Mooney M20M Pilot Operating Handbook
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Mooney M20M Pilot Operating Handbook

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27-0062
N1091A

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  • Page 1 27-0062 N1091A...
  • Page 242 LOG OF REVISIONS Page Description FAA Approval Initial issue. JR Brownell ODA STC Unit Administrator Garmin International, Inc. ODA-240087-CE Date: 1/13/2020 Added hardware variant functionality Erik Frisk information to Table 2 ODA STC Unit Administrator Added reference to -20 and -40 hardware Garmin International, Inc.
  • Page 243 Corrected table formatting See Cover Page Added clarification of Standby Reversionary capabilities Added clarification of EIS configuration to include all EIS capabilities and display parameters Included VFR GPS antenna and Backup Battery Pack as GI 275 system components Added clarifications for Standby instrument configurations with the GI 275;...
  • Page 244 Clarified procedures for AHRS failure; Added a Caution Note to describe Garmin cross- comparison for AHRS/ADC sensors with specific sensor selections enabled Clarified procedures for ADC failure; Added a Caution Note to describe Garmin cross- comparison for AHRS/ADC sensors with specific sensor selections enabled Added underline font to Note Added underline font to Note and Caution;...
  • Page 245 Clarified that barometric altitude is required when interfaced with GTN to provide VNAV functionality Removed typo Added a note to clarify traffic data availability based on services provided by local region/country; Removed typo Added underline font to Note Added underline font to Caution GI 275 Part 23 AML STC 190-02246-12 Rev.
  • Page 246 TABLE OF CONTENTS GENERAL ................... 8 ADAHRS ................... 13 GI 275 ADI ........13 TANDBY NSTRUMENTS AND THE ................13 ACKUP ATTERY ..................14 EFINITIONS ........15 UNCTIONS NCLUDED IN THIS NSTALLATION LIMITATIONS ................. 16 ............16 INIMUM OFTWARE ERSION ............
  • Page 247 NORMAL PROCEDURES ............40 ................40 EFORE AKEOFF ..............42 UTOPILOT PERATION EIS O .................. 44 PERATION PERFORMANCE ..............45 WEIGHT AND BALANCE ............. 45 SYSTEM DESCRIPTION............46 ................ 47 ONTROLS VERVIEW ................ 47 ISPLAY RIGHTNESS ..............47 YSTEM OWER OURCES .................

  • Page 248: General

    GENERAL The GI 275 Multifunction Instrument (hereafter referred to as the “GI 275”) is a panel-mounted, multifunction instrument with a single touch display and virtual “Pages” within each instrument that may be configured as individual “instruments”. The GI 275 can be configured as an ADI, HSI, EIS or MFD with multiple hazard awareness pages, depending on the number and type of integrated navigation and hazard sensor sources.
  • Page 249 Horizontal Situation Indicator (HSI) Units configured as an HSI will contain two pages; an HSI page and an HSI Map page. The HSI Page is a conventional HSI with CDI, VDI, heading indication and compass card. There are navigation annunciations and distance/time fields.
  • Page 250 Standby ADI The HSI and MFD can be configured as a “Standby” instrument to preserve the display of primary flight data in the event the primary ADI fails or the pilot reverts the display either through the rotation of the outer knob counter- clockwise or engages the reversionary switch.
  • Page 251 Engine Indication System (EIS) Units configured for EIS will always display Engine RPM, Fuel Quantity, and Manifold Pressure (if applicable) on the upper portion of the screen. Five configurable pages are available on the EIS unit:  Main Contains all gauges with red/yellow markings ...

  • Page 252: Adahrs

    Function GI 275 Base GI 275 GI 275 (-00) ADAHRS ADAHRS + AP (-10/-30) (-20/-40)   Primary ADI   MFD/Standby ADI         *   HSI/Standby ADI  Autopilot Interface *Requires interface to another GI 275 with an internal ADAHRS configured. Table 2- GI 275 Hardware Variant Functionality GMU 11 and GMU 44B Magnetometer Heading Sensors...

  • Page 253: Standby Instruments And The Gi 275 Adi

    ADAHRS The integral ADAHRS, included in the GI 275 -10, -20, -30, and -40 variants, senses aircraft attitude and air data for GI 275 display of primary flight data and can provide attitude and air data for use by other installed systems. The ADAHRS requires GPS and airspeed inputs for aiding the system.

  • Page 254: Definitions

    Definitions ADAHRS: Air Data and Attitude Heading Reference System ADC: Air Data Computer ADI: Attitude Direction Indicator ADS: Automatic Dependent Surveillance AHRS: Attitude Heading Reference System AMMD: Airport Moving Map Display CDI: Course Deviation Indicator CRS: Course EIS: Engine Indication System Flight Director FLTA: Forward-looking Terrain Alerting...

  • Page 255: Functions Included In This Installation

    Functions Included in this Installation The following table identifies the AFMS sections which contain information relevant to this installation. This table is for the purpose of navigating the AFMS and to assist with identification of important system functions included with this installation.

  • Page 256: Limitations

    LIMITATIONS Minimum Software Version The following or later software versions must be installed for this AFMS revision to be applicable to the installation: Component Identification Software Version GI 275 Multi-Function 2.20 Instrument NOTE This section is not intended to be a comprehensive list of approved software.

  • Page 257: Navigation Angle

    Navigation Angle The Magnetic/True Navigation Angle (as selected in the MENU → SYSTEM → UNITS Page) must match the navigation angle selected on all interfaced GPS/SBAS navigators. If this is not done the navigation deviations will not be accurate. ADAHRS Normal Operating Mode The ADAHRS integrity monitoring uses GPS data and air data.

