Skip to Content

Rule

Airworthiness Directives; Agusta S.p.A. Helicopters

Document Details

Information about this document as published in the Federal Register.

Enhanced Content

Relevant information about this document from Regulations.gov provides additional context. This information is not part of the official Federal Register document.

Published Document

This document has been published in the Federal Register. Use the PDF linked in the document sidebar for the official electronic format.

Start Preamble

AGENCY:

Federal Aviation Administration (FAA), Department of Transportation (DOT).

ACTION:

Final rule; request for comments.

SUMMARY:

We are adopting a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model AB412 and AB412EP helicopters with a certain rotor brake pinion installed. This AD requires inspecting the rotor brake pinion for a crack, and replacing it if there is a crack. This AD is prompted by a report of a rotor brake pinion failure. These actions are intended to detect a crack on the rotor brake pinion and prevent failure of the rotor brake pinion, which could lead to detachment of parts inside the transmission and subsequent loss of control of the helicopter.

DATES:

This AD becomes effective July 7, 2014.

We must receive comments on this AD by August 18, 2014.

ADDRESSES:

You may send comments by any of the following methods:

  • Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your comments electronically.
  • Fax: 202-493-2251.
  • Mail: Send comments to the U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590-0001.
  • Hand Delivery: Deliver to the “Mail” address between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

Examining the AD Docket

You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the Docket Operations Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the European Aviation Safety Agency (EASA) AD, any comments received, and other information. The street address for the Docket Operations Office (telephone 800-647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt.

For service information identified in this AD, contact AgustaWestland, Product Support Engineering, Via del Gregge, 100, 21015 Lonate Pozzolo (VA) Italy, ATTN: Maurizio D'Angelo; telephone 39-0331-664757; fax 39-0331-664680; or at http://www.agustawestland.com/​technical-bulletins. You may review the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137.

Start Further Info

FOR FURTHER INFORMATION CONTACT:

Matt Wilbanks, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110; email matt.wilbanks@faa.gov.

End Further Info End Preamble Start Supplemental Information

SUPPLEMENTARY INFORMATION:

Comments Invited

This AD is a final rule that involves requirements affecting flight safety, and we did not provide you with notice and an opportunity to provide your comments prior to it becoming effective. However, we invite you to participate in this rulemaking by submitting written comments, data, or views. We also invite comments relating to the economic, environmental, energy, or federalism impacts that resulted from adopting this AD. The most helpful comments reference a specific portion of the AD, explain the reason for any recommended change, and include supporting data. To ensure the docket does not contain duplicate comments, commenters should send only one copy of written comments, or if comments are filed electronically, commenters should submit them only one time. We will file in the docket all comments that we receive, as well as a report summarizing each substantive public contact with FAA personnel concerning this rulemaking during the comment period. We will consider all the comments we receive and may conduct additional rulemaking based on those comments.

Discussion

This AD is prompted by AD No. 2013-0187, dated August 16, 2013 (AD 2013-0187), issued by EASA, which is the Technical Agent for the Member States of the European Union, to correct an unsafe condition for Agusta Model AB412 and AB412EP helicopters. EASA advises of a report of a cracked pinion, part number (P/N) 412-040-301-101, installed in the rotor brake quill, P/N 412-040-123-103, on an AB412 helicopter. EASA states that the crack was discovered by a magnetic particle inspection during a scheduled overhaul of the rotor brake quill. EASA further states that an investigation revealed the crack was due to residual stress generated during the manufacturing process, and that this condition, if not detected and corrected, could lead to failure of the pinion with detachment of parts inside the transmission that could cause its malfunction or jamming, finally resulting in loss of control of the helicopter. To address this unsafe condition, EASA AD 2013-0187 requires magnetic particle inspecting the rotor brake pinion, and if there is a crack, replacing the rotor brake pinion.

FAA's Determination

These helicopters have been approved by the aviation authority of Italy and are approved for operation in the United States. Pursuant to our bilateral agreement with Italy, EASA, its technical representative, has notified us of the unsafe condition described in the EASA AD. We are issuing this AD because we evaluated all information provided by EASA and determined the unsafe condition exists and is likely to exist or develop on other helicopters of these same type designs.

