Airworthiness Directives; Airbus Model A330-200, A330-300, A340-200, and A340-300 Series Airplanes, 37523-37527 [E9-17539]

Download as PDF Federal Register / Vol. 74, No. 144 / Wednesday, July 29, 2009 / Rules and Regulations It was found one occurrence of a fuel booster pump circuit br[e]aker opening during an engine maintenance servicing. An inspection inside the fuel tank revealed the fuel booster pump[’]s electrical harness chafing against its body, causing the loss of the electrical wiring protection and resulting in a short circuit. Further in-tank inspections have showed other fuel booster pump electrical harnesses chafing either with the pump body and/or with adjacent fuel lines, causing damage to the harness protective layers and resulting * * * [in a] possible ignition source inside the fuel tank. * * * * * sroberts on DSKD5P82C1PROD with RULES The corrective actions include revising the Limitations section of the airplane flight manual (AFM) to include a minimum fuel quantity, adding a minimum fuel quantity limitation for operation of the fuel booster pump, inspecting the fuel booster pump electrical harness of the left- and right-hand fuel tanks for damage, replacing any fuel booster pump assembly having a damaged electrical harness, installing clamps on the tank structure, and installing tie down straps for the fuel booster pump electrical harness. Actions and Compliance (f) Unless already done, do the following actions. (1) Within 30 days after the effective date of this AD, insert in the Limitations section of the AFM a copy of this AD or the following statement: The minimum fuel quantity inside each tank must be 300 kg (662 pounds) or 370 liters (97.75 gallons). (2) As of the effective date of this AD, any fuel tank defueling or other maintenance action which demands use of the fuel booster pumps is limited to a minimum fuel quantity of no less than 300 kilograms (662 pounds) or 370 liters (97.75 gallons) inside the respective tank. (3) Within 4,000 flight hours, or 24 months, or at the next scheduled or unscheduled fuel tank opening after the effective date of this AD, whichever occurs first, do the following actions: (i) Inspect the fuel booster pump electrical harness of the left- and right-hand fuel tanks for damage on its external protection, in accordance with paragraph 3.F. (Part I) of the Accomplishment Instructions of Embraer Service Bulletin 120–28–0016, dated January 9, 2008. If any damaged fuel booster pump electrical harness is found, before further flight, replace the affected fuel booster pump assembly with another fuel booster pump assembly bearing the same part number, in accordance with the Accomplishment Instructions of Embraer Service Bulletin 120– 28–0016, dated January 9, 2008. (ii) Install clamps and tie down straps on the tank structure and attach each fuel booster pump electrical harness to the leftand right-hand fuel tanks to avoid eventual chafing against the pump body, adjacent fuel lines, structure or any other part, and to prevent damage to the harness protective layers, in accordance with paragraph 3.G. (Part II) of the Accomplishment Instructions of Embraer Service Bulletin 120–28–0016, dated January 9, 2008. VerDate Nov<24>2008 22:13 Jul 28, 2009 Jkt 217001 (4) After complying with the actions in paragraphs (f)(3)(i) and (f)(3)(ii) of this AD, the limitations imposed by paragraphs (f)(1) and (f)(2) of this AD are no longer required, and the AFM revision required by paragraph (f)(1) of this AD may be removed from the AFM. FAA AD Differences Note: This AD differs from the MCAI and/ or service information as follows: No differences. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, 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: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1405; fax (425) 227–1149. 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, the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. Related Information (h) Refer to MCAI Brazilian Airworthiness Directive 2008–05–01, effective June 13, 2008; and Embraer Service Bulletin 120–28– 0016, dated January 9, 2008; for related information. Material Incorporated by Reference (i) You must use Embraer Service Bulletin 120–28–0016, dated January 9, 2008, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Empresa Brasileira de Aeronautica S.A. (EMBRAER), Technical Publications Section (PC 060), Av. Brigadeiro ˜ Faria Lima, 2170—Putim—12227–901 Sao Jose dos Campos—SP—BRASIL; telephone: +55 12 3927–5852 or +55 12 3309–0732; fax: +55 12 3927–7546; e-mail: distrib@embraer.com.br; Internet: https:// www.flyembraer.com. PO 00000 Frm 00029 Fmt 4700 Sfmt 4700 37523 (3) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221 or 425–227–1152. (4) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on July 13, 2009. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–17534 Filed 7–28–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0211; Directorate Identifier 2008–NM–028–AD; Amendment 39–15980 AD 2009–15–17] RIN 2120–AA64 Airworthiness Directives; Airbus Model A330–200, A330–300, A340–200, and A340–300 Series Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. SUMMARY: We are adopting a new airworthiness directive (AD) for the products listed above. This 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: * * * * * [B]ogie beam internal paint has been degraded, leading to a loss of cadmium plating and thus allowing development of corrosion pitting. If not corrected, this situation under higher speed could result in the aircraft departing the runway or in the bogie [beam] detaching from the aircraft or [main landing] gear collapses, which would constitute an unsafe condition. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective September 2, 2009. E:\FR\FM\29JYR1.SGM 29JYR1 37524 Federal Register / Vol. 74, No. 144 / Wednesday, July 29, 2009 / Rules and Regulations The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of September 2, 2009. You may examine the AD docket on the Internet at https:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC. ADDRESSES: 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: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on March 10, 2009 (74 FR 10199). