GI 275 Part 23 AML STC Airplane Flight Manual Supplement

PRIMARY ADI ..................................................................................... 40 AUTOPILOT INTERFACES ..................................................................... 45 MFD ................................................................................................... 47 TERRAIN AWARENESS AND ALERTING ............................................... 49 ENGINE INDICATION SYSTEM.............................................................. 51 WIRELESS FUNCTIONS ........................................................................ 55 GI 275 Part 23 AML STC 190-02246-12 Rev. 1 Airplane Flight Manual Supplement Page 5 of 55 FAA APPROVED 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. The GI 275 can be used as a primary Engine Indication System (EIS) for single and twin-engine aircraft. The ADI and HSI can be installed as stand-alone primary flight instruments as long as there are other equivalent source(s) of primary flight information that are independently powered. The ADI or HSI can also be installed as a backup instrument. Any GI 275 ADI, HSI, or MFD may be configured with an optional internal battery to provide an independent and automatic backup power source. Individual GI 275s may be grouped or connected as follows to expand and enhance their capabilities and to provide redundancy. Groups of connected GI 275s are hereafter referred to as a “GI 275 system” in this document. Attitude Direction Indicator (ADI) Units configured as an ADI will contain a single page that displays aircraft attitude. Altitude, airspeed, vertical speed and heading may also be displayed on the ADI page depending on the aircraft configuration. 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. The HSI MAP Page includes a top- down view, inset map, hazard awareness overlays (traffic, terrain, topo), along with traditional lateral and vertical navigation cues. GI 275 Part 23 AML STC 190-02246-12 Rev. 1 Airplane Flight Manual Supplement Page 6 of 55 FAA APPROVED Multi-Function Display (MFD) Units configured as an MFD contain multiple installer configurable pages that may include HSI, HSI Map, CDI, Map, Terrain, Traffic, Weather, Radar Altimeter, Stormscope, and Engine Indication System (EIS) 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. If appropriately configured an ADI page will be available during both normal operation and when reverted to preserve the display of primary flight data. A stand-alone ADI may also be considered a Standby ADI since it provides full-time display of primary flight data. Engine Indication System (EIS) Units configured for EIS can display the following engine parameters: Engine RPM Manifold Pressure Oil Pressure Oil Temperature EGT, Primary EGT CHT TIT CDT IAT Alternator / Battery Fuel Flow, Pressure, Quantity Carb Temp Table 1- GI 275 System Function GI 275 Part 23 AML STC 190-02246-12 Rev. 1 Airplane Flight Manual Supplement Page 7 of 55 FAA APPROVED -00 Basic Instrument -10/-30 Includes internal ADAHRS -20/-40 Capable of Integrating with an Autopilot Table 2- GI 275 Hardware Variants GMU 11 and GMU 44B Magnetometer Heading Sensors GEA 24 or GEA 110 Engine Sensors GTP 59 OAT temperature Probe GSB 15 USB Port Backup Battery (internal) Table 3- GI 275 System Components MFD functions are supported by GPS navigator interfaces and a variety of other optional interfaces such as traffic systems, Stormscope®, and satellite and ADS weather sources. Although intuitive and user friendly, the system requires a reasonable degree of familiarity to avoid becoming too engrossed at the expense of basic instrument flying in IMC and basic see-and-avoid procedures in VMC. Pilot workload will be higher for pilots who are not familiar with the GI 275s or GI 275 system in an IFR environment, particularly without the autopilot engaged. Garmin provides a detailed Pilot’s Guide and a tablet trainer app. Pilots should take full advantage of these tools to enhance their familiarity with the GI 275 system. ADAHRS The integral ADAHRS, included in the GI 275 -10/-30 variant, 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. GI 275 includes an optional GMU 11 or GMU 44B magnetometer interface to determine magnetic heading and an OAT probe for measuring outside air temperature. Standby Instruments and the GI 275 ADI Except for installations that are limited to VFR, GI 275 systems require standby attitude, altitude, and airspeed instruments. Several types of standby instruments might be installed, including a standby GI 275 ADI, other ADI, or individual analog instruments. GI 275 system redundancy is satisfied by using a GI 275 MFD or HSI that is configured as a standby instrument, or by using a dedicated GI 275 ADI. When configured as a standby instrument the GI 275 MFD and HSI include an ADI Page which is displayed automatically when faults are detected or when selected by the pilot. Both the GI 275 primary and standby GI 275 Part 23 AML STC 190-02246-12 Rev. 1 Airplane Flight Manual Supplement Page 8 of 55 FAA APPROVED ADIs have their own integral ADAHRS and internal batteries for independence and redundancy. Backup Battery The GI 275 may be configured to include a backup battery to provide emergency power to a GI 275 ADI, HSI or MFD. The backup battery is mounted in an internal, partitioned aluminum chassis within the GI 275 to provide thermal security and automatic backup power when aircraft power is unavailable. NOTE Backup battery charging requires the battery temperature between 0°C and 60°C. A system message will indicate that the battery is no longer charging. GI 275 Part 23 AML STC 190-02246-12 Rev. 1 Airplane Flight Manual Supplement Page 9 of 55 FAA APPROVED Definitions ADAHRS: Air Data and Attitude Heading Reference System ADC: Air Data Computer ADS: Automatic Dependent Surveillance AHRS: Attitude Heading