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This paper aims to show the current situation and additional requirements for the aircraft automation systems based on the lessons learned from the two 737 MAX crashes.

In this study, the Swiss cheese model was used to find the real root causes of the 737 MAX accidents. Then, the results have been compared with the actions taken by the manufacturers and authorities. Based on the comparison, the necessary improvements to prevent such accidents are defined. Regarding the faulty sensor that forms the accidents, a synthetic sensor was developed using an aerodynamic model.

It has been proven that the safety-critical automation systems should not be designed by relying on a single set of sensor data. Automation levels should be defined in a standard way. Depending on the defined automation level, the system must be designed as either fail-safe or fail-operational system. When designing backup systems, it should be decided by looking at not only whether it has power but also the accuracy of the incoming signals.

Aviation certification requirements related to automation systems need to be revised and improved. With this context, it was revealed that the certification processes for automation systems should be re-evaluated and updated by aviation authorities, especially Federal Aviation Administration and European Union Aviation Safety Agency.

Task sharing between automation system and pilot based on the classification of automation levels and determining certification requirements accordingly has been brought to the agenda. A synthetic Angle of Attack sensor was developed by using an aerodynamic model for fault detection and diagnosis.

The purpose of this paper is to present a study of radial aircraft tire for safety assessment during various scenarios.

A detailed finite element (FE) model of aircraft tire was established based on the actual geometry of the target tire for numerical simulations. As the major component of this tire, rubber material usually presents a complicated mechanical behavior. To obtain the reliable hyperelastic properties of rubber, a series of material tests have been processed. Moreover, in order to validate the proposed model, the simulations results of inflation and static load scenarios were compared with the experimental results. Both of the control volume and corpuscular particle method methods were used in the numerical simulations of aircraft tire.

The comparisons of the two methods exhibit close agreement with the experimental results. To assess the safety of aircraft tire during the landing scenario, the dynamic simulations were processed with different landing weights and vertical landing speeds. According to the relevant airworthiness regulations and technical documents, the tire pressure, deflection and load have been chosen as the safety criteria. Subsequently, the analysis, results and comments have been discussed in detail.

The validated FE model proposed in present study can be effectively used in tire modeling in static and dynamic problems, and also in the design process of aircraft tire.

This study aims to optionally-piloted aircraft is useful for in-flight tests of new automatic controller’s concepts. The safety of this kind of experiment is an issue addressed in this paper. The prediction of possible safety-influencing factors makes it possible to assess the pilot’s ability to effectively prevent safety risks.

The analysis in this research paper focusses on two cases of monitoring; similar control standards for both pilot in command and the monitoring pilot or technical systems in one of these tasks and dissimilar control standard when monitoring pilot is not familiar with a control manner of the pilot in command or of the automatic control system. The increased workload is expected in the last case as the result of additional activities determined theoretically in the presented analysis. Details of the possible threats are obtained by simulation tests with various factors influencing the safety of landing. In addition to determining threats, the analysis includes the possibility of in time threat detection and preserving action.

The results show that the safety pilot has a different task than the pilot in command and needs to be familiar with the general principles of automatic controller operations and the particular algorithm being tested. Although commonly used landing procedure is relatively error-tolerant, new landing procedures for use in some specific conditions need more precise control and additional safety pilot preparation. Additional information presented to both the pilot in command and the safety pilot may increase mode and state awareness and reduce reaction time in an emergency condition.

In-flight tests of non-standard control algorithms there is a need to include additional preparation of the equipment and safety pilot. The research in this paper illustrates how to determine threats and safety-critical moments during the experimental flight can be observed. The danger is mitigated by the safety pilot, if familiar with both proper and improper operations of the controller and how the pilot in command should detect and predict danger caused by the tested control system.

The presented method of analysis combines the human factor with various technical aspects. The results obtained illustrate the real tasks of the person supervising the operation of the automatic control system and the role of a human as a safety pilot.