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1-6 of 6
Aircraft landing gear
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Series: ASM Technical Books
Publisher: ASM International
Published: 01 October 2005
DOI: 10.31399/asm.tb.faesmch.t51270072
EISBN: 978-1-62708-301-0
Abstract
This chapter documents the key findings of an investigation into the failure of an aircraft’s main wheel bearing housing. Using annotated images and a detailed SEM fractograph, it shows what investigators observed that led them to conclude that the flange on one of the hubs broke off due to a combination of fatigue, bending stresses, and wear. It also includes a recommendation to assess the structural integrity of the bearing housing after every 100 h of service using nondestructive techniques.
Book Chapter
Series: ASM Technical Books
Publisher: ASM International
Published: 01 October 2005
DOI: 10.31399/asm.tb.faesmch.t51270084
EISBN: 978-1-62708-301-0
Abstract
An aircraft tire burst while inflating, causing one of the flanges on the wheel hub to fracture. This chapter provides a summary of the investigation along with key findings. It includes images of the damaged hub and describes how various parts failed as the pressure in the tire increased. It explains that the hub material was of good quality under uniform load and that it fractured quickly by cleavage due to the force exerted by the overinflated tire.
Series: ASM Technical Books
Publisher: ASM International
Published: 01 October 2005
DOI: 10.31399/asm.tb.faesmch.t51270100
EISBN: 978-1-62708-301-0
Abstract
After several failed attempts to lower their starboard wheels for landing, pilots engaged the help of gravity through g-force maneuvers and managed to coax the wheels into place. An inspection following the incident revealed a broken universal joint in one of the linkages that opens and closes the doors to the undercarriage compartment. The failed component was removed from the aircraft and examined using optical and electron microscopes. Under low magnification, the fracture surface appeared jagged except for one corner that was relatively smooth. SEM fractography revealed the presence of fatigue striations in the smooth region and dimpling elsewhere. Based on their findings, investigators concluded that fatigue loading initiated a crack in the universal joint that progressed with time and that the final fracture occurred due to bending tensile overload.
Book Chapter
Series: ASM Technical Books
Publisher: ASM International
Published: 01 October 2005
DOI: 10.31399/asm.tb.faesmch.t51270120
EISBN: 978-1-62708-301-0
Abstract
This chapter describes an investigation following an aircraft accident in which the main undercarriage struts had failed. Visual examination revealed that the starboard strut fractured about 13 cm from the end nearest the underside of the wing. A close-up view of the fracture surface indicated that cracking initiated at the outer periphery of the strut and propagated inward until overload fracture occurred. SEM imaging revealed fatigue striations along the outer periphery and dimples elsewhere, indicative of tensile overload. Based on these observations, investigators concluded that the starboard strut failed by fatigue, which overloaded the port side strut as evidenced by its slant type fracture pattern.
Series: ASM Technical Books
Publisher: ASM International
Published: 01 October 2005
DOI: 10.31399/asm.tb.faesmch.t51270180
EISBN: 978-1-62708-301-0
Abstract
The nose landing gear on an aircraft malfunctioned during landing roll. After the incident, two fractured studs were found in the retraction jack support beam. Based on visual examination and the results of SEM fractography, investigators concluded that the studs failed by fatigue, a vulnerability because of the way they were mounted. A sketch showing the correct mounting configuration is included in the report.
Series: ASM Technical Books
Publisher: ASM International
Published: 01 October 2005
DOI: 10.31399/asm.tb.faesmch.9781627083010
EISBN: 978-1-62708-301-0