Airworthiness Directives; Airbus Model A330-300, A340-200, and A340-300 Series Airplanes, 2284-2287 [2011-586]

Download as PDF 2284 Federal Register / Vol. 76, No. 9 / Thursday, January 13, 2011 / Proposed Rules Inspection Service Bulletin ISB.53–167, including Appendix 2, Revision 4, dated June 10, 2010: Within 4,600 flight cycles after the last inspection done in accordance with paragraph (g) of this AD. (l) If any cracking is found during any inspection required by paragraph (j) or (k) of this AD, before further flight, accomplish the repair in accordance with a method approved by the FAA or EASA (or its delegated agent). Repair of an airplane in accordance with the requirements of this paragraph of this AD does not constitute terminating action for the inspection requirements of this AD. Credit for Actions Accomplished in Accordance With Previous Service Information (m) Inspections done before the effective date of this AD in accordance with BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53–167, including Appendix 2, Revision 2, dated November 17, 2008; or Revision 3, dated June 17, 2009; are acceptable for compliance with the corresponding requirements of paragraphs (j) and (k) of this AD. FAA AD Differences srobinson on DSKHWCL6B1PROD with PROPOSALS Issued in Renton, Washington, on January 5, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. BILLING CODE 4910–13–P Other FAA AD Provisions (n) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, 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: Todd Thompson, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1175; fax (425) 227–1149. 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. (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: A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120–0056. Public reporting for this collection of information is estimated to 18:03 Jan 12, 2011 Related Information (o) Refer to MCAI EASA Airworthiness Directive 2009–0070R1, dated July 2, 2010; and BAE Systems (Operations) Limited Modification Service Bulletin ISB.53–167, including Appendix 2, Revision 1, dated May 18, 2004; and BAE Systems (Operations) Limited Inspection Service Bulletin ISB.53– 167, including Appendix 2, Revision 4, dated June 10, 2010; for related information. [FR Doc. 2011–585 Filed 1–12–11; 8:45 am] Note 1: This AD differs from the MCAI and/or service information as follows: No differences. VerDate Mar<15>2010 be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave., SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES–200. Jkt 223001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–1309; Directorate Identifier 2010–NM–060–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A330–300, A340–200, and A340–300 Series Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for the products listed above. 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: Surface defects were visually detected on the rudder of one Airbus A319 and one A321 in-service aeroplane. Investigation has determined that the defects reported on both rudders corresponded to areas that had been reworked in production. The investigation confirmed that the defects were the result of de-bonding between the skin and honeycomb core. Such reworks were also performed on some rudders fitted on A330–300 and A340– 200/–300 aeroplanes. An extended de-bonding, if not detected and corrected, may degrade the structural PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 integrity of the rudder. The loss of the rudder leads to degradation of the handling qualities and reduces the controllability of the aeroplane. * * * * ** * 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 February 28, 2011. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–40, 1200 New Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Airbus SAS— Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone + 33 5 61 93 36 96; fax + 33 5 61 93 45 80, e-mail airworthiness.A330–A340@airbus.com; Internet https://www.airbus.com. You may review copies of the referenced 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. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone (425) 227–1138; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: E:\FR\FM\13JAP1.SGM 13JAP1 Federal Register / Vol. 76, No. 9 / Thursday, January 13, 2011 / Proposed Rules 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–2010–1309; Directorate Identifier 2010–NM–060–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. srobinson on DSKHWCL6B1PROD with PROPOSALS Discussion The European Aviation Safety Agency (EASA), which is the aviation authority for the Member States of the European Community, has issued EASA Airworthiness Directive 2010–0021, dated February 9, 2010 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: Surface defects were visually detected on the rudder of one Airbus A319 and one A321 in-service aeroplane. Investigation has determined that the defects reported on both rudders corresponded to areas that had been reworked in production. The investigation confirmed that the defects were the result of de-bonding between the skin and honeycomb core. Such reworks were