ASTM F2352-05(2008)
(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 – 05 (Reapproved 2008)
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. 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
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 Gy-
Rotor Blade Clearance 6.16
roplane.
Rotor Head Bearings 6.17
Current edition approved May 15, 2008. Published July 2008. Originally
Control Systems 6.18
approved in 2004. Last previous edition approved in 2005 as F2352 – 05. DOI:
Cockpit Design 6.19
10.1520/F2352-05R08.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959, United States.
F2352 – 05 (2008)
3.1.6 primary structure, n—those parts of the structure the
Section
Powerplant 7
failure of which would endanger the gyroplane.
General 7.1
3.1.7 ultimate load, n—limitloadmultipliedbythefactorof
Engine 7.2
safety.
Engine and Propeller Compatibility 7.3
Rotor Spin-Up and Brake Systems 7.4
3.2 Acronyms:
Powerplant and Rotor System Compatibility 7.5
3.2.1 AOI—Aircraft Operating Instructions
Propeller Clearance 7.6
Fuel System 7.7
3.2.2 ASTM—American Society for Testing and Materials
Oil System 7.8
3.2.3 CAS—calibrated airspeed
Cooling 7.9
3.2.4 CG—center of gravity
Induction System 7.10
Exhaust System 7.11
3.2.5 CN—normal force coefficient
Powerplant Controls and Accessories 7.12
3.2.6 IAS—indicated airspeed
Cowling and Nacelle 7.13
Equipment 8
3.2.7 ICAO—International Aviation Organization
General 8.1
3.2.8 LSA—light sport aircraft
Instruments—Installation 8.2
Electrical Systems and Equipment 8.3 3.2.9 MGW—maximum gross weight
Miscellaneous Equipment 8.4
3.2.10 MPRS—minimum power required airspeed
Operating Limitations and Information 9
3.2.11 VFR—Visual Flight Rules
General 9.1
Airspeed Limitations 9.2
3.2.12 V —straight and level airspeed at full power
H
Weight and Balance 9.3
3.2.13 V —minimum controllable level flight airspeed,
MIN
Powerplant and Propeller Limitations 9.4
Aircraft Operating Instructions, AOI 9.5 IAS
Maintenance Manual 9.6
3.2.14 V —never exceed airspeed, IAS
NE
Markings and Placards 9.7
3.2.15 V —best rate of climb airspeed, IAS
Propellers 10 Y
Design and Construction 10.1
Keywords 12
4. Flight
4.1 General:
2. Referenced Documents
2 4.1.1 Conditions of Compliance:
2.1 ASTM Standards:
4.1.1.1 Each requirement of this section must be met in
F2339 Practice for Design and Manufacture of Reciprocat-
loading conditions and at the most adverse combination of
ing Spark Ignition Engines for Light Sport Aircraft
weight and balance loading conditions within which the
F2449 Specification for Manufacturer Quality Assurance
gyroplane will be operated.
Program for Light Sport Gyroplane Aircraft
4.1.1.2 Unless otherwise stipulated, performance require-
F2483 Practice for Maintenance and the Development of
ments are at standard atmospheric conditions (15°C (59°F))
Maintenance Manuals for Light Sport Aircraft
3 and sea level pressure altitude).
2.2 Federal Aviation Regulations:
4.1.1.3 Each requirement of this section must be met for all
FAR-33 Airworthiness Standards: Aircraft Engines
configurations at which the gyroplane will be operated except
2.3 Joint Aviation Regulations:
as otherwise stated. (If, for example, a gyroplane is equipped
JAR-E Joint Aviation Requirements for Engines
with a canopy or doors and it is intended that the gyroplane
JAR-22 Sailplanes and Powered Sailplanes
may be operated with the canopy or doors removed, then the
gyroplane must meet the requirements both with and without
3. Terminology
the canopy or doors installed.)
3.1 Definitions:
4.1.2 Load Distribution Limits—A method must be speci-
3.1.1 factor of safety, n—multiplier of limit load to deter-
fied to determine the range of weight and balance of the pilot,
mine design ultimate load.
passenger, and fuel (and ballast if required) that ensures
3.1.2 fire proof, adj—capable of withstanding for a period
satisfactory control and safety margins.The range of balance is
of at least 15 min the application of heat by the standard flame.
normally determined by a “hang test” with specified angular
3.1.3 fire resistant, adj—capable of withstanding for a
limits between a fixed airframe component and a horizontal
period of at least 5 min of heat by standard flame.
reference.
