ASTM F2242-05

Standard Specification for Production Acceptance Testing System for Powered Parachute Aircraft

SCOPE
1.1 The following requirements apply for the manufacture powered parachute aircraft. This standard includes the production acceptance test 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: 28-Feb-2005
• ICS: 97.220.40 - Outdoor and water sports equipment
• Technical Committee: F37 - Light Sport Aircraft
• Drafting Committee: F37.30 - Power Parachute

Relations

• Replaces: ASTM F2242-03 - Standard Specification for Production Acceptance Testing System for Powered Parachute Aircraft
• Effective Date: 01-Mar-2005
• Replaced By: ASTM F2242-05(2008) - Standard Specification for Production Acceptance Testing System for Powered Parachute Aircraft
• Effective Date: 15-May-2008
• Referred By: ASTM F2244-14(2022) - Standard Specification for Design and Performance Requirements for Powered Parachute Aircraft
• Effective Date: 01-Mar-2005
• Referred By: ASTM F2563-16 - Standard Practice for Kit Assembly Instructions of Aircraft Intended Primarily for Recreation
• Effective Date: 01-Mar-2005
• Referred By: ASTM F2426-13(2018)e1 - Standard Guide on Wing Interface Documentation for Powered Parachute Aircraft
• Effective Date: 01-Mar-2005
• Referred By: ASTM F3060-20 - Standard Terminology for Aircraft
• Effective Date: 01-Mar-2005

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NOTICE: This standard has either been superseded and replaced by a new version or withdrawn.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 2242 – 05
Standard Specification for
Production Acceptance Testing System for Powered
1
Parachute Aircraft
This standard is issued under the fixed designation F 2242; 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 that have been set forth by the manufacturer in its Aircraft
Operating Instructions.
1.1 The following requirements apply for the manufacture
3.2 In addition, this specification provides minimum re-
powered parachute aircraft. This specification includes the
quirements to verify that each subsequent production airplane
production acceptance test requirements for powered parachute
has no obvious defects that would prevent the safe operation of
aircraft.
the airplane.
1.2 This specification applies to powered parachute aircraft
seeking civil aviation authority approval, in the form of flight
4. Production Acceptance Testing, Ground Testing
certificates, flight permits, or other like documentation.
4.1 Inspection Verification—There shall be a written proce-
1.3 This standard does not purport to address all of the
dure in effect to verify all top-level inspections have been
safety concerns, if any, associated with its use. It is the
completed and no discrepancies remain open.
responsibility of the user of this standard to establish appro-
4.2 Engine Break-In—There shall be a written procedure in
priate safety and health practices and determine the applica-
effect to perform the engine break-in. This procedure may
bility of regulatory requirements prior to use.
include all engine gage verification of operation. All engine
2. Terminology readings shall achieve the normal accepted range of readings
commensurate with a new engine. If not performed during
2.1 Definitions:
engine break-in, then this verification must be performed under
2.1.1 powered parachute, n—aircraft comprised of a flex-
separate procedures. All engine gages shall be verified to be
ible or semi-rigid wing connected to a fuselage in such a way
operating.
that the wing is not in position for flight until the aircraft is in
motion. This aircraft has a fuselage with seats, engine, and
5. Production Acceptance Testing, Flight Testing
wheels (or floats), such that the wing and engine cannot be
5.1 Every production aircraft shall be flight tested to the
flown without the wheels (or floats) and seat(s). Unique to the
following minimums:
powered parachute is the large displacement between the
5.1.1 Powered Parachutes—Fifteen minutes flight time,
center of lift (high) and the center of gravity (low), which is
including at least one takeoff and landing, trimming of flight
pendulum effect. Pendulum effect limits angle of attach
controls, and verification of control for left turn, right turn, and
changes, provides stall resistance and maintains flight stability.
flare (flare only is so equipped).
3.
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