14 CFR 27.613 - Material strength properties and design values. | Title 14 - Aeronautics and Space | Code of Federal Regulations

§ 27.613

Material strength properties and design values.

(a) Material strength properties must be based on enough tests of material meeting specifications to establish design values on a statistical basis.

(b) Design values must be chosen to minimize the probability of structural failure due to material variability. Except as provided in paragraphs (d) and (e) of this section, compliance with this paragraph must be shown by selecting design values that assure material strength with the following probability—

(1) Where applied loads are eventually distributed through a single member within an assembly, the failure of which would result in loss of structural integrity of the component, 99 percent probability with 95 percent confidence; and

(2) For redundant structure, those in which the failure of individual elements would result in applied loads being safely distributed to other load-carrying members, 90 percent probability with 95 percent confidence.

(c) The strength, detail design, and fabrication of the structure must minimize the probability of disastrous fatigue failure, particularly at points of stress concentration.

(d) Design values may be those contained in the following publications (available from the Naval Publications and Forms Center, 5801 Tabor Avenue, Philadelphia, Pennsylvania 19120) or other values approved by the Administrator:

(1) MIL-HDBK-5, “Metallic Materials and Elements for Flight Vehicle Structure”.

(2) MIL-HDBK-17, “Plastics for Flight Vehicles”.

(3) ANC-18, “Design of Wood Aircraft Structures”.

(4) MIL-HDBK-23, “Composite Construction for Flight Vehicles”.

(e) Other design values may be used if a selection of the material is made in which a specimen of each individual item is tested before use and it is determined that the actual strength properties of that particular item will equal or exceed those used in design.

(Secs. 313(a), 601, 603, 604, Federal Aviation Act of 1958 ( 49 U.S.C. 1354(a), 1421, 1423, 1424 ), sec. 6(c), Dept. of Transportation Act ( 49 U.S.C. 1655(c) ))

[Doc. No. 5074, 29 FR 15695, Nov. 24, 1964, as amended by Amdt. 27-16, 43 FR 50599, Oct. 30, 1978; Amdt. 27-26, 55 FR 8000, Mar. 6, 1990]

Title 14 published on 2012-01-01

The following are only the Rules published in the Federal Register after the published date of Title 14.

For a complete list of all Rules, Proposed Rules, and Notices view the Rulemaking tab.

2012-08-22; vol. 77 # 163 - Wednesday, August 22, 2012

77 FR 50576 - Damage Tolerance and Fatigue Evaluation of Composite Rotorcraft Structures; OMB Approval of Information Collection

GPO FDSys XML | Text

Additional Documents

type	regulations.gov
FR Doc.	2012-20685
RIN	2120-AJ52
Docket No.	FAA-2009-0660
Amdt. Nos.	27-47, 29-54

DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration

Final rule; OMB approval of information collection.

The rule published on December 1, 2011, and became effective on January 30, 2012. However, at the time of publication, the new information collection requirements imposed by 14 CFR 27.573 and 29.573 lacked OMB approval. This document announces receipt of OMB's June 28, 2012 approval.

14 CFR Parts 27 and 29

Summary

This document notifies the public of the Office of Management and Budget's (OMB's) approval of the information collection requirement contained in the FAA's final rule, “Damage Tolerance and Fatigue Evaluation of Composite Rotorcraft Structures,” which was published on December 1, 2011.

2012-08-13; vol. 77 # 156 - Monday, August 13, 2012

77 FR 48058 - Special Conditions: Eurocopter France, EC130T2; Use of 30-Minute Power Rating

GPO FDSys XML | Text

Additional Documents

type	regulations.gov
FR Doc.	2012-19444
RIN
Docket No.	FAA-2012-0820
Special Conditions No.	27-028-SC

DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration

Final special conditions; request for comments.

The effective date of these special conditions is July 30, 2012. We must receive your comments by September 27, 2012.

