ASTM F3063/F3063M-16a
(Specification)Standard Specification for Design and Integration of Fuel/Energy Storage and Delivery System Installations for Aeroplanes
Standard Specification for Design and Integration of Fuel/Energy Storage and Delivery System Installations for Aeroplanes
ABSTRACT
This specification prescribes minimum requirements for the design and integration of Fuel/Energy Storage and Delivery system installations for aeroplanes and is applicable to aeroplanes as defined in the 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 provided in this specification cover fuel system, fuel tanks, fuel pumps, fuel flow, pressure fueling systems, and fuel jettisoning system.
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 and health practices and determine the applicability of regulatory limitations prior to use.
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Designation: F3063/F3063M −16a
Standard Specification for
Design and Integration of Fuel/Energy Storage and Delivery
1
System Installations for Aeroplanes
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 F3116/F3116M Specification for Design Loads and Condi-
tions
1.1 This specification covers minimum requirements for the
2.2 Other Standard:
design and integration of Fuel/Energy Storage and Delivery
US 14 CFR Part 23 Airworthiness Standards: Normal,
system installations for aeroplanes.
Utility, Aerobatic and Commuter Category Airplanes
1.2 This specification is applicable to aeroplanes as defined
3
(Amendment 62)
in the F44 terminology standard.
1.3 The applicant for a design approval must seek the 3. Terminology
individual guidance to their respective CAA body concerning
3.1 The following are a selection of relevant terms. See
the use of this standard as part of a certification plan. For
Terminology F3060 for more definitions and abbreviations.
information on which CAA regulatory bodies have accepted
3.2 Definitions:
this standard (in whole or in part) as a means of compliance to
3.2.1 main pump, n—a pump that supplies sufficient fuel to
theirAeroplaneAirworthinessregulations(Hereinafterreferred
sustain the engine during normal operations.
to as “the Rules”), refer to ASTM F44 webpage
(www.ASTM.org/COMITTEE/F44.htm) which includes CAA 3.2.2 emergency pump, n—a pump that can sustain engine
website links. operation at full power in the event the main pump fails.
3.2.3 auxiliary pump, n—a pump that can provide some fuel
1.4 Units—The values stated are SI units followed by
flow during emergency operations but not enough to sustain
imperial units in brackets. The values stated in each system
engine operation at full power. Its function is to aid in priming
may not be exact equivalents; therefore, each system shall be
the engine and suppressing fuel vapors.
used independently of the other. Combining values from the
two systems may result in non-conformance with the standard.
3.3 Abbreviations:
1.5 This standard does not purport to address all of the
3.3.1 cc—cubic centimetre
safety concerns, if any, associated with its use. It is the
3.3.2 CFR—Code of Federal Regulations
responsibility of the user of this standard to establish appro-
3.3.3 RPM—rotation per minute
priate safety and health practices and determine the applica-
bility of regulatory limitations prior to use.
4. Fuel System
4.1 General:
2. Referenced Documents
4.1.1 Each fuel system must be constructed and arranged to
2
2.1 ASTM Standards:
ensure fuel flow at a rate and pressure established for proper
F3060 Terminology for Aircraft
engine and auxiliary power unit functioning under each likely
F3083/F3083M Specification for Emergency Conditions,
operating condition, including any maneuver for which certi-
Occupant Safety, and Accommodations
fication is requested and during which the engine or auxiliary
power unit is permitted to be in operation.
4.1.2 Eachfuelsystemforaturbineengineandcompression
1
ThisspecificationisunderthejurisdictionofASTMCommitteeF44onGeneral
ignition engine must be capable of sustained operation
Aviation Aircraft and is the direct responsibility of Subcommittee F44.40 on
Powerplant. throughout its flow and pressure range with fuel initially
Current edition approved Dec. 15, 2016. Published January 2017. Originally
saturated with water at 27°C [80°F] and having 0.75 cc of free
approved in 2015. Last previous edition approved in 2016 as F3063/F3063M – 16.
DOI: 10.1520/F3063_F3063M-16A.
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 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
1
---------------------- Page: 1 ----------------------
F3063/F3063M − 16a
waterper3.8L[1US-gal]addedandcooledtothemostcritical (3) That can be easily opened and closed.
condition for icing likely to be encountered in operation. (4) That is either located or protected to prevent fuel
4.1.3 Each fuel system for a turbine engine powered aero- spillage in the event of a landing with landing gear retracted.
plane must meet the applicable fuel venting requirements of 14 (5) That a
...
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 − 16 F3063/F3063M − 16a
Standard Specification for
Design and Integration of Fuel/Energy Storage and Delivery
1
System Installations for 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 and health practices and determine the applicability of regulatory
limitations prior to use.
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
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.
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
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 Feb. 1, 2016Dec. 15, 2016. Published March 2016January 2017. Originally approved in 2015. Last previous edition approved in 20152016 as
F3063/F3063M – 15.F3063/F3063M – 16. DOI: 10.1520/F3063_F3063M-16.10.1520/F3063_F3063M-16A.
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 − 16a
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 for proper engine
and auxiliary power unit functioning under each likely operating condition, including any maneuver for which certification is
requested and during which the engine or auxiliary power unit is permitted to be in operation.
4.1.2 Each fuel system for a turbine engine and compression ignition engine must be capable of sustained operation throughout
its flow and pressure range with fuel initially saturated with water at 27°C [80°F] and having 0.75 cc of free water
...
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