FAA Aircraft Performance Test 1

(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?

A. 1,700-foot increase.

B. 1,700-foot decrease.

C. 1,300-foot decrease.

Correct! Wrong!

(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?

A. 178 MPH.

B. 181 MPH.

C. 183 MPH.

Correct! Wrong!

What effect does high density altitude have on aircraft performance?

A. It increases engine performance.

B. It reduces climb performance.

C. It increases takeoff performance.

Correct! Wrong!

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

A. Efficiency is increased due to less friction on the propeller blades.

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

C. Efficiency is reduced due to the increased force of the propeller in the thinner air.

Correct! Wrong!

In the less dense, or thinner, air the propeller cannot exert the same force as it does in more dense air. Answer A is incorrect because less friction of air on the rotating propeller blades is a very minor factor. Answer C is incorrect because the efficiency of the propeller is reduced in less dense air, since it is unable to exert as much force as it could in more dense air.

(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

A. 4,600 feet MSL.

B. 5,877 feet MSL.

C. 8,500 feet MSL.

Correct! Wrong!

(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?

A. 1,200-foot increase.

B. 1,400-foot increase.

C. 1,650-foot increase.

Correct! Wrong!

(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?

A. 1,000-foot increase.

B. 1,100-foot decrease.

C. 1,300-foot increase.

Correct! Wrong!

(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

A. 31.4 gallons.

B. 36.1 gallons.

C. 40.1 gallons.

Correct! Wrong!

If the outside air temperature (OAT) at a given altitude is warmer than standard, the density altitude is

A. equal to pressure altitude.

B. lower than pressure altitude.

C. higher than pressure altitude.

Correct! Wrong!

What is density altitude?

A. The height above the standard datum plane.

B. The pressure altitude corrected for non-standard temperature.

C. The altitude read directly from the altimeter.

Correct! Wrong!

Under which condition will pressure altitude be equal to true altitude?

A. When the atmospheric pressure is 29.92 inches Hg.

B. When standard atmospheric conditions exist.

C. When indicated altitude is equal to the pressure altitude.

Correct! Wrong!

(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?

A. 10.6 gallons per hour.

B. 11.2 gallons per hour.

C. 11.8 gallons per hour.

Correct! Wrong!

Under what condition is pressure altitude and density altitude the same value?

A. At sea level, when the temperature is 0 °F.

B. When the altimeter has no installation error.

C. At standard temperature.

Correct! Wrong!

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

A. Low temperature, low relative humidity, and low density altitude.

B. High temperature, low relative humidity, and low density altitude.

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

Correct! Wrong!

Which factor would tend to increase the density altitude at a given airport?

A. An increase in barometric pressure.

B. An increase in ambient temperature.

C. A decrease in relative humidity.

Correct! Wrong!

(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

A. 2,000 feet MSL.

B. 2,900 feet MSL.

C. 3,500 feet MSL.

Correct! Wrong!

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

A. 3,527 feet MSL.

B. 3,556 feet MSL.

C. 3,639 feet MSL.

Correct! Wrong!

(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.

A. 2,913 feet MSL.

B. 3,010 feet MSL.

C. 2,991 feet MSL.

Correct! Wrong!

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

A. 1,341 feet MSL.

B. 1,451 feet MSL.

C. 1,562 feet MSL.

Correct! Wrong!

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

A. It increases performance.

B. It decreases performance.

C. It has no effect on performance.

Correct! Wrong!

(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.

A. 19.8" Hg.

B. 20.8" Hg.

C. 21.0" Hg.

Correct! Wrong!

FAA Aircraft Performance Test 1

(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?

(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?

What effect does high density altitude have on aircraft performance?

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

(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

(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?

(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?

If the outside air temperature (OAT) at a given altitude is warmer than standard, the density altitude is

What is density altitude?

Under which condition will pressure altitude be equal to true altitude?

(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?

Under what condition is pressure altitude and density altitude the same value?

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

Which factor would tend to increase the density altitude at a given airport?

(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

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

(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.

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

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

(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.

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