Airworthiness Directives; Airbus Airplanes, 31386-31389 [2013-11903]

Download as PDF 31386 Federal Register / Vol. 78, No. 101 / Friday, May 24, 2013 / Rules and Regulations DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–1163; Directorate Identifier 2011–NM–246–AD; Amendment 39–17456; AD 2013–10–03] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are superseding an existing airworthiness directive (AD) for all Airbus Model A330–200 and –300 series airplanes; and Model A340–200, –300, –500, and –600 series airplanes. That AD currently requires a one-time detailed inspection of both main landing gear (MLG) bogie beams in the region of the bogie stop pad for detection of deformation and damage, and corrective actions if necessary. This new AD adds Model A330–200 Freighter series airplanes to the applicability. For certain airplanes, this new AD also adds repetitive inspections for damage and corrosion of the sliding piston sub-assembly, with new related investigative and corrective actions. This AD was prompted by reports of corroded bogie stop pads, including some with cracking. We are issuing this AD to detect and correct deformation or damage under the bogie stop pad of both MLG bogie beams, which could result in a damaged bogie beam and consequent detachment of the beam from the airplane or collapse of the MLG and departure of the airplane from the runway. DATES: This AD becomes effective June 28, 2013. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of June 28, 2013. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of March 4, 2010 (75 FR 4477, January 28, 2010). ADDRESSES: You may examine the AD docket on the Internet at https:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC. FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, mstockstill on DSK4VPTVN1PROD with RULES SUMMARY: VerDate Mar<15>2010 17:44 May 23, 2013 Jkt 229001 International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone (425) 227–1138; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on November 16, 2012 (77 FR 68711), and proposed to supersede AD 2010–02–10, Amendment 39–16181 (75 FR 4477, January 28, 2010). That NPRM proposed to correct an unsafe condition for the specified products. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community has issued EASA Airworthiness Directive 2011–0211, dated October 31, 2011 (referred to after this as ‘‘the MCAI’’), to supersede EASA AD 2008–0223, dated December 15, 2008 (referred to in the existing AD), and correct an unsafe condition for the specified products. The MCAI states: During a scheduled maintenance inspection on the MLG [main landing gear], the bogie stop pad was found deformed and cracked. Upon removal of the bogie stop pad for replacement, the bogie beam was also found cracked. Laboratory investigation indicates that an overload event has occurred and no fatigue propagation of the crack was evident. A second bogie beam crack has subsequently been found on another aeroplane, located under a bogie stop pad which only had superficial paint damage. This condition, if not detected and corrected, could result in the aeroplane departing the runway or to the bogie detaching from the aeroplane or gear collapses, which would all constitute unsafe conditions at speeds above 30 knots. As a precautionary measure, EASA AD 2008–0223 [which corresponds to FAA AD 2010–02–10, Amendment 39–16181 (75 FR 4477, January 28, 2010] required one-time detailed inspections under the bogie stop pad of both MLG bogie beams and, in case deformation or damage is detected, to apply the associated repair. Numerous bogie stop pad were found corroded and a few cracked as a result of the one-time inspection required by EASA AD 2008–0223 on A330, A340–200 and A340– 300 aeroplanes. For the reasons describe above, this [EASA] AD, which supersedes EASA AD 2008–0223: —retains the initial inspection requirement of EASA AD 2008–0223 for A330, A340– 200 and A340–300 aeroplanes. —introduces a repetitive detailed visual inspection for A330, A340–200 and A340– 300 aeroplanes. —retains the requirement of EASA AD 2008– 0223 for A340–500 and A340–600 PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 aeroplanes, for which further mandatory requirements might follow in future depending on the results of the one-time mandatory inspection in place. The required actions include repetitive detailed inspections for damage and corrosion of the sliding piston subassembly, with new related investigative and corrective actions. Related investigative actions include a test for indications of corrosion and damage to the bogie assembly base material, and a magnetic particle inspection for cracks, corrosion, and damage of the bogie beam. Corrective actions include repairing affected parts. You may obtain further information by examining the MCAI in the AD docket. Revised Service Information Since we issued the NPRM (77 FR 68711, November 16, 2012), we have reviewed the following revised service information. No additional work is specified by these revisions. • Airbus Mandatory Service Bulletin A330–32–3220, Revision 02, dated December 13, 2012 (for Model A330– 200 and –300 series airplanes). • Airbus Mandatory Service Bulletin A330–32–3248, Revision 01, including Appendix 1, dated December 13, 2012 (for Model A330–200, –200 Freighter, and –300 series airplanes). We have revised paragraphs (i) and (j) of this AD to refer to the revised service information, added a new paragraph (l) to give credit for earlier revisions of this service information, and re-identified subsequent paragraphs accordingly. Comments We gave the public the opportunity to participate in developing this AD. We considered the comment received. Request To Remove or Revise Reporting Requirement Delta Air Lines, Inc. (Delta) asked that the compliance time for the reporting requirement specified in the NPRM (77 FR 68711, November 16, 2012) be extended from 30 to 180 days. Delta stated that, unless we plan to rescind or revise this AD in the near future based on the findings, paragraph (l)(1) of the NPRM (paragraph (m)(1) of the final rule) should be removed. Delta also recommended that the reporting be mandated only for positive