Airworthiness Directives; Airbus Airplanes, 63370-63374 [2016-21146]

Download as PDF 63370 Federal Register / Vol. 81, No. 179 / Thursday, September 15, 2016 / Rules and Regulations (j) Modification of Overhead Stowage Compartments and Re-Identification of Part Number Within 4 months after the effective date of this AD: Modify the overhead stowage compartments, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraphs (j)(1) through (j)(4) of this AD. (1) For airplanes identified in ATR Service Bulletin ATR42–25–0185, dated November 21, 2014: ATR Service Bulletin ATR42–25– 0185, dated November 21, 2014. (2) For airplanes identified in ATR Service Bulletin ATR42–25–0186, dated November 21, 2014: ATR Service Bulletin ATR42–25– 0186, dated November 21, 2014. (3) For airplanes identified in ATR Service Bulletin ATR72–25–1148, dated November 21, 2014: ATR Service Bulletin ATR72–25– 1148, dated November 21, 2014. (4) For airplanes identified in ATR Service Bulletin ATR72–25–1149, dated November 21, 2014: ATR Service Bulletin ATR72–25– 1149, dated November 21, 2014. rmajette on DSK2TPTVN1PROD with RULES (k) 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: Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1137; 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. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or EASA; or ATR—GIE Avions de Transport ´ Regional’s EASA DOA. If approved by the DOA, the approval must include the DOAauthorized signature. (l) Related Information Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2015–0018, dated February 5, 2015, 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–2015–0077. (m) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference VerDate Sep<11>2014 14:38 Sep 14, 2016 Jkt 238001 (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) ATR Service Bulletin ATR42–25–0180, dated August 19, 2013. (ii) ATR Service Bulletin ATR42–25–0185, dated November 21, 2014. (iii) ATR Service Bulletin ATR42–25–0186, dated November 21, 2014. (iv) ATR Service Bulletin ATR72–25–1141, dated August 19, 2013. (v) ATR Service Bulletin ATR72–25–1148, dated November 21, 2014. (vi) ATR Service Bulletin ATR72–25–1149, dated November 21, 2014. (3) For service information identified in this AD, contact ATR—GIE Avions de ´ ´ Transport Regional, 1, Allee Pierre Nadot, 31712 Blagnac Cedex, France; telephone +33 (0) 5 62 21 62 21; fax +33 (0) 5 62 21 67 18; email continued.airworthiness@atr.fr; Internet http://www.aerochain.com. (4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on August 25, 2016. John P. Piccola, Jr., Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–21292 Filed 9–14–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–6550; Directorate Identifier 2013–NM–162–AD; Amendment 39–18638; AD 2016–18–08] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are superseding Airworthiness Directive (AD) 90–11–05 for certain Airbus Model A300 B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and B4–203 airplanes and Model A300 B4– 600 series airplanes. AD 90–11–05 required repetitive detailed inspections SUMMARY: PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 for cracking in the aft hinge brackets of the outer shroud box that is located in the outer wing box, and related investigative and corrective actions if necessary. This new AD changes certain compliance times and adds airplanes to the applicability. This AD was prompted by reports of cracks in the aft hinge brackets of the outer shroud box that is located in the outer wing box, which were found during routine maintenance checks, and our subsequent determination that a change in inspection compliance times is needed. We are issuing this AD to detect and correct cracking of the aft hinge brackets of the outer shroud box; such cracking could affect the structural integrity of the airplane. DATES: This AD becomes effective October 20, 2016. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of October 20, 2016. ADDRESSES: For service information identified in this final rule, 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–2015–6550. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 6550; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone 800–647–5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA E:\FR\FM\15SER1.SGM 15SER1 Federal Register / Vol. 81, No. 179 / Thursday, September 15, 2016 / Rules and Regulations 98057–3356; telephone 425–227–2125; fax 425–227–1149. SUPPLEMENTARY INFORMATION: rmajette on DSK2TPTVN1PROD with RULES Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 90–11–05, Amendment 39–6603 (89–NM–223–AD) (55 FR 20129, May 15, 1990) (‘‘AD 90– 11–05’’). AD 90–11–05 applied to certain Airbus Model A300 B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and B4 203 airplanes and Model A300 B4– 600 series airplanes. The NPRM published in the Federal Register on December 14, 2015 (80 FR 77279) (‘‘the NPRM’’). The NPRM was prompted by a determination that a change to certain compliance times is needed. The NPRM proposed to continue to require doing repetitive detailed inspections for cracking in the hinge brackets of the forward and aft outer shroud boxes that are located in the outer wing box, and related investigative and corrective actions if necessary. The NPRM also proposed to change certain compliance times and add airplanes to the applicability. We are issuing this AD to detect and correct cracking of the aft hinge brackets of the outer shroud box; such cracking could affect the structural integrity of the airplane. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2013–0181R1, dated August 20, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Model A300 series airplanes and Model A300 B4–600 series airplanes. The MCAI states: In the past, aft hinge brackets of the outer wing box were found cracked. Fracture of a bracket would allow vertical movement of the inner shroud box structure, which could result in damage to the top skin of the inboard flap. In addition, the loads carried by the brackets will be transferred to the remaining supports, which may also crack and cause extensive structural damage. This condition, if not detected and corrected, could affect the structural integrity of the aeroplane. To address this potential unsafe condition, ´ ´ DGAC [Direction Generale de l’Aviation Civile] France issued * * * [an airworthiness directive] (later revised) to require repetitive inspections of the hinge bracket of the outer box and, depending on findings, corrective action(s). Since that [DGAC] AD was issued, a fleet survey and updated Fatigue and Damage Tolerance analysis were performed in order to substantiate the A300 Extended Service Goal (ESG) and A300–600 Extended Service Goal (ESG2) exercise. VerDate Sep<11>2014 14:38 Sep 14, 2016 Jkt 238001 The results of these analyses led to a change in the inspection thresholds and intervals in Flight Cycles (FC) and the introduction of Flight Hours (FH) limits. For the reasons described above, this [EASA] AD retains the requirements of DGAC France * * * [an airworthiness directive], which is superseded, but requires those actions within the new thresholds and intervals given by Airbus Service Bulletin (SB) A300–57–0142 Revision 04 or A300–57– 6010 Revision 05, as applicable to aeroplane model. Revision 1 of this [EASA] AD is issued to add model A300 B4–203 aeroplanes to the applicability and compliance time tables. This model is covered by Airbus SB A300– 57–0142, but was mistakenly omitted from the original [EASA] AD issue. The corrective action for a hinge bracket that is cracked or fractured is replacing the damaged hinge bracket with a new bracket. For airplanes on which a crack is found in one half bracket or both half brackets, related investigative actions include a general visual inspection for secondary damage (e.g., cracks, wear damage, pitting, and gouging) in the following areas: • The inner shroud-box forward attachments and the attachment brackets at the inboard end. • The inner and outer shroud-box structure, adjacent to the fractured bracket. • The top skin of the inboard flap. The corrective action for damage findings during the related investigative action is repair using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or EASA; or Airbus’s EASA Design Organization Approval (DOA). The compliance time for related investigative actions and corrective actions is before further flight. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 6550. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comment received on the NPRM and the FAA’s response to the comment. Request To Exclude Certain Airplanes From the Applicability FedEx requested that we exclude from the proposed applicability airplanes on which the actions specified in Airbus Service Bulletin A300–57–6011, Revision 2, dated July 10, 1989, have been accomplished. FedEx stated that it has accomplished the optional PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 63371 terminating actions provided in paragraph (j)(1) of the proposed AD, and specified in Airbus Service Bulletin A300–57–6011, Revision 2, dated July 10, 1989, on several of its airplanes. We disagree with FedEx’s request. As of the effective date of this AD, additional actions are required for airplanes on which the optional modification has been accomplished. These airplanes will need to have a onetime detailed visual inspection of the forward and aft outer shroud box with no cracking found, as required by paragraph (j)(2) of this AD. We have not changed this AD in this regard. Changes Made to This AD In paragraph (j)(2) of the proposed AD, we proposed to provide an optional method of compliance (i.e., a replacement and a one-time inspection) for actions specified in paragraph (g) of the proposed AD. We also proposed to give credit in paragraph (k)(2) of the proposed AD for replacements accomplished before the effective date of this AD using the same service information identified in paragraph (j)(2) of the AD: • Airbus Service Bulletin A300–57– 143, dated December 17, 1986. • Airbus Service Bulletin A300–57– 143, Revision 1, dated March 19, 1987. • Airbus Service Bulletin A300–57– 6011, dated December 17, 1986. • Airbus Service Bulletin A300–57– 6011, Revision 1, dated March 19, 1987. Since we cannot make this service information reasonably available, we have revised paragraph (j)(2) of the proposed AD, removed redundant paragraph (k)(2) of the proposed AD from this AD, and redesignated paragraph (k)(1) and subsequent subparagraphs accordingly. We revised paragraph (j)(2) of this AD by removing the references