ASA Chapter 8

(Refer to Figure 60.) How should the 500-pound weight be shifted to balance the plank on the fulcrum? A. 1 inch to the left. B. 1 inch to the right. C. 4.5 inches to the right.

A. 1 inch to the left.

(Refer to Figure 8.) What is the effect of a temperature increase from 35 to 50 degrees F on the density altitude if the pressure altitude remains at 3,000 feet MSL? A. 1,000 foot increase. B. 1,100 foot increase. C. 1,300 foot increase.

A. 1,000 foot increase.

(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 deg F Runway........................................................................................................Hard surface A. 1,004 feet. B. 1,205 feet. C. 1,506 feet.

A. 1,004 feet.

(Refer to Figure 40.) Determine the approximate ground roll distance required for takeoff. OAT......................................................................................................................100 deg F Pressure altitude.............................................................................................2,000 ft Takeoff weight.................................................................................................2,750 lb Headwind and component.......................................................................Calm A. 1,150 feet. B. 1,300 feet. C. 1,800 feet.

A. 1,150 feet.

(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. 1,341 feet MSL.

(Refer to Figure 34.) What is the maximum amount of baggage that may be loaded aboard the airplane for the CG to remain within the moment envelope? Weight (LB) MOM/1000 Empty weight 1,350 51.5 Pilot and front passenger 250 ---- Rear passenger 400 ---- Baggage ---- ---- Fuel, 30 gal ---- ---- Oil, 8 qt ---- -0.2 A. 105 pounds. B. 110 pounds. C. 120 pounds.

A. 105 pounds.

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

A. 15 degrees C and 29.92" Hg.

(Refer to Figure 36.) What is the crosswind component for a landing on Runway 18 if the tower reports the wind as 220 deg at 30 knots? A. 19 knots. B. 23 knots. C. 30 knots.

A. 19 knots.

(Refer to Figure 8.) Determine the density altitude for these conditions: Altimeter setting.....................................................................................30.35 Runway temperature..........................................................................+25 Degrees F Airport elevation....................................................................................3,894 ft MSL A. 2,000 feet MSL. B. 2,900 feet MSL. C. 3,500 feet MSL.

A. 2,000 feet MSL.

(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. 2,991 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. A. 3,527 feet MSL. B. 3,556 feet MSL. C. 3,639 feet MSL.

A. 3,527 feet MSL.

(Refer to Figures 32 and 33.) What is the maximum amount of baggage that can be carried when the airplane is loaded as follows? Front seat occupants..................................................................................387 lb Rear seat occupants...................................................................................293 lb Fuel (main wing tanks)................................................................................35 gal A. 45 pounds. B. 63 pounds. C. 220 pounds.

A. 45 pounds.

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

A. 650 feet.

(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? A. The CG moves forward approximately 3 inches. B. The weight changes, but the CG is not affected. C. The CG moves forward approximately 0.1 inch.

A. The CG moves forward approximately 3 inches.

Which items are included in the empty weight of an aircraft? A. Unusable fuel and undrainable oil. B. Only the airframe, powerplant, and optional equipment. C. Full fuel tanks and engine oil to capacity.

A. Unusable fuel and undrainable oil.

(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. A. Weight is reduced by 210 pounds and the CG is aft of limits. B. Weight is reduced by 210 pounds and the CG is unaffected. C. Weight is reduced to 2,680 pounds and the CG moves forward.

A. Weight is reduced by 210 pounds and the CG is aft of limits.

(Refer to Figure 37.) Determine the total distance required to land. OAT.......................................................................................................................32 deg 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. 1,400 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 and component.......................................................................Calm A. 1,000 feet. B. 1,400 feet. C. 1,700 feet.

B. 1,400 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 and component.......................................................................Calm A. 1,500 feet. B. 1,750 feet. C. 2,000 feet.

B. 1,750 feet.

(Refer to Figure 37.) Determine the approximate total distance required to land over a 50-foot obstacle. OAT.......................................................................................................................90 deg 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. 1,775 feet.

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

B. 1,925 feet.

(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. 11.2 gallons per hour.

