Chapter Nine Flight Control Systems

CHAPTER NINE

FLIGHT CONTROL SYSTEMS

900. INTRODUCTION

This chapter discusses the aircraft flight control systems. The information is designed to provide

you with an understanding of these systems to aid in understanding operating procedures and

limitations.

The primary flight control systems consist of elevator, spoilers, and rudder. All are manually

actuated by either the P or CP through a conventional control column and rudder pedal

arrangement. These control inputs are transmitted to the control surfaces through cables,

push/pull rods, and bellcranks.

Secondary flight controls consist of the flaps, speed brakes, pitch trim, roll trim, and rudder trim.

The speed brakes and flaps are electrically controlled and hydraulically actuated. Trim in the roll

and pitch axis is electrically operated and controlled by switches on each control wheel.

Directional (yaw axis) trim is electrically controlled by a switch on the center pedestal.

901. ENABLING OBJECTIVE

Recall the basic description, related systems, function, and operating limitations of the aircraft

flight control systems.

902. ENABLING STEPS

State the primary flight controls.

State the secondary flight controls.

Recall the locations of the trim indicators.

Recall how each system is actuated.

903. PRIMARY FLIGHT CONTROLS

Elevator

The elevator is mechanically operated, through a system of cables, torque tubes, and pushrods,

by the control columns on the fight deck. When the control column is positioned full aft, the

elevator moves 25 up and when the control column is positioned full forward the elevator

moves 12 downward.

FLIGHT CONTROL SYSTEMS

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