Airworthiness Directives; Turbomeca Arriel 2S1 and 2S2 Turboshaft Engines, 67562-67564 [E7-23031]

Download as PDF 67562 Federal Register / Vol. 72, No. 229 / Thursday, November 29, 2007 / Rules and Regulations 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 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 Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains the NPRM, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone (800) 647–5527) is 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 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. [Amended] 2. The FAA amends § 39.13 by adding the following new AD: I 2007–24–11 GROB–WERKE GMBH & CO KG: Amendment 39–15277; Docket No. FAA–2007–28670; Directorate Identifier 2007–CE–060–AD. rmajette on PROD1PC64 with RULES Effective Date (a) This airworthiness directive (AD) becomes effective January 3, 2008. Affected ADs (b) None. Applicability (c) This AD applies to the gliders Model G102 CLUB ASTIR III, serial numbers (SNs) 14:40 Nov 28, 2007 Jkt 214001 Reason (e) The mandatory continuing airworthiness information (MCAI) states: GROB received isolated difficulty reports regarding cracks on welded parts of the flight control system of the type G102, model CLUB ASTIR III & IIIb, and STANDARD ASTIR III. The cracks progress slowly from the welding seams periphery, and may eventually result in rupture at a matured stage. The MCAI requires all welded parts to be inspected and replaced if any cracks are found. Actions and Compliance (f) Unless already done, do the following actions: (1) Within the next 25 hours time-inservice (TIS) after January 3, 2008 (the effective date of this AD) or within the next 6 calendar months after January 3, 2008 (the effective date of this AD), whichever occurs first, inspect the welded parts of the flight control system for any cracks, deformations, or distortions following Grob Aerospace Service Bulletin No. MSB 306–35, dated April 27, 2007. Thereafter, repetitively inspect at intervals not to exceed 12 calendar months. (2) If you find any cracks, deformations, or distortions as a result of any inspection required by paragraph (f)(1) of this AD, before further flight, replace the affected part following Grob Aerospace Service Bulletin No. MSB 306–35, dated April 27, 2007. Note: This AD differs from the MCAI and/ or service information as follows: No differences. I VerDate Aug<31>2005 Subject (d) Air Transport Association of America (ATA) Code 27: Flight Controls. FAA AD Differences PART 39—AIRWORTHINESS DIRECTIVES § 39.13 5501 (suffix C) through 5652 (suffix C); Model G102 CLUB ASTIR IIIb, SNs 5501 (suffix Cb) through 5652 (suffix Cb); and Model G102 STANDARD ASTIR III, SNs 5502 (suffix S) through 5652 (suffix S), that are certificated in any category. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Greg Davison, Glider Program Manager, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4130; fax: (816) 329–4090. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), 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 MCAI European Aviation Safety Agency (EASA) Emergency AD No.: 2007–0135–E, dated May 14, 2007, and Grob Aerospace Service Bulletin No. MSB 306–35, dated April 27, 2007, for related information. Material Incorporated by Reference (i) You must use Grob Aerospace Service Bulletin No. MSB 306–35, dated April 27, 2007, 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 Grob Aerospace GmbH, Lettenbachstrasse 9, 86874 TussenhausenMattsies, Federal Republic of Germany. (3) You may review copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106; 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 Kansas City, Missouri, on November 20, 2007. Kim Smith, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–23016 Filed 11–28–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–28125; Directorate Identifier 2007–NE–17–AD; Amendment 39– 15276; AD 2007–24–10] RIN 2120–AA64 Airworthiness Directives; Turbomeca Arriel 2S1 and 2S2 Turboshaft Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: SUMMARY: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing E:\FR\FM\29NOR1.SGM 29NOR1 Federal Register / Vol. 72, No. 229 / Thursday, November 29, 2007 / Rules and Regulations airworthiness information (MCAI) provided by the European Aviation Safety Agency (EASA) to identify and correct an unsafe condition on Turbomeca Arriel 2S1 and 2S2 turboshaft engines. The MCAI states the following: During assembly of a new HP/LP fuel pump, the drain screw on the fuel filter unit failed when it was tightened to the torque value specified in the assembly schedule (12 Nm). Investigation of the screw showed that it was fully conformed to its specification, in terms of both dimensions and material. The mechanical calculations show, however, that a torque value of 12 Nm is too high for this screw, exceeding the elastic limit of the material. Failure of the affected screw could cause a fuel leak, resulting in an engine flame-out or engine fire. rmajette on PROD1PC64 with RULES We are issuing this AD to prevent a fuel leak as a result of a ruptured fuel filter drain screw that could lead to engine flame-out or an engine fire. DATES: This AD becomes effective December 14, 2007. The Director of the Federal Register approved the incorporation by reference of Turbomeca, S.A. Mandatory Service Bulletin No. 292 73 2824, dated February 1, 2007, listed in the AD as of December 14, 2007. We must receive comments on this AD by December 31, 2007. ADDRESSES: Use one of the following addresses to comment on this AD: • Federal eRulemaking Portal: Go to http://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: 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 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 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, VerDate Aug<31>2005 14:40 Nov 28, 2007 Jkt 214001 FAA, Engine and 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: Discussion EASA, which is the Technical Agent for the Member States of the European Community, has issued EASA AD No. 2007–0063, dated March 8, 2007, to correct an unsafe condition for the specified products. The EASA AD states: During assembly of a new HP/LP fuel pump, the drain screw on the fuel filter unit failed when it was tightened to the torque value specified in the assembly schedule (12 Nm). Investigation of the screw showed that it was fully conform to its specification, in terms of both dimensions and material. The mechanical calculations show, however, that a torque value of 12 Nm is too high for this screw, exceeding the elastic limit of the material. Failure of the affected screw could cause a fuel leak, resulting in an engine flame-out or engine fire. You may obtain further information by examining the EASA AD in the AD docket. Relevant Service Information Turbomeca has issued Mandatory Service Bulletin No. 292 73 2824, dated February 1, 2007. