Airworthiness Directives; Turboméca S.A. Arriel 2B and 2B1 Turboshaft Engines, 59065-59067 [2010-23833]

Download as PDF 59065 Federal Register / Vol. 75, No. 186 / Monday, September 27, 2010 / Rules and Regulations inboard-hinge bracket if a crack is found that is 0.30 inch or more; however, this AD requires corrective actions be done using a method approved by us. (1) If the crack is 0.30 inch or more: Replace the bracket before further flight. (2) If the crack is less than 0.30 inch: Continued flight for a maximum of 10 flight hours for repositioning of the airplane and replacement of the bracket is allowed, within the restricted flight envelope included in the attachment to Cessna Alert Service Letter ASL750–27–21, dated October 13, 2006, titled ‘‘Flight Restrictions.’’ New Requirements of This AD (k) Within 60 months after the effective date of this AD, do the applicable actions required by paragraphs (k)(1), (k)(2), (k)(3), and (k)(4) of this AD, in accordance with the Accomplishment Instructions of Cessna Service Bulletin SB750–27–62, Revision 3, dated August 21, 2009. Accomplishing the actions required by paragraph (k) of this AD terminates the requirements of paragraphs (g) through (j) of this AD. (1) For all airplanes except those having S/Ns 288 through 305 inclusive: Do an eddy current inspection for cracks of the bracket of the inboard horizontal stabilizer. Before further flight, replace any cracked bracket of the inboard horizontal stabilizer with a serviceable bracket. (2) For all airplanes except those having S/Ns 288 through 305 inclusive: Measure the lug thickness of the horizontal stabilizer hinges. If the lug thickness is not within the Special Flight Permits (i) Special flight permits, as described in Section 39.23 of the Federal Aviation Regulations (14 CFR 39.23), are allowed with the limitations required by paragraph (h)(2) of this AD. No Reporting or Return of Parts to Manufacturer (j) Cessna Alert Service Letter ASL750–27– 21, dated October 13, 2006, specifies submitting a sheet related to inspection results to the manufacturer; this AD does not include that requirement. The service letter also specifies sending the elevator assembly to the manufacturer for replacement of the acceptable tolerance range, as identified in Cessna Service Bulletin SB750–27–62, Revision 3, dated August 21, 2009, before further flight, replace the bearing plate with a serviceable bearing plate. (3) For all airplanes except those having S/Ns 288 through 305 inclusive: Modify the left and right horizontal stabilizer; and add the modification part number of the horizontal stabilizer to the modification section of the MS27253–1 identification plate. (4) For all airplanes: Replace the existing elevator assemblies with new elevator assemblies having part numbers 6734000–17 (for the left side) and 6734000–18 (for the right side). Credit for Actions Done Using the Previous Service Information (l) Actions accomplished before the effective date of this AD in accordance with the service bulletins identified in Table 1 of this AD are considered acceptable for compliance with the corresponding requirements of paragraphs (k)(1), (k)(2), and (k)(3) of this AD. TABLE 1—CREDIT FOR PREVIOUS SERVICE BULLETINS Revision level Service Bulletin Cessna Service Bulletin SB750–27–62 ............................................................................................................... Cessna Service Bulletin SB750–27–62 ............................................................................................................... Cessna Service Bulletin SB750–27–62 ............................................................................................................... (1) 1 2 Date October 13, 2008. October 22, 2008. December 17, 2008. 1 Original. Alternative Methods of Compliance (AMOCs) (m)(1) The Manager, Wichita ACO, 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: T.N. Baktha, Aerospace Engineer, Airframe Branch, ACE–118W, FAA, Wichita ACO, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209; telephone (316) 946–4155; fax (316) 946–4107. (2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. The AMOC approval letter must specifically reference this AD. mstockstill on DSKH9S0YB1PROD with RULES Material Incorporated by Reference (n) You must use Cessna Alert Service Letter ASL750–27–21, excluding the attachment titled ‘‘Inspection Results Form’’ and including the attachment titled ‘‘Flight Restrictions,’’ dated October 13, 2006; and Cessna Service Bulletin SB750–27–62, Revision 3, dated August 21, 2009, including Service Bulletin Supplemental Data, Revision D, dated September 18, 2009; as applicable; to do the actions required by this AD, unless the AD specifies otherwise. VerDate Mar<15>2010 16:28 Sep 24, 2010 Jkt 220001 (1) The Director of the Federal Register approved the incorporation by reference of Cessna Service Bulletin SB750–27–62, Revision 3, dated August 21, 2009, including Service Bulletin Supplemental Data, Revision D, dated September 18, 2009, under 5 U.S.C. 552(a) and 1 CFR part 51. (2) The Director of the Federal Register previously approved the incorporation by reference of Cessna Alert Service Letter