CFI Airplane Performance

Question 1 of 64

1. Question

Density altitude increases with

an increase in temperature only.
increases in pressure, temperature, and moisture content of the air.
increases in temperature and moisture content of the air, and a decrease in pressure.

Question 2 of 64

2. Question

What would increase the density altitude at a given airport?

An increase in air temperature
A decrease in relative humidity.
An increase in atmospheric pressure.

Question 3 of 64

3. Question

As altitude increases, the indicated airspeed at which a given airplane stalls in a particular configuration will

remain the same as at low altitude.
decrease as the true airspeed increases.
increase because the air density decreases.

Question 4 of 64

4. Question

An altimeter indicates 1,850 feet MSL when set to 30.18. What is the approximate pressure altitude?

1,590 feet.
1,824 feet.
2,110 feet.

Question 5 of 64

5. Question

Refer to the diagram below. Determine the density altitude.

Airport elevation 5,515 ft.
OAT 30°c
Altimeter setting 29.40″ Hg

6,000 feet.
8,450 feet.
9,100 feet.

Question 6 of 64

6. Question

Refer to the diagram below. Determine the density altitude.

Airport elevation 3,795 ft
OAT 24°c
Altimeter setting 29.70″ Hg

5,700 feet.
5,900 feet.
4,000 feet.

Question 7 of 64

7. Question

Refer to the diagram below. Determine the density altitude.
Airport elevation 3,450 feet
OAT 35 degrees C
Altimeter setting 30.40″ Hg

3,400 feet.
6,650 feet
5,950 feet.

Question 8 of 64

8. Question

Refer to the diagram below. 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?

900-foot increase.
1,100-foot decrease.
1,300-foot increase.

Question 9 of 64

9. Question

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

3,527 feet MSL.
3,556 feet MSL.
3,639 feet MSL.

Question 10 of 64

10. Question

What is pressure altitude?

The indicated altitude corrected for position and installation error.
The altitude indicated when the barometric pressure scale is set to 29.92.
The indicated altitude corrected for nonstandard temperature and pressure

Question 11 of 64

11. Question

Under what condition is indicated altitude the same as true altitude?

If the altimeter has no mechanical error.
When at sea level under standard conditions.
When at 18,000 feet MSL with the altimeter set at 29.92.

Question 12 of 64

12. Question

What is true altitude?

The vertical distance of the aircraft above sea level.
The vertical distance of the aircraft above the surface.
The height above the standard datum plane.

Question 13 of 64

13. Question

What is absolute altitude?

The altitude read directly from the altimeter.
The vertical distance of the aircraft above the surface.
The height above the standard datum plane.

Question 14 of 64

14. Question

Density altitude may be determined by correcting

true altitude for nonstandard temperature.
pressure altitude for nonstandard temperature.
indicated altitude for temperature variations.

Question 15 of 64

15. Question

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

Efficiency is increased due to less friction on the propeller blades.
Efficiency is reduced because the propeller exerts less force at high density altitudes than at low density altitudes.
Efficiency is reduced due to the increased force of the propeller in the thinner air

Question 16 of 64

16. Question

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

Low temperature, low relative humidity, and low density altitude.
High temperature, low relative humidity, and low density altitude.
High temperature, high relative humidity, and high density altitude.

Question 17 of 64

17. Question

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

equal to pressure altitude.
lower than pressure altitude.
higher than pressure altitude.

Question 18 of 64

18. Question

What effect does high density altitude have on aircraft performance?

It increases engine performance.
It reduces climb performance.
It increases takeoff performance.

Question 19 of 64

19. Question

If the atmospheric pressure and temperature remain the same, how would an increase in humidity affect takeoff performance?

Longer takeoff distance; the air is more dense.
Longer takeoff distance; the air is less dense.
Shorter takeoff distance; the air is more dense.

Question 20 of 64

20. Question

Which statement is true regarding takeoff performance with high density altitude conditions?

The acceleration rate will increase since the lighter air creates less drag.
The acceleration rate is slower because the engine and propeller efficiency is reduced.
A higher-than-normal indicated airspeed is required to produce sufficient lift since the air is less dense.

