Airworthiness Directives; Airbus Airplanes, 30608-30612 [2015-11393]

Download as PDF 30608 Federal Register / Vol. 80, No. 103 / Friday, May 29, 2015 / Rules and Regulations paragraph (i)(2) of this AD. Before further flight, do all applicable related investigative and corrective actions, replace the inboard and outboard midspar fittings with new parts, and do other specified actions (including installing new bushings and oversize fasteners), in accordance with part 2 or part 3, as applicable, of the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3183, Revision 6, dated February 7, 2014, except as required by paragraph (i)(2) of this AD. Repeat the inspections required by paragraphs (g)(1), (g)(2), and (g)(3) of this AD thereafter at the applicable intervals specified in table 2 or table 3 of paragraph 1.E., ‘‘Compliance,’’ of Boeing 707 Alert Service Bulletin A3183, Revision 6, dated February 7, 2014, except as required by paragraph (i)(1) of this AD. (1) A detailed inspection and a high frequency eddy current inspection (HFEC) for cracks in the inboard and outboard midspar fittings of the nacelle struts. (2) Open hole HFEC inspections for cracks in the torque bulkhead, midspar chords, drag fitting, and front spar support. (3) A surface HFEC inspection of the front spar support for cracks. Lhorne on DSK2VPTVN1PROD with RULES (h) Mid-Interval Inspections and Replacement of Nacelle Strut Midspar Fittings At the applicable time specified in table 4 or 5 of paragraph 1.E., ‘‘Compliance,’’ of Boeing 707 Alert Service Bulletin A3183, Revision 6, dated February 7, 2014: Do the inspections required by paragraphs (h)(1), (h)(2), and (h)(3) of this AD, in accordance with part 4 or part 5, as applicable, of the Accomplishment Instructions of Boeing 707 Alert Service Bulletin A3183, Revision 6, dated February 7, 2014, except as required by paragraph (i)(2) of this AD. Do all applicable related investigative, corrective, and other specified actions (including installing new bushings and oversize fasteners) before further flight. Repeat the inspections required by paragraphs (h)(1), (h)(2), and (h)(3) of this AD thereafter at the applicable intervals specified in table 4 or 5 of paragraph 1.E., ‘‘Compliance,’’ of Boeing 707 Alert Service Bulletin A3183, Revision 6, dated February 7, 2014. The threshold for the repetitive inspections required by paragraphs (h)(1), (h)(2), and (h)(3) of this AD is 1,500 flight cycles or 48 months, whichever occurs first, since the most recent midspar fitting replacement. (1) A detailed inspection and a surface HFEC inspection for cracks in the inboard and outboard midspar fittings of the nacelle struts. (2) An open hole HFEC inspection for cracks in the drag fitting and front spar support. (3) A surface HFEC inspection for cracks in the front spar support. (i) Exceptions to Service Information Specifications (1) Where Boeing 707 Alert Service Bulletin A3183, Revision 6, dated February 7, 2014, specifies a compliance time ‘‘after the Revision 6 date of this service bulletin,’’ this AD requires compliance within the specified compliance time after the effective date of this AD. VerDate Sep<11>2014 14:17 May 28, 2015 Jkt 235001 (2) Where Boeing 707 Alert Service Bulletin A3183, Revision 6, dated February 7, 2014, specifies to contact Boeing for appropriate action: Do corrective actions before further flight using a method approved in accordance with the procedures specified in paragraph (k) of this AD. (j) Special Flight Permit 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. (k) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in paragraph (l) of this AD. Information may be emailed to: 9-ANM-LAACO-AMOCRequests@faa.gov. (2) 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. (3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Los Angeles ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane and the approval must specifically refer to this AD. (l) Related Information For more information about this AD, contact Chandra Ramdoss, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles ACO, 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627–5239; fax: 562–627–5210; email: chandraduth.ramdoss@faa.gov. (m) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Boeing 707 Alert Service Bulletin A3183, Revision 6, dated February 7, 2014. (ii) Reserved. (3) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services 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, WA. For PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 information on the availability of this material at the FAA, call 425–227–1221. (4) 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. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on May 20, 2015. John P. Piccola, Jr., Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–12858 Filed 5–28–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0584; Directorate Identifier 2014–NM–092–AD; Amendment 39–18158; AD 2015–10–03] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2014–09– 05, for certain Airbus Model A330–200 and –300 series airplanes, and Model A340–200 and –300 series airplanes. AD 2014–09–05 required repetitive inspections of certain sidestay upper cardan pins of the main landing gear (MLG) and associated nuts and retainer assemblies, and pin replacement if necessary. This AD was prompted by a determination that a previously optional measurement is necessary to address the identified unsafe condition. This new AD continues to require a detailed inspection for visible chrome of each affected MLG sidestay upper cardan pin, associated nuts, and retainer assembly, and pin replacement if needed, and adds new requirements for measuring cardan pin clearance dimensions (gap check), doing corrective actions, and reporting all findings. We are issuing this AD to detect and correct migration of the sidestay upper cardan pin, which could result in disconnection of the sidestay upper arm from the airplane structure, and could result in a landing SUMMARY: E:\FR\FM\29MYR1.SGM 29MYR1 Federal Register / Vol. 80, No. 103 / Friday, May 29, 2015 / Rules and Regulations Lhorne on DSK2VPTVN1PROD with RULES gear collapse and consequent damage to the airplane and injury to occupants. DATES: This AD becomes effective July 6, 2015. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of May 14, 2014 (79 FR 23909, April 29, 2014). ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2014-0584; or in person at the Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC. For service information identified in this AD, contact Airbus SAS— Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@airbus.com; Internet http://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0584. FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1138; fax 425–227–1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2014–09–05, Amendment 39–17840 (79 FR 23909, April 29, 2014). AD 2014–09–05 applied to certain Airbus Model A330–200 and –300 series airplanes, and Model A340– 200 and –300 series airplanes. The NPRM published in the Federal Register on August 26, 2014 (79 FR 50863). The European Aviation Safety Agency, which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014–0066, corrected March 20, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition on certain Airbus Model A330–200 and –300 series VerDate Sep<11>2014 14:17 May 28, 2015 Jkt 235001 airplanes, and Model A340–200 and –300 series airplanes. The MCAI states: An A330 aeroplane equipped with Basic (main landing gear) MLG was rolling out after landing when it experienced a nose wheel steering fault (unrelated to the safety subject addressed by this [EASA] AD), which resulted in the crew stopping the aeroplane on the taxiway after vacating the runway. The subsequent investigation revealed that the right-hand MLG sidestay upper cardan pin had migrated out of position. The sidestay upper cardan nut and retainer were found in the landing gear bay detached from the upper cardan pin. The nut and the retainer were still bolted together. This condition, if not detected and corrected, could lead to a complete migration of the sidestay upper cardan pin and a disconnection of the sidestay upper arm from the aeroplane structure, possibly resulting in MLG collapse with consequent damage to the aeroplane and injury to occupants. To address this potential condition, Airbus published Alert Operators Transmission (AOT) A32L003–14, providing inspection instructions. For the reasons described above, this [EASA] AD requires accomplishment of repetitive [detailed inspections for visible chrome] of the MLG upper cardan pin, nut and retainer [and pin replacement if necessary]. This [EASA] AD also requires accomplishment of a gap check between wing rear spar fitting lugs and the bush flanges [and corrective actions if necessary. Corrective actions include repair or replacement of the cardan pin assembly]. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov/ #!documentDetail;D=FAA-2014-05840003. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM (79 FR 50863, August 26, 2014) and the FAA’s response to each comment. Request To Match the Applicability of Terminating Action to Inspections U.S. Airways requested that we revise the affected airplanes of paragraph (h) of the NPRM (79 FR 50863, August 26, 2014) to match those of paragraph (g) of the NPRM. U.S. Airways stated that paragraph (g) of the NPRM limits the repetitive inspections to MLG that have exceeded 8 years since first overhaul but not yet had a second overhaul; whereas paragraph (h) of the NPRM provides a new terminating action to the repetitive inspections, but does not limit the applicability to MLG that have exceeded 8 years since first overhaul but not yet had a second overhaul. We agree to revise the affected airplanes of paragraph (h) of this AD because the terminating action PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 30609 provisions of paragraph (h) of the NPRM (79 FR 50863, August 26, 2014) was intended to apply to the same subset of affected airplanes identified in paragraph (g)(1) of the NPRM. We have changed the language in paragraph (h) of this AD by limiting the affected airplanes to those identified in paragraph (g)(1) of this AD. Request To Change Compliance Time of Sending Results of Gap Check U.S. Airways requested that we revise the compliance time for sending the results of the inspection and gap check to Airbus from ‘‘before further flight’’ to ‘‘within 30 days.’’ U.S. Airways stated that paragraph (h)(2)(i) of the NPRM (79 FR 50863, August 26, 2014) states to send inspection findings to Airbus ‘‘before further flight,’’ if the gap check result measures between 0.6 mm and 1.5 mm, and paragraph (h)(2)(ii) states to repair within 30 days. U.S. Airways stated that mechanics who inspect the cardan pin typically do not send data directly to Airbus and that since the repair is not required for 30 days after the inspection, communicating the inspection findings should not restrict aircraft flight. We agree to revise the compliance time because the proposed compliance time for sending the results of the inspection and gap check does not affect the compliance time for accomplishment of the repair. We have changed the compliance time in paragraph (h)(2)(i) of this AD from before further flight, to 30 days. This difference has been coordinated with EASA. Request To Allow Replacement of Cardan Pin Assembly as Terminating Action U.S. Airways requested that we allow the replacement of the cardan pin assembly to be considered as a terminating action. Paragraph (h)(1) of the NPRM (79 FR 50863, August 26, 2014) would mandate the replacement of the cardan pin if the gap is found to be greater than 1.5mm. However paragraph (h)(2) of the NPRM would require an approved repair for smaller gaps. US Airways suggested that the AD also allow the replacement of the cardan pin assembly before further flight as an alternative to the actions specified in paragraphs (h)(2)(i) and (h)(2)(ii) of the NPRM. We agree with the request to allow replacement of the cardan pin assembly as an alternative to small repairs because replacing the cardan pin assembly is terminating action regardless of the size of the gap. We have revised paragraph (h) of this AD to E:\FR\FM\29MYR1.SGM 29MYR1 30610 Federal Register / Vol. 80, No. 103 / Friday, May 29, 2015 / Rules and Regulations provide for replacement of the cardan pin assembly as an option to doing a repair. Related Service Information Under 1 CFR Part 51 The manufacturer has issued Airbus AOT A32L003–14, dated March 10, 2014. The service information describes procedures for inspecting sidestay upper cardan pins of the MLG and associated nuts and retainer assemblies. 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 AD. Conclusion We reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these changes: • Are consistent with the intent that was proposed in the NPRM (79 FR 50863, August 26, 2014) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (79 FR 50863, August 26, 2014). Lhorne on DSK2VPTVN1PROD with RULES Costs of Compliance We estimate that this AD affects 83 airplanes of U.S. registry. The actions required by AD 2014–09– 05, Amendment 39–17840 (79 FR 23909, April 29, 2014), and retained in this AD take about 1 work-hour per product, at an average labor rate of $85 per work-hour. Required parts cost $0 per product. Based on these figures, the estimated cost of the actions that were required by AD 2014–09–05 is $85 per product. We also estimate that it will take about 1 work-hour per product to comply with the new basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD on U.S. operators to be $7,055, or $85 per product. In addition, we estimate that any necessary follow-on actions will take about 4 work-hours and require parts costing $7,530, for a cost of $7,870 per product. We have no way of determining the number of aircraft that might need these actions. 