Performance Charts & Graphs Quiz PPL

(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?

1,200-foot increase.

1,400-foot increase.

1,650-foot increase.

(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.

2,913 feet MSL.

3,010 feet MSL.

2,991 feet MSL.

(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

4,600 feet MSL.

5,877 feet MSL.

8,500 feet 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.

3,527 feet MSL.

3,556 feet MSL.

3,639 feet MSL.

(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.

1,451 feet MSL.

1,562 feet MSL.

(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

2,000 feet MSL.

2,900 feet MSL.

3,500 feet MSL.

(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 increase.

1,700-foot decrease.

1,300-foot decrease.

(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?

178 MPH.

181 MPH.

183 MPH.

(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" Hg

Wind........................................Calm

60.2 gallons.

70.1 gallons.

73.2 gallons.

(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

31.4 gallons.

36.1 gallons.

40.1 gallons.

(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?

10.6 gallons per hour.

11.2 gallons per hour.

11.8 gallons per hour.

(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.

19.8" Hg.

20.8" Hg.

21.0" Hg.

(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?

19 knots.

23 knots.

26 knots.

(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 knots.

29 knots.

35 knots.

(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?

16 knots.

20 knots.

24 knots.

(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?

Runway 6.

Runway 29.

Runway 32.

(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?

Runway 10.

Runway 14.

Runway 24.

(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?

19 knots.

23 knots.

30 knots.

(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

850 feet.

1,400 feet.

1,750 feet.

(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

1,925 feet.

750 feet.

1,450 feet.

(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

1,450 feet.

1,550 feet.

1,725 feet.

(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

1,525 feet.

1,950 feet.

1,775 feet.

(Refer to Figure 38.) Determine the approximate landing ground roll distance.

Pressure altitude.................Sea level

Headwind..............................4 kts

Temperature.............................Std

356 feet.

401 feet.

490 feet.

(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

1,205 feet.

1,004 feet.

1,506 feet.

(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

837 feet.

956 feet.

1,076 feet.

(Refer to Figure 38.) Determine the approximate landing ground roll distance.

Pressure altitude......................5,000 ft

Headwind...................................Calm

Temperature..............................101 °F

445 feet.

495 feet.

545 feet.

(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

816 feet.

794 feet.

836 feet.

(Refer to Figure 38.) Determine the approximate landing ground roll distance.

Pressure altitude.........................1,250 ft

Headwind.....................................8 kts

Temperature....................................Std

275 feet.

366 feet.

470 feet.

(Refer to Figure 40.) 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

1,500 feet.

1,750 feet.

2,000 feet.

(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

1,000 feet.

1,400 feet.

1,700 feet.

(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

1,150 feet.

1,300 feet.

1,800 feet.

(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

650 feet.

850 feet.

1,000 feet.

(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?

190 KTS.

159 KTS.

165 KTS.

(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?

1,000-foot increase.

1,100-foot decrease.

1,300-foot increase.