Airworthiness Directives; Turbomeca S.A. Arrius 2F Turboshaft Engines, 37793-37795 [E8-14311]

Download as PDF Federal Register / Vol. 73, No. 128 / Wednesday, July 2, 2008 / Rules and Regulations Applicability (c) This AD applies to Hartzell Propeller Inc. left-hand rotating ( )HC–( )(2,3)Y(K,R)– 2 two- and three-bladed, aluminum hub, ‘‘compact’’ series propellers, with hubs having a non-suffix serial number (SN), and lubrication holes located on the shoulder of the hub blade socket. These propellers are installed on Lycoming Engines LIO–360 series and LO–360 series reciprocating engines, installed on Piper Aircraft, Inc. Seneca PA–34–200 and Seminole PA–44– 180, and Hawker Beechcraft Corporation Model 76 Duchess, airplanes. (d) The parentheses appearing in the propeller model number indicates the presence or absence of an additional letter(s) that varies the basic propeller model. This AD still applies regardless of whether these letters are present or absent in the propeller model designation. Unsafe Condition (e) This AD results from four reports of propeller hub cracks, including two in-flight blade separation events. We are issuing this AD to prevent failure of the propeller hub, which could result in blade separation and loss of control of the airplane. Compliance (f) You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done. Initial Eddy Current Inspection (ECI) (g) Within 50 hours time-in-service (TIS) or 12 months after the effective date of this AD, whichever occurs first, perform an initial ECI of the area around the lubrication holes of the hub blade sockets. (h) Use paragraphs 3.A. through 3.A.(3)(d) of Hartzell Propeller Inc. Alert Service Bulletin (ASB) No. HC–ASB–61–297, Revision 1, dated November 14, 2007, to do the initial ECI. (i) If any cracks are found, remove the propeller hub from service before further flight. (j) If no cracks are found, mark the propeller using paragraph 3.A.(5)(a) of the Accomplishment Instructions of Hartzell Propeller Inc., ASB No. HC–ASB–61–297, Revision 1, dated November 14, 2007, to indicate compliance with this ASB. mstockstill on PROD1PC66 with RULES Repetitive ECIs (k) At repetitive intervals not to exceed 50 hours TIS or 12 months from the previous ECI, whichever occurs first, perform ECIs of the area around the lubrication holes of the hub blade sockets. (l) Use paragraphs 3.A. through 3.A.(3)(d) of Hartzell Propeller Inc. ASB No. HC–ASB– 61–297, Revision 1, dated November 14, 2007, to do the repetitive ECIs. (m) If any cracks are found, remove the propeller hub from service before further flight. Optional Terminating Action (n) As optional terminating action to the repetitive ECIs required by this AD, replace the non-suffix SN propeller hub with a propeller hub identified by an ‘‘A’’ or ‘‘B’’ suffix letter in the propeller hub SN. VerDate Aug<31>2005 17:12 Jul 01, 2008 Jkt 214001 37793 (o) Replacement propeller hub part numbers can be found in paragraph 2.A., Material Information, of Hartzell Propeller Inc. ASB No. HC–SB–61–297, Revision 1, dated November 14, 2007. DEPARTMENT OF TRANSPORTATION Prohibition of Propeller Hub Reuse [Docket No. FAA–2007–28053; Directorate Identifier 2007–NE–18–AD; Amendment 39– 15590; AD 2008–13–27] (p) After the effective date of this AD, propeller hubs that have a non-suffix SN, or an ‘‘E’’ suffix letter in the SN removed from affected propellers in this AD, are not eligible for installation on any engine in any aircraft. Previous Credit (q) ECIs of the propeller hubs done before the effective date of this AD that use Hartzell Propeller Inc. ASB No. HC–SB–61–297, dated September 17, 2007, comply with the requirements specified in this AD. Alternative Methods of Compliance (r) The Manager, Chicago Aircraft 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. Related Information (s) Contact Tim Smyth, Senior Aerospace Engineer, Chicago Aircraft Certification Office, FAA, Small Airplane Directorate, 2300 East Devon Avenue, Des Plaines, IL 60018–4696; e-mail: timothy.smyth@faa.gov; telephone (847) 294–8110; fax (847) 294– 7132, for more information about this AD. Material Incorporated by Reference (t) You must use Hartzell Propeller Inc. Alert Service Bulletin No. HC–ASB–61–297, Revision 1, dated November 14, 2007, to perform the ECIs required by this AD. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Hartzell Propeller Inc. Technical Publications Department, One Propeller Place, Piqua, OH 45356; telephone (937) 778–4200; fax (937) 778–4391, for a copy of this service information. You may review copies at the FAA, New England Region, 12 New England Executive Park, Burlington, MA; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http://www.archives.gov/federal-register/ cfr/ibr-locations.html. Issued in Burlington, Massachusetts, on June 19, 2008. Diane Cook, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E8–14312 Filed 7–1–08; 8:45 am] BILLING CODE 4910–13–P PO 00000 Federal Aviation Administration 14 CFR Part 39 RIN 2120–AA64 Airworthiness Directives; Turbomeca S.A. Arrius 2F Turboshaft Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: This AD is issued following a case of noncommanded in-flight engine shut-down which occurred on an ARRIUS 2F turboshaft engine, following the seizing of the gas generator. The result may be an emergency autorotation landing or, at worst, an accident. Investigations of this event have revealed that the seizing of the gas generator was caused by the fracture of the separator cage of the gas generator front bearing, due to high-cycle fatigue cracks initiated in the lubrication slots of the separator cage. We are issuing this AD to prevent uncommanded shutdown of the engine, which could lead to an accident. DATES: This AD becomes effective August 6, 2008. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of August 6, 2008. ADDRESSES: The Docket Operations office is located at Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. FOR FURTHER INFORMATION CONTACT: James Lawrence, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: james.lawrence@faa.gov; telephone (781) 238–7176; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR Frm 00019 Fmt 4700 Sfmt 4700 E:\FR\FM\02JYR1.SGM 02JYR1 37794 Federal Register / Vol. 73, No. 128 / Wednesday, July 2, 2008 / Rules and Regulations part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on August 28, 2007 (72 FR 49236). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states that: This AD is issued following a case of noncommanded in-flight engine shut-down which occurred on an Arrius 2F turboshaft engine, following the seizing of the gas generator. The result may be an emergency autorotation landing, or, at worst, an accident. Investigations of this event have revealed that the seizing of the gas generator was caused by the fracture of the separator cage of the gas generator front bearing, due to high-cycle fatigue cracks initiated in the lubrication slots of the separator cage. Modification Tf 12 introduces a new gas generator front bearing without lubrication slots on the separator cage. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. Change to the Compliance End Date We have changed the compliance time from ‘‘at the next shop visit after the effective date of the AD, but no later than April 30, 2008’’ to ‘‘at the next shop visit after the effective date of this AD, but no later than 30 days after the effective date of this AD’’ to allow the operators more time to complete the requirements of this AD. Conclusion We reviewed the available data and determined that air safety and the public interest require adopting the AD with the changes described previously. We determined that these changes will not increase the economic burden on any operator or increase the scope of the AD. mstockstill on PROD1PC66 with RULES Differences Between This AD and the MCAI or Service Information The Mandatory Continuing Airworthiness Information (MCAI) and service information require the operators to comply with the requirements at the next shop visit after the effective date of the AD, but no later than April 30, 2008. We require compliance at the next shop visit after the effective date of this AD, but no later than 30 days after the effective date of this AD. Costs of Compliance We estimate that this AD will affect 61 engines of U.S. registry. We also estimate that it will take about 10 work- VerDate Aug<31>2005 17:12 Jul 01, 2008 Jkt 214001 hours per engine to comply with this AD. The average labor rate is $80 per work-hour. Required parts will cost about $111,440. Based on these figures, we estimate the cost of this AD to the U.S. operators to be $6,846,640. Our cost estimate is exclusive of possible warranty coverage. 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 above, I certify this AD: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the 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 regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. 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 regulatory evaluation, any comments received, and PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 other information. The street address for the Docket Operations office (telephone (800) 647–5527) is provided in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: I 2008–13–27 Turbomeca S.A.: Amendment 39–15590. Docket No. FAA–2007–28053; Directorate Identifier 2007–NE–18–AD. Effective Date (a) This airworthiness directive (AD) becomes effective August 6, 2008. Affected ADs (b) None. Applicability (c) This AD applies to Turbomeca S.A. Arrius 2F turboshaft engines that have not incorporated Turbomeca Modification Tf 12A. These engines are installed on, but not limited to, Eurocopter EC120B helicopters. Reason (d) European Aviation Safety Agency (EASA) AD No. 2007–0057, dated March 1, 2007, states: This AD is issued following a case of noncommanded in-flight engine shut-down which occurred on an Arrius 2F turboshaft engine, following the seizing of the gas generator. The result may be an emergency autorotation landing, or, at worst, an accident. Investigations of this event have revealed that the seizing of the gas generator was caused by the fracture of the separator cage of the gas generator front bearing, due to high-cycle fatigue cracks