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: The operator of an A330 aircraft (which has a common bogie beam with the A340) has reported a fracture of the RH (right-hand) MLG (main landing gear) Bogie Beam whilst turning during low speed taxi maneuvers. The bogie [beam] fractured aft of the pivot point and remained attached to the sliding tube by the brake torque reaction rods. After this RH bogie [beam] failure, the aircraft continued for approximately 40 meters on the forks of the sliding member before coming to rest on the taxiway without any passenger injury. The preliminary investigations revealed that this event was due to corrosion pitting occurring on the bore of the bogie beam. Investigations are ongoing to determine why bogie beam internal paint has been degraded, leading to a loss of cadmium plating and thus allowing development of corrosion pitting. If not corrected, this situation under higher speed could result in the aircraft departing the runway or in the bogie [beam] detaching from the aircraft or [main landing] gear collapses, which would constitute an unsafe condition. To enable early detection and repair of any corrosion of the internal surfaces, EASA (European Aviation Safety Agency) AD 2007– 0314 required a one-time inspection on all MLG Bogie Beams except Enhanced MLG Bogie Beams and the reporting of the results to AIRBUS. The Revision 1 of AD 2007–0314 aimed to clarify the compliance time of the inspection and to extend the reporting period. The present AD which supersedes the AD 2007–0314R1: —Takes over the AD 2007–0314R1 requirements and —Reduces the inspection threshold from 6 to 4.5 years due to significant findings on the inspected aircraft. Required actions include applying protective treatments to the bogie beam and corrective actions. Corrective actions include repair of any damaged or corroded surfaces or surface treatments, and contacting MessierDowty for repair instructions and doing the repair. You may obtain further information by examining the MCAI in the AD docket. Comments We gave the public the opportunity to participate in developing this AD. We considered the comments received. Request To Revise References to the French Export Certificate in the NPRM Airbus requests that we revise the phrase ‘‘French export certificate of airworthiness’’ that is specified in paragraphs (f)(2), (f)(2)(i), (f)(3), and (f)(3)(i) of the NPRM. Airbus states that there is no more ‘‘French’’ export airworthiness certificate and states that it has been replaced with the EASA export airworthiness certificate. We agree to revise paragraphs (f)(2), (f)(2)(i), (f)(3), and (f)(3)(i) of this AD for the reason provided by the commenter. We have replaced the phrase ‘‘French export certificate of airworthiness’’ with ‘‘French or EASA export certificate of airworthiness.’’ Request To Revise Compliance Time Specified in Paragraphs (f)(3)(i) and (f)(3)(ii) of the NPRM Airbus requests that we revise the compliance time specified in paragraphs (f)(3)(i) and (f)(3)(ii) of the NPRM to include the additional phrase ‘‘or at the next scheduled bogie beam overhaul, whichever occurs first.’’ We disagree with revising the compliance time, ‘‘within 18 months after the effective date of this AD,’’ specified in paragraphs (f)(3)(i) and (f)(3)(ii) of this AD to include the additional phrase. The requested change would shorten the compliance time for certain operators. In developing an appropriate compliance time, we considered the safety implications and normal maintenance schedules for timely accomplishment of the required actions. We determined that the compliance time represents an appropriate interval in which the actions required by this AD can be done, in a timely manner within the fleet, while still maintaining an adequate level of safety. Operators are always permitted to accomplish the requirements of an AD at a time earlier than the specified compliance time. If additional data are presented that would justify a shorter compliance time, we might consider further rulemaking on this issue. We have not revised this AD in this regard. New Relevant Service Information Airbus and Messier-Dowty have issued the service information described in the following table. NEW SERVICE INFORMATION Service Bulletin Revision sroberts on DSKD5P82C1PROD with RULES Airbus Mandatory Service Bulletin A330–32–3225, including Appendix 1 ................................................. Airbus Mandatory Service Bulletin A340–32–4268, including Appendix 1 ................................................. Messier-Dowty Service Bulletin A33/34–32–271, including Appendixes A and B ...................................... Messier-Dowty Service Bulletin A33/34–32–272, including Appendixes A, B, C, and D ........................... Date 01 01 1 1 October 30, 2008. October 30, 2008. November 16, 2007. September 22, 2008. We referred to earlier revisions of the service bulletins in the NPRM, as described in the following table. SERVICE INFORMATION SPECIFIED IN THE NPRM Service Bulletin Date Airbus Mandatory Service Bulletin A330–32–3225, including Appendix 01 ........................................................................... VerDate Nov<24>2008 22:13 Jul 28, 2009 Jkt 217001 PO 00000 Frm 00030 Fmt 4700 Sfmt 4700 E:\FR\FM\29JYR1.SGM 29JYR1 November 21, 2007. 37525 Federal Register / Vol. 74, No. 144 / Wednesday, July 29, 2009 / Rules and Regulations SERVICE INFORMATION SPECIFIED IN THE NPRM—Continued Service Bulletin Date Airbus Mandatory Service Bulletin A340–32–4268, including Appendix 01 ........................................................................... Messier-Dowty Service Bulletin A33/34–32–271, including Appendix A ................................................................................ Messier-Dowty Service Bulletin A33/34–32–272, including Appendixes A, B, C, and D ....................................................... November 21, 2007. September 13, 2007. November 16, 2007. The new service information does not add work for airplanes on which the actions specified in the earlier revisions of the service bulletins have been accomplished. Revision 01 of Airbus Mandatory Service Bulletins A330–32–3225 and A340–32–4268 revises references to Messier-Dowty Service Bulletin A33/ 34–32–272. We have revised paragraphs (f)(1) and (h) of this AD to refer to Revision 01 of Airbus Mandatory Service Bulletins A330–32–3225 and A340–32–4268. We have also added Airbus Mandatory Service Bulletins A330–32–3225 and A340–32–4268, both dated November 21, 2007, to paragraph (f)(6) of this AD to give credit for actions done in accordance with these service bulletins before the effective date of this AD. Revision 1 of Messier-Dowty Service Bulletin A33/34–32–271 provides a new illustration and updates the procedures. We have revised paragraphs (f)(5) and (h) of this AD to refer to Revision 1 of Messier-Dowty Service Bulletin A33/ 34–32–271. We have also added Messier-Dowty Service Bulletin A33/ 34–32–271, including Appendix A, dated September 13, 2007, to paragraph (f)(6) of this AD to give credit for actions done in accordance with that service bulletin before the effective date of this AD. Revision 1 of Messier-Dowty Service Bulletin A33/34–32–272 provides new illustrations and updates the procedures. We have revised paragraphs (f)(1)(i), (f)(1)(ii), and (h), and Note 1 of this AD to refer to Revision 1 of MessierDowty Service Bulletin A33/34–32–272. We have also added Messier-Dowty Service Bulletin A33/34–32–272, including Appendixes A, B, C, and D, dated November 16, 2007, to paragraph (f)(6) of this AD to give credit for actions done in accordance with that service bulletin before the effective date of this AD. sroberts on DSKD5P82C1PROD with RULES Conclusion We reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting the AD with the changes described previously. We determined that these changes will not increase the economic burden on VerDate Nov<24>2008 22:13 Jul 28, 2009 Jkt 217001 any operator or increase the scope of the AD. 