Airworthiness Directives; Turbomeca S.A. Arriel 2B, 2B1, and 2B1A Turboshaft Engines, 74661-74663 [E8-29102]

Download as PDF Federal Register / Vol. 73, No. 237 / Tuesday, December 9, 2008 / Proposed Rules of information to the public under guidelines established by each agency pursuant to general guidelines issued by OMB. OMB’s guidelines were published at 67 FR 8452 (Feb. 22, 2002), and DOE’s guidelines were published at 67 FR 62446 (Oct. 7, 2002). DOE has reviewed today’s proposed rule under the OMB and DOE guidelines, and has concluded that it is consistent with applicable policies in those guidelines. IV. Approval of the Office of the Secretary The Secretary of Energy has approved publication of this proposed rule. List of Subjects in 10 CFR Part 1004 Electric power, Electric utilities, Energy, Freedom of Information, Reporting and recordkeeping requirements. Issued in Washington, DC. Ingrid Kolb, Director, Office of Management. For the reasons set forth in the preamble, the Department of Energy proposes to amend Part 1004 of Title 10 of the Code of Federal Regulations as set forth below. PART 1004—FREEDOM OF INFORMATION 1. The authority citation for part 1004 continues to read as follows: Authority: 5 U.S.C. 552. § 1004.1 [Amended] 2. Section 1004.1 is amended by removing the last sentence. § 1004.9 [Amended] 3. Section 1004.9(a)(4) is amended by removing ‘‘five’’ and ‘‘ten’’ in the first sentence and adding in both places ‘‘twenty’’. [FR Doc. E8–28940 Filed 12–8–08; 8:45 am] BILLING CODE 6450–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–28077; Directorate Identifier 2007–NE–20–AD] pwalker on PROD1PC71 with PROPOSALS RIN 2120–AA64 Airworthiness Directives; Turbomeca S.A. Arriel 2B, 2B1, and 2B1A Turboshaft Engines AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). VerDate Aug<31>2005 16:59 Dec 08, 2008 Jkt 217001 SUMMARY: We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed AD results from mandatory continuing airworthiness information (MCAI) provided by the aviation authority of France to identify and correct an unsafe condition on an aviation product. The MCAI states the following: Several cases of Gas Generator Turbine (HP Turbine) blade rearward displacement have been detected during borescope inspection or in repair centre following engine disassembly. Two of them resulted in blade rubs between the rear face of the fir-tree roots and the rear bearing support cover. High HP blade rearward displacement can potentially result in blade release due to fatigue of the blade, which would cause an uncommanded in-flight engine shutdown. We are proposing this AD to prevent an uncommanded in-flight engine shutdown which could result in an emergency autorotation landing or, at worst, an accident. DATES: We must receive comments on this proposed AD by January 8, 2009. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. • Fax: (202) 493–2251. Examining the AD Docket You may examine the AD docket on the Internet at https:// 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is the same as the Mail address provided in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Christopher Spinney, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: christopher.spinney@faa.gov; telephone (781) 238–7175; fax (781) 238–7199. PO 00000 Frm 00030 Fmt 4702 Sfmt 4702 74661 SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2007–28077; Directorate Identifier 2007–NE–27–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD. Using the search function of the Web site, anyone can find and read the comments in any of our dockets, including, if provided, the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78). Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2007–0109, dated April 19, 2007 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The EASA AD states: Several cases of Gas Generator Turbine (HP Turbine) blade rearward displacement have been detected during borescope inspection or in repair centre following engine disassembly. Two of them resulted in blade rubs between the rear face of the fir-tree roots and the rear bearing support cover. High HP blade rearward displacement can potentially result in blade release due to fatigue of the blade, which would cause an uncommanded in-flight engine shutdown. The evaluation of this condition has prompted to require a periodic borescope inspection in order to detect HP blade rearward displacement. Additionally, in case displacement is found above the specified limit, removal of Module 03 is required. You may obtain further information by examining the EASA AD in the AD docket. Relevant Service Information Turbomeca S.A. has issued Mandatory Service Bulletin No. 292 72 E:\FR\FM\09DEP1.SGM 09DEP1 74662 Federal Register / Vol. 73, No. 237 / Tuesday, December 9, 2008 / Proposed Rules 2825, Original Issue, dated April 5, 2007. The actions described in this service information are intended to correct the unsafe condition identified in the EASA AD. FAA’s Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of France, and is approved for operation in the United States. Pursuant to our bilateral agreement with France, they have notified us of the unsafe condition described in the EASA AD and service information referenced above. We are proposing 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 products of the same type design. This proposed AD would require inspecting for HP blade rearward displacement. Costs of Compliance We estimate