Page 1 480 Ruddiman Drive TRIO AP Flight Manual Supplement North Muskegon, MI 49445 L-1006-01 Rev D FOR Trio Pro Pilot Autopilot ON Cessna 172, 175, 177, 180, 182, 185 and Piper PA28 Aircraft Document Number L-1006-01 Revision D Original Release July 19, 2017 This Supplement must be attached to the FAA Approved Airplane Flight Manual when the Trio Pro Pilot Autopilot is installed and activated in accordance with STC SA04230CH. The Information contained herein supplements the information of the basic Airplane Flight Manual. For Limitations, Procedures and Performance information not contained in this Supplement, consult the basic Airplane Flight Manual. Timothy P. Smyth Manager, Chicago Aircraft Certification Office Federal Aviation Administration Des Plaines, Illinois DATE: 1 of 12
LOG OF REVISIONS Rev. No. Page Number(s) Description Date of Revision FAA Approval * New A B C D 1-12 1-12 Page 1 Page 1 Page 1 Original Release July 19, 2017 Added STC Number to Page 1 Updated Revision Numbers, Title Updated Revision Numbers, Title, Header Updated Revision Numbers, Title, Header 11/02/2017 11-26-2017 02-02-2018. DATE: July 19, 2017 2 of 12
TABLE OF CONTENTS Page SECTION I - GENERAL...4 SECTION II - LIMITATIONS...5 SECTION III - NORMAL PROCEDURES... 6-11 SECTION IV - EMERGENCY / ABNORMAL PROCEDURES...12 SECTION V - EMERGENCY / ABNORMAL PROCEDURES...12 DATE: July 19, 2017 3 of 12
SECTION I GENERAL EQUIPMENT DESCRIPTION The Trio Pro Pilot Autopilot system is comprised of an autopilot control head, a roll servo, a pitch servo, interface harness, and bracketry and hardware necessary to mount the servos and attach the servos to the aircraft roll and pitch control systems. Depending on the specific installation The autopilot control head may either be a round unit that fits into a standard 3.125 instrument panel opening or a Panel mount version installed in a standard radio stack. The Autopilot has both lateral and vertical control modes and several important safety features. The lateral modes allow basic wing leveling functions, and may be interfaced to either a portable or panel mounted GPS which will enable the autopilot to follow a flight plan originating in the GPS (TRK mode), fly a pilot selected groundtrack reference vector based on GPS guidance (CRS mode) or intercept back to a flight plan route after a vector or other off-track navigation is cancelled (INT mode). An added lateral navigation feature is the ability to select a Track Offset Position (TOP) of up to three nautical miles either right or left of the desired track. This adds greatly to safety when flying crowded airways or passing crowded navigation fixes during VFR operations. All basic vertical navigation functions are barometrically based and are completely standalone. These vertical modes include Altitude Hold, climbs and descents controlled by either vertical speed or airspeed and the ability to enter a preselected altitude. Precision GPS approaches are possible when the autopilot is being controlled by a certified WAAS capable panel mounted. In addition to the lateral and vertical navigation modes several safety features have also been incorporated. In the event of inadvertent penetration into IMC conditions during VFR flight, an AUTO 180 feature can be activated which will automatically energize both the H NAV and V NAV servos, place the aircraft in an altitude hold vertical mode, and execute either a right or left 180 degree turn to exit the IMC conditions as recommended by the FAA. In the event of a loss of control situation the RECOVER function will command both servos ON and initiate a straight ahead wings level recovery. The aircraft is protected from either a low airspeed stall or excess maximum airspeed as well by specific airspeeds set during the installation. The aircraft is also protected against the case where the pilot fails to disconnect either or both servos prior to takeoff. In this case the autopilot computers will recognize this situation and disconnect the servos from the flight controls. Note The Pro Pilot Autopilot does not replace any of the aircraft primary flight instruments; it is the pilots responsibility to fly and navigate the aircraft in accordance with the information displayed on the aircraft s primary flight instruments. DATE: July 19, 2017 4 of 12
SECTION II - Limitations 1. Minimum Engagement Altitude a. 500 feet AGL. b. In flight autopilot operation is prohibited below an altitude of 500 feet AGL on certificated aircraft where the autopilot has been installed via STC XXXXXXX. 2. Maximum Operating Altitude is 20,000 feet MSL. 3. This autopilot has not been evaluated to meet certification requirements for coupled instrument procedures, including coupled approaches. Therefore coupled instrument approaches and procedures are not authorized without further approval. 4. This autopilot may only be interfaced with GPS equipment listed on STC Group LLC document number 1006001. 5. V NAV terminology referenced in this manual is standard TRIO systems nomenclature, and should not be construed to authorized VNAV operations as defined by FAA policy. Note The FAA definition of VNAV specifies a descent to a specific GPS location in space. The Trio definition of V NAV (note the space between the letter V and NAV ) refers to the ability of the Trio Pro Pilot autopilot to climb or descend to a specific altitude, not a specific GPS location in space. DATE: July 19, 2017 5 of 12