Reference System AMMD: Airport Moving Map Display CDI: Course Deviation Indicator CRS: Course EIS: Engine Indication System FD: Flight Director FLTA: Forward-looking Terrain Alerting GPSS: GPS Steering HDG: Heading HSI: Horizontal Situation Indicator IFR: Instrument Flight Rules IMC: Instrument Meteorological Conditions LOI: Loss of Integrity MFD: Multi-Function Display MFI: Multi-Function Instrument PED: Portable Electronic Device SBAS: Space-based Augmentation System SVT: Synthetic Vision Technology TAWS: Terrain Awareness and Warning System (a TSO-C151b function) TIS-A: Traffic Information Service (Addressed) TIS-B: Traffic Information Service (Broadcast) VFR: Visual Flight Rules VMC: Visual Meteorological Conditions VNAV: Vertical Navigation VS: Vertical Speed GI 275 Part 23 AML STC 190-02246-12 Rev. 1 Airplane Flight Manual Supplement Page 10 of 55 FAA APPROVED 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 Instrument 2.01 NOTE This section is not intended to be a comprehensive list of approved software. It is intended to provide a means to determine if this AFMS revision is applicable to the software that is installed in the aircraft. Do not use this AFMS revision if the installation has a software version less than that shown in the table above. Heading Operational Area If the GI 275 is used as the heading source, IFR Operations are prohibited north of 72N and south of 70S latitudes. In addition, IFR operations are prohibited in the following four regions: 1) North of 65° North latitude between longitude 75° W and 120° W 2) North of 70° North latitude between longitude 70° W and 128° W 3) North of 70° North latitude between longitude 85° E and 114° E 4) South of 55° South latitude between longitude 120° E and 165° E Loss of heading may occur near the poles. Magnetic Variation Operational Area If the GI 275 is used as the heading source, IFR operations are prohibited in areas where the magnetic variation is greater than 99.9 degrees East or West. 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. GI 275 Part 23 AML STC 190-02246-12 Rev. 1 Airplane Flight Manual Supplement Page 11 of 55 FAA APPROVED ADAHRS Normal Operating Mode The ADAHRS integrity monitoring uses GPS data and air data. Since the integral ADC provides full time air data, the only required external input is from an approved and installed GPS. NOTE GI 275 attitude will remain valid if either GPS or Air Data is lost. Flight in IMC is not authorized unless the ADAHRS is receiving valid GPS and air data. The GI 275 monitors the integrity of these systems automatically and will advise the pilot if the GPS and/or air data is lost or invalid. NOTE In dual GPS installations, only one GPS needs to be available to the ADAHRS or AHRS for IFR flight. Aerobatic Maneuvers Do not conduct aerobatic maneuvers if uninterrupted attitude information is required from the GI 275 ADI. Electronic Standby and/or Primary Instrument Power The backup battery’s charge state for the standby and/or primary instrument must be verified before flight. The battery indication turns yellow if there is less than 60 minutes of battery capacity. For aircraft with service ceilings below 25000 ft, only 30 minutes of backup battery operation is required. Refer to the battery status and information found in the battery menu (Menu → Systems → Battery). Standby and/or Primary Flight Instruments  This installation does not have separate standby instruments or does not require standby instruments (aircraft limited to VFR).  This installation uses pneumatic or the aircrafts original primary flight display instruments.  This installation uses a connected GI 275 system with independent ADHARS and backup batteries for the primary and standby flight instruments. IFR flight must not be initiated unless the systems check in Section 2.7 is completed successfully to verify the following: • The backup battery is operational and sufficiently charged. Refer to Section 2.7. GI 275 Part 23 AML STC 190-02246-12 Rev. 1 Airplane Flight Manual Supplement Page 12 of 55 FAA APPROVED • Attitude, heading, altitude, and airspeed from AHRS/ADC 1 are operational on the pilot’s primary GI 275 ADI with no warnings, cautions, or advisories present • Selecting the Reversion Backup Switch to the “ON” position causes the standby GI 275 to change and lock to the ADI page, and displays primary flight information. WARNING Failure to observe these limitations may result in the loss of all attitude or air data or both, resulting in loss of aircraft control. 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 two AHRS/ADC sensors sources, 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. Operating primary and standby GI 275 ADIs on the same sensor source will inhibit the AHRS/ADC comparison monitor. Synthetic Vision The synthetic vision presentation must not be used as the sole reference for aircraft control (without reference to the primary flight instruments). The synthetic vision presentation must not be used as the sole reference for navigation or obstacle/terrain/traffic avoidance. If the installed TAWS or Terrain Alerting system is inoperative, the synthetic vision display on the GI 275 ADI must be selected off. Moving Maps The GI 275 Map page (ownship position relative to map features) must not be used as the primary or sole means of navigation or course guidance. Autopilot Disconnect The “AP DISC” button in the GI 275 ADI Menu → Options (if present for the installation) must disconnect the autopilot when pressed. If the button does not disconnect the autopilot when pressed, then the autopilot must not be used. GI 275 Part 23 AML STC 190-02246-12 Rev. 1 Airplane Flight Manual Supplement Page 13 of 55 FAA APPROVED Terrain Display Maneuvers and navigation must not be based solely on the display of terrain, obstacles, or wires on the moving map terrain displays. Terrain/TAWS Alerts Terrain/TAWS alerts must be inhibited when landing at an airport that is not in the airport database unless the airport can be designated as a user airport (GTN Navigator only). 