[Code of Federal Regulations]
[Title 14, Volume 1]
[Revised as of January 1, 2003]
From the U.S. Government Printing Office via GPO Access
[CITE: 14CFR23.25]

[Page 176-177]
 
                     TITLE 14--AERONAUTICS AND SPACE
 
CHAPTER I--FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION
 
PART 23--AIRWORTHINESS STANDARDS: NORMAL, UTILITY, ACROBATIC, AND COMMUTER CATEGORY AIRPLANES--Table of Contents
 
                            Subpart B--Flight
 
Sec. 23.25  Weight limits.

    (a) Maximum weight. The maximum weight is the highest weight at 
which compliance with each applicable requirement of this part (other 
than those complied with at the design landing weight) is shown. The 
maximum weight must be established so that it is--
    (1) Not more than the least of--
    (i) The highest weight selected by the applicant; or
    (ii) The design maximum weight, which is the highest weight at which 
compliance with each applicable structural loading condition of this 
part (other than those complied with at the design landing weight) is 
shown; or
    (iii) The highest weight at which compliance with each applicable 
flight requirement is shown, and
    (2) Not less than the weight with--
    (i) Each seat occupied, assuming a weight of 170 pounds for each 
occupant for normal and commuter category airplanes, and 190 pounds for 
utility and acrobatic category airplanes, except that seats other than 
pilot seats may be placarded for a lesser weight; and
    (A) Oil at full capacity, and
    (B) At least enough fuel for maximum continuous power operation of 
at least 30 minutes for day-VFR approved

[[Page 177]]

airplanes and at least 45 minutes for night-VFR and IFR approved 
airplanes; or
    (ii) The required minimum crew, and fuel and oil to full tank 
capacity.
    (b) Minimum weight. The minimum weight (the lowest weight at which 
compliance with each applicable requirement of this part is shown) must 
be established so that it is not more than the sum of--
    (1) The empty weight determined under Sec. 23.29;
    (2) The weight of the required minimum crew (assuming a weight of 
170 pounds for each crewmember); and
    (3) The weight of--
    (i) For turbojet powered airplanes, 5 percent of the total fuel 
capacity of that particular fuel tank arrangement under investigation, 
and
    (ii) For other airplanes, the fuel necessary for one-half hour of 
operation at maximum continuous power.

[Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23-7, 34 
FR 13086, Aug. 13, 1969; Amdt. 23-21, 43 FR 2317, Jan. 16, 1978; Amdt. 
23-34, 52 FR 1825, Jan. 15, 1987; Amdt. 23-45, 58 FR 42156, Aug. 6, 
1993; Amdt. 23-50, 61 FR 5183, Feb. 9, 1996]