Question 21 of 64

21. Question

Refer to the diagram below. Determine the ground roll required for takeoff.

Temperature 24 degrees C
Pressure altitude 2,500 feet
Weight 2,400 lb.
Headwind 25 kts.

256 feet.
370 feet.
230 feet.

Question 22 of 64

22. Question

Refer to the diagram below. Determine the ground roll required for takeoff.
Temperature 25 degrees C
Pressure Altitude    2,000 ft.
Weight    2,200 lb.
Headwind    15 knots

205 feet.
261 feet.
237 feet.

Question 23 of 64

23. Question

Refer to the diagram below. Determine the takeoff distance required to clear a 50-foot obstacle.

754 feet.
718 feet.
653 feet.

Question 24 of 64

24. Question

Refer to the diagram below. Determine the takeoff distance required to clear a 50-foot obstacle.
Temperature    3 degrees C
Pressure Altitude 6,000 ft.
Weight    3,000 lb.
Headwind    15 knots

1,464 feet.
1,215 feet.
1,331 feet.

Question 25 of 64

25. Question

How does increased weight affect the takeoff distance of an airplane?

The airplane will accelerate more slowly with the same power output, but the same airspeed is required to generate necessary lift for takeoff.
The airplane will accelerate more slowly with the same power output, and a higher airspeed is required to generate necessary lift for takeoff.
Every airplane has the same acceleration factor with the same power output, but a higher airspeed is needed to overcome the increased ground effect.

Question 26 of 64

26. Question

What effect does an uphill runway slope have upon takeoff performance?

Decreases takeoff speed.
Increases takeoff distance.
Decreases takeoff distance

Question 27 of 64

27. Question

When density altitude is beyond capability as indicated on the performance chart,

interpolate the data and attempt takeoff.
extrapolate the data and attempt takeoff.
do not attempt takeoff until conditions permit calculations to provide the data to determine a safe takeoff and climb out.

Question 28 of 64

28. Question

Refer to the diagram below. Determine the approximate total distance required to clear a 50-foot obstacle.

Temperature    20 degrees C
Pressure altitude 1,000 ft.
Surface sod
Weight    5,300 lb.
Wind    15 kts. headwind

1,724 feet.
1,816 feet.
2,061 feet.

Question 29 of 64

29. Question

Refer to the diagram below. Determine the approximate total distance required to clear a 50-foot obstacle.
Temperature 35 degrees C
Pressure altitude 3,000 ft.
Surface sod
Weight 5,100 lb.
Wind 20 kts. headwind

1,969 feet.
2,023 feet.
2,289 feet.

Question 30 of 64

30. Question

Refer to the diagram below. Determine the approximate total distance required to clear a 50-foot obstacle.

Temperature 25 degrees C
Pressure altitude 2,500 ft.
Surface asphalt
Weight 5,500 lb.
Wind 2 kts. tailwind

2,228 feet.
2,294 feet.
2,462 feet.

Question 31 of 64

31. Question

Refer to the diagram below.. The indicated airspeed that would give the greatest gain in altitude in a unit of time at 3,200 feet is determined to be

93 KIAS.
94 KIAS.
112 KIAS.

Question 32 of 64

32. Question

Refer to the diagram below. What indicated airspeed at 3,000 feet would result in the greatest increase in altitude for a given distance?

94 KIAS.
113 KIAS.
115 KIAS.

Question 33 of 64

33. Question

Refer to the diagram below. To maintain the best rate of climb, the indicated speed should be

maintained at a constant value during the climb.
adjusted to maintain the specified rate of climb.
reduced approximately .8 knots per 1,000 of altitude.

Question 34 of 64

34. Question

An aircraft is flying at a constant power setting and constant indicated altitude. If the outside air temperature (OAT) decreases, true airspeed will

decrease and true altitude will decrease.
increase and true altitude will increase.
increase and true altitude will decrease.

