Airworthiness Directives; SOCATA Model TBM 700 Airplanes, 59658-59661 [2010-24248]

Download as PDF WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS 59658 Federal Register / Vol. 75, No. 187 / Tuesday, September 28, 2010 / Proposed Rules standards for the following categories of electric motors: U-Frame, Design C, close-coupled pump, footless, vertical solid shaft normal thrust, 8-pole (900 rpm), and polyphase motors with a voltage of not more than 600 volts (other than 230 or 460 volts). (42 U.S.C. 6311(13)) EPCA also directs DOE to publish a final rule determining whether to amend existing electric motors standards within 24 months of the effective date of the previous final electric motors rule. (42 U.S.C. 6313(b)(4)(B)) The most recent electric motors standards set out in EISA 2007 and codified in the Code of Federal Regulations (CFR) on March 23, 2009, go into effect on December 19, 2010, under section 313(b)(2) of EISA 2007. Therefore, DOE must publish a final rule determining whether to amend the electric motors standards by December 19, 2012. (42 U.S.C. 6313(b)(4)(B)) Any amended standards established pursuant to this rulemaking would apply to products manufactured five years or more after the effective date of the previous electric motors standard. (42 U.S.C. 6313(b)(4)(B)(i)) Any amended standards that result from this rulemaking process, therefore, would have a compliance date of December 19, 2015. (42 U.S.C. 6313(b)(4)(B)) DOE is, therefore, beginning a rulemaking process to consider further amending these standards with a framework document for electric motors describing the procedural and analytical approaches DOE anticipates using in its evaluation. The focus of the public meeting noted above will be to discuss the analyses presented and issues identified in the framework document. At the public meeting, DOE will make a number of presentations, invite discussion on the rulemaking process as it applies to electric motors, and solicit comments, data, and information from participants and other interested parties. DOE encourages those who wish to participate in the public meeting to obtain the framework document and to be prepared to discuss its contents. A copy of the draft framework document is available at: http:// www1.eere.energy.gov/buildings/ appliance_standards/commercial/ electric_motors.html. Public meeting participants need not limit their comments to the issues identified in the framework document. DOE is also interested in comments on other relevant issues that participants believe would affect energy conservation standards for this equipment, applicable test procedures, or the preliminary determination on the VerDate Mar<15>2010 15:21 Sep 27, 2010 Jkt 220001 scope of coverage. DOE invites all interested parties, whether or not they participate in the public meeting, to submit comments and information on matters addressed in the framework document and on other matters relevant to DOE’s consideration of amended standards for electric motors in writing by October 28, 2010. The public meeting will be conducted in an informal, facilitated, conference style. There shall be no discussion of proprietary information, costs or prices, market shares, or other commercial matters regulated by U.S. antitrust laws. A court reporter will record the proceedings of the public meeting, after which a transcript will be available on the DOE Web site at: http:// www1.eere.energy.gov/buildings/ appliance_standards/commercial/ electric_motors.html and for purchase from the court reporter. After the public meeting and the close of the comment period on the framework document, DOE will begin conducting the analyses discussed in the framework document and reviewing the public comments received. DOE considers public participation to be a very important part of the process for setting energy conservation standards. DOE actively encourages the participation and interaction of the public during the comment period in each stage of the rulemaking process. Beginning with the framework document, and during each subsequent public meeting and comment period, interactions with and between members of the public provide a balanced discussion of the issues to assist DOE in the standards rulemaking process. Accordingly, anyone who wishes to participate in the public meeting, receive meeting materials, or be added to the DOE mailing list to receive future notices and information about this rulemaking should contact Ms. Brenda Edwards at (202) 586–2945, or via e-mail at Brenda.Edwards@ee.doe.gov. Issued in Washington, DC, on September 16, 2010. Cathy Zoi, Assistant