DO-160G (Environmental Conditions & Test Procedures)

The standard that defines environmental test conditions and procedures for airborne equipment. DO-160G specifies the environmental tests that equipment must pass to demonstrate it can function correctly in the aircraft environment, including tests for temperature (altitude, temperature variation, thermal shock), vibration (random, sinusoidal), humidity, shock, power input (normal and abnormal power conditions), voltage spike, audio frequency conducted susceptibility, induced signal susceptibility, radio frequency susceptibility (radiated and conducted), radio frequency emission, lightning (direct and indirect effects), icing, fluid susceptibility, sand and dust, fungus, salt spray, magnetic effect, fire/flammability, and waterproofness.

The standard defining environmental test conditions and procedures for airborne equipment, jointly published by RTCA (as DO-160, currently revision G) and EUROCAE (as ED-14, currently revision G). DO-160 specifies test categories and procedures for temperature, altitude, humidity, vibration, shock, power input, lightning, EMI/EMC, and other environmental conditions that airborne equipment must withstand. It is universally referenced in FAA TSOs, EASA ETSOs, and type certification programs as the environmental qualification standard for avionics and airborne equipment.

The EUROCAE publication of the environmental test standard that is technically identical to RTCA DO-160G. ED-14G defines the same environmental test conditions, procedures, and categories as DO-160G. It is referenced in EASA certification specifications, ETSOs, and certification programs as the accepted environmental qualification standard for airborne equipment.

The process of demonstrating, through analysis and testing, that airborne equipment performs its intended function within its specified performance envelope when subjected to the environmental conditions defined by its installation location on the aircraft. Environmental qualification encompasses both the test program and the supporting analysis that together establish equipment suitability for the intended operating environment.

Testing performed to demonstrate compliance with applicable airworthiness regulations and technical standards, the results of which are submitted to the certification authority as part of the type certificate, supplemental type certificate, or technical standard order authorization data package. Certification testing may include functional testing, performance testing, environmental testing, and safety-related testing.

The classification system defined in DO-160/ED-14 that assigns severity levels to environmental tests based on the equipment's installation location, intended use, and operational environment on the aircraft. Categories are designated by alphanumeric codes (e.g., A1, A2, B1, B2) within each test section, with each category specifying a set of test conditions and limits.

The specific test severity parameters (e.g., temperature extremes, vibration amplitudes, voltage limits) associated with each environmental test category in DO-160. Qualification levels define the exact conditions under which the equipment must operate or survive, and they vary based on the equipment's installation zone and the aircraft type (fixed-wing, rotorcraft, etc.).

DO-160 Sections 4 (Temperature and Altitude) and 5 (Temperature Variation) define tests that subject equipment to the extremes of temperature and altitude expected during aircraft operation. Section 4 tests include short-term and steady-state exposure at temperature extremes combined with altitude, ground survival temperature exposure, and (for unpressurized installations) decompression. Section 5 tests assess the equipment's ability to withstand rapid temperature changes.

DO-160 Section 8 defines vibration tests that subject equipment to sinusoidal or random vibration profiles representative of the vibration environment at the equipment's installation location on the aircraft. Test profiles vary by aircraft type (fixed-wing jet, propeller, helicopter) and installation location (instrument panel, rack-mounted, engine-mounted, etc.).

DO-160 Section 7 (Operational Shocks and Crash Safety) defines tests that subject equipment to mechanical shock pulses representative of operational events (e.g., hard landings, turbulence) and, where applicable, crash safety conditions. Operational shock tests verify continued function after shock; crash safety tests verify that equipment does not detach or become a hazard to occupants during a survivable crash.

DO-160 Section 10 (Waterproofness) defines tests that evaluate the equipment's resistance to water ingress. Test methods include water spray, water drip, condensation, and immersion, depending on the applicable category and the equipment's installation exposure to moisture.

DO-160 Section 11 (Fluids Susceptibility) defines tests that evaluate the equipment's resistance to degradation when exposed to operational fluids commonly encountered in the aircraft environment, including hydraulic fluid, jet fuel, lubricating oil, de-icing fluid, cleaning agents, and other fluids applicable to the installation.

DO-160 Section 12 (Sand and Dust) defines tests that evaluate the equipment's resistance to the ingress and abrasive effects of fine sand and dust particles. Testing verifies that the equipment maintains its function and that moving parts, seals, and filters are not adversely affected by particle exposure.

DO-160 Section 13 (Fungus Resistance) defines tests that evaluate whether the materials and components of the equipment support fungal growth that could degrade performance or safety. Equipment is exposed to fungal spore cultures under conditions favorable to growth (high humidity and temperature) and evaluated for evidence of fungal colonization.

