Airworthiness Directives; Airbus Airplanes, 7290-7298 [2015-01710]

Download as PDF 7290 Federal Register / Vol. 80, No. 27 / Tuesday, February 10, 2015 / Rules and Regulations (d) Compliance You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. (e) Required Actions Before further flight and thereafter at intervals not to exceed 10 hours time-inservice, using a light and a mirror, visually inspect the hopper for a crack at the four fan attachment points. The hopper is depicted as item ‘‘a’’ and the fan as item ‘‘b’’ in Figure 1 of Airbus Helicopters Emergency Alert Service Bulletin No. 05A020, Revision 0, dated October 20, 2014 (EASB). If there is a crack in the hopper, replace the hopper with an airworthy hopper. Examples of a crack are shown in Figure 2 of the EASB. Replacing the hopper does not constitute terminating action for the repetitive visual inspections required by this AD. (f) Special Flight Permits Special flight permits may be issued provided that the fan is removed. BILLING CODE 4910–13–P (h) Additional Information The subject of this AD is addressed in European Aviation Safety Agency (EASA) Emergency AD No. 2014–0229–E, dated October 20, 2014. You may view the EASA AD on the Internet at http:// www.regulations.gov by searching for and locating it in Docket No. FAA–2015–0133. rljohnson on DSK3VPTVN1PROD with RULES (i) Subject Joint Aircraft Service Component (JASC) Tracking Code: 6322 Main Rotor Drive Rotorcraft Cooling Fan System. (j) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference 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. (i) Airbus Helicopters Emergency Alert Service Bulletin No. 05A020, Revision 0, dated October 20, 2014. (ii) Reserved. (3) For Airbus Helicopters service information identified in this AD, contact Airbus Helicopters, Inc., 2701 N. Forum 15:13 Feb 09, 2015 Jkt 235001 Issued in Fort Worth, Texas, on January 16, 2015. Lance T. Gant, Acting Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2015–01803 Filed 2–9–15; 8:45 am] (g) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Group, FAA, may approve AMOCs for this EAD. Send your proposal to: Eric Haight, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5110; email eric.haight@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office, before operating any aircraft complying with this EAD through an AMOC. VerDate Sep<11>2014 Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232–0323; fax (972) 641–3775; or at http:// www.airbushelicopters.com/techpub. (4) You may view this service information at FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. For information on the availability of this material at the FAA, call (817) 222–5110. (5) 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: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0142; Directorate Identifier 2012–NM–161–AD; Amendment 39–18093; AD 2015–02–24] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2007–03– 18, AD 2008–17–02, AD 2012–08–03, and AD 2012–15–14, for certain Airbus Model A300 B4–2C, B4–103, and B4– 203 airplanes; Model A300 B4–600, B4– 600R, and F4–600R series airplanes, and Model A300 C4–605R Variant F airplanes (collectively called Model A300–600 series airplanes); and Model A310 series airplanes. AD 2007–03–18, AD 2008–17–02, AD 2012–08–03, and AD 2012–15–14 required repetitive inspections of the forward lugs of the aft bearing at rib 5 of the main landing gear (MLG) on the left-hand (LH) and righthand (RH) wings, and repair if necessary; and installation of new bushes with increased interference fit in the forward lug of the aft bearing at rib 5 of the MLG on the LH and RH wings. This new AD adds airplanes to the applicability; and adds, for certain airplanes, repetitive inspections of the MLG rib 5 aft bearing forward lugs, and SUMMARY: PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 repair if necessary. This AD was prompted by reports of cracking in the forward lug of the MLG rib 5 aft bearing attachment. We are issuing this AD to detect and correct cracking of the forward lugs of the aft bearing at rib 5 of the MLG on the LH and RH wings, which could affect the structural integrity of the MLG attachment, resulting in possible MLG collapse during landing or rollout. DATES: This AD becomes effective March 17, 2015. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of March 17, 2015. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of September 11, 2012 (77 FR 46937, August 7, 2012). The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of May 29, 2012 (77 FR 24367, April 24, 2012). The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of September 17, 2008 (73 FR 47032, August 13, 2008). The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of February 6, 2007 (72 FR 2612, January 22, 2007). ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2014-0142; or in person at the Docket Management Facility, U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC. For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. You may view this 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. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0142. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, E:\FR\FM\10FER1.SGM 10FER1 Federal Register / Vol. 80, No. 27 / Tuesday, February 10, 2015 / Rules and Regulations Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–2125; fax 425–227–1149. SUPPLEMENTARY INFORMATION: rljohnson on DSK3VPTVN1PROD with RULES Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2008–17–02, Amendment 39–15640 (73 FR 47032, August 13, 2008); AD 2012–08–03, Amendment 39–17019 (77 FR 24367, April 24, 2012); and AD 2012–15–14, Amendment 39–17143 (77 FR 46937, August 7, 2012). AD 2008–17–02, AD 2012–08–03, and AD 2012–15–14, applied to certain Airbus Model A300 B4–2C, B4–103, and B4–203 airplanes; Model A300 B4–600, B4–600R, and F4– 600R series airplanes, and Model A300 C4–605R Variant F airplanes (collectively called Model A300–600 series airplanes); and Model A310 series airplanes. The NPRM published in the Federal Register on March 12, 2014 (79 FR 13938). The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2012–0176, dated September 7, 2012, corrected September 20, 2012 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: Several cases of corrosion of the Main Landing Gear (MLG) Rib 5 aft fitting forward lug have been reported on A310 family aeroplanes. In some instances, corrosion pits caused the cracking of the forward lug. This condition, if not detected and corrected, may lead to the complete failure of the fitting and thus could affect the structural integrity of the MLG installation. EASA ADs 2006–0372R1 (http:// ad.easa.europa.eu/blob/easa_ad_2006_0372_ R1_superseeded.pdf/AD_2006-0372R1_1), 2007–0195 (http://ad.easa.europa.eu/blob/ easa_ad_2007_0195_superseded.pdf/AD_ 2007-0195_1) [which corresponds with FAA AD 2008–17–02, Amendment 39–15640 (73 FR 47032, August 13, 2008)], 2010–0250 (http://ad.easa.europa.eu/blob/easa_ad_ 2010_0250_superseded.pdf/AD_2010-0250_ 1) [which corresponds with FAA AD 2012– 15–14, Amendment 39–17143 (77 FR 46937, August 7, 2012)] and 2010–0251 (http:// ad.easa.europa.eu/blob/easa_ad_2010_0251_ superseded.pdf/AD_2010-0251_1) [which corresponds with FAA AD 2012–08–03, Amendment 39–17019 (77 FR 24367, April 24, 2012)] were issued to address this condition and required a repetitive inspection programme of the MLG Rib 5 fitting forward lugs and, as terminating action, the embodiment of mandatory design change (bushes with increased interference fit). VerDate Sep<11>2014 15:13 Feb 09, 2015 Jkt 235001 MLG Rib 5 forward lug on A320 family aeroplanes is a similar design to the A300/ A300–600/A310 family. Since those [EASA] ADs were issued, on two A321 aeroplanes, post modification (bushes with increased interference fit) MLG Rib 5 forward lugs were reportedly found ruptured. One other case was due to a sealant discrepancy that led to water ingress and consequently corrosion initiation, leading to cracking. Subsequent investigation results have shown that a remaining defect, not removed during the repair, had propagated, resulting in rupture of the lug. For the reasons stated above, this new [EASA] AD retains the requirements of EASA ADs 2006–0372R1, 2007–0195, 2010–0250 and 2010–0251, which are superseded, expands the applicability to all models and series of A300, A310, A300–600 and A300– 600ST aeroplanes, and requires: —For aeroplanes not yet modified or repaired, implementation of Modification Service Bulletin (SB) A300–57–0249, A310–57–2090, A300–57–6106, or A300– 57–9019, all at Revision 3, and —for aeroplanes which already embody that modifications, at original issue or revision 01 or 02 of the applicable SB, or have MLG Ribs already repaired in accordance with Airbus repair instruction R57240221 or R57249121, implementation of an additional inspection programme [repetitive detailed inspection for cracking or ultrasonic inspections for any crack indication] and associated corrective action(s) [detailed inspection for cracking if any crack indication found, and repair]. The unsafe condition is cracking of the forward lugs of the aft bearing at rib 5 of the MLG on the LH and RH wings, which could affect the structural integrity of the MLG attachment, resulting in possible MLG collapse during landing or rollout. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov/ #!documentDetail;D=FAA-2014-01420002. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM (79 FR 13938, March 12, 2014) and the FAA’s response to each comment. Request To Withdraw the NPRM (79 FR 13938, March 12, 2014) United Parcel Service (UPS) requested that we withdraw the NPRM (79 FR 13938, March 12, 2014) and focus on airplanes that have been serviced at the facilities where the two airplanes specified in the Discussion section of the NPRM had been reworked. UPS stated that both events are the result of an operator not following procedures. We disagree with the commenter’s request to withdraw the NPRM (79 FR PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 7291 13938, March 12, 2014). This issue concerns more than one operator and airplane model. We have no data indicating that these events are definitively limited to just one repair station or operator. Therefore, the unsafe condition may exist on other airplanes of a similar type design. Consequently, the actions required by this final rule must be done for airplanes identified in paragraph (c) of this AD. We have not changed this AD in this regard. Request To Revise Post-Modification Repetitive Inspection UPS requested that we revise the postmodification repetitive inspections to a one-time inspection. UPS stated that it does not believe that the root cause of the reported events is addressed in the NPRM (79 FR 13938, March 12, 2014). UPS explained that the primary focus of Airbus Mandatory Service Bulletin A300–57–6106, Revision 03, dated January 26, 2012, and the incident investigation is on sealing and protection in the bushing head area. UPS stated that the only difference between the sealing process of Airbus Mandatory Service Bulletin A300–57– 6106, Revision 03, dated January 26, 2012, and prior service bulletin revision levels, is the application of a single coat of polyurethane paint applied over the fillet seal around the bushing flange. UPS explained that, based on a process review of Airbus Service Bulletin A300– 57–6106 and the failure analysis results from the two post-modification reported events, it concurs that a postmodification check of the modification integrity is valid; however, the postmodification repetitive inspection should be a one-time inspection to verify proper accomplishment of the rework process. We disagree with the commenter’s request to revise the post-modification repetitive inspections to a one-time inspection. The corresponding MCAI specifies that the inspection be repeated; FAA ADs match the MCAI requirements if the MCAI provides an adequate level of safety and does not conflict with FAA policies. The sealing process could be compromised over time. Thus a repetitive inspection is considered necessary to ensure that corrosion will not occur and to ensure the structural integrity of the MLG rib 5. However, under the provisions of paragraph (aa) of this AD, we might approve requests for adjustments to the compliance time if data are submitted to substantiate that such an adjustment would provide an acceptable level of safety. We have not changed this AD in this regard. E:\FR\FM\10FER1.SGM 10FER1 7292 Federal Register / Vol. 80, No. 27 / Tuesday, February 10, 2015 / Rules and Regulations Request To Supersede AD 2007–03–18, Amendment 39–14929 (72 FR 5919, February 8, 2007) UPS requested that we revise the wording in paragraph (o) of the NPRM (79 FR 13938, March 12, 2014) to terminate the inspections required by AD 2007–03–18, Amendment 39–14929 (72 FR 5919, February 8, 2007); and to add AD 2007–03–18 to the list of superseded ADs in paragraph (b)(1) of the NPRM. UPS stated that it believes the intent of paragraph (g) of AD 2012– 15–14, Amendment 39–17143 (77 FR 46937, August 7, 2012), was to terminate the AD 2007–03–18 inspection requirements upon initiation of inspections as described in Airbus Mandatory Service Bulletin A300–57– 6107, including Appendix 01, dated August 8, 2007. We agree with the commenter’s request to add AD 2007–03–18, Amendment 39–14929 (72 FR 5919, February 8, 2007), to the list of superseded ADs in this final rule. We have revised paragraph (b) of this AD by removing paragraph (b)(2) of the NPRM (79 FR 13938, March 12, 2014); redesignating paragraph (b)(1) of the NPRM as paragraph (b) of this AD; adding new paragraph (b)(1) to this AD, which adds AD 2007–03–18 to the list of superseded ADs in this AD; and redesignating paragraphs (b)(1)(i) through (b)(1)(iii) of the NPRM as paragraphs (b)(2) through (b)(4) of this AD, respectively. rljohnson on DSK3VPTVN1PROD with RULES Request To Remove Repair Approval Requirement UPS requested that we remove the statement ‘‘For a repair method to be approved, the repair approval must specifically refer to this AD’’ in paragraph (x) of the NPRM (79 FR 13938, March 12, 2014). UPS acknowledged that the rules governing the AD repair and deviation approval process for foreign-manufactured aircraft differ from domestic-built airplanes. UPS recommended that the FAA meet with U.S. operators of foreign-built airplanes to discuss concerns about repair instructions being used that might not fully address the unsafe condition and to review options to alleviate those concerns. We concur with the commenter’s request to remove from this final rule the requirement that repair approvals must specifically refer to this AD. Our responses to specific aspects of this request are presented as follows. Since late 2006, we have included a standard paragraph titled ‘‘Airworthy Product’’ in all MCAI ADs in which the FAA develops an AD based on a foreign VerDate Sep<11>2014 15:13 Feb 09, 2015 Jkt 235001 authority’s AD. The MCAI or referenced service information in an FAA AD often directs the owner/operator to contact the manufacturer for corrective actions, such as a repair. Briefly, the Airworthy Product paragraph allowed owners/ operators to use corrective actions provided by the manufacturer if those actions were FAA-approved. In addition, the paragraph stated that any actions approved by the State of Design Authority (or its delegated agent) are considered to be FAA-approved. In the NPRM (79 FR 13938, March 12, 2014), we proposed to prevent the use of repairs that were not specifically developed to correct the unsafe condition, by requiring that the repair approval provided by the State of Design Authority or its delegated agent specifically refer to this FAA AD. This change was intended to clarify the method of compliance and to provide operators with better visibility of repairs that are specifically developed and approved to correct the unsafe condition. In addition, we proposed to change the phrase ‘‘its delegated agent’’ to include ‘‘the Design Approval Holder (DAH) with State of Design Authority’s design organization approval’’ to refer to a DAH authorized to approve required repairs for the proposed AD. UPS also commented on an NPRM having Directorate Identifier 2012–NM– 101–AD (78 FR 78285, December 26, 2013). UPS stated the following: ‘‘The proposed wording, being specific to repairs, eliminates the interpretation that Airbus messages are acceptable for approving minor deviations (corrective actions) needed during accomplishment of an AD mandated Airbus service bulletin.’’ This comment has made the FAA aware that some operators have misunderstood or misinterpreted the Airworthy Product paragraph to allow the owner/operator to use messages provided by the manufacturer as approval of deviations during the accomplishment of an AD-mandated action. The Airworthy Product paragraph does not approve messages or other information provided by the manufacturer for deviations to the requirements of the AD-mandated actions. The Airworthy Product paragraph only addresses the requirement to contact the manufacturer for corrective actions for the identified unsafe condition and does not cover deviations from other AD requirements. However, deviations to AD-required actions are addressed in 14 CFR 39.17, and anyone may request the approval for an alternative method of compliance to the AD-required actions using the procedures found in 14 CFR 39.19. PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 To address this misunderstanding and misinterpretation of the Airworthy Product paragraph, we have changed that paragraph and retitled it ‘‘Contacting the Manufacturer.’’ This paragraph now clarifies that for any requirement in this AD to obtain corrective actions from a manufacturer, the actions must be accomplished using a method approved by the FAA, EASA, or Airbus’s EASA Design Organization Approval (DOA). The Contacting the Manufacturer paragraph also clarifies that, if approved by the DOA, the approval must include the DOA-authorized signature. The DOA signature indicates that the data and information contained in the document are EASA-approved, which is also FAAapproved. Messages and other information provided by the manufacturer that do not contain the DOA-authorized signature approval are not EASA-approved, unless EASA directly approves the manufacturer’s message or other information. This clarification does not remove flexibility afforded previously by the Airworthy Product paragraph. Consistent with long-standing FAA policy, such flexibility was never intended for required actions. This is also consistent with the recommendation of the Airworthiness Directive Implementation Aviation Rulemaking Committee to increase flexibility in complying with ADs by identifying those actions in manufacturers’ service instructions that are ‘‘Required for Compliance’’ with ADs. We continue to work with manufacturers to implement this recommendation. But once we determine that an action is required, any deviation from the requirement must be approved as an alternative method of compliance. Other commenters to the NPRM having Directorate Identifier 2012–NM– 101–AD (78 FR 78285, December 26, 2013) pointed out that, in many cases, the foreign manufacturer’s service bulletin and the foreign authority’s MCAI may have been issued some time before the FAA AD. Therefore, the DOA may have provided U.S. operators with an approved repair, developed with full awareness of the unsafe condition, before the FAA AD is issued. Under these circumstances, to comply with the FAA AD, the operator would be required to go back to the manufacturer’s DOA and obtain a new approval document, adding time and expense to the compliance process with no safety benefit. Based on these comments, we removed the requirement that the DAHprovided repair specifically refer to this E:\FR\FM\10FER1.SGM 10FER1 Federal Register / Vol. 80, No. 27 / Tuesday, February 10, 2015 / Rules and Regulations AD. Before adopting such a requirement, the FAA will coordinate with affected DAHs and verify they are prepared to implement means to ensure that their repair approvals consider the unsafe condition addressed in the AD. Any such requirements will be adopted through the normal AD rulemaking process, including notice-and-comment procedures, when appropriate. We have also decided not to include a generic reference to either the ‘‘delegated agent’’ or the ‘‘DAH with State of Design Authority design organization approval,’’ but instead we will provide the specific delegation approval granted by the State of Design Authority for the DAH. Change to Paragraph (h)(3) of This AD We removed a requirement to use the latest revision of certain service information, which appeared as the last sentence at the end of paragraph (h)(3) of the NPRM (79 FR 13938, March 12, 2014). That requirement already appears in paragraph (h)(2) of this AD. rljohnson on DSK3VPTVN1PROD with RULES Conclusion We reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these changes: • Are consistent with the intent that was proposed in the NPRM (79 FR 13938, March 12, 2014) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (79 FR 13938, March 12, 2014). We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 We reviewed the following service bulletins. Airbus Service Bulletin A300–57– 0255, including Inspection Reporting Form, dated January 13, 2012. The service information describes procedures for inspections of the forward lugs of the aft bearing at rib 5 of the MLG on the LH and RH wings. Airbus Service Bulletin A300–57– 6112, including Inspection Reporting Form, dated January 13, 2012. The service information describes procedures for inspections of the forward lugs of the aft bearing at rib 5 of the MLG on the LH and RH wings. Airbus Service Bulletin A310–57– 2090, Revision 02, dated June 18, 2010. VerDate Sep<11>2014 15:13 Feb 09, 2015 Jkt 235001 The service information describes procedures for installation of new bushes with increased interference fit in the forward lug of the aft bearing at rib 5 of the MLG on the LH and RH wings. Airbus Service Bulletin A310–57– 2101, including Inspection Reporting Form, dated January 13, 2012. The service information describes procedures for inspections of the forward lugs of the aft bearing at rib 5 of the MLG on the LH and RH wings. This service information is reasonably available; see ADDRESSES for ways to access this service information. Costs of Compliance We estimate that this AD affects 194 airplanes of U.S. registry. The actions that are required by AD 2008–17–02, Amendment 39–15640 (73 FR 47032, August 13, 2008), and retained in this AD take about 5 workhours per product, at an average labor rate of $85 per work-hour. Based on these figures, the estimated cost of the actions that were required by AD 2008– 17–02 is $425 per product. The actions that are required by AD 2012–08–03, Amendment 39–17019 (77 FR 24367, April 24, 2012), and retained in this AD take about 38 work-hours per product, at an average labor rate of $85 per work-hour. Required parts cost about $4,590 per product. Based on these figures, the estimated cost of the actions that were required by AD 2012– 08–03 is $7,820 per product. The actions that are required by AD 2012–15–14, Amendment 39–17143 (77 FR 46937, August 7, 2012), and retained in this AD take about 3 work-hours per product, at an average labor rate of $85 per work-hour. Based on these figures, the estimated cost of the actions that were required by AD 2012–15–14 is $255 per product. We also estimate that it would 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 on U.S. operators to be $49,470, or $255 per product. We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this AD. We have no way of determining the number of products that may need these actions. According to the manufacturer, some of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 7293 Paperwork Reduction Act A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to 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 control number for the collection of information required by this AD is 2120–0056. The paperwork cost associated with this AD has been detailed in the Costs of Compliance section of this document and includes time for reviewing instructions, as well as completing and reviewing the collection of information. Therefore, all reporting associated with this AD is 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. 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); E:\FR\FM\10FER1.SGM 10FER1 7294 Federal Register / Vol. 80, No. 27 / Tuesday, February 10, 2015 / Rules and Regulations 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. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2014-0142; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800–647–5527) is in the ADDRESSES section. (4) AD 2012–15–14, Amendment 39–17143 (77 FR 46937, August 7, 2012). (c) Applicability This AD applies to the Airbus airplanes identified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category, all manufacturer serial numbers. (1) Airbus Model A300 B2–1A, B2–1C, B2K–3C, and B2–203 airplanes; Model A300 B4–2C, B4–103, and B4–203 airplanes; Model A300 B4–601, B4–603, B4–620, B4–622, B4– 605R, B4–622R, F4–605R, and F4–622R airplanes; and Model A300 C4–605R Variant F airplanes. (2) Airbus Model A310–203, –204, –221, –222, –304, –322, –324, and –325 airplanes. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. Adoption of the Amendment (e) Reason This AD was prompted by reports of cracking in the forward lug of the main landing gear (MLG) rib 5 aft bearing attachment. We are issuing this AD to detect and correct cracking of the forward lugs of the aft bearing at rib 5 of the MLG on the lefthand (LH) and right-hand (RH) wings, which could affect the structural integrity of the MLG attachment, resulting in possible MLG collapse during landing or rollout. Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: (f) Compliance Comply with this AD within the compliance times specified, unless already done. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. 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) 2007–03–18, Amendment 39–14929 (72 FR 5919, February 8, 2007); AD 2008– 17–02, Amendment 39–15640 (73 FR 47032, August 13, 2008); AD 2012–08– 03, Amendment 39–17019 (77 FR 24367, April 24, 2012); and AD 2012– 15–14, Amendment 39–17143 (77 FR 46937, August 7, 2012); and adding the following new AD: ■ 2015–02–24 Airbus: Amendment 39–18093. Docket No. FAA–2014–0142; Directorate Identifier 2012–NM–161–AD. rljohnson on DSK3VPTVN1PROD with RULES (a) Effective Date This AD becomes effective March 17, 2015. (b) Affected ADs This AD replaces the ADs specified in paragraphs (b)(1) through (b)(4) of this AD. (1) AD 2007–03–18, Amendment 39–14929 (72 FR 5919, February 8, 2007). (2) AD 2008–17–02, Amendment 39–15640 (73 FR 47032, August 13, 2008). (3) AD 2012–08–03, Amendment 39–17019 (77 FR 24367, April 24, 2012). VerDate Sep<11>2014 15:13 Feb 09, 2015 Jkt 235001 (g) Retained Repetitive Detailed Inspection and Corrective Actions This paragraph restates the requirements of paragraph (f) of AD 2008–17–02, Amendment 39–15640 (73 FR 47032, August 13, 2008). For Model A310 airplanes, except for those where LH and RH wing MLG rib 5 forward lugs have been repaired by installation of oversized interference fit bushes as per Airbus A310 Repair Instruction R572–49121, or which have had Airbus Service Bulletin A310–57–2090 (Airbus Modification 13329) embodied in service: Do the actions specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310– 57A2088, dated November 6, 2006. (1) Before the accumulation of 12,000 total flight cycles, or within 14 days after February 6, 2007 (the effective date of AD 2007–02–09, Amendment 39–14896 (72 FR 2612, January 22, 2007)), whichever occurs later: Perform a detailed visual inspection of the LH and RH wing MLG rib 5 aft bearing forward lugs. (2) If any crack is detected at LH and/or RH aft bearing forward lug, contact Airbus and proceed with the replacement before next flight. (3) Repeat the inspection at intervals not exceeding 100 flight cycles. (h) Retained Actions and Compliance This paragraph restates the requirements of paragraph (g) of AD 2008–17–02, Amendment 39–15640 (73 FR 47032, August 13, 2008), with new service information for paragraphs (h)(2), (h)(3), and (h)(4)(ii) of this AD, and specific delegation approval PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 language in paragraphs (h)(3) and (h)(4)(ii) of this AD. For Model A310 airplanes, except for those where LH and RH wing MLG rib 5 forward lugs have been repaired by installation of oversized interference fit bushes as per Airbus A310 Repair Instruction R572–49121, or which have had Airbus Service Bulletin A310–57–2090 (Airbus Modification 13329) embodied in service: Before the accumulation of 12,000 total flight cycles or before the accumulation of 12,000 flight cycles on MLG rib 5, or within 14 days after September 17, 2008 (the effective date of AD 2008–17–02), whichever occurs latest, perform either a detailed visual inspection (DVI) or an ultrasonic inspection of the LH and RH MLG rib 5 aft bearing forward lug for cracks, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310–57–2091, excluding Appendix 01, dated May 22, 2007. If a MLG rib 5 has been replaced on one side only, then the LH and RH must be considered separately. Doing this inspection ends the requirements of paragraph (g) of this AD for that MLG rib 5 only. (1) If no crack is detected during any inspection required by paragraph (h) of this AD: Repeat the applicable inspection at the time specified in paragraph (h)(1)(i) or (h)(1)(ii) of this AD. (i) Repeat the DVI thereafter at intervals not to exceed 100 flight cycles. (ii) Repeat the ultrasonic inspection thereafter at intervals not to exceed 825 flight cycles. (2) Replacement of the MLG rib 5 bushes with new bushes with high interference fit in the aft bearing forward lugs of MLG rib 5, in accordance with the Accomplishment Instructions of a service bulletin specified in paragraph (h)(2)(i), (h)(2)(ii), or (h)(2)(iii) of this AD, ends the repetitive inspections required by paragraph (h)(1) of this AD for that MLG rib 5 only. As of the effective date of this AD, use only Airbus Mandatory Service Bulletin A310–57–2090, Revision 03, dated January 23, 2012, for the actions specified in this paragraph. (i) Airbus Service Bulletin A310–57–2090, Revision 01, dated December 19, 2007. (ii) Airbus Mandatory Service Bulletin A310–57–2090, Revision 02, dated June 18, 2010. (iii) Airbus Mandatory Service Bulletin A310–57–2090, Revision 03, dated January 23, 2012. (3) If any crack is detected during the DVI required by paragraph (h) of