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SECTION 5 CESSNA PERFORMANCE MODEL 208B G1000 SAMPLE PROBLEM The following sample flight problem utilizes information from the various charts to determine the predicted performance data for a typical flight of an airplane equipped with a cargo pod. A similar calculation can be made for an airplane without a cargo pod using charts identified as appropriate for this configuration. The following information is known: AIRPLANE CONFIGURATION (CARGO POD INSTALLED) Takeoff weight 8600 Pounds Usable fuel 2224 Pounds TAKEOFF CONDITIONS Field pressure altitude 3500 Feet Temperature 16°C (standard + 8°C) Wind component along runway 12 Knot Headwind Field length 4000 Feet CRUISE CONDITIONS Total distance 650 Nautical Miles Pressure altitude 11,500 Feet Temperature 8°C Expected wind enroute 10 Knot Headwind LANDING CONDITIONS Field pressure altitude 1500 Feet Temperature 25°C Field length 3000 Feet 5-4 U.S. FAA APPROVED 208BPHBUS-00
CESSNA SECTION 5 MODEL 208B G1000 PERFORMANCE TAKEOFF The Takeoff Distance chart shows distances that are based on the short field technique. Conservative distances can be established by reading the chart at the next higher value of weight, altitude and temperature. For example, in this particular sample problem, the takeoff distance information presented for a weight of 8750 pounds, pressure altitude of 4000 feet and a temperature of 20°C should be used and results in the following: Ground roll 1875 Feet Total distance to clear a 50-foot obstacle 3295 Feet These distances are well within the available takeoff field length. However, a correction for the effect of wind may be made based on Note 2 of the takeoff chart. The correction for a 12 knot headwind is: 12 Knots 11 Knots X 10% = 11% Decrease This results in the following distances, corrected for wind: Ground roll, zero wind 1875 Feet Decrease in ground roll (1875 feet X 11%) -206 Feet Corrected ground roll 1669 Feet Total distance to clear a 50-foot obstacle, zero wind 3295 Feet Decrease in total distance (3295 feet X 11%) -362 Feet Corrected total distance to clear a 50-foot obstacle 2933 Feet The Maximum Engine Torque For Takeoff chart should be consulted for takeoff power setting. For the above ambient conditions, the power setting is: Takeoff torque 1865 Ft-Lbs The Maximum Engine Torque For Climb chart should be consulted for climb power setting from field elevation to cruise altitude. For the above ambient conditions, the power setting is: Field Elevation Maximum Climb Torque 1740 Ft-lbs Cruise Altitude Maximum Climb Torque 1360 Ft-lbs FAA APPROVED 208BPHBUS-00 U.S. 5-5
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CESSNA INTRODUCTION MODEL 208B G100
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CESSNA SECTION 1 MODEL 208B G1000 G
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CESSNA SECTION 2 MODEL 208B G1000 L
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SECTION 3 CESSNA EMERGENCY PROCEDUR
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SECTION 3 CESSNA ABNORMAL PROCEDURE
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CESSNA SECTION 3 MODEL 208B G1000 A
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CESSNA SECTION 4 MODEL 208B G1000 N
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CESSNA SECTION 5 MODEL 208B G1000 P
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CESSNA SECTION 6 MODEL 208B G1000 W
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SECTION 7 CESSNA AIRPLANE AND SYSTE
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CESSNA SECTION 8 MODEL 208B G1000 H
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