[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: 14CFR35.23]

[Page 812]
 
                     TITLE 14--AERONAUTICS AND SPACE
 
CHAPTER I--FEDERAL AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION
 
PART 35_AIRWORTHINESS STANDARDS: PROPELLERS--Table of Contents
 
                    Subpart B_Design and Construction
 
Sec.  35.23  Pitch control and indication.

    (a) No loss of normal propeller pitch control may cause hazardous 
overspeeding of the propeller under intended operating conditions.
    (b) Each pitch control system that is within the propeller, or 
supplied with the propeller, and that uses engine oil for feathering, 
must incorporate means to override or bypass the normally operative 
hydraulic system components so as to allow feathering if those 
components fail or malfunction.
    (c) Each propeller approved for installation on a turbopropeller 
engine must incorporate a provision for an indicator to indicate when 
the propeller blade angle is below the flight low pitch position. The 
provision must directly sense the blade position and be arranged to 
cause an indicator to indicate that the blade angle is below the flight 
low pitch position before the blade moves more than 8[deg] below the 
flight low pitch stop.

[Amdt. 35-2, 32 FR 3737, Mar. 4, 1967, as amended by Amdt. 35-5, 45 FR 
60182, Sept. 11, 1980]