Secretary, Energy Efficiency and Renewable Energy. [FR Doc. 2010–24288 Filed 9–27–10; 8:45 am] BILLING CODE 6450–01–P PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–0948; Directorate Identifier 2010–CE–041–AD] RIN 2120–AA64 Airworthiness Directives; SOCATA Model TBM 700 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for the products listed above that would supersede an existing AD. This proposed AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: SUMMARY: Following the rupture of an alternator and vapour cycle cooling system pulley drive assembly, the AD 2008–0067–E was published to require the replacement of the pulley drive assembly by a new one of an improved design. Later on, cases of rupture of the alternator and vapour cycle cooling system compressor drive shaft and of cracks on the standbyalternator and compressor support were reportedly found. Such failures could lead to the loss of the alternator and of the vapour cycle cooling systems, and could also cause mechanical damage inside the power plant compartment. To address this condition, the AD 2008– 0129–E superseded AD 2008–0067–E and mandates the removal, as a temporary measure, of the compressor drive belt and of the torque limiter, the conditional replacement of the pulley drive shear shaft, and repetitive inspections for cracks of the pulley drive assembly and of the alternator/ compressor support. The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI. DATES: We must receive comments on this proposed AD by November 12, 2010. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to http://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. E:\FR\FM\28SEP1.SGM 28SEP1 Federal Register / Vol. 75, No. 187 / Tuesday, September 28, 2010 / Proposed Rules • Hand Delivery: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. 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 this proposed AD, 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. FOR FURTHER INFORMATION CONTACT: Albert Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329– 4119; fax: (816) 329–4090. SUPPLEMENTARY INFORMATION: WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS 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–2010–0948; Directorate Identifier 2010–CE–041–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 http:// 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 On September 8, 2008, we issued AD 2008–19–06, Amendment 39–15673 (73 FR 54067; September 18, 2008). That AD required actions intended to address an unsafe condition on the products listed above. Since we issued AD 2008–19–06, a terminating action has been developed through installation of newly designed alternator/compressor support and pulley drive assemblies. The European Aviation Safety Agency (EASA), which is the Technical Agent VerDate Mar<15>2010 15:21 Sep 27, 2010 Jkt 220001 for the Member States of the European Community, has issued EASA AD No.: 2010–0130, dated June 29, 2010, to correct an unsafe condition for the specified products. The MCAI states: Following the rupture of an alternator and vapour cycle cooling system pulley drive assembly, the AD 2008–0067–E was published to require the replacement of the pulley drive assembly by a new one of an improved design. Later on, cases of rupture of the alternator and vapour cycle cooling system compressor drive shaft and of cracks on the standbyalternator and compressor support were reportedly found. Such failures could lead to the loss of the alternator and of the vapour cycle cooling systems, and could also cause mechanical damage inside the power plant compartment. To address this condition, the AD 2008– 0129–E superseded AD 2008–0067–E and mandates the removal, as a temporary measure, of the compressor drive belt and of the torque limiter, the conditional replacement of the pulley drive shear shaft, and repetitive inspections for cracks of the pulley drive assembly and of the alternator/ compressor support. Revision 1 of the AD 2008–0129–E introduced an alternative temporary solution with the aim to restore the capability to make use of the air conditioning system. This solution consists in replacing the original pulley drive assembly by a time-limited assembly of a new design, corresponding to the SOCATA modification MOD 70–0240–21. A definitive solution has been released to production aeroplanes by implementation of SOCATA modification MOD 70–0243–21 or Service Bulleting (SB) 70–176–21 for inservice aeroplanes. This AD which supersedes EASA AD 2008–0129R1–E retaining its requirements, limits the AD applicability and requires accomplishment of the terminating action. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information SOCATA has issued SB 70–176, Amendment 1, dated February 2010. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. FAA’s Determination and Requirements of the Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with this State of Design Authority, they have 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 and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 59659 Differences Between This Proposed AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information. We might also have proposed different actions in this AD from those in the MCAI in order to follow FAA policies. Any such differences are highlighted in a Note within the proposed AD. Costs of Compliance We estimate that this proposed AD will affect 66 products of U.S. registry. We also estimate that it would take about 8 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost about $0 per product. Where the service information lists required parts costs that are covered under warranty, we have assumed that there will be no charge for these costs. As we do not control warranty coverage for affected parties, some parties may incur costs higher than estimated here. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $44,880, or $680 per product. 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 E:\FR\FM\28SEP1.SGM 28SEP1 59660 Federal Register / Vol. 75, No. 187 / Tuesday, September 28, 2010 / Proposed Rules 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:g 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Amendment 39–15673 (73 FR 54067; September 18, 2008), and adding the following new AD: SOCATA: Docket No. FAA–2010–0948; Directorate Identifier 2010–CE–041–AD. Comments Due Date (a) We must receive comments by November 12, 2010. WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS Affected ADs (b) This AD supersedes AD 2008–19–06, Amendment 39–15673. Applicability (c) This AD applies to SOCATA TBM 700 airplanes, serial numbers (S/Ns) 434 through 509, 511 through 516, 519, 520, and 522 through 525, certificated in any category. Subject (d) Air Transport Association of America (ATA) Code 21: Air Conditioning. Reason (e) The mandatory continuing airworthiness information (MCAI) states: VerDate Mar<15>2010 15:21 Sep 27, 2010 Jkt 220001 Following the rupture of an alternator and vapour cycle cooling system pulley drive assembly, the AD 2008–0067–E was published to require the replacement of the pulley drive assembly by a new one of an improved design. Later on, cases of rupture of the alternator and vapour cycle cooling system compressor drive shaft and of cracks on the standbyalternator and compressor support were reportedly found. Such failures could lead to the loss of the alternator and of the vapour cycle cooling systems, and could also cause mechanical damage inside the power plant compartment. To address this condition, the AD 2008– 0129–E superseded AD 2008–0067–E and mandates the removal, as a temporary measure, of the compressor drive belt and of the torque limiter, the conditional replacement of the pulley drive shear shaft, and repetitive inspections for cracks of the pulley drive assembly and of the alternator/ compressor support. Revision 1 of the AD 2008–0129–E introduced an alternative temporary solution with the aim to restore the capability to make use of the air conditioning system. This solution consists in replacing the original pulley drive assembly by a time-limited assembly of a new design, corresponding to the SOCATA modification MOD 70–0240–21. A definitive solution has been released to production aeroplanes by implementation of SOCATA modification MOD 70–0243–21 or Service Bulleting (SB) 70–176–21 for inservice aeroplanes. This AD which supersedes EASA AD 2008–0129R1–E retaining its requirements, limits the AD applicability and requires accomplishment of the terminating action. Actions and Compliance (f) For airplanes S/Ns 434 through 459 only, unless already done, before further flight as of September 18, 2008 (the effective date of AD 2008–19–06), do the following actions following EADS SOCATA Mandatory TBM Aircraft Alert Service Bulletin SB 70– 161, amendment 2, dated July 2008: (1) Remove the pulley drive assembly, the torque limiter, the compressor drive belt, and the alternator/compressor support. (2) Inspect for cracks on the pulley drive surfaces and the alternator/compressor support welds. (i) If any crack is detected, before further flight, replace the pulley drive assembly following the accomplishment instructions in SOCATA Mandatory TBM Aircraft Service