[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: 14CFR25.307]

[Page 364]
 
                     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. 25.307  Proof of structure.

    (a) Compliance with the strength and deformation requirements of 
this subpart must be shown for each critical loading condition. 
Structural analysis may be used only if the structure conforms to that 
for which experience has shown this method to be reliable. The 
Administrator may require ultimate load tests in cases where limit load 
tests may be inadequate.
    (b)-(c) [Reserved]
    (d) When static or dynamic tests are used to show compliance with 
the requirements of Sec. 25.305(b) for flight structures, appropriate 
material correction factors must be applied to the test results, unless 
the structure, or part thereof, being tested has features such that a 
number of elements contribute to the total strength of the structure and 
the failure of one element results in the redistribution of the load 
through alternate load paths.

[Doc. No. 5066, 29 FR 18291, Dec. 24, 1964, as amended by Amdt. 25-23, 
35 FR 5672, Apr. 8, 1970; Amdt. 25-54, 45 FR 60172, Sept. 11, 1980; 
Amdt. 25-72, 55 FR 29775, July 20, 1990]

                              Flight Loads