this AD: Before further flight, contact Airbus for replacement instructions and replace the MLG rib 5 bushes before further flight. As of the effective date of this AD: Before further flight, replace using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). Repeat the applicable inspection in paragraph (h) of this AD at the time specified in paragraph (h)(1)(i) or (h)(1)(ii) of this AD. Accomplishing the replacement of the MLG rib 5 bushes with new bushes with high interference fit in the aft bearing forward lugs of MLG rib 5, in accordance with the Accomplishment E:\FR\FM\10FER1.SGM 10FER1 Federal Register / Vol. 80, No. 27 / Tuesday, February 10, 2015 / Rules and Regulations Instructions of a service bulletin specified in paragraph (h)(2)(i), (h)(2)(ii), or (h)(2)(iii) of this AD, ends the repetitive inspections required by paragraph (h)(1) of this AD for that MLG rib 5 only. (4) If any crack is detected during the ultrasonic inspection required by paragraph (h) of this AD, before further flight, accomplish the actions specified in paragraph (h)(4)(i) or (h)(4)(ii) of this AD, as applicable. (i) If any crack is not visible on MLG rib 5: Before further flight, repair MLG rib 5 using Airbus A310 Repair Instruction R572– 49121, Issue C, dated May 2007. After embodiment of the repair instruction, no further actions are necessary as required by paragraphs (g) and (h) of this AD and specified in Airbus Service Bulletin A310– 57–2091, excluding Appendix 01, dated May 22, 2007, for that MLG rib 5 only. (ii) If any crack is visible on MLG rib 5: Before further flight, contact Airbus for rib replacement instructions, and replace before further flight. As of the effective date of this AD: Before further flight, replace using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the EASA; or Airbus’s EASA DOA. Repeat the applicable inspection in paragraph (h) of this AD at the time specified in paragraph (h)(1)(i) or (h)(1)(ii) of this AD. Accomplishing the replacement of the MLG rib 5 bushes with new bushes with high interference fit in the aft bearing forward lugs of MLG rib 5, in accordance with the Accomplishment Instructions of a service bulletin specified in paragraph (h)(2)(i), (h)(2)(ii), or (h)(2)(iii) of this AD, ends the repetitive inspections required by paragraph (h) of this AD for that MLG rib 5 only. Note 1 to paragraph (h) of this AD: The ultrasonic inspection will detect any crack at an early stage and will limit the risk of extensive repairs. This earlier crack detection is not possible with the DVI. rljohnson on DSK3VPTVN1PROD with RULES (i) Retained Installation This paragraph restates the requirements of paragraph (g) of AD 2012–08–03, Amendment 39–17019 (77 FR 24367, April 24, 2012), and applies to the airplanes identified in paragraph (j) of this AD. Within 30 months after May 29, 2012 (the effective date of AD 2012–08–03), install new bushes with increased interference fit in the gear rib 5 aft bearing forward lug on the LH and RH wings, in accordance with the Accomplishment Instructions of the applicable service bulletin specified in paragraph (i)(1), (i)(2), or (i)(3) of this AD; except as specified in paragraph (k) of this AD. (1) Airbus Mandatory Service Bulletin A300–57–0249, Revision 03, dated January 18, 2012 (for Model A300 B4–2C, B4–103, and B4–203 airplanes). (2) Airbus Mandatory Service Bulletin A300–57–6106, Revision 03, dated January 26, 2012 (for Model A300–600 series airplanes). (3) Airbus Mandatory Service Bulletin A310–57–2090, Revision 03, dated January 23, 2012 (for Model A310 series airplanes). VerDate Sep<11>2014 15:13 Feb 09, 2015 Jkt 235001 (j) Affected Airplanes for the Actions Required by Paragraph (i) of This AD For airplanes identified in paragraphs (j)(1), (j)(2), and (j)(3) of this AD: Do the actions required by paragraph (i) of this AD. (1) Airbus Model A300 B4–2C, B4–103, and B4–203 airplanes; all serial numbers; except airplanes on which the MLG rib 5 forward lugs of the LH and RH wings have been repaired by installation of oversized interference fit bushes specified in Airbus Repair Instruction R57240221, or those on which the LH and RH wings have had Airbus Service Bulletin A300–57–0249 embodied in service. (2) Airbus Model A300 B4–601, B4–603, B4–620, and B4–622 airplanes; Airbus Model A300 B4–605R and B4–622R airplanes; Airbus Model A300 F4–605R and F4–622R airplanes; and Airbus Model A300 C4–605R Variant F airplanes; all serial numbers; except airplanes on which the MLG rib 5 forward lugs of the LH and RH wings have been repaired by installation of oversized interference fit bushes specified in Airbus Repair Instruction R57240221, or those on which the LH and RH wings have had Airbus Service Bulletin A300–57–6106 embodied in service. (3) Airbus Model A310–203, –204, –221, –222, –304, –322, –324, and –325 airplanes; all serial numbers; except airplanes on which the MLG rib 5 forward lugs of the LH and RH wings have been repaired by installation of oversized interference fit bushes specified in Airbus Repair Instruction R57249121, or those on which the LH and RH wings have had Airbus Service Bulletin A310–57–2090 embodied in service. (k) Retained Exception for Airplanes Identified in Paragraphs (j)(1), (j)(2), and (j)(3) of This AD This paragraph restates the requirements of paragraph (h) of AD 2012–08–03, Amendment 39–17019 (77 FR 24367, April 24, 2012), and applies to the airplanes identified in paragraphs (j)(1), (j)(2), and (j)(3) of this AD. If one wing had rib 5 forward lugs of the MLG repaired by installing oversized interference fit bushes, as specified in Airbus Repair Instruction R57240221 or Airbus Repair Instruction R572–49121, as applicable to the airplane model, then installing new bushes with increased interference fit in the aft bearing forward lug of the gear rib, as specified in paragraph (i) of this AD, is required for the opposite wing only. (l) Retained Terminating Action for Certain Inspections This paragraph restates the requirements of paragraph (i) of AD 2012–08–03, Amendment 39–17019 (77 FR 24367, April 24, 2012), and applies to the airplanes identified in paragraphs (j)(1), (j)(2), and (j)(3) of this AD. Installation of new bushes, as specified in paragraph (i) of this AD, is terminating action for the repetitive inspections required by AD 2007–03–18, Amendment 39–14929 (72 FR 5919, February 8, 2007); and by paragraphs (g) and (h) of this AD. (m) Retained Repetitive Inspections This paragraph restates the requirements of paragraph (g) of AD 2012–15–14, PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 7295 Amendment 39–17143 (77 FR 46937, August 7, 2012), and applies to the airplanes identified in paragraph (n) of this AD. Except as provided by paragraph (o) of this AD: Before the accumulation of 12,000 total flight cycles since new, or within 12,000 flight cycles since the most recent MLG rib 5 replacement, if applicable, or within 10 days after September 11, 2012 (the effective date of AD 2012–15–14, Amendment 39–17143 (77 FR 46937, August 7, 2012)), whichever occurs latest, do a detailed inspection or an ultrasonic inspection for cracking of the LH and RH MLG rib 5 aft bearing forward lugs, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–57–0251, including Appendix 01, dated August 8, 2007 (for Model A300 B4–103, B4–203, and B4–2C airplanes); or Airbus Mandatory Service Bulletin A300–57– 6107, including Appendix 01, dated August 8, 2007 (for Model A300–600 series airplanes). Repeat the applicable inspections thereafter at the applicable interval specified in paragraph (m)(1) or (m)(2) of this AD, until the modification specified in paragraph (q) of this AD is accomplished. (1) Repeat the detailed inspections at intervals not to exceed 100 flight cycles. (2) Repeat the ultrasonic inspections at intervals not to exceed 675 flight cycles. (n) Affected Airplanes for the Actions Required by Paragraph (m) of This AD For Airbus Model A300 B4–2C, B4–103, and B4–203 airplanes; Model A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4– 622R, F4–605R, and F4–622R airplanes; and Model A300 C4–605R Variant F airplanes; all serial numbers; except for airplanes identified in paragraphs (n)(1), (n)(2), and (n)(3) of this AD: Do the actions required by paragraph (m) of this AD, except as provided by paragraph (o) of this AD. (1) Airplanes on which LH and RH wing MLG rib 5 forward lugs have oversized interference fit bushings installed per Airbus Repair Instruction R57240221. (2) Model A300 B4–103, B4–203, and B4– 2C airplanes on which Airbus Service Bulletin A300–57–0249 has been done in service on the LH and RH wings. (3) Model A300–600 series airplanes on which Airbus Service Bulletin A300–57– 6106 has been done in service on the LH and RH wings. (o) Retained Exception for Certain Airplanes Identified in Paragraph (n) of This AD This paragraph restates the requirements of paragraph (h) of AD 2012–15–14, Amendment 39–17143 (77 FR 46937, August 7, 2012), and applies to the airplanes identified in paragraph (n) of this AD on which an inspection required by AD 2007– 03–18, Amendment 39–14929 (72 FR 5919, February 8, 2007), has been done as of September 11, 2012 (the effective date of AD 2012–15–14): Within 100 flight cycles after doing the most recent inspection required by AD 2007–03–18, or within 10 days after September 11, 2012, whichever occurs later, do a detailed or ultrasonic inspection as specified in paragraph (m) of this AD. Repeat the applicable inspection thereafter at the times specified in paragraph (m) of this AD. E:\FR\FM\10FER1.SGM 10FER1 7296 Federal Register / Vol. 80, No. 27 / Tuesday, February 10, 2015 / Rules and Regulations (p) Retained Repair This paragraph restates the requirements of paragraph (i) of AD 2012–15–14, Amendment 39–17143 (77 FR 46937, August 7, 2012), with specific delegation approval language. If any cracking is detected during any detailed or ultrasonic inspection of the LH and RH MLG rib 5 aft bearing forward lugs required by paragraph (m) of this AD, before further flight, repair using a method approved by Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the EASA; or Airbus’s EASA DOA. rljohnson on DSK3VPTVN1PROD with RULES (q) Retained Optional Terminating Modification This paragraph restates the optional terminating modification of paragraph (j) of AD 2012–15–14, Amendment 39–17143 (77 FR 46937, August 7, 2012), and applies to the airplanes identified in paragraph (n) of this AD. Performing the applicable actions specified in paragraphs (q)(1), (q)(2), (q)(3), and (q)(4) of this AD, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–57–0249, Revision 02, dated June 18, 2010 (for Model A300 B4–103, B4–203, and B4–2C airplanes); or Airbus Mandatory Service Bulletin A300– 57–6106, Revision 03, dated January 26, 2012 (for Model A300–600 series airplanes); terminates the repetitive inspections required by paragraph (m) of this AD. (1) Perform a general visual inspection and dye penetrant flaw detection inspection for corrosion and damage of the bore and spotfaces of the lug. (2) Determine that the diameter of the bore of the lug (dimension Y) is within the tolerance specified in the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–57–0249, Revision 02, dated June 18, 2010 (for Model A300 B4–103, B4– 203, and B4–2C airplanes); or Airbus Mandatory Service Bulletin A300–57–6106, Revision 03, dated January 26, 2012 (for Model A300–600 series airplanes). (3) If damage or corrosion is detected during any inspection specified in paragraph (q)(1) of this AD, or if dimension Y is outside the tolerance specified in the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–57–0249, Revision 02, dated June 18, 2010 (for Model A300 B4–103, B4–203, and B4–2C airplanes); or Airbus Mandatory Service Bulletin A300– 57–6106, Revision 03, dated January 26, 2012 (for Model A300–600 series airplanes); repair using a method approved by either the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or EASA; or Airbus’s EASA DOA. (4) Install bushings with an increased interference fit in the aft bearing forward lugs, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–57–0249, Revision 02, dated June 18, 2010 (for Model A300 B4–103, B4–203, and B4–2C airplanes); or Airbus Mandatory Service Bulletin A300– 57–6106, Revision 03, dated January 26, 2012 (for Model A300–600 series airplanes). VerDate Sep<11>2014 15:13 Feb 09, 2015 Jkt 235001 (r) Retained Terminating Action for AD 2007–03–18, Amendment 39–14929 (72 FR 5919, February 8, 2007) This paragraph restates the terminating action statement of paragraph (k) of AD 2012–15–14, Amendment 39–17143 (77 FR 46937, August 7, 2012), and applies to the airplanes identified in paragraph (n) of this AD. Doing the actions required by paragraph (q) of this AD terminates the inspections required by AD 2007–03–18, Amendment 39–14929 (72 FR 5919, February 8, 2007), for that airplane. (s) Retained Reporting This paragraph restates the requirements of paragraph (l) of AD 2012–15–14, Amendment 39–17143 (77 FR 46937, August 7, 2012), and applies to the airplanes identified in paragraph (n) of this AD. Submit a report (including both positive and negative findings), using the applicable report sheet attached to Airbus Mandatory Service Bulletin A300–57–0251, including Appendix 01, dated August 8, 2007 (for Model A300 B4–103, B4–203, and B4–2C airplanes); or Airbus Mandatory Service Bulletin A300–57– 6107, including Appendix 01, dated August 8, 2007 (for Model A300–600 series airplanes); of the first inspection required by paragraph (m) of this AD. Submit the report 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 (s)(1) or (s)(2) of this AD. (1) If the inspection was done on or after September 11, 2012 (the effective date of AD 2012–15–14, Amendment 39–17143 (77 FR 46937, August 7, 2012)): Submit the report within 30 days after the inspection. (2) If the inspection was done before September 11, 2012 (the effective date of AD 2012–15–14, Amendment 39–17143 (77 FR 46937, August 7, 2012)): Submit the report within 30 days after September 11, 2012. (t) New Repetitive Inspections For airplanes identified in paragraph (u) of this AD: At the applicable time specified in paragraph (v)(1) or (v)(2) of this AD, do a detailed inspection for cracking, or an ultrasonic inspection for any crack indications of the LH and RH MLG rib 5 aft bearing forward lugs, in accordance with the Accomplishment Instructions of the applicable service bulletin specified in paragraph (t)(1), (t)(2), or (t)(3) of this AD. Repeat the inspection thereafter at intervals not to exceed the applicable time specified in paragraph (v)(3) or (v)(4) of this AD. (1) Airbus Service Bulletin A300–57–0255, including Inspection Reporting Form, dated January 13, 2012 (for Model A300 B2–1A, B2–1C, B2K–3C, and B2–203 airplanes). (2) Airbus Service Bulletin A300–57–6112, including Inspection Reporting Form, dated January 13, 2012 (for Model A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4– 622R, F4–605R, and F4–622R airplanes). (3) Airbus Service Bulletin A310–57–2101, including Inspection Reporting Form, dated January 13, 2012 (for Model A310–203, -204, -221, -222, -304, -322, -324, and -325 airplanes). PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 (u) Affected Airplanes for the Actions Required by Paragraph (t) of This AD For airplanes on which any modification or repair described in the