ASTM F2244-10

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Designation:F2244 −10
StandardSpecification 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 3.1.3 poweredparachute,n—aircraftcomprisedofaflexible
or semi-rigid wing connected to a fuselage in such a way that
1.1 The following requirements apply for the manufacture
the wing is not in position for flight until the aircraft is in
of powered parachute aircraft. This specification includes
motion that aircraft has a fuselage with seats, engine, and
design and performance requirements for powered parachute
wheels (or floats), such that the wing and engine cannot be
aircraft.
flown without the wheels (or floats) and seat(s). Unique to the
1.2 This specification applies to powered parachute aircraft
powered parachute is the large displacement between the
seeking civil aviation authority approval, in the form of flight
center of lift (high) and the center of gravity (low), which is
certificates, flight permits, or other like documentation.
pendulum effect. Pendulum effect limits angle of attach
1.3 This standard does not purport to address all of the
changes, provides stall resistance and maintains flight stability.
safety concerns, if any, associated with its use. It is the
4. Flight
responsibility of the user of this standard to establish appro-
priate safety and health practices and determine the applica- 4.1 Performance Requirements:
bility of regulatory requirements prior to use. 4.1.1 Proof of Compliance—Each of the following require-
ments shall be met at the maximum takeoff weight and most
2. Referenced Documents
critical center of gravity (CG) position. To the extent that CG
2
2.1 ASTM Standards:
adjustment devices may be adjusted for flight, these compo-
F2240Specification for Manufacturer Quality Assurance
nents will be evaluated in the least favorable recommended
Program for Powered Parachute Aircraft
position as it affects either performance or structural strength.
F2241SpecificationforContinuedAirworthinessSystemfor
4.1.2 General Performance—All performance requirements
Powered Parachute Aircraft
apply in and shall be corrected to International Civil Aviation
F2242Specification for ProductionAcceptanceTesting Sys-
Organization (ICAO) defined standard atmosphere in still air
tem for Powered Parachute Aircraft
conditionsatsealevel.Speedsshallbegiveninindicated(IAS)
F2243Specification for Required Product Information to be
and calibrated (CAS) airspeeds in miles per hour (MPH).
Provided with Powered Parachute Aircraft
4.1.2.1 Wing Performance—For straight-ahead flight and
turns in either direction during climb, cruise, descent, and
3. Terminology
landing flare, it shall be shown that the limits of control input
3.1 Definitions:
are less than the wing stall limitations:
3.1.1 gross weight, n—total aircraft system weight(s) at
(1)If a fixed wing trim is available;
takeoff.
(2)If adjustable wing trim is available, it shall be tested to
3.1.2 maximum takeoff weight, n—gross weight limit as
both the most negative and most positive trim settings; and
defined by the manufacturer, proven through compliance with
(3)If separate left wing and right wing trim devises are
this specification and placarded on the aircraft as the not-to-
available, each shall be tested to both the maximum-left-and
exceed gross weight.
minimum-right trim settings and the minimum-left-and-
maximum-right trim settings.
1
This specification is under the jurisdiction of ASTM Committee F37 on Light
4.1.2.2 Climb—The following shall be measured:
Sport Aircraft and is the direct responsibility of Subcommittee F37.30 on Power
(1)Distance to clear a 15 m (50 ft) obstacle not to exceed
Parachute.
213 m (700 ft) from point of liftoff.
Current edition approved Jan. 1, 2010. Published January 2010. Originally
(2) Landing—Thetotallandingdistanceovera15m(50ft)
approved in 2003. Last previous edition approved in 2008 as F2244–08. DOI:
10.1520/F2244-10.
obstacle shall be achieved within 183 m (600 ft) total distance.
2
For referenced ASTM standards, visit the ASTM website, www.astm.org, or
4.1.2.3 Controllability and Maneuverability—The aircraft
contact ASTM Customer Service at service@astm.org. For Annual Book of ASTM
shall be safely controllable and maneuverable during takeoff,
Standards volume information, refer to the standard’s Document Summary page on
the ASTM website. climb, level flight (cruise), approach, and landing (power off
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