Challenge Questions PPL Sec 3.
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Challenge Questions PPL Sec 3.
uestion: 3290 Subject Code: H317
Which combination of atmospheric conditions will reduce aircraft takeoff and climb performance?
A) High temperature, high relative humidity, and high density altitude.
B) High temperature, low relative humidity, and low density altitude.
C) Low temperature, low relative humidity, and low density altitude.
Question: 3291 Subject Code: H317
What effect does high density altitude have on aircraft performance?
A) It reduces climb performance.
B) It increases takeoff performance.
C) It increases engine performance.
Question: 3292 Subject Code: H317
(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) 1,400foot increase.
B) 1,200foot increase.
C) 1,650foot increase.
Question: 3293 Subject Code: H317
(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) 3,010 feet MSL.
B) 2,991 feet MSL.
C) 2,913 feet MSL.
Question: 3294 Subject Code: H317
(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) 5,877 feet MSL.
B) 4,600 feet MSL.
C) 8,500 feet MSL.
Question: 3295 Subject Code: H317
(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) 3,556 feet MSL.
B) 3,639 feet MSL.
C) 3,527 feet MSL.
Question: 3296 Subject Code: H317
(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?
A) 900foot increase.
B) 1,300foot increase.
C) 1,100foot decrease.
Question: 3297 Subject Code: H317
(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) 1,562 feet MSL.
B) 1,451 feet MSL.
C) 1,341 feet MSL.
Question: 3298 Subject Code: H317
(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) 3,500 feet MSL.
B) 2,000 feet MSL.
C) 2,900 feet MSL.
Question: 3299 Subject Code: H317
(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) 1,700foot increase.
B) 1300foot decrease.
C) 1,700foot decrease.
Question: 3300 Subject Code: H317
What effect, if any, does high humidity have on aircraft performance?
A) It decreases performance.
B) It increases performance.
C) It has no effect on performance.
Question: 3678 Subject Code: H317
(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?
A) 183 MPH.
B) 178 MPH.
C) 181 MPH.
Question: 3679 Subject Code: H317
(Refer to figure 36.) What is the expected fuel consumption for a 1,000nautical mile flight under the following conditions?
Pressure altitude.... 8,000 ft
Temperature.......... 22 °C
Manifold pressure.... 20.8" Hg
Wind................. Calm
A) 73.2 gallons.
B) 60.2 gallons.
C) 70.1 gallons.
Question: 3680 Subject Code: H317
(Refer to figure 36.) What is the expected fuel consumption for a 500nautical mile flight under the following conditions?
Pressure altitude.... 4,000 ft
Temperature.......... +29 °C
Manifold pressure.... 21.3" Hg
Wind................. Calm
A) 40.1 gallons.
B) 36.1 gallons.
C) 31.4 gallons.
Question: 3681 Subject Code: H317
(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?
A) 10.6 gallons per hour.
B) 11.2 gallons per hour.
C) 11.8 gallons per hour.
Question: 3682 Subject Code: H317
(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.
A) 21.0" Hg.
B) 20.8" Hg.
C) 19.8" Hg.
Question: 3683 Subject Code: H317
(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?
A) 26 knots.
B) 19 knots.
C) 23 knots.
Question: 3684 Subject Code: H317
(Refer to figure 37.) Determine the maximum wind velocity for a 45° crosswind if the maximum crosswind component for the airplane is 25 knots.
A) 25 knots.
B) 29 knots.
C) 35 knots.
Question: 3685 Subject Code: H317
(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?
A) 16 knots.
B) 20 knots.
C) 24 knots.
Question: 3686 Subject Code: H317
(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 13knot maximum crosswind component?
A) Runway 6.
B) Runway 32.
C) Runway 29.
Question: 3687 Subject Code: H317
(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 13knot maximum crosswind component?
A) Runway 14.
B) Runway 24.
C) Runway 10.
Question: 3688 Subject Code: H317
(Refer to figure 37.) What is the crosswind component for a landing on Runway 18 if the tower reports the wind as 220° at 30 knots?
