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Information in this document is subject to change without notice. Dynon Avionics reserves the right to change or improve its products and to make changes in the content without obligation to notify any person or organization of such changes.
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Revision History DATE APPROVED DESCRIPTION OF CHANGE 6/1/2013 Initial release 3/1/2014 Updated for SV v10.0. • Added BANK ANGLE LIMIT • Mention of SV-AP-PANEL only active in EXPERT mode • 12/1/2016 ECO 246525 Changed default value of VSI Gain 9/8/2022 ECO 380245 Reformatted document.
This document is a supplemental reference to the Skyview System Installation Guide document. Using this Manual To reduce paper, Dynon does not provide a printed version of this manual. However, Dynon grants permission to third parties to print this manual, as necessary. The most recent PDF version is available for download at dynon.com/docs.
2 Important Steps Prior to In-Flight Tuning It is essential for good autopilot performance to ensure the autopilot servos are properly installed and correctly connected to the aircraft's flight control systems. Poor installation, or incorrect connection may result in poor performance or safety hazards. Ensure the servos are installed in accordance with the instructions in the system installation manual.
Broken Shear Screw Test Every Dynon autopilot servo contains a shear screw to mechanically limit the force the servo can provide. In the event this screw fails the affected axis will not function. To test for a broken shear screw: 1.
3 Roll Axis Tuning The roll axis should be tuned prior to tuning or engaging any other axis. Ensure all pre-flight items from Section 2 have been completed. Failure to complete pre-flight will prevent successful autopilot tuning. Tuning Procedures The following procedures should be conducted: •...
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3.1.2 Track Mode Autopilot performance in TRK mode is dependent on performance in HDG mode and GPS signal integrity. If autopilot is properly tuned in HDG mode, no changes should be necessary to achieve acceptable TRK mode performance. There are no settings available to the user that affect only track mode performance.
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3.1.4 GPS/GPSS/LNAV/LPV Navigation Mode Autopilot performance in GPS/GPSS/LNAV/LPV navigation modes is dependent on performance in HDG mode and navigation signal integrity. Any changes to HDG mode tuning will affect performance in GPS/GPSS/LPV navigation mode. To allow for optimal tuning performance, tune the autopilot for GPS/GPSS/LNAV/LPV performance in calm winds. Crosswind correction is applied automatically during normal operation.
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3.1.5 Roll Tuning Troubleshooting If performance is not acceptable, evaluate and perform the corresponding actions in the following table. If these actions do no resolve issues, contact Dynon Technical Support. Issue Action(s) Increase ROLL TORQUE. Reduce ROLL SENSITIVITY ROLL SLIP indications appear.
Roll Axis Parameters Parameter Description Default ROLL TORQUE Maximum output torque of servo. Amount of servo motor travel relative to autopilot output signal for roll ROLL HIGH axis. Applied at maximum autopilot speed limit (as set in pitch servo SPEED settings).
4 Pitch Axis Tuning The pitch axis should be tuned after tuning the roll axis. Ensure all pre-flight items from Section 2 have been completed. Failure to complete pre-flight checks is likely to prevent successful servo tuning. Tuning Procedures The following procedures should be conducted in smooth air. Ensure that the high and low autopilot airspeed limits are set appropriately before beginning these procedures.
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4.1.3 Altitude Hold Mode With the aircraft in trimmed, level flight: 1. Operate the aircraft at normal cruising speed. 2. Engage autopilot in HDG + ALT mode. 3. Increase altitude bug by 500 ft 4. Press NOSE UP to start VS climb at 500 fpm. Autopilot should automatically capture new altitude.
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6. If acceptable performance is not achieved, see troubleshooting steps in section 4.1.7. 4.1.6 Turbulence Tuning Procedure The Dynon autopilot can be adjusted to compensate for small updrafts and downdrafts. These settings can be adjusted in light turbulence or left at default values if performance is acceptable.
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4.1.7 Pitch Tuning Troubleshooting If performance is not acceptable, evaluate and perform the corresponding actions in the following table. If these actions do no resolve issues, contact Dynon Technical Support. Issue Action(s) Ensure aircraft is kept in trim during flight.
Pitch Axis Parameters Parameter Description Default PITCH TORQUE Maximum output torque of servo. Amount of servo motor travel relative to autopilot output signal for pitch axis. PITCH HIGH SPEED Applied at maximum autopilot speed limit. Linear interpolation between this SENSITIVITY setting and LOW SPEED SENSITIVITY based on airspeed.
5 Yaw Damper Tuning The yaw damper should be tuned after tuning the roll and pitch axis. Ensure all pre-flight items from Section 2 have been completed. Failure to complete pre-flight checks is likely to prevent successful servo tuning. Tuning Procedures The following procedures should be conducted in smooth air.
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5.1.2 Yaw Tuning Troubleshooting If performance is not acceptable, evaluate and perform the corresponding actions in the following table. If these actions do no resolve issues, contact Dynon Technical Support. Issue Action(s) Ensure aircraft is kept in trim during flight.
Yaw Damper Parameters Menu Parameter Description Default YAW TORQUE Maximum output torque of servo. Amount of servo motor travel relative to autopilot output signal for yaw axis. Applied at maximum autopilot speed limit. Linear interpolation YAW HIGH SPEED between this setting and LOW SPEED SENSITIVITY based on SENSITIVITY airspeed.
6 Lost Motion Compensation Lost Motion Compensation is an autopilot feature which allows the autopilot to automatically compensate for flight control systems that do not have tight coupling between the autopilot servo and the flight control surface. Lost Motion Compensation SHOULD NOT be used to compensate for improperly rigged control systems.
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6.1.2 Pitch Axis Lost Motion Tuning This procedure should only be used if the autopilot slowly oscillates about the commanded airspeed or commanded altitude. This procedure should be executed only after all other pitch tuning procedures have failed to yield satisfactory results. Most properly rigged aircraft will not benefit from using this procedure.
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