Add to ORKGFailed bolts of main undercarriage torque link of an aircraft were analyzed. Examination did not reveal cracks in any of the bolts. The bolt material was found to conform to BS-4S-99 specification. The hardness was measured to be about RC42. The bolt material was found to have a non-uniform and banded structure. Also, large non-metallic inclusions were found present in the material. In view of the above findings, it is recommended that the bolts manufactured from this batch of material be rejected and/or withdrawn from service immediately
A fractured main undercarriage fitting of an aircraft was analyzed. Analysis revealed that there was...
A fractured main undercarriage fitting of an aircraft was analyzed. Analysis revealed that there was...
Three Ti-6Al-4V bolts from mid-life jet aircraft failed during service operation. Each of the failed...
Failed bolts of main undercarriage torque link of an aircraft were analyzed. Examination did not rev...
Failed shear bolts used in the PTO shaft of an aircraft were analyzed. Examination showed that two o...
Four failed bolts used in an aircraft were sent to the laboratory for analysis. Examination revealed...
Four failed bolts used in an aircraft were sent to the laboratory for analysis. Examination revealed...
A fractured torque link lower sub-assembly and six fractured dowel pins belonging to main under-car...
A fractured torque link lower sub-assembly and six fractured dowel pins belonging to main under-car...
Two fractured bolts belonging to an aircraft engine removal ground equipment were brought to the lab...
Two fractured bolts belonging to an aircraft engine removal ground equipment were brought to the lab...
Two fractured bolts belonging to an aircraft engine removal ground equipment were brought to the lab...
Two fractured main landing attachment bolts from an aircraft were sent to the laboratory for analysi...
Two fractured main landing attachment bolts from an aircraft were sent to the laboratory for analysi...
The failure of bolt during landing is due to unidirect-ional bending fatigue under low nominal stre...
A fractured main undercarriage fitting of an aircraft was analyzed. Analysis revealed that there was...
A fractured main undercarriage fitting of an aircraft was analyzed. Analysis revealed that there was...
Three Ti-6Al-4V bolts from mid-life jet aircraft failed during service operation. Each of the failed...
Failed bolts of main undercarriage torque link of an aircraft were analyzed. Examination did not rev...
Failed shear bolts used in the PTO shaft of an aircraft were analyzed. Examination showed that two o...
Four failed bolts used in an aircraft were sent to the laboratory for analysis. Examination revealed...
Four failed bolts used in an aircraft were sent to the laboratory for analysis. Examination revealed...
A fractured torque link lower sub-assembly and six fractured dowel pins belonging to main under-car...
A fractured torque link lower sub-assembly and six fractured dowel pins belonging to main under-car...
Two fractured bolts belonging to an aircraft engine removal ground equipment were brought to the lab...
Two fractured bolts belonging to an aircraft engine removal ground equipment were brought to the lab...
Two fractured bolts belonging to an aircraft engine removal ground equipment were brought to the lab...
Two fractured main landing attachment bolts from an aircraft were sent to the laboratory for analysi...
Two fractured main landing attachment bolts from an aircraft were sent to the laboratory for analysi...
The failure of bolt during landing is due to unidirect-ional bending fatigue under low nominal stre...
A fractured main undercarriage fitting of an aircraft was analyzed. Analysis revealed that there was...
A fractured main undercarriage fitting of an aircraft was analyzed. Analysis revealed that there was...
Three Ti-6Al-4V bolts from mid-life jet aircraft failed during service operation. Each of the failed...