findings— not positive and negative findings—and specifically for those findings that are beyond the repair limits identified in the applicable component maintenance manual. Delta stated that this would allow findings to be batched together for a grouped report and would preclude undue compliance issues related to late reporting. E:\FR\FM\24MYR1.SGM 24MYR1 Federal Register / Vol. 78, No. 101 / Friday, May 24, 2013 / Rules and Regulations We do not agree to remove the reporting requirement in paragraph (m) of this AD. The reporting requirement is included in the requirements in the EASA AD, and our AD follows those requirements in order to ensure that the unsafe condition is adequately addressed. Reporting of both positive and negative findings is necessary to determine the scope of the problem. Reporting all findings will allow the manufacturer to conduct statistical analyses and apply the results to calculate more accurate life limits for the affected parts. We have made no change to the AD in this regard. In addition, we do not agree to extend the compliance time for the reporting requirement to 180 days; however, we will extend it to 90 days to be consistent with the compliance time for the reporting requirement in the EASA AD referred to in this AD. We have changed the compliance time for the reporting requirement in paragraph (m) of this AD accordingly. mstockstill on DSK4VPTVN1PROD with RULES Conclusion We reviewed the available data, including the comment received, and determined that air safety and the public interest require adopting the AD with the changes described previously. We also determined that these changes will not increase the economic burden on any operator or increase the scope of the AD. Costs of Compliance Based on the service information, we estimate that this AD affects about 67 products of U.S. registry. The actions that are required by AD 2010–02–10, Amendment 39–16181 (75 FR 4477, January 28, 2010), and retained in this AD take about 2 work-hours per product, at an average labor rate of $85 per work hour. Based on these figures, the estimated cost of the currently required actions is $170 per product. We estimate that it will take about 16 work-hours per product to comply with the new basic requirements of this AD. The average labor rate is $85 per workhour. Based on these figures, we estimate the cost of the AD on U.S. operators to be $91,120, or $1,360 per product. We have received no definitive data that will enable us to provide cost estimates for the on-condition actions specified in this AD. 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: VerDate Mar<15>2010 17:44 May 23, 2013 Jkt 229001 Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that 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); 3. Will not affect intrastate aviation in Alaska; and 4. 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. 31387 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 airworthiness directive (AD) 2010–02–10, Amendment 39–16181 (75 FR 4477, January 28, 2010), and adding the following new AD: ■ 2013–10–03 Airbus: Amendment 39–17456. Docket No. FAA–2012–1163; Directorate Identifier 2011–NM–246–AD. (a) Effective Date This airworthiness directive (AD) becomes effective June 28, 2013. (b) Affected ADs This AD supersedes AD 2010–02–10, Amendment 39–16181 (75 FR 4477, January 28, 2010). (c) Applicability This AD applies to all Airbus Model A330– 201, –202, –203, –223, –223F, –243, –243F, –301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes; Model A340–211, –212, –213, –311, –312, –313 airplanes; and Model A340–541 and –642 airplanes; certificated in any category; all serial numbers. (d) Subject Air Transport Association (ATA) of America Code 32: Landing gear. 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 (77 FR 68711, November 16, 2012), 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. (e) Reason This AD was prompted by reports of corroded bogie stop pads, some with cracking. We are issuing this AD to detect and correct deformation or damage under the bogie stop pad of both main landing gear (MLG) bogie beams, which could result in a damaged bogie beam and consequent detachment of the beam from the airplane or collapse of the MLG and departure of the airplane from the runway. (f) Compliance You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 (g) Retained One-Time Inspection and Corrective Actions, With Revised Service Information This paragraph restates the requirements of paragraph (f)(1) of AD 2010–02–10, Amendment 39–16181 (75 FR 4477, January 28, 2010), with revised service information. For Model A330–200 and –300 series airplanes, and Model A340–200, –300, –500, and –600 series airplanes, except as required E:\FR\FM\24MYR1.SGM 24MYR1 mstockstill on DSK4VPTVN1PROD with RULES 31388 Federal Register / Vol. 78, No. 101 / Friday, May 24, 2013 / Rules and Regulations by paragraph (i) of this AD: At the applicable compliance time specified in paragraph (g)(1), (g)(2), (g)(3), (g)(4), (g)(5), or (g)(6) of this AD, perform one-time detailed inspections of both MLG bogie beams in the region of the bogie stop pad for detection of deformation and damage, and apply the applicable corrective actions, in accordance with the Accomplishment Instructions of the applicable service bulletin specified in paragraph (g)(7) of this AD. Do all applicable corrective actions before further flight. (1) Airplanes with 22 months or less and 2,500 flight cycles or less from the first flight with the original bogie beam as of March 4, 2010 (the effective date of AD 2010–02–10, Amendment 39–16181 (75 FR 4477, January 28, 2010)): Not earlier than 2,500 flight cycles or 22 months on the original bogie beam, whichever occurs first, but not later than 40 months from first flight. (2) Airplanes with 22 months or less and 2,500 flight cycles or less from the installation date of a new bogie beam in service as of March 4, 2010 (the effective date of AD 2010–02–10, Amendment 39–16181 (75 FR 4477, January 28, 2010)): Not earlier than 2,500 flight cycles or 22 months from the installation date of the new bogie beam, whichever occurs first, but not later than 40 months from