IRIS TEXAN II - Flight Control System

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FOR SIMULATION USE ONLY – NOT A TRAINING AID
This counteracts some, but not all of the pitch change tendency of the aircraft due
to the operation of the speed brake. The speed brake extends to 70° from the
stowed position and may not be stopped at an intermediate deflection.
The speed brake switch is a three-position switch, spring-loaded to the centre
position, located on the top inside surface of each PCL. Rearward movement of
either switch extends the speed brake and forward movement retracts the speed
brake.
If the flaps are extended, the speed brake will not extend. Once extended, the speed
brake remains extended until either switch is moved forward to retract, the flaps
are extended, or the PCL is moved to MAX. Moving the FLAPS selector out of the UP
position, or moving the PCL to the maximum power position, trips a micro switch
which automatically retracts the speed brake.
The speed brake control circuit responds to the last entry.
Electrical power for the speed brake system is provided through a circuit breaker,
placarded SPEED BRAKE, on the generator bus circuit breaker panel in the front
cockpit.
FLIGHT CONTROL SYSTEM
The flight control system includes primary and secondary controls which may be
operated from either cockpit. The manually operated primary flight controls include
conventional ailerons, elevator, and rudder.
Secondary flight controls include electrically actuated pitch/roll/yaw trim systems
and a rudder trim aid device (TAD).
A combined aileron/elevator (roll/pitch) trim switch is located on each control stick
grip and a rudder (yaw) trim switch is located on each PCL. The control circuits give
the rear cockpit priority if trim selection conflicts between cockpits.
A trim interrupt button is located right of the roll/pitch trim switch on the top of the
control stick grip. Pressing and holding the button interrupts power to all trim
actuators and causes the trim aid device to disengage. A trim disconnect switch,
placarded TRIM DISCONNECT, is also installed on the trim control panel in each
cockpit.
Actuating the trim disconnect switch removes power from the trim system and
cause the trim aid device to disengage. Green TRIM OFF and TAD OFF advisory on
the EICAS display in each cockpit illuminates whenever the trim disconnect switch
is used.