Airworthiness Directives; Airbus Model A310 Series Airplanes, 27232-27237 [2011-10687]

Download as PDF 27232 Federal Register / Vol. 76, No. 91 / Wednesday, May 11, 2011 / Rules and Regulations Flight Standards District Office, as appropriate, or 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 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. FAA AD Differences Note 1: This AD differs from the MCAI and/or service information as follows: No Differences. Other FAA AD Provisions (o) 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. In accordance with 14 CFR 39.19, send your request to your principal inspector or local (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 (p) Refer to MCAI EASA Airworthiness Directive 2009–0057, dated March 13, 2009, and the service bulletins listed in Table 6 of this AD, for related information. TABLE 6—SERVICE INFORMATION Service Bulletin Revision Airbus Mandatory Service Bulletin A310–57–2048 ........................................................................................... Airbus Mandatory Service Bulletin A310–57–2050 ........................................................................................... Airbus Mandatory Service Bulletin A310–57–2064 ........................................................................................... Material Incorporated by Reference (q) You must use the applicable service information contained in Table 7 of this AD 01 02 02 Date May 22, 2007. August 27, 2009. December 21, 2007. to do the actions required by this AD, unless the AD specifies otherwise. TABLE 7—ALL MATERIAL INCORPORATED BY REFERENCE Service Bulletin Revision Airbus Mandatory Service Bulletin A310–57–2048 ........................................................................................... Airbus Mandatory Service Bulletin A310–57–2050, excluding Appendix 01 .................................................... Airbus Mandatory Service Bulletin A310–57–2064, excluding Appendix 1 ...................................................... srobinson on DSKHWCL6B1PROD with RULES (1) The Director of the Federal Register approved the incorporation by reference of the service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this 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.airwortheas@airbus.com; Internet https:// www.airbus.com. (3) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221. (4) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on April 22, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011–10685 Filed 5–10–11; 8:45 am] BILLING CODE 4910–13–P VerDate Mar<15>2010 16:21 May 10, 2011 Jkt 223001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–1276; Directorate Identifier 2010–NM–092–AD; Amendment 39–16689; AD 2011–10–08] RIN 2120–AA64 Airworthiness Directives; Airbus Model A310 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for the products listed above that would supersede two existing ADs. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: SUMMARY: ´ ´ DGAC [Direction Generale de l’Aviation Civile] France AD 1992–106–132(B) * * * PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 01 02 02 Date May 22, 2007. August 27, 2009. December 21, 2007. has been issued in order to mandate a set of inspections/modifications which address JAR/FAR [Joint Aviation Regulation/Federal Aviation Regulation] 25–571 requirements related to damage-tolerance and fatigue evaluation of structure. * * * * * The unsafe condition is reduced structural integrity of the wings, fuselage, and stabilizers. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective June 15, 2011. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of June 15, 2011. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of January 20, 1999 (63 FR 69179, December 16, 1998). ADDRESSES: You may examine the AD docket on the Internet at https:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC. E:\FR\FM\11MYR1.SGM 11MYR1 Federal Register / Vol. 76, No. 91 / Wednesday, May 11, 2011 / Rules and Regulations 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: Discussion srobinson on DSKHWCL6B1PROD with RULES We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on January 3, 2011 (76 FR 42), and proposed to supersede AD 98–26– 01, Amendment 39–10942 (63 FR 69179, December 16, 1998), and AD 91– 13–01, Amendment 39–7032 (56 FR 26602, June 10, 1991). The NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: ´ ´ DGAC [Direction Generale de l’Aviation Civile] France AD 1992–106–132(B) original issue up to revision 7 has been issued in order to mandate a set of inspections/ modifications which address JAR/FAR [Joint Aviation Regulation/Federal Aviation Regulation] 25–571 requirements related to damage-tolerance and fatigue evaluation of structure [FAA AD 98–26–01 corresponds to DGAC AD 1992–106–132(B)R4, dated June 5, 1996]. Following the Extended Design Service Goal activities part of the Structure Task Group for the A310 program, EASA AD 2007–0053 superseded DGAC France AD F–1992–106–132R7 in order to take into account the publication of Airbus Service Bulletins (SB) A310–55–2004 at Revision 5 and Airbus SB A310–53–2074 at Revision 3, whose inspection thresholds and/or intervals had been reduced. Revision 1 of this AD was issued to remove the mandatory requirements related to the wings (i.e. § 1.8, 1.9, 1.10, 1.13, and 1.18) from the Compliance section, which have been transferred to EASA AD 2007–0242. Revision 2 of this AD has been issued to remove the mandatory requirements of paragraph 1.15, 1.16 and 1.17 which have now been transferred to EASA AD 2009–0057 (§ 1.15 and 1.17) and 2009–0058 (§ 1.16) respectively. Revision 3 of this AD is issued to add a Note to the Applicability and amend the Required Action(s) and Compliance Time(s) section of this AD to clarify the allowed use of the referenced SBs by operators. In addition, a note has been added to paragraph 1.7 and the notes associated to paragraphs 1.1, 1.2, 1.3, 1.4, 1.5 and 1.12 have been clarified. The unsafe condition is reduced structural integrity of the wings, fuselage, and stabilizers. This NPRM proposed to continue to require certain actions specified in AD 98–26–01. VerDate Mar<15>2010 16:21 May 10, 2011 Jkt 223001 The NPRM also proposed to expand the inspection area of the high frequency eddy current rototest inspection required by paragraph (g) of AD 98–26–01. The required actions are as follows, depending on airplane configuration: • A defectoscope or rototest inspection to detect cracks in the area of frame 47 and frame 54, install new doublers, and repair if necessary. • Repetitive visual inspections to detect cracks on frame 46 between the left- and right-hand sides of stringers 21 and 22 on the forward and aft faces, and repair if necessary. • Repetitive visual inspections to detect cracks at the T-section connecting frame 50A to the beam between the leftand right-hand sides of frames 50 and 51, and modification if necessary. • Repetitive visual inspections to detect cracks in the lower milled side panel at the lap joint with the upper side panel at frame 47 and stringer 22, left- and right-hand sides, and repair if necessary. • An eddy current inspection to detect cracks on the upper integral part adjacent to the rear attach fittings on the horizontal stabilizer, modification of the horizontal stabilizer, and repair if necessary. • Repetitive high frequency eddy current rototest inspections for cracking of the doubler plate edge, rear spar area, and at specified fastener holes in the top skin chordwise splice along the contour of the steel doubler between ribs 3 and 4 on the left- and right-hand center and side boxes on the horizontal stabilizer, installing new fasteners if no cracking is found, and repair if necessary. • Repetitive inspections, either an eddy current or visual inspection, to detect cracks on the left and right vertical posts, numbers 1 through 5 inclusive, in the wing center box at frame 40/41, and modification if necessary. You may obtain further information by examining the MCAI in the AD docket. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. Conclusion We reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 27233 Differences Between This AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information. We might also have required different actions in this AD from those in the MCAI in order to follow our FAA policies. Any such differences are highlighted in a NOTE within the AD. Costs of Compliance We estimate that this AD will affect 44 products of U.S. registry. The actions that are required by AD 98–26–01 and are retained in this AD take about 1,087 work-hours per product, at an average labor rate of $85 per work hour. Required parts cost about $81,973 per product. Based on these figures, the estimated cost of the currently required actions is $174,368 per product. We also estimate that it will take about 3 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD to the U.S. operators to be $11,220, or $255 per product. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on E:\FR\FM\11MYR1.SGM 11MYR1 27234 Federal Register / Vol. 76, No. 91 / Wednesday, May 11, 2011 / Rules and Regulations the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this AD: 1. Is not a ’’significant regulatory action’’ under Executive Order 12866; 2. Is not a ’’significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains the NPRM, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Amendment 39–10942 (63 FR 69179, December 16, 1998) and Amendment 39–7032 (56 FR 26602, June 10, 1991) and adding the following new AD: srobinson on DSKHWCL6B1PROD with RULES ■ 2011–10–08 Airbus: Amendment 39–16689. Docket No. FAA–2010–1276; Directorate Identifier 2010–NM–092–AD. Effective Date (a) This airworthiness directive (AD) becomes effective June 15, 2011. VerDate Mar<15>2010 16:21 May 10, 2011 Jkt 223001 Affected ADs (b) This AD supersedes AD 98–26–01, Amendment 39–10942, and AD 91–13–01, Amendment 39–7032. Applicability (c) This AD applies to Airbus Model A310– 203, –204, –221, –222, –304, –322, –324, and –325 airplanes, certificated in any category, all certified models, all serial numbers. Subject (d) Air Transport Association (ATA) of America Codes 53: Fuselage, 55: Stabilizers, and 57: Wings. Reason (e) The mandatory continuing airworthiness information (MCAI) states: ´ ´ DGAC [Direction Generale de l’Aviation Civile] France AD 1992–106–132(B) * * * has been issued in order to mandate a set of inspections/modifications which address JAR/FAR [Joint Aviation Regulation/Federal Aviation Regulation] 25–571 requirements related to damage-tolerance and fatigue evaluation of structure. * * * * * The unsafe condition is reduced structural integrity of the wings, fuselage, and stabilizers. 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 Certain Requirements of AD 98–26–01 Actions for Service Bulletin A310–53–2016— No Changes (g) For airplanes listed in Airbus Service Bulletin A310–53–2016, Revision 5, dated December 7, 1992: Prior to the accumulation of 12,000 total flight cycles, or within 1,000 flight cycles after January 20, 1999 (the effective date of AD 98–26–01), whichever occurs later, perform a defectoscope or rototest inspection to detect cracks in the area of frame 47 and frame 54, and install new doublers, in accordance with Airbus Service Bulletin A310–53–2016, Revision 5, dated December 7, 1992. Except as provided by paragraph (m) of this AD, if any discrepancy is found, prior to further flight, perform follow-on corrective actions, as applicable, in accordance with Airbus Service Bulletin A310–53–2016, Revision 5, dated December 7, 1992. Note 1: Airplanes on which Airbus Modification 04980 is done in production are not affected by paragraph (g) of this AD. Actions for Service Bulletin A310–53–2054, With Latest Optional Modification (h) For airplanes listed in Airbus Service Bulletin A310–53–2054, Revision 2, dated May 22, 1990: Prior to the accumulation of 12,000 total flight cycles, or within 1,000 flight cycles after January 20, 1999, whichever occurs later, and thereafter at intervals not to exceed 3,000 flight cycles, perform a visual inspection to detect cracks on frame 46 between the left- and right-hand PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 sides of stringers 21 and 22 on the forward and aft faces, in accordance with Airbus Service Bulletin A310–53–2054, Revision 2, dated May 22, 1990. If any crack is found, prior to further flight, repair in accordance with Airbus Service Bulletin A310–53–2054, Revision 2, dated May 22, 1990. Note 2: Airplanes on which Airbus modification 05254 is done in production; or on which Airbus Service Bulletin A310–53– 2019, Revision 2, dated May 22, 1990, or Revision 3, dated February 28, 1991, is done in service; are not affected by paragraph (h) of this AD. (1) Prior to the effective date of this AD: Accomplishment of the repair required by paragraph (h) of this AD; or modification of the reinforcement angle runout in accordance with Airbus Service Bulletin A310–53–2019, Revision 2, dated May 22, 1990, or Revision 3, dated February 28, 1991; terminates the repetitive inspection requirements of paragraph (h) of this AD. (2) On or after the effective date of this AD: Accomplishment of the repair required by paragraph (h) of this AD; or modification of the reinforcement angle runout in accordance with Airbus Service Bulletin A310–53–2019, Revision 3, dated February 28, 1991; terminates the repetitive inspection requirements of paragraph (h) of this AD. Actions for Service Bulletin A310–53–2057— No Changes (i) For airplanes listed in Airbus Service Bulletin A310–53–2057, Revision 1, dated April 30, 1992: Perform a visual inspection to detect cracks at the T-section connecting frame 50A to the beam between the left- and right-hand sides of frames 50 and 51, in accordance with Airbus Service Bulletin A310–53–2057, Revision 1, dated April 30, 1992. Perform the inspection at the time specified in paragraph (i)(1) or (i)(2) of this AD, as applicable. If any crack is found, prior to further flight, accomplish Airbus Modifications No. 4853 and No. 5273, in accordance with Airbus Service Bulletin A310–53–2057, Revision 1, dated April 30, 1992. Accomplishment of these modifications terminates the requirements of this paragraph. Note 3: Airplanes on which Airbus modification 4853 is done are affected by paragraph (i) of this AD, except those airplanes on which Airbus Modification 5273 has been done or on which Airbus Service Bulletin A310–53–2011 has been done in service. (1) For the airplane having manufacturer’s serial number (MSN) 191: Prior to the accumulation of 24,000 total flight cycles, or within 1,000 flight cycles after January 20, 1999, whichever occurs later; and thereafter at intervals not to exceed 6,000 flight cycles. (2) For airplanes other than the airplane identified in paragraph (i)(1) of this AD: Prior to the accumulation of 12,000 total flight cycles, or within 1,000 flight cycles after January 20, 1999, whichever occurs later; and thereafter at intervals not to exceed 6,000 flight cycles. E:\FR\FM\11MYR1.SGM 11MYR1 Federal Register / Vol. 76, No. 91 / Wednesday, May 11, 2011 / Rules and Regulations srobinson on DSKHWCL6B1PROD with RULES Actions for Service Bulletin A310–53–2059— No Changes (j) For airplanes listed in Airbus Service Bulletin A310–53–2059, Revision 1, dated January 4, 1996: Perform a visual inspection to detect cracks in the lower milled side panel at the lap joint with the upper side panel at frame 47 and stringer 22, left- and right-hand sides, in accordance with Airbus Service Bulletin A310–53–2059, Revision 1, dated January 4, 1996. Perform the inspection at the time specified in paragraph (j)(1) or (j)(2) of this AD, as applicable. Except as provided by paragraph (m) of this AD, if any crack is found, prior to further flight, repair in accordance with Airbus Service Bulletin A310–53–2059, Revision 1, dated January 4, 1996. Thereafter, repeat the inspections at intervals not to exceed 9,000 flight cycles, or accomplish Airbus Modification 5997 (Airbus Service Bulletin A310–53–2058). Accomplishment of either the repair or Airbus Modification 5997 constitutes terminating action for the repetitive inspections required by this paragraph. Note 4: Airplanes on which Airbus Modification 5997 has been done completely in production, or on which Airbus Service Bulletin A310–53–2058 has been done in service, are not affected by the actions in paragraph (j) of this AD. (1) For Model A310–200 series airplanes, accomplish the inspection at the time specified in paragraph (j)(1)(i) or (j)(1)(ii) of this AD, as applicable. (i) For airplanes that have accumulated less than 20,000 total flight cycles as of January 20, 1999: Prior to the accumulation of 18,000 total flight cycles, or within 2,000 flight cycles after January 20, 1999, whichever occurs later. (ii) For airplanes that have accumulated 20,000 or more total flight cycles as of January 20, 1999: Within 1,000 flight cycles after January 20, 1999. (2) For Model A310–300 series airplanes, accomplish the inspection at the time specified in paragraph (j)(2)(i) or (j)(2)(ii) of this AD, as applicable. (i) For airplanes that have accumulated less than 19,700 total