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. Due to time delays inherent in gathering and processing weather data for datalink transmission, the weather information shown by the datalink weather product may be significantly older than the indicated weather product age. Do not rely solely upon datalink services to provide Temporary Flight Restriction (TFR) or Notice to Airmen (NOTAM) information. Not all TFRs and NOTAMS may be depicted. Traffic Display The display of traffic is intended as an aid to visual acquisition and must not be used as the sole basis for maneuvering the aircraft to avoid traffic. Stormscope® Display Stormscope® lightning information displayed is limited to supplemental use only. The use of the Stormscope® lightning data on the display for hazardous weather (thunderstorm) penetration is prohibited. Stormscope® lightning data on the display is intended only as an aid to enhance situational awareness of hazardous weather, not penetration. It is the flight crew’s responsibility to avoid hazardous weather using official weather data sources. Surface Operations The GI 275 Map page shall not be used as the sole basis for ground maneuvering. The zoomed-in Map page does not comply with the FAA requirements and is not certified as an airport moving map display (AMMD). Map page use is limited to airport surface orientation to improve flight crew situational awareness during ground operations. GI 275 Part 23 AML STC 190-02246-12 Rev. 1 Airplane Flight Manual Supplement Page 14 of 55 FAA APPROVED Type Ratings The standby GI 275 ADI is authorized for operations in aircraft that require a type rating. Fuel Flow Fuel flow values may be in error by as much as 15% if the K factor calibration is improperly set. Do not depend solely on the fuel flow indication to determine fuel used, fuel remaining, or fuel reserves. Fuel Computer The fuel computer functions must not be used as the primary means of determining the quantity of fuel in the tanks. The aircraft fuel quantity gauge(s) are the primary means of determining fuel quantity. Glove Usage The touchscreen can be operated with gloves made for capacitive touchscreens. VFR GPS The VFR GPS (VGPS) is an emergency position and temporary navigational aid available for use when the certified navigator data is unavailable or invalid or in VMC flight if no other GPS source is interfaced. Service Required It is prohibited to initiate flight when a “Service Required” advisory is present on the ADI or EIS display. Powerplant Gauge Markings When engine gauges are replaced by the GI 275 EIS in accordance with this STC, gauge markings shall be equivalent or most effectively displayed according to the cumulative Type Design data available for the aircraft. Portable Electronic Devices This STC does not relieve the operator from complying with the requirements of 91.21 or any other operational regulation regarding portable electronic devices. The GI 275 wireless interface and data provided to a portable electronic device are not approved to replace any certified avionics, including installed navigation or traffic/weather equipment. GI 275 Part 23 AML STC 190-02246-12 Rev. 1 Airplane Flight Manual Supplement Page 15 of 55 FAA APPROVED Database Updates Database updates via USB or wireless transfers must be done while the aircraft is on the ground and stationary. In-flight database transfers or updates are inhibited in flight. 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. The table below lists the minimum fully functional equipment required for operation of the GI 275. * Connected to GI 275 ADI ** Connected to GI 275 ADI or the GI 275 HSI/MFD as a Standby ADI Figure 1- Minimum GI 275 Flight Instrument System when installed with a GI 275 Standby ADI Figure 2- Minimum GI 275 Instrument System when installed with non-GI 275, supporting Standby Instruments Equipment Number installed VFR IFR GI 275 ADI 1 1 1 GI 275 HSI/MFD as Standby ADI 1 0 1 GMU 11 or 44B Magnetometer 1* 0 1* Reversion Backup Switch 1* 0 1* GPS/SBAS Navigator or VFR GPS antenna 1** 1 1** Non-stabilized Magnetic Compass 1 1 1 Equipment Number installed VFR IFR GI 275 ADI 1 1 1 GMU 11 or 44B Magnetometer 1 0 1 GPS/SBAS Navigator or VFR GPS antenna 1 1 1 Non-stabilized Magnetic Compass 1 1 1 GI 275 Part 23 AML STC 190-02246-12 Rev. 1 Airplane Flight Manual Supplement Page 16 of 55 FAA APPROVED Equipment Number installed Req’d GI 275 EIS 1 or 2* 1 or 2* Engine Adaptor Unit (GEA 24/110) 1 or 2* 1 or 2* * one GI 275 EIS and GEA 24/110 are required per engine Figure 3- Engine Indication System The following engine indications must be functional on the EIS display (if these gauges are present on the EIS display as installed): Tachometer, Manifold Pressure, Oil Pressure, Oil Temperature, Fuel Quantity, any additional engine instruments required by the aircraft Kinds of Equipment list as listed in the Aircraft Flight Manual. If the GI 275 EIS is installed between 15 degrees and 35 degrees of the pilot’s primary field of view, an external annunciator is required. Minimum Flight Crew Installation of a GI 275 does not affect a Minimum Flight Crew determination. Placards 2.30.1 GI 275 Reversion Backup Switch Adjacent to the GI 275 Reversion Backup Switch: On Auto GI 275 Part 23 AML STC 190-02246-12 Rev. 1 Airplane Flight Manual Supplement Page 17 of 55 FAA APPROVED 2.30.2 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” 2.30.3 Aircraft Category There is no placarding that is specific or unique to aircraft category. GI 275 Part 23 AML STC 190-02246-12 Rev. 1 Airplane Flight Manual Supplement Page 18 of 55 FAA APPROVED EMERGENCY PROCEDURES 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). 