Patent ID: 6811122
Filing Date: 2004-11-02
Classification: A62C,B64D,Y02T

Abstract:
Flame arrestor to plug the aircraft engines, which externally covers the compartment (1) wherein the previously mentioned engines (2) are located, characterized in having a range of additional elements to the composite material cover and arranged as follows:the first element to be assembled is a grid by which is attached with bolts (22) that go through the peripheral holes (8), the heads of the bolts (24) rest on external surface of the grid (6), the second element is a metallic plate (upper) (9) with a rectangular configuration which has a circular hole (10) in its center skirted by its corresponding peripheral holes (11): the grid (6) rests on the edges of the previously mentioned circular hole (10); the next part that the bolts (22) go through is the thin composite wall (25) with a chamfered (26) finish, that results in a bell shaped part with a hole (5) in the middle; afterward, the cylindrical ring (14) and the disc (15) are set forming a flanged cylinder located in the inferior part of the thin composite wall (25) of the platform (3), the bolts (22) go through the small diameter holes (16) distributed on the disc (15) and subsequently the interior cavity (27) coinciding in width with the cylindrical ring (14); subsequently, the bolts (22) go through the holes (17) of the lower metallic plate (12) and display the small diameter holes (18) confronted on the interior cavity (27) formed in the conjunction between the cylindrical ring (14) and the set disc (15), the composite material bevelled wall (26) and the lower metallic plate (12); and finally, after going through a metallic plate (lower) (12) the bolts (22) fasten the octagonal part (19) with edges (20) curved toward the exterior of the plate, distancing both parts a previously established measure by the separating elements (28).