service bulletins identified in paragraph (u)(1), (u)(2), or (u)(3) of this AD, as applicable, has been accomplished in service; and for airplanes with MLG rib 5 already repaired as specified in Airbus Repair Instruction R57240221 or R572–49121, including any airplane with the MLG rib 5 forward lugs repaired on one wing; by installation of oversized interference fit bushes, as specified in Airbus Repair Instruction R57240221 or R572– 49121, as applicable: Do the actions required by paragraph (t) of this AD. (1) Airbus Service Bulletin A300–57–0249, dated May 22, 2007; Revision 01, dated December 19, 2007; or Airbus Mandatory Service Bulletin A300–57–0249, Revision 02, dated June 18, 2010 (for Model A300 B4–2C, B4–103, and B4–203 airplanes). (2) Airbus Service Bulletin A300–57–6106, dated May 22, 2007; Revision 01, dated January 28, 2008; or Revision 02, dated June 18, 2010 (for Model A300 B4–601, B4–603, B4–605R, B4–620, B4–622, B4–622R, F4– 605R, F4–622R, and C4–605R Variant F airplanes). (3) Airbus Service Bulletin A310–57–2090, dated May 22, 2007; Revision 01, dated December 19, 2007; or Revision 02, dated June 18, 2010 (for Model A310 series airplanes). (v) Compliance Times for Paragraph (t) of This AD This paragraph specifies the compliance times for the actions specified in paragraph (t) of this AD. (1) For airplanes identified in paragraph (c)(1) of this AD: Do the initial inspection required by paragraph (t) of this AD within 2,500 flight cycles after any modification or repair specified in paragraph (u) of this AD was done, or within 550 flight cycles after the effective date of this AD, whichever occurs later. (2) For airplanes identified in paragraph (c)(2) of this AD: Do the initial inspection required by paragraph (t) of this AD within 2,500 flight cycles after any modification or repair specified in paragraph (u) of this AD was done, or within 775 flight cycles after the effective date of this AD, whichever occurs later. (3) For airplanes identified in paragraph (c)(1) of this AD: For the repetitive inspection required by paragraph (t) of this AD, repeat the inspection within 550 flight cycles after any detailed inspection, and within 1,000 flight cycles after any ultrasonic inspection, as applicable. (4) For airplanes identified in paragraph (c)(2) of this AD: For the repetitive inspection required by paragraph (t) of this AD, repeat the inspection within 775 flight cycles after any detailed inspection, and within 1,300 flight cycles after any ultrasonic inspection, as applicable. (w) New Requirement of This AD: Report and Detailed Inspection If, during any ultrasonic inspection required by paragraph (t) of this AD, any crack indication is detected: Before further E:\FR\FM\10FER1.SGM 10FER1 Federal Register / Vol. 80, No. 27 / Tuesday, February 10, 2015 / Rules and Regulations flight, report to Airbus using the applicable report sheet attached to the applicable Airbus service bulletin specified in paragraph (t)(1), (t)(2), or (t)(3) of this AD, and concurrently accomplish a detailed inspection for cracking of the affected MLG rib 5 aft bearing forward lug, in accordance with the Accomplishment Instructions of the applicable Airbus service bulletin specified in paragraph (t)(1), (t)(2), or (t)(3) of this AD. Repeat the detailed inspection thereafter at intervals not to exceed 100 flight cycles. (x) New Requirement of This AD: Cracking Repair If any cracking is detected during any detailed inspection required by paragraph (t) or (w) of this AD: Before further flight, repair the cracking using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the EASA; or Airbus’s EASA DOA. rljohnson on DSK3VPTVN1PROD with RULES (y) New Requirement of This AD: Reporting Submit a report (including both positive and negative findings), using the reporting sheet attached to the applicable Airbus service bulletin specified in paragraph (y)(1), (y)(2), or (y)(3) of this AD, of the first inspection required by paragraph (t) of this AD. Submit the report 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. Submit the report within 30 days after the inspection or within 30 days after the effective date of this AD, whichever occurs later. (1) Airbus Service Bulletin A300–57–0255, including Inspection Reporting Form, dated January 13, 2012 (for Model A300 B2–1A, B2–1C, B2K–3C, and B2–203 airplanes). (2) Airbus Service Bulletin A300–57–6112, including Inspection Reporting Form, dated January 13, 2012 (for Model A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4– 622R, F4–605R, and F4–622R airplanes). (3) Airbus Service Bulletin A310–57–2101, including Inspection Reporting Form, dated January 13, 2012 (for Model A310–203, –204, –221, –222, –304, –322, –324, and –325 airplanes). (z) Credit for Previous Actions (1) This paragraph provides credit for actions required by paragraph (i) of this AD, if those actions were performed before May 29, 2012 (the effective date of AD 2012–08– 03, Amendment 39–17019 (77 FR 24367, April 24, 2012)), using an applicable service bulletin specified in paragraph (z)(1)(i), (z)(1)(ii), or (z)(1)(iii) of this AD. (i) For Model A300 B4–2C, B4–103, and B4–203 airplanes: The service bulletins are specified in paragraphs (z)(1)(i)(A), (z)(1)(i)(B), and (z)(1)(i)(C) of this AD. (A) Airbus Service Bulletin A300–57–0249, dated May 22, 2007, which is not incorporated by reference in this AD. (B) Airbus Service Bulletin A300–57–0249, Revision 01, dated December 19, 2007, which is not incorporated by reference in this AD. (C) Airbus Mandatory Service Bulletin A300–57–0249, Revision 02, dated June 18, 2010, incorporated by reference in AD 2012– VerDate Sep<11>2014 15:13 Feb 09, 2015 Jkt 235001 15–14, Amendment 39–17143 (77 FR 46937, August 7, 2012). (ii) For Model A300 B4–601, B4–603, B4– 620, B4–622, B4–605R, B4–622R, F4–605R, and F4–622R airplanes; and Model A300 C4– 605R Variant F airplanes: The service bulletins are specified in paragraphs (z)(1)(ii)(A), (z)(1)(ii)(B), and (z)(1)(ii)(C) of this AD. (A) Airbus Service Bulletin A300–57–6106, dated May 22, 2007, which is not incorporated by reference in this AD. (B) Airbus Service Bulletin A300–57–6106, Revision 01, dated January 28, 2008, which is not incorporated by reference in this AD. (C) Airbus Service Bulletin A300–57–6106, Revision 02, dated June 18, 2010, which is not incorporated by reference in this AD. (iii) For Model A310 series airplanes: The service bulletins are specified in paragraphs (z)(1)(iii)(A), (z)(1)(iii)(B), and (z)(1)(iii)(C) of this AD. (A) Airbus Service Bulletin A310–57–2090, dated May 22, 2007, which is not incorporated by reference in this AD. (B) Airbus Service Bulletin A310–57–2090, Revision 01, dated December 19, 2007, incorporated by reference in AD 2008–17–02, Amendment 39–15640 (73 FR 47032, August 13, 2008). (C) Airbus Service Bulletin A310–57–2090, Revision 02, dated June 18, 2010, which is incorporated by reference in this AD. (2) This paragraph provides credit for actions required by paragraph (q) of this AD, if those actions were performed before September 11, 2012 (the effective date of AD 2012–15–14, Amendment 39–17143 (77 FR 46937, August 7, 2012)), using an applicable service bulletin specified in paragraphs (z)(2)(i), (z)(2)(ii), (z)(2)(iii), (z)(2)(iv), and (z)(2)(v) of this AD. (i) For Model A300 B4–2C, B4–103, and B4–203: Airbus Service Bulletin A300–57– 0249, dated May 22, 2007, which is not incorporated by reference in this AD. (ii) For Model A300 B4–2C, B4–103, and B4–203: Airbus Service Bulletin A300–57– 0249, Revision 01, dated December 19, 2007, which is not incorporated by reference in this AD. (iii) For Model A300 B4–601, B4–603, B4– 605R, B4–620, B4–622, B4–622R, F4–605R, F4–622R, and C4–605R Variant F airplanes: Airbus Service Bulletin A300–57–6106, dated May 22, 2007, which is not incorporated by reference in this AD. (iv) For Model A300 B4–601, B4–603, B4– 605R, B4–620, B4–622, B4–622R, F4–605R, F4–622R, and C4–605R Variant F airplanes: Airbus Service Bulletin A300–57–6106, Revision 01, dated January 28, 2008, which is not incorporated by reference in this AD. (v) For Model A300 B4–601, B4–603, B4– 605R, B4–620, B4–622, B4–622R, F4–605R, F4–622R, and C4–605R Variant F airplanes: Airbus Service Bulletin A300–57–6106, Revision 02, dated June 18, 2010, which is not incorporated by reference in this AD. (aa) 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 PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 7297 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, WA 98057–3356; phone 425–227–2125; fax 425–227–1149. Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. (i) 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. (ii) AMOCs approved previously for AD 2008–17–02, Amendment 39–15640 (73 FR 47032, August 13, 2008), are approved as AMOCs for the corresponding provisions of paragraphs (g) and (h) of this AD. (iii) AMOCs approved previously for AD 2012–08–03, Amendment 39–17019 (77 FR 24367, April 24, 2012), are approved as AMOCs for the corresponding provisions of paragraphs (i), (j), (k), and (l) of this AD. (iv) AMOCs approved previously for AD 2012–15–14, Amendment 39–17143 (77 FR 46937, August 7, 2012), are approved as AMOCs for the corresponding provisions of paragraphs (m) through (s) of this AD. (2) Contacting the Manufacturer: As of the effective date of this AD, for any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (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. (bb) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2012–0176, dated September 7, 2012, corrected September 20, 2012, for related information. You may E:\FR\FM\10FER1.SGM 10FER1 7298 Federal Register / Vol. 80, No. 27 / Tuesday, February 10, 2015 / Rules and Regulations rljohnson on DSK3VPTVN1PROD with RULES examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/ #!documentDetail;D=FAA-2014-0142-0002. (2) Service information identified in this AD that is not incorporated by reference in this AD is available at the addresses specified in paragraphs (cc)(9) and (cc)(10) of this AD. (cc) 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 this AD specifies otherwise. (3) The following service information was approved for IBR on March 17, 2015. (i) Airbus Service Bulletin A300–57–0255, including Inspection Reporting Form, dated January 13, 2012. (ii) Airbus Service Bulletin A300–57–6112, including Inspection Reporting Form, dated January 13, 2012. (iii) Airbus Service Bulletin A310–57– 2090, Revision 02, dated June 18, 2010. (iv) Airbus Service Bulletin A310–57– 2101, including Inspection Reporting Form, dated January 13, 2012. (4) The following service information was approved for IBR on September 11, 2012 (77 FR 46937, August 7, 2012). (i) Airbus Mandatory Service Bulletin A300–57–0249, Revision 02, dated June 18, 2010. (ii) Airbus Mandatory Service Bulletin A300–57–0251, including Appendix 01, dated August 8, 2007. (iii) Airbus Mandatory Service Bulletin A300–57–6106, Revision 03, dated January 26, 2012. (iv) Airbus Mandatory Service Bulletin A300–57–6107, including Appendix 01, August 8, 2007. (5) The following service information was approved for IBR on May 29, 2012 (77 FR 24367, April 24, 2012). (i) Airbus Mandatory Service Bulletin A300–57–0249, Revision 03, dated January 18, 2012. (ii) Airbus Mandatory Service Bulletin A310–57–2090, Revision 03, dated January 23, 2012. (6) The following service information was approved for IBR on September 17, 2008 (73 FR 47032, August 13, 2008). (i) Airbus Service Bulletin A310–57–2090, Revision 01, dated December 19, 2007. (ii) Airbus Service Bulletin A310–57–2091, excluding Appendix 01, dated May 22, 2007. (iii) Airbus A310 Repair Instruction R572– 49121, Issue C, dated May 2007. (7) The following service information was approved for IBR on February 6, 2007 (72 FR 2612, January 22, 2007). (i) Airbus Service Bulletin A310–57A2088, excluding Appendix 01, dated November 6, 2006. (ii) Reserved. (8) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth- VerDate Sep<11>2014 15:13 Feb 09, 2015 Jkt 235001 eas@airbus.com; Internet http:// www.airbus.com. (9) You may view this 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. (10) 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: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on January 21, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–01710 Filed 2–9–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0750; Directorate Identifier 2014–NM–147–AD; Amendment 39–18097; AD 2015–03–01] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc. Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for all Bombardier, Inc. Model CL–600–2B19 (Regional Jet Series 100 & 440) airplanes. This AD was prompted by reports of dislodged engine fan cowl panels. This AD requires installing additional attaching hardware on the left and right fan cowl access panels and the nacelle attaching structures. We are issuing this AD to prevent damage to the fuselage and flight control surfaces from dislodged engine fan cowl panels. DATES: This AD becomes effective March 17, 2015. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of March 17, 2015. ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2014-0750; or in person at the Docket Management Facility, U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room SUMMARY: PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 W12–140, 1200 New Jersey Avenue SE., Washington, DC. For service information identified in this AD, contact Bombardier, Inc., 400 ˆ ´ Cote-Vertu Road West, Dorval, Quebec H4S 1Y9, Canada; telephone 514–855– 5000; fax 514–855–7401; email thd.crj@aero.bombardier.com; Internet http://www.bombardier.com. You may view this 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. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0750. FOR FURTHER INFORMATION CONTACT: Andreas Rambalakos, Aerospace Engineer, Airframe and Mechanical Systems Branch, ANE–171, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7345; fax 516–794–5531. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all Bombardier, Inc. Model CL– 600–2B19 (Regional Jet Series 100 & 440) airplanes. The NPRM published in the Federal Register on October 2, 2014 (79 FR 59459). Transport Canada Civil Aviation (TCCA), which is the airworthiness authority for Canada, has issued Canadian Airworthiness Directive CF– 2014–20, dated July 9, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition. The MCAI states: There have been a number of engine fan cowl panel dislodgement incidents reported on the Bombardier CL–600–2B19 aeroplane fleet. The dislodged panels may cause damage to the fuselage and flight control surfaces of the aeroplane. Also, the debris from a dislodged panel may result in runway contamination and has the potential of causing injury on the ground. Although the majority of the subject panel dislodgements were reported on the first or second flight after an engine maintenance task was performed that required removal and reinstallation of the subject panels, the frequency of the dislodgements indicates that the existing attachment design is prone to human (maintenance) error. Bombardier has attempted to mitigate this issue by issuing maintenance advisories emphasizing the proper installation of engine fan cowl panels. In order to further mitigate the potential safety hazard of the subject panel dislodgement, Bombardier has issued E:\FR\FM\10FER1.SGM 10FER1

