iTeh StandardsiTeh Standards
EURUSD
Your shopping cart is empty.
ASTM

ASTM F3264-18b

(Specification)

Standard Specification for Normal Category Aeroplanes Certification

Standard Specification for Normal Category Aeroplanes Certification

SCOPE
1.1 Applicability:  
1.1.1 This specification identifies the industry standards which have been determined by consensus to demonstrate compliance to the requirements (“the Rules”) for Level 1, 2, 3, 4 Normal Category Aeroplanes.  
1.1.2 Only standards that are considered mature enough for general application to certification projects and have been found acceptable by committee consensus to propose to the CAAs for acceptance as a Means of Compliance to their Rules are included.  
1.1.3 In the event that a particular CAA’s requirements are not harmonized with the other CAA’s requirements, the standards will be written to include the non-harmonized requirements as well as the harmonized requirements with the applicability defined in the standard.  
1.2 Civil Aviation Authorities:  
1.2.1 CAAs may accept a specific revision of this specification as an acceptable Means of Compliance (MoC) to their requirements. Acceptance and applicability as a MoC to the CAA’s airworthiness rules remains the decision of the respective CAAs. CAAs may accept this specification, with or without limitations as defined in their specification acceptance document. For information on which CAAs have accepted these standards (in whole or in part) as an acceptable MoC to their Rules, refer to the ASTM F44 webpage (www.astm.org/COMMITTEE/F44.htm) which includes CAA website links.  
1.3 Applicant Responsibility:  
1.3.1 The applicant must seek individual guidance from their respective CAA concerning the use of this specification and any referenced Specifications, Practices, Test Methods, or Guides to show compliance to the CAA rules. Alternatively, an applicant may propose a MoC other than those included in this specification but it is their responsibility to obtain acceptance of their proposed MoC from their CAA.  
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.

General Information

Status
Historical
Publication Date
31-Oct-2018
ICS
49.020 - Aircraft and space vehicles in general
Technical Committee
F44 - General Aviation Aircraft
Drafting Committee
F44.10 - General
Current Stage
Ref Project

Relations

Replaces
ASTM F3264-18a - Standard Specification for Normal Category Aeroplanes Certification
Effective Date
01-Nov-2018
Referred By
ASTM F3563-22 - Standard Specification for Design and Construction of Large Fixed Wing Unmanned Aircraft Systems
Effective Date
01-Nov-2018
Referred By
ASTM F3457-20 - Standard Guide for Aircraft Certification Education Standards for Engineers and Professionals in Aerospace Industry
Effective Date
01-Nov-2018

