Garmin G1000

Garmin G1000

OutlineBlock DiagramsLine Replaceable Unit ConceptAircraft InstrumentationG1000 Components ExplainedFailure OperationsEmergency Power Distribution (C172 NAV III) Alerts (C172 NAV III & DA42 L360)References

-Some aircraft in the fleet are NOT equipped with GDU 1044B displays or GFC 700 FlightDirectors.

-This diagram appliesto both the C172 andthe DA-42 L360.

.Garmin 1000 Block Diagram

3Garmin 1000 Optional Equipment

-Select ERAU C172 Nav IIIs are equipped with GDL 69AData Links.*The XM subscriptions inthese aircraft are not maintained.

-All C172 Nav IIIs are equipped with CO Guardian carbonmonoxide detectors.

-406 MHz ELTs utilize GPS derived position information from GIA #1.

-Other optional equipmentis not installed in ERAU G1000 equipped aircraft.

Line Replaceable UnitsLine Replaceable UnitsEach box on the above block diagrams are considered line replaceable units (LRUs).

LRUs allow for the removal and reinstallation of equipment by maintenance in a fraction of the time it would take to replace/repair traditional equipment.

LRUs also allow for the manufacturer to mount various components behind the displays or in remote locations in the aircraft, based upon need.

The following slides demonstrate the removal of an LRU. *(They do not represent the location of LRUs in the C172 or DA42-L360)

Aft Avionics BayBehind MFDLeft Wing

GIA 63 #2COM2NAV2GPS 2

GTX 33Mode SXPDRw/ TIS

GIA 63 #1COM1NAV1GPS 1

GRS 77AHRS

GMU 44Magnetometer

GMA1347GDU 1040 #1(PFD)

GDU 1040 #2(MFD)Cockpit

GEA 71EngineAirframeInterface

GDC 74AADCCessna172SNav III11

Aft Avionics BayCockpit

GIA 63 #2COM2NAV2GPS 2

GTX 33Mode SXPDRw/ TIS

GIA 63 #1COM1NAV1GPS 1

GRS 77AHRS

GEA 71EngineAirframeInterface

GMA1347GDU 1040 #1(PFD)

GDU 1040 #2(MFD)

GMU 44Magnetometer

GDC 74AADCBehind PFDRight Wing TipBehind Engine CompartmentDiamondDA-42 L36012Aircraft Instrumentation

Round Dial Vs. G1000AirspeedAltitudeAttitudeDG/HSIVertical Speed

Airspeed Indicator

Markings Airspeed markings are the same as those depicted on a round dial airspeed indicator. Trend Vector The end of the trend vector displays approximately what airspeed will be reached in 6 seconds if the current rate of acceleration is maintained. This is displayed as a magenta line up and down the airspeed indicator.

True Airspeed

Attitude Indicator

Pitch Graduation Displayed in 2.5 increments. Bank Graduation Major tick marks at 30 and 60 and minor tick marks at 10, 20, and 45 are shown to both the left and right of zero.

Unusual Attitude RecoveryChevron DisplayNose High 50Nose Low 30De-clutterNose High 30Nose Low 20Bank 65

Altimeter

Trend Vector The end of the trend vector displays approximately what altitude will be reached in 6 seconds if the current rate of vertical speed is maintained.Altitude Graduation 20ft increments with numeric labels every 100ft.Barometric Setting BoxAltitude BugMetric DisplayVertical Speed Indicator

Vertical Speed Graduation Numbered labels are displayed in 1000 increments. The Vertical Speed Pointer displays the current vertical speed when the rate exceeds 100fpm.Vertical Speed PointerHorizontal Situation Indicator

HSI Displays heading information overlaid with navigation information to enhance horizontal situational awareness. Tick Marks Located at 45 intervals to aid in establishing intercept angles.

Current Track IndicatorNavigation SourceGPS Flight Phase

Turn Rate Trend VectorSlip/SkidTurn and Slip

Turn Rate Indicator Displays half-standard rate and standard rate turns. Rates greater than 4 deg/sec are depicted by an arrowhead.Slip/Skid One slip/skid indicator displacement is equal to one ball displacement on a traditional slip/skid indicator.21Primary Flight Display (PFD)&Multi-Function Display (MFD)GDUPFD/MFDBoth Displays are identical in hardware.The aircraft wiring harness determines whether the display functions as a PFD or an MFD.An Ethernet-based, high speed digital data-bus ties the display units and integrated avionics units together.

