AFMS, Garmin G5 AML STC

Section 5 – Performance ........................................................................................... 5-1 Section 6 – Weight and Balance ............................................................................... 6-1 Section 7 – System Description ................................................................................ 7-1 System Messages ........................................................................................................................... 7-1 AFMS, Garmin G5 AML STC 190-01112-13 Rev. 8 Page iv This page intentionally left blank. 190-01112-13 Rev. 8 AFMS, Garmin G5 AML STC Page 1–1 SECTION 1 – GENERAL The G5 Electronic Flight Instrument can display the following information to the pilot depending on the installation and location of the G5 instrument. • Primary attitude • Primary slip and turn rate information • Primary heading • Secondary airspeed • Secondary altimeter • Secondary ground track When installed in place of the attitude indicator, the primary function of the G5 is to provide attitude information to the pilot. When installed in place of the rate of turn indicator, the primary function of the G5 is to provide turn rate and slip ball information to the pilot. When installed in place of the directional gyro, the primary function of the G5 is to provide directional information to the pilot. NOTE: The pilot is reminded to perform appropriate flight and navigation instrument cross checks for the type of operation being conducted. In case of a loss of aircraft electrical power, a backup battery (optional when installed as a DG/HSI) sustains the G5 Electronic Flight Instrument for up to four hours. An optional GAD 29B/GAD 29D may be installed to provide course and heading datum to an autopilot based on the data selected for display on the HSI. An optional GAD 13 and OAT probe may be installed to provide measured outside air temperature (OAT) to the G5 for display of true airspeed (TAS), outside air temperature, winds, and density altitude. This STC allows the removal of the aircraft’s vacuum system if it is not required to support any other airframe system. AFMS, Garmin G5 AML STC 190-01112-13 Rev. 8 Page 1–2 Abbreviations and Terminology The following glossary is applicable within the airplane flight manual supplement ADI Attitude Direction Indicator AFMS Airplane Flight Manual Supplement ATT Attitude CDI Course Deviation Indicator DG Directional Gyro DR Dead Reckoning FAA Federal Aviation Administration GPS Global Positioning System GPSS GPS Roll Steering HDG Heading HSI Horizontal Situation Indicator ILS Instrument Landing System LOC Localizer (no glideslope available) LOI Loss of Integrity OAT Outside Air Temperature TAS True Airspeed VFR Visual Flight Rules VHF Very High Frequency VOR VHF Omni-directional Range 190-01112-13 Rev. 8 AFMS, Garmin G5 AML STC FAA APPROVED Page 2–1 SECTION 2 – LIMITATIONS System Software Requirements The G5 must utilize the following or later FAA approved software versions for this AFMS revision to be applicable: Component Software Version G5 Electronic Flight Instrument 8.00 Use of Secondary Instruments The original type design approved instruments for airspeed, altitude and vertical speed remain the primary indications for these parameters. If the G5 Electronic Flight Instrument is installed in place of the rate of turn indicator, the original type design approved instrument for attitude remains in the primary indication for attitude. If the G5 Electronic Flight Instrument is installed in place of the directional gyro, the original type design approved instruments for attitude remains the primary indication for attitude. NOTE: For aircraft approved for VFR-only operations, the G5 Electronic Flight Instrument may be installed as an attitude indicator and rate of turn indicator. Kinds of Operations No Change except for the following: • When a portable navigation source is selected on the G5, it shall not be used for the primary means of navigation for IFR operations. AFMS, Garmin G5 AML STC 190-01112-13 Rev. 8 Page 2–2 FAA APPROVED This page intentionally left blank. 190-01112-13 Rev. 8 AFMS, Garmin G5 AML STC FAA APPROVED Page 3–1 SECTION 3 – EMERGENCY PROCEDURES G5 Failure Indications If a G5 function fails, a large red ‘X’ is typically displayed over the instrument(s) or data experiencing the failure. Upon G5 power-up, certain instruments remain invalid as equipment begins to initialize. All instruments should be operational within one minute of power-up. If any instrument remains flagged and it is not likely an installation related problem, the G5 should be serviced by a Garmin-authorized repair facility. Attitude Failure Attitude failure is indicated by removal of the sky/ground presentation, a red X, and a yellow “ATTITUDE FAIL” on the display. Rate-of-turn and slip information will not be available. 