1. Use standby flight instruments for attitude, airspeed, altitude, and heading reference. 2. If GI 275 reversionary capability is available, the standby GI 275 should automatically change to the ADI page and promptly restore primary flight information. If manual reversion is required, move the Reversion Backup Switch to the “ON” position. 3. Refer directly to the navigation source for navigation information (such as GPS). 4. Seek VFR conditions or land as soon as practical. If autopilot is engaged: 5. Verify autopilot mode selections and cross check against standby flight and navigation data. Consider disengaging the autopilot. GI 275 Part 23 AML STC 190-02246-12 Rev. 1 Airplane Flight Manual Supplement Page 19 of 55 FAA APPROVED 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. 1. Continue flight by reference to the standby ADI or manually select “ON” to force reversion. 2. Seek VFR conditions or land as soon as practicable. If multiple AHRS sources are installed: 3. Select the operative AHRS (i.e., AHRS 1, 2 or 3) using the ADI sensors menu (MENU → SENSORS) NOTE If airborne AHRS alignment without an operative GPS navigator is necessary, minimize maneuvering and turbulence during and after the restart process. Without an operative GPS navigator, excessive maneuvering or turbulence may prevent the AHRS from aligning properly. Continue to minimize maneuvering and seek smooth air for the first 5 minutes after the attitude becomes valid following the airborne alignment. If maneuvering or turbulence cannot be avoided, carefully cross-check the AHRS for accuracy against other flight instruments until the alignment has completed and becomes stable. 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. GPS altitude is displayed in magenta, in the same location as normal operation. 1. Use standby Airspeed Indicator and Altimeter 2. Seek VFR conditions or land as soon as practical If multiple ADC sources are installed: 3. Select the operative ADC (i.e., ADC 1, 2, or 3) using the ADI Sensors menu (MENU → SENSORS) GI 275 Part 23 AML STC 190-02246-12 Rev. 1 Airplane Flight Manual Supplement Page 20 of 55 FAA APPROVED 3.1.4 ATTITUDE, ALT, or IAS monitor CAUTION If an ATTITUDE, ALT, or IAS miscompare CAUTION is displayed in amber on the attitude display or airspeed/altitude tape: 1. Cross check flight instruments against all available information to determine which indications are correct 2. Seek VFR conditions or land as soon as practical NOTE White ATTITUDE/ALT/IAS no compare annunciations indicate that the other AHRS/ADC source is not available. 3.1.5 Aircraft Electrical System Failure In the event of a total loss of aircraft electrical power, the GI 275 will cease to operate, except for displays which are equipped with an internal backup battery. Refer to procedures for failure of affected equipment and operation on backup battery. 3.1.6 Operation on Backup Battery (if installed) Displays equipped with a backup battery will continue to operate after a loss of aircraft electrical power. EIS displays will not be functional. Operation on battery power is indicated by the presence of a battery icon on the affected display. Green battery indication provides at least 60mins, yellow battery indication provides a range between 59mins and 15mins, and red battery indication provides less than 15mins of battery operation. 1. Seek VFR conditions and land as soon as practical. GI 275 Part 23 AML STC 190-02246-12 Rev. 1 Airplane Flight Manual Supplement Page 21 of 55 FAA APPROVED NOTE For protection, on backup battery operation is inhibited if the battery‘s temperature drops below -20° C or exceeds 80° C. 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 navigators or other hazard awareness systems. Depending on how these were installed and configured to the GI 275, some information from these configured systems will not be available when the GI 275 is operating on its backup battery. 3.1.7 Display Backup Malfunction Display backup malfunction is indicated by the unit locking on the ADI page. All other configured pages will not be accessible on the standby ADI or HSI. 3.1.8 Backup Battery Malfunction A malfunction of the backup battery is indicated by the following indication in the upper left corner of the screen with a system advisory message: 1. Seek VFR conditions or land as soon as practicable. 3.1.9 EIS Failure EIS failure is indicated by the loss of displayed information on the EIS, including a blank, frozen, or unresponsive display of EIS parameters. 1. Position engine controls to ensure operation within engine limitations. GI 275 Part 23 AML STC 190-02246-12 Rev. 1 Airplane Flight Manual Supplement Page 22 of 55 FAA APPROVED 3.1.10 Terrain Alerts Aural Alert Annunciation All Pages Annunciation Terrain Page Action “Terrain, Terrain Pull up, Pull up” -OR- “Obstacle, Obstacle Pull up, Pull up” -OR- “Wire, Wire Pull up, Pull up” -OR- “Warning, Terrain, Terrain” -OR- “Warning, Obstacle, Obstacle” -OR- “Warning, Wire, Wire” -OR- “Pull up” -OR- -OR- -OR- Disconnect autopilot and initiate maximum performance climb (maximum takeoff power and best angle of climb airspeed) NOTE: Only the climb maneuver is recommended, unless operating in VMC or it is determined, based on all available information, that turning in addition climbing is the safest course of action. “CAUTION, Terrain” -OR- “CAUTION, Obstacle” -OR- “CAUTION, Wire” -OR- -OR- Take corrective action until the alert ceases. Using all available information to determine the appropriate action, alter the flight path away from the threat by stopping descent, climbing, and/or turning. “Too low, Terrain” Establish climb to the minimum altitude for present position/procedure “Sink Rate” Decrease rate of descent “Don’t sink” Establish a positive rate of climb GI 275 Part 23 AML STC 190-02246-12 Rev. 1 Airplane Flight Manual Supplement Page 23 of 55 FAA APPROVED 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. Figure 4- Bottom of the ADI when HDG failed (with GPS) Figure 5- Top of the HSI when HDG failed (with GPS) If there is no GPS in the GI 275 system or if the GPS has failed, the heading failure will be indicated by a red “X” in place of the heading readout on the ADI or HSIs. Figure 6- Bottom of the ADI when HDG failed (no GPS) Figure 7- Top of the HSI when HDG failed (no GPS) GI 275 Part 23 AML STC 190-02246-12 Rev. 1 Airplane Flight Manual Supplement Page 24 of 55 FAA APPROVED If GPS track is not available: 1. 