Airworthiness Directives; Airbus Airplanes, 62673-62678 [2011-26113]

Download as PDF Federal Register / Vol. 76, No. 196 / Tuesday, October 11, 2011 / Proposed Rules This condition, if not corrected, and if occurring while the RAT is deployed, could result in a degraded direct current power which is distributed to essential aeroplane systems and therefore aeroplane operations might be impaired. * * * * * Actions (g) Within 28 months after the effective date of this AD, replace any RAT TRU having P/N 5913703 with a RAT TRU having P/N 5915825, in accordance with the Accomplishment Instructions of Dassault Mandatory Service Bulletin 7X–163, dated December 1, 2010. Parts Installation (h) As of the effective date of this AD, no person may install any RAT TRU having P/N 5913703, on any airplane. FAA AD Differences srobinson on DSK4SPTVN1PROD with PROPOSALS Other FAA AD Provisions (i) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to Attn: Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057– 3356; telephone (425) 227–1137; fax (425) 227–1149: Information may be e-mailed to: 9ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding 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. Related Information (j) Refer to MCAI European Aviation Safety Agency Airworthiness Directive 2011–0008, dated January 18, 2011; and Dassault Mandatory Service Bulletin 7X–163, dated December 1, 2010; for related information. Jkt 223001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–1066; Directorate Identifier 2011–NM–050–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD), for certain Airbus Model A300 B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and B4–203 airplanes and Model A300 B4–601, B4– 603, B4–620, B4–622, B4–605R, B4– 622R, and F4–605R airplanes, that would supersede an existing AD. This proposed AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: SUMMARY: Note 1: This AD differs from the MCAI and/or service information as follows: No differences. 17:42 Oct 07, 2011 [FR Doc. 2011–26112 Filed 10–7–11; 8:45 am] BILLING CODE 4910–13–P Compliance (f) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. VerDate Mar<15>2010 Issued in Renton, Washington, on September 28, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. Following the occurrence of cracks on the MLG [main landing gear] Rib 5 RH [righthand] and LH [left-hand] attachment fitting ´ ´ lower flanges, DGAC [Direction Generale de l’Aviation Civile] France AD 2003–318(B) was issued to require repetitive inspections and, as terminating action * * * [.] Subsequently, new cases of cracks were discovered during scheduled maintenance checks by operators of A300B4 and A300– 600 type aeroplanes on which the terminating action * * * [was] embodied. This condition, if not corrected, could affect the structural integrity of those aeroplanes. * * * * * 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 25, 2011. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: (202) 493–2251. • Mail: U.S. Department of Transportation, Docket Operations, PO 00000 Frm 00030 Fmt 4702 Sfmt 4702 62673 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, 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 http://www.airbus.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227– 1221. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this 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–2011–1066; Directorate Identifier 2011–NM–050–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any E:\FR\FM\11OCP1.SGM 11OCP1 62674 Federal Register / Vol. 76, No. 196 / Tuesday, October 11, 2011 / Proposed Rules personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion srobinson on DSK4SPTVN1PROD with PROPOSALS On November 3, 2010, we issued AD 2010–23–26, Amendment 39–16516 (75 FR 74610, December 1, 2010). That AD required actions intended to address an unsafe condition on the products listed above. Since we issued AD 2010–23–26, Amendment 39–16516 (75 FR 74610, December 1, 2010), we have determined that it is necessary to mandate the optional spot-facing modification specified in paragraph (q) of the existing AD: The European Aviation Safety Agency (EASA), which is the aviation authority for the Member States of the European Community, has issued EASA Airworthiness Directive 2011–0029, dated February 24, 2011 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: Following the occurrence of cracks on the MLG [main landing gear] Rib 5 RH [righthand] and LH [left-hand] attachment fitting ´ ´ lower flanges, DGAC [Direction Generale de l’Aviation Civile] France AD 2003–318(B) was issued to require repetitive inspections and, as terminating action, the embodiment of Airbus Service Bulletins (SB) A300–57– 0235 and A300–57–6088 * * *. Subsequently, new cases of cracks were discovered during scheduled maintenance checks by operators of A300B4 and A300– 600 type aeroplanes on which the terminating action SB’s were embodied. This condition, if not corrected, could affect the structural integrity of those aeroplanes. To address and correct this condition, Airbus developed an inspection programme for aeroplanes modified in accordance with SB A300–57–0235 or A300–57–6088. This inspection programme was required to be implemented by DGAC France AD F–2005– 113, original issue and later revision 1 [parallel to part of FAA AD 2006–12–13, Amendment 39–14639 (71 FR 33994, June 13, 2006)]. A new EASA [European Aviation Safety Agency] AD 2008–0111, superseding DGAC France AD F–2005–113R1, was issued to reduce the applicability. For aeroplanes already compliant with DGAC France AD F– 2005–113R1, no further action was required. Since EASA AD 2008–0111 issuance, Airbus reviewed the inspection programmes of SB A300–57A0246 and SB A300–57A6101 to introduce repetitive inspections including a new inspection technique for holes 47 and 54 and to reduce inspections threshold and intervals from 700 Flight Cycles (FC) to 400 FC until a revised terminating action is made available. For the reasons stated above, EASA AD 2009–0081 superseded EASA AD 2008–0111 and required operators to comply with the new inspection programme introduced in VerDate Mar<15>2010 17:42 Oct 07, 2011 Jkt 223001 Revisions 3 of Airbus SB A300–57A0246 and Airbus SB A300–57A6101. EASA AD 2009–0081 R1 [which corresponds to FAA AD 2010–23–26, Amendment 39–16516 (75 FR 74610, December 1, 2010)] has been published to introduce an optional terminating action which consisted of spot-facing the sensitive holes of the MLG Rib 5 (LH and RH) bottom flanges. Later discussions with Airbus have demonstrated the necessity to require the spot-facing modification as a final solution (no longer optional). This new [EASA] AD retains the inspection requirements of EASA AD 2009–0081 R1, which is superseded, and requires the spot-facing of sensitive holes of the MLG Rib 5 (LH and RH) bottom flanges as terminating action. Required actions include repairing discrepancies (e.g., cracking or a 2nd oversize or greater fastener hole). You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information Airbus has issued Mandatory Service Bulletins A300–57–0254, Revision 01, including Appendix 1, dated June 14, 2011; and A300–57–6110, Revision 01, including Appendix 1, dated June 6, 2011. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. FAA’s Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design. Differences Between This AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information. We might also have proposed different actions in this AD from those in the MCAI in order to follow FAA policies. Any such differences are PO 00000 Frm 00031 Fmt 4702 Sfmt 4702 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 155 products of U.S. registry. The actions that are required by AD 2010–23–26, Amendment 39–16516 (75 FR 74610, December 1, 2010), and retained in this AD take about 79 workhours per product, at an average labor rate of $85 per work hour. Required parts cost about $10,270 per product. Based on these figures, the estimated cost of the currently required actions is $16,985 per product. We estimate that it would take about 100 work-hours per product to comply with the new basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $1,317,500, or $8,500 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; E:\FR\FM\11OCP1.SGM 11OCP1 Federal Register / Vol. 76, No. 196 / Tuesday, October 11, 2011 / Proposed Rules 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: Airbus: Docket No. FAA–2011–1066; Directorate Identifier 2011–NM–050–AD. Comments Due Date (a) We must receive comments by November 25, 2011. Affected ADs (b) This AD supersedes AD 2010–23–26, Amendment 39–16516 (75 FR 74610, December 1, 2010). * * * Restatement of Requirements of AD 2000– 05–07, Amendment 39–11616 (65 FR 12077, March 8, 2000): Subject Reason [Amended] * (c) This AD applies to the airplanes, certificated in any category, identified in paragraphs (c)(1) and (c)(2) of this AD; except airplanes on which Airbus Modification 11912 or 11932 has been installed. (1) Airbus Model A300 B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and B4–203 airplanes. (2) Airbus Model A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4–622R, and F4–605R airplanes. 1. The authority citation for part 39 continues to read as follows: 2. The FAA amends § 39.13 by removing Amendment 39–16516 (75 FR 74610, December 1, 2010) and adding the following new AD: * Compliance (d) Air Transport Association (ATA) of America Code 57: Wings. § 39.13 of Airbus Service Bulletins (SB) A300–57– 0235 and A300–57–6088 * * *. Subsequently, new cases of cracks were discovered during scheduled maintenance checks by operators of A300B4 and A300– 600 type aeroplanes on which the terminating action SB’s were embodied. This condition, if not corrected, could affect the structural integrity of those aeroplanes. Applicability PART 39—AIRWORTHINESS DIRECTIVES Authority: 49 U.S.C. 106(g), 40113, 44701. 62675 (e) The mandatory continuing airworthiness information (MCAI) states: Following the occurrence of cracks on the MLG [main landing gear] Rib 5 RH [righthand] and LH [left-hand] attachment fitting ´ ´ lower flanges, DGAC [Direction Generale de l’Aviation Civile] France AD 2003–318(B) was issued to require repetitive inspections and, as terminating action, the embodiment (f) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Repetitive Inspections (g) Perform a detailed inspection and a high-frequency eddy current (HFEC) inspection to detect cracks in Gear Rib 5 of the main landing gear (MLG) attachment fittings at the lower flange, in accordance with the Accomplishment Instructions of any applicable service bulletin listed in Table 1 and Table 2 of this AD, at the time specified in paragraph (g)(1) or (g)(2) of this AD. After April 12, 2000 (the effective date of AD 2000–05–07, Amendment 39–11616 (65 FR 12077, March 8, 2000)), only the service bulletins listed in Table 2 of this AD may be used. Repeat the inspections thereafter at intervals not to exceed 1,500 flight cycles, until the actions specified in paragraph (i), (j), or (l) of this AD are accomplished. TABLE 1—REVISION 01 OF SERVICE BULLETINS Airbus service bulletin— Model— A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4– 622R and F4–605R airplanes. A300 B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and B4–203 airplanes. Revision— Dated— A300–57–6087 01 ............................................................... March 11, 1998. A300–57–0234 01 ............................................................... March 11, 1998. TABLE 2—OTHER REVISIONS OF SERVICE BULLETINS Airbus service bulletin— Model— srobinson on DSK4SPTVN1PROD with PROPOSALS A300 B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and B4–203 airplanes. (1) For airplanes that have accumulated 20,000 or more total flight cycles as of March 9, 1998 (the effective date of AD 98–03–06, Amendment 39–10298 (63 FR 5224, February 2, 1998)): Inspect within 500 flight cycles after March 9, 1998. VerDate Mar<15>2010 17:42 Oct 07, 2011 Jkt 223001 Dated— A300–57A6087 02, including Appendix 01 ......................... June 24, 1999. A300–57A0234 03, including Appendix 01 ......................... 04, including Appendix 01 ......................... 05, including Appendix 01 ......................... 02 ............................................................... May 19, 2000. February 19, 2002. March 10, 2008. June 24, 1999. 03, including Appendix 01 ......................... 04, including Appendix 01 ......................... 05, including Appendix 01 ......................... A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4– 622R, and F4–605R airplanes. Revision— September 2, 1999. May 19, 2000. February 19, 2002. (2) For airplanes that have accumulated less than 20,000 total flight cycles as of March 9, 1998: Inspect prior to the accumulation of 18,000 total flight cycles, or within 1,500 flight cycles after March 9, 1998, whichever occurs later. PO 00000 Frm 00032 Fmt 4702 Sfmt 4702 Note 1: For the purposes of this AD, a detailed inspection is defined as: ‘‘An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good E:\FR\FM\11OCP1.SGM 11OCP1 62676 Federal Register / Vol. 76, No. 196 / Tuesday, October 11, 2011 / Proposed Rules lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required.’’ Note 2: Accomplishment of the initial detailed and HFEC inspections prior to April 12, 2000, in accordance with Airbus Service Bulletin A300–57A0234 or A300–57A6087, both dated August 5, 1997, as applicable, is considered acceptable for compliance with the initial inspections required by paragraph (g) of this AD. Repair for Any Crack Found During Inspections Required by Paragraph (g) of This AD (h) If any crack is detected during any inspection required by paragraph (g) of this AD, prior to further flight, accomplish the requirements of paragraph (h)(1) or (h)(2) of this AD, as applicable. (1) If a crack is detected at one hole only, and the crack does not extend out of the spotface of the hole, repair in accordance with the Accomplishment Instructions of the applicable service bulletin in Table 2 of this AD. (2) If a crack is detected at more than one hole, or if any crack at any hole extends out of the spotface of the hole, repair in accordance with a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, or the European Aviation Safety Agency (EASA) (or its delegated agent). Terminating Modification for Repetitive Inspections Required by Paragraphs (g) and (j) of This AD (i) Except as required by paragraph (l) of this AD, prior to the accumulation of 21,000 total flight cycles, or within 2 years after October 20, 1999 (the effective date of AD 99–19–26, Amendment 39–11313 (64 FR 49966, September 15, 1999)), whichever occurs later: Modify Gear Rib 5 of the MLG attachment fittings at the lower flange in accordance with the Accomplishment Instructions of the applicable service bulletin in Table 3 of this AD. After July 18, 2006 (the effective date of AD 2006–12–13, Amendment 39–14639 (71 FR 33994, June 13, 2006)), only Revision 04 of Airbus Service Bulletin A300–57–6088, and Revisions 04 and 05 of Airbus Service Bulletin A300–57–0235 may be used. Accomplishment of this modification constitutes terminating action for the repetitive inspection requirements of paragraphs (g) and (j) of this AD. TABLE 3—SERVICE BULLETINS FOR TERMINATING MODIFICATION Airbus service bulletin— Model— A300 B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and B4–203 airplanes. Note 3: Accomplishment of the modification required by paragraph (i) of this AD prior to April 12, 2000, in accordance with Airbus Service Bulletin A300–57–6088 or A300–57–0235, both dated August 5, 1998; as applicable; is acceptable for compliance with the requirements of that paragraph. Dated— A300–57–6088 01, including Appendix 01 ......................... February 1, 1999. A300–57–0235 02 ............................................................... 04 ............................................................... 01, including Appendix 01 ......................... September 5, 2002. December 3, 2003. February 1, 1999. 03 ............................................................... 04 ............................................................... 