Unit 5: Airplane Performance and Weight and Balance (Study Session)

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. *See word .doc.

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) 1,000-foot increase.

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) 1,004 feet.

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) 1,150 feet.

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. *Pressure altitude is determined by adjusting the altimeter setting to 29.92" Hg. This is the true altitude plus or minus the pressure altitude conversion factor (based on current altimeter setting). Since 29.97 is not a number given on the conversion chart, you must interpolate. Compute 5/8 of -73 (since 29.97 is 5/8 of the way between 29.92 and 30.0), which is 45. Subtract 45 ft. from 1,386 ft. to obtain a pressure altitude of 1,341 feet. Note that if the altimeter setting is greater than standard (e.g., 29.97), the pressure altitude (i.e., altimeter set to 29.92) will be less than true altitude.

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 passengers 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°C and 29.92" Hg. B) 59°C and 1013.2 millibars. C) 59°F and 29.92 millibars.

A) 15°C and 29.92" Hg. (59°F)

Determine the condition of the airplane: Pilot and copilot = 375 lb Passengers -- aft position = 245 lb Baggage = 65 lb Fuel = 70 gal A) 185 pounds under allowable gross weight; CG is located within limits. B) 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) 185 pounds under allowable gross weight; CG is located within limits.

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) 19 knots.

Determine the condition of the airplane: Pilot and copilot = 316 lb Passengers Fwd position = 130 lb Aft position = 147 lb Baggage = 50 lb 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) 197 pounds under allowable gross weight; CG 83.6 inches aft of datum.

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) 2,000 feet MSL. 440 + 348 = 788 788/2 = 394 Indicated altitude to pressure altitude: 3,894 - 394 = 3,500

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. *Note that the question asks only for pressure altitude, not density altitude. Pressure altitude is determined by adjusting the altimeter setting to 29.92" Hg, i.e., adjusting for nonstandard pressure. This is the true altitude plus or minus the pressure altitude conversion factor (based on current altimeter setting). On the chart, an altimeter setting of 30.0 requires you to subtract 73 ft. to determine pressure altitude (note that at 29.92, nothing is subtracted because that is pressure altitude). Since 29.96 is halfway between 29.92 and 30.0, you need only subtract 36 (-73/2) from 3,563 ft. to obtain a pressure altitude of 3,527 ft. (3,563 - 36). Note that a higher-than-standard barometric pressure means pressure altitude is lower than true altitude.

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 = 35 gal A) 45 pounds. B) 63 pounds. C) 220 pounds.

A) 45 pounds.

Determine the approximate ground roll distance required for takeoff. OAT = 32°C 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) 650 feet.

You have planned a cross-country flight on a 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) Replan your journey to avoid the mountain pass. *Because the density altitude through the mountain pass is higher than the service ceiling of the aircraft, it will be impossible to fly through the pass given the current conditions. You must replan your journey to avoid the mountain pass.

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. *The empty weight of an airplane includes airframe, engines, and all items of operating equipment that have fixed locations and are permanently installed. It includes optional and special equipment, fixed ballast, hydraulic fluid, unusable fuel, and undrainable oil.

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.

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) 1,400 feet.

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 = Calm A) 1,000 feet. B) 1,400 feet. C) 1,700 feet.

B) 1,400 feet. *Begin in the left section of Fig. 40 by finding the intersection of the sea level pressure altitude and standard temperature (15°C) and proceed horizontally to the right to the first reference line. Then proceed parallel to the closest guideline, to 2,700 pounds. From there, proceed horizontally to the right to the third reference line. You skip the second reference line because the wind is calm. Then proceed upward parallel to the closest guideline to the far right side. To clear the 50-ft. obstacle, you need a takeoff distance of about 1,400 feet. NOTE: This question was previously released by the FAA and the FAA's objective is for you to select the "most correct" answer from the choices given. The actual answer is 1,250 feet, but since 1,400 feet is the closest answer, it should be chosen as correct.

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) 1,750 feet.

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) 1,775 feet.

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) 1,925 feet.

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.

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) 180 pounds under allowable gross weight; CG is located within limits.

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) 2,991 feet MSL. *Pressure altitude is determined by adjusting the altimeter setting to 29.92" Hg, i.e., adjusting for nonstandard pressure. This is the indicated altitude of 1,380 ft. plus or minus the pressure altitude conversion factor (based on the current altimeter setting). On the right side of Fig. 8 is a pressure altitude conversion factor schedule. Add 1,533 ft. for an altimeter setting of 28.30 and 1,630 ft. for an altimeter setting of 28.20. Using interpolation, you must subtract 20% of the difference between 28.3 and 28.2 from 1,630 ft. (1,630 - 1,533 = 97 × .2 = 19). Since 1,630 - 19 = 1,611, add 1,611 ft. to 1,380 ft. to get the pressure altitude of 2,991 feet.

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.

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) 23 knots.

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) 36.1 gallons.

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.

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.

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) 545 feet.

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) 70.1 gallons.

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) 75.4 pound-inches. C) 77.6 pound-inches.

B) 75.4 pound-inches.

