AD 2003-19-06

[Federal Register Volume 68, Number 180 (Wednesday, September 17, 2003)]
[Rules and Regulations]
[Pages 54327-54328]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 03-23673]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NE-05-AD; Amendment 39-13309; AD 2003-19-06]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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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 2\1/2\ 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.

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.

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 2\1/2\ 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

[[Page 54328]]

comments 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the Federal Aviation Administration amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

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 2\1/2\ 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.

    Issued in Burlington, Massachusetts, on September 11, 2003.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 03-23673 Filed 9-16-03; 8:45 am]
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