Eclipse 500 System Manual page 435

Section 16. Autoflight
16.5 System Description
16.5.1 Autopilot Servos
There are three servos in the aircraft, each controlling one axis of rotation. The roll
control servo is located near the wing root outside of the pressure vessel and the
pitch and yaw servos are located in the tail cone. Control of the servos is
accomplished through central processing modules located within each servo; making
a dedicated autoflight computer unnecessary.
The pitch and yaw servos have additional functionality in that the pitch servo also
provides stick pusher capability and the yaw servo can independently provide the
yaw damper feature. Each of the servos receives power from an individual Electronic
Circuit Breaker (ECB) located within Electronic Circuit Breaker Unit three (ECBU3),
which is connected to the right forward electrical bus.
16.5.2 Autopilot
GENERAL
When engaged, the autopilot controls the ailerons, elevators, and rudder to meet the
targets set by the flight director depicted on the PFD. Green AP text appears in the
upper left-hand portion of the ADI to indicate that the autopilot is engaged. The yaw
damper can be independently engaged in the roll (ailerons) and pitch (elevator) axis.
Should the autopilot be engaged without any previous flight director modes selected,
the autopilot will enter pitch and roll hold modes. Although the yaw damper can be
engaged independently, it is automatically engaged when the autopilot is engaged.
ENGAGEMENT ENVELOPE
The following conditions must be met for the autopilot to engage:
1. Pitch Attitude ........................................................................... Within -50° and +50°
2. Pitch Rate.............................................................................. Within ± 5° per second
3. Roll Angle ..........................................................Within 75° Left or Right Wing Down
4. Roll Rate ............................................................................. Within ± 10° per second
5. Time after Takeoff (Weight Off Wheels) .................................................. 15 seconds
6. Normal Acceleration-Flaps UP............................................................. Within 0g-2G
7. Normal Acceleration-Flaps Extended.............................................. Within 0.5g-1.5g
8. Lateral Acceleration ..............................................................................Within ± 0.5g
NOTE:
Once engaged the autopilot will maintain the following limits:
• Pitch attitude within -15° and +25°
• Pitch rate within ± 3.5° per second
• Roll angle within 30° Left or Right Wing Down
• Roll rate within ± 2° per second
Version 2.0 April 2007
Copyright © — Eclipse Aviation Corporation
Eclipse 5OO Systems Manual
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