flight cycles as of January 20, 1999: Prior to the accumulation of 18,000 total flight cycles, or within 1,700 flight cycles after January 20, 1999, whichever occurs later. (ii) For airplanes that have accumulated 19,700 or more total flight cycles as of January 20, 1999: Within 850 flight cycles after January 20, 1999. Actions for Service Bulletin A310–55–2002— No Changes (k) For airplanes listed in Airbus Service Bulletin A310–55–2002, Revision 4, dated April 28, 1989: Prior to the accumulation of 12,000 total flight cycles, or within 1,000 flight cycles after January 20, 1999, whichever occurs later, perform an eddy current inspection to detect cracks on the upper integral part adjacent to the rear attach fittings on the horizontal stabilizer, and modify the horizontal stabilizer, in accordance with Airbus Service Bulletin A310–55–2002, Revision 4, dated April 28, 1989. Except as provided by paragraph (m) of this AD, if any discrepancy is found, prior to VerDate Mar<15>2010 16:21 May 10, 2011 Jkt 223001 further flight, perform follow-on corrective actions, as applicable, in accordance with Airbus Service Bulletin A310–55–2002, Revision 4, dated April 28, 1989. Actions for Service Bulletin A310–57–2039— No Changes (l) For airplanes listed in Airbus Service Bulletin A310–57–2039, dated September 24, 1990: Perform either an eddy current or visual inspection to detect cracks on the left and right vertical posts, numbers 1 through 5 inclusive, in the wing center box at frame 40/41, in accordance with Airbus Service Bulletin A310–57–2039, dated September 24, 1990. Perform the inspection at the time specified in paragraph (l)(1) or (l)(2) of this AD, as applicable. Except as provided by paragraph (m) of this AD, if any crack is found, prior to further flight, accomplish the modification specified in Airbus Service Bulletin A310–57–2041, dated September 24, 1990, in accordance with Airbus Service Bulletin A310–57–2039, dated September 24, 1990. Note 5: Airplanes on which Airbus Modification 04977 has been done in production are not affected by the actions specified in paragraph (l) of this AD. (1) For airplanes on which Airbus Modification 7541/S7973 (reference Airbus Service Bulletin A310–57–2041) has not been accomplished: Inspect prior to the accumulation of 21,000 total flight cycles, or within 1,000 flight cycles after January 20, 1999, whichever occurs later; and thereafter at intervals not to exceed 4,200 flight cycles (for a visual inspection), or 7,500 flight cycles (for an eddy current inspection). (2) For airplanes on which Airbus Modification 7541/S7973 (reference Airbus Service Bulletin A310–57–2041) has been accomplished: Inspect at the time specified in the graph contained in Note 1 of paragraph 1.A.(2) of Airbus Service Bulletin A310–57– 2039, dated September 24, 1990, or within 1,000 flight cycles after January 20, 1999, whichever occurs later; and thereafter at intervals not to exceed 5,000 flight cycles (for a visual inspection), or 8,600 flight cycles (for an eddy current inspection). Exception to Certain Service Bulletin Repairs (m) If any crack is found during any inspection required by paragraph (g), (j), (k), or (l) of this AD, and the applicable service bulletin specifies to contact Airbus for an appropriate action: Prior to further flight, repair in accordance with a method approved by either the Manager, International Branch, ANM–116, or the DGAC (or its delegated agent), or European Aviation Safety Agency (EASA) (or its delegated agent). New Requirements of This AD: Actions Actions for Service Bulletin A310–55–2004 (n) For airplanes listed in Airbus Mandatory Service Bulletin A310–55–2004, Revision 05, dated October 13, 2006: At the applicable time specified in paragraph (n)(1) or (n)(2) of this AD, do a high frequency eddy current inspection for cracking of the doubler plate edge, the rear spar area, and specified fastener holes in the top skin chordwise splice along the contour of the steel doubler PO 00000 Frm 00017 Fmt 4700 Sfmt 4700 27235 between ribs 3 and 4 on the left-and righthand center and side boxes on the horizontal stabilizer, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310–55–2004, Revision 05, dated October 13, 2006. If any cracking is found, before further flight, repair in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310–55–2004, Revision 05, dated October 13, 2006; except where this service bulletin specifies to contact Airbus, before further flight, repair in accordance with a method approved by either the Manager, International Branch, ANM–116, FAA, or EASA (or its delegated agent). Thereafter, repeat the inspections at intervals not to exceed 9,700 flight cycles or 19,500 flight hours, whichever occurs first; except as required by paragraph (o) of this AD for the rear spar area. Note 6: Airplanes on which Airbus Modification 06070 has been done in production are not affected by the actions specified in paragraph (l) of this AD. (1) For airplanes on which Airbus Service Bulletin A310–55–2002 was accomplished prior to the accumulation of 6,000 total flight cycles on the airplane; and for airplanes having MSN 311 through 400 inclusive on which Airbus Modification 4933 was accomplished during production: Do the inspection at the later of the compliance times specified in paragraphs (l)(1)(i) and (l)(1)(ii) of this AD. (i) Prior to the accumulation of 14,400 total flight cycles or 28,500 total flight hours, whichever occurs first. (ii) Within 1,500 flight cycles or 18 months after the effective date of this AD, whichever occurs first. (2) For airplanes on which Airbus Service Bulletin A310–55–2002 was accomplished on or after the accumulation of 6,000 total flight cycles: Do the inspection at the later of the times specified in paragraph (l)(2)(i) and (l)(2)(ii) of this AD. (i) Within 9,700 flight cycles or 19,500 flight hours after accomplishing the modification, whichever occurs first. (ii) Within 1,500 flight cycles or 18 months after the effective date of this AD, whichever occurs first. (o) For airplanes on which the initial inspection required by paragraph (n) of this AD has been done and on which a repair was installed at fastener position A in accordance with Airbus Service Bulletin A310–55–2002: At the later of the times specified in paragraphs (o)(1) and (o)(2) of this AD, do a high frequency eddy current inspection for cracking of the rear spar area as specified in paragraph (n) of this AD, and repeat the high frequency eddy current inspection of the rear spar area thereafter at intervals not to exceed 4,800 flight cycles or 9,700 flight hours, whichever occurs first. (1) Within 4,800 flight cycles or 9,700 flight hours, whichever occurs first, after doing the repair in accordance with Airbus Service Bulletin A310–55–2002. (2) Within 400 flight cycles or 800 flight hours, whichever occurs first, after the effective date of this AD. E:\FR\FM\11MYR1.SGM 11MYR1 27236 Federal Register / Vol. 76, No. 91 / Wednesday, May 11, 2011 / Rules and Regulations Credit for Actions Accomplished in Accordance With Previous Service Information (p) Actions accomplished before the effective date of this AD in accordance with Airbus Service Bulletin A310–55–2004, Revision 2, dated February 7, 1991; Revision 3, dated April 16, 1997; and Revision 04, dated April 17, 2001; are acceptable for compliance with the corresponding actions specified in paragraph (n) of this AD. FAA AD Differences Note 7: This AD differs from the MCAI and/or service information as follows: No Differences. Other FAA AD Provisions (q) 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. 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 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 98–26–01, amendment 39–10942, 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 (r) Refer to MCAI EASA Airworthiness Directive 2007–0053R3, dated December 17, 2009, and the service bulletins listed in Table 1 of this AD, for related information. TABLE 1—RELATED INFORMATION Service Bulletin Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Revision Mandatory Service Bulletin A310–55–2004 ......................................................................... Service Bulletin A310–53–2016 ........................................................................................... Service Bulletin A310–53–2019 ........................................................................................... Service Bulletin A310–53–2054 ........................................................................................... Service Bulletin A310–53–2057 ........................................................................................... Service Bulletin A310–53–2059 ........................................................................................... Service Bulletin A310–55–2002 ........................................................................................... Service Bulletin A310–57–2039 ........................................................................................... Service Bulletin A310–57–2041 ........................................................................................... Material Incorporated by Reference (s) You must use the applicable service bulletins contained in Table 2 of this AD, to Date 05 .............................. 