A monitoring method, the purpose of which is, when a loss of power is detected in an aircraft engine, to generate an alarm in the form of a single message displayed on a display screen in the cockpit, in order to indicate if the level of damage suffered by the engine is critical or not. The steps implemented are based on alarm signals transmitted by a central processing unit of the engine and also on alarm signals transmitted by a diagnostic device for the onboard systems of the aircraft, in order to take account of both the situation of the engine and also the situation of the systems surrounding the engine which can be affected by damage to an engine.

A maintenance system is provided for an environmental conditioning element of an environmental control system of a vehicle. The maintenance system includes a data acquisition module configured to determine an ambient temperature, an altitude of the vehicle, and a measured ECS compressor temperature; a fouling module coupled to receive the ambient temperature, the altitude, and the measured ECS compressor temperature from the data acquisition module and configured to generate a fouling condition of the environmental conditioning element based on at least the ambient temperature, the altitude, and the measured ECS compressor temperature; and a reporting module coupled to receive the fouling condition from the fouling module and configured to generate a report for a user that includes the fouling condition.

An advisory system of a vessel that monitors variables of a vessel system inclusive of systems and subsystems that are used to operate the vessel. The advisory system may use machine-learning to learn from an operator (i) whether or not two variables are related to one another, and (ii) likelihood that a variable will reach a threshold, and, optionally, time until reaching the threshold. The system may receive operator feedback (i) to indicate whether the two variables are related to one another, and (ii) whether a behavior of the variable is normal or not normal. Thereafter, if a determination that the same two variables are related to one another and behaving in a similar manner, provide notification to the operator of the behavior. In response to determining that the variable is behaving (e.g., trending) in a similar manner that is not normal, providing a notification to the operator.

A method of manufacturing an aircraft assembly is disclosed including forming a first tension hole in a first aircraft component and a second tension hole in a second aircraft component. The first and second aircraft components are positioned relative to each other such that the first tension hole at least partially overlies the second tension hole, to define a pair of tension holes. The first aircraft component is secured relative to the second aircraft component by providing a first fastener between the first tension hole and the second tension hole of the pair of tension holes. A first shear hole is formed in the first aircraft component and a second shear hole is formed in the second aircraft component. The first shear hole is axially aligned with the second shear hole, to define a pair of shear holes.

A lift device includes a chassis, a lift assembly supported on the chassis, a platform including a platform floor, a sensor coupled to the platform and positioned adjacent the platform floor, and a control system in communication with the lift assembly and the sensor. The sensor is oriented to sense objects or obstacles above the platform. The platform is displaceable by the lift assembly between a raised position and a lowered position.

A method of real-time oil consumption is disclosed. A method of real-time oil consumption detection may include capturing a raw oil quantity, calculating a corrected oil quantity, calculating a predicted oil quantity, calculating a prediction error, and calculating an estimated oil consumption rate. Raw oil quantity may be captured from an oil quantity sensor in an engine. Corrected oil quantity may be calculated by taking raw oil quantity and applying environmental and engine operational conditions. Prediction error may be calculated by finding the difference between corrected oil quantity and predicted oil quantity. Oil consumption rate may be calculated by applying a regression algorithm to prediction error.

A method and apparatus for building a fuselage assembly for an aircraft. A number of fixtures may be drive across a floor to an assembly area to form an assembly fixture. The fuselage assembly may be built on the assembly fixture.

A system, and corresponding method, for predicting failure of aircraft wing anti ice valves includes a processor configured to receive sensor inputs from a plurality of components that have a synchronous or an anti-synchronous relationship. The sensor inputs indicate an operational characteristic of the components. Memory records historical data from the sensor inputs and the memory is communicatively connected to the processor. The processor compares the synchronous or anti-synchronous relationship of at least two components in the plurality of components and the processor calculates a tolerance for operation of the at least two components based on historical failure data. The processor identifies component operating times that exceed the tolerance and predicts failure of such a component based on the historical failure data.

An attachment for an end effector. The attachment may include a clamp and a foot adhesively bonded to an edge of the clamp and having a set of interlocking features that form a mechanical interlock with the clamp.

A robotic tool is positioned relative to a feature of a component during a manufacturing process. The tool may be used to perform a manufacturing operation on the component. The tool is also be used to dispose a fiducial mark with a known registration to the feature, even if the feature is subsequently obscured. The position of tools for subsequent manufacturing operations are then set relative to the fiducial mark.