also performed on some rudders fitted on A330–300 and A340– 200/–300 aeroplanes. An extended de-bonding, if not detected and corrected, may degrade the structural integrity of the rudder. The loss of the rudder leads to degradation of the handling qualities and reduces the controllability of the aeroplane. EASA AD 2009–0156 required inspections of specific areas and, depending on findings, the application of corrective actions for those rudders where production reworks have been identified. This AD retains the requirements of EASA AD 2009–0156, which is superseded, and in addition requires for the vacuum loss hole restoration: —a local ultrasonic inspection for reinforced area instead of the local thermography inspection, which is maintained for nonreinforced areas, and — an additional work for aeroplanes on which this thermography inspection has been performed in the reinforced area. The inspections include vacuum loss inspections and repetitive elasticity laminate checker inspections for defects including de-bonding between the skin and honeycomb core of the rudder, and VerDate Mar<15>2010 18:03 Jan 12, 2011 Jkt 223001 ultrasonic inspections for defects on rudders on which temporary restoration with resin or permanent vacuum loss hole restoration has been performed. The corrective action is repair, if necessary. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information Airbus has issued All Operators Telexes (AOTs) A330–55A3040 and A340–55A4036, both Revision 02, both dated September 30, 2009. 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 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 the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design. 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 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 Currently, there are no affected airplanes on the U.S. Register. However, if an affected airplane is imported and placed on the U.S. Register in the future, the required actions would take about 21 work hours, at an average labor rate of $85 per work hour. Based on these figures, we estimate the cost of this AD to be $1,785 per airplane. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue PO 00000 Frm 00018 Fmt 4702 Sfmt 4702 2285 rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, part A, subpart III, section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. E:\FR\FM\13JAP1.SGM 13JAP1 2286 Federal Register / Vol. 76, No. 9 / Thursday, January 13, 2011 / Proposed Rules § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: Airbus: Docket No. FAA–2010–1309; Directorate Identifier 2010–NM–060–AD. Comments Due Date (a) We must receive comments by February 28, 2011. Affected ADs (b) None. Applicability (c) This AD applies to Airbus Model A330– 301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes, Model A340–211, –212, and –213 airplanes; and Model A340– 311, –312, and –313 airplanes; all manufacturer serial numbers; certificated in any category; equipped with carbon fiber reinforced plastic rudders having part numbers and serial numbers listed in Table 1 of this AD. Subject (d) Air Transport Association (ATA) of America Code 55: Stabilizers. Reason (e) The mandatory continuing airworthiness information (MCAI) states: Surface defects were visually detected on the rudder of one Airbus A319 and one A321 in-service aeroplane. Investigation has determined that the defects reported on both rudders corresponded to areas that had been reworked in production. The investigation confirmed that the defects were the result of de-bonding between the skin and honeycomb core. Such reworks were also performed on some rudders fitted on A330–300 and A340– 200/–300 aeroplanes. An extended de-bonding, if not detected and corrected, may degrade the structural integrity of the rudder. The loss of the rudder leads to degradation of the handling qualities and reduces the controllability of the aeroplane. * TABLE 1—AFFECTED RUDDERS srobinson on DSKHWCL6B1PROD with PROPOSALS Rudder part number F554–70000–000–00 F554–70000–000–00 F554–70000–000–00 F554–70000–000–00 F554–70000–000–00 F554–70000–000–00 F554–70000–000–00 F554–70000–000–00 F554–70000–000–00 F554–70000–000–00 F554–70000–000–00 F554–70000–000–00 F554–70000–000–00 F554–70000–000–00 F554–70000–000–00 F554–70000–000–00 F554–70000–000–00 F554–70000–000–00 F554–70000–000–00 F554–70000–000–00 F554–70000–000–00 F554–70000–002–00 F554–71000–000–00 F554–71000–000–00 F554–71000–000–00 F554–71000–000–00 F554–71000–000–00 F554–71000–000–00 F554–71000–000–00 F554–71000–000–00 F554–71000–000–00 F554–71000–000–00 F554–71000–000–00 F554–71000–000–00 F554–71000–000–00 F554–71000–000–00 F554–71000–000–00 F554–71000–000–00 F554–71000–000–00 F554–71000–000–00 F554–70005–000–00 F554–70005–000–00 F554–70005–000–00 F554–70005–000–00 F554–70005–000–00 VerDate Mar<15>2010 Rudder serial number ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... ...... 