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. Course deviation indications will behave like a traditional CDI. VOR deviations will be relative to the selected course with a TO/FROM indication. Localizer deviations will not be affected by the selected course, and reverse sensing will occur when tracking inbound on a localizer back course. 3.2.2 Display Overtemperature If the display is in an overheating condition, the system will alert the pilot with a system message. 1. Prepare for loss of the affected display. 3.2.3 GPS Data Failure GPS data failure may be indicated by any or all of the following: • Loss of GPS course deviation information on HSI • Amber “LOI” text on the ADI • Amber “DR” text on the moving map • Amber “NO GPS POSITION” text on the moving map • Loss of waypoint bearing/distance information 1. Select alternate GPS source, if available, by pressing “CDI” button on ADI. If alternate GPS source is not available: 2. Select alternate navigation source (VOR or LOC, if available) or refer directly to external navigation data. GI 275 Part 23 AML STC 190-02246-12 Rev. 1 Airplane Flight Manual Supplement Page 25 of 55 FAA APPROVED 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 1. Select alternate navigation source or refer directly to external navigation data. 3.2.5 Synthetic Vision Malfunction If the synthetic vision depiction is known or suspected to be inaccurate or malfunctioning: 1. Turn off synthetic terrain using the Menu → Options → Terrain SVT menu on the ADI. 3.2.6 Electrical Load Shedding The following equipment is considered non-essential. If it becomes necessary to reduce electrical load (for example, during loss of generators or alternators), power to these units may be removed in the order listed. 1. MFD circuit breaker(s) [if installed and not configured as standby ADI] – PULL NOTE Any non-required displays on the co-pilot side may also be powered off. 3.2.7 AHRS ALIGN If an “AHRS ALIGN / Keep Wings Level” annunciation is displayed on the attitude indicator in flight, limit aircraft operation to: • ±10º bank • ±5º pitch • 200 KTAS or less CAUTION Exceeding these values may delay or prevent AHRS alignment. GI 275 Part 23 AML STC 190-02246-12 Rev. 1 Airplane Flight Manual Supplement Page 26 of 55 FAA APPROVED 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). 1. Monitor remaining parameters and set engine controls to operate within limitations. GI 275 Part 23 AML STC 190-02246-12 Rev. 1 Airplane Flight Manual Supplement Page 27 of 55 FAA APPROVED 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 Use Standby Magnetic Compass or GPS track information Display system is not receiving valid heading input from the ADAHRS or AHRS; accompanied by a red X through the digital heading display. Red X Reference the data source or alternate equipment. A red X through any display field, indicates that display field is not receiving data or is corrupted. Red EIS Alert Banner Observe the warning indication on the EIS display and take appropriate action. One or more engine parameters have exceeded a warning threshold. Red Engine Parameter Take appropriate action to correct condition causing engine parameter exceedance The engine parameter has exceeded the warning threshold. Terrain warning Take appropriate action to maneuver the aircraft away from the conflicting terrain Terrain warning due to aircraft proximity to surrounding terrain GI 275 Part 23 AML STC 190-02246-12 Rev. 1 Airplane Flight Manual Supplement Page 28 of 55 FAA APPROVED 3.3.2 CAUTION Annunciations – Yellow Annunciation Pilot Action Cause AHRS ALIGN – Keep Wings Level Limit aircraft attitude to ±10º bank and ±5º pitch as AHRS Aligns - OK to taxi. Attitude and Heading Reference System is aligning. AHRS may not align with excessive pitch/bank angles. AHRS NOT READY – Do Not Takeoff Remain stationary and allow AHRS to finish initialization and allow navigators to acquire sufficient GPS position. AHRS sensors are not ready for flight. Additionally, the interfaced navigator does not have sufficient GPS position. LOI Loss of Integrity Monitoring GPS integrity is insufficient for the current phase of flight. No GPS Position Use alternate information for positional and situational awareness GPS data is unavailable. Yellow X Reference the data source or alternate equipment. A yellow X through any display field, indicates that display field is not receiving data or is corrupted. ATTITUDE Fly aircraft manually and crosscheck attitude indication with standby attitude indicator and other sources of attitude information (airspeed, heading, altitude, etc.) The ADI attitude monitors have detected an AHRS malfunction or an error between AHRS sources (if multiple sources installed). Autopilot may disconnect if AHRS is being used to drive the autopilot. GI 275 Part 23 AML STC 190-02246-12 Rev. 1 Airplane Flight Manual Supplement Page 29 of 55 FAA APPROVED ALT and/or IAS (text on ADI) Cross-check the flagged information against other sources to identify erroneous information. Differences detected between displayed airspeed and/or altitude (multiple ADC installations only). AHRS 1/2/3 Confirm intended AHRS source selection The ADI is using the cross-side AHRS sensor and AHRS monitor is indicating a miscompare or no- compare (multiple ADI and AHRS installations only). ADC 1/2/3 Confirm intended ADC source selection The