ASTM F2244-14

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.

General Information

• Status: Historical
• Publication Date: 31-Oct-2014
• ICS: 49.020 - Aircraft and space vehicles in general
• Technical Committee: F37 - Light Sport Aircraft
• Drafting Committee: F37.30 - Power Parachute

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NOTICE: This standard has either been superseded and replaced by a new version or withdrawn.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:F2244 −14
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.Anumber in parentheses indicates the year of last reapproval.A
superscript epsilon (´) indicates an editorial change since the last revision or reapproval.
1. Scope 3.1.1 gross weight, n—total aircraft system weight(s) at
takeoff.
1.1 The following requirements apply for the manufacture
3.1.2 maximum takeoff weight, n—gross weight limit as
of powered parachute aircraft. This specification includes
defined by the manufacturer, proven through compliance with
design and performance requirements for powered parachute
this specification and placarded on the aircraft as the not-to-
aircraft.
exceed gross weight.
1.2 This specification applies to powered parachute aircraft
3.1.3 poweredparachute,n—aircraftcomprisedofaflexible
seeking civil aviation authority approval, in the form of flight
or semi-rigid wing connected to a fuselage in such a way that
certificates, flight permits, or other like documentation.
the wing is not in position for flight until the aircraft is in
1.3 This standard does not purport to address all of the
motion. That aircraft has a fuselage with seats, engine, and
safety concerns, if any, associated with its use. It is the
wheels (or floats), such that the wing and engine cannot be
responsibility of the user of this standard to establish appro-
flown without the wheels (or floats) and seat(s). Unique to the
priate safety and health practices and determine the applica-
powered parachute is the large displacement between the
bility of regulatory requirements prior to use.
center of lift (high) and the center of gravity (low), which is
pendulum effect. Pendulum effect limits angle of attack
2. Referenced Documents
changes, provides stall resistance and maintains flight stability.
2
2.1 ASTM Standards:
F2241SpecificationforContinuedAirworthinessSystemfor
4. Flight
Powered Parachute Aircraft
4.1 Performance Requirements:
F2242Specification for ProductionAcceptanceTesting Sys-
4.1.1 Proof of Compliance—Each of the following require-
tem for Powered Parachute Aircraft
ments shall be met at the maximum takeoff weight and most
F2243Specification for Required Product Information to be
critical center of gravity (CG) position. To the extent that CG
Provided with Powered Parachute Aircraft
adjustment devices may be adjusted for flight, these compo-
F2483Practice for Maintenance and the Development of
nents will be evaluated in the least favorable recommended
Maintenance Manuals for Light Sport Aircraft
position as it affects either performance or structural strength.
F2563Practice for Kit Assembly Instructions of Aircraft
4.1.2 General Performance—All performance requirements
Intended Primarily for Recreation
apply in and shall be corrected to International Civil Aviation
F2972Specification for Light SportAircraft Manufacturer’s
Organization (ICAO) defined standard atmosphere in still air
Quality Assurance System
conditionsatsealevel.Speedsshallbegiveninindicated(IAS)
and calibrated (CAS) airspeeds in miles per hour (MPH).
3. Terminology
4.1.2.1 Wing Performance—For straight-ahead flight and
3.1 Definitions:
turns in either direction during climb, cruise, descent, and
landing flare, it shall be shown that the limits of control input
are less than the wing stall limitations:
1
This specification is under the jurisdiction ofASTM Committee F37 on Light
(1)If a fixed wing trim is available;
Sport Aircraft and is the direct responsibility of Subcommittee F37.30 on Power
(2)If adjustable wing trim is available, it shall be tested to
Parachute.
both the most negative and most positive trim settings; and
Current edition approved Nov. 1, 2014. Published November 2014. Originally
(3)If separate left wing and right wing trim devises are
approved in 2003. Last previous edition approved in 2013 as F2244–13. DOI:
10.1520/F2244-14.
available, each shall be tested to both the maximum-left-and
2
For referenced ASTM standards, visit the ASTM website, www.astm.org, or
minimum-right trim settings and the minimum-left-and-
contact ASTM Customer Service at [e-mail]. For Annual Book of ASTM
maximum-right trim settings.
Standards volume information, refer to the standard’s Document Summary page on
the ASTM website. 4.1.2.2 Climb—The following shall be measured:
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States
1

---------------------- Page: 1 ----------------------
F2244−14
(1)Distance to clear a 15 m (50 ft) obstacle not to exceed (2) In-Flight Collapse—At least one type of in-flight chute
213 m (700
...

This document is not an ASTM standard and is intended only to provide the user of an ASTM 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 − 13 F2244 − 14
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
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:
3
F2240 Specification for Manufacturer Quality Assurance Program for Powered Parachute Aircraft (Withdrawn 2014)
F2241 Specification for Continued Airworthiness System for Powered Parachute Aircraft
F2242 Specification for Production Acceptance Testing System for Powered Parachute Aircraft
F2243 Specification for Required Product Information to be Provided with Powered Parachute Aircraft
F2483 Practice for Maintenance and the Development of Maintenance Manuals for Light Sport Aircraft
F2563 Practice for Kit Assembly Instructions of Aircraft Intended Primarily for Recreation
F2972 Specification for Light Sport Aircraft Manufacturer’s Quality Assurance System
3. Terminology
3.1 Definitions:
3.1.1 gross weight, n—total aircraft system weight(s) at takeoff.
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 attack 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.
1
This specification is under the jurisdiction of ASTM Committee F37 on Light Sport Aircraft and is the direct responsibility of Subcommittee F37.30 on Power Parachute.
Current edition approved June 1, 2013Nov. 1, 2014. Published July 2013November 2014. Originally approved in 2003. Last previous edition approved in 20102013 as
F2244 – 10.F2244 – 13. DOI: 10.1520/F2244-13.10.1520/F2244-14.
2
For referenced ASTM standards, visit the ASTM website, www.astm.org, or contact ASTM Customer Service at [e-mail]. 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

---------------------- Page: 1 ----------------------
F2244 − 14
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).
4.1.2.1 Wing Performance—For straight-ahead flight and turns in either direction during climb, cruise, descent, and landing
flare, it shall be shown that the limits of control input are less than the wing stall limitations:
(1) If a fixed wing trim is available;
(2) If adjustab
...