Buy Standard

ASTM F3264-18b - Standard Specification for Normal Category Aeroplanes CertificationASTM F3264-18b - Standard Specification for Normal Category Aeroplanes Certification
PreviousNext
Technical specification
ASTM F3264-18b - Standard Specification for Normal Category Aeroplanes Certification
English language
9 pages
sale 15% off
Preview
sale 15% off
Preview
REDLINE ASTM F3264-18b - Standard Specification for Normal Category Aeroplanes CertificationREDLINE ASTM F3264-18b - Standard Specification for Normal Category Aeroplanes Certification
PreviousNext
Technical specification
REDLINE ASTM F3264-18b - Standard Specification for Normal Category Aeroplanes Certification
English language
9 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:F3264 −18b
Standard Specification for
1
Normal Category Aeroplanes Certification
This standard is issued under the fixed designation F3264; 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 ization established in the Decision on Principles for the
Development of International Standards, Guides and Recom-
1.1 Applicability:
mendations issued by the World Trade Organization Technical
1.1.1 This specification identifies the industry standards
Barriers to Trade (TBT) Committee.
which have been determined by consensus to demonstrate
compliance to the requirements (“the Rules”) for Level 1, 2, 3,
2. Referenced Documents
4 Normal Category Aeroplanes.
2
1.1.2 Only standards that are considered mature enough for 2.1 ASTM Standards:
general application to certification projects and have been
NOTE 1—Referenced ASTM standards are listed in Sections5–10 of
found acceptable by committee consensus to propose to the
this specification.
CAAs for acceptance as a Means of Compliance to their Rules
F2490 Guide for Aircraft Electrical Load and Power Source
are included.
Capacity Analysis
1.1.3 In the event that a particular CAA’s requirements are
F3060 Terminology for Aircraft
not harmonized with the other CAA’s requirements, the stan-
F3061/F3061M Specification for Systems and Equipment in
dards will be written to include the non-harmonized require-
Small Aircraft
ments as well as the harmonized requirements with the
F3062/F3062M Specification forAircraft Powerplant Instal-
applicability defined in the standard.
lation
F3063/F3063M Specification for Aircraft Fuel and Energy
1.2 Civil Aviation Authorities:
Storage and Delivery
1.2.1 CAAs may accept a specific revision of this specifi-
F3064/F3064M Specification for Aircraft Powerplant
cation as an acceptable Means of Compliance (MoC) to their
Control, Operation, and Indication
requirements. Acceptance and applicability as a MoC to the
F3065/F3065M Specification for Aircraft Propeller System
CAA’s airworthiness rules remains the decision of the respec-
Installation
tive CAAs. CAAs may accept this specification, with or
F3066/F3066M Specification forAircraft Powerplant Instal-
without limitations as defined in their specification acceptance
lation Hazard Mitigation
document. For information on which CAAs have accepted
F3082/F3082M Specification for Weights and Centers of
these standards (in whole or in part) as an acceptable MoC to
Gravity of Aircraft
their Rules, refer to the ASTM F44 webpage (www.astm.org/
F3083/F3083M Specification for Emergency Conditions,
COMMITTEE/F44.htm) which includes CAA website links.
Occupant Safety and Accommodations
1.3 Applicant Responsibility:
F3093/F3093M Specification for Aeroelasticity Require-
1.3.1 The applicant must seek individual guidance from
ments
their respective CAA concerning the use of this specification
F3114 Specification for Structures
and any referenced Specifications, Practices, Test Methods, or
F3115/F3115M Specification for Structural Durability for
Guides to show compliance to the CAArules.Alternatively, an
Small Airplanes
applicant may propose a MoC other than those included in this
F3116/F3116M Specification for Design Loads and Condi-
specification but it is their responsibility to obtain acceptance
tions
of their proposed MoC from their CAA.
F3117 Specification for Crew Interface in Aircraft
1.4 This international standard was developed in accor-
F3120/F3120M Specification for Ice Protection for General
dance with internationally recognized principles on standard-
Aviation Aircraft
1
ThisspecificationisunderthejurisdictionofASTMCommitteeF44onGeneral
Aviation Aircraft and is the direct responsibility of Subcommittee F44.10 on
2
General. For referenced ASTM standards, visit the ASTM website, www.astm.org, or
Current edition approved Nov. 1, 2018. Published December 2018. Originally contact ASTM Customer Service at service@astm.org. For Annual Book of ASTM
approved in 2017. Last previous edition approved in 2018 as F3264–18a. DOI: Standards volume information, refer to the standard’s Document Summary page on
10.1520/F3264–18B. the ASTM website.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States
1

---------------------- Page: 1 ----------------------
F3264−18b
F3173/F3173M Specification for Aircraft Handling Charac- 3.3 Abbreviations:
teristics 3.3.1 CAA—Civil Aviation Authority
F3174/F3174M Specification for Establishing Operating
3.3.2 MoC—Means of Compliance
Limitations and Information for Aeroplanes
F3179/F3179M Specification for Performance of Aircraft
4. Ge
...

