[Code of Federal Regulations]
[Title 14, Volume 1]
[Revised as of January 1, 2003]
From the U.S. Government Printing Office via GPO Access
[CITE: 14CFR33.28]

[Page 739]
 
                     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]