(Refer to Figures 32 and 33.) Determine if the airplane weight and balance is within limits. Front seat occupants..................................................................................340 lb Rear seat occupants...................................................................................295 lb Fuel (main wing tanks)................................................................................44 gal Baggage...........................................................................................................56 lb A. 20 pounds overweight, CG aft of aft limits. B. 20 pounds overweight, CG within limits. C. 20 pounds overweight, CG forward of forward limits.

B. 20 pounds overweight, CG within limits.

(Refer to Figure 36.) What is the headwind component for a landing on Runway 18 if the tower reports the wind as 220 deg at 30 knots. A. 19 knots. B. 23 knots. C. 26 knots.

B. 23 knots.

(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 deg C Manifold Pressure..............................................................................21.3" Hg Wind.........................................................................................................Calm A. 31.4 gallons. B. 36.1 gallons. C. 40.1 gallons.

B. 36.1 gallons.

(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. 366 feet.

(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. 401 feet.

(Refer to Figure 38.) Determine the approximate landing ground roll distance. Pressure altitude.............................................................................................5,000 ft Headwind .........................................................................................................Calm Temperature...................................................................................................101 Deg F A. 495 feet. B. 545 feet. C. 445 feet.

B. 545 feet.

(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 deg C Manifold Pressure..............................................................................20.8" Hg Wind.........................................................................................................Calm A. 60.2 gal B. 70.1 gal C. 73.2 gal

B. 70.1 gal

(Refer to Figure 34.) Determine the moment with the following data: Weight (LB) MOM/1000 Empty weight 1,350 51.5 Pilot and front passenger 340 ---- Fuel (std tanks) Capacity ---- Oil, 8 qt ---- ---- A. 69.9 pound-inches. B. 74.9 pound-inches. C. 77.6 pound-inches.

B. 74.9 pound-inches.

(Refer to Figure 54.) Determine the aircraft loaded moment and the aircraft category. Weight (LB) MOM/1000 Empty weight 1,350 51.5 Pilot and front passenger 380 ---- Fuel, 48 gal 288 ---- Oil, 8 qt ---- ---- A. 78.2, normal category. B. 79.2 normal category. C. 80.4, utility category.

B. 79.2 normal category.

(Refer to Figure 34.) Calculate the moment of the airplane and determine which category is applicable. Weight (LB) MOM/1000 Empty weight 1,350 51.5 Pilot and front passenger 310 ---- Rear passenger 96 ---- Baggage ---- ---- Fuel, 38 gal ---- ---- Oil, 8 qt ---- -0.2 A. 79.2, utility category. B. 80.8, utility category. C. 81.2, utility category.

B. 80.8, utility category.

(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 deg F Runway........................................................................................................Hard surface A. 837 feet. B. 956 feet. C. 1,076 feet.

B. 956 feet.

(Refer to Figures 32 and 33.) With the airplane loaded as follows, what action can be taken to balance the airplane? Front seat occupants..................................................................................411 lb Rear seat occupants...................................................................................100 lb Fuel (main wing tanks)................................................................................44 gal A. Fill the auxiliary tanks. B. Add a 100-pounds weight to the baggage compartment. C. Transfer 10 gallons of fuel from the main tanks to the auxiliary tanks.

B. Add a 100-pounds weight to the baggage compartment.

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. An increase in ambient temperature.

(Refer to Figures 32 and 33.) Calculate the weight and balance and determine if the CG and the weight of the airplane are within limits. Front seat occupants..................................................................................350 lb Rear seat occupants...................................................................................325 lb Fuel (main wing tanks)................................................................................35 gal Baggage...........................................................................................................27 lb A. CG 81.7, out of limits forward B. CG 83.4, within limits. C. CG 84.1. within limits.

B. CG 83.4, within limits.

GIVEN: WEIGHT ARM MOMENT (LB) (IN) (LB-IN) Empty weight 1,495.0 101.4 151,593.0 Pilot and passengers 380.0 64.0 -- Fuel (30 gal usable-no reserve) -- 96.0 -- The CG is located how far aft of datum? A. CG 92.44. B. CG 94.01. C. CG 119.8.