SECTION III - NORMAL OPERATING PROCEDURES H NAV Servo LED V NAV Servo LED H NAV Servo On/Off On/Off Switch V NAV Servo On/Off GPSS/GPSV LED s Display Screen H MODE LEDs V MODE LEDs H MODE Pushbutton V MODE Pushbutton Slip-Skid Indicator Rotary Encoder And Pushbutton Trio Pro Pilot Autopilot Operation Power and Disconnect Controls ON/OFF Switch - disconnects all control head power and servo power. This switch is located on the front panel face of the Instrument mount unit. The power switch for the panel mount unit is located as a separate switch on the instrument panel Circuit Breaker the instrument panel mounted circuit breaker disconnects airframe power to the autopilot system. DATE: July 19, 2017 6 of 12
Pilot Controlled Steering (red yoke button) PCS button when pressed disconnects both the V NAV and H NAV servos. When the Pilot Controlled Steering (PCS) button is pressed and held for more than 3 seconds the PCS function is activated. The PCS function allows immediate disconnect of the roll and pitch servos so the pilot can fly the airplane to a specific altitude and/ or groundtrack. When the PCS button is released the servo will automatically reengage and the aircraft will hold that groundtrack in the course (CRS) mode. If the vertical rate at PCS switch release is less than 200 FPM the autopilot will go into altitude hold. If the vertical rate is +/-200 FPM or more, the autopilot will go into either the VS rate at release, or will lock to the airspeed present at release of the switch. The VS rate or airspeed is selected by the setting in the PREFERENCES menus. Alarms A flashing H NAV servo LED or V NAV servo LED (not in a PCS active state) indicates an automatic servo disconnect. An alarm message indicating the type of servo fault is displayed and an aural tone is transmitted to the audio system. A flashing waypoint identifier in the lower right display field indicates a negative or no closing velocity on the TO waypoint. This happens if you pass the last waypoint in your flight plan or turn such that you are flying away from the current waypoint. ERR displayed on the VS or ALT SEL display right side fields indicates an incorrect combination of preselected altitude and vertical rate has been set. Correct one of these parameters to clear. MINIMUM AIRSPEED the minimum airspeed threshold has been crossed and the autopilot is taking corrective action MAXIMUM AIRSPEED the maximum airspeed threshold has been crossed and the autopilot is taking corrective action. Safety Features. Auto servo disconnect on takeoff automatically ensures the servos are not engaged during the takeoff phase of flight Minimum and maximum airspeed envelope protection. Automatically takes vertical control of the aircraft when the minimum or maximum airspeed thresholds are exceeded and the servos are ON. If the airspeed decays below the minimum airspeed threshold the autopilot will take control and perform an immediate pitchover to regain airspeed. If the maximum airspeed is exceeded the autopilot will gently pitch the airplane up to reduce the airspeed below the maximum airspeed setting. In both cases, visual and aural alarms are provided to the pilot. The minimum airspeed alarm is released by turning off either servo, or changing the horizontal or vertical mode. The maximum airspeed alarm will reset automatically when the airspeed decays below the threshold setting Auto 180 - allows automatic FAA recommended 180 procedure for inadvertent VFR into IMC conditions. H NAV servo ON/OFF button activates the left AUTO 180 function when pressed for three seconds. The V NAV servo O/OFF button activates the right AUTO 180 function when pressed for three seconds. DATE: July 19, 2017 7 of 12
RECOVER automatically controls the aircraft to straight and level flight to prevent loss of. Control. This mode is selected by pressing and holding the instrument panel mounted RECOVER button for 1 second. Track Offset position used to side step the route centerline in the TRK mode. This is selected by pressing and turning the rotary encoder and pushbutton while in the track (TRK) mode. Circle Last Waypoint circles last flight plan waypoint (not applicable if GPSS is active). This feature is automatically activated when enabled in the PREFERENCES menu when the last waypoint in a flight plan or GO TO has been passed DATE: July 19, 2017 8 of 12
Navigation Features Lateral Navigation H NAV servo ON/OFF button Turns the roll servo ON or OFF by pressing the button Activates the left AUTO 180 function when pressed for three seconds H MODE pushbutton Switches the rotary encoder and pushbutton operation to H NAV functions on first press Changes the mode between TRK, CRS and INT modes (TRK CRS INT) TRK mode Tracks a flight plan or GO TO command from the host GPS Upper left field displays bearing to waypoint from current position Lower left field displays the current groundtrack (GTK) rotary encoder and pushbutton press and turn sets the TRACK OFFSET (TOP) value rotary encoder and pushbutton press (only) sequences GPS data the upper right display field rotary encoder and pushbutton turn (only) selects lower right display field GPS data rotary encoder and pushbutton double-click press (only) allows lower right field to scan incoming GPS data rotary encoder and pushbutton rotation counterclockwise immediately returns to rateof-turn display CRS mode Allows the pilot to fly a groundtrack referenced vector (heading bug functionality) Upper left field displays