3.1.4 limit load, n—maximum expected static load on a
component. NOTE 1—The method of determination of proper weight and balance
must be specified in the AOI.
3.1.5 power off, n—for testing purposes, engine at idle.
4.1.3 Weight Limits—The MGW, which is the highest
weight that complies with each applicable structural loading
condition and each applicable flight requirement, must be
For referenced ASTM standards, visit the ASTM website, www.astm.org, or
contact ASTM Customer Service at service@astm.org. For Annual Book of ASTM
established. The MGW must be specified in the AOI.
Standards volume information, refer to the standard’s Document Summary page on
4.1.4 Empty Weight:
the ASTM website.
4.1.4.1 The design empty weight shall be specified by the
Available from Federal Aviation Administration, 800 Independence Ave., SW,
Washington, DC 20591.
manufacturer.
Available from Global Engineering Documents, 15 Inverness Way, East
Englewood, CO 80112-5704 NOTE 2—The design empty weight must be included in the AOI.
F2352 – 05 (2008)
4.1.4.2 The actual empty weight shall be established by 4.2.4.1 The minimum achievable power off rate of descent
weighing the gyroplane with fixed ballast, required minimum and the associated airspeed must be established by test at the
equipment, and unusable fuel and, where appropriate, maxi- maximum gross weight with the gyroplane trimmed at the
mum oil, engine coolant, and hydraulic fluid, and excluding minimum rate of descent airspeed.
usablefuel,weightofoccupant(s),andotherreadilyremovable
NOTE 5—The minimum power off rate of descent must be identified in
items of load.
the AOI.
4.1.4.3 The condition of the gyroplane at the time of
4.2.4.2 The maximum achievable power off glide ratio must
determining actual empty weight must be one that is well
be established by test at maximum gross weight with the
defined and easily repeated.
gyroplane trimmed at the best glide ratio airspeed.
4.1.5 Removable Ballast—Removable ballast may be used
in compliance with the flight requirements of this section.
NOTE 6—The best glide ratio airspeed must be identified in the AOI.
4.1.6 Rotor Speed Limits:
4.2.5 Never Exceed Airspeed (V )—The maximum safe
NE
4.1.6.1 At the critical combinations of weight, altitude, and
operating airspeed, considering the controllability, maneuver-
airspeed, the rotor speed must be stable and remain within the
ability, and stability requirements (4.3.1-4.5.6) must be estab-
established safe range that would permit any expected maneu-
lished. This airspeed must be established for the worst-case
ver to be performed safely. The established safe rotor speed
power condition between idle and full power.
range must be identified in theAOI.The established safe range
NOTE 7—The established V must be identified in the AOI.
must be established by the rotor blade manufacture or accept-
NE
able history of safe operation.
4.2.6 Minimum Controllable Airspeed for Level Flight,
4.1.6.2 The established safe range must be speed in consid-
V —The minimum speed for level flight at maximum
MIN
eration of spanwise and chordwise flexure cycles on the rotor
takeoff power must be established.
at the worst combination of load and rotor speed, and rotor
NOTE 8—The established V must be identified in the AOI.
MIN
stiffness that assures the in-plane vibration natural frequency is
higher than the maximum rotor RPM by a minimum factor of
4.2.7 Best Rate of Climb Airspeed (V )—The airspeed at
Y
1.2.
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
NOTE 9—The established V must be identified in the AOI.
Y
materials of known design strength and fatigue properties, and
4.2.8 Minimum Power Required Airspeed (MPRS)—The
performance testing at the extremes of the established safe
airspeed at which minimum power is required for steady level
range rotor speed.
flight must be established.
