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ASTM F3082/F3082M-16

(Specification)

Standard Specification for Flight for General Aviation Aeroplanes

Standard Specification for Flight for General Aviation Aeroplanes

ABSTRACT
This specification covers airworthiness design standards associated with aeroplane flight. The applicant for a design approval shall seek the individual guidance of their respective civil aviation authority (CAA) body concerning the use of this specification as part of a certification plan.
Included in this specification are general requirements for proof of compliance, load distribution limits, weight limits (minimum and maximum weight), empty weight and corresponding center of gravity, and removable ballast.
SCOPE
1.1 This specification establishes the airworthiness design standards associated with aeroplane flight.  
1.2 The applicant for a design approval shall seek the individual guidance of their respective civil aviation authority (CAA) body concerning the use of this specification as part of a certification plan. For information on which CAA regulatory bodies have accepted this specification (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 Committee F44 webpage (www.astm.org/COMMITTEE/F44.htm), which includes CAA website links.  
1.3 Units—The values stated in either SI units or inch-pound units are to be regarded separately as standard. 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.

General Information

Status
Historical
Publication Date
31-Jan-2016
ICS
49.020 - Aircraft and space vehicles in general
Technical Committee
F44 - General Aviation Aircraft
Drafting Committee
F44.20 - Flight
Current Stage
Ref Project

Relations

Referred By
ASTM F3563-22 - Standard Specification for Design and Construction of Large Fixed Wing Unmanned Aircraft Systems
Effective Date
01-Feb-2016
Referred By
ASTM F3120/F3120M-20 - Standard Specification for Ice Protection for General Aviation Aircraft
Effective Date
01-Feb-2016
Referred By
ASTM F3264-23 - Standard Specification for Normal Category Aeroplanes Certification
Effective Date
01-Feb-2016
Referred By
ASTM F3060-20 - Standard Terminology for Aircraft
Effective Date
01-Feb-2016
Referred By
ASTM F3174/F3174M-21 - Standard Specification for Establishing Operating Limitations and Information for Aeroplanes
Effective Date
01-Feb-2016

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ASTM F3082/F3082M-16 - Standard Specification for Flight for General Aviation AeroplanesASTM F3082/F3082M-16 - Standard Specification for Flight for General Aviation Aeroplanes
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ASTM F3082/F3082M-16 - Standard Specification for Flight for General Aviation Aeroplanes
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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:F3082/F3082M −16
Standard Specification for
1
Flight for General Aviation Aeroplanes
This standard is issued under the fixed designation F3082/F3082M; 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 4. General
1.1 This specification establishes the airworthiness design
4.1 Proof of Compliance:
standards associated with aeroplane flight. 4.1.1 Each criterion of this specification shall be met at each
appropriate combination of weight and center of gravity within
1.2 The applicant for a design approval shall seek the
the range of loading conditions for which certification is
individual guidance of their respective civil aviation authority
requested. This shall be shown by:
(CAA) body concerning the use of this specification as part of
4.1.1.1 Tests upon an aeroplane of the type for which
a certification plan. For information on which CAA regulatory
certification is requested or by calculations based on, and equal
bodies have accepted this specification (in whole or in part) as
in accuracy to, the results of testing.
a means of compliance to their small aircraft airworthiness
4.1.1.2 Systematic investigation of each probable combina-
regulations (hereinafter referred to as “the Rules”), refer to
tion of weight and center of gravity, if compliance cannot be
ASTM Committee F44 webpage (www.astm.org/
reasonably inferred from combinations investigated.
COMMITTEE/F44.htm), which includes CAA website links.
4.1.2 The general tolerances in Table 1 are allowed during
1.3 Units—The values stated in either SI units or inch-
flight testing. However, greater tolerances may be allowed in
pound units are to be regarded separately as standard. The
particular tests, if properly justified.
values stated in each system may not be exact equivalents;
4.2 Load Distribution Limits:
therefore, each system shall be used independently of the other.
4.2.1 Ranges of weights and centers of gravity within which
Combining values from the two systems may result in non-
the aeroplane may be safely operated shall be established. If a
conformance with the standard.
weight and center of gravity combination is allowable only
1.4 This standard does not purport to address all of the
within certain lateral load distribution limits that could be
safety concerns, if any, associated with its use. It is the
inadvertently exceeded, these limits shall be established for the
responsibility of the user of this standard to establish appro-
corresponding weight and center of gravity combinations.
priate safety and health practices and determine the applica-
4.2.2 The load distribution limits shall not exceed any of the
bility of regulatory limitations prior to use.
following:
2. Referenced Documents
(1) The selected limits,
2
(2) The limits at which the structure is proven, or
2.1 ASTM Standards:
(3) The limits at which compliance with each applicable
F3060 Terminology for Aircraft
flight requirement is shown.
F3063/F3063M Specification for Design and Integration of
Fuel/Energy Storage and Delivery System Installations for
4.3 Weight Limits:
Aeroplanes
4.3.1 Maximum Weight—The maximum weight is the high-
F3174/F3174M Specification for Establishing Operating
est weight at which compliance with each applicable require-
Limitations and Information for Aeroplanes
ment (other than those complied with at the design landing
weight) is shown.The maximum weight shall be established so
3. Terminology
that it is:
3.1 See Terminology F3060 for definitions and abbrevia-
4.3.1.1 Not more than the least of:
tions.
(1) The highest weight selected by the applicant;
(2) The design maximum weight, which is the highest
1
ThisspecificationisunderthejurisdictionofASTMCommitteeF44onGeneral
weight at which compliance with each applicable structural
AviationAircraft and is the direct responsibility of Subcommittee F44.20 on Flight.
loading condition (other than those complied with at the design
Current edition approved Feb. 1, 2016. Published March 2016. DOI: 10.1520/
F3082_F3082M-16.
landing weight) is shown;
2
For referenced ASTM standards, visit the ASTM website, www.astm.org, or
(3) The highest weight at which compliance with each
contact ASTM Customer Service at service@astm.org. For Annual Book of ASTM
applicable flight requirement is shown.
Standards volume information, refer to the standard’s Document Summary page on
the ASTM website. 4.3.1.2 Not less than the weight with:
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States
1

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F3082/F3082M−16
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