1. Use standby instruments. 2. Seek VFR conditions or land as soon as practical. Heading Failure, Loss of Magnetometer Data, or Magnetic Field Error A heading failure, loss of magnetometer data, or magnetic field error is indicated by removal of the digital heading readout, a red X, and a yellow “HDG” on the display. 1. Use standby magnetic compass. NOTE: If the G5 DG/HSI has a valid GPS signal the G5 DG/HSI instrument will display the GPS track information in magenta. AFMS, Garmin G5 AML STC 190-01112-13 Rev. 8 Page 3–2 FAA APPROVED GPS Failure If GPS navigation receivers and/or navigation information are not available or invalid, the G5 will display Dead Reckoning mode (DR) or Loss of Integrity mode (LOI) on the HSI in the lower left corner. If Alternate Navigation Sources (ILS, LOC, VOR) Are Available: 1. Use alternate navigation source. If No Alternate Navigation Sources Are Available: If DR is Displayed on HSI: 1. Use the amber CDI for course information. 2. Fly toward known visual conditions. If LOI is Displayed on HSI: 1. Fly toward known visual conditions. For aircraft equipped with a GAD 29B/GAD 29D interfaced to an autopilot, GPSS will be displayed in amber text when GPSS emulation has been selected from the G5 menu. 1. Deselect GPSS from the G5 menu and select a different autopilot mode. Attitude Aligning During system initialization, the G5 displays the message ‘ALIGNING’ over the attitude indicator. The G5 will typically display valid attitude within the first minute of power-up. The G5 can also align itself while taxiing and during level flight. If the “ALIGNING” indication occurs during flight and attitude remains displayed, the attitude display is acceptable for use for flight in instrument conditions. The message will clear when the attitude solution is within the systems internal accuracy tolerances. It is recommended to maintain wings level to reduce the time for the system to align. Attitude Aligning / Keep Wings Level If the “ALIGNING KEEP WINGS LEVEL” indication occurs during flight, the G5 has detected an invalid attitude solution and will not display any attitude information. 1. Use standby instruments to maintain wings level flight. The system will display attitude when internal accuracy tolerances have been met. 2. If attitude does not return, seek VFR conditions or land as soon as practical. Loss of Electrical Power to the G5 Display In the event of a loss of aircraft electrical power to the G5 attitude display, the indicator will continue to function on its internal battery. If an internal battery is installed on the optional G5 HSI, the indicator will continue to function on the internal battery if aircraft power is lost. Internal battery endurance is indicated on the G5 display in hours and minutes. The charging symbol will be removed and the internal battery will not be charged. In the event the G5 attitude display powers down, the optional G5 HSI will automatically revert to displaying attitude information. It will not revert back to the DG/HSI format if the G5 attitude unit regains power. The DG/HSI presentation may be selected from the G5 menu on the G5 DG/HSI unit after reversion to the attitude display. 190-01112-13 Rev. 8 AFMS, Garmin G5 AML STC FAA APPROVED Page 3–3 Loss of Electrical Power to the GAD 29B/GAD 29D (If Installed) In the event of a loss of aircraft electrical power to the optional GAD 29B/GAD 29D, the heading and course datum will be unavailable to the autopilot and the autopilot may deviate from the intended path or may disconnect. GPS flight plan course information may be displayed on the HSI and VFR will be displayed in amber text on the HSI. GPSS will be displayed in amber text, if GPSS mode is selected. 1. Deselect GPSS from the G5 menu and select a different autopilot mode. 2. Lateral GPS course guidance may only be used in VFR conditions. Loss of Electrical Power to the GAD 13 (If Installed) In the event of a loss of aircraft electrical power to the optional GAD 13, the OAT and TAS indications will be replaced with a red X. The Density Altitude indication will be removed, and “No Wind Data” will be displayed in the wind field. 1. Use an alternate source of outside air temperature to calculate true airspeed, density altitude, and winds. AFMS, Garmin G5 AML STC 190-01112-13 Rev. 8 Page 3–4 FAA APPROVED Internal Battery Failure In the event of a failure of the G5 internal battery, “NO BATT” will be displayed with a red X. This indicates that the G5 internal battery is not functional. 