Flight Controls
T-45A UJPT, E2-C2, ADV, & IUT Eng-11
REFRESHER
*
The T-45A flight controls are powered by two
independent hydraulic systems and by pedal power.
PRESENTATION
I.
Major flight control components 1.4.14.3.1
Sg 1, fr 1
Lesson Organization
A.
Flight controls
Sg 1, fr 2
1.
Aileron system
2.
Stabilator system
3.
Rudder system
NOTE: Two stabilator vanes (strakes) are
FlIGHT CONTROL SYSTEM, FALPS/
SLATS, SPEED BRAKES, STRAKE
fixed surfaces located on each side of the
rear fuselage, forward of the stabilator.
Sg 1, fr 3
With the flaps extended and a high angle of
attack, they help direct airflow over the
HYD1
HYD2
STABILATOR
MECHANICAL LINKS
stabilator, providing enhanced aircraft pitch
Fwd/Aft
Fwd/AftRudderPedals
AILERON
Aileron / Stabilator
MECHANICAL LINKS
TrimSwitches
Fwd/AftCONTRAUG
RUDDER
andRudder Trim Switches
MECHANICAL LINKS
control. (SMURFs - side-mounted unit root
ELECTRICAL
Yaw Damper
Controller
Rudder Centering Unit
Stabilator Trim Actuator /
SpringFeelUnit
fences).
Aileron Trim Actuator /
Spring Feel Unit
Left Aileron
Right Aileron
Actuator/PCU
Actuator /PCU
HYD 2 EDP
HYD 1 EDP
NOTE: BUZZ STRIPS on vertical stabilizer,
StabilatorPCU/Actuator
Trim/YawDamperActuator
VORTEX GENERATORS and STALL
FLIGHT CONTROLS
FENCES on wing help control boundary
layer of air. ANGLE METAL STRIPS (stall
strips) at wing roots cause turbulence,
which affects the horizontal stabilator,
before wing stall to provide warning of
impending wing stall.
Sg 1, fr 4
B.
Flaps/slats
Flaps/Slats
Sg 1, fr 5
C.
Speed brakes
Speed Brakes
Page 11-4
(8-03) Original
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