  • Page 258: Standby And/Or Primary Flight Instruments

    Standby and/or Primary Flight Instruments Do not use a QFE altimeter setting with this system. System functions will not operate properly with a QFE altimeter setting. Use only QNH altimeter setting for height above mean sea level, or the standard pressure setting, as applicable. ...

  • Page 259: Sensor Selection

    Sensor Selection Do not select or operate on secondary AHRS or ADC sensors, unless directed to do so as part of an emergency or abnormal procedure in this AFMS. CAUTION In installations with a Garmin cross-comparison for AHRS/ADC sensors, changing the AHRS/ADC sensor source when a white ATTITUDE/IAS/ALT annunciation is displayed on the primary GI 275 ADI will result in the selection of an inoperative sensor source and subsequent loss of information.

  • Page 260: Datalink Products (Siriusxm And Fis-B)

    Datalink Products (SiriusXM and FIS-B) Do not use datalink weather information for maneuvering in, near, or around areas of hazardous weather. Information provided by datalink weather products may not accurately depict current weather conditions. Do not use the indicated datalink weather product age to determine the age of the weather information shown by the datalink weather product.

  • Page 261: Glove Usage

    Glove Usage The touchscreen can be operated with gloves made for capacitive touchscreens. VFR GPS The VFR GPS (VGPS) is an emergency position source which can provide temporary navigational aid for limited en-route direct-to capability when the certified navigator data is: ...

  • Page 262: Kinds Of Operations

    Kinds of Operations Unless placarded as limited to VFR only operations, equipment installed in a certified aircraft is approved for Day and Night / VFR and IFR operations in accordance with 14 Code of Federal Regulations Part 91, Part 121, and Part 135 when appropriately maintained.

  • Page 263: Minimum Flight Crew

    Equipment Number Req’d installed GI 275 EIS 1 or 2* 1 or 2* Engine Adaptor Unit (GEA 24/110) 1 or 2* 1 or 2* External EIS Annunciator 0, 1, 2, or 0, 1, 2, or * One GI 275 EIS and GEA 24/110 are required per engine ** An external annunciator is installed when the GI 275 EIS is outside of the pilot’s primary field of view.
  • Page 264 2.28.2 GI 275 Reversion Backup Switch Adjacent to the GI 275 Reversion Backup Switch: Auto 2.28.3 Installations Limited to VFR  This installation is not limited to VFR.  This installation is limited to VFR and the following placard is required: “AIRCRAFT LIMITED TO VFR”...

  • Page 265: Emergency Procedures

    EMERGENCY PROCEDURES NOTE Depending on the installation, some procedures contained within this section may not apply. Emergency Procedures 3.1.1 Loss of Primary Flight Information If the primary GI 275 ADI fails (loss of some or all primary flight information, display is blank, frozen, or unresponsive). Use standby flight instruments for attitude, airspeed, altitude, and heading reference.
  • Page 266 3.1.2 AHRS Failure AHRS failure is indicated by the removal of the attitude/heading information and a red X on the GI 275 ADI. Standard rate turn indications will also be removed. A heading failure may also occur as described in Section 3.2.1. Continue flight by reference to the standby ADI or manually select “ON”...
  • Page 267 3.1.3 ADC Failure ADC failure is indicated by:  Red X over the airspeed and altitude tapes  Yellow X over the digital vertical speed value If valid GPS data is available, the GI 275 will automatically revert to display GPS-calculated altitude relative to mean sea level.
  • Page 268 3.1.4 ATTITUDE, ALT, or IAS monitor CAUTION If an ATTITUDE, ALT, or IAS miscompare CAUTION is displayed in yellow on the attitude display or airspeed/altitude tape: Cross check flight instruments against all available information to determine which indications are correct Seek VFR conditions or land as soon as practical NOTE White ATTITUDE/ALT/IAS no compare annunciations indicate...
  • Page 269 NOTE For protection, backup battery operation is inhibited if the battery‘s temperature drops below -20° C or exceeds 80° C. Battery parameters such as the battery temperature can be viewed in the System Menu. CAUTION To conserve power and to preserve the display of primary flight data and direct-to navigation capabilities with the optional VGPS receiver, GI 275 backup battery operation internally load-sheds interfaces, which will disable the normal interface with certified...
  • Page 270 3.1.10 Terrain Alerts Annunciation Annunciation Aural Alert Action All Pages Terrain Page Disconnect autopilot “Terrain, Terrain and initiate maximum Pull up, Pull up” performance climb (maximum takeoff -OR- power and best angle of “Obstacle, Obstacle climb airspeed) Pull up, Pull up” -OR- NOTE: Only the climb -OR-...

  • Page 271: Abnormal Procedures

    Abnormal Procedures 3.2.1 Heading Failure If the GI 275 is configured with a VFR GPS or interfaced to a certified GPS source, the HDG indications will be replaced with track (TRK) indications in magenta in the event of a heading failure. The heading bug and course pointer will continue to function normally, using GPS ground track as a reference instead of magnetic heading.
  • Page 272 If GPS track is not available: Use standby compass for heading reference. NOTE Without magnetic heading or GPS track, the CDI provides no directional information. Only course deviation information is presented, and the orientation of the CDI is based on the selected course, regardless of aircraft heading.
  • Page 273 3.2.4 Navigation Data Failure (VOR/LOC/GS) Navigation data failure may be indicated by any or all of the following:  Loss of course deviation information on ADI  Loss of glideslope/glidepath information on ADI  Loss of bearing pointer on HSI Select alternate navigation source or refer directly to external navigation data.
  • Page 274 3.2.8 EIS Display Parameter Failure Indicated by individual parameters having a red or yellow X drawn through the gauge and data removed (see EIS failure procedure for loss of entire EIS function). Monitor remaining parameters and set engine controls to operate within limitations.

