will vary according to particular performance weight and cost requirements and therefore do not limit the scope of the present invention fig8 shows a side sectional view of the fan containment case 4 along the longitudinal axis of the jet engine 2 and along lines 8 8 shown in fig6 b layers 14 and 16 are applied to the fan case 4 in proximity to an air intake end of the jet engine 2 and are oriented to frame a blade containing region around the blades 6 in order to coincide with the area of the fan case 4 where point and tensile hoop loads are generated during a blade out event as shown in fig8 a third layer 18 is applied to the fan case 4 in proximity to the blade containing region as previously noted third layer 18 can be produced from a variety of materials including for example conventional frp material in order to help to carry the hoop tensile loads that accumulates during a blade out event the inventors have determined that the principal failure mode of the fan case 4 during a blade out event is a tensile failure resulting as the released blade 6 a is slowed by the fan case 4 the orientation of the associated tensile load in the fan case 4 is primarily in the radial direction as shown in fig5 by arrows 12 the tensile load resulting from the blade out event also causes a substantial hoop stress to be circumferentially generated in the fan case 4 the specifications for layer 18 will vary in accordance with the specifications for the fan case 4 as dictated for example by particular performance weight and cost requirements and therefore do not.