Textron Innovations

One embodiment is a rotorcraft (100) including a rotor system (120) and a transmission system (300) for providing rotational power to the rotor system (120), the transmission system (300) comprising a housing and a planetary pinion gear (500, 602, 702, 808) disposed in the housing. The rotorcraft (100) further includes a restraint assembly (600, 700, 800) associated with the planetary pinion gear (500, 602, 702, 808), the restraint assembly (600, 700, 800) configured to restrict radial deflection of the planetary pinion gear (500, 602, 702, 808) during operation thereof subsequent to a crack-through failure of the planetary pinion gear (500, 602, 702, 808).

A method (500) for testing actuator pressures, including setting (502) a test actuator and one or more restraining actuators to a quiescent state, where the test actuator and one or more restraining actuators are connected to a same movable element, determining (504) a quiescent pressure delta that is associated with a sum of a first pressure for the test actuator and one or more second pressures for the one or more restraining actuators, disengaging (506) the test actuator from the movable element, where the disengaging includes setting the test actuator to avoid applying pressure to the movable element, determining (510) a test pressure delta that is associated with a sum of third pressures for the one or more restraining actuators after the disengaging of the test actuator, and providing (516) a notification regarding failure of the test actuator according to a relationship between the test pressure delta and a threshold.

A method, system, and device for optimizing fuel usage is provided. The system includes a gauge (1001), a first indicator (1010) on the gauge (1001) representing a current operating condition of a vehicle, and a second indicator (1020) on the gauge (1001) representing an operating condition of the vehicle that correlates with an optimal fuel efficiency of the vehicle in relation to the operating condition shown by the gauge (1001), where the second indicator (1020) is continually updated as ambient operating conditions change, and where the optimal fuel efficiency represents the minimum total fuel used to travel a non-zero distance based on current conditions in which the system is being operated.

An aircraft (12) includes a turboshaft engine (14) for powering the aircraft (12); an inlet barrier filter, IBF, (16) for filtering air at an inlet (26) through which the turboshaft engine (14) draws inlet air; a differential pressure transducer (30) for measuring a differential pressure across the IBF (16) during operation of the aircraft (12); and a flight control computer system configured to, during operation of the aircraft (12), periodically calculate a restriction of an airflow through the IBF (16), periodically determine a rate of change of the restriction of the airflow, compare the rate of change to a threshold rate, and provide an alert to a pilot of the aircraft (12) when the determined rate of change exceeds the threshold rate.

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