the installation date of a new bogie beam in service. (3) Airplanes with 22 months or less and 2,500 flight cycles or less from the installation date of an overhauled bogie beam in service as of March 4, 2010 (the effective date of AD 2010–02–10, Amendment 39– 16181 (75 FR 4477, January 28, 2010)): Not earlier than 2,500 flight cycles or 22 months from the installation date of the overhauled bogie beam in service, whichever occurs first, but not later than 40 months from the installation date of the overhauled bogie beam in service. (4) Airplanes with more than 22 months or more than 2,500 flight cycles from the first flight with the original bogie beam, as of March 4, 2010 (the effective date of AD 2010– 02–10, Amendment 39–16181 (75 FR 4477, January 28, 2010)): Within 18 months after March 4, 2010 (the effective date of AD 2010– 02–10). (5) Airplanes with more than 22 months or more than 2,500 flight cycles from the installation date of a new bogie beam in service, as of March 4, 2010 (the effective date of AD 2010–02–10, Amendment 39– 16181 (75 FR 4477, January 28, 2010)): Within 18 months after March 4, 2010 (the effective date of AD 2010–02–10). (6) Airplanes with more than 22 months or more than 2,500 flight cycles from the installation date of an overhauled bogie beam in service, as of March 4, 2010 (the effective date of AD 2010–02–10, Amendment 39– 16181 (75 FR 4477, January 28, 2010)): Within 18 months after March 4, 2010 (the effective date of AD 2010–02–10). (7) Use the applicable service information to accomplish the actions required by paragraph (g) of this AD. (i) For Model A330–200 and –300 series airplanes: Airbus Mandatory Service Bulletin A330–32–3220, dated October 10, 2008; Revision 01, dated October 5, 2011; or Revision 02, dated December 13, 2012. VerDate Mar<15>2010 17:44 May 23, 2013 Jkt 229001 (ii) For Model A340–200 and –300 series airplanes: Airbus Mandatory Service Bulletin A340–32–4264, dated October 10, 2008. (iii) For Model A340–500 and –600 series airplanes: Airbus Mandatory Service Bulletin A340–32–5087, dated October 10, 2008. (ii) For Model A340–200 and –300 series airplanes: Airbus Mandatory Service Bulletin A340–32–4264, dated October 10, 2008. (iii) For Model A340–500 and –600 series airplanes: Airbus Mandatory Service Bulletin A340–32–5087, dated October 10, 2008. (h) Retained Reporting Requirement This paragraph restates the requirements of paragraph (f)(2) of AD 2010–02–10, Amendment 39–16181 (75 FR 4477, January 28, 2010). Report the results of the inspection required by paragraph (g) of this AD, including no findings, to Airbus, Customer Services Directorate, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex France; Attn: SEDCC1 Technical Data and Documentation Services; fax (+33) 5 61 93 28 06; email sb.reporting@airbus.com; at the applicable time specified in paragraph (h)(1) or (h)(2) of this AD. (1) If the inspection is done on or after March 4, 2010 (the effective date of AD 2010– 02–10, Amendment 39–16181 (75 FR 4477, January 28, 2010)): Submit the report within 30 days after doing the inspection. (2) If the inspection was done prior to March 4, 2010 (the effective date of AD 2010– 02–10, Amendment 39–16181 (75 FR 4477, January 28, 2010)): Submit the report within 30 days after March 4, 2010 (the effective date of AD 2010–02–10). (j) New Repetitive Inspections Except for bogie beams that have been inspected as specified in Airbus Mandatory Service Bulletin A340–32–5087: At the later of the times specified in paragraphs (j)(1) and (j)(2) of this AD, do the detailed inspection of both MLG bogie beams in the bogie stop pad area for damage and corrosion, and all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A330–32–3248, Revision 01, dated December 13, 2012 (for Model A330–200, –200 Freighter, and –300 series airplanes); or Airbus Mandatory Service Bulletin A340–32–4286, dated October 5, 2011 (for Model A340–200 and –300 series airplanes); except as required by paragraph (k) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspection thereafter at intervals not to exceed 2,500 flight cycles or 24 months, whichever is first. (1) Within 2,500 flight cycles or 24 months, whichever occurs first, accumulated by a MLG bogie beam since its first flight after the most recent accomplishment of Airbus Mandatory Service Bulletin A330–32–3220 or A340–32–4264, as applicable. (2) Within 3 months after the effective date of this AD. (i) New Inspections of Beams That Have Not Been Inspected As of the Effective Date of This AD For bogie beams on which the inspection required by paragraph (g) of this AD has not been accomplished as of the effective date of this AD: At the later of the times specified in paragraphs (i)(1) and (i)(2) of this AD, perform one-time detailed inspections of both MLG bogie beams in the region of the bogie stop pad for detection of deformation and damage, and apply the applicable corrective actions, in accordance with the Accomplishment Instructions of the applicable service information specified in paragraph (i)(3) of this AD. Do all applicable corrective actions before further flight. (1) At the applicable time specified in paragraph (i)(1)(i) or (i)(1)(ii) of this AD. (i) For bogie beams that have not been overhauled: Not earlier than 2,500 flight cycles or 22 months, whichever occurs first, on a bogie beam since its first flight on an airplane since new, but not later than 40 months since its first flight on an airplane since new. (ii) For bogie beams that have been overhauled: Not earlier than 2,500 flight cycles or 22 months, whichever occurs first, on a bogie beam since its first flight on an airplane after its most recent overhaul, but not later than 40 months since its first flight on an airplane after its most recent overhaul. (2) Within 90 days after the effective date of this AD. (3) Use the applicable service information specified in paragraph (i)(3)(i), (i)(3)(ii), or (i)(3)(iii) of this AD, to accomplish the actions required by paragraph (i) of this AD. (i) For Model A330–200 and –300 series airplanes: Airbus Mandatory Service Bulletin A330–32–3220, Revision 02, dated December 13, 2012. PO 00000 Frm 00022 Fmt 4700 Sfmt 4700 (k) Service Information Exception If any cracking of the bogie beam is detected during any inspection or repair required by paragraph (j) of this AD, or any repair required by paragraph (j) of this AD is beyond the maximum repair allowance specified in the applicable service information required by paragraph (j) of this AD: Before further flight, repair using a method approved by either the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent). (l) Credit for Previous Actions This paragraph provides credit for the actions specified in paragraphs (i) and (j) of this AD, if those actions were performed before the effective date of this AD using Airbus Mandatory Service Bulletin A330–32– 3220, dated October 10, 2008, or Airbus Mandatory Service Bulletin A330–32–3220, Revision 01, dated October 5, 2011; or Airbus Mandatory Service Bulletin A330–32–3248, dated October 5, 2011; as applicable; which are not incorporated by reference in this AD. (m) New Reporting Requirement Report the results of the initial inspection required by paragraph (j) of this AD, including both positive and negative findings, to Airbus, Customer Services Directorate, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex France; Attn: SEDCC1 Technical Data and Documentation Services; fax (+33) 5 61 93 28 06; email sb.reporting@airbus.com; at the applicable E:\FR\FM\24MYR1.SGM 24MYR1 Federal Register / Vol. 78, No. 101 / Friday, May 24, 2013 / Rules and Regulations time specified in paragraph (m)(1) or (m)(2) of this AD. (1) If the inspection is done on or after the effective date of this AD: Submit the report within 90 days after doing the inspection. (2) If the inspection was done prior to the effective date of this AD: Submit the report within 90 days after the effective date of this AD. mstockstill on DSK4VPTVN1PROD with RULES (n) Other FAA AD Provisions 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: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057– 3356; telephone (425) 227–1138; fax (425) 227–1149. Information may be emailed 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 2010–02–10, Amendment 39–16181 (75 FR 4477, January 28, 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. (3) Reporting Requirements: A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120–0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing, and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES–200. VerDate Mar<15>2010 17:44 May 23, 2013 Jkt 229001 (o) Special Flight Permits Special flight permits, as described in Section 21.197 and Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199), are not allowed if any crack is found during any inspection required by this AD. (p) Related Information (1) Refer to mandatory continued airworthiness information (MCAI) EASA Airworthiness Directive 2011–0211, dated October 31, 2011, and the service information specified in paragraphs (p)(1)(i) through (p)(1)(vii) of this AD, for related information. (i) Airbus Mandatory Service Bulletin A330–32–3220, dated October 10, 2008. (ii) Airbus Mandatory Service Bulletin A330–32–3220, Revision 01, dated October 5, 2011. (iii) Airbus Mandatory Service Bulletin A330–32–3220, Revision 02, dated December 13, 2012. (iv) Airbus Mandatory Service Bulletin A330–32–3248, Revision 01, including Appendix 01, dated December 13, 2012. (v) Airbus Mandatory Service Bulletin A340–32–4264, dated October 10, 2008. (vi) Airbus Mandatory Service Bulletin A340–32–4286, dated October 5, 2011. (vii) Airbus Mandatory Service Bulletin A340–32–5087, dated October 10, 2008. (2) For service information identified in this AD, contact Airbus SAS—Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; Internet https://www.airbus.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (q) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (3) The following service information was approved for IBR on June 28, 2013. (i) Airbus Mandatory Service Bulletin A330–32–3220, Revision 01, dated October 5, 2011. (ii) Airbus Mandatory Service Bulletin A330–32–3220, Revision 02, dated December 13, 2012. (iii) Airbus Mandatory Service Bulletin A330–32–3248, Revision 01, including Appendix 01, dated December 13, 2012. (iv) Airbus Mandatory Service Bulletin A340–32–4286, dated October 5, 2011. (4) The following service information was approved for IBR on March 4, 2010 (75 FR 4477, January 28, 2010). (i) Airbus Mandatory Service Bulletin A330–32–3220, dated October 10, 2008. (ii) Airbus Mandatory Service Bulletin A340–32–4264, dated October 10, 2008. (iii) Airbus Mandatory Service Bulletin A340–32–5087, dated October 10, 2008. PO 00000 Frm 00023 Fmt 4700 Sfmt 4700 31389 (5) For service information identified in this AD, contact Airbus SAS—Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; Internet https://www.airbus.com. (6) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (7) You may view this 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/cfr/ibrlocations.html. Issued in Renton, Washington, on May 13, 2013. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2013–11903 Filed 5–23–13; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–0855; Directorate Identifier 2011–NM–136–AD; Amendment 39–17452; AD 2013–09–10] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are superseding an existing airworthiness directive (AD) for all The Boeing Company Model 737– 100, –200, –200C, –300, –400, and –500 series airplanes. That AD currently requires repetitive inspections to detect cracking of the lower corners of the door frame and cross beam of the forward cargo door, and corrective actions if necessary. That AD also requires eventual modification of the outboard radius of the lower corners of the door frame and reinforcement of the cross beam of the forward cargo door, which terminates the existing repetitive inspections. This new AD revises the compliance times for the preventive modification; adds certain inspections for cracks in the number 5 cross beam of the forward cargo door; and adds inspections of the number 4 cross beam if cracks are found in the number 5 cross beam, and corrective actions if necessary. For certain airplanes, this SUMMARY: E:\FR\FM\24MYR1.SGM 24MYR1

