iTeh StandardsiTeh Standards
EURUSD
Your shopping cart is empty.
ASTM

ASTM F2241-05a(2008)

(Specification)

Standard Specification for Continued Airworthiness System for Powered Parachute Aircraft

Standard Specification for Continued Airworthiness System for Powered Parachute Aircraft

ABSTRACT
This specification covers the continued airworthiness requirements that apply to the manufacture of powered parachute aircrafts and their qualification for possible civil aviation authority approval in the form of flight certificates, flight permits, or other like documentation.
SCOPE
1.1 The following continued airworthiness requirements apply for the manufacture of powered parachute aircraft and their qualification for possible certification.
1.2 This specification applies to powered parachute aircraft seeking civil aviation authority approval, in the form of flight certificates, flight permits, or other like documentation.  
1.3 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 requirements prior to use.

General Information

Status
Historical
Publication Date
14-May-2008
ICS
49.020 - Aircraft and space vehicles in general
Technical Committee
F37 - Light Sport Aircraft
Drafting Committee
F37.30 - Power Parachute
Current Stage
Ref Project

Relations

Replaces
ASTM F2241-05a - Standard Specification for Continued Airworthiness System for Powered Parachute Aircraft
Effective Date
15-May-2008
Replaced By
ASTM F2241-13 - Standard Specification for Continued Airworthiness System for Powered Parachute Aircraft
Effective Date
01-Jun-2013
Referred By
ASTM F3060-20 - Standard Terminology for Aircraft
Effective Date
15-May-2008
Referred By
ASTM F2244-14(2022) - Standard Specification for Design and Performance Requirements for Powered Parachute Aircraft
Effective Date
15-May-2008
Referred By
ASTM F2483-18e1 - Standard Practice for Maintenance and the Development of Maintenance Manuals for Light Sport Aircraft
Effective Date
15-May-2008
Referred By
ASTM F2426-13(2018)e1 - Standard Guide on Wing Interface Documentation for Powered Parachute Aircraft
Effective Date
15-May-2008

Buy Standard

ASTM F2241-05a(2008) - Standard Specification for Continued Airworthiness System for Powered Parachute AircraftASTM F2241-05a(2008) - Standard Specification for Continued Airworthiness System for Powered Parachute Aircraft
PreviousNext
Technical specification
ASTM F2241-05a(2008) - Standard Specification for Continued Airworthiness System for Powered Parachute Aircraft
English language
2 pages
sale 15% off
Preview
sale 15% off
Preview
REDLINE ASTM F2241-05a(2008) - Standard Specification for Continued Airworthiness System for Powered Parachute AircraftREDLINE ASTM F2241-05a(2008) - Standard Specification for Continued Airworthiness System for Powered Parachute Aircraft
PreviousNext
Technical specification
REDLINE ASTM F2241-05a(2008) - Standard Specification for Continued Airworthiness System for Powered Parachute Aircraft
English language
2 pages
sale 15% off
Preview
sale 15% off
Preview

