Term
| The amount of excess load that can be imposed on the wing of an airplane depends on the |
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Definition
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Term
| Bank angles exceeding _____ degrees are prohibited by Doss procedures (not multiple choice |
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Definition
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Term
| The angle between the chord line of an airfoil and the relative wind is known as the angle of |
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Definition
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Term
| During the entry to a right turn, the nose of the aircraft swings slightly to the left before it swings along the horizon to the right. This is a |
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Definition
| slipping entry, caused by adverse yaw; more right rudder pressure should have been applied for the amount of aileron pressure being used |
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Term
| Which basic flight maneuver increases the load factor on an airplane as compared to straight-and-level flight? |
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Definition
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Term
When are the four forces that act on an aircraft in equilibrium? |
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Definition
| during unaccelerated flight |
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Term
| A pitch attitude exceeding _____ degrees from level flight is prohibited by Doss procedures (not multiple choice |
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Definition
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Term
| As altitude increases, the indicated airspeed at which an airplane stalls in the same configuration will |
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Definition
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Term
| What will cause the nose of an aircraft to move in the direction of the turn before the bank starts in a turn entry? |
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Definition
| Rudder being applied to soon |
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Term
| Which of the following best describes “yaw”? |
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Definition
| Control of the airplane about the vertical axis by using the rudder to move the nose right and left relative to the airplane’s flightpath |
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Term
| How will frost on the wings of an airplane affect takeoff performance? |
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Definition
| Frost will disrupt the smooth flow of air over the wing, adversely affecting its lifting capability |
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Term
| Which V-speed represents maneuvering speed? |
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Definition
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Term
| Why is frost considered hazardous to flight? |
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Definition
| Frost spoils the smooth flow of air over the wings, thereby decreasing lifting capability |
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Term
| Which of the following best describes “roll”? |
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Definition
| Control of the airplane about the longitudinal axis by use of the ailerons to attain a desired bank angle in relation to the natural horizon |
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Term
| An aircraft wing is designed to produce lift resulting from |
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Definition
| higher air pressure below the wing’s surface and lower air pressure above the wing’s surface |
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Term
| The airplane is trimmed for straight-and-level unaccelerated flight. The control stick is momentarily pushed forward and then released. If the airplane shows an initial tendency to return to the trimmed angle of attack, what type of stability has been demonstrated? |
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Definition
| positive static longitudinal stability |
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Term
| Which of the following best describes “pitch”? |
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Definition
| control of the airplane about the lateral axis by using the elevator to raise and lower the nose in relation to the natural horizon |
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Term
| When does P-factor cause the airplane to yaw to the left? |
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Definition
| When at high angles of attack |
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Term
| In what flight condition is torque effect the greatest in a single-engine airplane? |
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Definition
| Low airspeed, high power, high angle of attack |
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Term
| How does the wake turbulence vortex circulate around each wingtip? |
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Definition
| Outward, upward, and around each tip |
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Term
| The tendency of an aircraft to develop forces which restore it to its original condition, when disturbed from a condition of steady flight, is known as |
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Definition
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Term
| The amount of excess load that can be imposed on the wing of an airplane depends upon the |
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Definition
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Term
| The greatest vortex strength occurs when the generating aircraft is |
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Definition
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Term
| What important airspeed limitation is not color coded on the airspeed indicator? |
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Definition
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Term
| Which statement about adverse yaw is most correct? |
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Definition
adverse yaw can be seen during aileron deflection, when more lift on the rising wing results in more induced drag on that wing which pulls the nose toward the rising wing |
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Term
| The term “angle of attack” is defined as the angle |
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Definition
| between the wing chord line and the relative wind |
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Term
| The airplane will stall at a higher indicated airspeed when excessive maneuvering loads are imposed by steep turns, pull-ups, or other abrupt changes in its flightpath; this is called |
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Definition
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Term
| With the flaps in the CRUISE position, what is the positive load factor limit for the DA20-C1? (not multiple choice) |
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Definition
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Term
What causes an airplane to stall? |
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Definition
| Exceeding the critical angle of attack |
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Term
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Definition
| The result of the interference of the surface of the Earth with the airflow patterns about the airplane |
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Term
| Loading an airplane to the most aft CG will cause the airplane to be |
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Definition
| less stable at all speeds |
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Term
| What is the purpose of the rudder on an airplane? |
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Definition
