Airworthiness Directives; Airbus Model A300 B2-1C, B2-203, B2K-3C, B4-103, B4-203, B4-2C Airplanes; Model A310 Airplanes; and Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, and B4-622R Airplanes, 48024-48028 [E9-22667]

Download as PDF 48024 Federal Register / Vol. 74, No. 181 / Monday, September 21, 2009 / Proposed Rules 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 European Aviation Safety Agency Airworthiness Directive 2008– 0072, dated April 18, 2008, for related information. Issued in Renton, Washington, on September 11, 2009. Stephen P. Boyd, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–22576 Filed 9–18–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0789; Directorate Identifier 2008–NM–185–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A300 B2–1C, B2–203, B2K–3C, B4–103, B4–203, B4–2C Airplanes; Model A310 Airplanes; and Model A300 B4–601, B4–603, B4–605R, B4–620, B4–622, and B4–622R Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). srobinson on DSKHWCL6B1PROD with PROPOSALS 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: Cracks have been found on pylon side panels (upper section) at rib 8 on Airbus A300, A310 and A300–600 aircraft equipped with General Electric engines. Investigation of these findings indicates that this problem is likely to affect aircraft of this type design with other engine installations. This condition, if not corrected, can lead to reduced strength [structural integrity] of the pylon primary structure. The unsafe condition is reduced structural integrity of the pylon primary structure, which could cause VerDate Nov<24>2008 18:23 Sep 18, 2009 Jkt 217001 detachment of the engine from the fuselage. The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI. DATES: We must receive comments on this proposed AD by November 5, 2009. 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—EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; e-mail: account.airworth-eas@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 or 425–227–1152. this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2009–0789; Directorate Identifier 2008–NM–185–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 have lengthened the 30-day comment period for proposed ADs that address MCAI originated by aviation authorities of other countries to provide adequate time for interested parties to submit comments. The comment period for these proposed ADs is now typically 45 days, which is consistent with the comment period for domestic transport ADs. 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. Examining the AD Docket Cracks have been found on pylon side panels (upper section) at rib 8 on Airbus A300, A310 and A300–600 aircraft equipped with General Electric engines. Investigation of these findings indicates that this problem is likely to affect aircraft of this type design with other engine installations. This condition, if not corrected, can lead to reduced strength [structural integrity] of the pylon primary structure. In order to detect any crack propagation at an early stage, thus avoiding an extensive repair, Airbus issued Service Bulletins (SB) A300–54–0075, A310–54–2018 and A300– 54–6015. * * * This AD requires the implementation of this * * * inspection programme. 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: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2125; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2008–0181, dated October 1, 2008 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: The unsafe condition is reduced structural integrity of the pylon primary structure, which could cause detachment of the engine from the fuselage. Required actions include repetitive detailed visual inspections, or repetitive eddy current and detailed visual inspections, to detect cracks, depending on the airplane configuration, and corrective actions if necessary. The corrective actions include repairing the cracking, and E:\FR\FM\21SEP1.SGM 21SEP1 Federal Register / Vol. 74, No. 181 / Monday, September 21, 2009 / Proposed Rules contacting Airbus for repair instructions and doing the repair, as applicable. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information Airbus has issued Mandatory Service Bulletins A300–54–0075, A310–54– 2018, and A300–54–6015, all Revision 02, all including Appendices 1, 2, and 3, all dated June 26, 2008. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. Depending on the model and engine type, the initial compliance times for doing the inspections range between 9,300 flight cycles since doing the repair or modification and 22,600 flight cycles or 45,200 flight hours, whichever occurs first, since doing the repair or modification; the repetitive intervals are between 5,300 flight cycles and 33,900 flight cycles or 67,800 flight hours, whichever occurs first. srobinson on DSKHWCL6B1PROD with PROPOSALS 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 Based on the service information, we estimate that this proposed AD would affect about 230 products of U.S. registry. We also estimate that it would VerDate Nov<24>2008 18:23 Sep 18, 2009 Jkt 217001 take about 4 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $80 per work-hour. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $73,600, or $320 per product. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this proposed AD would not have federalism implications 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, PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 48025 the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: Airbus: Docket No. FAA–2009–0789; Directorate Identifier 2008–NM–185–AD. Comments Due Date (a) We must receive comments by November 5, 2009. Affected ADs (b) None. Applicability (c) This AD applies to the airplanes, certificated in any category, identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD. (1) Airbus Model A300 B2–1C, A300 B2– 203, A300 B2K–3C, A300 B4–103, A300 B4– 203, and A300 B4–2C airplanes, all serial numbers incorporating Airbus modification 02434 or 03599; (2) Airbus Model A310–203, A310–204, A310–221, A310–222, A310–304, A310–322, A310–324, and A310–325 airplanes, all serial numbers, except airplanes incorporating Airbus modification 10432; (3) Airbus Model A300 B4–601, A300 B4– 603, A300 B4–605R, A300 B4–620, A300 B4– 622, and A300 B4–622R airplanes, all serial numbers, except airplanes incorporating Airbus modification 10432. Subject (d) Air Transport Association (ATA) of America Code 54: Nacelles/Pylons. Reason (e) The mandatory continuing airworthiness information (MCAI) states: Cracks have been found on pylon side panels (upper section) at rib 8 on Airbus A300, A310 and A300–600 aircraft equipped with General Electric engines. Investigation of these findings indicates that this problem is likely to affect aircraft of this type design with other engine installations. This condition, if not corrected, can lead to reduced strength [structural integrity] of the pylon primary structure. In order to detect any crack propagation at an early stage, thus avoiding an extensive repair, Airbus issued Service Bulletins (SB) A300–54–0075, A310–54–2018 and A300– 54–6015. * * * This AD requires the implementation of this * * * inspection programme. The unsafe condition is reduced structural integrity of the pylon primary structure, which could cause detachment of the engine from the fuselage. Required actions include repetitive detailed visual inspections, or repetitive eddy current and detailed visual inspections, to detect cracks, depending on the airplane configuration, and corrective E:\FR\FM\21SEP1.SGM 21SEP1 48026 Federal Register / Vol. 74, No. 181 / Monday, September 21, 2009 / Proposed Rules actions if necessary. The corrective actions include repairing the cracking, and contacting Airbus for repair instructions and doing the repair, as applicable. Actions and Compliance (f) Unless already done, do the following actions. (1) For Configuration 01 airplanes as identified in the applicable service bulletin identified in Table 2 of this AD: At the applicable time specified in Table 1 of this AD, except as required by paragraphs (f)(2) and (f)(3) of this AD, perform a detailed visual inspection of the pylons 1 and 2 side panels (upper section) at rib 8, in accordance with the Accomplishment Instructions of the applicable service bulletin identified in Table 2 of this AD. Repeat the inspection at the time specified in Table 1 of this AD. TABLE 1—COMPLIANCE TIMES FOR CONFIGURATION 1 For model— That have accumulated— Inspect before the accumulation of— And repeat the inspection at intervals not to exceed— Or within— Whichever occurs later ≤17,500 total flight cycles 1 5,350 total flight cycles ..... 2,500 flight cycles 2 ........... 4,300 flight cycles. >17,500 total flight 1 .......... 4,300 flight cycles. ≤18,000 total flight cycles 1 20,000 total flight cycles or 40,000 total flight hours, whichever occurs first. 5,350 total flight cycles ..... 250 flight cycles 2 .............. A300 B4–103, B4–203, and B4–2C airplanes. A300 B4–103, B4–203, and B4–2C airplanes. 2,000 flight cycles 2 ........... 4,300 flight cycles. 4,300 flight cycles. ≤18,000 total flight cycles 1 20,000 total flight cycles or 40,000 total flight hours, whichever occurs first. 4,200 total flight cycles ..... 250 flight cycles 2 .............. A300 B4–601, B4–603, B4–605R, B4–620, B4– 622, and B4–622R airplanes. A300 B4–601, B4–603, B4–605R, B4–620, B4– 622, and B4–622R airplanes. A310–200 airplanes with GE CF6–80A3 or Pratt & Whitney engines. A310–200 airplanes with GE CF6–80A3 or Pratt & Whitney engines. A310–200 airplanes with GE CF6–80C2 engines. 2,000 flight cycles 2 ........... 3,600 flight cycles. >18,000 total flight cycles 1 20,000 total flight cycles or 40,000 total flight hours, whichever occurs first. 250 flight cycles 2 .............. 3,600 flight cycles. ≤18,000 total flight cycles 1 >18,000 total flight cycles 1 A310–300 SR 3 airplanes with Pratt & Whitney JT9D engines. A310–300 SR 3 airplanes with Pratt & Whitney JT9D engines. A310–300 SR 3 airplanes with GE engines. ≤18,000 total flight cycles 1 A310–300 SR 2 airplanes with GE engines. >18,000 total flight cycles 1 A310–300 SR 3 airplanes with Pratt & Whitney 4000 engines. A310–300 SR 3 airplanes with Pratt & Whitney 4000 engines. A310–300 LR 4 airplanes with Pratt & Whitney JT9D engines. A310–300 LR 4 airplanes with Pratt & Whitney JT9D engines. A310–300 LR 4 airplanes with GE engines. ≤18,000 total flight cycles 1 9,700 total flight cycles or 19,400 total flight hours, whichever occurs first. 19,500 total flight cycles or 55,500 total flight hours, whichever occurs first. 7,800 total flight cycles or 15,600 total flight hours, whichever occurs first. 19,500 total flight cycles or 55,500 total flight hours, whichever occurs first. 8,600 total flight cycles or 24,000 total flight hours, whichever occurs first. 19,500 total flight cycles or 55,500 total flight hours, whichever occurs first. 7,000 total flight cycles or 19,600 total flight hours, whichever occurs first. 19,500 total flight cycles or 55,500 total flight hours, whichever occurs first. 7,000 total flight cycles or 19,600 total flight hours, whichever occurs first. 19,500 total flight cycles or 55,500 total flight hours, whichever occurs first. 5,900 total flight cycles or 29,500 total flight hours, whichever occurs first. 19,500 total flight cycles or 55,500 total flight hours, whichever occurs first. 