PPL - Chapter 5

How should the 500-pound weight be shifted to balance the plank on the fulcrum?

1 inch to the left.

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?

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

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

1,150 feet.

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?

1,300-foot increase.

Determine the pressure altitude at an airport that is 1,386 feet MSL with an altimeter setting of 29.97.

1,341 feet MSL.

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

1,400 feet.

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?

1,650-foot increase.

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

1,725 feet.

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

1,750

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

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

1,925 feet.

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

105 lbs

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.

Approximately what true airspeed should a pilot expect with full throttle at 10,500 feet with a temperature of 36°F above standard?

165 knots.

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

Determine the condition of the airplane:Pilot and copilot = 400 lb Passengers -- aft position = 240 lb Baggage = 20 lb Fuel = 75 gal

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

Determine the condition of the airplane: Pilot and copilot = 400 lb Passengers -- aft position = 240 lb Baggage = 20 lb Fuel = 75 gal

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

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?

183 MPH.

Determine the condition of the airplane: Pilot and copilot = 375 lb Passengers -- aft position = 245 lb Baggage = 65 lb Fuel = 70 gal

185 pounds under allowable gross weight; CG is located within limits

Determine the condition of the airplane:Pilot and copilot = 375 lb Passengers -- aft position = 245 lb Baggage = 65 lb Fuel = 70 gal

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?

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

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

2,000 feet MSL.

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.

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

What is the HEADWIND component for a landing on Runway 18 if the tower reports the wind as 220° at 30 knots?

23 knots

What is the headwind component for a landing on Runway 18 if the tower reports the wind as 220° at 30 knots?

23 knots.

What is the maximum wind velocity for a 30° crosswind if the maximum crosswind component for the airplane is 12 knots?

24 knots.

Determine the pressure altitude at an airport that is 3,563 feet MSL with an altimeter setting of 29.96.

3,527 feet MSL.

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.

Determine the maximum wind velocity for a 45° crosswind if the maximum crosswind component for the airplane is 25 knots.

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 weight1,35051.5 Pilot and front passenger 340---Rear passengers 310--- Baggage 45--- Oil, 8 qt.------

40 gallons.

Determine the approximate landing ground roll distance. Pressure altitude = Sea level Headwind = 4 kts Temperature = Std

401 feet.

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

45 pounds.

Determine the approximate landing ground roll distance. Pressure altitude = 5,000 ft Headwind = Calm Temperature = 101°F

545 feet.

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

650 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

70.1 gallons.

21) Determine the moment with the following data: WEIGHT (LB)MOM/1000 Empty weight 1,350 51.5 Pilot and front passenger340 --- Fuel (std tanks) Capacity --- Oil, 8 qt.------

75.1 lb inches.

Determine the moment with the following data:WEIGHT (LB)MOM/1000 Empty weight1,350 51.5 Pilot and front passenger340 --- Fuel (std tanks)Capacity --- Oil, 8 qt.------

75.1 pound-inches.

Determine the density altitude for these conditions: Altimeter setting = 29.25 Runway temperature = +81°F Airport elevation = 5,250 ft MSL

8,500 feet MSL

Determine the total distance required to land over a 50-ft. obstacle. Pressure altitude = 3,750 ft Headwind = 12 knots Temperature = Std

816 feet.

Determine the total distance required to land over a 50-ft. obstacle. Pressure altitude = 3,750 ft Headwind = 12 kts Temperature = Std

816 feet.

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

83.4, within limits.

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

Add a 100-pound weight to the baggage compartment.

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

Add a 100lb weight to the baggage compartment.

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

Drain 9 gallons of fuel.

What effect does high density altitude, as compared to low density altitude, have on propeller efficiency and why?

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

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

It decreases performance.

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?

Runway 32.

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.

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

Unusable fuel and undrainable oil.

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?

Wait until the temperature decreases, and recalculate the takeoff performance.

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.

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

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

higher than pressure altitude.