A system and method of converting engines on a turboprop aircraft, including removing an existing engine and associated propeller from an aircraft fuselage, installing an engine mount adapter assembly to the fuselage, and installing a replacement engine to the engine mount adapter assembly, whereby at least some portions of the replacement engine are attached to the engine mount adapter assembly for structural support.

In an embodiment, a method includes acquiring a current condition indicator of a condition indicator set associated with an operating condition of a machine, the condition indicator set indicating sensor readings associated with an operating element of the machine under the operating condition. The method also includes determining, by a data server, a relative trend significance over a trend window of the condition indicator set based, at least in part, on an evaluation of the trend window in relation to a historical window of the condition indicator set. The method also includes determining, by the data server, whether trend criteria associated with the operating element is satisfied, where the trend criteria may include criteria related to the relative trend significance. The method also includes executing, by the data server, an alerting process in response to the determining that the trend criteria is satisfied.

A method of monitoring the health of an aircraft propeller whilst the propeller is in operation, the propeller having a plurality of blades extending radially outwardly from hub arms of a propeller hub, which in turn extend radially outwardly from a central axis extending through the propeller and a propeller drive shaft, is provided. The method comprises obtaining measurements representative of the strain in each of at least some of the hub arms using strain sensors, each of the strain sensors being provided on a respective hub arm. A corresponding propeller health monitoring system, an aircraft propeller comprising the system and an aircraft comprising the propeller are also provided.

A simplex Flight Control Computer (FCC), usable in conjunction with a neighboring FCC, includes an input providing module for receiving sensor, system and neighboring FCC data; a processing unit for executing a command partition and a monitor partition, the processing unit receives the sensor, system data and neighboring FCC data; the monitor partition monitors the neighboring FCC data and provides a monitoring indicative signal to the neighboring FCC, and the command partition generates command signals; a hardware monitoring module provides a validity signal indicating FCC health; an output cutoff module receiving the FCC validity signal and enable signals generated by each monitor partition; the output cutoff module providing an enable signal based on a predetermined enabling strategy; and an enable switch connected with the output cutoff module and the processing unit and providing a received signal from the command partition according to the enable signal.

A system including an aircraft, and a computing system remote from the aircraft. The aircraft includes a sensor, an aircraft component associated with the sensor, a first transmitter, and a first receiver. The computing system includes a processor, a second transmitter, and a second receiver. The aircraft transmits sensor data sensed by the sensor to the computing system. The computing system is configured to process the received sensor data to generate status data indicative of an operational mode of the aircraft component, and to transmit, when the status data is indicative of an altered operational mode of the aircraft component, the status data to the aircraft via the second transmitter. The aircraft is configured to indicate, based at least partially on the status data received by the first receiver, the altered operational mode of the aircraft component.

A sensor for monitoring rotors includes a rotating shaft coupled to a set of rotor blades and a non-rotating tube at least partially disposed within the rotating shaft and coupled to the rotating shaft. The non-rotating tube includes a first end and a second end, a sensor mount disposed within the non-rotating tube proximate to the second end of the non-rotating tube. One or more sensors are attached to the sensor mount.

An assistance method for assisting a pilot of a single-engined rotary-wing aircraft during a flight phase in autorotation, the aircraft including a hybrid power plant provided with a main engine, with an electric machine, with a main gearbox, and with an electrical energy storage device. The aircraft also includes a main rotor driven by the hybrid power plant. In the method, during a flight, operation of the main engine is monitored in order to detect a failure, in particular by means of a drop in power on the main rotor, then, when a failure of the main engine is detected, the electric machine is controlled to deliver auxiliary power We to the main rotor, making it possible to assist a pilot of the aircraft in performing the flight phase in autorotation following the failure.

Methods and systems for monitoring operation of hybrid electric engines of aircraft. The methods include monitoring a motor condition of an electrical power system associated with an engine condition using a motor sensor, wherein the electrical power system comprises an electric machine operably coupled to at least one shaft of an engine core, wherein the electric machine is configured to at least one of add power to the at least one shaft and extract power from the at least one shaft, receiving motor data from the motor sensor at a motor controller, wherein the motor controller is configured to control operation of, at least, the electric machine, analyzing the motor data to determine the presence of a fault in the engine core, and, when a fault is detected, performing a fault response action.

A system including a module for collecting vibration signals, a module for filtering the signals, a module for verifying whether the signals preserved by the filtering module correspond to signals representative of a set of flight conditions of the aircraft that are listed in a reference database, a module for identifying sources of vibration, a module for requesting a maneuver to be carried out by a pilot depending on the identified sources of vibration, a module for deciding, using a predefined decision tree, whether the preceding modules should be implemented again, and a module for transmitting a vibration report to a user device. The system allows assistance to be given, to the pilot, with the generation of a vibration report, and assistance to be given with maintenance of the aircraft.

An assembly is provided for an engine. This engine assembly includes a fuel system, a sensor and a processing system. The fuel system includes a fuel source, an engine component and a fuel circuit configured to direct fuel from the fuel source to the engine component. The sensor is configured to provide sensor data indicative of a measured parameter of the fuel directed through the fuel circuit from the fuel source to the engine component. The processing system is configured to identify a fuel leak in the fuel system based on the sensor data. The fuel leak is identified when a measured value corresponding to the measured parameter of the fuel is less than an expected value corresponding to an expected parameter for the fuel directed through the fuel circuit from the fuel source to the engine component.