T-45A UJPT, E2-C2, ADV, & IUT Eng-11
Sg 5, 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 augmentation system enhances flight
characteristics and compensates for pitch transients
during speed brake operation. The T-45A 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 parked.
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, CONTR AUG caution light,
RUDDER PEDAL ADJUST knob, CONTR AUG switch,
FLAPS/SLATS switch, EMERG FLAPS switch, FLAP
position indicator, SLATS caution light, SPD BRK and
SPD BRK FULL advisory lights, speed brake extend/
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.