Airworthiness Directives; Airbus Airplanes, 69846-69852 [2015-27449]

Download as PDF 69846 Federal Register / Vol. 80, No. 218 / Thursday, November 12, 2015 / Rules and Regulations and (i) of AD 2013–09–01, Amendment 39– 17442 (78 FR 27001, May 9, 2013), for the replaced skin panel only. (r) Exceptions to Service Information Specifications (1) Where Boeing Service Bulletin 737– 53A1177, Revision 7, dated June 14, 2013, specifies a compliance time ‘‘after the Revision 7 date of this service bulletin,’’ this AD requires compliance within the specified compliance time after the effective date of this AD. (2) Where Boeing Service Bulletin 737– 53A1177, Revision 6, dated May 31, 2001; and Boeing Service Bulletin 737–53A1177, Revision 7, dated June 14, 2013; specify to contact Boeing for certain procedures: Do the specified actions before further flight using a method approved in accordance with the procedures specified in paragraph (t) of this AD. (3) Where Boeing Service Bulletin 737– 53A1177, Revision 6, dated May 31, 2001; and Boeing Service Bulletin 737–53A1177, Revision 7, dated June 14, 2013; include the phrase ‘‘or is Boeing or FAA approved,’’ this AD requires the ‘‘Boeing Approval’’ to be requested in accordance with the procedures specified in paragraph (t) of this AD. mstockstill on DSK4VPTVN1PROD with RULES (s) Credit for Previous Actions (1) This paragraph provides credit for the actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using the applicable service information specified in paragraphs (s)(1)(i), (s)(1)(ii), and (s)(1)(iii) of this AD, which were incorporated by reference in AD 2002–07–08, Amendment 39–12702 (67 FR 17917, April 12, 2002). (i) Boeing Service Bulletin 737–53A1177, Revision 4, dated September 2, 1999. (ii) Boeing Service Bulletin 737–53A1177, Revision 5, dated February 15, 2001, which continues to be incorporated by reference in this AD. (iii) Boeing Service Bulletin 737–53A1177, Revision 6, dated May 31, 2001, which continues to be incorporated by reference in this AD. (2) This paragraph provides credit for the actions required by paragraphs (i) through (o) of this AD, if those actions were performed before the effective date of this AD using Boeing Service Bulletin 737–53A1177, Revision 6, dated May 31, 2001, which was incorporated by reference in AD 2002–07–08, Amendment 39–12702 (67 FR 17917, April 12, 2002) and continues to be incorporated by reference in this AD. (t) 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 (u)(1) of this AD. Information may be emailed to: 9-ANM-LAACO-AMOCRequests@faa.gov. VerDate Sep<11>2014 17:30 Nov 10, 2015 Jkt 238001 (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. (4) AMOCs approved for AD 2002–07–08, Amendment 39–12702 (67 FR 17917, April 12, 2002), are approved as AMOCs for the corresponding provisions of this AD. Issued in Renton, Washington, on October 11, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–26616 Filed 11–10–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–2461; Directorate Identifier 2013–NM–202–AD; Amendment 39–18310; AD 2015–22–05] RIN 2120–AA64 (u) Related Information (1) For more information about this AD, contact Jennifer Tsakoumakis, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712–4137; phone: 562–627– 5264; fax: 562–627–5210; email: Jennifer.Tsakoumakis@faa.gov. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (v)(3) and (v)(4) of this AD. (v) 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 Service Bulletin 737–53A1177, Revision 7, dated June 14, 2013. (ii) Reserved. (3) The following service information was approved for IBR on May 17, 2002 (67 FR 17917, April 12, 2002). (i) Boeing Service Bulletin 737–53A1177, Revision 5, dated February 15, 2001. (ii) Boeing Service Bulletin 737–53A1177, Revision 6, dated May 31, 2001. (4) For Boeing 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. (5) You may view this service information at 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. PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 2009–18– 15, for all Airbus Model A300, A310, and A300 B4–600, B4–600R, and F4– 600R series airplanes, and Model A300 C4–605R Variant F airplanes (collectively called Model A300–600 series airplanes). AD 2009–18–15 required revising the Airworthiness Limitations section (ALS) of the Instructions for Continued Airworthiness (ICA) to require additional life limits and/or replacements for certain main landing gear and nose landing gear components. This new AD requires revising the maintenance or inspection program to incorporate new maintenance requirements and airworthiness limitations. This AD was prompted by a determination that existing maintenance requirements and airworthiness limitations are inadequate to ensure the structural integrity of the airplane. We are issuing this AD to prevent failure of certain system components, which could result in reduced structural integrity of the airplane. DATES: This AD becomes effective December 17, 2015. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of December 17, 2015. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of October 27, 2009 (74 FR 48143, September 22, 2009). ADDRESSES: You may examine the AD docket on the Internet at http:// SUMMARY: E:\FR\FM\12NOR1.SGM 12NOR1 Federal Register / Vol. 80, No. 218 / Thursday, November 12, 2015 / Rules and Regulations www.regulations.gov/#!docketDetail;D= FAA-2015-2461; or in person at the Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC. For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 2461. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–2125; fax 425–227–1149. SUPPLEMENTARY INFORMATION: mstockstill on DSK4VPTVN1PROD with RULES Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2009–18–15, Amendment 39–16011 (74 FR 48143, September 22, 2009). AD 2009–18–15 applied to all Airbus Model A300, A310, and A300 B4–600, B4–600R, and F4–600R series airplanes; and Model A300 C4–605R Variant F airplanes (collectively called Model A300–600 series airplanes). The NPRM published in the Federal Register on July 14, 2015 (80 FR 40942). The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2013–0248, dated October 14, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Model A300, A310, and A300–600 series airplanes. The MCAI states: The airworthiness limitations for Airbus aeroplanes are currently published in Airworthiness Limitations Section (ALS) documents. The mandatory instructions and airworthiness limitations applicable to the Aging Systems Maintenance (ASM) are specified in Airbus A310 or A300–600 ALS Part 4 documents, which are approved by the VerDate Sep<11>2014 17:30 Nov 10, 2015 Jkt 238001 69847 European Aviation Safety Agency (EASA). EASA AD 2007–0092 [http:// ad.easa.europa.eu/blob/easa_ad_2007_ 0092.pdf/AD_2007-0092] [which corresponds to FAA AD 2009–06–06, Amendment 39– 15842 (74 FR 12228, March 24, 2009)] was issued to require compliance to the requirements as specified in these documents. The revision 02 of Airbus A310 and Airbus A300–600 ALS Part 4 documents introduces more restrictive maintenance requirements and/or airworthiness limitations. Failure to comply with the instructions of ALS Part 4 could result in an unsafe condition [reduced structural integrity of the airplane.] For the reasons described above, this new [EASA] AD retains the requirements of EASA AD 2007–0092, which is superseded, and requires the implementation of the new or more restrictive maintenance requirements and/or airworthiness limitations as specified in Airbus A310 ALS Part 4, Revision 02, or Airbus A300–600 ALS Part 4, Revision 02, as applicable to aeroplane type/model. • For Model A300 B4–600, B4–600R, and F4–600R series airplanes, and Model A300 C4–605R Variant F airplanes (collectively called Model A300–600 series airplanes): Part 1, ‘‘Safe Life Airworthiness Limitation Items,’’ Revision 01, dated September 5, 2013, of the Airbus Model A300–600 Airworthiness Limitations Section. • For Model A310 series airplanes: Part 1, ‘‘Safe Life Airworthiness Limitation Items,’’ Revision 01, dated September 5, 2013, of the Airbus Model A310 Airworthiness Limitations Section. 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. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov/#!document Detail;D=FAA-2015-2461-0002. Costs of Compliance Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (80 FR 40942, July 14, 2015) or on the determination of the cost to the public. Conclusion We reviewed the available data and determined that air safety and the public interest require adopting this AD as proposed, except for minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM (80 FR 40942, July 14, 2015) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (80 FR 40942, July 14, 2015). Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information. ‘‘Sub-part 1–2: Life Limits’’ and ‘‘Sub-part 1–3: Demonstrated fatigue lives’’ of Part 1, ‘‘Safe Life Airworthiness Limitation Items,’’ in each of these documents describe procedures for revising the maintenance or inspection program to incorporate new maintenance requirements and airworthiness limitations. • For Model A300 series airplanes: Part 1, ‘‘Safe Life Airworthiness Limitation Items,’’ Revision 01, dated September 5, 2013, of the Airbus Model A300 Airworthiness Limitations Section. PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 We estimate that this AD affects 177 airplanes of U.S. registry. The retained ALS revision required by AD 2009–18–15, Amendment 39–16011 (74 FR 48143, September 22, 2009), takes about 1 work-hour per product, at an average labor rate of $85 per workhour. Based on these figures, the estimated cost of the actions that were required by AD 2009–18–15 is $85 per product. We also estimate that it takes about 1 work-hour per product to comply with the new ALS revision 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 $15,045, or $85 per product. 