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. FAA’s Determination and Requirements of This 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 MCAI AD and service information referenced above. We are issuing this AD because we evaluated all the information provided by the EASA and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. This AD requires the replacement of the fuel filter drain screw and tightening it to an effective torque of 6.5 Nm. FAA’s Determination of the Effective Date An unsafe condition exists that requires the immediate adoption of this AD. The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule because of the high risk that the drain screw on the fuel filter unit may PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 67563 fail when tightened to the torque value specified in the assembly schedule. Failure of the affected screw could cause a fuel leak, resulting in an engine flame-out or engine fire. Therefore, we determined that notice and opportunity for public comment before issuing this AD are impracticable and that good cause exists for making this amendment effective in fewer than 30 days. Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2007–28125; Directorate Identifier 2007–NE–17–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD because of those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this AD. 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 E:\FR\FM\29NOR1.SGM 29NOR1 67564 Federal Register / Vol. 72, No. 229 / Thursday, November 29, 2007 / Rules and Regulations 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. 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 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. 2. The FAA amends § 39.13 by adding the following new AD: I 2007–24–10 Turbomeca: Amendment 39– 15276.; Docket No. FAA–2007–28125, Directorate Identifier 2007–NE–17–AD. Effective Date (a) This airworthiness directive (AD) becomes effective December 14, 2007. Applicability (c) This AD applies to Turbomeca Arriel 2S1 and 2S2 turboshaft engines, all serial numbers that have a hydro mechanical unit (HMU) installed that was manufactured before December 8, 2006, or repaired/ overhauled before December 8, 2006. These engines are installed on, but not limited to, Sikorsky S–76C helicopters. rmajette on PROD1PC64 with RULES Reason (d) European Aviation Safety Agency (EASA) AD No. 2007–0063, dated March 3, 2007, states: During assembly of a new HP/LP fuel pump, the drain screw on the fuel filter unit failed when it was tightened to the torque value specified in the assembly schedule (12 Nm). Investigation of the screw showed that it was fully conforming to its specification, VerDate Aug<31>2005 DEPARTMENT OF TRANSPORTATION FAA AD Differences RIN 2120–AA64 (f) This AD differs from the EASA AD and/ or service information as follows: (1) EASA AD No. 2007–0063 requires compliance with the AD within 30 HMU operating hours, but not later than 15 April 2007, whichever occurs first after the effective date of that AD. (2) This AD, written later, requires compliance within 30 HMU operating hours or 45 days after the effective date of this AD, whichever occurs first. (g) 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. (h) Refer to EASA AD 2007–0063, dated March 8, 2007, for related information. (i) Contact Christopher Spinney, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: Christopher.spinney@faa.gov; telephone (781) 238–7175; fax (781) 238– 7199, for more information about this AD. Material Incorporated by Reference Affected ADs (b) None. 14:40 Nov 28, 2007 Jkt 214001 BILLING CODE 4910–13–P (e) Unless already done, within 30 HMU operating hours or 45 days after the effective date of this AD, whichever occurs first, replace the fuel filter drain screw with a new one and tighten it to an effective torque of 6.5 Nm, using Turbomeca Mandatory Service Bulletin (MSB) No. 292 73 2824, dated February 1, 2007. Related Information [Amended] Issued in Burlington, Massachusetts, on November 20, 2007. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E7–23031 Filed 11–28–07; 8:45 am] Actions and Compliance Alternative Methods of Compliance (AMOCs) PART 39—AIRWORTHINESS DIRECTIVES § 39.13 in terms of both dimensions and material. The mechanical calculations show, however, that a torque value of 12 Nm is too high for this screw, exceeding the elastic limit of the material. Failure of the affected screw could cause a fuel leak, resulting in an engine flame-out or engine fire. (j) You must use Turbomeca Mandatory Service Bulletin No. 292 73 2824, dated February 1, 2007, to do the actions required by this AD. (k) 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. (l) 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. (m) You may review service information 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. PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–28656; Directorate Identifier 2007–NE–31–AD; Amendment 39– 15280; AD 2007–24–14] Airworthiness Directives; Hartzell Propeller Inc. Model HC–E5N–3( ), HC– E5N–3( )(L), and HC–E5B–5( ) Propellers Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for Hartzell Propeller Inc. Model HC–E5N–3( ), HC– E5N–3( )(L), and HC–E5B–5( ) propellers. This AD requires a onetime eddy current inspection of the propeller hub mounting bolt holes and replacement of the propeller hub if cracked. This AD results from the discovery of a five-bladed propeller hub with a large crack on the mounting flange of the hub. We are issuing this AD to prevent propeller hub failure, blade separation, damage to the airplane, and possible loss of airplane control. DATES: This AD becomes effective December 14, 2007. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of December 14, 2007. We must receive any comments on this AD by January 28, 2008. ADDRESSES: Use one of the following addresses to comment on this AD: • Federal eRulemaking Portal: Go to http://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: U.S. Docket Management Facility, 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. E:\FR\FM\29NOR1.SGM 29NOR1

