Table of Contents
1.0INTRODUCTIONANDDESCRIPTION
1.1Purpose
1.2SummaryofOperationalCharacteristics
1.3BriefDescriptionoftheSystemComponents
1.4UnitDescription
1.4.1SymbolGenerator/ProcessorUnit(SG)
1.4.2ControlPanel(CP)
1.4.3DisplayUnit(DU)
1.5Interchangeability
1.5.1General
1.5.2InterchangeabilityDesiredfortheARINC725EFI
1.6RegulatoryApproval
2.0INTERCHANGEABILITYSTANDARDS
2.1Introduction
2.2FormFactor,ConnectorsandIndexPinCoding
2.2.1SymbolGenerator/ProcessorUnit(SG)
2.2.2ControlPanel(CP)
2.2.3FormFactor"A"DisplayUnit
2.2.4FormFactor"B"DisplayUnit
2.2.5FormFactor"C"DisplayUnit
2.2.6FormFactor"D"DisplayUnit
2.2.7FormFactor"E"DisplayUnit
2.3Interwiring
2.4PowerCircuitry
2.4.1PrimaryPowerInput
2.4.2PowerControlCircuitry
2.4.3TheCommonGround
2.4.4TheACCommonCold
2.5EnvironmentalConditions
2.5.1ThermalInterfaceandDesign
2.5.1.1SG
2.5.1.2CP
2.5.1.3DisplayUnits
2.6Weights
2.7SystemFunctionsandSignalCharacteristics
2.8GroundingandBonding
3.0SYSTEMDESIGNCONSIDERATIONS
3.1General
3.2DisplayUnits
3.2.1DisplayDesignCriteria
3.2.1.1DisplayVisibility
3.2.1.2LineDefinition
3.2.1.3DisplayRefreshRate
3.2.1.4AbsolutePositionAccuracy
3.2.1.5RelativePositionAccuracy
3.2.1.6AllowableJitter
3.2.1.7PhosphorProtection
3.2.1.8PositionalStability
3.2.1.9DimensionalStability
3.2.1.10Focus
3.2.1.11Linearity
3.2.1.12OffCentering
3.2.1.13UniformityofBrightness
3.2.1.14BrightnessControl
3.2.1.15Convergence
3.2.2CathodeRayTubeAssemblyDesignCriteria
3.2.2.1PilotProtection
3.2.2.2X-RayRadiation
3.2.2.3AntireflectionCoating
3.2.2.4ViewingAngle
3.3SymbolGenerator/ProcessorUnit(SG)
3.3.1GeneralConsiderations
3.3.2PrimaryACPowerfortheSG
3.3.3SGPowerDissipation
3.4ControlPanel(CP)
3.4.1GeneralConsiderations
3.4.2ModeSelectandControls
3.4.3IntegralLighting
3.4.4PrimaryACPowerfortheCP
3.5SystemInterfaces
3.5.1DataSourceSwitching
3.5.2SGDigitalInputs
3.5.2.1ControlPanel(CP)Input-Flight
3.5.2.2ThrustControlComputer(TCC)Input
3.5.2.3FlightManagementComputer(FMC)Input
3.5.2.4FlightControlComputer(FCC)Input
3.5.2.5InertialReferenceSystemInput
3.5.2.6InstrumentLandingSystem(ILS)Input
3.5.2.7DistanceMeasurementEquipment(DME)Input
3.5.2.8VHFOmnirange(VOR)Input
3.5.2.9LowRangeRadioAltimeter(LRRA)Input
3.5.2.10WeatherRadar(WXR)Input
3.5.2.11AirDataSystem(ADS)Input
3.5.2.12AutomaticDirectionFinder(ADF)Input
3.5.2.13MicrowaveLandingSystem(MLS)InputProvisions
3.5.2.14FlightAugmentationComputer(FAC)Input
3.5.2.15FlightWarningComputerInput
3.5.2.16GlareShieldController(GSC)Input
3.5.3SGAnalogOutputs
3.5.4SGDigitalOutput(MaintenanceMonitor)
3.5.5CPDigitalOutputs
3.5.6CPAnalogInputs
3.5.7CPAnalogOutputs