18:03 Jan 12, 2011 TS–2013 TS–2015 TS–2016 TS–2017 TS–2018 TS–2020 TS–2021 TS–2024 TS–2026 TS–2035 TS–2036 TS–2040 TS–2042 TS–2055 TS–2056 TS–2058 TS–2059 TS–2061 TS–2062 TS–2063 TS–2065 TS–2074 TS–3003 TS–3004 TS–3005 TS–3006 TS–3007 TS–3008 TS–3011 TS–3015 TS–3033 TS–3061 TS–3064 TS–3066 TS–3071 TS–3072 TS–3075 TS–3079 TS–3084 TS–3087 TS–3100 TS–3106 TS–3107 TS–3119 TS–3124 Jkt 223001 * * * * Compliance (f) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Actions (g) Do the actions required by paragraphs (g)(1) through (g)(8) of this AD, in accordance with the Instructions of Airbus All Operators Telex (AOT) A330–55A3040 or A340– 55A4036, both Revision 02, both dated September 30, 2009, as applicable. (1) In the reinforced location of the rudder: Within 1,800 flight hours after the rudder has accumulated 13,000 total flight cycles since first installation, or within 1,800 flight hours after the effective date of this AD, whichever is later, do a vacuum loss inspection to detect defects, including de-bonding between the skin and honeycomb core of the rudder. (2) In the trailing edge location of the rudder: Within 21 months after the rudder has accumulated 13,000 total flight cycles since first installation, or within 21 months after the effective date of this AD, whichever is later, do an elasticity laminate checker inspection to detect defects, including debonding between the skin and honeycomb core of the rudder. If no defects are found, repeat the inspection two times at intervals not to exceed 4,500 flight cycles, but not fewer than 4,000 flight cycles from the most recent inspection. (3) In locations other than those identified in paragraphs (g)(1) and (g)(2) of this AD (e.g., lower rib, upper edge, leading edge, and other locations): Within 1,800 flight hours after the rudder has accumulated 13,000 total flight cycles since first installation, or within 1,800 flight hours after the effective date of this AD, whichever is later, do an elasticity laminate checker inspection to detect defects, including de-bonding between the skin and honeycomb core of the rudder. Repeat the inspection thereafter at intervals not to exceed 1,800 flight hours. (4) If no defects are found during any inspection required by paragraph (g)(3) of this AD: Within 21 months after the rudder PO 00000 Frm 00019 Fmt 4702 Sfmt 4702 has accumulated 13,000 total flight cycles since first installation, or within 21 months after the effective date of this AD, whichever is later, do a vacuum loss inspection on the other locations (e.g., lower rib, upper edge, leading edge, and other locations) to detect defects, including de-bonding between the skin and honeycomb core of the rudder. (5) Accomplishment of the inspection required by paragraph (g)(4) of this AD terminates the initial and repetitive inspections required by paragraph (g)(3) of this AD. (6) If any defect is found during any inspection required by this AD, before further flight, repair using a method approved by either the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency Airworthiness (EASA) (or its delegated agent). (7) If no defects are found during any inspection required by paragraphs (g)(1) and (g)(4) of this AD, before further flight, restore the vacuum loss holes by doing a temporary restoration with self-adhesive patches, a temporary restoration with resin, or a permanent restoration. Do the applicable actions specified in paragraph (g)(7)(i) or (g)(7)(ii) of this AD. (i) For airplanes on which a temporary restoration with patch is done: Within 900 flight hours after the restoration, do a detailed inspection for defects of the restored area and repeat the inspection thereafter at intervals not to exceed 900 flight hours until the permanent restoration is done. Do the permanent restoration within 21 months after the temporary restoration. (ii) For airplanes on which a temporary restoration with resin is done: Within 21 months after doing the temporary restoration, do the permanent restoration. (8) If any defect is found during any initial inspection required by paragraphs (g)(1), (g)(3), and (g)(4) of this AD, at the applicable time in paragraph (g)(8)(i) or (g)(8)(ii) of this AD: Report the inspection results to Airbus SAS, SEER1/SEER2/SEER3, Customer Services, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; fax +33 (0) 5 61 93 28 73; or e-mail to region1.StructureRepairSupport@airbus.com, region2.StructureRepairSupport@airbus.com, or region3.StructureRepairSupport@airbus.com. (i) Inspections done before the effective date of this AD: Within 30 days after the effective date of this AD. (ii) Inspections done on or after the effective date of this AD: Within 30 days after accomplishment of the inspection. Credit for Actions Accomplished in Accordance With Previous Service Information (h) Actions accomplished before the effective date of this AD in accordance with the service information identified in Table 2 of this AD, are considered acceptable for compliance with the corresponding actions specified in paragraphs (g)(1) through (g)(5) and paragraph (g)(7) of this AD for only the areas inspected. For all areas, the repetitive inspections required by this AD remain applicable. E:\FR\FM\13JAP1.SGM 13JAP1 2287 Federal Register / Vol. 76, No. 9 / Thursday, January 13, 2011 / Proposed Rules TABLE 2—CREDIT SERVICE INFORMATION Document Airbus Airbus Airbus Airbus AOT AOT AOT AOT