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. E:\FR\FM\12NOR1.SGM 12NOR1 69848 Federal Register / Vol. 80, No. 218 / Thursday, November 12, 2015 / Rules and Regulations 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 (a) Effective Date This AD becomes effective December 17, 2015. (b) Affected ADs (1) This AD replaces AD 2009–18–15, Amendment 39–16011 (74 FR 48143, September 22, 2009). (2) Accomplishing certain requirements of paragraph (g) of this AD satisfies the requirements of paragraph A. of AD 84–02– 04, Amendment 39–4795 (49 FR 2746, January 23, 1984). (c) Applicability This AD applies to Airbus Model A300 B2– 1A, B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and B4–203 airplanes; Model A300 B4–601, B4–603, B4–620, and B4–622 airplanes; Model A300 B4–605R and B4–622R airplanes; Model A300 F4–605R and F4– 622R, and A300 C4–605R Variant F airplanes; and Model A310–203, –204, –221, –222, –304, –322, –324, and –325 airplanes; certificated in any category, all manufacturer serial numbers. (d) Subject Air Transport Association (ATA) of America 32, Landing Gear. You may examine the AD docket on the Internet at http:// www.regulations.gov/#!docket Detail;D=FAA-2015-2461; 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. (e) Reason This AD was prompted by a determination that existing maintenance requirements and airworthiness limitations are inadequate to ensure the structural integrity of the airplane. We are issuing this AD to prevent failure of certain system components, which could result in reduced structural integrity of the airplane. List of Subjects in 14 CFR Part 39 (g) Retained Revision of Airworthiness Limitation Section (ALS) This paragraph restates the requirements of paragraph (h) of AD 2009–18–15, Amendment 39–16011 (74 FR 48143, September 22, 2009). For Model A300, A310, and A300–600 series airplanes: Within 3 months after October 27, 2009 (the effective date of AD 2009–18–15), revise the ALS of the instructions for continued airworthiness (ICA) to incorporate the applicable document listed in paragraph (g)(1), (g)(2), or (g)(3) of this AD. Accomplishing the actions specified in the applicable document satisfies the requirements of paragraph A. of AD 84–02– 04, Amendment 39–4795 (49 FR 2746, January 23, 1984). (1) For Model A300 series airplanes: Incorporate the applicable document listed in paragraph (g)(1)(i) or (g)(1)(ii) of this AD. (i) Section 05–10–00, Revision 28, dated February 27, 1998, of Chapter 05, ‘‘Service Life Limits and Maintenance Checks,’’ of the Airbus A300 Aircraft Maintenance Manual, except that the parts listed in table 1 to paragraph (g) of this AD are subject to the life limits defined in the document listed in paragraph (g)(1)(ii) of this AD. (ii) ‘‘Sub-part 1–2: Life Limits,’’ and ‘‘Subpart 1–3: Demonstrated Fatigue Lives’’ of Part 1, ‘‘Safe Life Airworthiness Limitation 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. mstockstill on DSK4VPTVN1PROD with RULES § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive AD 2009–18–15, Amendment 39–16011 (74 FR 48143, September 22, 2009), and adding the following new AD: ■ 2015–22–05 Airbus: Amendment 39–18310. Docket No. FAA–2015–2461; Directorate Identifier 2013–NM–202–AD. VerDate Sep<11>2014 17:30 Nov 10, 2015 Jkt 238001 (f) Compliance Comply with this AD within the compliance times specified, unless already done. PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 Items,’’ dated September 6, 2007, of the Airbus A300 ALS. TABLE 1 TO PARAGRAPH (g) OF THIS AD—PARTS SUBJECT TO THE LIFE LIMITS SPECIFIED IN THE DOCUMENT IDENTIFIED IN PARAGRAPH (g)(1)(ii) OF THIS AD Part No. (P/N) Part name P/N C61643–2, P/N C61643–4, P/N C61643–5. P/N A32210001205xx Main landing gear (MLG) shock absorber end fitting. Nose landing gear (NLG) pintle pin. NLG shock absorber bottom. Cross beam (Pratt & Whitney forward engine mount). P/N C62037–1 .......... P/N 196–0328–501 ... (2) For Model A310 series airplanes: Incorporate ‘‘Sub-part 1–2: Life Limits,’’ and ‘‘Sub-part 1–3: Demonstrated Fatigue Lives’’ of Part 1, ‘‘Safe Life Airworthiness Limitation Items,’’ dated December 21, 2006, of the Airbus A310 ALS. (3) For Model A300 B4–600, B4–600R, and F4–600R series airplanes, and Model A300 C4–605R Variant F airplanes (collectively called Model A300–600 series airplanes): Incorporate ‘‘Sub-part 1–2: Life Limits,’’ and ‘‘Sub-part 1–3: Demonstrated Fatigue Lives’’ of Part 1, ‘‘Safe Life Airworthiness Limitation Items,’’ dated December 21, 2006, of the Airbus A300–600 ALS. (h) Retained Initial Compliance Times and Repetitive Inspections This paragraph restates the requirements of paragraph (i) of AD 2009–18–15, Amendment 39–16011 (74 FR 48143, September 22, 2009). Do the replacement at the applicable time specified in paragraph (h)(1) or (h)(2) of this AD, except as provided by paragraph (i) of this AD. The replacement must be done thereafter within the interval specified in the applicable document identified in paragraph (g)(1), (g)(2), or (g)(3) of this AD. (1) For any life limitation/task that has been complied with before October 27, 2009 (the effective date of AD 2009–18–15, Amendment 39–16011), in accordance with the applicable document listed in paragraph (g)(1), (g)(2), or (g)(3) of this AD, or in accordance with paragraph (g) of AD 2009– 18–15, use the last accomplishment of each limitation/task as a starting point for accomplishing each corresponding limitation/task required by this AD. (2) For any life limitation/task that has not been complied with before October 27, 2009 (the effective date of AD 2009–18–15, Amendment 39–16011), in accordance with the applicable document listed in paragraphs (g)(1), (g)(2), and (g)(3) of this AD, or in accordance with paragraph (g) of AD 2009– 18–15, the initial compliance time starts from the date of initial entry into service as defined in the applicable document. (i) Retained Special Compliance Times This paragraph restates the requirements of paragraph (j) of AD 2009–18–15, Amendment E:\FR\FM\12NOR1.SGM 12NOR1 69849 Federal Register / Vol. 80, No. 218 / Thursday, November 12, 2015 / Rules and Regulations 39–16011 (74 FR 48143, September 22, 2009). For any airplane on which the history of accumulated landings is partial or unknown, or where the history of application details (airplane type, model, weight variant, etc.) is partial or unknown: Parts listed in figure 1 to paragraph (i) of this AD must be replaced at the associated compliance time. The replacement must be done thereafter at the interval specified in the applicable document(s) specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD. Note 1 to paragraph (i) of this AD: Airbus Service Information Letter 32–118, Revision 02, dated October 24, 2007, provides operators with guidance on the means to assign a conservative calculated life to parts whose history of accumulated landings is partial or unknown; and to select the limitations applicable to parts whose history of application details (aircraft type, aircraft model, weight variant, etc.) is partial or unknown. FIGURE 1 TO PARAGRAPH (i) OF THIS AD—SPECIAL COMPLIANCE TIMES Aircraft type applicability A300 Designation A310 A300–600 Start date Compliance time (whichever occurs first after the ‘‘start date’’) P/N X X X Calendar time Landings MAIN LANDING GEAR Aft pintle pin ................. Half ball housing (Fwd pintle bearing). Ball (Fwd pintle pin) ..... Pin (Multiple link/Frame 50). Pin (Drop link/Frame 50). A32140032200xx A32140056200xx A32140056202xx A32140057200xx A32140057202xx A32140062000xx A32140063000xx A32140036200xx A32140036202xx A32140036204xx A32140036206xx A32140042200xx A32140042202xx A32140068002xx A32140068004xx A32140069002xx A32140069004xx A32140012202xx A32140043202xx A53833451200xx A53833451206xx A53834451200xx A53834451202xx A53811122200xx ......... ......... ......... ......... ......... ......... ......... ......... ......... ......... ......... ......... ......... ......... ......... ......... ......... ......... ......... ......... ......... ......... ......... ......... X X X X X X X X X X X X X X X X X X X X X X X .................. .................. .................. .................. .................. .................. .................. .................. .................. .................. .................. .................. .................. .................. .................. .................. .................. .................. .................. .................. .................. .................. .................. .................. X .................. .................. .................. .................. X .................. X .................. .................. .................. .................. X X .................. .................. X X .................. X .................. .................. .................. X .................. December 13, December 13, December 13, December 13, December 13, December 13, December 13, December 13, December 13, December 13, December 13, December 13, December 13, December 13, December 13, December 13, December 13, December 13, December 13, December 13, December 13, December 13, April 25, 2007 April 25, 2007 2007 ..... 2007 ..... 2007 ..... 2007 ..... 2007 ..... 2007 ..... 2007 ..... 2007 ..... 2007 ..... 2007 ..... 2007 ..... 2007 ..... 2007 ..... 2007 ..... 2007 ..... 2007 ..... 