ASTM F3083/F3083M-15

Standard Specification for Emergency Conditions, Occupant Safety and Accommodations

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 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 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.  
1.4 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 and health practices and determine the applicability of regulatory limitations prior to use.

General Information

• Status: Historical
• Publication Date: 31-May-2015
• ICS: 49.020 - Aircraft and space vehicles in general
• Technical Committee: F44 - General Aviation Aircraft
• Drafting Committee: F44.30 - Structures

Relations

• Replaced By: ASTM F3083/F3083M-16 - Standard Specification for Emergency Conditions, Occupant Safety and Accommodations
• Effective Date: 01-Jun-2016
• Referred By: ASTM F3063/F3063M-21 - Standard Specification for Aircraft Fuel Storage and Delivery
• Effective Date: 01-Jun-2015
• Referred By: ASTM F3563-22 - Standard Specification for Design and Construction of Large Fixed Wing Unmanned Aircraft Systems
• Effective Date: 01-Jun-2015
• Referred By: ASTM F3061/F3061M-23a - Standard Specification for Systems and Equipment in Aircraft
• Effective Date: 01-Jun-2015
• Referred By: ASTM F3114-21 - Standard Specification for Structures
• Effective Date: 01-Jun-2015
• Referred By: ASTM F3180/F3180M-21 - Standard Specification for Low-Speed Flight Characteristics of Aircraft
• Effective Date: 01-Jun-2015
• Referred By: ASTM F3227/F3227M-22 - Standard Specification for Environmental Systems in Aircraft
• Effective Date: 01-Jun-2015
• Referred By: ASTM F3264-23 - Standard Specification for Normal Category Aeroplanes Certification
• Effective Date: 01-Jun-2015
• Referred By: ASTM F3408/F3408M-21 - Standard Specification for Aircraft Emergency Parachute Recovery Systems
• Effective Date: 01-Jun-2015
• Referred By: ASTM F3179/F3179M-22e1 - Standard Specification for Performance of Aircraft
• Effective Date: 01-Jun-2015

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:F3083/F3083M −15
StandardSpecification for
Emergency Conditions, Occupant Safety and
1
Accommodations
ThisstandardisissuedunderthefixeddesignationF3083/F3083M;thenumberimmediatelyfollowingthedesignationindicatestheyear
of original adoption or, in the case of revision, the year of last revision.Anumber in parentheses indicates the year of last reapproval.
A superscript epsilon (´) indicates an editorial change since the last revision or reapproval.
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1. Scope 2.3 European Aviation Safety Agency Regulations:
CS-23 Certification Specifications for Normal, Utility,
1.1 This specification addresses emergency conditions, oc-
Aerobatic, and Commuter Category Aeroplanes (Amend-
cupant safety and accommodations for occupants and cargo.
ment 3)
1.2 The applicant for a design approval must seek the
CS-VLACertifications Specifications for Very Light Aero-
individual guidance of their respective CAA body concerning
planes (Amendment 1)
the use of this standard as part of a certification plan. For
2.4 Other Standard:
information on which CAA regulatory bodies have accepted
PH1.25StandardSpecificationforSafetyPhotographicFilm
this standard (in whole or in part) as a means of compliance to
3. Terminology
their airworthiness regulations (Hereinafter referred to as “the
Rules”), refer to ASTM F44 webpage (www.ASTM.org/
3.1 See Terminology F3060 for definitions of terms used in
COMITTEE/F44.htm) which includes CAA website links.
this standard.
1.3 The values stated in either SI units or inch-pound units
3.2 Abbreviations:
are to be regarded separately as standard. The values stated in
3.2.1 g —peak deceleration for seat/restraint system test
p
each system may not be exact equivalents; therefore, each
3.2.2 HIC—head injury criteria
system shall be used independently of the other. Combining
3.2.3 t —rise time to the peak deceleration, g
r p
values from the two systems may result in non-conformance
with the standard.
4. Emergency Landing Conditions
1.4 This standard does not purport to address all of the
4.1 General:
safety concerns, if any, associated with its use. It is the
4.1.1 The airplane, although it may be damaged in emer-
responsibility of the user of this standard to establish appro-
gency landing conditions, must be designed as prescribed in
priate safety and health practices and determine the applica-
this section to protect each occupant under those conditions.
bility of regulatory limitations prior to use.
4.1.2 The structure must be designed to give each occupant
every reasonable chance of escaping serious injury when:
2. Referenced Documents
4.1.2.1 Proper use is made of the seats, safety belts, and
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2.1 ASTM Standards:
shoulder harnesses provided for in the design.
F3060Terminology for Aircraft
4.1.2.2 The occupant experiences the static inertia loads
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corresponding to the following ultimate load factors:
2.2 U.S. Code of Federal Regulations:
(1)Upward, 3.0 g, or 4.5 g for airplanes approved for
14 CFR Part 23Airworthiness Standards: Normal, Utility,
aerobatics;
Aerobatic and Commuter Category Airplanes
(2)Forward, 9.0 g;
49CFRPart572AnthropomorphicTestDevices(SubpartB)
(3)Sideward, 1.5 g; and
(4)Downward, 6.0 g when certification to the emergency
exit provisions of 5.6.4.4 is requested.
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ThisspecificationisunderthejurisdictionofASTMCommitteeF44onGeneral
4.1.2.3 Theitemsofmasswithinthecabin,thatcouldinjure
Aviation Aircraft and is the direct responsibility of Subcommittee F44.30 on
an occupant, experience the static inertia loads corresponding
Structures.
Current edition approved June 1, 2015. Published September 2015. DOI:
to the following ultimate load factors:
10.1520/F3083_F3083M-15.
(1)For Level 1 aircraft with a V not more than 83 km/h
S0
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For referenced ASTM standards, visit the ASTM website, www.astm.org, or
[45 kts]:
contact ASTM Customer Service at [e-mail]. For Annual Book of ASTM
Standards volume information, refer to the standard’s Document Summary page on
the ASTM website.
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Available from the U.S. Government Printing Office at www.ecfr.gov. Available from the European Aviation Safety Agency at www.easa.europa.eu.
Copyright © ASTM International, 100 Barr Harbor Drive, PO Box C700, West Conshohocken, PA 19428-2959. United States
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F3083/F3083M−15
(a)Upward, 3.0 g; crew or passenger occupancy during takeoff and landing, must
(b)Forward, 9.0 g; and successfully complete dynamic tests, or be demonstrated by
(c)Sideward, 1.5 g. rational analysis supported by dynamic tests, in accordance
(2)For all other aircraft: with each of the following conditions. These tests must be
(a)Upward, 3.0 g;
conducted with an occupant simulated by an anthropomorphic
(b)Forward, 18.0 g; and testdevice(ATD)definedby49CFRpart572,subpartB,oran
(c)Sideward, 4.5 g.
approved equivalent, with a nomina
...