ASTM F3082/F3082M-23a

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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: F3082/F3082M − 23 F3082/F3082M − 23a
Standard Specification for
Weights and Centers of Gravity of Aircraft
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
1.1 This specification establishes the airworthiness design standards associated with aeroplane weight and center of gravity.
1.2 The term “aeroplane” is utilized in this specification as it was originally conceived for normal category fixed wing aircraft with
a maximum certificated weight of 19 000 lb or less and a passenger seating configuration up to 19 as defined in the Rules. However,
these standards may be more broadly applicable and their usage should not be unnecessarily limited.
1.3 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.
1.4 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.
1.5 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.
2. Referenced Documents
2.1 ASTM Standards:
F3060 Terminology for Aircraft
F3063/F3063M Specification for Aircraft Fuel Storage and Delivery
3. Terminology
3.1 See Terminology F3060 for definitions and abbreviations.
This specification is under the jurisdiction of ASTM Committee F44 on General Aviation Aircraft and is the direct responsibility of Subcommittee F44.20 on Flight.
Current edition approved Feb. 15, 2023Sept. 1, 2023. Published February 2023September 2023. Originally approved in 2016. Last previous edition approved in 20222023
as F3082/F3082M – 22.F3082/F3082M – 23. DOI: 10.1520/F3082_F3082M-23.10.1520/F3082_F3082M-23A.
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.
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F3082/F3082M − 23a
4. Weight and CG Limits
4.1 Load Distribution Limits—The applicant must determine limits for weights and centers of gravity that provide for the safe
operation of the airplane.
4.1.1 Ranges of weights and centers of gravity within which the aeroplane may be safely operated shall be established. If a weight
and center of gravity combination is allowable only within certain lateral load distribution limits that could be inadvertently
exceeded, these limits shall be established for the corresponding weight and center of gravity combinations.
4.1.2 The load distribution limits shall not exceed any of the following:
(1) The selected limits,
(2) The limits at which the structure is proven, or
(3) The limits at which compliance with each applicable flight requirement is shown.
4.2 Removable Ballast—Removable ballast may be used in showing compliance with the flight requirements if:
4.2.1 The place for carrying ballast is properly designed and easily accessible to enable, during pre-flight inspection, that the
ballast is properly installed.
F3082/F3082M − 23a
4.2.2 Instructions are included in the aeroplane flight manual, approved manual material, or markings and placards for the proper
placement of the removable ballast under each loading condition for which removable ballast is necessary.
4.3 Weight Limits:
4.3.1 Maximum Weight—The maximum weight is the highest weight at which compliance with each applicable requirement (other
than those complied with at the design landing weight) is shown. The maximum weight shall be established so that it is:
4.3.1.1 Not more than the least of:
(1) The highest weight selected by the applicant;
(2) The design maximum weight, which is the highest weight at which compliance with each applicable structural loading
condition (other than those complied with at the design landing weight) is shown;
(3) The highest weight at which compliance with each applicable flight requirement is shown, and
4.3.1.2 Not less than the weight with:
(1) Each seat occupied, assuming a weight of 77 kg [170 lb] for each occupant or 86 kg [190 lb] for Level 1 aeroplanes with
a stall speed of 45 kts or lower and for aeroplanes approved for aerobatics except that seats other than pilot seats may be placarded
for a lesser weight, and
(a) Oil at full capacity,
(b) At least enough fuel for maximum continuous power operation for:
(1) 30 min for day-VFR-approved aeroplanes, and
(2) 45 min for night-VFR- and IFR-approved aeroplanes, or
(3) Level 1 aeroplanes with a stall speed of 45 kts or less enough fuel for 1 h of operation, or
(2) The required minimum crew, and fuel and oil to full capacity.
4.3.2 Minimum Weight—The minimum weight (the lowest weight at which compliance with each applicable requirement is
shown) shall be established so that it is not more than the sum of:
4.3.2.1 The empty weight determined under Section 6,
4.3.2.2 The weight of the required minimum
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