ASL750–27–21, excluding the attachment titled ‘‘Inspection Results Form’’ and including the attachment titled ‘‘Flight Restrictions,’’ dated October 13, 2006, on November 22, 2006 (71 FR 65047, November 7, 2006). (3) For service information identified in this AD, contact Cessna Aircraft Co., P.O. Box 7706, Wichita, Kansas 67277; telephone 316– 517–6215; fax 316–517–5802; e-mail citationpubs@cessna.textron.com; Internet https://www.cessnasupport.com/ newlogin.html. (4) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221. (5) You may also review copies of the service information that is incorporated by reference 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/ PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on September 15, 2010. Robert D. Breneman, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010–23834 Filed 9–24–10; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–28077; Directorate Identifier 2007–NE–20–AD; Amendment 39–16445; AD 2009–09–03R1] RIN 2120–AA64 ´ Airworthiness Directives; Turbomeca S.A. Arriel 2B and 2B1 Turboshaft Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are revising an existing airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing SUMMARY: E:\FR\FM\27SER1.SGM 27SER1 59066 Federal Register / Vol. 75, No. 186 / Monday, September 27, 2010 / Rules and Regulations airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Therefore, this AD revises AD 2007–0109 by retaining the same requirements of AD 2007–0109 except that applicability is limited to ARRIEL 2B, 2B1 and 2B1A engines which do not incorporate modification TU166. Since issuance of AD 2007–0109, ´ Turbomeca has released modification TU166 which consists in inserting HP blade dampers between the HP disc and the HP blade platform. Introduction of these dampers has demonstrated to limit axial displacement of the HP blade relative to the disk in case of blade lock rupture or opening, therefore eliminating the need for inspection and replacement. Comments We are issuing this AD to prevent an uncommanded in-flight engine shutdown which could result in an emergency autorotation landing or an accident. DATES: This AD becomes effective November 1, 2010. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of November 1, 2010. The Director of the Federal Register approved the incorporation by reference of ´ Turbomeca S.A. Mandatory Service Bulletin No. 292 72 2825, dated April 5, 2007, listed in this AD as of June 1, 2009 (74 FR 18981, April 27, 2009). ADDRESSES: The Docket Operations office is located at Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. FOR FURTHER INFORMATION CONTACT: Richard Woldan, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803–5299; telephone (781) 238–7136; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: mstockstill on DSKH9S0YB1PROD with RULES Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on May 12, 2010 (75 FR 26681). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states that: Since issuance of AD 2007–0109, ´ Turbomeca has released modification TU166 which consists in inserting HP blade dampers between the HP disc and the HP blade platform. Introduction of these dampers has demonstrated to limit axial displacement of the HP blade relative to the disk in case of blade lock rupture or opening, therefore eliminating the need for inspection and replacement. VerDate Mar<15>2010 16:28 Sep 24, 2010 Jkt 220001 We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. Conclusion We reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. Differences Between This AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in general, agree with their substance. But we required different actions in this AD from those in the MCAI in order to follow FAA policies. Any such differences are described in a separate paragraph of the AD. These requirements take precedence over the actions copied from the MCAI. Costs of Compliance Based on the service information, we estimate that this AD would affect about 248 products of U.S. registry. We also estimate that it would take about 2 work-hours per product to comply with this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of the AD on U.S. operators to be $42,160. 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. PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this AD: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (phone (800) 647–5527) is provided in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: ■ 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Amendment 39–15889 (74 FR 18981), and adding a new airworthiness directive, Amendment 39–16445, to read as follows: ■ ´ 2009–09–03R1 Turbomeca S.A.: Amendment 39–16445. Docket No. E:\FR\FM\27SER1.SGM 27SER1 Federal Register / Vol. 75, No. 186 / Monday, September 27, 2010 / Rules and Regulations FAA–2007–28077; Directorate Identifier 2007–NE–20–AD. Optional Terminating Action DEPARTMENT OF TRANSPORTATION (a) This airworthiness directive (AD) becomes effective November 1, 2010. (f) Incorporating modification TU166 terminates the repetitive inspection requirements of paragraphs (e)(2)(i) and (e)(2)(ii) of this AD. Affected ADs FAA AD Differences (b) This AD revises AD 