European Aviation Safety Agency Research Articles

How Have EU Legislators Established EU Agencies With Enforcement Tasks? Case Studies of the European Aviation Safety Agency and the European Medicines Agency

AbstractEuropean Union (EU) policies were long enforced according to a well‐established framework in which member state governments made legislative, administrative and operational arrangements for realizing policies made in Brussels. EU legislators, however, are increasingly creating EU agencies to help enforce EU policies. This article attempts to explain this puzzling development, as it examines how the establishment of EU enforcement agencies by EU legislators relates to the well‐established role of member states. This article relies on case studies of the European Aviation Safety Agency (EASA) and the European Medicines Agency (EMA). These case studies show that, during the establishment of those agencies, the member state enforcement framework provided institutional stability on the one hand yet facilitated institutional change on the other. This institutionalist account of EU agency establishment supplements functional and political ones that have so far prevailed in the academic discourse.

Laboratory Assessment of In-Pavement Airport Lamp’s Luminous Intensity Distribution

The luminous intensity measurements of airport navigational lighting should be performed in accordance with the recommendations of the European Aviation Safety Agency (EASA), which allows for the determination of the possibility of further operation or the need to replace particular lamps. This article presents a device and method for measuring the light main beam of in-pavement airport lamps used on runways and taxiways. During the measuring process in the laboratory dark room, the proposed system automatically prepares reports as heatmaps presenting angular relationships of light distribution. Photometric measurements were made using a BH1750 illuminance sensor, which was compared to a certified Sonopan L-200P luxmeter. The measurement stability of different BH1750 modes was investigated for different airport lamp power source thresholds. Due to distortions in spectral characteristic of BH1750, polynomial corrections were proposed. The functionality of the device was presented for the exemplary assessment of used and refurbished runway in-pavement airport lamps to compare their parameters change. The research results and device implementation were possible through scientific cooperation with the Poznań-Ławica Airport.

The Development of Drone Techology and its Regulation in the European Union

Abstract Unmanned Aerial Vehicles (UAVs), or drones, have rapidly transformed from niche gadgets to versatile tools with widespread applications across various sectors. This paper investigates the regulatory landscape of drones within the European Union (EU) and its intricate balance between fostering technological innovation and addressing safety, privacy, security, and environmental concerns. Drones’ exponential growth in Europe’s airspace has prompted the EU to establish a legal framework that addresses their multifaceted implications. While drones offer unprecedented opportunities in areas like disaster response and remote sensing, they also pose challenges such as airspace congestion, potential privacy breaches, and ecological disturbances. This paper examines the evolving legal frameworks, policy developments, and technological advancements that characterize drone regulation in the EU. The study delves into key considerations including air traffic management, data protection, privacy preservation, environmental sustainability, and international collaboration. By analysing EU regulations, such as the European Aviation Safety Agency (EASA) standards, the General Data Protection Regulation (GDPR), and European initiatives on unmanned aircraft systems, this paper uncovers the complex interplay of legal, technical, and ethical dimensions.

Experimentally Validated Neural Networks for Sensors Redundancy Purposes in Spark Ignition Engines

<div>In the aeronautical field, aircraft reliability is strictly dependent on propulsion systems. Indeed, a reliable propulsion system ensures the safety of pilots and passengers and the possibility of making comfortable flights. Typically, on aircraft equipped with spark ignition (SI) engines, one of the principal requirements to make them reliable is the correct balancing between the intake air mass and fuel flows. Advances in the implementation of sophisticated control and estimation strategies on SI engines allow realizing engines with improved features in terms of performance, reducing pollution emissions, and fuel consumption. Approaches based on sensor redundancy are applied to improve the reliability in measurements of the manifold air pressure (MAP) and flow (MAF) to avoid issues related to possible faults of sensors vital for the correct functioning of SI engines. Model-based estimation techniques, based on the speed–density and alpha-speed methods for determining the MAF in engine control units, are employed to obtain sensor-less redundancy. The prediction of MAP and MAF, for sensors redundancy purposes, can be made through neural networks, allowing the avoidance of effects due to unmodeled dynamical behaviors. A sensor redundancy approach based on feedforward neural networks (FNNs) is proposed in this work for MAP and MAF prediction of a SI engine. The present work focuses on the possibility of estimating the physical quantities related to SI engines, such as the MAP and the MAF, fundamental for their monitoring using neural networks trained by means of a model-based approach avoiding expensive experimental tests for producing training data. A well-known intake manifold dynamical model (IMDM), parametrized based on the CMD 22 aeronautical engine, is employed for generating synthetic training data in steady-state conditions functional for making the chosen FNNs able to predict both MAP and MAF even in transient behavior.</div> <div>The MAP and MAF are predicted through two virtual sensors based on two independent FNNs, having the same inputs, constituted by the engine speed and the throttle angle. An experimental investigation based on an aircraft endurance test of two hours proposed by the European Aviation Safety Agency (EASA) has been made on a controlled and monitored CMD 22 engine for comparing the experimentally measured MAP and MAF with the predicted ones by the FNNs. The results demonstrate the suitability of the proposed approach for sensor redundancy purposes in SI engines to increase their reliability.</div>

