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A detailed illustration of an airplane in flight, showcasing various aerodynamic principles and flight performance factors, with a blue sky background and cloud effects.

Flight Performance Proficiency Quiz

Test your knowledge of flight performance principles with our comprehensive quiz designed for aviation enthusiasts and professionals alike. Covering various topics related to aerodynamics, stability, and aircraft control, this quiz will challenge your understanding and enhance your skills.

Get ready to explore:

Multiple choice questions on flight dynamics
Real-world applications and scenarios
Important concepts essential for safe flying

55 Questions14 MinutesCreated by FlyingEagle42

Frost covering the upper surface of an airplane wing usually will cause:

The airplane to stall at an angle of attack that is higher than normal

The airplane to stall at an angle of attack that is lower than normal

Drag factors so large that sufficient speed cannot be obtained for takeoff

In a rapid recovery from a dive, the effects of load factor would cause the stall speed:

Increase

Decrease

Not vary

NoTo generate the same amount of lift as altitude is increased, an airplane must be flown at:t vary

The same true airspeed regardless of angle of attack

A lower true airspeed and a greater angle of attack

A higher true airspeed for any given angle of attack

As the angle of bank is increased, the vertical component of lift:

Decreases and the horizontal component of lift increases

Increases and the horizontal component of lift decreases

Decreases and the horizontal component of lift remains constant

What changes in airplane longitudinal control must be made to maintain altitude while the airspeed is being decreased?

Increase the angle of attack to produce more lift than drag

Increase the angle of attack to compensate for the decreasing lift

Decrease the angle of attack to compensate for the increasing drag

Longitudinal dynamic instability in an airplane can be identified by:

Bank oscillations becoming progressively steeper

Pitch oscillations becoming progressively steeper

Trilatitudinal roll oscillations becoming steeper

If the airplane attitude remains in a new position after the elevator control is pressed forward and released, the airplane displays:

Neutral longitudinal static stability

Positive longitudinal static stability

Neutral longitudinal dynamic stability

If the airplane attitude initially tends to return to its original position after the elevator control is pressed forward and released, the airplane displays:

Positive dynamic stability

Positive static stability

Neutral dynamic stability

If an airplane is loaded to the rear of its CG range, it will tend to be unstable about its:

Vertical axis

Lateral axis

Longitudinal axis

If a standard rate turn is maintained, how long would it take to turn 360°?

1 minute

2 minutes

3 minutes

While holding the angle of bank constant in a level turn, if the rate of turn is varied the load factor would

Remain constant regardless of air density and the resultant lift vector

Vary depending upon speed and air density provided the resultant lift vector varies proportionately

Vary depending upon the resultant lift vector

To increase the rate of turn and at the same time decrease the radius, a pilot should:

Maintain the bank and decrease airspeed

Increase the bank and increase airspeed

Increase the bank and decrease airspeed

Which is correct with respect to rate and radius of turn for an airplane flown in a coordinated turn at a constant altitude?

For a specific angle of bank and airspeed, the rate and radius of turn will not vary

To maintain a steady rate of turn, the angle of bank must be increased as the airspeed is decreased

The faster the true airspeed, the faster the rate and larger the radius of turn regardless of the angle of bank

While maintaining a constant angle of bank and altitude in a coordinated turn, an increase in airspeed will

Decrease the rate of turn resulting in a decreased load factor

Decrease the rate of turn resulting in no change in load factor

Increase the rate of turn resulting in no change in load factor

If an aircraft with a gross weight of 2,000 pounds was subjected to a 60° constant altitude bank, the total load would be:

3,000 pounds

4,000 pounds

12,000 pounds

If the airspeed is increased from 90 knots to 135 knots during a level 60° banked turn, the load factor will

Increase as well as the stall speed

Decrease and the stall speed will increase

Remain the same but the radius of turn will increase

Baggage weighing 90 pounds is placed in a normal category airplane’s baggage compartment which is placarded at 100 pounds. If this airplane is subjected to a positive load factor of 3.5 Gs, the total load of the baggage would be:

315 pounds and would be excessive

315 pounds and would not be excessive

350 pounds and would not be excessive

At high altitudes, an excessively rich mixture will cause the

Engine to overheat

Fouling of spark plugs

Engine to operate smoother even though fuel consumption is increasing

For take-off, the blade angle of a controllable-pitch propeller should be set at a

Small angle of attack and high RPM

Large angle of attack and low RPM

Large angle of attack and high RPM

To establish a climb after takeoff in an aircraft equipped with a constantspeed propeller, the output of the engine is reduced to climb power by decreasing manifold pressure and

