Section 7 - Autopilot
In order to prevent any mixup between the default G1000 autopilot and our STEC 55X please remove all autopilot hotkeys from your hardware except and only assign the following:
TOGGLE AUTOPILOT VS HOLD
TOGGLE AUTOPILOT HEADING HOLD
TOGGLE AUTOPILOT BACKCOURSE HOLD
TOGGLE AUTOPILOT APPROACH HOLD
TOGGLE AUTOPILOT ALTITUDE HOLD
AUTOPILOT NAV1 HOLD
AUTO THROTTLE TO GA
Overview
The Tecnam P2006t equipped with System Fifty Five X for its autopilot system. The System Fifty Five X is a rate autopilot that controls the roll and pitch axes of the aircraft. The autopilot's main function is to convert pilot commands to logic signals for the roll and pitch computers. As the pilot enters the desired mode by pressing the appropriate mode selector switch, the computer acknowledges the mode, causing the appropriate annunciator to illuminate.
Due to some limitations of the default autopilot in MSFS, here are some features of the S-Tec 55X autopilot system, that are not implemented:
Autopilot with GPS always uses GPSS mode. In other words, there is no standard GPS mode. If the pilot presses the nav button while the GPS source is being selected, it will set to GPSS mode instead of pressing the nav button twice.
Control Wheel Steering (CWS) is not available.
Altitude Correction on ALT mode is not available.
Autopilot Self-Test
When the aircraft started from cold and dark cockpit position, the S55X will conduct a self-test automatically before the autopilot can be engaged. The test can be seen as follows:
Observe that all segments of the hardware display and annunciators illumintase for 5 seconds.
Satisfactory completion of the Self-Test is indicated when the Ready (RDY) annunciator remains on at the end of the 5 second self-test.
Should a fault be detected, the FAIL annunciator will remain on at the conclusion of the self-test and the autopilot will not operate.
Normal Operating Procedures
Heading Mode
Set the heading bug on the DG or HSI to the desired heading, and press the HDG button. The HDG annunciator will illuminate. New headings can be selected simply by repositioning the heading bug.
When operating in the HDG mode, the system is not coupled to any navigation aid. It merely flies the heading bug. It will be necessary to monitor navigation instruments for course deviation due to wind drift and wind correction angles.
Approach (APR) Mode Switch
The APR Mode provide increased sensitivity for VOR or GPS approaches. The pilot may also select this mode if increased sensitivity is desired for enroute NAV tracking. To engage this mode press the APR switch on the Programmer / Computer. APR will be displayed on the annunciator.
GPS Steering (GPSS) Mode
The Autopilot is equipped with a GPS Steering (GPSS) Mode that can be used for normal GPS course tracking or for GPS approach. In GPSS Mode, the heading bug and / or course arrow position has no effect on the autopilot and may be preset for the missed approach heading, etc., as desired.
To enter the GPSS Mode, push the NAV button.
The autopilot will accept steering commands from the GPS unit and will fly the lateral segments of the approach without any further input from the pilot.
When in the GPSS Mode, NAV and GPSS will be annunciated
To delete the GPSS function, push the NAV button again or select HDG Mode.
Reverse (Rev) Mode
The Reverse Mode provides roll commands for intercept and tracking the localizer back course inbound or localizer front course outbound.
Vertical Speed
To engage vertical speed, the autopilot roll axis must be engaged. Selecting HDG Mode or any roll mode will satisfy this requirement. With any roll mode engaged, the pilot may select VS Mode by pressing the VS Mode select switch. The autopilot will synchronize with the aircraft's vertical speed at the time the mode is selected and the corresponding vertical speed will be indicated in the Programmer / Computer display. Vertical speed may now be modified in 100 ft. increments by rotating the VS knob clockwise or counter-clockwise.
The + (positive) symbol annunciation indicates a vertical speed climb selection. Clockwise rotation of the VS knob increases the rate of climb and counter-clockwise rotation decreases the rate of climb to 0. The - (negative) symbol annunciation indicates a vertical speed descent selection. Counter-clockwise rotation of the VS knob increases the rate of descent and clockwise rotation decreases the rate of descent to 0. Maximum selectable VS limits are 1600 feet-per-minute (FPM).
Autotrim
The Tecnam P2006 equipped with autotrim functionality. With the autotrim functioning normally, the aircraft elevator trim will be maintained automatically when the Autopilot Master switch is on. When the elevator trim is in motion, TRIM and the up or down symbol will annunciate indicating trim in motion and the direction of travel. Should the trim continue to run in excess of 7 seconds, all of these annunciations will flash. If a failure has occurred in the Autotrim, the system will automatically shuts down and airplane is in manual mode of operation.
The pilot is also provided with Manual Electric Trim when the autopilot is disengaged. To use Manual Electric Trim, simply move the trim switch located on the aircraft's control wheel in the desired direction of trim. FWD for nose down or AFT for nose up. TRIM will be annunciated and will flash while the trim is in motion.
System Failure and Caution Annunciations
Flashing RDY for 5 seconds
Indicates autopilot disconnect. All annunciations except RDY are cleared.
Flashing NAV, REV, or APR
Indicates off navigation course by 50% needle deviation or more.
Flashing NAV Steady FAIL
Indicates invalid Radio Navigational Signal.
Flashing GS
Indicates Off glideslope centerline by 50% needle deviation or more.
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