Agencies

[Federal Register Volume 78, Number 101 (Friday, May 24, 2013)]
[Rules and Regulations]
[Pages 31386-31389]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-11903]



[[Page 31386]]

=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-1163; Directorate Identifier 2011-NM-246-AD; 
Amendment 39-17456; AD 2013-10-03]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are superseding an existing airworthiness directive (AD) 
for all Airbus Model A330-200 and -300 series airplanes; and Model 
A340-200, -300, -500, and -600 series airplanes. That AD currently 
requires a one-time detailed inspection of both main landing gear (MLG) 
bogie beams in the region of the bogie stop pad for detection of 
deformation and damage, and corrective actions if necessary. This new 
AD adds Model A330-200 Freighter series airplanes to the applicability. 
For certain airplanes, this new AD also adds repetitive inspections for 
damage and corrosion of the sliding piston sub-assembly, with new 
related investigative and corrective actions. This AD was prompted by 
reports of corroded bogie stop pads, including some with cracking. We 
are issuing this AD to detect and correct deformation or damage under 
the bogie stop pad of both MLG bogie beams, which could result in a 
damaged bogie beam and consequent detachment of the beam from the 
airplane or collapse of the MLG and departure of the airplane from the 
runway.

DATES: This AD becomes effective June 28, 2013.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of June 28, 
2013.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of March 
4, 2010 (75 FR 4477, January 28, 2010).

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

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

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on November 16, 2012 
(77 FR 68711), and proposed to supersede AD 2010-02-10, Amendment 39-
16181 (75 FR 4477, January 28, 2010). That NPRM proposed to correct an 
unsafe condition for the specified products. The European Aviation 
Safety Agency (EASA), which is the Technical Agent for the Member 
States of the European Community has issued EASA Airworthiness 
Directive 2011-0211, dated October 31, 2011 (referred to after this as 
``the MCAI''), to supersede EASA AD 2008-0223, dated December 15, 2008 
(referred to in the existing AD), and correct an unsafe condition for 
the specified products. The MCAI states:

    During a scheduled maintenance inspection on the MLG [main 
landing gear], the bogie stop pad was found deformed and cracked. 
Upon removal of the bogie stop pad for replacement, the bogie beam 
was also found cracked.
    Laboratory investigation indicates that an overload event has 
occurred and no fatigue propagation of the crack was evident.
    A second bogie beam crack has subsequently been found on another 
aeroplane, located under a bogie stop pad which only had superficial 
paint damage.
    This condition, if not detected and corrected, could result in 
the aeroplane departing the runway or to the bogie detaching from 
the aeroplane or gear collapses, which would all constitute unsafe 
conditions at speeds above 30 knots.
    As a precautionary measure, EASA AD 2008-0223 [which corresponds 
to FAA AD 2010-02-10, Amendment 39-16181 (75 FR 4477, January 28, 
2010] required one-time detailed inspections under the bogie stop 
pad of both MLG bogie beams and, in case deformation or damage is 
detected, to apply the associated repair.
    Numerous bogie stop pad were found corroded and a few cracked as 
a result of the one-time inspection required by EASA AD 2008-0223 on 
A330, A340-200 and A340-300 aeroplanes.
    For the reasons describe above, this [EASA] AD, which supersedes 
EASA AD 2008-0223:

--retains the initial inspection requirement of EASA AD 2008-0223 
for A330, A340-200 and A340-300 aeroplanes.
--introduces a repetitive detailed visual inspection for A330, A340-
200 and A340-300 aeroplanes.
--retains the requirement of EASA AD 2008-0223 for A340-500 and 
A340-600 aeroplanes, for which further mandatory requirements might 
follow in future depending on the results of the one-time mandatory 
inspection in place.

The required actions include repetitive detailed inspections for damage 
and corrosion of the sliding piston sub-assembly, with new related 
investigative and corrective actions. Related investigative actions 
include a test for indications of corrosion and damage to the bogie 
assembly base material, and a magnetic particle inspection for cracks, 
corrosion, and damage of the bogie beam. Corrective actions include 
repairing affected parts. You may obtain further information by 
examining the MCAI in the AD docket.

Revised Service Information

    Since we issued the NPRM (77 FR 68711, November 16, 2012), we have 
reviewed the following revised service information. No additional work 
is specified by these revisions.
     Airbus Mandatory Service Bulletin A330-32-3220, Revision 
02, dated December 13, 2012 (for Model A330-200 and -300 series 
airplanes).
     Airbus Mandatory Service Bulletin A330-32-3248, Revision 
01, including Appendix 1, dated December 13, 2012 (for Model A330-200, 
-200 Freighter, and -300 series airplanes).
    We have revised paragraphs (i) and (j) of this AD to refer to the 
revised service information, added a new paragraph (l) to give credit 
for earlier revisions of this service information, and re-identified 
subsequent paragraphs accordingly.

Comments

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

Request To Remove or Revise Reporting Requirement

    Delta Air Lines, Inc. (Delta) asked that the compliance time for 
the reporting requirement specified in the NPRM (77 FR 68711, November 
16, 2012) be extended from 30 to 180 days. Delta stated that, unless we 
plan to rescind or revise this AD in the near future based on the 
findings, paragraph (l)(1) of the NPRM (paragraph (m)(1) of the final 
rule) should be removed. Delta also recommended that the reporting be 
mandated only for positive findings--not positive and negative 
findings--and specifically for those findings that are beyond the 
repair limits identified in the applicable component maintenance 
manual. Delta stated that this would allow findings to be batched 
together for a grouped report and would preclude undue compliance 
issues related to late reporting.