  • Page 275: Warnings, Cautions, And Advisories

    WARNINGs, CAUTIONs, and Advisories The following tables show the color and significance of the warning, caution, and advisory messages which may appear on the GI 275 displays. 3.3.1 WARNING Annunciations – Red Annunciation Pilot Action Cause HDG Fail Display system is not receiving valid heading Standby input from the ADAHRS or AHRS;...
  • Page 276 3.3.2 CAUTION Annunciations – Yellow Annunciation Pilot Action Cause AHRS Limit aircraft Attitude and Heading Reference ALIGN – attitude to ±10º bank System is aligning. AHRS may not Keep Wings and ±5º pitch as align with excessive pitch/bank Level AHRS Aligns - OK angles.
  • Page 277 ALT and/or Cross-check the Differences detected between flagged information displayed airspeed and/or altitude (text on ADI) against other (multiple ADC installations only). sources to identify erroneous information. AHRS 1/2/3 Confirm intended The ADI is using the cross-side AHRS source AHRS sensor and AHRS monitor is selection indicating a miscompare or no- compare (multiple ADI and AHRS...
  • Page 278 Battery Fault Observe the fault The Internal battery has detected an condition on the GI issue which may not allow the 275 by entering the battery to charge or discharge system messages for properly. Such as “Charge Inhibited - further details. Seek unable to charge the battery”...
  • Page 279 3.3.3 Advisories – White Annunciation Pilot Action Cause ATTITUDE, ALT, Be aware that the The other (unselected) or IAS other (unselected) AHRS/ADC source is (text on ADI) AHRS/ADC source is unavailable. not available AHRS 1/2/3 Confirm intended The ADI is using the cross- AHRS source side AHRS sensor (multiple selection...

  • Page 280: Normal Procedures

    NORMAL PROCEDURES Before Takeoff Review displays for any abnormal warning, caution, or advisory indications. Perform a visual inspection of the fuel tank or other method such as a dipstick, sight gauge, or drip gauge to verify that the fuel quantity indication provided by the GI 275 is accurate.
  • Page 281 Select the Reversion Backup Switch to the “AUTO” position and verify that the display return to their normal state and other configured pages are once again selectable. GI 275 Part 23 AML STC 190-02246-12 Rev. 4 Airplane Flight Manual Supplement Page 41 of 70 FAA APPROVED...
  • Page 282 Autopilot Operation Refer to Section 7.15 for the applicable autopilot interface capability and installation details. 4.2.1 Autopilot Disconnect Test The autopilot may receive attitude from a GI 275 ADI. If this is installed, an “AP DISC” button will be present in the Menu → Options menu, and this function must be tested using the following procedure.
  • Page 283 4.2.3 GPSS Emulation When enabled by the installer for autopilots that do not support GPSS roll steering, GPSS allows a configured legacy autopilot to fly GPS curved plan legs (e.g., arcs, procedure turns, etc.) as well as straight legs. When the GPSS emulation mode is enabled in the GI 275 ADI, the autopilot will direct the aircraft to and then guide the aircraft along the active GPS flight plan leg.

  • Page 284: Eis Operation

    4.2.4 Coupling the Autopilot for Enhanced Descent-Only VNAV The GI 275 allows for the display of Enhanced Descent Only (EDO) Vertical Navigation (VNAV) deviations when interfaced with a Garmin GTN. In order to provide autopilot coupling to the EDO VNAV guidance, the interface must also include a Garmin GFC 600 or GFC 500 with VNAV capability.

  • Page 285: Performance

    PERFORMANCE No change. WEIGHT AND BALANCE See current weight and balance data. GI 275 Part 23 AML STC 190-02246-12 Rev. 4 Airplane Flight Manual Supplement Page 45 of 70 FAA APPROVED...

  • Page 286: System Description

    SYSTEM DESCRIPTION The following units are installed in this aircraft:  ADI  HSI  HSI Standby ADI  MFD  MFD Standby ADI  EIS A detailed GI 275 Pilot’s Guide is available through the Garmin website or your Garmin dealer.

  • Page 287: Controls Overview

    Controls Overview A dual concentric knob with a center push-button provides the primary means with which to navigate between screens and access menus and functions of the GI 275. The outer knob will always change from Page-to-Page on GI 275s that have multiple pages.

  • Page 288: System Status

    Installed Circuit Breaker Label Equipment  Primary ADI  GI 275 configured for Engine Monitoring – Single Engine  GI 275 configured for Engine EIS L and EIS R Monitoring – Multi Engine  GI 275 configured as a MFD ...

  • Page 289: Databases

    Databases The GI 275 utilizes databases to provide some system functions. Database status information is available to the pilot at system startup on the MFD splash screen and during normal operations on the Menu → System → Databases (or DB) menu. Controls are provided for manually initiating a database update.

  • Page 290: Integrated Standby System

    the last crew profile used. Only one profile may be selected as active at a time. New profiles are created with the settings currently in use. Integrated Standby System Standby instruments (attitude, altitude, airspeed) may be provided by a second GI 275 display.