to the service information and instead specified that operators must do the replacement using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or EASA; or Airbus’s EASA Design Organization Approval (DOA). Conclusion We reviewed the available data, including the comment received, and determined that air safety and the public interest require adopting this AD as proposed except for minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and E:\FR\FM\15SER1.SGM 15SER1 63372 Federal Register / Vol. 81, No. 179 / Thursday, September 15, 2016 / Rules and Regulations • Airbus Service Bulletin A300–57– 143, Revision 2, dated July 10, 1989, which describes procedures for replacing the aft aluminum alloy brackets on the outer shroud box with new steel brackets. • Airbus Service Bulletin A300–57– 6010, Revision 05, dated February 21, 2011, which describes procedures for doing an inspection of the forward and aft hinge brackets on the outer shroud box. • Airbus Service Bulletin A300–57– 6011, Revision 2, dated July 10, 1989, which describes procedures for • Do not add any additional burden upon the public than was already proposed in the NPRM. Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information. • Airbus Service Bulletin A300–57– 0142, Revision 04, dated March 30, 2011, which describes procedures for doing an inspection of the forward and aft hinge brackets on the outer shroud box. replacing the aft aluminum alloy brackets on the outer shroud box with new steel brackets. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Costs of Compliance We estimate that this AD affects 3 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Inspection ...................... 8 work-hours × $85 per hour = $680 per inspection cycle. We estimate the following costs to do any necessary replacements that would Parts cost Cost per product $0 Cost on U.S. operators $680 per inspection cycle. be required based on the results of the inspection. We have no way of $2,040 per inspection cycle. determining the number of aircraft that might need these replacements: ON-CONDITION COSTS Action Labor cost Replacement .................................... 27 work-hours × $85 per hour = $2,295 ................................................... rmajette on DSK2TPTVN1PROD with RULES We have received no definitive data that would enable us to provide cost estimates for the on-condition related investigative and corrective actions specified in this AD. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will VerDate Sep<11>2014 14:38 Sep 14, 2016 Jkt 238001 Parts cost 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. 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: PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 $25,650 Cost per product $27,945 PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 90–11–05, Amendment 39–6603 (89– NM–223–AD) (55 FR 20129, May 15, 1990), and adding the following new AD: ■ 2016–18–08 Airbus: Amendment 39–18638. Docket No. FAA–2015–6550; Directorate Identifier 2013–NM–162–AD. (a) Effective Date This AD becomes effective October 20, 2016. (b) Affected ADs This AD replaces AD 90–11–05, Amendment 39–6603 (89–NM–223–AD) (55 FR 20129, May 15, 1990). (c) Applicability This AD applies to Airbus Model A300 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; and Model A300 B4–605R airplanes; certificated in any category; except airplanes on which Airbus Modification 6661 has been embodied during production. E:\FR\FM\15SER1.SGM 15SER1 Federal Register / Vol. 81, No. 179 / Thursday, September 15, 2016 / Rules and Regulations (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by reports of cracks in the aft hinge brackets of the outer shroud box that is located in the outer wing box, which were found during routine maintenance checks, and our subsequent determination that a change in inspection compliance times is needed. We are issuing this AD to detect and correct cracking of the aft hinge brackets of the outer shroud box; such cracking could affect the structural integrity of the airplane. rmajette on DSK2TPTVN1PROD with RULES (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections At the applicable compliance time specified in paragraph (g)(1), (g)(2), or (g)(3) of this AD: Do a detailed inspection for cracks and fractures of the hinge brackets of the forward and aft outer shroud boxes, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300– 57–0142, Revision 04, dated March 30, 2011; or Airbus Service Bulletin A300–57–6010, Revision 05, dated February 21, 2011; as applicable. Repeat the inspection thereafter at the applicable interval specified in paragraph (g)(1), (g)(2), or (g)(3) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300– 57–0142, Revision 04, dated March 30, 2011; or Airbus Service Bulletin A300–57–6010, Revision 05, dated February 21, 2011; as applicable. Doing the replacement specified in paragraph (j) of this AD terminates the repetitive inspections required by this paragraph. (1) For Model A300 B4–601, B4–603, B4– 605R, B4–620, B4–622, B4–2C, and B4–203 airplanes: Do the inspection at the later of the times specified in paragraphs (g)(1)(i) and (g)(1)(ii) of this AD. Repeat the inspection thereafter at intervals not to exceed 1,000 flight cycles or 2,000 flight hours, whichever occurs