DO-160 Section 14 (Salt Fog) defines tests that evaluate the equipment's resistance to corrosion and functional degradation when exposed to a salt-laden atmosphere representative of marine or coastal operating environments. The equipment is subjected to a fine salt spray mist for a specified duration, followed by a drying period and functional evaluation.

DO-160 Section 16 (Power Input) defines tests that evaluate equipment behavior under the range of power supply conditions encountered on the aircraft electrical bus, including normal voltage range, abnormal voltage conditions (overvoltage, undervoltage), power interruptions, voltage transients, and frequency variations (for AC equipment). The equipment must operate correctly within the normal power envelope and must not be damaged by abnormal power conditions.

Transient voltage disturbances on the aircraft power bus that arise from load switching, relay operation, generator faults, or lightning-induced coupling. DO-160 Section 17 (Voltage Spike) defines test waveforms and amplitudes that equipment must withstand without damage or unacceptable functional upset.

The characteristics of the electrical power supplied by the aircraft generating system and distributed through the power bus, including voltage regulation, frequency stability (AC systems), waveform distortion, and harmonic content. DO-160 Section 16 defines the expected power quality envelope that equipment must tolerate, while equipment design must also ensure it does not degrade power quality for other loads on the bus.

Electromagnetic energy generated by the equipment that is conducted back onto the aircraft wiring (power lines, signal lines) and may cause interference with other equipment connected to the same wiring. DO-160 Section 21 (Emission of Radio Frequency Energy) defines conducted emission limits measured on power input lines using a Line Impedance Stabilization Network (LISN).

Electromagnetic energy radiated into free space by the equipment or its associated wiring that may cause interference with aircraft radio systems or other electronic equipment. DO-160 Section 21 defines radiated emission limits measured at a specified distance from the equipment under test, covering the frequency range from 2 MHz to 6 GHz.

The ability of equipment to operate correctly in the presence of electromagnetic interference from external sources, including RF fields from aircraft radios, portable electronic devices, radar, and other installed equipment. DO-160 Sections 18 (Audio Frequency Conducted Susceptibility), 19 (Induced Signal Susceptibility), 20 (Radio Frequency Susceptibility — Conducted), and 20 (Radio Frequency Susceptibility — Radiated) define susceptibility test methods and severity levels.

Interconnected design practices that form the foundation of electromagnetic compatibility (EMC) in aircraft installations. Shielding uses conductive enclosures and cable shields to contain or exclude electromagnetic fields. Grounding provides a low-impedance return path for electrical currents and a reference potential. Bonding provides low-impedance electrical connections between metallic structural elements, equipment chassis, and cable shields to equalize potentials and facilitate current flow for EMC, lightning protection, and static charge dissipation.

The physical damage caused by lightning attachment to the aircraft structure, including burning, blasting, bending, and pitting at the attachment and exit points, as well as resistive heating and magnetic force effects along the current flow path. Direct effects are addressed through structural design, material selection, and the provision of adequate current-carrying paths that prevent catastrophic structural failure or fuel ignition.

The transient voltages and currents induced in aircraft wiring and equipment by the electromagnetic fields and resistive voltage drops produced when lightning current flows through the aircraft structure. Indirect effects can cause upset, damage, or erroneous operation of avionics and electrical systems. DO-160 Section 22 defines equipment-level tests for lightning indirect effects (pin injection testing and cable bundle testing).

The high-level radio frequency electromagnetic environment produced by ground-based and shipboard radar, broadcast transmitters, satellite communication stations, and other high-power RF sources that can illuminate aircraft during flight or ground operations. The HIRF environment can induce currents in aircraft wiring sufficient to cause upset or damage to avionics equipment. Regulatory requirements for HIRF protection are defined in 14 CFR 25.1317 (FAA) and CS-25.1317 (EASA).

A rapid transfer of electrostatic charge between bodies at different electrical potentials, caused by direct contact or a strong electrostatic field. In the aircraft context, ESD events can be generated by flight crew or maintenance personnel interacting with equipment and can cause upset, latch-up, or permanent damage to electronic circuits. DO-160 Section 25 defines ESD test methods and severity levels for airborne equipment.

The formal document recording the results of environmental qualification testing, including test configuration, test conditions, measured data, pass/fail determinations, and any anomalies or deviations. The QTR provides the certification authority with evidence that the equipment meets its environmental qualification requirements as defined in the Equipment Qualification Test Plan.