Abstract: A gearbox assembly includes a main housing, a plurality of gears, and a lubricant sump. The main housing defines an internal cavity. The gears are disposed within the internal cavity. The lubricant sump is coupled to the main housing. The lubricant sump includes a sump body and a heat exchanger core. The sump body defines a sump cavity and an airflow passage. The sump cavity is fluidly coupled to the internal cavity to collect lubricant used with the gears. The heat exchanger core is coupled to and extends from the sump body and is disposed at least partially within the airflow passage to cool the lubricant passing through the heat exchanger core.

Abstract: A rotary-wing aircraft may include a rotor system comprising, a gear module including, a servo having an output shaft linearly moveable along a second axis, a rotating pitch change shaft that rotates about the second axis, a pitch change assembly for coupling linear movement of the output shaft to rotational movement of the pitch change shaft, the pitch change assembly including, a flexible rod movable along the second axis, the flexible rod including a first end having a plate fixedly coupled with the output shaft and a second end operably coupled with the pitch change shaft, the second end disposed within the rotating pitch change shaft, and a bearing having a rotational outer surface coupled for rotation with the pitch change shaft and a non-rotating inner surface operably coupled with the flexible rod for linear movement.

Abstract: A lubricant system includes a first gearbox defining a first internal cavity, a second gearbox defining a second internal cavity, a first lubricant cooler positioned external the first and second internal cavities, a second lubricant cooler positioned external the first and second internal cavities, and a plurality of fluid passages fluidly connecting the first lubricant cooler and second lubricant coolers to each of the first gearbox and the second gearbox. The first lubricant cooler and the second lubricant cooler are configured to hold lubricant. The fluid passages include a first main fluid passage fluidly connecting the first lubricant cooler to the first gearbox, a second main fluid passage fluidly connecting the second lubricant cooler to the second gearbox, a first auxiliary passage fluidly connecting the first lubricant cooler to the second gearbox, and a second auxiliary passage fluidly connecting the second lubricant cooler to the first gearbox.

Abstract: A lubricant system includes a first gearbox defining a first internal cavity, a second gearbox defining a second internal cavity, a first lubricant cooler positioned external the first and second internal cavities, a second lubricant cooler positioned external the first and second internal cavities, and a plurality of fluid passages fluidly connecting the first lubricant cooler and second lubricant coolers to each of the first gearbox and the second gearbox. The first lubricant cooler and the second lubricant cooler are configured to hold lubricant. The fluid passages include a first main fluid passage fluidly connecting the first lubricant cooler to the first gearbox, a second main fluid passage fluidly connecting the second lubricant cooler to the second gearbox, a first auxiliary passage fluidly connecting the first lubricant cooler to the second gearbox, and a second auxiliary passage fluidly connecting the second lubricant cooler to the first gearbox.

Abstract: A lubricant system includes a first gearbox defining a first internal cavity, a second gearbox defining a second internal cavity, a first lubricant cooler positioned external the first and second internal cavities, a second lubricant cooler positioned external the first and second internal cavities, and a plurality of fluid passages fluidly connecting the first lubricant cooler and second lubricant coolers to each of the first gearbox and the second gearbox. The first lubricant cooler and the second lubricant cooler are configured to hold lubricant. The fluid passages include a first main fluid passage fluidly connecting the first lubricant cooler to the first gearbox, a second main fluid passage fluidly connecting the second lubricant cooler to the second gearbox, a first auxiliary passage fluidly connecting the first lubricant cooler to the second gearbox, and a second auxiliary passage fluidly connecting the second lubricant cooler to the first gearbox.

Abstract: An aircraft tail rotor system includes a rotating pitch change shaft, a translating element, and a pitch change bearing assembly including a first bearing and a second bearing. The pitch change bearing assembly is operable to transmit movement of the translating element to the rotating pitch change shaft via the first bearing or the second bearing. A failure section is formed at an interface between the first bearing and the translating element. When the failure section decouples the first bearing from the translating element such that the first bearing does not transmit movement of the translating element to the rotating pitch change shaft, the second bearing transmits movement of the translating element to the rotating pitch change shaft.

Abstract: A locking mechanism for a driveshaft disconnect coupling includes an input jaw member defining a rotation axis, an output jaw member connectable to the input jaw member for common rotation with the input jaw member, and a cartridge assembly. The cartridge assembly is fixed to the input jaw member, includes a pin, and defines a pin movement axis. The pin is movable along the pin axis between a radially inner position and a radially outer position, the pin being disengaged from the output jaw member in the radially inner position and the pin being engaged to the output jaw member in the radially outer position.

Abstract: An aircraft tail rotor system includes a rotating pitch change shaft, a translating element, and a pitch change bearing assembly including a first bearing and a second bearing. The pitch change bearing assembly is operable to transmit movement of the translating element to the rotating pitch change shaft via the first bearing or the second bearing. A failure section is formed at an interface between the first bearing and the translating element. When the failure section decouples the first bearing from the translating element such that the first bearing does not transmit movement of the translating element to the rotating pitch change shaft, the second bearing transmits movement of the translating element to the rotating pitch change shaft.

Abstract: A locking mechanism for a driveshaft disconnect coupling includes an input jaw member defining a rotation axis, an output jaw member connectable to the input jaw member for common rotation with the input jaw member, and a cartridge assembly. The cartridge assembly is fixed to the input jaw member, includes a pin, and defines a pin movement axis. The pin is movable along the pin axis between a radially inner position and a radially outer position, the pin being disengaged from the output jaw member in the radially inner position and the pin being engaged to the output jaw member in the radially outer position.