T-45C TS, ADV & IUT ENG-13
Flight Control System
D.
Aircraft interfaces 1.4.14.2
1.
Hydraulic system
a.
Ailerons and stabilator power control units
(PCUs) contain tandem actuators which receive
hydraulic power from both HYD 1 and HYD 2.
Failure of either hydraulic system will not affect
flight control operation.
b.
Rudders are mechanically operated
2.
Electrical
a.
28 VDC generator bus powers
(1) Aileron trim
(2) Rudder trim
(3) Standby stabilator trim
(4) Trim indicator (aileron, rudder, and
stabilator)
b.
28 VDC essential services bus powers , primary
stabilator trim only.
E.
Summary:
The aileron, stabilator, and rudder systems make up the
flight controls. The aileron and stabilator systems are
hydraulically operated with redundant actuators. The
rudder system is mechanical and should be locked when
the aircraft is parked. Toe pedals on the rudder pedals
activate the independent hydraulic wheel brakes. All
flight controls have trim capability. The control aug-
mentation system enhances the flight characteristics of
the aircraft.
(9-98) Change 1
Page 13-24
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