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: F3264 − 18a F3264 − 18b
Standard Specification for
1
Normal Category Aeroplanes Certification
This standard is issued under the fixed designation F3264; 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 Applicability:
1.1.1 This specification identifies the industry standards which have been determined by consensus to demonstrate compliance
to the requirements (“the Rules”) for Level 1, 2, 3, 4 Normal Category Aeroplanes.
1.1.2 Only standards that are considered mature enough for general application to certification projects and have been found
acceptable by committee consensus to propose to the CAAs for acceptance as a Means of Compliance to their Rules are included.
1.1.3 In the event that a particular CAA’s requirements are not harmonized with the other CAA’s requirements, the standards
will be written to include the non-harmonized requirements as well as the harmonized requirements with the applicability defined
in the standard.
1.2 Civil Aviation Authorities:
1.2.1 CAAs may accept a specific revision of this specification as an acceptable Means of Compliance (MoC) to their
requirements. Acceptance and applicability as a MoC to the CAA’s airworthiness rules remains the decision of the respective
CAAs. CAAs may accept this specification, with or without limitations as defined in their specification acceptance document. For
information on which CAAs have accepted these standards (in whole or in part) as an acceptable MoC to their Rules, refer to the
ASTM F44 webpage (www.astm.org/COMMITTEE/F44.htm) which includes CAA website links.
1.3 Applicant Responsibility:
1.3.1 The applicant must seek individual guidance from their respective CAA concerning the use of this specification and any
referenced Specifications, Practices, Test Methods, or Guides to show compliance to the CAA rules. Alternatively, an applicant
may propose a MoC other than those included in this specification but it is their responsibility to obtain acceptance of their
proposed MoC from their CAA.
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.
2. Referenced Documents
2
2.1 ASTM Standards:
NOTE 1—Referenced ASTM standards are listed in Sections 5 – 10 of this specification.
F2490 Guide for Aircraft Electrical Load and Power Source Capacity Analysis
F3060 Terminology for Aircraft
F3061/F3061M Specification for Systems and Equipment in Small Aircraft
F3062/F3062M Specification for Aircraft Powerplant Installation
F3063/F3063M Specification for Aircraft Fuel and Energy Storage and Delivery
F3064/F3064M Specification for Aircraft Powerplant Control, Operation, and Indication
F3065/F3065M Specification for Aircraft Propeller System Installation
F3066/F3066M Specification for Aircraft Powerplant Installation Hazard Mitigation
F3082/F3082M Specification for Weights and Centers of Gravity of Aircraft
F3083/F3083M Specification for Emergency Conditions, Occupant Safety and Accommodations
F3093/F3093M Specification for Aeroelasticity Requirements
1
This specification is under the jurisdiction of ASTM Committee F44 on General Aviation Aircraft and is the direct responsibility of Subcommittee F44.10 on General.
Current edition approved Oct. 1, 2018Nov. 1, 2018. Published November 2018December 2018. Originally approved in 2017. Last previous edition approved in 2018 as
F3264 – 18.F3264–18a. DOI: 10.1520/F3264-18A.10.1520/F3264–18B.
2
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 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, West Conshohocken, PA 19428-2959. United States
1

---------------------- Page: 1 ----------------------
F3264 − 18b
F3114 Specification for Structures
F3115/F3115M Specification for Structural Durability for Small Airplanes
F3116/F3116M Specification for Design Loads and Conditions
F3117 Specification for Crew Interface in Aircraft
F3120/F3120M Specification for Ice Pr
...

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 F3396/F3396M-23a(Practice)
Standard Practice for Aircraft Simplified Loads Criteria

