This document addresses issues related to assurance that COTS electronic hardware components will perform their intended function in the AEH equipment or system in which they are installed. Those issues may impact system design, reliability assessment, quality, testing, production or support; but this document is not intended to be specific to any of those disciplines.
This document is focused on the hardware issues raised in DOT/FAA/TC-16/57; it does not include issues related to software, firmware, etc.
This document is intended to fit within the development process for civil aircraft and systems. This document can be used to support design and analysis activities in RTCA DO-254/EUROCAE ED-80 and RTCA DO-297/EUROCAE ED-124, as well as SAE ARP4754.
This document addresses twelve (12) of the twenty-six (26) specific issues described in DOT/FAA/TC-16/57.
Rationale: Use of COTS electronic components is a necessity for AEH in aerospace systems; but most COTS components are not designed or intended for long-life, safety-critical, or rugged-environment applications such as AEH. This presents challenges for the design, production, support, and certification of AEH systems.
Although COTS hardware can have significant impacts on aerospace electronic impact system design, reliability assessment, quality, testing, production or support, there is no currently-agreed-upon method to assess those impacts in the certification process. This document describes an aerospace industry consensus process to do so, with respect to twelve specific COTS-related issues, as described in DOT/FAA/TC-15/57.
For each of the twelve issues, this document contains (1) a brief description of the issue, (2) aerospace industry consensus processes to assure that the issue has been addressed adequately in the system design, and (3) acceptable artifacts to verify that the issue has been addressed adequately in the system design.