Abstract: A fastening system having differentiable components includes a first bushing with a first mating feature to be inserted within a first receiver. A first fuse pin with a second mating figure and being configured to shear upon the application of a first predetermined load is configured to be inserted into the first receiver and mate with the first mating feature of the first bushing. The first and second mating features correspond and permit the insertion of the first fuse pin into the first bushing within the first receiver to selectively connect components. The first bushing may prevent the complete insertion of a second fuse pin having a third mating feature into the first receiver. A second bushing having a fourth mating feature may permit the complete insertion of the second fuse pin into the second bushing positioned within a second receiver.

Abstract: A fastening system having differentiable components includes a first fuse pin with a first mating figure and being configured to shear upon the application of a first predetermined load and a first receiver with a second mating feature. The first and second mating features correspond and permit the insertion of the first fuse pin into the first receiver to selectively connect components. The system may include a second fuse pin having a third mating feature and being configured to shear upon the application of a second predetermined load, which may differ from the first predetermined load. The second fuse pin having a third mating feature that prevents the insertion of the second fuse pin into the first receiver. The first fuse pin may be configured to connect together components of a first aircraft and the second fuse pin may be configured to connect together components of a different aircraft.

Abstract: A fastening system having differentiable components includes a first bushing with a first mating feature to be inserted within a first receiver. A first fuse pin with a second mating figure and being configured to shear upon the application of a first predetermined load is configured to be inserted into the first receiver and mate with the first mating feature of the first bushing. The first and second mating features correspond and permit the insertion of the first fuse pin into the first bushing within the first receiver to selectively connect components. The first bushing may prevent the complete insertion of a second fuse pin having a third mating feature into the first receiver. A second bushing having a fourth mating feature may permit the complete insertion of the second fuse pin into the second bushing positioned within a second receiver.

Abstract: A fastening system having differentiable components includes a first bushing with a first mating feature to be inserted within a first receiver. A first fuse pin with a second mating figure and being configured to shear upon the application of a first predetermined load is configured to be inserted into the first receiver and mate with the first mating feature of the first bushing. The first and second mating features correspond and permit the insertion of the first fuse pin into the first bushing within the first receiver to selectively connect components. The first bushing may prevent the complete insertion of a second fuse pin having a third mating feature into the first receiver. A second bushing having a fourth mating feature may permit the complete insertion of the second fuse pin into the second bushing positioned within a second receiver.

Abstract: An example apparatus includes a wall having an opening and a panel attached to the wall over the opening. The panel includes a shape-memory material (SMM). An example method includes bending the panel away from the wall via the panel at least partially changing from a first crystal phase to a second crystal phase. The panel bends away from the wall in response to a temperature of the panel increasing. The method further includes bending the panel toward the wall via the panel at least partially changing from the second crystal phase to the first crystal phase. The panel bends toward the wall in response to the temperature of the panel decreasing.

Abstract: A fastening system having differentiable components includes a first bushing with a first mating feature to be inserted within a first receiver. A first fuse pin with a second mating figure and being configured to shear upon the application of a first predetermined load is configured to be inserted into the first receiver and mate with the first mating feature of the first bushing. The first and second mating features correspond and permit the insertion of the first fuse pin into the first bushing within the first receiver to selectively connect components. The first bushing may prevent the complete insertion of a second fuse pin having a third mating feature into the first receiver. A second bushing having a fourth mating feature may permit the complete insertion of the second fuse pin into the second bushing positioned within a second receiver.

Abstract: A fastening system having differentiable components includes a first fuse pin with a first mating figure and being configured to shear upon the application of a first predetermined load and a first receiver with a second mating feature. The first and second mating features correspond and permit the insertion of the first fuse pin into the first receiver to selectively connect components. The system may include a second fuse pin having a third mating feature and being configured to shear upon the application of a second predetermined load, which may differ from the first predetermined load. The second fuse pin having a third mating feature that prevents the insertion of the second fuse pin into the first receiver. The first fuse pin may be configured to connect together components of a first aircraft and the second fuse pin may be configured to connect together components of a different aircraft.

Abstract: A rigging for moving an aircraft panel relative to an aircraft substructure includes a retaining base attached to a panel interior, and a slider rod held in contact with the substructure and adjustably engaged with the retaining base. The slider rod is manipulable from the panel exterior to adjustably engage the panel in a rigging position along a fair axis. The slider rod may include a tool appurtenance captively positioned within the riser bore that is exteriorly manipulable through a panel access port. Tool appurtenance manipulation may actuate the slider rod to adjustably engage the support hub and to move the panel into the fair position. A fit plate may be attached to the aircraft panel disposed intermediate to the retaining base, and may be adjustably attached to the aircraft panel for moving the aircraft panel into a fit position in a rigging plane.

Abstract: Apparatuses and methods for joining structural members. In one embodiment, an apparatus for joining a first member to a second member includes a first part and a second part configured to be engaged with and bonded to the first part. In one aspect of this embodiment, the first part includes a first surface facing a first direction, a second surface facing a second direction different than the first direction, a first recess at least proximate to the first surface, and a second recess at least proximate to the second surface. In another aspect of this embodiment, the second part includes a third surface facing a third direction, a fourth surface facing a fourth direction different than the third direction, a first protuberance at least proximate to the third surface, and a second protuberance at least proximate to the fourth surface.

Abstract: A rigging for moving an aircraft panel relative to an aircraft substructure includes a retaining base attached to a panel interior, and a slider rod held in contact with the substructure and adjustably engaged with the retaining base. The slider rod is manipulable from the panel exterior to adjustably engage the panel in a rigging position along a fair axis. The slider rod may include a tool appurtenance captively positioned within the riser bore that is exteriorly manipulable through a panel access port. Tool appurtenance manipulation may actuate the slider rod to adjustably engage the support hub and to move the panel into the fair position. A fit plate may be attached to the aircraft panel disposed intermediate to the retaining base, and may be adjustably attached to the aircraft panel for moving the aircraft panel into a fit position in a rigging plane.

Abstract: Apparatuses and methods for joining structural members. In one embodiment, an apparatus for joining a first member to a second member includes a first part and a second part configured to be engaged with and bonded to the first part. In one aspect of this embodiment, the first part includes a first surface facing a first direction, a second surface facing a second direction different than the first direction, a first recess at least proximate to the first surface, and a second recess at least proximate to the second surface. In another aspect of this embodiment, the second part includes a third surface facing a third direction, a fourth surface facing a fourth direction different than the third direction, a first protuberance at least proximate to the third surface, and a second protuberance at least proximate to the fourth surface.

Abstract: Apparatuses and methods for joining structural members. In one embodiment, an apparatus for joining a first member to a second member includes a first part and a second part configured to be engaged with and bonded to the first part. In one aspect of this embodiment, the first part includes a first surface facing a first direction, a second surface facing a second direction different than the first direction, a first recess at least proximate to the first surface, and a second recess at least proximate to the second surface. In another aspect of this embodiment, the second part includes a third surface facing a third direction, a fourth surface facing a fourth direction different than the third direction, a first protuberance at least proximate to the third surface, and a second protuberance at least proximate to the fourth surface.