ASTM F2352-04a

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.

General Information

• Status: Historical
• Publication Date: 31-Oct-2004
• ICS: 49.020 - Aircraft and space vehicles in general
• Technical Committee: F37 - Light Sport Aircraft
• Drafting Committee: F37.50 - Gyroplane

Relations

• Replaces: ASTM F2352-04 - Standard Specification for Design and Performance of Light Sport Gyroplane Aircraft
• Effective Date: 01-Nov-2004
• Replaced By: ASTM F2352-05 - Standard Specification for Design and Performance of Light Sport Gyroplane Aircraft
• Effective Date: 01-Feb-2005
• Referred By: ASTM F2507-15 - Standard Specification for Recreational Airpark Design
• Effective Date: 01-Nov-2004
• Referred By: ASTM F3060-20 - Standard Terminology for Aircraft
• Effective Date: 01-Nov-2004
• Referred By: ASTM F2483-18e1 - Standard Practice for Maintenance and the Development of Maintenance Manuals for Light Sport Aircraft
• Effective Date: 01-Nov-2004

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 2352 – 04a
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 responsibility of the user of this standard to establish appro-
priate safety and health practices and determine the applica-
1.1 Thisspecificationcoversthemanufactureofgyroplanes.
bility of regulatory limitations prior to use.
This specification includes design and performance require-
1.9 Table of Contents:
ments for light sport gyroplane aircraft.
Section
1.2 This specification applies to light gyroplane aircraft
Scope 1
seeking civil aviation authority approval in the form of flight
Table of Contents 1.9
certificates, flight permits, or other like documentation.
Referenced Documents 2
Terminology 3
1.3 A gyroplane for the purposes of this specification is
Definitions 3.1
defined as a rotorcraft to be used for day VFR only, with rotor
Acronyms 3.2
blades that are not engine-driven in flight and are supported in
Flight 4
General 4.1
flight by the reaction of the air on a single rotor that rotates
Performance 4.2
freely on a substantially vertical axis when the aircraft is in
Controllability and Maneuverability 4.3
horizontal flight. Longitudinal Lateral and Directional Control 4.4
Stability 4.5
1.4 These requirements apply to light gyroplanes of ortho-
Ground-Handling Characteristics 4.6
dox design.Aircraft having the following basic features will be
Miscellaneous Flight Requirements 4.7
so regarded: Structure 5
General 5.1
1.4.1 Rotors of either fixed collective pitch or collective
Flight Loads 5.2
pitch control that are not adjustable in flight,
Engine Torque 5.3
1.4.2 Single engine with fixed or ground adjustable pitch Control System Loads 5.4
Stabilizing and Control Surfaces 5.5
propeller,
Ground Loads 5.6
1.4.3 No more than two occupant seats, and
Main Component Requirements 5.7
1.4.4 Amaximum gross weight (MGW) of 725 kg (1600 lb) Emergency Landing Conditions 5.8
Other Loads 5.9
or less.
Design and Construction 6
1.5 Whereitcanbeshownthataparticularfeatureissimilar
General 6.1
in all significant respects to a feature that has historically Materials 6.2
Fabrication Methods 6.3
demonstrated compliance with this specification and can be
Locking of Connections 6.4
considered a separate entity in terms of its operation, that
Protection of Structure 6.5
Inspection 6.6
feature shall be deemed to be applicable and in compliance
Provisions for Rigging and Derigging 6.7
with this specification.
Material Strength Properties and Design Values 6.8
1.6 Wheretheserequirementsareinappropriatetoparticular
Fatigue Strength 6.9
design and construction features, it will be necessary to submit Special Factors of Safety 6.10
Bearing Factors 6.10.2
an appropriate amendment of this specification to ASTM
Fitting Factors 6.10.3
Committee F37 on Light Sport Aircraft for consideration and
Cable Factor 6.10.4
Rotor Components Factor 6.10.5
approval.
Flutter Prevention and Structural Stiffness 6.11
1.7 The values in SI units are to be regarded as the standard.
Control Surfaces and Rotors 6.12
The values in parentheses are for information only.
Control Surface Installations (Other Than Rotor Blades) 6.13
Control Surface Hinges (Other Than Rotor Blades) 6.14
1.8 This standard does not purport to address all of the
Rotor Mass Balance 6.15
safety concerns, if any, associated with its use. It is the
Rotor Blade Clearance 6.16
Rotor Head Bearings 6.17
Control Systems 6.18
1
Cockpit Design 6.19
This specification is under the jurisdiction of ASTM Committee F37 on Light
Powerplant 7
Sport Aircraft and is the direct responsibility of Subcommittee F37.50 on Gy-
General 7.1
roplane.
Engine 7.2
Current edition approved Nov. 1, 2004. Published November 2004. Originally
Engine and Propeller Compatibility 7.3
approved in 2004. Last previous edition approved in 2004 as F 2352 – 04.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959, United States.
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F 2352 – 04a
3.2.4 CG—center of gravity
Section
Rotor Spin-Up and Brake Systems 7.4
3.2.5 CN—normal force coefficient
Powerplant and Rotor System Compatibility 7.5
3.2.6 IAS—indicated airspeed
Propeller Clearance 7.6
3.2.7 ICAO—International Aviation Organization
Fuel System 7.7
Oil System 7.8
3.2.8 LSA—light sport aircraft
Cooling 7.9
3.2.9 MGW—maximum gross weight
Induction System 7.10
3.2.10 MPRS—minimum power required airspeed
Exhaust System 7.11
Powerplant Controls and Access
...