Stage 3 private pilot

2067. Density altitude, and its effect on landing performance, is defined by A— pressure altitude and ambient temperature. B— headwind and landing weight. C— humidity and braking friction forces.

A

3293. (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— 2,991 feet MSL. B— 2,913 feet MSL. C— 3,010 feet MSL.

A

3295. (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.

A

3296. (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.

A

3297. (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.

A

3298. (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.

A

3386. What are the standard temperature and pressure values for sea level? A— 15°C and 29.92" Hg. B— 59°C and 1013.2 millibars. C— 59°F and 29.92 millibars.

A

3704. (Refer to Figure 39.) Approximately how much additional takeoff distance will be required for a gyroplane to clear a 50-foot obstacle if the temperature increases from 75 to 90°F at a pressure altitude of 2,300 feet? A— 160 feet. B— 200 feet. C— 2,020 feet.

A

3707. (Refer to Figure 40.) 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— 1,150 feet. B— 1,300 feet. C— 1,800 feet.

A

3708. (Refer to Figure 40.) Determine the approximate ground roll distance required for takeoff. OAT ........................ 95°F Pressure altitude ............... 2,000 ft Takeoff weight ........... 2,500 lb Headwind component .... 20 kts A— 650 feet. B— 850 feet. C— 1,000 feet.

A

2199. What effect does an uphill runway slope have on takeoff performance? A— Increases takeoff speed. B— Increases takeoff distance. C— Decreases takeoff distance.

B

3246. 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.

B

3291. 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.

B

3300. 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.

B

3394. 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.

B

3699. (Refer to Figure 39.) Determine the total landing distance to clear a 50-foot obstacle in a gyroplane. The outside air temperature (OAT) is 75°F and the pressure altitude at the airport is 2,500 feet. A— 521 feet. B— 525 feet. C— 529 feet.

B

3705. (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 A— 1,500 feet. B— 1,750 feet. C— 2,000 feet.

B

3891. (Refer to Figure 57.) What is the maximum altitude for the balloon if the gross weight is 1,100 pounds and standard temperature exists at all altitudes? A— 1,000 feet. B— 4,000 feet. C— 5,500 feet.

B

2356. (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— 900-foot increase. B— 1,100-foot decrease. C— 1,300-foot increase.

C

3289. 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.

C

3290. 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.

C

3292. (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.

C

3294. (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.

C

3299. (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— 1,300-foot decrease. C— 1,700-foot decrease.

C

3697. (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 A— 794 feet. B— 836 feet. C— 816 feet.

C

3702. (Refer to Figure 39.) Determine the total takeoff distance required for a gyroplane to clear a 50-foot obstacle if the temperature is 95°F and the pressure altitude is 1,700 feet. A— 1,825 feet. B— 1,910 feet. C— 2,030 feet.

C

3703. (Refer to Figure 39.) Determine the total takeoff distance required for a gyroplane to clear a 50-foot obstacle if the temperature is standard at sea level pressure altitude. A— 950 feet. B— 1,090 feet. C— 1,200 feet.

C

3892. (Refer to Figure 57.) What is the maximum altitude for the balloon if the gross weight is 1,000 pounds and standard temperature exists at all altitudes? A— 4,000 feet. B— 5,500 feet. C— 11,000 feet.

C

2234. The most critical conditions of takeoff performance are the result of some combination of high gross weight, altitude, temperature, and A— unfavorable wind. B— obstacles surrounding the runway. C— powerplant systems.

a

2283. The most critical conditions of takeoff performance are the result of some combination of high gross weight, altitude, temperature, and A— unfavorable wind. B— obstacles surrounding the runway. C— powerplant systems.

a

3688. (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? A— 19 knots. B— 23 knots. C— 30 knots.

a

3694. (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 A— 1,004 feet. B— 1,205 feet. C— 1,506 feet.

a

3700. (Refer to Figure 39.) Approximately how much additional landing distance will be required for a gyroplane to clear a 50-foot obstacle with an increase in temperature from 40 to 60°F at 3,200 feet pressure altitude? A— 4 feet. B— 8 feet. C— 12 feet.

a

3679. (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 A— 60.2 gallons. B— 70.1 gallons. C— 73.2 gallons.

b

3680. (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.

b

3681. (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.

b

3687. (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? A— Runway 10. B— Runway 14. C— Runway 24.

b

3689. (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 A— 850 feet. B— 1,400 feet. C— 1,750 feet.

b

3690. (Refer to Figure 37.) Determine the total distance required to land. OAT ............................... Std Pressure altitude ............. 10,000 ft Weight ................ 2,400 lb Wind component .............. Calm Obstacle ......... 50 ft A— 750 feet. B— 1,925 feet. C— 1,450 feet.

b

3692. (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 lb Headwind component ..... 10 kts A— 1,525 feet. B— 1,775 feet. C— 1,950 feet.

b

3693. (Refer to Figure 38.) Determine the approximate landing ground roll distance. Pressure altitude .. Sea level Headwind ........ 4 kts Temperature ........... Std A— 356 feet. B— 401 feet. C— 490 feet.

b

3695. (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 A— 837 feet. B— 956 feet. C— 1,076 feet.

b

3696. (Refer to Figure 38.) 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.

b

3698. (Refer to Figure 38.) Determine the approximate landing ground roll distance. Pressure altitude ... 1,250 ft Headwind ................. 8 kts Temperature ................. Std A— 275 feet. B— 366 feet. C— 470 feet.

b

3864. (Refer to Figure 54.) How many feet will the glider sink in 1 statute mile at 53 MPH in still air? A— 144 feet. B— 171 feet. C— 211 feet.

b

3865. (Refer to Figure 54.) At what speed will the glider attain a sink rate of 5 feet per second in still air? A— 75 MPH. B— 82 MPH. C— 84 MPH.

b

3867. (Refer to Figure 54.) At what speed will the glider gain the most distance while descending 1,000 feet in still air? A— 44 MPH. B— 53 MPH. C— 83 MPH.

b

683. (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? A— 19 knots. B— 23 knots. C— 26 knots.

b

3678. (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? A— 190 kts. B— 159 kts. C— 165 kts.

c

3682. (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.

c

3684. (Refer to Figure 36.) 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.

c

3685. (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? A— 16 knots. B— 20 knots. C— 24 knots.

c

3686. (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? A— Runway 6. B— Runway 29. C— Runway 32.

c

3691. (Refer to Figure 37.) 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— 1,450 feet. B— 1,550 feet. C— 1,725 feet.

c

3701. (Refer to Figure 39.) Determine the total landing distance to clear a 50-foot obstacle in a gyroplane. The outside air temperature (OAT) is 80°F and the pressure altitude is 3,500 feet. A— 521 feet. B— 526 feet. C— 531 feet.

c

3732. (Refer to Figure 46.) What is the best rate-of-climb speed for the helicopter? A— 24 MPH. B— 40 MPH. C— 57 MPH.

c

3866. (Refer to Figure 54.) How many feet will the glider descend at minimum sink speed for 1 statute mile in still air? A— 132 feet. B— 170 feet. C— 180 feet.

c

3868. (Refer to Figure 54.) What approximate lift/drag ratio will the glider attain at 68 MPH in still air? A— 10.5:1. B— 21.7:1. C— 28.5:1.

c