RTCA DO-254 / EUROCAE ED-80 — Design Assurance Guidance for Airborne Electronic Hardware
DO-254Section 07: The Big Standards Map
Definition
The primary guidance document for design assurance of airborne electronic hardware, including complex programmable hardware devices such as FPGAs, ASICs, PLDs, and complex COTS components. DO-254 defines a hardware design lifecycle similar in structure to DO-178C's software lifecycle, including planning, requirements capture, conceptual design, detailed design, implementation (synthesis, place-and-route), verification, configuration management, and process assurance. The objectives scale based on the hardware Design Assurance Level (DAL A through E). DO-254 applies specifically to complex electronic hardware; simple hardware items may be addressed through conventional quality assurance processes.
Where This Shows Up
As avionics increasingly implement safety-critical functions in programmable hardware (FPGAs, ASICs), DO-254 provides the framework for ensuring these devices meet certification requirements. Unlike software which is deterministic (the same input always produces the same output), hardware can experience timing-related issues, metastability, and technology-specific failure modes. DO-254 addresses these concerns through requirements-based design and verification, combined with process assurance. The EUROCAE equivalent is ED-80.
Primary Sources
The primary document defining hardware design assurance objectives and processes.
FAA Advisory Circular recognizing DO-254 as an acceptable means for airborne electronic hardware design assurance.
EASA acceptable means of compliance referencing DO-254 / ED-80 for hardware design assurance.
Across Jurisdictions
AC 20-152A
FAA recognizes DO-254 for design assurance of complex airborne electronic hardware. Applicability is based on hardware complexity and DAL.
Related Terms
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