Agencies

[Federal Register Volume 80, Number 27 (Tuesday, February 10, 2015)]
[Rules and Regulations]
[Pages 7290-7298]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-01710]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0142; Directorate Identifier 2012-NM-161-AD; 
Amendment 39-18093; AD 2015-02-24]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are superseding Airworthiness Directive (AD) 2007-03-18, AD 
2008-17-02, AD 2012-08-03, and AD 2012-15-14, for certain Airbus Model 
A300 B4-2C, B4-103, and B4-203 airplanes; Model A300 B4-600, B4-600R, 
and F4-600R series airplanes, and Model A300 C4-605R Variant F 
airplanes (collectively called Model A300-600 series airplanes); and 
Model A310 series airplanes. AD 2007-03-18, AD 2008-17-02, AD 2012-08-
03, and AD 2012-15-14 required repetitive inspections of the forward 
lugs of the aft bearing at rib 5 of the main landing gear (MLG) on the 
left-hand (LH) and right-hand (RH) wings, and repair if necessary; and 
installation of new bushes with increased interference fit in the 
forward lug of the aft bearing at rib 5 of the MLG on the LH and RH 
wings. This new AD adds airplanes to the applicability; and adds, for 
certain airplanes, repetitive inspections of the MLG rib 5 aft bearing 
forward lugs, and repair if necessary. This AD was prompted by reports 
of cracking in the forward lug of the MLG rib 5 aft bearing attachment. 
We are issuing this AD to detect and correct cracking of the forward 
lugs of the aft bearing at rib 5 of the MLG on the LH and RH wings, 
which could affect the structural integrity of the MLG attachment, 
resulting in possible MLG collapse during landing or rollout.

DATES: This AD becomes effective March 17, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of March 17, 
2015.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of 
September 11, 2012 (77 FR 46937, August 7, 2012).
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of May 29, 
2012 (77 FR 24367, April 24, 2012).
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of 
September 17, 2008 (73 FR 47032, August 13, 2008).
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of 
February 6, 2007 (72 FR 2612, January 22, 2007).

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-0142; or in person at the 
Docket Management Facility, U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC.
    For service information identified in this AD, contact Airbus SAS, 
Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; 
email account.airworth-eas@airbus.com; Internet http://www.airbus.com. 
You may view this 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. It 
is also available on the Internet at http://www.regulations.gov by 
searching for and locating Docket No. FAA-2014-0142.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116,

[[Page 7291]]

Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 
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 supersede AD 2008-17-02, Amendment 39-15640 (73 FR 47032, 
August 13, 2008); AD 2012-08-03, Amendment 39-17019 (77 FR 24367, April 
24, 2012); and AD 2012-15-14, Amendment 39-17143 (77 FR 46937, August 
7, 2012). AD 2008-17-02, AD 2012-08-03, and AD 2012-15-14, applied to 
certain Airbus Model A300 B4-2C, B4-103, and B4-203 airplanes; Model 
A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-
605R Variant F airplanes (collectively called Model A300-600 series 
airplanes); and Model A310 series airplanes. The NPRM published in the 
Federal Register on March 12, 2014 (79 FR 13938).
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2012-0176, dated September 7, 2012, corrected 
September 20, 2012 (referred to after this as the Mandatory Continuing 
Airworthiness Information, or ``the MCAI''), to correct an unsafe 
condition for the specified products. The MCAI states:

Several cases of corrosion of the Main Landing Gear (MLG) Rib 5 aft 
fitting forward lug have been reported on A310 family aeroplanes. In 
some instances, corrosion pits caused the cracking of the forward 
lug.

This condition, if not detected and corrected, may lead to the 
complete failure of the fitting and thus could affect the structural 
integrity of the MLG installation.

EASA ADs 2006-0372R1 (http://ad.easa.europa.eu/blob/easa_ad_2006_0372_R1_superseeded.pdf/AD_2006-0372R1_1), 2007-0195 
(http://ad.easa.europa.eu/blob/easa_ad_2007_0195_superseded.pdf/AD_2007-0195_1) [which corresponds with FAA AD 2008-17-02, Amendment 
39-15640 (73 FR 47032, August 13, 2008)], 2010-0250 (http://ad.easa.europa.eu/blob/easa_ad_2010_0250_superseded.pdf/AD_2010-0250_1) [which corresponds with FAA AD 2012-15-14, Amendment 39-
17143 (77 FR 46937, August 7, 2012)] and 2010-0251 (http://ad.easa.europa.eu/blob/easa_ad_2010_0251_superseded.pdf/AD_2010-0251_1) [which corresponds with FAA AD 2012-08-03, Amendment 39-
17019 (77 FR 24367, April 24, 2012)] were issued to address this 
condition and required a repetitive inspection programme of the MLG 
Rib 5 fitting forward lugs and, as terminating action, the 
embodiment of mandatory design change (bushes with increased 
interference fit).

MLG Rib 5 forward lug on A320 family aeroplanes is a similar design 
to the A300/A300-600/A310 family. Since those [EASA] ADs were 
issued, on two A321 aeroplanes, post modification (bushes with 
increased interference fit) MLG Rib 5 forward lugs were reportedly 
found ruptured. One other case was due to a sealant discrepancy that 
led to water ingress and consequently corrosion initiation, leading 
to cracking. Subsequent investigation results have shown that a 
remaining defect, not removed during the repair, had propagated, 
resulting in rupture of the lug.

For the reasons stated above, this new [EASA] AD retains the 
requirements of EASA ADs 2006-0372R1, 2007-0195, 2010-0250 and 2010-
0251, which are superseded, expands the applicability to all models 
and series of A300, A310, A300-600 and A300-600ST aeroplanes, and 
requires:
--For aeroplanes not yet modified or repaired, implementation of 
Modification Service Bulletin (SB) A300-57-0249, A310-57-2090, A300-
57-6106, or A300-57-9019, all at Revision 3, and
--for aeroplanes which already embody that modifications, at 
original issue or revision 01 or 02 of the applicable SB, or have 
MLG Ribs already repaired in accordance with Airbus repair 
instruction R57240221 or R57249121, implementation of an additional 
inspection programme [repetitive detailed inspection for cracking or 
ultrasonic inspections for any crack indication] and associated 
corrective action(s) [detailed inspection for cracking if any crack 
indication found, and repair].

The unsafe condition is cracking of the forward lugs of the aft bearing 
at rib 5 of the MLG on the LH and RH wings, which could affect the 
structural integrity of the MLG attachment, resulting in possible MLG 
collapse during landing or rollout.
    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-0142-0002.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM (79 
FR 13938, March 12, 2014) and the FAA's response to each comment.

Request To Withdraw the NPRM (79 FR 13938, March 12, 2014)

    United Parcel Service (UPS) requested that we withdraw the NPRM (79 
FR 13938, March 12, 2014) and focus on airplanes that have been 
serviced at the facilities where the two airplanes specified in the 
Discussion section of the NPRM had been reworked. UPS stated that both 
events are the result of an operator not following procedures.
    We disagree with the commenter's request to withdraw the NPRM (79 
FR 13938, March 12, 2014). This issue concerns more than one operator 
and airplane model. We have no data indicating that these events are 
definitively limited to just one repair station or operator. Therefore, 
the unsafe condition may exist on other airplanes of a similar type 
design. Consequently, the actions required by this final rule must be 
done for airplanes identified in paragraph (c) of this AD. We have not 
changed this AD in this regard.

Request To Revise Post-Modification Repetitive Inspection

    UPS requested that we revise the post-modification repetitive 
inspections to a one-time inspection. UPS stated that it does not 
believe that the root cause of the reported events is addressed in the 
NPRM (79 FR 13938, March 12, 2014). UPS explained that the primary 
focus of Airbus Mandatory Service Bulletin A300-57-6106, Revision 03, 
dated January 26, 2012, and the incident investigation is on sealing 
and protection in the bushing head area. UPS stated that the only 
difference between the sealing process of Airbus Mandatory Service 
Bulletin A300-57-6106, Revision 03, dated January 26, 2012, and prior 
service bulletin revision levels, is the application of a single coat 
of polyurethane paint applied over the fillet seal around the bushing 
flange. UPS explained that, based on a process review of Airbus Service 
Bulletin A300-57-6106 and the failure analysis results from the two 
post-modification reported events, it concurs that a post-modification 
check of the modification integrity is valid; however, the post-
modification repetitive inspection should be a one-time inspection to 
verify proper accomplishment of the rework process.
    We disagree with the commenter's request to revise the post-
modification repetitive inspections to a one-time inspection. The 
corresponding MCAI specifies that the inspection be repeated; FAA ADs 
match the MCAI requirements if the MCAI provides an adequate level of 
safety and does not conflict with FAA policies. The sealing process 
could be compromised over time. Thus a repetitive inspection is 
considered necessary to ensure that corrosion will not occur and to 
ensure the structural integrity of the MLG rib 5. However, under the 
provisions of paragraph (aa) of this AD, we might approve requests for 
adjustments to the compliance time if data are submitted to 
substantiate that such an adjustment would provide an acceptable level 
of safety. We have not changed this AD in this regard.

[[Page 7292]]

Request To Supersede AD 2007-03-18, Amendment 39-14929 (72 FR 5919, 
February 8, 2007)

    UPS requested that we revise the wording in paragraph (o) of the 
NPRM (79 FR 13938, March 12, 2014) to terminate the inspections 
required by AD 2007-03-18, Amendment 39-14929 (72 FR 5919, February 8, 
2007); and to add AD 2007-03-18 to the list of superseded ADs in 
paragraph (b)(1) of the NPRM. UPS stated that it believes the intent of 
paragraph (g) of AD 2012-15-14, Amendment 39-17143 (77 FR 46937, August 
7, 2012), was to terminate the AD 2007-03-18 inspection requirements 
upon initiation of inspections as described in Airbus Mandatory Service 
Bulletin A300-57-6107, including Appendix 01, dated August 8, 2007.
    We agree with the commenter's request to add AD 2007-03-18, 
Amendment 39-14929 (72 FR 5919, February 8, 2007), to the list of 
superseded ADs in this final rule. We have revised paragraph (b) of 
this AD by removing paragraph (b)(2) of the NPRM (79 FR 13938, March 
12, 2014); re-designating paragraph (b)(1) of the NPRM as paragraph (b) 
of this AD; adding new paragraph (b)(1) to this AD, which adds AD 2007-
03-18 to the list of superseded ADs in this AD; and re-designating 
paragraphs (b)(1)(i) through (b)(1)(iii) of the NPRM as paragraphs 
(b)(2) through (b)(4) of this AD, respectively.