first. (i) Before the accumulation of 5,000 flight cycles or 10,400 flight hours since first flight, whichever occurs first. (ii) Within 100 flight cycles after the effective date of this AD. (2) For Model A300 B2–1C, B2–203, and B2K–3C airplanes: Do the inspection at the later of the times specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD. Repeat the inspection thereafter at intervals not to exceed 1,000 flight cycles or 1,000 flight hours, whichever occurs first. (i) Before the accumulation of 5,000 flight cycles or 5,400 flight hours since first flight, whichever occurs first. (ii) Within 100 flight cycles after the effective date of this AD. (3) For Model A300 B4–103 airplanes: Do the inspection at the later of the times specified in paragraphs (g)(3)(i) and (g)(3)(ii) of this AD. Repeat the inspection thereafter at intervals not to exceed 1,000 flight cycles or 1,300 flight hours, whichever occurs first. VerDate Sep<11>2014 14:38 Sep 14, 2016 Jkt 238001 (i) Before the accumulation of 5,000 flight cycles or 6,600 flight hours since first flight, whichever occurs first. (ii) Within 100 flight cycles after the effective date of this AD. (h) Corrective Action If any crack or fracture is found during any inspection required by paragraph (g) of this AD: Before further flight, replace the damaged hinge bracket with a new bracket, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300– 57–143, Revision 2, dated July 10, 1989; or Airbus A300–57–6011, Revision 2, dated July 10, 1989; as applicable. (i) Related Investigative and Corrective Actions If any crack or fracture is found during any inspection required by paragraph (g) of this AD: Before further flight, do a general visual inspection for secondary damage (e.g., cracks, wear damage, pitting, and gouging) in the areas specified in paragraphs (i)(1), (i)(2), and (i)(3) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–57–0142, Revision 04, dated March 30, 2011; or Airbus Service Bulletin A300–57–6010, Revision 05, dated February 21, 2011; as applicable. If any damage is found, before further flight, repair using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). (1) The inner shroud-box forward attachments and the attachment brackets at the inboard end. (2) The inner and outer shroud-box structure, adjacent to the fractured bracket. (3) The top skin of the inboard flap. (j) Optional Terminating Action for Inspection Requirements of Paragraph (g) of This AD (1) Replacement of the hinge bracket, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300– 57–143, Revision 2, dated July 10, 1989 (for Model A300 series airplanes); or Airbus Service Bulletin A300–57–6011, Revision 2, dated July 10, 1989; as applicable; terminates the inspection requirements of paragraph (g) of this AD (for Model A300 B4–600 series airplanes). (2) Replacement of a hinge bracket before the effective date of this AD terminates the repetitive inspections required by paragraph (g) of this AD, provided that after the hinge bracket replacement, but before further flight after the effective date of this AD, a one-time detailed inspection of the forward and aft outer shroud box has been done with no cracking found, in accordance with paragraph (g) of this AD. The replacement must be done in accordance with a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or EASA; or Airbus’s EASA DOA. (k) Credit for Previous Actions This paragraph provides credit for inspections required by paragraph (g) of this AD, if those actions were performed before PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 63373 the effective date of this AD using any of the applicable service information listed in paragraphs (k)(1) through (k)(8) of this AD. (1) Airbus Service Bulletin A300–57–142, dated December 17, 1986. (2) Airbus Service Bulletin A300–57–142, Revision 1, dated April 9, 1990. (3) Airbus Service Bulletin A300–57–142, Revision 2, dated January 16, 1991. (4) Airbus Service Bulletin A300–57–0142, Revision 03, dated February 22, 1999. (5) Airbus Service Bulletin A300–57–6010, Revision 1, dated December 14, 1990. (6) Airbus Service Bulletin A300–57–6010, Revision 02, dated March 30, 1998. (7) Airbus Service Bulletin A300–57–6010, Revision 03, dated September 16, 1998. (8) Airbus Service Bulletin A300–57–6010, Revision 04, dated February 22, 1999. (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-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. (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; EASA; or Airbus’s EASA 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 2013–0181R1, dated August 20, 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–2015–6550. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (n)(3) and (n)(4) 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. E:\FR\FM\15SER1.SGM 15SER1 63374 Federal Register / Vol. 81, No. 179 / Thursday, September 15, 2016 / Rules and Regulations (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Airbus Service Bulletin A300–57–0142, Revision 04, dated March 30, 2011. (ii) Airbus Service Bulletin A300–57–143, Revision 2, dated July 10, 1989. Pages 1, 3, 4, 7, 10, 13, and 14 of this document are identified as Revision 2, dated July 10, 1989; pages 2 and 8 are identified as original, dated December 12, 1986; and pages 5, 6, 9, 11, 12, and 15 are identified as Revision March 19, 1987. (iii) Airbus Service Bulletin A300–57– 6010, Revision 05, dated February 21, 2011. (iv) Airbus Service Bulletin A300–57– 6011, Revision 2, dated July 10, 1989. Pages 1, 2, 5, 7, 8, 11, and 12 of this document are identified as Revision 2, dated July 10, 1989; pages 3, 4, and 13 are identified as Revision 1, dated March 19, 1987; and pages 6, 9, 10 are identified as original, dated December 17, 1986. (3) 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. (4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Renton, Washington, on August 24, 2016. John P. Piccola, Jr., Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–21146 Filed 9–14–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–3781; Directorate Identifier 2015–SW–048–AD; Amendment 39–18649; AD 2016–18–18] RIN 2120–AA64 rmajette on DSK2TPTVN1PROD with RULES Airworthiness Directives; Agusta S.p.A. Helicopters Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model A109A, A109A II, A109C, A109E, A109K2, A109S, and SUMMARY: VerDate Sep<11>2014 14:38 Sep 14, 2016 Jkt 238001 AW109SP helicopters. This AD requires visually inspecting the tail rotor drive shaft assembly (drive shaft) for a crack. This AD was prompted by the discovery of three cracks on the drive shaft of a Model A109S helicopter. The actions of this AD are intended to detect a crack on the drive shaft to prevent failure of the driveshaft, failure of the tail rotor, and subsequent loss of helicopter control. DATES: This AD is effective October 20, 2016. The Director of the Federal Register approved the incorporation by reference of certain documents listed in this AD as of October 20, 2016. ADDRESSES: For service information identified in this final rule, contact AgustaWestland, Product Support Engineering, Via del Gregge, 100, 21015 Lonate Pozzolo (VA) Italy, ATTN: Maurizio D’Angelo; telephone 39–0331– 664757; fax 39–0331–664680; or at http://www.agustawestland.com/ technical-bulletins. You may review the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy, Room 6N–321, Fort Worth, TX 76177. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2015–3781. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 3781; or in person at the Docket Operations Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the European Aviation Safety Agency (EASA) AD, any incorporated-by-reference service information, the economic evaluation, any comments received, and other information. The street address for the Docket Operations Office (phone: 800– 647–5527) is U.S. Department of Transportation, Docket Operations Office, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Martin R. Crane, Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 10101 Hillwood Pkwy, Fort Worth, TX 76177; telephone (817) 222–5110; email martin.r.crane@faa.gov. SUPPLEMENTARY INFORMATION: Discussion On March 22, 2016, at 81 FR 15171, the Federal Register published our PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 notice of proposed rulemaking (NPRM), which proposed to amend 14 CFR part 39 by adding an AD that would apply to Agusta S.p.A. Model A109A, A109A II, A109C, A109E, A109K2, A109S, and AW109SP helicopters with a drive shaft part number (P/N) 109–8412–02–1 or 109–8412–02–3 installed. The NPRM proposed to require visually inspecting the drive shaft for a crack. The proposed requirements were intended to detect a crack on the drive shaft to prevent failure of the driveshaft, failure of the tail rotor, and subsequent loss of helicopter control. The NPRM was prompted by AD No. 2015–0054, dated March 27, 2015, issued by EASA, which is the Technical Agent for the Member States of the European Union, to correct an unsafe condition for the Model A109A with retrofit kit P/N 109–0820–27–101 installed, and Model A109A II, A109C, A109E, A109K2, A109LUH, A109S, and AW109SP helicopters. EASA advises that during scheduled maintenance on a Model A109S helicopter, three cracks were found on the drive shaft. An investigation could not determine the cause of the cracking but concluded it could not have been caused by fatigue. This condition, if not detected and corrected, could lead to tail rotor failure, possibly resulting in loss of helicopter control, EASA advises. EASA AD No. 2015–0054 consequently requires a one-time inspection of the drive shaft, and replacing the drive shaft if cracks are found. Comments We gave the public the opportunity to participate in developing this AD, but we received no comments on the NPRM (81 FR 15171, March 22, 2016). FAA’s Determination These helicopters have been approved by the aviation authority of Italy and are approved for operation in the United States. Pursuant to our bilateral agreement with Italy, EASA, its technical representative, has notified us of the unsafe condition described in the EASA AD. We are issuing this AD because we evaluated all information provided by EASA and determined the unsafe condition exists and is likely to exist or develop on other helicopters of these same type designs and that air safety and the public interest require adopting the AD requirements as proposed. Interim Action We consider this AD to be an interim action. The design approval holder has not determined the cause of the unsafe E:\FR\FM\15SER1.SGM 15SER1

