ASTM F2244-08
(Specification)Standard Specification for Design and Performance Requirements for Powered Parachute Aircraft
Standard Specification for Design and Performance Requirements for Powered Parachute Aircraft
ABSTRACT
This specification covers design and performance requirements for powered parachute aircraft. It also applies to powered parachute aircraft seeking civil aviation authority approval, in the form of flight certificates, flight permits, or other like documentation. Each of the performance requirements shall be met at the maximum takeoff weight and most critical center of gravity (CG) position. To the extent that CG adjustment devices may be adjusted for flight, these components will be evaluated in the least favorable recommended position as it affects either performance or structural strength. All performance requirements apply in and shall be corrected to International Civil Aviation Organization (ICAO) defined standard atmosphere in still air conditions at sea level. Speeds shall be given in indicated (IAS) and calibrated (CAS) airspeeds in miles per hour (MPH). The wing performance, climb performance, controllability and maneuverability, and reference parameters shall be carefully determined and evaluated. Stability requirements of the aircraft such as longitudinal stability, lateral stability, and directional stability shall be discussed as well. In terms of structural requirements, the load and proof of structure of the aircraft shall be considered.
SCOPE
1.1 The following requirements apply for the manufacture of powered parachute aircraft. This specification includes design and performance requirements for powered parachute aircraft.
1.2 This specification applies to powered parachute aircraft seeking civil aviation authority approval, in the form of flight certificates, flight permits, or other like documentation.
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.
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Designation: F2244 – 08
Standard Specification for
Design and Performance Requirements for Powered
1
Parachute Aircraft
This standard is issued under the fixed designation F2244; 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 3.1.2 maximum takeoff weight, n—gross weight limit as
defined by the manufacturer, proven through compliance with
1.1 The following requirements apply for the manufacture
this specification and placarded on the aircraft as the not-to-
of powered parachute aircraft. This specification includes
exceed gross weight.
design and performance requirements for powered parachute
3.1.3 powered parachute, n—aircraft comprised of a flex-
aircraft.
ible or semi-rigid wing connected to a fuselage in such a way
1.2 This specification applies to powered parachute aircraft
that the wing is not in position for flight until the aircraft is in
seeking civil aviation authority approval, in the form of flight
motion that aircraft has a fuselage with seats, engine, and
certificates, flight permits, or other like documentation.
wheels (or floats), such that the wing and engine cannot be
1.3 This standard does not purport to address all of the
flown without the wheels (or floats) and seat(s). Unique to the
safety concerns, if any, associated with its use. It is the
powered parachute is the large displacement between the
responsibility of the user of this standard to establish appro-
center of lift (high) and the center of gravity (low), which is
priate safety and health practices and determine the applica-
pendulum effect. Pendulum effect limits angle of attach
bility of regulatory requirements prior to use.
changes, provides stall resistance and maintains flight stability.
2. Referenced Documents
4. Flight
2
2.1 ASTM Standards:
4.1 Performance Requirements:
F2240 Specification for Manufacturer Quality Assurance
4.1.1 Proof of Compliance—Each of the following require-
Program for Powered Parachute Aircraft
ments shall be met at the maximum takeoff weight and most
F2241 Specification for Continued Airworthiness System
critical center of gravity (CG) position. To the extent that CG
for Powered Parachute Aircraft
adjustment devices may be adjusted for flight, these compo-
F2242 Specification for Production Acceptance Testing
nents will be evaluated in the least favorable recommended
System for Powered Parachute Aircraft
position as it affects either performance or structural strength.
F2243 Specification for Required Product Information to be
4.1.2 General Performance—Allperformancerequirements
Provided with Powered Parachute Aircraft
apply in and shall be corrected to International Civil Aviation
3. Terminology Organization (ICAO) defined standard atmosphere in still air
conditionsatsealevel.Speedsshallbegiveninindicated(IAS)
3.1 Definitions:
and calibrated (CAS) airspeeds in miles per hour (MPH).
3.1.1 gross weight, n—total aircraft system weight(s) at
4.1.2.1 Wing Performance—For straight-ahead flight and
takeoff. The weight limits must be established so that it is (1)
turns in either direction during climb, cruise, descent, and
the designed maximum weight at which compliance with each
landing flare, it shall be shown that the limits of control input
applicable structural loading condition is demonstrated, or (2)
are less than the wing stall limitations:
the highest weight at which compliance at each applicable
(1) If a fixed wing trim is available;
flight requirement is demonstrated.
