An aircraft nacelle arrangement includes a compression rod disposed between a first nacelle half and a second nacelle half, wherein the first nacelle half and the second nacelle half are rotatable about a hinge between a closed position and an open position, a compression rod disposed between the first nacelle half and the second nacelle half, and a mounting bracket coupled to an exhaust nozzle flange of the aircraft engine, wherein the compression rod extends through the mounting bracket.
NACELLE THRUST REVERSER COMPRESSION ROD SUPPORTING SYSTEM
DRUCKSTABLAGERUNGSSYSTEM FÜR EINEN GONDELSCHUBUMKEHRER
SYSTÈME DE SUPPORT DE TIGE DE COMPRESSION D'INVERSEUR DE POUSSÉE DE NACELLE
2024-01-24
Patent
Elektronische Ressource
Englisch
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