AIRPLANE
OPERATIONS
MANUAL
FLIGHT CONTROLS
REVISION 30
2-13-20
Page
5
Code
01
• During single-engine operation, when the rudder system is more
significantly required, the rudder hardover protection is disabled and
the RUD HDOV PROTFAIL caution message may be presented on
the EICAS.
• If a disagreement between FADECs from the same engine occurs,
rudder hardover protection is deactivated and the
RUD HDOV PROTFAIL caution message is presented on the
EICAS.
RUDDER DEFLECTION
AIRPLANES UNDER CTA AND FAA CERTIFICATION
The rudder’s main control primary stops, limit rudder deflection at
± 15° on ground or in flight.
AIRPLANES UNDER JAA CERTIFICATION
There are two rudder deflection versions:
• Airplanes with rudder main control primary stops, located on the
rear torque tube assembly, that limit the ruder deflection at ± 10° on
ground or in flight and;
• Airplanes Post-Mod. S.B. 145-27-0015 or equipped with an
equivalent modification factory incorporated, equipped with movable
rudder primary stops, which provide two different ranges of rudder
deflection:
- On ground: maximum rudder deflection is ± 15°.
- In flight: maximum rudder deflection is ± 10°.
The Movable Rudder Primary Stop System comprises a hydraulic
actuation system, which operates according to the air/ground logic
and will limit rudder deflection to 10° in the extended position and to
15° in the retracted position.
An amber indication light is provided on the main panel to alert the
crew in case of a disagreement between the actuator position and
the air/ground condition.
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