Airworthiness Directives; Turbomeca S.A. Turboshaft Engines, 44897-44899 [2013-17864]

Download as PDF ehiers on DSK2VPTVN1PROD with PROPOSALS-1 Federal Register / Vol. 78, No. 143 / Thursday, July 25, 2013 / Proposed Rules before collecting data from the public. It is our understanding that before a federal agency can require or request information from the public, the agency must (1) seek public comment on the proposed collections, and (2) submit the proposed collections for review and approval by OMB. Based on published guidance from the Executive Branch, it appears that the regular review and approval process can take anywhere from 6– 9 months from the date the process is initiated by the agency. The rulemaking requested in this petition appears to involve the collection of information subject to PRA requirements. For the reasons stated above, however, a delay of up to 9 months after the initiation of the rulemaking will cause harm to manufacturers and consumers that can and must be avoided. Under certain circumstances, an agency may obtain expedited or ‘‘emergency’’ OMB review of an information collection request. The regulations applicable to a request for emergency processing are set forth in 5 CFR § 1320.13 and state, in relevant part: (a) Any such request shall be accompanied by a written determination that: (1) The collection of information: (i) Is needed prior to the expiration of time periods established under this Part; and (ii) Is essential to the mission of the agency; and (2) The agency cannot reasonably comply with the normal clearance procedures under this Part because: (i) Public harm is reasonably likely to result if normal clearance procedures are followed; (or) (ii) An unanticipated event has occurred; . . . The circumstances described in this petition meet the requirements for expedited emergency review. Collecting EER information is based on regional standards that include minimum EER standards for CACs installed in the Southwestern Region. Collection of EER information, therefore, is essential to DOE’s ability to effectively enforce compliance with regional EER standards, and to provide complete information for the public to use in evaluating the energy efficiency of a covered product or covered equipment. [subsection (a)(1)(ii).] EER information must be collected and published in CCMS/CCD before completion of normal clearance procedures or significant public harm to manufacturers and consumers is likely to result. [subsection (a) (1) (ii), and (2)(i).] In addition, the adoption of regulations by the California Energy Commission applicable to higher efficiency CACs installed on or after January 1, 2014 may be regarded as an unanticipated event in light of the January 1, 2015 effective date for regional standards under federal law. [subsection (a)(2)(ii)]. The voluntary collection of EER information under the emergency procedure would place no additional burden on manufacturers, because they already have and maintain the EER information which is derived from the ‘‘A’’ test required under existing certification and compliance regulations. Very truly yours, HOWE, ANDERSON & STEYER, P.C. VerDate Mar<15>2010 13:49 Jul 24, 2013 Jkt 229001 Richard A. Steyer Attorney for First Co. cc: Ashley Armstrong, DOE, Laura Barhydt, DOE, First Co. [FR Doc. 2013–17894 Filed 7–24–13; 8:45 am] BILLING CODE 6450–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0381; Directorate Identifier 2013–NE–16–AD] RIN 2120–AA64 Airworthiness Directives; Turbomeca S.A. Turboshaft Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for all Turbomeca S.A. Arrius 2B1, 2B1A, 2B2, and 2K1 turboshaft engines. This proposed AD was prompted by in-flight shutdowns caused by interrupted fuel supply at the hydro-mechanical metering unit (HMU). This proposed AD would require initial and repetitive inspections of the HMU high pressure pump drive gear shaft splines, cleaning and inspections of the sleeve assembly splines, and replacement of the HMU if it fails inspection. We are proposing this AD to prevent in-flight shutdown and damage to the engine. DATES: We must receive comments on this proposed AD by September 23, 2013. SUMMARY: 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. For service information identified in this AD, contact Turbomeca, S.A., 40220 Tarnos, France; phone: 33 (0)5 59 74 40 00; telex: 570 042; fax: 33 (0)5 59 74 45 15. You may view this service information at the FAA, Engine & Propeller Directorate, 12 New England ADDRESSES: PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 44897 Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. 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 mandatory continuing airworthiness information (MCAI), the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (phone: 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: Frederick Zink, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7779; fax: 781–238– 7199; email: frederick.zink@faa.gov. 