A differential motion sensor for an aircraft, configured to detect a shear force, comprising: a base including a first surface extending along a first axis (X-axis) to define a length and extending along a second axis (Y-axis) to define a width, and including at least one hinge (110a, 110b) that pivots about a rotational axis extending along the second axis (Y-axis); and a cradle pivotably coupled to the at least one hinge (110a, 110b) and configured to move in a direction of the first axis (X-axis) when pivoting about the hinge (110a, 110b), wherein the differential motion sensor is configured to operate in a first mode when the cradle is aligned with the base and a second mode when the cradle is pivotably displaced with respect to the base; and further comprising at least one conductive fuse (122a, 122b) extending along a third axis (Z-axis) that is perpendicular to both the first axis (X-axis) and the second axis (Y-axis), the conductive fuse (122a, 122b) including first and second fuse portions and configured to sever at a fracture region in response to an applied shear force to the differential motion sensor induced when effecting the second mode, wherein the fracture region (132a, 132b) extends along the first axis (X-axis) such that the first and second fuse portions sever at the fracture region when the shear force applied to the differential motion sensor along the first axis (X-axis) exceeds a force threshold, and a first conductive terminal connected to the first fuse portion and a second conductive terminal connected to the second fuse portion, the first and second conductive terminals configured to deliver electrical current through the at least one conductive fuse, wherein the differential motion sensor is configured to operate in the first mode in response to the current flowing through the at least one conductive fuse and the second mode in response to fracturing the at least one conductive fuse at the fracture region such that the current does not flow through the at least one conductive fuse. a base including a first surface extending along a first axis (X-axis) to define a length and extending along a second axis (Y-axis) to define a width, and including at least one hinge (110a, 110b) that pivots about a rotational axis extending along the second axis (Y-axis); and a cradle pivotably coupled to the at least one hinge (110a, 110b) and configured to move in a direction of the first axis (X-axis) when pivoting about the hinge (110a, 110b), wherein the differential motion sensor is configured to operate in a first mode when the cradle is aligned with the base and a second mode when the cradle is pivotably displaced with respect to the base; and further comprising at least one conductive fuse (122a, 122b) extending along a third axis (Z-axis) that is perpendicular to both the first axis (X-axis) and the second axis (Y-axis), the conductive fuse (122a, 122b) including first and second fuse portions and configured to sever at a fracture region in response to an applied shear force to the differential motion sensor induced when effecting the second mode, wherein the fracture region (132a, 132b) extends along the first axis (X-axis) such that the first and second fuse portions sever at the fracture region when the shear force applied to the differential motion sensor along the first axis (X-axis) exceeds a force threshold, and a first conductive terminal connected to the first fuse portion and a second conductive terminal connected to the second fuse portion, the first and second conductive terminals configured to deliver electrical current through the at least one conductive fuse, wherein the differential motion sensor is configured to operate in the first mode in response to the current flowing through the at least one conductive fuse and the second mode in response to fracturing the at least one conductive fuse at the fracture region such that the current does not flow through the at least one conductive fuse.