•Oversee the Static Strength, Fatigue & Damage Tolerance and Mass Properties teams responsible for the simultaneous structural development and certification of the freighter and passenger variants of the clean-sheet Cessna SkyCourier. The group is comprised of nearly 40 team members distributed among 4 direct supervisors.•Represent Structures as a member of the overall Engineering Integrated Development Team. This team is composed of all engineering disciplines, is responsible for program execution and is led by the Chief Engineer. •Allocate program resources within budget and schedule constraints including the negotiation of rates and integration of contract engineers. •Coordinate design and certification activities for a supplier-provided cargo loading system.•Oversee the development of FAA-approved structural test plans/results and conformity inspection documentation for full-scale, component-level and flight controls systems certification testing. Testing includes: full-scale fuselage, wing, empennage and landing gear; windshield bird-strike; primary and secondary flight-control systems; cargo compartment and seat support structure. Additional activities include test coordination and scheduling to meet program milestones. •Collaborate with Structures-ODA unit member colleagues on development of the structural certification plan under 14 CFR Part 23 Amdt. 64. This includes establishing the certification basis; determining appropriate ASTM means of compliance via FAA issue paper; frequent direct communication with Wichita Aircraft Certification Office Branch structures specialists to discuss correlation of Amendment 63 and 64 rules and means of compliance; and development of a highly-regarded compliance cross-reference document to facilitate the connection of Amendment 63, 64 and ASTM means of compliance.

•Provided Structural Integrity support for the Citation Hemisphere, the largest clean-sheet business jet developed to date by Textron Aviation. Activities included preliminary layout of primary airframe structure, structural aspects of fly-by-wire flight control systems, structural certification approach and schedule planning.

•Led the Static Strength analysis team responsible for structural sizing and successful certification of the Citation Latitude. The overall team was comprised of nearly 20 team members distributed among 2 direct supervisors.•Overall structural design involved the development of a new pressurized fuselage while incorporating an existing wing, empennage and landing gear.•Coordinated the program-level Structural Integrity (Acoustics, Fatigue & Damage Tolerance, Interior Structures, Static & Dynamic Loads, Static Strength, Mass Properties, Material & Processes) activities for the program. •Developed, reviewed and approved structural and system-level certification plans for 14 CFR Part 25 approval. This involved application of 21.101 change product analysis in order to retain the certification basis for non-changed elements of the structure. •Reviewed and FAA-approved static strength test plans/results and conformity inspection documentation for full-scale, component-level and flight controls systems certification testing. Testing included: full-scale fuselage, wing and empennage; bird-strike; transparencies; primary and secondary flight-control systems; interior and seat support structure. •Served as primary 14 CFR Part 25 Structural - Static Analysis FAA delegate (TC ODA Unit Member). In this role, I approved test plans/results, structural analysis documents and served as the official FAA witness for structural tests. •Coordinated structural integrity efforts related to successful EASA validation including direct communication with EASA structural specialists. Activities involved change product analysis and discussion of significant differences between FAA and EASA regulations. Prepared multiple validation documents including official responses to CRIs and CAIs.

•Led the static strength team of 3 analysts responsible for structural sizing and successful certification of the Citation Sovereign+. Overall structural design of this derivative aircraft involved the development of a new metallic winglet and subsequent reinforcement of wing structure. Overall airplane was substantiated by analysis for increased loads. •Developed structural certification plan which involved extensive 21.101 change product analysis to maintain the overall certification basis of the aircraft. •Coordinated structural integrity efforts for successful EASA validation.

•Responsible for guiding the empennage static strength sizing conducted by our supplier-partner, Spirit-UK. This involved both on-site and remote activities since our supplier-partner’s primary team was in the United Kingdom. •Sizing methods included classical hand analysis and finite-element model methods.

•Oversaw a small team of structural analysts responsible for the in-production CitationJet series (Part 23) and Sovereign (Part 25) models. •Addressed production discrepancies (i.e. MRB activity) in a timely manner to facilitate factory flow while simultaneously maintaining certification requirements and avoiding/minimizing structural inspection impacts.•Supported post-TC product improvements via focused structural sizing, certification plan development and generation of static strength certification documents.

•Performed preliminary static strength sizing for primary/secondary structural members, flight control systems and general system components.•Provided experimental and production dispositions of discrepant parts/assemblies.•Conducted development and 14 CFR Part 25 certification static strength tests on full-scale airframe, flight control systems and component test articles.•Coordinated with Durability & Damage Tolerance group on structural designs and production support dispositions.•Prepared 14 CFR Part 25 static strength certification documents for major airframe and system changes.

•Managed layout and detail wing design for Proof of Concept aircraft.•Performed sizing and detail design of monolithic primary structure that satisfied damage tolerance and failsafe requirements.•Sized and analyzed a tubular spring steel landing gear design.•Performed preliminary analysis of a concept aircraft for configuration layout, performance, and manufacturability.