This report describes the development and validation of a double fail-operational digital flight control system architecture for critical pitch axis functions. Architectural tradeoffs are assessed, system simulator modifications are described, and demonstration testing results are critiqued. Assessment tools and their application are aso illustrated. Ultimately, the vital role of system simulation, tailored to digital mechanization attributes, is shown to be essential to vaildating the airworthiness of full-time critical functions such as augmented fly-by-wire systems for relaxed static stability airplanes. Keywords: Design verification; Digital flight controls; Fault tolerance; Redundancy management; Relaxed static stability; System reliability; System simulator; Validation methods. (jhd)


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