Agencies

[Federal Register Volume 81, Number 179 (Thursday, September 15, 2016)]
[Rules and Regulations]
[Pages 63370-63374]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-21146]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-6550; Directorate Identifier 2013-NM-162-AD; 
Amendment 39-18638; AD 2016-18-08]
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) 90-11-05 for 
certain Airbus Model A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-
203 airplanes and Model A300 B4-600 series airplanes. AD 90-11-05 
required repetitive detailed inspections for cracking in the aft hinge 
brackets of the outer shroud box that is located in the outer wing box, 
and related investigative and corrective actions if necessary. This new 
AD changes certain compliance times and adds airplanes to the 
applicability. This AD was prompted by reports of cracks in the aft 
hinge brackets of the outer shroud box that is located in the outer 
wing box, which were found during routine maintenance checks, and our 
subsequent determination that a change in inspection compliance times 
is needed. We are issuing this AD to detect and correct cracking of the 
aft hinge brackets of the outer shroud box; such cracking could affect 
the structural integrity of the airplane.

DATES: This AD becomes effective October 20, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of October 20, 
2016.

ADDRESSES: For service information identified in this final rule, 
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-
6550.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
6550; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The address for the Docket Office (telephone 800-
647-5527) is Docket Management Facility, U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA

[[Page 63371]]

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 90-11-05, Amendment 39-6603 (89-NM-223-AD) (55 
FR 20129, May 15, 1990) (``AD 90-11-05''). AD 90-11-05 applied to 
certain Airbus Model A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4 
203 airplanes and Model A300 B4-600 series airplanes. The NPRM 
published in the Federal Register on December 14, 2015 (80 FR 77279) 
(``the NPRM''). The NPRM was prompted by a determination that a change 
to certain compliance times is needed. The NPRM proposed to continue to 
require doing repetitive detailed inspections for cracking in the hinge 
brackets of the forward and aft outer shroud boxes that are located in 
the outer wing box, and related investigative and corrective actions if 
necessary. The NPRM also proposed to change certain compliance times 
and add airplanes to the applicability. We are issuing this AD to 
detect and correct cracking of the aft hinge brackets of the outer 
shroud box; such cracking could affect the structural integrity of the 
airplane.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2013-0181R1, dated August 20, 2013 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Model A300 
series airplanes and Model A300 B4-600 series airplanes. The MCAI 
states:

    In the past, aft hinge brackets of the outer wing box were found 
cracked. Fracture of a bracket would allow vertical movement of the 
inner shroud box structure, which could result in damage to the top 
skin of the inboard flap. In addition, the loads carried by the 
brackets will be transferred to the remaining supports, which may 
also crack and cause extensive structural damage.
    This condition, if not detected and corrected, could affect the 
structural integrity of the aeroplane.
    To address this potential unsafe condition, DGAC [Direction 
G[eacute]n[eacute]rale de l'Aviation Civile] France issued * * * [an 
airworthiness directive] (later revised) to require repetitive 
inspections of the hinge bracket of the outer box and, depending on 
findings, corrective action(s).
    Since that [DGAC] AD was issued, a fleet survey and updated 
Fatigue and Damage Tolerance analysis were performed in order to 
substantiate the A300 Extended Service Goal (ESG) and A300-600 
Extended Service Goal (ESG2) exercise.
    The results of these analyses led to a change in the inspection 
thresholds and intervals in Flight Cycles (FC) and the introduction 
of Flight Hours (FH) limits.
    For the reasons described above, this [EASA] AD retains the 
requirements of DGAC France * * * [an airworthiness directive], 
which is superseded, but requires those actions within the new 
thresholds and intervals given by Airbus Service Bulletin (SB) A300-
57-0142 Revision 04 or A300-57-6010 Revision 05, as applicable to 
aeroplane model.
    Revision 1 of this [EASA] AD is issued to add model A300 B4-203 
aeroplanes to the applicability and compliance time tables. This 
model is covered by Airbus SB A300-57-0142, but was mistakenly 
omitted from the original [EASA] AD issue.

    The corrective action for a hinge bracket that is cracked or 
fractured is replacing the damaged hinge bracket with a new bracket.
    For airplanes on which a crack is found in one half bracket or both 
half brackets, related investigative actions include a general visual 
inspection for secondary damage (e.g., cracks, wear damage, pitting, 
and gouging) in the following areas:
     The inner shroud-box forward attachments and the 
attachment brackets at the inboard end.
     The inner and outer shroud-box structure, adjacent to the 
fractured bracket.
     The top skin of the inboard flap.
    The corrective action for damage findings during the related 
investigative action is repair using a method approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; or 
EASA; or Airbus's EASA Design Organization Approval (DOA).
    The compliance time for related investigative actions and 
corrective actions is before further flight.
    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
6550.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comment received on the NPRM and 
the FAA's response to the comment.

Request To Exclude Certain Airplanes From the Applicability

    FedEx requested that we exclude from the proposed applicability 
airplanes on which the actions specified in Airbus Service Bulletin 
A300-57-6011, Revision 2, dated July 10, 1989, have been accomplished. 
FedEx stated that it has accomplished the optional terminating actions 
provided in paragraph (j)(1) of the proposed AD, and specified in 
Airbus Service Bulletin A300-57-6011, Revision 2, dated July 10, 1989, 
on several of its airplanes.
    We disagree with FedEx's request. As of the effective date of this 
AD, additional actions are required for airplanes on which the optional 
modification has been accomplished. These airplanes will need to have a 
one-time detailed visual inspection of the forward and aft outer shroud 
box with no cracking found, as required by paragraph (j)(2) of this AD. 
We have not changed this AD in this regard.

Changes Made to This AD

    In paragraph (j)(2) of the proposed AD, we proposed to provide an 
optional method of compliance (i.e., a replacement and a one-time 
inspection) for actions specified in paragraph (g) of the proposed AD. 
We also proposed to give credit in paragraph (k)(2) of the proposed AD 
for replacements accomplished before the effective date of this AD 
using the same service information identified in paragraph (j)(2) of 
the AD:
     Airbus Service Bulletin A300-57-143, dated December 17, 
1986.
     Airbus Service Bulletin A300-57-143, Revision 1, dated 
March 19, 1987.
     Airbus Service Bulletin A300-57-6011, dated December 17, 
1986.
     Airbus Service Bulletin A300-57-6011, Revision 1, dated 
March 19, 1987.
    Since we cannot make this service information reasonably available, 
we have revised paragraph (j)(2) of the proposed AD, removed redundant 
paragraph (k)(2) of the proposed AD from this AD, and redesignated 
paragraph (k)(1) and subsequent subparagraphs accordingly. We revised 
paragraph (j)(2) of this AD by removing the references to the service 
information and instead specified that operators must do the 
replacement using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or 
Airbus's EASA Design Organization Approval (DOA).

