Airworthiness Directives; Airbus Airplanes, 22939-22943 [2015-09288]

Download as PDF Federal Register / Vol. 80, No. 79 / Friday, April 24, 2015 / Proposed Rules On April 1, 2015, the U.S. Department of Energy (DOE) published in the Federal Register a notice of proposed rulemaking and public meeting for Energy Conservation Program: Test Procedure for Pumps. This document corrects terms in four equations. SUMMARY: DEPARTMENT OF ENERGY 10 CFR Parts 429 and 431 [Docket No. EERE–2013–BT–TP–0055] RIN 1905–AD50 Energy Conservation Program: Test Procedure for Pumps; Correction Office of Energy Efficiency and Renewable Energy, Department of Energy. ACTION: Notice of proposed rulemaking and public meeting; correction. AGENCY: Appendix A to Subpart Y of Part 431— Uniform Test Method for the Measurement of Energy Consumption of Pumps. [Corrected] 2. On page 17645: The equation in section II.B.1.1.1 is corrected by DATES: April 24, 2015. FOR FURTHER INFORMATION CONTACT: Ashley Armstrong, U.S. Department of Energy, Office of Energy Efficiency and Renewable Energy, Building Technologies Office, EE–5B, 1000 removing ‘‘13.46’’ and adding in its place ‘‘17.80’’. The corrected equation reads as follows: hpump,STD = ¥0.85 * In(Q100%)2 ¥ 0.38 * In(NS) * In(Q100%) ¥ 11.48 * In(NS)2 + 17.80 * In(Q100%) + 179.80 * In(NS) ¥ (C ¥ 555.6) [Docket No. FAA–2015–0831; Directorate Identifier 2014–NM–061–AD] BILLING CODE 6450–01–P Federal Aviation Administration 14 CFR Part 39 RIN 2120–AA64 tkelley on DSK3SPTVN1PROD with PROPOSALS 3. On page 17646: The equation in section III.D.1.2.1 is corrected by removing ‘‘MotorH’’ and adding in its place ‘‘MotorHP’’. The corrected equation reads as follows: Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: VerDate Sep<11>2014 17:05 Apr 23, 2015 Jkt 235001 PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 We propose to adopt a new airworthiness directive (AD) for all Airbus Model A318, A319, A320, and A321 series airplanes. This proposed AD was prompted by a report of a rupture of a main landing gear (MLG) sliding tube axle. This proposed AD would require an inspection to identify the part number and serial number of the MLG sliding tubes installed on the airplane; and an inspection of the axle on certain MLG sliding tubes for burned areas, and replacement of the sliding tube if necessary. We are proposing this AD to detect and correct cracks in the axle and (partial) detachment of the axle and wheel from the sliding tube, which could result in failure of an MLG. SUMMARY: E:\FR\FM\24APP1.SGM 24APP1 EP24AP15.002</GPH> [FR Doc. 2015–09566 Filed 4–23–15; 8:45 am] In the Federal Register published on April 1, 2015, in FR Doc. 2015–06945, make the following corrections: 1. On page 17604: Equation (6) is corrected by removing ‘‘13.46’’ and adding in its place ‘‘17.80’’. The corrected equation reads as follows: EP24AP15.001</GPH> DEPARTMENT OF TRANSPORTATION Corrections adding in its place ‘‘MotorHP’’. The corrected equation reads as follows: Issued in Washington, DC, on April 20, 2015. Kathleen B. Hogan, Deputy Assistant Secretary for Energy Efficiency, Energy Efficiency and Renewable Energy. Independence Avenue SW., Washington, DC 20585–0121. Telephone: (202) 586–6590. Email: ashley.armstrong@ee.doe.gov. EP24AP15.017</GPH> 4. On page 17648: The equation in section V.D.1.2.1 is corrected by removing ‘‘MotorHPMotorH’’ and 22939 22940 Federal Register / Vol. 80, No. 79 / Friday, April 24, 2015 / Proposed Rules We must receive comments on this proposed AD by June 8, 2015. 