05 ............................................................... A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4– 622R, and F4–605R airplanes. Revision— September 5, 2002. March 13, 2003. December 3, 2003. Restatement of Requirements of AD 2006– 12–13, Amendment 39–14639 (71 FR 33994, June 13, 2006): Additional Repetitive Inspections (j) For airplanes on which the modification specified in paragraph (i) or (l) of this AD has not been done before July 18, 2006 (the effective date of AD 2006–12–13, Amendment 39–14639 (69 FR 54063, September 7, 2004)), perform a detailed and an HFEC inspection to detect cracks of the lower flange of Gear Rib 5 of the MLG at holes 43, 47, 48, 49, 50, 52, and 54, in accordance with the applicable service bulletin listed in Table 4 of this AD. Perform the inspections at the applicable time specified in paragraph (j)(1), (j)(2), (j)(3), or (j)(4) of this AD. Repeat the inspections thereafter at intervals not to exceed 700 flight cycles until the terminating modification required by paragraph (l) of this AD is accomplished. Accomplishment of the inspections per paragraph (j) of this AD terminates the inspection requirements of paragraph (g) of this AD. TABLE 4—SERVICE BULLETINS FOR REPETITIVE INSPECTIONS Airbus service bulletin— Model— Revision— Dated— A300–57A6087 04, including Appendix 01 ......................... February 19, 2002. A300 B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and B4–203 airplanes. srobinson on DSK4SPTVN1PROD with PROPOSALS A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4– 622R, and F4–605R airplanes. A300–57A0234 05, including Appendix 01 ......................... 05, including Appendix 01 ......................... March 10, 2008. February 19, 2002. (1) For Model A300 B2–1C, B2K–3C, B2– 203, B4–2C, B4–103, and B4–203 airplanes; and Model A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4–622R, and F4–605R airplanes that have accumulated 18,000 or more total flight cycles as of July 18, 2006: Within 700 flight cycles after July 18, 2006. (2) For Model A300 B2–1C, B2K–3C, and B2–203 airplanes that have accumulated less than 18,000 total flight cycles as of July 18, VerDate Mar<15>2010 17:42 Oct 07, 2011 Jkt 223001 2006: Prior to the accumulation of 18,000 total flight cycles, or within 700 flight cycles after July 18, 2006, whichever occurs later. (3) For Model A300 B4–2C, B4–103, and B4–203 airplanes that have accumulated less than 18,000 total flight cycles as of July 18, 2006: Prior to the accumulation of 14,500 total flight cycles, or within 700 flight cycles after July 18, 2006, whichever occurs later. PO 00000 Frm 00033 Fmt 4702 Sfmt 4702 (4) For Model A300 B4–601, B4–603, B4– 620, B4–622, B4–605R, B4–622R, and F4– 605R airplanes that have accumulated less than 18,000 total flight cycles as of July 18, 2006: Prior to the accumulation of 11,600 total flight cycles, or within 700 flight cycles after July 18, 2006, whichever occurs later. E:\FR\FM\11OCP1.SGM 11OCP1 Federal Register / Vol. 76, No. 196 / Tuesday, October 11, 2011 / Proposed Rules Crack Repair (k) If any crack is detected during any inspection required by paragraph (j) of this AD, prior to further flight, accomplish the requirements of paragraphs (k)(1) and (k)(2) of this AD, as applicable. (1) If a crack is detected at only one hole, and the crack does not extend out of the spotface of the hole, repair in accordance with Airbus Service Bulletin A300–57A0234, Revision 05, including Appendix 01, dated February 19, 2002 (for Model A300 B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and B4– 203 airplanes); or A300–57A6087, Revision 04, including Appendix 01, dated February 19, 2002; or A300–57A6087, Revision 05, dated March 10, 2008 (for Model A300 B4– 601, B4–603, B4–620, B4–622, B4–605R, B4– 622R, and F4–605R airplanes); as applicable. (2) If a crack is detected at more than one hole, or if any crack at any hole extends out of the spotface of the hole, repair in accordance with a method approved by the Manager, International Branch, ANM–116, or the EASA (or its delegated agent). Terminating Modification for Repetitive Inspections Required by Paragraphs (g) and (j) of This AD for Certain Airplanes (l) For airplanes on which the terminating modification in paragraph (i) of this AD has 62677 not been accomplished before July 18, 2006: At the earlier of the times specified in paragraphs (l)(1) and (l)(2) of this AD, modify Gear Rib 5 of the MLG attachment fittings at the lower flange. Except as provided by paragraph (m) of this AD, do the modification in accordance with the applicable service bulletin in Table 5 of this AD. This action terminates the repetitive inspections requirements of paragraphs (g) and (j) of this AD. (1) Prior to the accumulation of 21,000 total flight cycles, or within 2 years after October 20, 1999, whichever is later. (2) Within 16 months after July 18, 2006. TABLE 5—SERVICE BULLETINS FOR TERMINATING MODIFICATION Airbus service bulletin— Model— (m) Where the applicable service bulletin specified in paragraph (l) of this AD specifies to contact Airbus for modification instructions; or if there is a previously installed repair at any of the affected fastener holes; or if a crack is found when accomplishing the modification: Prior to further flight, modify in accordance with a Dated— A300–57–6088 04 ............................................................... December 3, 2003. A300–57–0235 04 ............................................................... March 13, 2003. 05 ............................................................... A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4– 622R and F4–605R airplanes. A300 B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and B4–203 airplanes. Revision— December 3, 2003. method approved by the Manager, International Branch, ANM–116, or the EASA (or its delegated agent). Actions Accomplished per Previous Issues of Service Bulletins (n) Actions accomplished before July 18, 2006, in accordance with the service bulletins listed in Table 6 of this AD, are considered acceptable for compliance with the corresponding action specified in paragraphs (g) through (m) of this AD. TABLE 6—PREVIOUS ISSUES OF SERVICE BULLETINS Airbus service bulletin— Revision— Dated— A300–57–0235 ...................................................................... 02, 03 02 03 September 27, 1999. September 5, 2002. September 5, 2000. March 13, 2003. A300–57–6088 ...................................................................... srobinson on DSK4SPTVN1PROD with PROPOSALS No Reporting (o) Although the service bulletins identified in Tables 1, 2, 3, 4, 5, and 6 of this AD specify to submit certain information to the manufacturer, this AD does not include such a requirement. Restatement of Requirements of AD 2010– 23–26, Amendment 39–16516 (75 FR 74610, December 1, 2010), with Certain Service Information Required after the Effective Date of This AD: Actions and Compliance (p) Unless already done, do the following actions. (1) At the applicable time specified in paragraph (p)(2) of this AD, perform a detailed inspection for cracking at the locations specified in paragraphs (p)(1)(i), (p)(1)(ii), and (p)(1)(iii) of this AD, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–57A0246, Revision 03, dated March 11, 2009, or Revision 04, dated September 9, 2009; or Airbus Mandatory Service Bulletin A300–57A6101, Revision 03, dated March 11, 2009, or Revision 04, dated VerDate Mar<15>2010 17:42 Oct 07, 2011 Jkt 223001 including Appendix 01 .................................................... ......................................................................................... ......................................................................................... ......................................................................................... September 9, 2009; as applicable. As of the effective date of this AD only Revision 04 of these service bulletins may be used. (i) The bottom flange and vertical web in the area between the wing rear spar/gear Rib 5 attachment and the