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ASTM F3063/F3063M-15

(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

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.

General Information

Status
Historical
Publication Date
31-May-2015
ICS
49.050 - Aerospace engines and propulsion systems
Technical Committee
F44 - General Aviation Aircraft
Drafting Committee
F44.40 - Powerplant
Current Stage
Ref Project

Relations

Replaced By
ASTM F3063/F3063M-16 - Standard Specification for Design and Integration of Fuel/Energy Storage and Delivery System Installations for Aeroplanes
Effective Date
01-Feb-2016
Referred By
ASTM F3239-22a - Standard Specification for Aircraft Electric Propulsion Systems
Effective Date
01-Jun-2015
Referred By
ASTM F3563-22 - Standard Specification for Design and Construction of Large Fixed Wing Unmanned Aircraft Systems
Effective Date
01-Jun-2015
Referred By
ASTM F3064/F3064M-21 - Standard Specification for Aircraft Powerplant Control, Operation, and Indication
Effective Date
01-Jun-2015
Referred By
ASTM F3062/F3062M-20 - Standard Specification for Aircraft Powerplant Installation
Effective Date
01-Jun-2015
Referred By
ASTM F3264-23 - Standard Specification for Normal Category Aeroplanes Certification
Effective Date
01-Jun-2015
Referred By
ASTM F3397/F3397M-21 - Standard Practice for Aeroplane Turbine Fuel System Hot Weather Operations
Effective Date
01-Jun-2015
Referred By
ASTM F3432-20a - Standard Practice for Powerplant Instruments
Effective Date
01-Jun-2015
Referred By
ASTM F3082/F3082M-23a - Standard Specification for Weights and Centers of Gravity of Aircraft
Effective Date
01-Jun-2015

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ASTM F3063/F3063M-15 - Standard Specification for Design and Integration of Fuel/Energy Storage and Delivery System Installations for AeroplanesASTM F3063/F3063M-15 - Standard Specification for Design and Integration of Fuel/Energy Storage and Delivery System Installations for Aeroplanes
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ASTM F3063/F3063M-15 - Standard Specification for Design and Integration of Fuel/Energy Storage and Delivery System Installations for Aeroplanes
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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: F3063/F3063M −15
StandardSpecification for
Design and Integration of Fuel/Energy Storage and Delivery
1
System Installations for Aeroplanes
Thisstandard is issued under the fixed designation F3063/F3063M;the numberimmediatelyfollowingthedesignationindicatestheyear
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 2.2 Other Standard:
US 14 CFR Part 23 Airworthiness Standards: Normal,
1.1 This specification covers minimum requirements for the
Utility, Aerobatic and Commuter Category Airplanes
design and integration of Fuel/Energy Storage and Delivery
3
(Amendment 62)
system installations for aeroplanes.
1.2 This specification is applicable to aeroplanes as defined
3. Terminology
in the F44 terminology standard.
3.1 The following are a selection of relevant terms. See
1.3 The applicant for a design approval must seek the
Terminology F3060 for more definitions and abbreviations.
individual guidance to their respective CAA body concerning
3.2 Definitions:
the use of this standard as part of a certification plan. For
3.2.1 main pump, n—a pump that supplies sufficient fuel to
information on which CAA regulatory bodies have accepted
sustain the engine during normal operations.
this standard (in whole or in part) as a means of compliance to
3.2.2 emergency pump, n—a pump that can sustain engine
theirAeroplaneAirworthiness regulations (Hereinafter referred
operation at full power in the event the main pump fails.
to as “the Rules”), refer to ASTM F44 webpage
(www.ASTM.org/COMITTEE/F44.htm) which includes CAA
3.2.3 auxiliary pump, n—a pump that can provide some fuel
website links.
flow during emergency operations but not enough to sustain
engine operation at full power. Its function is to aid in priming
1.4 Units—The values stated are SI units followed by
the engine and suppressing fuel vapors.
imperial units in brackets. The values stated in each system
may not be exact equivalents; therefore, each system shall be
3.3 Abbreviations:
used independently of the other. Combining values from the
3.3.1 cc—cubic centimeter
two systems may result in non-conformance with the standard.
3.3.2 CFR—Code of Federal Regulations
1.5 This standard does not purport to address all of the
3.3.3 RPM—rotation per minute
safety concerns, if any, associated with its use. It is the
responsibility of the user of this standard to establish appro-
4. Fuel System
priate safety and health practices and determine the applica-
4.1 General:
bility of regulatory limitations prior to use.
4.1.1 Each fuel system must be constructed and arranged to
2. Referenced Documents
ensure fuel flow at a rate and pressure established for proper
2
engine and auxiliary power unit functioning under each likely
2.1 ASTM Standards:
operating condition, including any maneuver for which certi-
F3060 Terminology for Aircraft
fication is requested and during which the engine or auxiliary
F3083/F3083M Specification for Emergency Conditions,
power unit is permitted to be in operation.
Occupant Safety, and Accommodations
4.1.2 Eachfuelsystemforaturbineengineandcompression
F3116/F3116M Specification for Design Loads and Condi-
ignition engine must be capable of sustained operation
tions
throughout its flow and pressure range with fuel initially
saturated with water at 27°C [80°F] and having 0.75 cc of free
1
ThisspecificationisunderthejurisdictionofASTMCommitteeF44onGeneral
waterper3.8L[1US-gal]addedandcooledtothemostcritical
Aviation Aircraft and is the direct responsibility of Subcommittee F44.40 on
Powerplant.
condition for icing likely to be encountered in operation.
Current edition approved June 1, 2015. Published August 2015. DOI: 10.1520/
F3063_F3063M-15.
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 − 15
4.1.3 Each fuel system for a turbine engine powered aero- (5) That allows the fuel to be caught for examination.
plane must meet the applicable fuel venting requirements of 14 (6) That can be observed for proper closing.
CFR part 34 for the US or the applicable fuel venting
5. Fuel Tanks
requirements as contained in the rules specified by the appli-
cant’s local civil aviatio
...

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Standard Specification for Aircraft Powerplant Installation 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.
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.  
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3.1 This specification provides designers and manufacturers of electric propulsion for light sport aircraft design references and criteria to use in designing and manufacturing EPUs.  
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SCOPE
1.1 This practice covers minimum requirements for the design and manufacture of Electric Propulsion Units (EPU) for light sport aircraft, VFR use. The EPU shall as a minimum consist of the electric motor, associated controllers, disconnects and wiring, an Energy Storage Device (ESD) such as a battery or capacitor, or both, and EPU monitoring gauges and meters. Optional onboard charging devices, in-flight charging devices or other technology may be included.  
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