14 CFR Part 27

Summary

These special conditions are issued for the Eurocopter France Model EC130T2 helicopter. This model helicopter will have the novel or unusual design feature of a 30-minute power rating, generally intended to be used for hovering at increased power for search and rescue missions. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards.

2012-02-01; vol. 77 # 21 - Wednesday, February 1, 2012

77 FR 4890 - Damage Tolerance and Fatigue Evaluation for Composite Rotorcraft Structures, and Damage Tolerance and Fatigue Evaluation for Metallic Structures; Correction

GPO FDSys XML | Text

Additional Documents

type	regulations.gov
FR Doc.	2012-2170
RIN	2120-AJ52
Docket No.	FAA-2009-0660
Amdt. Nos.	27-47A, 29-54A
and Docket No.	FAA-2009-0413
Amdt. No.	29-55A

DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration

Final rule; correction.

This correction is effective February 1, 2012. The “Composite Rotorcraft Structures” final rule becomes effective January 30, 2012. The “Metallic Structures” final rule becomes effective January 31, 2012.

14 CFR Parts 27 and 29

Summary

The FAA is correcting two final rules, “Damage Tolerance and Fatigue Evaluation for Composite Rotorcraft Structures” (76 FR 74655), published December 1, 2011, and “Damage Tolerance and Fatigue Evaluation for Metallic Structures” (76 FR 75435), published December 2, 2011. In the “Composite Rotorcraft Structures” rule, the FAA amended its regulations to require evaluation of fatigue and residual static strength of composite rotorcraft structures using a damage tolerance evaluation, or a fatigue evaluation if the applicant establishes that a damage tolerance evaluation is impractical. In the “Metallic Structures” rule, the FAA amended its regulations to address advances in structural fatigue substantiation technology for metallic structures to provide an increased level of safety by avoiding or reducing the likelihood of the catastrophic fatigue failure of a metallic structure. This document corrects errors in the preamble of those two documents by adding a statement advising that affected parties do not need to comply with the information collection requirements until the Office of Management and Budget (OMB) approves the collections.

This is a list of United States Code sections, Statutes at Large, Public Laws, and Presidential Documents, which provide rulemaking authority for this CFR Part.

This list is taken from the Parallel Table of Authorities and Rules provided by GPO [Government Printing Office].

It is not guaranteed to be accurate or up-to-date, though we do refresh the database weekly. More limitations on accuracy are described at the GPO site.

United States Code

USC : Title 49 - TRANSPORTATION

§ 106 - Federal Aviation Administration

§ 40113 - Administrative

§ 44701 - General requirements

§ 44702 - Issuance of certificates

§ 44704 - Type certificates, production certificates, airworthiness certificates, and design organization certificates

Title 14 published on 2012-01-01

The following are ALL rules, proposed rules, and notices (chronologically) published in the Federal Register relating to 14 CFR 27 after this date.

2013-02-22; vol. 78 # 36 - Friday, February 22, 2013

78 FR 12254 - Interest in Restructure of Rotorcraft Airworthiness Standards

GPO FDSys XML | Text

Additional Documents

type	regulations.gov
FR Doc.	2013-03709
RIN

DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration

Request for comments.

Send your comments to reach us on or before May 23, 2013.

14 CFR Parts 27 and 29

Summary

The Federal Aviation Administration (FAA) is requesting comments and information on the public's interest in restructuring the rotorcraft airworthiness standards of normal category rotorcraft and transport category rotorcraft. Specifically, the agency is seeking comments on whether to change the existing applicability standards for maximum weight and number of passenger seats for either or both types of rotorcraft, or whether to consider other approaches for determining applicability. The FAA is soliciting public input because of some rotorcraft community interest in increasing the 7,000 pound maximum weight limit for the modern normal category rotorcraft and because there may be recommendations for new approaches to make the rotorcraft airworthiness standards more efficient and adaptable to future technology. This action is part of an effort to develop recommendations for possible FAA rulemaking action.