Bulletin SB 70–176, amendment 1, dated February 2010. (ii) Replacement of the assembly incorporates replacement of the pulley drive sheer shaft required by paragraph (f)(3) of this AD for airplanes with 30 hours time-inservice (TIS) or more with the torque limiter installed on the pulley drive shear shaft. (3) Replace any pulley drive shear shaft that has accumulated 30 hours TIS or more with the torque limiter installed. This action is not required if you replaced the whole assembly per paragraph (f)(2)(i) of this AD. (4) Re-install the pulley drive assembly and the alternator/compressor support, without re-installing the compressor drive belt or the torque limiter. PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 (5) Insert EADS SOCATA SB 70–161, amendment 2, dated June 2008, in the limitations section of the pilot’s operating handbook and install on the instrument panel and in the pilot’s primary field of vision a placard with the following text: ‘‘AIR COND’’ INOPERATIVE RECOMMENDED ‘‘AIR COND’’ SWITCH POSITION: ‘‘MANUAL’’ and insert EADS SOCATA SB 70–161–21, amendment 2, dated June 2008, in the limitations section of the pilot’s operating handbook. (g) For all S/N airplanes; (1) Within 100 hours TIS after September 18, 2008 (the effective date of AD 2008–19– 06), and repetitively thereafter at intervals not to exceed 100 hours TIS, inspect for cracks on the pulley drive surfaces and the alternator/compressor support welds, following EADS SOCATA Mandatory TBM Aircraft Alert Service Bulletin SB 70–161, amendment 2, dated July 2008. (i) For airplanes S/Ns 434 through 459, the inspection required in paragraph (f)(2) of this AD is considered the initial inspection required in paragraph (g)(1) of this AD. (ii) For accomplishment of the repetitive inspections required by paragraph (g)(1) of this AD, paragraph C.2 of the accomplishment instructions of EADS SOCATA Mandatory TBM Aircraft Alert Service Bulletin SB 70–161, amendment 2, dated July 2008, does not apply since the torque limiter has already been removed. (2) If cracks are found during any of the inspections required in paragraph (g)(1) of this AD, before further flight, replace the assembly following SOCATA Mandatory TBM Aircraft Service Bulletin SB 70–176, amendment 1, dated February 2010. (h) At the next annual inspection or within 5 months after the effective date of this AD, whichever occurs first, replace the alternator/ compressor support and pulley drive assemblies with P/N T700G215500700100 (alternator/compressor support) and P/N T700G215513500000 (Pulley drive assembly), following the accomplishment instructions of SOCATA SB 70–176, amendment 1, dated February 2010. (1) After the effective date of this AD, do not install alternator/compressor support P/N T700G215500700000 and a pulley drive assembly P/N T700G215510000000. (2) Accomplishment of corrective actions as required by paragraph (f)(2)(i), paragraph (g)(2), or paragraph (h) of this AD terminates the actions required in paragraphs (f) and (g) of this AD. Note 2: SOCATA SB 70–161–21 amendment 4, dated October 2009, has been published by SOCATA in order to close the range of airplane S/Ns concerned by temporary actions. FAA AD Differences Note 3: This AD differs from the MCAI and/or service information as follows: No differences. Other FAA AD Provisions (i) The following provisions also apply to this AD: E:\FR\FM\28SEP1.SGM 28SEP1 Federal Register / Vol. 75, No. 187 / Tuesday, September 28, 2010 / Proposed Rules (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: Albert Mercado, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4119; 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 FAAapproved if they are approved by the State of Design Authority (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. Special Flight Permit (j) We are allowing permission to ferry an airplane to a maintenance location to accomplish actions required by paragraph (1) of this AD provided that the air conditioning is switched off during the entire flight duration. Related Information (k) Refer to MCAI EASA AD No.: 2010– 0130, dated June 29, 2010; and SOCATA Service Bulletin SB 70–176, amendment 1, dated February 2010, for related information. Issued in Kansas City, Missouri, on September 22, 2010. Patrick R. Mullen, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010–24248 Filed 9–27–10; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 187 WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS [Docket No. FAA–2010–0326; Notice No. 10– 12] RIN 2120–AJ68 Update of Overflight Fees Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: This NPRM proposes to adjust existing Overflight Fees by using current SUMMARY: VerDate Mar<15>2010 15:21 Sep 27, 2010 Jkt 220001 FAA cost accounting data and air traffic activity data. This action is necessary because operational costs for providing air traffic control and related services for Overflights have increased steadily since the fees were established in 2001. The adjustment of Overflight Fees would result in an increased level of cost recovery for the services being provided. Send your comments on or before December 27, 2010. ADDRESSES: You may send comments identified by Docket Number FAA– 2010–0326 using any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov and follow the online instructions for sending your comments electronically. • Mail: Send comments to Docket Operations, M–30; U.S. Department of Transportation, 1200 New Jersey Avenue, SE., Room W12–140, West Building Ground Floor, Washington, DC 20590–0001. • Hand Delivery or Courier: Take comments to Docket Operations in Room W12–140 of the West Building Ground Floor at 1200 New Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. • Fax: Fax comments to Docket Operations at 202–493–2251. For more information on the rulemaking process, see the SUPPLEMENTARY INFORMATION section of this document. Privacy: We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. Using the search function of our docket web site, anyone can find and read the electronic form of all comments received into any of our dockets, including the name of the individual sending the comment (or signing the comment for an association, business, labor union, etc.). You may review DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78) or you may visit http://DocketsInfo.dot.gov. Docket: To read background documents or comments received, go to http://www.regulations.gov at any time and follow the online instructions for accessing the docket, or, go to Docket Operations in Room W12–140 of the West Building Ground Floor at 1200 New Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. FOR FURTHER INFORMATION CONTACT: For technical questions concerning this proposed rule contact David Lawhead, DATES: PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 59661 Office of Financial Controls, Financial Analysis Division (AFC 300), Federal Aviation Administration, 800 Independence Avenue, SW., Washington, DC 20591; telephone (202) 267–9759 facsimile (202) 267–5271, e-mail to Dave.Lawhead@FAA.gov. For legal questions concerning this proposed rule contact Michael Chase, AGC–240, Office of Chief Counsel, Regulations Division, Federal Aviation Administration, 800 Independence Avenue, SW., Washington, DC 20591; telephone: (202) 267–3110; e-mail to michael.chase@faa.gov. Later in this preamble under the Additional Information section, we discuss how you can comment on this proposal and how we will handle your comments. Included in this discussion is related information about the docket, privacy, and the handling of proprietary or confidential business information. We also discuss how you can get a copy of related rulemaking documents. SUPPLEMENTARY INFORMATION: Authority for This Rulemaking The FAA’s authority to establish these fees is found in Title 49 of the United States Code. This rulemaking is promulgated under the authority described in Chapter 453, Section 45301 et seq. Under that Chapter, the FAA is charged with prescribing regulations for the collection of fees for air traffic control and related services provided to aircraft, other than military and civilian aircraft of the United States government or a foreign government, that transit U.S.-controlled airspace, but neither take off from nor land in the United States (‘‘Overflights’’). This proposed regulation is within the scope of that authority. I. Background The FAA’s Overflight Fees were initially authorized in the Federal Aviation Reauthorization Act of 1996 (Pub. L. 104–264, enacted October 9, 1996). Overflight Fees are charges for aircraft flights that transit U.S.controlled airspace, but neither land in nor depart from the United States. Following enactment of the initial fee authority, and as mandated by that authority, the FAA issued an Interim Final Rule (IFR), ‘‘Fees for Air Traffic Services for Certain Flights through U.S. Controlled Airspace’’ (62 FR 13496), on March 20, 1997. Under the terms of the IFR, the FAA sought public comment on the IFR while concurrently beginning to assess Overflight Fees 60 days after its publication, on May 19, 1997. On July 17, 1997, petitions for judicial review of the IFR were filed in the U.S. E:\FR\FM\28SEP1.SGM 28SEP1

