[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: 14CFR33.28]



[Page 772]

 

                     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. 33.28  Electrical and electronic engine control systems.



    Each control system which relies on electrical and electronic means 

for normal operation must:

    (a) Have the control system description, the percent of available 

power or trust controlled in both normal operation and failure 

conditions, and the range of control of other controlled functions, 

specified in the instruction manual required by Sec. 33.5 for the 

engine;

    (b) Be designed and constructed so that any failure of aircraft-

supplied power or data will not result in an unacceptable change in 

power or thrust, or prevent continued safe operation of the engine;

    (c) Be designed and constructed so that no single failure or 

malfunction, or probable combination of failures of electrical or 

electronic components of the control system, results in an unsafe 

condition;

    (d) Have environmental limits, including transients caused by 

lightning strikes, specified in the instruction manual; and

    (e) Have all associated software designed and implemented to prevent 

errors that would result in an unacceptable loss of power or thrust, or 

other unsafe condition, and have the method used to design and implement 

the software approved by the Administrator.



[Doc. No. 24466, 58 FR 29095, May 18, 1993]