A cover for an opening on the exterior of an aircraft that contains a fire-resistant, high-temperature tolerant foam encased in a cover made of an aramid fabric. The cover is friction-fitted to the interior of the orifice. The cover can contain one or more durable rings embedded in the fire-resistant, high-temperature tolerant foam meant to protrude outward from the rest of the cover of the body to contact an interior of the orifice into which they are inserted holding the cover in place with friction instead of fasteners.

A cover for an opening on the exterior of an aircraft that contains a fire-resistant, high-temperature tolerant foam encased in a cover made of an aramid fabric. The cover is friction-fitted to the interior of the orifice. The cover can contain one or more durable rings embedded in the fire-resistant, high-temperature tolerant foam meant to protrude outward from the rest of the cover of the body to contact an interior of the orifice into which they are inserted holding the cover in place with friction instead of fasteners.

A rotorcraft is described and includes an inertial measurement unit (“IMU”) sensor mounted to the rotorcraft, the IMU sensor oriented relative to the rotorcraft such that a roll attitude of the rotorcraft occurs about a Z-axis and has a range of ±90 degrees, a pitch attitude of the rotorcraft occurs about an X-axis and has a range of ±180 degrees, and a yaw attitude of the rotorcraft occurs about a Y-axis and has a range of ±180 degrees.

A rotorcraft is described and includes an inertial measurement unit (“IMU”) sensor mounted to the rotorcraft, the IMU sensor oriented relative to the rotorcraft such that a roll attitude of the rotorcraft occurs about a Z-axis and has a range of ±90 degrees, a pitch attitude of the rotorcraft occurs about an X-axis and has a range of ±180 degrees, and a yaw attitude of the rotorcraft occurs about a Y-axis and has a range of ±180 degrees.

An aerospace cable that limits the occurrence of partial discharges includes an elongate electrically conductive element surrounded by a semiconductor layer and an insulation system around the semiconductor layer. This insulation system has an electrically insulating layer surrounding the semiconductor layer. Each layer of the insulation system has a radial thickness (ei . . . ), and in that an equivalent insulation thickness (teq) of this insulation system is greater than or equal to the result of a third-degree polynomial function equation of a minimum pressure and of a maximum temperature at which the cable is intended to be used.

An aerospace cable that limits the occurrence of partial discharges includes an elongate electrically conductive element surrounded by a semiconductor layer and an insulation system around the semiconductor layer. This insulation system has an electrically insulating layer surrounding the semiconductor layer. Each layer of the insulation system has a radial thickness (ei . . . ), and in that an equivalent insulation thickness (teq) of this insulation system is greater than or equal to the result of a third-degree polynomial function equation of a minimum pressure and of a maximum temperature at which the cable is intended to be used.

An aircraft thermal hydraulic active-warming system includes an active thermal-warming valve interoperably coupled between a hydraulic pressure line and a hydraulic low-pressure return line and a hydraulic actuator arranged in parallel with the active thermal-warming valve between the hydraulic pressure line and the hydraulic low-pressure return line.

An aircraft thermal hydraulic active-warming system includes an active thermal-warming valve interoperably coupled between a hydraulic pressure line and a hydraulic low-pressure return line and a hydraulic actuator arranged in parallel with the active thermal-warming valve between the hydraulic pressure line and the hydraulic low-pressure return line.

A detachable cargo mirror assembly for use on a rotorcraft surface that includes a bracket for mounting to a surface on the rotorcraft, the bracket comprising a base portion and a retainer portion having a first pair of opposing holes, an elongated arm having two opposing ends, a first end for coupling with the bracket and a second end coupled to a mirror apparatus, the first end having a passage; and a releasable connector that engages with the first pair of opposing holes and the passage in the elongated arm when the elongated arm is in a first position to display a desired image on the mirror apparatus. The detachable cargo mirror assembly can be removed or in a stowed position when not in use.

A detachable cargo mirror assembly for use on a rotorcraft surface that includes a bracket for mounting to a surface on the rotorcraft, the bracket comprising a base portion and a retainer portion having a first pair of opposing holes, an elongated arm having two opposing ends, a first end for coupling with the bracket and a second end coupled to a mirror apparatus, the first end having a passage; and a releasable connector that engages with the first pair of opposing holes and the passage in the elongated arm when the elongated arm is in a first position to display a desired image on the mirror apparatus. The detachable cargo mirror assembly can be removed or in a stowed position when not in use.