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:F2241 −05a(Reapproved 2008)
Standard Specification for
Continued Airworthiness System for Powered Parachute
Aircraft
This standard is issued under the fixed designation F2241; 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 wheels (or floats), such that the wing and engine cannot be
flown without the wheels (or floats) and seat(s). Unique to the
1.1 The following continued airworthiness requirements
powered parachute is the large displacement between the
apply for the manufacture of powered parachute aircraft and
center of lift (high) and the center of gravity (low), which is
their qualification for possible certification.
pendulum effect. Pendulum effect limits angle of attack
1.2 This specification applies to powered parachute aircraft
changes, provides stall resistance and maintains flight stability.
seeking civil aviation authority approval, in the form of flight
certificates, flight permits, or other like documentation.
4. Current Operators List Documentation
1.3 This standard does not purport to address all of the
4.1 The manufacturer shall maintain a list of registered
safety concerns, if any, associated with its use. It is the
aircraft owners that includes all aircraft in service by serial
responsibility of the user of this standard to establish appro-
number, registration number, together with the name and
priate safety and health practices and determine the applica-
address of the owner.
bility of regulatory requirements prior to use.
4.2 In cases where the appropriate Civil Aviation Authority
2. Referenced Documents
maintains records of registered owners sufficient for tracking
2.1 ASTM Standards:
aircraft and the manufacturer has access to such records, the
F2240 Specification for Manufacturer Quality Assurance
manufacturer may elect to utilize such records for complying
Program for Powered Parachute Aircraft
with this section.
F2241 Specification for ContinuedAirworthiness System for
Powered Parachute Aircraft
5. Monitoring, Investigation and Remedial Action
F2242 Specification for ProductionAcceptance Testing Sys-
5.1 The manufacturer shall maintain contact with dealers
tem for Powered Parachute Aircraft
and owners who report incidents or other situations that might
F2243 Specification for Required Product Information to be
Provided with Powered Parachute Aircraft relate to safety, operations, or maintenance of aircraft produced
F2244 Specification for Design and Performance Require- and placed in service. The manufacturer will promptly inves-
ments for Powered Parachute Aircraft tigate all reported failures, malfunctions, or defects and de-
velop the appropriate corrective action. The magnitude of the
3. Terminology
service problem will define the subsequent publication to the
operators.
3.1 Definitions:
3.1.1 powered parachute, n—aircraftcomprisedofaflexible
or semi-rigid wing connected to a fuselage in such a way that 6. Safety Directives
the wing is not in position for flight until the aircraft is in
6.1 A safety directive will be distributed to all operators
motion. That aircraft has a fuselage with seats, engine, and
when a condition is found to exist that may also exist in other
aircraft in the fleet and which would cause a deviation from
original design or unsafe condition for flight, rendering the
This specification is under the jurisdiction of ASTM Committee F37 on Light
Sport Aircraft and is the direct responsibility of Subcommittee F37.30 on Power
aircraft unairworthy. This change, maintenance procedure,
Parachute.
inspection procedure, or other procedures deemed appropriate
Current edition approved May 15, 2008. Published July 2008. Originally
by the manufacturer is mandatory and must be performed and
approved in 2003. Last previous edition approved in 2005 as F2241 – 05a. DOI:
10.1520/F2241-05AR08.
documented in the individual aircraft logs in order for that
For referenced ASTM standards, visit the ASTM website, www.astm.org, or
aircraft to maintain compliance withASTM standards. When a
contact ASTM Customer Service at service@astm.org. For Annual Book of ASTM
safety directive is issued, immedia
...


This document is not an ASTM standard and is intended only to provide the user of an ASTM 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:F2241–05 Designation: F 2241 – 05a (Reapproved 2008)
Standard Specification for
Continued Airworthiness System for Powered Parachute
Aircraft
This standard is issued under the fixed designation F 2241; 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 The following continued airworthiness requirements apply for the manufacture of powered parachute aircraft and their
qualification for possible certification.
1.2 This specification applies to powered parachute aircraft seeking civil aviation authority approval, in the form of flight
certificates, flight permits, or other like documentation.
1.3 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
requirements prior to use.
2. Referenced Documents
2.1 ASTM Standards:
F 2240 Specification for Manufacturer Quality Assurance Program for Powered Parachute Aircraft
F 2241 Specification for Continued Airworthiness System for Powered Parachute Aircraft
F 2242 Specification for Production Acceptance Testing System for Powered Parachute Aircraft
F 2243 Specification for Required Product Information to be Provided with Powered Parachute Aircraft
F 2244 Specification for Design and Performance Requirements for Powered Parachute Aircraft
3. Terminology
3.1 Definitions:
3.1.1 powered parachute, n—aircraft comprised of a flexible or semi-rigid wing connected to a fuselage in such a way that the
wing is not in position for flight until the aircraft is in motion.That aircraft has a fuselage with seats, engine, and wheels (or floats),
such that the wing and engine cannot be flown without the wheels (or floats) and seat(s). Unique to the powered parachute is the
large displacement between the center of lift (high) and the center of gravity (low), which is pendulum effect. Pendulum effect
limits angle of attack changes, provides stall resistance and maintains flight stability.
4. Current Operators List Documentation
4.1A current operators list will be maintained by the manufacturer that includes all aircraft in service by serial number,
registration number, together with the name and address of the owner/operator. In order for the special airworthiness certificate for
any light sport aircraft to be valid, the new owner of an aircraft that has transferred ownership must notify the manufacturer and
have the current operators list appropriately updated to include the new owners name.
4.1 The manufacturer shall maintain a list of registered aircraft owners that includes all aircraft in service by serial number,
registration number, together with the name and address of the owner.
4.2 IncaseswheretheappropriateCivilAviationAuthoritymaintainsrecordsofregisteredownerssufficientfortrackingaircraft
andthemanufacturerhasaccesstosuchrecords,themanufacturermayelecttoutilizesuchrecordsforcomplyingwiththissection.
5. Monitoring, Investigation and Remedial Action
5.1 The manufacturer shall maintain contact with dealers and owners who report incidents or other situations that might relate
to safety, operations, or maintenance of aircraft produced and placed in service. The manufacturer will promptly investigate all
reportedfailures,malfunctions,ordefectsanddeveloptheappropriatecorrectiveaction.Themagnitudeoftheserviceproblemwill
This specification is under the jurisdiction ofASTM Committee F37 on Light SportAircraft and is the direct responsibility of Subcommittee F37.30 on Power Parachute.
Current edition approved March 1, 2005. Published March 2005. Originally approved in 2003. Last previous edition approved in 2003 as F2241–03.
Current edition approved May 15, 2008. Published July 2008. Originally approved in 2003. Last previous edition approved in 2005 as F 2241 – 05a.
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.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700,
...

