A multi-spar wing structure for an aircraft comprising: a frame having a first side and a second side, the first side being substantially opposite to the second side of the frame, the frame comprising: a front spar; a rear spar; and a number of spars located between the front spar and the rear spar, wherein the front spar, the rear spar, and the number of spars form the frame; a plurality of bays located within the frame and defined by the spars (506, 508, 504); a first number of skin panels on the first side of the frame and a second number of skin panels on the second side of the frame; and a plurality of openings (630, 700, 702) in locations (536, 538, 542) in the skin panels (622, 620), wherein the locations (536, 538, 542) are selected such that at least some of the bays have an opening in one of the skin panels (622, 620); the openings in the plurality of openings (630, 700, 702) having a size (1004, 1006) and a shape selected to provide to an operator access to the interior of the wing; characterized in that: the locations (536, 538, 542) are selected such that the plurality of openings (630, 700, 702) alternate between the first side and the second side in a manner that avoids two adjacent bays in the plurality of bays having openings on a same side; the load carried by the skin panels on the wing is increased by the arrangement of the plurality of openings (630, 700, 702). a frame having a first side and a second side, the first side being substantially opposite to the second side of the frame, the frame comprising: a front spar; a rear spar; and a number of spars located between the front spar and the rear spar, wherein the front spar, the rear spar, and the number of spars form the frame; a plurality of bays located within the frame and defined by the spars (506, 508, 504); a first number of skin panels on the first side of the frame and a second number of skin panels on the second side of the frame; and a plurality of openings (630, 700, 702) in locations (536, 538, 542) in the skin panels (622, 620), wherein the locations (536, 538, 542) are selected such that at least some of the bays have an opening in one of the skin panels (622, 620); the openings in the plurality of openings (630, 700, 702) having a size (1004, 1006) and a shape selected to provide to an operator access to the interior of the wing; characterized in that: the locations (536, 538, 542) are selected such that the plurality of openings (630, 700, 702) alternate between the first side and the second side in a manner that avoids two adjacent bays in the plurality of bays having openings on a same side; the load carried by the skin panels on the wing is increased by the arrangement of the plurality of openings (630, 700, 702). a front spar; a rear spar; and a number of spars located between the front spar and the rear spar, wherein the front spar, the rear spar, and the number of spars form the frame; a plurality of bays located within the frame and defined by the spars (506, 508, 504); a first number of skin panels on the first side of the frame and a second number of skin panels on the second side of the frame; and a plurality of openings (630, 700, 702) in locations (536, 538, 542) in the skin panels (622, 620), wherein the locations (536, 538, 542) are selected such that at least some of the bays have an opening in one of the skin panels (622, 620); the openings in the plurality of openings (630, 700, 702) having a size (1004, 1006) and a shape selected to provide to an operator access to the interior of the wing; the locations (536, 538, 542) are selected such that the plurality of openings (630, 700, 702) alternate between the first side and the second side in a manner that avoids two adjacent bays in the plurality of bays having openings on a same side; the load carried by the skin panels on the wing is increased by the arrangement of the plurality of openings (630, 700, 702).