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Aircraft Performance
- 1. What effect does high density altitude, as compared to low density altitude, have on propeller efficiency and why?
- 2. What is density altitude?
- 3. If the outside air temperature (OAT) at a given altitude is warmer than standard, the density altitude is
- 4. Which combination of atmospheric conditions will reduce aircraft takeoff and climb performance?
- 5. What effect does high density altitude have on aircraft performance?
- 6. (Refer to Figure 8.) What is the effect of a temperature increase from 25 to 50 °F on the density altitude if the pressure altitude remains at 5,000 feet?
- 7. (Refer to Figure 8.) Determine the pressure altitude with an indicated altitude of 1,380 feet MSL with an altimeter setting of 28.22 at standard temperature.
- 8. (Refer to Figure 8.) Determine the density altitude for these conditions: Altimeter setting: 29.25. Runway temperatur: +81 °F. Airport elevatio: 5,250 ft MSL
- 9. (Refer to Figure 8.) Determine the pressure altitude at an airport that is 3,563 feet MSL with an altimeter setting of 29.96.
- 10. (Refer to Figure 8.) What is the effect of a temperature increase from 35 to 50 °F on the density altitude if the pressure altitude remains at 3,000 feet MSL?
- 11. (Refer to Figure 8.) Determine the pressure altitude at an airport that is 1,386 feet MSL with an altimeter setting of 29.97.
- 12. (Refer to Figure 8.) Determine the density altitude for these conditions: Altimeter setting: 30.35. Runway temperature: +25 °F. Airport elevation: 3,894 ft MSL
- 13. (Refer to Figure 8.) What is the effect of a temperature decrease and a pressure altitude increase on the density altitude from 90 °F and 1,250 feet pressure altitude to 55 °F and 1,750 feet pressure altitude?
- 14. What effect, if any, does high humidity have on aircraft performance?
- 15. Under which condition will pressure altitude be equal to true altitude?
- 16. Under what condition is pressure altitude and density altitude the same value?
- 17. Which factor would tend to increase the density altitude at a given airport?
- 18. (Refer to Figure 35.) Approximately what true airspeed should a pilot expect with 65 percent maximum continuous power at 9,500 feet with a temperature of 36 °F below standard?
- 19. (Refer to Figure 35.) What is the expected fuel consumption for a 1,000-nautical mile flight under the following conditions? Pressure altitude: 8,000 ft. Temperature: 22 °C. Manifold pressure: 20.8. HgWind: Calm
- 20. (Refer to Figure 35.) What is the expected fuel consumption for a 500-nautical mile flight under the following conditions? Pressure altitude: 4,000 ft. Temperature: + 29 °C. Manifold pressure: 21.3. Hg. Wind: Calm
- 21. (Refer to Figure 35.) What fuel flow should a pilot expect at 11,000 feet on a standard day with 65 percent maximum continuous power?
- 22. (Refer to Figure 35.) Determine the approximate manifold pressure setting with 2,450 RPM to achieve 65 percent maximum continuous power at 6,500 feet with a temperature of 36 °F higher than standard.
- 23. (Refer to Figure 36.) What is the headwind component for a landing on Runway 18 if the tower reports the wind as 220° at 30 knots?
- 24. (Refer to Figure 36.) Determine the maximum wind velocity for a 45° crosswind if the maximum crosswind component for the airplane is 25 knots.
- 25. (Refer to Figure 36.) What is the maximum wind velocity for a 30° crosswind if the maximum crosswind component for the airplane is 12 knots?
- 26. (Refer to Figure 36.) With a reported wind of north at 20 knots, which runway (6, 29, or 32) is acceptable for use for an airplane with a 13-knot maximum crosswind component?
- 27. (Refer to Figure 36.) With a reported wind of south at 20 knots, which runway (10, 14, or 24) is appropriate for an airplane with a 13-knot maximum crosswind component?
- 28. (Refer to Figure 36.) What is the crosswind component for a landing on Runway 18 if the tower reports the wind as 220° at 30 knots?
- 29. (Refer to Figure 37.) Determine the total distance required to land. OAT: 32 °F. Pressure altitude: 8,000 ft. Weight: 2,600 lb. Headwind component: 20 kts. Obstacle: 50 ft
- 30. (Refer to Figure 37.) Determine the total distance required to land. OAT: Std. Pressure altitude: 10,000 ft. Weight: 2,400 lbs. Wind component: Calm. Obstacle: 50 ft
- 31. (Refer to Figure 37.) Determine the total distance required to land. OAT: 90 °F. Pressure altitude: 3,000 ft. Weight: 2,900 lbs. Headwind component: 10 kts. Obstacle: 50 ft
- 32. (Refer to Figure 37.) Determine the approximate total distance required to land over a 50-foot obstacle. OAT: 90 °F.Pressure altitude: 4,000 ft. Weight: 2,800 lbs. Headwind component: 10 kts
- 33. (Refer to Figure 38.) Determine the approximate landing ground roll distance. Pressure altitude: Sea level. Headwind: 4 kts. Temperature: Std
- 34. (Refer to Figure 38.) Determine the total distance required to land over a 50-foot obstacle. Pressure altitude: 7,500 ft. Headwind: 8 kts. Temperature: 32 °F. Runway: Hard surface
- 35. (Refer to Figure 38.) Determine the total distance required to land over a 50-foot obstacle. Pressure altitude: 5,000 ft. Headwind: 8 kts. Temperature: 41 °F. Runway: Hard surface
- 36. (Refer to Figure 38.) Determine the approximate landing ground roll distance. Pressure altitude: 5,000 ft. Headwind: Calm. Temperature: 101 °F
- 37. (Refer to Figure 38.) Determine the total distance required to land over a 50-foot obstacle. Pressure altitude: 3,750 ft. Headwind: 12 kts. Temperature: Std
- 38. (Refer to Figure 38.) Determine the approximate landing ground roll distance. Pressure altitude: 1,250 ft. Headwind: 8 kts. Temperature: Std
- 39. (Refer to Figure 40.) Determine the total distance required for takeoff to clear a 50-foot obstacle. OAT: StdPressure altitude: 4,000 ft. Takeoff weight: 2,800 lb. Headwind component: Calm
- 40. (Refer to Figure 40.) Determine the total distance required for takeoff to clear a 50-foot obstacle. OAT: Std. Pressure altitude: Sea level. Takeoff weight: 2,700 lb. Headwind component: Calm
- 41. (Refer to Figure 40.) Determine the approximate ground roll distance required for takeoff. OAT: 38 °C. Pressure altitude: 2,000 ft. Takeoff weight: 2,750 lb. Headwind component: Calm
- 42. (Refer to Figure 40.) Determine the approximate ground roll distance required for takeoff. OAT: 32 °C. Pressure altitude: 2,000 ft. Takeoff weight: 2,500 lb. Headwind component: 20 kts
- 43. A pilot and two passengers landed on a 2,100 foot east-west gravel strip with an elevation of 1,800 feet. The temperature is warmer than expected and after computing the density altitude it is determined the takeoff distance over a 50 foot obstacle is 1,980 feet. The airplane is 75 pounds under gross weight. What would be the best choice?
- 44. (Refer to Figure 35.) Approximately what true airspeed should a pilot expect with full throttle at 10,500 feet with a temperature of 36 °F above standard?