Question 35 of 64

35. Question

An aircraft is flying at a constant power setting and constant indicated altitude. If the outside air temperature (OAT) increases, true airspeed will

increase and true altitude will decrease.
increase and true altitude will increase.
decrease and true altitude will increase.

Question 36 of 64

36. Question

As density altitude increases, which will occur if a constant indicated airspeed is maintained in a no-wind condition?

True airspeed increases; groundspeed decreases.
True airspeed decreases; groundspeed decreases.
!rue airspeed increases; groundspeed increases.

Question 37 of 64

37. Question

In a propeller-driven airplane, maximum range occurs at

minimum drag required.
minimum power required.
maximum lift/drag ratio.

Question 38 of 64

38. Question

The critical engine on most light multiengine airplanes with clockwise rotating propellers is the

left engine, because of the P-factor of the left propeller.
right engine, because of the P-factor of the left propeller.
left engine, because of the P-factor of the right propeller.

Question 39 of 64

39. Question

On a multiengine airplane with engines which rotate clockwise, the critical engine is the

left engine, because the right engine center of thrust is closer to the centerline of the fuselage.
right engine, because the left engine center of thrust is closer to the centerline of the fuselage.
left engine, because the right engine enter of thrust is farther away from the centerline of the fuselage.

Question 40 of 64

40. Question

What is the significance of the blue radial line on the airspeed indicator of a light multiengine airplane and when is it to be used? It indicates the

minimum speed at which the airplane is controllable when the critical engine is suddenly made inoperative and should be used at all altitudes when an engine is inoperative.
speed which will provide the maximum alltitude gain in a given time when one engine is inoperative and should be used for climb and final approach during engine-out operations.
speed which will provide the greatest height for a given distance of forward travel when one engine is inoperative and should be used for all climbs during engine-out operations.

Question 41 of 64

41. Question

On a multiengine airplane, where the propellers rotate in the same direction, why is the loss of power on one engine more critical than the loss of power on the other engine?

The corkscrew pattern of airflow from one propeller is less effective against the airflow from the critical engine.
The torque reaction from operation of the critical engine is more severe around the vertical axis as well as the longitudinal axis.
The asymmetric propeller thrust or P-factor results in the center of thrust from one engine being farther from the airplane centerline than the center of thrust from the other engine.

Question 42 of 64

42. Question

For an airplane with reciprocating, nonturbo charged engines, VMc

decreases with altitude.
increases with altitude.
is not affected by altitude.

Question 43 of 64

43. Question

When one engine fails on a twin-engine airplane, the resulting performance loss

may reduce the rate of climb by 80 percent or more.
reduces cruise indicated airspeed by 50 percent or more.
is approximately 50 percent since 50 percent of the normally available thrust is lost.

Question 44 of 64

44. Question

Which is true regarding the operation of a multiengine airplane with one engine inoperative?

Banking toward the operating engine increases VMC·
Banking toward the inoperative engine increases VMc·
VMc is a designed performance factor which must be proven during type certification and will not change as long as the ball is centered with appropriate rudder pressure.

Question 45 of 64

45. Question

In a twin-engine airplane, the single-engine service ceiling is the maximum density altitude at which VvsE will produce

50 feet per minute rate of climb.
100 feet per minute rate of climb
500 feet per minute rate of climb

Question 46 of 64

46. Question

When operating a light multiengine airplane at VMc, the pilot should expect performance to be sufficient to maintain

heading.
heading and altitude.
heading, altitude, and be able to climb at 50 feet per minute.

Question 47 of 64

47. Question

Which condition causes VMc to be the highest?

CG is at the most forward allowable position.
CG is at the most rearward allowable position.
Gross weight is at the maximum allowable value.

Question 48 of 64

48. Question

Refer to the diagram below. What is the approximate glide distance?

Height above terrain 7,500 ft.
Headwind 30 knots

11.5 miles.
16.5 miles.
21.5 miles.

Question 49 of 64

49. Question

Refer to the diagram below. What is the approximate glide distance?

Height above terrain 10,500 feet
Tailwind 20 knots

24 miles.
26 miles.
28 miles.

