Airworthiness Directives; Airbus Airplanes, 10540-10544 [2016-04290]

Download as PDF 10540 Federal Register / Vol. 81, No. 40 / Tuesday, March 1, 2016 / Proposed Rules Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206– 544–5000, extension 1; fax 206–766–5680; Internet https://www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on February 19, 2016. Dorr M. Anderson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–04292 Filed 2–29–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–3984; Directorate Identifier 2014–NM–119–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede Airworthiness Directive (AD) 2013–10– 03, for 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 currently requires 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. Since we issued AD 2013–10–03, we have determined that certain one-time inspections are no longer necessary, certain compliance times may be extended, and an optional terminating action should be provided. This proposed AD would 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. We are proposing this AD to detect and correct damage or corrosion under the bogie stop pad of both MLG bogie beams, which could result in a damaged bogie beam and consequent detachment of the beam asabaliauskas on DSK5VPTVN1PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 19:05 Feb 29, 2016 Jkt 238001 from the airplane, or collapse of the MLG and departure of the airplane from the runway. DATES: We must receive comments on this proposed AD by April 15, 2016. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Airbus SAS, Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 45 80; email: airworthiness.A330-A340@airbus.com; Internet https://www.airbus.com. You may 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. Examining the AD Docket You may examine the AD docket on the Internet at https:// 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: 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: Comments Invited We invite you to send any written relevant data, views, or arguments about PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2016–3984; Directorate Identifier 2014–NM–119–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion On May 13, 2013, we issued AD 2013–10–03, Amendment 39–17456 (78 FR 31386, May 24, 2013). AD 2013–10– 03 requires actions intended to address an unsafe condition on 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 superseded AD 2010– 02–10, Amendment 39–16181 (75 FR 4477, January 28, 2010)). Since we issued AD 2013–10–03, Amendment 39–17456 (78 FR 31386, May 24, 2013), we have determined that certain one-time inspections are no longer necessary, certain compliance times may be extended, and an optional terminating action should be provided. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2014– 0120R1, dated August 31, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Model A330– 200, –200 Freighter, and –300 series airplanes; and Model A340–200, –300, –500, and –600 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, E:\FR\FM\01MRP1.SGM 01MRP1 asabaliauskas on DSK5VPTVN1PROD with PROPOSALS Federal Register / Vol. 81, No. 40 / Tuesday, March 1, 2016 / Proposed Rules possibly resulting in damage to the aeroplane and injury to the occupants. To address this potential unsafe condition, EASA issued * * * [an earlier AD] 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 [earlier EASA] AD, applicable to A330, A340–200 and A340–300 aeroplanes, numerous bogie stop pad were found corroded and a few cracked. The one-time inspection was retained in EASA AD 2011–0211 [https:// ad.easa.europa.eu/blob/easa_ad_2011_0211_ superseded.pdf/AD_2011-0211_1] [which corresponds to FAA AD 2013–10–03, Amendment 39–17456 (78 FR 31386, May 24, 2013)], which superseded * * * [an earlier EASA AD], applicable to all A330 and A340 aeroplanes, which also introduced repetitive inspections for A330, A340–200 and A340– 300 aeroplanes, but not for the A340–500/600 aeroplanes. Since issuance of EASA AD 2011–0211, further investigation accomplished by Airbus led to the conclusion that the one-time inspection in accordance with Airbus Service Bulletin (SB) A330–32–3220, or Airbus SB A340–32–4264, or Airbus SB A340–32–5087, as applicable, is no longer necessary and, for those aeroplanes, only the inspections (initial and repetitive) in accordance with Airbus SB A330–32–3248 or Airbus SB A340–32–4286, as applicable, must remain. In addition, Airbus also determined that repetitive inspections of the MLG in accordance with Airbus SB A340–32–5112 are necessary for A340–500/-600 aeroplanes. Consequently, EASA issued * * * [another AD], which partially retained the requirements of EASA AD 2011–0211, which was superseded, and introduced repetitive detailed inspections of the MLG for A340– 500 and A340–600 aeroplanes. Since that [EASA] AD was issued, it was determined that repetitive inspections of the MLG are not necessary on the A340–500/-600 aeroplanes and that the threshold for the inspection of MLG P/N 10–210 series can be delayed. In addition, Airbus developed a mod of the MLG P/N 10–210 series that can be embodied both in production through mod 204421 and in service with Airbus SB A330–32–3268 or SB A340–32–4300, as applicable. This modification constitutes a terminating action for the repetitive inspections for aeroplanes equipped with MLG P/N 10–210 series. For the reasons described above, this [EASA] AD is revised and requires inspection of the MLG (with an amended threshold for MLG P/N 10–210 series) and introduces an option to terminate the repetitive inspection with a modification of the MLG P/N 10–210 series. 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 VerDate Sep<11>2014 19:05 Feb 29, 2016 Jkt 238001 particle inspection for cracks, corrosion, and damage of the bogie beam. Corrective actions include repairing affected parts. The optional terminating action modification of the bogie beam of an MLG having P/N 10–210 consists of installing a nickel under chrome 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 https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 3984. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A330–32–3248, Revision 02, dated April 16, 2014. This service information describes procedures for doing a detailed inspection for damage and corrosion of the MLG sliding piston subassembly, bogie beam stop pad and the bogie beam under the stop pad; and related investigative and corrective actions. Airbus has also issued Service Bulletin A330–32–3268 and Airbus Service Bulletin A340–32–4300, both dated April 20, 2015. This service information describes procedures for modification of the bogie beam of an MLG having P/N 10–210, which 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. FAA’s Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of these same type designs. Explanation of ‘‘RC’’ Procedures and Tests in Service Information The FAA worked in conjunction with industry, under the Airworthiness Directive Implementation Aviation Rulemaking Committee (ARC), to enhance the AD system. One enhancement was a new process for PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 10541 annotating which procedures and tests in the service information are required for compliance with an AD. Differentiating these procedures and tests from other tasks in the service information is expected to improve an owner’s/operator’s understanding of crucial AD requirements and help provide consistent judgment in AD compliance. The procedures and tests identified as Required for Compliance (RC) in any service information have a direct effect on detecting, preventing, resolving, or eliminating an identified unsafe condition. As specified in a Note under the Accomplishment Instructions of the specified service information, procedures and tests that are identified as RC in any service information must be done to comply with the proposed AD. However, procedures and 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 alternative method of compliance (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 will require approval of an AMOC. Costs of Compliance We estimate that this proposed AD affects 89 Model A330–200, –200 Freighter, and –300 series airplanes of U.S. registry. We estimate that it would take about 12 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $90,780, or $1,020 per product. Currently, there are no affected 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 perairplane cost specified above for the Model A330–200, –200 Freighter, and –300 series airplanes. In addition, we estimate that any necessary follow-on actions would take about 24 work-hours, and 1 work-hour for reporting, and require parts costing $78, for a cost of $2,203 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 E:\FR\FM\01MRP1.SGM 01MRP1 10542 Federal Register / Vol. 81, No. 40 / Tuesday, March 1, 2016 / Proposed Rules terminating action specified in this proposed AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. 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 proposed AD. asabaliauskas on DSK5VPTVN1PROD with PROPOSALS 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on VerDate Sep<11>2014 19:05 Feb 29, 2016 Jkt 238001 the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 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. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 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: ■ Airbus: Docket No. FAA–2016–3984; Directorate Identifier 2014–NM–119–AD. (a) Comments Due Date We must receive comments by April 15, 2016. (b) Affected ADs This AD replaces AD 2013–10–03, Amendment 39–17456 (78 FR 31386, May 24, 2013). (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 that have embodied Airbus Modification 204421 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, –313 airplanes. (d) Subject Air Transport Association (ATA) of America Code 32, Landing gear. PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 (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, which could result in a damaged bogie beam and consequent detachment of the beam from the airplane, or collapse of the MLG and departure of the airplane from the runway. (f) Compliance 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, Model A330–200 Freighter, and Model A330–300 series airplanes; and Model A340–200, and –300 series airplanes; equipped with a MLG having part number (P/N) 201252 series, or 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 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 subassembly, 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 02, dated April 16, 2014; or Airbus Service Bulletin A340–32–4286, dated October 5, 2011; 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 02, dated April 16, 2014; or Airbus Service Bulletin A340–32–4286, dated October 5, 2011; as applicable, except E:\FR\FM\01MRP1.SGM 01MRP1 Federal Register / Vol. 81, No. 40 / Tuesday, March 1, 2016 / Proposed Rules 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. asabaliauskas on DSK5VPTVN1PROD with PROPOSALS (h) Compliance Times for Paragraph (g) of This AD Actions 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 an MLG P/N 201252 series and 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 A340–32–4286; or Airbus Service Bulletin A340–32–4264; as applicable. (2) For airplanes identified in paragraph (g)(1) of this AD having an 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, Revision 01, dated December 13, 2012; or Airbus Service Bulletin A330–32– 3248, Revision 02, dated April 16, 2014; or Airbus Service Bulletin A340–32–4286, dated October 5, 2011; as applicable. (3) For airplanes identified in paragraph (g)(2) of this AD having an MLG P/N 201252 series and 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 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 an 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 an 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 VerDate Sep<11>2014 19:05 Feb 29, 2016 Jkt 238001 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) Reporting Requirement After accomplishing any of the corrective actions required by paragraph (g) of this AD or any repair required by paragraph (j) of this AD: Report the results of the corrective actions or repair to Airbus, Customer Services Directorate, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex France; Attn: SDC32 Technical Data and Documentation Services; fax: +33 5 61 93 28 06; email: sb.reporting@airbus.com, at the applicable time specified in paragraph (k)(1) or (k)(2) of this AD. (1) If the corrective action or repair was done on or after the effective date of this AD: Submit the report within 90 days after