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 required different actions in this AD from those in the MCAI in order to follow our FAA policies. Any such differences are highlighted in a NOTE within the AD. Costs of Compliance We estimate that this AD will affect 29 products of U.S. registry. We also estimate that it will take about 22 workhours per product to comply with the basic requirements of this AD. The average labor rate is $80 per work-hour. Based on these figures, we estimate the cost of this AD to the U.S. operators to be $51,040, or $1,760 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. PO 00000 Frm 00031 Fmt 4700 Sfmt 4700 Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this AD: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. Examining the AD Docket You may examine the AD docket on the Internet at 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 the NPRM, 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. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: ■ PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. E:\FR\FM\29JYR1.SGM 29JYR1 37526 § 39.13 Federal Register / Vol. 74, No. 144 / Wednesday, July 29, 2009 / Rules and Regulations [Amended] 2. The FAA amends § 39.13 by adding the following new AD: ■ 2009–15–17 Airbus: Amendment 39–15980. Docket No. FAA–2009–0211; Directorate Identifier 2008–NM–028–AD. Effective Date (a) This airworthiness directive (AD) becomes effective September 2, 2009. Affected ADs (b) None. Applicability (c) This AD applies to Airbus Model A330– 200, A330–300, A340–200, and A340–300 series airplanes; certificated in any category; all certified models; all serial numbers, except those on which Airbus modification 54500 has been embodied in production or Airbus Service Bulletin A330–32–3212 has been embodied in service. sroberts on DSKD5P82C1PROD with RULES Subject (d) Air Transport Association (ATA) of America Code 32: Landing Gear. Reason (e) The mandatory continuing airworthiness information (MCAI) states: The operator of an A330 aircraft (which has a common bogie beam with the A340) has reported a fracture of the RH (right-hand) MLG (main landing gear) Bogie Beam whilst turning during low speed taxi maneuvers. The bogie [beam] fractured aft of the pivot point and remained attached to the sliding tube by the brake torque reaction rods. After this RH bogie [beam] failure, the aircraft continued for approximately 40 meters on the forks of the sliding member before coming to rest on the taxiway without any passenger injury. The preliminary investigations revealed that this event was due to corrosion pitting occurring on the bore of the bogie beam. Investigations are ongoing to determine why bogie beam internal paint has been degraded, leading to a loss of cadmium plating and thus allowing development of corrosion pitting. If not corrected, this situation under higher speed could result in the aircraft departing the runway or in the bogie [beam] detaching from the aircraft or [main landing] gear collapses, which would constitute an unsafe condition. To enable early detection and repair of any corrosion of the internal surfaces, EASA (European Aviation Safety Agency) AD 2007– 0314 required a one-time inspection on all MLG Bogie Beams except Enhanced MLG Bogie Beams and the reporting of the results to AIRBUS. The Revision 1 of AD 2007–0314 aimed to clarify the compliance time of the inspection and to extend the reporting period. The present AD which supersedes the AD 2007–0314R1: —Takes over the AD 2007–0314R1 requirements and VerDate Nov<24>2008 22:13 Jul 28, 2009 Jkt 217001 —Reduces the inspection threshold from 6 to 4.5 years due to significant findings on the inspected aircraft. Required actions include applying protective treatments to the bogie beam and corrective actions. Corrective actions include repair of any damaged or corroded surfaces or surface treatments, and contacting Messier-Dowty for repair instructions and doing the repair. Actions and Compliance (f) Unless already done, do the following actions. (1) At the applicable compliance time specified in paragraph (f)(2) or (f)(3) of this AD: Clean the internal bore and perform a detailed visual inspection of internal surfaces of the MLG bogie beam (right-hand and lefthand) for any damage to the protective treatments or any corrosion, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A330–32– 3225 or A340–32–4268, both Revision 01, both dated October 30, 2008; as applicable. (i) If no damage and corrosion is found, before further flight, apply the protective treatments of the bogie beam, in accordance with the Accomplishment Instructions of Messier-Dowty Service Bulletin A33/34–32– 272, Revision 1, including Appendixes A, B, C, and D, dated September 22, 2008. (ii) If any damage or corrosion is found, before further flight, do all applicable corrective actions and apply the protective treatments of the bogie beam, in accordance with the Accomplishment Instructions of Messier-Dowty Service Bulletin A33/34–32– 272, Revision 1, including Appendixes A, B, C, and D, dated September 22, 2008. (2) For airplanes with 54 months or less time-in-service since the date of issuance of the original French airworthiness certificate or the date of issuance of the original French or EASA export certificate of airworthiness as of the effective date of this AD: At the latest of the applicable times specified in paragraphs (f)(2)(i), (f)(2)(ii), and (f)(2)(iii) of this AD, do the actions required by paragraph (f)(1) of this AD. (i) Not before 54 months since the date of issuance of the original French airworthiness certificate or the date of issuance of the original French or EASA export certificate of airworthiness, but no later than 72 months since the date of issuance of the original French airworthiness certificate or the date of issuance of the original French or EASA export certificate of airworthiness. (ii) Not before 54 months since the installation of a new bogie beam in-service before the effective date of this AD, but no later than 72 months since the installation of a new bogie beam in-service before the effective date of this AD. (iii) Not before 54 months since the last overhaul of a bogie beam before the effective date of this AD, but no later than 72 months since the last overhaul of a bogie beam before the effective date of this AD. (3) For airplanes with more than 54 months time-in-service since the date of issuance of PO 00000 Frm 00032 Fmt 4700 Sfmt 4700 the original French airworthiness certificate or the date of issuance of the original French or EASA export certificate of airworthiness as of the effective date of this AD: At the applicable time specified in paragraph (f)(3)(i), (f)(3)(ii), f)(3)(iii), (f)(3)(iv), or (f)(3)(v) of this