  • Page 291: Gps Approach Mode Annunciations

    GPS Approach Mode Annunciations When interfaced with a certified GPS navigator and the GPS navigator is the selected source, the GI 275 HSI and HSI Map display the current GPS operational mode. The GI 275 abbreviates the approach modes as defined in the table below.

  • Page 292: Aircraft Audio Interface

    Aircraft Audio Interface The primary (pilot) ADI is interfaced to the aircraft audio system to provide aural alerts (altitude alerter, minimums, terrain). If multiple ADIs are installed, only the primary ADI is interfaced to the audio system (to prevent duplicate aural alerts).

  • Page 293: System Data Logging

    If pilot-selected navigation angle settings differ on the navigator and the GI 275, the display aspects will be inaccurate. System Data Logging The GI 275 system incorporates a data logging feature that can record parameters related to the aircraft’s primary flight instruments, engine indications, and aircraft configuration.
  • Page 294 When dual GI 275 -10, -20, -30, and -40 variants are installed and configured, software monitors provide detection of sensor miscompares. If a monitor detects a difference between sources exceeding the allowable limit, a visual attitude, altitude, heading, or airspeed miscompare annunciation will be shown on the ADI.
  • Page 295 7.14.3 Synthetic Vision Technology SVT may optionally be provided to assist the pilot in maintaining situational awareness with terrain, obstacles, and airborne traffic. SVT controls are provided via Menu → Options → Terrain/SVT. Synthetic terrain, horizon headings, and airport signs can be enabled or disabled from this menu.
  • Page 296 7.14.4 Airspeed If configured, the airspeed tape on the left side of the ADI displays red/white striping to indicate the maximum allowable airspeed (V ). This maximum allowable airspeed display is configured to indicate the appropriate maximum allowable airspeed for the airplane. The airspeed tape displays a red low-speed awareness band at the lower range of the airspeed tape.
  • Page 297 navigation source is shown on the left side of the HSI or LDI. CDI source selection can be synchronized across multiple GI 275 and G500 TXi’s if enabled by the pilot. 7.14.7 HSI The course pointer and deviation indicator are shown as a single, solid line for GPS 1 and VLOC 1, and as an outline with no fill for GPS 2 and VLOC 2.

  • Page 298: Autopilot Interfaces

    7.14.10 Minimum Altitude Display and Alerting When enabled by the pilot, an altitude minimums bug will be displayed in cyan on the altitude tape. If a radar altimeter is installed, the pilot can select between barometric or radar-altitude minimums. If installed with a G500 TXi, the minimums set on the TXi will crossfill to the GI 275.
  • Page 299 7.15.1 Navigation Data for Autopilots The GI 275 can provide course and heading data to the autopilot based on the data selected for display on the HSI. For aircraft equipped with multiple GPS/NAV systems, the HSI can act as a selection hub for the autopilot’s NAV mode.

  • Page 300: Mfd

    7.15.2 Flight Director Display If autopilot flight director commands are interfaced to the GI 275, they will be presented as a single cue flight director on the ADI. Control of the flight director is accomplished via the autopilot/flight director controller; there are no pilot controls or adjustments for the flight director on the GI 275.
  • Page 301 The active flight plan of an interfaced navigator is shown in magenta on the Map. Traffic, Terrain, Weather, Land, and Aviation data can be selected for overlay on the Map as well. 7.16.2 Traffic Display The MFD can display traffic data from interfaced traffic systems. Sources of traffic data include TIS-A, TAS/TCAS, and ADS-B TIS-B.

  • Page 302: Terrain Awareness And Alerting

    Traffic can be displayed on the moving map as an overlay. Additional filtering based on traffic type (all, advisories, alerts) can be selected using the Menu Traffic selection. For TIS-A traffic selection of the advisories and alerts will result in display of alerted targets only. Traffic page units are always in nautical miles and feet.
  • Page 303 An annunciator located in the upper right corner of all configured pages on ADI, HSI and MFD units provides text annunciations of alert conditions.  For all GI 275 configurations which provide alerts and all configurations where the GI 275 is interfaced to a GTN with TAWS-B enabled: If a terrain alert occurs and the MFD is not selected to the dedicated terrain page, then a terrain “popup window”...
  • Page 304 7.17.1 Weather Data The MFD can display weather data from interfaced datalink systems. Sources of weather data include the Garmin “GDL 69(A)” and “GDL 69(A) SXM” Sirius XM receivers and Garmin ADS-B transceivers. If one of these optional weather datalink receivers is installed, the pilot will be able to access graphical and text weather products using the MFD.

  • Page 305: Engine Indication System

    Engine Indication System Engine gages are optionally provided for single and twin engine aircraft with four and six-cylinder reciprocating engines. The following indications are provided in all EIS installations:  Tachometer  Manifold Pressure (If required)  Oil Pressure  Oil Temperature Other engine gauges may be provided by either the EIS display or previously installed indicators in their original locations.
  • Page 306 All gauges will highlight the digital readout in yellow or red when entering a non-safe range and cause the colorized CAUTION or WARNING annunciator to flash at the bottom of the EIS screens. 7.18.1 Tachometer For aircraft in which a starting vibrator is installed the RPM indication is not accurate during engine cranking.
  • Page 307 7.18.5 Mixture Leaning GI 275 EIS provides two different lean assist methods, rich of peak or lean of peak. Lean assist mode is entered by pressing the Lean Button on the EGT page. Lean mode automatically detects the EGT peak and indicates peak by using a bar above the EGT indicator for the cylinder.
  • Page 308 7.18.6 Fuel Quantity Usable fuel may be displayed on the EIS display. Main fuel quantities are grouped together and aux/tip fuel quantities are grouped together. Previously installed aircraft low fuel quantity annunciators will be deactivated as part of the fuel quantity installation in some aircraft. In this case, the low fuel annunciators will be placarded as deactivated, and a red or yellow arc must be added to the fuel quantity gauge to indicate the fuel level that corresponds to the low fuel annunciation.
  • Page 309 7.18.9 Engine and Airframe Timers The Timers can be accessed from the Engine Menu. Timer Label Timer Function FLIGHT Flight timer increments in tenths of an hour whenever the aircraft is in an airborne state. This can be triggered via a weight on wheels switch, GPS ground speed, airspeed, or engine RPM depending on the aircraft installation.

