Embraer EMB145, Operation Manual

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FLIGHT CONTROLS
AIRPLANE
OPERATIONS
MANUAL
2-13-15
Page
2
Code
01
JUNE 29, 2001
AILERON CONTROL SYSTEM
The ailerons are positioned by the pilot´s control wheels, which are
linked together by a torque tube and cables to supply mechanical input
to two separate hydraulic actuators.
Each aileron actuator is supplied by both hydraulic systems. Either
hydraulic system is capable of providing full power control. If
necessary, each hydraulic system supply can be shut off, by means of
a button installed on the overhead panel. In case of loss of both
hydraulic systems, rotation of the pilot´s control wheels mechanically
positions the ailerons.
In case of jamming of either aileron, both panels may be disconnected
through a handle located on the control pedestal. This procedure will
release the free aileron from its jammed counterpart allowing the free
panel to be commanded. When disconnected, an amber light
illuminates on the control stand. Controls cannot be reconnected
during flight, requiring maintenance action.
An autopilot servo is installed on the left side of the torque tube. The
roll trim servo and the artificial feel unit are installed on the right side of
the torque tube. In case of system disconnection, the artificial feel unit
will actuate on the right aileron only and the autopilot must not be used.
The artificial feel unit is provided to give pilots a aerodynamic load
feedback imposed on the aileron surface.