2007 ..... 2007 ..... 2007 ..... 2007 ..... 2007 ..... 2007 ..... .............. .............. 13,500 13,500 13,500 13,500 13,500 13,500 13,500 13,500 13,500 13,500 13,500 13,500 13,500 13,500 13,500 13,500 13,500 13,500 13,500 13,500 13,500 13,500 13,500 18,000 9 9 9 9 9 9 9 9 9 9 9 9 9 9 9 9 9 9 9 9 9 9 9 9 years. years. years. years. years. years. years. years. years. years. years. years. years. years. years. years. years. years. years. years. years. years. years. years. December 13, December 13, December 13, December 13, April 25, 2007 December 13, April 25, 2007 December 13, April 25, 2007 December 13, April 25, 2007 December 13, December 13, December 13, December 13, December 13, April 25, 2007 April 25, 2007 2007 ..... 2007 ..... 2007 ..... 2007 ..... .............. 2007 ..... .............. 2007 ..... .............. 2007 ..... .............. 2007 ..... 2007 ..... 2007 ..... 2007 ..... 2007 ..... .............. .............. N/A N/A N/A N/A N/A N/A N/A N/A N/A 13,500 13,500 13,500 13,500 13,500 13,500 13,500 13,500 18,000 30 months. 30 months. 30 months. 30 months. 30 months. 30 months. 30 months. 30 months. 30 months. 9 years. 9 years. 9 years. 9 years. 9 years. 9 years. 9 years. 9 years. 9 years. December 13, December 13, December 13, December 13, April 25, 2007 2007 ..... 2007 ..... 2007 ..... 2007 ..... .............. N/A N/A N/A N/A N/A MLG Barrel Assembly Upper torque link pin nut. Torque link medium pin nut. Attaching fitting pin ....... mstockstill on DSK4VPTVN1PROD with RULES Pin (Connecting rod/ Upper rod). 00–200–402 ................. SL40089 ...................... SL40089P .................... SL40123 ...................... SL40123P .................... 00–200–358 ................. SL40114P .................... SL40132 ...................... SL40132P .................... C62311–1 .................... C62311–20 .................. C65815 ........................ C65815–1 .................... C65815–20 .................. C66472 ........................ C66472–1 .................... C66472–20 .................. D52751 ........................ X X X X X X X X X X X X X X X X X .................. .................. .................. .................. .................. X .................. X .................. .................. .................. .................. .................. .................. .................. .................. .................. .................. X .................. .................. .................. .................. X .................. .................. .................. X .................. X .................. .................. .................. .................. .................. X .................. MLG Shock Absorber Assembly Lower torque link pin nut. VerDate Sep<11>2014 00–200–402 ................. SL40089 ...................... SL40089P .................... SL40123 ...................... SL40123P .................... 17:30 Nov 10, 2015 Jkt 238001 PO 00000 X X X X X Frm 00013 .................. .................. .................. .................. X Fmt 4700 .................. .................. .................. .................. X Sfmt 4700 E:\FR\FM\12NOR1.SGM 12NOR1 30 30 30 30 30 months. months. months. months. months. 69850 Federal Register / Vol. 80, No. 218 / Thursday, November 12, 2015 / Rules and Regulations FIGURE 1 TO PARAGRAPH (i) OF THIS AD—SPECIAL COMPLIANCE TIMES—Continued Aircraft type applicability A300 Designation A310 A300–600 Start date Compliance time (whichever occurs first after the ‘‘start date’’) P/N Calendar time X X SL40054 ...................... X .................. .................. December 13, 2007 ..... at next removal/ installation.1 2 SL40054P .................... X .................. X April 25, 2007 .............. at next removal/ installation.1 2 SL40413P .................... Bogie beam pivot pin nut. X Landings .................. X .................. April 25, 2007 .............. at next removal/ installation.1 2 MLG Lock Link Assembly Lock link medium pin ... C61485–1 .................... C61485–20 .................. X X .................. .................. .................. X December 13, 2007 ..... April 25, 2007 .............. N/A N/A 30 months. 30 months. April 25, 2007 .............. 13,500 9 years. April 25, 2007 April 25, 2007 December 13, April 25, 2007 .............. .............. 2007 ..... .............. 13,500 13,500 13,200 13,500 9 9 9 9 years. years. years. years. December 13, December 13, April 25, 2007 April 25, 2007 December 13, December 13, April 25, 2007 April 25, 2007 April 25, 2007 December 13, December 13, April 25, 2007 2007 ..... 2007 ..... .............. .............. 2007 ..... 2007 ..... .............. .............. .............. 2007 ..... 2007 ..... .............. 13,200 13,200 13,500 13,500 13,200 13,200 13,500 13,500 13,500 13,200 13,200 13,500 9 9 9 9 9 9 9 9 9 9 9 9 years. years. years. years. years. years. years. years. years. years. years. years. NOSE LANDING GEAR Pintle pin ....................... A32210079200xx ......... X X X NLG Telescopic Strut Assembly Nut (Cylinder/Locking cylinder). Locking sleeve .............. C61375 ........................ D55955 ........................ C61389 ........................ C61389–1 .................... X X X X X X X X .................. X .................. X NLG Barrel Assembly Pin (Clevis/Telescopic strut). End fitting pin ............... mstockstill on DSK4VPTVN1PROD with RULES End fitting ..................... Rack ............................. Torque link pin (Upper & Lower). VerDate Sep<11>2014 D68062 ........................ X X X December 13, 2007 ..... at next removal/ installation.2 X X X December 13, 2007 ..... at next removal/ installation.2 AN6–17 ........................ X X X December 13, 2007 ..... at next removal/ installation.2 X X X December 13, 2007 ..... at next removal/ installation.2 X X X December 13, 2007 ..... at next removal/ installation.2 NAS1306–22D ............. End fitting pin nut ......... .................. .................. X X .................. .................. X X X .................. .................. X D68063 ........................ Upper pin (Link/Barrel) .................. .................. X X .................. .................. X X X .................. .................. X D61183 ........................ Link (Clevis/Barrel) ....... X X X X X X X X X X X X MS17825–6 ................. Lower pin (Link/Clevis) C62231–1 .................... C62231–2 .................... C62231–20 .................. D56530 ........................ C62268–1 .................... C62268–2 .................... C62268–20 .................. C62230–1 .................... D56526 ........................ C62267–1 .................... C62267–2 .................... C62267–20 .................. X X X December 13, 2007 ..... at next removal/ installation.2 C62032 ........................ C62032–1 .................... C61453 ........................ C61453–1 .................... C61453–20 .................. C61453–40 .................. C61453–41 .................. C62223–1 .................... C62223–20 .................. X X X X X X X X X X X .................. X X X X .................. X X X .................. X X X X .................. X April 25, 2007 April 25, 2007 December 13, April 25, 2007 April 25, 2007 April 25, 2007 April 25, 2007 December 13, April 25, 2007 13,500 13,500 13,200 13,500 13,500 13,500 13,500 13,200 13,500 17:30 Nov 10, 2015 Jkt 238001 PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 E:\FR\FM\12NOR1.SGM .............. .............. 2007 ..... .............. .............. .............. .............. 2007 ..... .............. 12NOR1 9 9 9 9 9 9 9 9 9 years. years. years. years. years. years. years. years. years. 69851 Federal Register / Vol. 80, No. 218 / Thursday, November 12, 2015 / Rules and Regulations FIGURE 1 TO PARAGRAPH (i) OF THIS AD—SPECIAL COMPLIANCE TIMES—Continued Aircraft type applicability A300 Designation A310 A300–600 Start date Compliance time (whichever occurs first after the ‘‘start date’’) P/N X Torque link medium pin nut. X X SL40110P .................... X X Calendar time Landings X April 25, 2007 .............. N/A 30 months. 4,000 24 months. NLG Shock Absorber Assembly Wheel axle nut ............. C62879 ........................ X X X April 25, 2007 .............. Upper cam dowel ......... C62270 ........................ X X X December 13, 2007 ..... at next removal/ installation. Upper cam .................... Lower cam .................... Restrictor ...................... C62034–1 .................... C62035 ........................ C62036 ........................ C62036–1 .................... C62036–2 .................... C67863 ........................ C67863–1 .................... C67863–2 .................... C67863–3 .................... C67863–4 .................... X X X X X X X X X X X X .................. .................. .................. .................. X X .................. X X X .................. .................. .................. .................. X X .................. X April 25, 2007 April 25, 2007 December 13, December 13, December 13, December 13, April 25, 2007 April 25, 2007 December 13, April 25, 2007 13,500 13,500 13,200 13,200 13,200 13,200 13,500 13,500 13,500 13,500 Lower cam dowel ......... C62866 ........................ X X X December 13, 2007 ..... at next removal/ installation.2 Nut (S/A/Barrel) ............ C64040 ........................ X .................. .................. December 13, 2007 ..... at next removal/ installation.1 2 C64040–1 .................... X X X December 13, 2007 ..... at next removal/ installation.1 2 .............. .............. 