Most large airplanes flying today are mostly metal, which has a relatively big coefficient of thermal expansion. Cruising altitudes of commercial jets can reach 10 km or more, where the air gets down to about -50 Celsius. Room temperature is more like +25 Celsius, and I would not be surprised if that large fuselage, sitting under the sun, gets up near +50 C.
This is quite a range of temperatures to handle. It would cause some contraction/expansion of metals. The larger the piece of metal, such as a wing spar or long airframe beam, the greater the contraction/expansion.
Is this a major design problem for large aircraft, and how is it handled?
EDIT: only interested in subsonic designs. I'm concerned about the cold high altitude air cooling most of the fuselage and making it contract. The nose and leading wing edges might not suffer from this, but I expect the rest of the aircraft will.