4,800 total flight cycles or 24,100 total flight hours, whichever occurs first. 1,500 flight cycles 2 ........... A310–200 airplanes with GE CF6–80C2 engines. srobinson on DSKHWCL6B1PROD with PROPOSALS A300 B2–1C, B2–203, and B2K–3C airplanes. A300 B2–1C, B2–203, and B2K–3C airplanes. 6,700 flight cycles or 13,400 flight hours, whichever occurs first. 6,700 flight cycles or 13,400 flight hours, whichever occurs first. 5,800 flight cycles or 11,600 flight hours, whichever occurs first. 5,800 flight cycles or 11,600 flight hours, whichever occurs first. 6,700 flight cycles or 18,700 flight hours, whichever occurs first. 6,700 flight cycles or 18,700 flight hours, whichever occurs first. 5,700 flight cycles or 15,900 flight hours, whichever occurs first. 5,700 flight cycles or 15,900 flight hours, whichever occurs first. 5,800 flight cycles or 16,200 flight hours, whichever occurs first. 5,800 flight cycles or 16,200 flight hours, whichever occurs first. 6,000 flight cycles or 30,300 flight hours, whichever occurs first. 6,000 flight cycles or 30,300 flight hours, whichever occurs first. 5,100 flight cycles or 25,500 flight hours, whichever occurs first. VerDate Nov<24>2008 >18,000 total flight cycles 1 >18,000 total flight cycles 1 ≤18,000 total flight cycles 1 >18,000 total flight cycles 1 ≤18,000 total flight cycles 1 >18,000 total flight cycles 1 ≤18,000 total flight cycles 1 >18,000 total flight cycles 1 ≤18,000 total flight cycles 1 18:23 Sep 18, 2009 Jkt 217001 PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 250 flight cycles 2 .............. 1,500 flight cycles 2 ........... 250 flight cycles 2 .............. 1,500 total flight cycles 2 ... 250 flight cycles 2 .............. 1,500 flight cycles 2 ........... 250 flight cycles 2 .............. 1,500 flight cycles 2 ........... 250 flight cycles 2 .............. 1,500 flight cycles 2 ........... 250 flight cycles 2 .............. 1,500 flight cycles 2 ........... E:\FR\FM\21SEP1.SGM 21SEP1 48027 Federal Register / Vol. 74, No. 181 / Monday, September 21, 2009 / Proposed Rules TABLE 1—COMPLIANCE TIMES FOR CONFIGURATION 1—Continued For model— That have accumulated— Inspect before the accumulation of— And repeat the inspection at intervals not to exceed— Or within— Whichever occurs later A310–300 LR 4 airplanes with GE engines. >18,000 total flight cycles 1 A310–300 LR 4 airplanes with Pratt & Whitney 4000 engines. A310–300 LR 4 airplanes with Pratt & Whitney 4000 engines. ≤18,000 total flight cycles 1 >18,000 total flight cycles 1 19,500 total flight cycles or 55,500 total flight hours, whichever occurs first. 4,800 total flight cycles or 24,000 total flight hours, whichever occurs first. 19,500 total flight cycles or 55,500 total flight hours, whichever occurs first. 250 flight cycles 2 .............. 1,500 flight cycles 2 ........... 250 flight cycles 2 .............. 5,100 flight cycles or 25,500 flight hours, whichever occurs first. 5,200 flight cycles or 26,300 flight hours, whichever occurs first. 5,200 flight cycles or 26,300 flight hours, whichever occurs first. 1 As of the effective date of this AD the effective date of this AD 3 ‘‘SR’’ applies to airplanes with average flights less than 4 flight hours. 4 ‘‘LR’’ refers to airplanes with average flights of 4 or more flight hours. 2 After (2) For Model A300 and A300–600 airplanes that have accumulated more than 40,000 total flight hours as of the effective date of this AD: Within 250 flight cycles after the effective date of this AD, do the actions specified in paragraph (f)(1) of this AD. (3) For Model A310 airplanes that have accumulated more than 55,500 total flight hours as of the effective date of this AD: Within 250 flight cycles after the effective date of this AD, do the actions specified in paragraph (f)(1) of this AD. (4) For Configuration 01 airplanes, as identified in the applicable service bulletin identified in Table 2 of this AD: If a crack is found during any inspection required by this AD, before further flight, install a doubler, in accordance with the Accomplishment Instructions of the applicable service bulletin identified in Table 2 of this AD. (5) For Configuration 02 airplanes, as identified in the applicable service bulletin identified in Table 2 of this AD: At the applicable time specified in paragraph 1.E.(2) of the applicable service bulletin identified in Table 2 of this AD, or within 250 flight cycles after the effective date of this AD, whichever occurs later, perform a detailed visual inspection of the pylons 1 and 2 side panels (upper section) at rib 8, in accordance with the Accomplishment Instructions of the applicable service bulletin identified in Table 2 of this AD. (6) For Configuration 03 airplanes, as identified in the applicable service bulletin identified in Table 2 of this AD: At the applicable time specified in paragraph 1.E.(2) of the applicable service bulletin identified in Table 2 of this AD, or within 250 flight cycles after the effective date of this AD, whichever occurs later, perform a detailed visual inspection, and a high frequency eddy current inspection as applicable, of the pylons 1 and 2 side panels (upper section) at rib 8, in accordance with the Accomplishment Instructions of the applicable service bulletin identified in Table 2 of this AD. (7) For Configuration 02 and 03 airplanes, as identified in the applicable service bulletin identified in Table 2 of this AD: If a crack is found during any inspection required by paragraph (f)(1), (f)(5), or (f)(6) of this AD, before further flight, repair in accordance with the Accomplishment Instructions of the applicable service bulletin identified in Table 2 of this AD. (8) For all airplanes, except those in Configuration 01, as identified in the applicable service bulletin identified in Table 2 of this AD: Repeat the inspection specified in paragraph (f)(1), (f)(5), or (f)(6) of this AD, as applicable, at the intervals specified in paragraph 1.E.