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 VerDate Sep<11>2014 14:17 May 28, 2015 Jkt 235001 to penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB control number. The control number for the collection of information required by this AD is 2120–0056. The paperwork cost associated with this AD has been detailed in the Costs of Compliance section of this document and includes time for reviewing instructions, as well as completing and reviewing the collection of information. Therefore, all reporting associated with this AD is mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at 800 Independence Ave. SW., Washington, DC 20591, ATTN: Information Collection Clearance Officer, AES–200. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2014-0584; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800–647–5527) is in the ADDRESSES section. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 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) 2014–09–05, Amendment 39–17840 (79 FR 23909, April 29, 2014), and adding the following new AD: ■ 2015–10–03 Airbus: Amendment 39–18158. Docket No. FAA–2014–0584; Directorate Identifier 2014–NM–092–AD. (a) Effective Date This AD becomes effective July 6, 2015. (b) Affected ADs This AD replaces AD 2014–09–05, Amendment 39–17840 (79 FR 23909, April 29, 2014). (c) Applicability This AD applies to the airplanes identified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category. (1) Airbus Model A330–201, –202, –203, –223, –243, –301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes, all manufacturer serial numbers (MSNs), equipped with basic (201252 series) main landing gear (MLG), or growth (201490 series) MLG. (2) Airbus Model A340–211, –212, –213, –311, –312, and –313 airplanes, all MSNs, equipped with basic (201252 series) MLG or growth (201490 series) MLG. E:\FR\FM\29MYR1.SGM 29MYR1 Federal Register / Vol. 80, No. 103 / Friday, May 29, 2015 / Rules and Regulations (d) Subject Air Transport Association (ATA) of America Code 32, Landing Gear. (e) Reason This AD was prompted by a report of a sidestay upper cardan pin of the MLG migrating out of position. We are issuing this AD to detect and correct migration of the sidestay upper cardan pin, which could result in disconnection of the sidestay upper arm from the airplane structure, and could result in a landing gear collapse and consequent damage to the airplane and injury to occupants. Lhorne on DSK2VPTVN1PROD with RULES (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Repetitive Detailed Inspections With No Changes This paragraph restates the requirements of paragraph (g) of AD 2014–09–05, Amendment 39–17840 (79 FR 23909, April 29, 2014), with no changes. (1) For airplanes identified in paragraphs (g)(1)(i) and (g)(1)(ii) of this AD on which the affected MLG has exceeded 8 years since first overhaul, as of May 14, 2014 (the effective date of AD 2014–09–05, Amendment 39– 17840 (79 FR 23909, April 29, 2014), except those MLG that have had a second overhaul: Within 30 days after May 14, 2014, accomplish a detailed inspection for visible chrome of each affected MLG sidestay upper cardan pin, and associated nut and retainer assembly, in accordance with the instructions of Airbus Alert Operators Transmission (AOT) A32L003–14, dated March 10, 2014, including Appendices 1, 2, and 3 (the issue date is not specified on the appendices). (i) Airplanes equipped with any MLG sidestay upper cardan pin subassembly part number (P/N) 201267202 (on 201252 series MLG). (ii) Airplanes equipped with any MLG sidestay upper cardan pin subassembly P/N 201483202 (on 201490 series MLG). (2) If, during any inspection required by paragraph (g)(1) of this AD, no pin chrome is visible inboard of the wing rear spar fitting lug, repeat the detailed inspection for visible chrome specified in paragraph (g)(1) of this AD thereafter at intervals not to exceed 10 days. (3) If, during any inspection required by paragraphs (g)(1) or (g)(2) of this AD, a pin chrome is visible inboard of the wing rear spar fitting lug, before further flight, replace the affected cardan pin assembly, in accordance with the instructions of Airbus AOT A32L003–14, dated March 10, 2014, including Appendices 1, 2, and 3 (the issue date is not specified on the appendices). Replacement of the affected cardan pin assembly terminates the repetitive inspections required by paragraph (g)(2) of this AD. Note 1 to paragraph (g) of this AD: MLG sidestay upper cardan pin subassembly P/N 201267202 (found in Airbus Illustrated Parts Catalogue (IPC) as item 32–11–18–01) includes the cardan pin P/N 201267600. VerDate Sep<11>2014 14:17 May 28, 2015 Jkt 235001 MLG sidestay upper cardan pin subassembly P/N 201483202 (found in Airbus IPC as item 32–11–18–01) includes the cardan pin P/N 201483600. (h) New Terminating Action—Gap Check For airplanes identified in paragraphs (g)(1)(i) and (g)(1)(ii) of this AD on which the affected MLG has exceeded 8 years since first overhaul, as of May 14, 2014 (the effective date of AD 2014–09–05, Amendment 39– 17840 (79 FR 23909, April 29, 2014), except those MLG that have had a second overhaul: Within 4 months after the effective date of this AD: Measure the cardan pin clearance dimensions (gap check) and do the applicable corrective action specified in paragraph (h)(1) or (h)(2) of this AD. Measuring the gap check and doing the applicable corrective action specified in paragraph (h)(1) or (h)(2) of this AD, as applicable, terminates the inspections required by paragraphs (g)(1) and (g)(2) of this AD for that sidestay upper cardan pin, nut, and retainer only. The measurement must be done in accordance with Airbus AOT A32L003–14, dated March 10, 2014, including Appendices 1, 2, and 3 (the issue date is not specified on the appendices). (1) If the total clearance dimension (gap check result) is equal to or greater than 1.5 mm, before further flight, replace the cardan pin assembly, in accordance with Airbus AOT A32L003–14, dated March 10, 2014, including Appendices 1, 2, and 3 (the issue date is not specified on the appendices). (2) If the total clearance dimension (gap check) is less than 1.5 mm but greater than 0.6 mm, do the actions specified in paragraphs (h)(2)(i) or (h)(2)(ii) of this AD. (i) Do the actions specified in paragraphs (h)(2)(i)(A) and (h)(2)(i)(B) of this AD. (A) Within 30 days after accomplishing the gap check, send the information (Appendix 2 proforma, photographs, and the movement traceability sheet) specified in paragraph 4.2.3, ‘‘Findings,’’ of Airbus AOT A32L003– 14, dated March 10, 2014, including Appendices 1, 2, and 3 (the issue date is not specified on the appendices), to Airbus at the address specified in Appendix 2 (the issue date is not specified on this appendix) of Airbus AOT A32L003–14, dated March 10, 2014. (B) Within 30 days after accomplishing the gap check, 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). If approved by the DOA, the approval must include the DOA-authorized signature. (ii) Within 30 days after accomplishing the gap check, replace