that this proposed AD would affect about 248 engines on helicopters of U.S. registry. We also estimate that it would take about 2 work-hours per engine to perform the proposed actions and that the average labor rate is $80 per work-hour. Based on these figures, we estimate the total cost of the proposed AD to U.S. operators to be $39,680. Our cost estimate is exclusive of possible warranty coverage. PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: pwalker on PROD1PC71 with PROPOSALS Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on 16:59 Dec 08, 2008 Jkt 217001 List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: 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. VerDate Aug<31>2005 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 proposed regulation: 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 proposed AD and placed it in the AD docket. Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: Turbomeca S.A.: Docket No. FAA–2007– 28077; Directorate Identifier 2007–NE– 20–AD. Comments Due Date (a) We must receive comments by January 8, 2009. Affected ADs (b) None. Applicability (c) This AD applies to Turbomeca S.A. Arriel 2B, 2B1, and 2B1A turboshaft engines. These engines are installed on, but not limited to, Eurocopter AS 350 B3 and EC 130 B4 helicopters. Reason (d) Several cases of Gas Generator Turbine (HP Turbine) blade rearward displacement have been detected during borescope inspection or in repair centre following engine disassembly. Two of them resulted in blade rubs between the rear face of the firtree roots and the rear bearing support cover. High HP blade rearward displacement can potentially result in blade release due to fatigue of the blade, which would cause an uncommanded in-flight engine shutdown. PO 00000 Frm 00031 Fmt 4702 Sfmt 4702 We are issuing this AD to prevent an uncommanded in-flight engine shutdown which could result in an emergency autorotation landing or, at worst, an accident. Actions and Compliance (e) Unless already done, do the following actions: Initial Inspection (1) Perform an initial HP turbine borescope inspection according to Turbomeca S.A. Mandatory Service Bulletin (MSB) No. 292 72 2825, dated April 5, 2007 as follows: (i) For engines with fewer than 500 hours and 450 cycles since new or since the last HP turbine borescope inspection, inspect before reaching 600 hours or 500 cycles whichever occurs first. Replace HP turbine modules with rearward turbine blade displacement greater than 0.5 mm. (ii) For the remaining engines, inspect within the next 100 hours. Replace HP turbine modules with rearward turbine blade displacement greater than 0.5 mm. Repetitive Inspections (2) Perform repetitive HP turbine borescope inspections according to Turbomeca S.A. MSB No. 292 72 2825, dated April 5, 2007: (i) Within 600 hours or 500 cycles from the previous inspection, whichever occurs first, if the rearward displacement of the turbine blades was less than 0.2 mm. Replace HP turbine modules with rearward turbine blade displacement greater than 0.5 mm. (ii) Within 100 hours of the previous inspection if the rearward displacement of the turbine blades was between 0.2 mm and 0.5 mm. Replace HP turbine modules with rearward turbine blade displacement greater than 0.5 mm. (3) After each inspection, the compliance certificate must be sent to Turbomeca S.A. within 7 days, according to § 2.D(1)(c) of Turbomeca S.A. MSB No. 292 72 2825, dated April 5, 2007. FAA AD Differences (f) We modified the drawdown times to be more consistent with the compliance times. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) 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. (2) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act, the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. Related Information (h) Refer to EASA Airworthiness Directive 2007–0109, dated April 19, 2007, and Turbomeca S.A. MSB No. 292 72 2825, dated April 5, 2007, for related information. (i) Contact Christopher Spinney, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA E:\FR\FM\09DEP1.SGM 09DEP1 Federal Register / Vol. 73, No. 237 / Tuesday, December 9, 2008 / Proposed Rules 01803; e-mail: christopher.spinney@faa.gov; telephone (781) 238–7175; fax (781) 238– 7199, for more information about this AD. Issued in Burlington, Massachusetts, on December 2, 2008. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E8–29102 Filed 12–8–08; 8:45 am] BILLING CODE 4910–13–P SOCIAL SECURITY ADMINISTRATION 20 CFR Part 416 [Docket No. SSA 2008–0034] RIN 0960–AG66 Technical Revisions to the Supplemental Security Income (SSI) Regulations on Income and Resources AGENCY: Social Security Administration. ACTION: Notice of proposed rulemaking. pwalker on PROD1PC71 with PROPOSALS SUMMARY: We propose to amend our Supplemental Security Income (SSI) regulations by making technical revisions to our rules on income and resources. Many of these revisions reflect legislative changes found in the Consolidated Appropriations Act of 2001, the Economic Growth and Tax Relief Reconciliation Act of 2001 (EGTRRA), an amendment to the National Flood Insurance Act of 1968, the Energy Employees Occupational Illness Compensation Program Act of 2000, and the Social Security Protection Act of 2004 (SSPA). We further propose to amend the SSI home exclusion rules to extend the home exclusion to individuals who, because of domestic abuse, leave a home that would otherwise be an excludable resource. Finally, we