1. If “NO BATT” is displayed on the G5 attitude indicator, do not fly in instrument meteorological conditions. WARNING If NO BATT is displayed on the G5 attitude indicator, the unit will not function in the event of a loss of aircraft electrical power to the G5 attitude indicator. Do not fly in instrument meteorological conditions if NO BATT is displayed on the G5 attitude indicator. 190-01112-13 Rev. 8 AFMS, Garmin G5 AML STC FAA APPROVED Page 4–1 SECTION 4 – NORMAL PROCEDURES G5 Power Button and Knob The G5 display will power on with the application of aircraft power. The G5 power button is used to turn the display on and off. Press and hold the power button to turn the display off. The knob performs the following functions: Press Press to access the Menu. From the Menu, press to select the desired menu item. Press to accept the displayed value when editing numeric data or selecting from a list. Press to sync the heading or track bug for the HSI. Turn From the Menu, turn the Knob to move the cursor to the desired menu item. For the ADI, rotate to adjust the baro setting on the secondary altitude display. For the HSI, rotate to adjust the heading or track bug. Turn to select the desired value when editing numeric data or selecting from a list. Backlight Intensity Adjustment The power up state of the G5 backlight is in Auto adjustment mode. To adjust the backlighting: To select Manual mode from Auto mode: 1. While the unit is turned on, press the Power button. 2. Turn the knob to manually adjust the backlight intensity. 3. Press the knob to close the backlight page. To select Auto mode from Manual mode: 1. While the unit is turned on, press the Power button. 2. Press the Power button again to select Auto. 3. Press the knob to close the backlight page. AFMS, Garmin G5 AML STC 190-01112-13 Rev. 8 Page 4–2 FAA APPROVED Prior to Flight in Instrument Meteorological Conditions 1. Press the Power button on the G5 attitude indicator. 2. Verify the battery status indicator is green on the G5 attitude indicator. (The battery status indicator will change from green to amber or red when battery status has decreased below 41%). Valid Battery Indication No Battery Detected WARNING If NO BATT is displayed on the G5 attitude indicator, or green battery status is not shown after pressing the power button on the G5 attitude indicator, do not fly in instrument meteorological conditions. 190-01112-13 Rev. 8 AFMS, Garmin G5 AML STC FAA APPROVED Page 4–3 Autopilot Operations with the G5 The G5 and optional GAD 29B/GAD 29D offer various integration capabilities dependent upon the type of autopilot installed in a particular aircraft. The G5 Electronic Flight Instrument installation in this aircraft provides the following autopilot functions (appropriate boxes will be checked):  This installation does not interface with the autopilot (basic wing leveling autopilot or no autopilot is installed in the aircraft).  A GAD 29B/GAD 29D Adapter is installed in this aircraft.  Course Selection coupling to the autopilot.  NAV Selection coupling to the autopilot.  Heading Bug coupling capability to the autopilot.  Roll Steering (GPSS) emulated via heading mode. OR  Roll Steering capable autopilot (GPSS menu function for emulation not applicable). Course / NAV Selection Coupling to the Autopilot (If Configured) When operating the autopilot in NAV mode, the deviation information from the installed navigation sources (i.e. GPS or NAV) is switched via the navigation source. The NAV source displayed on the HSI is the NAV source the autopilot is following. Many autopilots also use the course datum to determine the best intercept angles when operating in NAV mode. Heading Bug Coupling Capability to the Autopilot (If Configured) When operating the autopilot in HDG mode, the difference between the HDG bug location on the HSI and the actual aircraft heading creates an error signal which the autopilot will minimize by turning in the direction of the bug. If the bug is turned more than 180 degrees, the autopilot may turn the airplane in the opposite direction of the desired turn. Roll Steering (GPSS) Emulated via HDG Mode (If Configured) For autopilots that do not support digital GPSS signals, GPSS functionality may be emulated by operating the autopilot in HDG mode and selecting GPSS from the G5 menu. If the autopilot is already designed to receive roll steering information, the data is transmitted digitally from the navigator to the autopilot. When GPSS is selected on the G5 menu, the heading bug on the ADI and HSI changes to a hollow outline and a crossed-out heading bug appears on the G5 ADI and HSI display indicating that the autopilot is not coupled to the heading bug. The bug is still controllable and may still be used for reference. AFMS, Garmin G5 AML STC 190-01112-13 Rev. 8 Page 4–4 FAA APPROVED When GPSS is selected on the G5, GPSS turn commands are converted into a heading error signal to the autopilot. When