(2) of the applicable service bulletin identified in Table 2 of this AD. TABLE 2—SERVICE BULLETINS For model— Use Airbus mandatory Service Bulletin— A300 B2–1C, B2–203, B2K–3C, B4–103, B4–203, and B4–2C airplanes. A310 airplanes .......................................................... A300 B4–601, B4–603, B4–605R, B4–620, B4–622, and B4–622R airplanes. A300–54–0075, excluding Appendices 1, 2, and 3 02 June 26, 2008. A310–54–2018, excluding Appendices 1, 2, and 3 A300–54–6015, excluding Appendices 1, 2, and 3 02 02 June 26, 2008. June 26, 2008. (9) Inspections and corrective actions accomplished prior to the effective date of this AD in accordance with the service bulletins identified in Table 3 of this AD, as applicable to airplane model, are acceptable Revision— Dated— for compliance with the corresponding requirements of this AD. TABLE 3—AIRBUS SERVICE INFORMATION srobinson on DSKHWCL6B1PROD with PROPOSALS Service Bulletin— Revision— Dated— Airbus Airbus Airbus Airbus Airbus Airbus Original ...................... 01 .............................. Original ...................... 01 .............................. Original ...................... 01 .............................. August 11, 1993. November 9, 2007. August 11, 1993. November 16, 2007. August 11, 1993. November 9, 2007. Service Bulletin A300–54–0075 ........................................................................................... Mandatory Service Bulletin A300–54–0075 ......................................................................... Service Bulletin A310–54–2018 ........................................................................................... Mandatory Service Bulletin A310–54–2018 ......................................................................... Service Bulletin A300–54–6015 ........................................................................................... Mandatory Service Bulletin A300–54–6015 ......................................................................... VerDate Nov<24>2008 18:23 Sep 18, 2009 Jkt 217001 PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 E:\FR\FM\21SEP1.SGM 21SEP1 48028 Federal Register / Vol. 74, No. 181 / Monday, September 21, 2009 / Proposed Rules FAA AD Differences DEPARTMENT OF TRANSPORTATION Note 1: This AD differs from the MCAI and/or service information as follows: Although the MCAI/service information allows further flight after cracks are found during compliance with certain actions, this AD requires that you repair the crack(s) before further flight. Federal Aviation Administration Other FAA AD Provisions Airworthiness Directives; Empresa ´ Brasileira de Aeronautica S.A. (EMBRAER) Model EMB–500 Airplanes (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: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2125; fax (425) 227–1149. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate 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: 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 srobinson on DSKHWCL6B1PROD with PROPOSALS (h) Refer to MCAI European Aviation Safety Agency (EASA) Airworthiness Directive 2008–0181, dated October 1, 2008; and the service bulletins identified in Table 2 of this AD; for related information. Issued in Renton, Washington, on September 11, 2009. Stephen P. Boyd, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–22667 Filed 9–18–09; 8:45 am] BILLING CODE 4910–13–P VerDate Nov<24>2008 18:23 Sep 18, 2009 Jkt 217001 14 CFR Part 39 [Docket No. FAA–2009–0870; Directorate Identifier 2009–CE–049–AD] RIN 2120–AA64 AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). SUMMARY: We propose to adopt a new airworthiness directive (AD) for the products listed above. 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: It has been found the possibility of elevator mass balance fasteners becoming slack under certain conditions. The loose of at least two fasteners may lead to an unbalance condition, which may induce flutter on airplane elevators. The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI. DATES: We must receive comments on this proposed AD by November 5, 2009. 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 W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments PO 00000 Frm 00016 Fmt 4702 Sfmt 4702 received, and other information. The street address for the Docket Office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Karl Schletzbaum, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4146; fax: (816) 329–4090. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2009–0870; Directorate Identifier 2009–CE–049–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to 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 ˆ The Agencia Nacional de Aviacao ¸˜ Civil (ANAC), which is the aviation authority for Brazil, has issued AD No.: 2009–09–01, dated September 3, 2009 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: It has been found the possibility of elevator mass balance fasteners becoming slack under certain conditions. The loose of at least two fasteners may lead to an unbalance condition, which may induce flutter on airplane elevators. The MCAI requires replacement of the nuts of the right and left elevators mass balance fasteners. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information Embraer—Empresa Brasileira de Aeronautica S.A. has issued Phenom by Embraer Service Bulletin No. 500–55– 0001, dated July 24, 2009. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. E:\FR\FM\21SEP1.SGM 21SEP1

