ARINC 609 : 1987

1.0 INTRODUCTION AND DESCRIPTION
  1.1 Purpose of this Document
  1.2 Background
  1.3 Relationship to Other Specifications and
                    Standards
  1.4 Use of ARINC Report 609
  1.5 Definition of Terms
2.0 SYSTEM DESIGN CONSIDERATIONS FOR AIRCRAFT
                    ELECTRICAL POWER
  2.1 General
  2.2 Regulatory and Other Concerns
  2.3 Power Sources
  2.4 Power Distribution
  2.5 Built-In Test Equipment (BITE)
3.0 AIRCRAFT ELECTRICAL POWER COMPONENT DESIGN
  3.1 General
  3.2 AC Systems
  3.3 DC Systems
4.0 AIRCRAFT ELECTRICAL POWER DISTRIBUTION,
                    PROTECTION AND CONTROL CHARACTERISTICS
  4.1 General
  4.2 Special Requirements
  4.3 Distribution Considerations
  4.4 Distribution Protection Philosophy
  4.5 Control Philosophy
  4.6 Summary of Different System Considerations -
                    Specific Limits
  4.7 Requirements
5.0 AIRCRAFT ELECTRICAL POWER UTILIZING EQUIPMENT
                    DESIGN
  5.1 General
  5.2 Avionics
  5.3 Electric Motors and Electromechanical
                    Actuators
  5.4 Heaters
  5.5 Lighting
6.0 CONSIDERATIONS FOR THE ALL-ELECTRIC AIRPLANE
  6.1 Background
ATTACHMENTS
    1 115 and 230 Volt/400 Hz Limits
    2 28 VDC Transient Limits
    3 Envelope of Voltage Spikes
    4 270 VDC Limits
    5 Abnormal Transient Voltage 115 Volt/400 Hz
                    System
    6 Abnormal Transient Voltage 230 Volt/400 Hz
                    System
    7 Proposed Voltage Transient Limits for
                    C.V.V.F. AC Generators
    8 Abnormal Transient Voltage 115 Volt/Variable
                    Voltage System

Provides guidelines for designers of aircraft power system components and of power utilization components, both avionics and power converters such as motors, heaters, etc.