Continuous Glucose Monitoring by Insulin-Treated Pilots Flying Commercial Aircraft Within the ARA.MED.330 Diabetes Protocol: A Preliminary Feasibility Study.

Background and Aims: A preliminary study compared the use of continuous glucose monitoring (CGM) with the use of self-monitored blood glucose (SMBG) by aircraft pilots with insulin-treated diabetes in the United Kingdom, Ireland, and Austria, certified to fly commercial aircraft within the European Aviation Safety Agency ARA.MED.330 protocol. Methods: SMBG and simultaneous interstitial glucose measurements using CGM (Dexcom G6®) were recorded during pre- and in-flight periods. Results: Eight male pilots (seven with type 1 diabetes and one with type 3c diabetes), median age of 48.5 years and median diabetes duration of 11.5 years, participated. The correlation coefficient (R) between 874 contemporaneously recorded SMBG and CGM values was 0.843, P < 0.001. The mean glucose concentration was 8.78 mmol/L (standard deviation [SD] 0.67) using SMBG compared with 8.71 mmol/L (SD 0.85) recorded using CGM. The mean absolute relative difference was 9.39% (SD 3.12). Conclusions: CGM using Dexcom G6 systems is a credible alternative to SMBG for monitoring glucose levels when insulin-treated pilots fly commercial aircraft. The study was registered with Clinical Trials.gov NCT04395378.

Impact of Drone Regulations on Drone Use in Geospatial Applications and Research: Focus on Visual Range Conditions, Geofencing and Privacy Considerations

The European Aviation Safety Agency (EASA) laid down the new EU drone regulations in December 2020, which are seen as a development step towards enabling a reliable legal framework for drone operation and use. At the same time, it is still not clear how the new rules will influence drone usage in various drone-based applications and sectors. Therefore, the paper aims to discuss and analyse how recent rules may influence drone use and affect its economic viability with the focus on the geospatial sector. The discussion of rules’ impact is achieved based on three key items: visual range limitations, geofencing systems (virtual geographic boundary around specific areas of interest) and, finally, the effect of privacy considerations. To enrich the discussion and get more insight into rules’ impact, important issues from different technical and economic aspects were distributed in a questionnaire to collect data from participants who are actively developing or using the drone technology. The questionnaire results revealed that the majority of participants (75%) were of the opinion that it is somehow difficult to judge how the new regulations will help/hinder the drone use at least in the current stage of rules implementation. In addition, there is a tendency in conducting drone flights under visual line of sight conditions even if there are difficulties in keeping a continuous contact with the drone during flight operations. Finally, the results pointed out that 44% of participants faced problems with privacy issues that affected their flight missions, and as a consequence some of the projects even got cancelled.

Performance and Weight Parameters Calculation for Hydrogen- and Battery-Powered Aircraft Concepts

This article describes the creation of a program that would be useful for calculating mathematical models in order to estimate the weight of aircraft components. Using several parameters, it can calculate other parameters of civil transport aircraft powered by batteries or fuel cells. The main goals of this research were to add the missing dimensions and parameters to the aircraft database, create a simple but effective program for creating mathematical models, and use this program to find technological barriers to battery or hydrogen fuel-cell-powered aircraft concepts. The article introduces the reader to the problem of calculating OEW (operating empty weight) using Breguet–Leduc equations. A calculation model was created for OEW calculation. The result of this work is the verification of a mathematical model for battery-powered electric aircraft of the CS-23 (European Aviation Safety Agency Certification Specification for Normal, Utility, Aerobatic, and Commuter Category Aeroplanes) category by comparing the program’s outputs with real aircraft. Subsequently, the results of mathematical models are shown in graphs that specify the space of possible concepts of aircraft powered by batteries or fuel cells, sorted by the number of passengers and the range of the aircraft, delimited by two or three criteria, respectively.

