Understand RTCA DO-160 environmental qualification testing for airborne equipment, including temperature, altitude, vibration, shock, humidity, water ingress and electromagnetic compatibility requirements
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RTCA DO-160, Environmental Conditions and Test Procedures for Airborne Equipment, is an industry-consensus standard used to define environmental conditions and laboratory test procedures for equipment intended for installation in aircraft.
RTCA is a standards-development organisation. It is not the FAA, EASA, UK CAA or another aviation regulator. RTCA standards become influential because aircraft manufacturers, equipment suppliers, installers, design organisations and certification authorities recognise them as established technical references.
The roots of the DO-160 framework extend back to RTCA DO-138, published in 1968 for airborne electronic, electrical and instrument equipment. The first edition of DO-160 followed in 1975. Successive revisions expanded and refined the environmental disciplines, equipment categories, test methods and reporting expectations used within modern aerospace qualification programmes.
| Item | Information |
|---|---|
| Standard | RTCA DO-160 |
| Industry | Civil aerospace |
| Application | Airborne equipment |
| Purpose | Environmental qualification |
| Common tests | Temperature, altitude, humidity, vibration, shock, water, fluids, electrical power and EMC |
| Primary users | Aircraft OEMs, installers, design organisations, Tier 1 suppliers, avionics manufacturers and test laboratories |
| Geographic use | Worldwide |
| European counterpart | EUROCAE ED-14 |
| Current published baseline at latest internal review | RTCA DO-160G |
| Important limitation | Qualification evidence is not automatic certification |
The purpose of DO-160 is to provide a repeatable way to assess equipment performance under defined environmental conditions. Without a common framework, each aircraft programme could require entirely unique test methods, terminology and laboratory procedures.
DO-160 supports consistency by establishing:
Common environmental disciplines.
Defined equipment categories.
Standardised laboratory methods.
Test-condition tolerances.
Equipment operating requirements.
Reporting and environmental qualification identification.
A shared technical language between manufacturers, installers, laboratories and certification teams.
The categories are not a simple scale from weak to strong. The correct category depends on the equipment’s intended aircraft, installation zone, mounting arrangement, operating state and environmental exposure.
Selecting the most severe category is not automatically conservative or technically correct. It can result in irrelevant testing, unnecessary failures, avoidable redesign and evidence that does not properly represent the installation.
RTCA DO-160 is not an aircraft certification regulation. It provides environmental qualification methods that may be used to generate evidence supporting compliance activity.
The evidence chain normally includes several distinct layers:
| Layer | Primary function |
|---|---|
| Airworthiness requirement | Defines what must be demonstrated |
| Applicable TSO, ETSO or certification basis | Identifies the regulatory or approval route |
| RTCA DO-160 | Provides environmental categories and test procedures |
| Qualification or certification plan | Defines the proposed means of compliance |
| Environmental Qualification Form | Records the applicable sections and categories |
| Qualification test procedure | Controls the article, setup, method and acceptance criteria |
| Test report | Records the conditions achieved, observations and results |
| Installation assessment | Confirms relevance to the intended aircraft installation |
| Authorised compliance finding | Determines regulatory acceptance |
Passing a DO-160 test does not automatically prove that equipment is suitable for every aircraft installation. It does not establish unlimited service life. It does not replace configuration control, conformity, installation assessment or an authorised compliance finding.
FAA AC 21-16G explains how environmental qualification evidence generated using DO-160 revisions D, E, F and G may support compliance with certain airworthiness requirements. The Advisory Circular is not itself a regulation and describes an acceptable means, but not the only means, of compliance.
Airborne equipment can include electronic, electrical, electromechanical and mechanical products installed within or on an aircraft. Examples include:
Avionics computers.
Flight-control equipment.
Power-conversion equipment.
Displays and instruments.
Sensors and monitoring systems.
Communications equipment.
Cabin systems.
Electrical distribution equipment.