PFDMFDPFD/MFD

Right sideCOM VOL/SQCOM Frequency Transfer keyCOM Frequency SelectorCourse and Baro SelectorRange/Pan JoystickDirect-To, Flight Plan, Clear, Menu, Procedures, and Enter keysFlight Management System (FMS)Left sideNAV VOL/SQNAV Frequency Transfer keyNAV Frequency SelectorHeading SelectorAltitude SelectorPFD/MFD Bezel ControlsSecure Digital Memory CardsBottom SlotSupplemental Data Card Databases:Expanded BasemapTerrainAirport TerrainObstaclesSafe TaxiAirport Directory (AOPA)FliteCharts or ChartView (MFD Only)Top SlotUsed For:Importing/Exporting Flight PlansFlight Data LoggingLoading Database UpdatesPrimary Flight Display (PFD)Additional information on PFDTopNav frequency windowCom frequency windowWaypoint status windowAutopilot annunciation BottomInset MapOutside Air TemperatureTransponder windowSystem time

Primary Flight Display (PFD) Soft KeysAdditional information on PFDSoft keysINSET - Moving map inset optionsPFD - PFD configurations and bearing pointersOBS - GPS manual sequencing and course selection CDI - Selects HSI navigation source XPDR - Transponder code and mode selectionIDENT Transponder ident functionTMR/REF - Reference speeds and timer functionNRST - List of nearest airportsALERTS - Alerts window

Multi-Function Display (MFD)Page Group IconEngine GaugesNAV frequenciesCOM frequenciesWaypoint Status BarPage Group and Page NameMulti-Function Display (MFD)Page Group IconThe Page Group Icon shows which page group and active page is being viewed.

Page Groups:-Map -Waypoint -Auxiliary -Flight Plan -Nearest29Multi-Function Display (MFD)Map Page GroupNavigation MapTraffic MapStormscopeTerrain Proximity / TAWS-BWeather Data Link (Optional)

Multi-Function Display (MFD)Waypoint (WPT) Page GroupAirport Information Pages:-Airport Information-Airport Directory-Departure Information-Arrival Information-Approach Information-Weather InformationIntersection InformationNDB InformationVOR InformationUser Waypoint Information

Multi-Function Display (MFD)Aux Page GroupTrip PlanningUtilityGPS StatusSystem SetupSystem StatusXM Information

Multi-Function Display (MFD)Flight Plan Page GroupActive Flight Plan / Vertical NavigationFlight Plan Catalog

Multi-Function Display (MFD)Nearest Page GroupNearest Pages-Airports-Intersections-NDBs-VORs-User Waypoints-Frequencies-Airspaces

Audio PanelGMAAudio PanelThe digital audio panel features controls for three (3) major function groups:CommunicationsNavigationIntercom System (ICS)Intercom Volume and Manual Squelch Controls are also on the panel.Fail-Safe OperationA fail-safe circuit connects the pilots headset and microphone directly to COM1 in the event power is interrupted or the unit is turned off. Digital performance is no longer available resulting in analog operation.Reversionary ModePressing the DISPLAY BACKUP button activates/deactivates reversionary mode.

Marker Beacon ReceiverControlsAudio PanelSplit Com FunctionSplit COM performance varies significantly across installations and is affected by both the distance between the antennas and the separation of the tuned frequencies.Split COM operations are NOT authorized and are disabled in the Cessna 172 NAV III and DA-42 L360.Marker Beacon ReceiverThe marker beacon receiver is integrated into the audio panel.Beacon receiver arm/mute/disarm and High Sense controls are located on the panel.It is recommend the receiver be operated in low sense during ILS operations.

Marker Beacon IndicationsOuter MarkerMiddle MarkerInner MarkerIntegrated Avionics UnitGIAIntegrated Avionics UnitCommunications hubs for the systemPrimary communications paths for system components to the PFD and MFD.This provides for a high level of system redundancy and integrity as data is cross-checked to ensure proper system operation.Avionics housed within the each unit include:VHF COM TransceiverVOR/Localizer ReceiverGPS Receiver (WAAS upgrade if installed) Glide Slope ReceiverSystem Integration Processor

**See the G1000 LRU diagrams for LRU interfacing with the Integrated Avionics Units.

Integrated Avionics Units

C172: Aft Avionics Bay Looking Through Baggage DoorIntegrated Avionics Units

DA42-L360: Avionics Bay Looking Through Back Door Under Baggage CompartmentFront of AircraftAir Data ComputerGDCAir Data ComputerInputs include:Pitot StaticOutside Air TemperatureProduces:Airspeed IndicatorAltimeter Vertical Speed IndicatorOutside Air Temperature True Airspeed Other E6B type calculations provided within MFD pages.Designed Operating Range:Altitude -1,400 ft to 55,000 ftIAS up to 430 knotsOperates -55oC to +70oCAccuracy supports RVSM

