Consider a commercial jetliner that weighs about 200 000 kgs. It is found that 80% of the structure is made of 2024T3 aluminum, and 15% is made of carbon/epoxy composites. The remaining 5% part of the airplane is equally distributed between Ti6Al4V and AISI4340. If the jetliner is now redesigned with the following material distributions, what will be the new weight of the airplane? How much weight is saved, percentagewise? Carbon composite = 65% Aluminum = 30% Titanium = 2.5% Steel = 2.5%