Aircraft Performance

14 -13° 12 -9° 10 -5° 8 -1° 6 3° 4 7° 2 11° S.L. 15° 450 500 550 600 500 550 600 650 Range (nautical miles) (Includes distance to climb and descend) Figure 11-29. Best power mixture range. 11-25 )teef 000,1( TLA erusserP C° erutarepmeT dradnatS Po wer 65 % Po wer 55 % Po wer 65 % Po wer 55 % % % Po wer 75 Po wer 75 Associated conditions Mixture Leaned per section 4 Weight 2,300 lb. Wings No Fuel 48 gal usable Wheel Fairings installed Cruise Mid cruise setoN Range may be reduced by up to 7% if wheel fairings are not installed setoN CRUISE POWER SETTING 65% MAXIMUM CONTINUOUS POWER (OR FULL THROTTLE) 2,800 POUNDS ISA –20° (–36 °F) Standard day (ISA) ISA +20° (+36 °F) Fuel Fuel Fuel Engine Man. Engine Man. Engine Man. Press IOAT speed press flow per TAS IOAT speed press flow per TAS IOAT speed press flow per TAS ALT engine engine engine °F °C RPM "HG PSI GPH kts MPH °F °C RPM "HG PSI GPH kts MPH °F °C RPM "HG PSI GPH kts MPH S.L. 27 –3 2,450 20.7 6.6 11.5 147 169 63 17 2,450 21.2 6.6 11.5 150 173 99 37 2,450 21.8 6.6 11.5 153 176 2,000 19 –7 2,450 20.4 6.6 11.5 149 171 55 13 2,450 21.0 6.6 11.5 153 176 91 33 2,450 21.5 6.6 11.5 156 180 4,000 12 –11 2,450 20.1 6.6 11.5 152 175 48 9 2,450 20.7 6.6 11.5 156 180 84 29 2,450 21.3 6.6 11.5 159 183 6,000 5 –15 2,450 19.8 6.6 11.5 155 178 41 5 2,450 20.4 6.6 11.5 158 182 79 26 2,450 21.0 6.6 11.5 161 185 8,000 –2 –19 2,450 19.5 6.6 11.5 157 181 36 2 2,450 20.2 6.6 11.5 161 185 72 22 2,450 20.8 6.6 11.5 164 189 10,000 –8 –22 2,450 19.2 6.6 11.5 160 184 28 –2 2,450 19.9 6.6 11.5 163 188 64 18 2,450 20.3 6.5 11.4 166 191 12,000 –15 –26 2,450 18.8 6.4 11.3 162 186 21 –6 2,450 18.8 6.1 10.9 163 188 57 14 2,450 18.8 5.9 10.6 163 188 14,000 –22 –30 2,450 17.4 5.8 10.5 159 183 14 –10 2,450 17.4 5.6 10.1 160 184 50 10 2,450 17.4 5.4 9.8 160 184 16,000 –29 –34 2,450 16.1 5.3 9.7 156 180 7 –14 2,450 16.1 5.1 9.4 156 180 43 6 2,450 16.1 4.9 9.1 155 178 1. Full throttle manifold pressure settings are approximate. 2. Shaded area represents operation with full throttle. Figure 11-28. Cruise power setting. 45 minutes reserve at 55% power best economy mixture No reserve Add 0.6 NM for each degree Celsius above standard temperature and subtract 1 NM for each degree Celsius below standard temperature. setoN Sample Problem 9 65 percent, best power line. This is the solid line, that represents best economy. Draw a line straight down from OAT.........................................................................16 °C this intersection to the bottom of the graph. The TAS at 65 Pressure Altitude...............................................6,000 feet percent best power is 140 knots. However, it is necessary Power Setting................................65 percent, best power to subtract 8 knots from the speed since there are no wheel fairings. This note is listed under the title and conditions. Wheel Fairings..............................................Not installed The TAS is 132 knots. Begin by finding the correct OAT on the bottom left side of Crosswind and Headwind Component Chart the graph. Move up that line until it intersects the pressure Every aircraft is tested according to Federal Aviation altitude of 6,000 feet. Draw a line straight across to the Administration (FAA) regulations prior to certification. The aircraft is tested by a pilot with average piloting skills in 90° crosswinds with a velocity up to 0.2 V or two-tenths S0 of the aircraft’s stalling speed with power off, gear down, and flaps down. This means that if the stalling speed of the aircraft is 45 knots, it must be capable of landing in a 9-knot, 90° crosswind. The maximum demonstrated crosswind component is published in the AFM/POH. The crosswind and headwind component chart allows for figuring the headwind and crosswind component for any given wind direction and velocity. Sample Problem 10 Runway..........................................................................17 Wind........................................................140° at 25 knots Refer to Figure 11-31 to solve this problem. First, determine how many degrees difference there is between the runway and the wind direction. It is known that runway 17 means a direction of 170°; from that subtract the wind direction of 140°. This gives a 30° angular difference or wind angle. Next, locate the 30° mark and draw a line from there until it intersects the correct wind velocity of 25 knots. From