the cardan pin assembly, in accordance with Airbus AOT A32L003– 14, dated March 10, 2014, including Appendices 1, 2, and 3 (the issue date is not specified on the appendices). (i) New Reporting of Inspection Results For airplanes on which a gap check specified in paragraph (h) of this AD has been done: Except as required by paragraph (h)(2)(i) of this AD, at the applicable time specified in paragraphs (i)(1) and (i)(2) of this PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 30611 AD, report all findings (including no findings) to Airbus, in accordance with Airbus AOT A32L003–14, dated March 10, 2014, including Appendices 1, 2, and 3, (the issue date is not specified on the appendices). (1) If the gap check was done on or after the effective date of this AD: Submit the report within 30 days after the gap check. (2) If the gap check was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD. (j) 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-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) 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 EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Reporting Requirements: A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120–0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES–200. (k) Related Information Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA E:\FR\FM\29MYR1.SGM 29MYR1 30612 Federal Register / Vol. 80, No. 103 / Friday, May 29, 2015 / Rules and Regulations Airworthiness Directive 2014–0066 (Corrected March 20, 2014), for related information. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov/#!docketDetail;D=FAA2014-0584. (l) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (3) The following service information was approved for IBR on May 14, 2014, (79 FR 23909, April 29, 2014). (i) Airbus Alert Operators Transmission A32L003–14, dated March 10, 2014, including Appendices 1, 2, and 3 (the issue date is not specified on the appendices). (ii) Reserved. (4) 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 http://www.airbus.com. (5) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (6) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on April 30, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. Federal Aviation Administration (FAA), DOT. ACTION: Final rule. History On December 3, 2014, the FAA published in the Federal Register a notice of proposed rulemaking (NPRM) to remove Class E airspace at Forrest City, AR (79 FR 71710). Interested parties were invited to participate in this rulemaking effort by submitting written comments on the proposal to the FAA. No comments were received. Class E airspace designations are published in Paragraph 6005, of FAA Order 7400.9Y, dated August 6, 2014, and effective September 15, 2014, which is incorporated by reference in 14 CFR part 71.1. The Class E airspace designations listed in this document will be published subsequently in the Order. This action removes Class E airspace at Forrest City Municipal Airport, Forrest City, AR, due to the cancellation of Instrument Flight Rules (IFR) operations. The FAA is taking this Availability and Summary of Documents for Incorporation by Reference This document amends FAA Order 7400.9Y, Airspace Designations and [FR Doc. 2015–11393 Filed 5–28–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA–2014–0879; Airspace Docket No. 14–ASW–7] Revocation of Class E Airspace; Forrest City, AR AGENCY: Lhorne on DSK2VPTVN1PROD with RULES action to enhance airspace management within the National Airspace System (NAS). DATES: Effective 0901 UTC, August 20, 2015. The Director of the Federal Register approves this incorporation by reference action under title 1, Code of Federal Regulations, part 51, subject to the annual revision of FAA Order 7400.9 and publication of conforming amendments. ADDRESSES: FAA Order 7400.9Y, Airspace Designations and Reporting Points, and subsequent amendments can be viewed on line at http:// www.faa.gov/airtraffic/publications/. The Order is also available for inspection at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to http://www.archives.gov/ federal_register/code_of_federalregulations/ibr_locations.html. FAA Order 7400.9, Airspace Designations and Reporting Points, is published yearly and effective on September 15. For further information, you can contact the Airspace Policy and ATC Regulations Group, Federal Aviation Administration, 800 Independence Avenue SW., Washington, DC 29591; telephone: 202– 267–8783. FOR FURTHER INFORMATION CONTACT: Rebecca Shelby, Central Service Center, Operations Support Group, Federal Aviation Administration, Southwest Region, 2601 Meacham Blvd., Fort Worth, TX 76137; telephone: 817–321– 7740. SUPPLEMENTARY INFORMATION: SUMMARY: VerDate Sep<11>2014 14:17 May 28, 2015 Jkt 235001 PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 Reporting Points, dated August 6, 2014, and effective September 15, 2014. FAA Order 7400.9Y is publicly available as listed in the ADDRESSES section of this final rule. FAA Order 7400.9Y lists Class A, B, C, D, and E airspace areas, air traffic service routes, and reporting points. The Rule This action amends Title 14, Code of Federal Regulations (14 CFR) part 71 by removing Class E airspace extending upward from 700 feet above the surface at Forrest City Municipal Airport, Forrest City, AR. Controlled airspace is no longer needed due to cancellation of standard instrument approach procedures for IFR operations at the airport. The FAA has determined that this regulation only involves an established body of technical regulations for which frequent and routine amendments are necessary to keep them operationally current, is non-controversial and unlikely to result in adverse or negative comments. It, therefore, (1) is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034; February 26, 1979); and (3) does not warrant preparation of a Regulatory Evaluation as the anticipated impact is so minimal. Since this is a routine matter that only affects air traffic procedures and air navigation, it is certified that this rule, when promulgated, does not have a significant economic impact on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. The FAA’s authority to issue rules regarding aviation safety is found in Title 49 of the United States Code. 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. This rulemaking is promulgated under the authority described in Subtitle VII, Part A, Subpart I, Section 40103. Under that section, the FAA is charged with prescribing regulations to assign the use of airspace necessary to ensure the safety of aircraft and the efficient use of airspace. This regulation is within the scope of that authority as it removes controlled airspace at Forrest City Municipal Airport, Forrest City, AR. Environmental Review The FAA has determined that this action qualifies for categorical exclusion under the National Environmental Policy Act in accordance with FAA Order 1050.1E, ‘‘Environmental E:\FR\FM\29MYR1.SGM 29MYR1