AD, do the actions required by paragraph (f)(1) of this AD. (i) For airplanes on which the bogie beam has not been replaced or overhauled since the date of issuance of the original French airworthiness certificate or the date of issuance of the original French or EASA export certificate of airworthiness as of the effective date of this AD: Within 18 months after the effective date of this AD. (ii) For airplanes on which the bogie beam has been replaced in-service with a new bogie beam and the new bogie beam has more than 54 months time-in-service as of the effective date of this AD: Within 18 months after the effective date of this AD. (iii) For airplanes on which the bogie beam has been replaced in-service with a new bogie beam and the new bogie beam has 54 months or less time-in-service as of the effective date of this AD: Not before 54 months since the installation of a new bogie beam in-service before the effective date of this AD, but no later than 72 months since the installation of a new bogie beam inservice before the effective date of this AD. (iv) For airplanes on which the bogie beam has been overhauled and the overhauled bogie beam has more than 54 months timein-service as of the effective date of this AD: Within 18 months after the effective date of this AD, or at the next scheduled bogie beam overhaul, whichever occurs first. (v) For airplanes on which the bogie beam has been overhauled and the overhauled bogie beam has 54 months or less time-inservice as of the effective date of this AD: Not before 54 months since the last overhaul of a bogie beam before the effective date of this AD, but no later than 72 months since the last overhaul of a bogie beam before the effective date of this AD. (4) Within 30 days after accomplishment of the inspection required by paragraph (f)(1) of this AD or within 30 days after the effective date of this AD, whichever occurs later, report the results, including no findings, to Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; e-mail airworthiness.A330-A340@airbus.com. (5) Actions accomplished in accordance with Messier-Dowty Service Bulletin A33/ 34–32–271, Revision 1, including Appendixes A and B, dated November 16, 2007, are considered acceptable for compliance with the corresponding requirements of this AD. (6) Actions accomplished before the effective date of this AD in accordance with the service bulletins specified in Table 1 of this AD are considered acceptable for compliance with the corresponding requirements of this AD. E:\FR\FM\29JYR1.SGM 29JYR1 37527 Federal Register / Vol. 74, No. 144 / Wednesday, July 29, 2009 / Rules and Regulations TABLE 1—CREDIT SERVICE INFORMATION Service Bulletin Date Airbus Mandatory Service Bulletin A330–32–3225 ................................................................................................................. Airbus Mandatory Service Bulletin A340–32–4268 ................................................................................................................. Messier-Dowty Service Bulletin A33/34–32–271, including Appendix A ................................................................................ Messier-Dowty Service Bulletin A33/34–32–272, including Appendixes A, B, C, and D ....................................................... November 21, 2007. November 21, 2007. September 13, 2007. November 16, 2007. FAA AD Differences Note 1: This AD differs from the MCAI and/or service information as follows: The MCAI specifies repair and corrective actions in accordance with Airbus Mandatory Service Bulletin A330–32–3225 or A340–32– 4268, both dated November 21, 2007; however, these Airbus service bulletins do not describe those actions. Paragraphs (f)(1)(i) and (f)(1)(ii) of this AD specify repair and corrective actions in accordance with Messier-Dowty Service Bulletin A33/34–32– 272, Revision 1, including Appendixes A, B, C, and D, dated September 22, 2008. Other FAA AD Provisions (g) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, 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. (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, the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. Related Information (h) Refer to EASA Airworthiness Directive 2008–0093, dated May 20, 2008, and the service bulletins specified in Table 2 of this AD, for related information. TABLE 2—SERVICE INFORMATION Service Bulletin Revision Airbus Mandatory Service Bulletin A330–32–3225, including Appendix 1 ................................................. Airbus Mandatory Service Bulletin A340–32–4268, including Appendix 1 ................................................. Messier-Dowty Service Bulletin A33/34–32–271, including Appendixes A and B ...................................... Messier-Dowty Service Bulletin A33/34–32–272, including Appendixes A, B, C, and D ........................... Material Incorporated by Reference (i) You must use the service information contained in Table 3 of this AD to do the Date 01 01 1 1 October 30, 2008. October 30, 2008. November 16, 2007. September 22, 2008. actions required by this AD, unless the AD specifies otherwise. TABLE 3—MATERIAL INCORPORATED BY REFERENCE Service Bulletin Revision sroberts on DSKD5P82C1PROD with RULES Airbus Mandatory Service Bulletin A330–32–3225, including Appendix 1 ................................................. Airbus Mandatory Service Bulletin A340–32–4268, including Appendix 1 ................................................. Messier-Dowty Service Bulletin A33/34–32–271, including Appendixes A and B ...................................... Messier-Dowty Service Bulletin A33/34–32–272, including Appendixes A, B, C, and D ........................... (Pages identified as ‘‘intentionally blank’’ in the Messier-Dowty service bulletins identified in Table 3 of this AD are at the revision level and date specified in Table 3 for those documents.) (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For Airbus service information identified in this AD, contact Airbus SAS— Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; fax +33 5 61 93 45 80, e-mail airworthiness.A330-A340@airbus.com; Internet https://www.airbus.com. For MessierDowty service information identified in this AD, contact Messier Services Americas, VerDate Nov<24>2008 22:13 Jul 28, 2009 Jkt 217001 Customer Support Center, 45360 Severn Way, Sterling, Virginia 20166–8910; telephone 703–450–8233; fax 703–404–1621; Internet https://techpubs.services.messierdowty.com. (3) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221 or 425–227–1152. (4) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https://www.archives.gov/federal_register/ PO 00000 Frm 00033 Fmt 4700 Sfmt 4700 Date 01 01 1 1 October 30, 2008. October 30, 2008. November 16, 2007. September 22, 2008. code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on July 2, 2009. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–17539 Filed 7–28–09; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\29JYR1.SGM 29JYR1

