Cpl - Flight Performance And Planning
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- 1.Frost covering the upper surface of an airplane wing usually will cause:
- A.
The airplane to stall at an angle of attack that is higher than normal
- B.
The airplane to stall at an angle of attack that is lower than normal
- C.
Drag factors so large that sufficient speed cannot be obtained for takeoff
- 2.In a rapid recovery from a dive, the effects of load factor would cause the stall speed:
- A.
Increase
- B.
Decrease
- C.
Not vary
- 3.To generate the same amount of lift as altitude is increased, an airplane must be flown at:
- A.
The same true airspeed regardless of angle of attack
- B.
A lower true airspeed and a greater angle of attack
- C.
A higher true airspeed for any given angle of attack
- 4.As the angle of bank is increased, the vertical component of lift:
- A.
Decreases and the horizontal component of lift increases
- B.
Increases and the horizontal component of lift decreases
- C.
Decreases and the horizontal component of lift remains constant
- 5.What changes in airplane longitudinal control must be made to maintain altitude while the airspeed is being decreased?
- A.
Increase the angle of attack to produce more lift than drag
- B.
Increase the angle of attack to compensate for the decreasing lift
- C.
Decrease the angle of attack to compensate for the increasing drag
- 6.Longitudinal dynamic instability in an airplane can be identified by:
- A.
Bank oscillations becoming progressively steeper
- B.
Pitch oscillations becoming progressively steeper
- C.
Trilatitudinal roll oscillations becoming steeper
- 7.If the airplane attitude remains in a new position after the elevator control is pressed forward and released, the airplane displays:
- A.
Neutral longitudinal static stability
- B.
Positive longitudinal static stability
- C.
Neutral longitudinal dynamic stability
- 8.If the airplane attitude initially tends to return to its original position after the elevator control is pressed forward and released, the airplane displays:
- A.
Positive dynamic stability
- B.
Positive static stability
- C.
Neutral dynamic stability
- 9.If an airplane is loaded to the rear of its CG range, it will tend to be unstable about its:
- A.
Vertical axis
- B.
Lateral axis
- C.
Longitudinal axis
- 10.If a standard rate turn is maintained, how long would it take to turn 360°?
- A.
1 minute
- B.
2 minutes
- C.
3 minutes
- 11.While holding the angle of bank constant in a level turn, if the rate of turn is varied the load factor would
- A.
Remain constant regardless of air density and the resultant lift vector
- B.
Vary depending upon speed and air density provided the resultant lift vector varies proportionately
- C.
Vary depending upon the resultant lift vector
- 12.To increase the rate of turn and at the same time decrease the radius, a pilot should:
- A.
Maintain the bank and decrease airspeed
- B.
Increase the bank and increase airspeed
- C.
Increase the bank and decrease airspeed
- 13.Which is correct with respect to rate and radius of turn for an airplane flown in a coordinated turn at a constant altitude?
- A.
For a specific angle of bank and airspeed, the rate and radius of turn will not vary
- B.
To maintain a steady rate of turn, the angle of bank must be increased as the airspeed is decreased
- C.
The faster the true airspeed, the faster the rate and larger the radius of turn regardless of the angle of bank
- 14.While maintaining a constant angle of bank and altitude in a coordinated turn, an increase in airspeed will
- A.
Decrease the rate of turn resulting in a decreased load factor
- B.
Decrease the rate of turn resulting in no change in load factor
- C.
Increase the rate of turn resulting in no change in load factor
- 15.If an aircraft with a gross weight of 2,000 pounds was subjected to a 60° constant altitude bank, the total load would be:
- A.
3,000 pounds
- B.
4,000 pounds
- C.
12,000 pounds
- 16.If the airspeed is increased from 90 knots to 135 knots during a level 60° banked turn, the load factor will:
- A.
Increase as well as the stall speed
- B.
Decrease and the stall speed will increase
- C.
Remain the same but the radius of turn will increase
- 17.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:
- A.
315 pounds and would be excessive
- B.
315 pounds and would not be excessive
- C.
350 pounds and would not be excessive
- 18.At high altitudes, an excessively rich mixture will cause the
- A.
Engine to overheat
- B.
Fouling of spark plugs
- C.
Engine to operate smoother even though fuel consumption is increasing
- 19.For take-off, the blade angle of a controllable-pitch propeller should be set at a:
- A.
Small angle of attack and high RPM
- B.
Large angle of attack and low RPM
- C.
Large angle of attack and high RPM
- 20.To establish a climb after takeoff in an aircraft equipped with a constant-speed propeller, the output of the engine is reduced to climb power by decreasing manifold pressure and
- A.
Increasing RPM by decreasing propeller blade angle
- B.
Decreasing RPM by decreasing propeller blade angle
- C.
Decreasing RPM by increasing propeller blade angle
- 21.To determine pressure altitude prior to takeoff, the altimeter should be set to:
- A.
The current altimeter setting
- B.
29.92” Hg and the altimeter indication noted
- C.
The field elevation and the pressure reading in the altimeter setting window noted
- 22.Given: Pressure altitude ............................................ 5,000 ft True air temperature ....................................... +30°C From the conditions given, the approximate density altitude is:
- A.
7,800 ft
- B.
7,200 ft
- C.
9,000 ft
- 23.If all index units are positive when computing weight and balance, the location of the datum would be at the:
- A.
Centerline of the main wheels
- B.
Nose, or out in front of the airplane
- C.
Centerline of the nose or tailwheel, depending on the type of airplane
- 24.Given: 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?
- A.
86.0 inches
- B.
116.8 inches
- C.
125.0 inches
- 25.Given: 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?
- A.
89.11 inches
- B.
96.89 inches
- C.
106.92 inches
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