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 http://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 Airbus service information identified in this proposed AD, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. For Messier-Bugatti-Dowty service information identified in this proposed AD, 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. tkelley on DSK3SPTVN1PROD with PROPOSALS DATES: 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–2015– 0831; 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: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; fax 425–227–1149. VerDate Sep<11>2014 17:05 Apr 23, 2015 Jkt 235001 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–2015–0831; Directorate Identifier 2014–NM–061–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 http:// 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 The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014–0058, dated March 11, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Model A318, A319, A320, and A321 series airplanes. The MCAI states: A main landing gear (MLG) sliding tube axle rupture occurred in service. Investigation of the affected part showed that this failure was due to an abnormal grinding operation during overhaul by a certain maintenance and repair organisation located in Singapore. A population of MLG sliding tubes was subsequently identified whose axles may have been subject to this grinding operation, which may have resulted in areas of residual stress on the axles on the MLG sliding tubes. In addition, the MSN [manufacturer serial number] of the aeroplanes which are known to have had the affected parts installed have been identified. This condition, if not detected and corrected, could lead to cracks in the axle and (partial) detachment of axle and wheel from the sliding tube, possibly resulting in failure of a MLG with consequent damage to the aeroplane and injury to occupants. To address this potential unsafe condition, Messier-Bugatti-Dowty, the MLG gear manufacturer, issued Service Bulletin (SB) 200–32–313 and SB 201–32–62 [both dated February 25, 2013], providing inspection instructions and criteria for removal from service of the affected MLG sliding tubes. For the reasons described above, this [EASA] AD requires a one-time Special Detailed Inspection (SDI) of the axle on the affected MLG sliding tubes and, depending on findings, replacement of the MLG sliding tube. PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 The SDI includes a detailed visual inspection of the chromium plate for damage, and a Barkhausen noise inspection of the sliding tube axles for burned areas. 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–2015–0831. Related Service Information Under 1 CFR part 51 Airbus has issued Service Bulletin A320–32–1416, including Appendix 01, dated March 10, 2014 (for Model A319, A320, and A321 series airplanes). This service bulletin describes procedures for inspection of the MLG sliding tube axles, and replacement if necessary. Messier-Bugatti-Dowty has issued Service Bulletin 200–32–313, including Appendices A, B, and C, dated February 25, 2013 (for Model A318, A319, and A320 series airplanes); and Service Bulletin 201–32–62, including Appendices A, B, and C, dated February 25, 2013 (for Model A321 series airplanes). These service bulletins describe procedures for inspection of the MLG axles and brake flanges, and replacement if necessary. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. This service information is reasonably available; see ADDRESSES for ways to access this service information. 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 E:\FR\FM\24APP1.SGM 24APP1 22941 Federal Register / Vol. 80, No. 79 / Friday, April 24, 2015 / Proposed Rules owner’s/operator’s understanding of crucial AD requirements and help provide consistent judgment in AD compliance. The procedures and tests identified as RC (required for compliance) 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 a serviceable condition. Any substitutions or changes to procedures or tests identified as RC will require approval of an AMOC. tkelley on DSK3SPTVN1PROD with PROPOSALS Costs of Compliance We estimate that this proposed AD affects 3 airplanes of U.S. registry. We also estimate that it would take about 18 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 $4,590, or $1,530 per product. In addition, we estimate that any necessary follow-on actions would take about 3 work-hours, for a cost of $255 per product. We have received no definitive data that would enable us to provide part cost estimates for the oncondition actions specified in this proposed AD. We have no way of determining the number of aircraft that might need these actions. 