Request To Remove Repair Approval Requirement

    UPS requested that we remove the statement ``For a repair method to 
be approved, the repair approval must specifically refer to this AD'' 
in paragraph (x) of the NPRM (79 FR 13938, March 12, 2014). UPS 
acknowledged that the rules governing the AD repair and deviation 
approval process for foreign-manufactured aircraft differ from 
domestic-built airplanes. UPS recommended that the FAA meet with U.S. 
operators of foreign-built airplanes to discuss concerns about repair 
instructions being used that might not fully address the unsafe 
condition and to review options to alleviate those concerns.
    We concur with the commenter's request to remove from this final 
rule the requirement that repair approvals must specifically refer to 
this AD. Our responses to specific aspects of this request are 
presented as follows.
    Since late 2006, we have included a standard paragraph titled 
``Airworthy Product'' in all MCAI ADs in which the FAA develops an AD 
based on a foreign authority's AD. The MCAI or referenced service 
information in an FAA AD often directs the owner/operator to contact 
the manufacturer for corrective actions, such as a repair. Briefly, the 
Airworthy Product paragraph allowed owners/operators to use corrective 
actions provided by the manufacturer if those actions were FAA-
approved. In addition, the paragraph stated that any actions approved 
by the State of Design Authority (or its delegated agent) are 
considered to be FAA-approved.
    In the NPRM (79 FR 13938, March 12, 2014), we proposed to prevent 
the use of repairs that were not specifically developed to correct the 
unsafe condition, by requiring that the repair approval provided by the 
State of Design Authority or its delegated agent specifically refer to 
this FAA AD. This change was intended to clarify the method of 
compliance and to provide operators with better visibility of repairs 
that are specifically developed and approved to correct the unsafe 
condition. In addition, we proposed to change the phrase ``its 
delegated agent'' to include ``the Design Approval Holder (DAH) with 
State of Design Authority's design organization approval'' to refer to 
a DAH authorized to approve required repairs for the proposed AD.
    UPS also commented on an NPRM having Directorate Identifier 2012-
NM-101-AD (78 FR 78285, December 26, 2013). UPS stated the following: 
``The proposed wording, being specific to repairs, eliminates the 
interpretation that Airbus messages are acceptable for approving minor 
deviations (corrective actions) needed during accomplishment of an AD 
mandated Airbus service bulletin.''
    This comment has made the FAA aware that some operators have 
misunderstood or misinterpreted the Airworthy Product paragraph to 
allow the owner/operator to use messages provided by the manufacturer 
as approval of deviations during the accomplishment of an AD-mandated 
action. The Airworthy Product paragraph does not approve messages or 
other information provided by the manufacturer for deviations to the 
requirements of the AD-mandated actions. The Airworthy Product 
paragraph only addresses the requirement to contact the manufacturer 
for corrective actions for the identified unsafe condition and does not 
cover deviations from other AD requirements. However, deviations to AD-
required actions are addressed in 14 CFR 39.17, and anyone may request 
the approval for an alternative method of compliance to the AD-required 
actions using the procedures found in 14 CFR 39.19.
    To address this misunderstanding and misinterpretation of the 
Airworthy Product paragraph, we have changed that paragraph and 
retitled it ``Contacting the Manufacturer.'' This paragraph now 
clarifies that for any requirement in this AD to obtain corrective 
actions from a manufacturer, the actions must be accomplished using a 
method approved by the FAA, EASA, or Airbus's EASA Design Organization 
Approval (DOA).
    The Contacting the Manufacturer paragraph also clarifies that, if 
approved by the DOA, the approval must include the DOA-authorized 
signature. The DOA signature indicates that the data and information 
contained in the document are EASA-approved, which is also FAA-
approved. Messages and other information provided by the manufacturer 
that do not contain the DOA-authorized signature approval are not EASA-
approved, unless EASA directly approves the manufacturer's message or 
other information.
    This clarification does not remove flexibility afforded previously 
by the Airworthy Product paragraph. Consistent with long-standing FAA 
policy, such flexibility was never intended for required actions. This 
is also consistent with the recommendation of the Airworthiness 
Directive Implementation Aviation Rulemaking Committee to increase 
flexibility in complying with ADs by identifying those actions in 
manufacturers' service instructions that are ``Required for 
Compliance'' with ADs. We continue to work with manufacturers to 
implement this recommendation. But once we determine that an action is 
required, any deviation from the requirement must be approved as an 
alternative method of compliance.
    Other commenters to the NPRM having Directorate Identifier 2012-NM-
101-AD (78 FR 78285, December 26, 2013) pointed out that, in many 
cases, the foreign manufacturer's service bulletin and the foreign 
authority's MCAI may have been issued some time before the FAA AD. 
Therefore, the DOA may have provided U.S. operators with an approved 
repair, developed with full awareness of the unsafe condition, before 
the FAA AD is issued. Under these circumstances, to comply with the FAA 
AD, the operator would be required to go back to the manufacturer's DOA 
and obtain a new approval document, adding time and expense to the 
compliance process with no safety benefit.
    Based on these comments, we removed the requirement that the DAH-
provided repair specifically refer to this

[[Page 7293]]

AD. Before adopting such a requirement, the FAA will coordinate with 
affected DAHs and verify they are prepared to implement means to ensure 
that their repair approvals consider the unsafe condition addressed in 
the AD. Any such requirements will be adopted through the normal AD 
rulemaking process, including notice-and-comment procedures, when 
appropriate.
    We have also decided not to include a generic reference to either 
the ``delegated agent'' or the ``DAH with State of Design Authority 
design organization approval,'' but instead we will provide the 
specific delegation approval granted by the State of Design Authority 
for the DAH.

Change to Paragraph (h)(3) of This AD

    We removed a requirement to use the latest revision of certain 
service information, which appeared as the last sentence at the end of 
paragraph (h)(3) of the NPRM (79 FR 13938, March 12, 2014). That 
requirement already appears in paragraph (h)(2) of this AD.

Conclusion

    We reviewed the available data, including the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these changes:
     Are consistent with the intent that was proposed in the 
NPRM (79 FR 13938, March 12, 2014) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (79 FR 13938, March 12, 2014).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    We reviewed the following service bulletins.
    Airbus Service Bulletin A300-57-0255, including Inspection 
Reporting Form, dated January 13, 2012. The service information 
describes procedures for inspections of the forward lugs of the aft 
bearing at rib 5 of the MLG on the LH and RH wings.
    Airbus Service Bulletin A300-57-6112, including Inspection 
Reporting Form, dated January 13, 2012. The service information 
describes procedures for inspections of the forward lugs of the aft 
bearing at rib 5 of the MLG on the LH and RH wings.
    Airbus Service Bulletin A310-57-2090, Revision 02, dated June 18, 
2010. The service information describes procedures for installation of 
new bushes with increased interference fit in the forward lug of the 
aft bearing at rib 5 of the MLG on the LH and RH wings.
    Airbus Service Bulletin A310-57-2101, including Inspection 
Reporting Form, dated January 13, 2012. The service information 
describes procedures for inspections of the forward lugs of the aft 
bearing at rib 5 of the MLG on the LH and RH wings.
    This service information is reasonably available; see ADDRESSES for 
ways to access this service information.

Costs of Compliance

    We estimate that this AD affects 194 airplanes of U.S. registry.
    The actions that are required by AD 2008-17-02, Amendment 39-15640 
(73 FR 47032, August 13, 2008), and retained in this AD take about 5 
work-hours per product, at an average labor rate of $85 per work-hour. 
Based on these figures, the estimated cost of the actions that were 
required by AD 2008-17-02 is $425 per product.
    The actions that are required by AD 2012-08-03, Amendment 39-17019 
(77 FR 24367, April 24, 2012), and retained in this AD take about 38 
work-hours per product, at an average labor rate of $85 per work-hour. 
Required parts cost about $4,590 per product. Based on these figures, 
the estimated cost of the actions that were required by AD 2012-08-03 
is $7,820 per product.
    The actions that are required by AD 2012-15-14, Amendment 39-17143 
(77 FR 46937, August 7, 2012), and retained in this AD take about 3 
work-hours per product, at an average labor rate of $85 per work-hour. 
Based on these figures, the estimated cost of the actions that were 
required by AD 2012-15-14 is $255 per product.
    We also estimate that it would 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 on U.S. operators to be $49,470, or $255 per product.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this AD. We 
have no way of determining the number of products that may need these 
actions.
    According to the manufacturer, some of the costs of this AD may be 
covered under warranty, thereby reducing the cost impact on affected 
individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to 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 control 
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in 
the Costs of Compliance section of this document and includes time for 
reviewing instructions, as well as completing and reviewing the 
collection of information. Therefore, all reporting associated with 
this AD is 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.

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);

[[Page 7294]]

    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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-0142; or in person at the 
Docket Management Facility between 9 a.m. and 5 p.m., Monday through 
Friday, except Federal holidays. The AD docket contains this AD, the 
regulatory evaluation, any comments received, and other information. 
The street address for the Docket Operations office (telephone 800-647-
5527) is in the ADDRESSES section.

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) 
2007-03-18, Amendment 39-14929 (72 FR 5919, February 8, 2007); AD 2008-
17-02, Amendment 39-15640 (73 FR 47032, August 13, 2008); AD 2012-08-
03, Amendment 39-17019 (77 FR 24367, April 24, 2012); and AD 2012-15-
14, Amendment 39-17143 (77 FR 46937, August 7, 2012); and adding the 
following new AD:

2015-02-24 Airbus: Amendment 39-18093. Docket No. FAA-2014-0142; 
Directorate Identifier 2012-NM-161-AD.

(a) Effective Date

    This AD becomes effective March 17, 2015.

(b) Affected ADs

    This AD replaces the ADs specified in paragraphs (b)(1) through 
(b)(4) of this AD.
    (1) AD 2007-03-18, Amendment 39-14929 (72 FR 5919, February 8, 
2007).
    (2) AD 2008-17-02, Amendment 39-15640 (73 FR 47032, August 13, 
2008).
    (3) AD 2012-08-03, Amendment 39-17019 (77 FR 24367, April 24, 
2012).
    (4) AD 2012-15-14, Amendment 39-17143 (77 FR 46937, August 7, 
2012).

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs 
(c)(1) and (c)(2) of this AD, certificated in any category, all 
manufacturer serial numbers.
    (1) Airbus Model A300 B2-1A, B2-1C, B2K-3C, and B2-203 
airplanes; Model A300 B4-2C, B4-103, and B4-203 airplanes; Model 
A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, and 
F4-622R airplanes; and Model A300 C4-605R Variant F airplanes.
    (2) Airbus Model A310-203, -204, -221, -222, -304, -322, -324, 
and -325 airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by reports of cracking in the forward lug 
of the main landing gear (MLG) rib 5 aft bearing attachment. We are 
issuing this AD to detect and correct cracking of the forward lugs 
of the aft bearing at rib 5 of the MLG on the left-hand (LH) and 
right-hand (RH) wings, which could affect the structural integrity 
of the MLG attachment, resulting in possible MLG collapse during 
landing or rollout.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Retained Repetitive Detailed Inspection and Corrective Actions

    This paragraph restates the requirements of paragraph (f) of AD 
2008-17-02, Amendment 39-15640 (73 FR 47032, August 13, 2008). For 
Model A310 airplanes, except for those where LH and RH wing MLG rib 
5 forward lugs have been repaired by installation of oversized 
interference fit bushes as per Airbus A310 Repair Instruction R572-
49121, or which have had Airbus Service Bulletin A310-57-2090 
(Airbus Modification 13329) embodied in service: Do the actions 
specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A310-57A2088, dated November 6, 2006.
    (1) Before the accumulation of 12,000 total flight cycles, or 
within 14 days after February 6, 2007 (the effective date of AD 
2007-02-09, Amendment 39-14896 (72 FR 2612, January 22, 2007)), 
whichever occurs later: Perform a detailed visual inspection of the 
LH and RH wing MLG rib 5 aft bearing forward lugs.
    (2) If any crack is detected at LH and/or RH aft bearing forward 
lug, contact Airbus and proceed with the replacement before next 
flight.
    (3) Repeat the inspection at intervals not exceeding 100 flight 
cycles.

(h) Retained Actions and Compliance

    This paragraph restates the requirements of paragraph (g) of AD 
2008-17-02, Amendment 39-15640 (73 FR 47032, August 13, 2008), with 
new service information for paragraphs (h)(2), (h)(3), and 
(h)(4)(ii) of this AD, and specific delegation approval language in 
paragraphs (h)(3) and (h)(4)(ii) of this AD. For Model A310 
airplanes, except for those where LH and RH wing MLG rib 5 forward 
lugs have been repaired by installation of oversized interference 
fit bushes as per Airbus A310 Repair Instruction R572-49121, or 
which have had Airbus Service Bulletin A310-57-2090 (Airbus 
Modification 13329) embodied in service: Before the accumulation of 
12,000 total flight cycles or before the accumulation of 12,000 
flight cycles on MLG rib 5, or within 14 days after September 17, 
2008 (the effective date of AD 2008-17-02), whichever occurs latest, 
perform either a detailed visual inspection (DVI) or an ultrasonic 
inspection of the LH and RH MLG rib 5 aft bearing forward lug for 
cracks, in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A310-57-2091, excluding Appendix 01, dated May 22, 
2007. If a MLG rib 5 has been replaced on one side only, then the LH 
and RH must be considered separately. Doing this inspection ends the 
requirements of paragraph (g) of this AD for that MLG rib 5 only.
    (1) If no crack is detected during any inspection required by 
paragraph (h) of this AD: Repeat the applicable inspection at the 
time specified in paragraph (h)(1)(i) or (h)(1)(ii) of this AD.
    (i) Repeat the DVI thereafter at intervals not to exceed 100 
flight cycles.
    (ii) Repeat the ultrasonic inspection thereafter at intervals 
not to exceed 825 flight cycles.
    (2) Replacement of the MLG rib 5 bushes with new bushes with 
high interference fit in the aft bearing forward lugs of MLG rib 5, 
in accordance with the Accomplishment Instructions of a service 
bulletin specified in paragraph (h)(2)(i), (h)(2)(ii), or 
(h)(2)(iii) of this AD, ends the repetitive inspections required by 
paragraph (h)(1) of this AD for that MLG rib 5 only. As of the 
effective date of this AD, use only Airbus Mandatory Service 
Bulletin A310-57-2090, Revision 03, dated January 23, 2012, for the 
actions specified in this paragraph.
    (i) Airbus Service Bulletin A310-57-2090, Revision 01, dated 
December 19, 2007.
    (ii) Airbus Mandatory Service Bulletin A310-57-2090, Revision 
02, dated June 18, 2010.
    (iii) Airbus Mandatory Service Bulletin A310-57-2090, Revision 
03, dated January 23, 2012.
    (3) If any crack is detected during the DVI required by 
paragraph (h) of this AD: Before further flight, contact Airbus for 
replacement instructions and replace the MLG rib 5 bushes before 
further flight. As of the effective date of this AD: Before further 
flight, replace using a method approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or the European Aviation Safety Agency (EASA); or Airbus's EASA 
Design Organization Approval (DOA). Repeat the applicable inspection 
in paragraph (h) of this AD at the time specified in paragraph 
(h)(1)(i) or (h)(1)(ii) of this AD. Accomplishing the replacement of 
the MLG rib 5 bushes with new bushes with high interference fit in 
the aft bearing forward lugs of MLG rib 5, in accordance with the 
Accomplishment

