ASTM F2352-09
(Specification)Standard Specification for Design and Performance of Light Sport Gyroplane Aircraft
Standard Specification for Design and Performance of Light Sport Gyroplane Aircraft
ABSTRACT
This specification covers the manufacture of gyroplanes and includes design and performance requirements for light sport gyroplane aircraft. A gyroplane is a rotorcraft to be used for day visual flight rules (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. Aircraft having the following basic features will be so regarded: rotors of either fixed collective pitch or collective pitch control that are not adjustable in flight, single engine with fixed or ground adjustable pitch propeller, no more than two occupant seats, and a maximum gross weight of some value. For compliance, the following flight requirements should be met: load distribution limit, weight limit, empty weight, removable ballast, and rotor speed limit. In order to comply in terms of performance, the requirements for the following shall be evaluated: takeoff, climb, glide, never exceed airspeed, minimum controllable airspeed for level flight, best rate of climb airspeed, landing distance, maximum operating altitude, and height/velocity envelope. The gyroplane must be safely controllable and maneuverable with sufficient margin of control movement and blade freedom to correct for atmospheric turbulence and permit control of the attitude of the gyroplane at all power settings at the critical weight and balance at sea level and at the maximum operating altitude. The evaluation of the gyroplane's longitudinal lateral and directional control and stability shall be discussed. In terms of structure requirements, the following should be taken into consideration: flight loads, engine torque, control system loads, stabilizing and control surfaces, ground loads, main component requirements, emergency landing conditions, and other loads.
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.
1.8 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 reg...
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Designation: F2352 – 09
Standard Specification for
1
Design and Performance of Light Sport Gyroplane Aircraft
This standard is issued under the fixed designation F2352; 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 1.8 This standard does not purport to address all of the
safety concerns, if any, associated with its use. It is the
1.1 Thisspecificationcoversthemanufactureofgyroplanes.
responsibility of the user of this standard to establish appro-
This specification includes design and performance require-
priate safety and health practices and determine the applica-
ments for light sport gyroplane aircraft.
bility of regulatory limitations prior to use.
1.2 This specification applies to light gyroplane aircraft
1.9 Table of Contents:
seeking civil aviation authority approval in the form of flight
Section
certificates, flight permits, or other like documentation.
Scope 1
1.3 A gyroplane for the purposes of this specification is
Table of Contents 1.9
defined as a rotorcraft to be used for day VFR only, with rotor
Referenced Documents 2
Terminology 3
blades that are not engine-driven in flight and are supported in
Definitions 3.1
flight by the reaction of the air on a single rotor that rotates
Acronyms 3.2
freely on a substantially vertical axis when the aircraft is in
Flight 4
General 4.1
horizontal flight.
Performance 4.2
1.4 These requirements apply to light gyroplanes of ortho-
Controllability and Maneuverability 4.3
dox design.Aircraft having the following basic features will be Longitudinal Lateral and Directional Control 4.4
Stability 4.5
so regarded:
Ground-Handling Characteristics 4.6
1.4.1 Rotors of either fixed collective pitch or collective
Miscellaneous Flight Requirements 4.7
pitch control that are not adjustable in flight, Structure 5
General 5.1
1.4.2 Single engine with fixed or ground adjustable pitch
Flight Loads 5.2
propeller,
Engine Torque 5.3
1.4.3 No more than two occupant seats, and Control System Loads 5.4
Stabilizing and Control Surfaces 5.5
1.4.4 Amaximum gross weight (MGW) of 725 kg (1600 lb)
Ground Loads 5.6
or less.
Main Component Requirements 5.7
1.5 Whereitcanbeshownthataparticularfeatureissimilar Emergency Landing Conditions 5.8
Other Loads 5.9
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
considered a separate entity in terms of its operation, that Materials 6.2
Fabrication Methods 6.3
feature shall be deemed to be applicable and in compliance
Locking of Connections 6.4
with this specification.
Protection of Structure 6.5
Inspection 6.6
1.6 Wheretheserequirementsareinappropriatetoparticular
Provisions for Rigging and Derigging 6.7
design and construction features, it will be necessary to submit
Material Strength Properties and Design Values 6.8
an appropriate amendment of this specification to ASTM
Fatigue Strength 6.9
Special Factors of Safety 6.10
Committee F37 on Light Sport Aircraft for consideration and
Bearing Factors 6.10.2
approval.
