ASA Test Prep 2018 Private Pilot Chapter 8: "Aircraft Performance"

(refer to figure 61) if 50 pounds of weight is located at point X and 100 pounds at point Z, how much weight must be located at point Y to balance the plank?

300 pounds

(refer to figure 60) how should the 500-pound weight be shifted to balance the plank on the fulcrum?

1 inch to the left

(refer to figure 67) what effect does a 30-gallon fuel burn have on the weight and balance if the airplane weighed 2,784 pounds and the MOM/100 was 2,222 at takeoff?

moment will decrease to 2,087 in-lb

which items are included in the empty weight of an aircraft?

unusable fuel and undrainable fuel

an aircraft is loaded 110 pounds over maximum certificated gross weight. if fuel (gasoline) is drained to bring the aircraft weight within limits, how much fuel should be drained?

18.4 gallons

if an aircraft is loaded 90 pounds over maximum certificated gross weight and fuel (gasoline) is drained to bring the aircraft weight within limits, how much fuel should be drained?

15 gallons

(refer to figure 72) the positive limit load factor is represented by the

horizontal dashed line from C to point E

(refer to figures 32 and 33) upon landing, the front passenger (180 pounds) departs the airplane. a rear passenger (204 pounds) moves to the front passenger position. what effect does this have on the CG if the airplane weighed 2,690 pounds and the MOM/100 was 2,260 just prior to the passenger transfer?

the CG moves forward approximately 3 inches

(refer to figures 32 and 33) what effect does a 35-gallon fuel burn (main tanks) have on the weight and balance if the airplane weighed 2,890 pounds and the MOM/100 was 2,452 at takeoff?

weight is reduced by 210 pounds and the CG is aft of limits

(refer to figure 42) what effect does adding a 185-pound passenger have on the CG, if prior to boarding the passenger, the helicopter weighed 1,380 pounds and the moment is 136,647.5 pound-inches?

the CG is moved forward 1.78 inches

(refer to figure 44 and 45) what is the new CG of a gyroplane after a 10-gallon fuel burn if the original weight was 1,450 pounds and the MOM/1000 was 108 pound-inches?

out of limits forward

(refer to figure 53) how is the CG affected if radio and oxygen equipment weighing 35 pounds is added at station 43.8? the glider weighs 945 pounds with a moment of 78,000.2 pounds-inches prior to adding the equipment?

CG shifts forward 1.38 inches -- within limits

(refer to figure 53) what is the CG of the glider if the pilot and passenger each weigh 215 pounds?

81.08 inches aft of datum -- within limits

what constitutes the payload of a balloon?

total weight of passengers, cargo, and fuel

(refer to figure 56) the gross weight of the balloon is 1,350 pounds and the outside air temperature (OAT) is +51°F. the maximum height would be

10,000 feet

)refer to figure 56) the gross weight of the balloon is 1,200 pounds and the maximum height the pilot needs to attain is 5,000 feet. the maximum temperature to achieve this performance is

+97°F

(refer to figure 57) determine the maximum payload for a balloon flying at 2,500 feet at an ambient temperature of 91°F

505 pounds

(refer to figure 57) determine the maximum weight allowable for pilot and passenger for a flight at approximately 1,000 feet with a temperature of 68°F. launch with 20 gallons of propane

620 pounds

(refer to figure 57) what is the maximum weight allowed for pilot and passengers for a flight at 5,000 feet with a standard temperature? launch with 20 gallons of propane

670 pounds

problems caused by overloading an airplane include

reduced climb rate, excessive structural loads, and shortened cruising range

most aircraft are so designed that if all seats are occupied, all baggage allowed by the baggage compartment structure is carried, and all the fuel tanks are full, the aircraft will be

grossly overloaded

when operating an aircraft, the pilot in command is responsible for using

the most current weight and balance data

if the outside air temperature at a given altitude is warmer than standard, the density altitude is

higher than pressure altitude

(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 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

what are the standard temperature and pressure values for sea level?

15°C and 29.92" Hg

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

an increase in ambient temperature

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

high temperature, high relative humidity, and high density altitude

what effect does high density altitude have on aircraft performance?

it reduces climb performance

(refer to figure 8) what is the effect of a temperature increase from 25 to 50° on the density altitude if the pressure altitude remains at 5,000 feet?

1,650-foot increase

(refer to figure 6) 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 8) what is the effect of a temperature increase from 35 to 50°F on the density altitude if the pressure altitud remains at 3,500 feet MSL?

1,000 foot increase

(refer to figure 8) what is the effect of a temperature increase from 30 to 50°F on the density altitude of 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

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

it decreases performance

what effect ford high density altitude, as compare 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

(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

2,030 feet

density altitude, and its effect on landing performance, is defined by

pressure altitude and ambient temperature

(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?

4,000 feet

(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?

11,000 feet

(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

1,200 feet

)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 ay a pressure altitude of 2,300 feet?

160 feet

what effect does an uphill runway slope have on takeoff performance?

increases takeoff distance

the most critical conditions of takeoff performance are the result of some combination of high gross weight, altitude, temperature, and

unfavorable wind

(refer to figure 46) what is the best rate-of-climb speed for the helicopter?

57 MPH

(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?

165 kts

(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?

11,2 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

21.0" Hg

(refer to figure 39) determine the total landing distance to clear a 50-foot obstacle in a gyroplane. the outside air temperature is 75°F and the pressure altitude at the airport is 2,500 feet

525 feet

)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?

4 feet

(refer to figure 39) determine the total landing distance to clear a 50-foot obstacle in a gyroplane. the outside air temperature is 80°F and the pressure altitude is 3,500 feet

531 feet

(refer to figure 54) how many feet will the glider sink in 1 statute mile at 53 MPH in still air?

171 feet

(refer to figure 54) at what speed will the glider attain a sink rate of 5 feet per second in still air?

82 MPH

(refer to figure 54) how many feet will the glider descend at minimum sink speed for 1 statute mile in still air?

180 feet

(refer to figure 54) at what speed will the glider gain the most distance while descending 1,000 feet in still air?

53 MPH

(refer to figure 54) what approximate lift/drag ratio will the glider attain at 68 MPH in still air?

28.5:1

(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

(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

23 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

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?

24 knots

(refer to figure 36) with a reported wind of north at 30 knots, which runway (6, 9, or 32) is acceptable for use for an airplane with a 13-knot maximum crosswind component?

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 14

maximum endurance is obtained at the point of minimum power to maintain the aircraft

in steady, level flight

when range economy of operation are the principal goals, the pilot must ensure that the airplane will be operated at the recommended

long-range cruise performance