Abstract: A composite component may be coupled to an aluminum component with a plurality of fasteners. An expansion strap may be located between the composite component and the aluminum component. The expansion strap may have a coefficient of thermal expansion which is greater than the coefficient of thermal expansion of the composite component, and less than the coefficient of thermal expansion of the aluminum component. A first set of fasteners may be inserted through the composite component, the expansion strap, and the aluminum component. A second set of fasteners may be inserted through the composite component and the expansion strap. The expansion strap may decrease stress in the composite component at the fastener locations.

Abstract: A nacelle may include a pylon and a thrust reverser having an inner fixed structure. A locking mechanism may automatically engage and prevent relative movement between thrust reverser halves. A bumper may be coupled to the inner fixed structure. The locking mechanism may limit deflections between the thrust reverser and the pylon in response to a burst duct. A locking mechanism in the inner fixed structure may include a pressure relief door and an arrestor which hooks onto a retaining bar in a pylon bracket. The locking mechanism may allow the thrust reverser halves to be opened for access to the engine.

Abstract: Latch housing assemblies, latch hook assemblies, and latch assemblies are disclosed. Various disclosed latch housing assemblies include a latch pin coupled to an inner housing, and an outer housing having an inner surface coupled to an outer surface of the inner housing via at least one of a fuse pin and a spring. Various disclosed latch hook assemblies include a latch hook coupled to a latch housing, a weak point in the latch housing disposed between an inboard mount and an outboard mount, and a catch member mounted to the inboard mount and the outboard mount. Various disclosed latch assemblies include a latch housing, a bolt, and a deformable bushing at least partially surrounding the bolt, the deformable bushing configured to deform about a radius in response to a compressive load of about 1,000 lbf to about 3,000 lbf.

Abstract: A seal comprising a generally acorn shaped cross-sectional profile is described herein. The seal may be configured for use between two generally adjoining and/or nearly adjoining surfaces. The seal may be used to eliminate a gap or rubbing between a plurality of surfaces. The seal may have a non-circular cross-sectional interior profile.

Abstract: A thermal blanket system is provided on an aircraft component to protect the component, for example, from engine heat. The component has a latch half attached thereto, which is also covered by the thermal blanket system. In some scenarios, the latch half may need to be detached from the component because the latch was stuck closed. The thermal blanket system includes a portion thereof which overlaps the latch half and breaks away from the remainder of the thermal blanket system when the latch half is detached.

Abstract: A thermally protected attachment system is provided. A device including a cover hingeably coupled to a thermal blanket is provided. The thermal blanket and cover may be configured to insulate a cavity defined by the interior of the thermal blanket and the cover in response to the cover being in a closed position. The thermal blanket may be coupled to a thermal protection panel of an aircraft.