2009–09–03, Amendment 39–15889. ´ (c) This AD applies to Turbomeca S.A. ARRIEL 2B and 2B1 turboshaft engines that don’t incorporate modification TU166. These engines are installed on, but not limited to, Eurocopter AS 350 B3 and EC 130 B4 helicopters. (g) For clarification, we restructured the actions and compliance wording of this AD. ´ (h) We deleted the Turbomeca reporting requirement from the AD. (i) Although EASA Airworthiness Directive 2007–0109R1, dated November 9, 2009, applies to the ARRIEL 2B1A engine, this AD does not apply to that model because it has no U.S. type certificate. Reason Alternative Methods of Compliance (AMOCs) Effective Date Applicability (d) This AD results from: Since issuance of AD 2007–0109, ´ Turbomeca has released modification TU166 which consists in inserting HP blade dampers between the HP disc and the HP blade platform. Introduction of these dampers has demonstrated to limit axial displacement of the HP blade relative to the disk in case of blade lock rupture or opening, therefore eliminating the need for inspection and replacement. We are issuing this AD to prevent an uncommanded in-flight engine shutdown which could result in an emergency autorotation landing or an accident. Actions and Compliance (e) Unless already done, do the following actions: Initial Inspection mstockstill on DSKH9S0YB1PROD with RULES (1) Perform an initial high-pressure (HP) turbine borescope inspection according to ´ Turbomeca S.A. Mandatory Service Bulletin (MSB) No. 292 72 2825, Version B, dated September 21, 2009, or earlier version 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, Version B, dated September 21, 2009 or earlier version: (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. VerDate Mar<15>2010 16:28 Sep 24, 2010 Jkt 220001 (j) 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 (k) Refer to EASA Airworthiness Directive 2007–0109R1, dated November 9, 2009, and ´ Turbomeca S.A. MSB No. 292 72 2825, Version B, dated September 21, 2009, or earlier version, for related information. (l) Contact Richard Woldan, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803–5299; telephone (781) 238–7136; fax (781) 238–7199, for more information about this AD. Material Incorporated by Reference ´ (m) You must use Turbomeca S.A. Mandatory Service Bulletin No. 292 72 2825, Version B, dated September 21, 2009, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register previously approved the incorporation by ´ reference of Turbomeca S.A. Mandatory Service Bulletin No. 292 72 2825, dated April 5, 2007, on June 1, 2009 (74 FR 18981, April 27, 2009). (2) For service information identified in ´ this AD, contact Turbomeca, 40220 Tarnos, France; telephone 33 05 59 74 40 00, fax 33 05 59 74 45 15. (3) You may review copies at the FAA, New England Region, 12 New England Executive Park, Burlington, MA; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741–6030, or go to: http://www. archives.gov/federal-register/cfr/ibrlocations.html. Issued in Burlington, Massachusetts, on September 17, 2010. Robert J. Ganley, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 2010–23833 Filed 9–24–10; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 59067 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–1100; Directorate Identifier 2009–NE–37–AD; Amendment 39– 16441; AD 2010–20–07] RIN 2120–AA64 Airworthiness Directives; International Aero Engines AG V2500–A1, V2522– A5, V2524–A5, V2525–D5, V2527–A5, V2527E–A5, V2527M–A5, V2528–D5, V2530–A5, and V2533–A5 Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: The FAA is adopting a new airworthiness directive (AD) for all International Aero Engines AG (IAE) V2500–A1, V2525–D5 and V2528–D5 turbofan engines and certain serial numbers (S/Ns) of IAE V2522–A5, V2524–A5, V2527–A5, V2527E–A5, V2527M–A5, V2530–A5, and V2533–A5 turbofan engines. For certain S/Ns of V2500–A1, V2522–A5, V2524–A5, V2527–A5, V2527E–A5, V2527M–A5, V2530–A5, and V2533–A5 series turbofan engines, this AD requires initial and repetitive on-wing ultrasonic inspections of the high-pressure compressor (HPC) stage 3 to 8 drum for cracks. As mandatory terminating action to the repetitive inspections, this AD requires removal from service of the fully silver plated nuts attaching the HPC stage 3 to 8 drum to the HPC stage 9 to 12 drum, removal of silver residue from the HPC stage 3 to 8 drum, and fluorescent penetrant inspection (FPI) of the stage 3 to 8 drum within a specified time. For all other engines, this AD requires removal from service of the fully silver plated nuts attaching the HPC stage 3 to 8 drum to the HPC stage 9 to 12 drum, removal of silver residue from the HPC stage 3 to 8 drum, and FPI of the HPC stage 3 to 8 drum at the next drum piece-part exposure. This AD results from reports of 39 HPC stage 3 to 8 drums found cracked since March 2009. We are issuing this AD to prevent uncontained failure of the HPC stage 3 to 8 drum, which could result in damage to the airplane. DATES: This AD becomes effective November 1, 2010. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of November 1, 2010. ADDRESSES: You can get the service information identified in this AD from SUMMARY: E:\FR\FM\27SER1.SGM 27SER1

