Skip to Content

Rule

Airworthiness Directives; Turbomeca S.A. Arrius 2 B1, 2 B1A, 2 B1A 1, and 2 K1 Turboshaft Engines

Document Details

Information about this document as published in the Federal Register.

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), DOT.

ACTION:

Final rule.

SUMMARY:

The FAA is adopting a new airworthiness directive (AD) for Turbomeca S.A. Arrius 2 B1, 2 B1A, 2 B1A 1, and 2 K1 turboshaft engines. This AD requires replacement of the gas generator high pressure (HP) turbine disk before further flight after the engine has accumulated 5 minutes of operating time at the 21/2 minute one engine inoperative (OEI) power rating. This amendment is prompted by a failure of an HP turbine blade during accelerated aging simulation tests performed by the manufacturer on an Arrius 2 B1A engine. We are issuing this AD to prevent engine failure of the only operating engine while experiencing an OEI condition.

DATES:

This AD becomes effective October 22, 2003.

ADDRESSES:

You may get the service information identified in this AD from Turbomeca S.A., 64511 Bordes Cedex, France; telephone 33 05 59 64 40 00, fax 33 05 59 64 60 80.

You may examine the AD docket at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA. You may examine the service information, at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA.

Start Further Info

FOR FURTHER INFORMATION CONTACT:

Antonio Cancelliere, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803-5299; telephone (781) 238-7751; fax (781) 238-7199.

End Further Info End Preamble Start Supplemental Information

SUPPLEMENTARY INFORMATION:

The FAA proposed to amend 14 CFR part 39 with a proposed AD. The proposed AD applies to Turbomeca S.A. Arrius 2 B1, 2 B1A, 2 B1A 1, and 2 K1 turboshaft engines. We published the proposed AD in the Federal Register on May 20, 2003 (68 FR 27492). That action proposed to require replacement of the gas generator high pressure (HP) turbine disk before further flight after the engine has accumulated 5 minutes of operating time at the 21/2 minute one engine inoperative (OEI) power rating.

Comments

We provided the public the opportunity to participate in the development of this AD. We received no Start Printed Page 54328comments on the proposal or on the determination of the cost to the public.

Conclusion

We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed.

Changes to 14 CFR Part 39—Effect on the AD

On July 10, 2002, the FAA published a new version of 14 CFR part 39 (67 FR 47997, July 22, 2002), which governs the FAA's AD system. That regulation now includes material that relates to altered products, special flight permits, and alternative methods of compliance. The material previously was included in each individual AD. Since the material is included in 14 CFR part 39, we will not include it in future AD actions.

Regulatory Findings

We have 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 above, 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); and

(3) 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.

We prepared a summary of the costs to comply with this AD and placed it in the AD Docket. You may get a copy of this summary by sending a request to us at the address listed under ADDRESSES. Include “AD Docket No. 2003-NE-05-AD” in your request.

Start List of Subjects

List of Subjects in 14 CFR Part 39

End List of Subjects

Adoption of the Amendment

Start Amendment Part

Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation Administration amends

End Amendment Part 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

2003-19-06 Turbomeca S.A.: Amendment 39-13309. Docket No. 2003-NE-05-AD.

Effective Date

(a) This AD becomes effective October 22, 2003.

Affected ADs

(b) None.

Applicability

(c) This AD applies to Turbomeca S.A. Arrius 2 B1, 2 B1A, 2 B1A 1, and 2 K1 turboshaft engines. These engines are installed on, but not limited to, Eurocopter Deutschland GmbH model EC135 T1 and Agusta S.p.A. model A109 helicopters.

Unsafe Condition

(d) This AD is prompted by a failure of an HP turbine blade during accelerated aging simulation tests performed by the manufacturer on an Arrius 2 B1A engine. The actions specified in this AD are intended to prevent engine failure of the only operating engine while at one engine inoperative (OEI) condition.

Compliance

(e) You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done.

(f) After the effective date of this AD, replace the gas generator HP turbine disk before further flight after the engine has accumulated 5 minutes operating time at the 21/2 minute OEI power rating.

Alternative Methods of Compliance

(g) The Manager, Engine Certification Office, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19.

Material Incorporated by Reference

(h) None.

Related Information

(i) The subject of this AD is addressed in DGAC airworthiness directive 2003-098(A), dated March 5, 2003, and Turbomeca S.A. Alert Service Letters No. 2174/02/ARRIUS2B1/19 and No. 2175/02/ARRIUS2K1/3, both dated July 30, 2002.

Start Signature

Issued in Burlington, Massachusetts, on September 11, 2003.

Francis A. Favara,

Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service.

End Signature End Supplemental Information

[FR Doc. 03-23673 Filed 9-16-03; 8:45 am]

BILLING CODE 4910-13-P