KT Prep FlashCards
1.1 What is one purpose of wing flaps?
To enable the pilot to make steeper approaches to a landing without increasing the airspeed.
Extending the flaps increases the wing camber and the angle of attack of the wing.
1.1 One of the main functions of flaps during approach and landing is to
Increase the angle of descent without increasing the airspeed.
1.1 What is the purpose of the rudder on an airplane?
To control Yaw
The rudder is used to control yaw, which is rotation about the airplane’s vertical axis.
1.1 Which is not a primary flight control surface
Flaps
Three primary flight controls of an airplane are the ailerons, the elevator (stabilator), and the rudder.
1.1 The elevator controls movement around which axis
Lateral
The elevator is the primary control device for changing the pitch attitude of an airplane about the lateral axis.
1.1 True Statement concerning primary flight controls: The effectiveness of each control surface increases with speed because there is more airflow over them.
Rudder, alleron, and elevator effectiveness increase with speed because there is more airflow over the surface of the control device.
1.1 True statement concerning flaps: Flaps allow an increase in the angle of descent without increasing airspeed.
Flaps are attached to the trailing edge of the wing and are used during approach and landing to increase wing lift. This allows an increase in the angle of descent without increasing airspeed.
Which device is a secondary flight control?
Spoilers
Ailerons
Stabilators
Spoilers. Spoilers are high-drag devices that assist an aircraft in slowing down and losing altitude without gaining extra speed. They are common on gliders and some high-speed aircraft.
1.1 Trim systems are designed to do what?
They relieve the pilot of the need to maintain constant pressure on the flight controls.
Trim systems are used to relieve the pilot of the need to maintain constant pressure on the flight controls. They include trim tabs, anti-servo tabs, and ground adjustable tabs
1.2 The four-forces acting on an airplane in flight are
? lift, weight thrust, and drag
? lift weight, gravity, and thrust
? lift, gravity, power, and friction
lift, weight, thrust, and drag
1.2 when are the four/forces that act on an airplane in equilibrium
During unaccelerated level flight
1.2 What is the relationship of lift, drag, thrust, and weight when the airplane is in straight-and-level flight?
lift equals weight and thrust equals drag
1.2 Which statements relates to Bermoulli’s principle?
Air traveling faster over_____ of an ____ causes ____
air traveling faster over the curved upper surface of an airfoil causes lower pressure on the top surface
1.3 The acute angle A is the angle of ___
attack
1.3 The term “angle of attack” is defined as the angle between the…
chord line of the wing and the relative wind.
1.3 The angle between the chord line of an airfoil and the relative wind is known as the angle of
attack
1.3 The angle of attack at which an airplane wing stalls will
remain the same regardless of gross weight.
1.4 As altitude increases, the indicated airspeed at which a greater airplane stalls in a particular configuration will
remain the same regardless of altitude
1.5 In what flight condition must an aircraft be placed in order to spin?
stalled
1.5 During a spin to the left, which wing(s) is/are stalled?
both wings are stalled
1.6 What is good ground effect?
The result of the interference of the surface of the Earth with the airflow patterns about an airplane.
1.6 Floating caused by the phenomenon of ground effect will be most realized during an approach to land when at
less than the length of the wingspan above the surface.
1.6 What must a pilot be aware of as a result of ground effect?
induced drag, decreases; therefore, any excess speed at the point of flare may cause considerable floating.
1.6 An aircraft leaving ground effect during takeoff will
experience an increase in induced drag and a decrease in performance
1.6 Ground effect is most likely to result in which problem?
Becoming airborne before reaching recommended takeoff speed.
1.7 What force makes an airplane turn?
The horizontal component of lift.
1.8 What determines the longitudinal stability of an airplane?
The location of the CG with respect to the center of lift
1.8 An airplane said to be inherently stable will
? be difficult to stall
? require less effort to control
? not spin
require less effort to control
1.8 Changes in the center of pressure of a wing affect the aircraft’s?
? lift/drag ratio
? lifting capacity
? aerodynamic balance and controllability
aerodynamic balance and controllability
1.8 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
difficulty in recovering from a stalled condition.
1.8 What causes an airplane (except a T-tail) to pitch hosedown when power is reduced and controls are not adjusted?
The downwash on the elevators from the propeller slipstream in reduced and elevator effectiveness is reduced.
1.8 What is the effect of advancing the throttle in flight?
both aircraft and groundspeed and angle of attack will increase.
1.8 Loading an airplane to the most aft CG will cause the airplane to be
less stable at all speeds.
1.8 An airplane loaded with the Center of Gravity (CG) rear of the aft CG limit could
increase the likelihood of inadvertent overstress.
1.9 In what flight condition are torque effects more pronounced in a single-engine airplane?
low airspeed, high power, high angle of attack
1.9 The left-turning tendency of an airplane caused by P-factor is the result of the
propeller blade descending on the right, producing more thrust than the ascending blade on the left.
1.9 When does P-factor cause the airplane to yaw to the left?
? when at low angles of attack
? when at high angles of attack
? when at high airspeeds
When at high angles of attack
1.10 Which basic flight maneuver increases the load factor on an airplane as compared to straight-and-level flight?
? climbs
? turns
? stalls
Turns
1.10 The amount of excess load that can be imposed on the wing of an airplane depends upon the
? position of the CG
? Speed of the airplane
? abruptness at which the load is applied
speed of the airplane
1.10 During an approach to a stall, an increased load factor will cause the aircraft to
? stall at a higher airspeed
? have a tendency to spin
? be more difficult to control
stall at a higher airspeed
1.11 structural damage or failure is more likely to occur in smooth air at speeds above
? V NO2
? V Az
? V NE2
V NE2
1.11 Limit load factor is the ratio of
maximum sustainable load to the gross weight of the airplane
PPPT Refer to Figure 8 on page 215
What is the effect of a temperature increase from 25 to 50 degrees Fahrenheit on the density altitude if the pressure altitude remains at 5,000 feet?
