A panel for a nacelle structure that surrounds a jet engine core, the panel comprising: a center region that extends along a longitudinal axis of the jet engine core; an upper bifurcation region extending radially from the center region; a lower bifurcation region extending radially from the center region; a hinge beam region extending from the upper bifurcation region and configured to receive an upper thrust reverser track guide; and a latch beam region extending from the lower bifurcation region and configured to receive a lower thrust reverser track guide; wherein a bypass duct is formed in a space between the panel, when mounted, and the nacelle structure; and wherein the hinge beam region includes a lower flow portion that defines a portion of the bypass duct and an upper attachment portion that receives the upper thrust reverser track guide, and wherein the latch beam region includes an upper flow portion that defines a portion of the bypass duct and a lower attachment portion that receives the lower thrust reverser track guide, characterized in that: the center region, upper bifurcation region, and lower bifurcation region are constructed from a honeycomb core having an inner honeycomb side generally facing the engine core and an outer honeycomb side generally facing the bypass duct, and wherein an inner skin layer extends continuously across a bond panel surface generally facing the engine core and an outer skin layer extends continuously across a bond panel surface generally facing the bypass duct, the inner and outer skin layers (508, 510) extending across the center region, upper and lower bifurcation regions, hinge beam region, and latch beam region, the outer skin layer is perforated in at least the center region and the upper and lower bifurcation regions, and a portion of the panel comprises only the inner skin layer and the outer skin layer such that the inner skin layer is bonded to the outer skin layer in the transition from the lower flow portion to the upper attachment portion. a center region that extends along a longitudinal axis of the jet engine core; an upper bifurcation region extending radially from the center region; a lower bifurcation region extending radially from the center region; a hinge beam region extending from the upper bifurcation region and configured to receive an upper thrust reverser track guide; and a latch beam region extending from the lower bifurcation region and configured to receive a lower thrust reverser track guide; wherein a bypass duct is formed in a space between the panel, when mounted, and the nacelle structure; and wherein the hinge beam region includes a lower flow portion that defines a portion of the bypass duct and an upper attachment portion that receives the upper thrust reverser track guide, and wherein the latch beam region includes an upper flow portion that defines a portion of the bypass duct and a lower attachment portion that receives the lower thrust reverser track guide, characterized in that: the center region, upper bifurcation region, and lower bifurcation region are constructed from a honeycomb core having an inner honeycomb side generally facing the engine core and an outer honeycomb side generally facing the bypass duct, and wherein an inner skin layer extends continuously across a bond panel surface generally facing the engine core and an outer skin layer extends continuously across a bond panel surface generally facing the bypass duct, the inner and outer skin layers (508, 510) extending across the center region, upper and lower bifurcation regions, hinge beam region, and latch beam region, the outer skin layer is perforated in at least the center region and the upper and lower bifurcation regions, and a portion of the panel comprises only the inner skin layer and the outer skin layer such that the inner skin layer is bonded to the outer skin layer in the transition from the lower flow portion to the upper attachment portion. the center region, upper bifurcation region, and lower bifurcation region are constructed from a honeycomb core having an inner honeycomb side generally facing the engine core and an outer honeycomb side generally facing the bypass duct, and wherein an inner skin layer extends continuously across a bond panel surface generally facing the engine core and an outer skin layer extends continuously across a bond panel surface generally facing the bypass duct, the inner and outer skin layers (508, 510) extending across the center region, upper and lower bifurcation regions, hinge beam region, and latch beam region, the outer skin layer is perforated in at least the center region and the upper and lower bifurcation regions, and a portion of the panel comprises only the inner skin layer and the outer skin layer such that the inner skin layer is bonded to the outer skin layer in the transition from the lower flow portion to the upper attachment portion.