A330–55A3040 A330–55A3040 A340–55A4036 A340–55A4036 ....................................................................................... ....................................................................................... ....................................................................................... ....................................................................................... (i) For rudders on which temporary vacuum loss hole restoration with resin or permanent vacuum loss hole restoration has been done, as required by paragraph (g)(7) of this AD, in accordance with the applicable AOT in Table 2 of this AD before the effective date of this AD: Within 21 months after the restoration date, or within 3 months after the effective date of this AD, whichever occurs later, do an ultrasonic inspection for defects, including debonding of the reinforced area, in accordance with the Accomplishment Instructions of Airbus AOT A330–55A3040 or A340–55A4036, both Revision 02, both dated September 30, 2009, as applicable. If any defect is found, before further flight, repair using a method approved by either the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the EASA (or its delegated agent). (j) As of the effective date of this AD, no person may install any rudder identified in Table 1 of this AD on any airplane, unless the rudder has been inspected and all applicable corrective actions have been done in accordance with paragraph (g) or (i) of this AD, as applicable. FAA AD Differences srobinson on DSKHWCL6B1PROD with PROPOSALS Note 1: This AD differs from the MCAI and/or service information as follows: No differences. Other FAA AD Provisions (k) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, 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: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1138; fax (425) 227–1149. 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. (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. VerDate Mar<15>2010 Revision 18:03 Jan 12, 2011 Jkt 223001 Original .................................................... 01 ............................................................. Original .................................................... 01 ............................................................. (3) Reporting Requirements: A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120–0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave., SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES–200. Related Information (l) Refer to MCAI EASA Airworthiness Directive 2010–0021, dated February 9, 2010; and Airbus AOTs A330–55A3040 and A340– 55A4036, both Revision 02, both dated September 30, 2009; for related information. Date May 27, 2009. July 8, 2009. May 27, 2009. July 8, 2009. 165 See Public Law 111–203 (adding Exchange Act Section 13(n)(5)(D)(i)). [FR Doc. C2–2010–29719 Filed 1–12–11; 8:45 am] BILLING CODE 8011–01–P DEPARTMENT OF JUSTICE Drug Enforcement Administration 21 CFR Part 1308 [Docket No. DEA–345C] Schedules of Controlled Substances: Temporary Placement of Five Synthetic Cannabinoids Into Schedule I; Correction Drug Enforcement Administration (DEA), U.S. Department of Justice. ACTION: Notice of Intent; correction. AGENCY: Issued in Renton, Washington, on January 5, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. On November 24, 2010, the Drug Enforcement Administration (DEA) published a Notice of Intent announcing its intention to temporarily place five synthetic cannabinoids into Schedule I of the Controlled Substances Act. This notice corrects two administrative errors made in that document. [FR Doc. 2011–586 Filed 1–12–11; 8:45 am] FOR FURTHER INFORMATION CONTACT: BILLING CODE 4910–13–P Christine A. Sannerud, PhD, Chief, Drug and Chemical Evaluation Section, Office of Diversion Control, Drug Enforcement Administration, 8701 Morrissette Drive, Springfield, VA 22152, telephone (202) 307–7183, fax (202) 353–1263, or e-mail ode@dea.usdoj.gov. SUPPLEMENTARY INFORMATION: In a November 24, 2010, Notice of Intent published in the Federal Register (75 FR 71635), DEA announced its intention to temporarily place five synthetic cannabinoids into schedule I of the Controlled Substances Act (CSA) pursuant to 21 U.S.C. 811(h). Due to an administrative error, DEA included in that notice a paragraph addressing the Regulatory Flexibility Act (RFA) in the ‘‘Regulatory Certifications’’ section of that document. The provisions of the RFA have no application to temporary scheduling orders issued under 21 U.S.C. 811(h) or to notices of intention to issue such orders. Accordingly, DEA certification under the RFA is not SECURITIES AND EXCHANGE COMMISSION 17 CFR Parts 240 and 249 [Release No. 34–63347; File No. S7–35–10] RIN 3235–AK79 Security-Based Swap Data Repository Registration, Duties, and Core Principles; Correction Correction In proposed rule document C1–2010– 29719 beginning on page 79320 in the issue of December 20, 2010, make the following correction: On page 79320, in the second column, in instruction 5, footnote 165 is corrected to read as follows: PO 00000 Frm 00020 Fmt 4702 Sfmt 4702 SUMMARY: E:\FR\FM\13JAP1.SGM 13JAP1