A) 19 knots.
B) 30 knots.
C) 23 knots.
Question: 3689 Subject Code: H317
(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
A) 1,400 feet.
B) 1,750 feet.
C) 850 feet.
Question: 3690 Subject Code: H317
(Refer to figure 38.) Determine the total distance required to land.
OAT.................. Std
Pressure altitude.... 2,000 ft
Weight............... 2,300 lb
Wind component....... Calm
Obstacle............. 25 ft
A) 850 feet.
B) 1,450 feet.
C) 1,150 feet.
Question: 3691 Subject Code: H317
(Refer to figure 38.) Determine the total distance required to land.
OAT.................. 90 °F
Pressure altitude.... 3,000 ft
Weight............... 2,900 lb
Headwind component... 10 kts
Obstacle............. 50 ft
A) 1,725 feet.
B) 1,550 feet.
C) 1,450 feet.
Question: 3692 Subject Code: H317
(Refer to figure 38.) Determine the approximate total distance required to land over a 50foot obstacle.
OAT.................. 90 °F
Pressure altitude.... 4,000 ft
Weight............... 2,800 lb
Headwind component... 10 kts
A) 1,525 feet.
B) 1,950 feet.
C) 1,775 feet.
Question: 3693 Subject Code: H317
(Refer to figure 39.) Determine the approximate landing ground roll distance.
Pressure altitude... Sea level
Headwind............ 4 kts
Temperature......... Std
A) 490 feet.
B) 401 feet.
C) 356 feet.
Question: 3694 Subject Code: H317
(Refer to figure 39.) Determine the total distance required to land over a 50foot obstacle.
Pressure altitude.... 7,500 ft
Headwind............. 8 kts
Temperature.......... 32°F
Runway............... Hard surface
A) 1,506 feet.
B) 1,004 feet.
C) 1,205 feet.
Question: 3695 Subject Code: H317
(Refer to figure 39.) Determine the total distance required to land over a 50foot obstacle.
Pressure altitude.... 5,000 ft
Headwind............. 8 kts
Temperature.......... 41 °F
Runway............... Hard surface
A) 1,076 feet.
B) 837 feet.
C) 956 feet.
Question: 3696 Subject Code: H317
(Refer to figure 39.) Determine the approximate landing ground roll distance.
Pressure altitude... 5,000 ft
Headwind............ Calm
Temperature......... 101 °F
A) 495 feet.
B) 545 feet.
C) 445 feet.
Question: 3697 Subject Code: H317
(Refer to figure 39.) Determine the total distance required to land over a 50foot obstacle.
Pressure altitude.... 3,750 ft
Headwind............. 12 kts
Temperature.......... Std
A) 794 feet.
B) 836 feet.
C) 816 feet.
Question: 3698 Subject Code: H317
(Refer to figure 39.) Determine the approximate landing ground roll distance.
Pressure altitude.... 1,250 ft
Headwind............. 8 kts
Temperature.......... Std
A) 275 feet.
B) 470 feet.
C) 366 feet.
Question: 3705 Subject Code: H317
(Refer to figure 41.) Determine the total distance required for takeoff to clear a 50foot obstacle.
OAT.................. Std
Pressure altitude.... 4,000 ft
Takeoff weight....... 2,800 lb
Headwind component... Calm
A) 2,000 feet.
B) 1,500 feet.
C) 1,750 feet.
Question: 3706 Subject Code: H317
(Refer to figure 41.) Determine the total distance required for takeoff to clear a 50foot obstacle.
OAT................... Std
Pressure altitude..... Sea level
Takeoff weight........ 2,700 lb
Headwind component.... Calm
A) 1,700 feet.
B) 1,400 feet.
C) 1,000 feet.
Question: 3707 Subject Code: H317
(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
A) 1,800 feet.
B) 1,300 feet.
C) 1,150 feet.
Question: 3708 Subject Code: H317
(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
A) 850 feet.
