Failure analysis of plate assembly Track # 5 and Jack # 3 of an aircraft

Sujata, M and Madan, M and Bhaumik, SK (2008) Failure analysis of plate assembly Track # 5 and Jack # 3 of an aircraft. Project Report. National Aerospace Laboratories, Bangalore, India.

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Abstract

Failed plate assemblies from two aircrafts were analyzed. Fractographic study showed that in both the cases the failure was by fatigue. Evidences suggest that fatigue is stress related. It is recommended that a high strength aluminum alloy (2XXX or 7XXX series) be used instead of 6XXX series alloy for the above applications. It is also suggested that stress analysis be performed to examine the adequacy of the present structure for the applications in question.

Item Type: Proj.Doc/Technical Report (Project Report)
Uncontrolled Keywords: Helicopter;Cover plates;Fatigue;Inappropriate material selection
Subjects: AERONAUTICS > Aeronautics (General)
CHEMISTRY AND MATERIALS > Chemistry and Materials (General)
Division/Department: Materials Science Division, Materials Science Division, Materials Science Division
Depositing User: Ms. Alphones Mary
Date Deposited: 21 Jul 2011 10:49
Last Modified: 21 Jul 2011 10:49
URI: http://nal-ir.nal.res.in/id/eprint/9503

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