the commanded vector (CMD) Lower left field displays the current groundtrack (GTK) rotary encoder and pushbutton turn selects the vector the pilot wishes to fly rotary encoder and pushbutton press (only) sequences GPS data the upper right display field INT mode Flies a preselected intercept track back to the flight plan. Sequences back to TRK mode automatically when the flight plan has been intercepted. Upper right display field shows intercept distance to flight plan (IDS) Lower left field displays the current groundtrack (GTK) rotary encoder and pushbutton turn (only)modifies the preselected vector back to flight plan intercept rotary encoder and pushbutton press (only) sequences GPS data displayed in the upper right display field NOTE: INT may not engage if the crosstrack error (XTK) is less than 0.5 NM) DATE: July 19, 2017 9 of 12
Vertical Navigation V NAV servo ON/OFF button Turns the pitch servo ON or OFF by pressing the button Activates the right AUTO 180 function when pressed for three seconds V MODE pushbutton Switches the rotary encoder and pushbutton operation to V NAV functions on first press Allows setting parameters and controlling V NAV associated functions Sequences through the vertical mode control menus ( AH VS ALT SEL ALT SET) Pressing and holding for three seconds clears all V NAV settings (VS mode, ALT SEL mode) and returns the vertical mode to ALT HLD. ALT HOLD mode Always activates when V NAV is turned on the first time if no other V NAV functions (VS rate, ALT SEL) have been set. VS Mode allows setting the vertical rate for a climb or descent Turning the ENCODER sets the vertical rate. Upper right display changes from VS SET to VS ARM. With ARM active pressing the encoder will: Activate the vertical rate if the servo is ON. Upper right display field = VS ACT Places the unit in suspend if the servo is OFF. Upper right display field = VS SUSP When the V NAV servo is turned on the vertical mode will activate = VS ACT Pressing the ENCODER while VS is active will force the ALT HLD mode and put the VS mode in suspend. Pressing the encoder again will cancel the ALT HLD mode and return the VS mode to active ALT SEL sets a preselected altitude When selected initially displays the current altitude. Rotate the encoder to adjust the preselected altitude. Pushing the encoder will change in 1000 ft increments, rotating only will change in 100 ft increments. Display changes from ALT SEL to ALT ARM Press the ENCODER. The current altitude being used by the autopilot is displayed. Correct if necessary by rotating the ENCODER. Pressing the encoder again will activate the VS rate and altitude preselect. NOTE If a preselected altitude is active the VS ACT or VS SUSP display will change to VSP ACT and VSP SUS to signify a preselected altitude is active. DATE: July 19, 2017 10 of 12
NOTE If ERR is displayed in the VS or ALT SEL screens you have selected a climb rate with a preselected altitude below your current altitude, or a descent with a preselected altitude above your current altitude. The selected vertical rate will active but the preselect function will remain inactive until the mismatch is cleared. Trio Pro Pilot Autopilot fault annunciation NOTE In all cases of an autopilot fault or malfunction the pilot should rely on the flight instruments to ensure safety of flight. The autopilot does not connect to or supply data to any flight instrument. The servos are designed to exert very little pressure on the flight controls so any abnormal autopilot control inputs can be easily overcome until the autopilot can be disconnected. Several methods can be used to disconnect the autopilot servos including the yoke mounted PCS/ The H NAV and/or V NAV servo ON/OFF pushbutton, the front panel ON/OFF switch ( instrument mount only) the panel mounted power switch ( panel mount only) or the instrument panel circuit breaker providing power to the autopilot system. Any servo fault will result in an immediate disconnect of that servo from the flight controls A message is displayed on the front panel of the autopilot showing the type of fault that resulted in the disconnect condition. During a precision LPV approach the system will display ABORT APPROACH if any of the following conditions exist. The aircraft is more than 500 ft above the virtual glideslope when the vertical guidance becomes active. The V NAV altitude hold mode is activated and the H NAV guidance will be supplied by the GPSS roll steering input (ARINC 429 GPSS LED is ON) The horizontal mode is changed from track (TRK) to the course (CRS) or intercept (INT) mode. The H NAV guidance will be straight ahead on the approach course, or as commanded by the pilot. The V NAV guidance will be the altitude hold mode If the H NAV servo sustains a fault condition. If the H NAV servo faults the V NAV guidance will be the altitude hold mode. If the V NAV servo sustains a fault condition. If the V NAV servo faults the H NAV guidance will be supplied by the GPSS roll steering input (ARINC 429- GPSS LED is ON) The last fix in the approach sequence is passed. The V NAV altitude hold mode is activated and the H NAV guidance will be supplied by the GPSS roll steering input (ARINC 429) DATE: July 19, 2017 11 of 12
SECTION IV - EMERGENCY/ABNORMAL PROCEDURES A. EMERGENCY PROCEDURES No change to the basic AFM. B. ABNORMAL PROCEDURES No change to the basic AFM. SECTION V - PERFORMANCE No change to the basic AFM. DATE: July 19, 2017 12 of 12