Agencies

[Federal Register Volume 80, Number 103 (Friday, May 29, 2015)]
[Rules and Regulations]
[Pages 30608-30612]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-11393]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0584; Directorate Identifier 2014-NM-092-AD; 
Amendment 39-18158; AD 2015-10-03]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are superseding Airworthiness Directive (AD) 2014-09-05, 
for certain Airbus Model A330-200 and -300 series airplanes, and Model 
A340-200 and -300 series airplanes. AD 2014-09-05 required repetitive 
inspections of certain sidestay upper cardan pins of the main landing 
gear (MLG) and associated nuts and retainer assemblies, and pin 
replacement if necessary. This AD was prompted by a determination that 
a previously optional measurement is necessary to address the 
identified unsafe condition. This new AD continues to require a 
detailed inspection for visible chrome of each affected MLG sidestay 
upper cardan pin, associated nuts, and retainer assembly, and pin 
replacement if needed, and adds new requirements for measuring cardan 
pin clearance dimensions (gap check), doing corrective actions, and 
reporting all findings. We are issuing this AD to detect and correct 
migration of the sidestay upper cardan pin, which could result in 
disconnection of the sidestay upper arm from the airplane structure, 
and could result in a landing

[[Page 30609]]

gear collapse and consequent damage to the airplane and injury to 
occupants.

DATES: This AD becomes effective July 6, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of May 14, 2014 
(79 FR 23909, April 29, 2014).

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-0584; or in person at the 
Docket Management Facility, U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC.
    For service information identified in this AD, contact Airbus SAS--
Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; 
email airworthiness.A330-A340@airbus.com; Internet http://www.airbus.com. You may view this referenced service information at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, call 
425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0584.