Agencies

[Federal Register Volume 74, Number 144 (Wednesday, July 29, 2009)]
[Rules and Regulations]
[Pages 37523-37527]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-17539]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0211; Directorate Identifier 2008-NM-028-AD;
Amendment 39-15980 AD 2009-15-17]
RIN 2120-AA64

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

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

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for the
products listed above. This 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:
* * * * *
[B]ogie beam internal paint has been degraded, leading to a loss
of cadmium plating and thus allowing development of corrosion
pitting.
If not corrected, this situation under higher speed could result
in the aircraft departing the runway or in the bogie [beam]
detaching from the aircraft or [main landing] gear collapses, which
would constitute an unsafe condition.
* * * * *
We are issuing this AD to require actions to correct the unsafe
condition on these products.

DATES: This AD becomes effective September 2, 2009.

[[Page 37524]]

The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of September 2,
2009.

ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov or in person at the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.

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:

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on March 10, 2009 (74
FR 10199). That NPRM proposed to correct an unsafe condition for the
specified products. The MCAI states:

The operator of an A330 aircraft (which has a common bogie beam
with the A340) has reported a fracture of the RH (right-hand) MLG
(main landing gear) Bogie Beam whilst turning during low speed taxi
maneuvers. The bogie [beam] fractured aft of the pivot point and
remained attached to the sliding tube by the brake torque reaction
rods. After this RH bogie [beam] failure, the aircraft continued for
approximately 40 meters on the forks of the sliding member before
coming to rest on the taxiway without any passenger injury.
The preliminary investigations revealed that this event was due
to corrosion pitting occurring on the bore of the bogie beam.
Investigations are ongoing to determine why bogie beam internal
paint has been degraded, leading to a loss of cadmium plating and
thus allowing development of corrosion pitting.
If not corrected, this situation under higher speed could result
in the aircraft departing the runway or in the bogie [beam]
detaching from the aircraft or [main landing] gear collapses, which
would constitute an unsafe condition.
To enable early detection and repair of any corrosion of the
internal surfaces, EASA (European Aviation Safety Agency) AD 2007-
0314 required a one-time inspection on all MLG Bogie Beams except
Enhanced MLG Bogie Beams and the reporting of the results to AIRBUS.
The Revision 1 of AD 2007-0314 aimed to clarify the compliance
time of the inspection and to extend the reporting period.
The present AD which supersedes the AD 2007-0314R1:

--Takes over the AD 2007-0314R1 requirements and
--Reduces the inspection threshold from 6 to 4.5 years due to
significant findings on the inspected aircraft.

