[Code of Federal Regulations]

[Title 14, Volume 1]

[Revised as of January 1, 2006]

From the U.S. Government Printing Office via GPO Access

[CITE: 14CFR23.25]



[Page 182-183]

 

                     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 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



[[Page 183]]



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]