Aircraft Performance

Crosswind component Figure 10-31. Crosswind component chart. 11-26 tnenopmoc dniwdaeH 2 0,000 % % % 18,0 1 0 6 0 , 1 0 4 0 1 , 0 0 2 0 ,0 0 00 Pressure ALT (feet) Po wer 55 Po wer 65 Po wer 75 Weight Associa 3 t ,6 e 0 d 0 c l o b n . d gr it o i s o s n s weight 10,000 Flaps Up 8,000 Best power Mixture leaned to 100° 6,000 Best economy r M ic i h xt u o r f e p l e e a a k n e E d G t T o peak EGT 4,000 1,650° Max allowable EGT 2,000 Sea level Wheel Fairings installed –40° –30° –20° –10° 0° 10° 20° 30° 40° 100 120 140 160 180 200 Outside air temperature (°C) True airspeed (knots) Figure 11-30. Cruise performance graph. 0° 10° 70 20° 30° 60 50 Wind velocity 40° 50° 40 60° 30 70° 20 80° 10 90° 0 10 20 30 40 50 60 70 setoN Subtract 8 knots if wheel fairings are not installed. S tan d ard tem p eratu re p m at 3 6 I N m . M a . P t . 3 – 6 2 I N - b . l a M d . e P . p – r o 3 p - bla d e pr o p B B e e s s t t p e o co w n e o r my 2, 5 7 5 r 2, 70 0 r p there, draw a line straight down and a line straight across. usual, read the associated conditions and notes in order to The headwind component is 22 knots and the crosswind ascertain the basis of the chart information. Remember, when component is 13 knots. This information is important when calculating landing distance that the landing weight is not the taking off and landing so that, first of all, the appropriate same as the takeoff weight. The weight must be recalculated runway can be picked if more than one exists at a particular to compensate for the fuel that was used during the flight. airport, but also so that the aircraft is not pushed beyond its tested limits. Sample Problem 11 Pressure Altitude...............................................1,250 feet Landing Charts Temperature.........................................................Standard Landing performance is affected by variables similar to those affecting takeoff performance. It is necessary to compensate Refer to Figure 10-32. This example makes use of a landing for differences in density altitude, weight of the airplane, and distance table. Notice that the altitude of 1,250 feet is not headwinds. Like takeoff performance charts, landing distance on this table. It is, therefore, necessary to interpolate to find information is available as normal landing information, the correct landing distance. The pressure altitude of 1,250 as well as landing distance over a 50 foot obstacle. As is halfway between sea level and 2,500 feet. First, find the column for sea level and the column for 2,500 feet. Take the total distance of 1,075 for sea level and the total distance of 1,135 for 2,500 and add them together. Divide the total by two to obtain the distance for 1,250 feet. The distance is 1,105 feet total landing distance to clear a 50 foot obstacle. Repeat this process to obtain the ground roll distance for the pressure altitude. The ground roll should be 457.5 feet. Sample Problem 12 OAT.......................................................................... 57 °F Pressure Altitude.............................................. 4,000 feet Landing Weight...........................................2,400 pounds Headwind.............................................................. 6 knots Obstacle Height..................................................... 50 feet Using the given conditions and Figure 11-33, determine the landing distance for the aircraft. This graph is an example of