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Knowledge Test Prep > Ch 5 - Airplane Performance & Weight & Balance - Questions 519 - 569 > Flashcards

Ch 5 - Airplane Performance & Weight & Balance - Questions 519 - 569 Flashcards

1
Q

What are the standard temperatures and pressure values for seal level?

A

15 degrees celcius and 29.92 Hg.

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2
Q

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

A

It decreases performance

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3
Q

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

A

An increase in ambient temperature

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4
Q

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

A

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

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5
Q

What effect does high density altitude have on aircraft performance?

A

It reduces climb performance

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6
Q

Which combination of atmospheric conditions will reduce aircraft takeoff and climb performance?

A

High temperature, low relative humidity, and low density altitude

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7
Q

As air temperature increases, density altitude will

A

Increase

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8
Q

You have planned a cross-country flight on a warm spring morning. Your 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 re able to calcite 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

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9
Q

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

Wait until the temperature decreases, and recalculate that takeoff performance

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10
Q

If the outside air temperate (OAT) at a given altitude is warmer than standard, the density altitude is

A

High than pressure altitude

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11
Q

(Refer to Fg 8 on Pg 217) Determined 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

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12
Q

(Refer to Fg 8 on Pg 217) 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 fat increase

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13
Q

(Refer to Fg 8 on Pg 217) What is the effect of a temperature 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 decrease

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14
Q

(Refer to Fg 8 on Pg 219) 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

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15
Q

(Refer to Fg 8 on Pg 219) 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

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16
Q

(Refer to Fg 8 on Pg 219) What is the effect of a temperature increase from 25-50 degrees F on the deny altitude of the pressure altitude remains at 5,000 feet?

A

1,650-foot increase

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17
Q

(Refer to Fg 8 on Pg 219) Determine the density altitude for these conditions:
Altimeter Setting = 29.25
Runway Temperature = +81 degrees F
Airport Elevation = 5,250 Ft. MSL

A

8,500 feet MSL

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18
Q

(Refer to Fg 40 on Pg 220) Determine the approximate ground roll distance required for takeoff.
OAT = 38 degrees C
Pressure Altitude = 2,000 ft
Takeoff Weight - 2,750 lb
Headwind Component = Calm

A

1,150 feet

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19
Q

(Refer to Fg 40 on Pg 220) Determine the Toal 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

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20
Q

(Refer to Fg 40 on Pg 220) Determine the total distance required for takeoff to clear 50-foot obstacle.
OAT = Std
Pressure Altitude = 4,000 ft
Takeoff Weight - 2,800 lb
Headwind Component = Calm

A

1,750 feet

21
Q

(Refer to Fg 40 on Pg 220) Determine the approximate ground roll distance required for takeoff.
OAT = 32 degrees C
Pressure Altitude = 2,000 ft
Takeoff weight = 2,500 lb
Headwind Component = 20 kts

A

650 feet

22
Q

(Refer to Fg 35 on Pg 222) Who fuel flow should a pilot expect at 11,000 feet on a standard day with 65% maximum continuous power?

A

11.2 gallons per hour

23
Q

(Refer to Fg 35 on Pg 222) What is the expected fuel consumption for a 1,000-nautical mile flight under the following conditions?

Pressure Altitude = 8,000 ft
Temperature = 22 degrees C
Manifold Pressure = 20.8” Hg
Wind = Calm

A

70.1 gallons

24
Q

(Refer to Fg 35 on Pg 222) What is the expected fuel consumption for a 500-nautical mile flight under the following conditions?

A

36.1 gallons

25
Q

(Refer to Fg 35 on Pg 222) Determine the approximate manifold pressure setting with 2,450 RPM to achieve 65% maximum continuous power at 6,500 feet with a temperature of 36 degrees F than standard

A

21.0”Hg

26
Q

(Refer to Fg 35 on Pg 222) Approximately what true airspeed should a pilot expect with 65% maximum continuous power at 9,500 feet with a temperature of 36 degrees F below standard?