SIGNIFICANCE AND USE
4.1 This practice provides one means for determining the aeroplane structural loads for flight, control surfaces, and control systems. This practice satisfies the simplified loads requirements set forth in Specification F3116/F3116M for Normal Category Aeroplanes.
SCOPE
1.1 This practice provides an acceptable means of meeting the airworthiness requirements for the flight design loads and conditions of small normal category level 1 and 2 aeroplanes. The material was developed through open consensus of international experts in general aviation. This information was created by focusing on Normal Category aeroplanes. The content may be more broadly applicable; it is the responsibility of the applicant to substantiate broader applicability as a specific means of compliance. The topics covered within this practice are: Simplified Design Load Criteria, Acceptable Methods for Control Surface Loads Calculations, Acceptable Methods for Primary Control System Loads Calculations, and Control Surface Loading (Level 1 Aeroplanes).  
1.2 This practice is applicable to normal category, low-speed, level 1 and 2 aeroplanes. Use of the term aeroplane used throughout this practice will mean “normal category, low-speed, level 1 or 2 aeroplane,” unless otherwise stated.  
1.3 An applicant intending to propose this information as means of compliance for a design approval must seek guidance from their respective oversight authority (for example, published guidance from applicable CAAs) concerning the acceptable use and application thereof. For information on which oversight authorities have accepted this standard (in whole or in part) as an acceptable means of compliance to their regulatory requirements (hereinafter “the Rules”), refer to the ASTM Committee F44 web page (www.astm.org/COMMITTEE/F44.htm).  
1.4 This document may present information in either SI units, English Engineering units, or both. The values stated in each system are not necessarily exact equivalents; therefore, to ensure conformance with the standard, each system shall be used independently of the other, and values from the two systems shall not be combined.  
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 limitations 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.

  • Standard
    12 pages
    English language
    sale 15% off
  • Standard
    12 pages
    English language
    sale 15% off
ASTM
ASTM F3116/F3116M-23a(Specification)
Standard Specification for Design Loads and Conditions

ABSTRACT
This specification covers airworthiness requirements for the design loads and conditions of small airplanes, and is applicable to small airplanes as defined in the F44 terminology standard. The applicant for a design approval must seek individual guidance from their respective civil aviation authority (CAA) body concerning the use of this specification as part of a certification plan.
SCOPE
1.1 This specification addresses the airworthiness requirements for the design loads and conditions of small airplanes.  
1.2 This specification is applicable to small airplanes as defined in the F44 terminology standard. Use of the term airplane is used throughout this specification and will mean “small airplane.”  
1.3 The applicant for a design approval must seek individual guidance from their respective CAA body concerning the use of this standard as part of a certification plan. For information on which CAA regulatory bodies have accepted this standard (in whole or in part) as a means of compliance to their Small Airplane Airworthiness Rules (hereinafter referred to as “the Rules”), refer to ASTM F44 webpage (www.ASTM.org/COMMITTEE/F44.htm) which includes CAA website links.  
1.4 Units—Currently there is a mix of SI and Imperial units. In many locations, SI units have been included otherwise units are as they appear in Amendment 62 of 14 CFR Part 23. In a future revision values will be consistently stated in SI units followed by Imperial units in square brackets. The values stated in each system may not be exact equivalents; therefore, each system shall be used independently of the other. Combining values from the two systems may result in non-conformance with the standard.  
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 limitations 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
    17 pages
    English language
    sale 15% off
  • Technical specification
    17 pages
    English language
    sale 15% off
ASTM
ASTM F3061/F3061M-23b(Specification)
Standard Specification for Systems and Equipment in Aircraft

SCOPE
1.1 This specification covers the systems and equipment aspects of airworthiness and design for aircraft. The material was developed through open consensus of international experts in general aviation. This information was created by focusing on Level 1, 2, 3, and 4 Normal Category aeroplanes. The content may be more broadly applicable; it is the responsibility of the Applicant to substantiate broader applicability as a specific means of compliance. The topics covered within this specification are: Basic Information, Electrical Systems, Environmental Requirements, Manual Flight Controls, Automatic Flight Controls, Flight Data and Voice Recording, Hazard Mitigation, Hydraulic Systems, Instrumentation, Mechanical Systems and Equipment, Exterior Lighting, Oxygen Systems, Pneumatic Systems, Lightning Protection, and High-Intensity Radiated Field (HIRF) Protection.  
1.2 An applicant intending to propose this information as Means of Compliance for a design approval must seek guidance from their respective oversight authority (for example, published guidance from applicable civil aviation authorities (CAAs) concerning the acceptable use and application thereof. For information on which oversight authorities have accepted this standard (in whole or in part) as an acceptable Means of Compliance to their regulatory requirements (hereinafter “the Rules”), refer to the ASTM Committee F44 web page (www.astm.org/COMMITTEE/F44.htm).  
1.3 This document may present information in either SI units, English Engineering units, or both; the values stated in each system may not be exact equivalents. Each system shall be used independently of the other; combining values from the two systems may result in nonconformance with the standard.  
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
    35 pages
    English language
    sale 15% off
  • Technical specification
    35 pages
    English language
    sale 15% off
ASTM
ASTM F3232/F3232M-23a(Specification)
Standard Specification for Flight Controls in Small Aircraft