3.5.7.1CPDiscreteOutputs
3.5.8DisplayUnitAnalogInputs
3.5.9DisplayUnitAnalogOutputs
3.6"IntegrityMonitoring"and"FailureWarning"
onDisplay
3.6.1General
3.6.2InternalMonitoringConcept
3.6.3PrimaryInformationConcerningtheIntegrity
Monitoring
3.7"Built-In-Push-To-Test"Equipment
4.0STANDARDSIGNALCHARACTERISTICS
4.1GeneralAccuracyandOperatingRanges
4.1.1Resolution
4.1.2StandardizedSignaling
4.1.2.1DigitalDataStandards
4.1.2.2Standard"AppliedVoltage"
4.1.2.3"StandardGround"Signals
4.2DataSignals
4.2.1DigitalDataInputs
4.2.1.1ARINC704/705IRS/AHRS12
4.2.1.2ARINC706AirDataSystem12
4.2.1.3ARINC702FlightManagementComputer12
4.2.1.4ARINC701FlightControlComputer12,3
4.2.1.5ARINC703ThrustControlComputer12
4.2.1.6ARINC710ILS12
4.2.1.7ARINC711VOR12
4.2.1.8ARINC709DME12
4.2.1.9ARINC707RadioAltimeter12
4.2.1.10ARINC712ADF12
4.2.1.11ARINC726FlightWarningComputer12
4.2.1.12ARINC727MLSReceiver12
4.2.1.13ARINC708WeatherRadar12
4.2.1.14FlightAugmentationComputer(FAC)12
4.2.1.15GlareShieldController(GSC)12
4.2.2DigitalDataOutputs
4.3DiscreteInputs
4.3.1SGFunctionProgramPins
4.3.2SGSourceSelectPins
4.3.3CPFunctionProgramPins
4.3.4DUSourceSelectPins
4.4DiscreteOutputs
5.0CONTROLPANELDESIGN
5.1General
5.2FormFactorsandConnector
5.3Cooling
5.4PanelIllumination
5.5PowerSupplyforCPOperation
5.6DiscreteWordFormat
5.7LiquidSpillageProtection
5.8DigitalDataOutput
6.0PROVISIONSFORAUTOMATICTESTEQUIPMENT
6.1General
6.2UnitIdentification
6.2.1PinAllocation
6.2.2UseofATLASLanguage
ATTACHMENTS
1NotesApplicabletoStandardInterwiring
2StandardInterwiring
3TopInsertPinUsage
3AMiddleInsertPinUsage
4ARINC725SGConnectorLayout
5EFISymbolGeneratorEnvelope
6ControlPanelOutlineDrawing
7TypicalRemoteLightSensorOutline(Deleted)
8-1FormFactor"A"Display
8-2FormFactor"B"Display
8-3FormFactor"C"DUEnvelope
8-4FormFactor"D"DUEnvelope
8-5FormFactor"E"DUEnvelope
9TypicalEFIInterfaceDiagram
10EnvironmentalTestCategories
11ElectronicFlightInstrumentInterfacewith
theFlightManagementComputer
12ElectronicFlightInstrumentInterfacewith
theFlightWarningComputer
13ElectronicFlightInstrumentInterfacewith
theWeatherRadar
14-1MaintenanceMonitorDigitalOutputs
14-2MaintenanceMonitor
APPENDIX
1BibliographyoftheAEECARINC725Electronic
FlightInstrumentProject(EFI) Abstract
Describes the features of a color EFI system for installation in commercial transport aircraft. The EFI provides display functions that include Attitude Director Indicator (ADI), Horizontal Situation Indicator (HSI), Air Data, Map display, Weather display, Radio Altitude data, Flight Control Mode annunciation, Flight Path information, and Flight Warning display.
