly correspond
to the planned altitude and expected temperature conditions. The
torque setting for maximum cruise power is 1517 FT-LB torque at 1900
RPM which results in the following:
True Airspeed
173 Knots
Cruise Fuel Flow 364 PPH
208BPHCUS-00
5-7
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