loading page

Crack-like Effectiveness of Some Discontinuities in AA2024
  • Loris Molent,
  • M.R. Fox
Loris Molent
Boeing Aerostructures Australia Pty Ltd

Corresponding Author:[email protected]

Author Profile
M.R. Fox
National Transportation Safety Board Office of Research and Engineering
Author Profile


Maintaining aircraft airworthiness to ensure the fleet's safe operation and maintain its readiness is critically dependent on accurate modelling and reliable predictions of fatigue crack growth. In this process a knowledge of the representative initial discontinuity sizes that cause fatigue crack nucleation and early growth in aircraft is essential. Here the effective pre-crack size of aluminium alloy 2024, from samples of aircraft production material and tested under aircraft spectra, are considered.
20 Mar 2023Submitted to Fatigue & Fracture of Engineering Materials & Structures
20 Mar 2023Submission Checks Completed
20 Mar 2023Assigned to Editor
22 Mar 2023Reviewer(s) Assigned
30 May 2023Review(s) Completed, Editorial Evaluation Pending
31 May 2023Editorial Decision: Revise Minor
15 Jul 20231st Revision Received
15 Jul 2023Assigned to Editor
15 Jul 2023Submission Checks Completed
28 Jul 2023Reviewer(s) Assigned
14 Aug 2023Review(s) Completed, Editorial Evaluation Pending
16 Aug 2023Editorial Decision: Revise Minor
17 Aug 20232nd Revision Received
17 Aug 2023Assigned to Editor
17 Aug 2023Submission Checks Completed
21 Aug 2023Review(s) Completed, Editorial Evaluation Pending
21 Aug 2023Editorial Decision: Accept