Agencies

[Federal Register Volume 75, Number 186 (Monday, September 27, 2010)]
[Rules and Regulations]
[Pages 59065-59067]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-23833]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28077; Directorate Identifier 2007-NE-20-AD; 
Amendment 39-16445; AD 2009-09-03R1]
RIN 2120-AA64


Airworthiness Directives; Turbom[eacute]ca S.A. Arriel 2B and 2B1 
Turboshaft Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are revising an existing airworthiness directive (AD) for 
the products listed above. This AD results from mandatory continuing

[[Page 59066]]

airworthiness information (MCAI) issued by an aviation authority of 
another country to identify and correct an unsafe condition on an 
aviation product. The MCAI describes the unsafe condition as:

    Since issuance of AD 2007-0109, Turbom[eacute]ca has released 
modification TU166 which consists in inserting HP blade dampers 
between the HP disc and the HP blade platform. Introduction of these 
dampers has demonstrated to limit axial displacement of the HP blade 
relative to the disk in case of blade lock rupture or opening, 
therefore eliminating the need for inspection and replacement.

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

DATES: This AD becomes effective November 1, 2010. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in this AD as of November 1, 2010. The Director of 
the Federal Register approved the incorporation by reference of 
Turbom[eacute]ca S.A. Mandatory Service Bulletin No. 292 72 2825, dated 
April 5, 2007, listed in this AD as of June 1, 2009 (74 FR 18981, April 
27, 2009).

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

FOR FURTHER INFORMATION CONTACT: Richard Woldan, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803-5299; telephone (781) 
238-7136; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on May 12, 2010 (75 FR 
26681). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states that:

    Since issuance of AD 2007-0109, Turbom[eacute]ca has released 
modification TU166 which consists in inserting HP blade dampers 
between the HP disc and the HP blade platform. Introduction of these 
dampers has demonstrated to limit axial displacement of the HP blade 
relative to the disk in case of blade lock rupture or opening, 
therefore eliminating the need for inspection and replacement.
    Therefore, this AD revises AD 2007-0109 by retaining the same 
requirements of AD 2007-0109 except that applicability is limited to 
ARRIEL 2B, 2B1 and 2B1A engines which do not incorporate 
modification TU166.

Comments

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

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting the AD as proposed.

Differences Between This AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we required different actions 
in this AD from those in the MCAI in order to follow FAA policies. Any 
such differences are described in a separate paragraph of the AD. These 
requirements take precedence over the actions copied from the MCAI.

