ASTM F2352-14(2022)

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:F2352 −14 (Reapproved 2022)
Standard Specification for
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.Anumber in parentheses indicates the year of last reapproval.A
superscript epsilon (´) indicates an editorial change since the last revision or reapproval.
1. Scope 1.7 The values stated in SI units are to be regarded as
standard. The values given in parentheses are for information
1.1 Thisspecificationcoversthemanufactureofgyroplanes.
only.
This specification includes design and performance require-
1.8 This standard does not purport to address all of the
ments for light sport gyroplane aircraft.
safety concerns, if any, associated with its use. It is the
1.2 This specification applies to light gyroplane aircraft
responsibility of the user of this standard to establish appro-
seeking civil aviation authority approval in the form of flight
priate safety, health, and environmental practices and deter-
certificates, flight permits, or other like documentation.
mine the applicability of regulatory limitations prior to use.
1.3 A gyroplane for the purposes of this specification is
1.9 Table of Contents:
defined as a rotorcraft to be used for day VFR only, with rotor
Section
blades that are not engine-driven in flight and are supported in Scope 1
Table of Contents 1.9
flight by the reaction of the air on a single rotor that rotates
Referenced Documents 2
freely on a substantially vertical axis when the aircraft is in
Terminology 3
Definitions 3.1
horizontal flight.
Acronyms 3.2
1.4 These requirements apply to light gyroplanes of ortho- Flight 4
General 4.1
doxdesign.Aircrafthavingthefollowingbasicfeatureswillbe
Performance 4.2
so regarded:
Controllability and Maneuverability 4.3
Longitudinal Lateral and Directional Control 4.4
1.4.1 Rotors of either fixed collective pitch or collective
Stability 4.5
pitch control that are not adjustable in flight,
Ground-Handling Characteristics 4.6
1.4.2 Single engine with fixed or ground adjustable pitch Miscellaneous Flight Requirements 4.7
Structure 5
propeller,
General 5.1
1.4.3 No more than two occupant seats, and
Flight Loads 5.2
Engine Torque 5.3
1.4.4 Amaximumgrossweight(MGW)of725kg(1600lb)
Control System Loads 5.4
or less.
Stabilizing and Control Surfaces 5.5
Ground Loads 5.6
1.5 Whereitcanbeshownthataparticularfeatureissimilar
Main Component Requirements 5.7
in all significant respects to a feature that has historically
Emergency Landing Conditions 5.8
Other Loads 5.9
demonstrated compliance with this specification and can be
Design and Construction 6
considered a separate entity in terms of its operation, that
General 6.1
feature shall be deemed to be applicable and in compliance
Materials 6.2
Fabrication Methods 6.3
with this specification.
Locking of Connections 6.4
Protection of Structure 6.5
1.6 Wheretheserequirementsareinappropriatetoparticular
Inspection 6.6
designandconstructionfeatures,itwillbenecessarytosubmit
Provisions for Rigging and Derigging 6.7
an appropriate amendment of this specification to ASTM
Material Strength Properties and Design Values 6.8
Fatigue Strength 6.9
Committee F37 on Light Sport Aircraft for consideration and
Special Factors of Safety 6.10
approval.
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
This specification is under the jurisdiction ofASTM Committee F37 on Light
Control Surfaces and Rotors 6.12
Sport Aircraft and is the direct responsibility of Subcommittee F37.50 on Gyro-
Control Surface Installations (Other Than Rotor 6.13
plane.
Blades)
Current edition approved Oct. 1, 2022. Published October 2022. Originally
Control Surface Hinges (Other Than Rotor Blades) 6.14
approved in 2004. Last previous edition approved in 2014 as F2352–14. DOI:
Rotor Mass Balance 6.15
10.1520/F2352-14R22.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States
F2352−14 (2022)
CS-22EASA Certification Standard—Sailplanes and Pow-
Section
Rotor Blade Clearance 6.16
ered Sailplanes
Rotor Head Bearings 6.17
JAR-EJoint Aviation Requirements for Engines
Control Systems 6.18
JAR-22Sailplanes and Powered Sailplanes
Cockpit Design 6.19
Powerplant 7
General 7.1
3. Terminology
Engine 7.2
Engine and Propeller Compatibility 7.3
3.1 Definitions:
Rotor Spin-Up and Brake Systems 7.4
3.1.1 factor of safety, n—multiplier of limit load to deter-
Powerplant and Rotor System Compatibility 7.5
mine design ultimate load.
Propeller Clearance 7.6
Fuel System 7.7
3.1.2 fire proof, adj—capableofwithstandingforaperiodof
Oil System 7.8
at least 15 min the application of heat by the standard flame.
Cooling 7.9
Induction System 7.10
3.1.3 fire resistant, adj—capable of withstanding for a
Exhaust System 7.11
period of at least 5 min of heat by standard flame.