Use of Low-Power Unmanned Aerial Vehicles for Control of an Urbanized Area

The article presents an analysis of the current classification of unmanned aerial systems according to the European Aviation Safety Agency related to the use of unmanned aerial vehicles for urban area monitoring. The possible tasks solved by unmanned aerial vehicles in an urbanized area were investigated. An analysis of the crisis events - floods, fires and landslides in the Pleven region of the Republic of Bulgaria for the period from 2010 to 2020 was made and a model for the use of unmanned aircraft was proposed.

The Effectiveness of the Global Governance of the EU through EASA in its Grounding Boeing 737 MAX Decision on Member Countries

This paper will discuss the effectiveness of the European Union (EU) within the framework of global governance to recommend a grounding policy for Boeing 737 MAX 8 to countries that are members of the European Aviation Safety Agency (EASA). Through the EU's global governance approach, this paper will fully elaborate on the domino effect of the recommendations on member countries. Previously, we will discuss the background, the regional governance currently underway in the EU, the chronology of the incident of the accident of two airlines B737-8 aircraft that are outside of EASA and the EASA response in the form of US product grounding recommendations, and then the state response member countries against EASA recommendations. So, in the end, it can be concluded that EASA gets 50 percent effectiveness because the distance between the event and the recommendations issued is considered too hasty so the joining of member countries with EU attitudes generally does not run simultaneously. The importance of this research is to try to test the effectiveness of regional organizations in administering governance through agencies that stand under it.

Effect of Testing Conditions, Gauge, and Temper on Stress Corrosion Cracking of AA7xxx Aluminum Aerospace Plate Alloys

The European Aviation Safety Agency’s recent safety information bulletin (SIB 2018-04R2) describes a brittle intergranular cracking phenomenon in 7xxx aluminum alloys and recommends testing conditions. These testing conditions are severe compared with expectations regarding, temperature, humidity, and stress in aerostructures. In this study, strong increases in time to failure of smooth specimens tested in humid air were observed when reducing either temperature or stress to levels closer to what is representative of in-service conditions. The cracking morphologies after testing in hot, humid air were identical to those described in the literature for in-service occurrences of stress corrosion cracking (SCC), including the observation of crack arrest markings consistent with a mechanism of alternate local corrosion and crack propagation by hydrogen embrittlement. The differences between such fracture surfaces and those observed in the industry standard SCC screening test, which uses a chloride-containing solution to accelerate initiation and propagation, can be attributed to the pitting of the crack surface in a chloride-containing solution in the wake of the propagating crack. The performances of 7xxx-T7 aluminum plates SCC testing in either hot, humid air or a chloride-containing aqueous solution have been compared as a function of thickness, over-aging treatment, and composition. There is a strong effect of plate thickness in both tests, with substantial decreases in initiation time and lifetime for thinner plates. The effect of plate gauge is such that “legacy” materials (such as 7010-T7651, 7050-T7651, and 7050-T7451) passing the SIB 2018-04R2 test at high thicknesses, fail at lower gauges, yet have been flying for nearly 50 y. An increase in SCC performance with increased overaging is observed in both tests. As a consequence, comparisons of SCC performance of alloy compositions should be made wherever possible at identical plate thickness and for aging treatments that result in comparable strengths. When this is done, high Zn concentration 7449-T76++ (7449-T7651 with additional aging) shows a slightly worse strength-SCC balance than 7010-T7651 and 7050-T7651. The observed trends in SCC performance in the two tests are consistent, suggesting that similar repeated initiation and propagation mechanisms are responsible for cracking in humid air and in aqueous NaCl environments.

Development of an Organisational Certification Process for Specific Category Drone Operations

To govern and ensure the safety of increasing drone operations, the European Aviation Safety Agency (EASA) has defined three risk-based categories of unmanned aircraft system (UAS) operations. A large part of commercial UAS operations fall into the Specific category, which includes operations with medium risk that require an authority approval. One possible way to gain approval for these operations is the light UAS operator certificate (LUC) awarded by a national aviation authority. It offers organisations the privilege to assess and approve operations without applying for authorisation from an authority. However, only general information regarding the LUC is available in the European regulatory publications. Thus, there is currently a lack of detailed guidelines and practical information about the process and requirements for acquiring LUC status. This paper describes the development of a LUC application process model following a design science research approach. The model supports organisations to assess their LUC capabilities, develop their organisation, create the documentation to fulfil relevant requirements, and to apply for the certificate. Finally, the results of a case study where the process model was applied are presented.