Questions, Comments and Discussion

Ask us and Technical Secretary will try to provide an answer. You can facilitate discussion about the standard in here.

This May Also Interest You

ASTM
ASTM F2245-23(Specification)
Standard Specification for Design and Performance of a Light Sport Airplane

ABSTRACT
This specification covers airworthiness requirements for the design of powered fixed wing light sport aircraft, an “airplane.” In order to comply with flight requirements, the following shall be evaluated: load distribution limit, propeller speed and pitch limit, stalling speed, takeoff, climb, landing, balked landing, controllability and maneuverability, vibrations, and ground control and stability. For compliance of structure requirements, the following shall be considered: flight loads; control surface and system loads; horizontal stabilizing and balancing surfaces (balancing loads, maneuvering loads, and gust loads); vertical stabilizing surfaces (maneuvering loads, gust loads, and outboard fins or winglets); supplementary conditions for stabilizing surfaces; ailerons, wing flaps, and special devices; ground load conditions; water load conditions; emergency landing conditions; and other loads. The aircraft shall be designed with the following minimum instrumentation and equipment: flight and navigation instruments such as airspeed indicator, and altimeter; powerplant instruments such as fuel quantity indicator, tachometer (RPM), engine “kill” switch, and engine instruments; miscellaneous equipment such as master switch, and overload protection device; and safety belts and harnesses. Each airplane shall include a Pilot Operating Handbook (POH).
SCOPE
1.1 This specification covers airworthiness requirements for the design of powered fixed wing light sport aircraft, an “airplane.”  
1.2 This specification is applicable to the design of a light sport aircraft/airplane as defined by regulations and limited to VFR flight.  
1.3 Units—The values given in this standard are in SI units and are to be regarded as standard. The values given in parentheses are mathematical conversions to inch-pound (or other) units that are provided for information only and are not considered standard. The values stated in each system may not be exact equivalents. Where it may not be clear, some equations provide the units of the result directly following the equation.  
1.4 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, health, and environmental practices and determine the applicability of regulatory requirements prior to use.  
1.5 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.

