Airworthiness Directives; Airbus Airplanes, 31245-31250 [2017-13949]

Download as PDF jstallworth on DSK7TPTVN1PROD with RULES Federal Register / Vol. 82, No. 128 / Thursday, July 6, 2017 / Rules and Regulations onions for the 2011 through 2015 marketing years is $16.24 per 50-pound equivalent. NASS has not released data regarding the 2016 marketing year at this time. Multiplying the 2011–2015 marketing year average price of $16.24 by the estimated 2017 marketing year shipments of 325,000 50-pound equivalents yields an annual crop revenue estimate of $5,278,000. The estimated average annual revenue for each of the 30 producers is therefore calculated to be approximately $175,933 ($5,278,000 divided by 30), which is less than the Small Business Administration threshold of $750,000. In view of the foregoing, the majority of Walla Walla sweet onion producers, and all of the Walla Walla sweet onion handlers, may be classified as small entities. This rule continues in effect the action that decreased the assessment rate established for the Committee and collected from handlers for the 2017 and subsequent fiscal periods from $0.22 to $0.10 per 50-pound bag or equivalent of Walla Walla sweet onions handled. The Committee also unanimously recommended 2017 expenditures of $93,250. The assessment rate of $0.10 is $0.12 lower than the previously established assessment rate. Applying the $0.10 per 50-pound bag or equivalent assessment rate to the Committee’s 325,000 50-pound bag or equivalent crop estimate should provide $32,500 in assessment income. Thus, income derived from handler assessments, along with interest, other income, and funds from the Committee’s authorized reserve, will be adequate to cover budgeted expenses. This action will allow the Committee to reduce its financial reserve while still providing adequate funding to meet program expenses. This rule continues in effect the action that decreased the assessment obligation imposed on handlers. Assessments are applied uniformly on all handlers, and some of the costs may be passed on to producers. However, decreasing the assessment rate reduces the burden on handlers and may reduce the burden on producers. In addition, the Committee’s meeting was widely publicized throughout the Walla Walla sweet onion industry, and all interested persons were invited to attend the meeting and participate in Committee deliberations on all issues. Like all Committee meetings, the December 6, 2016, meeting was a public meeting, and all entities, both large and small, were able to express views on this issue. In accordance with the Paperwork Reduction Act of 1995 (44 U.S.C. VerDate Sep<11>2014 14:53 Jul 05, 2017 Jkt 241001 Chapter 35), the order’s information collection requirements have been previously approved by the OMB and assigned OMB No. 0581–0178, Vegetable and Specialty Crops. No changes in those requirements as a result of this action are necessary. Should any changes become necessary, they would be submitted to OMB for approval. This action imposes no additional reporting or recordkeeping requirements on either small or large Walla Walla sweet onion handlers. As with all Federal marketing order programs, reports and forms are periodically reviewed to reduce information requirements and duplication by industry and public sector agencies. USDA has not identified any relevant Federal rules that duplicate, overlap, or conflict with this rule. Comments on the interim rule were required to be received on or before April 28, 2017. One comment was received during the comment period from an individual who was outside of the regulated production area. The comment was generally opposed to all government regulation. In the comment, the commenter failed to specifically address any of the merits of the rule. Accordingly, no changes have been made to the rule, based on the comment received. Therefore, for reasons given in the interim rule, we are adopting the interim rule as a final rule, without change. To view the interim rule, go to: https://www.regulations.gov/ document?D=AMS-SC-16-0116-0001. This action also affirms information contained in the interim rule concerning Executive Orders 12866, 12988, 13175, and 13563; the Paperwork Reduction Act (44 U.S.C. Chapter 35); and the EGov Act (44 U.S.C. 101). After consideration of all relevant material presented, it is hereby found that finalizing the interim rule, without change, as published in the Federal Register (82 FR 11789, February 27, 2017) will tend to effectuate the declared policy of the Act. List of Subjects in 7 CFR Part 956 Marketing agreements, Onions, Reporting and recordkeeping requirements. PART 956—SWEET ONIONS GROWN IN THE WALLA WALLA VALLEY IN SOUTHEAST WASHINGTON AND NORTHEAST OREGON Accordingly, the interim rule amending 7 CFR part 956, which was published at 82 FR 11789 on February ■ PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 31245 27, 2017, is adopted as final without change. Dated: June 29, 2017. Bruce Summers, Acting Administrator, Agricultural Marketing Service. [FR Doc. 2017–14177 Filed 7–5–17; 8:45 am] BILLING CODE 3410–02–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–3984; Directorate Identifier 2014–NM–119–AD; Amendment 39–18945; AD 2017–14–01] 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) 2013–10– 03, which applied to all Airbus Model A330–200, –200 Freighter, and –300 series airplanes; and Model A340–200, –300, –500, and –600 series airplanes. AD 2013–10–03 required one-time inspections for deformation and damage of the bogie beams of the main landing gear (MLG); repetitive inspections for damage and corrosion of the sliding piston sub-assembly on certain airplanes; and related investigative and corrective actions if necessary. This new AD removes Model A340–500 and 600 series airplanes from the applicability; removes certain one-time inspections of the MLG bogie beams and the sliding piston sub-assembly; revises certain compliance times; and requires replacement of certain MLGs with MLGs having an improved bogie beam, which constitutes terminating action for the repetitive inspections on the modified MLG. This AD was prompted by reports of corroded and cracked bogie beams under the bogie stop pad. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective August 10, 2017. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of August 10, 2017. ADDRESSES: For Airbus service information identified in this final rule, contact Airbus SAS, Airworthiness Office—EAL, 1 Rond Point Maurice SUMMARY: E:\FR\FM\06JYR1.SGM 06JYR1 31246 Federal Register / Vol. 82, No. 128 / Thursday, July 6, 2017 / Rules and Regulations Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 45 80; email: airworthiness.A330–A340@airbus.com; Internet http://www.airbus.com. For Messier-Bugatti-Dowty service information identified in this final rule, contact Messier Services Americas, Customer Support Center, 45360 Severn Way, Sterling, VA 20166–8910; phone: 703–450–8233; fax: 703–404–1621; Internet: https://techpubs.services/ messier-dowty.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–2016– 3984. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 3984; 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 address for the Docket Office (telephone 800–647–5527) is 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 20590. FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; fax 425–227–1149. SUPPLEMENTARY INFORMATION: jstallworth on DSK7TPTVN1PROD with RULES Discussion We issued a supplemental notice of proposed rulemaking (SNPRM) to amend 14 CFR part 39 to supersede AD 2013–10–03, Amendment 39–17456 (78 FR 31386, May 24, 2013) (‘‘AD 2013– 10–03’’). AD 2013–10–03 applied to all Airbus Model A330–200, –200 Freighter, and –300 series airplanes; and Model A340–200, –300, –500, and –600 series airplanes. The SNPRM published in the Federal Register on March 22, 2017 (82 FR 14642) (‘‘the SNPRM’’). We preceded the SNPRM with a notice of proposed rulemaking (NPRM) that published in the Federal Register on VerDate Sep<11>2014 14:53 Jul 05, 2017 Jkt 241001 March 1, 2016 (81 FR 10540) (‘‘the NPRM’’). The NPRM was prompted by reports of corroded and cracked bogie beams under the bogie stop pad. The NPRM proposed to remove Model A340–500, and –600 series airplanes from the applicability, remove certain one-time inspections of the MLG bogie beams and the sliding piston subassembly; revise certain compliance times and provide, for certain airplanes, an optional terminating action for the repetitive actions. The SNPRM proposed to require replacement of a MLG having part number (P/N) 201252 series and P/N 201490 series with a MLG that has an improved bogie beam, which would constitute terminating action for the repetitive inspections on the modified MLG. We are issuing this AD to detect and correct damage or corrosion under the bogie stop pad of both MLG bogie beams; this condition could result in a damaged bogie beam and consequent detachment of the beam from the airplane, collapse of the MLG, or departure of the airplane from the runway, possibly resulting in damage to the airplane and injury to occupants. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2016–0108, dated June 8, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus Model A330–200, –200 Freighter, and –300 series airplanes; and Model A340–200 and –300 series airplanes. The MCAI states: During a scheduled maintenance inspection on the Main Landing Gear (MLG), the bogie stop pad was found deformed and cracked. Upon removal of the bogie stop pad for replacement, the bogie beam was also found cracked. The results of a laboratory investigation indicated that an overload event had occurred and no fatigue propagation of the crack was evident. A second bogie beam crack was subsequently found on another aeroplane, located under a bogie stop pad which only had superficial paint damage. This condition, if not detected and corrected, could lead to landing gear bogie detachment from the aeroplane, or landing gear collapse, or a runway excursion, possibly resulting in damage to the aeroplane and injury to the occupants and/or people on the ground. To address this potential unsafe condition, EASA issued AD 2008–0223 [which corresponds to FAA AD 2010–02–10, Amendment 39–16181 (75 FR 4477, January 28, 2010)] to require accomplishment of a one-time detailed inspection under the bogie stop pad of both MLG bogie beams. As a result of the one-time inspection required by that [EASA] AD, numerous bogie stop pad were found corroded and a few cracked. The PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 one-time inspection was retained in EASA AD 2011–0211 [which corresponds to FAA AD 2013–10–03], which superseded EASA AD 2008–0223, which also introduced repetitive inspections, except for A340–500/ –600 aeroplanes. After EASA AD 2011–0211 was issued, further investigation led to the conclusion that the one-time inspection was no longer necessary and only the repetitive inspections should remain. In addition, it was determined that repetitive inspections were also necessary for MLG on A340–500/–600 aeroplanes. Prompted by these conclusions, EASA issued AD 2014–0120, partially retaining the requirements of EASA AD 2011–0211, which was superseded, and introducing repetitive detailed inspections of the MLG on A340– 500 and A340–600 aeroplanes. Subsequently, further analysis indicated that repetitive inspections of the MLG on A340–500/–600 aeroplanes were not necessary after all. In addition, the threshold for the inspection of MLG P/N 10–210 series was raised from 24 to 126 months, and Airbus developed a modification of the MLG P/N 10–210 series which provides an (optional) terminating action for the repetitive inspections. Consequently, EASA AD 2014–0120 was revised to delete the requirements for A340– 500/–600 aeroplanes, to amend the inspection threshold for MLG P/N 10–210 series, and to introduce an optional terminating action for aeroplanes with MLG P/N 10–210 series. Since EASA AD 2014–0120R1 was issued, Airbus developed a modification (mod 205289) of the MLG P/N 201252 series and P/N 201490 series that must be embodied in service with Airbus SB A330–32–3275 or SB A340–32–4305. It was also identified that A340–500/–600 aeroplanes could be removed from the applicability of this [EASA] AD as no more actions were required on these aeroplanes. For the reason described above, this [EASA] AD retains the requirements of EASA AD 2014–0120R1, which is superseded, removes the A340–500/–600 aeroplanes from the Applicability and requires the modification of the MLG P/N 201252 series and P/N 201490 series, which constitutes terminating action for the repetitive inspections required by this [EASA] AD. The required actions include repetitive detailed inspections for damage and corrosion of the sliding piston subassembly, and related investigative and corrective actions if necessary. Related investigative actions include a test for indications of corrosion and damage to the bogie assembly base material, and a magnetic particle inspection for cracks, corrosion, and damage of the bogie beam. Corrective actions include repairing affected parts. The required terminating action (for a MLG having P/N 201252 series or P/N 201490 series) and the optional terminating action (for a MLG having P/ N 10–210 series) are modifications of the bogie beam of a MLG, which consist of installing a nickel under chrome E:\FR\FM\06JYR1.SGM 06JYR1 Federal Register / Vol. 82, No. 128 / Thursday, July 6, 2017 / Rules and Regulations coating, a new bogie beam stop pad, and new stop pad brackets. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 3984. Comments We gave the public the opportunity to participate in developing this AD. We considered the comment received. Air Line Pilots Association, International supported the SNPRM. jstallworth on DSK7TPTVN1PROD with RULES Conclusion We reviewed the available data, including the comment received, and determined that air safety and the public interest require adopting this AD as proposed except for minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the SNPRM for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the SNPRM. Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information. • Airbus Service Bulletin A330–32– 3248, Revision 05, including Appendix 1, dated May 4, 2016; and Airbus Service Bulletin A340–32–4286, Revision 02, including Appendix 1, dated January 5, 2016; which describe procedures for doing an inspection for damage and corrosion of the MLG sliding piston sub-assembly, bogie beam stop pad and the bogie beam under the stop pad, and related investigative and corrective actions. These documents are distinct since they apply to different airplane models. • Airbus Service Bulletin A330–32– 3268, Revision 01, dated September 21, 2015, which describes procedures for modification of the bogie beam of a MLG having P/N 10–210 series on Model A330 airplanes that includes installing a nickel under chrome coating, a new bogie beam stop pad, and new stop pad brackets. • Airbus Service Bulletin A330–32– 3275, dated December 23, 2015, which describes procedures for modification of the bogie beam of a MLG having P/N 201252 series or P/N 201490 series on Model A330 airplanes that includes installing a nickel under chrome coating, a new bogie beam stop pad, and new stop pad brackets. • Airbus Service Bulletin A340–32– 4300, dated April 20, 2015; and Revision 01, dated September 21, 2015; VerDate Sep<11>2014 14:53 Jul 05, 2017 Jkt 241001 31247 which describe procedures for modification of the bogie beam of a MLG having P/N 10–210 series on Model A340 airplanes that include installing a nickel under chrome coating, a new bogie beam stop pad, and new stop pad brackets. These service bulletins are distinct due to editorial revisions. • Airbus Service Bulletin A340–32– 4305, dated December 23, 2015, which describes procedures for modification of the bogie beam of a MLG having P/N 201252 series or P/N 201490 series on Model A340 airplanes that includes installing a nickel under chrome coating, a new bogie beam stop pad, and new stop pad brackets. Messier-Bugatti-Dowty has issued the following service information. • Messier-Bugatti-Dowty Service Bulletin A33/34–32–305, including Appendix A, dated April 13, 2015, which describes procedures for modification of the bogie beam of a MLG having MLG P/N 10–210 series that includes installing a nickel under chrome coating, a new bogie beam stop pad, and new stop pad brackets. • Messier-Bugatti-Dowty Service Bulletin A33/34–32–306, Revision 1, including Appendix A, dated May 31, 2016, which describes procedures for modification of the bogie beam of a MLG having P/N 201252 series or P/N 201490 series that includes installing a nickel under chrome coating, a new bogie beam stop pad, and new stop pad brackets. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. product. We have no way of determining the number of aircraft that might need these actions. According to the manufacturer, all of the parts costs of the optional terminating action specified in 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. We have received no definitive data that would enable us to provide the work-hour cost estimates for the optional terminating action specified in this AD. Costs of Compliance We estimate that this AD affects 89 Model A330–200, –200 Freighter, and –300 series airplanes of U.S. registry. We estimate that it will take about 13 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 $98,345, or $1,105 per product. Currently, there are no Model A340– 200 or –300 series airplanes on the U.S. Register. However, if an affected airplane is imported and placed on the U.S. Register in the future, it would be subject to the same per-airplane cost specified above for the Model A330– 200, –200 Freighter, and –300 series airplanes. In addition, we estimate that any necessary follow-on actions will take about 24 work-hours and require parts costing $78, for a cost of $2,118 per We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 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 E:\FR\FM\06JYR1.SGM 06JYR1 31248 Federal Register / Vol. 82, No. 128 / Thursday, July 6, 2017 / Rules and Regulations List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2013–10–03, Amendment 39–17456 (78 FR 31386, May 24, 2013), and adding the following new AD: ■ 2017–14–01 Airbus: Amendment 39–18945; Docket No. FAA–2016–3984; Directorate Identifier 2014–NM–119–AD. (a) Effective Date This AD is effective August 10, 