Failure of Aircraft Wing Leading Edge Panel

ASM Failure Analysis Case Histories: Air and Spacecraft Pub Date : 2019-06-01 DOI:10.31399/asm.fach.aero.c0006421

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Abstract

Cracks were found on the wing leading edge of a test aircraft made from AZ31B magnesium alloy. Crack lengths were approximately 230 mm (9 in.) long on the left side and approximately 130 mm (5 in.) long on the right side. The cracks ran parallel to the leading edge. The 230-mm (9-in.) crack was received for examination. Visual examination of the submitted panel revealed two cracks. One crack ran through six adjacent fastener holes. Sections of the beveled edges of the holes were missing and corrosion was evident. Visual examination of the fastener holes after separation of the crack showed that the fracture faces were corroded. Optical examination of either side of the middle group of fastener holes showed that the area of suspected crack initiation had suffered excessive corrosion. Examination of the holes on the end of the crack showed fracture characteristics typical of fatigue and/or corrosion fatigue. It was concluded that crack propagation of the fracture in the wing panel occurred by a combination of corrosion and high-cycle fatigue in the end fastener holes. It was recommended that future panels be manufactured of 2024 aluminum.

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飞机机翼前缘板失效

在一架由AZ31B镁合金制成的试验飞机的机翼前缘发现了裂纹。裂缝的左侧长度约为230毫米(9英寸)，右侧长度约为130毫米(5英寸)。裂缝与前缘平行。接收230毫米(9英寸)裂缝进行检查。对提交的面板进行目视检查发现有两个裂缝。一条裂缝穿过六个相邻的紧固件孔。孔的斜角边缘部分缺失，腐蚀很明显。分离裂纹后对紧固件孔的目视检查显示，断口面已被腐蚀。对中间组扣孔两侧的光学检查表明，疑似裂纹萌生的区域受到了过度的腐蚀。对裂纹末端孔的检查显示出典型的疲劳和/或腐蚀疲劳的断裂特征。分析认为，翼板断裂裂纹扩展是端部紧固件孔腐蚀和高周疲劳共同作用的结果。建议未来的面板使用2024铝制造。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

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ASM Failure Analysis Case Histories: Air and Spacecraft

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