[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: 14CFR33.14]



[Page 770]

 

                     TITLE 14--AERONAUTICS AND SPACE

 

CHAPTER I--FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION

 

PART 33_AIRWORTHINESS STANDARDS: AIRCRAFT ENGINES--Table of Contents

 

               Subpart B_Design and Construction; General

 

Sec. 33.14  Start-stop cyclic stress (low-cycle fatigue).



    By a procedure approved by the FAA, operating limitations must be 

established which specify the maximum allowable number of start-stop 

stress cycles for each rotor structural part (such as discs, spacers, 

hubs, and shafts of the compressors and turbines), the failure of which 

could produce a hazard to the aircraft. A start-stop stress cycle 

consists of a flight cycle profile or an equivalent representation of 

engine usage. It includes starting the engine, accelerating to maximum 

rated power or thrust, decelerating, and stopping. For each cycle, the 

rotor structural parts must reach stabilized temperature during engine 

operation at a maximum rate power or thrust and after engine shutdown, 

unless it is shown that the parts undergo the same stress range without 

temperature stabilization.



[Amdt. 33-10, 49 FR 6850, Feb. 23, 1984]