(2) If adjustable wing trim is available, it shall be tested to
both the most negative and most positive trim settings; and
1
This specification is under the jurisdiction of ASTM Committee F37 on Light
(3) If separate left wing and right wing trim devises are
Sport Aircraft and is the direct responsibility of Subcommittee F37.30 on Power
available, each shall be tested to both the maximum-left-and
Parachute.
minimum-right trim settings and the minimum-left-and-
Current edition approved May 15, 2008. Published June 2008. Originally
approved in 2003. Last previous edition approved in 2005 as F2244 – 05. DOI:
maximum-right trim settings.
10.1520/F2244-08.
4.1.2.2 Climb—The following shall be measured:
2
For referenced ASTM standards, visit the ASTM website, www.astm.org, or
(1) Distance to clear a 15 m (50 ft) obstacle not to exceed
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 213 m (700 ft) from point of liftoff.
the ASTM website.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959,
...
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:F2244–05 Designation: F 2244 – 08
Standard Specification for
Design and Performance Requirements for Powered
1
Parachute Aircraft
This standard is issued under the fixed designation F 2244; 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 The following requirements apply for the manufacture of powered parachute aircraft.This specification includes design and
performance requirements for powered parachute aircraft.
1.2 This specification applies to powered parachute aircraft seeking civil aviation authority approval, in the form of flight
certificates, flight permits, or other like documentation.
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:
F 2240 Specification for Manufacturer Quality Assurance Program for Powered Parachute Aircraft
F 2241 Specification for Continued Airworthiness System for Powered Parachute Aircraft
F 2242 Specification for Production Acceptance Testing System for Powered Parachute Aircraft
F 2243 Specification for Required Product Information to be Provided with Powered Parachute Aircraft
3. Terminology
3.1 Definitions:
3.1.1 gross weight, n—total aircraft system weight at takeoff. This weight includes anything and everything that is on or a part
of the powered parachute aircraft, including, but not limited to, the wing, risers, fuselage, seats, engine, instruments, wheels, fuel,
oil,water,pilot,passenger,clothing,andsoforth.—totalaircraftsystemweight(s)attakeoff.Theweightlimitsmustbeestablished
so that it is (1) the designed maximum weight at which compliance with each applicable structural loading condition is
demonstrated, or (2) the highest weight at which compliance at each applicable flight requirement is demonstrated.
3.1.2 maximum takeoff weight, n—gross weight limit as defined by the manufacturer, proven through compliance with this
specification and placarded on the aircraft as the not-to-exceed gross weight.
3.1.3 powered parachute, n—aircraft comprised of a flexible or semi-rigid wing connected to a fuselage in such a way that the
wing is not in position for flight until the aircraft is in motion that aircraft has a fuselage with seats, engine, and wheels (or floats),
such that the wing and engine cannot be flown without the wheels (or floats) and seat(s). Unique to the powered parachute is the
large displacement between the center of lift (high) and the center of gravity (low), which is pendulum effect. Pendulum effect
limits angle of attach changes, provides stall resistance and maintains flight stability.
4. Flight
4.1 Performance Requirements:
4.1.1 Proof of Compliance—Each of the following requirements shall be met at the maximum takeoff weight and most critical
center of gravity (CG) position. To the extent that CG adjustment devices may be adjusted for flight, these components will be
evaluated in the least favorable recommended position as it affects either performance or structural strength.
4.1.2 General Performance—All performance requirements apply in and shall be corrected to International Civil Aviation
Organization (ICAO) defined standard atmosphere in still air conditions at sea level. Speeds shall be given in indicated (IAS) and
calibrated (CAS) airspeeds in miles per hour (MPH).
1
This specification is under the jurisdiction ofASTM Committee F37 on Light SportAircraft and is the direct responsibility of Subcommittee F37.30 on Power Parachute.
Current edition approved March 1, 2005. Published March 2005. Originally approved in 2003. Last previous edition approved in 2003 as F2244–03.
Current edition approved May 15, 2008. Published June 2008. Originally approved in 2003. Last previous edition approved in 2005 as F 2244 – 05.
2
For referencedASTM standards, visit theASTM website, www.astm.org, or contactASTM 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.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959, United States.
1
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