Assembly of aircraft wings
A method of joining a wing skin to a structural element of an aircraft wing. A locating through hole is formed in the structural element, extending along a path between a first side of the structural element and a second side of the structural element. A spark containment cap is attached to the first side of the structural element to covering an opening of the locating through hole. A portion of the wing skin is positioned on the second side of the structural element. A fastening through hole having a larger diameter than the locating through hole is formed through both the wing skin and the structural element and along the path of the locating through hole. A fastener is inserted into the fastening through hole and the structural element secured to the wing skin, an end of the fastener being covered by the spark containment cap.
1 . A method of joining a wing skin to a structural element of an aircraft wing, the method comprising:
forming a locating through hole in the structural element, the locating through hole extending along a path between a first side of the structural element and a second side of the structural element;
attaching a spark containment cap to the first side of the structural element, the spark containment cap covering an opening of the locating through hole;
positioning a portion of the wing skin on the second side of the structural element;
forming a fastening through hole, having a diameter larger than the locating through hole, through both the wing skin and the structural element and along the path of the locating through hole, such that the fastening through hole comprises:
a first opening in the wing skin, and
a second opening in the structural element and covered by the spark containment cap; and
inserting a fastener into the fastening through hole and securing the structural element to the wing skin, an end of the fastener being covered by the spark containment cap,
wherein attaching the spark containment cap comprises providing a temporary fastener within the locating through hole prior to the forming the fastening through hole step, the temporary fastener configured to secure the spark containment cap to the structural element.
2 . The method according to claim 1 , wherein the spark containment cap comprises a washer.
3 . The method according to claim 2 , wherein the washer is formed of an electrically insulative material.
4 . The method according to claim 2 , wherein attaching the spark containment cap comprises providing a temporary fastener within the locating through hole, the temporary fastener configured to secure the spark containment cap to the structural element,
wherein the temporary fastener is a snap lock pin fastener and the spark containment cap comprises a surface arranged such that, when the temporary fastener is inserted into the spark containment cap, the temporary fastener engages with the surface to resist removal from the spark containment cap, and,
wherein the surface with which the temporary fastener engages is the washer.
5 . The method according to claim 1 , wherein the spark containment cap comprises a portion configured to receive adhesive for attaching the spark containment cap to the structural element, and
wherein attaching the spark containment cap to the first side of the structural element comprises providing and curing the adhesive.
6 . The method of claim 5 , wherein the portion is a skirt disposed along a perimeter of the spark containment cap, the skirt configured such that adhesive provided to the skirt is confined within the skirt.
7 . The method according to claim 1 , wherein a diameter of the locating through hole is less than half of the diameter of the fastening through hole.
8 . The method of claim 7 , wherein the diameter of the locating through hole is less than a quarter of the diameter of the fastening through hole.
9 . The method of claim 7 , wherein a diameter of the fastening through hole is more than three quarters of an internal diameter of the spark containment cap.
10 . The method of claim 1 , wherein the structural element is a rib or a spar of the aircraft wing.
11 . The method of claim 1 , wherein the structural element forms a portion of a fuel tank and the spark containment cap is provided within the fuel tank.
12 . A method of joining a wing skin to a structural element of an aircraft wing, the method comprising:
forming a locating through hole in the structural element, the locating through hole extending along a path between a first side of the structural element and a second side of the structural element;
attaching a spark containment cap to the first side of the structural element, the spark containment cap covering an opening of the locating through hole;
positioning a portion of the wing skin on the second side of the structural element;
forming a fastening through hole, having a diameter larger than the locating through hole, through both the wing skin and the structural element and along the path of the locating through hole, such that the fastening through hole comprises:
a first opening in the wing skin, and
a second opening in the structural element and covered by the spark containment cap; and
inserting a fastener into the fastening through hole and securing the structural element to the wing skin, an end of the fastener being covered by the spark containment cap,
wherein attaching the spark containment cap comprises providing a temporary fastener within the locating through hole, the temporary fastener configured to secure the spark containment cap to the structural element,
wherein the temporary fastener is threaded, and the spark containment cap comprises a corresponding threaded receiving portion configured to receive a threaded portion of the temporary fastener.
13 . A method of joining a wing skin to a structural element of an aircraft wing, the method comprising:
forming a locating through hole in the structural element, the locating through hole extending along a path between a first side of the structural element and a second side of the structural element;
attaching a spark containment cap to the first side of the structural element, the spark containment cap covering an opening of the locating through hole;
positioning a portion of the wing skin on the second side of the structural element;
forming a fastening through hole, having a diameter larger than the locating through hole, through both the wing skin and the structural element and along the path of the locating through hole, such that the fastening through hole comprises:
a first opening in the wing skin, and
a second opening in the structural element and covered by the spark containment cap; and
inserting a fastener into the fastening through hole and securing the structural element to the wing skin, an end of the fastener being covered by the spark containment cap,
wherein attaching the spark containment cap comprises providing a temporary fastener within the locating through hole, the temporary fastener configured to secure the spark containment cap to the structural element,
wherein the temporary fastener is a snap lock pin fastener and the spark containment cap comprises a surface arranged such that, when the temporary fastener is inserted into the spark containment cap, the temporary fastener engages with the surface to resist removal from the spark containment cap.