Rtca Do 160g Pdf Download

  
  1. DO-160, Environmental Conditions and Test Procedures for Airborne Equipment is a standard for the environmental testing of avionics hardware. It is published by the Radio Technical Commission for Aeronautics (RTCA) and supersedes DO-138.
  2. RTCA DO-160G Section 22 Commercial aircraft Complete set of tests included In place for a long period MIL-STD-461G CS117 (new) Military aircraft and surface naval ships Complemented by other STDs like 464 Introduced in 2015, based on DO-160G RTCA → Radio Technical Commission for Aeronautics.
  1. Rtca Do 160f Pdf Download
  2. Do 160e
Environmental Conditions and Test Procedures for Airborne Equipment
StatusPublished
Year started1975
Latest versionG
December 2010
Organization
Committee
DomainAviation
Abbreviation
  • RTCA DO-160
  • EUROCAE ED-14
Websitertca.org

DO-160, Environmental Conditions and Test Procedures for Airborne Equipment is a standard for the environmental testing of avionics hardware. It is published by the Radio Technical Commission for Aeronautics (RTCA) and supersedes DO-138.

Rtca Do 160g Pdf Download

RTCA is a private, not-for-profit association founded in 1935 as the Radio Technical Commission for Aeronautics, now referred to simply as “RTCA”.

Outline of contents[edit]

Introduction[edit]

The DO-160 document was first published on February 28, 1975 to specify test conditions for the design of avionics electronic hardware in airborne systems. Since then the standard has undergone subsequent revisions up through Revision G.

Purpose[edit]

This document outlines a set of minimal standard environmental test conditions (categories) and corresponding test procedures for airborne equipment for the entire spectrum of aircraft from light general aviation aircraft and helicopters through the jumbo jets and supersonic transport categories of aircraft. The purpose of these tests is to provide a controlled (laboratory) means of assuring the performance characteristics of airborne equipment in environmental conditions similar of those which may be encountered in airborne operation of the equipment.The standard environmental test conditions and test procedures contained within the standard, may be used in conjunction with applicable equipment performance standards, as a minimum specification under environmental conditions, which can ensure an adequate degree of confidence in performance during use aboard an air vehicle.The Standard Includes Sections on:

SectionNameDescription
Standard conditions
4.0TemperatureThis checks the effects of temperature on the system. Condensation also can be a factor coming from cold temperatures.
AltitudeThese tests check the effects (in terms of performance) of altitude, including loss of cabin pressure on the device/system/equipment. Factors tested include dielectric strength, cooling under low pressure, and resilience to rapid change in air pressure. The norm defines the different temperature profiles under which the equipment must be tested. Due to the variety of aircraft, the equipment are classified in categories.
5.0Temperature VariationThese tests exercise the assemblies capability of surviving extreme temperature changes and the effects of differing coefficients of thermal expansion.
6.0HumidityThese tests under humidity check the effects of high concentrations of humidity and the articles ability to withstand moisture effects. Typically moisture sensitive devices have issues with this test and require conformal coat or other types of protection.
7.0Shock & Crash safetyThis aircraft type dependent test checks the effects of mechanical shock. Crash safety test insures the item does not become a projectile in a crash. The norm describes the test procedure for airborne equipment.
8.0VibrationAircraft type dependent test checks the effects of vibration and the equipment's ability to operate during all vibration scenarios.
9.0Explosion proofnessThese tests subject the test article to an environment under vacuum, with a gaseous mixture of combustibles. The unit must operate and be subjected to any actuation including knob turns and button pushes and not ignite the environment.
10.0Water proofnessThese tests subject the test article to various scenarios of dripping water or pooled water to verify the unit will fully operate in the given condition.
11.0Aviation related fluids susceptibility including a variety of fluids ranging from carbonated sugared beverage to various cleaners and solvents.
12.0Sand & DustThese tests subject the unit to an environment of blowing sand and dust of specific particle sizes in which the unit must operate at the end of exposures.
13.0Fungus ResistanceThis tests determine whether equipment material is adversely affected by fungi under conditions favorable for their development, namely, high humidity, warm atmosphere and presence of inorganic salts.
14.0Salt & FogThis test verifies the test articles ability to survive multiple exposures of salt fog and drying and the environment's ability to cause accelerated corrosion.
15.0Magnetic effectThis ensures that the aircraft's compass is not affected.
16.0Power inputInput power conducted emissions and susceptibility, transients, drop-outs and hold-up. The power input tests simulate conditions of aircraft power from before engine start to after landing including emergencies.
17.0Voltage spikeThis test determines whether equipment can withstand the effects of voltage spikes arriving at the equipment on its power leads, either AC or DC.
18.0Audio Frequency Conducted SusceptibilityThis test determines whether the equipment will accept frequency components of a magnitude normally expected when the equipment is installed in the A/C. These frequency components are normally harmonically related to the power source fundamental frequency.
19.0Induced Signal SusceptibilityThis test determines whether the equipment interconnect circuit configuration will accept a level of induced voltages caused by the installation environment. This section relates specifically to interfering signals related to the power frequency and its harmonics, audio frequency signals, and electrical transients that are generated by other on-board equipment or systems and coupled to sensitive circuits within the EUT through its interconnecting wiring.
20.0 and 21.0RF emission and susceptibilityRadio frequency energy: -- radiated emissions and radiated susceptibility (HIRF) via an (Electromagnetic reverberation chamber).
22.0 and 23.0Lightning susceptibilityDirect and indirect effects depending on mounting location; includes induced transients into the airframe or wire bundle.
24.0IcingThis test determine performance characteristics for equipment that must operate when exposed to icing conditions that would be encountered under conditions of rapid changes in temperature, altitude and humidity.
25.0ESDThis checks for resilience vs ESD in handling and operation.
26.0FlammabilityThis analysis and test verifies the assembly will not provide a source to fire.

