ASTM F2245-09

Standard Specification for Design and Performance of a Light Sport Airplane

ABSTRACT
This specification covers airworthiness requirements for the design of powered fixed wing light sport aircraft, an “airplane.” In order to comply with flight requirements, the following shall be evaluated: load distribution limit, propeller speed and pitch limit, stalling speed, takeoff, climb, landing, balked landing, controllability and maneuverability, vibrations, and ground control and stability. For compliance of structure requirements, the following shall be considered: flight loads; control surface and system loads; horizontal stabilizing and balancing surfaces (balancing loads, maneuvering loads, and gust loads); vertical stabilizing surfaces (maneuvering loads, gust loads, and outboard fins or winglets); supplementary conditions for stabilizing surfaces; ailerons, wing flaps, and special devices; ground load conditions; water load conditions; emergency landing conditions; and other loads. The aircraft shall be designed with the following minimum instrumentation and equipment: flight and navigation instruments such as airspeed indicator, and altimeter; powerplant instruments such as fuel quantity indicator, tachometer (RPM), engine “kill” switch, and engine instruments; miscellaneous equipment such as master switch, and overload protection device; and safety belts and harnesses. Each airplane shall include a Pilot Operating Handbook (POH).
SCOPE
1.1 This specification covers airworthiness requirements for the design of powered fixed wing light sport aircraft, an “airplane.”
1.2 This specification is applicable to the design of a light sport aircraft/airplane as defined by regulations and limited to VFR flight.
1.3 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-Mar-2009
• ICS: 49.020 - Aircraft and space vehicles in general
• Technical Committee: F37 - Light Sport Aircraft
• Drafting Committee: F37.20 - Airplane

Relations

• Replaces: ASTM F2245-08 - Standard Specification for Design and Performance of a Light Sport Airplane
• Effective Date: 01-Apr-2009
• Replaced By: ASTM F2245-10 - Standard Specification for Design and Performance of a Light Sport Airplane
• Effective Date: 01-May-2010
• Referred By: ASTM F3035-22 - Standard Practice for Production Acceptance in the Manufacture of a Fixed Wing Light Sport Aircraft
• Effective Date: 01-Apr-2009
• Referred By: ASTM F3298-19 - Standard Specification for Design, Construction, and Verification of Lightweight Unmanned Aircraft Systems (UAS)
• Effective Date: 01-Apr-2009
• Referred By: ASTM F2483-18e1 - Standard Practice for Maintenance and the Development of Maintenance Manuals for Light Sport Aircraft
• Effective Date: 01-Apr-2009
• Referred By: ASTM F3060-20 - Standard Terminology for Aircraft
• Effective Date: 01-Apr-2009
• Referred By: ASTM F3409-19e1 - Standard Practice for Simplified Aircraft Loads Determination
• Effective Date: 01-Apr-2009
• Referred By: ASTM F2745-15(2023) - Standard Specification for Required Product Information to be Provided with an Airplane
• Effective Date: 01-Apr-2009
• Referred By: ASTM F2930-16e1 - Standard Guide for Compliance with Light Sport Aircraft Standards
• Effective Date: 01-Apr-2009
• Referred By: ASTM F2746-14(2023) - Standard Specification for Pilot’s Operating Handbook (POH) for Light Sport Airplane
• Effective Date: 01-Apr-2009
• Referred By: ASTM F2507-15 - Standard Specification for Recreational Airpark Design
• Effective Date: 01-Apr-2009
• Referred By: ASTM F2840-14(2023) - Standard Practice for Design and Manufacture of Electric Propulsion Units for Light Sport Aircraft
• Effective Date: 01-Apr-2009