  • Page 310: Wireless Functions

    Wireless Functions The GI 275 has a wireless transceiver to provide data to personal electronic devices (PEDs) and includes a Bluetooth and Wi-Fi transceiver. Data such as traffic, datalink weather, entertainment audio information, and attitude information is sent from the GI 275 to the PED. Limitations regarding database operations are found in Section 2.25.
  • Page 312 Garmin International, Inc. 1200 E. 151 Street Olathe, KS 66062 USA Telephone: 913-397-8200 www.garmin.com AFMS – GFC 500 Mooney M20M/M20R/M20S Series 190-02291-18 Rev. 5...
  • Page 313 ESP/USP airspeed reference 07/05/19 Garmin ODA STC corrections Unit Administrator Robert G. Murray Various Procedure Corrections 12/16/19 Garmin ODA STC Unit Administrator Add GI 275 Information See Cover See Cover 190-02291-18 Rev. 5 AFMS – GFC 500 Mooney M20M/M20R/M20S Series Page i...
  • Page 314 This page intentionally left blank. AFMS – GFC 500 Mooney M20M/M20R/M20S Series 190-02291-18 Rev. 5 Page ii...
  • Page 315 ALTITUDE HOLD (ALT) MODE, MANUAL CAPTURE ..............4-2 VERTICAL NAVIGATION (VNAV) ...................... 4-3 GO AROUND ............................4-4 MANUAL PITCH TRIM WITH AUTOPILOT ENGAGED ..............4-4 LATERAL MODES ..........................4-5 190-02291-18 Rev. 5 AFMS – GFC 500 Mooney M20M/M20R/M20S Series Page iii...
  • Page 316 Section 7 – System Description ................7-1 AFCS OVERVIEW ..........................7-1 AUTOPILOT CONTROL UNIT AND DISPLAY ..................7-4 PREFLIGHT TEST ..........................7-7 MESSAGES AND ANNUNCIATIONS ....................7-7 LIGHTING .............................. 7-8 AFMS – GFC 500 Mooney M20M/M20R/M20S Series 190-02291-18 Rev. 5 Page iv...

  • Page 317: Section 1 - General

    CAUTION Operating procedures, techniques, etc., which may result in damage to equipment if not carefully followed. NOTE Operating procedures, techniques, etc., which is considered essential to emphasize. 190-02291-18 Rev. 5 AFMS – GFC 500 Mooney M20M/M20R/M20S Series Page 1–1...

  • Page 318: Abbreviations And Terminology

    AFCS heading mode Indicated Airspeed Instrument Landing System Interrupt KIAS Knots Indicated Airspeed LNAV Lateral Navigation LNAV+V Lateral Navigation with Advisory Vertical Guidance LNAV/VNAV Lateral Navigation / Vertical Navigation Approach AFMS – GFC 500 Mooney M20M/M20R/M20S Series 190-02291-18 Rev. 5 Page 1–2...

  • Page 319: Installed Equipment Interfaces

    Is Navigator #1 interfaced to GFC 500?   VHF Nav Radio #1 Is VHF Nav Radio #1 interfaced to GFC 500?   VHF Nav Radio #2 Pitch Trim Servo Yaw Damper 190-02291-18 Rev. 5 AFMS – GFC 500 Mooney M20M/M20R/M20S Series Page 1–3...

  • Page 320: Installed Features Checklist

    Vertical Speed (VS)   Approach Mode Altitude Capture via Altitude Preselect   Indicated Airspeed (IAS)   VOR/LOC Vertical Navigation (VNAV)  GPS Approach Glidepath  ILS Glideslope AFMS – GFC 500 Mooney M20M/M20R/M20S Series 190-02291-18 Rev. 5 Page 1–4...

  • Page 321: Section 2 - Limitations

    The autopilot must be disengaged below 800 feet AGL for all operations other than approach operations. The GFC 500 autopilot is approved for Category 1 precision approaches and non-precision approaches only. 190-02291-18 Rev. 5 AFMS – GFC 500 Mooney M20M/M20R/M20S Series Page 2–1...
  • Page 322 This page intentionally left blank. AFMS – GFC 500 Mooney M20M/M20R/M20S Series 190-02291-18 Rev. 5 Page 2–2...

  • Page 323: Section 3 - Emergency Procedures

    Do not attempt to re-engage the autopilot or use manual electric pitch trim until the cause of the malfunction has been corrected. 190-02291-18 Rev. 5 AFMS – GFC 500 Mooney M20M/M20R/M20S Series Page 3–1...