forward reaction-rod pick-up lug. (ii) On the inboard side, around the fastener holes at locations 43, 47 to 50, 52, and 54. (iii) On the outboard side, the lower flange, the vertical web and around the fastener holes at locations 43, 47 to 50, 52 and 54. (2) Do the inspection required by paragraph (p)(1) of this AD at the later of the times in paragraphs (p)(2)(i) and (p)(2)(ii) of this AD. (i) Within 400 flight cycles after the accomplishment of the actions required by paragraph (i) or (l) of this AD, as applicable. (ii) Within 400 flight cycles or 4 months after January 5, 2011 (the effective date of AD 2010–23–26, Amendment 39–16516 (75 FR 74610, December 1, 2010)), whichever occurs first. (3) If no cracking is detected during the inspection required by paragraph (p)(1) of PO 00000 Frm 00034 Fmt 4702 Sfmt 4702 this AD, before further flight, perform a fluorescent penetrant inspection (FPI) at holes location 47 and 54, in the right-hand and left-hand MLG Rib 5 attachment fitting lower flange, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–57A0246, Revision 03, dated March 11, 2009, or Revision 04, dated September 9, 2009; or Airbus Mandatory Service Bulletin A300– 57A6101, Revision 03, dated March 11, 2009, or Revision 04, dated September 9, 2009; as applicable. As of the effective date of this AD, only Revision 04 of these service bulletins may be used. (4) Thereafter, at intervals not to exceed 400 flight cycles, repeat the detailed and FPI inspections, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–57A0246, Revision 03, dated March 11, 2009, or Revision 04, dated September 9, 2009; or Airbus Mandatory Service Bulletin A300– 57A6101, Revision 03, dated March 11, 2009, or Revision 04, dated September 9, 2009; as applicable; until the terminating action required by paragraph (q) of this AD has been E:\FR\FM\11OCP1.SGM 11OCP1 62678 Federal Register / Vol. 76, No. 196 / Tuesday, October 11, 2011 / Proposed Rules accomplished. As of the effective date of this AD, only Revision 04 of these service bulletins may be used. (5) If any crack is detected during any of the inspections required by paragraphs (p)(1), (p)(3), and (p)(4) of this AD, and Airbus Mandatory Service Bulletin A300–57A0246, Revision 03, dated March 11, 2009, or Revision 04, dated September 9, 2009; or Airbus Mandatory Service Bulletin A300– 57A6101, Revision 03, dated March 11, 2009, or Revision 04, dated September 9, 2009; recommends contacting Airbus for appropriate action: Before further flight, contact Airbus for a repair solution, and do the repair; or repair the cracking using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, or EASA or its delegated agent. As of the effective date of this AD, only Revision 04 of these service bulletins may be used. New Requirements of This AD: applicable. Accomplishing this modification terminates the repetitive inspection requirements of paragraph (p)(4) of this AD. Terminating Action (q) Within 30 months after the effective date of this AD: Modify the spot-faces around all the fastener holes at locations 43, 47 to 50, 52, and 54 (except for spot-faces of holes which have been previously repaired) on the bottom flange MLG ribs, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–57–0254, Revision 01, including Appendix 1, dated June 14, 2011; or Airbus Mandatory Service Bulletin A300–57–6110, Revision 01, including Appendix 1, dated June 6, 2011; as (s) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): Manager, International Branch, ANM–116, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Dan Rodina, Aerospace Engineer, Credit for Actions Accomplished in Accordance With Previous Service Information (r) Modifying the spot-faces before the effective date of this AD, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–57–0254, dated June 4, 2010; or Airbus Mandatory Service Bulletin A300–57–6110, dated June 7, 2010; as applicable; is considered acceptable for compliance with the requirements of paragraph (q) of this AD. FAA AD Differences Note 4: This AD differs from the MCAI and/or service information as follows: No differences. Other FAA AD Provisions International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057– 3356; telephone (425) 227–2125; fax (425) 227–1149. Information may be e-mailed to: 9ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. The AMOC approval letter must specifically reference this AD. AMOCs approved previously in accordance with AD 2000–05–07, Amendment 39–11616 (65 FR 12077, March 8, 2000); AD 2006–12–13, Amendment 39– 14639 (69 FR 54063, September 7, 2004); and AD 2010–23–26, Amendment 39–16516 (75 FR 74610, December 1, 2010), are approved as AMOCs for the corresponding provisions of 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. Related Information (t) Refer to MCAI EASA Airworthiness Directive 2011–0029, dated February 24, 2011; and the service information specified in Table 7 of this AD, for related information. TABLE 7—RELATED SERVICE INFORMATION Airbus— Revision— Dated— Mandatory Service Bulletin A300–57A0246 ......................... Mandatory Service Bulletin A300–57–0254 .......................... Mandatory Service Bulletin A300–57A6101 ......................... Mandatory Service Bulletin A300–57–6110 .......................... Service Bulletin A300–57A0234 ............................................ 04, including Appendices 1 and 2 ....................................... 01 ......................................................................................... 04, including Appendices 1 and 2 ....................................... 01 ......................................................................................... 02 ......................................................................................... 03, including Appendix 01 ................................................... 04, including Appendix 01 ................................................... 05, including Appendix 01 ................................................... 02, including Appendix 01 ................................................... 03, including Appendix 01 ................................................... 04, including Appendix 01 ................................................... 05, including Appendix 01 ................................................... 04 ......................................................................................... 05 ......................................................................................... 04 ......................................................................................... September 9, 2009. June 14, 2011. September 9, 2009. June 6, 2011. June 24, 1999. September 2, 1999. May 19, 2000. February 19, 2002. June 24, 1999. May 19, 2000. February 19, 2002. March 10, 2008. March 13, 2003. December 3, 2003. December 3, 2003. Service Bulletin A300–57A6087 ............................................ Service Bulletin A300–57–0235 ............................................ Service Bulletin A300–57–6088 ............................................ CONSUMER PRODUCT SAFETY COMMISSION ACTION: 16 CFR Chapter II SUMMARY: [FR Doc. 2011–26113 Filed 10–7–11; 8:45 am] srobinson on DSK4SPTVN1PROD with PROPOSALS Issued in Renton, Washington, on September 30, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [Docket No. CPSC–2011–0074] BILLING CODE 4910–13–P Table Saw Blade Contact Injuries; Advance Notice of Proposed Rulemaking; Request for Comments and Information Consumer Product Safety Commission. AGENCY: VerDate Mar<15>2010 17:42 Oct 07, 2011 Jkt 223001 PO 00000 Frm 00035 Fmt 4702 Sfmt 4702 Advance notice of proposed rulemaking. The Consumer Product Safety Commission (‘‘CPSC’’ or ‘‘Commission’’ or ‘‘we’’) is considering whether a new performance safety standard is needed to address an unreasonable risk of injury associated with table saws. We are conducting this proceeding under the authority of the Consumer Product Safety Act (‘‘CPSA’’), 15 U.S.C. 2051– 2084. This advance notice of proposed rulemaking (‘‘ANPR’’) invites written comments from interested persons E:\FR\FM\11OCP1.SGM 11OCP1