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Term
| Which would likely result in a slipping turn? |
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Definition
| increasing the rate of turn without using rudder |
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Term
| During an approach to a stall, an increased load factor will cause the airplane to |
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Definition
| stall at a higher airspeed |
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Term
| Which action will result in an airplane exceeding its critical angle of attack? |
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Definition
| Demanding more Gs than the wing can provide at a given airspeed |
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Term
| What is one purpose of wing flaps? |
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Definition
| To enable the pilot to make steeper approaches to a landing without increasing the airspeed |
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Term
| During a spin to the left, which wing(s) is/are stalled? |
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Definition
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Term
| How does frost affect the lifting surfaces of an airplane on takeoff? |
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Definition
| frost mat prevent the airplane from becoming airborne at normal takeoff speed |
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Term
In what flight condition must an airplane be placed in order to spin? |
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Definition
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Term
| What force makes an airplane turn? |
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Definition
| The horizontal component of lift |
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Term
| The airplane is trimmed for straight-and-level unaccelerated flight. The control stick is momentarily pushed forward and then released. The airplane enters a series of self-damping pitch oscillations and eventually returns to straight-and-level unaccelerated flight at the trimmed angle of attack. What type of stability has been demonstrated? |
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Definition
| Positive static and dynamic stability |
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Term
| The left turning tendency of an airplane caused by P-factor is the result of the |
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Definition
| propeller blade descending on the right, producing more thrust than the ascending blade on the left |
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Term
| . If severe turbulence is encountered, the aircraft’s airspeed should be reduced below |
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Definition
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Term
| The wind condition that requires maximum caution when avoiding wake turbulence on landing is a |
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Definition
| light, quartering tailwind |
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Term
| The four forces acting on an airplane in flight are: |
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Definition
| Lift, weight, thrust and drag |
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Term
| Ground effect is most likely to result in which problem? |
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Definition
| Becoming airborne before reaching recommended takeoff speed |
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Term
| What is the definition of Va? |
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Definition
| The design maneuvering speed |
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Term
| An airplane has been loaded in such a manner that the CG is located aft of the CG limit. One undesirable flight characteristic a pilot might experience with this airplane would be |
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Definition
difficulty in recovering from a stalled condition |
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Term
| Which V-speed represents maneuvering speed? |
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Definition
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Term
| Lift produced by an airfoil is the net force developed perpendicular to the |
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Definition
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Term
The angle of attack at which an airplane wing stalls will |
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Definition
| remain the same regardless of weight. |
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Term
| What is the definition of Vne? |
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Definition
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Term
| What determines the longitudinal stability of an airplane? |
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Definition
| The location of the CG with respect to the center of lift |
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Term
| Which statement relates to Bernoulli’s principle? |
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Definition
| Air traveling faster over the curved upper surface of an airfoil causes lower pressure on the top surface |
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Term
| If an airplane weighs 4,500 pounds, what approximate weight would the airplane structure be required to support during a 45 degree banked turn while maintaining altitude? (chart included) |
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Definition
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Term
| What must a pilot be aware of as a result of ground effect? |
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Definition
| Induced drag decreases; therefore, any excess speed at the point of flare may cause considerable floating |
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Term
| L/D Max, the speed which results in the maximum lift-to-drag ration, is also |
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Definition
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Term
| Floating caused by the phenomenon of ground effect will be most realized during an approach to land when at |
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Definition
| less than the length of the wingspan above the surface |
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Term
| What is the relationship of lift, drag, thrust and weight when the airplane is in straight and level, unaccelerated flight? |
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Definition
lift equals weight and thrust equals drag |
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Term
| Wingtip vortices created by aircraft tend to |
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Definition
| sink below the aircraft generating turbulence |
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Term
| With the flaps in the CRUISE position, what is the negative load factor limit for the DA20-C1? (not multiple choice) |
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Definition
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Term
| What causes an airplane to pitch nosedown when power is reduced and controls are not adjusted? |
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Definition
| The downwash on the elevators from the propeller slipstream is reduced and elevator effectiveness is reduced |
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Term
| A propeller rotating clockwise (as seen from the rear) creates a spiraling slipstream that tends to rotate the airplane to the |
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Definition
| left around the vertical axis |
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Term
| An Airplane said to be inherently stable will |
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Definition
| require less effort to control |
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