4.2 Performance:
4.2.1 General—The performance in accordance with Sec-
NOTE 10—The established MPRS must be identified in the AOI.
tion 4 applies:
4.2.9 Landing Distance—The distance required to land and
4.2.1.1 With normal piloting skill under average conditions;
come to rest from a point 15 m (50 ft) above the landing
4.2.1.2 In and shall be corrected to International Civil
surface, with zero wind, must be established. The approach
Aviation Organization (ICAO) defined standard atmosphere in
airspeed to achieve this performance must be established.
still air conditions at sea level;
4.2.1.3 Speeds shall be given in indicated (IAS) and cali-
NOTE 11—This landing distance and the approach speed to achieve this
brated (CAS) airspeeds; landing distance must be identified in the AOI.
4.2.1.4 At the most critical weight and CG combination;
4.2.10 Maximum Operating Altitude—The maximum safe
4.2.1.5 At the most unfavorable center of gravity for each
operating altitude considering the controllability, maneuver-
condition; and
ability, and stability requirements (4.3.1-4.5.6) must be estab-
4.2.1.6 Using engine power not in excess of the maximum
lished, except that demonstrating safe operating pressure alti-
declaredfortheenginetypeandwithoutexceedingpowerplant
tudes in excess of 3000 m (10 000 ft) is not required.
and propeller limitations in accordance with 9.4.
NOTE 12—The maximum operating altitude must be identified in the
4.2.2 Takeoff—The distance(s) required from rest, to takeoff
AOI.
and climb to 15 m (50 ft) above the takeoff surface, with zero
wind, with normally accepted flight technique(s) must be 4.2.11 Height/Velocity Envelope—The combinations of
established (with and without pre-rotator if it is intended that height and forward airspeed from which a safe landing cannot
the gyroplane is to be operated both ways). be made following engine failure must be established as a
limiting height-speed envelope (graph).
NOTE 3—These established takeoff distances must be identified in the
AOI.
NOTE 13—The height-speed envelope graph must be included in the
AOI.
4.2.3 Climb—The time for climb from leaving the ground
4.3 Controllability and Maneuverability:
up to 300 m (1000 ft) above the field must be established and
4.3.1 General—The gyroplane must be safely controllable
must be less than 4 min.
and maneuverable with sufficient margin of control movement
NOTE 4—The established climb must be identified in the AOI.
and blade freedom to correct for atmospheric turbulence and
4.2.4 Glide: permit control of the attitude of the gyroplane at all power
F2352 – 05 (2008)
settings at the critical weight and balance at sea level and at the 4.4 Longitudinal Lateral and Directional Control:
maximum operating altitude: 4.4.1 It must be possible at any speed including vertical
4.3.1.1 During s
...
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:F2352–04a Designation: F 2352 – 05 (Reapproved 2008)
Standard Specification for
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 (´) 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
Ground Loads 5.6
Main Component Requirements 5.7
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 Nov. 1, 2004. Published November 2004. Originally approved in 2004. Last previous edition approved in 2004 as F2352–04.
Current edition approved May 15, 2008. Published July 2008. Originally approved in 2004. Last previous edition approved in 2005 as F 2352 – 05.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959, United States.
F 2352 – 05 (2008)
Section
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
General 7.1
Engine 7.2
Engine and Propeller Compatibility 7.3
Rotor Spin-Up and Brake Systems 7.4
Powerplant and Rotor System Compatibil- 7.5
ity
Propeller Clearance 7.6
Fuel System 7.7
Oil System 7.8
Cooling 7.9
Induction System 7.10
Exhaust System 7.11
Powerplant Controls and Accessories 7.12
Cowling and Nacelle 7.13
Equipment 8
General 8.1
Instruments—Installation 8.2
Electrical Systems and Equipment 8.3
Miscellaneous Equipment 8.4
Operating Limitations and Information 9
General 9.1
Airspeed Limitations 9.2
Weight and Balance 9.3
Powerplant and Propeller Limitations 9.4
Aircraft Operating Instructions, AOI 9.5
Maintenance Manual 9.6
Markings and Placards 9.7
Propellers 10
Design and Construction 10.1
Keywords 11
Keywords 12
2. Referenced Documents
2.1 ASTM Standards:
F 2339Practice for Design and Manufacture of Reciprocating Spark Ignition Engines for Light Sport Aircraft Practice for
Design and Manufacture of Reciprocating Spark Ignition Engines for Light Sport Aircraft
F 2449 Specification for Manufacturer Quality Assurance Program for Light Sport Gyroplane Aircraft
F 2483 Practice for Maintenance and the Development of Maintenance Manuals for Light Sport Aircraft
2.2 Federal Aviation Regulations:
For referencedASTM standards, visit theASTM website, www.astm.org, or contactASTM Customer Service at service@astm.org. For Annual Book of ASTM Standards
volume information, refer to the standard’s Document Summary page on the ASTM website.