  • Page 324: Autopilot Failure / Abnormal Disconnect

    The yaw damper disconnect may be accompanied by an amber YD with a red X in the autopilot status box. The YD is inoperative and will not be available. The autopilot may be re-engaged and disengaged normally, but the yaw damper will remain inoperative. AFMS – GFC 500 Mooney M20M/M20R/M20S Series 190-02291-18 Rev. 5 Page 3–2...

  • Page 325: Pitch Trim Failure

    3. Autopilot ........RESELECT VERTICAL AND LATERAL MODES (if necessary) 4. Throttle ......................ADJUST as necessary NOTE Overspeed protection mode provides a pitch up command to decelerate the airplane to or below the maximum autopilot operating speed. 190-02291-18 Rev. 5 AFMS – GFC 500 Mooney M20M/M20R/M20S Series Page 3–3...

  • Page 326: Underspeed Protection (Minspd)

    3. Autopilot .........RESELECT VERTICAL AND LATERAL MODES (if necessary) 4. Throttle ......................ADJUST as necessary NOTE Autopilot Underspeed Protection Mode provides a pitch down command to maintain 80 KIAS. AFMS – GFC 500 Mooney M20M/M20R/M20S Series 190-02291-18 Rev. 5 Page 3–4...

  • Page 327: Section 3A - Abnormal Procedures

    2. NAV Source ..................SELECT a valid NAV source 3. NAV Key ..........................PRESS If on an instrument approach at the time the navigation signal is lost: 4. Missed Approach Procedure ..............EXECUTE (as necessary) 190-02291-18 Rev. 5 AFMS – GFC 500 Mooney M20M/M20R/M20S Series Page 3–5...

  • Page 328: Loss Of Airspeed Data

    1. Autopilot ........... SELECT different lateral and/or vertical mode (as necessary) If on an instrument approach: 1. AP DISC / TRIM INT button ..........PRESS, Continue the approach manually 2. Missed Approach Procedure ..............EXECUTE (as necessary) AFMS – GFC 500 Mooney M20M/M20R/M20S Series 190-02291-18 Rev. 5 Page 3–6...

  • Page 329: Heading Data Source Failure

    2. AP DISC / TRIM INT Button .................PRESS AND RELEASE 3. Manual Elevator Trim ..................RE-TRIM as required NOTE Electric pitch trim should be considered inoperative until the cause of the mistrim has been investigated and corrected. 190-02291-18 Rev. 5 AFMS – GFC 500 Mooney M20M/M20R/M20S Series Page 3–7...

  • Page 330: Yaw Damper Disconnect

    A flashing amber ‘YD’ in the autopilot status box indicates that the yaw damper has disconnected. If the disconnect was not pilot initiated, Refer to Section 3 – Emergency Procedures, YAW AXIS FAILURE / ABNORMAL DISCONNECT, for further information. AFMS – GFC 500 Mooney M20M/M20R/M20S Series 190-02291-18 Rev. 5 Page 3–8...

  • Page 331: Section 4 - Normal Procedures

    Yaw Damper Engagement with Autopilot Off –- The yaw damper, if installed, may be engaged with the autopilot disengaged. This will provide yaw damping and turn coordination. YD will be annunciated in the autopilot status box. 190-02291-18 Rev. 5 AFMS – GFC 500 Mooney M20M/M20R/M20S Series Page 4–1...

  • Page 332: Manual Autopilot Disconnect

    ALT key is pressed. The altitude reference is displayed in the autopilot status box. The reference may be changed by +/- 200 FT using the UP / DN wheel. AFMS – GFC 500 Mooney M20M/M20R/M20S Series 190-02291-18 Rev. 5 Page 4–2...

  • Page 333: Vertical Navigation (Vnav)

    VNAV altitude reference. ALTS will be the armed mode during the descent if the altitude preselect is set at or above the VNAV reference altitude, indicating that the autopilot / flight director will capture the altitude preselect altitude reference. 190-02291-18 Rev. 5 AFMS – GFC 500 Mooney M20M/M20R/M20S Series Page 4–3...

  • Page 334: Go Around

    If TRIM UP message is displayed ............MANUALLY TRIM nose up If TRIM DOWN message is displayed ..........MANUALLY TRIM nose down AFMS – GFC 500 Mooney M20M/M20R/M20S Series 190-02291-18 Rev. 5 Page 4–4...

  • Page 335: Lateral Modes

    If the CDI is one dot or less from center, the autopilot will enter the capture mode when the NAV key is pressed. 190-02291-18 Rev. 5 AFMS – GFC 500 Mooney M20M/M20R/M20S Series Page 4–5...

  • Page 336: Approaches

    APR key is pressed. The glideslope cannot be captured until the localizer is captured. The autopilot can capture the glideslope from above or below the glideslope. AFMS – GFC 500 Mooney M20M/M20R/M20S Series 190-02291-18 Rev. 5 Page 4–6...

  • Page 337: Loc Approach (Gs Out)

    8. GO AROUND (GA) button ........PRESS, Execute Missed Approach Procedure 9. Apply GA power. NOTE Pressing the GA button will not disconnect the autopilot. Select NAV or HDG mode to fly the missed approach procedure. 190-02291-18 Rev. 5 AFMS – GFC 500 Mooney M20M/M20R/M20S Series Page 4–7...

  • Page 338: Gps Approach (Lpv, Lnav/Vnav, Lp+V, Or Lnav+V)

    8. GO AROUND (GA) button ........PRESS, Execute Missed Approach Procedure 9. Apply GA power. NOTE Pressing the GA button will not disconnect the autopilot. Select NAV or HDG mode to fly the missed approach procedure. AFMS – GFC 500 Mooney M20M/M20R/M20S Series 190-02291-18 Rev. 5 Page 4–8...

