A bypass turbojet nacelle comprising a fixed structure, a fixed cowl and a cowl movable in translation between advanced and withdrawn positions by a ram with a reverser flap movable thereon, and a deployment system comprising a first slider integral with the movable cowl, a first groove comprising a first part and a curved, second part integral with the fixed structure, a second slider movable in translation in the second groove part, a first connecting rod rotatable on the first slider and on the second slider, and a second connecting rod articulated on both the first connecting rod first end and the reverser flap. The ram rod is articulated on the first connecting rod. Moving the first slider from the advanced to the withdrawn position moves the second slider along the first part and, when the first slider reaches the withdrawn position, the second slider moves along the second part.

Systems and methods for conditioning a fluid using bleed air from a bypass duct of a turbofan engine are disclosed. The system comprises a heat exchanger configured to facilitate heat transfer between a flow of bleed air from the bypass duct of the turbofan engine and the fluid, and a fluid propeller configured to drive the bleed air through the heat exchanger. The fluid propeller is disposed downstream of the heat exchanger.

An aircraft oil management system includes a generator, pump, and pump control system. The generator is mechanically coupled to a prime mover via a the rotor shaft and is configured to output three-phase power. The pump is mechanically decoupled from the rotor shaft and delivers oil to the generator. The pump control system drives the pump independent of a rotational speed of the rotor shaft.

Disclosed is a sump cover for a sump basin of a generator of an aircraft, the sump cover having: a sump cover shell shaped as an inverted bowl, a front portion of the sump cover shell including a first plurality of fastener features, each configured to fasten to one of a second plurality of fastener features in the sump basin; and a sump cover support extending outwardly from the sump cover shell, past a perimeter edge of the sump cover shell, configured to fit through a sump port and against a sump tube of the sump basin, wherein the sump cover support and the first plurality of fastener features define a multi-point mounting configuration between the sump cover and the sump basin.

Disclosed is a sump cover for a sump basin of a generator of an aircraft, the sump cover having: a sump cover shell shaped as an inverted bowl, a front portion of the sump cover shell including a first plurality of fastener features, each configured to fasten to one of a second plurality of fastener features in the sump basin; and a sump cover support extending outwardly from the sump cover shell, past a perimeter edge of the sump cover shell, configured to fit through a sump port and against a sump tube of the sump basin, wherein the sump cover support and the first plurality of fastener features define a multi-point mounting configuration between the sump cover and the sump basin.

A modular power overlay architecture includes at least two sets of power overlay tiles arranged to provide for or meet a desired power overlay architecture demand. The power overlay assembly can include a base having seats to receive the power overlay tiles. The power overlay tiles can include power switching components arranged relative to a conductive surface commonly arranged relative to each of the at least two sets of power overlay tiles.

A modular power overlay architecture includes at least two sets of power overlay tiles arranged to provide for or meet a desired power overlay architecture demand. The power overlay assembly can include a base having seats to receive the power overlay tiles. The power overlay tiles can include power switching components arranged relative to a conductive surface commonly arranged relative to each of the at least two sets of power overlay tiles.

Methods and systems for controlling windmilling in an engine are described. An electric starter motor is coupled to the engine, a circuit element is coupled to the electric starter engine and to a DC signal source, and a control system coupled to the engine and to the circuit element. The control system is configured for: determining whether the engine is in a windmilling state; when the engine is in a windmilling state, commanding the circuit element to apply a DC signal to the electric starter motor; and modulating the DC signal applied to the electric starter motor to control a level of rotational motion of the engine.

A method for operating a hybrid electric propulsion system of an aircraft, the hybrid electric propulsion system comprising a turbomachine, an electric machine coupled to the turbomachine, and a propulsor coupled to the turbomachine, the method comprising: operating the turbomachine to drive the propulsor; receiving data indicative of a failure condition of the hybrid electric propulsion system; and extracting power from the turbomachine using the electric machine to slow down one or more rotating components of the turbomachine in response to receiving the data indicative of the failure condition.

A modular power overlay architecture includes at least two sets of power overlay tiles arranged to provide for or meet a desired power overlay architecture demand. The power overlay assembly can include a base having seats to receive the power overlay tiles. The power overlay tiles can include power switching components arranged relative to a conductive surface commonly arranged relative to each of the at least two sets of power overlay tiles.