Question 50 of 64

50. Question

Refer to the diagram below. What is the approximate glide distance?

Height above terrain 5,500 feet
Tailwind 10 knots

11 miles.
12 miles.
13 miles.

Question 51 of 64

51. Question

Refer to the diagram below. What would be the indicated stall speed in a 60° banked turn with the gear and flaps up?

110 KIAS.
117 KIAS.
121 KIAS

Question 52 of 64

52. Question

Refer to the diagram below. What would be the indicated stall speed in a 30° banked turn with the gear down and flaps set at 15°?

77 KIAS.
82 KIAS.
88 KIAS.

Question 53 of 64

53. Question

Refer to the diagram below. What would be the indicated stall speed during a 40° banked turn with the gear down and flaps set at 45°?

81 KIAS.
83 KIAS.
89 KIAS.

Question 54 of 64

54. Question

What can a pilot expect when landing at an airport located in the mountains?

Higher true airspeed and longer landing distance.
Higher indicated airspeed and shorter landing distance.
Lower true airspeed and longer landing distance.

Question 55 of 64

55. Question

Refer to the diagram below. What is the total landing distance over a 50-foot obstacle?

Temperature                                     15 degrees C
Pressure altitude                            4,000 feet
Weight                                                 3,000 pounds
Headwind                                           22 knots

1,250 feet.
1,175 feet.
1,050 feet.

Question 56 of 64

56. Question

Refer to the diagram below. Determine the approximate groundroll.

Temperature                      33 degrees C
Pressure altitude             6,000 feet
Weight                                  2.800 pounds
Headwind                             14 knots

742 feet.
1,200 feet.
1,400 feet.

Question 57 of 64

57. Question

Refer to the diagram below. What is the total landing distance over a 50-foot obstacle?

Temperature                                  35 degrees
Pressure altitude                          2,000 feet
Weight                                               3,400 pounds
Headwind                                          10 knots

1,650 feet.
1,575 feet.
1,475 feet.

Question 58 of 64

58. Question

Refer to the diagram below. Determine the approximate crosswind component.

Landing Rwy 30
Wind 020 degrees at 15 knots

4 knots.
15 knots.
22 knots.

Question 59 of 64

59. Question

Refer to the diagram below. Determine the approximate crosswind component.

Landing Rwy 03
Wind 060 degrees at 35 knots

12 knots.
18 knots.
22 knots.

Question 60 of 64

60. Question

Refer to the diagram below. What is the crosswind component for a landing on Runway 18 if the tower reports the wind as 220 degrees at 25 knots?

16 knots.
19 knots.
22 knots.

Question 61 of 64

61. Question

Refer to the diagram below. Determine the approximate crosswind component.

Landing Rwy 22
Wind 260 degrees at 23 knots

10 knots.
15 knots.
17 knots.

Question 62 of 64

62. Question

Refer to the diagram below. Using a maximum demonstrated crosswind component equal to 0.2 Vso , what is a pilot able to determine?

Vso                                                    70 knots
Landing Rwy                                 35
Wind                                                300 degrees at 20 knots

Headwind component is excessive.
Headwind component exceeds the crosswind component.
Maximum demonstrated crosswind component is exceeded.

Question 63 of 64

63. Question

Refer to the diagram below. Using a maximum demonstrated crosswind component equal to 0.2 Vso , what is a pilot able to determine?

Vso                                                60 knots
Landing Rwy                             12
Wind                                             150 degrees at 20 knots

Headwind component exceeds recommended limits.
Crosswind component is within safe limits.
Maximum demonstrated crosswind component is exceeded

Question 64 of 64

64. Question

Refer to the diagram below. Using a maximum demonstrated crosswind component equal to 0.2 Vso , what is a pilot able to determine?

Vso                                          65 knots
Landing Rwy                       17
Wind                                       200 degrees at 30 knots

Crosswind component is within safe limits.
Crosswind component exceeds the headwind component.
Maximum demonstrated crosswind component is exceeded.