Powerplant Controls and Accessories 7.12
Cowling and Nacelle 7.13
3.1.4 limit load, n—maximum expected static load on a
Equipment 8
component.
General 8.1
Instruments—Installation 8.2
3.1.5 power off, n—for testing purposes, engine at idle.
Electrical Systems and Equipment 8.3
Miscellaneous Equipment 8.4
3.1.6 primary structure, n—those parts of the structure the
Operating Limitations and Information 9
failure of which would endanger the gyroplane.
General 9.1
Airspeed Limitations 9.2
3.1.7 ultimate load, n—limitloadmultipliedbythefactorof
Weight and Balance 9.3
safety.
Powerplant and Propeller Limitations 9.4
Pilot Operating Handbook, POH 9.5
3.2 Acronyms:
Maintenance Manual 9.6
3.2.1 ASTM—American Society for Testing and Materials
Markings and Placards 9.7
Propellers 10
3.2.2 CAS—calibrated airspeed
Design and Construction 10.1
Keywords 12
3.2.3 CG—center of gravity
1.10 This international standard was developed in accor-
3.2.4 CN—normal force coefficient
dance with internationally recognized principles on standard-
3.2.5 IAS—indicated airspeed
ization established in the Decision on Principles for the
3.2.6 ICAO—International Aviation Organization
Development of International Standards, Guides and Recom-
mendations issued by the World Trade Organization Technical
3.2.7 LSA—light sport aircraft
Barriers to Trade (TBT) Committee.
3.2.8 MGW—maximum gross weight
3.2.9 MPRS—minimum power required airspeed
2. Referenced Documents
2 3.2.10 POH—Pilot Operating Handbook
2.1 ASTM Standards:
F2339Practice for Design and Manufacture of Reciprocat- 3.2.11 VFR—Visual Flight Rules
ing Spark Ignition Engines for Light Sport Aircraft
3.2.12 V —straight and level airspeed at full power
H
F2483Practice for Maintenance and the Development of
3.2.13 V —minimum controllable level flight airspeed,
MIN
Maintenance Manuals for Light Sport Aircraft
IAS
F2972Specification for Light SportAircraft Manufacturer’s
3.2.14 V —never exceed airspeed, IAS
NE
Quality Assurance System
3.2.15 V —best rate of climb airspeed, IAS
2.2 CAA Standard: Y
CAP 643 British Light Gyroplane Airworthiness
4. Flight
Requirements, Section T
4.1 General:
2.3 Federal Aviation Regulations:
4.1.1 Conditions of Compliance:
FAR-33Airworthiness Standards: Aircraft Engines
4.1.1.1 Unless otherwise specified, each requirement of this
2.4 Joint Aviation Regulations:
section must be met for the most adverse combinations of
CS-EEASA Certification Standard—Engines
weight and balance loading conditions within which the
gyroplane will be operated.
For referenced ASTM standards, visit the ASTM website, www.astm.org, or
4.1.1.2 Unless otherwise stipulated, performance require-
contact ASTM Customer Service at service@astm.org. For Annual Book of ASTM
ments are at standard atmospheric conditions (15°C (59°F))
Standards volume information, refer to the standard’s Document Summary page on
and sea level pressure altitude).
the ASTM website.
4.1.1.3 Each requirement of this section must be met for all
Available from Civil Aviation Authority (CAA), Aviation House, Beehive
Ringroad, Crawley, West Sussex RH6 0YR, https://www.caa.co.uk/.
configurations at which the gyroplane will be operated except
Available from Federal Aviation Administration (FAA), 800 Independence
as otherwise stated. (If, for example, a gyroplane is equipped
Ave., SW, Washington, DC 20591, https://www.faa.gov.
with a canopy or doors and it is intended that the gyroplane
Available from IHS Market, 15 Inverness Way East, Englewood, CO 80112,
https://www.global.ihs.com. may be operated with the canopy or doors removed, then the
F2352−14 (2022)
gyroplane must meet the requirements both with and without 4.2.1.3 Speeds shall be given in indicated (IAS) and cali-
the canopy or doors installed.) brated (CAS) airspeeds;
4.1.2 Load Distribution Limits—A method must be speci- 4.2.1.4 At the most critical weight and CG combination;
fied to determine the range of weight and balance of the pilot, 4.2.1.5 At the most unfavorable center of gravity for each
passenger, and fuel (and ballast if required) that ensures condition; and
satisfactorycontrolandsafetymargins.Therangeofbalanceis 4.2.1.6 Using engine power not in excess of the maximum
normally determined by a “hang test” with specified angular declaredfortheenginetypeandwithoutexceedingpowerplant
limits between a fixed airframe component and a horizontal and propeller limitations in accordance with 9.4.
reference. 4.2.2 Takeoff—The distance(s) required from rest, to takeoff
and climb to 15 m (50 ft) above the takeoff surface, with zero
NOTE 1—The method of determination of proper weight and balance
wind, with normally accepted flight technique(s) must be
must be specified in the POH.
established (with and without pre-rotator if it is intended that
4.1.3 Weight Limits—The MGW, which is the highest
the gyroplane is to be operated both ways).
weight that complies with each applicable structural loading
condition and each applicable flight requirement, must be NOTE 3—These established takeoff distances must be identified in the
POH.
established. The MGW must be specified in the POH.