doing corrective action or repair. (2) If the corrective action or repair was done prior to the effective date of this AD: Submit the report within 90 days after the effective date of this AD. (l) Terminating Action Limitation Accomplishment of corrective actions as required by paragraph (g) of this AD does not constitute terminating action for the repetitive inspections required by this AD. (m) Optional Terminating Action for Certain Airplanes For airplanes with any MLG having P/N 10–210 series: Modification on an airplane of the bogie beam of each MLG having P/N 10– 210 series as specified in the Accomplishment Instructions of Airbus Service Bulletin A330–32–3268, dated April 20, 2015; or Airbus Service Bulletin A340– 32–4300, dated April 20, 2015; as applicable; constitutes terminating action for the requirements of this AD for that airplane, provided that, following in-service modification, the airplane remains in postservice bulletin configuration. (n) Credit for Previous Actions 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 paragraph (n)(1), (n)(2), or (n)(3), (n)(4), or (n)(5) of this AD. (1) Airbus Service Bulletin A330–32–3248, dated October 5, 2011, which is not incorporated by reference in this AD. (2) 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, Amendment 39–17456 (78 FR 31386, May 24, 2013). (3) Airbus Service Bulletin A330–32–3220, dated October 10, 2008, which was incorporated by reference in AD 2010–02–10, Amendment 39–16181 (75 FR 4477, January 28, 2010). PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 10543 (4) Airbus Service Bulletin A330–32–3220, Revision 01, dated October 5, 2011, which was incorporated by reference in AD 2013– 10–03, Amendment 39–17456 (78 FR 31386, May 24, 2013). (5) Airbus Service Bulletin A330–32–3220, Revision 02, dated December 13, 2012, which was incorporated by reference in AD 2013– 10–03, Amendment 39–17456 (78 FR 31386, May 24, 2013). (o) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone: 425–227–1138; fax: 425–227– 1149. Information may be emailed to: 9ANM-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 2013–10–03, Amendment 39–17456 (78 FR 31386, May 24, 2013), 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. (4) 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 E:\FR\FM\01MRP1.SGM 01MRP1 10544 Federal Register / Vol. 81, No. 40 / Tuesday, March 1, 2016 / Proposed Rules 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. (p) Special Flight Permits Special flight permits, as described in Section 21.197 and Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199), are not allowed if any crack is found during any inspection required by this AD. (q) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2014–0120R1, dated August 31, 2015, for related information. This MCAI may be found in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2016–3984. (2) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 45 80; email: airworthiness.A330-A340@airbus.com; Internet https://www.airbus.com. You may 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. Issued in Renton, Washington, on February 19, 2016. Dorr M. Anderson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–04290 Filed 2–29–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–2859; Directorate Identifier 2016–NE–04–AD] asabaliauskas on DSK5VPTVN1PROD with PROPOSALS RIN 2120–AA64 Airworthiness Directives; Turbomeca S.A. Turboshaft Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for all SUMMARY: VerDate Sep<11>2014 19:05 Feb 29, 2016 Jkt 238001 Turbomeca S.A. Arriel 1D and 1D1 turboshaft engines with a premodification (mod) TU357 gas generator module (M03), installed. This proposed AD was prompted by reports of divergent rubbing between the piston shaft small diameter labyrinth and the rear bearing support. This proposed AD would require removing the premodification (mod) TU357 gas generator module (M03) and replacing with a part eligible for installation. We are proposing this AD to prevent failure of the labyrinth seal and engine, in-flight shutdown, and loss of control of the helicopter. We must receive comments on this proposed AD by May 2, 2016. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Mail: Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. • Fax: 202–493–2251. For service information identified in this NPRM, contact Turbomeca S.A., 40220 Tarnos, France; phone: 33 (0)5 59 74 40 00; fax: 33 (0)5 59 74 45 15. You may view this service information at the FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA. For information on the availability of this material at the FAA, call 781–238– 7125. DATES: Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 2859; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the mandatory continuing airworthiness information (MCAI), the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Philip Haberlen, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 781–238–7770; fax: 781–238–7199; email: philip.haberlen@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this NPRM. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2016–2859; Directorate Identifier 2016– NE–04–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this NPRM. We will consider all comments received by the closing date and may amend this NPRM based on those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this NPRM. Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA AD 2016– 0009, dated January 13, 2016 (referred to hereinafter as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: Some cases of divergent rubbing between the piston shaft small diameter labyrinth and the rear bearing support have been reported. This condition, if not corrected, could lead to an uncommanded engine in-flight shutdown. You may obtain further information by examining the MCAI in the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 2859. Related Service Information Turbomeca S.A. has issued Mandatory Service Bulletin (MSB) No. 292 72 1357, Version B, dated November 12, 2015. The MSB describes procedures for installing a postmodification (mod) TU357 gas generator module (M03). 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 of this NPRM. FAA’s Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of France, and is approved for operation in the United States. Pursuant to our bilateral E:\FR\FM\01MRP1.SGM 01MRP1

