User manual
Aerosoft F-16 Fighting Falcon 1.00 Manual
Page 11 of 46
FLIGHT SYSTEMS
To fully understand the flying capabilities of the F-16 it is important to understand some of the main
systems and principles that make it the maneuverable fighter it is. Translated from RNoAF F-16AM
technical training documents to a very basic technical English by Dag R. Stangeland.
F-16AM FLIGHT CONTROL SYSTEM (FLCS)
The Flight Control System in the F-16 is a computer controlled system. The main 3 components of this
system are as follows:
Primary FLCS: Controls the aircraft in the PITCH, ROLL and YAW axis via the primary control
surfaces.
o Horizontal stabilizers (Pitch)
o Flaperon (Roll)
o Rudder (Yaw)
Secondary FLCS: The purpose of this system is to increase/optimize lift, aerodynamic braking
and enhance maneuverability. To do this the secondary control surfaces are used.
o Leading Edge Flap (LEF)
o Trailing Edge Flap (TEF)
o Speedbrakes
The Air Data System (ADS):
o The ADS transmits signals to the FLCS via a pneumatic origin, such as AOA, Airspeed,
Altitude, Mach-number, Temperature and Sideslip.
The pilot induces steering commands to the FLCS via the Side Stick Controller (SSC) and rudder pedals.
Then the signals are generated electrically and sent to the FLCS, where they are processed together with
inputs from the air data system and feedback from gyros and accelometer. Based on these inputs, the
final rudder deflection/input is generated and will determine what position the rudder should be in. The
signal from the FLCS out to the Integrated Servo Actuator (ISA) is electrically driven but the main ISA that
moves the rudder/control surface is hydraulically powered from hyd. system A and B. In addition to SSC
and rudder pedals the pilot can give inputs to the FLCS via Manual Trim Panel (MTP). The MTP can trim
the aircraft in all 3 axes. The FLCS is also equipped with an Autopilot (AP) function that can maintain
attitude, altitude and heading based on the pilot’s choice. The Horizontal Stabilizers moves the aircraft
in the pitch axis and assists during roll. They operate symmetrically in pitch maneuvering and
asymmetric during roll maneuvering. They can move 25° up and 25° down from streamline.
The Flaperons move the aircraft around the roll axis. They can deflect 23° up to 20° down from
streamline position. When the Landing Gear Handle is set to the down position, both flaperons will
automatically go down to 20° and work as Trailing Edge Flaps. If flaperon is in the TEF mode and you
maintain airspeed in excess of 240 kts the down deflection will decrease gradually from 20° and be fully
streamline when reaching 370 kts. TEF mode will then be unavailable. Rudder pedals send inputs to the
aircraft in the yaw axis. The rudder can deflect 30° to each side from the center position.