2007 ..... 2007 ..... 2007 ..... 2007 ..... .............. .............. 2007 ..... .............. 9 9 9 9 9 9 9 9 9 9 years. years. years. years. years. years. years. years. years. years. 1 When the nut is temporarily removed and reinstalled for the purpose of performing maintenance outside a workshop, no replacement is required provided the nut’s removal and reinstallation are performed on the same assembly and neither the assembly nor the nut accumulates time in service during the period between the removal and reinstallation. 2 If the removal/installation was done after the start date, but before the effective date of this AD, the compliance time is within 3 months after October 27, 2009 (the effective date of AD 2009–18–15, Amendment 39–16011 (74 FR 48143, September 22, 2009)). mstockstill on DSK4VPTVN1PROD with RULES (j) New Requirements of This AD: Maintenance Program Revision Items,’’ dated Revision 01, September 5, 2013, of the Airbus A310 ALS. Within 3 months after the effective date of this AD: Revise the maintenance or inspection program, as applicable, to incorporate the applicable limitation, replacement, or inspection specified in paragraph (j)(1), (j)(2), or (j)(3) of this AD, as applicable. Doing any task required by this paragraph terminates the corresponding task required by paragraph (g), (h), and (i) of this AD. (1) For Model A300 series airplanes: Incorporate ‘‘Sub-part 1–2: Life Limits,’’ and ‘‘Sub-part 1–3: Demonstrated Fatigue Lives’’ of Part 1, ‘‘Safe Life Airworthiness Limitation Items,’’ Revision 01, dated September 5, 2013, of the Airbus A300 ALS. (2) For Model A300 B4–600, B4–600R, and F4–600R series airplanes, and Model A300 C4 605R Variant F airplanes (collectively called Model A300–600 series airplanes): Incorporate ‘‘Sub-part 1–2: Life Limits,’’ and ‘‘Sub-part 1–3: Demonstrated Fatigue Lives’’ of Part 1, ‘‘Safe Life Airworthiness Limitation Items,’’ Revision 01, dated September 5, 2013, of the Airbus A300–600 ALS. (3) For Model A310 series airplanes: Incorporate ‘‘Sub-part 1–2: Life Limits,’’ and ‘‘Sub-part 1–3: Demonstrated Fatigue Lives’’ of Part 1, ‘‘Safe Life Airworthiness Limitation (k) New Limitation: No Alternative Actions or Intervals After accomplishment of the revision required by paragraph (j) of this AD, no alternative actions (e.g., inspections) or intervals may be used unless the actions or intervals are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (l) of this AD. VerDate Sep<11>2014 17:30 Nov 10, 2015 Jkt 238001 (l) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 telephone 425–227–2125; 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: As of the effective date of this AD, for any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the 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. (m) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2013–0248, dated October 14, 2013, 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–2015–2461–0002. E:\FR\FM\12NOR1.SGM 12NOR1 69852 Federal Register / Vol. 80, No. 218 / Thursday, November 12, 2015 / Rules and Regulations mstockstill on DSK4VPTVN1PROD with RULES (2) Service information identified in this AD that is not incorporated by reference in this AD is available at the addresses specified in paragraphs (n)(5) and (n)(6) of this AD. (n) 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 November 27, 2015. (i) ALS Part 1, ‘‘Safe Life Airworthiness Limitation Items,’’ Revision 01, dated September 5, 2013, of the Airbus Model A300 Airworthiness Limitations Section. (ii) ALS Part 1, ‘‘Safe Life Airworthiness Limitation Items,’’ Revision 01, dated September 5, 2013, of the Airbus Model A300–600 Airworthiness Limitations Section. (iii) ALS Part 1, ‘‘Safe Life Airworthiness Limitation Items,’’ Revision 01, dated September 5, 2013, of the Airbus Model A310 Airworthiness Limitations Section. (4) The following service information was approved for IBR on October 27, 2009 (74 FR 48143, September 22, 2009). (i) Section 05–10–00 of Chapter 05, ‘‘Service Life Limits and Maintenance Checks,’’ of the Airbus A300 Aircraft Maintenance Manual (AMM), Revision 28, dated February 27, 1998. (A) The AMM title page; the Record of Revisions, Effective Pages, and Table of Content pages; and Section 05–10–00; for Chapter 05 of Airbus A300 AMM are all dated February 27, 1998. (B) The revision level of Chapter 05 of the Airbus A300 AMM is indicated only in the Record of Revisions section of Chapter 05. (C) The List of Effective Pages (LOEP) for Chapter 05 of the Airbus A300 AMM contains the discrepancies identified in paragraphs (n)(4)(i)(C)(1) through (n)(4)(i)(C)(4) of this AD. (1) The Transmittal Letter page, page 4 of the LOEP and Table of Contents sections, page 2 of Subsection 05–00–01, Subsection 05–10–00, and page 1 of Subsection 05–11– 11, are not listed in the LOEP for Chapter 05 of the Airbus A300 AMM. (2) The LOEP for Chapter 05 of the Airbus A300 AMM does not specify a date for the Record of Revisions page. (3) The LOEP for Chapter 05 of the Airbus A300 AMM identifies three pages for Subsection 05–11–00, Configuration 5; however, only one page exists. (4) The LOEP for Chapter 05 of the Airbus A300 AMM identifies three pages for Subsection 05–11–00, Configuration 9; however, those pages do not exist. (ii) Airbus A300 Airworthiness Limitations Section, ALS Part 1, ‘‘Safe Life Airworthiness Limitations Items’’ dated September 6, 2007. (iii) Airbus A300–600 Airworthiness Limitations Section, ALS Part 1, ‘‘Safe Life Airworthiness Limitations Items’’ dated December 21, 2006. (iv) Airbus A310 Airworthiness Limitations Section, ALS Part 1, ‘‘Safe Life VerDate Sep<11>2014 17:30 Nov 10, 2015 Jkt 238001 Airworthiness Limitation Items’’ dated December 21, 2006. (5) For service information identified in this AD, contact Airbus, Airworthiness Office—EAS, 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. (6) 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. (7) 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 October 21, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–27449 Filed 11–10–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF COMMERCE Bureau of Industry and Security 15 CFR Part 744 [Docket No. 150911846–5846–01] RIN 0694–AG74 Addition of Certain Persons and Modification of Certain Entries to the Entity List; and Removal of Certain Persons From the Entity List Bureau of Industry and Security, Commerce. ACTION: Final rule. AGENCY: This rule amends the Export Administration Regulations (EAR) by adding seven persons under ten entries to the Entity List. The seven persons who are added to the Entity List have been determined by the U.S. Government to be acting contrary to the national security or foreign policy interests of the United States. These persons will be listed on the Entity List under the destinations of China and Hong Kong. This final rule also removes two persons from the Entity List. One entity requested removal from the Entity List in accordance with the procedure for requesting removal or modification of an Entity List entity. The End-User Review Committee (ERC) decided to remove this entity following a review of information provided in the removal request. The ERC decided to remove a SUMMARY: PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 second person from the Entity List following a proposal submitted by an ERC member agency, in accordance with the procedure for requesting removal or modification of an Entity List entity. Finally, this final rule modifies ten existing entries on the Entity List consisting of one entry under China and nine entries under Hong Kong to provide additional or modified addresses and/or aliases for these persons. DATES: This rule is effective on November 12, 2015. FOR FURTHER INFORMATION CONTACT: Chair, End-User Review Committee, Office of the Assistant Secretary, Export Administration, Bureau of Industry and Security, Department of Commerce, Phone: (202) 482–5991, Fax: (202) 482– 3911, Email: ERC@bis.doc.gov. SUPPLEMENTARY INFORMATION: Background The Entity List (Supplement No. 4 to Part 744) identifies entities and other persons reasonably believed to be involved, or to pose a significant risk of being or becoming involved, in activities contrary to the national security or foreign policy interests of the United States. The EAR imposes additional license requirements on, and limits the availability of most license exceptions for, exports, reexports, and transfers (in-country) to those listed. The ‘‘license review policy’’ for each listed entity or other person is identified in the License Review Policy column on the Entity List and the impact on the availability of license exceptions is described in the Federal Register notice adding entities or other persons to the Entity List. BIS places entities and other persons on the Entity List pursuant to sections of part 744 (Control Policy: End-User and End-Use Based) and part 746 (Embargoes and Other Special Controls) of the EAR. The ERC, composed of representatives of the Departments of Commerce (Chair), State, Defense, Energy and, where appropriate, the Treasury, makes all decisions regarding additions to, removals from, or other modifications to the Entity List. The ERC makes all decisions to add an entry to the Entity List by majority vote and all decisions to remove or modify an entry by unanimous vote. ERC Entity List Decisions Additions to the Entity List This rule implements the decision of the ERC to add seven persons under ten entries to the Entity List. These seven persons are being added on the basis of E:\FR\FM\12NOR1.SGM 12NOR1