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 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 adding the following new airworthiness directive (AD): ■ Airbus: Docket No. FAA–2015–0831; Directorate Identifier 2014–NM–061–AD. (a) Comments Due Date We must receive comments by June 8, 2015. (b) Affected ADs None. (c) Applicability This AD applies to the Airbus airplanes identified in paragraphs (c)(1) through (c)(4) of this AD, certificated in any category, all manufacturer serial numbers. (1) Airbus Model A318–111, –112, –121, and –122 airplanes. (2) Airbus Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes. (3) Airbus Model A320–211, –212, –214, –231, –232, and –233 airplanes. (4) Airbus Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. (d) Subject Air Transport Association (ATA) of America Code 32, Landing gear. (e) Reason This AD was prompted by a report of a rupture of a main landing gear (MLG) sliding tube axle. We are issuing this AD to detect and correct cracks in the axle and (partial) detachment of the axle and wheel from the sliding tube, which could result in failure of an MLG. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) MLG Sliding Tube Part Number and Serial Number Identification Within 3 months after the effective date of this AD: Do an inspection to identify the part number and serial number of the MLG sliding tubes installed on the airplane. A review of airplane maintenance records is acceptable in lieu of this inspection if the part number and serial number of the MLG sliding tubes can be conclusively determined from that review. (h) Identification of Airplanes Not Affected by the Requirements of Paragraph (i) of This AD An airplane with a manufacturer serial number (MSN) not listed in figure 1 to paragraph (h) of this AD is not affected by the requirements of paragraph (i) of this AD, provided it can be determined that no MLG sliding tube having a part number and serial number listed in table 1 to paragraphs (h), (i), (k)(1), (k)(2), (l)(1), and (l)(2) of this AD has been installed on that airplane since first flight of the airplane. FIGURE 1 TO PARAGRAPH (h) OF THIS AD Affected airplanes listed by MSN 0179 VerDate Sep<11>2014 0214 17:05 Apr 23, 2015 Jkt 235001 0296 PO 00000 Frm 00015 0412 Fmt 4702 Sfmt 4702 E:\FR\FM\24APP1.SGM 0558 24APP1 0604 22942 Federal Register / Vol. 80, No. 79 / Friday, April 24, 2015 / Proposed Rules FIGURE 1 TO PARAGRAPH (h) OF THIS AD—Continued 0607 0754 0909 1030 1108 0668 0771 0914 1041 1148 0704 0799 0925 1070 1294 TABLE 1 TO PARAGRAPHS (h), (i), (k)(1), (k)(2), (l)(1), AND (l)(2) OF THIS AD—AFFECTED MLG SLIDING TUBES tkelley on DSK3SPTVN1PROD with PROPOSALS Part No. 201160302 201160302 201160302 201371302 201371302 201371302 201371302 201371302 201371302 201371302 201371302 201371302 201371302 201371302 201371302 201371302 201160302 201371304 201371304 201371304 201371304 201371304 201371304 201371304 201371304 201371304 201371304 201371304 201371304 201371304 201371304 201371304 201371304 201371304 201371304 201371304 201371304 201371304 201371304 201371304 201371304 201371304 201371304 201522353 201522350 201522350 201522350 201522350 201522350 201522353 201522353 201522353 201522353 201522353 201383350 201383350 201383350 201383350 201383350 201383350 ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ ............................ VerDate Sep<11>2014 17:05 Apr 23, 2015 Serial No. 78B. 1016B11. 1144B. B4493. B4513. SS4359. B4530. B4517. B4568. B4498. 4490B. B202–4598. B165–4623. B244–4766. B267–4794. B272–4813. 