Available from Federal Aviation Administration, 800 Independence Ave., SW, Washington, DC 20591.
F 2352 – 05 (2008)
FAR-33 Airworthiness Standards: Aircraft Engines
2.3 Joint Aviation Regulations:
JAR-E Joint Aviation Requirements for Engines
JAR-22 Sailplanes and Powered Sailplanes
3. Terminology
3.1 Definitions:
3.1.1 factor of safety, n—multiplier of limit load to determine design ultimate load.
3.1.2 fire proof, adj—capable of withstanding for a period of at least 15 min the application of heat by the standard flame.
3.1.3 fire resistant, adj—capable of withstanding for a period of at least 5 min of heat by standard flame.
3.1.4 limit load, n—maximum expected static load on a component.
3.1.5 power off, n—for testing purposes, engine at idle.
3.1.6 primary structure, n—those parts of the structure the failure of which would endanger the gyroplane.
3.1.7 ultimate load, n—limit load multiplied by the factor of safety.
3.2 Acronyms:
3.2.1 AOI—Aircraft Operating Instructions
3.2.2 ASTM—American Society for Testing and Materials
3.2.3 CAS—calibrated airspeed
3.2.4 CG—center of gravity
3.2.5 CN—normal force coefficient
3.2.6 IAS—indicated airspeed
3.2.7 ICAO—International Aviation Organization
3.2.8 LSA—light sport aircraft
3.2.9 MGW—maximum gross weight
3.2.10 MPRS—minimum power required airspeed
3.2.11 VFR—Visual Flight Rules
3.2.12 V — straight and level airspeed at full power
H
3.2.13 V —minimum controllable level flight airspeed, IAS
MIN
3.2.14 V — never exceed airspeed, IAS
NE
3.2.15 V — best rate of climb airspeed, IAS
Y
4. Flight
4.1 General:
4.1.1 Conditions of Compliance:
4.1.1.1 Each requirement of this section must be met in loading conditions and at the most adverse combination of weight and
balance loading conditions within which the gyroplane will be operated.
4.1.1.2 Unless otherwise stipulated, performance requirements are at standard atmospheric conditions (15°C (59°F)) and sea
level pressure altitude).
4.1.1.3 Each requirement of this section must be met for all configurations at which the gyroplane will be operated except as
otherwise stated. (If, for example, a gyroplane is equipped with a canopy or doors and it is intended that the gyroplane may be
operated with the canopy or doors removed, then the gyroplane must meet the requirements both with and without the canopy or
doors installed.)
4.1.2 Load Distribution Limits—A method must be specified to determine the range of weight and balance of the pilot,
passenger, and fuel (and ballast if required) that ensures satisfactory control and safety margins. The range of balance is normally
determined by a “hang test” with specified angular limits between a fixed airframe component and a horizontal reference.
NOTE 1—The method of determination of proper weight and balance must be specified in the AOI.
4.1.3 Weight Limits—The MGW, which is the highest weight that complies with each applicable structural loading condition
and each applicable flight requirement, must be established. The MGW must be specified in the AOI.
4.1.4 Empty Weight:
4.1.4.1 The design empty weight shall be specified by the manufacturer.
NOTE 2—The design empty weight must be included in the AOI.
4.1.4.2 The actual empty weight shall be established by weighing the gyroplane with fixed ballast, required minimum
equipment,andunusablefueland,whereappropriate,maximumoil,enginecoolant,andhydraulicfluid,andexcludingusablefuel,
weight of occupant(s), and other readily removable items of load.
Available from Global Engineering Documents, 15 Inverness Way, East Englewood, CO 80112-5704
F 2352 – 05 (2008)
4.1.4.3 Theconditionofthegyroplaneatthetimeofdeterminingactualemptyweightmustbeonethatiswelldefinedandeasily
repeated.
