Gleim Chapter 1
15. The term "angle of attack" is defined as the angle between the A. chord line of the wing and the relative wind. B. airplane's longitudinal axis and that of the air striking the airfoil. C. airplane's center line and the relative wind.
A
20. During a spin to the left, which wing(s) is/are stalled? A. Both wings are stalled. B. Neither wing is stalled. C. Only the left wing is stalled.
A
21. What is ground effect? A. The result of the interference of the surface of the Earth with the airflow patterns about an airplane. B. The result of an alteration in airflow patterns increasing induced drag about the wings of an airplane. C. The result of the disruption of the airflow patterns about the wings of an airplane to the point where the wings will no longer support the airplane in flight.
A
22. Floating caused by the phenomenon of ground effect will be most realized during an approach to land when at A. less than the length of the wingspan above the surface. B. twice the length of the wingspan above the surface. C. a higher-than-normal angle of attack.
A
26. What force makes an airplane turn? A. The horizontal component of lift. B. The vertical component of lift. C. Centrifugal force.
A
27. What determines the longitudinal stability of an airplane? A. The location of the CG with respect to the center of lift. B. The effectiveness of the horizontal stabilizer, rudder, and rudder trim tab. C. The relationship of thrust and lift to weight and drag.
A
32. What is the effect of advancing the throttle in flight? A. Both aircraft groundspeed and angle of attack will increase. B. Airspeed will remain relatively constant but the aircraft will climb. C. The aircraft will accelerate, which will cause a turn to the right.
A
33. Loading an airplane to the most aft CG will cause the airplane to be A. less stable at all speeds. B. less stable at slow speeds, but more stable at high speeds. C. less stable at high speeds, but more stable at low speeds.
A
35. In what flight condition are torque effects more pronounced in a single-engine airplane? A. Low airspeed, high power, high angle of attack. B. Low airspeed, low power, low angle of attack. C. High airspeed, high power, high angle of attack.
A
43. During an approach to a stall, an increased load factor will cause the aircraft to A. stall at a higher airspeed B. have a tendency to spin C. be more difficult to control
A
46. (Refer to Figure 72 below.) A positive load factor of 2 at 80 mph would cause the airplane to A. stall. B. break apart. C. operate normally, as it is within the normal operating range.
A
The four forces acting on an airplane in flight are A. lift, weight, thrust, and drag. B. lift, weight, gravity, and thrust C. lift, gravity, power, and friction
A
Trim systems are designed to do what? A. They relieve the pilot of the need to maintain constant pressure on the flight controls. B. They are used during a Cochin Landing to increase wing lift. C. They move in the opposite direction from one another to control rule.
A
What is one purpose of wing flaps? A. To enable the pilot to make steeper approaches to a landing without increasing airspeed. B. To relieve the pilot of maintaining continuous pressure on the controls. C. To decrease wing the area to vary the lift.
A
What is the purpose of the rudder on an airplane? A. To control yaw. B. To control overbanking tendency. C. To control roll.
A
What is the relationship of lift, drag, thrust, and weight when the airplane is in straight and level fight? A. Lift equals weight and thrust equals drag. B. Lift, drag, and weight equal thrust. C. Lift and weight equal thrust and drag.
A
When are the four forces that act on a airplane in equilibrium? A. During unaccelerated level flight. B. When the aircraft is accelerating. C. When the aircraft is at rest on the ground.
A
Which device is a secondary flight control? A. Spoilers B. Ailerons C. Stabilators
A
Which is not a primary flight control surface? A. Flaps B. Sabilator C. Ailerons
A
Which statement is true concerning primary flight controls? A. The effectiveness of each control surface increases with speed because there is more airflow over them. B. Only when all three primary flight controls move in sequence do the air flow and pressure distribution change over and around the airfoil. C. Primary flight controls include ailerons, rudder, elevator, and trim systems.
A
(Refer to Figure 1 below.) The acute angle A is the angle of A. incidence. B. attack. C. dihedral.
B
16. The angle between the chord line of an airfoil A. lift. B. attack. C. incidence.
B
23) What must a pilot be aware of as a result of ground effect? A. Wingtip vortices increase creating wake turbulence problems for arriving and departing aircraft. B. Induced drag decreases; therefore, any excess speed at the point of flare may cause considerable floating. C. A full stall landing will require less up elevator deflection than would a full stall when done free of ground effect.
B
24 An aircraft leaving ground effect during takeoff A. experience a reduction in ground friction and require a slight power reduction. B. experience an increase in induced drag and a decrease in performance. C. require a lower angle of attack to maintain the same lift coefficient.
B
25. Ground effect is most likely to result in which problem? A. Settling to the surface abruptly during landing. B. Becoming airborne before reaching recommended takeoff speed. C. Inability to get airborne even though airspeed is sufficient for normal takeoff needs.