2017. (b) Affected ADs This AD replaces AD 2013–10–03, Amendment 39–17456 (78 FR 31386, May 24, 2013) (‘‘AD 2013–10–03’’). (c) Applicability This AD applies to Airbus airplanes identified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category, all serial numbers, except those airplanes that have embodied Airbus Modification 204421 or Airbus Modification 205289 in production. (1) Model A330–201, –202, –203, –223, –223F, –243, –243F, –301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes. (2) Model A340–211, –212, –213, –311, –312, and –313 airplanes. (d) Subject Air Transport Association (ATA) of America Code 32, Landing gear. jstallworth on DSK7TPTVN1PROD with RULES (e) Reason This AD was prompted by reports of corroded and cracked bogie beams under the bogie stop pad. We are issuing this AD to detect and correct damage or corrosion under the bogie stop pad of both main landing gear (MLG) bogie beams; this condition could result in a damaged bogie beam and consequent detachment of the beam from the airplane, collapse of the MLG, or departure of the airplane from the runway, possibly resulting in damage to the airplane and injury to occupants. (f) Compliance Comply with this AD within the compliance times specified, unless already done. VerDate Sep<11>2014 14:53 Jul 05, 2017 Jkt 241001 (g) Repetitive Inspections, Related Investigative Actions, and Corrective Actions For Model A330–200, –200 Freighter, and –300 series airplanes; and Model A340–200 and –300 series airplanes; equipped with a MLG having part number (P/N) 201252 series, P/N 201490 series, or P/N 10–210 series: Do the applicable actions required by paragraph (g)(1) or (g)(2) of this AD. (1) For airplanes equipped, as of the effective date of this AD, with a MLG that has been previously inspected, as specified in Airbus Service Bulletin A330–32–3220, Airbus Service Bulletin A330–32–3248, Airbus Service Bulletin A340–32–4264, or Airbus Service Bulletin A340–32–4286, as applicable: At the applicable times specified in paragraphs (h)(1) and (h)(2) of this AD, do a detailed inspection for damage (e.g., cracking and fretting) and corrosion of the MLG sliding piston sub-assembly, bogie beam stop pad, and the bogie beam under the stop pad; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330– 32–3248, Revision 05, including Appendix 1, dated May 4, 2016; or Airbus Service Bulletin A340–32–4286, Revision 02, including Appendix 1, dated January 5, 2016; as applicable; except as required by paragraph (j) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspection of the MLG sliding piston sub-assembly, bogie beam stop pad, and the bogie beam under the stop pad, thereafter, at intervals not to exceed 2,500 flight cycles or 24 months, whichever occurs first. (2) For airplanes equipped, as of the effective date of this AD, with a MLG that has not been previously inspected, as specified in Airbus Service Bulletin A330–32–3220, Airbus Service Bulletin A330–32–3248, Airbus Service Bulletin A340–32–4264, or Airbus Service Bulletin A340–32–4286, as applicable: At the applicable times specified in paragraphs (h)(3) and (h)(4) of this AD, do a detailed inspection for damage (e.g., cracking and fretting) and corrosion of the MLG sliding piston sub-assembly, bogie beam stop pad, and the bogie beam under the stop pad; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330– 32–3248, Revision 05, including Appendix 1, dated May 4, 2016; or Airbus Service Bulletin A340–32–4286, Revision 02, including Appendix 1, dated January 5, 2016; as applicable; except as required by paragraph (j) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspection of the MLG sliding piston sub-assembly, bogie beam stop pad, and the bogie beam under the stop pad, thereafter, at intervals not to exceed 2,500 flight cycles or 24 months, whichever occurs first. (h) Compliance Times for the Actions Required by Paragraph (g) of This AD Do the applicable actions required by paragraph (g) of this AD at the applicable time specified in paragraph (h)(1), (h)(2), (h)(3), or (h)(4) of this AD. PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 (1) For airplanes identified in paragraph (g)(1) of this AD having a MLG P/N 201252 series or P/N 201490 series: Before the accumulation of 2,500 total flight cycles or 24 months, whichever occurs first since the later of the times specified in paragraphs (h)(1)(i) and (h)(1)(ii) of this AD. (i) Since first flight after a MLG overhaul. (ii) Since first flight after the most recent accomplishment of an inspection of the MLG, as specified in Airbus Service Bulletin A330– 32–3220, Airbus Service Bulletin A330–32– 3248, Airbus Service Bulletin A340–32–4264, or Airbus Service Bulletin A340–32–4286, as applicable. (2) For airplanes identified in paragraph (g)(1) of this AD having a MLG P/N 10–210 series: Before the accumulation of 126 months since first flight of the MLG on an airplane or since first flight on an airplane after the most recent inspection of the MLG, as specified in Airbus Service Bulletin A330– 32–3248, or Airbus Service Bulletin A340– 32–4286, as applicable. (3) For airplanes identified in paragraph (g)(2) of this AD having a MLG P/N 201252 series or P/N 201490 series: At the later of the times specified in paragraphs (h)(3)(i) and (h)(3)(ii) of this AD. (i) Before the accumulation of 2,500 total flight cycles or 24 months, whichever occurs first since the later of the times specified in paragraphs (h)(3)(i)(A) and (h)(3)(i)(B) of this AD. (A) Since first flight of the MLG on an airplane. (B) Since first flight after a MLG overhaul. (ii) Within 16 months after the effective date of this AD. (4) For airplanes identified in paragraph (g)(2) of this AD having a MLG P/N 10–210 series: Before the accumulation of 126 months since first flight of the MLG on an airplane. (i) Optional Overhaul For the purposes of this AD, accomplishment of a MLG overhaul is acceptable instead of an inspection required by paragraph (g) of this AD. The inspections required by paragraph (g) of this AD are not terminated by a MLG overhaul, but are required at the next applicable compliance time required by paragraph (g) of this AD. (j) Service Information Exception If the applicable service information specified in paragraph (g) of this AD specifies to contact Messier-Dowty for instructions, or if any repair required by paragraph (g) of this AD is beyond the maximum repair allowance specified in the applicable service information specified in paragraph (g) of this AD: Before further flight, repair 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). (k) MLG Modification For airplanes equipped with a MLG having P/N 201252 series or a MLG having P/N 201490 series: Before the accumulation of 126 months since first flight of the MLG on an airplane or since first flight on an airplane after the most recent overhaul as of the E:\FR\FM\06JYR1.SGM 06JYR1 Federal Register / Vol. 82, No. 128 / Thursday, July 6, 2017 / Rules and Regulations effective date of this AD, as applicable, replace that MLG with a MLG having P/N 201252 series or a MLG having P/N 201490 series that has an improved bogie beam, as defined in Airbus Service Bulletin A330–32– 3275, dated December 23, 2015; or Airbus Service Bulletin A340–32–4305, dated December 23, 2015; as applicable; and in accordance with the Accomplishment Instructions of Messier-Bugatti-Dowty Service Bulletin A33/34–32–306, Revision 1, including Appendix A, dated May 31, 2016. (l) Terminating Action Limitation Accomplishment of corrective actions required by paragraph (g) of this AD does not constitute terminating action for the repetitive inspections required by this AD. jstallworth on DSK7TPTVN1PROD with RULES (m) Terminating Action for Certain Airplanes (1) For airplanes with any MLG having P/ N 10–210 series: Modification of the bogie beam of each MLG having P/N 10–210 series, as specified in Airbus Service Bulletin A330– 32–3268, Revision 01, dated September 21, 2015; or Airbus Service Bulletin A340–32– 4300, dated April 20, 2015; or Revision 01, dated September 21, 2015; as applicable; and in accordance with the Accomplishment Instructions of Messier-Bugatti-Dowty Service Bulletin A33/34–32–305, including Appendix A, dated April 13, 2015; constitutes terminating action for the repetitive inspection requirements of this AD for that airplane, provided that, following inservice modification, the airplane remains in the post-service bulletin configuration. (2) For airplanes with any MLG having P/ N 201252 series or P/N 201490 series: Installation of both left-hand and right-hand MLG having P/N 201252 series or P/N 201490 series that has an improved bogie beam, as required by paragraph (k) of this AD, constitutes terminating action for the repetitive inspections requirements of this AD for that airplane, provided that, following in-service modification, the airplane remains in the post-service bulletin configuration. (n) Parts Installation Prohibition Do not install on any airplane a pre-Airbus modification MLG having P/N 201252 series or a pre-Airbus modification MLG having P/ N 201490 series, as specified in paragraph (n)(1) or (n)(2) of this AD, as applicable; or a pre-Airbus modification MLG having P/N 10–210 series, as specified in paragraph (n)(3) or (n)(4) of this AD, as