4.1.5 Removable Ballast—Removable ballast may be used in compliance with the flight requirements of this section.
4.1.6 Rotor Speed Limits:
4.1.6.1 At the critical combinations of weight, altitude, and airspeed, the rotor speed must be stable and remain within the
established safe range that would permit any expected maneuver to be performed safely. The established safe rotor speed range
must be identified in theAOI. The established safe range must be established by the rotor blade manufacture or acceptable history
of safe operation.
4.1.6.2 The established safe range must be speed in consideration of spanwise and chordwise flexure cycles on the rotor at the
worst combination of load and rotor speed, and rotor stiffness that assures the in-plane vibration natural frequency is higher than
the maximum rotor RPM by a minimum factor of 1.2.
4.1.6.3 Compliance may also be established by use of acceptable aircraft manufacturing practices, correct use of materials of
known design strength and fatigue properties, and performance testing at the extremes of the established safe range rotor speed.
4.2 Performance:
4.2.1 General—The performance in accordance with Section 4 applies:
4.2.1.1 With normal piloting skill under average conditions;
4.2.1.2 In and shall be corrected to International Civil Aviation Organization (ICAO) defined standard atmosphere in still air
conditions at sea level;
4.2.1.3 Speeds shall be given in indicated (IAS) and calibrated (CAS) airspeeds;
4.2.1.4 At the most critical weight and CG combination;
4.2.1.5 At the most unfavorable center of gravity for each condition; and
4.2.1.6 Using engine power not in excess of the maximum declared for the engine type and without exceeding power plant and
propeller limitations in accordance with 9.4.
4.2.2 Takeoff—Thedistance(s)requiredfromrest,totakeoffandclimbto15m(50ft)abovethetakeoffsurface,withzerowind,
with normally accepted flight technique(s) must be established (with and without pre-rotator if it is intended that the gyroplane is
to be operated both ways).
NOTE 3—These established takeoff distances must be identified in the AOI.
4.2.3 Climb—The time for climb from leaving the ground up to 300 m (1000 ft) above the field must be established and must
be less than 4 min.
NOTE 4—The established climb must be identified in the AOI.
4.2.4 Glide:
4.2.4.1 The minimum achievable power off rate of descent and the associated airspeed must be established by test at the
maximum gross weight with the gyroplane trimmed at the minimum rate of descent airspeed.
NOTE 5—The minimum power off rate of descent must be identified in the AOI.
4.2.4.2 The maximum achievable power off glide ratio must be established by test at maximum gross weight with the gyroplane
trimmed at the best glide ratio airspeed.
NOTE 6—The best glide ratio airspeed must be identified in the AOI.
4.2.5 Never Exceed Airspeed (V )—The maximum safe operating airspeed, considering the controllability, maneuverability,
NE
and stability requirements (4.3.1-4.5.6) must be established. This airspeed must be established for the worst-case power condition
between idle and full power.
NOTE 7—The established V must be identified in the AOI.
NE
4.2.6 Minimum Controllable Airspeed for Level Flight, V —The minimum speed for level flight at maximum takeoff power
MIN
must be established.
NOTE 8—The established V must be identified in the AOI.
MIN
4.2.7 Best Rate of Climb Airspeed (V )—The airspeed at which the maximum rate of climb is achieved must be established.
Y
NOTE 9—The established V must be identified in the AOI.
Y
4.2.8 Minimum Power Required Airspeed (MPRS)—The airspeed at which minimum power is required for steady level flight
must be established.
NOTE 10—The established MPRS must be identified in the AOI.
4.2.9 Landing Distance—The distance required to land and come to rest from a point 15 m (50 ft) above the landing surface,
with zero wind, must be established. The approach airspeed to achieve this performance must be established.
NOTE 11—This landing distance and the approach speed to achieve this landing distance must be identified in the AOI.
F 2352 – 05 (2008)
4.2.10 Maximum Operating Altitude—The maximum safe operating altitude considering the controllability, maneuverability,
and stability requirements (4.3.1-4.5.6) must be established, except that demonstrating safe operating pressure altitudes in excess
of 3000 m (10 000 ft) is not required.
NOTE 12—The maximum operating altitude must be identified in the AOI.
4.2.11 Height/Velocity Envelope—The combinations of height and forward airspeed from which a safe landing cannot be made
following engine failure must be established as a limiting height-speed envelope (grap
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