A question for you aeronautical engineer types: What determines the maximum gross weight of an airframe?
I understand that Van's has rated the RV-12 airframe and powerplant at 1320# max gross weight, which is (not coincidentally I'm sure) the limit for LSA craft. How arbitrary is this number? For example, if Van designed a plane which met all of the LSA requirements but could support a takeoff weight of 1500#, wouldn't he just arbitrarily limit the max gross weight to 1320# to meet the specs? That might make more sense than de-engineering the craft to reduce its capabilities.
So, if a builder were to go the E-AB certification route, is it possible to have a higher max gross weight for his RV-12? How would that be calculated?
I understand that Van's has rated the RV-12 airframe and powerplant at 1320# max gross weight, which is (not coincidentally I'm sure) the limit for LSA craft. How arbitrary is this number? For example, if Van designed a plane which met all of the LSA requirements but could support a takeoff weight of 1500#, wouldn't he just arbitrarily limit the max gross weight to 1320# to meet the specs? That might make more sense than de-engineering the craft to reduce its capabilities.
So, if a builder were to go the E-AB certification route, is it possible to have a higher max gross weight for his RV-12? How would that be calculated?