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66 Cards in this Set
- Front
- Back
One of the main functions of flaps during the approach and landing is to
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provide the same amount of lift at a slower airspeed
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Which is true regarding the use of flaps during level turns
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the raising of flaps increases the stall speed
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A rectangular wing, as compared to other wing planforms, has a tendency to stall first at the
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wing root, with the stall progression toward the wingtip
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The angle of attack of a wing directly controls the
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distribution of pressure acting on the wing
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Frost covering the upper surface of an airplane wing usually will cause
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the airplane to stall at an angle of attack that is lower than normal
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By changing the angle of attack of a wing, the pilot can control the airplane's
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lift, airspeed, and drag
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The critical angle of attack is exceeded when
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a stall occurs
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The angle of attack at which a wing stalls remains constant regardless of
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weight, dynamic pressure, bank angle, or pitch attitude
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the need to slow an aircraft below Va is brought about by following weather phenomenon
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turbulence which causes an increase in stall speed
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Stall speed is affected by
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weight, load factor, and power
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An airplane will stall at the same
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angle of attack regardless of the attitude with relation to the horizon
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In rapid recovery from a dive, the effects of load factor would cause the stall speed to
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increase
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The stalling speed of an airplane is most affected by
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variations in airplane loading
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(Refer to figure 2 below) Select the correct statement regarding stall speeds
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power-on stalls occur at lower airspeeds in shallower banks
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(Refer to figure 2) Select the correct statement regarding stall speeds. The airplane will stall
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10 knots higher in a power-on, 60' bank, with gear and flaps up, than with gear and flaps down
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Recovery from a stall in any airplane becomes more difficult when its
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center of gravity moves aft
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In small airplanes, normal recovery from spins may become difficult if the
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CG is too far rearward, and rotation is around the CG
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Which statement is true relative to changing angle of attack
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an increase in angle of attack will increase drag
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To generate the same amount of lift as altitude is increased, an airplane must be flown at
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a higher true airspeed for any given angle of attack
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As angle of bank is increased, the vertical component of lift
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decreases and the horizontal component of lift increases
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Which is true regarding the forces acting on an aircraft in a steady-state descent? the sum of all
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forward forces is equal to the sum of all rearward forces
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during the transition from straight-and-level flight to a climb, the angle of attack is increased and lift
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is momentarily increased
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What changes in airplane longitudinal control must be made to maintain altitude while the airspeed is being decreased
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increase the angle of attack to compensate for the decreasing lift
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Which is true regarding the force of lift in steady, unaccelerated flight
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There is a corresponding indicated airspeed required for every angle of attack to generate sufficent lift to maintain altitude
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In theory, if the airspeed of an airplane is doubled while in level flight, parasite drag will become
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four times greater
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As airspeed decreases in level flight below that speed for maximum lift/drag ratio, total drag of an airplane
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increases because of increased induced drag
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Which performance is characteristic of flight at maximum lift/drag ratio in a propeller-driven airplane? maximum
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range and maximum distance glide
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In theory, if the angle of attack and other factors remain constant and the airspeed is doubled, the lift produced at the higher speed will be
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four times greater than at the lower speed
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An aircraft wing is designed to produce lift resulting from a difference in the
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higher air pressure below the wing's surface and lower air pressure above the wing's surface
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(Refer to figure 3 on page 33) if an airplane glides at an angle of attack of 10', how much altitude will it lose in 1 mile
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480 mile
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(Refer to figure 3 below) how much altitude will this airplane lose in 3 statute miles of gliding at an angle of attack of 8'?
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1,320 feet
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(refer ti figure 3 above) The L/D ratio at a 2' angle of attack is approximately the same as the L/D ratio for a
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16.5' angle of attack
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Lift on a wing is most properly defined as the
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force acting perpendicular to the relative wind
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(Refer to figure 1 above) At an airspeed represented by point B, in steady flight, the pilot can expect to obtain the airplane's maximum
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glide range
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(Refer to figure 1 above) at the airspeed represented by point A, in steady flight, the airplane will
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have its maximum L/D ratio
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On a wing, the force of lift acts perpendicular to and the force of drag acts parallel to the
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flightpath
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Which statement is true regarding the opposing forces acting on an airplane in steady-state level flight?
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these forces are equal
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An airplane leaving ground effect will
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experience an increase in induced drag and require more thrust
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To produce the same lift while in ground effect as when out of ground effect, the airplane requires
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a lower angle of attack
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If the same angle of attack is maintained in ground effect as when out of ground effect, lift will
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increase, and induced drag will decrease
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Longitudinal stability involves the motion of the airplane controlled by its
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elevator
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Longitudinal dynamic instability in an airplane can be identified by
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pitch oscillations becoming progressively steeper
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If the airplane attitude remains in a new position after the elevator control is pressed forward and released, the airplane displays
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neutral longitudinal static stability
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If the airplane attitude initially tends to return to its original position after the elevator control is pressed forward and released, the airplane displays
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positive static stability
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If an airplane is loaded to the rear of its CG range, it will tend to be unstable about its
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lateral axis
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If airspeed is increased during a level turn, what action would be necessary to maintain altitude? the angle of attack
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must be decreased or angle of bank increased
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If a standard rate turn is maintained, how long would it take to turn 360'
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2 minutes
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While holding the angle of bank constant in a level turn, if the rate of turn is varied the load factor would
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remain constant regardless of air density and the resultant lift vector
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To increase the rate of turn and at the same time decrease the radius, a pilot should
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Increase the bank and decrease airspeed
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Which is correct with respect to rate and radius of turn for an airplane flown in a coordinated turn at a constant altitude?
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for a specific angle of bank and airspeed, the rate and radius of turn will not vary
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While maintaining a constant angle of bank and altitude in a coordinated turn, an increase in airspeed will
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decrease the rate of turn resulting in no change in load factor
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Why is it necessary to increase back elevator pressure to maintain altitude during a turn? to compensate for the
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loss of the vertical component of lift
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To maintain altitude during a turn, the angle of attack must be increased to compensate for the decrease in the
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vertical component of lift
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The ratio between the total airload imposed on the wing and the gross weight of an aircraft in flgiht is known as
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load factor and directly affects stall speed
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Load factor is the lift generated by the wings of an aircraft at any given time
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divided by the total weight of the aircraft
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For a given angle of bank, in any airplane, the load factor imposed in a coordinated constant-altitude turn
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is constant and the stall speed increases
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Airplane wing loading during a level coordinated turn in smooth air depends upon the
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angle of bank
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(Refer to figure 4 below) What increases in load factor would take place if the angle of bank were increased from 60' to 80'
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4 G's
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(Refer to figure 4 below) What is the stall speed of an airplane under a load factor of 2 G's if the unaccelerated stall speed is 60 knots
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84 knots
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If an aircraft with a gross weight of 2,000 pounds was subjected to a 60' constant-altitude bank, the total load would be
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4,000 pounds
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If the airspeed is increase from 90 knots to 135 knots during a level 60' banked turn, the load factor will
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remain the same but the radius of turn will increase
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Baggage weighting 90 knots 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 G's, the total load of baggage would be
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315 pounds and would not be excessive
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Which factor below is the best indication of positive or negative G's in an aircraft
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change in how heavy or light you feel in your seat
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Transonic airflow typically occurs in airplane speed regimes between Mach
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0.75 and 1.20
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Accelerating past critical Mach may result in the onset of compressibility effects such as
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control difficulties
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Acceleration past critical Mach speed may cause compressibility issues such as
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drag increases
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