Agencies

[Federal Register Volume 76, Number 196 (Tuesday, October 11, 2011)]
[Proposed Rules]
[Pages 62673-62678]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-26113]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-1066; Directorate Identifier 2011-NM-050-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD), for 
certain Airbus Model A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-
203 airplanes and Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, 
B4-622R, and F4-605R airplanes, that would supersede an existing AD. 
This proposed AD results from mandatory continuing airworthiness 
information (MCAI) originated by an aviation authority of another 
country to identify and correct an unsafe condition on an aviation 
product. The MCAI describes the unsafe condition as:

    Following the occurrence of cracks on the MLG [main landing 
gear] Rib 5 RH [right-hand] and LH [left-hand] attachment fitting 
lower flanges, DGAC [Direction G[eacute]n[eacute]rale de l'Aviation 
Civile] France AD 2003-318(B) was issued to require repetitive 
inspections and, as terminating action * * * [.]
    Subsequently, new cases of cracks were discovered during 
scheduled maintenance checks by operators of A300B4 and A300-600 
type aeroplanes on which the terminating action * * * [was] 
embodied. This condition, if not corrected, could affect the 
structural integrity of those aeroplanes.
* * * * *
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 25, 
2011.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     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, 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 http://www.airbus.com. You may review copies of the referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue, SW., Renton, Washington. For information on the availability of 
this material at the FAA, call 425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this 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-2011-1066; 
Directorate Identifier 2011-NM-050-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any

[[Page 62674]]

personal information you provide. We will also post a report 
summarizing each substantive verbal contact we receive about this 
proposed AD.

Discussion

    On November 3, 2010, we issued AD 2010-23-26, Amendment 39-16516 
(75 FR 74610, December 1, 2010). That AD required actions intended to 
address an unsafe condition on the products listed above.
    Since we issued AD 2010-23-26, Amendment 39-16516 (75 FR 74610, 
December 1, 2010), we have determined that it is necessary to mandate 
the optional spot-facing modification specified in paragraph (q) of the 
existing AD: The European Aviation Safety Agency (EASA), which is the 
aviation authority for the Member States of the European Community, has 
issued EASA Airworthiness Directive 2011-0029, dated February 24, 2011 
(referred to after this as ``the MCAI''), to correct an unsafe 
condition for the specified products. The MCAI states:

    Following the occurrence of cracks on the MLG [main landing 
gear] Rib 5 RH [right-hand] and LH [left-hand] attachment fitting 
lower flanges, DGAC [Direction G[eacute]n[eacute]rale de l'Aviation 
Civile] France AD 2003-318(B) was issued to require repetitive 
inspections and, as terminating action, the embodiment of Airbus 
Service Bulletins (SB) A300-57-0235 and A300-57-6088 * * *.
    Subsequently, new cases of cracks were discovered during 
scheduled maintenance checks by operators of A300B4 and A300-600 
type aeroplanes on which the terminating action SB's were embodied. 
This condition, if not corrected, could affect the structural 
integrity of those aeroplanes.
    To address and correct this condition, Airbus developed an 
inspection programme for aeroplanes modified in accordance with SB 
A300-57-0235 or A300-57-6088. This inspection programme was required 
to be implemented by DGAC France AD F-2005-113, original issue and 
later revision 1 [parallel to part of FAA AD 2006-12-13, Amendment 
39-14639 (71 FR 33994, June 13, 2006)].
    A new EASA [European Aviation Safety Agency] AD 2008-0111, 
superseding DGAC France AD F-2005-113R1, was issued to reduce the 
applicability. For aeroplanes already compliant with DGAC France AD 
F-2005-113R1, no further action was required.
    Since EASA AD 2008-0111 issuance, Airbus reviewed the inspection 
programmes of SB A300-57A0246 and SB A300-57A6101 to introduce 
repetitive inspections including a new inspection technique for 
holes 47 and 54 and to reduce inspections threshold and intervals 
from 700 Flight Cycles (FC) to 400 FC until a revised terminating 
action is made available.
    For the reasons stated above, EASA AD 2009-0081 superseded EASA 
AD 2008-0111 and required operators to comply with the new 
inspection programme introduced in Revisions 3 of Airbus SB A300-
57A0246 and Airbus SB A300-57A6101.
    EASA AD 2009-0081 R1 [which corresponds to FAA AD 2010-23-26, 
Amendment 39-16516 (75 FR 74610, December 1, 2010)] has been 
published to introduce an optional terminating action which 
consisted of spot-facing the sensitive holes of the MLG Rib 5 (LH 
and RH) bottom flanges.
    Later discussions with Airbus have demonstrated the necessity to 
require the spot-facing modification as a final solution (no longer 
optional). This new [EASA] AD retains the inspection requirements of 
EASA AD 2009-0081 R1, which is superseded, and requires the spot-
facing of sensitive holes of the MLG Rib 5 (LH and RH) bottom 
flanges as terminating action.

Required actions include repairing discrepancies (e.g., cracking or a 
2nd oversize or greater fastener hole). You may obtain further 
information by examining the MCAI in the AD docket.

Relevant Service Information

    Airbus has issued Mandatory Service Bulletins A300-57-0254, 
Revision 01, including Appendix 1, dated June 14, 2011; and A300-57-
6110, Revision 01, including Appendix 1, dated June 6, 2011. The 
actions described in this service information are intended to correct 
the unsafe condition identified in the MCAI.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

Differences Between This AD and the MCAI or Service Information

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

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 155 products of U.S. registry.
    The actions that are required by AD 2010-23-26, Amendment 39-16516 
(75 FR 74610, December 1, 2010), and retained in this AD take about 79 
work-hours per product, at an average labor rate of $85 per work hour. 
Required parts cost about $10,270 per product. Based on these figures, 
the estimated cost of the currently required actions is $16,985 per 
product.
    We estimate that it would take about 100 work-hours per product to 
comply with the new basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Based on these figures, we estimate 
the cost of the proposed AD on U.S. operators to be $1,317,500, or 
$8,500 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;

[[Page 62675]]

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

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by removing Amendment 39-16516 (75 FR 
74610, December 1, 2010) and adding the following new AD:

Airbus: Docket No. FAA-2011-1066; Directorate Identifier 2011-NM-
050-AD.

Comments Due Date

    (a) We must receive comments by November 25, 2011.

Affected ADs

    (b) This AD supersedes AD 2010-23-26, Amendment 39-16516 (75 FR 
74610, December 1, 2010).

Applicability

    (c) This AD applies to the airplanes, certificated in any 
category, identified in paragraphs (c)(1) and (c)(2) of this AD; 
except airplanes on which Airbus Modification 11912 or 11932 has 
been installed.
    (1) Airbus Model A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and 
B4-203 airplanes.
    (2) Airbus Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, 
B4-622R, and F4-605R airplanes.