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.

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 passengers 96 --- Fuel, 38 gal. --- --- Oil, 8 qt. --- -0.2 A) 79.2, utility category. B) 80.8, utility category. C) 81.2, normal category.

B) 80.8, utility category. *See .doc.

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) 956 feet.

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 = 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) Add a 100-pound weight to the baggage compartment. *See .doc for graphs. *C was wrong. No need to change weight, just moment.

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.

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 lb Fuel = 35 gal 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? (See Word .doc) A) CG 92.44. B) CG 94.01. C) CG 119.8.

B) CG 94.01. *Divide total moments by total weights.

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) 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. *The propeller produces thrust in proportion to the mass of air being accelerated through the rotating propeller. If the air is less dense, the propeller efficiency is decreased. Remember, higher density altitude refers to less dense air.

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.

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) Runway 14. *If the wind is from the south at 20 knots, runway 14, i.e., 140°, would provide a 40° crosswind component (180° - 140°). Given a 20-knot wind, find the intersection between the 20-knot arc and the angle between wind direction and the flight path of 40°. Dropping straight downward to the horizontal axis gives 13 knots, which is the maximum crosswind component of the example airplane.

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) groundspeed at touchdown, a longer ground roll, and the likelihood of overshooting the desired touchdown point.

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

B) increase.

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) 1,300-foot increase.

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) 1,650-foot increase.

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) 1,700-foot decrease.

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) 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.

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) 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.

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) 183 MPH. *Refer to Figure 35 and locate the column for -36°F (ISA -20°C). Interpolation will be required to determine the true airspeed (TAS) at 9,500 feet. At 8,000 feet, TAS is 181 MPH, and at 10,000 feet, TAS is 184 MPH; therefore, the difference is 3 MPH. 10,000 feet - 8,000 feet = 2,000 feet 9,500 feet - 8,000 feet = 1,500 feet 1,500 feet ÷ 2,000 feet = .75 .75 × 3 MPH = 2.25 MPH 181 MPH + 2.25 MPH = 183.25 MPH

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) 21.0" Hg. *The part of the chart on the right is for temperatures 36°F greater than standard. At 6,500 ft. with a temperature of 36°F higher than standard, the required manifold pressure change is 1/4 of the difference between the 21.0" Hg at 6,000 ft. and the 20.8" Hg at 8,000 ft., or slightly less than 21.0. Thus, 21.0 is the best answer given. The manifold pressure is closer to 21.0 than 20.8.

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) 24 knots.

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? A) 30 pounds. B) 50 pounds. C) 300 pounds.

C) 300 pounds.

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) 35 knots.

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 passengers 310 --- Baggage 45 --- Oil, 8 qt. --- --- A) 24 gallons. B) 32 gallons. C) 40 gallons.

C) 40 gallons.

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) 8,500 feet MSL. *With an altimeter setting of 29.25" Hg, about 626 ft. (579 plus 1/2 the 94-ft. pressure altitude conversion factor difference between 29.2 and 29.3) must be added to the field elevation of 5,250 ft. to obtain the pressure altitude, or 5,876 feet. Note that barometric pressure is less than standard and pressure altitude is greater than true altitude. Next, convert pressure altitude to density altitude. On the chart, find the point at which the pressure altitude line for 5,876 ft. crosses the 81°F line. The density altitude at that spot shows somewhere in the mid-8,000s of feet. The closest answer choice is 8,500 feet. Note that, when temperature is higher than standard, density altitude exceeds pressure altitude.

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) 816 feet. *The total distance to clear a 50-ft. obstacle for a 3,750-ft. pressure altitude is required. Note that this altitude lies halfway between 2,500 ft. and 5,000 ft. Halfway between the total distance at 2,500 ft. of 1,135 ft. and the total distance at 5,000 ft. of 1,195 ft. is 1,165 ft. Since the headwind is 12 kt., the total distance must be reduced by 30% (10% for each 4 kt.).

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.

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) Runway 32. *If the wind is from the north (i.e., either 360° or 0°) at 20 knots, runway 32, i.e., 320°, would provide a 40° crosswind component (360° - 320°). Given a 20-knot wind, find the intersection between the 20-knot arc and the angle between wind direction and the flight path of 40°. Dropping straight downward to the horizontal axis gives 13 knots, which is the maximum crosswind component of the example airplane.

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) Wait until the temperature decreases, and recalculate the takeoff performance. *The majority of pilot-induced accidents occur during the takeoff and landing phases of flight. In this instance, the pilot in command of this aircraft has an important decision to make. The takeoff distance over a 50-foot obstacle appears on initial inspection to be possible (1,980 feet on a 2,100-foot runway). It is important to remember, however, the performance charts are based on ideal conditions and created by testing brand new aircraft with optimal performance and highly experienced test pilots at the controls. It would be ill-advised for this pilot to attempt to take off. The pilot should wait for the temperature to decrease and recalculate the takeoff performance.

Determine if the airplane weight and balance is within limits. Front seat occupants = 415 lb Rear seat occupants = 110 lb Fuel, main 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.