Aircraft Performance

(Refer to figure 39.) 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

1,004 feet.

(Refer to figure 41.) Determine the approximate ground roll distance required for takeoff. OAT 100 °F Pressure altitude 2,000 ft Takeoff weight 2,750 lb Headwind component Calm

1,150 feet.

(Refer to figure 8.) What is the effect of a temperature increase from 30 to 50 °F on the density altitude if the pressure altitude remains at 3,000 feet MSL?

1,300-foot increase.

(Refer to figure 8.) Determine the pressure altitude at an airport that is 1,386 feet MSL with an altimeter setting of 29.97.

1,341 feet MSL.

(Refer to figure 38.) 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

1,400 feet.

Refer to figure 41.) 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

1,400 feet.

(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?

1,650-foot increase.

(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?

1,700-foot decrease.

(Refer to figure 41.) Determine the total distance required for takeoff to clear a 50-foot obstacle. OAT Std Pressure altitude 4,000 ft Takeoff weight 2,800 lb Headwind component Calm

1,750 feet.

(Refer to figure 38.) Determine the approximate total distance required to land over a 50-foot obstacle. OAT 90 °F Pressure altitude 4,000 ft Weight 2,800 lb Headwind component 10 kts

1,775 feet.

(Refer to figure 36.) What fuel flow should a pilot expect at 11,000 feet on a standard day with 65 percent maximum continuous power?

11.2 gallons per hour.

(Refer to figure 36.) 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?

183 MPH.

(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.

2,991 feet MSL.

(Refer to figure 36.) 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.

21.0 inches Hg.

(Refer to figure 37.) What is the headwind component for a landing on Runway 18 if the tower reports the wind as 220° at 30 knots?

23 knots.

(Refer to figure 37.) What is the maximum wind velocity for a 30° crosswind if the maximum crosswind component for the airplane is 12 knots?

24 knots.

(Refer to figure 8.) Determine the pressure altitude at an airport that is 3,563 feet MSL with an altimeter setting of 29.96.

3,527 feet MSL.

(Refer to figure 37.) Determine the maximum wind velocity for a 45° crosswind if the maximum crosswind component for the airplane is 25 knots.v

35 knots.

Refer to figure 37.) Determine the maximum wind velocity for a 45° crosswind if the maximum crosswind component for the airplane is 25 knots.

35 knots.

(Refer to figure 39.) Determine the approximate landing ground roll distance. Pressure altitude 1,250 ft Headwind 8 kts Temperature Std

366 feet.

Refer to figure 39.) Determine the approximate landing ground roll distance. Pressure altitude Sea level Headwind 4 kts Temperature Std

401 feet.

(Refer to figure 39.) Determine the approximate landing ground roll distance. Pressure altitude 5,000 ft Headwind Calm Temperature 101 °F

545 feet.

(Refer to figure 41.) Determine the approximate ground roll distance required for takeoff. OAT 90 °F Pressure altitude 2,000 ft Takeoff weight 2,500 lb Headwind component 20 kts

650 feet.

(Refer to figure 36.) 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 inches Hg Wind Calm

70.1 gallons.

(Refer to figure 26.) Estimate the time en route from Addison (area 2) to Dallas Executive (area 3). The wind is from 300° at 15 knots, the true airspeed is 120 knots, and the magnetic variation is 7° east.

8 minutes

Refer to figure 26.) Estimate the time en route from Addison (area 2) to Dallas Executive (area 3). The wind is from 300° at 15 knots, the true airspeed is 120 knots, and the magnetic variation is 7° east.

8 minutes.

(Refer to figure 8.) Determine the density altitude for these conditions: Altimeter setting 29.25 Runway temperature +81 °F Airport elevation 5,250 ft MSL

8,500 feet MSL.

(Refer to figure 39.) Determine the total distance required to land over a 50-foot obstacle. Pressure altitude 3,750 ft Headwind 12 kts Temperature Std

816 feet.

(Refer to figure 39.) Determine the total distance required to land over a 50-foot obstacle. Pressure altitude 3,750 ft Headwind 12 kts Temperature Std

816 feet.

(Refer to figure 39.) 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

956 feet.

(Refer to figure 39.) 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

956 feet.

Ground effect is most likely to result in which problem?

Becoming airborne before reaching recommended takeoff speed.

What effect does high density altitude, as compared to low density altitude, have on propeller efficiency and why?

Efficiency is reduced because the propeller exerts less force at high density altitudes than at low density altitudes.

Which combination of atmospheric conditions will reduce aircraft takeoff and climb performance?

High temperature, high relative humidity, and high density altitude.

What must a pilot be aware of as a result of ground effect?

Induced drag decreases; therefore, any excess speed at the point of flare may cause considerable floating.

What effect, if any, does high humidity have on aircraft performance?

It decreases performance.

What effect does high density altitude have on aircraft performance?

It reduces climb performance.

(Refer to figure 37.) 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?

Runway 14

(Refer to figure 37.) 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?

Runway 32.

What is ground effect?

The result of the interference of the surface of the Earth with the airflow patterns about an airplane.

Floating caused by the phenomenon of ground effect will be most realized during an approach to land when at

less than the length of the wingspan above the surface.