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MECHANISM
SHAFT
ASSEMBLY
TRIM ACTUATOR
LOAD LIMITER RUDDER
YAW CABLE DAMPERPEDAL
CIRCUIT
ASSEMBLY DUAL PATH SPLIT RUDDER FEEL QUADRANTS UNIT
AFT QUADRANT
GF1010_012
ARTIFICIAL FEEL
Rudder Control System Operation
Each rudder pedal assembly uses an artificial feel unit and pedal input is transmitted via control rods to the forward quadrant and shaft assembly. The cable system has a single path in the fuselage and dualized in the rotor burst zone. The forward cable quadrant (one in each control circuit) transmits the cable circuit to the aft quadrant. Artificial feel is provided by a linear spring unit (rudder feel unit), connected to the aft quadrant.
Rudder input from the aft quadrant is received by a load limiting bungee (telescopic rod) which protects the system from rapid inputs. The load limiter delivers pilot input to a summing mechanism which adds the trim and yaw damping commands to the pilot commanded rudder input.
Yaw dampers are used to improve the airplane’s lateral/directional stability and turn coordination. Dual yaw dampers operate in an active/standby mode to provide continuous yaw damping in the event of one failed yaw damping channel. The active/standby status will be switched each flight leg.
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual Volume 2
RUDDER CONTROL (CONT'D)
Rudder Control System Operation (Cont’d)
Initial yaw damper engagement is controlled by flight guidance computer at IAC power up. In flight, the pilot must select the YAW switch located on the guidance panel if re-engagement of the yaw damping system is necessary.
The yaw damper authority, given neutral trim, provides a nominal value of 7.5 ° rudder left or right. Yaw damper condition is continuously monitored and any fault detected is displayed on EICAS. To ensure full motor performance in cold conditions, each actuator has a thermofoil heater which is powered, controlled and monitored by the Heater Brake Monitor Unit (HBMU). For the damping control systems characteristics, refer to the AFCS Chapter 4 of this manual.
The summing mechanism output is transmitted to a control rod to the Rudder Travel Limiter (RTL). The RTL limits the rudder surface travel at high speeds and allows full rudder surface travel at low speeds. The RTL output drives a torque tube which is connected (via load limiting bungees) to the input lever of the associated hydraulic PCUs. There are three PCUs powering the rudder system.
Rudder Travel limiter
The RTL limits rudder authority as a function of Calibrated Airspeed (CAS) and flap position to protect the deflection of the rudder surface beyond the structural capability of the vertical stabilizer, while allowing for sufficient authority to control the airplane. The RTL also allows for full rudder authority at high airspeed in the event of total loss of (FCU) control.
The position of the rudder is shown on EICAS Flight Control page (rudder trim position is shown on Primary page). Left and right rudder indication is displayed by a pointer on the synoptic page.
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