Required actions include applying protective treatments to the bogie
beam and corrective actions. Corrective actions include repair of any
damaged or corroded surfaces or surface treatments, and contacting
Messier-Dowty for repair instructions and doing the repair. You may
obtain further information by examining the MCAI in the AD docket.

Comments

We gave the public the opportunity to participate in developing
this AD. We considered the comments received.

Request To Revise References to the French Export Certificate in the
NPRM

Airbus requests that we revise the phrase ``French export
certificate of airworthiness'' that is specified in paragraphs (f)(2),
(f)(2)(i), (f)(3), and (f)(3)(i) of the NPRM. Airbus states that there
is no more ``French'' export airworthiness certificate and states that
it has been replaced with the EASA export airworthiness certificate.
We agree to revise paragraphs (f)(2), (f)(2)(i), (f)(3), and
(f)(3)(i) of this AD for the reason provided by the commenter. We have
replaced the phrase ``French export certificate of airworthiness'' with
``French or EASA export certificate of airworthiness.''

Request To Revise Compliance Time Specified in Paragraphs (f)(3)(i) and
(f)(3)(ii) of the NPRM

Airbus requests that we revise the compliance time specified in
paragraphs (f)(3)(i) and (f)(3)(ii) of the NPRM to include the
additional phrase ``or at the next scheduled bogie beam overhaul,
whichever occurs first.''
We disagree with revising the compliance time, ``within 18 months
after the effective date of this AD,'' specified in paragraphs
(f)(3)(i) and (f)(3)(ii) of this AD to include the additional phrase.
The requested change would shorten the compliance time for certain
operators. In developing an appropriate compliance time, we considered
the safety implications and normal maintenance schedules for timely
accomplishment of the required actions. We determined that the
compliance time represents an appropriate interval in which the actions
required by this AD can be done, in a timely manner within the fleet,
while still maintaining an adequate level of safety. Operators are
always permitted to accomplish the requirements of an AD at a time
earlier than the specified compliance time. If additional data are
presented that would justify a shorter compliance time, we might
consider further rulemaking on this issue. We have not revised this AD
in this regard.

New Relevant Service Information

Airbus and Messier-Dowty have issued the service information
described in the following table.

New Service Information
------------------------------------------------------------------------
Service Bulletin Revision Date
------------------------------------------------------------------------
Airbus Mandatory Service 01 October 30, 2008.
Bulletin A330-32-3225,
including Appendix 1.
Airbus Mandatory Service 01 October 30, 2008.
Bulletin A340-32-4268,
including Appendix 1.
Messier-Dowty Service 1 November 16, 2007.
Bulletin A33/34-32-271,
including Appendixes A and
B.
Messier-Dowty Service 1 September 22, 2008.
Bulletin A33/34-32-272,
including Appendixes A, B,
C, and D.
------------------------------------------------------------------------

We referred to earlier revisions of the service bulletins in the
NPRM, as described in the following table.

Service Information Specified in the NPRM
------------------------------------------------------------------------
Service Bulletin Date
------------------------------------------------------------------------
Airbus Mandatory Service Bulletin November 21, 2007.
A330-32-3225, including Appendix 01.

[[Page 37525]]

Airbus Mandatory Service Bulletin November 21, 2007.
A340-32-4268, including Appendix 01.
Messier-Dowty Service Bulletin A33/ September 13, 2007.
34-32-271, including Appendix A.
Messier-Dowty Service Bulletin A33/ November 16, 2007.
34-32-272, including Appendixes A,
B, C, and D.
------------------------------------------------------------------------

The new service information does not add work for airplanes on
which the actions specified in the earlier revisions of the service
bulletins have been accomplished.
Revision 01 of Airbus Mandatory Service Bulletins A330-32-3225 and
A340-32-4268 revises references to Messier-Dowty Service Bulletin A33/
34-32-272. We have revised paragraphs (f)(1) and (h) of this AD to
refer to Revision 01 of Airbus Mandatory Service Bulletins A330-32-3225
and A340-32-4268. We have also added Airbus Mandatory Service Bulletins
A330-32-3225 and A340-32-4268, both dated November 21, 2007, to
paragraph (f)(6) of this AD to give credit for actions done in
accordance with these service bulletins before the effective date of
this AD.
Revision 1 of Messier-Dowty Service Bulletin A33/34-32-271 provides
a new illustration and updates the procedures. We have revised
paragraphs (f)(5) and (h) of this AD to refer to Revision 1 of Messier-
Dowty Service Bulletin A33/34-32-271. We have also added Messier-Dowty
Service Bulletin A33/34-32-271, including Appendix A, dated September
13, 2007, to paragraph (f)(6) of this AD to give credit for actions
done in accordance with that service bulletin before the effective date
of this AD.
Revision 1 of Messier-Dowty Service Bulletin A33/34-32-272 provides
new illustrations and updates the procedures. We have revised
paragraphs (f)(1)(i), (f)(1)(ii), and (h), and Note 1 of this AD to
refer to Revision 1 of Messier-Dowty Service Bulletin A33/34-32-272. We
have also added Messier-Dowty Service Bulletin A33/34-32-272, including
Appendixes A, B, C, and D, dated November 16, 2007, to paragraph (f)(6)
of this AD to give credit for actions done in accordance with that
service bulletin before the effective date of this AD.

