ASTM F2564-06

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.
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: 30-Apr-2006
• ICS: 49.020 - Aircraft and space vehicles in general
• Technical Committee: F37 - Light Sport Aircraft
• Drafting Committee: F37.10 - Glider

Relations

• Replaced By: ASTM F2564-10 - Standard Specification for Design and Performance of a Light Sport Glider
• Effective Date: 01-Jan-2010
• Referred By: ASTM F3060-20 - Standard Terminology for Aircraft
• Effective Date: 01-May-2006
• Referred By: ASTM F3035-22 - Standard Practice for Production Acceptance in the Manufacture of a Fixed Wing Light Sport Aircraft
• Effective Date: 01-May-2006
• Referred By: ASTM F2245-23 - Standard Specification for Design and Performance of a Light Sport Airplane
• Effective Date: 01-May-2006

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 – 06
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 3.1.2 maximum empty weight, W (kg)—largest empty
E
weightoftheglider,includingalloperationalequipmentthatis
1.1 Thisspecificationcoversairworthinessrequirementsfor
installed in the glider: weight of the airframe, powerplant,
the design of a powered or non-powered fixed wing light sport
required equipment, optional and specific equipment, fixed
aircraft, a “glider.”
ballast, full engine coolant and oil, hydraulic fluid, and the
1.2 This specification is applicable to the design of a light
unusable fuel. Hence, the maximum empty weight equals
sportaircraftgliderasdefinedbyregulationsandlimitedtoday
maximum takeoff weight minus minimum useful load:
VFR flight.
W = W– W .
1.3 Aglider for the purposes of this specification is defined E U
3.1.3 minimum useful load, W (kg)—where W = W– W .
U U E
as a heavier than air aircraft that remains airborne through the
3.2 Abbreviations:
dynamic reaction of the air with a fixed wing and in which the
3.2.1 AOI—Aircraft Operating Instructions
ability to remain aloft in free flight does not depend on the
2
3.2.2 AR—Aspect Ratio = b /S
propulsion from a power plant.Apowered glider is defined for
3.2.3 b—wing span (m)
the purposes of this specification as a glider equipped with a
3.2.4 c—chord (m)
power plant in which the flight characteristics are those of a
3.2.5 CAS—calibrated air speed (m/s, kts)
glider when the power plant is not in operation.
3.2.6 C —lift coefficient of the aircraft
L
1.4 ThevaluesinSIunitsaretoberegardedasthestandard.
3.2.7 C —drag coefficient of the aircraft
D
The values in parenthesis are for information only.
3.2.8 CG—center of gravity
1.5 This standard does not purport to address all of the
3.2.9 C —moment coefficient (C is with respect to c/4
m m
safety concerns, if any, associated with its use. It is the
point, positive nose up)
responsibility of the user of this standard to establish appro-
3.2.10 C —zero lift moment coefficient
MO
priate safety and health practices and determine the applica-
3.2.11 C —normal coefficient
n
bility of regulatory requirements prior to use.
2
3.2.12 g—acceleration as a result of gravity = 9.81 m/s
2. Referenced Documents
3.2.13 IAS—indicated air speed (m/s, kts)
2
3.2.14 ICAO—International Civil Aviation Organization
2.1 ASTM Standards:
3.2.15 LSA—light sport aircraft
F2279 PracticeforQualityAssuranceintheManufactureof
3.2.16 n—load factor
Fixed Wing Light Sport Aircraft
3.2.17 n —glider positive maneuvering limit load factor
F2295 Practice for Continued Operational Safety Monitor- 1
at V
ing of a Light Sport Aircraft A
3.2.18 n —glider positive maneuvering limit load factor
F2316 SpecificationforAirframeEmergencyParachutesfor 2
at V
Light Sport Aircraft D
3.2.19 n —glider negative maneuvering limit load factor
F2339 Practice for Design and Manufacture of Reciprocat- 3
at V
A
ing Spark Ignition Engines for Light Sport Aircraft
3.2.20 n —glider negative maneuvering limit load factor
4
3. Terminology
at V
D
2 2
3.2.21 q—dynamic pressure = 0.004823 V kg/m , when V
3.1 Definitions:
is in km/h
3.1.1 flaps—any movable high lift device.
2
3.2.22 S—wing area (m )
3.2.23 V—airspeed (m/s, kts)
1
This specification is under the jurisdiction ofASTM Committee F37 on Light
3.2.24 V —design maneuvering speed
Sport Aircraft and is the direct responsibility of Subcommittee F37.10 on Glider. A
Current edition approved May 1, 2006. Published May 2006. DOI: 10.1520/ 3.2.25 V —design cruising speed
C
F2564-06.
3.2.26 V —design diving speed
D
2
For referenced ASTM standards, visit the ASTM website, www.astm.org, or
3.2.27 V —demonstrated flight diving speed (V # V )
DF DF D
contact ASTM Customer Service at [e-mail]. For Annual Book of ASTM
3.2.28 V —design flap speed
Standards volume information, refer to the standard’s Document Summary page on
F
the ASTM website.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959, United States.
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F2564 – 06
3.2.29 V —maximum flap extended speed 4.3.1.3 For a two-place glider not less than the empty
FE
weight of the glider, plus a weight of the occupants of 160 kg,
3.2.30 V —maximum speed in level flight with maximum
H
plus the required minimum equipment, plus, for a powered
continuous power (corrected for sea level standard conditions)
glider, sufficient fuel for at least 30 min of flight at maxi
...