Fatigue-Based Assessments in Aircraft Structures - Designing and Retaining Aircraft Structural Integrity

摘要

The processes of fatigue substantiation of civil transport aircraft are reviewed. The requirements for safe life, fail safe and damage tolerance design are described and related to the written requirements of JAA and FAA regulators. The substantiation of fixed wing aircraft is contrasted with requirements for rotary wing aircraft, where safe life design rather than damage tolerant is still the norm. The contribution of Health and Usage Monitoring Systems (HUMS) to safety in safe life helicopter designs is assessed. Challenges to the fail-safe/damage-tolerant approach posed by ageing aircraft, and the introduction of alternative materials such as carbon fibre polymer composites are described. The actions taken by regulators, manufacturers and operators to maintain airworthiness in the face of these challenges are described.