ASTM F3065/F3065M-15

Standard Specification for Installation and Integration of Propeller Systems

ABSTRACT
This specification covers airworthiness requirements for the installation and integration of propeller systems, and is applicable to aeroplanes as defined in F44 terminology standard. The applicant for a design approval must seek the individual guidance to their respective civil aviation authority (CAA) body concerning the use of this specification as part of a certification plan.
The requirements prescribed in this specification cover: propeller installation aspects (general propeller, feathering propellers, variable-pitch propellers, pusher propeller installation, propeller clearance), structural aspects (propeller vibration and fatigue), propeller control limitations (propeller speed and pitch limits, propeller reversing systems), and associated propeller systems (oil system-propeller feathering systems, turbopropeller-drag limiting systems).
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 and health practices and determine the applicability of regulatory limitations prior to use.

General Information

• Status: Historical
• Publication Date: 30-Apr-2015
• ICS: 49.050 - Aerospace engines and propulsion systems
• Technical Committee: F44 - General Aviation Aircraft
• Drafting Committee: F44.40 - Powerplant

Relations

• Replaced By: ASTM F3065/F3065M-18 - Standard Specification for Aircraft Propeller System Installation
• Effective Date: 01-Jan-2018
• Referred By: ASTM F3239-22a - Standard Specification for Aircraft Electric Propulsion Systems
• Effective Date: 01-May-2015
• Referred By: ASTM F3563-22 - Standard Specification for Design and Construction of Large Fixed Wing Unmanned Aircraft Systems
• Effective Date: 01-May-2015
• Referred By: ASTM F3264-23 - Standard Specification for Normal Category Aeroplanes Certification
• Effective Date: 01-May-2015

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 −15
Standard Specification for
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Installation and Integration of Propeller Systems
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 4. Propeller Installation Aspects
1.1 This specification addresses the airworthiness require-
4.1 Propeller—General:
ments for the installation and integration of propeller systems.
4.1.1 Each propeller must:
4.1.1.1 Have a type certificate, or
1.2 This specification is applicable to aeroplanes as defined
4.1.1.2 Meet the requirements acceptable to the certifying
in F44 terminology standard.
aviation authority for inclusion in the approved aeroplane.
1.3 The applicant for a design approval must seek the
4.1.2 Enginepowerandpropellershaftrotationalspeedmay
individual guidance to their respective CAA body concerning
not exceed the limits for which the propeller is certificated or
the use of this standard as part of a certification plan. For
approved.
information on which CAA regulatory bodies have accepted
this standard (in whole or in part) as a means of compliance to
4.2 Feathering Propellers—Eachfeatherablepropellermust
their Small Aircraft Airworthiness regulations (Hereinafter
have a means to un-feather in flight.
referred to as “the Rules”), refer to ASTM F44 webpage
4.3 Variable-Pitch Propellers—The propeller blade pitch
(www.ASTM.org/COMITTEE/F44.htm) which includes CAA
control system must meet the following requirements:
website links.
4.3.1 No single failure or malfunction in the propeller
1.4 Units—The values stated are SI units followed by
system will result in unintended travel of the propeller blades
Imperial units in square brackets. The values stated in each
to a position below the in-flight low-pitch position. Failure of
system may not be exact equivalents; therefore, each system
structural elements need not be considered if the occurrence of
shall be used independently of the other. Combining values
such a failure is shown to be extremely remote.
from the two systems may result in non-conformance with the
4.3.2 For propellers incorporating a method to select blade
standard.
pitch below the in-flight low pitch position, provisions must be
1.5 This standard does not purport to address all of the
made to sense and indicate to the flight crew that the propeller
safety concerns, if any, associated with its use. It is the blades are below that position by a defined amount. The
responsibility of the user of this standard to establish appro-
method for sensing and indicating the propeller blade pitch
priate safety and health practices and determine the applica- position must be such that its failure does not affect the control
bility of regulatory limitations prior to use.
of the propeller.
4.3.3 The propeller control system, operating in normal and
2. Referenced Documents
alternative operating modes and in transition between operat-
2
ing modes, performs the defined functions throughout the
2.1 ASTM Standards:
declared operating conditions and flight envelope.
F3060 Terminology for Aircraft
4.3.4 The propeller control system functionality is not
adversely affected by the declared environmental conditions,
3. Terminology
including temperature, electromagnetic interference (EMI),
3.1 See Terminology F3060.
high intensity radiated fields (HIRF) and lightning.
4.3.5 A method is provided to indicate that an operating
mode change has occurred if flight crew action is required.
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ThisspecificationisunderthejurisdictionofASTMCommitteeF44onGeneral
4.3.6 No single failure or malfunction of electrical or
Aviation Aircraft and is the direct responsibility of Subcommittee F44.40 on
electronic components in the control system results in a
Powerplant.
hazardous propeller effect.
Current edition approved May 1, 2015. Published June 2015. DOI: 10.1520/
F3065-15.
4.3.7 Failures or malfunctions directly affecting the propel-
2
For referenced ASTM standards, visit the ASTM website, www.astm.org, or
ler control system in a typical airplane, such as structural
contact ASTM Customer Service at [e-mail]. For Annual Book of ASTM
failures of attachments to the control, fire, or overheat, do not
Standards volume information, refer to the standard’s Document Summary page on
the ASTM website. lead to a hazardous propeller effect.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States
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F3065/F3065M − 15
4.3.8 The loss of normal propeller pitch control does not (1) 18 cm [7 in.] for each aeroplane with
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