Increasing RPM by decreasing propeller blade angle

Decreasing RPM by decreasing propeller blade angle

Decreasing RPM by increasing propeller blade angle

To determine pressure altitude prior to takeoff, the altimeter should be set to:

The current altimeter setting

29.92” Hg and the altimeter indication noted

The field elevation and the pressure reading in the altimeter setting window noted

Pressure altitude …………………………………….. 5,000 ft True air temperature ………………………………… +30°C

7,800 ft

7,200 ft

9,000 ft

If all index units are positive when computing weight and balance, the location of the datum would be at the

Centreline of the main wheels

Nose, or out in front of the airplane

Centreline of the nose or tailwheel, depending on the type of airplane

Weight A – 155 pounds at 45 inches aft of datum Weight B – 165 pounds at 145 inches aft of datum Weight C – 95 pounds at 185 inches aft of datum Based on this information, where would the CG be located aft of datum?

86.0 inches

116.8 inches

125.0 inches

Weight A – 140 pounds at 17 inches aft of datum Weight B – 120 pounds at 110 inches aft of datum Weight C – 85 pounds at 210 inches aft of datum Based on this information, the CG would be located how far aft of datum?

89.11 inches

96.89 inches

106.92 inches

Total weight ……………………………………. 4,137 lbs CG location ……………………………………. Station 67.8 Fuel consumption ………………………………13.7 GPH Fuel CG ………………………………………… Station 68.0 After 1 hour 30 minutes of flight time, the CG would be located at station

67.79

68.79

70.78

An aircraft is loaded with a ramp weight of 3,650 pounds and having a CG of 94.0, approximately how much baggage would have to be moved from the rear baggage area at station 180 to the forward baggage area at station 40 in order to move the CG to 92.0?

52.14 pounds

62.24 pounds

78.14 pounds

Temperature …………………………………. 30°F Pressure altitude …………………………….. 6,000 ft Weight ………………………………………… 3,300 lbs Headwind ……………………………………... 20 kts What is the total takeoff distance over a 50-foot obstacle?

1,100 feet

1,300 feet

1,500 feet

Temperature …………………………………... 50°F Pressure altitude ……………………………… 2,000 ft Weight ………………………………………….. 2,700 lbs Wind ……………………………………………. Calm What is the total takeoff distance over a 50-foot obstacle?

800 feet

650 feet

1,050 feet

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

Increase takeoff speed

Increases takeoff distance

Decreases takeoff distance

Aircraft weight ……………………………….. 4,000 lbs Airport pressure altitude ……………………. 2,000 ft Temperature at 2,000 ft …………………….. 32°C Using a maximum rate of climb under the given conditions, how much time would be required to climb to a pressure altitude of 8,000 feet

7 minutes

8.4 minutes

11.2 minutes

Aircraft weight ………………………………….. 3,400 lbs Airport pressure altitude ………………………. 6,000 ft Temperature at 6,000 ft ……………………….. 10°C Using a maximum rate of climb under the given conditions, how much fuel would be from engine start to a pressure altitude of 16,000 feet?

43 pounds

45 pounds

49 pounds

Weight ………………………………………. 3,400 lb Airport pressure altitude …………………… 4,000 ft Temperature at 4,000 ft …………………….. 14°C Using a normal climb under the given conditions, how much time would be required to climb a pressure altitude of 8,000 feet?

4.8 minutes

5 minutes

5.5 minutes

Airport pressure altitude …………………………….. 2,000 ft Airport temperature ………………………………...... 20°C Cruise pressure altitude ……………………………. . 10,000 ft Cruise temperature …………………………………… 0°C What will be the fuel, time, and distance required to climb to cruise altitude under the given conditions?

5 gallons, 9 minutes, 13 NM

6 gallons, 11 minutes, 16 NM

7 gallons, 12 minutes, 18 NM

Using a normal climb, how much fuel would be used from engine start to 10,000 feet pressure altitude? Aircraft weight ……………………………………….. 3,500 lb Airport pressure altitude ……………………………. 4,000 ft Temperature …………………………………………. 21°C

23 pounds

31 pounds

35 pounds

Using a maximum rate of climb, how much fuel would be used from engine start to 10,000 feet pressure altitude? Weight ……………………………………………. 3,800 lb Airport pressure altitude ……………………….. 4,000 ft Temperature ……………………………………… 30°C

28 pounds

35 pounds

40 pounds

Weight ……………………………………….. 3,700 lb Pressure altitude ……………………………. 22,000 ft Temperature ………………………………… -10°C What is the maximum rate of climb under the given conditions?