Exploring Design Options for Wing Leading Edge Against Bird Strike

This study investigates the effects of bird strike on the wing leading edge of a trainer aircraft in accordance with the European Aviation Safety Agency’s CS-23 standards (“Normal, Utility, Aerobatic and Commuter Aeroplanes,” Certification Specifications, Part 23, Occupant Physical Environment), and it compares various options for the design of energy-absorbing support structures. In this study, the bird model with hemispherical-ended cylindrical geometry is simulated using the smoothed particle hydrodynamics finite element approach. After validating the impact of the bird model on a rigid plate, a bird strike on the wing leading edge is modeled; and the results are compared with the existing experimental and simulation data available in the literature. Finally, different design options for the support structure configurations of the wing leading edge (including traditional rib design, honeycomb sandwich, triangular reinforcement, and negative Poisson ratio structures) are evaluated, and the results are compared. It is found that a honeycomb sandwich panel support structure provides the best collision and weight performance.

Design advancements for an integrated mission management system for small air transport vehicles in the COAST project

PurposeThis paper aims to describe the activities that are ongoing, in the Cost Optimized Avionics SysTem (COAST) project, to design an integrated mission management system (IIMS) to be used as support to the pilot and/or to act as a backup in case of pilot incapacitation onboard on small air transport (SAT) vehicles, under single-pilot operations.Design/methodology/approachThe COAST project, funded by Clean Sky 2 programme, is developing enabling technologies for single-pilot operations in the European Aviation Safety Agency CS-23 category vehicles. Such technologies include specific tools that are designed as individual enablers for single-pilot operations and specifically address: the real-time support to pilot’s decision making in maintaining the vehicle self-separation (this technology is the tactical separation system [TSS]); the real-time support to pilot’s situational awareness about observed and forecasted weather conditions (this technology is the advanced weather awareness system [AWAS]); and the real-time management of emergency conditions due to pilot’s incapacitation under single-pilot operations (this technology is the flight reconfiguration system [FRS]). Based on the outcomes of the design activities of such individual tools, in the COAST project emerged the opportunity to proceed with the design of a further system, leveraging the individual tools and benefitting from their integration.FindingsThe IMMS design started in the year 2020 and the activities carried out up to mid-2021 allowed to define the concept of operations of the system, its high-level requirements (functional, interface and operational requirements) and the preliminary system architecture.Originality/valueThe IMMS contributes enabling the implementation of single-pilot operations in CS-23 category vehicles, thanks to the possibility to support, in normal operational conditions, the pilot’s decision-making and, in emergency conditions due to pilot’s incapacitation, the automatic flight management up to the safe destination.

State flight safety of civil aircraft

The article is devoted to the study of the system of state regulation and management of flight safety, the definition of the subjects of such activities. The research methodology is based on the methods of documentary analysis and synthesis, comparative analysis, objective truth, which allows to systematically trace the impact of legal regulation in the field of air transport. As a result, it was stated that state regulation is an important component in ensuring the safety of flights of civil aircraft. With proper legal regulation, a high level of aircraft safety will be ensured. The state policy of ensuring the safety of aircraft in civil aviation is a set of goals, objectives, priorities, principles, strategic programs and planned measures developed and implemented by public authorities, which allows the state to achieve its goals in the aviation industry, using legal, economic, administrative and other methods and means of influence, based on available resources. The peculiarity of this public policy is that, first, it is closely linked to both foreign and domestic processes in the country; secondly, has a great influence on the development of all socio-economic&#x0D; relations; thirdly, it is provided by a system of public administration bodies headed by the head of state; fourth, it is quite dynamic and costly; fifth, it needs constant control and adjustment by the state. State regulation of flight safety of civil aircraft consists in the formation of state policy and development strategy, defining tasks, functions, conditions of state bodies and use of Ukrainian airspace, application of aviation security measures, adoption of mandatory aviation rules of Ukraine, state control over their implementation and establishing responsibility for their violation. Analysis of flight safety and aviation statistics in recent publications and studies.&#x0D; The results of the analysis of statistical data on aviation events that have occurred over the past six years indicate a significant deterioration in flight safety during aviation operations, both in absolute and relative accident rates.&#x0D; To increase the level of flight safety, public authorities and aviation entities should take effective measures to implement a safety management system in accordance with the requirements of ICAO, the European Aviation Safety Agency and the European Organization for the Safety of Air Navigation (Eurocontrol) [4, с. 117].

