A method for manufacturing a main rotor for a generator is provided. The method includes printing at least part of a rotor shaft by a three-dimensional printing process. The step of printing at least part of the rotor shaft includes printing a plurality of closed outlets and a plurality of open outlets. A rotor core is printed by the three-dimensional printing process. The step of printing the rotor core includes printing a plurality of liquid coolant conduits that extend through the rotor core and fluidly connecting the plurality of liquid coolant conduits to the plurality of closed openings.

A system includes three switches each having a single pole and dual throws. The respective single pole is on a supply side of the each respective switch. The dual throws are on a load side of each respective switch, and include a respective normally open (NO) throw and a respective normally closed (NC) throw. A first voltage detector is connected from the single pole of the first switch to the NC throw of the third switch. A second voltage detector is connected from the single pole of the second switch to the NC throw of the first switch. A third voltage detector is connected from the single pole of the third switch to a NC throw of the second switch.

A system includes three switches each having a single pole and dual throws. The respective single pole is on a supply side of the each respective switch. The dual throws are on a load side of each respective switch, and include a respective normally open (NO) throw and a respective normally closed (NC) throw. A first voltage detector is connected from the single pole of the first switch to the NC throw of the third switch. A second voltage detector is connected from the single pole of the second switch to the NC throw of the first switch. A third voltage detector is connected from the single pole of the third switch to a NC throw of the second switch.

An aircraft navigation light includes: a navigation lighting arrangement, having: a power input, couple able to an aircraft on-board power supply network, at least one navigation light source, and a power conditioning circuit, coupled between the power input and the at least one navigation light source for conditioning a power flow from the power input to the at least one navigation light source; an auxiliary power supply, coupled to the power conditioning circuit for diverting power from the navigation lighting arrangement; and a power supply output, coupled to the auxiliary power supply, for supplying power from the auxiliary power supply to an exterior aircraft light, external to the aircraft navigation light.

An aircraft navigation light includes: a navigation lighting arrangement, having: a power input, couple able to an aircraft on-board power supply network, at least one navigation light source, and a power conditioning circuit, coupled between the power input and the at least one navigation light source for conditioning a power flow from the power input to the at least one navigation light source; an auxiliary power supply, coupled to the power conditioning circuit for diverting power from the navigation lighting arrangement; and a power supply output, coupled to the auxiliary power supply, for supplying power from the auxiliary power supply to an exterior aircraft light, external to the aircraft navigation light.

A toggle assembly includes a first joint member having a first lug and a second lug, a second joint member, and a third joint member. The second joint member has a first arm that receives a first rolling element, a second arm that receives a second rolling element, a third arm, and a fourth arm. The second joint member is pivotally connected to the first joint member via a first pin that extends through the first lug, the first rolling element, the second rolling element, and the second lug. The third joint member has a third lug and a fourth lug disposed opposite the third lug. The third joint member is pivotally connected to the second joint member via a cross rod pin that extends through the third lug, the third arm and the fourth arm.

A system and method for adaptively controlling a cooldown cycle of an auxiliary power unit (APU) that is operating and rotating at a rotational speed includes reducing the rotational speed of the APU to a predetermined cooldown speed magnitude that ensures combustor inlet temperature has reached a predetermined temperature value, determining, based on one or more of operational parameters of the APU, when a lean blowout of the APU is either imminent or has occurred, and when a lean blowout is imminent or has occurred, varying one or more parameters associated with the shutdown/cooldown cycle.

A system and method for adaptively controlling a cooldown cycle of an auxiliary power unit (APU) that is operating and rotating at a rotational speed includes reducing the rotational speed of the APU to a predetermined cooldown speed magnitude that ensures combustor inlet temperature has reached a predetermined temperature value, determining, based on one or more of operational parameters of the APU, when a lean blowout of the APU is either imminent or has occurred, and when a lean blowout is imminent or has occurred, varying one or more parameters associated with the shutdown/cooldown cycle.

An aircraft (41) including a fuselage (14) having a skin (15) and extending along a longitudinal axis (39) from a front end to a rear end (17) of the aircraft, and an engine (30) including an air intake (31) forming an opening in the skin (15) and an exhaust (32) forming another opening in the skin (15). The engine is in a rear fuselage section, in which the exhaust (32) is situated ahead of the air intake (31) along the longitudinal direction (39).

An aircraft (41) including a fuselage (14) having a skin (15) and extending along a longitudinal axis (39) from a front end to a rear end (17) of the aircraft, and an engine (30) including an air intake (31) forming an opening in the skin (15) and an exhaust (32) forming another opening in the skin (15). The engine is in a rear fuselage section, in which the exhaust (32) is situated ahead of the air intake (31) along the longitudinal direction (39).