Airworthiness Directives; Airbus Airplanes, 12401-12405 [2017-03951]

Download as PDF Federal Register / Vol. 82, No. 41 / Friday, March 3, 2017 / Rules and Regulations Issued in Renton, Washington, on February 17, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–03968 Filed 3–2–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–9298; Directorate Identifier 2015–NM–161–AD; Amendment 39–18811; AD 2017–05–01] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for all Airbus Model A300 series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) that indicates that a section of the wing and aft fuselage is subject to widespread fatigue damage (WFD). This AD requires an inspection to determine if certain modifications have been done. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective April 7, 2017. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of April 7, 2017. 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: continued.airworthiness-wb.external@ 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–2016–9298. mstockstill on DSK3G9T082PROD with RULES SUMMARY: Examining the AD Docket You may examine the AD docket on the Internet at http:// VerDate Sep<11>2014 16:07 Mar 02, 2017 Jkt 241001 www.regulations.gov by searching for and locating Docket No. FAA–2016– 9298; 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 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 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 by adding an AD that would apply to all Airbus Model A300 series airplanes. The NPRM published in the Federal Register on October 26, 2016 (81 FR 74354) (‘‘the NPRM’’). The NPRM was prompted by an evaluation by the DAH that indicates that a section of the wing and aft fuselage is subject to WFD. The NPRM proposed to require an inspection to determine if certain modifications have been done. For airplanes on which the specified modifications have not been done, this AD requires accomplishing those modifications, including doing related investigative and corrective actions if necessary. We are issuing this AD to prevent reduced structural integrity of these airplanes due to the failure of certain structural components. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2015– 0173R1, dated August 31, 2016, (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Model A300 series airplanes. The MCAI states: A widespread fatigue damage (WFD) analysis conducted on A300 aeroplanes identified areas which are susceptible to crack development. This condition, if not corrected, could affect the structural integrity of the aeroplane. To address this issue, Airbus developed a modification (mod) to reinforce the structure of the aeroplane. Airbus issued Service Bulletin (SB) A300–53–0271 to provide PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 12401 instructions for a cold expansion of the foot attachment holes of certain fuselage frames, ´ ´ and DGAC [Direction Generale de l’Aviation Civile] France issued AD F–2004–001 to require this mod [which corresponds with certain requirements in FAA AD 2004–23– 20, Amendment 39–13875 (69 FR 68779, November 26, 2004)]. Since that [DGAC] AD was issued, Airbus released twelve other mods with corresponding SBs, to complete the set of inspections and repairs in the frame of the A300 WFD campaign. EASA issued AD 2015–0115 to require ten of these mods through section 3 of ALS [Airworthiness Limitations Section] Part 2, and decision is made to delete section 3 from ALS Part 2. For the reasons described above, EASA issued AD 2015–0173, retaining the requirements of DGAC France AD F–2004– 001, which was superseded, to require implementation of the additional inspection, modification and/or repair actions, as applicable to aeroplane model. This [EASA] AD is revised to give credit for previous use of any earlier revision of an affected Airbus SB, based on the fact that no additional work is included in the later SB revisions. Required actions include an inspection to determine if certain modifications have been done. For airplanes on which the specified modifications have not been done, this AD requires accomplishing those modifications, including doing related investigative and corrective actions if necessary. Depending on airplane configuration, the compliance times for modifying the airplane structure range between 13,300 flight cycles and 48,000 flight cycles since first flight of the airplane. 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–2016– 9298. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. Conclusion We reviewed the relevant 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 for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. E:\FR\FM\03MRR1.SGM 03MRR1 12402 Federal Register / Vol. 82, No. 41 / Friday, March 3, 2017 / Rules and Regulations Related Service Information Under 1 CFR Part 51 Airbus issued the following service information: • Airbus Service Bulletin A300–53– 0239, Revision 02, dated March 6, 2000. This service information describes procedures to modify the longitudinal junction. The modification includes the addition of external doublers and installation of interference fit attachments and related investigative and corrective actions. The related investigative actions are rotary probe inspections for cracking of the fastener holes. The corrective action is repair. • Airbus Service Bulletin A300–53– 247, Revision 2, dated July 20, 1990. This service information describes procedures to modify the