Pumps, valves and actuators.
Battery systems and associated electronics.
Externally mounted equipment.
Equipment installed near engines, rotors or propellers.
Qualification must remain connected to the controlled equipment configuration. Changes to hardware, enclosure design, mass, stiffness, mounting, connectors, wiring, software-controlled operating modes, thermal dissipation or electrical architecture may affect whether previous evidence remains applicable.
DO-160 testing is intended to demonstrate equipment performance under declared environmental conditions. It is not intended to reproduce every second of an aircraft’s operational life.
A credible programme connects:
The intended aircraft environment.
The equipment function and criticality.
The installation location.
The applicable sections and categories.
The controlled equipment configuration.
The test setup and mounting arrangement.
Functional operation and monitoring.
Acceptance criteria.
Recorded evidence and deviations.
Technical and regulatory acceptance.
The test laboratory applies the agreed method and records objective evidence. The equipment manufacturer, installer, design organisation and responsible certification personnel retain their respective responsibilities for environmental definition, category selection, conformity, compliance and installation approval.
DO-160 is widely used across international civil aerospace programmes. EUROCAE ED-14 is its closely aligned European counterpart. RTCA and EUROCAE coordinate the development of the environmental conditions and test procedures.
Regulatory use still depends on the applicable programme. The controlling revision may be specified through an FAA TSO, EASA ETSO, customer requirement, aircraft certification plan, contract or approved deviation.
Aircraft equipment may encounter conditions significantly different from those experienced in a normal laboratory or office environment. Qualification can reveal weaknesses associated with:
Low atmospheric pressure.
Extreme or changing temperatures.
Condensation and humidity.
Aircraft vibration.
Operational and emergency shock.
Water and fluid exposure.
Corrosion.
Electrical power disturbances.
Electromagnetic interference.
Lightning-induced transients.
Icing.
Fire and flammability.
Qualification converts assumptions into controlled evidence. It does not guarantee that failure is impossible. It demonstrates performance against the specified conditions and acceptance criteria.
Engineers do not purchase a standard merely to possess it. They use it to solve qualification and evidence problems.
DO-160 provides a recognised route for assessing whether equipment can perform under environmental conditions associated with its intended aircraft installation.
Test results may form part of a wider evidence package supporting certification, TSO, ETSO, type-certificate, supplemental type-certificate or customer approval activity.
Early category and installation review can expose gaps before formal testing begins. This can reduce invalid setups, unsuitable fixtures, missed operating modes and late programme retesting.
Development testing can identify weak connectors, inadequate supports, unsuitable materials, thermal limitations, sealing problems and electromagnetic vulnerabilities before qualification hardware is committed.
Failures observed under controlled exposure can support root-cause investigation and targeted design improvement. Qualification should not be confused with a complete reliability or service-life demonstration.
Independent, traceable testing gives customers evidence that agreed requirements were assessed using controlled equipment, documented methods and defined acceptance criteria.
DO-160 provides methods. Regulations define the compliance objective. The approved programme determines how the resulting evidence will be used
Purpose: Assess equipment performance and survival under high and low temperatures, reduced pressure, decompression and overpressure conditions where applicable.
What is evaluated: Ground survival, short-time operation, normal operation, altitude performance, cooling loss and pressure-related behaviour.
Typical failure modes:
Thermal shutdown.
Component drift.
Seal leakage.
Insulation breakdown.
Overheating.
Arcing at reduced pressure.
Enclosure deformation.
Failure during decompression.
Industry applications: Avionics, sensors, power electronics, displays, battery equipment and systems installed in pressurised or unpressurised locations.
Related testing services: Temperature testing, altitude testing, climatic testing and functional monitoring.
Purpose: Assess the effect of temperature change on equipment and materials.
What is evaluated: Differential expansion, contraction, sealing, joints, connectors, soldered interfaces and functional performance during or after changing temperatures.
