[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: 14CFR25.307]



[Page 370]

 

                     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