Related Service Information

Agusta has issued Bollettino Tecnico No. 412-135, Revision A, dated July 29, 2013, which describes procedures for a one-time magnetic particle inspection of the rotor brake pinion, P/N 412-040-Start Printed Page 35036301-101, installed on Model AB412 and AB412EP helicopters.

AD Requirements

This AD requires, within 100 hours time-in-service, magnetic particle inspecting the rotor brake pinion, P/N 412-040-301-101, for a crack. If there is a crack, this AD requires replacing the pinion before further flight.

Differences Between This AD and the EASA AD

The EASA AD does not apply to pinions installed in a rotor brake quill assembly that has been overhauled, while this AD does.

Costs of Compliance

There are no costs of compliance with this AD because there are no helicopters with this type certificate on the U.S. Registry.

FAA's Justification and Determination of the Effective Date

There are no helicopters with this type certificate on the U.S. Registry. Therefore, we believe it is unlikely that we will receive any adverse comments or useful information about this AD from U.S. operators.

Since an unsafe condition exists that requires the immediate adoption of this AD, we determined that notice and opportunity for public comment before issuing this AD are unnecessary because there are none of these products on the U.S. Registry and that good cause exists for making this amendment effective in less than 30 days.

Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. “Subtitle VII: Aviation Programs,” describes in more detail the scope of the Agency's authority.

We are issuing this rulemaking under the authority described in “Subtitle VII, Part A, Subpart III, Section 44701: General requirements.” Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action.

Regulatory Findings

We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government.

For the reasons discussed, I certify that this AD:

1. Is not a “significant regulatory action” under Executive Order 12866;

2. Is not a “significant rule” under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);

3. Will not affect intrastate aviation in Alaska to the extent that it justifies making a regulatory distinction; and

4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act.

Start List of Subjects

List of Subjects in 14 CFR Part 39

  • Air transportation
  • Aircraft
  • Aviation safety
  • Incorporation by reference
  • Safety
End List of Subjects

Adoption of the Amendment

Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows:

Start Part

PART 39—AIRWORTHINESS DIRECTIVES

End Part Start Amendment Part

1. The authority citation for part 39 continues to read as follows:

End Amendment Part Start Authority

Authority: 49 U.S.C. 106(g), 40113, 44701.

End Authority
[Amended]
Start Amendment Part

2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD):

End Amendment Part

2014-12-07 Agusta S.p.A.: Amendment 39-17868; Docket No. FAA-2014-0378; Directorate Identifier 2013-SW-050-AD.

(a) Applicability

This AD applies to Agusta S.p.A. (Agusta) Model AB412 and AB412EP helicopters with a rotor brake pinion, part number 412-040-301-101, installed, certificated in any category.

(b) Unsafe Condition

This AD defines the unsafe condition as a crack in a rotor brake pinion. This condition could result in failure of a rotor brake pinion, detachment of parts inside the transmission causing a malfunction or jamming, and subsequent loss of control of the helicopter.

(c) Effective Date

This AD becomes effective July 7, 2014.

(d) Compliance

You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time.

(e) Required Actions

Within 100 hours time-in-service, magnetic particle inspect each rotor brake pinion for a crack. If there is a crack, before further flight, replace the rotor brake pinion.

(f) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Matt Wilbanks, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110; email matt.wilbanks@faa.gov.

(2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office, before operating any aircraft complying with this AD through an AMOC.

(g) Additional Information

(1) AgustaWestland Bollettino Tecnico No. 412-135, Revision A, dated July 29, 2013, which is not incorporated by reference, contains additional information about the subject of this AD. For service information identified in this AD, contact AgustaWestland, Product Support Engineering, Via del Gregge, 100, 21015 Lonate Pozzolo (VA) Italy, ATTN: Maurizio D'Angelo; telephone 39-0331-664757; fax 39-0331-664680; or at http://www.agustawestland.com/​technical-bulletins. You may review a copy of the service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth Texas 76137.

(2) The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2013-0187, dated August 16, 2013. You may view the EASA AD on the Internet at http://www.regulations.gov in Docket No. FAA-2014-0378.

(h) Subject

Joint Aircraft Service Component (JASC) Code: 6321: Main Rotor Brake.

Start Signature

Issued in Fort Worth, Texas, on June 6, 2014.

Lance T. Gant,

Acting Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service.

End Signature End Supplemental Information

[FR Doc. 2014-13838 Filed 6-18-14; 8:45 am]

BILLING CODE 4910-13-P