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: F2245 – 09
Standard Specification for
1
Design and Performance of a Light Sport Airplane
This standard is issued under the fixed designation F2245; 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 (N)—largest empty
E
weightoftheairplane,includingalloperationalequipmentthat
1.1 Thisspecificationcoversairworthinessrequirementsfor
is installed in the airplane: weight of the airframe, powerplant,
the design of powered fixed wing light sport aircraft, an
required equipment, optional and specific equipment, fixed
“airplane.”
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
sport aircraft/airplane as defined by regulations and limited to
maximumtakeoffweightminusminimumusefulload:W =W
E
VFR flight.
− W .
1.3 This standard does not purport to address all of the U
3.1.3 minimum useful load, W (N)—where W = W − W .
U U E
safety concerns, if any, associated with its use. It is the
3.1.4 night—hoursbetweentheendofeveningciviltwilight
responsibility of the user of this standard to establish appro-
and the beginning of morning civil twilight.
priate safety and health practices and determine the applica-
3.1.4.1 Discussion—Civiltwilightendsintheeveningwhen
bility of regulatory requirements prior to use.
the center of the sun’s disc is 6° below the horizon, and begins
2. Referenced Documents inthemorningwhenthecenterofthesun’sdiscis6°belowthe
2
horizon.
2.1 ASTM Standards:
3.2 Abbreviations:
F2316 SpecificationforAirframeEmergencyParachutesfor
2
3.2.1 AR—aspect ratio = b S
Light Sport Aircraft
/
3.2.2 b—wing span, (m)
F2339 Practice for Design and Manufacture of Reciprocat-
3.2.3 c—chord, (m)
ing Spark Ignition Engines for Light Sport Aircraft
3.2.4 CAS—calibrated air speed, (m/s, kts)
F2538 Practice for Design and Manufacture of Reciprocat-
3.2.5 C —lift coefficient of the airplane
ing Compression Ignition Engines for Light SportAircraft L
3
3.2.6 C —drag coefficient of the airplane
2.2 Federal Aviation Regulations:
D
3.2.7 CG—center of gravity
FAR-33 Airworthiness Standards: Aircraft Engines
4
3.2.8 C —moment coefficient (C is with respect to c/4
2.3 Joint Aviation Requirements:
m m
point, positive nose up)
JAR-E Engines
3.2.9 C —zero lift moment coefficient
JAR-22 Sailplanes and Powered Sailplanes
MO
3.2.10 C —normal coefficient
n
2
3. Terminology
3.2.11 g—acceleration as a result of gravity = 9.81 m/s
3.2.12 IAS—indicated air speed (m/s, kts)
3.1 Definitions:
3.2.13 ICAO—International Civil Aviation Organization
3.1.1 flaps—any movable high lift device.
3.2.14 LSA—light sport aircraft
3.2.15 MAC—mean aerodynamic chord (m)
1
This specification is under the jurisdiction of ASTM Committee F37 on Light
3.2.16 n—load factor
SportAircraft and is the direct responsibility of Subcommittee F37.20 onAirplane.
3.2.17 n —airplane positive maneuvering limit load factor
Current edition approved April 1, 2009. Published May 2009. Originally 1
approved in 2004. Last previous edition approved in 2008 as F2245–08. DOI: 3.2.18 n —airplane negative maneuvering limit load factor
2
10.1520/F2245-09.
3.2.19 n —load factor on wheels
3
2
For referenced ASTM standards, visit the ASTM website, www.astm.org, or
3.2.20 P—power, (kW)
contact ASTM Customer Service at [e-mail]. For Annual Book of ASTM
3
3.2.21 r—air density (kg/m )=1.225 at sea level standard
Standards volume information, refer to the standard’s Document Summary page on
the ASTM website.
conditions
3
Available from Federal Aviation Administration (FAA), 800 Independence
3.2.22 POH—Pilot Operating Handbook
Ave., SW, Washington, DC 20591, http://www.faa.gov.
2 2
4 3.2.23 q—dynamic pressure (N/m)= 1 2rV
Available from Global Engineering Documents, 15 Inverness Way, East
/
Englewood, CO 80112-5704, http://global.ihs.com. 3.2.24 RC—climb rate (m/s)
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959, United States.
1

---------------------- Page: 1 ----------------------
F2245 – 09
2
3.2.25 S—wing area (m ) 4.2.3 EmptyCG,mostforward,andmostrearwardCGshall
3.2.26 V—airspeed (m/s, kts) be determined.
3.2.27 V —design maneuvering speed
4.2.4 Fixed or removable ballast, or both, may be used if
A
3.2.28 V —design cruising speed
properly installed and placarded.
C
3.2.29 V —design diving speed
D
4.3 Propeller Speed and Pitch Limits—Propeller configura-
3.2.30 V —demonstrated flight diving speed (V # V )
DF DF D tion shall not allow the engine to exceed safe operating
...