Air Data ComputerC172: Behind Avionics Bay Cooling Fan. Picture Taken From Behind Avionics BayFrontofAircraft

Air Data Computer

DA42-L360: Behind PFDFrontofAircraftOutside Air Temperature Probe (GTP)

C172DA42-L360Attitude Heading Reference System (AHRS)GRSAttitude Heading Reference SystemProduces:

Attitude Indicator

Heading/HSI

Slip/Skid

Turn Rate Trend Vector

Solid state component utilizing MEMS technology.Alignment can occur in as little as 1 min even while the aircraft is taxiing. In-air dynamic restarts can occur at bank angles up to 20.Inputs from GPS, GDC, and GMU are used as reference to enhance performance and integrity. Failure of the AHRS will occur before any hazardous or misleading information is displayed. Attitude Heading Reference System

Attitude Heading Reference SystemMicro Electro-Mechanical System (MEMS)MEMS technology determines attitude by measuring changes in vibration through tiny elements.When an acceleration occurs in any of the three axis of rotation, the vibration frequency changes slightly which induces a voltage that can be measured as a change in pitch, bank or yaw.

Attitude Heading Reference SystemExternal Inputs (GDC, GPS, GMU):The AHRS is not totally self-sufficient and must have GPS input or both the Magnetometer and the ADC to consider itself reliable.If the AHRS does not have sufficient inputs to cross-check itself, or if it does detect an error, it will flag itself as unreliable and display red-X ATTITUDE FAIL.A gyroscope, whether physical or electronic, must be referenced to something in the real world. That is, a gyroscope must have an erecting mechanism.The G1000 AHRS maintains its alignment primarily by using GPS and ADC-determined flight path information.The AHRS also uses the vertical component of the magnetometers output to correct pitch.

Attitude Heading Reference System

Attitude Heading Reference SystemC172: Behind Avionics Bay Cooling Fan. Picture Taken From Behind Avionics BayFrontofAircraft

Attitude Heading Reference System

Front of AircraftDA42-L360: Avionics Bay Looking Through Back Door Under Baggage CompartmentMagnetometerGMUMagnetometerSenses the Earths magnetic field information and measures both the vertical and horizontal components. Data is sent to the AHRS for processing.Powered directly by the AHRS.

MagnetometerC172: 7.5ft in from left wing tip. 27 inches back from leading edge58Mode S Transponder GTXMode S TransponderFeatures:Solid-state unit requiring no warm-up time. Automatically transitions to ALT reporting mode at a ground speed of 30kts.Interrogation/Reply Capability:Mode SProvides data-link capability allowing for the reception and presentation (if selected) of airborne traffic, using the FAA-provided TIS (Traffic Information Service) system within a 55 mile radius of select ground sites. ERAU aircraft are equipped with and present traffic information through the use of ADS-B and TIS-B which does NOT rely on Mode S transponder input.Mode CMode A

Mode S Transponder

C172: Aft Avionics Bay Looking Through Baggage DoorMode S Transponder

Front of AircraftDA42-L360: Avionics Bay Looking Through Back Door Under Baggage CompartmentEngine/Airframe UnitGEAEngine/Airframe UnitMain processing unit for all engine instrumentation and airframe data.Input Capabilities:Manifold Pressure/Engine RPMOil Temp/PressureEGT/CHT on all cylindersElectrical System DataFuel System DataVacuum System DataAirframe DataThe Engine Indication System (EIS) may also produce annunciations associated with cabin and baggage doors.

C172: Located behind MFD Engine/Airframe Unit

Engine/Airframe UnitLeft Engine GEA

Right Engine GEA

DA42-L360: Located Behind Engine Compartment in Engine NacelleADS-B Datalink TransceiverGDL 90ADS-B Data LinkTransmits, receives and decodes Automatic Dependant Surveillance-Broadcast (ADS-B) and Traffic Information Service-Broadcast (TIS-B) traffic information.Incorporates a WAAS GPS receiver (TSO-C145a). Transmits/Receives through two Universal Access Transceiver (UAT) antennas. Interfaces through GIA #2.

