ASTM F3065/F3065M-18

Standard Specification for Aircraft Propeller System Installation

SCOPE
1.1 This specification addresses the airworthiness requirements for the installation and integration of propeller systems.  
1.2 This specification is applicable to aeroplanes as defined in F44 terminology standard.  
1.3 The applicant for a design approval must seek the individual guidance to their respective CAA body concerning the use of this standard as part of a certification plan. For information on which CAA regulatory bodies have accepted this standard (in whole or in part) as a means of compliance to their Small Aircraft Airworthiness regulations (Hereinafter referred to as “the Rules”), refer to ASTM F44 webpage (www.ASTM.org/COMITTEE/F44.htm) which includes CAA website links.  
1.4 Units—The values stated are SI units followed by Imperial units in square brackets. The values stated in each system may not be exact equivalents; therefore, each system shall be used independently of the other. Combining values from the two systems may result in non-conformance with the standard.  
1.5 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility of the user of this standard to establish appropriate safety, health, and environmental practices and determine the applicability of regulatory limitations prior to use.  
1.6 This international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for the Development of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.

General Information

• Status: Historical
• Publication Date: 31-Dec-2017
• ICS: 49.050 - Aerospace engines and propulsion systems
• Technical Committee: F44 - General Aviation Aircraft
• Drafting Committee: F44.40 - Powerplant

Relations

• Replaces: ASTM F3065/F3065M-15 - Standard Specification for Installation and Integration of Propeller Systems
• Effective Date: 01-Jan-2018
• Referred By: ASTM F3264-23 - Standard Specification for Normal Category Aeroplanes Certification
• Effective Date: 01-Jan-2018
• Referred By: ASTM F3239-22a - Standard Specification for Aircraft Electric Propulsion Systems
• Effective Date: 01-Jan-2018
• Referred By: ASTM F3563-22 - Standard Specification for Design and Construction of Large Fixed Wing Unmanned Aircraft Systems
• Effective Date: 01-Jan-2018

Standards Content (Sample)

NOTICE: This standard has either been superseded and replaced by a new version or withdrawn.
Contact ASTM International (www.astm.org) for the latest information
Designation: F3065/F3065M −18
Standard Specification for
1
Aircraft Propeller System Installation
ThisstandardisissuedunderthefixeddesignationF3065/F3065M;thenumberimmediatelyfollowingthedesignationindicatestheyear
of original adoption or, in the case of revision, the year of last revision.Anumber in parentheses indicates the year of last reapproval.
A superscript epsilon (´) indicates an editorial change since the last revision or reapproval.
1. Scope 2. Referenced Documents
2
2.1 ASTM Standards:
1.1 This specification addresses the airworthiness require-
F3060Terminology for Aircraft
ments for the installation and integration of propeller systems.
3. Terminology
1.2 This specification is applicable to aeroplanes as defined
in F44 terminology standard.
3.1 See Terminology F3060.
1.3 The applicant for a design approval must seek the
4. Propeller Installation Aspects
individual guidance to their respective CAA body concerning
4.1 Propeller—General:
the use of this standard as part of a certification plan. For
4.1.1 Each propeller must:
information on which CAA regulatory bodies have accepted
4.1.1.1 Have a type certificate, or
this standard (in whole or in part) as a means of compliance to
4.1.1.2 Meet the requirements acceptable to the certifying
their Small Aircraft Airworthiness regulations (Hereinafter
aviation authority for inclusion in the approved aeroplane.
referred to as “the Rules”), refer to ASTM F44 webpage
4.1.2 Enginepowerandpropellershaftrotationalspeedmay
(www.ASTM.org/COMITTEE/F44.htm) which includes CAA
not exceed the limits for which the propeller is certificated or
website links.
approved.
1.4 Units—The values stated are SI units followed by
4.2 Feathering Propellers—Eachfeatherablepropellermust
Imperial units in square brackets. The values stated in each
have a means to un-feather in flight.
system may not be exact equivalents; therefore, each system
4.3 Variable-Pitch Propellers—The propeller blade pitch
shall be used independently of the other. Combining values
control system must meet the following requirements:
from the two systems may result in non-conformance with the
4.3.1 No single failure or malfunction in the propeller
standard.
system will result in unintended travel of the propeller blades
1.5 This standard does not purport to address all of the
to a position below the in-flight low-pitch position. Failure of
safety concerns, if any, associated with its use. It is the
structural elements need not be considered if the occurrence of
responsibility of the user of this standard to establish appro-
such a failure is shown to be extremely remote.
priate safety, health, and environmental practices and deter-
4.3.2 For propellers incorporating a method to select blade
mine the applicability of regulatory limitations prior to use.
pitch below the in-flight low pitch position, provisions must be
1.6 This international standard was developed in accor- made to sense and indicate to the flight crew that the propeller
blades are below that position by a defined amount. The
dance with internationally recognized principles on standard-
ization established in the Decision on Principles for the method for sensing and indicating the propeller blade pitch
position must be such that its failure does not affect the control
Development of International Standards, Guides and Recom-
mendations issued by the World Trade Organization Technical of the propeller.
4.3.3 The propeller control system, operating in normal and
Barriers to Trade (TBT) Committee.
alternative operating modes and in transition between operat-
ing modes, performs the defined functions throughout the
declared operating conditions and flight envelope.
1
ThisspecificationisunderthejurisdictionofASTMCommitteeF44onGeneral
Aviation Aircraft and is the direct responsibility of Subcommittee F44.40 on
2
Powerplant. For referenced ASTM standards, visit the ASTM website, www.astm.org, or
Current edition approved Jan. 1, 2018. Published January 2018. Originally contact ASTM Customer Service at [e-mail]. For Annual Book of ASTM
approved in 2015. Last previous edition approved in 2015 as F3065/F3065M–15. Standards volume information, refer to the standard’s Document Summary page on
DOI: 10.1520/F3065_F3065M-18. the ASTM website.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States
1

