Failure analysis of main fitting subassembly of main landing gear of an aircraft

Venkataswamy, MA and Sujata, M and Parameswara, MA and Suresh Kumar, M and Madan, M and Bhaumik, SK (2005) Failure analysis of main fitting subassembly of main landing gear of an aircraft. Project Report. National Aerospace Laboratories, Bangalore.

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From the failure pattern, it appears most probable that the main fitting subassembly of the main landing gear has fractured during a heavy landing. Multiple fatigue cracks were observed at the crack initiation region. These cracks were very shallow having depth of about 0.6 mm. The fatigue cracks do not appear to be the primary reason for the failure in the present case. However, this needs to be examined by assessing the intensity of the impact forces in the last landing. No mechanical and/or metallurgical abnormalities were responsible for the fatigue crack initiation and fatigue appears to be stress related. The region below the tie down shackle support lug on the AFT is vulnerable for fatigue crack initiation and the crack initiation is accelerated if the aircraft goes through a series of heavy landings.

Item Type: Monograph (Project Report)
Uncontrolled Keywords: Aircraft;landing gear;impact
Subjects: AERONAUTICS > Aeronautics (General)
CHEMISTRY AND MATERIALS > Chemistry and Materials (General)
Depositing User: Mrs Manoranjitha M D
Date Deposited: 19 Jul 2011 04:39
Last Modified: 19 Jul 2011 04:39

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