Abstract
The main rotor drive plate of the helicopter is defined as a flight safety part. Failure to follow maintenance instructions might result in an accident involving serious injury or death of crew members and/or serious damage to the helicopter. In this work, the failure of five of the shear bolts in this assembly during installation torque wrenching was analyzed. Visual inspection, fractographic and metallographic examinations, chemical analysis and mechanical testing (static tensile and hardness tests) did not indicate any deviation from the requirements of the aeronautical military standards. A specially designed bolt force sensor, which is based on strain gauge technology, was used to monitor the actual load that develops in the bolt when it is torque-wrenched into a nut. Based on comparison of the behavior of bolts that had been lubricated in different ways with antiseize material, it was concluded that the bolts failed because of improper application of the antiseize material, which led to development of overloads.
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