  • Technical specification
    35 pages
    English language
    sale 15% off
  • Technical specification
    35 pages
    English language
    sale 15% off
ASTM
ASTM F2745-15(2023)(Specification)
Standard Specification for Required Product Information to be Provided with an Airplane

SCOPE
1.1 The following requirements apply to the documentation of Light Sport Airplanes. This specification covers the Pilot’s Operating Handbook (POH), Flight Training Supplement (FTS), Maintenance Manual, Aircraft Kit Assembly Instructions (KAI), Component Original Equipment Manufacturer (OEM) manuals, Aircraft OEM’s Statement of Compliance, Registration, and Airframe Records information required for aircraft designed and manufactured in accordance with the ASTM Standards.  
1.1.1 This specification covers the minimum requirements for information that shall be provided by the airplane OEM or seller of a new light sport airplane, light sport airplane kit, engines, propellers, or accessories (that is, radio, transponder, instruments, GPS, etc.) as a part of the initial sale or transfer to the first end-user.  
1.1.2 This specification does not apply to the sale or transfer of used light sport airplane, engines, propellers, or accessories.  
1.2 This specification applies to airplanes seeking civil aviation authority approval, in the form of airworthiness certificates or other like documentation.  
1.3 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, health, and environmental practices and determine the applicability of regulatory limitations prior to use.  
1.4 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.

  • Technical specification
    3 pages
    English language
    sale 15% off
ASTM
ASTM F2746-14(2023)(Specification)
Standard Specification for Pilot’s Operating Handbook (POH) for Light Sport Airplane

SCOPE
1.1 This specification provides the minimum requirements for a Pilot’s Operating Handbook (POH) for an aircraft designed, manufactured, and operated as a light sport aircraft.  
1.2 This specification defines the POH information that shall be provided by the aircraft manufacturer of a new airplane or airplane kit as a part of the initial sale or transfer to the first-end user.
Note 1: The POH may also be referred to as an Aircraft Operating Instruction (AOI). However, POH is considered the approved nomenclature.  
1.3 This specification applies to an airplane seeking civil aviation authority approval, in the form of flight certificates, flight permits, or other like documentation as a light sport aircraft.  
1.4 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, health, and environmental practices and determine the applicability of regulatory limitations prior to use.  
1.5 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.

  • Technical specification
    3 pages
    English language
    sale 15% off
ASTM
ASTM F3619-22(Specification)
Standard Specification for Aeroelasticity Requirements for a Light Sport Airplane

SCOPE
1.1 This specification addresses the aeroelasticity requirements of the airplane and is applicable to the design of a light sport aircraft/airplane as defined by regulations.  
1.2 This specification shall apply to airplanes with VH greater than 62 m/s (120 KCAS) and with VNE less than or equal to 129 m/s (250 KCAS). The content of this specification may be more broadly applicable. It is the responsibility of the applicant to substantiate broader applicability as a specific means of compliance.  
1.3 Units—The values given in this standard are in SI units and are to be regarded as standard. The values given in parentheses are mathematical conversions to inch-pound (or other) units that are provided for information only and are not considered standard. The values stated in each system may not be exact equivalents. Where it may not be clear, some equations provide the units of the result directly following the equation. It is also noted that the internationally accepted units for altitude and airspeed are feet and knots, respectively. This is the only exception to standard SI units.  
1.4 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, health, and environmental practices and determine the applicability of regulatory limitations prior to use.  
1.5 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.

  • Technical specification
    2 pages
    English language
    sale 15% off
ASTM
ASTM F2244-14(2022)(Specification)
Standard Specification for Design and Performance Requirements for Powered Parachute Aircraft

ABSTRACT
This specification covers design and performance requirements for powered parachute aircraft. It also applies to powered parachute aircraft seeking civil aviation authority approval, in the form of flight certificates, flight permits, or other like documentation. Each of the performance requirements shall be met at the maximum takeoff weight and most critical center of gravity (CG) position. To the extent that CG adjustment devices may be adjusted for flight, these components will be evaluated in the least favorable recommended position as it affects either performance or structural strength. All performance requirements apply in and shall be corrected to International Civil Aviation Organization (ICAO) defined standard atmosphere in still air conditions at sea level. Speeds shall be given in indicated (IAS) and calibrated (CAS) airspeeds in miles per hour (MPH). The wing performance, climb performance, controllability and maneuverability, and reference parameters shall be carefully determined and evaluated. Stability requirements of the aircraft such as longitudinal stability, lateral stability, and directional stability shall be discussed as well. In terms of structural requirements, the load and proof of structure of the aircraft shall be considered.
SCOPE
1.1 The following requirements apply for the manufacture of powered parachute aircraft. This specification includes design and performance requirements for powered parachute aircraft.  
1.2 This specification applies to powered parachute aircraft seeking civil aviation authority approval, in the form of flight certificates, flight permits, or other like documentation.  
1.3 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, health, and environmental practices and determine the applicability of regulatory requirements prior to use.  
1.4 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.