Agencies

[Federal Register Volume 81, Number 40 (Tuesday, March 1, 2016)]
[Proposed Rules]
[Pages 10540-10544]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-04290]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-3984; Directorate Identifier 2014-NM-119-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede Airworthiness Directive (AD) 2013-10-
03, for 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 currently requires 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. Since we issued AD 2013-10-03, we have 
determined that certain one-time inspections are no longer necessary, 
certain compliance times may be extended, and an optional terminating 
action should be provided. This proposed AD would 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. 
We are proposing this AD to detect and correct damage or corrosion 
under the bogie stop pad of both MLG bogie beams, which could result in 
a damaged bogie beam and consequent detachment of the beam from the 
airplane, or collapse of the MLG and departure of the airplane from the 
runway.

DATES: We must receive comments on this proposed AD by April 15, 2016.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this NPRM, contact Airbus 
SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 
45 80; email: airworthiness.A330-A340@airbus.com; Internet https://www.airbus.com. You may 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.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://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 proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Operations office (telephone: 800-647-5527) is in the ADDRESSES 
section. Comments will be available in the AD docket shortly after 
receipt.

FOR FURTHER INFORMATION CONTACT: 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: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2016-3984; 
Directorate Identifier 2014-NM-119-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On May 13, 2013, we issued AD 2013-10-03, Amendment 39-17456 (78 FR 
31386, May 24, 2013). AD 2013-10-03 requires actions intended to 
address an unsafe condition on 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 superseded AD 2010-02-10, 
Amendment 39-16181 (75 FR 4477, January 28, 2010)).
    Since we issued AD 2013-10-03, Amendment 39-17456 (78 FR 31386, May 
24, 2013), we have determined that certain one-time inspections are no 
longer necessary, certain compliance times may be extended, and an 
optional terminating action should be provided.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2014-0120R1, dated August 31, 2015 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for all Airbus Model A330-200, -200 
Freighter, and -300 series airplanes; and Model A340-200, -300, -500, 
and -600 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,

[[Page 10541]]

