ARINC 571 : 70 SUPP 2

1.0 INTRODUCTION AND DESCRIPTION
  1.1 Purpose
  1.2 Functions and Modes of Operation
    1.2.1 Basic Mode of Operation
    1.2.2 Specific Functions and Outputs
  1.3 Reliability
  1.4 Unit Description
    1.4.1 Inertial Navigator
    1.4.2 Alignment Panel
    1.4.3 Remote Display Unit (Optional)
    1.4.4 Battery Unit
  1.5 Interchangeability
  1.6 Regulatory Approval
2.0 STANDARDS REQUIRED TO EFFECT INTERCHANGEABILITY
  2.1 Form Factors, Connectors, and Index Pin Coding
    2.1.1 Inertial Navigation Sensor Unit
    2.1.2 Alignment Panel
    2.1.3 Battery Unit
  2.2 Input and Output Signal Characteristics
  2.3 Standard Interwiring
  2.4 Power Circuitry
    2.4.1 AC Power Unit
      2.4.1.1 Primary Power
      2.4.1.2 Heater Power
    2.4.2 26 Volt AC Synchro Excitation
    2.4.3 Battery Supply
    2.4.4 Battery Charger
    2.4.5 Airplane Computer Bus
      2.4.5.1 Standby Computer Bus
      2.4.5.2 Optional Full-Time Computer Bus
    2.4.6 Power Control Circuitry
    2.4.7 115 Volt Heater Power Input
  2.5 Weights
  2.6 Environmental Conditions
  2.7 Inertial Sensor Mounting
    2.7.1 Sensor Unit Orientation
    2.7.2 Mounting Tolerances
  2.8 External Program Control
3.0 SYSTEM DESIGN CONSIDERATIONS
  3.1 General
    3.1.1 Range of Operation
    3.1.2 Relationship to Remote Computers
    3.1.3 Attitude Output Isolation
    3.1.4 Alignment Status
    3.1.5 Duration of Operation
    3.1.6 World-Wide Navigation
  3.2 Basic Modes of System Operation
    3.2.1 OFF (No Power Supplied)
    3.2.2 Alignment (Normal Power Supplied)
    3.2.3 Navigation
    3.2.4 ATT. REF. (Normal Power Supplied)
  3.3 Outputs
    3.3.1 Analog Outputs
    3.3.2 Digital Outputs
      3.3.2.1 Basic Output
      3.3.2.2 Secondary Two-Wire Output
      3.3.2.3 ARINC 561 BCD Type Output ("Customer Option")
      3.3.2.4 ARINC 561 Binary Type Output
  3.4 Integrity Monitoring and Failure Warning
    3.4.1 General
    3.4.2 Integrity Monitors and Failure Warning Outputs
      3.4.2.1 Master Warning
      3.4.2.2 Attitude Warning Outputs
        3.4.2.2.1 Primary Attitude Failure Warning Output (Pitch
                  and Roll)
        3.4.2.2.2 Monitor Integrity
        3.4.2.2.3 Failure Warning Delays
        3.4.2.2.4 Auxiliary Pitch and Roll Warning Output
      3.4.2.3 Heading Warning Output
      3.4.2.4 HSI Warning Output
      3.4.2.5 Digital Data Warning Output
    3.4.3 Operational Reliability During Critical Landing
                  Phase Analysis
  3.5 Inertial Sensor System Accuracy
    3.5.1 General
    3.5.2 Mark 1
    3.5.3 Mark 2
4.0 STANDARD SIGNAL CHARACTERISTICS
  4.1 General Accuracy and Operating Ranges
    4.1.1 Resolution
    4.1.2 Standardized Output Signals
      4.1.2.1 Synchro Standards
      4.1.2.2 Standard "Applied Voltage"
      4.1.2.3 "Standard Ground" Signal
      4.1.2.4 Phase Reversing Voltage Standards
  4.2 Inputs
    4.2.1 Latitude
    4.2.2 Longitude
    4.2.3 Automatic Initialization (Customer Option)
  4.3 Outputs
    4.3.1 Platform Heading and True Heading
      4.3.1.1 Analog Output
      4.3.1.2 Digital Outputs of True Heading
    4.3.2 Pitch
      4.3.2.1 General
      4.3.2.2 Output No. 1, 2 and 3
      4.3.2.3 Output No. 4 (Two-wire)
      4.3.2.4 Output No. 5 (Two-wire)
    4.3.3 Roll
      4.3.3.1 General
      4.3.3.2 Output No. 1, 2 and 3