propose to update our ‘‘conditional-payment’’ rule to eliminate the liquid resource requirement as a prerequisite to receiving conditional payments. DATES: To be sure that we consider your comments, we must receive them no later than February 9, 2009. ADDRESSES: You may submit comments by any one of four methods—Internet, facsimile, regular mail, or handdelivery. Commenters should not submit the same comments multiple times or by more than one method. Regardless of which of the following methods you choose, please state that your comments refer to Docket No. SSA 2008–0034 to ensure that we can associate your comments with the correct regulation: 1. Federal eRulemaking portal at https://www.regulations.gov. (This is the VerDate Aug<31>2005 16:59 Dec 08, 2008 Jkt 217001 most expedient method for submitting your comments, and we strongly urge you to use it.) In the ‘‘Search Documents’’ section of the Web page, type ‘‘SSA 2008–0034’’, select ‘‘Go,’’ and then click ‘‘Send a Comment or Submission.’’ The Federal eRulemaking portal issues you a tracking number when you submit a comment. 2. Telefax to (410) 966–2830. 3. Letter to the Commissioner of Social Security, P.O. Box 17703, Baltimore, MD 21235–7703. 4. Deliver your comments to the Office of Regulations, Social Security Administration, 922 Altmeyer Building, 6401 Security Boulevard, Baltimore, Maryland 21235–6401, between 8 a.m. and 4:30 p.m. on regular business days. All comments are posted on the Federal eRulemaking portal, although they may not appear for several days after receipt of the comment. You may also inspect the comments on regular business days by making arrangements with the contact person shown in this preamble. Caution: All comments we receive from members of the public are available for public viewing on the Federal eRulemaking portal at https:// www.regulations.gov. Therefore, you should be careful to include in your comments only information that you wish to make publicly available on the Internet. We strongly urge you not to include any personal information, such as your Social Security number or medical information, in your comments. FOR FURTHER INFORMATION CONTACT: Donna Gonzalez, Social Insurance Specialist, Social Security Administration, Office of Income Security Programs, 252 Altmeyer Building, 6401 Security Boulevard, Baltimore, MD 21235–6401, (410) 965– 7961, for information about this notice. For information on eligibility or filing for benefits, call our national toll-free number, 1–800–772–1213 or TTY 1– 800–325–0778, or visit our Internet site, Social Security Online, at https:// www.socialsecurity.gov. SUPPLEMENTARY INFORMATION: Electronic Version The electronic file of this document is available on the date of publication in the Federal Register at https:// www.gpoaccess.gov/fr/. Background The primary goal of the SSI program is to ensure a minimum level of income to people who are age 65 or older, blind, or disabled, and who have limited income and resources. The law provides that SSI payments can be made only to PO 00000 Frm 00032 Fmt 4702 Sfmt 4702 74663 people who have income and resources below specified amounts. Therefore, an individual’s income and resources are major factors in deciding whether the individual is eligible to receive SSI payments and in computing the amount of those payments. Consolidated Appropriations Act of 2001, Public Law 106–554 This law amended section 1612(a)(1) of the Social Security Act (the Act) (42 U.S.C. 1382a(a)(1)) to change how we treat statutory employees under the SSI program. See Public Law 106–554, app. A, § 519 (Dec. 21, 2000). Statutory employees are certain independent contractors, including agent-drivers or commission-drivers, certain full-time life insurance salespersons, home workers, and traveling or city salespersons. Act at § 210(j)(3) (42 U.S.C. 410(j)(3)). We consider such individuals, by statute, to be employees, rather than self-employed independent contractors, for wage and income purposes. Previously, we treated statutory employees the same as employees for SSI eligibility and payment-amount purposes. For such employees, we considered their wages as their earned income. After this change to the Act, we now count as earned income the net earnings of selfemployed individuals, including statutory employees, thereby allowing them to deduct business expenses before calculating their income. This provision became effective for tax years beginning on or after January 1, 2001. Economic Growth and Tax Relief Reconciliation Act of 2001, Public Law 107–16 (EGTRRA) The EGTRRA excludes the payment of a refundable child tax credit (CTC) from income for purposes of eligibility for public benefits funded in whole or part with Federal funds. Public Law 107–16, § 203, 115 Stat. 49 (June 7, 2001) (referring to Internal Revenue Code § 24, 26 U.S.C. 24). Such a payment is also excluded from resources for these purposes during the month the payment is received and the following month. This change became effective for SSI purposes for taxable years beginning on or after January 1, 2001. Social Security Protection Act of 2004 (SSPA), Public Law 108–203 The SSPA amended the Act to create a uniform 9-month resource exclusion period for certain tax refunds and for any unspent portion of past-due Social Security and SSI payments. Act at § 1613(a)(7) (42 U.S.C. 1382b(a)(7)), as amended by Public Law 108–203, § 431 (Mar. 2, 2004). This amendment E:\FR\FM\09DEP1.SGM 09DEP1