Conclusion

    We reviewed the available data, including the comment received, and 
determined that air safety and the public interest require adopting 
this AD as proposed except for minor editorial changes. We have 
determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and

[[Page 63372]]

     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information.
     Airbus Service Bulletin A300-57-0142, Revision 04, dated 
March 30, 2011, which describes procedures for doing an inspection of 
the forward and aft hinge brackets on the outer shroud box.
     Airbus Service Bulletin A300-57-143, Revision 2, dated 
July 10, 1989, which describes procedures for replacing the aft 
aluminum alloy brackets on the outer shroud box with new steel 
brackets.
     Airbus Service Bulletin A300-57-6010, Revision 05, dated 
February 21, 2011, which describes procedures for doing an inspection 
of the forward and aft hinge brackets on the outer shroud box.
     Airbus Service Bulletin A300-57-6011, Revision 2, dated 
July 10, 1989, which describes procedures for replacing the aft 
aluminum alloy brackets on the outer shroud box with new steel 
brackets.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

Costs of Compliance

    We estimate that this AD affects 3 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                     Labor cost          Parts cost     Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspection.....................  8 work-hours x $85 per               $0  $680 per            $2,040 per
                                  hour = $680 per                          inspection cycle.   inspection cycle.
                                  inspection cycle.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements 
that would be required based on the results of the inspection. We have 
no way of determining the number of aircraft that might need these 
replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                   Action                                 Labor cost                Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replacement................................  27 work-hours x $85 per hour =              $25,650         $27,945
                                              $2,295.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition related investigative and 
corrective actions specified in this AD.

Authority for This Rulemaking

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

Regulatory Findings

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

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) 
90-11-05, Amendment 39-6603 (89-NM-223-AD) (55 FR 20129, May 15, 1990), 
and adding the following new AD:

2016-18-08 Airbus: Amendment 39-18638. Docket No. FAA-2015-6550; 
Directorate Identifier 2013-NM-162-AD.

(a) Effective Date

    This AD becomes effective October 20, 2016.

(b) Affected ADs

    This AD replaces AD 90-11-05, Amendment 39-6603 (89-NM-223-AD) 
(55 FR 20129, May 15, 1990).

(c) Applicability

    This AD applies to Airbus Model A300 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; and Model A300 B4-605R airplanes; certificated 
in any category; except airplanes on which Airbus Modification 6661 
has been embodied during production.

[[Page 63373]]

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Reason

    This AD was prompted by reports of cracks in the aft hinge 
brackets of the outer shroud box that is located in the outer wing 
box, which were found during routine maintenance checks, and our 
subsequent determination that a change in inspection compliance 
times is needed. We are issuing this AD to detect and correct 
cracking of the aft hinge brackets of the outer shroud box; such 
cracking could affect the structural integrity of the airplane.

(f) Compliance

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

(g) Repetitive Inspections

    At the applicable compliance time specified in paragraph (g)(1), 
(g)(2), or (g)(3) of this AD: Do a detailed inspection for cracks 
and fractures of the hinge brackets of the forward and aft outer 
shroud boxes, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A300-57-0142, Revision 04, dated March 30, 
2011; or Airbus Service Bulletin A300-57-6010, Revision 05, dated 
February 21, 2011; as applicable. Repeat the inspection thereafter 
at the applicable interval specified in paragraph (g)(1), (g)(2), or 
(g)(3) of this AD, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-57-0142, Revision 04, 
dated March 30, 2011; or Airbus Service Bulletin A300-57-6010, 
Revision 05, dated February 21, 2011; as applicable. Doing the 
replacement specified in paragraph (j) of this AD terminates the 
repetitive inspections required by this paragraph.
    (1) For Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, B4-
2C, and B4-203 airplanes: Do the inspection at the later of the 
times specified in paragraphs (g)(1)(i) and (g)(1)(ii) of this AD. 
Repeat the inspection thereafter at intervals not to exceed 1,000 
flight cycles or 2,000 flight hours, whichever occurs first.
    (i) Before the accumulation of 5,000 flight cycles or 10,400 
flight hours since first flight, whichever occurs first.
    (ii) Within 100 flight cycles after the effective date of this 
AD.
    (2) For Model A300 B2-1C, B2-203, and B2K-3C airplanes: Do the 
inspection at the later of the times specified in paragraphs 
(g)(2)(i) and (g)(2)(ii) of this AD. Repeat the inspection 
thereafter at intervals not to exceed 1,000 flight cycles or 1,000 
flight hours, whichever occurs first.
    (i) Before the accumulation of 5,000 flight cycles or 5,400 
flight hours since first flight, whichever occurs first.
    (ii) Within 100 flight cycles after the effective date of this 
AD.
    (3) For Model A300 B4-103 airplanes: Do the inspection at the 
later of the times specified in paragraphs (g)(3)(i) and (g)(3)(ii) 
of this AD. Repeat the inspection thereafter at intervals not to 
exceed 1,000 flight cycles or 1,300 flight hours, whichever occurs 
first.
    (i) Before the accumulation of 5,000 flight cycles or 6,600 
flight hours since first flight, whichever occurs first.
    (ii) Within 100 flight cycles after the effective date of this 
AD.

