ASTM F2564-13
(Specification)Standard Specification for Design and Performance of a Light Sport Glider
Standard Specification for Design and Performance of a Light Sport Glider
ABSTRACT
This specification covers airworthiness requirements for the design of a powered or non-powered fixed wing light sport aircraft, a �glider.� Stability shall be shown by a tendency for the glider to return toward steady flight after: (1) a �push� from steady flight that results in a speed increase, followed by a non-abrupt release of the pitch control; and (2) a �pull� from steady flight that results in a speed decrease, followed by a non-abrupt release of the pitch control. Strength requirements are specified in terms of limit loads (the maximum loads to be expected in service) and ultimate loads (limit loads multiplied by prescribed factors of safety). The suitability of each structural design detail and part having an important bearing on safety shall be established by test. Each combination of engine, exhaust, cooling and fuel system on a powered glider must be compatible with the glider, and function in a safe and satisfactory manner within the operational limits of the glider and powerplant. Each aircraft shall include Aircraft Operating Instructions (AOI).
SCOPE
1.1 This specification covers airworthiness requirements for the design of a powered or non-powered fixed wing light sport aircraft, a “glider.”
1.2 This specification is applicable to the design of a light sport aircraft glider as defined by regulations and limited to day VFR flight.
1.3 A glider for the purposes of this specification is defined as a heavier than air aircraft that remains airborne through the dynamic reaction of the air with a fixed wing and in which the ability to remain aloft in free flight does not depend on the propulsion from a power plant. A powered glider is defined for the purposes of this specification as a glider equipped with a power plant in which the flight characteristics are those of a glider when the power plant is not in operation.
1.4 The values in SI units are to be regarded as the standard. The values in parenthesis are for information only.
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 requirements prior to use.
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Designation:F2564 −13
StandardSpecification for
1
Design and Performance of a Light Sport Glider
This standard is issued under the fixed designation F2564; the number immediately following the designation indicates the year of
original adoption or, in the case of revision, the year of last revision.Anumber 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 Standards:
CS-22 Subpart HCertification Specifications for Sailplanes
1.1 Thisspecificationcoversairworthinessrequirementsfor
3
and Powered Sailplanes
the design of a powered or non-powered fixed wing light sport
aircraft, a “glider.”
3. Terminology
1.2 This specification is applicable to the design of a light
3.1 Definitions:
sportaircraftgliderasdefinedbyregulationsandlimitedtoday
3.1.1 electric propulsion unit, EPU—any electric motor and
VFR flight.
all associated devices used to provide thrust for an electric
1.3 Aglider for the purposes of this specification is defined
aircraft.
as a heavier than air aircraft that remains airborne through the
3.1.2 energy storage device, ESD—used to store energy as
dynamic reaction of the air with a fixed wing and in which the
part of a Electric Propulsion Unit (EPU). Typical energy
ability to remain aloft in free flight does not depend on the
storage devices include but are not limited to batteries, fuel
propulsion from a power plant.Apowered glider is defined for
cells or capacitors.
the purposes of this specification as a glider equipped with a
3.1.3 feathering—a single action from the cockpit that
power plant in which the flight characteristics are those of a
repositionsthepropellerbladestolowdragconfigurationwhen
glider when the power plant is not in operation.
the engine is not operating.
1.4 ThevaluesinSIunitsaretoberegardedasthestandard.
3.1.4 flaps—any movable high lift device.
The values in parenthesis are for information only.
3.1.5 maximum empty weight, W (kg) —largest empty
E
1.5 This standard does not purport to address all of the
weightoftheglider,includingalloperationalequipmentthatis
safety concerns, if any, associated with its use. It is the
installed in the glider: weight of the airframe, powerplant,
responsibility of the user of this standard to establish appro-
excluding energy storage device (ESD) for electric propulsion
priate safety and health practices and determine the applica-
unit when removable, required equipment, optional and spe-
bility of regulatory requirements prior to use.
cific equipment, fixed ballast, full engine coolant and oil,
2. Referenced Documents
hydraulic fluid, and the unusable fuel. Hence, the maximum
2 emptyweightequalsmaximumtakeoffweightminusminimum
2.1 ASTM Standards:
useful load: W = W– W .
E U
F2279Practice for QualityAssurance in the Manufacture of
3.1.6 minimum useful load, W (kg) —where W = W– W .
Fixed Wing Light Sport Aircraft
U U E
F2295Practice for Continued Operational Safety Monitor-
3.1.7 The terms “engine” referring to internal combustion
ing of a Light Sport Aircraft
enginesand“motor”referringtoelectricmotorsforpropulsion
F2316Specification for Airframe Emergency Parachutes
are used interchangeably within this standard.
