-
Motion about the lateral axis is called
pitch
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In straight and level unaccelerated flight, which of the following is correct?
Lift equals weight
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Dihedral contributes most to stability of the airplane about its
longitudinal axis
-
If an aircraft has neutral static stability and is deflected from the attitude for which it is trimmed, it will
remain in the new attitude
-
When an aircraft has differential ailerons
the up airleron deflects more than the down aileron
-
An aircraft with positive dynamic pitch stability
would return to level flight through a series of constantly reducing oscillations after being displace by and air gust
-
Primary control surfaces on conventional aircraft are the
airlerons, elavators, rudder
-
The ratio of the total gross weight of the aircraft divided by the total wing area is called
wing loading
-
The elevators of a conventional airplane are used to provide rotation about the
lateral axis
-
The two forces acting along an aircraft's longitudinal axis are
thrust and drag
-
When the control wheel is displaced on the right
the right aileron will move up
-
The purpose of spring tabs or servo tabs is to
assist the pilot in moving the control surfaces
-
If the control stick of an aircraft with properly rigged flight controls is moved rearward and to the left, the right aileron will move
down and the elevator will move up
-
The vertical flight of a helicopter is controlled by
increasing or decreasing collective pitch
-
An airplane that has a tendency to gradually increase a pitching moment that has been set into motion has
poor longitudinal stability
-
Which statement is correct concerning torque effect on helicopters?
Torque direction is the opposite of rotor blade rotiation
-
If the control stick of an aircraft with properly rigged flight controls is moved forward and to the right, the left aileron will move
down and the elevator will move down
-
Movement of an airplane along its lateral axis (roll) is also movement
around or about the longitudinal axis controlled by the airlerons
-
Movement about the longitudinal (roll) in a helicopter is effected by movement of
the cyclic pitch control
-
Movement about the lateral axis (pitch) in a helicopter is effected by movement of
the cyclic pitch control
-
An airplane is controlled directionally about its vertical axis by
the rudder
-
The elevators of a conventional airplane are used to provid rotation about the
lateral axis
-
A helicopter in forward flight, cruise configuration, changes direction of flight by
tilting the main rotor disk in the desired direction
-
Tilting of the rotor tip-path plane is controlled by the
collective
-
A tandem-roter helicopter uses
two main rotors, counterrotating
-
A decrease in the pitch of the tail rotor blades causes the fuselage of the ship to
turn in the opposite direction of the main rotor
-
What is the cause of main rotor-blade "coning"?
lift force
-
A single-rotor helicopter wishing to move toward 6:00 postition would need the highest blade pitch imputed at the
3:00 position
-
Gyroscopic precession cause the resultant ultimate force to occur how many degrees from the applied force?
90o in direction of rotation
-
Translational lift affects a helicopter that is
moving horizontally at more than 15kn.
-
Th difference between the angles of incidence for two airfoils on a biplane is called
decalage
-
The action of the rotor blade that minimizes the effects caused by dissymmetry of lift is
Flapping
-
The principle factor in limiting helcopter maximum speed in foward flight is
retreating blade stall
-
When the helicopter blades are at their lowest pitch and all have the same angle, the collective stick is
full down and the cyclic stick is centered
-
What turns the main rotor during autorotation?
Aerodynameic Forces
-
The fastest moving point on a rotor blade is the
advancing blade tip
-
How is the torque force associated with single-rotor helicopters compensated?
A tail rotor with variable pitch mechanism
-
In a hover, which component(s) act vertically?
all of the above
-
Blade hunting is caused by
coriolis effect
-
the direction that a helicopter is facing may be changed by the
antitorque pedals
-
the tendency of a helicopter to drift in the direction of the tail rotor thrust is referred to as
translating tendency
-
Rotor droop is counteracted by
centrifugal force
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