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–2013–0381; Directorate Identifier 2013–NE–16–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 view 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 AD 2013– E:\FR\FM\25JYP1.SGM 25JYP1 44898 Federal Register / Vol. 78, No. 143 / Thursday, July 25, 2013 / Proposed Rules 0082, dated April 2, 2013, referred to hereinafter as ‘‘the MCAI’’, to correct an unsafe condition for the specified products. The MCAI states: A number of in-flight shutdown occurrences have been reported for Arrius 2 engines. The results of the technical investigations concluded that these events were caused by deterioration of the splines on the high pressure (HP)/low pressure (LP) pump assembly drive shaft of the hydromechanical metering unit (HMU), which eventually interrupted the fuel supply to the engine. This condition, if not detected and corrected, could lead to further cases of engine in-flight shutdown, possibly resulting in forced landing. To address these occurrences, Turbomeca published Service Bulletin (SB) No. SB 319 73 2825, which provides inspection instructions. After that SB was issued, further similar occurrences prompted Turbomeca to perform a new assessment of the issue. As a result, it was determined that repetitive inspections of the HMU, including an additional inspection of the sleeve assembly, was necessary to address the issue. Those instructions are provided in Turbomeca Mandatory SB (MSB) No. SB 319 73 2825 version G. For the reasons described above, this AD requires repetitive inspections of drive gear shaft splines of the HP pump, and depending on findings, accomplishment of applicable corrective actions. You may obtain further information by examining the MCAI in the AD docket. We are proposing this AD to prevent inflight shutdown and damage to the engine. ehiers on DSK2VPTVN1PROD with PROPOSALS-1 Relevant Service Information Turbomeca S.A. has issued Mandatory Service Bulletin No. SB 319 73 2825, Version G, dated January 24, 2013. The service information describes procedures for correcting the unsafe condition described in the MCAI. 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 the European Community, EASA has notified us of the unsafe condition described in the MCAI 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 initial and repetitive inspections and cleaning of the HMU high pressure pump drive gear shaft splines, cleaning and inspections of the sleeve assembly splines, and VerDate Mar<15>2010 13:49 Jul 24, 2013 Jkt 229001 replacement of the HMU if it fails inspection. this proposed AD and placed it in the AD docket. Costs of Compliance We estimate that this proposed AD would affect 162 engines installed on helicopters of U.S. registry. We also estimate that it would take about one hour per engine to comply with this proposed AD. The average labor rate is $85 per hour. Required parts cost about $753 per engine. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $135,756. List of Subjects in 14 CFR Part 39 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. PART 39—AIRWORTHINESS DIRECTIVES 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), (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. We prepared a regulatory evaluation of the estimated costs to comply with PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 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: 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ Turbomeca S.A.: Docket No. FAA–2013– 0381; Directorate Identifier 2013–NE– 16–AD. (a) Comments Due Date We must receive comments by September 23, 2013. (b) Affected ADs None. (c) Applicability This AD applies to all Turbomeca S.A. Arrius 2B1, 2B1A, 2B2, and 2K1 turboshaft engines. (d) Reason This AD was prompted by in-flight shutdowns caused by interrupted fuel supply at the hydro-mechanical metering unit (HMU). We are issuing this AD to prevent inflight shutdown and damage to the engine. (e) Actions and Compliance Unless already done, do the following actions. (f) Initial Visual Inspection for HMUs Not Previously Inspected (1) On the effective date of this AD, for those HMUs that have not previously been inspected per Turbomeca Mandatory Service Bulletin (MSB) No. SB 319 73 2825, Version G, dated January 24, 2013, or earlier versions; perform an initial visual inspection of HMU aft splines of the high pressure pump for wear, corrosion, scaling, or cracks, and clean and inspect the sleeve assembly splines for wear, corrosion, scaling, or cracks, at the following: (i) For HMUs that have accumulated more than 150 operating hours (OHs) since new or since last overhaul, within 50 HMU OHs after effective date of this AD. (ii) For HMUs that have accumulated 150 or fewer OHs since new or since last overhaul, before exceeding 200 HMU OHs. E:\FR\FM\25JYP1.SGM 25JYP1 Federal Register / Vol. 78, No. 143 / Thursday, July 25, 2013 / Proposed Rules (g) Initial Visual Inspection for HMUs That Have Been Previously Inspected (1) On the effective date of this AD, for those HMUs that have been previously inspected per Turbomeca MSB No. SB 319 73 2825, Version G, dated January 24, 2013, or earlier versions; perform a visual inspection of HMU aft splines of the high pressure pump for wear, corrosion, scaling, or cracks, and clean and inspect the sleeve assembly splines for wear, corrosion, scaling, or cracks, at the following: (i) For HMUs that have accumulated 300 OHs or more since last inspection, within 200 HMU OHs after effective date of this AD. (ii) For HMUs that have accumulated fewer than 300 OHs since last inspection, before exceeding 500 HMU OHs. Issued in Burlington, Massachusetts, on July 18, 2013. Colleen M. D’Alessandro, Assistant Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2013–17864 Filed 7–24–13; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0499; Directorate Identifier 2013–NE–20–AD] RIN 2120–AA64 (h) Repetitive Visual Inspections of HMUs (1) Thereafter, repetitively visually inspect the HMU aft splines of the high pressure pump, and clean and inspect the sleeve assembly splines for wear, corrosion, scaling, or cracks, at intervals not to exceed 500 HMU OHs. (2) If, during any initial or repetitive inspection required by this AD, an HMU does not pass inspection, then before further flight, replace the sleeve assembly on the affected high pressure pump drive gear shaft or replace the affected HMU. (i) Installation Prohibition After the effective date of this AD, do not install any engine on any helicopter unless the HMU was inspected as required by this AD. (j) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, FAA, may approve AMOCs to this AD. Use the procedures found in 14 CFR 39.19 to make your request. ehiers on DSK2VPTVN1PROD with PROPOSALS-1 (k) Related Information (1) For more information about this AD, contact Frederick Zink, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; email: frederick.zink@faa.gov; phone: 781– 238–7779; fax: 781–238–7199. (2) Refer to European Aviation Safety Agency, AD 2013–0082, dated April 2, 2013, for more information. You may examine the AD on the Internet at https:// www.regulations.gov. (3) Turbomeca MSB No. SB 319 73 2825, Version G, dated January 24, 2013, which is not incorporated by reference in this AD, can be obtained from Turbomeca, S.A. using the contact information in paragraph (k)(4) of this AD. (4) For service information identified in this AD, contact Turbomeca, S.A., 40220 Tarnos, France; phone: 33 (0)5 59 74 40 00; telex: 570 042; fax: 33 (0)5 59 74 45 15. (5) You may view this service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. VerDate Mar<15>2010 13:49 Jul 24, 2013 Jkt 229001 Airworthiness Directives; General Electric Company Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain General Electric Company (GE) GE90– 110B1 and –115B turbofan engines. This proposed AD was prompted by multiple events of a leaking variable bypass valve (VBV) actuator fuel supply tube. This proposed AD would require replacement of this VBV actuator fuel supply tube with a part eligible for installation. We are proposing this AD to prevent failure of the affected fuel supply tube, fuel leakage, engine fire, and damage to the airplane. DATES: We must receive comments on this proposed AD by September 23, 2013. SUMMARY: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact General Electric Company, GE Aviation, Room 285, One Neumann Way, Cincinnati, OH 45215; phone: 513–552–3272; email: geae.aoc@ge.com. You may view this service information at the FAA, Engine & Propeller Directorate, 12 New England ADDRESSES: PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 44899 Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility 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 Office (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Jason Yang, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7747; fax: 781–238– 7199; email: jason.yang@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2013–0499; Directorate Identifier 2013– NE–20–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 because of 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 we receive about this proposed AD. Discussion We have received multiple reports of a leaking VBV actuator fuel supply tube, part number (P/N) 2165M22P01, installed on GE90–110B1 and –115B turbofan engines. One of the leaks led to an under cowl engine fire. The vibratory excitation frequency of this VBV actuator fuel supply tube mode shape is within the frequency range generated by the engine during cruise. Because the tube’s end weld is a high stress concentration location, the tube can and has cracked in this area and eventually failed due to high-cycle fatigue. This proposed AD, therefore, requires replacement of the affected VBV E:\FR\FM\25JYP1.SGM 25JYP1