C172 2nd Baggage CompartmentADS-B Data Link Antennas

WAAS GPS Receiver AntennaUniversal Access Transceiver (UAT) AntennasAutomatic Dependant Surveillance-Broadcast (ADS-B)PurposeInformation produced by ADS-B and TIS-B is intended to enhance a pilots visual acquisition of nearby aircraft and NOT in place of acknowledging traffic advisories by ATC without visual acquisition or for initiation of avoidance maneuvers. Utilizes GPS positioning to transmit:Aircraft PositionVelocityProjected TrackAltitudeFlight IdentificationData Link Capable of Receiving:ADS-B information from other ADS-B equipped aircraft and Ground Based Transceivers (GBTs)TIS-BFIS-B

ADS-B ArchitectureXM Satellite Data LinkGDL 69AXM Satellite Data LinkProvides XM Satellite Weather and XM Satellite Radio entertainment services.The GDL 69A is interfaced directly with the MFD and displays graphical weather information on the MFD and PFD inset map.

*The XM WX Satellite Weather subscription must be maintained.*Do not utilize XM Weather information to penetrate hazardous weather.*Only a handful of C172 are equipped with the GDL 69A and the XM subscriptions are not maintained.

XM Satellite Data Link

C172: Aft Avionics Bay Looking Through Baggage DoorAutopilotHoneywell KAP 140AutopilotThe autopilot utilizes information from:AHRS (Heading)ADC (Altitude)GIA2 (NAV/LOC/GP/GPS)Turn Coordinator (Turn Rate)This turn coordinator is located behind the instrument panel and is not visible to the pilot.The autopilot is linked to the system through GIA #2. *See KING KAP 140 supplemental in POH for operational guidance.

C172: Turn Coordinator Located Behind Instrument PanelAutopilot

Autopilot

DA42-L360: Turn Coordinator Located Behind Instrument PanelFrontOf AircraftCooling FansCessna 172 NAV IIIDA42-LCooling FansThe C172 system contains four cooling fans:Display cooling fan behind PFD and MFD.Avionics bay cooling fan in baggage compartment.Instrument panel cooling fan in dash.The DA42-L360 system contains three cooling fans:Display cooling fan behind PFD and MFD.Avionics bay cooling fan.Cooling Fans

PFD/MFD Display Cooling Fans

Instrument Panel FanAvionics Bay FanC172Cooling Fans

Front of AircraftDA42-L360: Avionics Bay Looking Through Back Door Under Baggage CompartmentFailure OperationsSystem Failure Indications

PFD/MFD FailureSingle Display FailureIf one display fails, the primary flight instruments and Engine Indication System (EIS) are displayed on the remaining screen. This operation mode is called Reversionary Mode.The onside radio of the failed display will automatically tune to 121.5.The failed GDUs associated Integrated Avionics Unit (GIA) will also be lost. Dual Display FailureBoth radios automatically tune to 121.5.The audio panel is subsequently lost and the pilots headset connected to COM 1 through a fail-safe circuit.

PFD/MFD Failure

PFD FailureReversionary ModeThe system will automatically detect a display failure and initiate reversionary mode.

The DISPLAY BACKUP button can also be pressed to manually initiate reversionary mode.

Reversionary Mode

Audio Panel FailureA fail-safe circuit connects the pilots headset and microphone directly to COM1 in the event power is interrupted or the unit is turned off. Digital performance is no longer available resulting in analog operation.

Intercom communications will be lost.

Stuck PTTIf the push-to-talk (PTT) key becomes stuck, the COM transmitter stops transmitting after 35 seconds of continuous operation. An alert appears on the PFD to advise the pilot of a stuck microphone.

Air Data Computer FailurePresentation of the airspeed, altitude, vertical speed, OAT and TAS display a red X. If the OAT probe fails, a red X appears both on the TAS box and the OAT box. Pressure altitude reporting for the transponder is lost (Mode C) and only Mode A capabilities are available.Associated ADC instrumentation will still be displayed in the event of a Pitot-Static system blockage.The KAP 140 autopilot will not operate in vertical speed, altitude capture, or altitude hold modes.Air Data Computer Failure

Attitude Heading Reference SystemFailureIf improper operation is detected when compared to other aircraft sensors (GPS, ADC, Magnetometer) all attitude and heading presentations are removed and replaced with a red X and the words Attitude Fail.Failure indications are designed to display before Hazardous or Misleading Information (HMI) is presented.The KAP 140 autopilot will only operate in Roll Mode.

Attitude Heading Reference System Failure

Attitude Heading Reference System Failure

Magnetometer FailureLoss of the Horizontal Situation Indicator (HSI), heading information, and the turn rate trend-vector will occur if the magnetometer fails.

