When the control column is moved back and the hand-wheel turned to the left.

The left aileron moves up and the elevators move up.

The elevators move down and the left aileron moves down.

The elevators move up and the left aileron moves down.

If the control column is moved forward and to the left.

Left aileron moves up, right aileron down, elevator down.

Left aileron moves up, right aileron moves down, elevator up.

Left aileron moves down, right aileron up, elevator down.

A differential aileron control is one which gives.

A larger aileron up travel than down.

Equal aileron travel in each direction, but variable for stick movement.

The down-going aileron more travel than the up-going one.

On an aircraft fitted with spoilers for lateral control, roll to the right is caused by

Right spoiler extending, left spoiler remaining retracted.

Left spoiler extending, right spoiler remaining retracted.

When an aileron trim control in the cockpit is moved to counteract a tendency to fly left wing low, an aileron trim tab fitted to the port aileron will.

Move up and cause the left aileron to move down and the right aileron to move down to a lesser degree.

Move up and this will cause the left aileron to move down and the right aileron to move up.

Move up and cause the left aileron to move down but the right aileron will remain neutral.

You have adjusted the elevator trim tab to correct for nose heavy. What was the direction of travel of the trim tab?

The elevator trim tab has moved down.

The port elevator tab has moved up and starboard moved down.

The elevator trim tab has moved up.

Which of the following are primary control surfaces?

Roll spoilers, elevators, tabs.

Elevators, roll spoilers, tabs.

The outboard ailerons on some large aircraft.

Are isolated to improve sensitivity.

Aerodynamic balance of a control surface may be achieved.

By a horn at the extremity of the surface forward of the hinge line.

By weights added to the control surface aft of the hinge line.

By a trimming strip at the trailing edge of the surface.

A projection of the outer edge of the control surface forward of the hinge line.

A rod projecting upward from the main control surface to which the control cables are attached.

A rod projecting forward from the control surface with a weight on the end.

A combined yawing and rolling motion.

Primarily a pitching instability.

With respect to flight spoilers, they.

Can operate both on the ground and in flight.

The two switches for pitch trim are located.

On the control column acting like an 'AND' switch.

On the control column with the captain having priority over the First Officer.

On the control column acting like an 'OR' switch.

A wing mounted stall warning vane.

Gives a visual indication of impending stall.

Powered flight control systems are used on transport aircraft.

Due to the increase in speed and size of aircraft.

Because at low level air density is high.

Because the pilot has too many tasks to perform.

A differential aileron control system results in.

Aileron drag being reduced on the outer wing in a turn.

Aileron drag being reduced on the inner wing in a turn.

Aileron drag being compensated by small rudder movements.

Spoiler panels are controlled by.

The aileron control wheel and speed brake lever.

The aileron control wheel only.

Is an eccentric flywheel driven by an electric motor and mounted on the control column.

Is a linear actuator attached to the base of the control column.

Vibrates the elevators to cause buffeting of the airframe.

Moving the elevator trim wheel fully aft, then the.

Aircraft tends to go nose down.

Aircraft tends to roll to the right.

What are two benefits of a yaw damper system?

Increasing the stability of the aircraft and smoother ride for the passengers.

Increased resistance to the controls and artificial feel at higher speeds.

Purpose of trailing edge flap of the aircraft when extended?

Increasing the lift on take off and decrease aircraft speed during landing

Decreasing the lift and speed of the aircraft on take off

Increasing the drag and lift on take off

On large aircrafts the mechanical control network connected to the flight control as a back -up ?

The hydraulic systems failure or failure of the hydraulic control system

The hydraulic control system and the auto flight system failure

The fly by wire system is?

The action of the pilots from cockpit transmits to electrical signals to various flight control actuators

The action of the pilots from cockpit transmits to electrical signals through a computer to various flight control actuators

The action of the pilots from cockpit transmits to electrical signals to flight control surfaces

The improved of flight by optics system is?

Flight by optics networks able to transfer data at higher speeds than wired systems

Flight by optics networks able to transfer data at medium speeds

When yaw damper actives:

Aircraft controlled manually or during operations involving the autopilot

Rudder limiter on high speed aircrafts reduce rudder deflection to:

Minimize the risk of exceeding structural limitation

Maximize the risk of exceeding structural limitation

Rigging an aircraft flight control system by setting:

Cabble tension, adjusting travel limits of flight controls, tab and travel stops

Belt crank , torque tubes and adjusting travel limits of flight controls

Travel stops, torque tubes and adjusting travel limits of flight controls

ATA 27- FLIGHT CONTROLS

Authored by ysnt hcns

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Professional Development

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MULTIPLE CHOICE QUESTION

30 sec • 1 pt

In normal flight, if the control wheel is moved to the left, then the aileron on the right wing will.

Decrease the angle of attack of the right hand wing.

Increase the angle of attack of the right hand wing.

Keep the angle of attack of the right wing constant.

MULTIPLE CHOICE QUESTION

30 sec • 1 pt

Aileron input is fed into the yaw damper system to.

Prevent nose pitching down.

Prevent nose pitching up.

Prevent adverse yaw in a turn.

MULTIPLE CHOICE QUESTION

30 sec • 1 pt

In an automatic flight control system, when may the yaw damper be applied?

During manual control only.

During automatic control only.

During either manual or automatic control.

MULTIPLE CHOICE QUESTION

30 sec • 1 pt

The aircraft is controlled about the lateral axis by the.

Elevator.

Ailerons.

Rudder.

MULTIPLE CHOICE QUESTION

30 sec • 1 pt

The aircraft is controlled about the vertical axis by the.

Rudder.

Ailerons.

Elevator.

MULTIPLE CHOICE QUESTION

30 sec • 1 pt

A stick shaker is a device which.

Vibrates the control column near stalling speed.

Gives a short period of extra lift to assist take off.

Helps extricate an aircraft from soft ground.

MULTIPLE CHOICE QUESTION

30 sec • 1 pt

The aircraft is controlled about the longitudinal axis by the

Elevator.

Rudder

Ailerons.

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ATA 27- FLIGHT CONTROLS

In normal flight, if the control wheel is moved to the left, then the aileron on the right wing will.

Aileron input is fed into the yaw damper system to.

In an automatic flight control system, when may the yaw damper be applied?

The aircraft is controlled about the lateral axis by the.

The aircraft is controlled about the vertical axis by the.

A stick shaker is a device which.

The aircraft is controlled about the longitudinal axis by the

Which of the following is not a primary flying control?

A tab which assists the pilot to move a flying control by moving automatically in the opposite direction to the control surface is called a.

When spoilers are used asymmetrically, they combine with.

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