fuselage upper door frame structure, which consists of eddy current inspections of certain structure for cracks, and structural modification or repair. • Airbus Service Bulletin A300–53– 0271, Revision 05, dated June 21, 2013. This service information describes procedures to modify the fuselage frame (FR), which includes cold expansion of the fastener holes between FR 41 and FR 54, and related investigative and corrective actions. The related investigative actions including rotary probe inspections for cracking of the fastener holes. The corrective action is repair. • Airbus Service Bulletin A300–53– 0366, dated April 7, 2005. This service information describes procedures to modify the fuselage frame, which includes installing an additional external doubler on the fuselage lap joint at fuselage stringers (STGR) 22, left and right, between FR 26 and FR 40. • Airbus Service Bulletin A300–53– 0368, dated April 7, 2005. This service information describes procedures to modify the rear fuselage, which includes installing an additional external doubler on the fuselage lap joint at STGR 51, left and right, between FR 72 and FR 80. • Airbus Service Bulletin A300–53– 0369, Revision 03, dated September 1, 2010. This service information describes procedures to modify the rear fuselage, which includes reinforcing the butt joint at FR 72 by installation of an additional external doubler at the butt joint of FR 72 at STGR 14, left and right. • Airbus Service Bulletin A300–53– 0373, Revision 03, dated September 1, 2010. This service information describes procedures to modify the rear fuselage, which includes reinforcing the butt joint at FR65 by installation of an additional external doubler at the butt joint of FR65 between STGR 13 left and right. • Airbus Service Bulletin A300–53– 0374, Revision 04, dated July 5, 2013. This service information describes procedures to modify the rear fuselage, which includes reinforcing the butt joints at FR55 and FR58 by installation of additional external doublers without cutout at certain butt joints. • Airbus Service Bulletin A300–53– 0375, Revision 01, dated June 24, 2013. This service information describes procedures to modify the forward fuselage, which includes reinforcing the fuselage circumferential butt joint at FR 26 by installation of an additional external doubler at the butt joint of FR 26 between STGR 13 left and STGR 13 right. • Airbus Service Bulletin A300–53– 0393, dated September 27, 2013. This service information describes procedures to modify the fuselage frame which includes reinforcing the longitudinal butt joints with additional butt straps at certain fuselage frames and stringers. • Airbus Service Bulletin A300–57– 0203, Revision 04, dated February 18, 2015. This service information describes procedures to modify the outer wing, which includes removal of the wing stringer and run-out plate at STGR 19 on the bottom wing skin; replacement of the taper-lok bolts with interference fit parallel bolts; and related investigative and corrective actions. Related investigative actions include detailed visual and high frequency eddy current (HFEC) inspections of the stringer runouts for cracks; eddy current inspections for cracks of the fastener holes; and detailed visual and HFEC inspections of the stringer run-outs for cracks and damage. Corrective actions include repair. • Airbus Service Bulletin A300–57– 0258, dated September 30, 2014 (for Model A300 B4–103 and A300 B4–2C airplanes). This service information describes procedures to modify the wing structure, which includes a first oversize of the critical holes on certain wing stringers, and related investigative and corrective actions. Related investigated actions include detailed visual inspections for damage of the top wing skin external surface and the stringer joint; and roto-probe inspections for damage of the fastener holes. Corrective actions include repair. • Airbus Service Bulletin A300–57– 0259, dated September 30, 2014 (for Model A300 B2–1C, A300 B2–203, and A300 B2K–3C airplanes). This service information describes procedures to modify the wing structure, which includes a first oversize of the critical holes on certain wing stringers, and related investigative and corrective actions. Related investigated actions include detailed visual inspections for damage of the top wing skin external surface and the stringer joint; and rotoprobe inspections for damage of the fastener holes. Corrective actions include repair. 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 8 airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Labor cost Modification ............................. mstockstill on DSK3G9T082PROD with RULES Action 3,291 work-hours × $85 per hour = $279,735 ....................... In addition, we estimate that any necessary follow-on actions will take about 15 work-hours and require parts costing $10,000, for a cost of $11,275 per product. We have no way of determining the number of aircraft that might need this action. VerDate Sep<11>2014 16:07 Mar 02, 2017 Jkt 241001 Parts cost 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 PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 $142,845 Cost per product $422,580 Cost on U.S. operators $3,380,640 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 E:\FR\FM\03MRR1.SGM 03MRR1 Federal Register / Vol. 82, No. 41 / Friday, March 3, 2017 / Rules and Regulations 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: and B4–203 airplanes, certificated in any category, all manufacturer serial numbers. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by an evaluation by the design approval holder that indicates that a section of the wing and aft fuselage is subject to widespread fatigue damage. We are issuing this AD to prevent reduced structural integrity of these airplanes due to the failure of certain structural components. PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ (f) Compliance Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 12403 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2017–05–01 Airbus: Amendment 39–18811; Docket No. FAA–2016–9298; Directorate Identifier 2015–NM–161–AD. (a) Effective Date This AD is effective April 7, 2017. (b) Affected ADs This AD affects AD 2004–23–20, Amendment 39–13875 (69 FR 68779, November 26, 2004) (‘‘AD 2004–23–20’’). (c) Applicability This AD applies to Airbus Model A300 B2– 1A, B2–1C, B2K–3C, B2–203, B4–2C, B4–103, Comply with this AD within the compliance times specified, unless already done. (g) Verification of Embodied Modifications Within 4 months after the effective date of this AD, verify whether the Airbus modifications specified in table 1 to paragraphs (g), (h), and (i) of this AD, as applicable to airplane model, have been embodied on the airplane, in accordance with the Accomplishment Instructions of the applicable Airbus service bulletin specified in table 1 to paragraphs (g), (h), and (i) of this AD. A review of the airplane maintenance records is acceptable to accomplish the verification required by this paragraph, provided those records can be used to conclusively determine whether the modifications have been embodied. TABLE 1 TO PARAGRAPHS (g), (h), AND (i) OF THIS AD—AIRBUS MODIFICATION AND APPLICABLE SERVICE BULLETIN Set Airbus modification Set 1A ............................................. 751 ................................................. 7301 ............................................... 10326 ............................................. 12735 ............................................. 12736 ............................................. 12737 ............................................. 12798 ............................................. 07757 and 12977 .......................... 13611 ............................................. 13692 ............................................. 13716 ............................................. 12794 ............................................. 12796 ............................................. mstockstill on DSK3G9T082PROD with RULES Set 1B ............................................. (h) Corrective Actions for Modifications Which Have Not Been Embodied If, during the verification required by paragraph (g) of this AD, it is determined that any modification has not been embodied, do the applicable actions specified in paragraphs (h)(1), (h)(2), and (h)(3) of this AD. (1) If it is determined that any Airbus modification, specified in the applicable Airbus Service Bulletin, identified in ‘‘Set 1A’’ of table 1 to paragraphs (g), (h), and (i) of this AD is not embodied: Within the applicable compliance time specified in the applicable Airbus Service Bulletin identified in ‘‘Set 1A’’ of table 1 to paragraphs (g), (h), VerDate Sep<11>2014 16:07 Mar 02, 2017 Jkt 241001 Applicable Airbus service bulletin A300–53–247, Revision 2, dated July 20, 1990. A300–53–0239, Revision 02, dated March 6, 2000. A300–57–0203, Revision 04, dated February 18, 2015. A300–53–0366, dated April 7, 2005. A300–53–0368, dated April 7, 2005. A300–53–0369, Revision 03, dated September 1, 2010. A300–53–0375, Revision 01, dated June 24, 2013. A300–53–0271, Revision 05, dated June 21, 2013. A300–57–0258, dated September 30, 2014. A300–53–0393, dated September 27, 2013. A300–57–0259, dated September 30, 2014. A300–53–0374, Revision 04, dated July 5, 2013. A300–53–0373, Revision 03, dated September 1, 2010. and (i) of this AD, or within 4 months after the effective date of this AD, whichever occurs later, do the applicable actions specified in paragraphs (h)(1)(i) through (h)(1)(xi) of this AD, except as required by paragraph (i) of this AD. Do all applicable related investigative and corrective actions before further flight. (i) For airplanes on which Airbus Service Bulletin A300–53–0239, Revision 02, dated March 6, 2000, has not been embodied: Modify the longitudinal junction and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 Service Bulletin A300–53–0239, Revision 02, dated March 6, 2000. (ii) For airplanes on which Airbus Service Bulletin A300–53–247, Revision 2, dated July 20, 1990, has not been embodied: Modify the fuselage upper door frame structure by doing eddy current inspections for cracks of the structure specified in Airbus Service Bulletin A300–53–247, Revision 2, dated July 20, 1990, and a structural modification or repair, as applicable, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–53–247, Revision 2, dated July 20, 1990. (iii) For airplanes on which Airbus Service Bulletin A300–53–0271, Revision 05, dated E:\FR\FM\03MRR1.SGM 03MRR1 mstockstill on DSK3G9T082PROD with RULES 12404 Federal Register / Vol. 82, No. 41 / Friday, March 3, 2017 / Rules and Regulations June 21, 2013, has not been embodied: Modify the fuselage frame, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–53–0271, Revision 05, dated June 21, 2013. (iv) For airplanes on which Airbus Service Bulletin A300–53–0366, dated April 7, 2005, has not been embodied: Modify the fuselage frame, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–53–0366, dated April 7, 2005. (v) For airplanes on which Airbus Service Bulletin A300–53–0368, dated April 7, 2005, has not been embodied: Modify the rear fuselage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–53–0366, dated April 7, 2005. (vi) For airplanes on which Airbus Service Bulletin A300–53–0369, Revision 03, dated September 1, 2010, has not been embodied: Modify the rear fuselage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–53–0369, Revision 03, dated September 1, 2010. (vii) For airplanes on which Airbus Service Bulletin A300–53–0375, Revision 01, dated June 24, 2013, has not been embodied: Modify the forward fuselage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–53–0375, Revision 01, dated June 24, 2013. (viii) For airplanes on which Airbus Service Bulletin A300–53–0393, dated September 27, 2013, has not been embodied: Modify the fuselage frame, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–53–0393, dated September 27, 2013. (ix) For airplanes on which Airbus Service Bulletin A300–57–0203, Revision 04, dated February 18, 2015, has not been embodied: Modify the outer wing, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300– 57–0203, Revision 04, dated February 18, 2015. (x) For airplanes on which Airbus Service Bulletin A300–57–0258, dated September 30, 2014, has not been embodied: Modify the wing structure and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300– 57–0258, dated September 30, 2014. (xi) For airplanes on which Airbus Service Bulletin A300–57–0259, dated September 30, 2014, has not been embodied: Modify the wing structure, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300– 57–0259, dated September 30, 2014. (2) If it is determined that Airbus Service Bulletin A300–53–0374, Revision 04 dated July 5, 2013 (mod 12794) has not been embodied: Within the compliance time specified in paragraphs (h)(2)(i), (h)(2)(ii), (h)(2)(iii), and (h)(2)(iv) of this AD, as applicable, modify the rear fuselage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300– VerDate Sep<11>2014 16:07 Mar 02, 2017 Jkt 241001 53–0374, Revision 04, dated July 5, 2013, except as required by paragraph (i) of this AD. (i) For Model A300 B2 and A300 B4–100 airplanes, fuselage frame (FR) 55: Within 31,300 flight cycles since first flight of the airplane, or within 4 months after the effective date of this AD, whichever occurs later. (ii) For Model A300 B2 and A300 B4–100 airplanes, FR 58: Within 49,700 flight cycles since first flight of the airplane, or within 4 months after the effective date of this AD, whichever occurs later. (iii) For Model A300 B4–200 airplanes, FR 55: Within 33,600 flight cycles since first flight of the airplane, or within 4 months after the effective date of this AD, whichever occurs later. (iv) For Model A300 B4–200 airplanes, FR 58: Within 55,800 flight cycles since first flight of the airplane, or within 4 months after the effective date of this AD, whichever occurs later. (3) If it is determined that Airbus Service Bulletin A300–53–0373, Revision 03, dated September 1, 2010 (mod 12796) has not been embodied: Within the compliance time specified in paragraphs (h)(3)(i), (h)(3)(ii), and (h)(3)(iii) of this AD, as applicable, modify the rear fuselage, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–53–0373, Revision 03, dated September 1, 2010, except as required by paragraph (i) of this AD. (i) For Model A300 B2 airplanes: Within 42,700 flight cycles since first flight of the airplane, or within 4 months after the effective date of this AD, whichever occurs later. (ii) For Model A300 B4–100 airplanes: Within 41,700 flight cycles since first flight of the airplane, or within 4 months after the effective date of this AD, whichever occurs later. (iii) For Model A300 B4–200 airplanes: Within 47,900 flight cycles since first flight of the airplane, or within 4 months after the effective date of this AD, whichever occurs later. (i) Exception to the Service Information Where any service information identified in table 1 to paragraphs (g), (h), and (i) of this AD specifies to contact the manufacturer for instructions or solutions, 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). (j) Terminating Action for Certain Requirements in AD 2004–23–20 Accomplishing the modification required by paragraph (h)(1)(iii) of this AD terminates the modification required by paragraph (i) of AD 2004–23–20 for that airplane only. (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 PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 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 425–227–1405; fax 425–227–2125. 