АНАЛІЗ ВІДПОВІДНОСТІ РЕГУЛЮВАННЯ ДІЯЛЬНОСТІ ПОВІТРЯНОГО ТРАНСПОРТУ УКРАЇНИ ВИМОГАМ ЄВРОПЕЙСЬКОГО СОЮЗУ ДО КРАЇН – КАНДИДАТІВ

The article is devoted to the analysis of the conformity of the regulation of air transport activities of Ukraine with the requirements of the European Union to the candidate countries and the determination of priorities for the development of Ukraine in the field of civil aviation. Systematization of the questionnaire made it possible to determine its general and profile content blocks: air transportation; airport management; provision of air navigation services; aviation insurance; aviation security; aviation security; ensuring environmental friendliness of air transport activities; participation in international activities; social protection of aviation personnel; administrative capacity of air transport. A meaningful analysis of the profile blocks shows the positive dynamics of bringing the requirements for flight operation in the civil aviation of Ukraine into compliance with the international requirements for aviation safety, the introduction of appropriate procedures for Ukrainian aviation enterprises and objects of aviation activity by incorporating the relevant directives and regulations of the European Union into the Air Code, Aviation Rules of Ukraine and other regulatory documents. The latter allowed Ukrainian air carriers that have a valid operator's certificate, issued in accordance with the requirements and procedures for flight operation in civil aviation, approved by the State Aviation Service of Ukraine, to continue unhindered passenger and cargo flights, including in EU countries, under martial law conditions and bans on the use of Ukrainian airspace by civil aircraft. A conclusion was drawn on the expediency of ensuring the further development, adoption and implementation of aviation rules of Ukraine in accordance with the standards and recommended practice of the International Civil Aviation Organization, regulations of the International Air Transport Association, the European Association for the Safety of Air Navigation ("Eurocontrol"), the European Aviation Safety Agency, others international aviation organizations and taking into account the legislation of the European Union in the field of civil aviation.

ВОЗДЕЙСТВИЕ ВУЛКАНИЧЕСКОГО ПЕПЛА НА АВИАЦИОННЫЕ ГАЗОТУРБИННЫЕ ДВИГАТЕЛИ

Volcanic ash clouds emitted into the Earth’s atmosphere by more than a thousand active volcanoes pose an immediate se-rious threat to flight safety, since volcanic ash particles in high concentrations can cause significant damage to aircraft. This article presents the consequences of an aircraft getting into a cloud of volcanic ash (damage to the fuselage and aer-odynamic surfaces of the aircraft, turbojet sustainer engines, antennas, air pressure and temperature receivers, other aircraft sys-tems), and also describes in detail the mechanisms and examples of the impact of volcanic ash on various types aircraft gas tur-bine engines. The global statistics of aircraft hitting volcanic ash clouds from 1935 to 2021 is given. The results of engineering tests of PW F100 bypass gas turbine engines under the influence of volcanic ash in the condi-tions of the scientific and CalspanTechnical Corporation, founded in 1943 in the United States of America, are considered. Also presented are the results of work under the VIPR (Vehicle Integrated Propulsion Research) program of the National Aerospace Agency of the United States of America (NASA) for a comprehensive study of the impact of volcanic ash on the F-117 (PW2040) power plant of the Boeing C-17 Globemaster III military transport aircraft. The results of research by the NASA national agency and the Calspan Corporation are compared with the main data of certification tests of the advanced PD-14 aircraft gas turbine engine developed by JSC «UEC-Aviadvigatel» in the conditions of the closed ground test facility Ts-17T of the FAA «CIAM named after P.I. Baranov» in accordance with the requirements of the European Aviation Safety Agency (EASA).

