Abstract: An apparatus is described and in one embodiment includes a first portion comprising an inner diameter, a first outer diameter, and a first length and a second portion, wherein the first portion and the second portion are integrally connected together, the second portion comprising the inner diameter, at least one second outer diameter, and a second length. The embodiment further includes a flange comprising a contact surface, wherein the inner diameter of the first portion and the second portion provides a hollow pathway through the apparatus.

Abstract: An apparatus is provided in one example embodiment and may include a first portion comprising an inner diameter, a first outer diameter, and a first length and a second portion, wherein the first portion and the second portion are integrally connected together, the second portion comprising the inner diameter, at least one second outer diameter, and a second length. The apparatus may further include a flange comprising a contact surface, wherein the inner diameter of the first portion and the second portion provides a hollow pathway through the apparatus.

Abstract: A transmission support for securing a transmission to a rotorcraft includes two side beams each including a roof beam portion configured to be secured to structural elements of the rotorcraft cabin, and a pylon beam portion extending from the roof beam portion toward the other of the side beams. The pylon beam portion is configured to engage the transmission upon the transmission being received between the side beams. The support further has cross beams extending between and interconnecting the two side beams. The side beams and cross beams are part of a monolithic structure. A method of manufacturing the transmission support is provided.

Abstract: In one embodiment, a horizontal stabilizer spar is held on the empennage of a rotorcraft by saddle fittings clamping the stabilizer spar at positions spaced apart along a longitudinal direction of the stabilizer spar. Stabilizer mounts are connected at respective ends to the saddle fittings and to vertical spars on the empennage. At least one of the stabilizer mounts is constructed to allow movement of the saddle fittings with respect to the vertical spars with at least four directions of freedom. The movable stabilizer mount is floatingly attached to a vertical spar, while the saddle fittings are connected to the respective stabilizer mounts by way of spherical bearings.

Abstract: In one embodiment, a horizontal stabilizer spar is held on the empennage of a rotorcraft by saddle fittings clamping the stabilizer spar at positions spaced apart along a longitudinal direction of the stabilizer spar. Stabilizer mounts are connected at respective ends to the saddle fittings and to vertical spars on the empennage. At least one of the stabilizer mounts is constructed to allow movement of the saddle fittings with respect to the vertical spars with at least four directions of freedom. The movable stabilizer mount is floatingly attached to a vertical spar, while the saddle fittings are connected to the respective stabilizer mounts by way of spherical bearings.