ASTM F2564-10

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-Dec-2009
• ICS: 49.020 - Aircraft and space vehicles in general
• Technical Committee: F37 - Light Sport Aircraft
• Drafting Committee: F37.10 - Glider

Relations

• Replaces: ASTM F2564-06 - Standard Specification for Design and Performance of a Light Sport Glider
• Effective Date: 01-Jan-2010
• Replaced By: ASTM F2564-11 - Standard Specification for Design and Performance of a Light Sport Glider
• Effective Date: 01-Nov-2011
• Referred By: ASTM F3060-20 - Standard Terminology for Aircraft
• Effective Date: 01-Jan-2010
• Referred By: ASTM F3035-22 - Standard Practice for Production Acceptance in the Manufacture of a Fixed Wing Light Sport Aircraft
• Effective Date: 01-Jan-2010
• Referred By: ASTM F2245-23 - Standard Specification for Design and Performance of a Light Sport Airplane
• Effective Date: 01-Jan-2010

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 – 10
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 3. Terminology
1.1 Thisspecificationcoversairworthinessrequirementsfor 3.1 Definitions:
the design of a powered or non-powered fixed wing light sport 3.1.1 flaps—any movable high lift device.
aircraft, a “glider.” 3.1.2 maximum empty weight, W (kg)—largest empty
E
1.2 This specification is applicable to the design of a light weightoftheglider,includingalloperationalequipmentthatis
sportaircraftgliderasdefinedbyregulationsandlimitedtoday installed in the glider: weight of the airframe, powerplant,
VFR flight. required equipment, optional and specific equipment, fixed
1.3 Aglider for the purposes of this specification is defined ballast, full engine coolant and oil, hydraulic fluid, and the
as a heavier than air aircraft that remains airborne through the unusable fuel. Hence, the maximum empty weight equals
dynamic reaction of the air with a fixed wing and in which the maximum takeoff weight minus minimum useful load:
ability to remain aloft in free flight does not depend on the W = W– W .
E U
propulsion from a power plant.Apowered glider is defined for 3.1.3 minimum useful load, W (kg)—where W = W – W .
U U E
the purposes of this specification as a glider equipped with a 3.2 Abbreviations:
power plant in which the flight characteristics are those of a 3.2.1 AOI—Aircraft Operating Instructions
2
glider when the power plant is not in operation. 3.2.2 AR—Aspect Ratio = b /S
1.4 ThevaluesinSIunitsaretoberegardedasthestandard. 3.2.3 b—wing span (m)
The values in parenthesis are for information only. 3.2.4 c—chord (m)
1.5 This standard does not purport to address all of the 3.2.5 CAS—calibrated air speed (m/s, kts)
safety concerns, if any, associated with its use. It is the 3.2.6 C —lift coefficient of the aircraft
L
responsibility of the user of this standard to establish appro- 3.2.7 C —drag coefficient of the aircraft
D
priate safety and health practices and determine the applica- 3.2.8 CG—center of gravity
bility of regulatory requirements prior to use. 3.2.9 C —moment coefficient (C is with respect to c/4
m m
point, positive nose up)
2. Referenced Documents
3.2.10 C —zero lift moment coefficient
MO
2
2.1 ASTM Standards: 3.2.11 C —normal coefficient
n
2
F2279 PracticeforQualityAssuranceintheManufactureof
3.2.12 g—acceleration as a result of gravity = 9.81 m/s
Fixed Wing Light Sport Aircraft 3.2.13 IAS—indicated air speed (m/s, kts)
F2295 Practice for Continued Operational Safety Monitor-
3.2.14 ICAO—International Civil Aviation Organization
ing of a Light Sport Aircraft 3.2.15 LSA—light sport aircraft
F2316 SpecificationforAirframeEmergencyParachutesfor
3.2.16 n—load factor
Light Sport Aircraft 3.2.17 n —glider positive maneuvering limit load factor
1
F2339 Practice for Design and Manufacture of Reciprocat-
at V
A
ing Spark Ignition Engines for Light Sport Aircraft 3.2.18 n —glider positive maneuvering limit load factor
2
at V
D
3.2.19 n —glider negative maneuvering limit load factor
3
1
This specification is under the jurisdiction ofASTM Committee F37 on Light
at V
A
Sport Aircraft and is the direct responsibility of Subcommittee F37.10 on Glider.
3.2.20 n —glider negative maneuvering limit load factor
4
Current edition approved Jan. 1, 2010. Published January 2010. Originally
at V
approved in 2006. Last previous edition approved in 2006 as F2564–06. DOI:
D
2 2
10.1520/F2564-10.
3.2.21 q—dynamic pressure = 0.004823 V kg/m , when V
2
For referenced ASTM standards, visit the ASTM website, www.astm.org, or
is in km/h
contact ASTM Customer Service at [e-mail]. For Annual Book of ASTM
2
3.2.22 S—wing area (m )
Standards volume information, refer to the standard’s Document Summary page on
the ASTM website. 3.2.23 V—airspeed (m/s, kts)
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959, United States.
1

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F2564 – 10
3.2.24 V —design maneuvering speed 4.3.1.3 For a two-place glider not less than the empty
A
3.2.25 V —design cruising speed weight of the glider, plus a weight of the occupants of 160 kg,
C
3.2.26 V —design diving speed plus the required minimum equipment, plus, for a powered
D
3.2.27 V —demonstrated flight diving speed glider, sufficient fuel for at least 30 min of flight at maximum
DF
3.2.28 V —design flap speed continuous power.
F
3.2.29 V —maximum flap extended speed
4.3.2 The design empty weig
...

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:F2564–06 Designation: F2564 – 10
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 flaps—any movable high lift device.
3.1.2 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 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
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
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 May 1, 2006. Published May 2006. DOI: 10.1520/F2564-06.on Light SportAircraft and is the direct responsibility of Subcommittee F37.10 on
Glider.
Current edition approved Jan. 1, 2010. Published January 2010. Originally approved in 2006. Last previous edition approved in 2006 as F2564–06. DOI:
10.1520/F2564-10.
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 – 10
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
3.2.25 V —design crui
...