ASTM F2244-03

Standard Specification for Design and Performance Requirements for Powered Parachute Aircraft

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 Applicability—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: 09-Jun-2003
• ICS: 97.220.40 - Outdoor and water sports equipment
• Technical Committee: F37 - Light Sport Aircraft
• Drafting Committee: F37.30 - Power Parachute

Relations

• Replaced By: ASTM F2244-05 - Standard Specification for Design and Performance Requirements for Powered Parachute Aircraft
• Effective Date: 01-Mar-2005
• Referred By: ASTM F2426-13(2018)e1 - Standard Guide on Wing Interface Documentation for Powered Parachute Aircraft
• Effective Date: 10-Jun-2003
• Referred By: ASTM F2483-18e1 - Standard Practice for Maintenance and the Development of Maintenance Manuals for Light Sport Aircraft
• Effective Date: 10-Jun-2003
• Referred By: ASTM F2507-15 - Standard Specification for Recreational Airpark Design
• Effective Date: 10-Jun-2003
• Referred By: ASTM F3060-20 - Standard Terminology for Aircraft
• Effective Date: 10-Jun-2003

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NOTICE: This standard has either been superseded and replaced by a new version or withdrawn.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: F 2244 – 03
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 (e) indicates an editorial change since the last revision or reapproval.
1. Scope with this specification and placarded on the aircraft as the
not-to-exceed gross weight.
1.1 The following requirements apply for the manufacture
3.1.3 powered parachute, n—aircraft comprised of a flex-
of Powered Parachute Aircraft. This specification includes
ible or semi-rigid wing connected to a fuselage in such a way
design and performance requirements for powered parachute
that the wing is not in position for flight until the aircraft is in
aircraft.
motion that aircraft has a fuselage with seats, engine, and
1.2 Applicability—This specification applies to powered
wheels (or floats), such that the wing and engine cannot be
parachute aircraft seeking civil aviation authority approval, in
flown without the wheels (or floats) and seat(s). Unique to the
the form of flight certificates, flight permits, or other like
powered parachute is the large displacement between the
documentation.
center of lift (high) and the center of gravity (low), which is
1.3 This standard does not purport to address all of the
pendulum effect. Pendulum effect limits angle of attach
safety concerns, if any, associated with its use. It is the
changes, provides stall resistance and maintains flight stability.
responsibility of the user of this standard to establish appro-
priate safety and health practices and determine the applica-
4. Flight
bility of regulatory requirements prior to use.
4.1 Performance Requirements:
2. Referenced Documents 4.1.1 Proof of Compliance—Each of the following require-
ments shall be met at the maximum takeoff weight and most
2.1 ASTM Standards:
critical center of gravity (CG) position. To the extent that CG
F 2240 Specification for Manufacturer Quality Assurance
2
adjustment devices may be adjusted for flight, these compo-
Program for Powered Parachute Aircraft
nents will be evaluated in the least favorable recommended
F 2241 Specification for Continued Airworthiness System
2
position as it affects either performance or structural strength.
for Powered Parachute Aircraft
4.1.2 General Performance—All performance requirements
F 2242 Specification for Production Acceptance Testing
2
apply in and shall be corrected to International Civil Aviation
System for Powered Parachute Aircraft
Organization (ICAO) defined standard atmosphere in still air
F 2243 Specification for Required Product Information to
2
conditionsatsealevel.Speedsshallbegiveninindicated(IAS)
be Provided with Powered Parachute Aircraft
and calibrated (CAS) airspeeds in miles per hour (MPH).
3. Terminology
4.1.2.1 Wing Performance—For straight-ahead flight and
turns in either direction during climb, cruise, descent, and
3.1 Definitions:
landing flare, it shall be shown that the limits of control input
3.1.1 gross weight , n—is the total aircraft system weight at
are less than the wing stall limitations:
takeoff.Thisweightincludesanythingandeverythingthatison
(1) If a fixed wing trim is available;
or a part of the powered parachute aircraft, including, but not
(2) If adjustable wing trim is available, it shall be tested to
limitedto,thewing,risers,fuselage,seats,engine,instruments,
both the most negative and most positive trim settings;
wheels, fuel, oil, water, pilot, passenger, clothing, and so forth.
(3) If separate left wing and right wing trim devises are
3.1.2 maximum takeoff weight , n—is the gross weight limit
available, each shall be tested to both the maximum-left-and
as defined by the manufacturer, proven through compliance
minimum-right trim settings and the minimum-left-and-
maximum-right trim settings.
4.1.2.2 Climb—The following shall be measured:
1
This specification is under the jurisdiction of ASTM Committee F37 on Light
(1) Distance to clear a 15 m (50 ft) obstacle not to exceed
Sport Aircraft and is the direct responsibility of Subcommittee F37.30 on Power
213 m (700 ft) from point of liftoff.
Parachute.
(2) Landing—The total landing distance over a 15 m (50 ft)
Current edition approved June 10, 2003. Published July 2003.
2
Annual Book of ASTM Standards, Vol 15.07. obstacle shall be achieved within 183 m (600 ft) total distance.
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F2244–03
4.1.2.3 Controllability and Maneuverability—The aircraft 5.1.2.4 3.3 on push-pull control syste
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