ASTM F2564-11

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.

General Information

• Status: Historical
• Publication Date: 31-Oct-2011
• ICS: 49.020 - Aircraft and space vehicles in general
• Technical Committee: F37 - Light Sport Aircraft
• Drafting Committee: F37.10 - Glider

Relations

• Replaces: ASTM F2564-10 - Standard Specification for Design and Performance of a Light Sport Glider
• Effective Date: 01-Nov-2011
• Replaced By: ASTM F2564-13 - Standard Specification for Design and Performance of a Light Sport Glider
• Effective Date: 01-May-2013
• Referred By: ASTM F2245-23 - Standard Specification for Design and Performance of a Light Sport Airplane
• Effective Date: 01-Nov-2011
• Referred By: ASTM F3060-20 - Standard Terminology for Aircraft
• Effective Date: 01-Nov-2011
• Referred By: ASTM F3035-22 - Standard Practice for Production Acceptance in the Manufacture of a Fixed Wing Light Sport Aircraft
• Effective Date: 01-Nov-2011

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:F2564 −11
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 3. Terminology
1.1 Thisspecificationcoversairworthinessrequirementsfor 3.1 Definitions:
the design of a powered or non-powered fixed wing light sport
3.1.1 feathering—a single action from the cockpit that
aircraft, a “glider.”
repositionsthepropellerbladestolowdragconfigurationwhen
the engine is not operating.
1.2 This specification is applicable to the design of a light
sportaircraftgliderasdefinedbyregulationsandlimitedtoday
3.1.2 flaps—any movable high lift device.
VFR flight.
3.1.3 maximum empty weight, W (kg) —largest empty
E
1.3 Aglider for the purposes of this specification is defined weightoftheglider,includingalloperationalequipmentthatis
as a heavier than air aircraft that remains airborne through the installed in the glider: weight of the airframe, powerplant,
dynamic reaction of the air with a fixed wing and in which the required equipment, optional and specific equipment, fixed
ability to remain aloft in free flight does not depend on the ballast, full engine coolant and oil, hydraulic fluid, and the
propulsion from a power plant.Apowered glider is defined for unusable fuel. Hence, the maximum empty weight equals
the purposes of this specification as a glider equipped with a maximum takeoff weight minus minimum useful load: W =
E
power plant in which the flight characteristics are those of a W– W .
U
glider when the power plant is not in operation.
3.1.4 minimum useful load, W (kg) —where W = W– W .
U U E
1.4 ThevaluesinSIunitsaretoberegardedasthestandard.
3.2 Abbreviations:
The values in parenthesis are for information only.
3.2.1 AOI—Aircraft Operating Instructions
1.5 This standard does not purport to address all of the
2
3.2.2 AR—Aspect Ratio = b /S
safety concerns, if any, associated with its use. It is the
3.2.3 b—wing span (m)
responsibility of the user of this standard to establish appro-
priate safety and health practices and determine the applica-
3.2.4 c—chord (m)
bility of regulatory requirements prior to use.
3.2.5 CAS—calibrated air speed (m/s, kts)
3.2.6 C —lift coefficient of the aircraft
2. Referenced Documents L
2
3.2.7 C —drag coefficient of the aircraft
D
2.1 ASTM Standards:
F2279Practice for QualityAssurance in the Manufacture of
3.2.8 CG—center of gravity
Fixed Wing Light Sport Aircraft
3.2.9 C —moment coefficient (C is with respect to c/4
m m
F2295Practice for Continued Operational Safety Monitor-
point, positive nose up)
ing of a Light Sport Aircraft
3.2.10 C —zero lift moment coefficient
MO
F2316Specification forAirframe Emergency Parachutes for
Light Sport Aircraft 3.2.11 C —normal coefficient
n
F2339Practice for Design and Manufacture of Reciprocat- 2
3.2.12 g—acceleration as a result of gravity = 9.81 m/s
ing Spark Ignition Engines for Light Sport Aircraft
3.2.13 IAS—indicated air speed (m/s, kts)
3.2.14 ICAO—International Civil Aviation Organization
1
This specification is under the jurisdiction ofASTM Committee F37 on Light
3.2.15 LSA—light sport aircraft
Sport Aircraft and is the direct responsibility of Subcommittee F37.10 on Glider.
Current edition approved Nov. 1, 2011. Published December 2011. Originally
3.2.16 n—load factor
approved in 2006. Last previous edition approved in 2010 as F2564–10. DOI:
3.2.17 n —glider positive maneuvering limit load factor
10.1520/F2564-11. 1
2
For referenced ASTM standards, visit the ASTM website, www.astm.org, or at V
A
contact ASTM Customer Service at [e-mail]. For Annual Book of ASTM
3.2.18 n —glider positive maneuvering limit load factor
Standards volume information, refer to the standard’s Document Summary page on 2
the ASTM website. at V
D
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States
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F2564−11
3.2.19 n —glider negative maneuvering limit load factor powerplant or propeller, if retractable, must be retracted,
3
at V except as otherwise noted.
A
3.2.20 n —glider negative maneuvering limit load factor
4.3 Load Distribution Limits:
4
at V
D 4.3.1 The maximum flying weight shall be determined.
2 2
4.3.1.1 The maximum weight must be determined so that it
3.2.21 q—dynamic pressure = 0.004823 V kg/m , when V
is:
is in km/h
2 (1)The highest weight selected by the applicant, and
3.2.22 S—wing area (m )
(2)The design maximum weight, which is the highest
3.2.23 V—airspeed (m/s, kts)
weight at which complian
...