Subject

    (d) Air Transport Association (ATA) of America Code 57: Wings.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    Following the occurrence of cracks on the MLG [main landing 
gear] Rib 5 RH [right-hand] and LH [left-hand] attachment fitting 
lower flanges, DGAC [Direction G[eacute]n[eacute]rale de l'Aviation 
Civile] France AD 2003-318(B) was issued to require repetitive 
inspections and, as terminating action, the embodiment of Airbus 
Service Bulletins (SB) A300-57-0235 and A300-57-6088 * * *.
    Subsequently, new cases of cracks were discovered during 
scheduled maintenance checks by operators of A300B4 and A300-600 
type aeroplanes on which the terminating action SB's were embodied. 
This condition, if not corrected, could affect the structural 
integrity of those aeroplanes.
* * * * *

Compliance

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

Restatement of Requirements of AD 2000-05-07, Amendment 39-11616 (65 FR 
12077, March 8, 2000):

Repetitive Inspections

    (g) Perform a detailed inspection and a high-frequency eddy 
current (HFEC) inspection to detect cracks in Gear Rib 5 of the main 
landing gear (MLG) attachment fittings at the lower flange, in 
accordance with the Accomplishment Instructions of any applicable 
service bulletin listed in Table 1 and Table 2 of this AD, at the 
time specified in paragraph (g)(1) or (g)(2) of this AD. After April 
12, 2000 (the effective date of AD 2000-05-07, Amendment 39-11616 
(65 FR 12077, March 8, 2000)), only the service bulletins listed in 
Table 2 of this AD may be used. Repeat the inspections thereafter at 
intervals not to exceed 1,500 flight cycles, until the actions 
specified in paragraph (i), (j), or (l) of this AD are accomplished.

                                    Table 1--Revision 01 of Service Bulletins
----------------------------------------------------------------------------------------------------------------
                                       Airbus service
               Model--                   bulletin--          Revision--                     Dated--
----------------------------------------------------------------------------------------------------------------
A300 B4-601, B4-603, B4-620, B4-622,     A300-57-6087  01....................  March 11, 1998.
 B4-605R, B4-622R and F4-605R
 airplanes.
A300 B2-1C, B2K-3C, B2-203, B4-2C,       A300-57-0234  01....................  March 11, 1998.
 B4-103, and B4-203 airplanes.
----------------------------------------------------------------------------------------------------------------


                                  Table 2--Other Revisions of Service Bulletins
----------------------------------------------------------------------------------------------------------------
                                       Airbus service
               Model--                   bulletin--          Revision--                     Dated--
----------------------------------------------------------------------------------------------------------------
A300 B4-601, B4-603, B4-620, B4-622,     A300-57A6087  02, including Appendix  June 24, 1999.
 B4-605R, B4-622R, and F4-605R                          01.
 airplanes.
                                                       03, including Appendix  May 19, 2000.
                                                        01.
                                                       04, including Appendix  February 19, 2002.
                                                        01.
                                                       05, including Appendix  March 10, 2008.
                                                        01.
A300 B2-1C, B2K-3C, B2-203, B4-2C,       A300-57A0234  02....................  June 24, 1999.
 B4-103, and B4-203 airplanes.
                                                       03, including Appendix  September 2, 1999.
                                                        01.
                                                       04, including Appendix  May 19, 2000.
                                                        01.
                                                       05, including Appendix  February 19, 2002.
                                                        01.
----------------------------------------------------------------------------------------------------------------

     (1) For airplanes that have accumulated 20,000 or more total 
flight cycles as of March 9, 1998 (the effective date of AD 98-03-
06, Amendment 39-10298 (63 FR 5224, February 2, 1998)): Inspect 
within 500 flight cycles after March 9, 1998.
    (2) For airplanes that have accumulated less than 20,000 total 
flight cycles as of March 9, 1998: Inspect prior to the accumulation 
of 18,000 total flight cycles, or within 1,500 flight cycles after 
March 9, 1998, whichever occurs later.

    Note 1:  For the purposes of this AD, a detailed inspection is 
defined as: ``An intensive visual examination of a specific 
structural area, system, installation, or assembly to detect damage, 
failure, or irregularity. Available lighting is normally 
supplemented with a direct source of good

[[Page 62676]]

lighting at intensity deemed appropriate by the inspector. 
Inspection aids such as mirror, magnifying lenses, etc., may be 
used. Surface cleaning and elaborate access procedures may be 
required.''


    Note 2:  Accomplishment of the initial detailed and HFEC 
inspections prior to April 12, 2000, in accordance with Airbus 
Service Bulletin A300-57A0234 or A300-57A6087, both dated August 5, 
1997, as applicable, is considered acceptable for compliance with 
the initial inspections required by paragraph (g) of this AD.

Repair for Any Crack Found During Inspections Required by Paragraph (g) 
of This AD

    (h) If any crack is detected during any inspection required by 
paragraph (g) of this AD, prior to further flight, accomplish the 
requirements of paragraph (h)(1) or (h)(2) of this AD, as 
applicable.
    (1) If a crack is detected at one hole only, and the crack does 
not extend out of the spotface of the hole, repair in accordance 
with the Accomplishment Instructions of the applicable service 
bulletin in Table 2 of this AD.
    (2) If a crack is detected at more than one hole, or if any 
crack at any hole extends out of the spotface of the hole, repair in 
accordance with a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA, or the 
European Aviation Safety Agency (EASA) (or its delegated agent).

Terminating Modification for Repetitive Inspections Required by 
Paragraphs (g) and (j) of This AD

    (i) Except as required by paragraph (l) of this AD, prior to the 
accumulation of 21,000 total flight cycles, or within 2 years after 
October 20, 1999 (the effective date of AD 99-19-26, Amendment 39-
11313 (64 FR 49966, September 15, 1999)), whichever occurs later: 
Modify Gear Rib 5 of the MLG attachment fittings at the lower flange 
in accordance with the Accomplishment Instructions of the applicable 
service bulletin in Table 3 of this AD. After July 18, 2006 (the 
effective date of AD 2006-12-13, Amendment 39-14639 (71 FR 33994, 
June 13, 2006)), only Revision 04 of Airbus Service Bulletin A300-
57-6088, and Revisions 04 and 05 of Airbus Service Bulletin A300-57-
0235 may be used. Accomplishment of this modification constitutes 
terminating action for the repetitive inspection requirements of 
paragraphs (g) and (j) of this AD.

                             Table 3--Service Bulletins for Terminating Modification
----------------------------------------------------------------------------------------------------------------
                                       Airbus service
               Model--                   bulletin--          Revision--                     Dated--
----------------------------------------------------------------------------------------------------------------
A300 B4-601, B4-603, B4-620, B4-622,     A300-57-6088  01, including Appendix  February 1, 1999.
 B4-605R, B4-622R, and F4-605R                          01.
 airplanes.
                                                       02....................  September 5, 2002.
                                                       04....................  December 3, 2003.
A300 B2-1C, B2K-3C, B2-203, B4-2C,       A300-57-0235  01, including Appendix  February 1, 1999.
 B4-103, and B4-203 airplanes.                          01.
                                                       03....................  September 5, 2002.
                                                       04....................  March 13, 2003.
                                                       05....................  December 3, 2003.
----------------------------------------------------------------------------------------------------------------


    Note 3: Accomplishment of the modification required by paragraph 
(i) of this AD prior to April 12, 2000, in accordance with Airbus 
Service Bulletin A300-57-6088 or A300-57-0235, both dated August 5, 
1998; as applicable; is acceptable for compliance with the 
requirements of that paragraph.