[[Page 31387]]

    We do not agree to remove the reporting requirement in paragraph 
(m) of this AD. The reporting requirement is included in the 
requirements in the EASA AD, and our AD follows those requirements in 
order to ensure that the unsafe condition is adequately addressed. 
Reporting of both positive and negative findings is necessary to 
determine the scope of the problem. Reporting all findings will allow 
the manufacturer to conduct statistical analyses and apply the results 
to calculate more accurate life limits for the affected parts. We have 
made no change to the AD in this regard.
    In addition, we do not agree to extend the compliance time for the 
reporting requirement to 180 days; however, we will extend it to 90 
days to be consistent with the compliance time for the reporting 
requirement in the EASA AD referred to in this AD. We have changed the 
compliance time for the reporting requirement in paragraph (m) of this 
AD accordingly.

Conclusion

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

Costs of Compliance

    Based on the service information, we estimate that this AD affects 
about 67 products of U.S. registry.
    The actions that are required by AD 2010-02-10, Amendment 39-16181 
(75 FR 4477, January 28, 2010), and retained in this AD take about 2 
work-hours per product, at an average labor rate of $85 per work hour. 
Based on these figures, the estimated cost of the currently required 
actions is $170 per product.
    We estimate that it will take about 16 work-hours per product to 
comply with the new basic requirements of this AD. The average labor 
rate is $85 per work-hour. Based on these figures, we estimate the cost 
of the AD on U.S. operators to be $91,120, or $1,360 per product.
    We have received no definitive data that will enable us to provide 
cost estimates for the on-condition actions specified in this AD.

Authority for This Rulemaking

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

Regulatory Findings

    We determined that this AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government.
    For the reasons discussed above, I certify that 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);
    3. Will not affect intrastate aviation in Alaska; and
    4. 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 (77 FR 68711, November 16, 
2012), 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 airworthiness directive (AD) 
2010-02-10, Amendment 39-16181 (75 FR 4477, January 28, 2010), and 
adding the following new AD:

2013-10-03 Airbus: Amendment 39-17456. Docket No. FAA-2012-1163; 
Directorate Identifier 2011-NM-246-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective June 28, 
2013.

(b) Affected ADs

    This AD supersedes AD 2010-02-10, Amendment 39-16181 (75 FR 
4477, January 28, 2010).

(c) Applicability

    This AD applies to all Airbus Model A330-201, -202, -203, -223, 
-223F, -243, -243F, -301, -302, -303, -321, -322, -323, -341, -342, 
and -343 airplanes; Model A340-211, -212, -213, -311, -312, -313 
airplanes; and Model A340-541 and -642 airplanes; certificated in 
any category; all serial numbers.

(d) Subject

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

(e) Reason

    This AD was prompted by reports of corroded bogie stop pads, 
some with cracking. We are issuing this AD to detect and correct 
deformation or damage under the bogie stop pad of both main landing 
gear (MLG) bogie beams, which could result in a damaged bogie beam 
and consequent detachment of the beam from the airplane or collapse 
of the MLG and departure of the airplane from the runway.

(f) Compliance

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

(g) Retained One-Time Inspection and Corrective Actions, With Revised 
Service Information

    This paragraph restates the requirements of paragraph (f)(1) of 
AD 2010-02-10, Amendment 39-16181 (75 FR 4477, January 28, 2010), 
with revised service information. For Model A330-200 and -300 series 
airplanes, and Model A340-200, -300, -500, and -600 series 
airplanes, except as required

[[Page 31388]]

by paragraph (i) of this AD: At the applicable compliance time 
specified in paragraph (g)(1), (g)(2), (g)(3), (g)(4), (g)(5), or 
(g)(6) of this AD, perform one-time detailed inspections of both MLG 
bogie beams in the region of the bogie stop pad for detection of 
deformation and damage, and apply the applicable corrective actions, 
in accordance with the Accomplishment Instructions of the applicable 
service bulletin specified in paragraph (g)(7) of this AD. Do all 
applicable corrective actions before further flight.
    (1) Airplanes with 22 months or less and 2,500 flight cycles or 
less from the first flight with the original bogie beam as of March 
4, 2010 (the effective date of AD 2010-02-10, Amendment 39-16181 (75 
FR 4477, January 28, 2010)): Not earlier than 2,500 flight cycles or 
22 months on the original bogie beam, whichever occurs first, but 
not later than 40 months from first flight.
    (2) Airplanes with 22 months or less and 2,500 flight cycles or 
less from the installation date of a new bogie beam in service as of 
March 4, 2010 (the effective date of AD 2010-02-10, Amendment 39-
16181 (75 FR 4477, January 28, 2010)): Not earlier than 2,500 flight 
cycles or 22 months from the installation date of the new bogie 
beam, whichever occurs first, but not later than 40 months from the 
installation date of a new bogie beam in service.
    (3) Airplanes with 22 months or less and 2,500 flight cycles or 
less from the installation date of an overhauled bogie beam in 
service as of March 4, 2010 (the effective date of AD 2010-02-10, 
Amendment 39-16181 (75 FR 4477, January 28, 2010)): Not earlier than 
2,500 flight cycles or 22 months from the installation date of the 
overhauled bogie beam in service, whichever occurs first, but not 
later than 40 months from the installation date of the overhauled 
bogie beam in service.
    (4) Airplanes with more than 22 months or more than 2,500 flight 
cycles from the first flight with the original bogie beam, as of 
March 4, 2010 (the effective date of AD 2010-02-10, Amendment 39-
16181 (75 FR 4477, January 28, 2010)): Within 18 months after March 
4, 2010 (the effective date of AD 2010-02-10).
    (5) Airplanes with more than 22 months or more than 2,500 flight 
cycles from the installation date of a new bogie beam in service, as 
of March 4, 2010 (the effective date of AD 2010-02-10, Amendment 39-
16181 (75 FR 4477, January 28, 2010)): Within 18 months after March 
4, 2010 (the effective date of AD 2010-02-10).
    (6) Airplanes with more than 22 months or more than 2,500 flight 
cycles from the installation date of an overhauled bogie beam in 
service, as of March 4, 2010 (the effective date of AD 2010-02-10, 
Amendment 39-16181 (75 FR 4477, January 28, 2010)): Within 18 months 
after March 4, 2010 (the effective date of AD 2010-02-10).
    (7) Use the applicable service information to accomplish the 
actions required by paragraph (g) of this AD.
    (i) For Model A330-200 and -300 series airplanes: Airbus 
Mandatory Service Bulletin A330-32-3220, dated October 10, 2008; 
Revision 01, dated October 5, 2011; or Revision 02, dated December 
13, 2012.
    (ii) For Model A340-200 and -300 series airplanes: Airbus 
Mandatory Service Bulletin A340-32-4264, dated October 10, 2008.
    (iii) For Model A340-500 and -600 series airplanes: Airbus 
Mandatory Service Bulletin A340-32-5087, dated October 10, 2008.