Fitting Factors 6.10.3
1.7 The values in SI units are to be regarded as the standard.
Cable Factor 6.10.4
Rotor Components Factor 6.10.5
The values in parentheses are for information only.
Flutter Prevention and Structural Stiffness 6.11
Control Surfaces and Rotors 6.12
Control Surface Installations (Other Than Rotor Blades) 6.13
1
Control Surface Hinges (Other Than Rotor Blades) 6.14
This specification is under the jurisdiction of ASTM Committee F37 on Light
Rotor Mass Balance 6.15
Sport Aircraft and is the direct responsibility of Subcommittee F37.50 on Gyro-
Rotor Blade Clearance 6.16
plane.
Rotor Head Bearings 6.17
Current edition approved Oct. 1, 2009. Published November 2009. Originally
Control Systems 6.18
approved in 2004. Last previous edition approved in 2008 as F2352 – 05 (2008).
Cockpit Design 6.19
DOI: 10.1520/F2352-09.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959, United States.
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F2352 – 09
3.1.3 fire resistant, adj—capable of withstanding for a
Section
Powerplant 7
period of at least 5 min of heat by standard flame.
General 7.1
3.1.4 limit load, n—maximum expected static load on a
Engine 7.2
component.
Engine and Propeller Compatibility 7.3
Rotor Spin-Up and Brake Systems 7.4
3.1.5 power off, n—for testing purposes, engine at idle.
Powerplant and Rotor System Compatibility 7.5
3.1.6 primary structure, n—those parts of the structure the
Propeller Clearance 7.6
failure of which would endanger the gyroplane.
...
This document is not anASTM standard and is intended only to provide the user of anASTM standard an indication of what changes have been made to the previous version. Because
it may not be technically possible to adequately depict all changes accurately, ASTM recommends that users consult prior editions as appropriate. In all cases only the current version
of the standard as published by ASTM is to be considered the official document.
Designation:F2352–05 (Reapproved 2008) Designation: F2352 – 09
Standard Specification for
1
Design and Performance of Light Sport Gyroplane Aircraft
This standard is issued under the fixed designation F2352; 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
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.
1.8 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
limitations prior to use.
1.9 Table of Contents:
Section
Scope 1
Table of Contents 1.9
Referenced Documents 2
Terminology 3
Definitions 3.1
Acronyms 3.2
Flight 4
General 4.1
Performance 4.2
Controllability and Maneuverability 4.3
Longitudinal Lateral and Directional Control 4.4
Stability 4.5
Ground-Handling Characteristics 4.6
Miscellaneous Flight Requirements 4.7
Structure 5
General 5.1
Flight Loads 5.2
Engine Torque 5.3
Control System Loads 5.4
Stabilizing and Control Surfaces 5.5
1
This specification is under the jurisdiction of ASTM Committee F37 on Light Sport Aircraft and is the direct responsibility of Subcommittee F37.50 on Gyroplane.
Current edition approved May 15, 2008. Published July 2008. Originally approved in 2004. Last previous edition approved in 2005 as F2352–05. DOI:
10.1520/F2352-05R08.
Current edition approved Oct. 1, 2009. Published November 2009. Originally approved in 2004. Last previous edition approved in 2008 as F2352 – 05 (2008). DOI:
10.1520/F2352-09.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959, United States.
1
---------------------- Page: 1 ----------------------
F2352 – 09
Section
Ground Loads 5.6
Main Component Requirements 5.7
Emergency Landing Conditions 5.8
Other Loads 5.9
Design and Construction 6
General 6.1
Materials 6.2
Fabrication Methods 6.3
Locking of Connections 6.4
Protection of Structure 6.5
Inspection 6.6
Provisions for Rigging and Derigging 6.7
Material Strength Properties and Design 6.8
Values
Fatigue Strength 6.9
Special Factors of Safety 6.10
Bearing Factors 6.10.2
Fitting Factors 6.10.3
Cable Factor 6.10.4
Rotor Components Factor 6.10.5
Flutter Prevention and Structural Stiffness 6.11
Control Surfaces and Rotors 6.12
Control Surface Installations (Other Than 6.13
Rotor Blades)
Control Surface Hinges (Other Than Rotor 6.14
Blades)
Rotor Mass Balance 6.15
Rotor Blade Clearance 6.16
Rotor Head Bearings 6.17
Control Systems 6.18
Cockpit Design 6.19
Powerplant 7
Gener
...
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