Chapter 5 Flashcards by Joseph Mexicano

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

15°C and 29.92” Hg.

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

An increase in ambient temperature.

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What effect does high density altitude, as compared 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.

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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.

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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.

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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.

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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.

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

3,527 feet MSL.

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

1,341 feet MSL.

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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.

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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.

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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.

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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.

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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

1,400 feet.

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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

1750ft

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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

650ft

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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.

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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

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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

36.1 gallons.

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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

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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

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

165 kn=ts

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

19 knots

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

23 knots

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

35 knots

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

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

24 knots

With a reported wind of south at 20 knots, which runway is appropriate for an airplane with a 13-knot maximum crosswind component?

Runway 14

``` Determine the total distance required to land. OAT = Std Pressure altitude = 10,000 ft Weight = 2,400 lb Wind component = Calm Obstacle = 50 ft ```

1925 ft

``` 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 ```

1775 ft

``` 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 ```

1725 ft

``` 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 ```

1400 ft

If an emergency situation requires a downwind landing, pilots should expect a faster

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

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

401 ft

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

816 ft

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

545 ft

Determine the approximate landing ground roll distance. Pressure altitude = 1,250 ft Headwind = 8 kts Temperature = Std

366 ft

``` 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 ```

956 ft

``` 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 ```

1004 ft

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

The CG is located how far aft of datum?

94.01

What is the maximum amount of fuel that may be aboard the airplane on takeoff if loaded as follows?

40 gallons

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

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

1 inch to the left.

Calculate the moment of the airplane and determine which category is applicable.

81.2, normal category.

Determine the moment with the following data:

75.4 pound-inches

Determine the aircraft loaded moment and the aircraft category.

79.2 normal category

What is the maximum amount of baggage that may be loaded aboard the airplane for the CG to remain within the moment envelope?

105 pounds

``` 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 = 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 = 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.

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.

``` 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 ```

20 pounds overweight, CG within limits.

``` 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 ```

CG 83.4, within limits.

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

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.

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.

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.