Agencies

[Federal Register Volume 76, Number 9 (Thursday, January 13, 2011)]
[Proposed Rules]
[Pages 2284-2287]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-586]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-1309; Directorate Identifier 2010-NM-060-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus Model A330-300, A340-200, and
A340-300 Series Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above. This proposed AD results from mandatory
continuing airworthiness information (MCAI) 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:

Surface defects were visually detected on the rudder of one
Airbus A319 and one A321 in-service aeroplane. Investigation has
determined that the defects reported on both rudders corresponded to
areas that had been reworked in production. The investigation
confirmed that the defects were the result of de-bonding between the
skin and honeycomb core. Such reworks were also performed on some
rudders fitted on A330-300 and A340-200/-300 aeroplanes.
An extended de-bonding, if not detected and corrected, may
degrade the structural integrity of the rudder. The loss of the
rudder leads to degradation of the handling qualities and reduces
the controllability of the aeroplane.
* * * * ** *
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 February 28,
2011.

ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-40, 1200 New
Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone + 33 5 61 93 36 96; fax + 33 5
61 93 45 80, e-mail airworthiness.A330-A340@airbus.com; Internet https://www.airbus.com. You may review copies of the referenced 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.

Examining the AD Docket

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

FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425)
227-1138; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

[[Page 2285]]

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-2010-1309;
Directorate Identifier 2010-NM-060-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.

Discussion

The European Aviation Safety Agency (EASA), which is the aviation
authority for the Member States of the European Community, has issued
EASA Airworthiness Directive 2010-0021, dated February 9, 2010
(referred to after this as ``the MCAI''), to correct an unsafe
condition for the specified products. The MCAI states:

Surface defects were visually detected on the rudder of one
Airbus A319 and one A321 in-service aeroplane. Investigation has
determined that the defects reported on both rudders corresponded to
areas that had been reworked in production. The investigation
confirmed that the defects were the result of de-bonding between the
skin and honeycomb core. Such reworks were also performed on some
rudders fitted on A330-300 and A340-200/-300 aeroplanes.
An extended de-bonding, if not detected and corrected, may
degrade the structural integrity of the rudder. The loss of the
rudder leads to degradation of the handling qualities and reduces
the controllability of the aeroplane.
EASA AD 2009-0156 required inspections of specific areas and,
depending on findings, the application of corrective actions for
those rudders where production reworks have been identified.
This AD retains the requirements of EASA AD 2009-0156, which is
superseded, and in addition requires for the vacuum loss hole
restoration:

--a local ultrasonic inspection for reinforced area instead of the
local thermography inspection, which is maintained for non-
reinforced areas, and
-- an additional work for aeroplanes on which this thermography
inspection has been performed in the reinforced area.