5 ................................ 3 ................................ 2 ................................ 1 ................................ 1 ................................ 4 ................................ Original ...................... Original ...................... October 13, 2006. December 7, 1992. February 28, 1991. May 22, 1990. April 30, 1992. January 4, 1996. April 28, 1989. September 24, 1990. September 24, 1990. do the actions required by this AD, unless the AD specifies otherwise. TABLE 2—ALL MATERIAL INCORPORATED BY REFERENCE Service Bulletin Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Airbus Revision Mandatory Service Bulletin A310–55–2004 ......................................................................... Service Bulletin A310–53–2016 ........................................................................................... Service Bulletin A310–53–2019 ........................................................................................... Service Bulletin A310–53–2054 ........................................................................................... Service Bulletin A310–53–2057 ........................................................................................... Service Bulletin A310–53–2059 ........................................................................................... Service Bulletin A310–55–2002 ........................................................................................... Service Bulletin A310–57–2039 ........................................................................................... Service Bulletin A310–57–2041 ........................................................................................... Note 8: Only pages 1 and 6 of Airbus Service Bulletin A310–53–2019, Revision 3, dated February 28, 1991, show revision level 3 and issue date February 28, 1991. All other pages of this document show the original issue date of February 8, 1985. (1) The Director of the Federal Register approved the incorporation by reference of Date 05 .............................. 5 ................................ 3 ................................ 2 ................................ 1 ................................ 1 ................................ 4 ................................ Original ...................... Original ...................... October 13, 2006. December 7, 1992. February 28, 1991. May 22, 1990. April 30, 1992. January 4, 1996. April 28, 1989. September 24, 1990. September 24, 1990. the service information contained in Table 3 of this AD under 5 U.S.C. 552(a) and 1 CFR part 51. TABLE 3—NEW MATERIAL INCORPORATED BY REFERENCE srobinson on DSKHWCL6B1PROD with RULES Service Bulletin Revision Date Airbus Mandatory Service Bulletin A310–55–2004, excluding Appendix 01 .................................. Airbus Service Bulletin A310–53–2019 ........................................................................................... Airbus Service Bulletin A310–57–2041 ........................................................................................... 05 .............................. 3 ................................ Original ...................... October 13, 2006. February 28, 1991. September 24, 1990. Note 9: Only pages 1 and 6 of Airbus Service Bulletin A310–53–2019, Revision 3, pages of this document show the original issue date of February 8, 1985. VerDate Mar<15>2010 16:21 May 10, 2011 Jkt 223001 dated February 28, 1991, show revision level 3 and issue date February 28, 1991. All other PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 E:\FR\FM\11MYR1.SGM 11MYR1 27237 Federal Register / Vol. 76, No. 91 / Wednesday, May 11, 2011 / Rules and Regulations (2) The Director of the Federal Register previously approved the incorporation by reference of the service information contained in Table 4 of this AD on January 20, 1999 (63 FR 69179, December 16, 1998). TABLE 4—MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE Service Bulletin Airbus Airbus Airbus Airbus Airbus Airbus Service Service Service Service Service Service Bulletin Bulletin Bulletin Bulletin Bulletin Bulletin A310–53–2016 A310–53–2054 A310–53–2057 A310–53–2059 A310–55–2002 A310–57–2039 ........................................................................................... ........................................................................................... ........................................................................................... ........................................................................................... ........................................................................................... ........................................................................................... (3) For service information identified in this 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.airwortheas@airbus.com; Internet https:// www.airbus.com. (4) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221. (5) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on April 22, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011–10687 Filed 5–10–11; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2011–0038; Directorate Identifier 2010–NM–153–AD; Amendment 39–16684; AD 2011–10–03] srobinson on DSKHWCL6B1PROD with RULES RIN 2120–AA64 Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model ERJ 170 Airplanes; and Model ERJ 190–100 STD, ERJ 190– 100 LR, ERJ 190–100 IGW, ERJ 190– 200 STD, ERJ 190–200 LR, and ERJ 190–200 IGW Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: VerDate Mar<15>2010 16:21 May 10, 2011 Revision Jkt 223001 We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: SUMMARY: [T]he occurrence of drill marks [has been found] at the lower ring region of the rear pressure bulkhead between [the] circumferential splice joint and rear skin located between stringers 12 and 13. These marks may result in formation of fatigue cracks accelerated by corrosion reducing the structural strength of the rear pressure bulkhead, which may cause a sudden decompression of the passenger cabin. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective June 15, 2011. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of June 15, 2011. ADDRESSES: You may examine the AD docket on the Internet at https:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC. FOR FURTHER INFORMATION CONTACT: Cindy Ashforth, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone 425–227–2768; fax 425–227–1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 Date 5 ................................ 2 ................................ 1 ................................ 1 ................................ 4 ................................ Original ...................... December 7, 1992. May 22, 1990. April 30, 1992. January 4, 1996. April 28, 1989. September 24, 1990. Register on February 10, 2011 (76 FR 7511). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: [T]he occurrence of drill marks [has been found] at the lower ring region of the rear pressure bulkhead between [the] circumferential splice joint and rear skin located between stringers 12 and 13. These marks may result in formation of fatigue cracks accelerated by corrosion reducing the structural strength of the rear pressure bulkhead, which may cause a sudden decompression of the passenger cabin. * * * * * The required actions include doing a detailed inspection for signs of drill marks and repairing if necessary. You may obtain further information by examining the MCAI in the AD docket. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. Conclusion We reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. Differences Between This AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information. We might also have required different actions in this AD from those in the MCAI in order to follow our FAA policies. Any such differences are highlighted in a NOTE within the AD. E:\FR\FM\11MYR1.SGM 11MYR1