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:F2245–08 Designation: F 2245 – 09
Standard Specification for
1
Design and Performance of a Light Sport Airplane
This standard is issued under the fixed designation F2245; 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 Thisspecificationcoversairworthinessrequirementsforthedesignofpoweredfixedwinglightsportaircraft,an“airplane.”
1.2 This specification is applicable to the design of a light sport aircraft/airplane as defined by regulations and limited to VFR
flight.
1.3 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:
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
F2538 Practice for Design and Manufacture of Reciprocating Compression Ignition Engines for Light Sport Aircraft
3
2.2 Federal Aviation Regulations:
FAR-33 Airworthiness Standards: Aircraft Engines
4
2.3 Joint Aviation Requirements:
JAR-E Engines
JAR-22 Sailplanes and Powered Sailplanes
3. Terminology
3.1 Definitions:
3.1.1 flaps—any movable high lift device.
3.1.2 maximum empty weight, W (N)—largest empty weight of the airplane, including all operational equipment that is
E
installed in the airplane: 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 (N)—where W = W − W .
U U E
3.1.4 night—hours between the end of evening civil twilight and the beginning of morning civil twilight.
3.1.4.1 Discussion—Civil twilight ends in the evening when the center of the sun’s disc is 6 degrees 6° below the horizon, and
begins in the morning when the center of the sun’s disc is 6 degrees6° below the horizon.
3.2 Abbreviations:
2
3.2.1 AR—aspect ratio = b S
/
3.2.2 b—wing span, (m)
3.2.3 c—chord, (m)
3.2.4 CAS—calibrated air speed, (m/s, kts)
3.2.5 C — lift coefficient of the airplane
L
3.2.6 C — drag coefficient of the airplane
D
3.2.7 CG—center of gravity
3.2.8 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 F37.20 on Airplane.
Current edition approved Sept.April 1, 2008.2009. Published October 2008.May 2009. Originally approved in 2004. Last previous edition approved in 20072008 as
F2245–07a.F2245–08.
2
ForreferencedASTMstandards,visittheASTMwebsite,www.astm.org,[e-mail] Annual Book ofASTM Standards
volume information, refer to the standard’s Document Summary page on the ASTM website.
3
Available from Federal Aviation Administration (FAA), 800 Independence Ave., SW, Washington, DC 20591, http://www.faa.gov.
4
Available from Global Engineering Documents, 15 Inverness Way, East Englewood, CO 80112-5704, http://global.ihs.com.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959, United States.
1

---------------------- Page: 1 ----------------------
F2245–09
3.2.9 C — zero lift moment coefficient
MO
3.2.10 C — normal coefficient
n
2
3.2.11 g—acceleration as a result of gravity = 9.81 m/s
3.2.12 IAS—indicated air speed (m/s, kts)
3.2.13 ICAO—International Civil Aviation Organization
3.2.14 LSA—light sport aircraft
3.2.15 MAC—mean aerodynamic chord (m)
3.2.16 n—load factor
3.2.17 n —airplane positive maneuvering limit load factor
1
3.2.18 n —airplane negative maneuvering limit load factor
2
3.2.19 n —load factor on wheels
3
3.2.20 P—power, (kW)
3
3.2.21 r—air density (kg/m )=1.225 at sea level standard conditions
3.2.22 POH—Pilot Operating Handbook
2 2
3.2.23 q—dynamic pressure (N/m)= 1 2rV
/
3.2.24 RC—climb rate (m/s)
2
3.2.25 S—wing area (m )
3.2.26 V—airspeed (m/s, kts)
3.2.27 V — design maneuvering speed
A
3.2.28 V — design cruising speed
C
3.2.29 V
...