An integrated access panel is disclosed that can be used to assist in adjusting a component like a fan blade of a turbofan engine. in one form the integrated access panel is hinged at one end such that the panel remains attached during adjustment of the fan blade. The access panel can be positioned in an angled flow surface of a nacelle such that the fan blade cannot be removed from a wheel without removal of the nacelle or opening of the access panel. The integrated access panel can be spring-loaded and positioned to allow the fan blade to be removed from a wheel by moving the access panel out of the way. Subsequent blade removal can occur by rotation of the wheel to locate another blade in proximity to the access panel.
GAS TURBINE ENGINE ACCESS PANEL
GASTURBINENMOTOR-ZUGANGSTAFEL
PANNEAU D'ACCÈS POUR MOTEUR À TURBINE À GAZ
2019-05-22
Patent
Elektronische Ressource
Englisch
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
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