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YAW DAMPER
The yaw damper provides stability augmentation and turn coordination for the airplane yaw axis, via 2 linear actuators, in series with the rudder control system.
The yaw damper function will automatically engage on the ground, within 3 seconds after successful completion of AFCS power-up test. As with the autopilot, the yaw damper operates in an active/standby configuration. When engaged, the active yaw damper will center both linear actuators.
The YD will not automatically engage once the airplane is airborne. The YD button, located on the guidance panel may be used to re-engage the YD. When YD is engaged, the associated arrow on the guidance panel is illuminated.
One valid yaw damper must be engaged for autopilot operation. Autopilot engagement without YD will occur only when YD has failed in flight.
GF0410_012
For more information on yaw damper see Chapter 10, FLIGHT CONTROLS.
Volume 2 Flight Crew Operating Manual Rev 2A, Apr 11, 2005
The autopilot cannot be engaged without flight director guidance modes active. When no vertical or lateral mode is active, the autopilot will engage the pitch and roll FD modes. Autopilot is engaged via the AP button on the guidance panel.
GF0410_013
Autopilot control authority:
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Roll rate is limited to ± 7.5°/sec.
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Pitch rate is ± 0.3 G in straight and level flight and maximum 0.7 G pitch up in a turn.
The autopilot can engage throughout the range:
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Pitch = ± 50°
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Roll = ± 75°
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Once engaged, the autopilot will reduce the pitch and roll angles below control limits.
Autopilot control limits:
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Roll = ± 35° except in Approach Track (APPT) mode. When in APPT mode, the roll limits are reduced linearly from ± 25°, above 200 feet radio altitude, to ± 5° at 0 feet radio altitude.
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Pitch = ± 20°. In APPT mode, the nose-down pitch limit is reduced below 300 feet programmed by vertical rate and radio altitude.
Rev 3, Apr 25, 2005 Flight Crew Operating Manual Volume 2
AUTOMATIC FLIGHT CONTROL SYSTEM
AUTOPILOT DISENGAGE
Normal disengagement of the autopilot is accomplished by activating any of the following:
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AP button on guidance panel. AP
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Autopilot quick disconnect (DISC) button on either control wheel.
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Manual stabilizer trim when touch control steering (TCS) not active.
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YD button on FGC panel.
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TCS button on either control wheel (while depressed). When the TCS button on either control wheel is activated, the aileron and elevator servo clutches are released, the autopilot is disengaged and the flight director is re-synchronized. Releasing the TCS button re-engages the servo clutches and autopilot is engaged, if within normal pitch and roll limits. Where applicable, the flight director modes will react as if the autopilot had just been engaged.
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