applicable. (1) For any airplane that is in a post-Airbus Modification 205289 configuration, or on which the modification required by paragraph (k) of this AD has been done: From the effective date of this AD. (2) For any airplane that is in a pre-Airbus Modification 205289 configuration, or on which the modification required by paragraph (k) of this AD has not been done: After modification of that airplane, as required by paragraph (k) of this AD. (3) For any airplane that is in post-Airbus Modification 204421 configuration, or on which the modification specified in paragraph (m)(1) of this AD has been done: From the effective date of this AD. (4) For an airplane that is in pre-Airbus Modification 204421, or on which the VerDate Sep<11>2014 14:53 Jul 05, 2017 Jkt 241001 modification specified in paragraph (m)(1) of this AD has not been done: After modification of that airplane, as specified in paragraph (m)(1) of this AD. (o) Credit for Previous Actions (1) This paragraph provides credit for the actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using the service information identified in paragraphs (o)(1)(i) through (o)(1)(vii) or (o)(2) of this AD, as applicable. (i) Airbus Service Bulletin A330–32–3248, dated October 5, 2011, which is not incorporated by reference in this AD. (ii) Airbus Service Bulletin A330–32–3248, Revision 01, including Appendix 01, dated December 13, 2012, which was incorporated by reference in AD 2013–10–03. (iii) Airbus Service Bulletin A330–32– 3248, Revision 02, dated April 16, 2014, which is not incorporated by reference in this AD. (iv) Airbus Service Bulletin A330–32– 3248, Revision 03, dated November 27, 2014, which is not incorporated by reference in this AD. (v) Airbus Service Bulletin A330–32–3248, Revision 04, dated January 5, 2016, which is not incorporated by reference in this AD. (vi) Airbus Service Bulletin A340–32– 4286, dated October 5, 2011, which was incorporated by reference in AD 2013–10–03. (vii) Airbus Service Bulletin A340–32– 4286, Revision 01, dated November 27, 2014, which is not incorporated by reference in this AD. (2) This paragraph provides credit for the actions required by paragraph (k) of this AD, if those actions were performed before the effective date of this AD using MessierBugatti-Dowty Service Bulletin A33/34–32– 306, dated December 21, 2015, which is not incorporated by reference in this AD. (p) 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 manager of the International Branch, send it to the attention of the person identified in paragraph (q)(2) of this AD. 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. (ii) AMOCs approved previously for AD 2013–10–03 are not approved as AMOCs with 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 PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 31249 accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): Except as required by paragraph (j) of this AD: If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (q) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2016–0108, dated June 8, 2016, for related information. This MCAI may be found in the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016–3984. (2) For more information about this AD, contact Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; fax 425–227–1149. (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (r)(3), (r)(4), and (r)(5) of this AD. (r) 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. (i) Airbus Service Bulletin A330–32–3248, Revision 05, including Appendix 1, dated May 4, 2016. (ii) Airbus Service Bulletin A330–32–3268, Revision 01, dated September 21, 2015. (iii) Airbus Service Bulletin A330–32– 3275, dated December 23, 2015. (iv) Airbus Service Bulletin A340–32– 4286, Revision 02, including Appendix 1, dated January 5, 2016. (v) Airbus Service Bulletin A340–32–4300, dated April 20, 2015. (vi) Airbus Service Bulletin A340–32– 4300, Revision 01, dated September 21, 2015. (vii) Airbus Service Bulletin A340–32– 4305, dated December 23, 2015. (viii) Messier Bugatti Dowty Service Bulletin A33/34–32–305, including Appendix A, dated April 13, 2015. (ix) Messier Bugatti Dowty Service Bulletin A33/34–32–306, Revision 1, including Appendix A, dated May 31, 2016. (3) For Airbus service information identified in this AD, contact Airbus SAS, E:\FR\FM\06JYR1.SGM 06JYR1 31250 Federal Register / Vol. 82, No. 128 / Thursday, July 6, 2017 / Rules and Regulations Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 45 80; email: airworthiness.A330-A340@airbus.com; Internet http://www.airbus.com. (4) For Messier-Bugatti-Dowty service information identified in this final rule, contact Messier Services Americas, Customer Support Center, 45360 Severn Way, Sterling, VA 20166–8910; phone: 703–450–8233; fax: 703–404–1621; Internet: https:// techpubs.services/messier-dowty.com. (5) 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. (6) 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 June 23, 2017. Chris Spangenberg, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–13949 Filed 7–5–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0125; Directorate Identifier 2016–NM–193–AD; Amendment 39–18946; AD 2017–14–02] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc., Airplanes For service information identified in this final rule, contact Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416–375–4000; fax 416–375– 4539; email thd.qseries@ 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–2017– 0125. ADDRESSES: Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0125; 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 Office (telephone 800–647– 5527) is 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 20590. FOR FURTHER INFORMATION CONTACT: Cesar Gomez, Aerospace Engineer, Airframe and Mechanical Systems Branch, ANE–171, FAA, New York Aircraft Certification Office (ACO), 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone: 516–228–7318; fax: 516–794–5531. SUPPLEMENTARY INFORMATION: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. Discussion We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model DHC–8–401 and DHC–8–402 airplanes. This AD was prompted by a report that a pilot was unable to move the rudder pedal due to an obstruction. This AD requires an inspection to determine if wiring shrouds are present, and modifying the wiring shrouds if necessary. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective August 10, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of August 10, 2017. We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Bombardier, Inc., Model DHC–8–401 and DHC–8–402 airplanes. The NPRM published in the Federal Register on March 2, 2017 (82 FR 12301). The NPRM was prompted by a report that a pilot was unable to move the rudder pedal due to an obstruction. The NPRM proposed to require an inspection to determine if wiring shrouds are present, and modifying the wiring shrouds if necessary. We are issuing this AD to prevent an obstruction that could prevent rudder pedal movement during critical phases of flight or ground operations, AGENCY: jstallworth on DSK7TPTVN1PROD with RULES SUMMARY: VerDate Sep<11>2014 14:53 Jul 05, 2017 Jkt 241001 PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 potentially resulting in loss of control of the airplane. Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian AD CF–2016–27, dated September 14, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Bombardier, Inc., Model DHC–8–401 and DHC–8–402 airplanes. The MCAI states: An operator reported that the flying pilot was unable to move the rudder pedal due to an obstruction caused by the non-flying pilot’s foot. The shoe belonging to the nonflying pilot was placed between the rudder pedal and the newly installed wiring shroud and prevented rudder pedal movement. The wiring shroud was installed to support the wire harnesses installed below the cockpit instrument panel. If not corrected, this condition could prevent rudder movement during critical phases of flight or ground operation, and result in loss of control of the aeroplane. This [Canadian] AD was issued to re-work the wiring shrouds to eliminate potential for obstruction. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0125. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA’s response to each comment. Support for the NPRM The Air Line Pilots Association, International, stated that it supports the NPRM. Request To Refer to Updated Service Information and Provide Credit Horizon Air requested that we revise the proposed AD to refer to the newest version of the service information, Bombardier Service Bulletin 84–25–169, Revision B, dated February 17, 2017. Horizon Air also asked that we provide credit for previous actions done using Bombardier Service Bulletin 84–25–169, Revision A, dated April 25, 2016. We agree with the commenter’s requests. We have determined that the new service information does not require any additional actions for airplanes modified using Revision A. We have revised this AD to refer to Bombardier Service Bulletin 84–25–169, Revision B, dated February 17, 2017. We have also added paragraph (h) to this AD to provide credit for previous actions and redesignated subsequent paragraphs accordingly. E:\FR\FM\06JYR1.SGM 06JYR1