Agencies

[Federal Register Volume 74, Number 181 (Monday, September 21, 2009)]
[Proposed Rules]
[Pages 48024-48028]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-22667]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0789; Directorate Identifier 2008-NM-185-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus Model A300 B2-1C, B2-203, B2K-
3C, B4-103, B4-203, B4-2C Airplanes; Model A310 Airplanes; and Model
A300 B4-601, B4-603, B4-605R, B4-620, B4-622, and B4-622R 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:

The unsafe condition is reduced structural integrity of the pylon
primary structure, which could cause detachment of the engine from the
fuselage. The proposed AD would require actions that are intended to
address the unsafe condition described in the MCAI.

DATES: We must receive comments on this proposed AD by November 5,
2009.

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--EAW (Airworthiness
Office), 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; e-mail:
account.airworth-eas@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 or 425-227-1152.

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: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-2125; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2009-0789;
Directorate Identifier 2008-NM-185-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 have lengthened the 30-day comment period for proposed ADs that
address MCAI originated by aviation authorities of other countries to
provide adequate time for interested parties to submit comments. The
comment period for these proposed ADs is now typically 45 days, which
is consistent with the comment period for domestic transport ADs.
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 Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2008-0181, dated October 1, 2008 (referred to
after this as ``the MCAI''), to correct an unsafe condition for the
specified products. The MCAI states:

Cracks have been found on pylon side panels (upper section) at
rib 8 on Airbus A300, A310 and A300-600 aircraft equipped with
General Electric engines. Investigation of these findings indicates
that this problem is likely to affect aircraft of this type design
with other engine installations. This condition, if not corrected,
can lead to reduced strength [structural integrity] of the pylon
primary structure.
In order to detect any crack propagation at an early stage, thus
avoiding an extensive repair, Airbus issued Service Bulletins (SB)
A300-54-0075, A310-54-2018 and A300-54-6015. * * *
This AD requires the implementation of this * * * inspection
programme.

The unsafe condition is reduced structural integrity of the pylon
primary structure, which could cause detachment of the engine from the
fuselage. Required actions include repetitive detailed visual
inspections, or repetitive eddy current and detailed visual
inspections, to detect cracks, depending on the airplane configuration,
and corrective actions if necessary. The corrective actions include
repairing the cracking, and

[[Page 48025]]

contacting Airbus for repair instructions and doing the repair, as
applicable.
You may obtain further information by examining the MCAI in the AD
docket.

Relevant Service Information

Airbus has issued Mandatory Service Bulletins A300-54-0075, A310-
54-2018, and A300-54-6015, all Revision 02, all including Appendices 1,
2, and 3, all dated June 26, 2008. The actions described in this
service information are intended to correct the unsafe condition
identified in the MCAI.
Depending on the model and engine type, the initial compliance
times for doing the inspections range between 9,300 flight cycles since
doing the repair or modification and 22,600 flight cycles or 45,200
flight hours, whichever occurs first, since doing the repair or
modification; the repetitive intervals are between 5,300 flight cycles
and 33,900 flight cycles or 67,800 flight hours, whichever occurs
first.

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

Based on the service information, we estimate that this proposed AD
would affect about 230 products of U.S. registry. We also estimate that
it would take about 4 work-hours per product to comply with the basic
requirements of this proposed AD. The average labor rate is $80 per
work-hour. Based on these figures, we estimate the cost of the proposed
AD on U.S. operators to be $73,600, or $320 per product.

Authority for This Rulemaking

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

Regulatory Findings

We determined that this proposed AD would not have federalism
implications 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.

Sec. 39.13 [Amended]

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

Airbus: Docket No. FAA-2009-0789; Directorate Identifier 2008-NM-
185-AD.

