[Code of Federal Regulations]
[Title 14, Volume 1]
[Revised as of January 1, 2004]
From the U.S. Government Printing Office via GPO Access
[CITE: 14CFR33.19]

[Page 762]
 
                     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. 33.19  Durability.

    (a) Engine design and construction must minimize the development of 
an unsafe condition of the engine between overhaul periods. The design 
of the compressor and turbine rotor cases must provide for the 
containment of damage from rotor blade failure. Energy levels and 
trajectories of fragments resulting from rotor blade failure that lie 
outside the compressor and turbine rotor cases must be defined.
    (b) Each component of the propeller blade pitch control system which 
is a part of the engine type design must meet the requirements of 
Sec. 35.42 of this chapter.

[Doc. No. 3025, 29 FR 7453, June 10, 1964, as amended by Amdt. 33-9, 45 
FR 60181, Sept. 11, 1980; Amdt. 33-10, 49 FR 6851, Feb. 23, 1984]