B) 650 feet.
C) 1,000 feet.
Which combination of atmospheric conditions will reduce aircraft takeoff and climb performance?
A) High temperature, high relative humidity, and high density altitude.
B) High temperature, low relative humidity, and low density altitude.
C) Low temperature, low relative humidity, and low density altitude.
Question: 3291 Subject Code: H317
What effect does high density altitude have on aircraft performance?
A) It reduces climb performance.
B) It increases takeoff performance.
C) It increases engine performance.
Question: 3292 Subject Code: H317
(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) 1,400foot increase.
B) 1,200foot increase.
C) 1,650foot increase.
Question: 3293 Subject Code: H317
(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) 3,010 feet MSL.
B) 2,991 feet MSL.
C) 2,913 feet MSL.
Question: 3294 Subject Code: H317
(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) 5,877 feet MSL.
B) 4,600 feet MSL.
C) 8,500 feet MSL.
Question: 3295 Subject Code: H317
(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) 3,556 feet MSL.
B) 3,639 feet MSL.
C) 3,527 feet MSL.
Question: 3296 Subject Code: H317
(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?
A) 900foot increase.
B) 1,300foot increase.
C) 1,100foot decrease.
Question: 3297 Subject Code: H317
(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) 1,562 feet MSL.
B) 1,451 feet MSL.
C) 1,341 feet MSL.
Question: 3298 Subject Code: H317
(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) 3,500 feet MSL.
B) 2,000 feet MSL.
C) 2,900 feet MSL.
Question: 3299 Subject Code: H317
(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) 1,700foot increase.
B) 1300foot decrease.
C) 1,700foot decrease.
Question: 3300 Subject Code: H317
What effect, if any, does high humidity have on aircraft performance?
A) It decreases performance.
B) It increases performance.
C) It has no effect on performance.
Question: 3678 Subject Code: H317
(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?
A) 183 MPH.
B) 178 MPH.
C) 181 MPH.
Question: 3679 Subject Code: H317
(Refer to figure 36.) What is the expected fuel consumption for a 1,000nautical mile flight under the following conditions?
Pressure altitude.... 8,000 ft
Temperature.......... 22 °C
Manifold pressure.... 20.8" Hg
Wind................. Calm
A) 73.2 gallons.
B) 60.2 gallons.
C) 70.1 gallons.
Question: 3680 Subject Code: H317
(Refer to figure 36.) What is the expected fuel consumption for a 500nautical mile flight under the following conditions?
Pressure altitude.... 4,000 ft
Temperature.......... +29 °C
Manifold pressure.... 21.3" Hg
Wind................. Calm
A) 40.1 gallons.
B) 36.1 gallons.
C) 31.4 gallons.
Question: 3681 Subject Code: H317
(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?
A) 10.6 gallons per hour.
B) 11.2 gallons per hour.
C) 11.8 gallons per hour.
Question: 3682 Subject Code: H317
(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.
A) 21.0" Hg.
B) 20.8" Hg.
C) 19.8" Hg.
Question: 3683 Subject Code: H317
(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?
A) 26 knots.
B) 19 knots.
C) 23 knots.
Question: 3684 Subject Code: H317
(Refer to figure 37.) Determine the maximum wind velocity for a 45° crosswind if the maximum crosswind component for the airplane is 25 knots.
A) 25 knots.
B) 29 knots.
C) 35 knots.
Question: 3685 Subject Code: H317
(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?
A) 16 knots.
B) 20 knots.
C) 24 knots.
Question: 3686 Subject Code: H317
(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 13knot maximum crosswind component?
A) Runway 6.
B) Runway 32.
C) Runway 29.
Question: 3687 Subject Code: H317
(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 13knot maximum crosswind component?
A) Runway 14.
B) Runway 24.
C) Runway 10.
Question: 3688 Subject Code: H317
(Refer to figure 37.) What is the crosswind component for a landing on Runway 18 if the tower reports the wind as 220° at 30 knots?
