• Led the Fatigue Assessment of the Wingbox Spars in support of the Serial and Retrofit Spar Modification activities. Directed the work of others in order to meet program deadlines and presented during the PDR and CDR meetings to the Design Review Panel.• Performed Rib sizing analysis of castellations, cutouts, spar attachments and flap attachments in support of the Rib Foot Serial Modification.• Diagrammed the Rib Foot Spectrum Analysis Tool through the list of associated tools and modified certain retrofit analysis tools for their specific use on the Rib Foot Serial Modification.• Coordinated with a variety of the Test Community at Airbus on the development of a test to review the preliminary design solution to a group of damages found on the Fatigue Test Article (EF).• Worked with suppliers, internal FEM & Static groups and A380 Filton team to provide technical and project support on A380 EF Modification, Serial Rib Foot Modification, Spar Modification and other associated tasks.

• Assembled the detailed system requirements of the Boom Control System (BCS) to determine the viability of the current hardware configuration.• Coordinated with the Seattle Boom Controls Team, St. Louis Actuator Software Team, and Wichita Software/Systems Team working on the BCS to find potential solutions to hardware deficiencies.• Requested by name to serve as a liaison between the Boeing Wichita Controls Groups and multiple divisions within the company.• Converted a legacy PSIM model of a 747-200 in FORTRAN to C++ for use in the first full flight regime six Degree of Freedom (DOF) aircraft simulation for the VC-25A and E-4B aircraft.• Researched available hardware performance and requirements documentation, created Simulink models of the controls loops, and recorded simulated flight conditions to validate the implementation of the flight dynamics for the VC-25A.• Created forward instrument panels with operational avionics in an object oriented software environment tied into a legacy full flight regime six DOF aircraft simulation for VC-25A, B-52, E-4B, and KC-135 to simulate existing and modified cockpit layouts for customer feedback on development programs.• Assembled an interface between the B-52 six DOF aircraft simulation and the Multi-Mode Radar Simulation (MMRS) to support the business development efforts for replacing the current B-52 radar with a modern radar system.• Developed flight guidance application control laws and mode logic for coupling auto-throttle, pitch autopilot, and roll autopilot to modified Flight Management Computer System (FMCS) for Lateral Navigation (LNAV) roll steering and Vertical Navigation (VNAV) Airspeed/Mach, Altitude, and Vertical Speed Targets for VC-25A Avionics Modernization Program (AMP).• Regularly briefed and demonstrated simulations to senior Boeing and Government officials to support various development programs initiatives for B-52, VC-25A, and etc.

• Completed stress analysis in detailed sizing of primary metallic structure, lugs, mechanisms and fittings.• Performed crack growth analysis for the latest Durability and Damage Tolerance Assessment (DADTA).• Developed growth factors to support the Economic Life Details for the Service Life Extension study.• Created a Damage Tolerance Analysis document of the replacement engine strut for Airworthiness Certification Analysis.• Evaluated structure for crack propagation and corrosion with use of Non-Destructive Inspection (NDI) Techniques.• Managed a teardown of potential hotspots on aircraft structure and used that information to be feed back into the DADTA, general maintenance and inspects of the structure.• Provided support on technical inquires for Aircraft on Ground (AOG) ranging from disassembly plans for replacement of parts to one time flight repairs.• Created site training curriculum on Introduction to Stress Analysis Tools for new hires.• Collaborated with the Subject Matter Experts (SME) to present the computing applications used at the Boeing Wichita site.