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

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2014-09-05, Amendment 39-17840 (79 FR 23909, 
April 29, 2014). AD 2014-09-05 applied to certain Airbus Model A330-200 
and -300 series airplanes, and Model A340-200 and -300 series 
airplanes. The NPRM published in the Federal Register on August 26, 
2014 (79 FR 50863).
    The European Aviation Safety Agency, which is the Technical Agent 
for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2014-0066, corrected March 20, 2014 (referred 
to after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition on certain Airbus Model 
A330-200 and -300 series airplanes, and Model A340-200 and -300 series 
airplanes. The MCAI states:

    An A330 aeroplane equipped with Basic (main landing gear) MLG 
was rolling out after landing when it experienced a nose wheel 
steering fault (unrelated to the safety subject addressed by this 
[EASA] AD), which resulted in the crew stopping the aeroplane on the 
taxiway after vacating the runway.
    The subsequent investigation revealed that the right-hand MLG 
sidestay upper cardan pin had migrated out of position. The sidestay 
upper cardan nut and retainer were found in the landing gear bay 
detached from the upper cardan pin. The nut and the retainer were 
still bolted together.
    This condition, if not detected and corrected, could lead to a 
complete migration of the sidestay upper cardan pin and a 
disconnection of the sidestay upper arm from the aeroplane 
structure, possibly resulting in MLG collapse with consequent damage 
to the aeroplane and injury to occupants.
    To address this potential condition, Airbus published Alert 
Operators Transmission (AOT) A32L003-14, providing inspection 
instructions.
    For the reasons described above, this [EASA] AD requires 
accomplishment of repetitive [detailed inspections for visible 
chrome] of the MLG upper cardan pin, nut and retainer [and pin 
replacement if necessary]. This [EASA] AD also requires 
accomplishment of a gap check between wing rear spar fitting lugs 
and the bush flanges [and corrective actions if necessary. 
Corrective actions include repair or replacement of the cardan pin 
assembly].

You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2014-0584-0003.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM (79 
FR 50863, August 26, 2014) and the FAA's response to each comment.

Request To Match the Applicability of Terminating Action to Inspections

    U.S. Airways requested that we revise the affected airplanes of 
paragraph (h) of the NPRM (79 FR 50863, August 26, 2014) to match those 
of paragraph (g) of the NPRM. U.S. Airways stated that paragraph (g) of 
the NPRM limits the repetitive inspections to MLG that have exceeded 8 
years since first overhaul but not yet had a second overhaul; whereas 
paragraph (h) of the NPRM provides a new terminating action to the 
repetitive inspections, but does not limit the applicability to MLG 
that have exceeded 8 years since first overhaul but not yet had a 
second overhaul.
    We agree to revise the affected airplanes of paragraph (h) of this 
AD because the terminating action provisions of paragraph (h) of the 
NPRM (79 FR 50863, August 26, 2014) was intended to apply to the same 
subset of affected airplanes identified in paragraph (g)(1) of the 
NPRM. We have changed the language in paragraph (h) of this AD by 
limiting the affected airplanes to those identified in paragraph (g)(1) 
of this AD.

Request To Change Compliance Time of Sending Results of Gap Check

    U.S. Airways requested that we revise the compliance time for 
sending the results of the inspection and gap check to Airbus from 
``before further flight'' to ``within 30 days.'' U.S. Airways stated 
that paragraph (h)(2)(i) of the NPRM (79 FR 50863, August 26, 2014) 
states to send inspection findings to Airbus ``before further flight,'' 
if the gap check result measures between 0.6 mm and 1.5 mm, and 
paragraph (h)(2)(ii) states to repair within 30 days. U.S. Airways 
stated that mechanics who inspect the cardan pin typically do not send 
data directly to Airbus and that since the repair is not required for 
30 days after the inspection, communicating the inspection findings 
should not restrict aircraft flight.
    We agree to revise the compliance time because the proposed 
compliance time for sending the results of the inspection and gap check 
does not affect the compliance time for accomplishment of the repair. 
We have changed the compliance time in paragraph (h)(2)(i) of this AD 
from before further flight, to 30 days. This difference has been 
coordinated with EASA.

Request To Allow Replacement of Cardan Pin Assembly as Terminating 
Action

    U.S. Airways requested that we allow the replacement of the cardan 
pin assembly to be considered as a terminating action. Paragraph (h)(1) 
of the NPRM (79 FR 50863, August 26, 2014) would mandate the 
replacement of the cardan pin if the gap is found to be greater than 
1.5mm. However paragraph (h)(2) of the NPRM would require an approved 
repair for smaller gaps. US Airways suggested that the AD also allow 
the replacement of the cardan pin assembly before further flight as an 
alternative to the actions specified in paragraphs (h)(2)(i) and 
(h)(2)(ii) of the NPRM.
    We agree with the request to allow replacement of the cardan pin 
assembly as an alternative to small repairs because replacing the 
cardan pin assembly is terminating action regardless of the size of the 
gap. We have revised paragraph (h) of this AD to

[[Page 30610]]

provide for replacement of the cardan pin assembly as an option to 
doing a repair.

Related Service Information Under 1 CFR Part 51

    The manufacturer has issued Airbus AOT A32L003-14, dated March 10, 
2014. The service information describes procedures for inspecting 
sidestay upper cardan pins of the MLG and associated nuts and retainer 
assemblies. 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 
AD.

Conclusion

    We reviewed the available data, including the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these changes:
     Are consistent with the intent that was proposed in the 
NPRM (79 FR 50863, August 26, 2014) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (79 FR 50863, August 26, 2014).