  • Technical specification
    5 pages
    English language
    sale 15% off
ASTM
ASTM F2352-14(2022)(Specification)
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 stated in SI units are to be regarded as standard. The values given 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, health, and environmental practices an...

  • Technical specification
    17 pages
    English language
    sale 15% off
ASTM
ASTM F2355-14(2022)(Specification)
Standard Specification for Design and Performance Requirements for Lighter-Than-Air Light Sport Aircraft

ABSTRACT
This specification covers design and performance requirements that apply for the manufacture of lighter-than-air light sport aircraft. Performance requirements for balloons, airships and thermal airships are: proof of compliance; general performance; flight performance; climb; controllability and maneuverability; descent; landing; and stability and control. Structure requirements for airships, thermal airships, balloons and vectored thrust balloons are presented in details. The power plant installation shall be easily accessible for inspection and maintenance. The equipments for airships and free balloons are presented in details. The operating limitations and other information necessary for safe operation shall be established and documented in a flight manual, which will be made available to the pilot upon aircraft delivery.
SCOPE
1.1 This specification covers design and performance requirements that apply for the manufacture of lighter-than-air light sport aircraft.  
1.2 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, health, and environmental practices and determine the applicability of regulatory requirements prior to use.  
1.3 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.

  • Technical specification
    6 pages
    English language
    sale 15% off
ASTM
ASTM F2564-14(2022)(Specification)
Standard Specification for Design and Performance of a Light Sport Glider

ABSTRACT
This specification covers airworthiness requirements for the design of a powered or non-powered fixed wing light sport aircraft, a “glider.” Stability shall be shown by a tendency for the glider to return toward steady flight after: (1) a “push” from steady flight that results in a speed increase, followed by a non-abrupt release of the pitch control; and (2) a “pull” from steady flight that results in a speed decrease, followed by a non-abrupt release of the pitch control. Strength requirements are specified in terms of limit loads (the maximum loads to be expected in service) and ultimate loads (limit loads multiplied by prescribed factors of safety). The suitability of each structural design detail and part having an important bearing on safety shall be established by test. Each combination of engine, exhaust, cooling and fuel system on a powered glider must be compatible with the glider, and function in a safe and satisfactory manner within the operational limits of the glider and powerplant. Each aircraft shall include Aircraft Operating Instructions (AOI).
SCOPE
1.1 This specification covers airworthiness requirements for the design of a powered or non-powered fixed wing light sport aircraft, a “glider.”  
1.2 This specification is applicable to the design of a light sport aircraft glider as defined by regulations and limited to day VFR flight.  
1.3 A glider for the purposes of this specification is defined as a heavier than air aircraft that remains airborne through the dynamic reaction of the air with a fixed wing and in which the ability to remain aloft in free flight does not depend on the propulsion from a power plant. A powered glider is defined for the purposes of this specification as a glider equipped with a power plant in which the flight characteristics are those of a glider when the power plant is not in operation.  
1.4 The values stated in SI units are to be regarded as standard. The values given in parenthesis are for information only.  
1.5 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, health, and environmental practices and determine the applicability of regulatory requirements prior to use.  
1.6 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.