Agencies

[Federal Register Volume 78, Number 143 (Thursday, July 25, 2013)]
[Proposed Rules]
[Pages 44897-44899]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-17864]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0381; Directorate Identifier 2013-NE-16-AD]
RIN 2120-AA64


Airworthiness Directives; Turbomeca S.A. 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 all 
Turbomeca S.A. Arrius 2B1, 2B1A, 2B2, and 2K1 turboshaft engines. This 
proposed AD was prompted by in-flight shutdowns caused by interrupted 
fuel supply at the hydro-mechanical metering unit (HMU). This proposed 
AD would require initial and repetitive inspections of the HMU high 
pressure pump drive gear shaft splines, cleaning and inspections of the 
sleeve assembly splines, and replacement of the HMU if it fails 
inspection. We are proposing this AD to prevent in-flight shutdown and 
damage to the engine.

DATES: We must receive comments on this proposed AD by September 23, 
2013.

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.
    For service information identified in this AD, contact Turbomeca, 
S.A., 40220 Tarnos, France; phone: 33 (0)5 59 74 40 00; telex: 570 042; 
fax: 33 (0)5 59 74 45 15. You may view this service information at the 
FAA, Engine & Propeller Directorate, 12 New England Executive Park, 
Burlington, MA. For information on the availability of this material at 
the FAA, call 781-238-7125.

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 mandatory 
continuing airworthiness information (MCAI), the regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Operations office (phone: 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: Frederick Zink, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; phone: 781-238-7779; 
fax: 781-238-7199; email: frederick.zink@faa.gov.

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-2013-0381; 
Directorate Identifier 2013-NE-16-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 view 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 
AD 2013-

[[Page 44898]]

0082, dated April 2, 2013, referred to hereinafter as ``the MCAI'', to 
correct an unsafe condition for the specified products. The MCAI 
states:

    A number of in-flight shutdown occurrences have been reported 
for Arrius 2 engines. The results of the technical investigations 
concluded that these events were caused by deterioration of the 
splines on the high pressure (HP)/low pressure (LP) pump assembly 
drive shaft of the hydro-mechanical metering unit (HMU), which 
eventually interrupted the fuel supply to the engine.
    This condition, if not detected and corrected, could lead to 
further cases of engine in-flight shutdown, possibly resulting in 
forced landing.
    To address these occurrences, Turbomeca published Service 
Bulletin (SB) No. SB 319 73 2825, which provides inspection 
instructions. After that SB was issued, further similar occurrences 
prompted Turbomeca to perform a new assessment of the issue. As a 
result, it was determined that repetitive inspections of the HMU, 
including an additional inspection of the sleeve assembly, was 
necessary to address the issue. Those instructions are provided in 
Turbomeca Mandatory SB (MSB) No. SB 319 73 2825 version G.
    For the reasons described above, this AD requires repetitive 
inspections of drive gear shaft splines of the HP pump, and 
depending on findings, accomplishment of applicable corrective 
actions.

You may obtain further information by examining the MCAI in the AD 
docket. We are proposing this AD to prevent in-flight shutdown and 
damage to the engine.

Relevant Service Information

    Turbomeca S.A. has issued Mandatory Service Bulletin No. SB 319 73 
2825, Version G, dated January 24, 2013. The service information 
describes procedures for correcting the unsafe condition described in 
the MCAI.

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 the European Community, EASA has notified us 
of the unsafe condition described in the MCAI 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 initial and repetitive 
inspections and cleaning of the HMU high pressure pump drive gear shaft 
splines, cleaning and inspections of the sleeve assembly splines, and 
replacement of the HMU if it fails inspection.

Costs of Compliance

    We estimate that this proposed AD would affect 162 engines 
installed on helicopters of U.S. registry. We also estimate that it 
would take about one hour per engine to comply with this proposed AD. 
The average labor rate is $85 per hour. Required parts cost about $753 
per engine. Based on these figures, we estimate the cost of the 
proposed AD on U.S. operators to be $135,756.

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),
    (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.
    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

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):

Turbomeca S.A.: Docket No. FAA-2013-0381; Directorate Identifier 
2013-NE-16-AD.

