ASTM F2242-03

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: 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 F2242-05 - Standard Specification for Production Acceptance Testing System 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 F3060-20 - Standard Terminology for Aircraft
• Effective Date: 10-Jun-2003
• Referred By: ASTM F2563-16 - Standard Practice for Kit Assembly Instructions of Aircraft Intended Primarily for Recreation
• Effective Date: 10-Jun-2003
• Referred By: ASTM F2244-14(2022) - Standard Specification for Design and Performance Requirements for Powered Parachute 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NOTICE: This standard has either been superseded and replaced by a new version or withdrawn.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 2242 – 03
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 3.2 In addition, this practice provides minimum require-
mentstoverifythateachsubsequentproductionairplanehasno
1.1 The following requirements apply for the manufacture
obvious defects that would prevent the safe operation of the
powered parachute aircraft. This standard includes the produc-
airplane.
tion acceptance test requirements for powered parachute air-
craft.
4. Production Acceptance Testing, Ground Testing
1.2 Applicability—This specification applies to powered
4.1 Inspection Verification—There shall be a written proce-
parachute aircraft seeking civil aviation authority approval, in
dure in effect to verify all top-level inspections have been
the form of flight certificates, flight permits, or other like
completed and no discrepancies remain open.
documentation.
4.2 Engine Break-in—There shall be a written procedure in
1.3 This standard does not purport to address all of the
effect to perform the engine break-in. This procedure may
safety concerns, if any, associated with its use. It is the
include all engine gage verification of operation. All engine
responsibility of the user of this standard to establish appro-
readings shall achieve the normal accepted range of readings
priate safety and health practices and determine the applica-
commensurate with a new engine. If not performed during
bility of regulatory requirements prior to use.
engine break-in, then this verification must be performed under
2. Terminology separate procedures. All engine gages shall be verified to be
operating.
2.1 Definitions:
2.1.1 powered parachute, n—aircraft comprised of a flex-
5. Production Acceptance Testing, Flight Testing
ible or semi-rigid wing connected to a fuselage in such a way
5.1 Every production aircraft shall be flight tested to the
that the wing is not in position for flight until the aircraft is in
following minimums:
motion. This aircraft has a fuselage with seats, engine, and
5.1.1 Powered Parachutes—Fifteen minutes flight time,
wheels (or floats), such that the wing and engine cannot be
including at least one takeoff and landing, trimming of flight
flown without the wheels (or floats) and seat(s). Unique to the
controls, and verification of control for left turn, right turn, and
powered parachute is the large displacement between the
flare (flare only is so equipped).
center of lift (high) and the center of gravity (low), which is
5.2 Instrument Verification—There shall be a written proce-
pendulum effect. Pendulum effect limits angle of attach
dure in effect to verify that all other instrum
...