Comments Due Date

(a) We must receive comments by November 5, 2009.

Affected ADs

(b) None.

Applicability

(c) This AD applies to the airplanes, certificated in any
category, identified in paragraphs (c)(1), (c)(2), and (c)(3) of
this AD.
(1) Airbus Model A300 B2-1C, A300 B2-203, A300 B2K-3C, A300 B4-
103, A300 B4-203, and A300 B4-2C airplanes, all serial numbers
incorporating Airbus modification 02434 or 03599;
(2) Airbus Model A310-203, A310-204, A310-221, A310-222, A310-
304, A310-322, A310-324, and A310-325 airplanes, all serial numbers,
except airplanes incorporating Airbus modification 10432;
(3) Airbus Model A300 B4-601, A300 B4-603, A300 B4-605R, A300
B4-620, A300 B4-622, and A300 B4-622R airplanes, all serial numbers,
except airplanes incorporating Airbus modification 10432.

Subject

(d) Air Transport Association (ATA) of America Code 54:
Nacelles/Pylons.

Reason

(e) The mandatory continuing airworthiness information (MCAI)
states:
Cracks have been found on pylon side panels (upper section) at
rib 8 on Airbus A300, A310 and A300-600 aircraft equipped with
General Electric engines. Investigation of these findings indicates
that this problem is likely to affect aircraft of this type design
with other engine installations. This condition, if not corrected,
can lead to reduced strength [structural integrity] of the pylon
primary structure.
In order to detect any crack propagation at an early stage, thus
avoiding an extensive repair, Airbus issued Service Bulletins (SB)
A300-54-0075, A310-54-2018 and A300-54-6015. * * *
This AD requires the implementation of this * * * inspection
programme.

The unsafe condition is reduced structural integrity of the pylon
primary structure, which could cause detachment of the engine from
the fuselage. Required actions include repetitive detailed visual
inspections, or repetitive eddy current and detailed visual
inspections, to detect cracks, depending on the airplane
configuration, and corrective

[[Page 48026]]

actions if necessary. The corrective actions include repairing the
cracking, and contacting Airbus for repair instructions and doing
the repair, as applicable.

Actions and Compliance

(f) Unless already done, do the following actions.
(1) For Configuration 01 airplanes as identified in the
applicable service bulletin identified in Table 2 of this AD: At the
applicable time specified in Table 1 of this AD, except as required
by paragraphs (f)(2) and (f)(3) of this AD, perform a detailed
visual inspection of the pylons 1 and 2 side panels (upper section)
at rib 8, in accordance with the Accomplishment Instructions of the
applicable service bulletin identified in Table 2 of this AD. Repeat
the inspection at the time specified in Table 1 of this AD.

Table 1--Compliance Times for Configuration 1
----------------------------------------------------------------------------------------------------------------
And repeat the
That have Inspect before the inspection at
For model-- accumulated-- accumulation of-- Or within-- intervals not to
exceed--

