Table of Contents
1.0INTRODUCTION
1.1Purpose
1.2SystemDescription
1.2.1SystemArchitecture
1.2.2SystemsConfiguration
1.2.2.1SingleSystem
1.2.2.1.1SingleSystem/DedicatedDisplay/
ControlUnit
1.2.2.1.2SingleSystem/Multi-FunctionDisplay
System(MFDS)
1.2.2.2DualSystem
1.2.2.2.1DualSystem/DedicatedDisplay/Control
Unit
1.2.2.2.2DualSystem/Multi-FunctionDisplay
System
1.2.3UnitDescription
1.2.3.1WeightandBalanceComputer(WBC)
1.2.3.2CalibrationMemoryModule(CMM)
1.2.3.3DedicatedDisplay/ControlUnit(DDCU)
1.2.3.4LoadSensors(LS)
1.2.3.5LoadSensorMounting(LSM)
1.2.3.6PitchAttitudeSensor(PAS)
1.3Interchangeability
1.4RegulatoryApproval
1.5Reliability
2.0INTERCHANGEABILITYSTANDARDS
2.1Introduction
2.2FormFactors,ConnectorsandIndex
PinCoding
2.2.1WeightandBalanceComputer(WBC)
2.2.2DedicatedDisplay/ControlUnit(DDCU)
2.2.3CalibrationMemoryModule(CMM)
2.2.4PitchAttitudeSensor(PAS)
2.2.5LoadSensor(LS)
2.2.6LoadSensorMounting(LSM)
2.2.7AircraftIdentification(A/C-ID)
2.2.8Interwiring
2.2.9PowerCircuitry--PrimaryA/CPowerInput
2.2.10Weights
2.2.11Cooling
2.2.12EnvironmentalConditions
3.0SYSTEMDESIGNANDPERFORMANCEREQUIREMENTS
3.1General
3.2Operation/Function
3.3GeneralSystemHardwareLayout
3.4CLASSISystem
3.4.1Sensors
3.4.2Computer
3.4.3CalibrationMemoryModule
3.4.4Accuracy
3.5CLASSIISystem
3.5.1Sensors
3.5.2Computer
3.5.3CalibrationMemoryModule
3.5.4Accuracy
3.6SystemLayout
3.6.1LoadSensors(LS)
3.6.1.1StandardSensorRequirements
3.6.1.2EnvironmentalConditions
3.6.1.3Interchangeability
3.6.1.4Self-Test
3.6.1.5MechanicalPerformanceoftheSensors
3.6.1.5.1Measurement
3.6.1.5.2ExternalInfluences
3.6.2Computer
3.6.2.1ComputerRequirementsandFunction
3.6.2.2Interchangeability
3.6.2.3Self-Test
3.6.3CalibrationMemoryModule(CMM)
3.6.3.1StandardRequirements
3.6.3.2Self-Test
3.6.4PitchAttitudeSensor(PAS)
3.6.5DedicatedDisplay/ControlUnit(DDCU)
3.6.5.1FunctionandStandardRequirements
3.6.5.2DataTransfer
3.6.5.3Self-Test
3.6.6CalibrationRemoteControlUnit(CRCU)
3.6.6.1FunctionandStandardRequirements
3.6.7LoadSensorandMountingAssembly
3.6.7.1GeneralDesignObjectives
3.6.8ElectricalPerformance
3.6.9Inputs-Outputs
3.6.9.1GeneralCharacteristicsforDiscrete
Signals
3.6.9.2DiscreteOutputs
3.6.9.3DiscreteInputs
3.6.9.4ARINC429Outputs
3.6.9.5ARINC429Inputs
3.6.9.6AnalogInputs
3.7MaintenanceandFaultIsolation
3.7.1FaultMonitoring
3.7.1.1FirstFailureDetection
3.7.1.2MonitorFunction
3.7.1.2.1CentralProcessorUnit
3.7.1.2.2ComputerMemoryandCMM
3.7.1.2.3Input/Output
3.7.1.2.4ElectricalPower
3.7.1.2.5Sensors
3.7.2MaintenanceFunction
3.7.2.1MaintainabilityofSensorsandMountings
3.7.3Self-Test
3.7.4CalibrationSchedule
3.7.5AutomaticIn-FlightRecalibration
ATTACHMENTS
1BlockDiagramofTypicalConfiguration
(SingleSystem)
2BlockDiagramofTypicalConfiguration
(DualSystem)
3DedicatedDisplayandControlUnit
Envelope
4CalibrationMemoryModuleEnvelopeand
Footprint
5PitchAttitudeSensorEnvelopeand
Footprint
6SensorAttachmentDimensionsforLug
Installation
7NotesApplicabletoStandardInterwiring
8WBComponentLocation
9SystemInterwiring(SingleSystem)
10WBC-InterfacetoNLG-Sensors
(SingleSystem)
11WBC-InterfacetoMLG(SingleSystem)
12SystemInterwiring(DualSystem)
13WBCInterfacetoNLGSensors
(DualSystem)
14WBCInterfacetoMLGSensors
(DualSystem)
15EnvironmentalTestCategories
16ARINC429ParameterList Abstract
Describes a system of sensors and monitoring equipment to determine aircraft weight while it is on the ground. The system serves as an aid to the pilot for determining aircraft weight distribution and center of gravity (CG).