1108B. B041–4871. B045–4869. B001–4781. B051–4892. B110–1952. B054–4891. B063–4921. B071–4911. B071–4917. B080–1933. B117–5010. B120–4989. B132–2023. B114–1956. B208–2009. B133–1947. B154–5037. B89 4952. B129–1964. B227–2010. B170–5031. B182–5047. B239–2053. B1401–2856. B1813–3142. B116–5004. B011–149. B014–25. B019–56. B019–57. B021–69. B022–60. B03–111. B03–110. B112–317. B174–351. B179–392. 4377B. 4393B. B1831. B1832. SS4355B. SS4400B. Jkt 235001 0720 0828 0939 1083 1356 (i) Inspections For each MLG sliding tube, identified as required by paragraph (g) of this AD, having a part number and serial number listed in table 1 to paragraphs (h), (i), (k)(1), (k)(2), (l)(1), and (l)(2) of this AD: Within 3 months after the effective date of this AD, inspect each affected MLG axle and brake flange by doing a detailed visual inspection of the chromium plate for damage, and a Barkhausen noise inspection of the sliding tube axles for burned areas, in accordance with the Accomplishment Instructions of Messier-Bugatti-Dowty Service Bulletin 200– 32–313, including Appendices A, B, and C, dated February 25, 2013 (for Model A318, A319, and A320 series airplanes); or MessierBugatti-Dowty Service Bulletin 201–32–62, including Appendices A, B, and C, dated February 25, 2013 (for Model A321 series airplanes); or Airbus Service Bulletin A320– 32–1416, including Appendix 01, dated March 10, 2014 (for Model A319, A320, and A321 series airplanes). (j) Corrective Action If, during any inspection required by paragraph (i) of this AD, any damage is detected: Before further flight, replace the MLG sliding tube with a serviceable tube, in accordance with the Accomplishment Instructions of Messier-Bugatti-Dowty Service Bulletin 200–32–313, including Appendices A, B, and C, dated February 25, 2013 (for Model A318, A319, and A320 series airplanes); or Messier-Bugatti-Dowty Service Bulletin 201–32–62, including Appendices A, B, and C, dated February 25, 2013 (for Model A321 series airplanes); or Airbus Service Bulletin A320–32–1416, including Appendix 01, dated March 10, 2014 (for Model A319, A320, and A321 series airplanes). (k) Definition of Serviceable Sliding Tube For the purpose of this AD, a serviceable sliding tube is defined in paragraphs (k)(1) and (k)(2) of this AD. (1) A sliding tube having a part number and serial number not listed in table 1 to paragraphs (h), (i), (k)(1), (k)(2), (l)(1), and (l)(2) of this AD. (2) A sliding tube having a part number and serial number listed in table 1 to paragraphs (h), (i), (k)(1), (k)(2), (l)(1), and (l)(2) of this AD that has passed the inspections required by paragraph (i) of this AD. (l) Parts Installation Prohibitions (1) For airplanes that have an MLG sliding tube installed that has a part number and serial number listed in table 1 to paragraphs (h), (i), (k)(1), (k)(2), (l)(1), and (l)(2) of this AD: After an airplane is returned to service following accomplishment of the actions required by paragraphs (g), (h), and (i) of this AD, no person may install on any airplane an PO 00000 Frm 00016 Fmt 4702 Sfmt 4702 0726 0841 0986 1093 2713 0731 0855 1028 1098 2831 MLG sliding tube having a part number and serial number listed in table 1 to paragraphs (h), (i), (k)(1), (k)(2), (l)(1), and (l)(2) of this AD. (2) For airplanes that, as of the effective date of this AD, do not have an MLG sliding tube installed that has a part number and serial number listed in table 1 to paragraphs (h), (i), (k)(1), (k)(2), (l)(1), and (l)(2) of this AD: No person may install on any airplane an MLG sliding tube having a part number and serial number listed in table 1 to paragraphs (h), (i), (k)(1), (k)(2), (l)(1), and (l)(2) of this AD. (m) 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: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; fax 425–227–1149. Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Required for Compliance (RC): 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 a serviceable condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (3) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). If approved by E:\FR\FM\24APP1.SGM 24APP1 Federal Register / Vol. 80, No. 79 / Friday, April 24, 2015 / Proposed Rules the DOA, the approval must include the DOA-authorized signature. (n) Special Flight Permits Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the airplane can be modified (if the operator elects to do so), provided the MLG remains extended throughout the flight. (o) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) European Aviation Safety Agency (EASA) Airworthiness Directive 2014–0058, dated March 11, 2014, 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– 2015–0831. (2) For Airbus service information identified in this AD, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ airbus.com; Internet http://www.airbus.com. (3) For Messier-Bugatti-Dowty service information identified in this AD, 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. (4) 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 April 9, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–09288 Filed 4–23–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–0926; Directorate Identifier 2014–NM–121–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). tkelley on DSK3SPTVN1PROD with PROPOSALS AGENCY: We propose to supersede Airworthiness Directive (AD) 97–07–14, for certain Airbus Model A320–111, –211, and –231 airplanes. AD 97–07–14 SUMMARY: VerDate Sep<11>2014 17:05 Apr 23, 2015 Jkt 235001 currently requires modification of an area on the front spar of the wing center section by installing shims and new fasteners to reinforce pressure floor fittings. Since we issued AD 97–07–14, we have determined the need for repetitive inspections on airplanes on which the modification of the rib flange on the front spar of the wing center section has been done. This proposed AD would continue to require modifying the rib flange on the front spar of the wing center section by installing shims and new fasteners to reinforce pressure floor fittings; and would require repetitive high frequency eddy current inspections for cracking of the radius of the rib flanges and vertical stiffener at frame 36, a rototest inspection for cracking of the fastener holes of the rib flanges, repair if needed, and adding additional airplanes to the applicability. We are proposing this AD to prevent fatigue cracking on the rib flange area of the front spar of the wing center section, which can reduce the structural integrity of fuselage frame 36 and the wing center section. DATES: We must receive comments on this proposed AD by June 8, 2015. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to http://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 proposed AD, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. 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–2015– PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 22943 0926; 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: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; 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–2015–0926; Directorate Identifier 2014–NM–121–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 http:// 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 March 27, 1997, we issued AD 97– 07–14, Amendment 39–9988 (62 FR 16473, April 7, 1997). AD 97–07–14 requires modification of an area on the front spar of the wing center section by installing shims and new fasteners to reinforce pressure floor fittings on certain Airbus Model A320–111, –211 and –231 airplanes. Since we issued AD 97–07–14, Amendment 39–9988 (62 FR 16473, April 7, 1997), we have determined the need for repetitive inspections on airplanes on which Airbus Modification 20976 (modification of the rib flange on the front spar of the wing center section) was done in production, or was done using Airbus Service Bulletin A320–57– 1013, dated April 12, 1989; or Airbus Service Bulletin A320–57–1013, Revision 1, dated September 29, 1992. The European Aviation Safety Agency (EASA), which is the Technical Agent E:\FR\FM\24APP1.SGM 24APP1