Agencies

[Federal Register Volume 73, Number 237 (Tuesday, December 9, 2008)]
[Proposed Rules]
[Pages 74661-74663]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-29102]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28077; Directorate Identifier 2007-NE-20-AD]
RIN 2120-AA64


Airworthiness Directives; Turbomeca S.A. Arriel 2B, 2B1, and 2B1A 
Turboshaft Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
products listed above. This proposed AD results from mandatory 
continuing airworthiness information (MCAI) provided by the aviation 
authority of France to identify and correct an unsafe condition on an 
aviation product. The MCAI states the following:

    Several cases of Gas Generator Turbine (HP Turbine) blade 
rearward displacement have been detected during borescope inspection 
or in repair centre following engine disassembly. Two of them 
resulted in blade rubs between the rear face of the fir-tree roots 
and the rear bearing support cover. High HP blade rearward 
displacement can potentially result in blade release due to fatigue 
of the blade, which would cause an uncommanded in-flight engine 
shutdown.

We are proposing this AD to prevent an uncommanded in-flight engine 
shutdown which could result in an emergency autorotation landing or, at 
worst, an accident.

DATES: We must receive comments on this proposed AD by January 8, 2009.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 1200 New Jersey Avenue, SE., West Building Ground 
Floor, Room W12-140, Washington, DC 20590-0001.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
     Fax: (202) 493-2251.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://
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 proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Operations office (telephone (800) 647-5527) is 
the same as the Mail address provided in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Christopher Spinney, Aerospace 
Engineer, Engine Certification Office, FAA, Engine & Propeller 
Directorate, 12 New England Executive Park, Burlington, MA 01803; e-
mail: christopher.spinney@faa.gov; telephone (781) 238-7175; fax (781) 
238-7199.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2007-
28077; Directorate Identifier 2007-NE-27-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to https://
www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact 
with FAA personnel concerning this proposed AD. Using the search 
function of the Web site, anyone can find and read the comments in any 
of our dockets, including, if provided, the name of the individual who 
sent the comment (or signed the comment on behalf of an association, 
business, labor union, etc.). You may review the DOT's complete Privacy 
Act Statement in the Federal Register published on April 11, 2000 (65 
FR 19477-78).

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2007-0109, dated April 19, 2007 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The EASA AD states:

    Several cases of Gas Generator Turbine (HP Turbine) blade 
rearward displacement have been detected during borescope inspection 
or in repair centre following engine disassembly. Two of them 
resulted in blade rubs between the rear face of the fir-tree roots 
and the rear bearing support cover.
    High HP blade rearward displacement can potentially result in 
blade release due to fatigue of the blade, which would cause an 
uncommanded in-flight engine shutdown.
    The evaluation of this condition has prompted to require a 
periodic borescope inspection in order to detect HP blade rearward 
displacement. Additionally, in case displacement is found above the 
specified limit, removal of Module 03 is required.

You may obtain further information by examining the EASA AD in the AD 
docket.