initiated in the lubrication slots of the separator cage. Modification Tf12 introduces a new gas generator front bearing without lubrication slots on the separator cage. We are issuing this AD to prevent uncommanded shutdown of the engine, which could lead to an accident. Actions and Compliance (e) Unless already done, do the following actions. E:\FR\FM\02JYR1.SGM 02JYR1 Federal Register / Vol. 73, No. 128 / Wednesday, July 2, 2008 / Rules and Regulations (1) At the next engine shop visit after the effective date of this AD, but no later than 30 days after the effective date of this AD, replace the engine module 02 with a module that incorporates Turbomeca Modification Tf 12A. Turbomeca Modification Tf 12A installs into the engine module 02 a new gas generator front bearing without lubrication slots on the separator cage. (2) Use the Instructions to be Incorporated section of Turbomeca Mandatory Service Bulletin No. 319 72 4012, Update No. 1, dated September 19, 2006, to do the actions in paragraph (e)(1) of this AD. DEPARTMENT OF TRANSPORTATION FAA AD Differences AGENCY: (f) The Mandatory Continuing Airworthiness Information (MCAI) and service information require the operators to comply with the requirements at the next shop visit after the effective date of the AD, but no later than April 30, 2008. We require compliance at the next shop visit after the effective date of this AD, but no later than 30 days after the effective date of this AD. Other FAA AD Provisions (g) Alternative Methods of Compliance (AMOCs): The Manager, Engine Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Related Information (h) Refer to EASA AD 2007–0057, dated March 1, 2007, for related information. (i) Contact James Lawrence, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: james.lawrence@faa.gov; telephone (781) 238–7176; fax (781) 238– 7199, for more information about this AD. Material Incorporated by Reference mstockstill on PROD1PC66 with RULES (j) You must use Turbomeca Mandatory Service Bulletin No. 319 72 4012, Update No. 1, dated September 19, 2006, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Turbomeca, 40220 Tarnos, France; telephone (33) 05 59 74 40 00, fax (33) 05 59 74 45 15. (3) You may review copies at the FAA, New England Region, 12 New England Executive Park, Burlington, MA; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Burlington, Massachusetts, on June 18, 2008. Diane Cook, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E8–14311 Filed 7–1–08; 8:45 am] BILLING CODE 4910–13–P VerDate Aug<31>2005 17:12 Jul 01, 2008 Jkt 214001 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–0297; Directorate Identifier 2007–NM–330–AD; Amendment 39–15586; AD 2008–13–23] RIN 2120–AA64 Airworthiness Directives; Dornier Model 328–100 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. SUMMARY: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: During maintenance water has been found in the elevator [assembly]. The unsafe condition is water or ice accumulating in the elevator assembly, which could result in corrosion and consequent reduced structural integrity of the flight control surface, or an unbalanced flight control surface. These conditions could result in reduced controllability of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products. This AD becomes effective August 6, 2008. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of August 6, 2008. ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2125; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: DATES: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 37795 part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on March 13, 2008 (73 FR 13503). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: During maintenance water has been found in the elevator [assembly]. The unsafe condition is water or ice accumulating in the elevator assembly, which could result in corrosion and consequent reduced structural integrity of the flight control surface, or an unbalanced flight control surface. These conditions could result in reduced controllability of the airplane. You may obtain further information by examining the MCAI in the AD docket. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. Conclusion We reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. Differences Between This AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information. We might also have required different actions in this AD from those in the MCAI in order to follow our FAA policies. Any such differences are highlighted in a NOTE within the AD. Costs of Compliance We estimate that this AD will affect about 12 products of U.S. registry. We also estimate that it will take about 2 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $80 per work-hour. Required parts will cost about $100 per product. Where the service information lists required parts costs that are covered under warranty, we have assumed that there will be no charge for these parts. As we do not control warranty coverage for affected parties, some parties may incur costs higher than estimated here. Based on these E:\FR\FM\02JYR1.SGM 02JYR1

