A waiting link to support an engine on an aircraft includes a body portion including a first body portion opening, a second body portion opening, and a space therebetween. A first bearing is received in the first body portion opening and moveable in a generally vertical direction. A second bearing is received in the second body portion opening. The first and second bearings include a first and second bearing opening, respectively, that receives a first and second attachment member, respectively, that secures the body portion to a first and second structure, respectively. A cam is located in the space. The cam is pivotable between a first position and a second position. The waiting link does not provide a load path when the cam is in the first position, and when a primary load path fails, the waiting link provides the load path when the cam is in the second position.
SECONDARY LOAD PATH FOR GAS TURBINE ENGINE
SEKUNDÄRER BELASTUNGSPFAD FÜR EINEN GASTURBINENMOTOR
CHEMIN DE CHARGE SECONDAIRE POUR MOTEUR À TURBINE À GAZ
2017-06-28
Patent
Elektronische Ressource
Englisch
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
Gas turbine engine mounting structure with secondary load path
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