Inspection interval optimization of aircraft landing gear component based on risk assessment using equivalent initial flaw size distribution method

The nondestructive inspection interval is highly related with both system reliability and maintenance burden. Conventional inspection interval decision criteria based on the deterministic crack propagation analysis could require too much frequent inspection or sometimes occur structural failure owing to the rapid crack propagation than expected. The stochastic crack growth analysis method was proposed to compensate for the shortcomings of the deterministic analysis. This research studied the crack growth of aircraft landing gear components based on the equivalent initial flaw size distribution algorithm, and then we assessed failure risk. The calculated risk was validated using Monte-Carlo simulation, and finally, the optimum inspection interval was proposed to satisfy the US Airforce risk management criteria.

Automated summary

The research assessed crack growth and failure risk of aircraft landing gear components using stochastic crack growth analysis method and the equivalent initial flaw size distribution algorithm, validated the calculated risk with Monte-Carlo simulation, and proposed the optimum inspection interval to satisfy US Airforce risk management criteria.