Residual Fatigue Properties of a 2024-T351 Aluminium Alloy from the Teardown of AIRBUS A320 Wing Panels after Service

Fabien Billy; Gilbert Hénaff; Guillaume Benoit; Sjoerd van der Veen

doi:10.4028/www.scientific.net/AMR.891-892.621

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HomeAdvanced Materials ResearchAdvanced Materials Research Vols. 891-892Residual Fatigue Properties of a 2024-T351...

Residual Fatigue Properties of a 2024-T351 Aluminium Alloy from the Teardown of AIRBUS A320 Wing Panels after Service

Abstract:

This paper reports on investigations on the residual fatigue resistance of a 2024 aluminium alloy of an A320 aircraft at the end of life. The fatigue data (S-N and da/dN curves) are compared with data obtained on a pristine alloy using a similar procedure. The results are analysed on the basis of fracture surfaces observations and of AFGROW fatigue life computations.

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Periodical:

Advanced Materials Research (Volumes 891-892)

Pages:

621-626

DOI:

https://doi.org/10.4028/www.scientific.net/AMR.891-892.621

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Online since:

March 2014

Authors:

Fabien Billy, Gilbert Hénaff*, Guillaume Benoit, Sjoerd van der Veen

Keywords:

Ageing Aircraft, Fatigue Crack Initiation, Fatigue Crack Propagation, Fractography

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