content_image/548617.jpg content_image/548618.jpg content_image/548619.jpg
<img src='content_image/548617.jpg'>

After completion of the static rigging, a functional check of the flight control system must be accomplished. The nature of the functional check varies with the type of helicopter and system concerned, but usually includes determining that: 

1. The direction of movement of the main and tail rotor blades is correct in relation to movement of the pilot’s controls. 

2. The operation of interconnected control systems (engine throttle and collective pitch) is properly coordinated. 

3. The range of movement and neutral position of the pilot’s controls are correct. 

4. The maximum and minimum pitch angles of the main rotor blades are within specified limits. This includes checking the fore-and-aft and lateral cyclic pitch and collective pitch blade angles. 

5. The tracking of the main rotor blades is correct. 

6. In the case of multirotor aircraft, the rigging and movement of the rotor blades are synchronized. 

7. When tabs are provided on main rotor blades, they are correctly set. 

8. The neutral, maximum, and minimum pitch angles and coning angles of the tail rotor blades are correct. 

9. When dual controls are provided, they function correctly and in synchronization. 

Upon completion of rigging, a thorough check should be made of all attaching, securing, and pivot points. All bolts, nuts, and rod ends should be properly secured and safetied as specified in the manufacturers’ maintenance and service instructions. 

## Configurations of Rotary-Wing Aircraft 

## Autogyro 

An autogyro is an aircraft with a free-spinning horizontal rotor that turns due to passage of air upward through the rotor. This air motion is created from forward motion of the aircraft resulting from either a tractor or pusher configured engine/propeller design. [Figure 2-24] 

## Single Rotor Helicopter 

An aircraft with a single horizontal main rotor that provides both lift and direction of travel is a single rotor helicopter. A secondary rotor mounted vertically on the tail counteracts the rotational force (torque) of the main rotor to correct yaw of the fuselage. [Figure 2-25] 

<img src='content_image/548618.jpg'>

<img src='content_image/548619.jpg'>