Agencies

[Federal Register Volume 80, Number 218 (Thursday, November 12, 2015)]
[Rules and Regulations]
[Pages 69846-69852]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-27449]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-2461; Directorate Identifier 2013-NM-202-AD; 
Amendment 39-18310; AD 2015-22-05]
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) 2009-18-15, 
for all Airbus Model A300, A310, and A300 B4-600, B4-600R, and F4-600R 
series airplanes, and Model A300 C4-605R Variant F airplanes 
(collectively called Model A300-600 series airplanes). AD 2009-18-15 
required revising the Airworthiness Limitations section (ALS) of the 
Instructions for Continued Airworthiness (ICA) to require additional 
life limits and/or replacements for certain main landing gear and nose 
landing gear components. This new AD requires revising the maintenance 
or inspection program to incorporate new maintenance requirements and 
airworthiness limitations. This AD was prompted by a determination that 
existing maintenance requirements and airworthiness limitations are 
inadequate to ensure the structural integrity of the airplane. We are 
issuing this AD to prevent failure of certain system components, which 
could result in reduced structural integrity of the airplane.

DATES: This AD becomes effective December 17, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of December 17, 
2015.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of October 
27, 2009 (74 FR 48143, September 22, 2009).

ADDRESSES: You may examine the AD docket on the Internet at http://

[[Page 69847]]

www.regulations.gov/#!docketDetail;D= FAA-2015-2461; or in person at 
the Docket Management Facility, U.S. Department of Transportation, 
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 
New Jersey Avenue SE., Washington, DC.
    For service information identified in this AD, contact Airbus SAS, 
Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; 
email account.airworth-eas@airbus.com; Internet http://www.airbus.com. 
You may view this referenced service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information 
on the availability of this material at the FAA, call 425-227-1221. It 
is also available on the Internet at http://www.regulations.gov by 
searching for and locating Docket No. FAA-2015-2461.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; 
fax 425-227-1149.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2009-18-15, Amendment 39-16011 (74 FR 48143, 
September 22, 2009). AD 2009-18-15 applied to all Airbus Model A300, 
A310, and A300 B4-600, B4-600R, and F4-600R series airplanes; and Model 
A300 C4-605R Variant F airplanes (collectively called Model A300-600 
series airplanes). The NPRM published in the Federal Register on July 
14, 2015 (80 FR 40942).
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2013-0248, dated October 14, 2013 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Model A300, A310, 
and A300-600 series airplanes. The MCAI states:

The airworthiness limitations for Airbus aeroplanes are currently 
published in Airworthiness Limitations Section (ALS) documents.
    The mandatory instructions and airworthiness limitations 
applicable to the Aging Systems Maintenance (ASM) are specified in 
Airbus A310 or A300-600 ALS Part 4 documents, which are approved by 
the European Aviation Safety Agency (EASA). EASA AD 2007-0092 
[http://ad.easa.europa.eu/blob/easa_ad_2007_0092.pdf/AD_2007-0092] 
[which corresponds to FAA AD 2009-06-06, Amendment 39-15842 (74 FR 
12228, March 24, 2009)] was issued to require compliance to the 
requirements as specified in these documents.
    The revision 02 of Airbus A310 and Airbus A300-600 ALS Part 4 
documents introduces more restrictive maintenance requirements and/
or airworthiness limitations. Failure to comply with the 
instructions of ALS Part 4 could result in an unsafe condition 
[reduced structural integrity of the airplane.]
    For the reasons described above, this new [EASA] AD retains the 
requirements of EASA AD 2007-0092, which is superseded, and requires 
the implementation of the new or more restrictive maintenance 
requirements and/or airworthiness limitations as specified in Airbus 
A310 ALS Part 4, Revision 02, or Airbus A300-600 ALS Part 4, 
Revision 02, as applicable to aeroplane type/model.

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2015-2461-0002.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (80 FR 40942, July 14, 
2015) or on the determination of the cost to the public.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting this AD as proposed, except for 
minor editorial changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (80 FR 40942, July 14, 2015) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (80 FR 40942, July 14, 2015).

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information. ``Sub-part 1-
2: Life Limits'' and ``Sub-part 1-3: Demonstrated fatigue lives'' of 
Part 1, ``Safe Life Airworthiness Limitation Items,'' in each of these 
documents describe procedures for revising the maintenance or 
inspection program to incorporate new maintenance requirements and 
airworthiness limitations.
     For Model A300 series airplanes: Part 1, ``Safe Life 
Airworthiness Limitation Items,'' Revision 01, dated September 5, 2013, 
of the Airbus Model A300 Airworthiness Limitations Section.
     For Model A300 B4-600, B4-600R, and F4-600R series 
airplanes, and Model A300 C4-605R Variant F airplanes (collectively 
called Model A300-600 series airplanes): Part 1, ``Safe Life 
Airworthiness Limitation Items,'' Revision 01, dated September 5, 2013, 
of the Airbus Model A300-600 Airworthiness Limitations Section.
     For Model A310 series airplanes: Part 1, ``Safe Life 
Airworthiness Limitation Items,'' Revision 01, dated September 5, 2013, 
of the Airbus Model A310 Airworthiness Limitations Section.
    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.