[[Page 7295]]

Instructions of a service bulletin specified in paragraph (h)(2)(i), 
(h)(2)(ii), or (h)(2)(iii) of this AD, ends the repetitive 
inspections required by paragraph (h)(1) of this AD for that MLG rib 
5 only.
    (4) If any crack is detected during the ultrasonic inspection 
required by paragraph (h) of this AD, before further flight, 
accomplish the actions specified in paragraph (h)(4)(i) or 
(h)(4)(ii) of this AD, as applicable.
    (i) If any crack is not visible on MLG rib 5: Before further 
flight, repair MLG rib 5 using Airbus A310 Repair Instruction R572-
49121, Issue C, dated May 2007. After embodiment of the repair 
instruction, no further actions are necessary as required by 
paragraphs (g) and (h) of this AD and specified in Airbus Service 
Bulletin A310-57-2091, excluding Appendix 01, dated May 22, 2007, 
for that MLG rib 5 only.
    (ii) If any crack is visible on MLG rib 5: Before further 
flight, contact Airbus for rib replacement instructions, and replace 
before further flight. As of the effective date of this AD: Before 
further flight, replace using a method approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or the EASA; or Airbus's EASA DOA. Repeat the applicable inspection 
in paragraph (h) of this AD at the time specified in paragraph 
(h)(1)(i) or (h)(1)(ii) of this AD. Accomplishing the replacement of 
the MLG rib 5 bushes with new bushes with high interference fit in 
the aft bearing forward lugs of MLG rib 5, in accordance with the 
Accomplishment Instructions of a service bulletin specified in 
paragraph (h)(2)(i), (h)(2)(ii), or (h)(2)(iii) of this AD, ends the 
repetitive inspections required by paragraph (h) of this AD for that 
MLG rib 5 only.
    Note 1 to paragraph (h) of this AD: The ultrasonic inspection 
will detect any crack at an early stage and will limit the risk of 
extensive repairs. This earlier crack detection is not possible with 
the DVI.

(i) Retained Installation

    This paragraph restates the requirements of paragraph (g) of AD 
2012-08-03, Amendment 39-17019 (77 FR 24367, April 24, 2012), and 
applies to the airplanes identified in paragraph (j) of this AD. 
Within 30 months after May 29, 2012 (the effective date of AD 2012-
08-03), install new bushes with increased interference fit in the 
gear rib 5 aft bearing forward lug on the LH and RH wings, in 
accordance with the Accomplishment Instructions of the applicable 
service bulletin specified in paragraph (i)(1), (i)(2), or (i)(3) of 
this AD; except as specified in paragraph (k) of this AD.
    (1) Airbus Mandatory Service Bulletin A300-57-0249, Revision 03, 
dated January 18, 2012 (for Model A300 B4-2C, B4-103, and B4-203 
airplanes).
    (2) Airbus Mandatory Service Bulletin A300-57-6106, Revision 03, 
dated January 26, 2012 (for Model A300-600 series airplanes).
    (3) Airbus Mandatory Service Bulletin A310-57-2090, Revision 03, 
dated January 23, 2012 (for Model A310 series airplanes).

(j) Affected Airplanes for the Actions Required by Paragraph (i) of 
This AD

    For airplanes identified in paragraphs (j)(1), (j)(2), and 
(j)(3) of this AD: Do the actions required by paragraph (i) of this 
AD.
    (1) Airbus Model A300 B4-2C, B4-103, and B4-203 airplanes; all 
serial numbers; except airplanes on which the MLG rib 5 forward lugs 
of the LH and RH wings have been repaired by installation of 
oversized interference fit bushes specified in Airbus Repair 
Instruction R57240221, or those on which the LH and RH wings have 
had Airbus Service Bulletin A300-57-0249 embodied in service.
    (2) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 
airplanes; Airbus Model A300 B4-605R and B4-622R airplanes; Airbus 
Model A300 F4-605R and F4-622R airplanes; and Airbus Model A300 C4-
605R Variant F airplanes; all serial numbers; except airplanes on 
which the MLG rib 5 forward lugs of the LH and RH wings have been 
repaired by installation of oversized interference fit bushes 
specified in Airbus Repair Instruction R57240221, or those on which 
the LH and RH wings have had Airbus Service Bulletin A300-57-6106 
embodied in service.
    (3) Airbus Model A310-203, -204, -221, -222, -304, -322, -324, 
and -325 airplanes; all serial numbers; except airplanes on which 
the MLG rib 5 forward lugs of the LH and RH wings have been repaired 
by installation of oversized interference fit bushes specified in 
Airbus Repair Instruction R57249121, or those on which the LH and RH 
wings have had Airbus Service Bulletin A310-57-2090 embodied in 
service.

(k) Retained Exception for Airplanes Identified in Paragraphs (j)(1), 
(j)(2), and (j)(3) of This AD

    This paragraph restates the requirements of paragraph (h) of AD 
2012-08-03, Amendment 39-17019 (77 FR 24367, April 24, 2012), and 
applies to the airplanes identified in paragraphs (j)(1), (j)(2), 
and (j)(3) of this AD. If one wing had rib 5 forward lugs of the MLG 
repaired by installing oversized interference fit bushes, as 
specified in Airbus Repair Instruction R57240221 or Airbus Repair 
Instruction R572-49121, as applicable to the airplane model, then 
installing new bushes with increased interference fit in the aft 
bearing forward lug of the gear rib, as specified in paragraph (i) 
of this AD, is required for the opposite wing only.

(l) Retained Terminating Action for Certain Inspections

    This paragraph restates the requirements of paragraph (i) of AD 
2012-08-03, Amendment 39-17019 (77 FR 24367, April 24, 2012), and 
applies to the airplanes identified in paragraphs (j)(1), (j)(2), 
and (j)(3) of this AD. Installation of new bushes, as specified in 
paragraph (i) of this AD, is terminating action for the repetitive 
inspections required by AD 2007-03-18, Amendment 39-14929 (72 FR 
5919, February 8, 2007); and by paragraphs (g) and (h) of this AD.

(m) Retained Repetitive Inspections

    This paragraph restates the requirements of paragraph (g) of AD 
2012-15-14, Amendment 39-17143 (77 FR 46937, August 7, 2012), and 
applies to the airplanes identified in paragraph (n) of this AD. 
Except as provided by paragraph (o) of this AD: Before the 
accumulation of 12,000 total flight cycles since new, or within 
12,000 flight cycles since the most recent MLG rib 5 replacement, if 
applicable, or within 10 days after September 11, 2012 (the 
effective date of AD 2012-15-14, Amendment 39-17143 (77 FR 46937, 
August 7, 2012)), whichever occurs latest, do a detailed inspection 
or an ultrasonic inspection for cracking of the LH and RH MLG rib 5 
aft bearing forward lugs, in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A300-57-0251, 
including Appendix 01, dated August 8, 2007 (for Model A300 B4-103, 
B4-203, and B4-2C airplanes); or Airbus Mandatory Service Bulletin 
A300-57-6107, including Appendix 01, dated August 8, 2007 (for Model 
A300-600 series airplanes). Repeat the applicable inspections 
thereafter at the applicable interval specified in paragraph (m)(1) 
or (m)(2) of this AD, until the modification specified in paragraph 
(q) of this AD is accomplished.
    (1) Repeat the detailed inspections at intervals not to exceed 
100 flight cycles.
    (2) Repeat the ultrasonic inspections at intervals not to exceed 
675 flight cycles.

(n) Affected Airplanes for the Actions Required by Paragraph (m) of 
This AD

    For Airbus Model A300 B4-2C, B4-103, and B4-203 airplanes; Model 
A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, and 
F4-622R airplanes; and Model A300 C4-605R Variant F airplanes; all 
serial numbers; except for airplanes identified in paragraphs 
(n)(1), (n)(2), and (n)(3) of this AD: Do the actions required by 
paragraph (m) of this AD, except as provided by paragraph (o) of 
this AD.
    (1) Airplanes on which LH and RH wing MLG rib 5 forward lugs 
have oversized interference fit bushings installed per Airbus Repair 
Instruction R57240221.
    (2) Model A300 B4-103, B4-203, and B4-2C airplanes on which 
Airbus Service Bulletin A300-57-0249 has been done in service on the 
LH and RH wings.
    (3) Model A300-600 series airplanes on which Airbus Service 
Bulletin A300-57-6106 has been done in service on the LH and RH 
wings.

(o) Retained Exception for Certain Airplanes Identified in Paragraph 
(n) of This AD

    This paragraph restates the requirements of paragraph (h) of AD 
2012-15-14, Amendment 39-17143 (77 FR 46937, August 7, 2012), and 
applies to the airplanes identified in paragraph (n) of this AD on 
which an inspection required by AD 2007-03-18, Amendment 39-14929 
(72 FR 5919, February 8, 2007), has been done as of September 11, 
2012 (the effective date of AD 2012-15-14): Within 100 flight cycles 
after doing the most recent inspection required by AD 2007-03-18, or 
within 10 days after September 11, 2012, whichever occurs later, do 
a detailed or ultrasonic inspection as specified in paragraph (m) of 
this AD. Repeat the applicable inspection thereafter at the times 
specified in paragraph (m) of this AD.

[[Page 7296]]

(p) Retained Repair

    This paragraph restates the requirements of paragraph (i) of AD 
2012-15-14, Amendment 39-17143 (77 FR 46937, August 7, 2012), with 
specific delegation approval language. If any cracking is detected 
during any detailed or ultrasonic inspection of the LH and RH MLG 
rib 5 aft bearing forward lugs required by paragraph (m) of this AD, 
before further flight, repair using a method approved by Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or the EASA; or Airbus's EASA DOA.

(q) Retained Optional Terminating Modification

    This paragraph restates the optional terminating modification of 
paragraph (j) of AD 2012-15-14, Amendment 39-17143 (77 FR 46937, 
August 7, 2012), and applies to the airplanes identified in 
paragraph (n) of this AD. Performing the applicable actions 
specified in paragraphs (q)(1), (q)(2), (q)(3), and (q)(4) of this 
AD, in accordance with the Accomplishment Instructions of Airbus 
Mandatory Service Bulletin A300-57-0249, Revision 02, dated June 18, 
2010 (for Model A300 B4-103, B4-203, and B4-2C airplanes); or Airbus 
Mandatory Service Bulletin A300-57-6106, Revision 03, dated January 
26, 2012 (for Model A300-600 series airplanes); terminates the 
repetitive inspections required by paragraph (m) of this AD.
    (1) Perform a general visual inspection and dye penetrant flaw 
detection inspection for corrosion and damage of the bore and 
spotfaces of the lug.
    (2) Determine that the diameter of the bore of the lug 
(dimension Y) is within the tolerance specified in the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A300-57-0249, Revision 02, dated June 18, 2010 (for Model A300 B4-
103, B4-203, and B4-2C airplanes); or Airbus Mandatory Service 
Bulletin A300-57-6106, Revision 03, dated January 26, 2012 (for 
Model A300-600 series airplanes).
    (3) If damage or corrosion is detected during any inspection 
specified in paragraph (q)(1) of this AD, or if dimension Y is 
outside the tolerance specified in the Accomplishment Instructions 
of Airbus Mandatory Service Bulletin A300-57-0249, Revision 02, 
dated June 18, 2010 (for Model A300 B4-103, B4-203, and B4-2C 
airplanes); or Airbus Mandatory Service Bulletin A300-57-6106, 
Revision 03, dated January 26, 2012 (for Model A300-600 series 
airplanes); repair using a method approved by either the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or EASA; or Airbus's EASA DOA.
    (4) Install bushings with an increased interference fit in the 
aft bearing forward lugs, in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A300-57-0249, 
Revision 02, dated June 18, 2010 (for Model A300 B4-103, B4-203, and 
B4-2C airplanes); or Airbus Mandatory Service Bulletin A300-57-6106, 
Revision 03, dated January 26, 2012 (for Model A300-600 series 
airplanes).

(r) Retained Terminating Action for AD 2007-03-18, Amendment 39-14929 
(72 FR 5919, February 8, 2007)

    This paragraph restates the terminating action statement of 
paragraph (k) of AD 2012-15-14, Amendment 39-17143 (77 FR 46937, 
August 7, 2012), and applies to the airplanes identified in 
paragraph (n) of this AD. Doing the actions required by paragraph 
(q) of this AD terminates the inspections required by AD 2007-03-18, 
Amendment 39-14929 (72 FR 5919, February 8, 2007), for that 
airplane.

(s) Retained Reporting

    This paragraph restates the requirements of paragraph (l) of AD 
2012-15-14, Amendment 39-17143 (77 FR 46937, August 7, 2012), and 
applies to the airplanes identified in paragraph (n) of this AD. 
Submit a report (including both positive and negative findings), 
using the applicable report sheet attached to Airbus Mandatory 
Service Bulletin A300-57-0251, including Appendix 01, dated August 
8, 2007 (for Model A300 B4-103, B4-203, and B4-2C airplanes); or 
Airbus Mandatory Service Bulletin A300-57-6107, including Appendix 
01, dated August 8, 2007 (for Model A300-600 series airplanes); of 
the first inspection required by paragraph (m) of this AD. Submit 
the report 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 (s)(1) or (s)(2) of this AD.
    (1) If the inspection was done on or after September 11, 2012 
(the effective date of AD 2012-15-14, Amendment 39-17143 (77 FR 
46937, August 7, 2012)): Submit the report within 30 days after the 
inspection.
    (2) If the inspection was done before September 11, 2012 (the 
effective date of AD 2012-15-14, Amendment 39-17143 (77 FR 46937, 
August 7, 2012)): Submit the report within 30 days after September 
11, 2012.