Conclusion

We reviewed the available data, including the comments received,
and determined that air safety and the public interest require adopting
the AD with the changes described previously. We determined that these
changes will not increase the economic burden on any operator or
increase the scope of the AD.

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 required different actions in this AD from those
in the MCAI in order to follow our FAA policies. Any such differences
are highlighted in a NOTE within the AD.

Costs of Compliance

We estimate that this AD will affect 29 products of U.S. registry.
We also estimate that it will take about 22 work-hours per product to
comply with the basic requirements of this AD. The average labor rate
is $80 per work-hour. Based on these figures, we estimate the cost of
this AD to the U.S. operators to be $51,040, or $1,760 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 AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket.

Examining the AD Docket

You may examine the AD docket on the Internet at 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 the NPRM, 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.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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

[[Page 37526]]

Sec. 39.13 [Amended]

0
2. The FAA amends Sec. 39.13 by adding the following new AD:

2009-15-17 Airbus: Amendment 39-15980. Docket No. FAA-2009-0211;
Directorate Identifier 2008-NM-028-AD.

Effective Date

(a) This airworthiness directive (AD) becomes effective
September 2, 2009.

Affected ADs

(b) None.

Applicability

(c) This AD applies to Airbus Model A330-200, A330-300, A340-
200, and A340-300 series airplanes; certificated in any category;
all certified models; all serial numbers, except those on which
Airbus modification 54500 has been embodied in production or Airbus
Service Bulletin A330-32-3212 has been embodied in service.

Subject

(d) Air Transport Association (ATA) of America Code 32: Landing
Gear.

Reason

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

--Takes over the AD 2007-0314R1 requirements and
--Reduces the inspection threshold from 6 to 4.5 years due to
significant findings on the inspected aircraft.

Required actions include applying protective treatments to the bogie
beam and corrective actions. Corrective actions include repair of
any damaged or corroded surfaces or surface treatments, and
contacting Messier-Dowty for repair instructions and doing the
repair.

Actions and Compliance

(f) Unless already done, do the following actions.
(1) At the applicable compliance time specified in paragraph
(f)(2) or (f)(3) of this AD: Clean the internal bore and perform a
detailed visual inspection of internal surfaces of the MLG bogie
beam (right-hand and left-hand) for any damage to the protective
treatments or any corrosion, in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A330-32-3225 or
A340-32-4268, both Revision 01, both dated October 30, 2008; as
applicable.
(i) If no damage and corrosion is found, before further flight,
apply the protective treatments of the bogie beam, in accordance
with the Accomplishment Instructions of Messier-Dowty Service
Bulletin A33/34-32-272, Revision 1, including Appendixes A, B, C,
and D, dated September 22, 2008.
(ii) If any damage or corrosion is found, before further flight,
do all applicable corrective actions and apply the protective
treatments of the bogie beam, in accordance with the Accomplishment
Instructions of Messier-Dowty Service Bulletin A33/34-32-272,
Revision 1, including Appendixes A, B, C, and D, dated September 22,
2008.
(2) For airplanes with 54 months or less time-in-service since
the date of issuance of the original French airworthiness
certificate or the date of issuance of the original French or EASA
export certificate of airworthiness as of the effective date of this
AD: At the latest of the applicable times specified in paragraphs
(f)(2)(i), (f)(2)(ii), and (f)(2)(iii) of this AD, do the actions
required by paragraph (f)(1) of this AD.
(i) Not before 54 months since the date of issuance of the
original French airworthiness certificate or the date of issuance of
the original French or EASA export certificate of airworthiness, but
no later than 72 months since the date of issuance of the original
French airworthiness certificate or the date of issuance of the
original French or EASA export certificate of airworthiness.
(ii) Not before 54 months since the installation of a new bogie
beam in-service before the effective date of this AD, but no later
than 72 months since the installation of a new bogie beam in-service
before the effective date of this AD.
(iii) Not before 54 months since the last overhaul of a bogie
beam before the effective date of this AD, but no later than 72
months since the last overhaul of a bogie beam before the effective
date of this AD.
(3) For airplanes with more than 54 months time-in-service since
the date of issuance of the original French airworthiness
certificate or the date of issuance of the original French or EASA
export certificate of airworthiness as of the effective date of this
AD: At the applicable time specified in paragraph (f)(3)(i),
(f)(3)(ii), f)(3)(iii), (f)(3)(iv), or (f)(3)(v) of this AD, do the
actions required by paragraph (f)(1) of this AD.
(i) For airplanes on which the bogie beam has not been replaced
or overhauled since the date of issuance of the original French
airworthiness certificate or the date of issuance of the original
French or EASA export certificate of airworthiness as of the
effective date of this AD: Within 18 months after the effective date
of this AD.
(ii) For airplanes on which the bogie beam has been replaced in-
service with a new bogie beam and the new bogie beam has more than
54 months time-in-service as of the effective date of this AD:
Within 18 months after the effective date of this AD.
(iii) For airplanes on which the bogie beam has been replaced
in-service with a new bogie beam and the new bogie beam has 54
months or less time-in-service as of the effective date of this AD:
Not before 54 months since the installation of a new bogie beam in-
service before the effective date of this AD, but no later than 72
months since the installation of a new bogie beam in-service before
the effective date of this AD.
(iv) For airplanes on which the bogie beam has been overhauled
and the overhauled bogie beam has more than 54 months time-in-
service as of the effective date of this AD: Within 18 months after
the effective date of this AD, or at the next scheduled bogie beam
overhaul, whichever occurs first.
(v) For airplanes on which the bogie beam has been overhauled
and the overhauled bogie beam has 54 months or less time-in-service
as of the effective date of this AD: Not before 54 months since the
last overhaul of a bogie beam before the effective date of this AD,
but no later than 72 months since the last overhaul of a bogie beam
before the effective date of this AD.
(4) Within 30 days after accomplishment of the inspection
required by paragraph (f)(1) of this AD or within 30 days after the
effective date of this AD, whichever occurs later, report the
results, including no findings, to Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; e-mail airworthiness.A330-A340@airbus.com.
(5) Actions accomplished in accordance with Messier-Dowty
Service Bulletin A33/34-32-271, Revision 1, including Appendixes A
and B, dated November 16, 2007, are considered acceptable for
compliance with the corresponding requirements of this AD.
(6) Actions accomplished before the effective date of this AD in
accordance with the service bulletins specified in Table 1 of this
AD are considered acceptable for compliance with the corresponding
requirements of this AD.