Agencies

[Federal Register Volume 82, Number 128 (Thursday, July 6, 2017)]
[Rules and Regulations]
[Pages 31245-31250]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-13949]


=======================================================================
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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-3984; Directorate Identifier 2014-NM-119-AD; 
Amendment 39-18945; AD 2017-14-01]
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) 2013-10-03, 
which applied to all Airbus Model A330-200, -200 Freighter, and -300 
series airplanes; and Model A340-200, -300, -500, and -600 series 
airplanes. AD 2013-10-03 required one-time inspections for deformation 
and damage of the bogie beams of the main landing gear (MLG); 
repetitive inspections for damage and corrosion of the sliding piston 
sub-assembly on certain airplanes; and related investigative and 
corrective actions if necessary. This new AD removes Model A340-500 and 
600 series airplanes from the applicability; removes certain one-time 
inspections of the MLG bogie beams and the sliding piston sub-assembly; 
revises certain compliance times; and requires replacement of certain 
MLGs with MLGs having an improved bogie beam, which constitutes 
terminating action for the repetitive inspections on the modified MLG. 
This AD was prompted by reports of corroded and cracked bogie beams 
under the bogie stop pad. We are issuing this AD to address the unsafe 
condition on these products.

DATES: This AD is effective August 10, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of August 10, 
2017.

ADDRESSES: For Airbus service information identified in this final 
rule, contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point 
Maurice

[[Page 31246]]

Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; 
fax: +33 5 61 93 45 80; email: airworthiness.A330-A340@airbus.com; 
Internet http://www.airbus.com.
    For Messier-Bugatti-Dowty service information identified in this 
final rule, contact Messier Services Americas, Customer Support Center, 
45360 Severn Way, Sterling, VA 20166-8910; phone: 703-450-8233; fax: 
703-404-1621; Internet: https://techpubs.services/messier-dowty.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-2016-
3984.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
3984; 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 address for the Docket Office (telephone 800-
647-5527) is 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 20590.

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

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a supplemental notice of proposed rulemaking (SNPRM) to 
amend 14 CFR part 39 to supersede AD 2013-10-03, Amendment 39-17456 (78 
FR 31386, May 24, 2013) (``AD 2013-10-03''). AD 2013-10-03 applied to 
all Airbus Model A330-200, -200 Freighter, and -300 series airplanes; 
and Model A340-200, -300, -500, and -600 series airplanes. The SNPRM 
published in the Federal Register on March 22, 2017 (82 FR 14642) 
(``the SNPRM''). We preceded the SNPRM with a notice of proposed 
rulemaking (NPRM) that published in the Federal Register on March 1, 
2016 (81 FR 10540) (``the NPRM''). The NPRM was prompted by reports of 
corroded and cracked bogie beams under the bogie stop pad. The NPRM 
proposed to remove Model A340-500, and -600 series airplanes from the 
applicability, remove certain one-time inspections of the MLG bogie 
beams and the sliding piston sub-assembly; revise certain compliance 
times and provide, for certain airplanes, an optional terminating 
action for the repetitive actions. The SNPRM proposed to require 
replacement of a MLG having part number (P/N) 201252 series and P/N 
201490 series with a MLG that has an improved bogie beam, which would 
constitute terminating action for the repetitive inspections on the 
modified MLG. We are issuing this AD to detect and correct damage or 
corrosion under the bogie stop pad of both MLG bogie beams; this 
condition could result in a damaged bogie beam and consequent 
detachment of the beam from the airplane, collapse of the MLG, or 
departure of the airplane from the runway, possibly resulting in damage 
to the airplane and injury to occupants.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2016-0108, dated June 8, 2016 (referred to after this as the Mandatory 
Continuing Airworthiness Information, or ``the MCAI''), to correct an 
unsafe condition for certain Airbus Model A330-200, -200 Freighter, and 
-300 series airplanes; and Model A340-200 and -300 series airplanes. 
The MCAI states:

