Originally Posted by
westhawk
I have never before heard of a "minimum zero fuel weight" limitation. Without any wish to oversimplify, I must still ask whether it is possible that this limitation may be applied for the same reason as a "maximum zero fuel weight" limitation, but in the opposite sense? Could there be a structural reason for this limitation as there is with Max ZFW? Suppose full wing fuel were assumed with too little weight in the fuselage between the wings. Might the structures require a minimum weight be carried in the fuselage with wings full in much the same way that a maximum weight to be carried in the fuselage is established with zero fuel?
min Zero Fuel Weight is essentially the minimum design weight....the aircraft simply cannot be any lighter
Originally Posted by FAR. 25.321
(b) Considering compressibility effects at each speed, compliance with the
flight load requirements of this subpart must be shown--
(1) At each critical altitude within the range of altitudes selected by the
applicant;
(2) At each weight from the design minimum weight to the design maximum
weight appropriate to each particular flight load condition;