Add to ORKGTwo fractured main landing attachment bolts from an aircraft were sent to the laboratory for analysis. Examination showed that both the bolts have failed by fatigue. Examination also revealed numerous cracks at the thread roots of the bolts. The most probable reason for fatigue crack initiation appears to be the existence of fine cracks at the thread roots, possibly generated during tightening of the bolts
A failed main rotor blade fork (big) of a helicopter was forwarded to this laboratory for analyzing ...
The wheel hub in question has failed by fatigue. Three fatigue cracks were identified and all of the...
The main fitting subassembly of main landing gear of an aircraft was sent to the laboratory for ana...
Two fractured main landing attachment bolts from an aircraft were sent to the laboratory for analysi...
From the failure pattern, it appears most probable that the main fitting subassembly of the main lan...
From the failure pattern, it appears most probable that the main fitting subassembly of the main lan...
A few fractured bolts recovered from an in flight incident of an aircraft were received for analysi...
A few fractured bolts recovered from an in flight incident of an aircraft were received for analysi...
A failed jack attachment bolt belonging to an aircraft was sent to the laboratory for investigation....
A failed jack attachment bolt belonging to an aircraft was sent to the laboratory for investigation....
A failed bolt of horizontal stabilizer support (RH) of a helicopter was analyzed. Analysis showed th...
A failed bolt of horizontal stabilizer support (RH) of a helicopter was analyzed. Analysis showed th...
A fractured tie rod of the engine rear attachment was analyzed. Fractographic features suggest that ...
A failed main rotor blade fork (big) of a helicopter was forwarded to this laboratory for analyzing ...
Two fractured bolts belonging to an aircraft engine removal ground equipment were brought to the lab...
A failed main rotor blade fork (big) of a helicopter was forwarded to this laboratory for analyzing ...
The wheel hub in question has failed by fatigue. Three fatigue cracks were identified and all of the...
The main fitting subassembly of main landing gear of an aircraft was sent to the laboratory for ana...
Two fractured main landing attachment bolts from an aircraft were sent to the laboratory for analysi...
From the failure pattern, it appears most probable that the main fitting subassembly of the main lan...
From the failure pattern, it appears most probable that the main fitting subassembly of the main lan...
A few fractured bolts recovered from an in flight incident of an aircraft were received for analysi...
A few fractured bolts recovered from an in flight incident of an aircraft were received for analysi...
A failed jack attachment bolt belonging to an aircraft was sent to the laboratory for investigation....
A failed jack attachment bolt belonging to an aircraft was sent to the laboratory for investigation....
A failed bolt of horizontal stabilizer support (RH) of a helicopter was analyzed. Analysis showed th...
A failed bolt of horizontal stabilizer support (RH) of a helicopter was analyzed. Analysis showed th...
A fractured tie rod of the engine rear attachment was analyzed. Fractographic features suggest that ...
A failed main rotor blade fork (big) of a helicopter was forwarded to this laboratory for analyzing ...
Two fractured bolts belonging to an aircraft engine removal ground equipment were brought to the lab...
A failed main rotor blade fork (big) of a helicopter was forwarded to this laboratory for analyzing ...
The wheel hub in question has failed by fatigue. Three fatigue cracks were identified and all of the...
The main fitting subassembly of main landing gear of an aircraft was sent to the laboratory for ana...