B
28. An airplane said to be inherently stable will A. be difficult to stall. B. require less effort to control. C. not spin.
B
30. An airplane has been loaded in such a manner that the CG is located aft of the aft CG limit. One undesirable flight characteristic a pilot might experience with this airplane would be A. a longer takeoff run. B. difficulty in recovering from a stalled condition. C. stalling at higher-than-normal airspeed.
B
31. What causes an airplane (except a T-tail) to pitch nosedown when power is reduced and controls are not adjusted? A. The CG shifts forward when thrust and drag are reduced. B. The downwash on the elevators from the propeller slipstream is reduced and elevator effectiveness is reduced. C. When thrust is reduced to less than weight, lift is also reduced and the wings can no longer support the weight.
B
36, The left turning tendency of an airplane caused by P-factor is the result of the A. clockwise rotation of the engine and the propeller turning the airplane counterclockwise. B. propeller blade descending on the right, producing more thrust than the ascending blade on the left. C. gyroscopic forces applied to the rotating propeller blades acting 90° in advance of the point the force was applied.
B
37. When does P-factor cause the airplane to yaw to the left? A. When at low angles of attack. B. When at high angles of attack. C. When at high airspeeds.
B
38. Which basic flight maneuver increases the load factor on an airplane as compared to straight-and- level flight? A. Climbs. B. Turns. C. Stalls.
B
41. (Refer to Figure 2 below.) If an airplane weighs 4,500 pounds, what approximate weight would the airplane structure be required to support during a 45° banked turn while maintaining altitude? A. 4,500 pounds. B. 6,750 pounds. C. 7,200 pounds.
B
42. The amount of excess load that can be imposed on the wing of an airplane depends upon the A. position of the CG. B. speed of the airplane. C. abruptness at which the load is applied.
B
48, (Refer to Figure 72 below.) The airspeed indicated by points A and J is A. maximum structural cruising speed. B. normal stall speed. C. maneuvering speed.
B
The elevator controls movement around which axis? A. Longitudinal. B. Lateral. C. Vertical.
B
Which of the following is true concerning flaps? A. Apps are attached to the Leading Edge of the wing and are used to increase lift. B. Allow an increase in the angle of descent without increasing airspeed. C. Flaps are a high drag devices deployed from the wings to reduce lift.
B
17. The angle of attack at which an airplane wing stalls will A. increase if the CG is moved forward. B. change with an increase in gross weight. C. remain the same regardless of gross wei
C
18. As altitude increases, the indicated airspeed at which a given airplane stalls in a particular configuration will A. decrease as the true airspeed decreases. B. decrease as the true airspeed increases. C. remain the same regardless of altitude.
C
19. In what flight condition must an aircraft be placed in order to spin? A. Partially stalled with one wing low. B. In a steep diving spiral. C. Stalled.
C
29, Changes in the center of pressure of a wing affect the aircraft's A. lift/drag ratio. B. lifting capacity. C. aerodynamic balance and controllability.
C
34. An airplane loaded with the Center of Gravity (CG) rear of the aft CG limit could A. make it easier to recover from stalls and spins. B. make it more difficult to flare for landing. C. increase the likelihood of inadvertent overstress.
C
39. (Refer to Figure 2 below.) If an airplane weighs 3,300 pounds, what approximate weight would the airplane structure be required to support during a 30° banked turn while maintaining altitude? A. 1,200 pounds. B. 3,100 pounds. C. 3,960 pounds.
C
40. (Refer to Figure 2 below.) If an airplane weighs 2,300 pounds, what approximate weight would the airplane structure be required to support during a 60° banked turn while maintaining altitude? A. 2,300 pounds. B. 3,400 pounds. C. 4,600 pounds.
C
44. Structural damage or failure is more likely to occur in smooth air at speeds above A. VNO• B. VA• C. VNE•
C
45. Limit load factor is the ratio of A. angle of attack to stall speed. B. angle of attack to power-on configuration- specific stall speed. C. maximum sustainable load to the gross weight of the airplane.
C
47. (Refer to Figure 72 below.) What load factor would be created if positive 15 feet per second gusts were encountered at 120 mph? A. 2.8 B. 3.0 C. 2.0
C
One of the main functions of flaps during approach and landing is to A. Decrease the angle of descent without increasing the airspeed. B. Permit a touchdown at a higher indicated airspeed. C. Increase the angle of descent without increasing the airspeed.
C
Which statement relates to Bernoulli's principle? A. For every action, there is an equal and opposite reaction. B. An additional upward force is generated as the lower surface of the wing deflects air downward. C. Air traveling faster over the curved upper surface of an airfoil causes lower pressure on
C