---------Whichever occurs later---------
----------------------------------------------------------------------------------------------------------------
A300 B2-1C, B2-203, and B2K-3C <=17,500 total 5,350 total flight 2,500 flight 4,300 flight
airplanes. flight cycles \1\. cycles. cycles \2\. cycles.
A300 B2-1C, B2-203, and B2K-3C >17,500 total 20,000 total 250 flight cycles 4,300 flight
airplanes. flight \1\. flight cycles or \2\. cycles.
40,000 total
flight hours,
whichever occurs
first.
A300 B4-103, B4-203, and B4-2C <=18,000 total 5,350 total flight 2,000 flight 4,300 flight
airplanes. flight cycles \1\. cycles. cycles \2\. cycles.
A300 B4-103, B4-203, and B4-2C >18,000 total 20,000 total 250 flight cycles 4,300 flight
airplanes. flight cycles \1\. flight cycles or \2\. cycles.
40,000 total
flight hours,
whichever occurs
first.
A300 B4-601, B4-603, B4-605R, B4- <=18,000 total 4,200 total flight 2,000 flight 3,600 flight
620, B4-622, and B4-622R flight cycles \1\. cycles. cycles \2\. cycles.
airplanes.
A300 B4-601, B4-603, B4-605R, B4- >18,000 total 20,000 total 250 flight cycles 3,600 flight
620, B4-622, and B4-622R flight cycles \1\. flight cycles or \2\. cycles.
airplanes. 40,000 total
flight hours,
whichever occurs
first.
A310-200 airplanes with GE CF6- <=18,000 total 9,700 total flight 1,500 flight 6,700 flight
80A3 or Pratt & Whitney engines. flight cycles \1\. cycles or 19,400 cycles \2\. cycles or 13,400
total flight flight hours,
hours, whichever whichever occurs
occurs first. first.
A310-200 airplanes with GE CF6- >18,000 total 19,500 total 250 flight cycles 6,700 flight
80A3 or Pratt & Whitney engines. flight cycles \1\. flight cycles or \2\. cycles or 13,400
55,500 total flight hours,
flight hours, whichever occurs
whichever occurs first.
first.
A310-200 airplanes with GE CF6- <=18,000 total 7,800 total flight 1,500 flight 5,800 flight
80C2 engines. flight cycles \1\. cycles or 15,600 cycles \2\. cycles or 11,600
total flight flight hours,
hours, whichever whichever occurs
occurs first. first.
A310-200 airplanes with GE CF6- >18,000 total 19,500 total 250 flight cycles 5,800 flight
80C2 engines. flight cycles \1\. flight cycles or \2\. cycles or 11,600
55,500 total flight hours,
flight hours, whichever occurs
whichever occurs first.
first.
A310-300 SR \3\ airplanes with <=18,000 total 8,600 total flight 1,500 total flight 6,700 flight
Pratt & Whitney JT9D engines. flight cycles \1\. cycles or 24,000 cycles \2\. cycles or 18,700
total flight flight hours,
hours, whichever whichever occurs
occurs first. first.
A310-300 SR \3\ airplanes with >18,000 total 19,500 total 250 flight cycles 6,700 flight
Pratt & Whitney JT9D engines. flight cycles \1\. flight cycles or \2\. cycles or 18,700
55,500 total flight hours,
flight hours, whichever occurs
whichever occurs first.
first.
A310-300 SR \3\ airplanes with <=18,000 total 7,000 total flight 1,500 flight 5,700 flight
GE engines. flight cycles \1\. cycles or 19,600 cycles \2\. cycles or 15,900
total flight flight hours,
hours, whichever whichever occurs
occurs first. first.
A310-300 SR \2\ airplanes with >18,000 total 19,500 total 250 flight cycles 5,700 flight
GE engines. flight cycles \1\. flight cycles or \2\. cycles or 15,900
55,500 total flight hours,
flight hours, whichever occurs
whichever occurs first.
first.
A310-300 SR \3\ airplanes with <=18,000 total 7,000 total flight 1,500 flight 5,800 flight
Pratt & Whitney 4000 engines. flight cycles \1\. cycles or 19,600 cycles \2\. cycles or 16,200
total flight flight hours,
hours, whichever whichever occurs
occurs first. first.
A310-300 SR \3\ airplanes with >18,000 total 19,500 total 250 flight cycles 5,800 flight
Pratt & Whitney 4000 engines. flight cycles \1\. flight cycles or \2\. cycles or 16,200
55,500 total flight hours,
flight hours, whichever occurs
whichever occurs first.
first.
A310-300 LR \4\ airplanes with <=18,000 total 5,900 total flight 1,500 flight 6,000 flight
Pratt & Whitney JT9D engines. flight cycles \1\. cycles or 29,500 cycles \2\. cycles or 30,300
total flight flight hours,
hours, whichever whichever occurs
occurs first. first.
A310-300 LR \4\ airplanes with >18,000 total 19,500 total 250 flight cycles 6,000 flight
Pratt & Whitney JT9D engines. flight cycles \1\. flight cycles or \2\. cycles or 30,300
55,500 total flight hours,
flight hours, whichever occurs
whichever occurs first.
first.
A310-300 LR \4\ airplanes with <=18,000 total 4,800 total flight 1,500 flight 5,100 flight
GE engines. flight cycles \1\. cycles or 24,100 cycles \2\. cycles or 25,500
total flight flight hours,
hours, whichever whichever occurs
occurs first. first.

[[Page 48027]]

A310-300 LR \4\ airplanes with >18,000 total 19,500 total 250 flight cycles 5,100 flight
GE engines. flight cycles \1\. flight cycles or \2\. cycles or 25,500
55,500 total flight hours,
flight hours, whichever occurs
whichever occurs first.
first.
A310-300 LR \4\ airplanes with <=18,000 total 4,800 total flight 1,500 flight 5,200 flight
Pratt & Whitney 4000 engines. flight cycles \1\. cycles or 24,000 cycles \2\. cycles or 26,300
total flight flight hours,
hours, whichever whichever occurs
occurs first. first.
A310-300 LR \4\ airplanes with >18,000 total 19,500 total 250 flight cycles 5,200 flight
Pratt & Whitney 4000 engines. flight cycles \1\. flight cycles or \2\. cycles or 26,300
55,500 total flight hours,
flight hours, whichever occurs
whichever occurs first.
first.
----------------------------------------------------------------------------------------------------------------
\1\ As of the effective date of this AD
\2\ After the effective date of this AD
\3\ ``SR'' applies to airplanes with average flights less than 4 flight hours.
\4\ ``LR'' refers to airplanes with average flights of 4 or more flight hours.

