[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: 14CFR35.23]



[Page 809]

 

                     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]