Multi-spar port box joint
A method for connecting a wing. A frame for a wing may be positioned relative to a fuselage of an aircraft. The frame may have bays and comprise a front spar, a rear spar, and a number of spars located between the front and rear spars. A first number of skin panels may be on a first side of the frame, and a second number of skin panels may be on a second side of the frame. The first side may be opposite to the second side. Openings may be in the first and second numbers of skin panels. The openings may be in locations such that each bay has an opening and such that the openings may alternate between the first side and the second side between adjacent bays in the bays. The frame may be attached to the fuselage using the openings to access an interior of the frame.
1. A method for accessing an interior of an aircraft, the method comprising:
accessing the interior of the aircraft using a plurality of openings in skin panels on a frame for an airfoil for the aircraft in which the plurality of openings provide access to a plurality of bays in the interior of the airfoil and in which the plurality of openings alternate between a first side and a second side of the frame in a manner that avoids two adjacent bays in the plurality of bays having openings on a same side.
2. The method of claim 1 , wherein the interior of the airfoil is an interior of a wing.
3. The method of claim 1 , wherein the plurality of openings alternating between the first side and the second side of the plurality of bays increases a load carried by the skin panels.
4. The method of claim 2 further comprising:
positioning the wing relative to a fuselage of the aircraft; and
securing the wing to the fuselage using the plurality of openings to access an interior of the wing.
5. The method of claim 4 , wherein securing the wing to the fuselage using the plurality of openings to access the interior of the wing comprises:
securing the wing to the fuselage with fasteners using the plurality of openings to access the interior of the wing to install the fasteners.
6. The method of claim 2 further comprising:
performing maintenance on a joint for the wing from the interior of the wing accessed through the plurality of openings.
7. The method of claim 1 further comprising:
adding reinforcements to edges of the plurality of openings to increase a load carried by the skin panels on the airfoil.
8. The method of claim 1 further comprising:
installing a plurality of covers for the plurality of openings in which the plurality of covers is configured to increase a load carried by the skin panels and carry at least a portion of the load across the plurality of covers.
9. The method of claim 8 , wherein the plurality of covers reduces at least one of a pressure change inside the frame during flight of the aircraft and debris entering the plurality of bays.