(b) Compliance with the flight load requirements of this subpart must be shown—
(1) At each critical altitude within the range in which the airplane may be expected to operate;
(2) At each weight from the design minimum weight to the design maximum weight; and
(3) For each required altitude and weight, for any practicable distribution of disposable load within the operating limitations specified in §§23.1583 through 23.1589.
(c) When significant, the effects of compressibility must be taken into account.
[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23–45, 58 FR 42160, Aug. 6, 1993]