In the aerospace industry, each year several commercial airplanes stop its service to carry out detailed routine inspections of their structural members and systems, including the power plant. Among several maintenance services to be performed in an airplane during a check, the corrosion prevention and control program is the one of the most important service since it includes methods of inspection and tasks to prevent corrosion in all airplane structural areas, such as fuselage, wings, stabilizers, flight control surfaces etc. During routine inspections, upon discrepancy detection, some actions must be immediately taken in order to correct the problem and avoid the loss of airplane structural strength. The corrosion removal from any aircraft structural member, in general consists in blending out the damage and carry out a visual and ND inspection (e. g. remaining thickness measurement by ultrasonic test). However, all care must be taken during remaining thickness measurement since systematic and random errors can affect in the results, compromising the final quality of measured parts. The main purpose of this paper is to perform an experimental study of remaining thickness measurement in an aircraft outer wing skin after corrosion removal, objecting to determine the uncertainty sources of the usual method. Also, the study intends to determine the expanded uncertainty in order to purpose a new methodology for the metrological treatment of this process, establishing a conformity zone.


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