Agencies

[Federal Register Volume 75, Number 187 (Tuesday, September 28, 2010)]
[Proposed Rules]
[Pages 59658-59661]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-24248]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0948; Directorate Identifier 2010-CE-041-AD]
RIN 2120-AA64


Airworthiness Directives; SOCATA Model TBM 700 Airplanes

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

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
products listed above that would supersede an existing AD. This 
proposed AD results from mandatory continuing airworthiness information 
(MCAI) originated by an aviation authority of another country to 
identify and correct an unsafe condition on an aviation product. The 
MCAI describes the unsafe condition as:

    Following the rupture of an alternator and vapour cycle cooling 
system pulley drive assembly, the AD 2008-0067-E was published to 
require the replacement of the pulley drive assembly by a new one of 
an improved design.
    Later on, cases of rupture of the alternator and vapour cycle 
cooling system compressor drive shaft and of cracks on the standby-
alternator and compressor support were reportedly found.
    Such failures could lead to the loss of the alternator and of 
the vapour cycle cooling systems, and could also cause mechanical 
damage inside the power plant compartment.
    To address this condition, the AD 2008-0129-E superseded AD 
2008-0067-E and mandates the removal, as a temporary measure, of the 
compressor drive belt and of the torque limiter, the conditional 
replacement of the pulley drive shear shaft, and repetitive 
inspections for cracks of the pulley drive assembly and of the 
alternator/compressor support.

The proposed AD would require actions that are intended to address the 
unsafe condition described in the MCAI.

DATES: We must receive comments on this proposed AD by November 12, 
2010.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://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.

[[Page 59659]]

     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.

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 this proposed AD, 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.

FOR FURTHER INFORMATION CONTACT: Albert Mercado, Aerospace Engineer, 
FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, 
Missouri 64106; telephone: (816) 329-4119; fax: (816) 329-4090.

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-2010-0948; 
Directorate Identifier 2010-CE-041-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 http://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

    On September 8, 2008, we issued AD 2008-19-06, Amendment 39-15673 
(73 FR 54067; September 18, 2008). That AD required actions intended to 
address an unsafe condition on the products listed above.
    Since we issued AD 2008-19-06, a terminating action has been 
developed through installation of newly designed alternator/compressor 
support and pulley drive assemblies.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
AD No.: 2010-0130, dated June 29, 2010, to correct an unsafe condition 
for the specified products. The MCAI states:

    Following the rupture of an alternator and vapour cycle cooling 
system pulley drive assembly, the AD 2008-0067-E was published to 
require the replacement of the pulley drive assembly by a new one of 
an improved design.
    Later on, cases of rupture of the alternator and vapour cycle 
cooling system compressor drive shaft and of cracks on the standby-
alternator and compressor support were reportedly found.
    Such failures could lead to the loss of the alternator and of 
the vapour cycle cooling systems, and could also cause mechanical 
damage inside the power plant compartment.
    To address this condition, the AD 2008-0129-E superseded AD 
2008-0067-E and mandates the removal, as a temporary measure, of the 
compressor drive belt and of the torque limiter, the conditional 
replacement of the pulley drive shear shaft, and repetitive 
inspections for cracks of the pulley drive assembly and of the 
alternator/compressor support.
    Revision 1 of the AD 2008-0129-E introduced an alternative 
temporary solution with the aim to restore the capability to make 
use of the air conditioning system. This solution consists in 
replacing the original pulley drive assembly by a time-limited 
assembly of a new design, corresponding to the SOCATA modification 
MOD 70-0240-21.
    A definitive solution has been released to production aeroplanes 
by implementation of SOCATA modification MOD 70-0243-21 or Service 
Bulleting (SB) 70-176-21 for in-service aeroplanes.
    This AD which supersedes EASA AD 2008-0129R1-E retaining its 
requirements, limits the AD applicability and requires 
accomplishment of the terminating action.

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

Relevant Service Information

    SOCATA has issued SB 70-176, Amendment 1, dated February 2010. The 
actions described in this service information are intended to correct 
the unsafe condition identified in the MCAI.

FAA's Determination and Requirements of the Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with this State of Design Authority, they 
have 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 and determined the unsafe condition exists 
and is likely to exist or develop on other products of the same type 
design.

Differences Between This Proposed AD and the MCAI or Service 
Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we might have found it 
necessary to use different words from those in the MCAI to ensure the 
AD is clear for U.S. operators and is enforceable. In making these 
changes, we do not intend to differ substantively from the information 
provided in the MCAI and related service information.
    We might also have proposed different actions in this AD from those 
in the MCAI in order to follow FAA policies. Any such differences are 
highlighted in a Note within the proposed AD.