Costs of Compliance

    We estimate that this AD affects 177 airplanes of U.S. registry.
    The retained ALS revision required by AD 2009-18-15, Amendment 39-
16011 (74 FR 48143, September 22, 2009), takes about 1 work-hour per 
product, at an average labor rate of $85 per work-hour. Based on these 
figures, the estimated cost of the actions that were required by AD 
2009-18-15 is $85 per product.
    We also estimate that it takes about 1 work-hour per product to 
comply with the new ALS revision 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 $15,045, or $85 per product.

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.

[[Page 69848]]

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-2015-2461; 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 
2009-18-15, Amendment 39-16011 (74 FR 48143, September 22, 2009), and 
adding the following new AD:

2015-22-05 Airbus: Amendment 39-18310. Docket No. FAA-2015-2461; 
Directorate Identifier 2013-NM-202-AD.

(a) Effective Date

    This AD becomes effective December 17, 2015.

(b) Affected ADs

    (1) This AD replaces AD 2009-18-15, Amendment 39-16011 (74 FR 
48143, September 22, 2009).
    (2) Accomplishing certain requirements of paragraph (g) of this 
AD satisfies the requirements of paragraph A. of AD 84-02-04, 
Amendment 39-4795 (49 FR 2746, January 23, 1984).

(c) Applicability

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

(d) Subject

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

(e) Reason

    This AD was prompted by a determination that existing 
maintenance requirements and airworthiness limitations are 
inadequate to ensure the structural integrity of the airplane. We 
are issuing this AD to prevent failure of certain system components, 
which could result in reduced structural integrity of the airplane.

(f) Compliance

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

(g) Retained Revision of Airworthiness Limitation Section (ALS)

    This paragraph restates the requirements of paragraph (h) of AD 
2009-18-15, Amendment 39-16011 (74 FR 48143, September 22, 2009). 
For Model A300, A310, and A300-600 series airplanes: Within 3 months 
after October 27, 2009 (the effective date of AD 2009-18-15), revise 
the ALS of the instructions for continued airworthiness (ICA) to 
incorporate the applicable document listed in paragraph (g)(1), 
(g)(2), or (g)(3) of this AD. Accomplishing the actions specified in 
the applicable document satisfies the requirements of paragraph A. 
of AD 84-02-04, Amendment 39-4795 (49 FR 2746, January 23, 1984).
    (1) For Model A300 series airplanes: Incorporate the applicable 
document listed in paragraph (g)(1)(i) or (g)(1)(ii) of this AD.
    (i) Section 05-10-00, Revision 28, dated February 27, 1998, of 
Chapter 05, ``Service Life Limits and Maintenance Checks,'' of the 
Airbus A300 Aircraft Maintenance Manual, except that the parts 
listed in table 1 to paragraph (g) of this AD are subject to the 
life limits defined in the document listed in paragraph (g)(1)(ii) 
of this AD.
    (ii) ``Sub-part 1-2: Life Limits,'' and ``Sub-part 1-3: 
Demonstrated Fatigue Lives'' of Part 1, ``Safe Life Airworthiness 
Limitation Items,'' dated September 6, 2007, of the Airbus A300 ALS.

  Table 1 to Paragraph (g) of This AD--Parts Subject to the Life Limits
 Specified in the Document Identified in Paragraph (g)(1)(ii) of This AD
------------------------------------------------------------------------
              Part No. (P/N)                          Part name
------------------------------------------------------------------------
P/N C61643-2, P/N C61643-4, P/N C61643-5..  Main landing gear (MLG)
                                             shock absorber end fitting.
P/N A32210001205xx........................  Nose landing gear (NLG)
                                             pintle pin.
P/N C62037-1..............................  NLG shock absorber bottom.
P/N 196-0328-501..........................  Cross beam (Pratt & Whitney
                                             forward engine mount).
------------------------------------------------------------------------

    (2) For Model A310 series airplanes: Incorporate ``Sub-part 1-2: 
Life Limits,'' and ``Sub-part 1-3: Demonstrated Fatigue Lives'' of 
Part 1, ``Safe Life Airworthiness Limitation Items,'' dated December 
21, 2006, of the Airbus A310 ALS.
    (3) For Model A300 B4-600, B4-600R, and F4-600R series 
airplanes, and Model A300 C4-605R Variant F airplanes (collectively 
called Model A300-600 series airplanes): Incorporate ``Sub-part 1-2: 
Life Limits,'' and ``Sub-part 1-3: Demonstrated Fatigue Lives'' of 
Part 1, ``Safe Life Airworthiness Limitation Items,'' dated December 
21, 2006, of the Airbus A300-600 ALS.

(h) Retained Initial Compliance Times and Repetitive Inspections

    This paragraph restates the requirements of paragraph (i) of AD 
2009-18-15, Amendment 39-16011 (74 FR 48143, September 22, 2009). Do 
the replacement at the applicable time specified in paragraph (h)(1) 
or (h)(2) of this AD, except as provided by paragraph (i) of this 
AD. The replacement must be done thereafter within the interval 
specified in the applicable document identified in paragraph (g)(1), 
(g)(2), or (g)(3) of this AD.
    (1) For any life limitation/task that has been complied with 
before October 27, 2009 (the effective date of AD 2009-18-15, 
Amendment 39-16011), in accordance with the applicable document 
listed in paragraph (g)(1), (g)(2), or (g)(3) of this AD, or in 
accordance with paragraph (g) of AD 2009-18-15, use the last 
accomplishment of each limitation/task as a starting point for 
accomplishing each corresponding limitation/task required by this 
AD.
    (2) For any life limitation/task that has not been complied with 
before October 27, 2009 (the effective date of AD 2009-18-15, 
Amendment 39-16011), in accordance with the applicable document 
listed in paragraphs (g)(1), (g)(2), and (g)(3) of this AD, or in 
accordance with paragraph (g) of AD 2009-18-15, the initial 
compliance time starts from the date of initial entry into service 
as defined in the applicable document.

(i) Retained Special Compliance Times

    This paragraph restates the requirements of paragraph (j) of AD 
2009-18-15, Amendment

[[Page 69849]]

39-16011 (74 FR 48143, September 22, 2009). For any airplane on 
which the history of accumulated landings is partial or unknown, or 
where the history of application details (airplane type, model, 
weight variant, etc.) is partial or unknown: Parts listed in figure 
1 to paragraph (i) of this AD must be replaced at the associated 
compliance time. The replacement must be done thereafter at the 
interval specified in the applicable document(s) specified in 
paragraphs (g)(1), (g)(2), and (g)(3) of this AD.

    Note 1 to paragraph (i) of this AD:  Airbus Service Information 
Letter 32-118, Revision 02, dated October 24, 2007, provides 
operators with guidance on the means to assign a conservative 
calculated life to parts whose history of accumulated landings is 
partial or unknown; and to select the limitations applicable to 
parts whose history of application details (aircraft type, aircraft 
model, weight variant, etc.) is partial or unknown.