(t) New Repetitive Inspections

    For airplanes identified in paragraph (u) of this AD: At the 
applicable time specified in paragraph (v)(1) or (v)(2) of this AD, 
do a detailed inspection for cracking, or an ultrasonic inspection 
for any crack indications of the LH and RH MLG rib 5 aft bearing 
forward lugs, in accordance with the Accomplishment Instructions of 
the applicable service bulletin specified in paragraph (t)(1), 
(t)(2), or (t)(3) of this AD. Repeat the inspection thereafter at 
intervals not to exceed the applicable time specified in paragraph 
(v)(3) or (v)(4) of this AD.
    (1) Airbus Service Bulletin A300-57-0255, including Inspection 
Reporting Form, dated January 13, 2012 (for Model A300 B2-1A, B2-1C, 
B2K-3C, and B2-203 airplanes).
    (2) Airbus Service Bulletin A300-57-6112, including Inspection 
Reporting Form, dated January 13, 2012 (for Model A300 B4-601, B4-
603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, and F4-622R 
airplanes).
    (3) Airbus Service Bulletin A310-57-2101, including Inspection 
Reporting Form, dated January 13, 2012 (for Model A310-203, -204, -
221, -222, -304, -322, -324, and -325 airplanes).

(u) Affected Airplanes for the Actions Required by Paragraph (t) of 
This AD

    For airplanes on which any modification or repair described in 
the service bulletins identified in paragraph (u)(1), (u)(2), or 
(u)(3) of this AD, as applicable, has been accomplished in service; 
and for airplanes with MLG rib 5 already repaired as specified in 
Airbus Repair Instruction R57240221 or R572-49121, including any 
airplane with the MLG rib 5 forward lugs repaired on one wing; by 
installation of oversized interference fit bushes, as specified in 
Airbus Repair Instruction R57240221 or R572-49121, as applicable: Do 
the actions required by paragraph (t) of this AD.
    (1) Airbus Service Bulletin A300-57-0249, dated May 22, 2007; 
Revision 01, dated December 19, 2007; or Airbus Mandatory Service 
Bulletin A300-57-0249, Revision 02, dated June 18, 2010 (for Model 
A300 B4-2C, B4-103, and B4-203 airplanes).
    (2) Airbus Service Bulletin A300-57-6106, dated May 22, 2007; 
Revision 01, dated January 28, 2008; or Revision 02, dated June 18, 
2010 (for Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, B4-
622R, F4-605R, F4-622R, and C4-605R Variant F airplanes).
    (3) Airbus Service Bulletin A310-57-2090, dated May 22, 2007; 
Revision 01, dated December 19, 2007; or Revision 02, dated June 18, 
2010 (for Model A310 series airplanes).

(v) Compliance Times for Paragraph (t) of This AD

    This paragraph specifies the compliance times for the actions 
specified in paragraph (t) of this AD.
    (1) For airplanes identified in paragraph (c)(1) of this AD: Do 
the initial inspection required by paragraph (t) of this AD within 
2,500 flight cycles after any modification or repair specified in 
paragraph (u) of this AD was done, or within 550 flight cycles after 
the effective date of this AD, whichever occurs later.
    (2) For airplanes identified in paragraph (c)(2) of this AD: Do 
the initial inspection required by paragraph (t) of this AD within 
2,500 flight cycles after any modification or repair specified in 
paragraph (u) of this AD was done, or within 775 flight cycles after 
the effective date of this AD, whichever occurs later.
    (3) For airplanes identified in paragraph (c)(1) of this AD: For 
the repetitive inspection required by paragraph (t) of this AD, 
repeat the inspection within 550 flight cycles after any detailed 
inspection, and within 1,000 flight cycles after any ultrasonic 
inspection, as applicable.
    (4) For airplanes identified in paragraph (c)(2) of this AD: For 
the repetitive inspection required by paragraph (t) of this AD, 
repeat the inspection within 775 flight cycles after any detailed 
inspection, and within 1,300 flight cycles after any ultrasonic 
inspection, as applicable.

(w) New Requirement of This AD: Report and Detailed Inspection

    If, during any ultrasonic inspection required by paragraph (t) 
of this AD, any crack indication is detected: Before further

[[Page 7297]]

flight, report to Airbus using the applicable report sheet attached 
to the applicable Airbus service bulletin specified in paragraph 
(t)(1), (t)(2), or (t)(3) of this AD, and concurrently accomplish a 
detailed inspection for cracking of the affected MLG rib 5 aft 
bearing forward lug, in accordance with the Accomplishment 
Instructions of the applicable Airbus service bulletin specified in 
paragraph (t)(1), (t)(2), or (t)(3) of this AD. Repeat the detailed 
inspection thereafter at intervals not to exceed 100 flight cycles.

(x) New Requirement of This AD: Cracking Repair

    If any cracking is detected during any detailed inspection 
required by paragraph (t) or (w) of this AD: Before further flight, 
repair the cracking using a method approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or the EASA; or Airbus's EASA DOA.

(y) New Requirement of This AD: Reporting

    Submit a report (including both positive and negative findings), 
using the reporting sheet attached to the applicable Airbus service 
bulletin specified in paragraph (y)(1), (y)(2), or (y)(3) of this 
AD, of the first inspection required by paragraph (t) of this AD. 
Submit the report 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. Submit the report within 30 days 
after the inspection or within 30 days after the effective date of 
this AD, whichever occurs later.
    (1) Airbus Service Bulletin A300-57-0255, including Inspection 
Reporting Form, dated January 13, 2012 (for Model A300 B2-1A, B2-1C, 
B2K-3C, and B2-203 airplanes).
    (2) Airbus Service Bulletin A300-57-6112, including Inspection 
Reporting Form, dated January 13, 2012 (for Model A300 B4-601, B4-
603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, and F4-622R 
airplanes).
    (3) Airbus Service Bulletin A310-57-2101, including Inspection 
Reporting Form, dated January 13, 2012 (for Model A310-203, -204, -
221, -222, -304, -322, -324, and -325 airplanes).

(z) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by 
paragraph (i) of this AD, if those actions were performed before May 
29, 2012 (the effective date of AD 2012-08-03, Amendment 39-17019 
(77 FR 24367, April 24, 2012)), using an applicable service bulletin 
specified in paragraph (z)(1)(i), (z)(1)(ii), or (z)(1)(iii) of this 
AD.
    (i) For Model A300 B4-2C, B4-103, and B4-203 airplanes: The 
service bulletins are specified in paragraphs (z)(1)(i)(A), 
(z)(1)(i)(B), and (z)(1)(i)(C) of this AD.
    (A) Airbus Service Bulletin A300-57-0249, dated May 22, 2007, 
which is not incorporated by reference in this AD.
    (B) Airbus Service Bulletin A300-57-0249, Revision 01, dated 
December 19, 2007, which is not incorporated by reference in this 
AD.
    (C) Airbus Mandatory Service Bulletin A300-57-0249, Revision 02, 
dated June 18, 2010, incorporated by reference in AD 2012-15-14, 
Amendment 39-17143 (77 FR 46937, August 7, 2012).
    (ii) For Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-
622R, F4-605R, and F4-622R airplanes; and Model A300 C4-605R Variant 
F airplanes: The service bulletins are specified in paragraphs 
(z)(1)(ii)(A), (z)(1)(ii)(B), and (z)(1)(ii)(C) of this AD.
    (A) Airbus Service Bulletin A300-57-6106, dated May 22, 2007, 
which is not incorporated by reference in this AD.
    (B) Airbus Service Bulletin A300-57-6106, Revision 01, dated 
January 28, 2008, which is not incorporated by reference in this AD.
    (C) Airbus Service Bulletin A300-57-6106, Revision 02, dated 
June 18, 2010, which is not incorporated by reference in this AD.
    (iii) For Model A310 series airplanes: The service bulletins are 
specified in paragraphs (z)(1)(iii)(A), (z)(1)(iii)(B), and 
(z)(1)(iii)(C) of this AD.
    (A) Airbus Service Bulletin A310-57-2090, dated May 22, 2007, 
which is not incorporated by reference in this AD.
    (B) Airbus Service Bulletin A310-57-2090, Revision 01, dated 
December 19, 2007, incorporated by reference in AD 2008-17-02, 
Amendment 39-15640 (73 FR 47032, August 13, 2008).
    (C) Airbus Service Bulletin A310-57-2090, Revision 02, dated 
June 18, 2010, which is incorporated by reference in this AD.
    (2) This paragraph provides credit for actions required by 
paragraph (q) of this AD, if those actions were performed before 
September 11, 2012 (the effective date of AD 2012-15-14, Amendment 
39-17143 (77 FR 46937, August 7, 2012)), using an applicable service 
bulletin specified in paragraphs (z)(2)(i), (z)(2)(ii), (z)(2)(iii), 
(z)(2)(iv), and (z)(2)(v) of this AD.
    (i) For Model A300 B4-2C, B4-103, and B4-203: Airbus Service 
Bulletin A300-57-0249, dated May 22, 2007, which is not incorporated 
by reference in this AD.
    (ii) For Model A300 B4-2C, B4-103, and B4-203: Airbus Service 
Bulletin A300-57-0249, Revision 01, dated December 19, 2007, which 
is not incorporated by reference in this AD.
    (iii) For Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, 
B4-622R, F4-605R, F4-622R, and C4-605R Variant F airplanes: Airbus 
Service Bulletin A300-57-6106, dated May 22, 2007, which is not 
incorporated by reference in this AD.
    (iv) For Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, B4-
622R, F4-605R, F4-622R, and C4-605R Variant F airplanes: Airbus 
Service Bulletin A300-57-6106, Revision 01, dated January 28, 2008, 
which is not incorporated by reference in this AD.
    (v) For Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, B4-
622R, F4-605R, F4-622R, and C4-605R Variant F airplanes: Airbus 
Service Bulletin A300-57-6106, Revision 02, dated June 18, 2010, 
which is not incorporated by reference in this AD.
    (aa) 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: Dan Rodina, 
Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; phone 425-227-2125; fax 425-227-1149. Information may be 
emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov.
    (i) 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.
    (ii) AMOCs approved previously for AD 2008-17-02, Amendment 39-
15640 (73 FR 47032, August 13, 2008), are approved as AMOCs for the 
corresponding provisions of paragraphs (g) and (h) of this AD.
    (iii) AMOCs approved previously for AD 2012-08-03, Amendment 39-
17019 (77 FR 24367, April 24, 2012), are approved as AMOCs for the 
corresponding provisions of paragraphs (i), (j), (k), and (l) of 
this AD.
    (iv) AMOCs approved previously for AD 2012-15-14, Amendment 39-
17143 (77 FR 46937, August 7, 2012), are approved as AMOCs for the 
corresponding provisions of paragraphs (m) through (s) of this AD.
    (2) Contacting the Manufacturer: As of the effective date of 
this AD, for any requirement in this AD to obtain corrective actions 
from a manufacturer, the action must be accomplished using a method 
approved by the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. If 
approved by the DOA, the approval must include the DOA-authorized 
signature.
    (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.

(bb) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2012-0176, dated September 7, 
2012, corrected September 20, 2012, for related information. You may

[[Page 7298]]

examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-0142-0002.
    (2) Service information identified in this AD that is not 
incorporated by reference in this AD is available at the addresses 
specified in paragraphs (cc)(9) and (cc)(10) of this AD.

(cc) 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 this AD specifies otherwise.
    (3) The following service information was approved for IBR on 
March 17, 2015.
    (i) Airbus Service Bulletin A300-57-0255, including Inspection 
Reporting Form, dated January 13, 2012.
    (ii) Airbus Service Bulletin A300-57-6112, including Inspection 
Reporting Form, dated January 13, 2012.
    (iii) Airbus Service Bulletin A310-57-2090, Revision 02, dated 
June 18, 2010.
    (iv) Airbus Service Bulletin A310-57-2101, including Inspection 
Reporting Form, dated January 13, 2012.
    (4) The following service information was approved for IBR on 
September 11, 2012 (77 FR 46937, August 7, 2012).
    (i) Airbus Mandatory Service Bulletin A300-57-0249, Revision 02, 
dated June 18, 2010.
    (ii) Airbus Mandatory Service Bulletin A300-57-0251, including 
Appendix 01, dated August 8, 2007.
    (iii) Airbus Mandatory Service Bulletin A300-57-6106, Revision 
03, dated January 26, 2012.
    (iv) Airbus Mandatory Service Bulletin A300-57-6107, including 
Appendix 01, August 8, 2007.
    (5) The following service information was approved for IBR on 
May 29, 2012 (77 FR 24367, April 24, 2012).
    (i) Airbus Mandatory Service Bulletin A300-57-0249, Revision 03, 
dated January 18, 2012.
    (ii) Airbus Mandatory Service Bulletin A310-57-2090, Revision 
03, dated January 23, 2012.
    (6) The following service information was approved for IBR on 
September 17, 2008 (73 FR 47032, August 13, 2008).
    (i) Airbus Service Bulletin A310-57-2090, Revision 01, dated 
December 19, 2007.
    (ii) Airbus Service Bulletin A310-57-2091, excluding Appendix 
01, dated May 22, 2007.
    (iii) Airbus A310 Repair Instruction R572-49121, Issue C, dated 
May 2007.
    (7) The following service information was approved for IBR on 
February 6, 2007 (72 FR 2612, January 22, 2007).
    (i) Airbus Service Bulletin A310-57A2088, excluding Appendix 01, 
dated November 6, 2006.
    (ii) Reserved.
    (8) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; 
Internet http://www.airbus.com.
    (9) You may view this 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.
    (10) 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: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on January 21, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-01710 Filed 2-9-15; 8:45 am]
BILLING CODE 4910-13-P