The invention relates to a cradle (10) for an aircraft turbopropeller engine (12) of a substantially axial orientation, comprising a front arch (16) and a rear arch (18) extending transversely relative to said axial direction (A), said arches (16, 18) being open at their lower ends and connected to each other by at least one axial longeron (34) extending between said arches (16, 18), characterised in that the longeron (34) is arranged in an upper portion of the cradle (10) and is formed in a single piece with the front arch (16).
CRADLE FOR A TURBOPROPELLER ENGINE WITH INTEGRATED AIR INLET DUCT
2019-09-05
Patent
Electronic Resource
English
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
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