The invention relates to a propulsion assembly for an aircraft, comprising a nacelle (24) which comprises a fan compartment (48), a front cowling (34) forming an air inlet, and an intermediate section (36) including at least one intermediate cowling (66, 70) of the stationary and removable type that delimits the fan compartment (48) on the outside and is attached to another structure of the propulsion assembly via removable attachment through-members (86, 90, 94). The intermediate cowling is connected to another element of the propulsion assembly by means of a hinge system (96, 100) which, by removing the removable attachment through-members, is configured to enable movement of the intermediate cowling between a closed position, in which it extends as a continuation of the front cowling (34), and an open position, in which the intermediate cowling is offset upstream or downstream so as to open the fan compartment (48).
ENSEMBLE PROPULSIF POUR AÉRONEF COMPRENANT UN CAPOT INTERMÉDIAIRE DE TYPE FIXE DÉMONTABLE MONTÉ SUR UN SYSTÈME D'ARTICULATION
PROPULSION ASSEMBLY FOR AN AIRCRAFT, COMPRISING AN INTERMEDIATE COWL OF THE STATIONARY, REMOVABLE TYPE, MOUNTED ON A HINGE SYSTEM
ANTRIEBSANORDNUNG FÜR EIN FLUGZEUG MIT EINER AUF EINEM SCHARNIERSYSTEM MONTIERTEN STATIONÄREN UND ENTFERNBAREN ZWISCHENVERKLEIDUNG
05.02.2025
Patent
Elektronische Ressource
Französisch
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