The user of the standard must also decide interdependently of the standard, how much additional test margin to allow for uncertainty of test conditions and measurement in each test.

Version History[edit]

  • RTCA/DO-160, RTCA, INC., February 28, 1975
  • RTCA/DO-160 A, RTCA, INC., January 25, 1980
  • RTCA/DO-160 B, RTCA, INC., July 20, 1984
  • RTCA/DO-160 C, RTCA, INC., December 4, 1989
  • RTCA/DO-160 C, Change 1, RTCA, INC., September 27, 1990
  • RTCA/DO-160 C, Change 2, RTCA, INC., June 19, 1992
  • RTCA/DO-160 C, Change 3, RTCA, INC., May 13, 1993
  • RTCA/DO-160 D, RTCA, INC., July 29, 1997
  • RTCA/DO-160 D Change 1, RTCA, INC., December 14, 2000
  • RTCA/DO-160 D Change 2, RTCA, INC., June 12, 2001
  • RTCA/DO-160 D Change 3, RTCA, INC., December 5, 2002
  • RTCA/DO-160 E, RTCA, INC., December 9, 2004
  • RTCA/DO-160 F, RTCA, INC., December 6, 2007
  • RTCA/DO-160 G, RTCA, INC., December 8, 2010
  • RTCA/DO-160 G Change 1, RTCA, INC., December 16, 2014

Resources[edit]

  • FAR Part 23/25 §1301/§1309
  • FAR Part 27/29
  • AC 23/25.1309
  • RTCA DO-160

Bibliography[edit]

  • Aircraft Systems: Mechanical, Electrical and Avionics Subsystems Integration (Aerospace Series (PEP)) (Jun 3, 2008) by Ian Moir and Allan Seabridge
  • RTCA List of Available Documents, RTCA Inc., https://web.archive.org/web/20130512172348/http://www.rtca.org/Files/ListofAvailableDocsMarch2013.pdf (March 2013)
  • Avionics: Development and Implementation (Electrical Engineering Handbook) by Cary R. Spitzer (Hardcover - Dec 15, 2006)
  • Avionics Navigation Systems (April 1997) by Myron Kayton and Walter R. Fried
  • The European Organization for Civil Aviation Equipment EUROCAE ED-14

Certification in Europe[edit]

  • Replace FAA with EASA, JAA or CAA
  • Replace FAR with JAR
  • Replace AC with AMJ
Rtca

See also[edit]

External links[edit]

Rtca Do 160f Pdf Download

  • Video Tutorial by Aerospacepal.com

Do 160e

Retrieved from 'https://en.wikipedia.org/w/index.php?title=DO-160&oldid=955949789'