Relevant Service Information

    Turbomeca S.A. has issued Mandatory Service Bulletin No. 292 72

[[Page 74662]]

2825, Original Issue, dated April 5, 2007. The actions described in 
this service information are intended to correct the unsafe condition 
identified in the EASA AD.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of France, 
and is approved for operation in the United States. Pursuant to our 
bilateral agreement with France, they have notified us of the unsafe 
condition described in the EASA AD and service information referenced 
above. We are proposing 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 products of the same type design. 
This proposed AD would require inspecting for HP blade rearward 
displacement.

Costs of Compliance

    We estimate that this proposed AD would affect about 248 engines on 
helicopters of U.S. registry. We also estimate that it would take about 
2 work-hours per engine to perform the proposed actions and that the 
average labor rate is $80 per work-hour. Based on these figures, we 
estimate the total cost of the proposed AD to U.S. operators to be 
$39,680. 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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 proposed 
regulation:
    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 proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

    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]

    2. The FAA amends Sec.  39.13 by adding the following new AD:

Turbomeca S.A.: Docket No. FAA-2007-28077; Directorate Identifier 
2007-NE-20-AD.

Comments Due Date

    (a) We must receive comments by January 8, 2009.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Turbomeca S.A. Arriel 2B, 2B1, and 2B1A 
turboshaft engines. These engines are installed on, but not limited 
to, Eurocopter AS 350 B3 and EC 130 B4 helicopters.

Reason

    (d) Several cases of Gas Generator Turbine (HP Turbine) blade 
rearward displacement have been detected during borescope inspection 
or in repair centre following engine disassembly. Two of them 
resulted in blade rubs between the rear face of the fir-tree roots 
and the rear bearing support cover. High HP blade rearward 
displacement can potentially result in blade release due to fatigue 
of the blade, which would cause an uncommanded in-flight engine 
shutdown.
    We are issuing this AD to prevent an uncommanded in-flight 
engine shutdown which could result in an emergency autorotation 
landing or, at worst, an accident.

Actions and Compliance

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

Initial Inspection

    (1) Perform an initial HP turbine borescope inspection according 
to Turbomeca S.A. Mandatory Service Bulletin (MSB) No. 292 72 2825, 
dated April 5, 2007 as follows:
    (i) For engines with fewer than 500 hours and 450 cycles since 
new or since the last HP turbine borescope inspection, inspect 
before reaching 600 hours or 500 cycles whichever occurs first. 
Replace HP turbine modules with rearward turbine blade displacement 
greater than 0.5 mm.
    (ii) For the remaining engines, inspect within the next 100 
hours. Replace HP turbine modules with rearward turbine blade 
displacement greater than 0.5 mm.

Repetitive Inspections

    (2) Perform repetitive HP turbine borescope inspections 
according to Turbomeca S.A. MSB No. 292 72 2825, dated April 5, 
2007:
    (i) Within 600 hours or 500 cycles from the previous inspection, 
whichever occurs first, if the rearward displacement of the turbine 
blades was less than 0.2 mm. Replace HP turbine modules with 
rearward turbine blade displacement greater than 0.5 mm.
    (ii) Within 100 hours of the previous inspection if the rearward 
displacement of the turbine blades was between 0.2 mm and 0.5 mm. 
Replace HP turbine modules with rearward turbine blade displacement 
greater than 0.5 mm.
    (3) After each inspection, the compliance certificate must be 
sent to Turbomeca S.A. within 7 days, according to Sec.  2.D(1)(c) 
of Turbomeca S.A. MSB No. 292 72 2825, dated April 5, 2007.

FAA AD Differences

    (f) We modified the drawdown times to be more consistent with 
the compliance times.

Other FAA AD Provisions

    (g) The following provisions also apply to this AD:
    (1) 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.
    (2) Reporting Requirements: For any reporting requirement in 
this AD, under the provisions of the Paperwork Reduction Act, the 
Office of Management and Budget (OMB) has approved the information 
collection requirements and has assigned OMB Control Number 2120-
0056.

Related Information

    (h) Refer to EASA Airworthiness Directive 2007-0109, dated April 
19, 2007, and Turbomeca S.A. MSB No. 292 72 2825, dated April 5, 
2007, for related information.
    (i) Contact Christopher Spinney, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & Propeller Directorate, 12 New 
England Executive Park, Burlington, MA

[[Page 74663]]

01803; e-mail: christopher.spinney@faa.gov; telephone (781) 238-
7175; fax (781) 238-7199, for more information about this AD.

    Issued in Burlington, Massachusetts, on December 2, 2008.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E8-29102 Filed 12-8-08; 8:45 am]
BILLING CODE 4910-13-P
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