A mounting assembly (110) includes an engine mount link (132), an engine mount block (134), a fusible component (138), and a catcher component (140). The engine mount block (134) is connected to a pylon (106) and the engine mount link (132). The fusible component (138) and the catcher component (140) have respective first and second shear strengths (S1, S2). The catcher component (140) is disposed within a catcher aperture (C1). When an applied shear stress on the fusible component (138) is less than the first shear strength (S1), the engine mount link (132) is stationary with respect to the engine mount block (134). When the applied shear stress on the fusible component (138) exceeds the first shear strength (S1), the fusible component (138) mechanically fails and causes the catcher component (140) to move relative to the catcher aperture (C1) further causing a corresponding movement of the engine mount link (132).
MOUNTING ASSEMBLY FOR GAS TURBINE ENGINE
MONTAGEANORDNUNG FÜR GASTURBINENMOTOR
ENSEMBLE DE MONTAGE POUR MOTEUR À TURBINE À GAZ
31.07.2024
Patent
Elektronische Ressource
Englisch
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
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