Private Pilot Written Test Ch. 4

b

203. 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

204. Which basic flight maneuver increases the load factor on an airplane as compared to straight-and-level flight? A. Climbs. B. Turns. C. Stalls.

c

205. 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.

a

206. What is one purpose of wing flaps? A. To enable the pilot to make steeper approaches to a landing without increasing the airspeed. B. To relieve the pilot of maintaining continuous pressure on the controls. C. To decrease wing area to vary the lift.

a

295. What force makes an airplane turn? A. The horizontal component of lift. B. The vertical component of lift. C. Centrifugal force.

c

304. 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.

a

305. 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.

c

306. 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 weight.

a

307. 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

308. 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.

b

309. 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

310. 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.

a

311. During an approach to a stall, an increased load factor will cause the airplane to A. stall at a higher airspeed. B. have a tendency to spin. C. be more difficult to control.

a

312. Angle of attack is defined as the angle between the chord line of an airfoil and the A. direction of the relative wind. B. pitch angle of an airfoil. C. rotor plane of rotation.

a

7. Which V-speed represents maneuvering speed? A. V(A). B. V(LO). C. V(NE).

a

179. 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.

c

180. 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 the top surface.

a

181. When are the four forces that act on an airplane in equilibrium? A. During unaccelerated flight. B. When the aircraft is accelerating. C. When the aircraft is at rest on the ground.

c

182. Select the four flight fundamentals involved in maneuvering an aircraft. A. Aircraft power, pitch, bank, and trim. B. Starting, taxiing, takeoff, and landing. C. Straight-and-level flight, turns, climbs, and descents.

b

187. (Refer to Figure 1. [lift vector]) The acute angle A is the angle of A. incidence. B. attack. C. dihedral.

a

188. The term 'angle of attack' is defined as the angle A. between the wing chord line and the relative wind. B. between the airplane's climb angle and the horizon. C. formed by the longitudinal axis of the airplane and the chord line of the wing.

b

189. The angle between the chord line of an airfoil and the relative wind is known as the angle of A. lift. B. attack. C. incidence.

a

190. What is the relationship of lift, drag, thrust, and weight when the airplane is in straight-and-level flight? A. Lift equals weight and thrust equals drag. B. Lift, drag, and weight equal thrust. C. Lift and weight equal thrust and drag.

a

191. How will frost on the wings of an airplane affect takeoff performance? A. Frost will disrupt the smooth flow of air over the wing, adversely affecting its lifting capability. B. Frost will change the camber of the wing, increasing its lifting capability. C. Frost will cause the airplane to become airborne with a higher angle of attack, decreasing the stall speed.

a

192. In what flight condition is torque effect the greatest 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.

b

193. 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 counter-clockwise. 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

194. 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

195. An airplane said to be inherently stable will A. be difficult to stall. B. require less effort to control. C. not spin.

a

196. 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.

c

197. 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.

b

198. What causes an airplane (except a T-tail) to pitch nose-down 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.

a

199. What is the purpose of the rudder on an airplane? A. To control yaw. B. To control overbanking tendency. C. To control roll.

c

200. (Refer to Figure 2. [Load factor Chart]) 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

201. (Refer to Figure 2. [Load factor Chart]) 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.

b

202. (Refer to Figure 2. [Load factor Chart]) If an airplane weighs 4,500 pounds, what approximate weight would the airplane structure to be required to support during a 45' banked turn while maintaining altitude? A. 4,500 pounds. B. 6,750 pounds. C. 7,200 pounds.