Costs of Compliance

    We estimate that this AD affects 83 airplanes of U.S. registry.
    The actions required by AD 2014-09-05, Amendment 39-17840 (79 FR 
23909, April 29, 2014), and retained in this AD take about 1 work-hour 
per product, at an average labor rate of $85 per work-hour. Required 
parts cost $0 per product. Based on these figures, the estimated cost 
of the actions that were required by AD 2014-09-05 is $85 per product.
    We also estimate that it will take about 1 work-hour per product to 
comply with the new basic requirements of this AD. The average labor 
rate is $85 per work-hour. Based on these figures, we estimate the cost 
of this AD on U.S. operators to be $7,055, or $85 per product.
    In addition, we estimate that any necessary follow-on actions will 
take about 4 work-hours and require parts costing $7,530, for a cost of 
$7,870 per product. We have no way of determining the number of 
aircraft that might need these actions.

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a current valid OMB control number. The control 
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in 
the Costs of Compliance section of this document and includes time for 
reviewing instructions, as well as completing and reviewing the 
collection of information. Therefore, all reporting associated with 
this AD is mandatory. Comments concerning the accuracy of this burden 
and suggestions for reducing the burden should be directed to the FAA 
at 800 Independence Ave. SW., Washington, DC 20591, ATTN: Information 
Collection Clearance Officer, AES-200.

Authority for This Rulemaking

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

Regulatory Findings

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

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2014-0584; or in person at the 
Docket Management Facility between 9 a.m. and 5 p.m., Monday through 
Friday, except Federal holidays. The AD docket contains this AD, the 
regulatory evaluation, any comments received, and other information. 
The street address for the Docket Operations office (telephone 800-647-
5527) is in the ADDRESSES section.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2014-09-05, Amendment 39-17840 (79 FR 23909, April 29, 2014), and 
adding the following new AD:

2015-10-03 Airbus: Amendment 39-18158. Docket No. FAA-2014-0584; 
Directorate Identifier 2014-NM-092-AD.

(a) Effective Date

    This AD becomes effective July 6, 2015.

(b) Affected ADs

    This AD replaces AD 2014-09-05, Amendment 39-17840 (79 FR 23909, 
April 29, 2014).

(c) Applicability

    This AD applies to the airplanes identified in paragraphs (c)(1) 
and (c)(2) of this AD, certificated in any category.
    (1) Airbus Model A330-201, -202, -203, -223, -243, -301, -302, -
303, -321, -322, -323, -341, -342, and -343 airplanes, all 
manufacturer serial numbers (MSNs), equipped with basic (201252 
series) main landing gear (MLG), or growth (201490 series) MLG.
    (2) Airbus Model A340-211, -212, -213, -311, -312, and -313 
airplanes, all MSNs, equipped with basic (201252 series) MLG or 
growth (201490 series) MLG.

[[Page 30611]]

(d) Subject

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

(e) Reason

    This AD was prompted by a report of a sidestay upper cardan pin 
of the MLG migrating out of position. We are issuing this AD to 
detect and correct migration of the sidestay upper cardan pin, which 
could result in disconnection of the sidestay upper arm from the 
airplane structure, and could result in a landing gear collapse and 
consequent damage to the airplane and injury to occupants.

(f) Compliance

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

(g) Retained Repetitive Detailed Inspections With No Changes

    This paragraph restates the requirements of paragraph (g) of AD 
2014-09-05, Amendment 39-17840 (79 FR 23909, April 29, 2014), with 
no changes.
    (1) For airplanes identified in paragraphs (g)(1)(i) and 
(g)(1)(ii) of this AD on which the affected MLG has exceeded 8 years 
since first overhaul, as of May 14, 2014 (the effective date of AD 
2014-09-05, Amendment 39-17840 (79 FR 23909, April 29, 2014), except 
those MLG that have had a second overhaul: Within 30 days after May 
14, 2014, accomplish a detailed inspection for visible chrome of 
each affected MLG sidestay upper cardan pin, and associated nut and 
retainer assembly, in accordance with the instructions of Airbus 
Alert Operators Transmission (AOT) A32L003-14, dated March 10, 2014, 
including Appendices 1, 2, and 3 (the issue date is not specified on 
the appendices).
    (i) Airplanes equipped with any MLG sidestay upper cardan pin 
subassembly part number (P/N) 201267202 (on 201252 series MLG).
    (ii) Airplanes equipped with any MLG sidestay upper cardan pin 
subassembly P/N 201483202 (on 201490 series MLG).
    (2) If, during any inspection required by paragraph (g)(1) of 
this AD, no pin chrome is visible inboard of the wing rear spar 
fitting lug, repeat the detailed inspection for visible chrome 
specified in paragraph (g)(1) of this AD thereafter at intervals not 
to exceed 10 days.
    (3) If, during any inspection required by paragraphs (g)(1) or 
(g)(2) of this AD, a pin chrome is visible inboard of the wing rear 
spar fitting lug, before further flight, replace the affected cardan 
pin assembly, in accordance with the instructions of Airbus AOT 
A32L003-14, dated March 10, 2014, including Appendices 1, 2, and 3 
(the issue date is not specified on the appendices). Replacement of 
the affected cardan pin assembly terminates the repetitive 
inspections required by paragraph (g)(2) of this AD.
    Note 1 to paragraph (g) of this AD: MLG sidestay upper cardan 
pin subassembly P/N 201267202 (found in Airbus Illustrated Parts 
Catalogue (IPC) as item 32-11-18-01) includes the cardan pin P/N 
201267600. MLG sidestay upper cardan pin subassembly P/N 201483202 
(found in Airbus IPC as item 32-11-18-01) includes the cardan pin P/
N 201483600.

