Quote from electricdeathjet:
How does carbon fiber (ie 787) structures cope with the cold, is there a marked difference to conventional materials?
Quote from CarbonBrake:
For example, spars and ribs of the [A]320-series are manufactured out of aluminum/zinc alloys (type 7010 and 7050), top skin panels of the main wing out of 7050 and the bottom skin panels out of aluminum/copper alloy 2024. They show excellent fatique strength over a broad temperature range even at low temperatures mentioned above.
But what about the composite tailplanes and fins of A320s and other current types, not to mention nose-cones and belly fairings?