A tiltrotor aircraft comprising: a fuselage; and a wing including a left outboard section, a midwing section and a right outboard section, the midwing section of the wing disposed above the fuselage, the wing including a wing airframe comprising: a wing airframe core assembly having a bottom side; and a wing skin assembly disposed on the wing airframe core assembly, the wing skin assembly including a lower wing skin assembly disposed on the bottom side of the wing airframe core assembly, the lower wing skin assembly including a plurality of access holes (150, 160, 162) including a pair of first outboard access holes (150, 162) located proximate to the fuselage to form buckle zones (128, 130), each of the buckle zones further comprising one of the first outboard access holes wherein the pair of first access holes of the lower wing skin assembly are sized such that the buckle zones (128, 130) have a failure load, the buckle zones locally susceptible to buckling when an impact compression force exceeds the failure load, thereby protecting the fuselage from being crushed by the wing; wherein the impact compression force is caused by the downward inertia of the wing during an impact; and wherein the wing skin assembly is thickened at the midwing section of the wing to enable the wing to buckle outboard of the midwing section in response to the impact. a fuselage; and a wing including a left outboard section, a midwing section and a right outboard section, the midwing section of the wing disposed above the fuselage, the wing including a wing airframe comprising: a wing airframe core assembly having a bottom side; and a wing skin assembly disposed on the wing airframe core assembly, the wing skin assembly including a lower wing skin assembly disposed on the bottom side of the wing airframe core assembly, the lower wing skin assembly including a plurality of access holes (150, 160, 162) including a pair of first outboard access holes (150, 162) located proximate to the fuselage to form buckle zones (128, 130), each of the buckle zones further comprising one of the first outboard access holes wherein the pair of first access holes of the lower wing skin assembly are sized such that the buckle zones (128, 130) have a failure load, the buckle zones locally susceptible to buckling when an impact compression force exceeds the failure load, thereby protecting the fuselage from being crushed by the wing; wherein the impact compression force is caused by the downward inertia of the wing during an impact; and wherein the wing skin assembly is thickened at the midwing section of the wing to enable the wing to buckle outboard of the midwing section in response to the impact. a wing airframe core assembly having a bottom side; and a wing skin assembly disposed on the wing airframe core assembly, the wing skin assembly including a lower wing skin assembly disposed on the bottom side of the wing airframe core assembly, the lower wing skin assembly including a plurality of access holes (150, 160, 162) including a pair of first outboard access holes (150, 162) located proximate to the fuselage to form buckle zones (128, 130), each of the buckle zones further comprising one of the first outboard access holes wherein the pair of first access holes of the lower wing skin assembly are sized such that the buckle zones (128, 130) have a failure load, the buckle zones locally susceptible to buckling when an impact compression force exceeds the failure load, thereby protecting the fuselage from being crushed by the wing; wherein the impact compression force is caused by the downward inertia of the wing during an impact; and wherein the wing skin assembly is thickened at the midwing section of the wing to enable the wing to buckle outboard of the midwing section in response to the impact.