A carbon dioxide detector fabrication with screen printing technique for use in airplanes

Purpose From the beginning of aviation history, fire has been a serious problem for aircrafts. The purpose of this study is to provide a reference document on current risks and proposed reductions for smoke and fire incidents in commercial transport aircrafts. For this purpose, metal oxide carbon dioxide (CO2) detector was produced with the screen printing technique to detect CO2 and carbon monoxide gases from the sensors required to observe the occurrence of fire that may occur in the aircraft and to take the necessary steps to control it. Design/methodology/approach The screen printing technique was used as the gas sensor production technique for the produced sensor and tin oxide was used as the metal oxide in the produced samples. The samples produced were examined under the gases with specified gas detecting properties, and it was concluded that they can be used simultaneously with smoke detectors to increase the detection reliability and decrease the alarm time with the smoke detectors currently used in today's passenger aircrafts. Findings When the electrical characteristics of the sensor made were examined, it was observed that it meets the requirements of the Federal Aviation Administration and European Aviation Safety Agency standards (the fire should be detected within 1 min), and the false alarm situation experienced in the smoke sensors used today can be eliminated. Originality/value There is no other sensor than the smoke detectors that are used for fire detection in cargo section, lavatories and avionic compartment on aircrafts. With this study, the gas detecting feature of the produced samples was examined under the specified gases, and it was concluded that they can be used simultaneously with smoke detectors to increase detection reliability and decrease alarm time as compared to with the smoke detectors currently used in today's passenger aircrafts.

Dynamic Mechanics of Rigid Helicopter Systems During Ditching

Aircraft and helicopter often fly above open waters and thus have to observe regulations to ensure safe water landing under emergency conditions. This practice is also referred to as ditching - one of several types of slamming problems that are under review by the current regulations of the Federal Aviation Administration (FAA) and the European Aviation Safety Agency (EASA). Ditching is related to the controlled landing on water, with distinctive features such as hydrodynamic slamming loads, complex hydromechanics at tremendous forward speeds, as well as the interaction of multiphase fluid dynamics (air, water, and vapor). This paper presents the knowledge on system mechanics during helicopter ditching. The discussion begins with the fundamental kinetics of the rigid body, and then delves into dynamic relations to describe the effect of forces on motions. In the end, the paper discusses several relevant theories to further contribute to the understanding of the problem of impact.

Gust load alleviation on an aircraft wing by trailing edge Circulation Control

This paper reports an investigation of gust load alleviation using Circulation Control for a three-dimensional wing including aerodynamic and structure interaction. The Field Velocity Method is introduced to the unsteady Reynolds averaged Navier–Stokes solutions for gust response simulations. Structural dynamic equations of motion are coupled with the unsteady Reynolds averaged Navier–Stokes solutions to consider the aeroelastic effects due to the gust response. The effects of gust load alleviation on the BAH wing using Circulation Control are tested under typical ‘one-minus-cosine’ gust profiles from certification specification defined by European Aviation Safety Agency. The results show a promising capability of Circulation Control for gust load alleviation as significant gust load alleviation effects have been achieved for both the rigid and elastic BAH wings in the test cases. For the BAH wing considering aeroelasticity, the displacement oscillations induced by gusts have been effectively suppressed by Circulation Control. The results also show that Circulation Control has the fast frequency response characteristics, where more than 50% of the total change in lift coefficient can be obtained within the non-dimensional time s =U∞tc¯=1.

Departure Passenger Flow Simulation: Case Study on Izmir Adnan Menderes Airport Pre and Post COVID-19

The flow of departing passengers from the airport inside the terminal is affected by strategic and tactical decisions of airport operation teams. The decisions made by the managers regarding opening and closing times of check-in, boarding, and gates are critical to optimize the performance of the terminal operation. In this research, Izmir Adnan Menderes Airport was taken as a use case.Departure terminal building of check-in, security control, and boarding gates was taken as the focus entities.The simulation passenger input data were produced for check-in, security, and boarding gates using different distribution probability methodologies to match the actual data. Three days of data (300 flights, 3 thousand passengers) has been derived with the help of a custom generator. A unique simulation tool called Departure Passenger Flow Simulator (DPFs) has been developed for research. Due to manage passenger flow pre and post COVID-19, the opening and closing times of assets (check-in and gates) were simulated in 6 iterations in DPFs in 3 different scenarios. As a result of the research, it was understood that the resources for Izmir Adnan Menderes Airport were sufficient, considering the COVID-19 measures published by the European Aviation Safety Agency (EASA) and the General Directorate of Civil Aviation.