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 Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (l) Related Information Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2015–0173R1, dated August 31, 2016, 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–2016–9298. (m) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Airbus Service Bulletin A300–53–0239, Revision 02, dated March 6, 2000. (ii) Airbus Service Bulletin A300–53–247, Revision 2, dated July 20, 1990. (iii) Airbus Service Bulletin A300–53– 0271, Revision 05, dated June 21, 2013. (iv) Airbus Service Bulletin A300–53– 0366, dated April 7, 2005. (v) Airbus Service Bulletin A300–53–0368, dated April 7, 2005. (vi) Airbus Service Bulletin A300–53– 0369, Revision 03, dated September 1, 2010. (vii) Airbus Service Bulletin A300–53– 0373, Revision 03, dated September 1, 2010. E:\FR\FM\03MRR1.SGM 03MRR1 Federal Register / Vol. 82, No. 41 / Friday, March 3, 2017 / Rules and Regulations (viii) Airbus Service Bulletin A300–53– 0374, Revision 04, dated July 5, 2013. (ix) Airbus Service Bulletin A300–53– 0375, Revision 01, dated June 24, 2013. (x) Airbus Service Bulletin A300–53–0393, dated September 27, 2013. (xi) Airbus Service Bulletin A300–57– 0203, Revision 04, dated February 18, 2015. (xii) Airbus Service Bulletin A300–57– 0258, dated September 30, 2014. (xiii) Airbus Service Bulletin A300–57– 0259, dated September 30, 2014. (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: continued.airworthiness-wb.external@ 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 February 16, 2017. Thomas Groves, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–03951 Filed 3–2–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–9357; Directorate Identifier 2016–CE–030–AD; Amendment 39–18798; AD 2017–04–03] RIN 2120–AA64 Airworthiness Directives; Pilatus Aircraft Ltd. Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for Pilatus Aircraft Ltd. Models PC–6, PC–6–H1, PC–6–H2, PC–6/350, PC–6/350–H1, PC– 6/350–H2, PC–6/A, PC–6/A–H1, PC–6/ A–H2, PC–6/B–H2, PC–6/B1–H2, PC–6/ B2–H2, PC–6/B2–H4, PC–6/C–H2, and PC–6/C1–H2 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct mstockstill on DSK3G9T082PROD with RULES SUMMARY: VerDate Sep<11>2014 16:07 Mar 02, 2017 Jkt 241001 an unsafe condition on an aviation product. The MCAI describes the unsafe condition as certain combinations of the aileron counterweight and the attaching parts possibly resulting in reduced thread engagement and leading to disconnection of the aileron counterweight from the aileron. We are issuing this AD to require actions to address the unsafe condition on these products. DATES: This AD is effective April 7, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of April 7, 2017. ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 9357; or in person at Document 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 service information identified in this AD, contact Pilatus Aircraft Ltd., Customer Technical Support (MCC), P.O. Box 992, CH–6371 Stans, Switzerland; phone: +41 (0)41 619 3333; fax: +41 (0)41 619 7311; email: supportPC12@pilatus-aircraft.com; Internet: http://www.pilatusaircraft.com. You may view this referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329– 4148. It is also available on the Internet at http://www.regulations.gov by searching for Docket No. FAA–2016– 9357. FOR FURTHER INFORMATION CONTACT: Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329– 4059; fax: (816) 329–4090; email: doug.rudolph@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to Pilatus Aircraft Ltd. Models PC–6, PC–6–H1, PC–6–H2, PC–6/350, PC–6/350–H1, PC–6/350–H2, PC–6/A, PC–6/A–H1, PC–6/A–H2, PC–6/B–H2, PC–6/B1–H2, PC–6/B2–H2, PC–6/B2– H4, PC–6/C–H2, and PC–6/C1–H2 airplanes. The NPRM was published in the Federal Register on November 4, 2016 (81 FR 76883). The NPRM proposed to correct an unsafe condition PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 12405 for the specified products and was based on mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country. The MCAI states: The proper installation of the aileron counterweight requires a combination, peculiar to each aileron, of anchor nut types, bolt types, number of washers, and the definition of the bolt torque. Some combinations of counterweight and attaching parts, which could result in reduced thread engagement, have been reported on a PC–6 aeroplane. This condition, if not detected and corrected, may lead to a disconnection of the aileron counterweight from the aileron, possibly resulting in reduced control of the aeroplane. To address this potential unsafe condition, Pilatus issued Service Bulletin (SB) No. 57– 006 (hereafter referred to as ‘the SB’ in this AD) to provide inspection instructions. For the reason described above, this AD requires identification and inspection of the affected aileron mass-balance counterweight attachment parts and, depending on findings, accomplishment of applicable corrective action(s). The MCAI can be found in the AD docket on the Internet at: https://www. regulations.gov/document?D=FAA2016-9357-0002. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comment received on the proposal and the FAA’s response to the comment. Request for Clarification on the Unsafe Condition Lukas Owens stated that in the event of loss of the ailerons, some degree of roll control is available by using the secondary effect of rudder. The requester stated that while not an efficient way to turn the aircraft, a pilot has at least some directional control and that short or rapid bursts of power may increase the effectiveness of the rudder to some degree, acting as a form of torque and slipstream effect. The requester asked why the AD change is needed or how it is justified. We infer that the commenter, in addition to asking why the AD action is necessary and how it is justified, believes the AD action is not needed and is not justified. However, the commenter does not present solutions that address the unsafe condition of the mass balance weight potentially separating from the airplane. For this reason, we have not changed this AD based on this comment. Conclusion We reviewed the relevant data, considered the comment received, and E:\FR\FM\03MRR1.SGM 03MRR1

