T-45C TS, ADV & IUT ENG-13
Flight Control System
Sg 6, fr 1
This lesson has presented the major components, physical
characteristics, functional descriptions, and operation limitations
of the flight control system.
The flight controls consist of ailerons to control roll, stabilator to
control pitch, and rudder to control yaw. The control augmenta-
tion system enhances flight characteristics and compensates for
pitch transients during speed brake operation. The T-45C also
employs flaps and slats to increase lift and speed brakes to
increase drag. All flight controls except the rudder are
hydraulically operated. The rudder is a mechanical system and
should be secured with the gust lock lever when the aircraft is
The flight control system controls and indicators consist of the
following: aileron/stabilator trim switch, AILERON trim indicator,
STBY STAB TRIM switch, STABILATOR position indicator, rudder
pedals, RUDDER trim indicator, RUDDER TRIM control, C AUG
caution light, RUDDER PEDAL ADJUST knob, CONTR AUG
switch, FLAPS/SLATS switch, EMER FLAPS switch, FLAP
position advisory light, SLATS caution light, SP BRK and FULL
advisory lights, extend/retract switch.
The flaps/slats should not be lowered above 200 KIAS.
Because knowledge of the aircraft and its systems directly affects
flight safety, your understanding of this system is imperative.