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Our FAA Designated Engineering Representatives (DER’s) are authorized to approve and recommend approval of Aircraft Systems and Equipment (including TSO Approvals) up to and including Design Assurance Level A for Software (DO-178B) and Airborne Electronic Hardware (DO-254).
Our DER’s were appointed by the FAA with the authority to act on their behalf during the Certification Process. Our DER’s are fully authorized to issue FAA Form 8110-3, Statement of Compliance with the Federal Aviation Regulations and to provide complete On-Site or WebEx Training.
Special Skills Required By A DO-178B / DO-254 DER
A Comprehensive familiarity with and understanding of RTCA/DO-178B, Software Considerations in Airborne Systems and Equipment Certification and DO-254, Design Assurance Guidelines for Airborne Electronic Hardware.
A solid understanding of the systems safety assessment process.
A demonstrated knowledge of the rationale for, and the significance of, each stage in the software and airborne electronic hardware development process, as well as its supporting standards, procedures, and documentation.
Experience gained from participation in a technically responsible capacity over a complete development program life cycle. This qualification may be satisfied by an aggregate over several different development programs.
Experience interacting with all phases of software and airborne electronic hardware development and testing processes, including utilization of the associated configuration and quality control procedures.
Fluency in high-level and assembly-level programming languages and familiarity with support software used in a development process. Familiarity with tools available to facilitate the development, documentation, and consistency-checking processes.
Demonstrated knowledge of the sources of software and airborne electronic hardware anomalies, the relative merits of the types of testing procedures which are available to protect against them, and the characteristics of a thorough test program.
Familiarity with the aspects of real-time avionics systems, such as the use of interrupts, multitasking, software reentrancy, etc. This includes an appreciation of the types of analysis and testing necessary to ensure the integrity of these mechanisms.
An understanding of the techniques which may be employed to reduce criticality levels, such as system architecture, multiversion programming and partitioning.
Knowledge of hardware characteristics such as input/output schemes, memory organization and multiport access communication bus protocols, and processor architecture, all of which have an impact on the software interface and the potential for the creation of anomalies.
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