the autopilot is operated in HDG mode, the autopilot will fly the turn commands from the GPS navigator. If the GPSS data is invalid (for example, if there is no active GPS leg) or the selected navigation source on the G5 ADI and HSI is not GPS, the annunciated GPSS text will be yellow and a zero turn command will be sent to the autopilot. HSI Source Selection (If Configured) For aircraft configured with two navigation inputs to the G5, the desired source may be selected using the G5 knob and menu selection. Press the G5 knob to cycle between the NAV1 and NAV2 input. HSI Portable Navigation Device GPS VFR Annunciation (If Configured) For aircraft configured for a portable navigation device input to the G5, a GPS VFR indicated in magenta will be displayed on the HSI. When the G5 with a portable navigation device is interfaced there is not enough guidance data for IFR use . 190-01112-13 Rev. 8 AFMS, Garmin G5 AML STC FAA APPROVED Page 5–1 SECTION 5 – PERFORMANCE No change. AFMS, Garmin G5 AML STC 190-01112-13 Rev. 8 Page 5–2 FAA APPROVED This page intentionally left blank. 190-01112-13 Rev. 8 AFMS, Garmin G5 AML STC FAA APPROVED Page 6–1 SECTION 6 – WEIGHT AND BALANCE See current weight and balance data. AFMS, Garmin G5 AML STC 190-01112-13 Rev. 8 Page 6–2 FAA APPROVED This page intentionally left blank. 190-01112-13 Rev. 8 AFMS, Garmin G5 AML STC Page 7–1 SECTION 7 – SYSTEM DESCRIPTION Refer to Garmin G5 Electronic Flight Instrument Pilot’s Guide for Certified Aircraft, part number 190-01112-12 Rev A (or later approved revisions), for a description of the G5 electronic flight instrument. This reference material is not required to be on board the aircraft but does contain a more in-depth description of all the functions and capabilities of the G5. The ATT circuit breaker supplies power to the G5 instrument for normal power operation and to charge the internal battery. The DG circuit breaker supplies power to the G5 instrument for normal power operation when configured as a DG, and to charge the internal battery (if installed). The HSI circuit breaker supplies power to the G5 instrument for normal power operation when configured as an HSI, and to charge the internal battery (if installed). The GAD circuit breaker supplies power to the optional GAD 29B/GAD 29D adapter and optional GAD 13 adapter for normal power operation. System Messages The G5 has the capability to display system messages to the crew along the bottom of the display. A system message is indicated through a white indication on the G5. Messages can be displayed by pressing the G5 knob and selecting the Message menu item. (For Reference Only) AFMS, Garmin G5 AML STC 190-01112-13 Rev. 8 Page 7–2 The following table shows the meaning of each message. System messages are displayed in white text. Message Meaning External Power Lost Aircraft power has been removed from the G5. Critical battery fault! Powering off Battery has critical fault condition and the unit is about to power off to avoid damage to the battery. Battery fault Battery has a fault condition – unit needs service. Battery charger fault Battery charger has a fault condition – unit needs service. Low battery Battery charge level is low. Hardware fault Unit has a hardware fault – unit needs service. Power supply fault Unit power supply fault detected – unit needs service. Unit temperature limit exceeded Unit is too hot or too cold. Network address conflict Another G5 with the same address is detected on the network (most commonly a wiring error on one of the units). Communication error General communication error (most commonly appears in conjunction with Network Address Conflict message). Factory calibration data invalid Unit calibration data not valid – unit needs service. Magnetic field model database out of date Internal magnetic field database is out of date - software update required. Magnetometer Hardware fault The magnetometer has detected a fault – unit needs service. Heading data may not be available. Using external GPS data GPS data from another network LRU is being used. The unit's internal GPS receiver is enabled, but unable to establish a GPS fix. Not receiving RS-232 data The G5 is not receiving RS-232 data from the GPS navigator – system needs service. Not receiving ARINC 429 data The G5 is not receiving ARINC 429 data from the navigation source – system needs service. GPS receiver fault The G5 on-board GPS receiver has a fault. ARINC 429 interface configuration error The G5 ARINC 429 port is receiving information from an incorrect source – system needs service. Software version mismatch The G5 attitude indicator and the G5 HSI units have different software. Cross fill of baro, heading and altitude bugs is disabled. These messages remain while the condition persists.