Typical failure modes: Cracking, delamination, seal movement, connector loosening, condensation-related faults and intermittent electrical operation.
Industry applications: Electronics, enclosures, sensors, optical equipment and assemblies containing dissimilar materials.
Related testing services: Thermal cycling, temperature variation and combined climatic testing.
Combining Sections 4 and 5 may reduce test time. It can also complicate failure attribution and qualification credit if an anomaly occurs. The decision should be made during test planning, not improvised during testing.
Purpose: Assess resistance to warm, humid and condensation-related environments.
What is evaluated: Moisture absorption, condensation, corrosion, leakage paths, insulation performance and post-exposure functionality.
Typical failure modes: Electrical leakage, short circuits, connector corrosion, coating degradation, fogging, swelling and intermittent operation.
Industry applications: Avionics, connectors, harnesses, enclosures, sensors and cabin or externally exposed equipment.
Related testing services: Humidity testing, temperature-humidity cycling and post-exposure functional assessment.
Purpose: Assess equipment behaviour under operational shock and emergency landing or crash-safety loads.
What is evaluated: Functional performance, structural integrity, mounting security and the risk of equipment becoming detached.
Typical failure modes: Broken mounts, fastener movement, connector separation, internal component damage, permanent deformation and loss of function.
Industry applications: Equipment racks, avionics, cabin equipment, displays, power systems and structural attachments.
Related testing services: Mechanical shock testing, crash-safety loading, drop testing and fixture engineering.
Purpose: Determine whether installed equipment can perform as intended and maintain structural integrity under aircraft vibration.
Section 8 is one of the most installation-sensitive parts of DO-160. The applicable aircraft type, zone, category, mounting and vibration environment must be understood before a test profile is selected.
What is evaluated:
Equipment function during vibration.
Structural endurance.
Resonant behaviour.
Mounting integrity.
Connector and wiring stability.
Changes in critical or resonant frequencies.
Performance before, during and after exposure.
Fixed-wing vibration environments can be influenced by engines, propellers, aerodynamic loading, local structure, equipment location and mounting stiffness. A fuselage-mounted avionics unit may experience a different environment from equipment installed near an engine, propeller or tail structure.
Rotorcraft environments contain strong periodic components associated with rotor speed, blade passage, transmission systems, shafting and local structural response. A generic fixed-wing profile should not be assumed to represent a helicopter installation.
Jet and turbofan installations can introduce broadband vibration and engine-related disturbance frequencies. Equipment mounted directly on or near the powerplant may require different consideration from equipment installed within a protected equipment bay.
Random vibration uses a power spectral density profile across a defined frequency range. It is used where the environment contains broadband energy rather than one dominant sinusoidal frequency.
A random vibration test requires control of frequency range, spectral shape, overall level, duration, axis, fixture response, control strategy, authorised notching or limiting, functional monitoring, aborts and acceptance criteria.
Sinusoidal testing may represent dominant periodic inputs. Sine-on-random testing combines discrete tonal components with a broadband random environment where both are relevant.
A defensible vibration programme should define:
Aircraft type and installation zone.
Applicable category.
Equipment mass and centre of gravity.
Mounting interfaces and fastener conditions.
Fixture design and dynamic suitability.
Test axes.
Control and response accelerometers.
Functional modes and monitoring.
Pre-test resonance investigation.
Performance and endurance exposure.
Post-test inspection and functional checks.
Reportable resonance changes and deviations.
Typical failure modes: Cracked circuit boards, fretting connectors, loose fasteners, broken brackets, wire fatigue, relay chatter, intermittent electrical faults, seal degradation, resonance amplification and fixture-induced overtest or undertest.
Industry applications: Avionics, power electronics, displays, sensors, equipment racks, battery systems, pumps, valves and flight-control equipment.
Related testing services: Sine vibration, random vibration, sine-on-random testing, resonance surveys, mechanical shock and fixture design.