    During a scheduled maintenance inspection on the Main Landing 
Gear (MLG), the bogie stop pad was found deformed and cracked. Upon 
removal of the bogie stop pad for replacement, the bogie beam was 
also found cracked. The results of a laboratory investigation 
indicated that an overload event had occurred and no fatigue 
propagation of the crack was evident. A second bogie beam crack was 
subsequently found on another aeroplane, located under a bogie stop 
pad which only had superficial paint damage.
    This condition, if not detected and corrected, could lead to 
landing gear bogie detachment from the aeroplane, or landing gear 
collapse, or a runway excursion, possibly resulting in damage to the 
aeroplane and injury to the occupants and/or people on the ground.
    To address this potential unsafe condition, EASA issued AD 2008-
0223 [which corresponds to FAA AD 2010-02-10, Amendment 39-16181 (75 
FR 4477, January 28, 2010)] to require accomplishment of a one-time 
detailed inspection under the bogie stop pad of both MLG bogie 
beams. As a result of the one-time inspection required by that 
[EASA] AD, numerous bogie stop pad were found corroded and a few 
cracked. The one-time inspection was retained in EASA AD 2011-0211 
[which corresponds to FAA AD 2013-10-03], which superseded EASA AD 
2008-0223, which also introduced repetitive inspections, except for 
A340-500/-600 aeroplanes.
    After EASA AD 2011-0211 was issued, further investigation led to 
the conclusion that the one-time inspection was no longer necessary 
and only the repetitive inspections should remain. In addition, it 
was determined that repetitive inspections were also necessary for 
MLG on A340-500/-600 aeroplanes.
    Prompted by these conclusions, EASA issued AD 2014-0120, 
partially retaining the requirements of EASA AD 2011-0211, which was 
superseded, and introducing repetitive detailed inspections of the 
MLG on A340-500 and A340-600 aeroplanes. Subsequently, further 
analysis indicated that repetitive inspections of the MLG on A340-
500/-600 aeroplanes were not necessary after all. In addition, the 
threshold for the inspection of MLG P/N 10-210 series was raised 
from 24 to 126 months, and Airbus developed a modification of the 
MLG P/N 10-210 series which provides an (optional) terminating 
action for the repetitive inspections.
    Consequently, EASA AD 2014-0120 was revised to delete the 
requirements for A340-500/-600 aeroplanes, to amend the inspection 
threshold for MLG P/N 10-210 series, and to introduce an optional 
terminating action for aeroplanes with MLG P/N 10-210 series.
    Since EASA AD 2014-0120R1 was issued, Airbus developed a 
modification (mod 205289) of the MLG P/N 201252 series and P/N 
201490 series that must be embodied in service with Airbus SB A330-
32-3275 or SB A340-32-4305. It was also identified that A340-500/-
600 aeroplanes could be removed from the applicability of this 
[EASA] AD as no more actions were required on these aeroplanes.
    For the reason described above, this [EASA] AD retains the 
requirements of EASA AD 2014-0120R1, which is superseded, removes 
the A340-500/-600 aeroplanes from the Applicability and requires the 
modification of the MLG P/N 201252 series and P/N 201490 series, 
which constitutes terminating action for the repetitive inspections 
required by this [EASA] AD.

The required actions include repetitive detailed inspections for damage 
and corrosion of the sliding piston sub-assembly, and related 
investigative and corrective actions if necessary. Related 
investigative actions include a test for indications of corrosion and 
damage to the bogie assembly base material, and a magnetic particle 
inspection for cracks, corrosion, and damage of the bogie beam. 
Corrective actions include repairing affected parts.
    The required terminating action (for a MLG having P/N 201252 series 
or P/N 201490 series) and the optional terminating action (for a MLG 
having P/N 10-210 series) are modifications of the bogie beam of a MLG, 
which consist of installing a nickel under chrome

[[Page 31247]]

coating, a new bogie beam stop pad, and new stop pad brackets.
    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
3984.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comment received. Air Line Pilots 
Association, International supported the SNPRM.

Conclusion

    We reviewed the available data, including the comment received, and 
determined that air safety and the public interest require adopting 
this AD as proposed except for minor editorial changes. We have 
determined that these minor changes:
     Are consistent with the intent that was proposed in the 
SNPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the SNPRM.

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information.
     Airbus Service Bulletin A330-32-3248, Revision 05, 
including Appendix 1, dated May 4, 2016; and Airbus Service Bulletin 
A340-32-4286, Revision 02, including Appendix 1, dated January 5, 2016; 
which describe procedures for doing an inspection for damage and 
corrosion of the MLG sliding piston sub-assembly, bogie beam stop pad 
and the bogie beam under the stop pad, and related investigative and 
corrective actions. These documents are distinct since they apply to 
different airplane models.
     Airbus Service Bulletin A330-32-3268, Revision 01, dated 
September 21, 2015, which describes procedures for modification of the 
bogie beam of a MLG having P/N 10-210 series on Model A330 airplanes 
that includes installing a nickel under chrome coating, a new bogie 
beam stop pad, and new stop pad brackets.
     Airbus Service Bulletin A330-32-3275, dated December 23, 
2015, which describes procedures for modification of the bogie beam of 
a MLG having P/N 201252 series or P/N 201490 series on Model A330 
airplanes that includes installing a nickel under chrome coating, a new 
bogie beam stop pad, and new stop pad brackets.
     Airbus Service Bulletin A340-32-4300, dated April 20, 
2015; and Revision 01, dated September 21, 2015; which describe 
procedures for modification of the bogie beam of a MLG having P/N 10-
210 series on Model A340 airplanes that include installing a nickel 
under chrome coating, a new bogie beam stop pad, and new stop pad 
brackets. These service bulletins are distinct due to editorial 
revisions.
     Airbus Service Bulletin A340-32-4305, dated December 23, 
2015, which describes procedures for modification of the bogie beam of 
a MLG having P/N 201252 series or P/N 201490 series on Model A340 
airplanes that includes installing a nickel under chrome coating, a new 
bogie beam stop pad, and new stop pad brackets.
    Messier-Bugatti-Dowty has issued the following service information.
     Messier-Bugatti-Dowty Service Bulletin A33/34-32-305, 
including Appendix A, dated April 13, 2015, which describes procedures 
for modification of the bogie beam of a MLG having MLG P/N 10-210 
series that includes installing a nickel under chrome coating, a new 
bogie beam stop pad, and new stop pad brackets.
     Messier-Bugatti-Dowty Service Bulletin A33/34-32-306, 
Revision 1, including Appendix A, dated May 31, 2016, which describes 
procedures for modification of the bogie beam of a MLG having P/N 
201252 series or P/N 201490 series that includes installing a nickel 
under chrome coating, a new bogie beam stop pad, and new stop pad 
brackets.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

Costs of Compliance

    We estimate that this AD affects 89 Model A330-200, -200 Freighter, 
and -300 series airplanes of U.S. registry.
    We estimate that it will take about 13 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 $98,345, or $1,105 per product.
    Currently, there are no Model A340-200 or -300 series airplanes on 
the U.S. Register. However, if an affected airplane is imported and 
placed on the U.S. Register in the future, it would be subject to the 
same per-airplane cost specified above for the Model A330-200, -200 
Freighter, and -300 series airplanes.
    In addition, we estimate that any necessary follow-on actions will 
take about 24 work-hours and require parts costing $78, for a cost of 
$2,118 per product. We have no way of determining the number of 
aircraft that might need these actions.
    According to the manufacturer, all of the parts costs of the 
optional terminating action specified in 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. We have received no 
definitive data that would enable us to provide the work-hour cost 
estimates for the optional terminating action specified in this AD.

Authority for This Rulemaking

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

Regulatory Findings

    We determined that this AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

[[Page 31248]]

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]

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2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2013-10-03, Amendment 39-17456 (78 FR 31386, May 24, 2013), and adding 
the following new AD:

2017-14-01 Airbus: Amendment 39-18945; Docket No. FAA-2016-3984; 
Directorate Identifier 2014-NM-119-AD.

