FPP
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
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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