ABSTRACT
This specification applies to the flight control aspects of airworthiness and design for "small" aircraft. It establishes the Aircraft Type Code (ATC) compliance matrix based on airworthiness level, number of engines, type of engine(s), stall speed, cruise speed, meteorological conditions, altitude, and maneuvers. An ATC is defined by taking into account both the technical considerations regarding the design of the aircraft and the airworthiness level established based upon risk-based criteria. The requirements established by this specification for manual flight control cover control surface installation, operation and arrangement, control system stops, trim systems, control system locks, limit load static tests, operation tests, control system details, spring devices, cable systems, wing flap controls, wing flap position, and flap interconnection. Requirements for automatic flight control cover automatic pilot systems, stability augmentation, and artificial stall barrier system.
SCOPE
1.1 This specification covers international standards for the flight control aspects of airworthiness and design for “small” aircraft.  
1.2 The applicant for a design approval must seek the individual guidance of their respective CAA body concerning the use of this specification as part of a certification plan. For information on which CAA regulatory bodies have accepted this specification (in whole or in part) as a means of compliance to their Small Aircraft Airworthiness regulations (hereinafter referred to as “the Rules”), refer to ASTM F44 webpage (www.ASTM.org/COMMITTEE/F44.htm) which includes CAA website links. Annex A1 maps the Means of Compliance described in this Standard to EASA CS 23, amendment 5, or later, and FAA 14 CFR 23, amendment 64, or later.  
1.3 The values stated in either SI units or inch-pound units are to be regarded separately as standard. The values stated in each system are not necessarily exact equivalents; therefore, to ensure conformance with the standard, each system shall be used independently of the other, and values from the two systems shall not be combined.  
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
    20 pages
    English language
    sale 15% off
  • Technical specification
    20 pages
    English language
    sale 15% off
ASTM
ASTM F3367-23(Practice)
Standard Practice for Simplified Methods for Addressing High-Intensity Radiated Fields (HIRF) and Indirect Effects of Lightning on Aircraft

SCOPE
1.1 This practice covers simplified methods for addressing High-Intensity Radiated Fields (HIRF) and the Indirect Effects of Lightning (IEL) on aircraft. The material was developed through open consensus of international experts in general aviation. This information was created by focusing on Aircraft Certification Level 1, Level 2, and Level 3 Normal Category aeroplanes. The content may be more broadly applicable. It is the responsibility of the applicant to substantiate broader applicability as a specific means of compliance. The topics covered within this practice are: Overview; Minimum Design Requirements; Aeroplane Assessment Level; HIRF and IEL Safety Analysis; HIRF Compliance; IEL Compliance.  
1.2 An applicant intending to propose this information as Means of Compliance for a design approval must seek guidance from their respective oversight authority (for example, published guidance from applicable CAA) concerning the acceptable use and application thereof. For information on which oversight authorities have accepted this practice (in whole or in part) as an acceptable Means of Compliance to their regulatory requirements (hereinafter “the Rules”), refer to the ASTM Committee F44 web page (www.astm.org/COMMITTEE/F44.htm).  
1.3 Units—The values stated in SI units are to be regarded as standard. No other units of measurement are included in this standard.  
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.