      4.3.3.3 Output No. 4 (Two-wire)
      4.3.3.4 Output No. 5 (Two-wire)
    4.3.4 Present Position
      4.3.4.1 BCD Output
      4.3.4.2 Binary Output (Serial)
    4.3.5 N-S and E-W Velocity
    4.3.6 Vertical Acceleration
      4.3.6.1 Analog
      4.3.6.2 Digital
    4.3.7 Drift Angle (DA)
      4.3.7.1 Analog Output
      4.3.7.2 Digital Output
    4.3.8 Track Angle (See 4.3.1)
      4.3.8.1 Analog Output
      4.3.8.2 Digital Outputs
    4.3.9 Ground Speed
    4.3.10 Failure Warning Outputs
      4.3.10.1 Master Warning
      4.3.10.2 Primary Warning
      4.3.10.3 Auxiliary Warning
      4.3.10.4 Advisory Outputs
    4.3.11 Alignment Status (See Sec. 3.1.4)
    4.3.12 Platform Azimuth
    4.3.13 Integrated Vertical Acceleration (Customer
                  Option)
    4.3.14 Along Track Horizontal Acceleration (Customer
                  Option)
5.0 BASIC DIGITAL SIGNAL STANDARDS
  5.1 Basic Serial Data Transmission Standards
    5.1.1 Basic Transmission System
    5.1.2 Data Transmission Circuit
    5.1.3 Word Synchronization
    5.1.4 Clock
  5.2 Word Structure
    5.2.1 Word Structure
    5.2.2 Standard Languages (Two-wire)
      5.2.2.1. General
      5.2.2.2. BCD/BNR Indicator
      5.2.2.3 Binary Coded Decimal (BCD)
      5.2.2.4 Binary Words (BNR)
    5.2.3 Special Code Assignment for Sign and Status
                  Designation
      5.2.3.1 General
    5.2.4 Parity Checking (See Figure 1 Page 17)
  5.3 Transmission Order
  5.4 Electrical Characteristics
    5.4.1 DC Signaling with Return to Zero Logic
    5.4.2 Signal Logic Levels
  5.5
    5.5.1 Output Load Capability
    5.5.2 Electromagnetic Noise Rejection
    5.5.3 Reverse Current Capability
  5.6 Digital Receiver
    5.6.1 Input Load Characteristics
    5.6.2 Electromagnetic Noise Rejection
    5.6.3 Digital Transmission Monitoring
                  (Figure 1 and 2)
ATTACHMENTS
    1 ISS Output Usage
    2-1 ARINC 571 Standard Interwiring
    2-2 ARINC 571 Standard Interwiring
    2-2A Mode Control and Display Interwiring (Optional)
    2-2B Display Interface Wiring (Optional)
    2-3 Notes Applicable to the INAV Standard
                  Interwiring
    3-1A ISS Unit Mounting Dimensions and Tolerances
    3-1B ISS Nav Unit Dimensions and Tolerances
    3-2 Battery Unit Form Factor
    4 Synchro Outputs & Excitation
    5 ISS Platform Mount
    6 ISS Block Diagram
    7 Alignment Panel
    8 Not Used
    9 Navigational Mneomonics Defined
    10-1 ISS Digital Output Standards
    10-2 ARINC BCD Digital Word Structures
    10-3 Digital Voltage Outputs
    10-4 Output Signal Timing Tolerances
    10-5 Digital Label/Address Codes
    10-6 ARINC 575 DADS Label/Address Code Assignments
    10-7 Input and Output Circuit Standards
    10-8 BCD Code Assignments
    10-9 Typical Example of Standard Binary Data
                  Expressed Two's Complement Fractional Notation
    11 ISS/INS "Computer Bus" Power
    12 Signal Phase Reversal for Two-wire Pitch &
                  Roll Outputs

Provides basic features for inertial sensor consisting of the necessary inertial measuring devices and associated electronics specifically designed for installation in commercial transport type aircraft. Provides the basic outputs for aircraft attitude, vertical and horizontal velocity, heading, plus the outputs of drift angle, track and present position.