ASTM F2352-04
(Specification)Standard Specification for Design and Performance of Light Sport Gyroplane Aircraft
Standard Specification for Design and Performance of Light Sport Gyroplane Aircraft
SCOPE
1.1 This specification covers the manufacture of gyroplanes. This specification includes design and performance requirements for light sport gyroplane aircraft.
1.2 This specification applies to light gyroplane aircraft seeking civil aviation authority approval in the form of flight certificates, flight permits, or other like documentation.
1.3 A gyroplane for the purposes of this specification is defined as a rotorcraft to be used for day VFR only, with rotor blades that are not engine-driven in flight and are supported in flight by the reaction of the air on a single rotor that rotates freely on a substantially vertical axis when the aircraft is in horizontal flight.
1.4 These requirements apply to light gyroplanes of orthodox design. Aircraft having the following basic features will be so regarded:
1.4.1 Rotors of either fixed collective pitch or collective pitch control that are not adjustable in flight,
1.4.2 Single engine with fixed or ground adjustable pitch propeller,
1.4.3 No more than two occupant seats, and
1.4.4 A maximum gross weight (MGW) of 725 kg (1600 lb) or less.
1.5 Where it can be shown that a particular feature is similar in all significant respects to a feature that has historically demonstrated compliance with this specification and can be considered a separate entity in terms of its operation, that feature shall be deemed to be applicable and in compliance with this specification.
1.6 Where these requirements are inappropriate to particular design and construction features, it will be necessary to submit an appropriate amendment of this specification to ASTM Committee F37 on Light Sport Aircraft for consideration and approval.
1.7 The values in SI units are to be regarded as the standard. The values in parentheses are for information only.
T1.8 his 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 limitations prior to use.
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Designation: F 2352 – 04
Standard Specification for
1
Design and Performance of Light Sport Gyroplane Aircraft
This standard is issued under the fixed designation F 2352; 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 1.7 The values in SI units are to be regarded as the standard.
The values in parentheses are for information only.
1.1 Thisspecificationcoversthemanufactureofgyroplanes.
1.8 This standard does not purport to address all of the
This specification includes design and performance require-
safety concerns, if any, associated with its use. It is the
ments for light sport gyroplane aircraft.
responsibility of the user of this standard to establish appro-
1.2 This specification applies to light gyroplane aircraft
priate safety and health practices and determine the applica-
seeking civil aviation authority approval in the form of flight
bility of regulatory limitations prior to use.
certificates, flight permits, or other like documentation.
1.9 Table of Contents:
1.3 A gyroplane for the purposes of this specification is
Section
defined as a rotorcraft to be used for day VFR only, with rotor
Scope 1
blades that are not engine-driven in flight and are supported in
Referenced Documents 2
flight by the reaction of the air on a single rotor that rotates Terminology 3
Definitions 3.1
freely on a substantially vertical axis when the aircraft is in
Abbreviations 3.2
horizontal flight.
Flight 4
1.4 These requirements apply to light gyroplanes of ortho-
General 4.1
Performance 4.2
dox design.Aircraft having the following basic features will be
Controllability and Maneuverability 4.3
so regarded:
Stability 4.4
1.4.1 Rotors of either fixed collective pitch or collective Ground-Handling Characteristics 4.5
Miscellaneous Flight Requirements 4.6
pitch control that are not adjustable in flight,
Structure 5
1.4.2 Single engine with fixed or ground adjustable pitch
General 5.1
propeller, Flight Loads 5.2
Control System Loads 5.3
1.4.3 No more than two occupant seats, and
Stabilizing and Control Surfaces 5.4
1.4.4 Amaximum gross weight (MGW) of 725 kg (1600 lb)
Ground Loads 5.5
or less. Main Component Requirements 5.6
Emergency Landing Conditions 5.7
1.5 Whereitcanbeshownthataparticularfeatureissimilar
Other Loads 5.8
in all significant respects to a feature that has historically
Design and Construction 6
demonstrated compliance with this specification and can be General 6.1
Control Surfaces and Rotors 6.2
considered a separate entity in terms of its operation, that
Control Systems 6.3
feature shall be deemed to be applicable and in compliance
Cockpit Design 6.4
with this specification. Powerplant 7
General 7.1
1.6 Wheretheserequirementsareinappropriatetoparticular
Fuel System 7.2
design and construction features, it will be necessary to submit
Oil System 7.3
Cooling 7.4
an appropriate amendment of this specification to ASTM
Induction System 7.5
Committee F37 on Light Sport Aircraft for consideration and
Exhaust System 7.6
approval.
Powerplant Controls and Accessories 7.7
Equipment 8
General 8.1
Instruments—Installation 8.2
1
Electrical systems and Equipment 8.3
This specification is under the jurisdiction of ASTM Committee F37 on Light
Miscellaneous Equipment 8.4
Sport Aircraft and is the direct responsibility of Subcommittee F37.50 on Gy-
Operating Limitations and Information 9
roplane.
General 9.1
Current edition approved July 1, 2004. Published August 2004.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959, United States.
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F2352–04
4.1.1.1 Each requirement of this section must be met in
Section
Markings and Placards 9.2
loading conditions and at the most adverse combination of
Propellers 10
weight and balance loading conditions within which the
Design and Construction 10.1
gyroplane will be operated.
Keywords 11
4.1.1.2 Unless otherwise stipulated, performance require-
2. Referenced Documents
ments are at standard atmospheric conditions (15°C (59°F))
2
2.1 ASTM Standards:
and sea level pressure altitude).
F 2339 Practice for Design and Manufacture of Reciprocat-
4.1.1.3 Each requirement of this section must be met for all
ing Spark Ignition Engines for Light Sport Aircraft
configurations at which the gyroplane will be operated except
3
2.2 Federal Aviation Regulations:
as otherwise stated. (If, for example, a gyroplane is equipped
FAR-33 Airworthiness Standards: Aircraft Engines
with a canopy or doors and it is intended that the gyroplane
4
2.3 Joint Aviation Regulations:
may be operated with the canopy or doo
...
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