Restatement of Requirements of AD 2006-12-13, Amendment 39-14639 (71 FR 
33994, June 13, 2006):

Additional Repetitive Inspections

    (j) For airplanes on which the modification specified in 
paragraph (i) or (l) of this AD has not been done before July 18, 
2006 (the effective date of AD 2006-12-13, Amendment 39-14639 (69 FR 
54063, September 7, 2004)), perform a detailed and an HFEC 
inspection to detect cracks of the lower flange of Gear Rib 5 of the 
MLG at holes 43, 47, 48, 49, 50, 52, and 54, in accordance with the 
applicable service bulletin listed in Table 4 of this AD. Perform 
the inspections at the applicable time specified in paragraph 
(j)(1), (j)(2), (j)(3), or (j)(4) of this AD. Repeat the inspections 
thereafter at intervals not to exceed 700 flight cycles until the 
terminating modification required by paragraph (l) of this AD is 
accomplished. Accomplishment of the inspections per paragraph (j) of 
this AD terminates the inspection requirements of paragraph (g) of 
this AD.

                              Table 4--Service Bulletins for Repetitive Inspections
----------------------------------------------------------------------------------------------------------------
                                       Airbus service
               Model--                   bulletin--          Revision--                     Dated--
----------------------------------------------------------------------------------------------------------------
A300 B4-601, B4-603, B4-620, B4-622,     A300-57A6087  04, including Appendix  February 19, 2002.
 B4-605R, B4-622R, and F4-605R                          01.
 airplanes.
                                                       05, including Appendix  March 10, 2008.
                                                        01.
A300 B2-1C, B2K-3C, B2-203, B4-2C,       A300-57A0234  05, including Appendix  February 19, 2002.
 B4-103, and B4-203 airplanes.                          01.
----------------------------------------------------------------------------------------------------------------

    (1) For Model A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-
203 airplanes; and Model A300 B4-601, B4-603, B4-620, B4-622, B4-
605R, B4-622R, and F4-605R airplanes that have accumulated 18,000 or 
more total flight cycles as of July 18, 2006: Within 700 flight 
cycles after July 18, 2006.
    (2) For Model A300 B2-1C, B2K-3C, and B2-203 airplanes that have 
accumulated less than 18,000 total flight cycles as of July 18, 
2006: Prior to the accumulation of 18,000 total flight cycles, or 
within 700 flight cycles after July 18, 2006, whichever occurs 
later.
    (3) For Model A300 B4-2C, B4-103, and B4-203 airplanes that have 
accumulated less than 18,000 total flight cycles as of July 18, 
2006: Prior to the accumulation of 14,500 total flight cycles, or 
within 700 flight cycles after July 18, 2006, whichever occurs 
later.
    (4) For Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-
622R, and F4-605R airplanes that have accumulated less than 18,000 
total flight cycles as of July 18, 2006: Prior to the accumulation 
of 11,600 total flight cycles, or within 700 flight cycles after 
July 18, 2006, whichever occurs later.

[[Page 62677]]

Crack Repair

    (k) If any crack is detected during any inspection required by 
paragraph (j) of this AD, prior to further flight, accomplish the 
requirements of paragraphs (k)(1) and (k)(2) of this AD, as 
applicable.
    (1) If a crack is detected at only one hole, and the crack does 
not extend out of the spotface of the hole, repair in accordance 
with Airbus Service Bulletin A300-57A0234, Revision 05, including 
Appendix 01, dated February 19, 2002 (for Model A300 B2-1C, B2K-3C, 
B2-203, B4-2C, B4-103, and B4-203 airplanes); or A300-57A6087, 
Revision 04, including Appendix 01, dated February 19, 2002; or 
A300-57A6087, Revision 05, dated March 10, 2008 (for Model A300 B4-
601, B4-603, B4-620, B4-622, B4-605R, B4-622R, and F4-605R 
airplanes); as applicable.
    (2) If a crack is detected at more than one hole, or if any 
crack at any hole extends out of the spotface of the hole, repair in 
accordance with a method approved by the Manager, International 
Branch, ANM-116, or the EASA (or its delegated agent).

Terminating Modification for Repetitive Inspections Required by 
Paragraphs (g) and (j) of This AD for Certain Airplanes

    (l) For airplanes on which the terminating modification in 
paragraph (i) of this AD has not been accomplished before July 18, 
2006: At the earlier of the times specified in paragraphs (l)(1) and 
(l)(2) of this AD, modify Gear Rib 5 of the MLG attachment fittings 
at the lower flange. Except as provided by paragraph (m) of this AD, 
do the modification in accordance with the applicable service 
bulletin in Table 5 of this AD. This action terminates the 
repetitive inspections requirements of paragraphs (g) and (j) of 
this AD.
    (1) Prior to the accumulation of 21,000 total flight cycles, or 
within 2 years after October 20, 1999, whichever is later.
    (2) Within 16 months after July 18, 2006.

                             Table 5--Service Bulletins for Terminating Modification
----------------------------------------------------------------------------------------------------------------
                                       Airbus service
               Model--                   bulletin--          Revision--                     Dated--
----------------------------------------------------------------------------------------------------------------
A300 B4-601, B4-603, B4-620, B4-622,     A300-57-6088  04....................  December 3, 2003.
 B4-605R, B4-622R and F4-605R
 airplanes.
A300 B2-1C, B2K-3C, B2-203, B4-2C,       A300-57-0235  04....................  March 13, 2003.
 B4-103, and B4-203 airplanes.
                                                       05....................  December 3, 2003.
----------------------------------------------------------------------------------------------------------------

    (m) Where the applicable service bulletin specified in paragraph 
(l) of this AD specifies to contact Airbus for modification 
instructions; or if there is a previously installed repair at any of 
the affected fastener holes; or if a crack is found when 
accomplishing the modification: Prior to further flight, modify in 
accordance with a method approved by the Manager, International 
Branch, ANM-116, or the EASA (or its delegated agent).

Actions Accomplished per Previous Issues of Service Bulletins

    (n) Actions accomplished before July 18, 2006, in accordance 
with the service bulletins listed in Table 6 of this AD, are 
considered acceptable for compliance with the corresponding action 
specified in paragraphs (g) through (m) of this AD.

                                  Table 6--Previous Issues of Service Bulletins
----------------------------------------------------------------------------------------------------------------
        Airbus service bulletin--                   Revision--                           Dated--
----------------------------------------------------------------------------------------------------------------
A300-57-0235.............................  02, including Appendix 01...  September 27, 1999.
                                           03..........................  September 5, 2002.
A300-57-6088.............................  02..........................  September 5, 2000.
                                           03..........................  March 13, 2003.
----------------------------------------------------------------------------------------------------------------

No Reporting

    (o) Although the service bulletins identified in Tables 1, 2, 3, 
4, 5, and 6 of this AD specify to submit certain information to the 
manufacturer, this AD does not include such a requirement.
    Restatement of Requirements of AD 2010-23-26, Amendment 39-16516 
(75 FR 74610, December 1, 2010), with Certain Service Information 
Required after the Effective Date of This AD:

