Chapter 5: Airplane performance and Weight& Balance

(Refer to Figure 32 on page 243 and Figure 33 on page 243.) 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

(Refer to Figure 32 on page 243 and Figure 33 on page 243.) 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. is unaffected. B. Weight is reduced by 210 pounds and the CG CG moves forward. C. Weight is reduced to 2,680 pounds and the

A

(Refer to Figure 36 below.pg. 220)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

(Refer to Figure 38 below.pg. 225)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

(Refer to Figure 40 below.pg. 216)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 A. 1,150 feet. B. 1,300 feet. C. 1,800 feet.

A

(Refer to Figure 40 on page 216.) Determine the approximate ground roll distance required for takeoff. OAT = 32°C Pressure altitude = %3D 2,000 ft Takeoff weight = 2,500 lb Headwind component = 20 kts A. 650 feet. B. 850 feet. C. 1,000 feet.

A

(Refer to Figure 67 on page 235.) Determine the condition of the airplane: Pilot and copilot = 375 lb Passengers -- aft position = 245 Ib Baggage = 65 lb Fuel = 70 gal A. 185 pounds under allowable gross weight; CG is located within limits. В. 162 pounds under allowable gross weight; CG is located within limits. C. 162 pounds under allowable gross weight; CG is located aft of the aft limit.

A

(Refer to Figure 67 on page 237.) Determine the condition of the airplane: Pilot and copilot = 316 lb Passengers Fwd position = 130 lb Aft position = %3D 147 lb Baggage = 50 Ib Fuel = 75 gal A. 197 pounds under allowable gross weight; CG 83.6 inches aft of datum. B. 163 pounds under allowable gross weight; CG 82 inches aft of datum. C. 197 pounds under allowable gross weight; CG 84.6 inches aft of datum.

A

(Refer to Figure 8 on page 213.) Determine the density altitude for these conditions: Altimeter setting = 30.35 Runway temperature = +25°Fton Airport elevation = 3,894 ft. MSL A. 2,000 feet MSL. B. 2,900 feet MSL C. 3,500 feet MSL.

A

(Refer to Figure 8 on page 213.) 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

(Refer to Figure 8 on page 215.) 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

(Refer to Figure 8 on page 215.) 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

243 and Figure (Refer to Figure 32 on page 33 on page 243.) 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 %3D = 35 gal A. 45 pounds. B. 63 pounds. C. 220 pounds.

A

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

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

You have planned a cross-country flight on warm spring morning. Your course includes a mountain pass, which is at 11,500 feet MSL. The service ceiling of your airplane is 14,000 feet MSL. After checking the local weather report, you are able to calculate the density altitude of the mountain pass as 14,800 feet MSL. Which of the following is the correct action to take? A. Replan your journey to avoid the mountain pass. B. Continue as planned since density altitude is only a factor for takeoff. C. Continue as planned because mountain thermals will assist your climb.

A

(Refer to Figure 32 on page 239 and Figure 33 on page 239.) 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 Main wing tanks %3! = 44 gal A. Fill the auxiliary wing tanks. B. Add a 100-pound weight to the baggage compartment. C. Transfer 10 gallons of fuel from the main tanks to the auxiliary tanks.

B

(Refer to Figure 32 on page 241 and Figure 33 on page 241.) 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 Baggage = 27 Ib Fuel = 35 gal A. CG 81.7, out of limits forward. B. CG 83.4, within limits. C. CG 84.1, within limits.

B

(Refer to Figure 32 on page 241 and Figure 33 on page 241.) Determine if the airplane weight and balance is within limits. Front seat occupants = 340 lb Rear seat occupants = 295 Ib Fuel (main wing tanks) = %3D 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

(Refer to Figure 32 on page 245 and Figure 33 on page 245.) 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 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

(Refer to Figure 35 below.pg. 218)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

(Refer to Figure 35 below.pg. 218)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

(Refer to Figure 35 on page 218.) 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

(Refer to Figure 36 on page 220.) 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

(Refer to Figure 36 on page 220.) With a reported wind of south at 20 knots, which runway is appropriate for an airplane with a 13-knot maximum crosswind component? A. Runway 10. B. Runway 14. C. Runway 24.

