ASTM F3066/F3066M-17
(Specification)Standard Specification for Aircraft Powerplant Installation Hazard Mitigation
Standard Specification for Aircraft Powerplant Installation Hazard Mitigation
SCOPE
1.1 This specification covers minimum requirements for hazard mitigation in propulsion systems installed on small aeroplanes.
1.2 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.
1.3 Units—The values stated are SI units followed by imperial units in 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.
1.4 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.
1.5 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.
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Designation: F3066/F3066M −17
Standard Specification for
1
Aircraft Powerplant Installation Hazard Mitigation
ThisstandardisissuedunderthefixeddesignationF3066/F3066M;thenumberimmediatelyfollowingthedesignationindicatestheyear
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 F3061/F3061M Specification for Systems and Equipment in
Small Aircraft
1.1 This specification covers minimum requirements for
F3062/F3062M Specification for Installation of Powerplant
hazard mitigation in propulsion systems installed on small
Systems
aeroplanes.
F3114 Specification for Structures
1.2 The applicant for a design approval must seek the
F3116/F3116M Specification for Design Loads and Condi-
individual guidance to their respective CAA body concerning
tions
the use of this standard as part of a certification plan. For
F3120/F3120M Specification for Ice Protection for General
information on which CAA regulatory bodies have accepted
Aviation Aircraft
this standard (in whole or in part) as a means of compliance to
3
2.2 Federal Aviation Regulations:
their Small Aircraft Airworthiness regulations (Hereinafter
14 CFR Part 23 Amendment 62
referred to as “the Rules”), refer to ASTM F44 webpage
(www.ASTM.org/COMITTEE/F44.htm) which includes CAA
3. Terminology
website links.
3.1 See Terminology F3060 for definitions and abbrevia-
1.3 Units—The values stated are SI units followed by
tions.
imperial units in brackets. The values stated in each system
may not be exact equivalents; therefore, each system shall be
4. Engines
used independently of the other. Combining values from the
4.1 For Turbine Engine Installations:
two systems may result in non-conformance with the standard.
4.1.1 Design precautions must be taken to minimize the
1.4 This standard does not purport to address all of the
hazards to the aeroplane in the event of an engine rotor failure
safety concerns, if any, associated with its use. It is the
or of a fire originating inside the engine which burns through
responsibility of the user of this standard to establish appro-
the engine case.
priate safety, health, and environmental practices and deter-
4.1.2 The powerplant systems associated with engine con-
mine the applicability of regulatory limitations prior to use.
trol devices, systems, and instrumentation must be designed to
1.5 This international standard was developed in accor-
give reasonable assurance that those operating limitations that
dance with internationally recognized principles on standard-
adversely affect turbine rotor structural integrity will not be
ization established in the Decision on Principles for the
exceeded in service.
Development of International Standards, Guides and Recom-
4.1.3 For turbine engines installations embedded in the
mendations issued by the World Trade Organization Technical
fuselage behind the cabin, the effects of a fan exiting forward
Barriers to Trade (TBT) Committee.
of the inlet case (fan disconnect) must be addressed, the
passengers must be protected, and the aeroplane must be
2. Referenced Documents
controllable to allow for continued safe flight and landing.
2
2.1 ASTM Standards:
4.2 Engine Isolation—The powerplants must be arranged
F3060 Terminology for Aircraft
and isolated from each other to allow operation, in at least one
configuration, so that the failure or malfunction of any engine,
or the failure or malfunction (including destruction by fire in
1
ThisspecificationisunderthejurisdictionofASTMCommitteeF44onGeneral
the engine compartment) of any system that can affect an
Aviation Aircraft and is the direct responsibility of Subcommittee F44.40 on
Powerplant.
engine (other than a fuel tank if only one fuel tank is installed),
Current edition approved Dec. 1, 2017. Published January 2018. Originally
will not:
approved in 2015. Last previous edition approved in 2015 as F3066/F3066M – 15.
DOI: 10.1520/F3066_F3066M-17.
2
For referenced ASTM standards, visit the ASTM website, www.astm.org, or
3
contact ASTM Customer Service at service@astm.org. For Annual Book of ASTM AvailablefromU.S.GovernmentPrintingOfficeSuperintendentofDocuments,
Standards volume information, refer to the standard’s Document Summary page on 732 N. Capitol St., NW, Mail Stop: SDE, Washington, DC 20401, http://
the ASTM website. www.access.gpo.gov.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States
1
---------------------- Page: 1 ----------------------
F3066/F3066M − 17
4.2.1 Prevent the continued safe operation of the remaining (1) Adversely affect installed engine operation or cause a
engines; or sustained loss of power or thrust; or an unaccepta
...
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: F3066/F3066M − 15 F3066/F3066M − 17
Standard Specification for
Aircraft Powerplant Systems Specific Installation Hazard
1
Mitigation
This standard is issued under the fixed designation F3066/F3066M; 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 covers minimum requirements for hazard mitigation in propulsion systems installed on small aeroplanes.
1.2 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.
1.3 Units—The values stated are SI units followed by imperial units in 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.
1.4 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.
1.5 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
F3061F3061/F3061M Specification for Systems and Equipment in Small Aircraft
F3062/F3062M Specification for Installation of Powerplant Systems
F3114 Specification for Structures
F3116/F3116M Specification for Design Loads and Conditions
F3120/F3120M Specification for Ice Protection for General Aviation Aircraft
3
2.2 Federal Aviation Regulations:
14 CFR Part 23 Amendment 62
3. Terminology
3.1 See Terminology F3060 for definitions and abbreviations.
4. Engines
4.1 For Turbine Engine Installations:
4.1.1 Design precautions must be taken to minimize the hazards to the aeroplane in the event of an engine rotor failure or of
a fire originating inside the engine which burns through the engine case.
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, 2015Dec. 1, 2017. Published August 2015January 2018. Originally approved in 2015. Last previous edition approved in 2015 as
F3066/F3066M – 15. DOI: 10.1520/F3066_F3066M-15.10.1520/F3066_F3066M-17.
2
For referenced ASTM standards, visit the ASTM website, www.astm.org, or contact ASTM Customer Service at service@astm.org. For Annual Book of ASTM Standards
volume information, refer to the standard’s Document Summary page on the ASTM website.
3
Available from U.S. Government Printing Office Superintendent of Documents, 732 N. Capitol St., NW, Mail Stop: SDE, Washington, DC 20401, http://
www.access.gpo.gov.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States
1
---------------------- Page: 1 ----------------------
F3066/F3066M − 17
4.1.2 The powerplant systems associated with engine control devices, systems, and instrumentation must be designed to give
reasonable assurance that those operating limitations that adversely affect turbine rotor structural integrity will not be exceeded in
service.
4.1.3 For turbine engines installations embedded in the fuselage behind the cabin, the effects of a fan exiting forward of the inlet
case (fan disconnect) must be addressed, the passengers must be protected, and the aeroplane must be controllable to allow for
continued safe flight and landing.
4.2 Engine Isolation—The powerplants must be arranged and isolated from each other to allow operation, in at least one
configuration, so that the failure or malfunct
...
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