The inspections include vacuum loss inspections and repetitive
elasticity laminate checker inspections for defects including de-
bonding between the skin and honeycomb core of the rudder, and
ultrasonic inspections for defects on rudders on which temporary
restoration with resin or permanent vacuum loss hole restoration has
been performed. The corrective action is repair, if necessary. You may
obtain further information by examining the MCAI in the AD docket.

Relevant Service Information

Airbus has issued All Operators Telexes (AOTs) A330-55A3040 and
A340-55A4036, both Revision 02, both dated September 30, 2009. 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 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 the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.

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 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

Currently, there are no affected airplanes on the U.S. Register.
However, if an affected airplane is imported and placed on the U.S.
Register in the future, the required actions would take about 21 work
hours, at an average labor rate of $85 per work hour. Based on these
figures, we estimate the cost of this AD to be $1,785 per airplane.

Authority for This Rulemaking

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

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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

[[Page 2286]]

Sec. 39.13 [Amended]

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

Airbus: Docket No. FAA-2010-1309; Directorate Identifier 2010-NM-
060-AD.

Comments Due Date

(a) We must receive comments by February 28, 2011.

Affected ADs

(b) None.

Applicability

(c) This AD applies to Airbus Model A330-301, -302, -303, -321,
-322, -323, -341, -342, and -343 airplanes, Model A340-211, -212,
and -213 airplanes; and Model A340-311, -312, and -313 airplanes;
all manufacturer serial numbers; certificated in any category;
equipped with carbon fiber reinforced plastic rudders having part
numbers and serial numbers listed in Table 1 of this AD.

Table 1--Affected Rudders
------------------------------------------------------------------------
Rudder serial
Rudder part number number
------------------------------------------------------------------------
F554-70000-000-00.................................... TS-2013
F554-70000-000-00.................................... TS-2015
F554-70000-000-00.................................... TS-2016
F554-70000-000-00.................................... TS-2017
F554-70000-000-00.................................... TS-2018
F554-70000-000-00.................................... TS-2020
F554-70000-000-00.................................... TS-2021
F554-70000-000-00.................................... TS-2024
F554-70000-000-00.................................... TS-2026
F554-70000-000-00.................................... TS-2035
F554-70000-000-00.................................... TS-2036
F554-70000-000-00.................................... TS-2040
F554-70000-000-00.................................... TS-2042
F554-70000-000-00.................................... TS-2055
F554-70000-000-00.................................... TS-2056
F554-70000-000-00.................................... TS-2058
F554-70000-000-00.................................... TS-2059
F554-70000-000-00.................................... TS-2061
F554-70000-000-00.................................... TS-2062
F554-70000-000-00.................................... TS-2063
F554-70000-000-00.................................... TS-2065
F554-70000-002-00.................................... TS-2074
F554-71000-000-00.................................... TS-3003
F554-71000-000-00.................................... TS-3004
F554-71000-000-00.................................... TS-3005
F554-71000-000-00.................................... TS-3006
F554-71000-000-00.................................... TS-3007
F554-71000-000-00.................................... TS-3008
F554-71000-000-00.................................... TS-3011
F554-71000-000-00.................................... TS-3015
F554-71000-000-00.................................... TS-3033
F554-71000-000-00.................................... TS-3061
F554-71000-000-00.................................... TS-3064
F554-71000-000-00.................................... TS-3066
F554-71000-000-00.................................... TS-3071
F554-71000-000-00.................................... TS-3072
F554-71000-000-00.................................... TS-3075
F554-71000-000-00.................................... TS-3079
F554-71000-000-00.................................... TS-3084
F554-71000-000-00.................................... TS-3087
F554-70005-000-00.................................... TS-3100
F554-70005-000-00.................................... TS-3106
F554-70005-000-00.................................... TS-3107
F554-70005-000-00.................................... TS-3119
F554-70005-000-00.................................... TS-3124
------------------------------------------------------------------------

Subject

(d) Air Transport Association (ATA) of America Code 55:
Stabilizers.