305 ft/min

320 ft/min

384 ft/min

What would be the endurance at an altitude of 7,500 feet, using 52 percent power? Note: (With 48 gallons of fuel – no reserve)

6.1 hours

7.7 hours

8.0 hours

What would be the approximate true airspeed and fuel consumption per hour at an altitude of 7,500 feet, using 52 percent power?

103 MPH TAS, 6.3 GPH

105 MPH TAS, 6.6 GPH

105 MPH TAS, 6.2 GPH

Pressure altitude …………………………………… 18,000 ft Temperature ………………………………………… -41°C Power ……………………………………………….. 2,500 RPM -26” MP Recommended lean mixture usable fuel ………………………… 318 lb

2 hours 27 minutes

3 hours 12 minutes

3 hours 42 minutes

Pressure altitude …………………………………....... 18,000 ft Temperature ………………………………………..... -1°C Power ………………………………………………… 2,200 RPM -20” MP Recommended lean mixture usable fuel …………………………… 318 lb What is the approximate flight time available under the given conditions? (Allow for VFR day fuel reserve)

4 hours 50 minutes

5 hours 20 minutes

5 hours 59 minutes

Pressure altitude ……………………………………… 6,000 ft Temperature …………………………………………… -17°C Power …………………………………………………… 2,300 RPM -23” MP Usable fuel available …………………………………… 370 lb What is the maximum available flight time under the conditions stated?

4 hours 20 minutes

4 hours 30 minutes

4 hours 50 minutes

Pressure altitude ……………………………………… 6,000 ft Temperature …………………………………………… +13°C Power …………………………………………………… 2,500 RPM -23” MP Usable fuel available …………………………………… 460 lb What is the maximum available flight time under the conditions stated?

4 hours 58 minutes

5 hours 7 minutes

5 hours 12 minutes

Fuel quantity ……………………………………………… 65 gal Power-cruise (lean) ………………………………………. 55 percent Approximately how much flight time would be available with a night VFR fuel reserve remaining?

3 hours 8 minutes

3 hours 22 minutes

3 hours 43 minutes

Fuel quantity ………………………………………………… 65 gal Best power (level flight) ……………………………………. 55 percent Approximately how much flight time would be available with a day VFR fuel reserve remaining?

4 hours 17 minutes

4 hours 30 minutes

5 hours 4 minutes

(Refer to figure 8) Approximately how much fuel would be consumed when climbing at 75 percent power for 7 minutes?

1.82 gallons

1.97 gallons

2.12 gallons

(Refer to Figure 8) Determine the amount of fuel consumed during takeoff and climb at 70 percent power for 10 minutes

2.66 gallons

2.88 gallons

3.2 gallons

(Refer to Figure 8) With 38 gallons of fuel aboard at cruise power (55 percent), how much flight time is available with night VFR fuel reserve still remaining?

2 hours 34 minutes

2 hours 49 minutes

3 hours 18 minutes

(Refer to Figure 31) Rwy 30 is being used for landing. Which surface wind would exceed the airplane’s crosswind capability of 0.2 VSO, if VSO is 60 knots?

260° at 20 knots

275° at 25 knots

315° at 35 knots

(Refer to Figure 31) The surface wind is 180° at 25 knots. What is the crosswind component for a Rwy 13 landing?

19 knots

21 knots

23 knots

(Refer to Figure 31) What is the headwind component for a Rwy 13 takeoff if the surface wind is 190° at 15 knots?

7 knots

13 knots

15 knots

Temperature ………………………………………… 50°F Pressure altitude ……………………………………. Sea level Weight ………………………………………………… 3,000 lb Headwind ……………………………………………... 10 kts Determine the approximate ground roll

425 feet

636 feet

836 feet

Temperature ………………………………………… 80°F Pressure altitude ……………………………………. 4,000 ft Weight ……………………………………………… 2,800 lb Headwind ……………………………………………... 24 kts What is the total landing distance over a 50-foot obstacle?

1,125 feet

1,250 feet

1,325 feet

Temperature ………………………………………… 70°F Pressure altitude ……………………………………. Sea level Weight ………………………………………………… 3,400 lb Headwind ……………………………………………... 16 kts Determine the approximate ground roll.

689 feet

716 feet

1,275 feet

Temperature ………………………………………… 85°F Pressure altitude ……………………………………. 6,000 ft Weight ………………………………………………… 2,800 lb Headwind ……………………………………………... 14 kts Determine the approximate ground roll.

742 feet

1,280 feet

1,480 feet

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