ASTM F3063/F3063M-18
(Specification)Standard Specification for Aircraft Fuel and Energy Storage and Delivery
Standard Specification for Aircraft Fuel and Energy Storage and Delivery
SCOPE
1.1 This specification covers minimum requirements for the design and integration of Fuel/Energy Storage and Delivery system installations for aeroplanes.
1.2 This specification is applicable to aeroplanes as defined in the 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 Aeroplane 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 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.
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Designation: F3063/F3063M −18
Standard Specification for
1
Aircraft Fuel and Energy Storage and Delivery
ThisstandardisissuedunderthefixeddesignationF3063/F3063M;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 2. Referenced Documents
2
2.1 ASTM Standards:
1.1 This specification covers minimum requirements for the
F3060 Terminology for Aircraft
design and integration of Fuel/Energy Storage and Delivery
F3083/F3083M Specification for Emergency Conditions,
system installations for aeroplanes.
Occupant Safety, and Accommodations
1.2 This specification is applicable to aeroplanes as defined
F3116/F3116M Specification for Design Loads and Condi-
in the F44 terminology standard.
tions
F3117 Specification for Crew Interface in Aircraft
1.3 The applicant for a design approval must seek the
F3179/F3179M SpecificationforPerformanceofAeroplanes
individual guidance to their respective CAA body concerning
2.2 Other Standard:
the use of this standard as part of a certification plan. For
US 14 CFR Part 23 Airworthiness Standards: Normal,
information on which CAA regulatory bodies have accepted
Utility, Aerobatic and Commuter Category Airplanes
this standard (in whole or in part) as a means of compliance to
3
(Amendment 62)
theirAeroplaneAirworthinessregulations(Hereinafterreferred
to as “the Rules”), refer to ASTM F44 webpage
3. Terminology
(www.ASTM.org/COMITTEE/F44.htm) which includes CAA
3.1 The following are a selection of relevant terms. See
website links.
Terminology F3060 for more definitions and abbreviations.
1.4 Units—The values stated are SI units followed by
3.2 Definitions:
imperial units in brackets. The values stated in each system
3.2.1 main pump, n—a pump that supplies sufficient fuel to
may not be exact equivalents; therefore, each system shall be
sustain the engine during normal operations.
used independently of the other. Combining values from the
3.2.2 emergency pump, n—a pump that can sustain engine
two systems may result in non-conformance with the standard.
operation at full power in the event the main pump fails.
1.5 This standard does not purport to address all of the
3.2.3 auxiliary pump, n—a pump that can provide some fuel
safety concerns, if any, associated with its use. It is the
flow during emergency operations but not enough to sustain
responsibility of the user of this standard to establish appro-
engine operation at full power. Its function is to aid in priming
priate safety, health, and environmental practices and deter-
the engine and suppressing fuel vapors.
mine the applicability of regulatory limitations prior to use.
3.3 Abbreviations:
1.6 This international standard was developed in accor-
3.3.1 cc—cubic centimetre
dance with internationally recognized principles on standard-
3.3.2 CFR—Code of Federal Regulations
ization established in the Decision on Principles for the
3.3.3 RPM—rotation per minute
Development of International Standards, Guides and Recom-
mendations issued by the World Trade Organization Technical
4. Fuel System
Barriers to Trade (TBT) Committee.
4.1 General:
2
For referenced ASTM standards, visit the ASTM website, www.astm.org, or
1
ThisspecificationisunderthejurisdictionofASTMCommitteeF44onGeneral contact ASTM Customer Service at service@astm.org. For Annual Book of ASTM
Aviation Aircraft and is the direct responsibility of Subcommittee F44.40 on Standards volume information, refer to the standard’s Document Summary page on
Powerplant. the ASTM website.
3
Current edition approved Jan. 1, 2018. Published January 2018. Originally Available from U.S. Government Printing Office Superintendent of Documents,
approved in 2015. Last previous edition approved in 2016 as F3063/F3063M – 16a. 732 N. Capitol St., NW, Mail Stop: SDE, Washington, DC 20401, http://
DOI: 10.1520/F3063_F3063M-18. www.access.gpo.gov.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States
1
---------------------- Page: 1 ----------------------
F3063/F3063M − 18
4.1.1 Each fuel system must be constructed and arranged to 4.3.1 There must be at least one drain to allow safe drainage
ensure fuel flow at a rate and pressure established for proper of the entire fuel system with the aeroplane in its normal
engine and auxiliary power unit functioning under each likely ground attitude.
operating condition, including any maneuver for which certi- 4.3.2 Each drain installed for the purposes of draining the
fication is requested and during which the engine or auxiliary
entire fuel system or for the purposes of draining hazardous
power unit is permitted
...
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: F3063/F3063M − 16a F3063/F3063M − 18
Standard Specification for
Design and Integration of Fuel/Energy Aircraft Fuel and
Energy Storage and Delivery System Installations for
1
Aeroplanes
This standard is issued under the fixed designation F3063/F3063M; 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 the design and integration of Fuel/Energy Storage and Delivery system
installations for aeroplanes.
1.2 This specification is applicable to aeroplanes as defined in the 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 Aeroplane 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 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
F3083/F3083M Specification for Emergency Conditions, Occupant Safety, and Accommodations
F3116/F3116M Specification for Design Loads and Conditions
F3117 Specification for Crew Interface in Aircraft
F3179/F3179M Specification for Performance of Aeroplanes
2.2 Other Standard:
3
US 14 CFR Part 23 Airworthiness Standards: Normal, Utility, Aerobatic and Commuter Category Airplanes (Amendment 62)
3. Terminology
3.1 The following are a selection of relevant terms. See Terminology F3060 for more definitions and abbreviations.
3.2 Definitions:
3.2.1 main pump, n—a pump that supplies sufficient fuel to sustain the engine during normal operations.
3.2.2 emergency pump, n—a pump that can sustain engine operation at full power in the event the main pump fails.
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 Dec. 15, 2016Jan. 1, 2018. Published January 2017January 2018. Originally approved in 2015. Last previous edition approved in 2016 as
F3063/F3063M – 16.F3063/F3063M – 16a. DOI: 10.1520/F3063_F3063M-16A.10.1520/F3063_F3063M-18.
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 ----------------------
F3063/F3063M − 18
3.2.3 auxiliary pump, n—a pump that can provide some fuel flow during emergency operations but not enough to sustain engine
operation at full power. Its function is to aid in priming the engine and suppressing fuel vapors.
3.3 Abbreviations:
3.3.1 cc—cubic centimetre
3.3.2 CFR—Code of Federal Regulations
3.3.3 RPM—rotation per minute
4. Fuel System
4.1 General:
4.1.1 Each fuel system must be constructed and arranged to ensure fuel flow at a rate and pressure established
...
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