  • Page 339: Loc Bc Approach

    8. GO AROUND (GA) button ........PRESS, Execute Missed Approach Procedure 9. Apply GA power. NOTE Pressing the GA button will not disconnect the autopilot. Select NAV or HDG mode to fly the missed approach procedure. 190-02291-18 Rev. 5 AFMS – GFC 500 Mooney M20M/M20R/M20S Series Page 4–9...

  • Page 340: Vor Approach

    8. GO AROUND (GA) button ........PRESS, Execute Missed Approach Procedure 9. Apply GA power. NOTE Pressing the GA button will not disconnect the autopilot. Select NAV or HDG mode to fly the missed approach procedure. AFMS – GFC 500 Mooney M20M/M20R/M20S Series 190-02291-18 Rev. 5 Page 4–10...

  • Page 341: Disabling Esp

    ESP can be disabled on the GI 275 with the following procedure. ESP will default to “Enabled” on the next power cycle. GI 275 Knob ......................PRESS and HOLD 2. Options ..........................SELECT 3. ESP Button ........................... SELECT 4. Back Button………………………………………… ..........PRESS and HOLD 190-02291-18 Rev. 5 AFMS – GFC 500 Mooney M20M/M20R/M20S Series Page 4–11...

  • Page 342: Section 5 - Performance

    SECTION 5 – PERFORMANCE No Change. 190-02291-18 Rev. 5 AFMS – GFC 500 Mooney M20M/M20R/M20S Series Page 5–1...

  • Page 343: Section 6 - Weight And Balance

    SECTION 6 – WEIGHT AND BALANCE No change to loading information. Refer to current weight and balance report and equipment list for changes to empty weight/moment and installed equipment. 190-02291-18 Rev. 5 AFMS – GFC 500 Mooney M20M/M20R/M20S Series Page 6–1...

  • Page 344: Section 7 - System Description

    69 KIAS. An aural “AIRSPEED, AIRSPEED” voice alert will sound for installations connected to an audio panel. Underspeed Protection is exited automatically when airspeed exceeds 74 KIAS. 190-02291-18 Rev. 5 AFMS – GFC 500 Mooney M20M/M20R/M20S Series Page 7–1...
  • Page 345 The engagement and disengagement attitude limits are displayed with double hash marks on the roll indicator according to the airplane attitude and whether or not ESP is active in roll. When ESP is inactive AFMS – GFC 500 Mooney M20M/M20R/M20S Series 190-02291-18 Rev. 5...
  • Page 346 The opposite roll limit remains at the engagement limit. Lower Disengagement Limit Indication depicted at 30° after ESP activation Figure 7-2: Engagement Limit Indications Upon ESP Activation 190-02291-18 Rev. 5 AFMS – GFC 500 Mooney M20M/M20R/M20S Series Page 7–3...

  • Page 347: Autopilot Control Unit And Display

    Pushing the AP Key on the GMC 507 mode controller when the autopilot is engaged. • Pulling the autopilot circuit breaker. AUTOPILOT CONTROL UNIT AND DISPLAY Figure 7-3: GMC 507 Control Unit (Reference Only) Figure 7-4: G5 Display (Reference Only) AFMS – GFC 500 Mooney M20M/M20R/M20S Series 190-02291-18 Rev. 5 Page 7–4...
  • Page 348 Selected Altitude is to be captured instead of the VNAV Target Altitude. ** ALTV arms automatically if the VNAV Target Altitude is to be captured instead of the Selected Altitude. 190-02291-18 Rev. 5 AFMS – GFC 500 Mooney M20M/M20R/M20S Series Page 7–5...
  • Page 349 The autopilot is capable of commanding the aircraft in the following ranges: Pitch 20° nose up to 15° nose down Roll ±30° AFMS – GFC 500 Mooney M20M/M20R/M20S Series 190-02291-18 Rev. 5 Page 7–6...

  • Page 350: Preflight Test

    Elevator Trim Up – Autopilot is holding elevator nose up force. The pitch trim TRIM UP needs to be adjusted nose up. Yaw Damper normal disconnect. 190-02291-18 Rev. 5 AFMS – GFC 500 Mooney M20M/M20R/M20S Series Page 7–7...

  • Page 351: Lighting

    When the aircraft’s dimming bus is used to control cockpit lighting, the GMC 507 mode control panel lighting is controlled by the dimming bus. AFMS – GFC 500 Mooney M20M/M20R/M20S Series 190-02291-18 Rev. 5 Page 7–8...
  • Page 361 LOG OF REVISIONS Page Revision Date Number Description FAA Approved Number Robert Murray 05/01/2013 Complete Supplement Robert Murray ODA STC Unit Administrator Garmin International, Inc. ODA-240087-CE 05/01/2013 Date: Michael Warren 03/08/2016 New supplement format with GTX Michael Warren 3X5 added. ODA STC Unit Administrator Garmin International, Inc.
  • Page 362 Table of Contents SECTION PAGE Section 1. GENERAL GTX 33X GTX 3X5 Capabilities Installation Configuration Definitions Section 2. LIMITATIONS Minimum Equipment ADS-B Out TIS Traffic Display with User Navigation Angle Applicable System Software Pressure Altitude Broadcast Inhibit (PABI) Datalinked Weather Display (GTX 345 Only) Portable Electronic Devices Section 3.