Agencies

[Federal Register Volume 73, Number 128 (Wednesday, July 2, 2008)]
[Rules and Regulations]
[Pages 37793-37795]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-14311]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28053; Directorate Identifier 2007-NE-18-AD; 
Amendment 39-15590; AD 2008-13-27]
RIN 2120-AA64


Airworthiness Directives; Turbomeca S.A. Arrius 2F Turboshaft 
Engines

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

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for the 
products listed above. This AD results from mandatory continuing 
airworthiness information (MCAI) issued by an aviation authority of 
another country to identify and correct an unsafe condition on an 
aviation product. The MCAI describes the unsafe condition as:

    This AD is issued following a case of non-commanded in-flight 
engine shut-down which occurred on an ARRIUS 2F turboshaft engine, 
following the seizing of the gas generator. The result may be an 
emergency autorotation landing or, at worst, an accident.
    Investigations of this event have revealed that the seizing of 
the gas generator was caused by the fracture of the separator cage 
of the gas generator front bearing, due to high-cycle fatigue cracks 
initiated in the lubrication slots of the separator cage.

We are issuing this AD to prevent uncommanded shutdown of the engine, 
which could lead to an accident.

DATES: This AD becomes effective August 6, 2008. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in this AD as of August 6, 2008.

ADDRESSES: The Docket Operations office is located at Docket Management 
Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, 
SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-
0001.

FOR FURTHER INFORMATION CONTACT: James Lawrence, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; e-mail: 
james.lawrence@faa.gov; telephone (781) 238-7176; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR

[[Page 37794]]

part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on August 28, 2007 (72 
FR 49236). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states that:

    This AD is issued following a case of non-commanded in-flight 
engine shut-down which occurred on an Arrius 2F turboshaft engine, 
following the seizing of the gas generator. The result may be an 
emergency autorotation landing, or, at worst, an accident.
    Investigations of this event have revealed that the seizing of 
the gas generator was caused by the fracture of the separator cage 
of the gas generator front bearing, due to high-cycle fatigue cracks 
initiated in the lubrication slots of the separator cage.
    Modification Tf 12 introduces a new gas generator front bearing 
without lubrication slots on the separator cage.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM or on the determination of 
the cost to the public.

Change to the Compliance End Date

    We have changed the compliance time from ``at the next shop visit 
after the effective date of the AD, but no later than April 30, 2008'' 
to ``at the next shop visit after the effective date of this AD, but no 
later than 30 days after the effective date of this AD'' to allow the 
operators more time to complete the requirements of this AD.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting the AD with the changes described 
previously. We determined that these changes will not increase the 
economic burden on any operator or increase the scope of the AD.

Differences Between This AD and the MCAI or Service Information

    The Mandatory Continuing Airworthiness Information (MCAI) and 
service information require the operators to comply with the 
requirements at the next shop visit after the effective date of the AD, 
but no later than April 30, 2008. We require compliance at the next 
shop visit after the effective date of this AD, but no later than 30 
days after the effective date of this AD.