possibly resulting in damage to the aeroplane and injury to the 
occupants.
    To address this potential unsafe condition, EASA issued * * * 
[an earlier AD] 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 [earlier 
EASA] AD, applicable to A330, A340-200 and A340-300 aeroplanes, 
numerous bogie stop pad were found corroded and a few cracked.
    The one-time inspection was retained in EASA AD 2011-0211 
[https://ad.easa.europa.eu/blob/easa_ad_2011_0211_superseded.pdf/AD_2011-0211_1] [which corresponds to FAA AD 2013-10-03, Amendment 
39-17456 (78 FR 31386, May 24, 2013)], which superseded * * * [an 
earlier EASA AD], applicable to all A330 and A340 aeroplanes, which 
also introduced repetitive inspections for A330, A340-200 and A340-
300 aeroplanes, but not for the A340-500/-600 aeroplanes.
    Since issuance of EASA AD 2011-0211, further investigation 
accomplished by Airbus led to the conclusion that the one-time 
inspection in accordance with Airbus Service Bulletin (SB) A330-32-
3220, or Airbus SB A340-32-4264, or Airbus SB A340-32-5087, as 
applicable, is no longer necessary and, for those aeroplanes, only 
the inspections (initial and repetitive) in accordance with Airbus 
SB A330-32-3248 or Airbus SB A340-32-4286, as applicable, must 
remain.
    In addition, Airbus also determined that repetitive inspections 
of the MLG in accordance with Airbus SB A340-32-5112 are necessary 
for A340-500/-600 aeroplanes.
    Consequently, EASA issued * * * [another AD], which partially 
retained the requirements of EASA AD 2011-0211, which was 
superseded, and introduced repetitive detailed inspections of the 
MLG for A340-500 and A340-600 aeroplanes.
    Since that [EASA] AD was issued, it was determined that 
repetitive inspections of the MLG are not necessary on the A340-500/
-600 aeroplanes and that the threshold for the inspection of MLG P/N 
10-210 series can be delayed. In addition, Airbus developed a mod of 
the MLG P/N 10-210 series that can be embodied both in production 
through mod 204421 and in service with Airbus SB A330-32-3268 or SB 
A340-32-4300, as applicable. This modification constitutes a 
terminating action for the repetitive inspections for aeroplanes 
equipped with MLG P/N 10-210 series.
    For the reasons described above, this [EASA] AD is revised and 
requires inspection of the MLG (with an amended threshold for MLG P/
N 10-210 series) and introduces an option to terminate the 
repetitive inspection with a modification of the MLG P/N 10-210 
series.

    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 optional terminating action modification of the bogie beam of 
an MLG having P/N 10-210 consists of installing a nickel under chrome 
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 https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
3984.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A330-32-3248, Revision 02, dated 
April 16, 2014. This service information describes procedures for doing 
a detailed 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.
    Airbus has also issued Service Bulletin A330-32-3268 and Airbus 
Service Bulletin A340-32-4300, both dated April 20, 2015. This service 
information describes procedures for modification of the bogie beam of 
an MLG having P/N 10-210, which 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.

FAA's Determination and Requirements of This Proposed AD

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

Explanation of ``RC'' Procedures and Tests in Service Information

    The FAA worked in conjunction with industry, under the 
Airworthiness Directive Implementation Aviation Rulemaking Committee 
(ARC), to enhance the AD system. One enhancement was a new process for 
annotating which procedures and tests in the service information are 
required for compliance with an AD. Differentiating these procedures 
and tests from other tasks in the service information is expected to 
improve an owner's/operator's understanding of crucial AD requirements 
and help provide consistent judgment in AD compliance. The procedures 
and tests identified as Required for Compliance (RC) in any service 
information have a direct effect on detecting, preventing, resolving, 
or eliminating an identified unsafe condition.
    As specified in a Note under the Accomplishment Instructions of the 
specified service information, procedures and tests that are identified 
as RC in any service information must be done to comply with the 
proposed AD. However, procedures and 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 alternative method of compliance (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 will require approval of an AMOC.

Costs of Compliance

    We estimate that this proposed AD affects 89 Model A330-200, -200 
Freighter, and -300 series airplanes of U.S. registry.
    We estimate that it would take about 12 work-hours per product to 
comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Based on these figures, we estimate 
the cost of this proposed AD on U.S. operators to be $90,780, or $1,020 
per product.
    Currently, there are no affected 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 would 
take about 24 work-hours, and 1 work-hour for reporting, and require 
parts costing $78, for a cost of $2,203 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

[[Page 10542]]

terminating action specified in this proposed AD may be covered under 
warranty, thereby reducing the cost impact on affected individuals. We 
do not control warranty coverage for affected individuals. 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 proposed AD.

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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    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.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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) 
2013-10-03, Amendment 39-17456 (78 FR 31386, May 24, 2013), and adding 
the following new AD:

Airbus: Docket No. FAA-2016-3984; Directorate Identifier 2014-NM-
119-AD.

(a) Comments Due Date

    We must receive comments by April 15, 2016.

(b) Affected ADs

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

(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 that have embodied Airbus Modification 
204421 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, -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, which could result in a damaged 
bogie beam and consequent detachment of the beam from the airplane, 
or collapse of the MLG and departure of the airplane from the 
runway.

