[Code of Federal Regulations]
[Title 14, Volume 1]
[Revised as of January 1, 2004]
From the U.S. Government Printing Office via GPO Access
[CITE: 14CFR25.301]

[Page 363]
 
                     TITLE 14--AERONAUTICS AND SPACE
 
CHAPTER I--FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION
 
PART 25--AIRWORTHINESS STANDARDS: TRANSPORT CATEGORY AIRPLANES--Table of Contents
 
                          Subpart C--Structure
 
Sec. 25.301  Loads.

                                 General


    (a) Strength requirements are specified in terms of limit loads (the 
maximum loads to be expected in service) and ultimate loads (limit loads 
multiplied by prescribed factors of safety). Unless otherwise provided, 
prescribed loads are limit loads.
    (b) Unless otherwise provided, the specified air, ground, and water 
loads must be placed in equilibrium with inertia forces, considering 
each item of mass in the airplane. These loads must be distributed to 
conservatively approximate or closely represent actual conditions. 
Methods used to determine load intensities and distribution must be 
validated by flight load measurement unless the methods used for 
determining those loading conditions are shown to be reliable.
    (c) If deflections under load would significantly change the 
distribution of external or internal loads, this redistribution must be 
taken into account.

[Doc. No. 5066, 29 FR 18291, Dec. 24, 1964, as amended by Amdt. 25-23, 
35 FR 5672, Apr. 8, 1970]