Abstract: A composite lug assembly includes a composite lug defining a loaded side and an unloaded side and having at least one hole extending therebetween, a shoulder bushing assembly including a first side bushing having a first cylindrical portion adapted to fit in the hole and a first shoulder portion extending from the first cylindrical portion and a second side bushing having a second cylindrical portion adapted to fit within the first cylindrical portion and a second shoulder portion extending from the second cylindrical portion wherein the first side bushing is made of a different material than the second side bushing.

Abstract: A composite lug assembly includes a composite lug defining a loaded side and an unloaded side and having at least one hole extending therebetween, a shoulder bushing assembly including a first side bushing having a first cylindrical portion adapted to fit in the hole and a first shoulder portion extending from the first cylindrical portion and a second side bushing having a second cylindrical portion adapted to fit within the first cylindrical portion and a second shoulder portion extending from the second cylindrical portion wherein the first side bushing is made of a different material than the second side bushing.

Abstract: An assemblage for bonding the skin of an airfoil to the core of the airfoil includes a hybrid caul plate assembly for covering the surface of the airfoil assembly which is exposed to bonding pressure. The hybrid caul plate includes a central elastomeric component and peripheral semi-rigid metal components. The semi-rigid metal components are formed from a steel sinusoidal mesh and are axially elongated. The mesh is flexible in the direction of elongation, but are rigid in the transverse direction. The peripheral semi-rigid caul componnents will thus closely conform to the contours of the core in the axial direction, and will, at the same time, provide support for the edges of the core so that the core edges will not be crushed or deformed by bonding pressure applied to the assemblage during the skin-to-core bonding process. The result of using the hybrid caul plate assembly is an improved skin-to-core bond wherein bridging or voids in the bond line at the periphery of the airfoil are avoided.

Abstract: The described embodiment of an edge-of-part (EOP) scribe device is operative to simultaneously scribe opposed trim lines in an oversized, cured leading-edge sheath mounted on a sheath mold assembly. The EOP scribe device includes a primary carriage assembly having rollers secured thereto wherein the primary carriage assembly is translatable along side rails secured to the sheath mold assembly, opposed pairs of guide rails affixed to the primary carriage assembly, and a secondary carriage assembly mounted in movable combination with each pair of guide rails. Each secondary carriage assembly includes a spring-loaded scribe head for inscribing a trim line in the cured leading-edge sheath, a rigid follower linkage secured to the secondary carriage assembly, and a follower slide roller mounted in rotatable combination with the rigid follower linkage and operative to rotatably engage a trim line template mounted on the sheath mold assembly.