(2) For Model A300 and A300-600 airplanes that have accumulated
more than 40,000 total flight hours as of the effective date of this
AD: Within 250 flight cycles after the effective date of this AD, do
the actions specified in paragraph (f)(1) of this AD.
(3) For Model A310 airplanes that have accumulated more than
55,500 total flight hours as of the effective date of this AD:
Within 250 flight cycles after the effective date of this AD, do the
actions specified in paragraph (f)(1) of this AD.
(4) For Configuration 01 airplanes, as identified in the
applicable service bulletin identified in Table 2 of this AD: If a
crack is found during any inspection required by this AD, before
further flight, install a doubler, in accordance with the
Accomplishment Instructions of the applicable service bulletin
identified in Table 2 of this AD.
(5) For Configuration 02 airplanes, as identified in the
applicable service bulletin identified in Table 2 of this AD: At the
applicable time specified in paragraph 1.E.(2) of the applicable
service bulletin identified in Table 2 of this AD, or within 250
flight cycles after the effective date of this AD, whichever occurs
later, perform a detailed visual inspection of the pylons 1 and 2
side panels (upper section) at rib 8, in accordance with the
Accomplishment Instructions of the applicable service bulletin
identified in Table 2 of this AD.
(6) For Configuration 03 airplanes, as identified in the
applicable service bulletin identified in Table 2 of this AD: At the
applicable time specified in paragraph 1.E.(2) of the applicable
service bulletin identified in Table 2 of this AD, or within 250
flight cycles after the effective date of this AD, whichever occurs
later, perform a detailed visual inspection, and a high frequency
eddy current inspection as applicable, of the pylons 1 and 2 side
panels (upper section) at rib 8, in accordance with the
Accomplishment Instructions of the applicable service bulletin
identified in Table 2 of this AD.
(7) For Configuration 02 and 03 airplanes, as identified in the
applicable service bulletin identified in Table 2 of this AD: If a
crack is found during any inspection required by paragraph (f)(1),
(f)(5), or (f)(6) of this AD, before further flight, repair in
accordance with the Accomplishment Instructions of the applicable
service bulletin identified in Table 2 of this AD.
(8) For all airplanes, except those in Configuration 01, as
identified in the applicable service bulletin identified in Table 2
of this AD: Repeat the inspection specified in paragraph (f)(1),
(f)(5), or (f)(6) of this AD, as applicable, at the intervals
specified in paragraph 1.E.(2) of the applicable service bulletin
identified in Table 2 of this AD.

Table 2--Service Bulletins
----------------------------------------------------------------------------------------------------------------
Use Airbus mandatory
For model-- Service Bulletin-- Revision-- Dated--
----------------------------------------------------------------------------------------------------------------
A300 B2-1C, B2-203, B2K-3C, B4-103, A300-54-0075, excluding 02 June 26, 2008.
B4-203, and B4-2C airplanes. Appendices 1, 2, and 3.
A310 airplanes....................... A310-54-2018, excluding 02 June 26, 2008.
Appendices 1, 2, and 3.
A300 B4-601, B4-603, B4-605R, B4-620, A300-54-6015, excluding 02 June 26, 2008.
B4-622, and B4-622R airplanes. Appendices 1, 2, and 3.
----------------------------------------------------------------------------------------------------------------

(9) Inspections and corrective actions accomplished prior to
the effective date of this AD in accordance with the service
bulletins identified in Table 3 of this AD, as applicable to
airplane model, are acceptable for compliance with the corresponding
requirements of this AD.

Table 3--Airbus Service Information
----------------------------------------------------------------------------------------------------------------
Service Bulletin-- Revision-- Dated--
----------------------------------------------------------------------------------------------------------------
Airbus Service Bulletin A300-54-0075.. Original........................... August 11, 1993.
Airbus Mandatory Service Bulletin A300- 01................................. November 9, 2007.
54-0075.
Airbus Service Bulletin A310-54-2018.. Original........................... August 11, 1993.
Airbus Mandatory Service Bulletin A310- 01................................. November 16, 2007.
54-2018.
Airbus Service Bulletin A300-54-6015.. Original........................... August 11, 1993.
Airbus Mandatory Service Bulletin A300- 01................................. November 9, 2007.
54-6015.
----------------------------------------------------------------------------------------------------------------

[[Page 48028]]

FAA AD Differences

Note 1: This AD differs from the MCAI and/or service
information as follows: Although the MCAI/service information allows
further flight after cracks are found during compliance with certain
actions, this AD requires that you repair the crack(s) before
further flight.

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: Dan
Rodina, Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington
98057-3356; telephone (425) 227-2125; fax (425) 227-1149. Before
using any approved AMOC on any airplane to which the AMOC applies,
notify your appropriate 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: 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 European Aviation Safety Agency (EASA)
Airworthiness Directive 2008-0181, dated October 1, 2008; and the
service bulletins identified in Table 2 of this AD; for related
information.

Issued in Renton, Washington, on September 11, 2009.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E9-22667 Filed 9-18-09; 8:45 am]
BILLING CODE 4910-13-P

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