Agencies

[Federal Register Volume 76, Number 91 (Wednesday, May 11, 2011)]
[Rules and Regulations]
[Pages 27232-27237]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-10687]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-1276; Directorate Identifier 2010-NM-092-AD; 
Amendment 39-16689; AD 2011-10-08]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A310 Series Airplanes

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

ACTION: Final rule.

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

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

    DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] 
France AD 1992-106-132(B) * * * has been issued in order to mandate 
a set of inspections/modifications which address JAR/FAR [Joint 
Aviation Regulation/Federal Aviation Regulation] 25-571 requirements 
related to damage-tolerance and fatigue evaluation of structure.
* * * * *

The unsafe condition is reduced structural integrity of the wings, 
fuselage, and stabilizers. We are issuing this AD to require actions to 
correct the unsafe condition on these products.

DATES: This AD becomes effective June 15, 2011.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of June 15, 
2011.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of January 
20, 1999 (63 FR 69179, December 16, 1998).

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

[[Page 27233]]


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: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on January 3, 2011 (76 
FR 42), and proposed to supersede AD 98-26-01, Amendment 39-10942 (63 
FR 69179, December 16, 1998), and AD 91-13-01, Amendment 39-7032 (56 FR 
26602, June 10, 1991).
    The NPRM proposed to correct an unsafe condition for the specified 
products. The MCAI states:

    DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] 
France AD 1992-106-132(B) original issue up to revision 7 has been 
issued in order to mandate a set of inspections/modifications which 
address JAR/FAR [Joint Aviation Regulation/Federal Aviation 
Regulation] 25-571 requirements related to damage-tolerance and 
fatigue evaluation of structure [FAA AD 98-26-01 corresponds to DGAC 
AD 1992-106-132(B)R4, dated June 5, 1996].
    Following the Extended Design Service Goal activities part of 
the Structure Task Group for the A310 program, EASA AD 2007-0053 
superseded DGAC France AD F-1992-106-132R7 in order to take into 
account the publication of Airbus Service Bulletins (SB) A310-55-
2004 at Revision 5 and Airbus SB A310-53-2074 at Revision 3, whose 
inspection thresholds and/or intervals had been reduced.
    Revision 1 of this AD was issued to remove the mandatory 
requirements related to the wings (i.e. Sec.  1.8, 1.9, 1.10, 1.13, 
and 1.18) from the Compliance section, which have been transferred 
to EASA AD 2007-0242.
    Revision 2 of this AD has been issued to remove the mandatory 
requirements of paragraph 1.15, 1.16 and 1.17 which have now been 
transferred to EASA AD 2009-0057 (Sec.  1.15 and 1.17) and 2009-0058 
(Sec.  1.16) respectively.
    Revision 3 of this AD is issued to add a Note to the 
Applicability and amend the Required Action(s) and Compliance 
Time(s) section of this AD to clarify the allowed use of the 
referenced SBs by operators. In addition, a note has been added to 
paragraph 1.7 and the notes associated to paragraphs 1.1, 1.2, 1.3, 
1.4, 1.5 and 1.12 have been clarified.

The unsafe condition is reduced structural integrity of the wings, 
fuselage, and stabilizers.
    This NPRM proposed to continue to require certain actions specified 
in AD 98-26-01.
    The NPRM also proposed to expand the inspection area of the high 
frequency eddy current rototest inspection required by paragraph (g) of 
AD 98-26-01. The required actions are as follows, depending on airplane 
configuration:
     A defectoscope or rototest inspection to detect cracks in 
the area of frame 47 and frame 54, install new doublers, and repair if 
necessary.
     Repetitive visual inspections to detect cracks on frame 46 
between the left- and right-hand sides of stringers 21 and 22 on the 
forward and aft faces, and repair if necessary.
     Repetitive visual inspections to detect cracks at the T-
section connecting frame 50A to the beam between the left- and right-
hand sides of frames 50 and 51, and modification if necessary.
     Repetitive visual inspections to detect cracks in the 
lower milled side panel at the lap joint with the upper side panel at 
frame 47 and stringer 22, left- and right-hand sides, and repair if 
necessary.
     An eddy current inspection to detect cracks on the upper 
integral part adjacent to the rear attach fittings on the horizontal 
stabilizer, modification of the horizontal stabilizer, and repair if 
necessary.
     Repetitive high frequency eddy current rototest 
inspections for cracking of the doubler plate edge, rear spar area, and 
at specified fastener holes in the top skin chordwise splice along the 
contour of the steel doubler between ribs 3 and 4 on the left- and 
right-hand center and side boxes on the horizontal stabilizer, 
installing new fasteners if no cracking is found, and repair if 
necessary.
     Repetitive inspections, either an eddy current or visual 
inspection, to detect cracks on the left and right vertical posts, 
numbers 1 through 5 inclusive, in the wing center box at frame 40/41, 
and modification if necessary. You may obtain further information by 
examining the MCAI in the AD docket.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM or on the determination of 
the cost to the public.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting the AD as proposed.

