Failure analysis of main door Assembly edge frame of an aircraft

Sujata, M and Madan, M and Bhaumik, SK (2008) Failure analysis of main door Assembly edge frame of an aircraft. Project Report. National Aerospace Laboratories, Bangalore, India.

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Abstract

During pressure testing on fuselage of an aircraft, the boss of door assembly edge frame LH top had fractured. The fractured boss was sent to the laboratory for establishing the cause of failure. Fractographic study revealed that the boss has fractured under bending overload. Examination of the mating fracture surfaces showed that the bending load acted in a direction from inside the aircraft to outside at an angle with the horizontal. Subsequent inspection of the door assembly suggests that the boss in question had experienced excessive bending load due to non-uniform load sharing by the locking pins. It appears most probable that the looseness of the pins in the assembly was the reason for such overload on the boss in question.

Item Type: Proj.Doc/Technical Report (Project Report)
Uncontrolled Keywords: Aircraft;Door assembly;Boss;Overload failure
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: 25 Jul 2011 12:05
Last Modified: 25 Jul 2011 12:05
URI: http://nal-ir.nal.res.in/id/eprint/9482

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