  • Page 363: Section 1. General

    Section 1. GENERAL GTX 33X The Garmin GTX 33X family consists of the GTX 330 ES and GTX 33 ES (Non- Diversity Mode S Transponders) and the GTX 330D ES and GTX 33D ES (Diversity Mode S Transponders). The ES option of any of the transponders provides ADS-B extended squitter functionality.
  • Page 364 Optional Interfaces Required Interfaces GTX 33D Installs only Top Antenna Bottom Antenna Garmin Audio Panel GTN 6XX/7XX GTX 33 Heading Source Garmin GNS 480 Traffic System GTX 33D Secondary GPS Altitude Source Squat Switch Power/Ground Temperature External Ident External Standby Figure 2 –...

  • Page 365: Gtx 3X5

    GTX 3X5 The Garmin GTX 3X5 family consists of the GTX 335, 335D, 335R, 335DR, 345, 345D, 345R, and 345DR transponders. The functional differences between each of these transponders are described in Table 1. Transponder models with a “D” designation are diversity capable and support both a top fuselage and bottom fuselage antenna.
  • Page 366 Optional Interfaces Required Interfaces GTX 3X5D/3X5DR Installs only Top Antenna Bottom Antenna Audio Panel Heading Source GTX 3X5 with GPS only GPS Antenna Air Data Source Radio Altitude External GPS Source Source WOW Switch Time Mark GTX 345D/345DR only Secondary GPS GTX 3X5 Keep Alive Input Altitude Source...
  • Page 367 The GTX 335 performs the following additional functions: • Reception of TIS-A traffic data from a ground station • Provide TIS-A traffic alerting to the pilot via interfaced display and audio output. The GTX 345 performs the following additional functions: •...

  • Page 368: Capabilities

    Capabilities The Garmin GTX 33X and GTX 3X5 as installed in this aircraft have been shown to meet the equipment requirements of 14 CFR § 91.227 when operating in accordance with sections 2.1 and 2.2 of this supplement. Installation Configuration This aircraft is equipped with a GTX 33X and/or GTX 3X5 with the following interfaces/ features: Equipment Installed:...
  • Page 369 Interfaced GPS/SBAS Position Source(s): GPS #1 GPS #2 (if installed)  Internal  Internal  GTN 6XX/7XX Series  GTN 6XX/7XX Series  GNS 400W/500W Series  GNS 400W/500W Series  GNS 480  GNS 480  GIA 63W  GIA 63W ...
  • Page 370 Interfaced Remote Control Display (Required for remotely mounted GTX variants): Transponder #1 Remote Control Transponder #2 Remote Control Display Display (if installed)  GTN 6XX/7XX  GTN 6XX/7XX  GNS 480  GNS 480  G950/1000 Display  G950/1000 Display ...

  • Page 371: Definitions

    Definitions The following terminology is used within this document: ADS-B: Automatic Dependent Surveillance-Broadcast AFM: Airplane Flight Manual AFMS: Airplane Flight Manual Supplement ATCRBS: Air Traffic Control Radar Beacon System CFR: Code of Federal Regulations Extended Squitter GNSS: Global Navigation Satellite System GNS: Garmin Navigation System GPS:...

  • Page 372: Section 2. Limitations

    Section 2. LIMITATIONS Minimum Equipment The GTX 33X and GTX 3X5 must have the following system interfaces fully functional in order to be compliant with the requirements for 14 CFR 91.227 ADS- B Out operations: Number Interfaced Equipment Number Installed Required Uncorrected Pressure Altitude Source...

  • Page 373: Applicable System Software

    Applicable System Software This AFMS/AFM is applicable to the software versions shown in Table 3. The Main GTX software version is displayed on the splash screen during start up for the GTX 330 and GTX 3X5 panel mounted units, and the External LRU or System page on the interfaced remote control display for remotely mounted GTX transponders.

  • Page 374: Section 3. Emergency Procedures

    Section 3. EMERGENCY PROCEDURES Emergency Procedures No Change. Abnormal Procedures 3.2.1 LOSS OF AIRCRAFT ELECTRICAL POWER GENERATION XPDR Circuit Breaker ................. PULL Transponder and ADS-B Out functions will no longer be available. NOTE This guidance is supplementary to any guidance provided in the POH or AFM for the installed aircraft for loss of power generation.

  • Page 375: Section 4. Normal Procedures

    Section 4. NORMAL PROCEDURES The procedures described below are specific only to the panel mounted GTX 330 or GTX 3X5 transponders. Cockpit Reference Guides and Pilot Guides for interfaced remote control displays will provide additional operating information specific to the displays or other traffic systems.

  • Page 376: Before Takeoff

    Before Takeoff For GTX 330 installations: ADS-B TX ..................VERIFY ON NO ADSB ................EXTINGUISHED For GTX 3X5 installations: 1090ES TX CTL ................VERIFY ON NO 1090ES TX ..............EXTINGUISHED NOTE The ADS-B TX or 1090ES TX CTL must be turned on and the NO ADS-B or NO 1090ES TX Annunciation (or associated display annunciations) must be EXTINGUISHED for the system to meet the requirements specified in 14 CFR 91.227.

  • Page 377: Section 7. System Description

    Section 7. SYSTEM DESCRIPTION The Garmin GTX 330 and GTX 3X5 Pilot’s Guides, part numbers, and revisions listed below contain additional information regarding GTX system description, control, and function. Title Part Number Revision GTX 330 Pilot’s Guide 190-00207-00 Rev. G (or later) GTX 3X5 Pilot’s Guide 190-01499-00 Rev.

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