[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: 14CFR25.301]



[Page 369]

 

                     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]