A control system having one or more controllers configured to determine a maintenance date of an engine based on monitored parameters of the engine of an aircraft. The one or more controllers also are configured to, determine an amount of coating sprayed on the engine on the determined maintenance date based on the monitored parameters and determined maintenance date. The one or more controllers also are configured to adjust the maintenance date based on needs of an aircraft fleet and regularly scheduled maintenance of the engine.

Method and apparatus for unsupervised aircraft design. A plurality of design problem data and service event data for an aircraft is received from an electronic data repository. Embodiments communicate with sensors on the aircraft during flight operations and capturing service data and sensor data. A high order vector is generated for each received problem report and service event data and each high order vector is concatenated into a high order vector matrix. Embodiments generate a reduced order symptom-normalized matrix by factorization of the concatenated high order vector matrix and generate a similarity matrix from the symptom-normalized matrix. An impact score is computed for each in-service event data as a function of similar problem reports using the similarity matrix. Embodiments generate a priority matrix configured to identify service event data having high impact scores and communicate a real-time alert of the high impact scored service event.

A manufacturing assistance apparatus includes a learning unit and an estimator. The learning unit is configured to load a plurality of pieces of actual measurement data in each of which a gap and a plurality of parameters are associated with each other, and construct an estimation model on the basis of machine learning in which the plurality of pieces of actual measurement data serve as teacher data. The gap is provided between a first workpiece and a second workpiece that eventually structure an airframe of an aircraft and that are eventually fastened to each other. The estimation model estimates the gap from the plurality of parameters. The estimator is configured to derive an estimation value of a length of the gap on which measurement has not yet been performed, on the basis of the estimation model constructed by the learning unit and the plurality of parameters.

This decision aid method includes the following steps: acquiring (110) operating states of systems, the operating states being determined by a monitoring system; determining (120) an availability state of each operational capacity, based on the operating states of only the systems of the aircraft implementing that operational capacity, each availability state being chosen from among the group consisting of: a normal state, a downgraded state, an impacted state and a lost state; selecting (150) one or more operational capacities based on the current movement context of the aircraft; communicating (150) the availability state of each selected operational capacity to the pilot.

A data evaluation system, in particular for data evaluation on interfaces on board an aircraft, includes a data processing server having a receiver device, a data processing processor and an external server interface, and includes multiple data readers, coupled to the data processing server via the receiver device, that each have a device processor and a data capture component connected to the device processor and are configured to forward data captured by the data capture component to the data processing server for conditioning.

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.

Every junction part for an airplane wing is manufactured with overmaterial. Each part is measured with a laser based interferometer or other scanning technique and the as built measurements are compared with a model to generate a new trajectory milling program to fill or prevent gaps between parts using a points cloud and B-Spline algorithm to generate a new surface to be milled. Once the program is generated (new trajectories) and post processed, it is sent to a milling machine to perform overmaterial milling on already milled parts with overmaterial. This technique can be used to eliminate gaps between junction parts and the corresponding need for shims.

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 manufacturing method includes deriving, from statistic data, a representative value of a clearance provided between first and second workpieces, executing a first insertion process, and executing a second insertion process. The statistic data is obtained from measuring the clearance. The executing the first insertion process includes testing insertion of a tolerance shim into the clearance when the representative value is less than a tolerance of the clearance, and testing insertion of a double-tolerance jig into the clearance when the tolerance shim is insertable into the clearance. The executing the second insertion process includes testing insertion of a difference shim into the clearance when the representative value is greater than the tolerance, testing insertion of a representative shim into the clearance when the difference shim is insertable into the clearance, and testing insertion of an addition jig into the clearance when the representative shim is insertable into the clearance.

The invention relates to a method for monitoring at least one aircraft engine, said method including an acquisition (100) according to the first and second sets of measurements of respectively endogenous and exogenous variables. The method also includes: a normalization (200) of the measurements of the first set relative to the measurements of the second set, a generation (300) of a current model representative of the evolution of the behavior of the engine based on the normalized measurements, a detection (400) of potential abnormality in the behavior of the engine based on a comparison of the current model with a reference model, a generation (500) of a maintenance message, a transmission (600) of said ground message,
the acquisition, normalization, generation of a current model, the detection and generation of a maintenance message being made on board the aircraft.