4.1.4 Empty Weight:
4.2.3 Climb—The time for climb from leaving the ground
4.1.4.1 The design empty weight shall be specified by the
up to 300 m (1000 ft) above the field must be established and
manufacturer.
must be less than 4 min.
NOTE 2—The design empty weight must be included in the POH.
NOTE 4—The established climb must be identified in the POH.
4.1.4.2 The actual empty weight shall be established by
4.2.4 Glide:
weighing the gyroplane with fixed ballast, required minimum
4.2.4.1 The minimum achievable power off rate of descent
equipment, and unusable fuel and, where appropriate, maxi-
and the associated airspeed must be established by test at the
mum oil, engine coolant, and hydraulic fluid, and excluding
maximum gross weight with the gyroplane trimmed at the
usablefuel,weightofoccupant(s),andotherreadilyremovable
minimum rate of descent airspeed.
items of load.
NOTE 5—The minimum power off rate of descent must be identified in
4.1.4.3 The condition of the gyroplane at the time of
the POH.
determining actual empty weight must be one that is well
4.2.4.2 Themaximumachievablepoweroffglideratiomust
defined and easily repeated.
be established by test at maximum gross weight with the
4.1.5 Removable Ballast—Removable ballast may be used
gyroplane trimmed at the best glide ratio airspeed.
in compliance with the flight requirements of this section.
4.1.6 Rotor Speed Limits:
NOTE 6—The best glide ratio airspeed must be identified in the POH.
4.1.6.1 At the critical combinations of weight, altitude, and
4.2.5 Never Exceed Airspeed (V )—The maximum safe
NE
airspeed, the rotor speed must be stable and remain within the
operating airspeed, considering the controllability,
established safe range that would permit any expected maneu-
maneuverability, and stability requirements (4.3.1 – 4.5.7)
ver to be performed safely. The established safe rotor speed
must be established. This airspeed must be established for the
rangemustbeidentifiedinthePOH.Theestablishedsaferange
worst-case power condition between idle and full power.
must be established by the rotor blade manufacture or accept-
NOTE 7—The established V must be identified in the POH.
able history of safe operation.
NE
4.1.6.2 The established safe range must be speed in consid-
4.2.6 Minimum Controllable Airspeed for Level Flight,
eration of spanwise and chordwise flexure cycles on the rotor
V —Theminimumspeedforlevelflightatmaximumtakeoff
MIN
at the worst combination of load and rotor speed, and rotor
power must be established.
stiffnessthatassuresthein-planevibrationnaturalfrequencyis
NOTE 8—The established V must be identified in the POH.
MIN
higher than the maximum rotor RPM by a minimum factor of
4.2.7 Best Rate of Climb Airspeed (V )—The airspeed at
1.2.
Y
which the maximum rate of climb is achieved must be
4.1.6.3 Compliance may also be established by use of
established.
acceptable aircraft manufacturing practices, correct use of
materials of known design strength and fatigue properties, and
NOTE 9—The established V must be identified in the POH.
Y
performance testing at the extremes of the established safe
4.2.8 Minimum Power Required Airspeed (MPRS)—The
range rotor speed.
airspeed at which minimum power is required for steady level
4.2 Performance:
flight must be established.
4.2.1 General—The performance in accordance with Sec-
NOTE 10—The established MPRS must be identified in the POH.
tion 4 applies:
4.2.1.1 Withnormalpilotingskillunderaverageconditions; 4.2.9 Landing Distance—The distance required to land and
4.2.1.2 In and shall be corrected to International Civil come to rest from a point 15 m (50 ft) above the landing
Aviation Organization (ICAO) defined standard atmosphere in surface, with zero wind, must be established. The approach
still air conditions at sea level; airspeed to achieve this performance must be established.
F2352−14 (2022)
NOTE11—Thislandingdistanceandtheapproachspeedtoachievethis
4.3.5 The gyroplane shall not require unusual attention to
landing distance must be identified in the POH.
prevent or stop any pitch oscillation at any and all power
settingsatthemostcriticalweightandCGcombinationatboth
4.2.10 Maximum Operating Altitude—The maximum safe
operating altitude considering the controllability, sea level and at the maximum operating altitude:
maneuverability, and stability requirements (4.3.1 – 4.5.7) 4.3.5.1 Duri
...