PL.VI.B.S2

From the FAA library

• Pilot's Handbook of Aeronautical Knowledgep. 11-5
  Chapter 11: Aircraft Performance › Performance › Straight-and-Level Flight

  Straight-and-Level Flight All of the principal components of flight performance involve steady-state flight conditions and equilibrium of the aircraft. For the aircraft to remain in steady, level flight, equilibrium must be obtained by a lift equal ... aircraft weight and a powerplant thrust equal to the aircraft drag. Thus, the aircraft drag defines the thrust required to maintain steady, level flight. As presented in Chapter 4, Aerodynamics of Flight, all parts of an aircraft contribute…

• Pilot's Handbook of Aeronautical Knowledgep. 5-24
  Chapter 5: Aerodynamics of Flight › Aerodynamic Forces in Flight Maneuvers › Forces in Descents

  Figure 5-36. Changes in lift during climb entry. The thrust required for a stabilized climb equals drag plus a percentage of weight dependent on the angle of climb. For example, a 10° climb would require thrust to equal drag ... plus 17 percent of weight. To climb straight up would require thrust to equal all of weight and drag. Therefore, the angle of climb for climb performance is dependent on the amount of excess thrust available to overcome a portion…

• Pilot's Handbook of Aeronautical Knowledgep. 5-3
  Chapter 5: Aerodynamics of Flight › Thrust

  Figure 5-2. Force vectors during a stabilized climb. Likewise, if the engine power is increased, thrust becomes greater than drag and the airspeed increases. As long as the thrust continues to be greater than the drag, the aircraft continues ... accelerate. When drag equals thrust, the aircraft flies at a constant airspeed. Straight-and-level flight may be sustained at a wide range of speeds. The pilot coordinates AOA and thrust in all speed regimes if the aircraft…

• Pilot's Handbook of Aeronautical Knowledgep. 6-2
  Chapter 6: Flight Controls › Flight Control Systems › Primary Flight Controls

  Flight Control Systems Flight Controls Aircraft flight control systems consist of primary and secondary systems. The ailerons, elevator (or stabilator), and rudder constitute the primary control system and are required to control an aircraft safely during flight. Wing flaps, leading ... control system and improve the performance characteristics of the airplane or relieve the pilot of excessive control forces. Primary Flight Controls Aircraft control systems are carefully designed to provide adequate responsiveness to control inputs while allowing a natural feel…

• Pilot's Handbook of Aeronautical Knowledgep. 5-51
  Chapter 6: Flight Controls

  Chapter Summary In order to sustain an aircraft in flight, a pilot must understand how thrust, drag, lift, and weight act on the aircraft. By understanding the aerodynamics of flight, how design, weight, load factors, and gravity affect an aircraft ... during flight maneuvers from stalls to high speed flight, the pilot learns how to control the balance between these forces. For information on stall speeds, load factors, and other important aircraft data, always consult the AFM/POH for specific information pertaining…

• Pilot's Handbook of Aeronautical Knowledgep. 8-11
  Chapter 8: Flight Instruments › Electronic Flight Display (EFD)

  case of the VSI, a blocked static system produces a continuous zero indication. [Figure 8-11] Some aircraft are equipped with an alternate static source in the flight deck. In the case of a blocked static source, opening the alternate ... static source introduces static pressure from the flight deck into the system. Flight deck static pressure is lower than outside static pressure. Check the aircraft AOM/POH for airspeed corrections when utilizing alternate static pressure. Figure 8-11. Blocked static system…