(a) Comments Due Date

    We must receive comments by September 23, 2013.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Turbomeca S.A. Arrius 2B1, 2B1A, 2B2, and 
2K1 turboshaft engines.

(d) Reason

    This AD was prompted by in-flight shutdowns caused by 
interrupted fuel supply at the hydro-mechanical metering unit (HMU). 
We are issuing this AD to prevent in-flight shutdown and damage to 
the engine.

(e) Actions and Compliance

    Unless already done, do the following actions.

(f) Initial Visual Inspection for HMUs Not Previously Inspected

    (1) On the effective date of this AD, for those HMUs that have 
not previously been inspected per Turbomeca Mandatory Service 
Bulletin (MSB) No. SB 319 73 2825, Version G, dated January 24, 
2013, or earlier versions; perform an initial visual inspection of 
HMU aft splines of the high pressure pump for wear, corrosion, 
scaling, or cracks, and clean and inspect the sleeve assembly 
splines for wear, corrosion, scaling, or cracks, at the following:
    (i) For HMUs that have accumulated more than 150 operating hours 
(OHs) since new or since last overhaul, within 50 HMU OHs after 
effective date of this AD.
    (ii) For HMUs that have accumulated 150 or fewer OHs since new 
or since last overhaul, before exceeding 200 HMU OHs.

[[Page 44899]]

(g) Initial Visual Inspection for HMUs That Have Been Previously 
Inspected

    (1) On the effective date of this AD, for those HMUs that have 
been previously inspected per Turbomeca MSB No. SB 319 73 2825, 
Version G, dated January 24, 2013, or earlier versions; perform a 
visual inspection of HMU aft splines of the high pressure pump for 
wear, corrosion, scaling, or cracks, and clean and inspect the 
sleeve assembly splines for wear, corrosion, scaling, or cracks, at 
the following:
    (i) For HMUs that have accumulated 300 OHs or more since last 
inspection, within 200 HMU OHs after effective date of this AD.
    (ii) For HMUs that have accumulated fewer than 300 OHs since 
last inspection, before exceeding 500 HMU OHs.

(h) Repetitive Visual Inspections of HMUs

    (1) Thereafter, repetitively visually inspect the HMU aft 
splines of the high pressure pump, and clean and inspect the sleeve 
assembly splines for wear, corrosion, scaling, or cracks, at 
intervals not to exceed 500 HMU OHs.
    (2) If, during any initial or repetitive inspection required by 
this AD, an HMU does not pass inspection, then before further 
flight, replace the sleeve assembly on the affected high pressure 
pump drive gear shaft or replace the affected HMU.

(i) Installation Prohibition

    After the effective date of this AD, do not install any engine 
on any helicopter unless the HMU was inspected as required by this 
AD.

(j) Alternative Methods of Compliance (AMOCs)

    The Manager, Engine Certification Office, FAA, may approve AMOCs 
to this AD. Use the procedures found in 14 CFR 39.19 to make your 
request.

(k) Related Information

    (1) For more information about this AD, contact Frederick Zink, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, MA 
01803; email: frederick.zink@faa.gov; phone: 781-238-7779; fax: 781-
238-7199.
    (2) Refer to European Aviation Safety Agency, AD 2013-0082, 
dated April 2, 2013, for more information. You may examine the AD on 
the Internet at https://www.regulations.gov.
    (3) Turbomeca MSB No. SB 319 73 2825, Version G, dated January 
24, 2013, which is not incorporated by reference in this AD, can be 
obtained from Turbomeca, S.A. using the contact information in 
paragraph (k)(4) of this AD.
    (4) For service information identified in this AD, contact 
Turbomeca, S.A., 40220 Tarnos, France; phone: 33 (0)5 59 74 40 00; 
telex: 570 042; fax: 33 (0)5 59 74 45 15.
    (5) You may view this service information at the FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, 
MA. For information on the availability of this material at the FAA, 
call 781-238-7125.


    Issued in Burlington, Massachusetts, on July 18, 2013.
Colleen M. D'Alessandro,
Assistant Manager, Engine & Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2013-17864 Filed 7-24-13; 8:45 am]
BILLING CODE 4910-13-P