Devices and methods to structurally close and seal openings in an aircraft wing fuel tank
Closure devices and methods are provided for closing a stringer penetration space defined between a stringer and a wing rib of an aircraft wing section. According to certain embodiments, the closure devices will integrally include a forward face plate positioned in covering relationship to at least a portion of the stringer penetration space, and a rearwardly projecting attachment arm rigidly adapted for rigid attachment to the stringer so as to positionally fix the forward face plate relative to the stringer penetration space.
1. A closure device for closing a stringer penetration space defined between a stringer and a wing rib of an aircraft wing section, wherein the closure device integrally comprises:
(a) a forward face plate positioned so as to be structurally unattached to the wing rib in covering relationship to at least a portion of the stringer penetration space; and
(b) an attachment arm rigidly adapted for rigid structural attachment to the stringer so as to positionally fix the forward face plate relative to the stringer penetration space, wherein
the forward face plate includes (i) a central plate portion, (ii) an upper plate portion extending from an upper edge of the central plate portion, and (iii) a lower plate portion extending from a lower edge of the central plate portion, and wherein
the attachment arm extends rearwardly from the central plate portion of the forward face plate, and wherein
the upper and lower plate portions are angularly oriented in opposite directions relative to the central plate portion such that the upper plate portion is oriented in a rearwardly inclined direction relative to the central plate portion and the lower plate portion is oriented in a forwardly inclined direction relative to the central plate portion.
2. A method of sealing a stringer penetration space defined between a stringer and a wing rib of an aircraft wing section comprising:
(i) rigidly fixing the attachment arm of the closure device according to claim 1 to the stringer such that the forward face plate is positioned in covering relationship to at least a portion of the stringer penetration space; and
(ii) applying an aircraft sealant around a peripheral edge of the forward face plate.
3. A fuel tank section of an aircraft wing comprising:
a pair of spaced-apart wing ribs extending in a direction between leading and trailing edges of the aircraft wing;
stringers extending in a spanwise direction through the wing ribs and defining therebetween stringer penetration spaces with the wing ribs;
upper and lower wing skins attached to the wing ribs and stringers; and
closure devices closing the stringer penetration spaces defined between the stringers and the wing ribs, wherein each of the closure devices is the closure device according to claim 1 , wherein
the attachment arm of the each closure device is rigidly fixed to an adjacent one of the stringers such that the forward face plate is positioned so as to be structurally unattached to the adjacent one of the wing ribs in covering relationship to a respective one of the stringer penetration spaces.
4. The fuel tank section according to claim 3 , further comprising a sealant applied about a peripheral edge of the forward face plate.
5. An aircraft wing which comprises the fuel tank section according to claim 3 .
6. An aircraft which comprises the aircraft wing according to claim 5 .