Differences Between This AD and the MCAI or Service Information

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

Costs of Compliance

    We estimate that this AD will affect 44 products of U.S. registry. 
The actions that are required by AD 98-26-01 and are retained in this 
AD take about 1,087 work-hours per product, at an average labor rate of 
$85 per work hour. Required parts cost about $81,973 per product. Based 
on these figures, the estimated cost of the currently required actions 
is $174,368 per product.
    We also estimate that it will take about 3 work-hours per product 
to comply with the basic requirements of this AD. The average labor 
rate is $85 per work-hour. Based on these figures, we estimate the cost 
of this AD to the U.S. operators to be $11,220, or $255 per product.

Authority for This Rulemaking

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

Regulatory Findings

    We determined that this AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on

[[Page 27234]]

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

Examining the AD Docket

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

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The FAA amends Sec.  39.13 by removing Amendment 39-10942 (63 FR 
69179, December 16, 1998) and Amendment 39-7032 (56 FR 26602, June 10, 
1991) and adding the following new AD:

2011-10-08 Airbus: Amendment 39-16689. Docket No. FAA-2010-1276; 
Directorate Identifier 2010-NM-092-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective June 15, 
2011.

Affected ADs

    (b) This AD supersedes AD 98-26-01, Amendment 39-10942, and AD 
91-13-01, Amendment 39-7032.

Applicability

    (c) This AD applies to Airbus Model A310-203, -204, -221, -222, 
-304, -322, -324, and -325 airplanes, certificated in any category, 
all certified models, all serial numbers.

Subject

    (d) Air Transport Association (ATA) of America Codes 53: 
Fuselage, 55: Stabilizers, and 57: Wings.

Reason

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

    DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] 
France AD 1992-106-132(B) * * * has been issued in order to mandate 
a set of inspections/modifications which address JAR/FAR [Joint 
Aviation Regulation/Federal Aviation Regulation] 25-571 requirements 
related to damage-tolerance and fatigue evaluation of structure.
* * * * *
The unsafe condition is reduced structural integrity of the wings, 
fuselage, and stabilizers.

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 Certain Requirements of AD 98-26-01

Actions for Service Bulletin A310-53-2016--No Changes

    (g) For airplanes listed in Airbus Service Bulletin A310-53-
2016, Revision 5, dated December 7, 1992: Prior to the accumulation 
of 12,000 total flight cycles, or within 1,000 flight cycles after 
January 20, 1999 (the effective date of AD 98-26-01), whichever 
occurs later, perform a defectoscope or rototest inspection to 
detect cracks in the area of frame 47 and frame 54, and install new 
doublers, in accordance with Airbus Service Bulletin A310-53-2016, 
Revision 5, dated December 7, 1992. Except as provided by paragraph 
(m) of this AD, if any discrepancy is found, prior to further 
flight, perform follow-on corrective actions, as applicable, in 
accordance with Airbus Service Bulletin A310-53-2016, Revision 5, 
dated December 7, 1992.

    Note 1:  Airplanes on which Airbus Modification 04980 is done in 
production are not affected by paragraph (g) of this AD.

Actions for Service Bulletin A310-53-2054, With Latest Optional 
Modification

    (h) For airplanes listed in Airbus Service Bulletin A310-53-
2054, Revision 2, dated May 22, 1990: Prior to the accumulation of 
12,000 total flight cycles, or within 1,000 flight cycles after 
January 20, 1999, whichever occurs later, and thereafter at 
intervals not to exceed 3,000 flight cycles, perform a visual 
inspection to detect cracks on frame 46 between the left- and right-
hand sides of stringers 21 and 22 on the forward and aft faces, in 
accordance with Airbus Service Bulletin A310-53-2054, Revision 2, 
dated May 22, 1990. If any crack is found, prior to further flight, 
repair in accordance with Airbus Service Bulletin A310-53-2054, 
Revision 2, dated May 22, 1990.

    Note 2:  Airplanes on which Airbus modification 05254 is done in 
production; or on which Airbus Service Bulletin A310-53-2019, 
Revision 2, dated May 22, 1990, or Revision 3, dated February 28, 
1991, is done in service; are not affected by paragraph (h) of this 
AD.

    (1) Prior to the effective date of this AD: Accomplishment of 
the repair required by paragraph (h) of this AD; or modification of 
the reinforcement angle runout in accordance with Airbus Service 
Bulletin A310-53-2019, Revision 2, dated May 22, 1990, or Revision 
3, dated February 28, 1991; terminates the repetitive inspection 
requirements of paragraph (h) of this AD.
    (2) On or after the effective date of this AD: Accomplishment of 
the repair required by paragraph (h) of this AD; or modification of 
the reinforcement angle runout in accordance with Airbus Service 
Bulletin A310-53-2019, Revision 3, dated February 28, 1991; 
terminates the repetitive inspection requirements of paragraph (h) 
of this AD.

Actions for Service Bulletin A310-53-2057--No Changes

    (i) For airplanes listed in Airbus Service Bulletin A310-53-
2057, Revision 1, dated April 30, 1992: Perform a visual inspection 
to detect cracks at the T-section connecting frame 50A to the beam 
between the left- and right-hand sides of frames 50 and 51, in 
accordance with Airbus Service Bulletin A310-53-2057, Revision 1, 
dated April 30, 1992. Perform the inspection at the time specified 
in paragraph (i)(1) or (i)(2) of this AD, as applicable. If any 
crack is found, prior to further flight, accomplish Airbus 
Modifications No. 4853 and No. 5273, in accordance with Airbus 
Service Bulletin A310-53-2057, Revision 1, dated April 30, 1992. 
Accomplishment of these modifications terminates the requirements of 
this paragraph.

    Note 3:  Airplanes on which Airbus modification 4853 is done are 
affected by paragraph (i) of this AD, except those airplanes on 
which Airbus Modification 5273 has been done or on which Airbus 
Service Bulletin A310-53-2011 has been done in service.

    (1) For the airplane having manufacturer's serial number (MSN) 
191: Prior to the accumulation of 24,000 total flight cycles, or 
within 1,000 flight cycles after January 20, 1999, whichever occurs 
later; and thereafter at intervals not to exceed 6,000 flight 
cycles.
    (2) For airplanes other than the airplane identified in 
paragraph (i)(1) of this AD: Prior to the accumulation of 12,000 
total flight cycles, or within 1,000 flight cycles after January 20, 
1999, whichever occurs later; and thereafter at intervals not to 
exceed 6,000 flight cycles.

[[Page 27235]]

Actions for Service Bulletin A310-53-2059--No Changes

    (j) For airplanes listed in Airbus Service Bulletin A310-53-
2059, Revision 1, dated January 4, 1996: Perform a visual inspection 
to detect cracks in the lower milled side panel at the lap joint 
with the upper side panel at frame 47 and stringer 22, left- and 
right-hand sides, in accordance with Airbus Service Bulletin A310-
53-2059, Revision 1, dated January 4, 1996. Perform the inspection 
at the time specified in paragraph (j)(1) or (j)(2) of this AD, as 
applicable. Except as provided by paragraph (m) of this AD, if any 
crack is found, prior to further flight, repair in accordance with 
Airbus Service Bulletin A310-53-2059, Revision 1, dated January 4, 
1996. Thereafter, repeat the inspections at intervals not to exceed 
9,000 flight cycles, or accomplish Airbus Modification 5997 (Airbus 
Service Bulletin A310-53-2058). Accomplishment of either the repair 
or Airbus Modification 5997 constitutes terminating action for the 
repetitive inspections required by this paragraph.