Actions and Compliance

    (p) Unless already done, do the following actions.
    (1) At the applicable time specified in paragraph (p)(2) of this 
AD, perform a detailed inspection for cracking at the locations 
specified in paragraphs (p)(1)(i), (p)(1)(ii), and (p)(1)(iii) of 
this AD, in accordance with the Accomplishment Instructions of 
Airbus Mandatory Service Bulletin A300-57A0246, Revision 03, dated 
March 11, 2009, or Revision 04, dated September 9, 2009; or Airbus 
Mandatory Service Bulletin A300-57A6101, Revision 03, dated March 
11, 2009, or Revision 04, dated September 9, 2009; as applicable. As 
of the effective date of this AD only Revision 04 of these service 
bulletins may be used.
    (i) The bottom flange and vertical web in the area between the 
wing rear spar/gear Rib 5 attachment and the forward reaction-rod 
pick-up lug.
    (ii) On the inboard side, around the fastener holes at locations 
43, 47 to 50, 52, and 54.
    (iii) On the outboard side, the lower flange, the vertical web 
and around the fastener holes at locations 43, 47 to 50, 52 and 54.
    (2) Do the inspection required by paragraph (p)(1) of this AD at 
the later of the times in paragraphs (p)(2)(i) and (p)(2)(ii) of 
this AD.
    (i) Within 400 flight cycles after the accomplishment of the 
actions required by paragraph (i) or (l) of this AD, as applicable.
    (ii) Within 400 flight cycles or 4 months after January 5, 2011 
(the effective date of AD 2010-23-26, Amendment 39-16516 (75 FR 
74610, December 1, 2010)), whichever occurs first.
    (3) If no cracking is detected during the inspection required by 
paragraph (p)(1) of this AD, before further flight, perform a 
fluorescent penetrant inspection (FPI) at holes location 47 and 54, 
in the right-hand and left-hand MLG Rib 5 attachment fitting lower 
flange, in accordance with the Accomplishment Instructions of Airbus 
Mandatory Service Bulletin A300-57A0246, Revision 03, dated March 
11, 2009, or Revision 04, dated September 9, 2009; or Airbus 
Mandatory Service Bulletin A300-57A6101, Revision 03, dated March 
11, 2009, or Revision 04, dated September 9, 2009; as applicable. As 
of the effective date of this AD, only Revision 04 of these service 
bulletins may be used.
    (4) Thereafter, at intervals not to exceed 400 flight cycles, 
repeat the detailed and FPI inspections, in accordance with the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A300-57A0246, Revision 03, dated March 11, 2009, or Revision 04, 
dated September 9, 2009; or Airbus Mandatory Service Bulletin A300-
57A6101, Revision 03, dated March 11, 2009, or Revision 04, dated 
September 9, 2009; as applicable; until the terminating action 
required by paragraph (q) of this AD has been

[[Page 62678]]

accomplished. As of the effective date of this AD, only Revision 04 
of these service bulletins may be used.
    (5) If any crack is detected during any of the inspections 
required by paragraphs (p)(1), (p)(3), and (p)(4) of this AD, and 
Airbus Mandatory Service Bulletin A300-57A0246, Revision 03, dated 
March 11, 2009, or Revision 04, dated September 9, 2009; or Airbus 
Mandatory Service Bulletin A300-57A6101, Revision 03, dated March 
11, 2009, or Revision 04, dated September 9, 2009; recommends 
contacting Airbus for appropriate action: Before further flight, 
contact Airbus for a repair solution, and do the repair; or repair 
the cracking using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA, or EASA or its 
delegated agent. As of the effective date of this AD, only Revision 
04 of these service bulletins may be used.
    New Requirements of This AD:

Terminating Action

    (q) Within 30 months after the effective date of this AD: Modify 
the spot-faces around all the fastener holes at locations 43, 47 to 
50, 52, and 54 (except for spot-faces of holes which have been 
previously repaired) on the bottom flange MLG ribs, in accordance 
with the Accomplishment Instructions of Airbus Mandatory Service 
Bulletin A300-57-0254, Revision 01, including Appendix 1, dated June 
14, 2011; or Airbus Mandatory Service Bulletin A300-57-6110, 
Revision 01, including Appendix 1, dated June 6, 2011; as 
applicable. Accomplishing this modification terminates the 
repetitive inspection requirements of paragraph (p)(4) of this AD.

Credit for Actions Accomplished in Accordance With Previous Service 
Information

    (r) Modifying the spot-faces before the effective date of this 
AD, in accordance with the Accomplishment Instructions of Airbus 
Mandatory Service Bulletin A300-57-0254, dated June 4, 2010; or 
Airbus Mandatory Service Bulletin A300-57-6110, dated June 7, 2010; 
as applicable; is considered acceptable for compliance with the 
requirements of paragraph (q) of this AD.

FAA AD Differences

    Note 4: This AD differs from the MCAI and/or service information 
as follows: No differences.

Other FAA AD Provisions

    (s) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): Manager, 
International Branch, ANM-116, FAA, has the authority to approve 
AMOCs for this AD, if requested using the procedures found in 14 CFR 
39.19. In accordance with 14 CFR 39.19, send your request to your 
principal inspector or local Flight Standards District Office, as 
appropriate. If sending information directly to the International 
Branch, send it 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. Information may be e-mailed to: 
9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, 
notify your appropriate principal inspector, or lacking a principal 
inspector, the manager of the local flight standards district 
office/certificate holding district office. The AMOC approval letter 
must specifically reference this AD. AMOCs approved previously in 
accordance with AD 2000-05-07, Amendment 39-11616 (65 FR 12077, 
March 8, 2000); AD 2006-12-13, Amendment 39-14639 (69 FR 54063, 
September 7, 2004); and AD 2010-23-26, Amendment 39-16516 (75 FR 
74610, December 1, 2010), are approved as AMOCs for the 
corresponding provisions of 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.

Related Information

    (t) Refer to MCAI EASA Airworthiness Directive 2011-0029, dated 
February 24, 2011; and the service information specified in Table 7 
of this AD, for related information.

                                      Table 7--Related Service Information
----------------------------------------------------------------------------------------------------------------
                Airbus--                             Revision--                           Dated--
----------------------------------------------------------------------------------------------------------------
Mandatory Service Bulletin A300-57A0246.  04, including Appendices 1 and   September 9, 2009.
                                           2.
Mandatory Service Bulletin A300-57-0254.  01.............................  June 14, 2011.
Mandatory Service Bulletin A300-57A6101.  04, including Appendices 1 and   September 9, 2009.
                                           2.
Mandatory Service Bulletin A300-57-6110.  01.............................  June 6, 2011.
Service Bulletin A300-57A0234...........  02.............................  June 24, 1999.
                                          03, including Appendix 01......  September 2, 1999.
                                          04, including Appendix 01......  May 19, 2000.
                                          05, including Appendix 01......  February 19, 2002.
Service Bulletin A300-57A6087...........  02, including Appendix 01......  June 24, 1999.
                                          03, including Appendix 01......  May 19, 2000.
                                          04, including Appendix 01......  February 19, 2002.
                                          05, including Appendix 01......  March 10, 2008.
Service Bulletin A300-57-0235...........  04.............................  March 13, 2003.
                                          05.............................  December 3, 2003.
Service Bulletin A300-57-6088...........  04.............................  December 3, 2003.
----------------------------------------------------------------------------------------------------------------


    Issued in Renton, Washington, on September 30, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-26113 Filed 10-7-11; 8:45 am]
BILLING CODE 4910-13-P