  • Technical specification
    19 pages
    English language
    sale 15% off
ASTM
ASTM F3035-22(Practice)
Standard Practice for Production Acceptance in the Manufacture of a Fixed Wing Light Sport Aircraft

SIGNIFICANCE AND USE
4.1 The purpose of this practice is to provide the minimum requirements necessary for the establishment of a production acceptance program for a manufacturer of light sport aircraft.  
4.2 The purpose of this specification is to provide the minimum requirements for the establishment of a ground and flight test program for verifying the initial production aircraft meets certain operational performance requirements that have been set forth by the manufacturer in its Pilot’s Operating Handbook (POH).  
4.3 In addition, this specification provides minimum requirements to verify that each subsequent production airplane has no obvious defects that would prevent the safe operation of the airplane.  
4.4 All requirements given in this specification are to be performed in accordance with the manufacturer’s Specification F2972-compliant quality assurance system requirements.  
4.5 The following criteria should not be construed as requirements for specific features to be included on a LSA. When a requirement specifies a feature that does not exist on a LSA, the requirement does not apply.
SCOPE
1.1 The following requirements apply for the manufacture of fixed wing aircraft, including gliders. This practice includes the production acceptance test requirements.  
1.2 This practice applies to aircraft seeking civil aviation authority approval, in the form of flight certificates, flight permits, or other like documentation.  
1.3 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, health, and environmental practices and determine the applicability of regulatory limitations prior to use.  
1.4 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.

  • Standard
    3 pages
    English language
    sale 15% off
ASTM
ASTM F2316-12(2022)(Specification)
Standard Specification for Airframe Emergency Parachutes

ABSTRACT
This specification covers minimum requirements for the design, manufacture, and installation of airframe emergency parachutes for light sport aircraft. Materials used for parts and assemblies, shall meet the conditions specified for (1) suitability and durability, (2) strength and other properties assumed in the design data, and (3) effects of environmental conditions, such as temperature and humidity, expected in service. Parachute model designations shall include the following: (1) parachute system parts list, (2) new parachutes model designations, (3) design changes, and (4) installation design changes. The strength requirements shall be specified in terms of limit loads and ultimate loads. The following minimum performance standards for the basic parachute system design shall be met: (1) parachute strength test to determine the ultimate load factor, (2) rate of descent, (3) component strength test, (4) staged deployment, and (5) environmental conditions. The installation design requirements are specified for the following: (1) coordination, (2) weight and balance, (3) system mounting, (4) extraction performance, (5) parachute attachment to the airframe, (6) activating housing routing, and (7) occupant restraint. Other requirements such as system function and operations and product marking are also detailed.
SCOPE
1.1 This specification covers minimum requirements for the design, manufacture, and installation of parachutes for airframes. Airframe emergency parachutes addressed in this specification refer to parachute systems designed, manufactured, and installed to recover the airframe and its occupants at a survivable rate of descent. This specification is not applicable to deep-stall parachutes, spin recovery parachutes, drogue parachutes, or other airframe emergency aerodynamic decelerators not specifically intended for safely lowering the airframe and occupants to the ground. The specification is applicable to these types of parachutes if they are an integral part of an airframe emergency parachute system designed to recover the airframe and occupants at a survivable rate of descent.  
1.2 The values stated in SI units are to be regarded as standard. There may be values given in parentheses that are mathematical conversions to inch-pound units. Values in parentheses are provided for information only and are not considered standard.  
1.2.1 Note that within the aviation community mixed units are appropriate in accordance with International Civil Aviation Organization (ICAO) agreements. While the values stated in SI units are regarded as standard, certain values such as airspeeds in knots and altitude in feet are also accepted as standard.  
1.3 Airframe emergency parachute recovery systems have become an acceptable means of greatly reducing the likelihood of serious injury or death in an in-flight emergency. Even though they have saved hundreds of lives in many different types of conditions, inherent danger of failure, even if properly designed, manufactured and installed, remains due to the countless permutations of random variables (attitude, altitude, accelerations, airspeed, weight, geographic location, etc.) that may exist at time of usage. The combination of these variables may negatively influence the life saving function of these airframe emergency parachute systems. They are designed to be a supplemental safety device and to be used at the discretion of the pilot when deemed to provide the best chance of survivability.  
1.4 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, health, and environmental practices and determine the applicability of regulatory requirements prior to use.  
1.5 This international standard was developed in accordance with internationally recognized principles on standardization established in the Decision on Principles fo...

  • Technical specification
    6 pages
    English language
    sale 15% off