[[Page 37527]]

Table 1--Credit Service Information
------------------------------------------------------------------------
Service Bulletin Date
------------------------------------------------------------------------
Airbus Mandatory Service Bulletin November 21, 2007.
A330-32-3225.
Airbus Mandatory Service Bulletin November 21, 2007.
A340-32-4268.
Messier-Dowty Service Bulletin A33/ September 13, 2007.
34-32-271, including Appendix A.
Messier-Dowty Service Bulletin A33/ November 16, 2007.
34-32-272, including Appendixes A,
B, C, and D.
------------------------------------------------------------------------

FAA AD Differences

Note 1: This AD differs from the MCAI and/or service information
as follows: The MCAI specifies repair and corrective actions in
accordance with Airbus Mandatory Service Bulletin A330-32-3225 or
A340-32-4268, both dated November 21, 2007; however, these Airbus
service bulletins do not describe those actions. Paragraphs
(f)(1)(i) and (f)(1)(ii) of this AD specify repair and corrective
actions in accordance with Messier-Dowty Service Bulletin A33/34-32-
272, Revision 1, including Appendixes A, B, C, and D, dated
September 22, 2008.

Other FAA AD Provisions

(g) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, 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.
(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, the
Office of Management and Budget (OMB) has approved the information
collection requirements and has assigned OMB Control Number 2120-
0056.

Related Information

(h) Refer to EASA Airworthiness Directive 2008-0093, dated May
20, 2008, and the service bulletins specified in Table 2 of this AD,
for related information.

Table 2--Service Information
------------------------------------------------------------------------
Service Bulletin Revision Date
------------------------------------------------------------------------
Airbus Mandatory Service 01 October 30, 2008.
Bulletin A330-32-3225,
including Appendix 1.
Airbus Mandatory Service 01 October 30, 2008.
Bulletin A340-32-4268,
including Appendix 1.
Messier-Dowty Service 1 November 16, 2007.
Bulletin A33/34-32-271,
including Appendixes A and
B.
Messier-Dowty Service 1 September 22, 2008.
Bulletin A33/34-32-272,
including Appendixes A, B,
C, and D.
------------------------------------------------------------------------

Material Incorporated by Reference

(i) You must use the service information contained in Table 3 of
this AD to do the actions required by this AD, unless the AD
specifies otherwise.

Table 3--Material Incorporated by Reference
------------------------------------------------------------------------
Service Bulletin Revision Date
------------------------------------------------------------------------
Airbus Mandatory Service 01 October 30, 2008.
Bulletin A330-32-3225,
including Appendix 1.
Airbus Mandatory Service 01 October 30, 2008.
Bulletin A340-32-4268,
including Appendix 1.
Messier-Dowty Service 1 November 16, 2007.
Bulletin A33/34-32-271,
including Appendixes A and
B.
Messier-Dowty Service 1 September 22, 2008.
Bulletin A33/34-32-272,
including Appendixes A, B,
C, and D.
------------------------------------------------------------------------

(Pages identified as ``intentionally blank'' in the Messier-Dowty
service bulletins identified in Table 3 of this AD are at the
revision level and date specified in Table 3 for those documents.)
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For Airbus service information identified in this AD,
contact Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; fax +33 5 61 93 45 80, e-mail
airworthiness.A330-A340@airbus.com; Internet https://www.airbus.com.
For Messier-Dowty service information identified in this AD, contact
Messier Services Americas, Customer Support Center, 45360 Severn
Way, Sterling, Virginia 20166-8910; telephone 703-450-8233; fax 703-
404-1621; Internet https://techpubs.services.messier-dowty.com.
(3) You may review copies of the service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the availability of this material at
the FAA, call 425-227-1221 or 425-227-1152.
(4) You may also review copies of the service information that
is incorporated by reference at the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call 202-741-6030, or go to: https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

Issued in Renton, Washington, on July 2, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E9-17539 Filed 7-28-09; 8:45 am]
BILLING CODE 4910-13-P

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