DO-357 provides user guidance supporting DO-160G. It includes rationale and practical guidance but does not contain requirements.
Purpose: Assess whether equipment can cause ignition within specified explosive atmospheres or withstand an internal explosion without propagating it, depending on the applicable category.
Typical failure modes: Hot-surface ignition, electrical arcing, enclosure leakage and flame propagation.
Industry applications: Equipment installed near fuel systems, fuel vapours or other potentially flammable atmospheres.
Related services: Specialist explosive-atmosphere testing. Do not claim in-house capability without a reviewed route.
Purpose: Assess equipment resistance to relevant water exposure.
What is evaluated: Dripping water, spray, rain, continuous exposure and ingress-related functionality, depending on the selected category.
Typical failure modes: Water ingress, short circuits, corrosion, seal leakage and optical fogging.
Related services: Rain testing, water-ingress testing and enclosure assessment.
Purpose: Assess whether airborne equipment is adversely affected by specified fluids that may be encountered during operation or maintenance.
What is evaluated: Material compatibility, coatings, seals, labels, connectors, electrical performance and post-exposure function.
Typical failure modes: Swelling, softening, cracking, coating loss, corrosion, leakage and electrical degradation.
Industry applications: Equipment exposed to fuel, hydraulic fluid, lubricants, cleaners, de-icing fluids and other installation-relevant contaminants.
Related services: Fluid susceptibility testing, material compatibility assessment and post-exposure functional testing.
The exact fluid, grade, exposure route, temperature, duration, recovery, cleaning method and acceptance criteria must be controlled. Testing every listed fluid is not automatically required.
Assesses the magnetic effect of equipment and its potential influence on aircraft magnetic instruments. This is not general EMC testing and should not be claimed as an in-house service without confirmation.
Assesses equipment performance when exposed to specified aircraft electrical power characteristics, variations, interruptions and abnormal conditions. The applicable power architecture and category must be confirmed from the installation.
| Section | Subject |
|---|---|
| 17 | Voltage spike |
| 18 | Audio-frequency conducted susceptibility on power inputs |
| 19 | Induced signal susceptibility |
| 20 | Radio-frequency susceptibility, radiated and conducted |
| 21 | Emission of radio-frequency energy |
| 22 | Lightning-induced transient susceptibility |
These sections require specialist electrical or EMC facilities, controlled cable configurations, grounding, bonding, operating modes and susceptibility criteria. They should not be treated as interchangeable with mechanical or climatic qualification.
Where Resonate does not provide a test in-house, a reviewed partner route may be considered. Responsibility for the final evidence chain must remain clear.
Incorrect category selection can produce irrelevant evidence. The category should represent the declared aircraft installation and approved qualification strategy.
A poor fixture can change the load path, stiffness and resonance behaviour of the equipment. The laboratory setup must represent the controlled mounting interface as closely as the qualification objective requires.
Engineers may focus on overall acceleration while overlooking frequency content, tonal components, mounting response and local structural amplification.
Testing late leaves little room for redesign, replacement hardware, failure investigation or retest.
Fixture resonances, excessive mass, poor stiffness and inaccessible control locations can compromise test validity.
A unit that powers up after exposure may still have failed during the test. Operating modes, performance parameters, data rates and monitoring points should be agreed before testing.
Development testing explores weaknesses and may use non-production configurations. Qualification testing normally requires controlled configuration, approved procedures and traceable evidence.
A new enclosure, connector, circuit board, software mode or mounting arrangement can affect qualification applicability. Similarity must be demonstrated, not assumed.
Test-slot availability is only one schedule factor. Hardware readiness, fixtures, procedures, conformity, instrumentation, safety review and acceptance criteria can become the real critical path.
Resonate testing provides high quality fire, mechanical, and environmental test solutions and certification services across a wide range of industrial sectors. From Primes to SME’s, Resonate Testing provides a bespoke and tailored service to our clients.
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