ADI is using the cross-side ADC sensor and ADC monitor is indicating a miscompare or no- compare (multiple ADI and ADC installations only). Yellow Alert Banner on EIS Observe the caution indication on the EIS display and take appropriate action. One or more engine parameters have exceeded a caution threshold. Yellow EIS Parameter Take appropriate action to correct condition causing engine parameter exceedance. The engine parameter has exceeded the caution threshold. Traffic Caution Visually acquire the traffic to see and avoid. The interfaced traffic system has determined that nearby traffic may be a threat to the aircraft. Terrain Caution Take appropriate action to maneuver the aircraft away from the conflicting terrain Terrain caution due to aircraft proximity to surrounding terrain TAWS N/A, TAWS FAIL Use vigilance, terrain depiction and TAWS alerting are no longer provided. External system that is providing TAWS alerting has failed, or the GI 275 cannot communicate with the system. GI 275 Part 23 AML STC 190-02246-12 Rev. 1 Airplane Flight Manual Supplement Page 30 of 55 FAA APPROVED 3.3.3 Advisories – White Annunciation Pilot Action Cause ATTITUDE, ALT, or IAS (text on ADI) Be aware that the other (unselected) AHRS/ADC source is not available The other (unselected) AHRS/ADC source is unavailable. AHRS 1/2/3 Confirm intended AHRS source selection The ADI is using the cross- side AHRS sensor (multiple ADI and ADC installations only). ADC 1/2/3 Confirm intended ADC source selection The ADI is using the cross- side ADC sensor (multiple ADI and ADC installations only). Messages Icon View and consider advisory messages. Refer to the GI 275 Pilot Guide for appropriate pilot or service action. Typically, these indicate system or database status, or data communication issues within the GI 275 System. Terrain Inhibited Use vigilance, traffic system will not provide alerting. Terrain is inhibited or a terrain test is in progress External Navigator Message Icon View and consider advisory messages on interfaced navigator. Refer to Pilot Guide for the external navigator for appropriate pilot of service action. Typically, these indicate system or database status. GI 275 Part 23 AML STC 190-02246-12 Rev. 1 Airplane Flight Manual Supplement Page 31 of 55 FAA APPROVED NORMAL PROCEDURES Before Takeoff 1. Review displays for any abnormal warning, caution, or advisory indications. 2. 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. Do not use the unverified fuel quantity indication provided by the GI 275 as the sole means of complying with the requirements of CFR 14 91.103, 91.151, or 91.167. 3. If equipped with a TAWS/Terrain warning system, ensure that the terrain alert audio test can be heard clearly (a system test audio clip is played during the startup self-test). 4.1.1 ADI System Check 1. Verify that no amber or red battery icon is displayed on the primary or standby ADI. If a yellow icon is present, verify the battery’s remaining capacity is more than 30 mins if the aircraft’s service ceiling is below 25,000ft. 2. Verify that attitude, heading, altitude, and airspeed are displayed normally on the ADI (no warnings, cautions, or advisories related to these functions). 3. Select the Reversion Backup Switch to the “ON” position a. Verify that the ADI information is displayed on the backup display b. Ensure that attitude, heading, altitude, and airspeed are displayed normally on the standby ADI (no warnings, cautions, or advisories related to these functions) 4. 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. 1 Airplane Flight Manual Supplement Page 32 of 55 FAA APPROVED Autopilot Operation 4.2.1 Autopilot Disconnect Test In some installations, 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. 1. While on the ground, engage the autopilot. 2. In the ADI Menu → Options, press the AP DISC button and verify that the autopilot disconnects. CAUTION Do not use the autopilot if the AP DISC button fails to disengage the autopilot normally. 4.2.2 Autopilot NAV / APR mode coupling To couple the autopilot NAV / APR mode: 1. Select the desired navigation source on the Pilot’s ADI (NAV Options Menu) or the CDI button. 2. Select the desired NAV / APR mode on the autopilot. NOTE The autopilot will use the source that is displayed on the Pilot’s ADI or HSI. 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 NAV autopilot mode is enabled. 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. To use GPSS: 1. Select the desired GPS navigation source on the Pilot’s ADI. 2. Enable GPSS emulation on the ADI using the AP REF button in the Menu → Options → NAV Options → HDG Options menu. 3. Engage the autopilot in HDG mode. NOTE When GPSS emulation is enabled, the GI 275 ADI’s heading bug function will be disabled. This is indicated by a hollowed- out heading bug, and the ADI/HSI heading button will display “GPSS” near the crossed-out heading bug. The “GPSS” text GI 275 Part 23 AML STC 190-02246-12 Rev. 1 Airplane Flight Manual Supplement Page 33 of 55 FAA APPROVED will be white when GPSS commands are available, and it will be amber when there is no GPSS command available. NOTE The GPSS commands to the autopilot are based on the GPS source displayed on the pilot’s side ADI (typically the primary ADI or ADI #1). 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 with VNAV capability. If EDO VNAV is enabled on the GTN in these installations, EDO VNAV guidance may be coupled to the autopilot using the VNAV function of the GFC.  This installation is equipped and configured to provide EDO VNAV display and autopilot coupling.  This installation is equipped and configured to provide EDO VNAV display only.  