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The DO-160 standard was first published on January 25, 1980 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 F. The tests in RTCA/DO-160 provide a laboratory means of demonstrating the performance characteristics of airborne equipment in environmental conditions that may be encountered in operation of the equipment in aircraft. It is not the intent of RTCA/DO-160 to be used as a measure of service life of the airborne equipment subjected to these tests.
This document outlines a set of minimal standard environmental test conditions (categories) and corresponding test procedures for airborne equipment. 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:
| Name | Description |
|---|---|
| Standard conditions | |
| Temperature | This checks the effects of temperature on the system. Condensation also can be a factor coming from cold temperatures. |
| Altitude | These 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. |
| Temperature variation | |
| Humidity | These tests under humidity check the effects of water dripping / splashing on the unit (corrosion). |
| Shock & Crash safety | This 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. |
| Vibration | Aircraft type dependent test checks the effects of vibration. |
| Explosion proof | |
| Water proof | |
| Fluids susceptibility | Aviation related fluids susceptibility |
| Sand & Dust | |
| Fungus resist | This checks the materials for decomposition in warm moist climates. |
| Salt & Fog | |
| Magnetic effect | This ensures that the aircraft's compass is not affected. |
| power input | Input 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. |
| Voltage spike | |
| Audio Frequency Conducted Susceptibility | |
| Induced Signal Susceptibility | |
| RF emission and susceptibility | Radio frequency energy: -- radiated emissions and radiated susceptibility (HIRF) via an (Electromagnetic reverberation chamber). |
| Lightning susceptibility | Direct and indirect effects depending on mounting location; includes induced transients into the airframe/wirebundle. |
| Icing | |
| ESD | This checks for resilience vs ESD in handling and operation. |
| Flammability |
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.
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