(h) Corrective Action

    If any crack or fracture is found during any inspection required 
by paragraph (g) of this AD: Before further flight, replace the 
damaged hinge bracket with a new bracket, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-57-143, 
Revision 2, dated July 10, 1989; or Airbus A300-57-6011, Revision 2, 
dated July 10, 1989; as applicable.

(i) Related Investigative and Corrective Actions

    If any crack or fracture is found during any inspection required 
by paragraph (g) of this AD: Before further flight, do a general 
visual inspection for secondary damage (e.g., cracks, wear damage, 
pitting, and gouging) in the areas specified in paragraphs (i)(1), 
(i)(2), and (i)(3) of this AD, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-57-0142, Revision 04, 
dated March 30, 2011; or Airbus Service Bulletin A300-57-6010, 
Revision 05, dated February 21, 2011; as applicable. If any damage 
is found, before further flight, repair using a method approved by 
the Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; or the European Aviation Safety Agency (EASA); or 
Airbus's EASA Design Organization Approval (DOA).
    (1) The inner shroud-box forward attachments and the attachment 
brackets at the inboard end.
    (2) The inner and outer shroud-box structure, adjacent to the 
fractured bracket.
    (3) The top skin of the inboard flap.

(j) Optional Terminating Action for Inspection Requirements of 
Paragraph (g) of This AD

    (1) Replacement of the hinge bracket, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-57-143, 
Revision 2, dated July 10, 1989 (for Model A300 series airplanes); 
or Airbus Service Bulletin A300-57-6011, Revision 2, dated July 10, 
1989; as applicable; terminates the inspection requirements of 
paragraph (g) of this AD (for Model A300 B4-600 series airplanes).
    (2) Replacement of a hinge bracket before the effective date of 
this AD terminates the repetitive inspections required by paragraph 
(g) of this AD, provided that after the hinge bracket replacement, 
but before further flight after the effective date of this AD, a 
one-time detailed inspection of the forward and aft outer shroud box 
has been done with no cracking found, in accordance with paragraph 
(g) of this AD. The replacement must be done in accordance with a 
method approved by the Manager, International Branch, ANM-116, 
Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA.

(k) Credit for Previous Actions

    This paragraph provides credit for inspections required by 
paragraph (g) of this AD, if those actions were performed before the 
effective date of this AD using any of the applicable service 
information listed in paragraphs (k)(1) through (k)(8) of this AD.
    (1) Airbus Service Bulletin A300-57-142, dated December 17, 
1986.
    (2) Airbus Service Bulletin A300-57-142, Revision 1, dated April 
9, 1990.
    (3) Airbus Service Bulletin A300-57-142, Revision 2, dated 
January 16, 1991.
    (4) Airbus Service Bulletin A300-57-0142, Revision 03, dated 
February 22, 1999.
    (5) Airbus Service Bulletin A300-57-6010, Revision 1, dated 
December 14, 1990.
    (6) Airbus Service Bulletin A300-57-6010, Revision 02, dated 
March 30, 1998.
    (7) Airbus Service Bulletin A300-57-6010, Revision 03, dated 
September 16, 1998.
    (8) Airbus Service Bulletin A300-57-6010, Revision 04, dated 
February 22, 1999.

(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.
    (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; EASA; or Airbus's EASA 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 2013-0181R1, dated August 20, 
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-2015-6550.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (n)(3) and (n)(4) 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.

[[Page 63374]]

    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) Airbus Service Bulletin A300-57-0142, Revision 04, dated 
March 30, 2011.
    (ii) Airbus Service Bulletin A300-57-143, Revision 2, dated July 
10, 1989. Pages 1, 3, 4, 7, 10, 13, and 14 of this document are 
identified as Revision 2, dated July 10, 1989; pages 2 and 8 are 
identified as original, dated December 12, 1986; and pages 5, 6, 9, 
11, 12, and 15 are identified as Revision March 19, 1987.
    (iii) Airbus Service Bulletin A300-57-6010, Revision 05, dated 
February 21, 2011.
    (iv) Airbus Service Bulletin A300-57-6011, Revision 2, dated 
July 10, 1989. Pages 1, 2, 5, 7, 8, 11, and 12 of this document are 
identified as Revision 2, dated July 10, 1989; pages 3, 4, and 13 
are identified as Revision 1, dated March 19, 1987; and pages 6, 9, 
10 are identified as original, dated December 17, 1986.
    (3) 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.
    (4) You may view this service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on August 24, 2016.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-21146 Filed 9-14-16; 8:45 am]
BILLING CODE 4910-13-P