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The reliability of the software running in airborne vehicles (civil or military) is shown by the fact that most airborne accidents occur due to manual errors. Unfortunately reliable software is not necessarily easy to use or intuitive, poor user interface design has been a contributing cause of many aerospace accidents and deaths. [citation needed]
The DO-254/ED-80 standard is the counterpart to the well-established software standard RTCA DO-178C/EUROCAE ED-12C. With DO-254/ED-80, the certification authorities have indicated that avionics equipment contains both hardware and software, and each is critical to safe operation of aircraft .
DO-178B, Software Considerations in Airborne Systems and Equipment Certification is a guideline dealing with the safety of safety-critical software used in certain airborne systems. It was jointly developed by the safety-critical working group RTCA SC-167 of the Radio Technical Commission for Aeronautics (RTCA) and WG-12 of the European ...
As modules often share an extensive part of their hardware and lower-level software architecture, maintenance of the modules is easier than with previous specific architectures. Applications can be reconfigured on spare modules if the primary module that supports them is detected faulty during operations, increasing the overall availability of ...
The Software Level, also known as the Development Assurance Level (DAL) or Item Development Assurance Level (IDAL) as defined in ARP4754 (DO-178C only mentions IDAL as synonymous with Software Level [10]), is determined from the safety assessment process and hazard analysis by examining the effects of a failure condition in the system. The ...
ARP4754(), Aerospace Recommended Practice (ARP) Guidelines for Development of Civil Aircraft and Systems, is a published standard from SAE International, dealing with the development processes which support certification of Aircraft systems, addressing "the complete aircraft development cycle, from systems requirements through systems verification."
Aircraft that regularly operate in icing conditions have systems to detect and prevent ice forming (anti-icing) and/or remove the ice accumulation after it has formed (de-icing). This can be achieved by heating the spaces in internal structure with engine bleed air, chemical treatment, electrical heating and expansion/contraction of the skin ...
The aircraft manufacturer is usually the only source of this comprehensive flight model. The vertical profile is constructed by the FMS during pre-flight. Together with the lateral flight plan, it makes use of the aircraft's starting empty weight, fuel weight, center of gravity, and cruising altitude.