  • Standard
    8 pages
    English language
    sale 15% off
  • Standard
    8 pages
    English language
    sale 15% off
ASTM
ASTM F3331-18(2023)(Practice)
Standard Practice for Aircraft Water Loads

SIGNIFICANCE AND USE
4.1 This practice provides one means for determining the aeroplane structural loads for either dual floats or single hulls when taxiing on, taking off from, or landing on water. This practice satisfies the water loads requirements set forth in the Design Loads and Conditions Specification for Normal Category Aeroplanes.
SCOPE
1.1 This practice provides equations for calculating water loads for aeroplane dual floats and single hulls. The material was developed through open consensus of international experts in general aviation. This information was created by focusing on Level 1, 2, 3, and 4 Normal Category aeroplanes. The content may be more broadly applicable; it is the responsibility of the Applicant to substantiate broader applicability as a specific means of compliance.  
1.2 An applicant intended to propose this information as Means of Compliance for a design approval must seek guidance from their respective oversight authority (for example, published guidance from applicable CAAs) concerning the acceptable use and application thereof. For information on which oversight authorities have accepted this standard (in whole or in part) as an acceptable Means of Compliance to their regulatory requirements (hereinafter “the Rules”), refer to ASTM Committee F44 web page (www.astm.org/COMMITTEE/F44.htm).  
1.3 Units—The values stated in inch-pound units are to be regarded as standard.  
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.

  • Standard
    5 pages
    English language
    sale 15% off
ASTM
ASTM F3083/F3083M-23a(Specification)
Standard Specification for Emergency Conditions, Occupant Safety and Accommodations

ABSTRACT
This specification covers emergency conditions, occupant safety and accommodations for occupants and cargo. The applicant for a design approval must seek the individual guidance of their respective civil aviation authority (CAA) body concerning the use of this standard as part of a certification plan.
SCOPE
1.1 This specification addresses emergency conditions, occupant safety and accommodations for occupants and cargo.  
1.2 The applicant for a design approval must seek the individual guidance of their respective civil aviation authority (CAA) body concerning the use of this standard as part of a certification plan. For information on which CAA regulatory bodies have accepted this standard (in whole or in part) as a means of compliance to their airworthiness regulations (Hereinafter referred to as “the Rules”), refer to ASTM F44 webpage (www.ASTM.org/COMITTEE/F44.htm) which includes CAA website links.  
1.3 The values stated in either SI units or inch-pound units are to be regarded separately as standard. The values stated in each system are not necessarily exact equivalents; therefore, to ensure conformance with the standard, each system shall be used independently of the other, and values from the two systems shall not be combined.  
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
    14 pages
    English language
    sale 15% off
  • Technical specification
    14 pages
    English language
    sale 15% off
ASTM
ASTM F3082/F3082M-23a(Specification)
Standard Specification for Weights and Centers of Gravity of Aircraft

ABSTRACT
This specification covers airworthiness design standards associated with aeroplane flight. The applicant for a design approval shall seek the individual guidance of their respective civil aviation authority (CAA) body concerning the use of this specification as part of a certification plan.
SCOPE
1.1 This specification establishes the airworthiness design standards associated with aeroplane weight and center of gravity.  
1.2 The term “aeroplane” is utilized in this specification as it was originally conceived for normal category fixed wing aircraft with a maximum certificated weight of 19 000 lb or less and a passenger seating configuration up to 19 as defined in the Rules. However, these standards may be more broadly applicable and their usage should not be unnecessarily limited.  
1.3 The applicant for a design approval shall seek the individual guidance of their respective civil aviation authority (CAA) body concerning the use of this specification as part of a certification plan. For information on which CAA regulatory bodies have accepted this specification (in whole or in part) as a means of compliance to their small aircraft airworthiness regulations (hereinafter referred to as “the Rules”), refer to ASTM Committee F44 webpage (www.astm.org/COMMITTEE/F44.htm), which includes CAA website links.  
1.4 Units—The values stated in either SI units or inch-pound units are to be regarded separately as standard. The values stated in each system may not be exact equivalents; therefore, each system shall be used independently of the other. Combining values from the two systems may result in non-conformance with the standard.  
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 limitations 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
    4 pages
    English language
    sale 15% off
  • Technical specification
    4 pages
    English language
    sale 15% off
ASTM
ASTM F3179/F3179M-23(Specification)
Standard Specification for Performance of Aircraft