(a) Effective Date

    This AD is effective August 10, 2017.

(b) Affected ADs

    This AD replaces AD 2013-10-03, Amendment 39-17456 (78 FR 31386, 
May 24, 2013) (``AD 2013-10-03'').

(c) Applicability

    This AD applies to Airbus airplanes identified in paragraphs 
(c)(1) and (c)(2) of this AD, certificated in any category, all 
serial numbers, except those airplanes that have embodied Airbus 
Modification 204421 or Airbus Modification 205289 in production.
    (1) Model A330-201, -202, -203, -223, -223F, -243, -243F, -301, 
-302, -303, -321, -322, -323, -341, -342, and -343 airplanes.
    (2) Model A340-211, -212, -213, -311, -312, and -313 airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by reports of corroded and cracked bogie 
beams under the bogie stop pad. We are issuing this AD to detect and 
correct damage or corrosion under the bogie stop pad of both main 
landing gear (MLG) bogie beams; this condition could result in a 
damaged bogie beam and consequent detachment of the beam from the 
airplane, collapse of the MLG, or departure of the airplane from the 
runway, possibly resulting in damage to the airplane and injury to 
occupants.

(f) Compliance

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

(g) Repetitive Inspections, Related Investigative Actions, and 
Corrective Actions

    For Model A330-200, -200 Freighter, and -300 series airplanes; 
and Model A340-200 and -300 series airplanes; equipped with a MLG 
having part number (P/N) 201252 series, P/N 201490 series, or P/N 
10-210 series: Do the applicable actions required by paragraph 
(g)(1) or (g)(2) of this AD.
    (1) For airplanes equipped, as of the effective date of this AD, 
with a MLG that has been previously inspected, as specified in 
Airbus Service Bulletin A330-32-3220, Airbus Service Bulletin A330-
32-3248, Airbus Service Bulletin A340-32-4264, or Airbus Service 
Bulletin A340-32-4286, as applicable: At the applicable times 
specified in paragraphs (h)(1) and (h)(2) of this AD, do a detailed 
inspection for damage (e.g., cracking and fretting) and corrosion of 
the MLG sliding piston sub-assembly, bogie beam stop pad, and the 
bogie beam under the stop pad; and do all applicable related 
investigative and corrective actions; in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A330-32-3248, 
Revision 05, including Appendix 1, dated May 4, 2016; or Airbus 
Service Bulletin A340-32-4286, Revision 02, including Appendix 1, 
dated January 5, 2016; as applicable; except as required by 
paragraph (j) of this AD. Do all applicable related investigative 
and corrective actions before further flight. Repeat the inspection 
of the MLG sliding piston sub-assembly, bogie beam stop pad, and the 
bogie beam under the stop pad, thereafter, at intervals not to 
exceed 2,500 flight cycles or 24 months, whichever occurs first.
    (2) For airplanes equipped, as of the effective date of this AD, 
with a MLG that has not been previously inspected, as specified in 
Airbus Service Bulletin A330-32-3220, Airbus Service Bulletin A330-
32-3248, Airbus Service Bulletin A340-32-4264, or Airbus Service 
Bulletin A340-32-4286, as applicable: At the applicable times 
specified in paragraphs (h)(3) and (h)(4) of this AD, do a detailed 
inspection for damage (e.g., cracking and fretting) and corrosion of 
the MLG sliding piston sub-assembly, bogie beam stop pad, and the 
bogie beam under the stop pad; and do all applicable related 
investigative and corrective actions; in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A330-32-3248, 
Revision 05, including Appendix 1, dated May 4, 2016; or Airbus 
Service Bulletin A340-32-4286, Revision 02, including Appendix 1, 
dated January 5, 2016; as applicable; except as required by 
paragraph (j) of this AD. Do all applicable related investigative 
and corrective actions before further flight. Repeat the inspection 
of the MLG sliding piston sub-assembly, bogie beam stop pad, and the 
bogie beam under the stop pad, thereafter, at intervals not to 
exceed 2,500 flight cycles or 24 months, whichever occurs first.

(h) Compliance Times for the Actions Required by Paragraph (g) of This 
AD

    Do the applicable actions required by paragraph (g) of this AD 
at the applicable time specified in paragraph (h)(1), (h)(2), 
(h)(3), or (h)(4) of this AD.
    (1) For airplanes identified in paragraph (g)(1) of this AD 
having a MLG P/N 201252 series or P/N 201490 series: Before the 
accumulation of 2,500 total flight cycles or 24 months, whichever 
occurs first since the later of the times specified in paragraphs 
(h)(1)(i) and (h)(1)(ii) of this AD.
    (i) Since first flight after a MLG overhaul.
    (ii) Since first flight after the most recent accomplishment of 
an inspection of the MLG, as specified in Airbus Service Bulletin 
A330-32-3220, Airbus Service Bulletin A330-32-3248, Airbus Service 
Bulletin A340-32-4264, or Airbus Service Bulletin A340-32-4286, as 
applicable.
    (2) For airplanes identified in paragraph (g)(1) of this AD 
having a MLG P/N 10-210 series: Before the accumulation of 126 
months since first flight of the MLG on an airplane or since first 
flight on an airplane after the most recent inspection of the MLG, 
as specified in Airbus Service Bulletin A330-32-3248, or Airbus 
Service Bulletin A340-32-4286, as applicable.
    (3) For airplanes identified in paragraph (g)(2) of this AD 
having a MLG P/N 201252 series or P/N 201490 series: At the later of 
the times specified in paragraphs (h)(3)(i) and (h)(3)(ii) of this 
AD.
    (i) Before the accumulation of 2,500 total flight cycles or 24 
months, whichever occurs first since the later of the times 
specified in paragraphs (h)(3)(i)(A) and (h)(3)(i)(B) of this AD.
    (A) Since first flight of the MLG on an airplane.
    (B) Since first flight after a MLG overhaul.
    (ii) Within 16 months after the effective date of this AD.
    (4) For airplanes identified in paragraph (g)(2) of this AD 
having a MLG P/N 10-210 series: Before the accumulation of 126 
months since first flight of the MLG on an airplane.

(i) Optional Overhaul

    For the purposes of this AD, accomplishment of a MLG overhaul is 
acceptable instead of an inspection required by paragraph (g) of 
this AD. The inspections required by paragraph (g) of this AD are 
not terminated by a MLG overhaul, but are required at the next 
applicable compliance time required by paragraph (g) of this AD.

(j) Service Information Exception

    If the applicable service information specified in paragraph (g) 
of this AD specifies to contact Messier-Dowty for instructions, or 
if any repair required by paragraph (g) of this AD is beyond the 
maximum repair allowance specified in the applicable service 
information specified in paragraph (g) of this AD: Before further 
flight, repair 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).

(k) MLG Modification

    For airplanes equipped with a MLG having P/N 201252 series or a 
MLG having P/N 201490 series: Before the accumulation of 126 months 
since first flight of the MLG on an airplane or since first flight 
on an airplane after the most recent overhaul as of the

[[Page 31249]]

effective date of this AD, as applicable, replace that MLG with a 
MLG having P/N 201252 series or a MLG having P/N 201490 series that 
has an improved bogie beam, as defined in Airbus Service Bulletin 
A330-32-3275, dated December 23, 2015; or Airbus Service Bulletin 
A340-32-4305, dated December 23, 2015; as applicable; and in 
accordance with the Accomplishment Instructions of Messier-Bugatti-
Dowty Service Bulletin A33/34-32-306, Revision 1, including Appendix 
A, dated May 31, 2016.

