[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: 14CFR33.19]



[Page 771]

 

                     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]