Aerodynamics and Spin Awareness 3
PA.V.A.K2 Aerodynamics associated with steep turns, to include: PA.V.A.K2a a. Coordinated and uncoordinated flight PA.V.A.K2b b. Overbanking tendencies PA.V.A.K2c c. Maneuvering speed, including the impact of weight changes PA.V.A.K2d d. Load factor and accelerated stalls PA.V.A.K2e e. Rate and radius of turn
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1. The airspeed indicated by points A and J is (Refer to Figure 72: Velocity vs. G-Loads)
Answer (C) is correct. (FAA-H-8083-25B Chap 5) Points A and J are the normal stall speed (VS1). At this speed in the clean configuration, the airplane will stall. The normal stall speed is shown on the airspeed indicator at the low-speed end of the green arc.
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2. What load factor would be created if positive 15 feet per second gusts were encountered at 120 mph? (Refer to Figure 72: Velocity vs. G-Loads)
Answer (C) is correct. (FAA-H-8083-25B Chap 5) Begin at the bottom of Fig. 72 by locating 120 mph and then move up vertically to the positive 15-feet-per-second (+15 fps) diagonal white line. Next, move left horizontally to determine the load factor of 2.0.
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3. A positive load factor of 2 at 80 mph would cause the airplane to (Refer to Figure 72: Velocity vs. G-Loads)
Answer (C) is correct. (FAA-H-8083-25B Chap 5) The Velocity vs. G-loads chart (Fig. 72) has indicated airspeed on the horizontal axis and load factor on the vertical axis. Locate the intersection of 2 on the vertical axis and 80 on the horizontal axis. Notice that operating where these coordinates intersect, which is the blue shaded area, would be indicative of a stalled condition.
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4. Structural damage or failure is more likely to occur in smooth air at speeds above
Answer (C) is correct. (FAA-H-8083-25B) Never exceed speed (VNE) is a design limit speed where load factors could be exceeded with airspeeds in excess of VNE from a variety of phenomena. Operating above this speed is prohibited since it may result in damage or structural failure.
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5. During an approach to a stall, an increased load factor will cause the aircraft to
Answer (B) is correct. (FAA-H-8083-25B Chap 5) The greater the load (whether from gross weight or from centrifugal force), the more lift is required. Therefore, an aircraft will stall at higher airspeeds when the load and/or load factor is increased.
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6. The amount of excess load that can be imposed on the wing of an airplane depends upon the
Answer (B) is correct. (FAA-H-8083-25B Chap 5) The amount of excess load that can be imposed on the wing depends upon how fast the airplane is flying. At low speeds, the maximum available lifting force of the wing is only slightly greater than the amount necessary to support the weight of the airplane. Thus, any excess load would simply cause the airplane to stall. At high speeds, the lifting capacity of the wing is so great (as a result of the greater flow of air over the wings) that a sudden movement of the elevator controls (strong gust of wind) may increase the load factor beyond safe limits. This is why maximum speeds are established by airplane manufacturers.
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7. 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? (Refer to Figure 2: Load Factor Chart)
Answer (C) is correct. (FAA-H-8083-25B Chap 5) Look on the left side of the chart in Fig. 2 under 45° and note that the load factor curve is 1.414. Thus, a 4,500-lb. airplane in a 45° bank would require its wings to support 6,363 lb. (4,500 lb. × 1.414). The closest answer choice to this value is 6,750 lb.
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8. 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? (Refer to Figure 2: Load Factor Chart)
Answer (B) is correct. (FAA-H-8083-25B Chap 5) Note on Fig. 2 that, at a 60° bank angle, the load factor is 2. Thus, a 2,300-lb. airplane in a 60° bank would require its wings to support 4,600 lb. (2,300 lb. × 2).
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9. 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? (Refer to Figure 2: Load Factor Chart)
Answer (B) is correct. (FAA-H-8083-25B Chap 5) Look on the left side of the chart in Fig. 2 to see that, at a 30° bank angle, the load factor is 1.154. Thus, a 3,300-lb. airplane in a 30° bank would require its wings to support 3,808.2 lb. (3,300 lb. × 1.154). The closest answer choice to this value is 3,960 lb.
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10. Which basic flight maneuver increases the load factor on an airplane as compared to straight-and-level flight?
Answer (A) is correct. (FAA-H-8083-25B Chap 5) Turns increase the load factor because the lift from the wings is used to pull the airplane around a corner as well as to offset the force of gravity. The wings must carry the airplane’s weight plus offset centrifugal force during the turn. For example, a 60° bank results in a load factor of 2; i.e., the wings must support twice the weight they do in level flight.
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11. Which V-speed represents maneuvering speed?
Answer (C) is correct. (14 CFR 1.2) VA means design maneuvering speed.
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12. What is an important airspeed limitation that is not color coded on airspeed indicators?
Answer (C) is correct. (FAA-H-8083-25B Chap 8) The maneuvering speed of an airplane is an important airspeed limitation not color-coded on the airspeed indicator. It is found in the airplane manual (Pilot’s Operating Handbook) or placarded on the flight deck. Maneuvering speed is the maximum speed at which full deflection of the airplane controls can be made without incurring structural damage. Maneuvering speed or less should be held in turbulent air to prevent structural damage due to excessive loads.
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