Costs of Compliance

    We estimate that this proposed AD will affect 66 products of U.S. 
registry. We also estimate that it would take about 8 work-hours per 
product to comply with the basic requirements of this proposed AD. The 
average labor rate is $85 per work-hour. Required parts would cost 
about $0 per product. Where the service information lists required 
parts costs that are covered under warranty, we have assumed that there 
will be no charge for these costs. As we do not control warranty 
coverage for affected parties, some parties may incur costs higher than 
estimated here.
    Based on these figures, we estimate the cost of the proposed AD on 
U.S. operators to be $44,880, or $680 per product.

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

[[Page 59660]]

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:g
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by removing Amendment 39-15673 (73 FR 
54067; September 18, 2008), and adding the following new AD:

SOCATA: Docket No. FAA-2010-0948; Directorate Identifier 2010-CE-
041-AD.

Comments Due Date

    (a) We must receive comments by November 12, 2010.

Affected ADs

    (b) This AD supersedes AD 2008-19-06, Amendment 39-15673.

Applicability

    (c) This AD applies to SOCATA TBM 700 airplanes, serial numbers 
(S/Ns) 434 through 509, 511 through 516, 519, 520, and 522 through 
525, certificated in any category.

Subject

    (d) Air Transport Association of America (ATA) Code 21: Air 
Conditioning.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:

    Following the rupture of an alternator and vapour cycle cooling 
system pulley drive assembly, the AD 2008-0067-E was published to 
require the replacement of the pulley drive assembly by a new one of 
an improved design.
    Later on, cases of rupture of the alternator and vapour cycle 
cooling system compressor drive shaft and of cracks on the standby-
alternator and compressor support were reportedly found.
    Such failures could lead to the loss of the alternator and of 
the vapour cycle cooling systems, and could also cause mechanical 
damage inside the power plant compartment.
    To address this condition, the AD 2008-0129-E superseded AD 
2008-0067-E and mandates the removal, as a temporary measure, of the 
compressor drive belt and of the torque limiter, the conditional 
replacement of the pulley drive shear shaft, and repetitive 
inspections for cracks of the pulley drive assembly and of the 
alternator/compressor support.
    Revision 1 of the AD 2008-0129-E introduced an alternative 
temporary solution with the aim to restore the capability to make 
use of the air conditioning system. This solution consists in 
replacing the original pulley drive assembly by a time-limited 
assembly of a new design, corresponding to the SOCATA modification 
MOD 70-0240-21.
    A definitive solution has been released to production aeroplanes 
by implementation of SOCATA modification MOD 70-0243-21 or Service 
Bulleting (SB) 70-176-21 for in-service aeroplanes.
    This AD which supersedes EASA AD 2008-0129R1-E retaining its 
requirements, limits the AD applicability and requires 
accomplishment of the terminating action.

Actions and Compliance

    (f) For airplanes S/Ns 434 through 459 only, unless already 
done, before further flight as of September 18, 2008 (the effective 
date of AD 2008-19-06), do the following actions following EADS 
SOCATA Mandatory TBM Aircraft Alert Service Bulletin SB 70-161, 
amendment 2, dated July 2008:
    (1) Remove the pulley drive assembly, the torque limiter, the 
compressor drive belt, and the alternator/compressor support.
    (2) Inspect for cracks on the pulley drive surfaces and the 
alternator/compressor support welds.
    (i) If any crack is detected, before further flight, replace the 
pulley drive assembly following the accomplishment instructions in 
SOCATA Mandatory TBM Aircraft Service Bulletin SB 70-176, amendment 
1, dated February 2010.
    (ii) Replacement of the assembly incorporates replacement of the 
pulley drive sheer shaft required by paragraph (f)(3) of this AD for 
airplanes with 30 hours time-in-service (TIS) or more with the 
torque limiter installed on the pulley drive shear shaft.
    (3) Replace any pulley drive shear shaft that has accumulated 30 
hours TIS or more with the torque limiter installed. This action is 
not required if you replaced the whole assembly per paragraph 
(f)(2)(i) of this AD.
    (4) Re-install the pulley drive assembly and the alternator/
compressor support, without re-installing the compressor drive belt 
or the torque limiter.
    (5) Insert EADS SOCATA SB 70-161, amendment 2, dated June 2008, 
in the limitations section of the pilot's operating handbook and 
install on the instrument panel and in the pilot's primary field of 
vision a placard with the following text:

