An engine communication system for aircraft engines having a nacelle with two cowlings extending annularly about the aircraft engine and defining a radially outward surface thereof, and at least one sensor positioned radially inward from the nacelle. The system includes a cowling gap positioned between the two cowlings when coupled together, and an engine control device communicatively coupled to the sensor and configured to at least one of receive engine data from the sensor and receive instruction data from a transmitter device positioned radially outward from the cowling gap. The system also includes a linearly polarized antenna communicatively coupled to the engine control device and positioned radially inward from the cowling gap and extending radially outward toward the cowling gap. The antenna is configured to at least one of receive and transmit the engine data and the instruction data through the cowling gap.

An aircraft comprising a fastening element and an engine pylon with two rear covers. Each cover includes a movable lower cover mounted articulated on a rear portion in which in the closed position, the two movable lower covers are moved together and in which in the open position, they are tilted and moved apart from each other. For each movable lower cover, a hinge system, and at least one locking system locks the two movable lower covers together in the closed position and locks each movable lower cover to the fastening element in the open position. The presence of the movable lower covers provides, inter alia, easy access to the inside of the engine pylon, and the locking system locks the movable lower covers.

An aircraft with an in-boom lift propulsor includes a fuselage, a boom with a recess in the upper surface, and a lift propulsor comprising of a motor assembly and a propulsive element. Motor on the aircraft is operated through an interaction between the motor's magnetic field and electric current in a wire winding to generate force on a shaft of the motor. The in-boom lift propulsor helps prevent damages to the motor assembly and the aircraft by absorbing torque from the rotor and absorbing moment from the mating flange 328, where the mating flange 328 joins the motor assembly to the boom. The boom includes an access panel to service the motor assembly and invertor during maintenance.

An aircraft with an in-boom lift propulsor includes a fuselage, a boom with a recess in the upper surface, and a lift propulsor comprising of a motor assembly and a propulsive element. Motor on the aircraft is operated through an interaction between the motor's magnetic field and electric current in a wire winding to generate force on a shaft of the motor. The in-boom lift propulsor helps prevent damages to the motor assembly and the aircraft by absorbing torque from the rotor and absorbing moment from the mating flange 328, where the mating flange 328 joins the motor assembly to the boom. The boom includes an access panel to service the motor assembly and invertor during maintenance.

An aircraft propulsion unit includes a turbojet engine, a lateral pylon connected to the fuselage of the aircraft, and a nacelle on the lateral pylon. The nacelle includes an upstream section having an air intake, a downstream section housing a reverse thrust device, and a middle section having two fan half-cowls surrounding a fan housing of the turbojet engine, and when said half-cowls are in a closed position defining an aerodynamic continuity between the upstream and downstream sections. The fan half-cowls include a maintenance half-cowl positioned under the horizontal median plane of the nacelle, able to move between the closed position and an open position allowing access to the turbojet engine for maintenance operations on the turbojet engine. The nacelle further includes at least one standby lock, designed to hold the maintenance half-cowl in a position intermediate to the closed and open positions.

An assembly is provided for an aircraft propulsion system. This assembly includes a nacelle inner structure that extends axially along and circumferentially about an axial centerline. The nacelle inner structure includes an internal compartment and a cowl. The internal compartment is configured to house a core of a gas turbine engine. The cowl is configured to form an outer radial periphery of the internal compartment. An aft end portion of the cowl is also configured to form an outer radial periphery of a compartment exhaust to the internal compartment. The aft end portion of the cowl includes a plurality of axial fingers arranged circumferentially about the axial centerline in an array.

A nacelle for an aircraft propulsion assembly includes an actuator, a secondary door subject to the actuator and contributing to defining an external aerodynamic surface of the nacelle in a first position, a main door contributing to defining the external aerodynamic surface and including a recess that the actuator passes through in a deployed position but not in a retracted position, and a flap connected to the main door. The flap is movable between a closed position wherein the flap closes off at least a first region of the recess through which the actuator passes in the deployed position whereby the flap contributes to defining the external aerodynamic surface, and an open position wherein the flap is moved away from the recess so as to clear the passage for the actuator through the first region of the recess.

A nacelle for an aircraft propulsion assembly includes an actuator, a secondary door subject to the actuator and contributing to defining an external aerodynamic surface of the nacelle in a first position, a main door contributing to defining the external aerodynamic surface and including a recess that the actuator passes through in a deployed position but not in a retracted position, and a flap connected to the main door. The flap is movable between a closed position wherein the flap closes off at least a first region of the recess through which the actuator passes in the deployed position whereby the flap contributes to defining the external aerodynamic surface, and an open position wherein the flap is moved away from the recess so as to clear the passage for the actuator through the first region of the recess.

A pressure relief door assembly includes a pressure relief door, a pressure-actuated latch, and a temperature-actuated lock. The latch is disposable in each of a latched configuration (to retain the pressure relief door in a closed position) and an unlatched configuration (to allow the pressure relief door to move into an open position). The lock is disposable in each of an unlocked configuration (to allow the pressure relief door to move into the open position when the latch is in its unlatched configuration) and a locked configuration (e.g., to lock the latch in its latched configuration, to lock the pressure relief door in its closed position, or both). The lock may include a bimetallic coil, that when exposed to a temperature that satisfies a temperature threshold, expands a sufficient amount to engage a locking pin with a corresponding portion of the latch to retain the latch in its latched configuration.

A pressure relief door assembly includes a pressure relief door, a pressure-actuated latch, and a temperature-actuated lock. The latch is disposable in each of a latched configuration (to retain the pressure relief door in a closed position) and an unlatched configuration (to allow the pressure relief door to move into an open position). The lock is disposable in each of an unlocked configuration (to allow the pressure relief door to move into the open position when the latch is in its unlatched configuration) and a locked configuration (e.g., to lock the latch in its latched configuration, to lock the pressure relief door in its closed position, or both). The lock may include a bimetallic coil, that when exposed to a temperature that satisfies a temperature threshold, expands a sufficient amount to engage a locking pin with a corresponding portion of the latch to retain the latch in its latched configuration.