Costs of Compliance

    We estimate that this AD will affect 61 engines of U.S. registry. 
We also estimate that it will take about 10 work-hours per engine to 
comply with this AD. The average labor rate is $80 per work-hour. 
Required parts will cost about $111,440. Based on these figures, we 
estimate the cost of this AD to the U.S. operators to be $6,846,640. 
Our cost estimate is exclusive of possible warranty coverage.

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 above, I certify this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the 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 regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket.

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 regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Operations office (telephone (800) 647-5527) is provided in 
the ADDRESSES section. Comments will be available in the AD docket 
shortly after receipt.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA 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 AD:

2008-13-27 Turbomeca S.A.: Amendment 39-15590. Docket No. FAA-2007-
28053; Directorate Identifier 2007-NE-18-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective August 
6, 2008.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Turbomeca S.A. Arrius 2F turboshaft 
engines that have not incorporated Turbomeca Modification Tf 12A. 
These engines are installed on, but not limited to, Eurocopter 
EC120B helicopters.

Reason

    (d) European Aviation Safety Agency (EASA) AD No. 2007-0057, 
dated March 1, 2007, states:
    This AD is issued following a case of non-commanded in-flight 
engine shut-down which occurred on an Arrius 2F turboshaft engine, 
following the seizing of the gas generator. The result may be an 
emergency autorotation landing, or, at worst, an accident.
    Investigations of this event have revealed that the seizing of 
the gas generator was caused by the fracture of the separator cage 
of the gas generator front bearing, due to high-cycle fatigue cracks 
initiated in the lubrication slots of the separator cage.
    Modification Tf12 introduces a new gas generator front bearing 
without lubrication slots on the separator cage.

We are issuing this AD to prevent uncommanded shutdown of the 
engine, which could lead to an accident.

Actions and Compliance

    (e) Unless already done, do the following actions.

[[Page 37795]]

    (1) At the next engine shop visit after the effective date of 
this AD, but no later than 30 days after the effective date of this 
AD, replace the engine module 02 with a module that incorporates 
Turbomeca Modification Tf 12A. Turbomeca Modification Tf 12A 
installs into the engine module 02 a new gas generator front bearing 
without lubrication slots on the separator cage.
    (2) Use the Instructions to be Incorporated section of Turbomeca 
Mandatory Service Bulletin No. 319 72 4012, Update No. 1, dated 
September 19, 2006, to do the actions in paragraph (e)(1) of this 
AD.

FAA AD Differences

    (f) The Mandatory Continuing Airworthiness Information (MCAI) 
and service information require the operators to comply with the 
requirements at the next shop visit after the effective date of the 
AD, but no later than April 30, 2008. We require compliance at the 
next shop visit after the effective date of this AD, but no later 
than 30 days after the effective date of this AD.

Other FAA AD Provisions

    (g) Alternative Methods of Compliance (AMOCs): The Manager, 
Engine Certification Office, FAA, has the authority to approve AMOCs 
for this AD, if requested using the procedures found in 14 CFR 
39.19.

Related Information

    (h) Refer to EASA AD 2007-0057, dated March 1, 2007, for related 
information.
    (i) Contact James Lawrence, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
james.lawrence@faa.gov; telephone (781) 238-7176; fax (781) 238-
7199, for more information about this AD.

Material Incorporated by Reference

    (j) You must use Turbomeca Mandatory Service Bulletin No. 319 72 
4012, Update No. 1, dated September 19, 2006, to do the actions 
required by this AD, unless the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact 
Turbomeca, 40220 Tarnos, France; telephone (33) 05 59 74 40 00, fax 
(33) 05 59 74 45 15.
    (3) You may review copies at the FAA, New England Region, 12 New 
England Executive Park, Burlington, MA; or at the National Archives 
and Records Administration (NARA). For information on the 
availability of this material at NARA, call (202) 741-6030, or go 
to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Burlington, Massachusetts, on June 18, 2008.
Diane Cook,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E8-14311 Filed 7-1-08; 8:45 am]
BILLING CODE 4910-13-P