RTCA DO-160: Environmental Testing Standard for Airborne Equipment
RTCA DO-160 is the primary environmental testing standard for airborne electrical and electronic equipment. It defines the laboratory test conditions and procedures used to verify that equipment can survive and operate correctly under the environmental stresses encountered during flight operations.
The standard is developed by the Radio Technical Commission for Aeronautics (RTCA) and is recognised by the FAA, EASA, and the Department of Defense. DO-160G is the current revision, published in 2010, and is the version most commonly specified for civil, military, and unmanned airborne platforms.
What Is RTCA DO-160?
RTCA DO-160 defines how airborne equipment must be tested rather than how it must perform. It is an environmental qualification standard, not a performance standard. Its purpose is to confirm that a piece of equipment will maintain its function and structural integrity when exposed to the mechanical, climatic, and electromagnetic conditions it will encounter throughout its operational life.
The standard applies to a wide range of equipment including avionics computers, communication and navigation systems, power distribution units, lighting controllers, NVIS-compatible lamps, and flight data sensors.
DO-160 testing is a prerequisite for airworthiness approval on most civil and military aircraft programmes. For defence equipment installed on dual-use or airborne platforms, compliance with RTCA DO-160 is often required alongside MIL-STD-810 for ground and airborne environmental testing and MIL-STD-461 for electromagnetic compatibility.
RTCA DO-160 Testing: Key Test Sections
RTCA DO-160 environmental testing is divided into sections, each covering a specific environmental stress. Equipment is tested against the sections relevant to its installed location and operational environment.
| Section | Test Type | Purpose |
|---|---|---|
| Section 4 | Temperature and Altitude | Simulates temperature extremes and reduced pressure at altitude |
| Section 5 | Temperature Variation | Rapid thermal cycling between hot and cold extremes |
| Section 6 | Humidity | Exposure to high humidity and condensation |
| Section 7 | Operational Shock and Crash Safety | Verifies structural and mechanical durability under impact |
| Section 8 | Vibration | Confirms function under continuous vibration and turbulence |
| Section 9 | Explosive Atmosphere | Tests safety in fuel vapour environments |
| Section 10 | Waterproofness | Evaluates protection against rain and water spray |
| Section 20 | Radio Frequency Susceptibility | Confirms EMC compliance under strong RF fields |
| Section 21 | Emission of Radio Frequency Energy | Measures RF emissions from the equipment itself |
| Section 22 | Lightning Induced Transient Susceptibility | Simulates lightning strikes and induced electrical surges |
| Section 25 | Electrostatic Discharge | Tests resilience to static discharge events |
Each section assigns severity category levels based on the equipment’s installed location on the aircraft. A cockpit-mounted display faces different temperature and vibration profiles than an externally mounted antenna or an unpressurised avionics bay component.
RTCA DO-160 Category Levels
The standard uses installation categories to define how severe the test conditions must be for each piece of equipment.
| Category | Location | Environmental Exposure |
|---|---|---|
| Category A | Protected cabin interior | Lowest severity, controlled temperature and humidity |
| Category B | Unpressurised area inside the fuselage | Moderate severity, wider temperature range |
| Category C | External installation | Highest severity, full environmental exposure |
Correctly identifying the installation category is a critical step in test planning. Equipment tested to a lower category than its actual installation environment may fail in service even if it passed its qualification testing.
RTCA DO-160 and Aviation Lighting
For manufacturers and suppliers of aerospace lighting and tactical avionics, RTCA DO-160 testing covers the specific stresses that airborne lighting systems must survive.
Temperature and vibration testing confirms that cockpit lighting, instrument panel lamps, and external lights maintain function across the thermal and vibration profiles of the aircraft’s operating envelope.
Waterproofness and humidity testing verifies sealing integrity for connectors, housings, and lens assemblies exposed to condensation, rain, or humidity ingress.
Section 22 lightning testing confirms that lighting control circuits and LED drivers can withstand the transient voltages induced by nearby lightning strikes without damage or malfunction.
Electrostatic discharge testing prevents premature LED or driver circuit failure caused by static discharge during maintenance or in dry operating environments.
DO-160 compliance supports airworthiness certification and demonstrates compatibility with broader avionics integration programmes. For procurement and programme teams, it is frequently a precondition for inclusion in aircraft modernisation, UAV, and defence retrofit programmes.
Our LED flight deck lights and aircraft safety signs comparator are designed with airborne environmental requirements in mind. For broader aviation lighting, explore our aviation product range.
Need Aviation-Grade Lighting That Meets DO-160 Requirements?
Betalight Tactical supplies lighting solutions for aviation, defence, and tactical applications. Contact our team for specification advice on DO-160 compliant lighting for your platform.
Frequently Asked Questions
It identifies the revision level. Version G is the seventh major revision of the standard, which superseded earlier versions A through F.
It depends on the platform. Many military aircraft reference DO-160G for environmental qualification, while ground vehicles rely on MIL-STD-810.
Section 22 covers lightning induced transient susceptibility. It tests whether equipment can withstand the electrical transients induced in aircraft wiring by a nearby lightning strike.
This is a critical test for any electronic system installed on an aircraft, as lightning-induced surges are one of the most severe electrical events an airborne system will encounter.