(f) Compliance

    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, Model A330-200 Freighter, and Model A330-300 
series airplanes; and Model A340-200, and -300 series airplanes; 
equipped with a MLG having part number (P/N) 201252 series, or 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 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 subassembly, 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 02, 
dated April 16, 2014; or Airbus Service Bulletin A340-32-4286, dated 
October 5, 2011; 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 02, dated April 16, 2014; or Airbus Service Bulletin A340-
32-4286, dated October 5, 2011; as applicable, except

[[Page 10543]]

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 Paragraph (g) of This AD Actions

    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 an MLG P/N 201252 series and 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 A340-32-4286; or Airbus Service Bulletin A340-32-4264; as 
applicable.
    (2) For airplanes identified in paragraph (g)(1) of this AD 
having an 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, Revision 01, 
dated December 13, 2012; or Airbus Service Bulletin A330-32-3248, 
Revision 02, dated April 16, 2014; or Airbus Service Bulletin A340-
32-4286, dated October 5, 2011; as applicable.
    (3) For airplanes identified in paragraph (g)(2) of this AD 
having an MLG P/N 201252 series and 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 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 an 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 an 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) Reporting Requirement

    After accomplishing any of the corrective actions required by 
paragraph (g) of this AD or any repair required by paragraph (j) of 
this AD: Report the results of the corrective actions or repair to 
Airbus, Customer Services Directorate, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex France; Attn: SDC32 Technical Data and 
Documentation Services; fax: +33 5 61 93 28 06; email: 
sb.reporting@airbus.com, at the applicable time specified in 
paragraph (k)(1) or (k)(2) of this AD.
    (1) If the corrective action or repair was done on or after the 
effective date of this AD: Submit the report within 90 days after 
doing corrective action or repair.
    (2) If the corrective action or repair was done prior to the 
effective date of this AD: Submit the report within 90 days after 
the effective date of this AD.

(l) Terminating Action Limitation

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

(m) Optional Terminating Action for Certain Airplanes

    For airplanes with any MLG having P/N 10-210 series: 
Modification on an airplane of the bogie beam of each MLG having P/N 
10-210 series as specified in the Accomplishment Instructions of 
Airbus Service Bulletin A330-32-3268, dated April 20, 2015; or 
Airbus Service Bulletin A340-32-4300, dated April 20, 2015; as 
applicable; constitutes terminating action for the requirements of 
this AD for that airplane, provided that, following in-service 
modification, the airplane remains in post-service bulletin 
configuration.

(n) Credit for Previous Actions

    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 paragraph (n)(1), (n)(2), or (n)(3), (n)(4), or (n)(5) of this 
AD.
    (1) Airbus Service Bulletin A330-32-3248, dated October 5, 2011, 
which is not incorporated by reference in this AD.
    (2) 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, Amendment 39-17456 (78 FR 31386, May 24, 
2013).
    (3) Airbus Service Bulletin A330-32-3220, dated October 10, 
2008, which was incorporated by reference in AD 2010-02-10, 
Amendment 39-16181 (75 FR 4477, January 28, 2010).
    (4) Airbus Service Bulletin A330-32-3220, Revision 01, dated 
October 5, 2011, which was incorporated by reference in AD 2013-10-
03, Amendment 39-17456 (78 FR 31386, May 24, 2013).
    (5) Airbus Service Bulletin A330-32-3220, Revision 02, dated 
December 13, 2012, which was incorporated by reference in AD 2013-
10-03, Amendment 39-17456 (78 FR 31386, May 24, 2013).

(o) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it to ATTN: Vladimir 
Ulyanov, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, 
WA 98057-3356; telephone: 425-227-1138; 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 2013-10-03, Amendment 39-
17456 (78 FR 31386, May 24, 2013), 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.
    (4) 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

[[Page 10544]]

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.

(p) Special Flight Permits

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

(q) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2014-0120R1, dated August 31, 2015, for related 
information. This MCAI may be found in the AD docket on the Internet 
at https://www.regulations.gov by searching for and locating Docket 
No. FAA-2016-3984.
    (2) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; 
fax: +33 5 61 93 45 80; email: airworthiness.A330-A340@airbus.com; 
Internet https://www.airbus.com. You may 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.

    Issued in Renton, Washington, on February 19, 2016.
Dorr M. Anderson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-04290 Filed 2-29-16; 8:45 am]
 BILLING CODE 4910-13-P
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