Agencies

[Federal Register Volume 82, Number 41 (Friday, March 3, 2017)]
[Rules and Regulations]
[Pages 12401-12405]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-03951]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9298; Directorate Identifier 2015-NM-161-AD; 
Amendment 39-18811; AD 2017-05-01]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Airbus Model A300 series airplanes. This AD was prompted by an 
evaluation by the design approval holder (DAH) that indicates that a 
section of the wing and aft fuselage is subject to widespread fatigue 
damage (WFD). This AD requires an inspection to determine if certain 
modifications have been done. We are issuing this AD to address the 
unsafe condition on these products.

DATES: This AD is effective April 7, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of April 7, 
2017.

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: continued.airworthiness-wb.external@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-2016-9298.

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-2016-
9298; 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 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 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 by adding an AD that would apply to all Airbus Model A300 
series airplanes. The NPRM published in the Federal Register on October 
26, 2016 (81 FR 74354) (``the NPRM''). The NPRM was prompted by an 
evaluation by the DAH that indicates that a section of the wing and aft 
fuselage is subject to WFD. The NPRM proposed to require an inspection 
to determine if certain modifications have been done. For airplanes on 
which the specified modifications have not been done, this AD requires 
accomplishing those modifications, including doing related 
investigative and corrective actions if necessary. We are issuing this 
AD to prevent reduced structural integrity of these airplanes due to 
the failure of certain structural components.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2015-0173R1, dated August 31, 2016, (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for all Airbus Model A300 series airplanes. 
The MCAI states:

    A widespread fatigue damage (WFD) analysis conducted on A300 
aeroplanes identified areas which are susceptible to crack 
development.
    This condition, if not corrected, could affect the structural 
integrity of the aeroplane.
    To address this issue, Airbus developed a modification (mod) to 
reinforce the structure of the aeroplane. Airbus issued Service 
Bulletin (SB) A300-53-0271 to provide instructions for a cold 
expansion of the foot attachment holes of certain fuselage frames, 
and DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] 
France issued AD F-2004-001 to require this mod [which corresponds 
with certain requirements in FAA AD 2004-23-20, Amendment 39-13875 
(69 FR 68779, November 26, 2004)].
    Since that [DGAC] AD was issued, Airbus released twelve other 
mods with corresponding SBs, to complete the set of inspections and 
repairs in the frame of the A300 WFD campaign. EASA issued AD 2015-
0115 to require ten of these mods through section 3 of ALS 
[Airworthiness Limitations Section] Part 2, and decision is made to 
delete section 3 from ALS Part 2.
    For the reasons described above, EASA issued AD 2015-0173, 
retaining the requirements of DGAC France AD F-2004-001, which was 
superseded, to require implementation of the additional inspection, 
modification and/or repair actions, as applicable to aeroplane 
model.
    This [EASA] AD is revised to give credit for previous use of any 
earlier revision of an affected Airbus SB, based on the fact that no 
additional work is included in the later SB revisions.

    Required actions include an inspection to determine if certain 
modifications have been done. For airplanes on which the specified 
modifications have not been done, this AD requires accomplishing those 
modifications, including doing related investigative and corrective 
actions if necessary. Depending on airplane configuration, the 
compliance times for modifying the airplane structure range between 
13,300 flight cycles and 48,000 flight cycles since first flight of the 
airplane. 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-2016-9298.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM or on the determination of 
the cost to the public.

Conclusion

    We reviewed the relevant 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 for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

[[Page 12402]]

