Increase while the lift is changing but will retrun to its original value
Fully articulated rotors
Decrease when the aircraft structure and cable become cold.
Increase when the aircraft structure and cables become cold.
Be unaffected if stainless steel cable is intalled.
Transmits control inputs to rotor head.
Coordinates control inputs from hydraulic pack.
It disconnects the rotor whenever the engine stops or slows below the equivalent of rotor RPM.
Blade pitch angle.
Degrees of blade flap travel
Leading edge to trailing edge.
Blade tip to blade tip
Blade tip to blade butt
Angle of attack
Lonitudinal dihedral angle
Angle of incidence
More than the advacing blade
Equal to the advacing blade
Less than the advancing blade
Compensation for torque
Causes the tail to pivot in the opposite driection of torque rotaiton around the main rotor axis
Causes the tail to pivot in the direction of torque rotaion around the main rotor axis
Is required to counteract main rotor torque produced by takeoff RPM
Changing pitch of main rotor blades
Varying the pitch of the tail rotor blades
Changing the tail rotor RPM
Rotor blades are out of track
Rotor blades are out of balance
Blade "droop" stops are not adjusted properly
The top or grip of the cellective
The top of the cyclic
The quadrant on the console
The tail rotor is inaccurately rigged
The engine power suddenly drops
Collective is rigged at too high an angle
Tilts the tip path plane in the direction of desired movement.
Changes pitch on both blades equally.
Controls rotor RPM and manifold pressure.
Blance the main rotor in a chordwise direction.
It is not adjustable
Balance the main rotor in a spanwise direction
Cyclic is moved
Collective control action
Collective sleeve movement
Lower the tail boom
Rest in the neutral position
Raise the tail boom
The tail rotor being out of spanwise balance
The main rotor being out of spanwise balance
The main rotor being out of track
While the blades are rotating at a specific RPM and collective pitch angle
On a special fixture before they are installed due to their flexibility
By direct measurement from the fuselage structure to a specific blade station when the blade is parallel to the fuselage centerline
Transverse flow lift
Low frequency vertical vibration
High frequency vertical vibration
Low frequency lateral vibration
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