(l) Terminating Action Limitation

    Accomplishment of corrective actions required by paragraph (g) 
of this AD does not constitute terminating action for the repetitive 
inspections required by this AD.

(m) Terminating Action for Certain Airplanes

    (1) For airplanes with any MLG having P/N 10-210 series: 
Modification of the bogie beam of each MLG having P/N 10-210 series, 
as specified in Airbus Service Bulletin A330-32-3268, Revision 01, 
dated September 21, 2015; or Airbus Service Bulletin A340-32-4300, 
dated April 20, 2015; or Revision 01, dated September 21, 2015; as 
applicable; and in accordance with the Accomplishment Instructions 
of Messier-Bugatti-Dowty Service Bulletin A33/34-32-305, including 
Appendix A, dated April 13, 2015; constitutes terminating action for 
the repetitive inspection requirements of this AD for that airplane, 
provided that, following in-service modification, the airplane 
remains in the post-service bulletin configuration.
    (2) For airplanes with any MLG having P/N 201252 series or P/N 
201490 series: Installation of both left-hand and right-hand MLG 
having P/N 201252 series or P/N 201490 series that has an improved 
bogie beam, as required by paragraph (k) of this AD, constitutes 
terminating action for the repetitive inspections requirements of 
this AD for that airplane, provided that, following in-service 
modification, the airplane remains in the post-service bulletin 
configuration.

(n) Parts Installation Prohibition

    Do not install on any airplane a pre-Airbus modification MLG 
having P/N 201252 series or a pre-Airbus modification MLG having P/N 
201490 series, as specified in paragraph (n)(1) or (n)(2) of this 
AD, as applicable; or a pre-Airbus modification MLG having P/N 10-
210 series, as specified in paragraph (n)(3) or (n)(4) of this AD, 
as applicable.
    (1) For any airplane that is in a post-Airbus Modification 
205289 configuration, or on which the modification required by 
paragraph (k) of this AD has been done: From the effective date of 
this AD.
    (2) For any airplane that is in a pre-Airbus Modification 205289 
configuration, or on which the modification required by paragraph 
(k) of this AD has not been done: After modification of that 
airplane, as required by paragraph (k) of this AD.
    (3) For any airplane that is in post-Airbus Modification 204421 
configuration, or on which the modification specified in paragraph 
(m)(1) of this AD has been done: From the effective date of this AD.
    (4) For an airplane that is in pre-Airbus Modification 204421, 
or on which the modification specified in paragraph (m)(1) of this 
AD has not been done: After modification of that airplane, as 
specified in paragraph (m)(1) of this AD.

(o) Credit for Previous Actions

    (1) This paragraph provides credit for the actions required by 
paragraph (g) of this AD, if those actions were performed before the 
effective date of this AD using the service information identified 
in paragraphs (o)(1)(i) through (o)(1)(vii) or (o)(2) of this AD, as 
applicable.
    (i) Airbus Service Bulletin A330-32-3248, dated October 5, 2011, 
which is not incorporated by reference in this AD.
    (ii) Airbus Service Bulletin A330-32-3248, Revision 01, 
including Appendix 01, dated December 13, 2012, which was 
incorporated by reference in AD 2013-10-03.
    (iii) Airbus Service Bulletin A330-32-3248, Revision 02, dated 
April 16, 2014, which is not incorporated by reference in this AD.
    (iv) Airbus Service Bulletin A330-32-3248, Revision 03, dated 
November 27, 2014, which is not incorporated by reference in this 
AD.
    (v) Airbus Service Bulletin A330-32-3248, Revision 04, dated 
January 5, 2016, which is not incorporated by reference in this AD.
    (vi) Airbus Service Bulletin A340-32-4286, dated October 5, 
2011, which was incorporated by reference in AD 2013-10-03.
    (vii) Airbus Service Bulletin A340-32-4286, Revision 01, dated 
November 27, 2014, which is not incorporated by reference in this 
AD.
    (2) This paragraph provides credit for the actions required by 
paragraph (k) of this AD, if those actions were performed before the 
effective date of this AD using Messier-Bugatti-Dowty Service 
Bulletin A33/34-32-306, dated December 21, 2015, which is not 
incorporated by reference in this AD.

(p) 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 manager of the International Branch, send it to the 
attention of the person identified in paragraph (q)(2) of this AD. 
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.
    (ii) AMOCs approved previously for AD 2013-10-03 are not 
approved as AMOCs with 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 EASA; or Airbus's EASA DOA. If 
approved by the DOA, the approval must include the DOA-authorized 
signature.
    (3) Required for Compliance (RC): Except as required by 
paragraph (j) of this AD: If any service information contains 
procedures or tests that are identified as RC, those procedures and 
tests must be done to comply with this AD; any procedures or tests 
that are not identified as RC are recommended. Those procedures and 
tests that are not identified as RC may be deviated from using 
accepted methods in accordance with the operator's maintenance or 
inspection program without obtaining approval of an AMOC, provided 
the procedures and tests identified as RC can be done and the 
airplane can be put back in an airworthy condition. Any 
substitutions or changes to procedures or tests identified as RC 
require approval of an AMOC.

(q) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2016-0108, dated June 8, 2016, for related 
information. This MCAI may be found in the AD docket on the Internet 
at http://www.regulations.gov by searching for and locating Docket 
No. FAA-2016-3984.
    (2) For more information about this AD, contact Vladimir 
Ulyanov, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, 
WA 98057-3356; telephone 425-227-1138; fax 425-227-1149.
    (3) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (r)(3), (r)(4), and (r)(5) of this AD.

(r) 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.
    (i) Airbus Service Bulletin A330-32-3248, Revision 05, including 
Appendix 1, dated May 4, 2016.
    (ii) Airbus Service Bulletin A330-32-3268, Revision 01, dated 
September 21, 2015.
    (iii) Airbus Service Bulletin A330-32-3275, dated December 23, 
2015.
    (iv) Airbus Service Bulletin A340-32-4286, Revision 02, 
including Appendix 1, dated January 5, 2016.
    (v) Airbus Service Bulletin A340-32-4300, dated April 20, 2015.
    (vi) Airbus Service Bulletin A340-32-4300, Revision 01, dated 
September 21, 2015.
    (vii) Airbus Service Bulletin A340-32-4305, dated December 23, 
2015.
    (viii) Messier Bugatti Dowty Service Bulletin A33/34-32-305, 
including Appendix A, dated April 13, 2015.
    (ix) Messier Bugatti Dowty Service Bulletin A33/34-32-306, 
Revision 1, including Appendix A, dated May 31, 2016.
    (3) For Airbus service information identified in this AD, 
contact Airbus SAS,

[[Page 31250]]

Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 
93 45 80; email: airworthiness.A330-A340@airbus.com; Internet http://www.airbus.com.
    (4) For Messier-Bugatti-Dowty service information identified in 
this final rule, contact Messier Services Americas, Customer Support 
Center, 45360 Severn Way, Sterling, VA 20166-8910; phone: 703-450-
8233; fax: 703-404-1621; Internet: https://techpubs.services/messier-dowty.com.
    (5) 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.
    (6) 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 June 23, 2017.
Chris Spangenberg,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-13949 Filed 7-5-17; 8:45 am]
 BILLING CODE 4910-13-P