Paint Stripping of Commercial Aircraft - Evaluation of Materials and Process
This document details the technical requirements to be used in the evaluation of materials and processes developed for use in stripping organic finishes from fixed wing commercial aircraft. The requirements herein are intended to ensure that the materials and processes used are not detrimental to the commercial aircraft when used as specified. These requirements are not intended to judge performance of the stripping method.
Rationale: SAE MA4872A presents technical requirements for evaluation of materials and processes to be used for stripping of organic finishes from fixed wing commercial aircraft. This standard discusses three categories of methods for stripping organic finishes: chemical, mechanical and thermal. As technology has advanced, laser coating removal has become a more viable option for stripping of organic finishes on aircraft.
SAE MA4872A was developed to include processes involving light sources under the thermal process category which encompasses laser stripping processes. Due to the advances in laser stripping technology since this standard was initially created, it is proposed that the standard be reviewed and updated to ensure that the test methods under the thermal process category are appropriate for evaluation of a laser stripping process. It is also proposed that these test methods be reviewed for concurrence with current common test practices.
SAE MA4872A also presents wide range of composite test materials, of which all presented composite materials require testing for thermal processes. In contrast, SAE MA4872A presents a vulnerability ranking for metallic materials for testing of which only the most vulnerable metallic material requires testing. Additionally, some of the materials referenced in SAE MA4872A appear to be no longer commercially available or no longer in-service. It is proposed that referenced test materials be reviewed for relevance and currency, and that the possibility of presenting a vulnerability ranking for composite materials, similar to that presented for metallic materials, be reviewed.