Related Service Information Under 1 CFR Part 51

    Airbus issued the following service information:
     Airbus Service Bulletin A300-53-0239, Revision 02, dated 
March 6, 2000. This service information describes procedures to modify 
the longitudinal junction. The modification includes the addition of 
external doublers and installation of interference fit attachments and 
related investigative and corrective actions. The related investigative 
actions are rotary probe inspections for cracking of the fastener 
holes. The corrective action is repair.
     Airbus Service Bulletin A300-53-247, Revision 2, dated 
July 20, 1990. This service information describes procedures to modify 
the fuselage upper door frame structure, which consists of eddy current 
inspections of certain structure for cracks, and structural 
modification or repair.
     Airbus Service Bulletin A300-53-0271, Revision 05, dated 
June 21, 2013. This service information describes procedures to modify 
the fuselage frame (FR), which includes cold expansion of the fastener 
holes between FR 41 and FR 54, and related investigative and corrective 
actions. The related investigative actions including rotary probe 
inspections for cracking of the fastener holes. The corrective action 
is repair.
     Airbus Service Bulletin A300-53-0366, dated April 7, 2005. 
This service information describes procedures to modify the fuselage 
frame, which includes installing an additional external doubler on the 
fuselage lap joint at fuselage stringers (STGR) 22, left and right, 
between FR 26 and FR 40.
     Airbus Service Bulletin A300-53-0368, dated April 7, 2005. 
This service information describes procedures to modify the rear 
fuselage, which includes installing an additional external doubler on 
the fuselage lap joint at STGR 51, left and right, between FR 72 and FR 
80.
     Airbus Service Bulletin A300-53-0369, Revision 03, dated 
September 1, 2010. This service information describes procedures to 
modify the rear fuselage, which includes reinforcing the butt joint at 
FR 72 by installation of an additional external doubler at the butt 
joint of FR 72 at STGR 14, left and right.
     Airbus Service Bulletin A300-53-0373, Revision 03, dated 
September 1, 2010. This service information describes procedures to 
modify the rear fuselage, which includes reinforcing the butt joint at 
FR65 by installation of an additional external doubler at the butt 
joint of FR65 between STGR 13 left and right.
     Airbus Service Bulletin A300-53-0374, Revision 04, dated 
July 5, 2013. This service information describes procedures to modify 
the rear fuselage, which includes reinforcing the butt joints at FR55 
and FR58 by installation of additional external doublers without cutout 
at certain butt joints.
     Airbus Service Bulletin A300-53-0375, Revision 01, dated 
June 24, 2013. This service information describes procedures to modify 
the forward fuselage, which includes reinforcing the fuselage 
circumferential butt joint at FR 26 by installation of an additional 
external doubler at the butt joint of FR 26 between STGR 13 left and 
STGR 13 right.
     Airbus Service Bulletin A300-53-0393, dated September 27, 
2013. This service information describes procedures to modify the 
fuselage frame which includes reinforcing the longitudinal butt joints 
with additional butt straps at certain fuselage frames and stringers.
     Airbus Service Bulletin A300-57-0203, Revision 04, dated 
February 18, 2015. This service information describes procedures to 
modify the outer wing, which includes removal of the wing stringer and 
run-out plate at STGR 19 on the bottom wing skin; replacement of the 
taper-lok bolts with interference fit parallel bolts; and related 
investigative and corrective actions. Related investigative actions 
include detailed visual and high frequency eddy current (HFEC) 
inspections of the stringer runouts for cracks; eddy current 
inspections for cracks of the fastener holes; and detailed visual and 
HFEC inspections of the stringer run-outs for cracks and damage. 
Corrective actions include repair.
     Airbus Service Bulletin A300-57-0258, dated September 30, 
2014 (for Model A300 B4-103 and A300 B4-2C airplanes). This service 
information describes procedures to modify the wing structure, which 
includes a first oversize of the critical holes on certain wing 
stringers, and related investigative and corrective actions. Related 
investigated actions include detailed visual inspections for damage of 
the top wing skin external surface and the stringer joint; and roto-
probe inspections for damage of the fastener holes. Corrective actions 
include repair.
     Airbus Service Bulletin A300-57-0259, dated September 30, 
2014 (for Model A300 B2-1C, A300 B2-203, and A300 B2K-3C airplanes). 
This service information describes procedures to modify the wing 
structure, which includes a first oversize of the critical holes on 
certain wing stringers, and related investigative and corrective 
actions. Related investigated actions include detailed visual 
inspections for damage of the top wing skin external surface and the 
stringer joint; and roto-probe inspections for damage of the fastener 
holes. Corrective actions include repair.
    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 8 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
               Action                         Labor cost            Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Modification.......................  3,291 work-hours x $85 per         $142,845        $422,580      $3,380,640
                                      hour = $279,735.
----------------------------------------------------------------------------------------------------------------

    In addition, we estimate that any necessary follow-on actions will 
take about 15 work-hours and require parts costing $10,000, for a cost 
of $11,275 per product. We have no way of determining the number of 
aircraft that might need this action.

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

[[Page 12403]]

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 adding the following new airworthiness 
directive (AD):

2017-05-01 Airbus: Amendment 39-18811; Docket No. FAA-2016-9298; 
Directorate Identifier 2015-NM-161-AD.

(a) Effective Date

    This AD is effective April 7, 2017.

(b) Affected ADs

    This AD affects AD 2004-23-20, Amendment 39-13875 (69 FR 68779, 
November 26, 2004) (``AD 2004-23-20'').

(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, certificated in any 
category, all manufacturer serial numbers.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Reason

    This AD was prompted by an evaluation by the design approval 
holder that indicates that a section of the wing and aft fuselage is 
subject to widespread fatigue damage. We are issuing this AD to 
prevent reduced structural integrity of these airplanes due to the 
failure of certain structural components.