A) 19 knots.
B) 30 knots.
C) 23 knots.
Question: 3689 Subject Code: H317
(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
A) 1,400 feet.
B) 1,750 feet.
C) 850 feet.
Question: 3690 Subject Code: H317
(Refer to figure 38.) Determine the total distance required to land.
OAT.................. Std
Pressure altitude.... 2,000 ft
Weight............... 2,300 lb
Wind component....... Calm
Obstacle............. 25 ft
A) 850 feet.
B) 1,450 feet.
C) 1,150 feet.
Question: 3691 Subject Code: H317
(Refer to figure 38.) Determine the total distance required to land.
OAT.................. 90 °F
Pressure altitude.... 3,000 ft
Weight............... 2,900 lb
Headwind component... 10 kts
Obstacle............. 50 ft
A) 1,725 feet.
B) 1,550 feet.
C) 1,450 feet.
Question: 3692 Subject Code: H317
(Refer to figure 38.) Determine the approximate total distance required to land over a 50foot obstacle.
OAT.................. 90 °F
Pressure altitude.... 4,000 ft
Weight............... 2,800 lb
Headwind component... 10 kts
A) 1,525 feet.
B) 1,950 feet.
C) 1,775 feet.
Question: 3693 Subject Code: H317
(Refer to figure 39.) Determine the approximate landing ground roll distance.
Pressure altitude... Sea level
Headwind............ 4 kts
Temperature......... Std
A) 490 feet.
B) 401 feet.
C) 356 feet.
Question: 3694 Subject Code: H317
(Refer to figure 39.) Determine the total distance required to land over a 50foot obstacle.
Pressure altitude.... 7,500 ft
Headwind............. 8 kts
Temperature.......... 32°F
Runway............... Hard surface
A) 1,506 feet.
B) 1,004 feet.
C) 1,205 feet.
Question: 3695 Subject Code: H317
(Refer to figure 39.) Determine the total distance required to land over a 50foot obstacle.
Pressure altitude.... 5,000 ft
Headwind............. 8 kts
Temperature.......... 41 °F
Runway............... Hard surface
A) 1,076 feet.
B) 837 feet.
C) 956 feet.
Question: 3696 Subject Code: H317
(Refer to figure 39.) Determine the approximate landing ground roll distance.
Pressure altitude... 5,000 ft
Headwind............ Calm
Temperature......... 101 °F
A) 495 feet.
B) 545 feet.
C) 445 feet.
Question: 3697 Subject Code: H317
(Refer to figure 39.) Determine the total distance required to land over a 50foot obstacle.
Pressure altitude.... 3,750 ft
Headwind............. 12 kts
Temperature.......... Std
A) 794 feet.
B) 836 feet.
C) 816 feet.
Question: 3698 Subject Code: H317
(Refer to figure 39.) Determine the approximate landing ground roll distance.
Pressure altitude.... 1,250 ft
Headwind............. 8 kts
Temperature.......... Std
A) 275 feet.
B) 470 feet.
C) 366 feet.
Question: 3705 Subject Code: H317
(Refer to figure 41.) Determine the total distance required for takeoff to clear a 50foot obstacle.
OAT.................. Std
Pressure altitude.... 4,000 ft
Takeoff weight....... 2,800 lb
Headwind component... Calm
A) 2,000 feet.
B) 1,500 feet.
C) 1,750 feet.
Question: 3706 Subject Code: H317
(Refer to figure 41.) Determine the total distance required for takeoff to clear a 50foot obstacle.
OAT................... Std
Pressure altitude..... Sea level
Takeoff weight........ 2,700 lb
Headwind component.... Calm
A) 1,700 feet.
B) 1,400 feet.
C) 1,000 feet.
Question: 3707 Subject Code: H317
(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
A) 1,800 feet.
B) 1,300 feet.
C) 1,150 feet.
Question: 3708 Subject Code: H317
(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
A) 850 feet.
B) 650 feet.
C) 1,000 feet.
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