[Code of Federal Regulations]
[Title 14, Volume 1]
[Revised as of January 1, 2007]
From the U.S. Government Printing Office via GPO Access
[CITE: 14CFR33.14]

[Page 773]
 
                     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]