This document is not anASTM standard and is intended only to provide the user of anASTM 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:F2564–10 Designation: F2564 – 11
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.Anumber 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 ThisspecificationisapplicabletothedesignofalightsportaircraftgliderasdefinedbyregulationsandlimitedtodayVFR
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
propulsionfromapowerplant.Apoweredgliderisdefinedforthepurposesofthisspecificationasagliderequippedwithapower
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 for Light Sport Aircraft
F2339 Practice for Design and Manufacture of Reciprocating Spark Ignition Engines for Light Sport Aircraft
3. Terminology
3.1 Definitions:
3.1.1 feathering—a single action from the cockpit that repositions the propeller blades to low drag configuration when the
engine is not operating.
3.1.2 flaps—any movable high lift device.
3.1.2
3.1.3 maximum empty weight, W (kg)—largestemptyweightoftheglider,includingalloperationalequipmentthatisinstalled
E
in the glider: weight of the airframe, powerplant, 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
3.1.3
3.1.4 minimum useful load, W (kg) —where W = W – W .
U U E
3.2 Abbreviations:
3.2.1 AOI—Aircraft Operating Instructions
2
3.2.2 AR—Aspect Ratio = b /S
3.2.3 b—wing span (m)
3.2.4 c—chord (m)
3.2.5 CAS—calibrated air speed (m/s, kts)
3.2.6 C —lift coefficient of the aircraft
L
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 Jan.Nov. 1, 2010.2011. Published January 2010.December 2011. Originally approved in 2006. Last previous edition approved in 20062010 as
F2564–106. DOI: 10.1520/F2564-101.
2
ForreferencedASTMstandards,visittheASTMwebsite,www.astm.org,[e-mail] 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

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F2564 – 11
3.2.7 C —drag coefficient of the aircraft
D
3.2.8 CG—center of gravity
3.2.9 C —moment coefficient (C is with respect to c/4 point, positive nose up)
m m
3.2.10 C —zero lift moment coefficient
MO
3.2.11 C —normal coefficient
n
2
3.2.12 g—acceleration as a result of gravity = 9.81 m/s
3.2.13 IAS—indicated air speed (m/s, kts)
3.2.14 ICAO—International Civil Aviation Organization
3.2.15 LSA—light sport aircraft
3.2.16 n—load factor
3.2.17 n —glider positive maneuvering limit load factor at V
1 A
3.2.18 n —glider positive maneuvering limit load factor at V
2 D
3.2.19 n —glider negative maneuvering limit load factor at V
3 A
3.2.20 n —glider negative maneuvering limit load factor at V
4 D
2 2
3.2.21 q—dynamic pressure = 0.004823 V kg/m , when V is in km/h
2
3.2.22 S—wing area (m )
3.2.23 V—airspeed (m/s, kts)
3.2.24 V —design maneuvering speed
A
3.2
...