Retrogression and Re-ageing (RRA) technology is a two stage heat treatment of 7075-T6 aluminium alloy used to improve corrosion resistance while retaining MIL-HDBK-5J structural properties. This report assesses the compliance of this industrial trial with the requirements of the compliance matrices in the Stage II Design Development Plan and, by extension, the Stage II Process Specification for RRA.

This report presents an overview of a proposed S&T planning framework, encompassing Foresight Planning, designed to assist the development of S&T Plans for Royal Australian Navy (RAN) capability acquisition.

An investigation into the abnormal discolouration of oil in ADF helicopter tail rotor transmissions.

A Monte Carlo model will then be used to test if the low-kt ECS distribution can accurately predict the fatigue lives of the high-kt specimens. If successful, this will allow low-kt ECS distributions, which are easier to derive, to be used under high-kt conditions.

This report presents a hybrid method for simulating sequences of correlated Gamma random variables for modelling sea clutter, using a combination of linear and/or nonlinear transforms.

The F-111 Adhesive Bonded Repair Assessment Program (FABRAP) was created to generate statistically valid data regarding the efficacy of the tap-test as a non-destructive-inspection technique and the environmental durability of adhesive bonds. In FABRAP Phase I Testing, over 300 repairs were tap tested and 820 residual strength tests conducted using a pneumatic adhesion tensile testing instrument. This report details the FABRAP process and summarises the results from the Phase I testing.

The experiment described in this paper was conducted to test if perceptual limitations were the reason for poor performance in the DSTO AOSC Maritime Hover trial.

This report presents examples of components from ADF aircraft that exhibited surface pitting which formed during the anodising pre-treatment process. In three of the examples, fatigue cracking had initiated from the surface pits leading to failure of the components.

This report examines the research conducted on 7050-T7451 and how corrosion pitting could influence the fatigue life of components in RAAF aircraft manufactured from this alloy. The report shows that corrosion pitting causes not only a reduction in time to failure at a certain stress but also up to a 50% reduction in the fatigue threshold.

This report describes the development of a Thermal Wave Interferometry (TWI) system for the characterisation of film thickness. The system was shown to resolve variations in paint thickness of less than 1.5 μm