Patent ID: 8876041
Filing Date: 2014-11-04
Classification: B64D,E05B,E05C,F02C,F05D

Abstract:
1. A nacelle for a turbojet engine, comprising: an air intake structure configured to direct an air flow towards a fan of the turbojet engine; and a middle structure configured to surround said fan and to which is attached the air intake structure in order to provide an aerodynamic continuity, wherein the air intake structure includes at least one inner panel attached to the middle structure and defines, with the latter, a nacelle fixed structure, the air intake structure further including at least one outer longitudinal panel that includes an air intake lip in order to define a removable air intake structure that is axially movable along a rail-guideway sliding system, and wherein the removable air intake structure is provided with peripheral locking means including at least one electric lock that interacts with a complementary retaining means, wherein at least one of the peripheral locking means and the complementary retaining means is attached to the nacelle fixed structure, and the rail-guideway sliding system is also attached to the nacelle fixed structure, and wherein a fitting situated on the at least one outer longitudinal panel forms an opening that is configured to provide for insertion of a tool from outside of the outer longitudinal panel such that while inserted in the opening, the tool engages with adjusting means for adjustment of a prestress of the complementary retaining means.