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ASTM F2242-05(2018)

(Specification)

Standard Specification for Production Acceptance Testing System for Powered Parachute Aircraft

Standard Specification for Production Acceptance Testing System for Powered Parachute Aircraft

ABSTRACT
This specification covers the minimum requirements for production acceptance testing of a powered parachute aircraft. The test includes ground and flight testing. In ground testing, the aircraft shall undergo inspection verification and engine break-in. In flight testing, on the other hand, the aircraft shall be inspected for performance while on a specified flight time, including takeoff and landing, and shall undergo instrument verification. In addition, this specification also provides for post flight acceptance testing, which shall include a review of all flight critical attachments and structures.
SCOPE
1.1 The following requirements apply for the manufacture powered parachute aircraft. This specification includes the production acceptance test requirements for powered parachute aircraft.  
1.2 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, health, and environmental practices and determine the applicability of regulatory requirements prior to use.  
1.4 This international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for the Development of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.

General Information

Status
Published
Publication Date
31-Oct-2018
ICS
49.020 - Aircraft and space vehicles in general
Technical Committee
F37 - Light Sport Aircraft
Drafting Committee
F37.30 - Power Parachute
Current Stage
Ref Project

Relations

Replaces
ASTM F2242-05(2013) - Standard Specification for Production Acceptance Testing System for Powered Parachute Aircraft
Effective Date
01-Nov-2018
Referred By
ASTM F2426-13(2018)e1 - Standard Guide on Wing Interface Documentation for Powered Parachute Aircraft
Effective Date
01-Nov-2018
Referred By
ASTM F3060-20 - Standard Terminology for Aircraft
Effective Date
01-Nov-2018
Referred By
ASTM F2244-14(2022) - Standard Specification for Design and Performance Requirements for Powered Parachute Aircraft
Effective Date
01-Nov-2018
Referred By
ASTM F2563-16 - Standard Practice for Kit Assembly Instructions of Aircraft Intended Primarily for Recreation
Effective Date
01-Nov-2018

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ASTM F2242-05(2018) - Standard Specification for Production Acceptance Testing System for Powered Parachute AircraftASTM F2242-05(2018) - Standard Specification for Production Acceptance Testing System for Powered Parachute Aircraft
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ASTM F2242-05(2018) - Standard Specification for Production Acceptance Testing System for Powered Parachute Aircraft
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This international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles for the
Development of International Standards, Guides and Recommendations issued by the World Trade Organization Technical Barriers to Trade (TBT) Committee.
Designation:F2242 −05 (Reapproved 2018)
Standard Specification for
Production Acceptance Testing System for Powered
Parachute Aircraft
This standard is issued under the fixed designation F2242; 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 (´) indicates an editorial change since the last revision or reapproval.
1. Scope flight test program for verifying the initial (first run) production
aircraft meets certain operational performance requirements
1.1 The following requirements apply for the manufacture
that have been set forth by the manufacturer in its Aircraft
powered parachute aircraft. This specification includes the
Operating Instructions.
production acceptance test requirements for powered parachute
aircraft. 3.2 In addition, this specification provides minimum re-
quirements to verify that each subsequent production airplane
1.2 This specification applies to powered parachute aircraft
has no obvious defects that would prevent the safe operation of
seeking civil aviation authority approval, in the form of flight
the airplane.
certificates, flight permits, or other like documentation.
1.3 This standard does not purport to address all of the
4. Production Acceptance Testing, Ground Testing
safety concerns, if any, associated with its use. It is the
4.1 Inspection Verification—There shall be a written proce-
responsibility of the user of this standard to establish appro-
dure in effect to verify all top-level inspections have been
priate safety, health, and environmental practices and deter-
completed and no discrepancies remain open.
mine the applicability of regulatory requirements prior to use.
1.4 This international standard was developed in accor-
4.2 Engine Break-In—There shall be a written procedure in
dance with internationally recognized principles on standard-
effect to perform the engine break-in. This procedure may
ization established in the Decision on Principles for the
include all engine gage verification of operation. All engine
Development of International Standards, Guides and Recom-
readings shall achieve the normal accepted range of readings
mendations issued by the World Trade Organization Technical
commensurate with a new engine. If not performed during
Barriers to Trade (TBT) Committee.
engine break-in, then this verification must be performed under
separate procedures. All engine gages shall be verified to be
2. Terminology
operating.
2.1 Definitions:
2.1.1 powered parachute, n—aircraftcomprisedofaflexible
5. Production Acceptance Testing, Flight Testing
or semi-rigid wing connected to a fuselage in such a way that
5.1 Every production aircraft shall be flight tested to the
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
...

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4.1 The purpose of this practice is to provide the minimum requirements necessary for the establishment of a production acceptance program for a manufacturer of light sport aircraft.  
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SCOPE
1.1 This specification covers minimum requirements for the design, manufacture, and installation of parachutes for airframes. Airframe emergency parachutes addressed in this specification refer to parachute systems designed, manufactured, and installed to recover the airframe and its occupants at a survivable rate of descent. This specification is not applicable to deep-stall parachutes, spin recovery parachutes, drogue parachutes, or other airframe emergency aerodynamic decelerators not specifically intended for safely lowering the airframe and occupants to the ground. The specification is applicable to these types of parachutes if they are an integral part of an airframe emergency parachute system designed to recover the airframe and occupants at a survivable rate of descent.  
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1.2.1 Note that within the aviation community mixed units are appropriate in accordance with International Civil Aviation Organization (ICAO) agreements. While the values stated in SI units are regarded as standard, certain values such as airspeeds in knots and altitude in feet are also accepted as standard.  
1.3 Airframe emergency parachute recovery systems have become an acceptable means of greatly reducing the likelihood of serious injury or death in an in-flight emergency. Even though they have saved hundreds of lives in many different types of conditions, inherent danger of failure, even if properly designed, manufactured and installed, remains due to the countless permutations of random variables (attitude, altitude, accelerations, airspeed, weight, geographic location, etc.) that may exist at time of usage. The combination of these variables may negatively influence the life saving function of these airframe emergency parachute systems. They are designed to be a supplemental safety device and to be used at the discretion of the pilot when deemed to provide the best chance of survivability.  
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