Agencies

[Federal Register Volume 72, Number 229 (Thursday, November 29, 2007)]
[Rules and Regulations]
[Pages 67562-67564]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-23031]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28125; Directorate Identifier 2007-NE-17-AD; 
Amendment 39-15276; AD 2007-24-10]
RIN 2120-AA64


Airworthiness Directives; Turbomeca Arriel 2S1 and 2S2 Turboshaft 
Engines

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

ACTION: Final rule; request for comments.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for the 
products listed above. This AD results from mandatory continuing

[[Page 67563]]

airworthiness information (MCAI) provided by the European Aviation 
Safety Agency (EASA) to identify and correct an unsafe condition on 
Turbomeca Arriel 2S1 and 2S2 turboshaft engines. The MCAI states the 
following:

    During assembly of a new HP/LP fuel pump, the drain screw on the 
fuel filter unit failed when it was tightened to the torque value 
specified in the assembly schedule (12 Nm). Investigation of the 
screw showed that it was fully conformed to its specification, in 
terms of both dimensions and material. The mechanical calculations 
show, however, that a torque value of 12 Nm is too high for this 
screw, exceeding the elastic limit of the material. Failure of the 
affected screw could cause a fuel leak, resulting in an engine 
flame-out or engine fire.

We are issuing this AD to prevent a fuel leak as a result of a ruptured 
fuel filter drain screw that could lead to engine flame-out or an 
engine fire.

DATES: This AD becomes effective December 14, 2007.
    The Director of the Federal Register approved the incorporation by 
reference of Turbomeca, S.A. Mandatory Service Bulletin No. 292 73 
2824, dated February 1, 2007, listed in the AD as of December 14, 2007.
    We must receive comments on this AD by December 31, 2007.

