Updated: Apr 12, 2022
CHAPTER TITLE: Flight Controls
Below is a list of the figures (diagrams, charts, and pictures) from the PHAK Chapter 6. They are listed in the order they are found in the Pilot's Handbook of Aeronautical Knowledge.
Mechanical flight control system.
Hydromechanical flight control system.
Helicopter flight control system.
Airplane controls, movement, axes of rotation, and type of stability.
Adverse yaw is caused by higher drag on the outside wing that is producing more lift.
Coupled ailerons and rudder.
Flaperons on a Skystar Kitfox MK 7.
The elevator is the primary control for changing the pitch attitude of an aircraft.
Aircraft with a T-tail design at a high AOA and an aft CG.
When the aerodynamic efficiency of the horizontal tail surface is inadequate due to an aft CG condition, an elevator down spring may be used to supply a mechanical load to lower the nose.
The stabilator is a one-piece horizontal tail surface that pivots up and down about a central hinge point.
The Piaggio P180 includes a variable-sweep canard design that provides longitudinal stability about the lateral axis.
The effect of left rudder pressure.
Beechcraft Bonanza V35.
Five common types of flaps.
Leading edge high lift devices.
Spoilers reduce lift and increase drag during descent and landing.
The movement of the elevator is opposite to the direction of movement of the elevator trim tab.
An antiservo tab attempts to streamline the control surface and is used to make the stabilator less sensitive by opposing the force exerted by the pilot.
A ground adjustable tab is used on the rudder of many small airplanes to correct for a tendency to fly with the fuselage slightly misaligned with the relative wind.
Some aircraft, including most jet transports, use an adjustable stabilizer to provide the required pitch trim forces.
Basic autopilot system integrated into the flight control system.