Costs of Compliance

    Based on the service information, we estimate that this AD would 
affect about 248 products of U.S. registry. We also estimate that it 
would take about 2 work-hours per product to comply with this AD. The 
average labor rate is $85 per work-hour. Based on these figures, we 
estimate the cost of the AD on U.S. operators to be $42,160.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government.
    For the reasons discussed above, I certify this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Operations office (phone (800) 647-5527) is provided in the 
ADDRESSES section. Comments will be available in the AD docket shortly 
after receipt.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Amendment 39-15889 (74 FR 
18981), and adding a new airworthiness directive, Amendment 39-16445, 
to read as follows:

2009-09-03R1 Turbom[eacute]ca S.A.: Amendment 39-16445. Docket No.

[[Page 59067]]

FAA-2007-28077; Directorate Identifier 2007-NE-20-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective November 
1, 2010.

Affected ADs

    (b) This AD revises AD 2009-09-03, Amendment 39-15889.

Applicability

    (c) This AD applies to Turbom[eacute]ca S.A. ARRIEL 2B and 2B1 
turboshaft engines that don't incorporate modification TU166. These 
engines are installed on, but not limited to, Eurocopter AS 350 B3 
and EC 130 B4 helicopters.

Reason

    (d) This AD results from:
    Since issuance of AD 2007-0109, Turbom[eacute]ca has released 
modification TU166 which consists in inserting HP blade dampers 
between the HP disc and the HP blade platform. Introduction of these 
dampers has demonstrated to limit axial displacement of the HP blade 
relative to the disk in case of blade lock rupture or opening, 
therefore eliminating the need for inspection and replacement.
    We are issuing this AD to prevent an uncommanded in-flight 
engine shutdown which could result in an emergency autorotation 
landing or an accident.

Actions and Compliance

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

Initial Inspection

    (1) Perform an initial high-pressure (HP) turbine borescope 
inspection according to Turbom[eacute]ca S.A. Mandatory Service 
Bulletin (MSB) No. 292 72 2825, Version B, dated September 21, 2009, 
or earlier version 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 Turbom[eacute]ca S.A. MSB No. 292 72 2825, Version B, 
dated September 21, 2009 or earlier version:
    (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.

Optional Terminating Action

    (f) Incorporating modification TU166 terminates the repetitive 
inspection requirements of paragraphs (e)(2)(i) and (e)(2)(ii) of 
this AD.

FAA AD Differences

    (g) For clarification, we restructured the actions and 
compliance wording of this AD.
    (h) We deleted the Turbom[eacute]ca reporting requirement from 
the AD.
    (i) Although EASA Airworthiness Directive 2007-0109R1, dated 
November 9, 2009, applies to the ARRIEL 2B1A engine, this AD does 
not apply to that model because it has no U.S. type certificate.

Alternative Methods of Compliance (AMOCs)

    (j) 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

    (k) Refer to EASA Airworthiness Directive 2007-0109R1, dated 
November 9, 2009, and Turbom[eacute]ca S.A. MSB No. 292 72 2825, 
Version B, dated September 21, 2009, or earlier version, for related 
information.
    (l) Contact Richard Woldan, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803-5299; telephone (781) 
238-7136; fax (781) 238-7199, for more information about this AD.

Material Incorporated by Reference

    (m) You must use Turbom[eacute]ca S.A. Mandatory Service 
Bulletin No. 292 72 2825, Version B, dated September 21, 2009, to do 
the actions required by this AD, unless the AD specifies otherwise.
    (1) The Director of the Federal Register previously approved the 
incorporation by reference of Turbom[eacute]ca S.A. Mandatory 
Service Bulletin No. 292 72 2825, dated April 5, 2007, on June 1, 
2009 (74 FR 18981, April 27, 2009).
    (2) For service information identified in this AD, contact 
Turbom[eacute]ca, 40220 Tarnos, France; telephone 33 05 59 74 40 00, 
fax 33 05 59 74 45 15.
    (3) You may review copies at the FAA, New England Region, 12 New 
England Executive Park, Burlington, MA; or at the National Archives 
and Records Administration (NARA). For information on the 
availability of this material at NARA, call (202) 741-6030, or go 
to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Burlington, Massachusetts, on September 17, 2010.
Robert J. Ganley,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2010-23833 Filed 9-24-10; 8:45 am]
BILLING CODE 4910-13-P