(h) Retained Reporting Requirement

    This paragraph restates the requirements of paragraph (f)(2) of 
AD 2010-02-10, Amendment 39-16181 (75 FR 4477, January 28, 2010). 
Report the results of the inspection required by paragraph (g) of 
this AD, including no findings, to Airbus, Customer Services 
Directorate, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex 
France; Attn: SEDCC1 Technical Data and Documentation Services; fax 
(+33) 5 61 93 28 06; email sb.reporting@airbus.com; at the 
applicable time specified in paragraph (h)(1) or (h)(2) of this AD.
    (1) If the inspection is done on or after March 4, 2010 (the 
effective date of AD 2010-02-10, Amendment 39-16181 (75 FR 4477, 
January 28, 2010)): Submit the report within 30 days after doing the 
inspection.
    (2) If the inspection was done prior to March 4, 2010 (the 
effective date of AD 2010-02-10, Amendment 39-16181 (75 FR 4477, 
January 28, 2010)): Submit the report within 30 days after March 4, 
2010 (the effective date of AD 2010-02-10).

(i) New Inspections of Beams That Have Not Been Inspected As of the 
Effective Date of This AD

    For bogie beams on which the inspection required by paragraph 
(g) of this AD has not been accomplished as of the effective date of 
this AD: At the later of the times specified in paragraphs (i)(1) 
and (i)(2) of this AD, perform one-time detailed inspections of both 
MLG bogie beams in the region of the bogie stop pad for detection of 
deformation and damage, and apply the applicable corrective actions, 
in accordance with the Accomplishment Instructions of the applicable 
service information specified in paragraph (i)(3) of this AD. Do all 
applicable corrective actions before further flight.
    (1) At the applicable time specified in paragraph (i)(1)(i) or 
(i)(1)(ii) of this AD.
    (i) For bogie beams that have not been overhauled: Not earlier 
than 2,500 flight cycles or 22 months, whichever occurs first, on a 
bogie beam since its first flight on an airplane since new, but not 
later than 40 months since its first flight on an airplane since 
new.
    (ii) For bogie beams that have been overhauled: Not earlier than 
2,500 flight cycles or 22 months, whichever occurs first, on a bogie 
beam since its first flight on an airplane after its most recent 
overhaul, but not later than 40 months since its first flight on an 
airplane after its most recent overhaul.
    (2) Within 90 days after the effective date of this AD.
    (3) Use the applicable service information specified in 
paragraph (i)(3)(i), (i)(3)(ii), or (i)(3)(iii) of this AD, to 
accomplish the actions required by paragraph (i) of this AD.
    (i) For Model A330-200 and -300 series airplanes: Airbus 
Mandatory Service Bulletin A330-32-3220, Revision 02, dated December 
13, 2012.
    (ii) For Model A340-200 and -300 series airplanes: Airbus 
Mandatory Service Bulletin A340-32-4264, dated October 10, 2008.
    (iii) For Model A340-500 and -600 series airplanes: Airbus 
Mandatory Service Bulletin A340-32-5087, dated October 10, 2008.

(j) New Repetitive Inspections

    Except for bogie beams that have been inspected as specified in 
Airbus Mandatory Service Bulletin A340-32-5087: At the later of the 
times specified in paragraphs (j)(1) and (j)(2) of this AD, do the 
detailed inspection of both MLG bogie beams in the bogie stop pad 
area for damage and corrosion, and all applicable related 
investigative and corrective actions, in accordance with the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A330-32-3248, Revision 01, dated December 13, 2012 (for Model A330-
200, -200 Freighter, and -300 series airplanes); or Airbus Mandatory 
Service Bulletin A340-32-4286, dated October 5, 2011 (for Model 
A340-200 and -300 series airplanes); except as required by paragraph 
(k) of this AD. Do all applicable related investigative and 
corrective actions before further flight. Repeat the inspection 
thereafter at intervals not to exceed 2,500 flight cycles or 24 
months, whichever is first.
    (1) Within 2,500 flight cycles or 24 months, whichever occurs 
first, accumulated by a MLG bogie beam since its first flight after 
the most recent accomplishment of Airbus Mandatory Service Bulletin 
A330-32-3220 or A340-32-4264, as applicable.
    (2) Within 3 months after the effective date of this AD.