                                             Figure 1 to Paragraph (i) of This AD--Special Compliance Times
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                     Aircraft type applicability                                           Compliance time  (whichever
                                   --------------------------------------------------------------                        occurs first after the ``start
            Designation                      A300              A310       A300-600                     Start date                    date'')
                                   -------------------------------------------------     P/N                           ---------------------------------
                                              X                 X            X                                           Landings       Calendar time
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                    MAIN LANDING GEAR
--------------------------------------------------------------------------------------------------------------------------------------------------------
Aft pintle pin....................  A32140032200xx.......           X   ...........  ...........  December 13, 2007...      13,500  9 years.
                                    A32140056200xx.......           X   ...........  ...........  December 13, 2007...      13,500  9 years.
                                    A32140056202xx.......           X   ...........  ...........  December 13, 2007...      13,500  9 years.
                                    A32140057200xx.......           X   ...........  ...........  December 13, 2007...      13,500  9 years.
                                    A32140057202xx.......           X   ...........           X   December 13, 2007...      13,500  9 years.
                                    A32140062000xx.......           X   ...........  ...........  December 13, 2007...      13,500  9 years.
                                    A32140063000xx.......           X   ...........           X   December 13, 2007...      13,500  9 years.
Half ball housing (Fwd pintle       A32140036200xx.......           X   ...........  ...........  December 13, 2007...      13,500  9 years.
 bearing).                          A32140036202xx.......           X   ...........  ...........  December 13, 2007...      13,500  9 years.
                                    A32140036204xx.......           X   ...........  ...........  December 13, 2007...      13,500  9 years.
                                    A32140036206xx.......           X   ...........  ...........  December 13, 2007...      13,500  9 years.
                                    A32140042200xx.......           X   ...........           X   December 13, 2007...      13,500  9 years.
                                    A32140042202xx.......           X   ...........           X   December 13, 2007...      13,500  9 years.
                                    A32140068002xx.......           X   ...........  ...........  December 13, 2007...      13,500  9 years.
                                    A32140068004xx.......           X   ...........  ...........  December 13, 2007...      13,500  9 years.
                                    A32140069002xx.......           X   ...........           X   December 13, 2007...      13,500  9 years.
                                    A32140069004xx.......           X   ...........           X   December 13, 2007...      13,500  9 years.
Ball (Fwd pintle pin).............  A32140012202xx.......           X   ...........  ...........  December 13, 2007...      13,500  9 years.
                                    A32140043202xx.......           X   ...........           X   December 13, 2007...      13,500  9 years.
Pin (Multiple link/Frame 50)......  A53833451200xx.......           X   ...........  ...........  December 13, 2007...      13,500  9 years.
                                    A53833451206xx.......           X   ...........  ...........  December 13, 2007...      13,500  9 years.
                                    A53834451200xx.......           X   ...........  ...........  December 13, 2007...      13,500  9 years.
                                    A53834451202xx.......           X   ...........           X   April 25, 2007......      13,500  9 years.
Pin (Drop link/Frame 50)..........  A53811122200xx.......  ...........           X   ...........  April 25, 2007......      18,000  9 years.
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                   MLG Barrel Assembly
--------------------------------------------------------------------------------------------------------------------------------------------------------
Upper torque link pin nut.........  00-200-402...........           X   ...........  ...........  December 13, 2007...         N/A  30 months.
                                    SL40089..............           X   ...........  ...........  December 13, 2007...         N/A  30 months.
                                    SL40089P.............           X   ...........  ...........  December 13, 2007...         N/A  30 months.
                                    SL40123..............           X   ...........  ...........  December 13, 2007...         N/A  30 months.
                                    SL40123P.............           X            X            X   April 25, 2007......         N/A  30 months.
Torque link medium pin nut........  00-200-358...........           X   ...........  ...........  December 13, 2007...         N/A  30 months.
                                    SL40114P.............           X            X   ...........  April 25, 2007......         N/A  30 months.
                                    SL40132..............           X   ...........  ...........  December 13, 2007...         N/A  30 months.
                                    SL40132P.............           X   ...........           X   April 25, 2007......         N/A  30 months.
Attaching fitting pin.............  C62311-1.............           X   ...........  ...........  December 13, 2007...      13,500  9 years.
                                    C62311-20............           X   ...........           X   April 25, 2007......      13,500  9 years.
Pin (Connecting rod/Upper rod)....  C65815...............           X   ...........  ...........  December 13, 2007...      13,500  9 years.
                                    C65815-1.............           X   ...........  ...........  December 13, 2007...      13,500  9 years.
                                    C65815-20............           X   ...........  ...........  December 13, 2007...      13,500  9 years.
                                    C66472...............           X   ...........  ...........  December 13, 2007...      13,500  9 years.
                                    C66472-1.............           X   ...........  ...........  December 13, 2007...      13,500  9 years.
                                    C66472-20............           X   ...........           X   April 25, 2007......      13,500  9 years.
                                    D52751...............  ...........           X   ...........  April 25, 2007......      18,000  9 years.
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                               MLG Shock Absorber Assembly
--------------------------------------------------------------------------------------------------------------------------------------------------------
Lower torque link pin nut.........  00-200-402...........           X   ...........  ...........  December 13, 2007...         N/A  30 months.
                                    SL40089..............           X   ...........  ...........  December 13, 2007...         N/A  30 months.
                                    SL40089P.............           X   ...........  ...........  December 13, 2007...         N/A  30 months.
                                    SL40123..............           X   ...........  ...........  December 13, 2007...         N/A  30 months.
                                    SL40123P.............           X            X            X   April 25, 2007......         N/A  30 months.
                                                                                                                       ---------------------------------

[[Page 69850]]

 
Bogie beam pivot pin nut..........  SL40054..............           X   ...........  ...........  December 13, 2007...  at next removal/installation.1 2
                                                                                                                       ---------------------------------
                                    SL40054P.............           X   ...........           X   April 25, 2007......  at next removal/installation.1 2
                                                                                                                       ---------------------------------
                                    SL40413P.............  ...........           X   ...........  April 25, 2007......  at next removal/installation.1 2
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                 MLG Lock Link Assembly
--------------------------------------------------------------------------------------------------------------------------------------------------------
Lock link medium pin..............  C61485-1.............           X   ...........  ...........  December 13, 2007...         N/A  30 months.
                                    C61485-20............           X   ...........           X   April 25, 2007......         N/A  30 months.
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                    NOSE LANDING GEAR
--------------------------------------------------------------------------------------------------------------------------------------------------------
Pintle pin........................  A32210079200xx.......           X            X            X   April 25, 2007......      13,500  9 years.
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                              NLG Telescopic Strut Assembly
--------------------------------------------------------------------------------------------------------------------------------------------------------
Nut (Cylinder/Locking cylinder)...  C61375...............           X            X   ...........  April 25, 2007......      13,500  9 years.
                                    D55955...............           X            X            X   April 25, 2007......      13,500  9 years.
Locking sleeve....................  C61389...............           X            X   ...........  December 13, 2007...      13,200  9 years.
                                    C61389-1.............           X            X            X   April 25, 2007......      13,500  9 years.
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                                   NLG Barrel Assembly
--------------------------------------------------------------------------------------------------------------------------------------------------------
Pin (Clevis/Telescopic strut).....  C62231-1.............           X   ...........  ...........  December 13, 2007...      13,200  9 years.
                                    C62231-2.............           X   ...........  ...........  December 13, 2007...      13,200  9 years.
                                    C62231-20............           X            X            X   April 25, 2007......      13,500  9 years.
                                    D56530...............           X            X            X   April 25, 2007......      13,500  9 years.
Lower pin (Link/Clevis)...........  C62268-1.............           X   ...........  ...........  December 13, 2007...      13,200  9 years.
                                    C62268-2.............           X   ...........  ...........  December 13, 2007...      13,200  9 years.
                                    C62268-20............           X            X            X   April 25, 2007......      13,500  9 years.
Link (Clevis/Barrel)..............  C62230-1.............           X            X            X   April 25, 2007......      13,500  9 years.
                                    D56526...............           X            X            X   April 25, 2007......      13,500  9 years.
Upper pin (Link/Barrel)...........  C62267-1.............           X   ...........  ...........  December 13, 2007...      13,200  9 years.
                                    C62267-2.............           X   ...........  ...........  December 13, 2007...      13,200  9 years.
                                    C62267-20............           X            X            X   April 25, 2007......      13,500  9 years.
                                                                                                                       ---------------------------------
End fitting pin nut...............  D68062...............           X            X            X   December 13, 2007...  at next removal/installation.\2\
                                                                                                                       ---------------------------------
                                    MS17825-6............           X            X            X   December 13, 2007...  at next removal/installation.\2\
                                                                                                                       ---------------------------------
End fitting pin...................  AN6-17...............           X            X            X   December 13, 2007...  at next removal/installation.\2\
                                                                                                                       ---------------------------------
                                    D61183...............           X            X            X   December 13, 2007...  at next removal/installation.\2\
                                                                                                                       ---------------------------------
                                    D68063...............           X            X            X   December 13, 2007...  at next removal/installation.\2\
                                                                                                                       ---------------------------------
                                    NAS1306-22D..........           X            X            X   December 13, 2007...  at next removal/installation.\2\
                                                                                                                       ---------------------------------
End fitting.......................  C62032...............           X            X            X   April 25, 2007......      13,500  9 years.
                                    C62032-1.............           X            X            X   April 25, 2007......      13,500  9 years.
Rack..............................  C61453...............           X   ...........  ...........  December 13, 2007...      13,200  9 years.
                                    C61453-1.............           X            X            X   April 25, 2007......      13,500  9 years.
                                    C61453-20............           X            X            X   April 25, 2007......      13,500  9 years.
                                    C61453-40............           X            X            X   April 25, 2007......      13,500  9 years.
                                    C61453-41............           X            X            X   April 25, 2007......      13,500  9 years.
Torque link pin (Upper & Lower)...  C62223-1.............           X   ...........  ...........  December 13, 2007...      13,200  9 years.
                                    C62223-20............           X            X            X   April 25, 2007......      13,500  9 years.