ADDRESSES: Use one of the following addresses to comment on this AD:
     Federal eRulemaking Portal: Go to http://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: 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 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 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 and 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: 

Discussion

    EASA, which is the Technical Agent for the Member States of the 
European Community, has issued EASA AD No. 2007-0063, dated March 8, 
2007, to correct an unsafe condition for the specified products. The 
EASA AD states:

    During assembly of a new HP/LP fuel pump, the drain screw on the 
fuel filter unit failed when it was tightened to the torque value 
specified in the assembly schedule (12 Nm). Investigation of the 
screw showed that it was fully conform to its specification, in 
terms of both dimensions and material. The mechanical calculations 
show, however, that a torque value of 12 Nm is too high for this 
screw, exceeding the elastic limit of the material. Failure of the 
affected screw could cause a fuel leak, resulting in an engine 
flame-out or engine fire.

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

Relevant Service Information

    Turbomeca has issued Mandatory Service Bulletin No. 292 73 2824, 
dated February 1, 2007. The actions described in this service 
information are intended to correct the unsafe condition identified in 
the MCAI.

FAA's Determination and Requirements of This 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 MCAI AD and service information referenced 
above. We are issuing this AD because we evaluated all the information 
provided by the EASA and determined the unsafe condition exists and is 
likely to exist or develop on other products of the same type design. 
This AD requires the replacement of the fuel filter drain screw and 
tightening it to an effective torque of 6.5 Nm.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because of 
the high risk that the drain screw on the fuel filter unit may fail 
when tightened to the torque value specified in the assembly schedule. 
Failure of the affected screw could cause a fuel leak, resulting in an 
engine flame-out or engine fire. Therefore, we determined that notice 
and opportunity for public comment before issuing this AD are 
impracticable and that good cause exists for making this amendment 
effective in fewer than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2007-28125; Directorate 
Identifier 2007-NE-17-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this AD because of 
those comments.
    We will post all comments we receive, without change, to http://
www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this AD.

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

[[Page 67564]]

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.

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:

2007-24-10 Turbomeca: Amendment 39-15276.; Docket No. FAA-2007-
28125, Directorate Identifier 2007-NE-17-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective December 
14, 2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Turbomeca Arriel 2S1 and 2S2 turboshaft 
engines, all serial numbers that have a hydro mechanical unit (HMU) 
installed that was manufactured before December 8, 2006, or 
repaired/overhauled before December 8, 2006. These engines are 
installed on, but not limited to, Sikorsky S-76C helicopters.

Reason

    (d) European Aviation Safety Agency (EASA) AD No. 2007-0063, 
dated March 3, 2007, states:

    During assembly of a new HP/LP fuel pump, the drain screw on the 
fuel filter unit failed when it was tightened to the torque value 
specified in the assembly schedule (12 Nm). Investigation of the 
screw showed that it was fully conforming to its specification, in 
terms of both dimensions and material. The mechanical calculations 
show, however, that a torque value of 12 Nm is too high for this 
screw, exceeding the elastic limit of the material. Failure of the 
affected screw could cause a fuel leak, resulting in an engine 
flame-out or engine fire.

Actions and Compliance

    (e) Unless already done, within 30 HMU operating hours or 45 
days after the effective date of this AD, whichever occurs first, 
replace the fuel filter drain screw with a new one and tighten it to 
an effective torque of 6.5 Nm, using Turbomeca Mandatory Service 
Bulletin (MSB) No. 292 73 2824, dated February 1, 2007.

FAA AD Differences

    (f) This AD differs from the EASA AD and/ or service information 
as follows:
    (1) EASA AD No. 2007-0063 requires compliance with the AD within 
30 HMU operating hours, but not later than 15 April 2007, whichever 
occurs first after the effective date of that AD.
    (2) This AD, written later, requires compliance within 30 HMU 
operating hours or 45 days after the effective date of this AD, 
whichever occurs first.

Alternative Methods of Compliance (AMOCs)

    (g) 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 2007-0063, dated March 8, 2007, for related 
information.
    (i) Contact Christopher Spinney, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
Christopher.spinney@faa.gov; telephone (781) 238-7175; fax (781) 
238-7199, for more information about this AD.

Material Incorporated by Reference

    (j) You must use Turbomeca Mandatory Service Bulletin No. 292 73 
2824, dated February 1, 2007, to do the actions required by this AD.
    (k) 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.
    (l) 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.
    (m) You may review service information 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 November 20, 2007.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
 [FR Doc. E7-23031 Filed 11-28-07; 8:45 am]
BILLING CODE 4910-13-P