Reason

(e) The mandatory continuing airworthiness information (MCAI)
states:
Surface defects were visually detected on the rudder of one
Airbus A319 and one A321 in-service aeroplane. Investigation has
determined that the defects reported on both rudders corresponded to
areas that had been reworked in production. The investigation
confirmed that the defects were the result of de-bonding between the
skin and honeycomb core. Such reworks were also performed on some
rudders fitted on A330-300 and A340-200/-300 aeroplanes.
An extended de-bonding, if not detected and corrected, may
degrade the structural integrity of the rudder. The loss of the
rudder leads to degradation of the handling qualities and reduces
the controllability of the aeroplane.
* * * * *

Compliance

(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.

Actions

(g) Do the actions required by paragraphs (g)(1) through (g)(8)
of this AD, in accordance with the Instructions of Airbus All
Operators Telex (AOT) A330-55A3040 or A340-55A4036, both Revision
02, both dated September 30, 2009, as applicable.
(1) In the reinforced location of the rudder: Within 1,800
flight hours after the rudder has accumulated 13,000 total flight
cycles since first installation, or within 1,800 flight hours after
the effective date of this AD, whichever is later, do a vacuum loss
inspection to detect defects, including de-bonding between the skin
and honeycomb core of the rudder.
(2) In the trailing edge location of the rudder: Within 21
months after the rudder has accumulated 13,000 total flight cycles
since first installation, or within 21 months after the effective
date of this AD, whichever is later, do an elasticity laminate
checker inspection to detect defects, including de-bonding between
the skin and honeycomb core of the rudder. If no defects are found,
repeat the inspection two times at intervals not to exceed 4,500
flight cycles, but not fewer than 4,000 flight cycles from the most
recent inspection.
(3) In locations other than those identified in paragraphs
(g)(1) and (g)(2) of this AD (e.g., lower rib, upper edge, leading
edge, and other locations): Within 1,800 flight hours after the
rudder has accumulated 13,000 total flight cycles since first
installation, or within 1,800 flight hours after the effective date
of this AD, whichever is later, do an elasticity laminate checker
inspection to detect defects, including de-bonding between the skin
and honeycomb core of the rudder. Repeat the inspection thereafter
at intervals not to exceed 1,800 flight hours.
(4) If no defects are found during any inspection required by
paragraph (g)(3) of this AD: Within 21 months after the rudder has
accumulated 13,000 total flight cycles since first installation, or
within 21 months after the effective date of this AD, whichever is
later, do a vacuum loss inspection on the other locations (e.g.,
lower rib, upper edge, leading edge, and other locations) to detect
defects, including de-bonding between the skin and honeycomb core of
the rudder.
(5) Accomplishment of the inspection required by paragraph
(g)(4) of this AD terminates the initial and repetitive inspections
required by paragraph (g)(3) of this AD.
(6) If any defect is found during any inspection required by
this AD, before further flight, repair using a method approved by
either the Manager, International Branch, ANM-116, Transport
Airplane Directorate, FAA; or the European Aviation Safety Agency
Airworthiness (EASA) (or its delegated agent).
(7) If no defects are found during any inspection required by
paragraphs (g)(1) and (g)(4) of this AD, before further flight,
restore the vacuum loss holes by doing a temporary restoration with
self-adhesive patches, a temporary restoration with resin, or a
permanent restoration. Do the applicable actions specified in
paragraph (g)(7)(i) or (g)(7)(ii) of this AD.
(i) For airplanes on which a temporary restoration with patch is
done: Within 900 flight hours after the restoration, do a detailed
inspection for defects of the restored area and repeat the
inspection thereafter at intervals not to exceed 900 flight hours
until the permanent restoration is done. Do the permanent
restoration within 21 months after the temporary restoration.
(ii) For airplanes on which a temporary restoration with resin
is done: Within 21 months after doing the temporary restoration, do
the permanent restoration.
(8) If any defect is found during any initial inspection
required by paragraphs (g)(1), (g)(3), and (g)(4) of this AD, at the
applicable time in paragraph (g)(8)(i) or (g)(8)(ii) of this AD:
Report the inspection results to Airbus SAS, SEER1/SEER2/SEER3,
Customer Services, 1 Rond Point Maurice Bellonte, 31707 Blagnac
Cedex, France; fax +33 (0) 5 61 93 28 73; or e-mail to
region1.StructureRepairSupport@airbus.com,
region2.StructureRepairSupport@airbus.com, or
region3.StructureRepairSupport@airbus.com.
(i) Inspections done before the effective date of this AD:
Within 30 days after the effective date of this AD.
(ii) Inspections done on or after the effective date of this AD:
Within 30 days after accomplishment of the inspection.