Magnetometer Failure

Integrated Avionics Unit FailureSingle Unit FailureThe associated COM/NAV/GPS receiver data is no longer available. The pilot should tune and select the COM and VHF NAV receiver on the operative GIA unit.The operative GPS receiver will automatically take over any active GPS navigation.**Failure of GIA#2 will result in the loss of the GDL 90, KAP 140 Autopilot, and CO Guardian Carbon Monoxide Detector (C172 Only).Dual Unit FailureThe transponder (GTX), engine/airframe unit (GEA), and clock will be lost in addition to both GIA unit associated COM/VHF NAV/GPS receivers.The ADC and AHRS will provide data directly to the GDUs through backup paths.Failure of the Ethernet High-Speed Data Bus between the PFD/MFD will result in the inability for a GDU to communicate with the opposite GIA. Integrated Avionics Unit Failure

Dual GIA FailureNote the Transponder (GTX) and Engine Airframe Unit (GEA) failure associated with the dual GIA failure.Transponder FailureTransponder failure will not affect any other LRU.

A red X will be displayed over the transponder window on the PFD.Engine/Airframe Unit FailureA GEA unit failure will result in the loss of all engine/airframe data.Due to the DA42-L360 having two GEAs only the onside data will be lost in the event of a single GEA unit failure.

A much more likely scenario would be one in which an individual probe or sensor fails. In this case the individual indication would display a red X. Engine/Airframe Unit Failure

Complete GEA unit failure.System StatusLRU Status information can be accessed through the MFDs Auxiliary chapter, System Status page.

Checkmark: Active LRUs Red X: Failed LRUs

Pertinent database information is also displayed.

ANN TEST Causes an annunciation test tone to be played and all audio panel lights to illuminateEmergency Power DistributionCessna 172 NAV IIIEmergency Power DistributionThe standby battery will provide at least 30 mins of power to the essential bus provided the battery is fully charged.Essential Bus Components:Standby BatteryPFDEISAHRSADCCOM 1 TransceiverNAV 1 (VOR/LOC/GS/GPS) ReceiversStandby Instrument Back Lights

Standby BatteryBehind PFDAlertsCessna 172 NAV III&Diamond DA42 L360Alert DefinitionsWarnings (Red)Caution (Yellow)Message Advisory (White)Aural Warnings (Tone or Voice)

Soft-Key Function:Warning: Press soft-key to acknowledge, silence tone, and read.Caution: Press soft-key to acknowledge and readAdvisory: Press soft-key to read, scroll with FMS knob.

WarningsC172 NAV IIICO LVL HIGH HIGH VOLTSLOW VOLTS*OIL PRESSUREPITCH TRIM**DA42 L360AP TRIM FAILDOOR OPENL/R ALTN FAILL/R FUEL PR HIL/R FUEL PR LOL/R OIL PRESL/R STARTER

*Aural tone is inhibited while the aircraft is on the ground.**KAP 140 installations only. No aural tone will occur.Produces a continuous tone requiring acknowledgment by the pilot.

Visual annunciator is displayed next to the Vertical Speed Indicator on right side of PFD.

Press alert soft-key to acknowledge alert. CautionsC172 NAV IIILOW FUEL LLOW FUEL RLOW VACUUMSTBY BATTDA42 L360L/R AUX FUEL EL/R FUEL LOWL/R VOLTS LOWPITOT FAILPITOT HT OFFSTAL HT FAILSTAL HT OFFSTICK LIMIT

Produces a single tone.

Visual annunciator is displayed next to the Vertical Speed Indicator on right side of PFD.

Press alert soft-key on PFD to acknowledge alert.AdvisoriesSystem Message Advisory CategoriesPFD & MFDDatabaseGMA (Audio Panel)GIA (Integrated Avionics)GEA (Engine/Systems)GTX (Transponder)GRS (AHRS)GMU (Magnetometer)GDL (Data-link)GDC (ADC)MiscNo tone is produced.

Alert soft-key will flash, requiring pilot acknowledgement.

Reference the G1000 Cockpit Reference Guide (CRG) for advisory explanation.

ReferencesAIMCessna 172 NAV III Information ManualCessna 172S NAV III An Advanced Pilots GuideDiamond DA42 L360 Airplane Flight ManualG1000 Cockpit Reference GuideG1000 Guide for DPE/CFIsG1000 Pilot GuideNasiri, Steven. A Critical Review of MEMS Gyroscopes Technology and Commercialization Status. InvenSense. 26 Oct. 2008. McClellan, J. Mac. Garmin G1000 Ignites a New Passion. Jan. 2004. Flying Magazine. http://www.flyingmag.com/avionics/358/garmin-g1000-ignites-a-new-passion.htmlWhite, Elecia, and Jose A. Rios. FAA Certification of a MEMS Attitude and Heading Reference System. Crossbow Technology, Inc.