B. CG 94.01.

(Refer to Figures 32 and 33.) Which action can adjust the airplane's weight to maximum gross weight and the CG within limits for takeoff? Front seat occupants..................................................................................425 lb Rear seat occupants...................................................................................300 lb Fuel (main wing tanks)................................................................................44 gal A. Drain 12 gallons of fuel. B. Drain 9 gallons of fuel. C. Transfer 12 gallons of fuel from the main tanks to the auxiliary tanks.

B. Drain 9 gallons of fuel.

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

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. It decreases performance.

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. It reduces climb performance.

(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. Runway 14.

(Refer to Figure 8.) What is the effect of a temperature increase from 25 to 50 degrees 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. 1,650 foot increase.

(Refer to Figure 8.) What is the effect of a termperature decrease and a pressure altitude increase on the density altitude from 90 degrees F and 1,250 feet pressure altitude to 55 degrees F and 1,750 feet pressure altitude? A. 1,700 foot increase. B. 1,300 foot decrease. C. 1,700 foot decrease.

C. 1,700 foot decrease.

(Refer to Figure 37.) Determine the total distance required to land. OAT.......................................................................................................................90 deg 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. 1,725 feet.

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? A. 10 gallons. B. 12 gallons. C. 15 gallons.

C. 15 gallons.

(Refer to Figure 35.) Approximately what true airspeed should a pilot expect with full throttle at 10,500 feet with a a temperature 36 deg F above standard? A. 190 kts. B. 159 kts. C. 165 kts.

C. 165 kts.

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? A. 15.7 gallons. B. 16.2 gallons. C. 18.4 gallons.

C. 18.4 gallons.

(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 deg F higher than standard. A. 19.8" Hg. B. 20.8" Hg. C. 21.0" Hg.

C. 21.0" Hg.

(Refer to Figure 36.) What is the maximum wind velocity for a 30 deg crosswind if the maximum crosswind component for the airplane is 12 knots? A. 16 knots. B. 20 knots. C. 24 knots.

C. 24 knots.

(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 lcoated at point Y to balance the plank? A. 30 pounds. B. 50 pounds. C. 300 pounds.

C. 300 pounds.

(Refer to Figure 36.) Determine the maximum wind velocity for a 45 deg crosswind if the maximum crosswind component for the airplane is 25 knots. A. 25 knots. B. 29 knots. C. 35 knots.

C. 35 knots.

(Refer to Figure 34.) What is the maximum amount of fuel that may be aboard the airplane on takeoff if loaded as follows? Weight (LB) MOM/1000 Empty weight 1,350 51.5 Pilot and front passenger 340 ---- Rear passenger 310 ---- Baggage 45 ---- Oil, 8 qt ---- ---- A. 24 gallons. B. 32 gallons. C. 40 gallons.

C. 40 gallons.

(Refer to Figure 8.) Determine the density altitude for these conditions: Altimeter setting.....................................................................................29.25 Runway temperature...........................................................................+81 Degrees F Airport elevation....................................................................................5,250 ft MSL A. 4,600 feet MSL. B. 5,877 feet MSL. C. 8,500 feet MSL

C. 8,500 feet MSL

(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. 816 feet.

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

(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. A. No effect on CG. B. Moment will increase to 2,357 in-lb. C. Moment will decrease to 2,087 in-lb.

C. Moment will decrease to 2,087 in-lb.

(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. Runway 32.

(Refer to Figures 32 and 33.) Determine if the airplane weight and balance is within limits. Front seat occupants..................................................................................415 lb Rear seat occupants...................................................................................110 lb Fuel (main wing tanks)................................................................................44 gal Fuel (aux tanks).............................................................................................. 19 gal Baggage...........................................................................................................32 lb A. 19 pounds overweight, CG within limits. B. 19 pounds overweight, CG out of limits forward. C. Weight within limits, CG out of limits.

C. Weight within limits, CG out of limits.

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. higher than pressure altitude.