*G- Complex Shear Modulus η- Loss Factor

D – Distance between neutral axis of host structure and composite system sE, vE, cE- Elastic modulus of structure, viscoelastic material, and constraining layer, respectively sh, vh, ch- Thickness of structure, viscoelastic layer, and constraining layer, respectively vg- Shear parameter nC- Rao correction factor ξ- Beam eigenvalue)(xYr- Cantilever beam mode shape dW- Energy dissipated by viscoelastic material U- Max strain energy of viscoelastic material Aircraft design represents an optimization of structures and aerodynamics to meet weight, strength and reliability constraints. Included in this optimization is the landing gear system, which typically accounts for 3 – 7 % of the total aircraft weight. For fixed gear designs, a significant amount of the total drag can be attributed to the landing gear, and so both reduction in weight and drag are priorities when designing a landing syster. The use of constrained layer visco-elastic damping on landing gear structural members is a new application since historic use of constrained layer damping has been found on thin plate-like structures. Benefits of low weight and low drag are achievable using the conformal treatment, and this paper investigates specific constrained layer damping applications for cantilever-loaded spring steel landing gear. Achievable damping levels are examined for a 386 lb. aircraft using available damping materials that have been tested to quantify loss factor. Results of the analysis show optimal constrained layer thicknesses for a variety of materials. Weight and aerodynamic drag are quantified for the landing gear with the damping treatment installed