2012-08-22; vol. 77 # 163 - Wednesday, August 22, 2012

77 FR 50576 - Damage Tolerance and Fatigue Evaluation of Composite Rotorcraft Structures; OMB Approval of Information Collection

GPO FDSys XML | Text

Additional Documents

type	regulations.gov
FR Doc.	2012-20685
RIN	2120-AJ52
Docket No.	FAA-2009-0660
Amdt. Nos.	27-47, 29-54

DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration

Final rule; OMB approval of information collection.

The rule published on December 1, 2011, and became effective on January 30, 2012. However, at the time of publication, the new information collection requirements imposed by 14 CFR 27.573 and 29.573 lacked OMB approval. This document announces receipt of OMB's June 28, 2012 approval.

14 CFR Parts 27 and 29

Summary

This document notifies the public of the Office of Management and Budget's (OMB's) approval of the information collection requirement contained in the FAA's final rule, “Damage Tolerance and Fatigue Evaluation of Composite Rotorcraft Structures,” which was published on December 1, 2011.

2012-08-13; vol. 77 # 156 - Monday, August 13, 2012

77 FR 48058 - Special Conditions: Eurocopter France, EC130T2; Use of 30-Minute Power Rating

GPO FDSys XML | Text

Additional Documents

type	regulations.gov
FR Doc.	2012-19444
RIN
Docket No.	FAA-2012-0820
Special Conditions No.	27-028-SC

DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration

Final special conditions; request for comments.

The effective date of these special conditions is July 30, 2012. We must receive your comments by September 27, 2012.

14 CFR Part 27

Summary

These special conditions are issued for the Eurocopter France Model EC130T2 helicopter. This model helicopter will have the novel or unusual design feature of a 30-minute power rating, generally intended to be used for hovering at increased power for search and rescue missions. The applicable airworthiness regulations do not contain adequate or appropriate safety standards for this design feature. These special conditions contain the additional safety standards that the Administrator considers necessary to establish a level of safety equivalent to that established by the existing airworthiness standards.

2012-02-01; vol. 77 # 21 - Wednesday, February 1, 2012

77 FR 4890 - Damage Tolerance and Fatigue Evaluation for Composite Rotorcraft Structures, and Damage Tolerance and Fatigue Evaluation for Metallic Structures; Correction

GPO FDSys XML | Text

Additional Documents

type	regulations.gov
FR Doc.	2012-2170
RIN	2120-AJ52
Docket No.	FAA-2009-0660
Amdt. Nos.	27-47A, 29-54A
and Docket No.	FAA-2009-0413
Amdt. No.	29-55A

DEPARTMENT OF TRANSPORTATION, Federal Aviation Administration

Final rule; correction.

This correction is effective February 1, 2012. The “Composite Rotorcraft Structures” final rule becomes effective January 30, 2012. The “Metallic Structures” final rule becomes effective January 31, 2012.

14 CFR Parts 27 and 29

Summary

The FAA is correcting two final rules, “Damage Tolerance and Fatigue Evaluation for Composite Rotorcraft Structures” (76 FR 74655), published December 1, 2011, and “Damage Tolerance and Fatigue Evaluation for Metallic Structures” (76 FR 75435), published December 2, 2011. In the “Composite Rotorcraft Structures” rule, the FAA amended its regulations to require evaluation of fatigue and residual static strength of composite rotorcraft structures using a damage tolerance evaluation, or a fatigue evaluation if the applicant establishes that a damage tolerance evaluation is impractical. In the “Metallic Structures” rule, the FAA amended its regulations to address advances in structural fatigue substantiation technology for metallic structures to provide an increased level of safety by avoiding or reducing the likelihood of the catastrophic fatigue failure of a metallic structure. This document corrects errors in the preamble of those two documents by adding a statement advising that affected parties do not need to comply with the information collection requirements until the Office of Management and Budget (OMB) approves the collections.

14 CFR 27.613 - Material strength properties and design values.

CFR Toolbox

Law about... Articles from Wex

Find a Lawyer

Get Involved