Credit for Actions Accomplished in Accordance With Previous Service
Information

(h) Actions accomplished before the effective date of this AD in
accordance with the service information identified in Table 2 of
this AD, are considered acceptable for compliance with the
corresponding actions specified in paragraphs (g)(1) through (g)(5)
and paragraph (g)(7) of this AD for only the areas inspected. For
all areas, the repetitive inspections required by this AD remain
applicable.

[[Page 2287]]

Table 2--Credit Service Information
------------------------------------------------------------------------
Document Revision Date
------------------------------------------------------------------------
Airbus AOT A330-55A3040....... Original......... May 27, 2009.
Airbus AOT A330-55A3040....... 01............... July 8, 2009.
Airbus AOT A340-55A4036....... Original......... May 27, 2009.
Airbus AOT A340-55A4036....... 01............... July 8, 2009.
------------------------------------------------------------------------

(i) For rudders on which temporary vacuum loss hole restoration
with resin or permanent vacuum loss hole restoration has been done,
as required by paragraph (g)(7) of this AD, in accordance with the
applicable AOT in Table 2 of this AD before the effective date of
this AD: Within 21 months after the restoration date, or within 3
months after the effective date of this AD, whichever occurs later,
do an ultrasonic inspection for defects, including debonding of the
reinforced area, in accordance with the Accomplishment Instructions
of Airbus AOT A330-55A3040 or A340-55A4036, both Revision 02, both
dated September 30, 2009, as applicable. If any defect is found,
before further flight, repair using a method approved by either the
Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA; or the EASA (or its delegated agent).
(j) As of the effective date of this AD, no person may install
any rudder identified in Table 1 of this AD on any airplane, unless
the rudder has been inspected and all applicable corrective actions
have been done in accordance with paragraph (g) or (i) of this AD,
as applicable.

FAA AD Differences

Note 1: This AD differs from the MCAI and/or service information
as follows: No differences.

Other FAA AD Provisions

(k) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, 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: Vladimir Ulyanov, Aerospace
Engineer, International Branch, ANM-116, Transport Airplane
Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-
3356; telephone (425) 227-1138; fax (425) 227-1149. 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.
(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: A federal agency may not conduct or
sponsor, and a person is not required to respond to, nor shall a
person be subject to a penalty for failure to comply with a
collection of information subject to the requirements of the
Paperwork Reduction Act unless that collection of information
displays a current valid OMB Control Number. The OMB Control Number
for this information collection is 2120-0056. Public reporting for
this collection of information is estimated to be approximately 5
minutes per response, including the time for reviewing instructions,
completing and reviewing the collection of information. All
responses to this collection of information are mandatory. Comments
concerning the accuracy of this burden and suggestions for reducing
the burden should be directed to the FAA at: 800 Independence Ave.,
SW., Washington, DC 20591, Attn: Information Collection Clearance
Officer, AES-200.

Related Information

(l) Refer to MCAI EASA Airworthiness Directive 2010-0021, dated
February 9, 2010; and Airbus AOTs A330-55A3040 and A340-55A4036,
both Revision 02, both dated September 30, 2009; for related
information.

Issued in Renton, Washington, on January 5, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-586 Filed 1-12-11; 8:45 am]
BILLING CODE 4910-13-P

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