F2339Practice for Design and Manufacture of Reciprocat-
3.1.8 The term “engine idle” or “throttle closed” when in
ing Spark Ignition Engines for Light Sport Aircraft
reference to electric propulsion units shall mean the minimum
F2840Practice for Design and Manufacture of Electric
power or propeller rotational speed condition for the electric
Propulsion Units for Light Sport Aircraft
motor as defined without electronic braking of the propeller
rotational speed.
1
This specification is under the jurisdiction ofASTM Committee F37 on Light 3.2 Abbreviations:
Sport Aircraft and is the direct responsibility of Subcommittee F37.10 on Glider.
3.2.1 AOI—Aircraft Operating Instructions
Current edition approved May 1, 2013. Published June 2013. Originally
2
3.2.2 AR—Aspect Ratio = b /S
approved in 2006. Last previous edition approved in 2011 as F2564–11. DOI:
10.1520/F2564-13.
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
3
Standards volume information, refer to the standard’s Document Summary page on Available from EuropeanAviation SafetyAgency (EASA), Postfach 10 12 53,
the ASTM website. D-50452 Koeln, Germany, http://www.easa.eu.int/home.php.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States
1
---------------------- Page: 1 ----------------------
F2564−13
3.2.3 b—wing span (m) 3.2.41 W —maximum empty aircraft weight (kg)
E
3.2.4 c—chord (m) 3.2.42 W —minimum useful load (kg)
U
2
3.2.5 CAS—calibrated air speed (m/s, kts) 3.2.
...
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: F2564 − 11 F2564 − 13
Standard Specification for
1
Design and Performance of a Light Sport Glider
This standard is issued under the fixed designation F2564; 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 airworthiness requirements for the design of a powered or non-powered fixed wing light sport
aircraft, a “glider.”
1.2 This specification is applicable to the design of a light sport aircraft glider as defined by regulations and limited to day VFR
flight.
1.3 A glider for the purposes of this specification is defined as a heavier than air aircraft that remains airborne through the
dynamic reaction of the air with a fixed wing and in which the ability to remain aloft in free flight does not depend on the
propulsion from a power plant. A powered glider is defined for the purposes of this specification as a glider equipped with a power
plant in which the flight characteristics are those of a glider when the power plant is not in operation.
1.4 The values in SI units are to be regarded as the standard. The values in parenthesis are for information only.
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
requirements prior to use.
2. Referenced Documents
2
2.1 ASTM Standards:
F2279 Practice for Quality Assurance in the Manufacture of Fixed Wing Light Sport Aircraft
F2295 Practice for Continued Operational Safety Monitoring of a Light Sport Aircraft
F2316 Specification for Airframe Emergency Parachutes
F2339 Practice for Design and Manufacture of Reciprocating Spark Ignition Engines for Light Sport Aircraft
F2840 Practice for Design and Manufacture of Electric Propulsion Units for Light Sport Aircraft
2.2 Other Standards:
3
CS-22 Subpart H Certification Specifications for Sailplanes and Powered Sailplanes
3. Terminology
3.1 Definitions:
3.1.1 electric propulsion unit, EPU—any electric motor and all associated devices used to provide thrust for an electric aircraft.
3.1.2 energy storage device, ESD—used to store energy as part of a Electric Propulsion Unit (EPU). Typical energy storage
devices include but are not limited to batteries, fuel cells or capacitors.
3.1.3 feathering—a single action from the cockpit that repositions the propeller blades to low drag configuration when the
engine is not operating.
3.1.4 flaps—any movable high lift device.
3.1.5 maximum empty weight, W (kg) —largest empty weight of the glider, including all operational equipment that is installed
E
in the glider: weight of the airframe, powerplant, excluding energy storage device (ESD) for electric propulsion unit when
removable, required equipment, optional and specific equipment, fixed ballast, full engine coolant and oil, hydraulic fluid, and the
unusable fuel. Hence, the maximum empty weight equals maximum takeoff weight minus minimum useful load: W = W – W .
E U
1
This specification is under the jurisdiction of ASTM Committee F37 on Light Sport Aircraft and is the direct responsibility of Subcommittee F37.10 on Glider.
Current edition approved Nov. 1, 2011May 1, 2013. Published December 2011June 2013. Originally approved in 2006. Last previous edition approved in 20102011 as
F2564 – 10.F2564 – 11. DOI: 10.1520/F2564-11.10.1520/F2564-13.
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 European Aviation Safety Agency (EASA), Postfach 10 12 53, D-50452 Koeln, Germany, http://www.easa.eu.int/home.php.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States
1
---------------------- Page: 1 ----------------------
F2564 − 13
3.1.6 minimum useful load, W (kg) —where W = W – W .
U U E
3.1.7 The terms “engine” referring to internal combustion engines and “motor” referring to electric motors for propulsion are
used interchangeably within this standard.
3.1.8 The term “engine idle” or “throttle closed” when in reference to electric propulsion units shall me
...
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