Structure Integration Manager- in charge of A380 full-scale fatigue test tear-down activities- in charge of recurring cost reduction project in structure perimeter- A380 Central Program interface with R&T structure-wise

Missions- Act as single point of contact between A380 FAL and all MAP (Production Support Engineering) transnational teams for a/c in St40/32/31- Set-up and lead a 3 years transnational and musltiskill project, aiming at solving structure issues encountered in station 40 (major components assembly) to secure the production ramp-up (Operational management of a trans-national team of 40 multidisciplinary engineers, reporting to Head of FAL MAP and A380 Chief Engineering organization)- Provide leadership across all MAP teams (fuselage, wing, HTP/VTP, powerplant, landing gears) in finding the optimum solutions to structure or components installation related issues.- Identify design deficiencies leading to increase FAL workload and drive MAP to find solutions through DQN (Design Query Note)- Manage concessions drumbeating and time-to-answer to be in line with commitments towards FAL- Ensure Safety on stations for MAP representativesMain results- Key bottelnecks takled, leading to 2 M€ recurring costs saving per year.

Missions- Manage all R&T Transverse / Non specific structure activities (NDT/Structure Health Monitoring, assembly technologies (bonding, welding, fastening), repairs, upstream technologies)- Patent interface between Structure Research and IP departmentsDimensions- Portfolio : 2 to 3 M€/year- Team : up to 12 people (S/C included)

Mission- Set-up, lead and manage internally or externally funded multinational research projects (Project organization : WBS, Gantt, management rules and communication channels, management of working groups in a non-hierarchical manner)- Maximize external funding through negotiations with external partners (universities, test labs, research organizations, SME's and industrial partners) and funding parties- Accountable for TCQ : planning, budget monotoring, risk analysis, reporting, quality (KPI )Main projects- MAAXIMUS European project (FP7): “More Affordable Aircraft through eXtended, Integrated and Mature nUmerical Sizing”Figures : 67 M€, 5 years, 57 European partnersObjectives :To set-up a multi-skill framework for design, sizing, manufacturing, assembly and test allowing, fast development and righ-first-time validation of an optimized composite fuselage.To design, size and manufacture a full-scale composite fuselage barrel made of 2 single-piece sections (A30X cross-section), automatically assembled together at SA-FAL with a crawler robot and tested up to failureWebsite : http://www.maaximus.eu/- IARCAS European project (FP5) : “Improve ans Assess Repair Capability of metallic Aircraft Structures” (2001 – 2006)Figures : 7.8 M€, 5 years, 14 European partnersObjectives :To improve current repairs, to design repairs for materials and technologies applied on A380, to extend allowable damage limits

Missions- Evaluation of new manufacturing process (welding, bonding)- Evaluation of performance of new materials (Glare, Lithium based aluminum, Mg-Sc)- Investigations of improved design concepts with respects to fatigue performance (new longitudinal and circumferential joints for fuselage)- Structural tests for down-selection of most promizing materials/technologies/design principles (test program, panel manufacturing follow-up, test management, test/analysis correlations, test reports,…)- Promotion for implementation on aircraftDevelopments- Implementation of laser beam welded stringers on A318 and A380, including all development tests for certification prior implementation on aircraft (materials, processes, calculation methods, trade-off studies, support to certification and SRM)- Implementation of Glare material on A380- Fuselage clips shape optimization for A380F

Missions- Extensive use of Finite Element softwares, especially for non-linear analyses wrt static, Fatigue and damage tolerance- Structural tests for advanced design concepts and sizing approaches validation for fatigue crack initiation, crack propagation and residual strength in bolted joints and fuselage/wing stiffened panels (test program, panel manufacturing follow-up, test management, test/analysis correlations, test reports,…)Specific developments- Fatigue and Damage Tolerance guidelines in the Large Aircraft Division (LAD)(ie : Large Damage Capability, Initial Flaw Concept, F&DT of welded and Glare panels)- Main LGB pre-sizing for materials and technology down-selection (welding of lateral panels)- Fuselage shells sizing with respect to fatigue (A380 Large Damage Capability, A350 Aluminium-Lithium fuselage shell pre-sizing and minimum thickness requirements, A340-600 Fr 54 circumferential double-shear joint enhancement)- Effect of built-up stresses on fatigue behaviour of wing to fuselage root joint- Effects of defect (waves, pores) on delamination growth in composite fuselage panels