``AIR COND'' INOPERATIVE

RECOMMENDED ``AIR COND'' SWITCH POSITION: ``MANUAL''

and insert EADS SOCATA SB 70-161-21, amendment 2, dated June 2008, 
in the limitations section of the pilot's operating handbook.
    (g) For all S/N airplanes;
    (1) Within 100 hours TIS after September 18, 2008 (the effective 
date of AD 2008-19-06), and repetitively thereafter at intervals not 
to exceed 100 hours TIS, inspect for cracks on the pulley drive 
surfaces and the alternator/compressor support welds, following EADS 
SOCATA Mandatory TBM Aircraft Alert Service Bulletin SB 70-161, 
amendment 2, dated July 2008.
    (i) For airplanes S/Ns 434 through 459, the inspection required 
in paragraph (f)(2) of this AD is considered the initial inspection 
required in paragraph (g)(1) of this AD.
    (ii) For accomplishment of the repetitive inspections required 
by paragraph (g)(1) of this AD, paragraph C.2 of the accomplishment 
instructions of EADS SOCATA Mandatory TBM Aircraft Alert Service 
Bulletin SB 70-161, amendment 2, dated July 2008, does not apply 
since the torque limiter has already been removed.
    (2) If cracks are found during any of the inspections required 
in paragraph (g)(1) of this AD, before further flight, replace the 
assembly following SOCATA Mandatory TBM Aircraft Service Bulletin SB 
70-176, amendment 1, dated February 2010.
    (h) At the next annual inspection or within 5 months after the 
effective date of this AD, whichever occurs first, replace the 
alternator/compressor support and pulley drive assemblies with P/N 
T700G215500700100 (alternator/compressor support) and P/N 
T700G215513500000 (Pulley drive assembly), following the 
accomplishment instructions of SOCATA SB 70-176, amendment 1, dated 
February 2010.
    (1) After the effective date of this AD, do not install 
alternator/compressor support P/N T700G215500700000 and a pulley 
drive assembly P/N T700G215510000000.
    (2) Accomplishment of corrective actions as required by 
paragraph (f)(2)(i), paragraph (g)(2), or paragraph (h) of this AD 
terminates the actions required in paragraphs (f) and (g) of this 
AD.

    Note 2: SOCATA SB 70-161-21 amendment 4, dated October 2009, has 
been published by SOCATA in order to close the range of airplane S/
Ns concerned by temporary actions.

FAA AD Differences

    Note 3: This AD differs from the MCAI and/or service information 
as follows: No differences.

Other FAA AD Provisions

    (i) The following provisions also apply to this AD:

[[Page 59661]]

    (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: Albert Mercado, Aerospace Engineer, FAA, Small 
Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 
64106; telephone: (816) 329-4119; 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 
(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.

Special Flight Permit

    (j) We are allowing permission to ferry an airplane to a 
maintenance location to accomplish actions required by paragraph (1) 
of this AD provided that the air conditioning is switched off during 
the entire flight duration.

Related Information

    (k) Refer to MCAI EASA AD No.: 2010-0130, dated June 29, 2010; 
and SOCATA Service Bulletin SB 70-176, amendment 1, dated February 
2010, for related information.

    Issued in Kansas City, Missouri, on September 22, 2010.
Patrick R. Mullen,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-24248 Filed 9-27-10; 8:45 am]
BILLING CODE 4910-13-P