    Note 4:  Airplanes on which Airbus Modification 5997 has been 
done completely in production, or on which Airbus Service Bulletin 
A310-53-2058 has been done in service, are not affected by the 
actions in paragraph (j) of this AD.

    (1) For Model A310-200 series airplanes, accomplish the 
inspection at the time specified in paragraph (j)(1)(i) or 
(j)(1)(ii) of this AD, as applicable.
    (i) For airplanes that have accumulated less than 20,000 total 
flight cycles as of January 20, 1999: Prior to the accumulation of 
18,000 total flight cycles, or within 2,000 flight cycles after 
January 20, 1999, whichever occurs later.
    (ii) For airplanes that have accumulated 20,000 or more total 
flight cycles as of January 20, 1999: Within 1,000 flight cycles 
after January 20, 1999.
    (2) For Model A310-300 series airplanes, accomplish the 
inspection at the time specified in paragraph (j)(2)(i) or 
(j)(2)(ii) of this AD, as applicable.
    (i) For airplanes that have accumulated less than 19,700 total 
flight cycles as of January 20, 1999: Prior to the accumulation of 
18,000 total flight cycles, or within 1,700 flight cycles after 
January 20, 1999, whichever occurs later.
    (ii) For airplanes that have accumulated 19,700 or more total 
flight cycles as of January 20, 1999: Within 850 flight cycles after 
January 20, 1999.

Actions for Service Bulletin A310-55-2002--No Changes

    (k) For airplanes listed in Airbus Service Bulletin A310-55-
2002, Revision 4, dated April 28, 1989: Prior to the accumulation of 
12,000 total flight cycles, or within 1,000 flight cycles after 
January 20, 1999, whichever occurs later, perform an eddy current 
inspection to detect cracks on the upper integral part adjacent to 
the rear attach fittings on the horizontal stabilizer, and modify 
the horizontal stabilizer, in accordance with Airbus Service 
Bulletin A310-55-2002, Revision 4, dated April 28, 1989. Except as 
provided by paragraph (m) of this AD, if any discrepancy is found, 
prior to further flight, perform follow-on corrective actions, as 
applicable, in accordance with Airbus Service Bulletin A310-55-2002, 
Revision 4, dated April 28, 1989.

Actions for Service Bulletin A310-57-2039--No Changes

    (l) For airplanes listed in Airbus Service Bulletin A310-57-
2039, dated September 24, 1990: Perform either an eddy current or 
visual inspection to detect cracks on the left and right vertical 
posts, numbers 1 through 5 inclusive, in the wing center box at 
frame 40/41, in accordance with Airbus Service Bulletin A310-57-
2039, dated September 24, 1990. Perform the inspection at the time 
specified in paragraph (l)(1) or (l)(2) of this AD, as applicable. 
Except as provided by paragraph (m) of this AD, if any crack is 
found, prior to further flight, accomplish the modification 
specified in Airbus Service Bulletin A310-57-2041, dated September 
24, 1990, in accordance with Airbus Service Bulletin A310-57-2039, 
dated September 24, 1990.

    Note 5:  Airplanes on which Airbus Modification 04977 has been 
done in production are not affected by the actions specified in 
paragraph (l) of this AD.

    (1) For airplanes on which Airbus Modification 7541/S7973 
(reference Airbus Service Bulletin A310-57-2041) has not been 
accomplished: Inspect prior to the accumulation of 21,000 total 
flight cycles, or within 1,000 flight cycles after January 20, 1999, 
whichever occurs later; and thereafter at intervals not to exceed 
4,200 flight cycles (for a visual inspection), or 7,500 flight 
cycles (for an eddy current inspection).
    (2) For airplanes on which Airbus Modification 7541/S7973 
(reference Airbus Service Bulletin A310-57-2041) has been 
accomplished: Inspect at the time specified in the graph contained 
in Note 1 of paragraph 1.A.(2) of Airbus Service Bulletin A310-57-
2039, dated September 24, 1990, or within 1,000 flight cycles after 
January 20, 1999, whichever occurs later; and thereafter at 
intervals not to exceed 5,000 flight cycles (for a visual 
inspection), or 8,600 flight cycles (for an eddy current 
inspection).

Exception to Certain Service Bulletin Repairs

    (m) If any crack is found during any inspection required by 
paragraph (g), (j), (k), or (l) of this AD, and the applicable 
service bulletin specifies to contact Airbus for an appropriate 
action: Prior to further flight, repair in accordance with a method 
approved by either the Manager, International Branch, ANM-116, or 
the DGAC (or its delegated agent), or European Aviation Safety 
Agency (EASA) (or its delegated agent).

New Requirements of This AD: Actions

Actions for Service Bulletin A310-55-2004

    (n) For airplanes listed in Airbus Mandatory Service Bulletin 
A310-55-2004, Revision 05, dated October 13, 2006: At the applicable 
time specified in paragraph (n)(1) or (n)(2) of this AD, do a high 
frequency eddy current inspection for cracking of the doubler plate 
edge, the rear spar area, and specified fastener holes in the top 
skin chordwise splice along the contour of the steel doubler between 
ribs 3 and 4 on the left-and right-hand center and side boxes on the 
horizontal stabilizer, in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A310-55-2004, 
Revision 05, dated October 13, 2006. If any cracking is found, 
before further flight, repair in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A310-55-2004, 
Revision 05, dated October 13, 2006; except where this service 
bulletin specifies to contact Airbus, before further flight, repair 
in accordance with a method approved by either the Manager, 
International Branch, ANM-116, FAA, or EASA (or its delegated 
agent). Thereafter, repeat the inspections at intervals not to 
exceed 9,700 flight cycles or 19,500 flight hours, whichever occurs 
first; except as required by paragraph (o) of this AD for the rear 
spar area.

    Note 6:  Airplanes on which Airbus Modification 06070 has been 
done in production are not affected by the actions specified in 
paragraph (l) of this AD.

