Abstract: Methods, apparatus, systems, and articles of manufacture are disclosed. An example locking assembly for an arresting hook system includes a track coupled to a frame of an aircraft. The track includes a forward end and an aft end opposite the forward end. The track includes a first lock positioned at the forward end and a second lock positioned at the aft end. The locking assembly includes a guide coupled to a hook shank of the arresting hook system. The guide is to move along at least a portion of the track, engage the first lock when the hook shank is in a stowed position, and bypass the second lock as the hook shank moves from the stowed position to a deployed position.

Abstract: Methods, apparatus, systems, and articles of manufacture are disclosed. An example arresting hook system for an aircraft includes a linkage assembly defining a trapeze deployment assembly of the arresting hook system, a pivot assembly to pivotally couple a hook shank to a primary pivot joint of an aft body, a vertical actuator coupled to a forward body and a frame of the aircraft to move the arresting hook system between a stowed position and an intermediate position, and a vertical damper actuator (VDA) including a cylinder and a piston. The cylinder pivotally coupled to the frame of the aircraft via a VDA pivot joint, the VDA to rotate relative to the frame of the aircraft, the piston having an end operatively coupled to the pivot assembly, the VDA to move the arresting hook system between the intermediate position and a deployed position.

Abstract: Methods, apparatus, systems, and articles of manufacture are disclosed. An example pivot assembly for use with an arresting hook includes a coupler having a first opening defining a first axis and a second opening defining a second axis, the first opening transverse relative to the second opening. A linkage arm has a body and an arm. The body includes a third opening defining a third axis. The first opening of the coupler is to receive the body of the linkage arm such that the second opening of the coupler coaxially aligns with the third opening of linkage arm. A pin extends through the second opening and the third opening to couple the coupler and the linkage arm.

Abstract: Methods, apparatus, systems, and articles of manufacture are disclosed. An example pivot assembly for use with an arresting hook includes a coupler having a first opening defining a first axis and a second opening defining a second axis, the first opening transverse relative to the second opening. A linkage arm has a body and an arm. The body includes a third opening defining a third axis. The first opening of the coupler is to receive the body of the linkage arm such that the second opening of the coupler coaxially aligns with the third opening of linkage arm. A pin extends through the second opening and the third opening to couple the coupler and the linkage arm.

Abstract: Methods, apparatus, systems, and articles of manufacture are disclosed. An example locking assembly for an arresting hook system includes a track coupled to a frame of an aircraft. The track includes a forward end and an aft end opposite the forward end. The track includes a first lock positioned at the forward end and a second lock positioned at the aft end. The locking assembly includes a guide coupled to a hook shank of the arresting hook system. The guide is to move along at least a portion of the track, engage the first lock when the hook shank is in a stowed position, and bypass the second lock as the hook shank moves from the stowed position to a deployed position.

Abstract: Methods, apparatus, systems, and articles of manufacture are disclosed. An example arresting hook system for an aircraft includes a linkage assembly defining a trapeze deployment assembly of the arresting hook system, a pivot assembly to pivotally couple a hook shank to a primary pivot joint of an aft body, a vertical actuator coupled to a forward body and a frame of the aircraft to move the arresting hook system between a stowed position and an intermediate position, and a vertical damper actuator (VDA) including a cylinder and a piston. The cylinder pivotally coupled to the frame of the aircraft via a VDA pivot joint, the VDA to rotate relative to the frame of the aircraft, the piston having an end operatively coupled to the pivot assembly, the VDA to move the arresting hook system between the intermediate position and a deployed position.