ASTM F2244-05
(Specification)Standard Specification for Design and Performance Requirements for Powered Parachute Aircraft
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.
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Designation: F 2244 – 05
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 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:
F 2240 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
F 2241 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-
F 2242 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.
F 2243 Specification for Required Product Information to
4.1.2 General Performance—Allperformancerequirements
be 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 at take-
4.1.2.1 Wing Performance—For straight-ahead flight and
off. This weight includes anything and everything that is on or
turns in either direction during climb, cruise, descent, and
a part of the powered parachute aircraft, including, but not
landing flare, it shall be shown that the limits of control input
limitedto,thewing,risers,fuselage,seats,engine,instruments,
are less than the wing stall limitations:
wheels, fuel, oil, water, pilot, passenger, clothing, and so forth.
(1) If a fixed wing trim is available;
(2) If adjustable wing trim is available, it shall be tested to
1
This specification is under the jurisdiction of ASTM Committee F37 on Light
both the most negative and most positive trim settings; and
Sport Aircraft and is the direct responsibility of Subcommittee F37.30 on Power
(3) If separate left wing and right wing trim devises are
Parachute.
available, each shall be tested to both the maximum-left-and
Current edition approved March 1, 2005. Published March 2005. Originally
minimum-right trim settings and the minimum-left-and-
approved in 2003. Last previous edition approved in 2003 as F 2244 – 03.
2
For referenced ASTM standards, visit the ASTM website, www.astm.org, or
maximum-right trim settings.
contact ASTM Customer Service at service@astm.org. For Annual Book of ASTM
4.1.2.2 Climb—The following shall be measured:
Standards volume information, refer to the standard’s Document Summary page on
the ASTM website.
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F2244–05
(1) Distance to clear a 15 m (50 ft) obstacle not to
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