ASTM F3173/F3173M-17
(Specification)Standard Specification for Aircraft Handling Characteristics
Standard Specification for Aircraft Handling Characteristics
SCOPE
1.1 This specification addresses the airworthiness requirements for aeroplane handling characteristics in flight and on ground and water.
1.2 The term “aeroplane” is utilized in this specification as it was originally conceived for normal category fixed wing aircraft with a certified maximum take-off weight of 19 000 lb or less and a passenger seating configuration up to 19 as defined in the Rules. However, this standard may be more broadly applicable.
1.3 The applicant for a design approval must seek individual guidance from their respective 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 Airworthiness Rules (hereinafter referred to as “the Rules”), refer to the ASTM Committee F44 webpage (www.ASTM.org/COMITTEE/F44.htm) which includes CAA website links. It will be the responsibility of the applicant to validate any applicability beyond that identified in this specification and request acceptance from the applicable CAA.
1.4 Units—Normally, the values stated are SI units followed by US customary units in square 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 nonconformance 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:F3173/F3173M −17
Standard Specification for
1
Aircraft Handling Characteristics
ThisstandardisissuedunderthefixeddesignationF3173/F3173M;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 mendations issued by the World Trade Organization Technical
Barriers to Trade (TBT) Committee.
1.1 This specification addresses the airworthiness require-
ments for aeroplane handling characteristics in flight and on
2. Referenced Documents
ground and water.
2
2.1 ASTM Standards:
1.2 The term “aeroplane” is utilized in this specification as
F3060 Terminology for Aircraft
it was originally conceived for normal category fixed wing
F3061/F3061M Specification for Systems and Equipment in
aircraft with a certified maximum take-off weight of 19 000 lb
Small Aircraft
or less and a passenger seating configuration up to 19 as
F3116/F3116M Specification for Design Loads and Condi-
defined in the Rules. However, this standard may be more
tions
broadly applicable.
F3174/F3174M Specification for Establishing Operating
Limitations and Information for Aeroplanes
1.3 Theapplicantforadesignapprovalmustseekindividual
F3179/F3179M SpecificationforPerformanceofAeroplanes
guidance from their respective CAA body concerning the use
of this specification as part of a certification plan. For infor-
3. Terminology
mation on which CAA regulatory bodies have accepted this
specification (in whole or in part) as a means of compliance to 3.1 Refer to Terminology F3060 referenced in Section 2.
their Airworthiness Rules (hereinafter referred to as “the
4. Flight Characteristics
Rules”), refer to the ASTM Committee F44 webpage
(www.ASTM.org/COMITTEE/F44.htm) which includes CAA
4.1 General—Unless otherwise specified in a specific
website links. It will be the responsibility of the applicant to
requirement, the aeroplane shall meet the requirements of 4.2
validate any applicability beyond that identified in this speci-
– 4.9, Sections 5–8, 9.1, and 9.2 at all practical loading
fication and request acceptance from the applicable CAA.
conditions and operating altitudes for which certification has
been requested, not exceeding that established in Maximum
1.4 Units—Normally, the values stated are SI units followed
Operating Altitude Specification F3174/F3174M and without
by US customary units in square brackets. The values stated in
requiring exceptional piloting skill, alertness, or strength.
each system may not be exact equivalents; therefore, each
system shall be used independently of the other. Combining 4.2 Control Forces:
values from the two systems may result in nonconformance
4.2.1 The aeroplane shall be safely controllable and maneu-
with the standard. verable during all flight phases including:
4.2.1.1 Takeoff,
1.5 This standard does not purport to address all of the
4.2.1.2 Climb,
safety concerns, if any, associated with its use. It is the
4.2.1.3 Level flight,
responsibility of the user of this standard to establish appro-
4.2.1.4 Descent,
priate safety, health, and environmental practices and deter-
4.2.1.5 Go-around, and
mine the applicability of regulatory limitations prior to use.
4.2.1.6 Landing (power on and idle power) with the wing
1.6 This international standard was developed in accor-
flaps extended and retracted.
dance with internationally recognized principles on standard-
4.2.2 It shall be possible to make a smooth transition from
ization established in the Decision on Principles for the
one flight condition to another (including turns and slips)
Development of International Standards, Guides and Recom-
without danger of exceeding the limit load factor under any
probable operating condition (including, for multiengine
1
ThisspecificationisunderthejurisdictionofASTMCommitteeF44onGeneral
2
AviationAircraft and is the direct responsibility of Subcommittee F44.20 on Flight. For referenced ASTM standards, visit the ASTM website, www.astm.org, or
Current edition approved Sept. 1, 2017. Published October 2017. Originally contact ASTM Customer Service at service@astm.org. For Annual Book of ASTM
approved in 2015. Last previous edition approved in 2015 as F3173/F3173M – 15. Standards volume information, refer to the standard’s Document Summary page on
DOI: 10.1520/F3173_F3173M-17. the ASTM website.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States
1
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F3173/F3173M−17
aeroplanes, those conditions normally encountered in the (1) From the fully extended position to the most extended
sudden critical loss of thrust). gated position;
4.2.3
...
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: F3173/F3173M − 15 F3173/F3173M − 17
Standard Specification for
1
Aircraft Handling Characteristics of Aeroplanes
This standard is issued under the fixed designation F3173/F3173M; 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 establishesaddresses the airworthiness design standards associated with general airplane-handling
requirements for aeroplane handling characteristics in flight and on ground and water.
1.2 This specification is applicable to aeroplanes.The term “aeroplane” is utilized in this specification as it was originally
conceived for normal category fixed wing aircraft with a certified maximum take-off weight of 19 000 lb or less and a passenger
seating configuration up to 19 as defined in the Rules. However, this standard may be more broadly applicable.
1.3 The applicant for a design approval shallmust seek the individual guidance offrom their respective civil aviation authority
(CAA) 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 Airworthiness Rules (hereinafter referred to as “the Rules”), refer to the ASTM Committee F44 webpage
(www.ASTM.org/COMITTEE/F44.htm) which includes CAA website links. It will be the responsibility of the applicant to validate
any applicability beyond that identified in this specification and request acceptance from the applicable CAA.
1.4 Units—The Normally, the values stated in either are SI units or inch-pound units are to be regarded separately as standard.
followed by US customary units in square 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 nonconformance 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 requirementslimitations 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
F3061/F3061M Specification for Systems and Equipment in Small Aircraft
F3116/F3116M Specification for Design Loads and Conditions
F3174/F3174M Specification for Establishing Operating Limitations and Information for Aeroplanes
F3179/F3179M Specification for Performance of Aeroplanes
3
2.2 Federal Standard:
14 CFR Part 23 (Amendment 62) Airworthiness Standards: Normal, Utility, Aerobatic, and Commuter Category Aircraft
3. Terminology
3.1 Refer to Terminology F3060 referenced in Section 2.
4. General RequirementsFlight Characteristics
4.1 General—Unless otherwise specified in a specific requirement, the airplaneaeroplane shall meet the requirements of 4.2 –
4.9, Sections 5 – 8, 9.1, and 9.2 at all practical loading conditions and operating altitudes for which certification has been requested,
1
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 Dec. 1, 2015Sept. 1, 2017. Published February 2016October 2017. Originally approved in 2015. Last previous edition approved in 2015 as
F3173/F3173M – 15. DOI: 10.1520/F3173_F3173M-15.10.1520/F3173_F3173M-17.
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.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States
1
---------------------- Page: 1 ----------------------
F3173/F3173M − 17
not exceedi
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