    (1) For airplanes on which Airbus Service Bulletin A310-55-2002 
was accomplished prior to the accumulation of 6,000 total flight 
cycles on the airplane; and for airplanes having MSN 311 through 400 
inclusive on which Airbus Modification 4933 was accomplished during 
production: Do the inspection at the later of the compliance times 
specified in paragraphs (l)(1)(i) and (l)(1)(ii) of this AD.
    (i) Prior to the accumulation of 14,400 total flight cycles or 
28,500 total flight hours, whichever occurs first.
    (ii) Within 1,500 flight cycles or 18 months after the effective 
date of this AD, whichever occurs first.
    (2) For airplanes on which Airbus Service Bulletin A310-55-2002 
was accomplished on or after the accumulation of 6,000 total flight 
cycles: Do the inspection at the later of the times specified in 
paragraph (l)(2)(i) and (l)(2)(ii) of this AD.
    (i) Within 9,700 flight cycles or 19,500 flight hours after 
accomplishing the modification, whichever occurs first.
    (ii) Within 1,500 flight cycles or 18 months after the effective 
date of this AD, whichever occurs first.
    (o) For airplanes on which the initial inspection required by 
paragraph (n) of this AD has been done and on which a repair was 
installed at fastener position A in accordance with Airbus Service 
Bulletin A310-55-2002: At the later of the times specified in 
paragraphs (o)(1) and (o)(2) of this AD, do a high frequency eddy 
current inspection for cracking of the rear spar area as specified 
in paragraph (n) of this AD, and repeat the high frequency eddy 
current inspection of the rear spar area thereafter at intervals not 
to exceed 4,800 flight cycles or 9,700 flight hours, whichever 
occurs first.
    (1) Within 4,800 flight cycles or 9,700 flight hours, whichever 
occurs first, after doing the repair in accordance with Airbus 
Service Bulletin A310-55-2002.
    (2) Within 400 flight cycles or 800 flight hours, whichever 
occurs first, after the effective date of this AD.

[[Page 27236]]

Credit for Actions Accomplished in Accordance With Previous Service 
Information

    (p) Actions accomplished before the effective date of this AD in 
accordance with Airbus Service Bulletin A310-55-2004, Revision 2, 
dated February 7, 1991; Revision 3, dated April 16, 1997; and 
Revision 04, dated April 17, 2001; are acceptable for compliance 
with the corresponding actions specified in paragraph (n) of this 
AD.

FAA AD Differences

    Note 7:  This AD differs from the MCAI and/or service 
information as follows: No Differences.

Other FAA AD Provisions

    (q) 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. 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 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 98-26-01, amendment 39-
10942, 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

    (r) Refer to MCAI EASA Airworthiness Directive 2007-0053R3, 
dated December 17, 2009, and the service bulletins listed in Table 1 
of this AD, for related information.

                                          Table 1--Related Information
----------------------------------------------------------------------------------------------------------------
           Service Bulletin                           Revision                               Date
----------------------------------------------------------------------------------------------------------------
Airbus Mandatory Service Bulletin A310- 05.................................  October 13, 2006.
 55-2004.
Airbus Service Bulletin A310-53-2016..  5..................................  December 7, 1992.
Airbus Service Bulletin A310-53-2019..  3..................................  February 28, 1991.
Airbus Service Bulletin A310-53-2054..  2..................................  May 22, 1990.
Airbus Service Bulletin A310-53-2057..  1..................................  April 30, 1992.
Airbus Service Bulletin A310-53-2059..  1..................................  January 4, 1996.
Airbus Service Bulletin A310-55-2002..  4..................................  April 28, 1989.
Airbus Service Bulletin A310-57-2039..  Original...........................  September 24, 1990.
Airbus Service Bulletin A310-57-2041..  Original...........................  September 24, 1990.
----------------------------------------------------------------------------------------------------------------

Material Incorporated by Reference

    (s) You must use the applicable service bulletins contained in 
Table 2 of this AD, to do the actions required by this AD, unless 
the AD specifies otherwise.

                                 Table 2--All Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
           Service Bulletin                           Revision                               Date
----------------------------------------------------------------------------------------------------------------
Airbus Mandatory Service Bulletin A310- 05.................................  October 13, 2006.
 55-2004.
Airbus Service Bulletin A310-53-2016..  5..................................  December 7, 1992.
Airbus Service Bulletin A310-53-2019..  3..................................  February 28, 1991.
Airbus Service Bulletin A310-53-2054..  2..................................  May 22, 1990.
Airbus Service Bulletin A310-53-2057..  1..................................  April 30, 1992.
Airbus Service Bulletin A310-53-2059..  1..................................  January 4, 1996.
Airbus Service Bulletin A310-55-2002..  4..................................  April 28, 1989.
Airbus Service Bulletin A310-57-2039..  Original...........................  September 24, 1990.
Airbus Service Bulletin A310-57-2041..  Original...........................  September 24, 1990.
----------------------------------------------------------------------------------------------------------------


    Note 8:  Only pages 1 and 6 of Airbus Service Bulletin A310-53-
2019, Revision 3, dated February 28, 1991, show revision level 3 and 
issue date February 28, 1991. All other pages of this document show 
the original issue date of February 8, 1985.

    (1) The Director of the Federal Register approved the 
incorporation by reference of the service information contained in 
Table 3 of this AD under 5 U.S.C. 552(a) and 1 CFR part 51.

                                 Table 3--New Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
           Service Bulletin                           Revision                               Date
----------------------------------------------------------------------------------------------------------------
Airbus Mandatory Service Bulletin A310- 05.................................  October 13, 2006.
 55-2004, excluding Appendix 01.
Airbus Service Bulletin A310-53-2019..  3..................................  February 28, 1991.
Airbus Service Bulletin A310-57-2041..  Original...........................  September 24, 1990.
----------------------------------------------------------------------------------------------------------------


    Note 9:  Only pages 1 and 6 of Airbus Service Bulletin A310-53-
2019, Revision 3, dated February 28, 1991, show revision level 3 and 
issue date February 28, 1991. All other pages of this document show 
the original issue date of February 8, 1985.


[[Page 27237]]


    (2) The Director of the Federal Register previously approved the 
incorporation by reference of the service information contained in 
Table 4 of this AD on January 20, 1999 (63 FR 69179, December 16, 
1998).

                             Table 4--Material Previously Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
           Service Bulletin                           Revision                               Date
----------------------------------------------------------------------------------------------------------------
Airbus Service Bulletin A310-53-2016..  5..................................  December 7, 1992.
Airbus Service Bulletin A310-53-2054..  2..................................  May 22, 1990.
Airbus Service Bulletin A310-53-2057..  1..................................  April 30, 1992.
Airbus Service Bulletin A310-53-2059..  1..................................  January 4, 1996.
Airbus Service Bulletin A310-55-2002..  4..................................  April 28, 1989.
Airbus Service Bulletin A310-57-2039..  Original...........................  September 24, 1990.
----------------------------------------------------------------------------------------------------------------

     (3) For service information identified in this 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.
    (4) You may review copies of the service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington. For information on the availability of this material at 
the FAA, call 425-227-1221.
    (5) You may also review copies of the service information that 
is incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at NARA, call 202-741-6030, or go to: https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on April 22, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-10687 Filed 5-10-11; 8:45 am]
BILLING CODE 4910-13-P