This installation does not support EDO VNAV display or coupling. EIS Operation 4.3.1 Main EIS Page The Main EIS page of the GI 275 displays all engine gauges that have limitations (red and/or yellow markings). The crew must periodically review the engine indications on the Main EIS page if the GI 275 is displaying any other EIS page. GI 275 Part 23 AML STC 190-02246-12 Rev. 1 Airplane Flight Manual Supplement Page 34 of 55 FAA APPROVED PERFORMANCE No change. WEIGHT AND BALANCE See current weight and balance data. GI 275 Part 23 AML STC 190-02446-12 Rev. 1 Airplane Flight Manual Supplement Page 35 of 55 SYSTEM DESCRIPTION A detailed GI 275 Pilot’s Guide is available through the Garmin website or your Garmin dealer. If a GSB 15 is installed it provides a USB port for loading software and databases. This can also power portable electronic devices but does not provide any data connection to the GI 275 for those devices. Wireless connectivity is provided for ground database updates. Database updates cannot be performed in-flight. Additionally, the GI 275 supports a Bluetooth connection to personal electronic devices running Garmin Pilot for the supplemental display of traffic, attitude and GPS position. This connection will work in-flight however the personal electronic device must be paired with GI 275 while on the ground. The following colors are used consistently within the GI 275 system: Color Functions Red Warning conditions Operating Limits Yellow Caution conditions Conditional operating ranges Green Safe operating conditions Normal operating ranges VOR/Localizer Data White Scales and Markings Current data and values, status Magenta GPS Data Active flight plan legs Cyan Pilot-selectable references 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. A display touch is required in most cases to select the display field of a Page that will be changed by inner knob rotation or press. The inner knob changes the value of the selected field. For primary, stand-alone ADIs the outer knob does not provide any control since there is no other page GI 275 Part 23 AML STC 190-02446-12 Rev. 1 Airplane Flight Manual Supplement Page 36 of 55 available for selection. When the outer knob is rotated, a momentary display of knob function is provided at the top of each page. To access the Menu, press and hold the inner knob. To access the Menu via touchscreen, swipe up from the bottom of the GI 275 display. Display Brightness Display brightness is controlled automatically based on input to a bezel-mounted photocell. The brightness level can be manually adjusted using controls in the Menu → Backlight selection. Optionally, brightness can be controlled using the aircraft’s cockpit lighting dimmer control. System Power Sources The GI 275 primarily depends on aircraft power to function. The GI 275 system is directly connected to the aircraft’s main or essential bus and energized when the aircraft master switch is turned on. Other systems, like the navigation equipment, weather datalink, and autopilot are typically located on the avionics bus and may not be functional when this bus is powered off. The major components of the GI 275 are protected with resettable circuit breakers available to the pilot. These breakers are labeled as follows (appropriate boxes will be checked): Installed Circuit Breaker Label Equipment  PFD Primary ADI  EIS GI 275 configured for Engine Monitoring – Single Engine  EIS L and EIS R GI 275 configured for Engine Monitoring – Multi Engine  MFD GI 275 configured as a MFD  MFD/STBY ADI GI 275 configured as a MFD with standby ADI  ATT GI 275 configured as an Attitude Indicator only  HSI GI 275 configured as an HSI  HSI/STBY ADI GI 275 configured as an HSI with standby ADI  ENG SNSR GEA (24 or 110) Engine/Airframe Unit  STBY ADI Standby ADI (Stand-alone) GI 275 Part 23 AML STC 190-02446-12 Rev. 1 Airplane Flight Manual Supplement Page 37 of 55  USB GSB 15 USB Interface System Status The GI 275 status can be viewed via the Menu → System → Info menu. This includes the serial number and system ID of the unit, the software version loaded on the unit, and the AHRS and ADC software versions. An External LRUs list displays information and status of various units that are interfaced to the GI 275 system. This list only includes LRUs that can report status information, which is typically limited to other Garmin LRUs. Software versions, serial numbers, and LRU status is typically provided. A green checkmark indicates normal online status, and a red X indicates offline or failed status. Some LRUs, like the GDL 69, GSR 56, and GTX 345, provide a button to see more detailed information about the status of that unit. 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. EIS units only use a Nav database. System time (as received from an interfaced GPS navigator or the internal VFR GPS) is used to determine if a database is within its effective period. Databases are displayed in amber if they are expired, not yet effective, or if the current date/time is unknown. Databases are displayed in white if they are within their effective date range. All database status information is depicted in white on the System Status page. Databases can be updated using the USB port, by syncing with other compatible units, or using database concierge through a PED. Databases are stored internally on the GI 275s. The terrain and basemap databases are updated periodically and do not expire. The Garmin or Jeppesen navigation database contains data associated with navigation including airports, navigation aids, airways, airspaces, and other data. This database is updated on a 28-day cycle. The obstacle database contains data for obstacles and wires that pose a potential hazard to aircraft. Obstacles 200 feet and higher are included in the obstacle database. Wires which have been identified as a hazard to fixed wing aircraft are included in the database. Coverage of the obstacle database includes the United States and Europe. Wire coverage is limited to the United States. This database is updated on a 56-day cycle. CAUTION Not all obstacles or wires are included