A

183MPH

27
Q

(Refer to Fg 35 on Pg 222) Approximately what true airspeed should a pilot expect with full throttle at 10,500 feet with a temperature of 36 degrees F above standard?

A

165 kts

28
Q

(Refer to Fg 36 on Pg 224) What is the the crosswind component for a landing on Runway 18 if the tower reports the wind as 220 degrees at 30 kts?

A

19 kts

29
Q

(Refer to Fg 36 on Pg 224) What is the headwind component for a landing on Runway 18 if the tower reports the wind as 220 degrees at 30 knots?

A

23 Knots

30
Q

(Refer to Fg 36 on Pg 224) Determine the maximum wind velocity for a 45 degrees crosswind if the maximum crosswind component for the airplane is 25 knots.

A

35 Knots

31
Q

(Refer to Fg 36 on Pg 224) With a reported wind if north at 20 knits, which runway is acceptable for use of an airplane with a 13-knot maximum crosswind component?

A

Runway 32

32
Q

(Refer to Fg 36 on Pg 224) What is the maximum wind velocity for a 30 degree crosswind if the maximum crosswind component for the airplane is 12knots?

A

24 Knots

33
Q

(Refer to Fg 36 on Pg 224) 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 14

34
Q

(Refer to Fg 37 on Pg 226) Determine the total distance required to land
OAT = Std
Pressure Altitude = 10,000 ft
Weight = 2,300lb
Wind Component = Calm
Obstacle = 50 ft

A

1,925 feet

35
Q

(Refer to Fg 36 on Pg 224) Determine the approximate total distance required to land over a 50-ft. obstacle
OAT = 90 degrees F
Pressure Altitude = 4,000 ft
Weight = 2,800 lb
Headwind Component = 10 kts

A

1,775 feet

36
Q

(Refer to Fg 36 on Pg 224) Determine the total distance required to land
OAT = 90 degrees F
Pressure Altitude = 3,000 ft
Weight = 2,900lb
Headwind Component = 10 kts
Obstacle = 50 ft

A

1,725 feet

37
Q

(Refer to Fg 36 on Pg 224) Determine the total distance required land
OAT = 32 degrees F
Pressure Altitude = 8,000 ft
Weight = 2,600 lb
Headwind Component = 20 kts
Obstacle = 50 ft

A

1,750 feet

38
Q

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

A

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

39
Q

(Refer to Fg 38 on Pg 229) Determine the approximate landing ground roll distance.
Pressure Altitude = Sea level
Headwind = 4 kts
Temperature = Std

A

401 feet

40
Q

(Refer to Fg 38 on Pg 229) Determine the total distance required to land over a 50-ft. obstacle.
Pressure Altitude = 3,750 ft
Headwind = 12 kts
Temperature = Std

A

816 feet

41
Q

(Refer to Fg 38 on Pg 229) Determine the approximate landing ground roll distance.
Pressure Altitude = 5,000 ft
Headwind = Calm
Temperature = 101 degrees F

A

545 feet

42
Q

(Refer to Fg 38 on Pg 229) Determine the approximate landing ground roll distance.
Pressure Altitude = 1,250 ft
Headwind = 8 kts
Temperature = Std

A

366 feet

43
Q

(Refer to Fg 38 on Pg 229) Determine the total distance required to land over a 50-foot obstacle.
Pressure Altitude = 5,000 ft
Headwind = 8 kts
Temperature = 41 degrees F
Runway = Hard Surface

A

956 feet

44
Q

(Refer to Fg 38 on Pg 229) Determine the total distance required to land over a 50-foot obstacle.
Pressure Altitude = 7,500 ft
Headwind = 8 kts
Temperature = 32 degrees F
Runway = Hard Surface

A

1,004 feet

45
Q

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

A

Unusable fuel and undeniable oil

46
Q

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

18.4 gallons

47
Q

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

15 gallons

48
Q

Question 568 from textbook

A

Page 230

49
Q

Question 569 from textbook

A

On Page 230

Knowledge Test Prep (16 decks)

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