(h) New Terminating Action--Gap Check

    For airplanes identified in paragraphs (g)(1)(i) and (g)(1)(ii) 
of this AD on which the affected MLG has exceeded 8 years since 
first overhaul, as of May 14, 2014 (the effective date of AD 2014-
09-05, Amendment 39-17840 (79 FR 23909, April 29, 2014), except 
those MLG that have had a second overhaul: Within 4 months after the 
effective date of this AD: Measure the cardan pin clearance 
dimensions (gap check) and do the applicable corrective action 
specified in paragraph (h)(1) or (h)(2) of this AD. Measuring the 
gap check and doing the applicable corrective action specified in 
paragraph (h)(1) or (h)(2) of this AD, as applicable, terminates the 
inspections required by paragraphs (g)(1) and (g)(2) of this AD for 
that sidestay upper cardan pin, nut, and retainer only. The 
measurement must be done in accordance with Airbus AOT A32L003-14, 
dated March 10, 2014, including Appendices 1, 2, and 3 (the issue 
date is not specified on the appendices).
    (1) If the total clearance dimension (gap check result) is equal 
to or greater than 1.5 mm, before further flight, replace the cardan 
pin assembly, in accordance with Airbus AOT A32L003-14, dated March 
10, 2014, including Appendices 1, 2, and 3 (the issue date is not 
specified on the appendices).
    (2) If the total clearance dimension (gap check) is less than 
1.5 mm but greater than 0.6 mm, do the actions specified in 
paragraphs (h)(2)(i) or (h)(2)(ii) of this AD.
    (i) Do the actions specified in paragraphs (h)(2)(i)(A) and 
(h)(2)(i)(B) of this AD.
    (A) Within 30 days after accomplishing the gap check, send the 
information (Appendix 2 proforma, photographs, and the movement 
traceability sheet) specified in paragraph 4.2.3, ``Findings,'' of 
Airbus AOT A32L003-14, dated March 10, 2014, including Appendices 1, 
2, and 3 (the issue date is not specified on the appendices), to 
Airbus at the address specified in Appendix 2 (the issue date is not 
specified on this appendix) of Airbus AOT A32L003-14, dated March 
10, 2014.
    (B) Within 30 days after accomplishing the gap check, 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). If approved by the DOA, the approval must include the DOA-
authorized signature.
    (ii) Within 30 days after accomplishing the gap check, replace 
the cardan pin assembly, in accordance with Airbus AOT A32L003-14, 
dated March 10, 2014, including Appendices 1, 2, and 3 (the issue 
date is not specified on the appendices).

(i) New Reporting of Inspection Results

    For airplanes on which a gap check specified in paragraph (h) of 
this AD has been done: Except as required by paragraph (h)(2)(i) of 
this AD, at the applicable time specified in paragraphs (i)(1) and 
(i)(2) of this AD, report all findings (including no findings) to 
Airbus, in accordance with Airbus AOT A32L003-14, dated March 10, 
2014, including Appendices 1, 2, and 3, (the issue date is not 
specified on the appendices).
    (1) If the gap check was done on or after the effective date of 
this AD: Submit the report within 30 days after the gap check.
    (2) If the gap check was done before the effective date of this 
AD: Submit the report within 30 days after the effective date of 
this AD.

(j) 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. 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) 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 EASA; 
or Airbus's EASA DOA. If approved by the DOA, the approval must 
include the DOA-authorized signature.
    (3) Reporting Requirements: A federal agency may not conduct or 
sponsor, and a person is not required to respond to, nor shall a 
person be subject to a penalty for failure to comply with a 
collection of information subject to the requirements of the 
Paperwork Reduction Act unless that collection of information 
displays a current valid OMB Control Number. The OMB Control Number 
for this information collection is 2120-0056. Public reporting for 
this collection of information is estimated to be approximately 5 
minutes per response, including the time for reviewing instructions, 
completing and reviewing the collection of information. All 
responses to this collection of information are mandatory. Comments 
concerning the accuracy of this burden and suggestions for reducing 
the burden should be directed to the FAA at: 800 Independence Ave. 
SW., Washington, DC 20591, Attn: Information Collection Clearance 
Officer, AES-200.

(k) Related Information

    Refer to Mandatory Continuing Airworthiness Information (MCAI) 
EASA

[[Page 30612]]

Airworthiness Directive 2014-0066 (Corrected March 20, 2014), for 
related information. You may examine the MCAI in the AD docket on 
the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-
2014-0584.

(l) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (3) The following service information was approved for IBR on 
May 14, 2014, (79 FR 23909, April 29, 2014).
    (i) Airbus Alert Operators Transmission A32L003-14, dated March 
10, 2014, including Appendices 1, 2, and 3 (the issue date is not 
specified on the appendices).
    (ii) Reserved.
    (4) 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 http://www.airbus.com.
    (5) You may view this service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.
    (6) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on April 30, 2015.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-11393 Filed 5-28-15; 8:45 am]
BILLING CODE 4910-13-P