in the databases. GI 275 Part 23 AML STC 190-02446-12 Rev. 1 Airplane Flight Manual Supplement Page 38 of 55 The Garmin SafeTaxi™ database contains airport diagrams for selected airports. This database is updated on a 56-day cycle. The magnetic variation model contains data about variations in the earth’s magnetic field based on location. This database is included with the navigation database and is updated on a five-year cycle. Crew Profiles The crew profile function is provided for all units to allow the retention of pilot- selectable configurations and settings. If the aircraft is operated by multiple pilots, each pilot can recall their individual settings for use. These profiles include settings from all displays in the system. If an MFD is installed, the splash screen provides the option for the pilot to select a crew profile upon power up. Otherwise the crew profile can be set in the System → Crew Profile Menu. If no selection is made, the GI 275 will default to 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. The GI 275 can be a standby to itself, consisting of two GI 275 displays installed adjacent to each other, with one display configured as the ADI and the second display configured as either an HSI or an MFD. The standby ADI needs to be of the -10/-30 type with its own integral ADAHRS. A Reversion Backup Switch is installed which will force the standby ADI into the display backup mode of operation when moved to the “ON” position. A backup battery will provide power to the ADI, MFD, HSI, or standby ADI in the event of aircraft power failure. This configuration will provide the following functionality: • If the ADI fails or communication with the primary ADI is lost, the MFD with a standby ADI or standby HSI will automatically display its backup primary flight information (attitude, altitude, airspeed). • Two GI 275 -10 variants monitor and compare their independent attitude, altitude, and airspeed data. If either GI 275 detects a difference between any of the parameters (attitude, altitude, or airspeed), the MFD or HSI will automatically revert to display the standby ADI to restore primary flight information. Amber miscompare annunciations will appear to indicate the discrepancy. 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 GI 275 Part 23 AML STC 190-02446-12 Rev. 1 Airplane Flight Manual Supplement Page 39 of 55 operational mode. The GI 275 abbreviates the approach modes as defined in the table below. Description Annunciation Lateral Navigation LNAV Localizer Performance with Vertical Guidance LPV Localizer Performance without Vertical Guidance LP Localizer performance approach with advisory vertical guidance LP+V Lateral and vertical navigation approach L/VNAV Lateral navigation approach with advisory vertical guidance LNAV+V VFR GPS A Garmin GI 275 may be interfaced with its own optional VFR GPS antenna. In the event that the certified GPS navigation information becomes unavailable, the GI 275 VFR GPS (VGPS) provides 2D GPS position information and Direct To navigation capability. Aside from selecting VGPS as the CDI source and then selecting a Direct To waypoint, airport, or navigational aid within the GI 275 Direct To Menu, there is no pilot action required to enable or use the VFR GPS. When VGPS data is in use, "VGPS” is annunciated as the selected navigation source. Synthetic Vision and Terrain alerting functionality is available with the VGPS. 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). An MFD may be interfaced to the audio system for terrain alerts or touch clicks, but only if there is no primary ADI installed. The GI 275 EIS is not interfaced to the audio system. Messages Messages are available on all installed GI 275s. A Message annunciation flashes in the upper left corner of each display to notify the pilot when a new advisory is GI 275 Part 23 AML STC 190-02446-12 Rev. 1 Airplane Flight Manual Supplement Page 40 of 55 available. The pilot may select Messages in the Menu to display a list of active Messages. Not all Messages are common to all interfaced GI 275s, meaning unit specific issues will not be shown on all the other GI 275s. System Settings The Menu → System → Setup page provides pilot controls for click volume, time format, and local time offset. Controls are provided to set the nearest airport criteria so that airports not usable by the aircraft type do not appear in waypoint searches. Units of Measure for temperature, barometric pressure, and nav angle are pilot controllable via the Menu → System → Units page. These units are propagated throughout the GI 275 system. Adjustments to temperature units will not affect EIS temperature gauges. All units across all systems must be verified the units match for each function and LRU. The units and markings on the ADI are not user-configurable. They match the units as specified in the aircraft’s FAA approved Airplane Flight Manual and standby instruments. 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. Recorded data is stored in internal memory and can be exported via a USB drive. Primary ADI ADI functions are selected by touching the desired adjustable field on the display. Once selected, the inner knob changes the value (Altitude, IAS, Baro, or Heading). An inner knob press will sync the altitude, IAS, or heading to the current value. Baro sync toggles the ADI in and out of standard altimeter setting (29.92”hg and labeled “STD”). The selectable field defaults to Baro when the knob is idle for a period of time. The default timeout is 10 seconds and may be changed in the Menu. When interfaced to a Garmin G500/600 TXi, the GI 275 will sync barometer (if Baro Sync is enabled), selected heading, selected altitude, and selected airspeed bugs with the TXi. It is recommended that BARO SYNC be enabled when using VNAV functionality as the GTN will only use the pilot-side BARO unless there is a failure.