Agencies

[Federal Register Volume 80, Number 79 (Friday, April 24, 2015)]
[Proposed Rules]
[Pages 22939-22943]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-09288]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0831; Directorate Identifier 2014-NM-061-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
Airbus Model A318, A319, A320, and A321 series airplanes. This proposed 
AD was prompted by a report of a rupture of a main landing gear (MLG) 
sliding tube axle. This proposed AD would require an inspection to 
identify the part number and serial number of the MLG sliding tubes 
installed on the airplane; and an inspection of the axle on certain MLG 
sliding tubes for burned areas, and replacement of the sliding tube if 
necessary. We are proposing this AD to detect and correct cracks in the 
axle and (partial) detachment of the axle and wheel from the sliding 
tube, which could result in failure of an MLG.

[[Page 22940]]


DATES: We must receive comments on this proposed AD by June 8, 2015.

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 http://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 Airbus service information identified in this proposed AD, 
contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax 
+33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet 
http://www.airbus.com.
    For Messier-Bugatti-Dowty service information identified in this 
proposed AD, 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.

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-2015-
0831; 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: Sanjay Ralhan, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; 
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-2015-0831; 
Directorate Identifier 2014-NM-061-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 http://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

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2014-0058, dated March 11, 2014 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model 
A318, A319, A320, and A321 series airplanes. The MCAI states:

    A main landing gear (MLG) sliding tube axle rupture occurred in 
service. Investigation of the affected part showed that this failure 
was due to an abnormal grinding operation during overhaul by a 
certain maintenance and repair organisation located in Singapore. A 
population of MLG sliding tubes was subsequently identified whose 
axles may have been subject to this grinding operation, which may 
have resulted in areas of residual stress on the axles on the MLG 
sliding tubes. In addition, the MSN [manufacturer serial number] of 
the aeroplanes which are known to have had the affected parts 
installed have been identified.
    This condition, if not detected and corrected, could lead to 
cracks in the axle and (partial) detachment of axle and wheel from 
the sliding tube, possibly resulting in failure of a MLG with 
consequent damage to the aeroplane and injury to occupants.
    To address this potential unsafe condition, Messier-Bugatti-
Dowty, the MLG gear manufacturer, issued Service Bulletin (SB) 200-
32-313 and SB 201-32-62 [both dated February 25, 2013], providing 
inspection instructions and criteria for removal from service of the 
affected MLG sliding tubes.
    For the reasons described above, this [EASA] AD requires a one-
time Special Detailed Inspection (SDI) of the axle on the affected 
MLG sliding tubes and, depending on findings, replacement of the MLG 
sliding tube.

The SDI includes a detailed visual inspection of the chromium plate for 
damage, and a Barkhausen noise inspection of the sliding tube axles for 
burned areas. 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-2015-0831.

Related Service Information Under 1 CFR part 51

    Airbus has issued Service Bulletin A320-32-1416, including Appendix 
01, dated March 10, 2014 (for Model A319, A320, and A321 series 
airplanes). This service bulletin describes procedures for inspection 
of the MLG sliding tube axles, and replacement if necessary.
    Messier-Bugatti-Dowty has issued Service Bulletin 200-32-313, 
including Appendices A, B, and C, dated February 25, 2013 (for Model 
A318, A319, and A320 series airplanes); and Service Bulletin 201-32-62, 
including Appendices A, B, and C, dated February 25, 2013 (for Model 
A321 series airplanes). These service bulletins describe procedures for 
inspection of the MLG axles and brake flanges, and replacement if 
necessary.
    The actions described in this service information are intended to 
correct the unsafe condition identified in the MCAI. This service 
information is reasonably available; see ADDRESSES for ways to access 
this service information.

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

[[Page 22941]]

owner's/operator's understanding of crucial AD requirements and help 
provide consistent judgment in AD compliance. The procedures and tests 
identified as RC (required for compliance) 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 a serviceable 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 3 airplanes of U.S. 
registry.
    We also estimate that it would take about 18 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 $4,590, or $1,530 
per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 3 work-hours, for a cost of $255 per product. We have 
received no definitive data that would enable us to provide part cost 
estimates for the on-condition actions specified in this proposed AD. 
We have no way of determining the number of aircraft that might need 
these actions.

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 adding the following new airworthiness 
directive (AD):

Airbus: Docket No. FAA-2015-0831; Directorate Identifier 2014-NM-
061-AD.

(a) Comments Due Date

    We must receive comments by June 8, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs 
(c)(1) through (c)(4) of this AD, certificated in any category, all 
manufacturer serial numbers.
    (1) Airbus Model A318-111, -112, -121, and -122 airplanes.
    (2) Airbus Model A319-111, -112, -113, -114, -115, -131, -132, 
and -133 airplanes.
    (3) Airbus Model A320-211, -212, -214, -231, -232, and -233 
airplanes.
    (4) Airbus Model A321-111, -112, -131, -211, -212, -213, -231, 
and -232 airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by a report of a rupture of a main landing 
gear (MLG) sliding tube axle. We are issuing this AD to detect and 
correct cracks in the axle and (partial) detachment of the axle and 
wheel from the sliding tube, which could result in failure of an 
MLG.

 (f) Compliance

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

(g) MLG Sliding Tube Part Number and Serial Number Identification

    Within 3 months after the effective date of this AD: Do an 
inspection to identify the part number and serial number of the MLG 
sliding tubes installed on the airplane. A review of airplane 
maintenance records is acceptable in lieu of this inspection if the 
part number and serial number of the MLG sliding tubes can be 
conclusively determined from that review.