(k) Service Information Exception

    If any cracking of the bogie beam is detected during any 
inspection or repair required by paragraph (j) of this AD, or any 
repair required by paragraph (j) of this AD is beyond the maximum 
repair allowance specified in the applicable service information 
required by paragraph (j) of this AD: Before further flight, repair 
using a method approved by either the Manager, International Branch, 
ANM-116, Transport Airplane Directorate, FAA; or the European 
Aviation Safety Agency (EASA) (or its delegated agent).

(l) Credit for Previous Actions

    This paragraph provides credit for the actions specified in 
paragraphs (i) and (j) of this AD, if those actions were performed 
before the effective date of this AD using Airbus Mandatory Service 
Bulletin A330-32-3220, dated October 10, 2008, or Airbus Mandatory 
Service Bulletin A330-32-3220, Revision 01, dated October 5, 2011; 
or Airbus Mandatory Service Bulletin A330-32-3248, dated October 5, 
2011; as applicable; which are not incorporated by reference in this 
AD.

(m) New Reporting Requirement

    Report the results of the initial inspection required by 
paragraph (j) of this AD, including both positive and negative 
findings, to Airbus, Customer Services Directorate, 1 Rond Point 
Maurice Bellonte, 31707 Blagnac Cedex France; Attn: SEDCC1 Technical 
Data and Documentation Services; fax (+33) 5 61 93 28 06; email 
sb.reporting@airbus.com; at the applicable

[[Page 31389]]

time specified in paragraph (m)(1) or (m)(2) of this AD.
    (1) If the inspection is done on or after the effective date of 
this AD: Submit the report within 90 days after doing the 
inspection.
    (2) If the inspection was done prior to the effective date of 
this AD: Submit the report within 90 days after the effective date 
of this AD.

(n) Other FAA AD Provisions

    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: Vladimir 
Ulyanov, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, 
Washington 98057-3356; telephone (425) 227-1138; fax (425) 227-1149. 
Information may be emailed 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 2010-02-10, 
Amendment 39-16181 (75 FR 4477, January 28, 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.
    (3) Reporting Requirements: A federal agency may not conduct or 
sponsor, and a person is not required to respond to, nor shall a 
person be subject to a penalty for failure to comply with a 
collection of information subject to the requirements of the 
Paperwork Reduction Act unless that collection of information 
displays a current valid OMB Control Number. The OMB Control Number 
for this information collection is 2120-0056. Public reporting for 
this collection of information is estimated to be approximately 5 
minutes per response, including the time for reviewing instructions, 
completing, and reviewing the collection of information. All 
responses to this collection of information are mandatory. Comments 
concerning the accuracy of this burden and suggestions for reducing 
the burden should be directed to the FAA at: 800 Independence Ave. 
SW., Washington, DC 20591, Attn: Information Collection Clearance 
Officer, AES-200.

(o) Special Flight Permits

    Special flight permits, as described in Section 21.197 and 
Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197 
and 21.199), are not allowed if any crack is found during any 
inspection required by this AD.

(p) Related Information

    (1) Refer to mandatory continued airworthiness information 
(MCAI) EASA Airworthiness Directive 2011-0211, dated October 31, 
2011, and the service information specified in paragraphs (p)(1)(i) 
through (p)(1)(vii) of this AD, for related information.
    (i) Airbus Mandatory Service Bulletin A330-32-3220, dated 
October 10, 2008.
    (ii) Airbus Mandatory Service Bulletin A330-32-3220, Revision 
01, dated October 5, 2011.
    (iii) Airbus Mandatory Service Bulletin A330-32-3220, Revision 
02, dated December 13, 2012.
    (iv) Airbus Mandatory Service Bulletin A330-32-3248, Revision 
01, including Appendix 01, dated December 13, 2012.
    (v) Airbus Mandatory Service Bulletin A340-32-4264, dated 
October 10, 2008.
    (vi) Airbus Mandatory Service Bulletin A340-32-4286, dated 
October 5, 2011.
    (vii) Airbus Mandatory Service Bulletin A340-32-5087, dated 
October 10, 2008.
    (2) For service information identified in this AD, contact 
Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; 
Internet https://www.airbus.com. You may review copies of the 
referenced service information at the FAA, Transport Airplane 
Directorate, 1601 Lind Avenue SW., Renton, WA. For information on 
the availability of this material at the FAA, call 425-227-1221.

(q) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (3) The following service information was approved for IBR on 
June 28, 2013.
    (i) Airbus Mandatory Service Bulletin A330-32-3220, Revision 01, 
dated October 5, 2011.
    (ii) Airbus Mandatory Service Bulletin A330-32-3220, Revision 
02, dated December 13, 2012.
    (iii) Airbus Mandatory Service Bulletin A330-32-3248, Revision 
01, including Appendix 01, dated December 13, 2012.
    (iv) Airbus Mandatory Service Bulletin A340-32-4286, dated 
October 5, 2011.
    (4) The following service information was approved for IBR on 
March 4, 2010 (75 FR 4477, January 28, 2010).
    (i) Airbus Mandatory Service Bulletin A330-32-3220, dated 
October 10, 2008.
    (ii) Airbus Mandatory Service Bulletin A340-32-4264, dated 
October 10, 2008.
    (iii) Airbus Mandatory Service Bulletin A340-32-5087, dated 
October 10, 2008.
    (5) For service information identified in this AD, contact 
Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; 
Internet https://www.airbus.com.
    (6) You may review copies of the service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, 
call 425-227-1221.
    (7) You may view this 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/cfr/ibr-locations.html.

    Issued in Renton, Washington, on May 13, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-11903 Filed 5-23-13; 8:45 am]
BILLING CODE 4910-13-P

This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.