[[Page 69851]]

 
Torque link medium pin nut........  SL40110P.............           X            X            X   April 25, 2007......         N/A  30 months.
--------------------------------------------------------------------------------------------------------------------------------------------------------
                                                               NLG Shock Absorber Assembly
--------------------------------------------------------------------------------------------------------------------------------------------------------
Wheel axle nut....................  C62879...............           X            X            X   April 25, 2007......       4,000  24 months.
                                                                                                                       ---------------------------------
Upper cam dowel...................  C62270...............           X            X            X   December 13, 2007...    at next removal/installation.
                                                                                                                       ---------------------------------
Upper cam.........................  C62034-1.............           X            X            X   April 25, 2007......      13,500  9 years.
Lower cam.........................  C62035...............           X            X            X   April 25, 2007......      13,500  9 years.
Restrictor........................  C62036...............           X   ...........  ...........  December 13, 2007...      13,200  9 years.
                                    C62036-1.............           X   ...........  ...........  December 13, 2007...      13,200  9 years.
                                    C62036-2.............           X   ...........  ...........  December 13, 2007...      13,200  9 years.
                                    C67863...............           X   ...........  ...........  December 13, 2007...      13,200  9 years.
                                    C67863-1.............           X            X            X   April 25, 2007......      13,500  9 years.
                                    C67863-2.............           X            X            X   April 25, 2007......      13,500  9 years.
                                    C67863-3.............           X   ...........  ...........  December 13, 2007...      13,500  9 years.
                                    C67863-4.............           X            X            X   April 25, 2007......      13,500  9 years.
                                                                                                                       ---------------------------------
Lower cam dowel...................  C62866...............           X            X            X   December 13, 2007...  at next removal/installation.\2\
                                                                                                                       ---------------------------------
Nut (S/A/Barrel)..................  C64040...............           X   ...........  ...........  December 13, 2007...  at next removal/installation.1 2
                                                                                                                       ---------------------------------
                                    C64040-1.............           X            X            X   December 13, 2007...  at next removal/installation.1 2
--------------------------------------------------------------------------------------------------------------------------------------------------------
\1\ When the nut is temporarily removed and reinstalled for the purpose of performing maintenance outside a workshop, no replacement is required
  provided the nut's removal and reinstallation are performed on the same assembly and neither the assembly nor the nut accumulates time in service
  during the period between the removal and reinstallation.
\2\ If the removal/installation was done after the start date, but before the effective date of this AD, the compliance time is within 3 months after
  October 27, 2009 (the effective date of AD 2009-18-15, Amendment 39-16011 (74 FR 48143, September 22, 2009)).

(j) New Requirements of This AD: Maintenance Program Revision

    Within 3 months after the effective date of this AD: Revise the 
maintenance or inspection program, as applicable, to incorporate the 
applicable limitation, replacement, or inspection specified in 
paragraph (j)(1), (j)(2), or (j)(3) of this AD, as applicable. Doing 
any task required by this paragraph terminates the corresponding 
task required by paragraph (g), (h), and (i) of this AD.
    (1) For Model A300 series airplanes: Incorporate ``Sub-part 1-2: 
Life Limits,'' and ``Sub-part 1-3: Demonstrated Fatigue Lives'' of 
Part 1, ``Safe Life Airworthiness Limitation Items,'' Revision 01, 
dated September 5, 2013, of the Airbus A300 ALS.
    (2) For Model A300 B4-600, B4-600R, and F4-600R series 
airplanes, and Model A300 C4 605R Variant F airplanes (collectively 
called Model A300-600 series airplanes): Incorporate ``Sub-part 1-2: 
Life Limits,'' and ``Sub-part 1-3: Demonstrated Fatigue Lives'' of 
Part 1, ``Safe Life Airworthiness Limitation Items,'' Revision 01, 
dated September 5, 2013, of the Airbus A300-600 ALS.
    (3) For Model A310 series airplanes: Incorporate ``Sub-part 1-2: 
Life Limits,'' and ``Sub-part 1-3: Demonstrated Fatigue Lives'' of 
Part 1, ``Safe Life Airworthiness Limitation Items,'' dated Revision 
01, September 5, 2013, of the Airbus A310 ALS.

(k) New Limitation: No Alternative Actions or Intervals

    After accomplishment of the revision required by paragraph (j) 
of this AD, no alternative actions (e.g., inspections) or intervals 
may be used unless the actions or intervals are approved as an 
alternative method of compliance (AMOC) in accordance with the 
procedures specified in paragraph (l) of this AD.

(l) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it to ATTN: Dan Rodina, 
Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-2125; 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: As of the effective date of 
this AD, for any requirement in this AD to obtain corrective actions 
from a manufacturer, the action must be accomplished using a method 
approved by the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; or the 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.

(m) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2013-0248, dated October 14, 
2013, 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-2015-2461-0002.

[[Page 69852]]

    (2) Service information identified in this AD that is not 
incorporated by reference in this AD is available at the addresses 
specified in paragraphs (n)(5) and (n)(6) of this AD.

(n) 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 
November 27, 2015.
    (i) ALS Part 1, ``Safe Life Airworthiness Limitation Items,'' 
Revision 01, dated September 5, 2013, of the Airbus Model A300 
Airworthiness Limitations Section.
    (ii) ALS Part 1, ``Safe Life Airworthiness Limitation Items,'' 
Revision 01, dated September 5, 2013, of the Airbus Model A300-600 
Airworthiness Limitations Section.
    (iii) ALS Part 1, ``Safe Life Airworthiness Limitation Items,'' 
Revision 01, dated September 5, 2013, of the Airbus Model A310 
Airworthiness Limitations Section.
    (4) The following service information was approved for IBR on 
October 27, 2009 (74 FR 48143, September 22, 2009).
    (i) Section 05-10-00 of Chapter 05, ``Service Life Limits and 
Maintenance Checks,'' of the Airbus A300 Aircraft Maintenance Manual 
(AMM), Revision 28, dated February 27, 1998.
    (A) The AMM title page; the Record of Revisions, Effective 
Pages, and Table of Content pages; and Section 05-10-00; for Chapter 
05 of Airbus A300 AMM are all dated February 27, 1998.
    (B) The revision level of Chapter 05 of the Airbus A300 AMM is 
indicated only in the Record of Revisions section of Chapter 05.
    (C) The List of Effective Pages (LOEP) for Chapter 05 of the 
Airbus A300 AMM contains the discrepancies identified in paragraphs 
(n)(4)(i)(C)(1) through (n)(4)(i)(C)(4) of this AD.
    (1) The Transmittal Letter page, page 4 of the LOEP and Table of 
Contents sections, page 2 of Subsection 05-00-01, Subsection 05-10-
00, and page 1 of Subsection 05-11-11, are not listed in the LOEP 
for Chapter 05 of the Airbus A300 AMM.
    (2) The LOEP for Chapter 05 of the Airbus A300 AMM does not 
specify a date for the Record of Revisions page.
    (3) The LOEP for Chapter 05 of the Airbus A300 AMM identifies 
three pages for Subsection 05-11-00, Configuration 5; however, only 
one page exists.
    (4) The LOEP for Chapter 05 of the Airbus A300 AMM identifies 
three pages for Subsection 05-11-00, Configuration 9; however, those 
pages do not exist.
    (ii) Airbus A300 Airworthiness Limitations Section, ALS Part 1, 
``Safe Life Airworthiness Limitations Items'' dated September 6, 
2007.
    (iii) Airbus A300-600 Airworthiness Limitations Section, ALS 
Part 1, ``Safe Life Airworthiness Limitations Items'' dated December 
21, 2006.
    (iv) Airbus A310 Airworthiness Limitations Section, ALS Part 1, 
``Safe Life Airworthiness Limitation Items'' dated December 21, 
2006.
    (5) For service information identified in this AD, contact 
Airbus, Airworthiness Office--EAS, 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.
    (6) 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.
    (7) 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 October 21, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-27449 Filed 11-10-15; 8:45 am]
BILLING CODE 4910-13-P