(h) Identification of Airplanes Not Affected by the Requirements of 
Paragraph (i) of This AD

    An airplane with a manufacturer serial number (MSN) not listed 
in figure 1 to paragraph (h) of this AD is not affected by the 
requirements of paragraph (i) of this AD, provided it can be 
determined that no MLG sliding tube having a part number and serial 
number listed in table 1 to paragraphs (h), (i), (k)(1), (k)(2), 
(l)(1), and (l)(2) of this AD has been installed on that airplane 
since first flight of the airplane.

                  Figure 1 to Paragraph (h) of This AD
------------------------------------------------------------------------
 
------------
                    Affected airplanes listed by MSN
------------------------------------------------------------------------
     0179         0214        0296        0412        0558        0604

[[Page 22942]]

 
     0607         0668        0704        0720        0726        0731
     0754         0771        0799        0828        0841        0855
     0909         0914        0925        0939        0986        1028
     1030         1041        1070        1083        1093        1098
     1108         1148        1294        1356        2713        2831
------------------------------------------------------------------------


  Table 1 to Paragraphs (h), (i), (k)(1), (k)(2), (l)(1), and (l)(2) of
                   This AD--Affected MLG Sliding Tubes
------------------------------------------------------------------------
                 Part No.                            Serial No.
------------------------------------------------------------------------
201160302.................................  78B.
201160302.................................  1016B11.
201160302.................................  1144B.
201371302.................................  B4493.
201371302.................................  B4513.
201371302.................................  SS4359.
201371302.................................  B4530.
201371302.................................  B4517.
201371302.................................  B4568.
201371302.................................  B4498.
201371302.................................  4490B.
201371302.................................  B202-4598.
201371302.................................  B165-4623.
201371302.................................  B244-4766.
201371302.................................  B267-4794.
201371302.................................  B272-4813.
201160302.................................  1108B.
201371304.................................  B041-4871.
201371304.................................  B045-4869.
201371304.................................  B001-4781.
201371304.................................  B051-4892.
201371304.................................  B110-1952.
201371304.................................  B054-4891.
201371304.................................  B063-4921.
201371304.................................  B071-4911.
201371304.................................  B071-4917.
201371304.................................  B080-1933.
201371304.................................  B117-5010.
201371304.................................  B120-4989.
201371304.................................  B132-2023.
201371304.................................  B114-1956.
201371304.................................  B208-2009.
201371304.................................  B133-1947.
201371304.................................  B154-5037.
201371304.................................  B89 4952.
201371304.................................  B129-1964.
201371304.................................  B227-2010.
201371304.................................  B170-5031.
201371304.................................  B182-5047.
201371304.................................  B239-2053.
201371304.................................  B1401-2856.
201371304.................................  B1813-3142.
201371304.................................  B116-5004.
201522353.................................  B011-149.
201522350.................................  B014-25.
201522350.................................  B019-56.
201522350.................................  B019-57.
201522350.................................  B021-69.
201522350.................................  B022-60.
201522353.................................  B03-111.
201522353.................................  B03-110.
201522353.................................  B112-317.
201522353.................................  B174-351.
201522353.................................  B179-392.
201383350.................................  4377B.
201383350.................................  4393B.
201383350.................................  B1831.
201383350.................................  B1832.
201383350.................................  SS4355B.
201383350.................................  SS4400B.
------------------------------------------------------------------------

(i) Inspections

    For each MLG sliding tube, identified as required by paragraph 
(g) of this AD, having a part number and serial number listed in 
table 1 to paragraphs (h), (i), (k)(1), (k)(2), (l)(1), and (l)(2) 
of this AD: Within 3 months after the effective date of this AD, 
inspect each affected MLG axle and brake flange by doing a detailed 
visual inspection of the chromium plate for damage, and a Barkhausen 
noise inspection of the sliding tube axles for burned areas, in 
accordance with the Accomplishment Instructions of Messier-Bugatti-
Dowty Service Bulletin 200-32-313, including Appendices A, B, and C, 
dated February 25, 2013 (for Model A318, A319, and A320 series 
airplanes); or Messier-Bugatti-Dowty Service Bulletin 201-32-62, 
including Appendices A, B, and C, dated February 25, 2013 (for Model 
A321 series airplanes); or Airbus Service Bulletin A320-32-1416, 
including Appendix 01, dated March 10, 2014 (for Model A319, A320, 
and A321 series airplanes).