---------------------- Page: 1 ----------------------
F3065/F3065M − 18
4.3.4 The propeller control system functionality is not 4.5.1 Propeller clearances in section 4.5 are the minimum
adversely affected by the declared environmental conditions, allowable, unless otherwise substantiated, under the following
including temperature, electromagnetic interference (EMI), conditions:
high intensity radiated fields (HIRF) and lightning. 4.5.1.1 With the mo
...

This document is not an ASTM standard and is intended only to provide the user of an ASTM standard an indication of what changes have been made to the previous version. Because
it may not be technically possible to adequately depict all changes accurately, ASTM recommends that users consult prior editions as appropriate. In all cases only the current version
of the standard as published by ASTM is to be considered the official document.
Designation: F3065/F3065M − 15 F3065/F3065M − 18
Standard Specification for
Installation and Integration of Propeller SystemsAircraft
1
Propeller System Installation
This standard is issued under the fixed designation F3065/F3065M; the number immediately following the designation indicates the year
of original adoption or, in the case of revision, the year of last revision. A number in parentheses indicates the year of last reapproval.
A superscript epsilon (´) indicates an editorial change since the last revision or reapproval.
1. Scope
1.1 This specification addresses the airworthiness requirements for the installation and integration of propeller systems.
1.2 This specification is applicable to aeroplanes as defined in F44 terminology standard.
1.3 The applicant for a design approval must seek the individual guidance to their respective CAA body concerning the use of
this standard as part of a certification plan. For information on which CAA regulatory bodies have accepted this standard (in whole
or in part) as a means of compliance to their Small Aircraft Airworthiness regulations (Hereinafter referred to as “the Rules”), refer
to ASTM F44 webpage (www.ASTM.org/COMITTEE/F44.htm) which includes CAA website links.
1.4 Units—The values stated are SI units followed by Imperial units in square brackets. The values stated in each system may
not be exact equivalents; therefore, each system shall be used independently of the other. Combining values from the two systems
may result in non-conformance with the standard.
1.5 This standard does not purport to address all of the safety concerns, if any, associated with its use. It is the responsibility
of the user of this standard to establish appropriate safety safety, health, and healthenvironmental practices and determine the
applicability of regulatory limitations prior to use.
1.6 This international standard was developed in accordance with internationally recognized principles on standardization
established in the Decision on Principles for the Development of International Standards, Guides and Recommendations issued
by the World Trade Organization Technical Barriers to Trade (TBT) Committee.
2. Referenced Documents
2
2.1 ASTM Standards:
F3060 Terminology for Aircraft
3. Terminology
3.1 See Terminology F3060.
4. Propeller Installation Aspects
4.1 Propeller—General:
4.1.1 Each propeller must:
4.1.1.1 Have a type certificate, or
4.1.1.2 Meet the requirements acceptable to the certifying aviation authority for inclusion in the approved aeroplane.
4.1.2 Engine power and propeller shaft rotational speed may not exceed the limits for which the propeller is certificated or
approved.
4.2 Feathering Propellers—Each featherable propeller must have a means to un-feather in flight.
4.3 Variable-Pitch Propellers—The propeller blade pitch control system must meet the following requirements:
4.3.1 No single failure or malfunction in the propeller system will result in unintended travel of the propeller blades to a position
below the in-flight low-pitch position. Failure of structural elements need not be considered if the occurrence of such a failure is
shown to be extremely remote.
1
This specification is under the jurisdiction of ASTM Committee F44 on General Aviation Aircraft and is the direct responsibility of Subcommittee F44.40 on Powerplant.
Current edition approved May 1, 2015Jan. 1, 2018. Published June 2015January 2018. Originally approved in 2015. Last previous edition approved in 2015 as
F3065/F3065M – 15. DOI: 10.1520/F3065-15.10.1520/F3065_F3065M-18.
2
For referenced ASTM standards, visit the ASTM website, www.astm.org, or contact ASTM Customer Service at [e-mail]. For Annual Book of ASTM Standards
volume information, refer to the standard’s Document Summary page on the ASTM website.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States
1

---------------------- Page: 1 ----------------------
F3065/F3065M − 18
4.3.2 For propellers incorporating a method to select blade pitch below the in-flight low pitch position, provisions must be made
to sense and indicate to the flight crew that the propeller blades are below that position by a defined amount. The method for
sensing and indicating the propeller blade pitch position must be such that its failure does not affect the control of the propeller.
4.3.3 The propeller control system, operating in normal and alternative operating modes and in transition between operating
modes, performs the defined functions throughout the decl
...