ABSTRACT
This specification provides airworthiness design requirements for general aeroplane performance, and is applicable to small aeroplanes as defined in Terminology F3060. The applicant for a design approval shall seek the individual guidance to their respective civil aviation authority (CAA) body concerning the use of this specification as part of a certification plan.
SCOPE
1.1 This specification covers the airworthiness design standards associated with general aeroplane performance. The material was developed through open consensus of international experts in general aviation. This information was created by focusing on Normal Category aeroplanes. The content may be more broadly applicable; it is the responsibility of the Applicant to substantiate broader applicability as a specific means of compliance. The topics covered within this specification are: Stalling, Takeoff and Landing Speeds; Takeoff Performance, Distances and Path; Climb; Landing Performance and Distances; Balked Landing.  
1.2 An applicant intending to propose this information as Means of Compliance for a design approval must seek guidance from their respective oversight authority (for example, published guidance from applicable civil aviation authorities (CAAs)) concerning the acceptable use and application thereof. For information on which oversight authorities have accepted this standard (in whole or in part) as an acceptable Means of Compliance to their regulatory requirements (hereinafter “the Rules”), refer to ASTM Committee F44 webpage (www.astm.org/COMMITTEE/F44.htm).  
1.3 Units—This specification may present information in either SI units, English Engineering units, or both. The values stated in each system are not necessarily exact equivalents; therefore, to ensure conformance with the standard, each system shall be used independently of the other, and values from the two systems shall not be combined.  
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
    13 pages
    English language
    sale 15% off
  • Technical specification
    13 pages
    English language
    sale 15% off
ASTM
ASTM F3233/F3233M-23(Specification)
Standard Specification for Flight and Navigation Instrumentation in Aircraft

ABSTRACT
This specification establishes the requirements for the instrumentation aspects of airworthiness and design for "small" aircraft. It prescribes the Aircraft Type Code (ATC) compliance matrix based on airworthiness level, number of engines, type of engine(s), stall speed, cruise speed, meteorological conditions, altitude, and maneuvers. An ATC is defined by taking into account both the technical considerations regarding the design of the aircraft and the airworthiness level established based upon risk-based criteria. The instrumentation requirements established by this specification cover flight and navigation instruments, electronic display instrument systems, airspeed indicating system, static pressure system, magnetic direction indicator, and instruments using a power source.
SCOPE
1.1 This specification covers flight and navigation instrumentation aspects of airworthiness and design. The material was developed through open consensus of international experts in general aviation. This information was created by focusing on Level 1, 2, 3, and 4 Normal Category aeroplanes; however, the content may be more broadly applicable, and should not be unduly limited. The topics covered within this specification are flight and navigation instruments including those for airspeed, altitude, attitude, heading, free air temperature, and speed warning.  
1.2 The applicant for a design approval shall seek the individual guidance of their respective CAA body concerning the use of this specification as part of a certification plan. For information on which CAA regulatory bodies have accepted this specification (in whole or in part) as a means of compliance to their Small Aircraft Airworthiness regulations (hereinafter referred to as “the Rules”), refer to ASTM F44 webpage (www.ASTM.org/COMMITTEE/F44.htm), which includes CAA website links. Annex A1 maps the means of compliance described in this specification to EASA CS 23, amendment 5 or later, and FAA 14 CFR 23, amendment 64 or later.  
1.3 The values stated in either SI units or inch-pound units are to be regarded separately as standard. The values stated in each system are not necessarily exact equivalents; therefore, to ensure conformance with the standard, each system shall be used independently of the other, and values from the two systems shall not be combined.  
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
    13 pages
    English language
    sale 15% off
  • Technical specification
    13 pages
    English language
    sale 15% off