51-P99967A194

Technical Characteristics

• ~1

  data on certain environmental and performanc

• ~1

  (aim-54); aircraft, ( ac-130h, mc-130h, ec-130e, h

• End Item Identification

  engine, aircraft tf33-pw-102 (c-135e, ec-135h/k/p); countermeasure set an/slq-32; trainer, b-1b aircraft; test station, oq-290(v)msm; missile, tomahawk; support equipment, b-1 aircraft; support equipment, b-52 aircraft; missile, air-to-air, phoenix

• Test Data Document

  81349-mil-m-38510 specification (includes engineering type bulletins, brochures,etc., that reflect specification type data in specification format; excludes commercial catalogs, industry directories, and similar trade publications, reflecting general type

• Maximum Power Dissipation Rating

  400.0 milliwatts

• Specification/Standard Data

  81349-mil-m-38510/104 government specification

• Inclosure Configuration

  dual-in-line

• Time Rating Per Chacteristic

  75.00 nanoseconds maximum propagation delay time, low to high level output and 75.00 nanoseconds maximum propagation delay time, high to low level output

• Body Length

  0.896 inches maximum

• Design Function And Quantity

  2 receiver, line differential

• Inclosure Material

  ceramic and glass

• Terminal Surface Treatment

  solder

• Body Width

  0.220 inches minimum and 0.310 inches maximum

• Input Circuit Pattern

  dual 5 input

• Storage Temp Range

  -65.0/+150.0 deg celsius

• Terminal Type And Quantity

  16 printed circuit

• Body Height

  0.140 inches minimum and 0.185 inches maximum

• Voltage Rating And Type Per Characteristic

  -20.0 volts minimum power source and 20.0 volts maximum power source

• Special Features

  weapon system essential; design analysis

• Nuclear Hardness Critical Feature

  hardened

• Criticality Code Justification

  feat

• Case Outline Source And Designator

  d-2 mil-m-38510

• Operating Temp Range

  -55.0/+125.0 deg celsius