(j) Corrective Action

    If, during any inspection required by paragraph (i) of this AD, 
any damage is detected: Before further flight, replace the MLG 
sliding tube with a serviceable tube, in accordance with the 
Accomplishment Instructions of Messier-Bugatti-Dowty Service 
Bulletin 200-32-313, including Appendices A, B, and C, dated 
February 25, 2013 (for Model A318, A319, and A320 series airplanes); 
or Messier-Bugatti-Dowty Service Bulletin 201-32-62, including 
Appendices A, B, and C, dated February 25, 2013 (for Model A321 
series airplanes); or Airbus Service Bulletin A320-32-1416, 
including Appendix 01, dated March 10, 2014 (for Model A319, A320, 
and A321 series airplanes).

(k) Definition of Serviceable Sliding Tube

    For the purpose of this AD, a serviceable sliding tube is 
defined in paragraphs (k)(1) and (k)(2) of this AD.
    (1) A sliding tube having a part number and serial number not 
listed in table 1 to paragraphs (h), (i), (k)(1), (k)(2), (l)(1), 
and (l)(2) of this AD.
    (2) A sliding tube having a part number and serial number listed 
in table 1 to paragraphs (h), (i), (k)(1), (k)(2), (l)(1), and 
(l)(2) of this AD that has passed the inspections required by 
paragraph (i) of this AD.

(l) Parts Installation Prohibitions

    (1) For airplanes that have an MLG sliding tube installed that 
has a part number and serial number listed in table 1 to paragraphs 
(h), (i), (k)(1), (k)(2), (l)(1), and (l)(2) of this AD: After an 
airplane is returned to service following accomplishment of the 
actions required by paragraphs (g), (h), and (i) of this AD, no 
person may install on any airplane an MLG sliding tube having a part 
number and serial number listed in table 1 to paragraphs (h), (i), 
(k)(1), (k)(2), (l)(1), and (l)(2) of this AD.
    (2) For airplanes that, as of the effective date of this AD, do 
not have an MLG sliding tube installed that has a part number and 
serial number listed in table 1 to paragraphs (h), (i), (k)(1), 
(k)(2), (l)(1), and (l)(2) of this AD: No person may install on any 
airplane an MLG sliding tube having a part number and serial number 
listed in table 1 to paragraphs (h), (i), (k)(1), (k)(2), (l)(1), 
and (l)(2) of this AD.

(m) 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: Sanjay 
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-1405; fax 425-227-1149. Information may be 
emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office. The 
AMOC approval letter must specifically reference this AD.
    (2) Required for Compliance (RC): 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 a serviceable 
condition. Any substitutions or changes to procedures or tests 
identified as RC require approval of an AMOC.
    (3) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or the 
European Aviation Safety Agency (EASA); or Airbus's EASA Design 
Organization Approval (DOA). If approved by

[[Page 22943]]

the DOA, the approval must include the DOA-authorized signature.

(n) Special Flight Permits

    Special flight permits may be issued in accordance with sections 
21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 
and 21.199) to operate the airplane to a location where the airplane 
can be modified (if the operator elects to do so), provided the MLG 
remains extended throughout the flight.

(o) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) European Aviation Safety Agency (EASA) Airworthiness 
Directive 2014-0058, dated March 11, 2014, 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-
2015-0831.
    (2) For Airbus service information identified in this AD, 
contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; 
Internet http://www.airbus.com. (3) For Messier-Bugatti-Dowty 
service information identified in this AD, 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.
    (4) 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 April 9, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-09288 Filed 4-23-15; 8:45 am]
 BILLING CODE 4910-13-P