ASTM F3066/F3066M-15
(Specification)Standard Specification for Powerplant Systems Specific Hazard Mitigation
Standard Specification for Powerplant Systems Specific Hazard Mitigation
ABSTRACT
This specification covers minimum requirements for hazard mitigation in propulsion systems installed on small aeroplanes. 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: engines (turbine engine installations, engine isolation), powerplant ice protection (induction system icing protection, turbine engines, engine rain hail ice and bird ingestion, etc.), designated fire zones (for reciprocating engine, for turbine engines), fire protection (combustion heater, shutoff means), firewalls, fire detection, fire extinguishing, and flammable fluid fire protection.
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 and health practices and determine the applicability of regulatory limitations prior to use.
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Standards Content (Sample)
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Designation: F3066/F3066M −15
Standard Specification for
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Powerplant Systems Specific 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.
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1. Scope 2.2 Federal Aviation Regulations:
14 CFR Part 23 Amendment 62
1.1 This specification covers minimum requirements for
hazard mitigation in propulsion systems installed on small
3. Terminology
aeroplanes.
3.1 See Terminology F3060 for definitions and abbrevia-
1.2 The applicant for a design approval must seek the
tions.
individual guidance to their respective CAA body concerning
4. Engines
the use of this standard as part of a certification plan. For
information on which CAA regulatory bodies have accepted
4.1 For Turbine Engine Installations:
this standard (in whole or in part) as a means of compliance to
4.1.1 Design precautions must be taken to minimize the
their Small Aircraft Airworthiness regulations (Hereinafter
hazards to the aeroplane in the event of an engine rotor failure
referred to as “the Rules”), refer to ASTM F44 webpage
or of a fire originating inside the engine which burns through
(www.ASTM.org/COMITTEE/F44.htm) which includes CAA
the engine case.
website links.
4.1.2 The powerplant systems associated with engine con-
trol devices, systems, and instrumentation must be designed to
1.3 Units—The values stated are SI units followed by
give reasonable assurance that those operating limitations that
imperial units in brackets. The values stated in each system
adversely affect turbine rotor structural integrity will not be
may not be exact equivalents; therefore, each system shall be
exceeded in service.
used independently of the other. Combining values from the
4.1.3 For turbine engines installations embedded in the
two systems may result in non-conformance with the standard.
fuselage behind the cabin, the effects of a fan exiting forward
1.4 This standard does not purport to address all of the
of the inlet case (fan disconnect) must be addressed, the
safety concerns, if any, associated with its use. It is the
passengers must be protected, and the aeroplane must be
responsibility of the user of this standard to establish appro-
controllable to allow for continued safe flight and landing.
priate safety and health practices and determine the applica-
bility of regulatory limitations prior to use. 4.2 Engine Isolation—The powerplants must be arranged
and isolated from each other to allow operation, in at least one
2. Referenced Documents
configuration, so that the failure or malfunction of any engine,
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or the failure or malfunction (including destruction by fire in
2.1 ASTM Standards:
the engine compartment) of any system that can affect an
F3060 Terminology for Aircraft
engine (other than a fuel tank if only one fuel tank is installed),
F3061 Specification for Systems and Equipment in Small
will not:
Aircraft
4.2.1 Prevent the continued safe operation of the remaining
F3062/F3062M Specification for Installation of Powerplant
engines; or
Systems
4.2.2 Require immediate action by any crewmember for
continued safe operation of the remaining engines.
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ThisspecificationisunderthejurisdictionofASTMCommitteeF44onGeneral
Aviation Aircraft and is the direct responsibility of Subcommittee F44.40 on
5. Powerplant Ice Protection
Powerplant.
Current edition approved May 1, 2015. Published August 2015. DOI: 10.1520/
5.1 Induction System Icing Protection:
F3066_F3066M-15.
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For referenced ASTM standards, visit the ASTM website, www.astm.org, or
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contact ASTM Customer Service at service@astm.org. For Annual Book of ASTM Available from U.S. Government Printing Office Superintendent of Documents,
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
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F3066/F3066M − 15
5.1.1 Reciprocating engines. Each reciprocating engine air system components that would adversely affect engine opera-
induction system must have means to prevent and eliminate tion or cause a serious loss of power or thrust.
icing. Unless this is done by other means, it must be shown 5.2.2 (1) Under the icing conditions specified in 14 CFR
that, in air free of visible moisture at a temperature of –1°C Part 23 and (2) in snow, both falling and blowing, within the
[30°F]. limitations established for the aeroplane for such operation.
5.1.2 Each
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