B

(Refer to Figure 37 below.) 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

(Refer to Figure 37 on page 222.) Determine the approximate total distance required to land over a 50-ft. 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

(Refer to Figure 37 on page 222.) 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

(Refer to Figure 38 on page 225.) 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

(Refer to Figure 38 on page 225.) 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

(Refer to Figure 38 on page 225.) 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

(Refer to Figure 38 on page 225.) 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

(Refer to Figure 40 on page 216.) 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

(Refer to Figure 40 on page 216.) 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 = %3D Calm s A. 1,000 feet. B. 1,400 feet. C. 1,700 feet.

B

(Refer to Figure 67 on page 235.) Determine the condition of the airplane: Pilot and copilot = 400 lb Passengers aft position = 240 lb Baggage = 20 lb Fuel = 75 gal A. 157 pounds under allowable gross weight; CG is located within limits. B. 180 pounds under allowable gross weight; CG is located within limits. C. 180 pounds under allowable gross weight, but CG is located aft of the aft limit.

B

(Refer to Figure 8 on page 215.) 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.

B

As air temperature increases, density altitude will A. decrease. B. increase. C. remain the same.

B

If an emergency situation requires a downwind landing, pilots should expect a faster A. airspeed at touchdown, a longer ground roll, and better control throughout the landing roll. B. groundspeed at touchdown, a longer ground roll, and the likelihood of overshooting the desired touchdown point. C. groundspeed at touchdown, a shorter ground roll, and the likelihood of undershooting the desired touchdown point.

B

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

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

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

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

(Refer to Figure 32 on page 245 and Figure 33 on page 245.) Determine if the airplane weight and balance is within limits. Front seat occupants = %3D 415 Ib Rear seat occupants %3D 110 Ib Fuel, main tanks = 44 gal Fuel, aux. tanks = 19 gal Baggage = %3D 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

(Refer to Figure 35 on page 218.) 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. 178 MPH. B. 181 MPH. C. 183 MPH.

C

(Refer to Figure 35 on page 218.) 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

(Refer to Figure 35 on page 218.) 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

(Refer to Figure 36 on page 220.) 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

(Refer to Figure 36 on page 220.) 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

(Refer to Figure 36 on page 220.) With a reported wind of north at 20 knots, which runway is acceptable for use for an airplane with a 13-knot maximum crosswind component? A. Runway 6. B. Runway 29. C. Runway 32.

C

(Refer to Figure 37 on page 222.) Determine the total distance required to land. OAT = 90°F Pressure altitude = 3,000 ft Weight = 2,900 Ib Headwind component = 10 kts Obstacle = 50 ft A. 1,450 feet. B. 1,550 feet. C. 1,725 feet.

C

(Refer to Figure 38 on page 225.) Determine the total distance required to land over a 50-ft. obstacle. Pressure altitude = 3,750 ft Headwind = 12 kts Temperature = Std A. 794 feet. B. 836 feet. C. 816 feet.

C

(Refer to Figure 8 below.pg. 213)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

(Refer to Figure 8 below.pg. 215)Determine the density altitude for these conditions: Altimeter setting = %3D 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

(Refer to Figure 8 on page 213.) 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. 1,000-foot increase. B. 1,100-foot decrease. C. 1,300-foot increase.

C

(Refer to Figure 8 on page 215.) 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

A pilot and two passengers landed on a 2,100 foot east-west gravel strip with an elevation of 1,800 feet. The temperature is warmer than expected and after computing the density altitude it is determined the takeoff distance over a 50 foot obstacle is 1,980 feet. The airplane is 75 pounds under gross weight. What would be the best choice? A. Taking off into the headwind will give the extra climb-out time needed. B. Try a takeoff without the passengers to make sure the climb is adequate. C. Wait until the temperature decreases, and recalculate the takeoff performance.

C

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

If an aircraft is loaded 90 pounds over maximum certificated drained to bring the aircraft weight within limits, how gross weight and fuel (gasoline) is much fuel should be drained? A. 10 gallons. B. 12 gallons. C. 15 gallons.

C

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

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 ue low density altitude. C. High temperature, high relative humidity, and. high density altitude.

C