(f) Compliance

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

(g) Verification of Embodied Modifications

    Within 4 months after the effective date of this AD, verify 
whether the Airbus modifications specified in table 1 to paragraphs 
(g), (h), and (i) of this AD, as applicable to airplane model, have 
been embodied on the airplane, in accordance with the Accomplishment 
Instructions of the applicable Airbus service bulletin specified in 
table 1 to paragraphs (g), (h), and (i) of this AD. A review of the 
airplane maintenance records is acceptable to accomplish the 
verification required by this paragraph, provided those records can 
be used to conclusively determine whether the modifications have 
been embodied.

 Table 1 to Paragraphs (g), (h), and (i) of This AD--Airbus Modification
                     and Applicable Service Bulletin
------------------------------------------------------------------------
                                      Airbus         Applicable Airbus
              Set                  modification       service bulletin
------------------------------------------------------------------------
Set 1A........................  751..............  A300-53-247, Revision
                                                    2, dated July 20,
                                                    1990.
                                7301.............  A300-53-0239,
                                                    Revision 02, dated
                                                    March 6, 2000.
                                10326............  A300-57-0203,
                                                    Revision 04, dated
                                                    February 18, 2015.
                                12735............  A300-53-0366, dated
                                                    April 7, 2005.
                                12736............  A300-53-0368, dated
                                                    April 7, 2005.
                                12737............  A300-53-0369,
                                                    Revision 03, dated
                                                    September 1, 2010.
                                12798............  A300-53-0375,
                                                    Revision 01, dated
                                                    June 24, 2013.
                                07757 and 12977..  A300-53-0271,
                                                    Revision 05, dated
                                                    June 21, 2013.
                                13611............  A300-57-0258, dated
                                                    September 30, 2014.
                                13692............  A300-53-0393, dated
                                                    September 27, 2013.
                                13716............  A300-57-0259, dated
                                                    September 30, 2014.
Set 1B........................  12794............  A300-53-0374,
                                                    Revision 04, dated
                                                    July 5, 2013.
                                12796............  A300-53-0373,
                                                    Revision 03, dated
                                                    September 1, 2010.
------------------------------------------------------------------------

(h) Corrective Actions for Modifications Which Have Not Been Embodied

    If, during the verification required by paragraph (g) of this 
AD, it is determined that any modification has not been embodied, do 
the applicable actions specified in paragraphs (h)(1), (h)(2), and 
(h)(3) of this AD.
    (1) If it is determined that any Airbus modification, specified 
in the applicable Airbus Service Bulletin, identified in ``Set 1A'' 
of table 1 to paragraphs (g), (h), and (i) of this AD is not 
embodied: Within the applicable compliance time specified in the 
applicable Airbus Service Bulletin identified in ``Set 1A'' of table 
1 to paragraphs (g), (h), and (i) of this AD, or within 4 months 
after the effective date of this AD, whichever occurs later, do the 
applicable actions specified in paragraphs (h)(1)(i) through 
(h)(1)(xi) of this AD, except as required by paragraph (i) of this 
AD. Do all applicable related investigative and corrective actions 
before further flight.
    (i) For airplanes on which Airbus Service Bulletin A300-53-0239, 
Revision 02, dated March 6, 2000, has not been embodied: Modify the 
longitudinal junction and do all applicable related investigative 
and corrective actions, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-53-0239, Revision 02, 
dated March 6, 2000.
    (ii) For airplanes on which Airbus Service Bulletin A300-53-247, 
Revision 2, dated July 20, 1990, has not been embodied: Modify the 
fuselage upper door frame structure by doing eddy current 
inspections for cracks of the structure specified in Airbus Service 
Bulletin A300-53-247, Revision 2, dated July 20, 1990, and a 
structural modification or repair, as applicable, in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A300-53-
247, Revision 2, dated July 20, 1990.
    (iii) For airplanes on which Airbus Service Bulletin A300-53-
0271, Revision 05, dated

[[Page 12404]]

June 21, 2013, has not been embodied: Modify the fuselage frame, and 
do all applicable related investigative and corrective actions, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-53-0271, Revision 05, dated June 21, 2013.
    (iv) For airplanes on which Airbus Service Bulletin A300-53-
0366, dated April 7, 2005, has not been embodied: Modify the 
fuselage frame, in accordance with the Accomplishment Instructions 
of Airbus Service Bulletin A300-53-0366, dated April 7, 2005.
    (v) For airplanes on which Airbus Service Bulletin A300-53-0368, 
dated April 7, 2005, has not been embodied: Modify the rear 
fuselage, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A300-53-0366, dated April 7, 2005.
    (vi) For airplanes on which Airbus Service Bulletin A300-53-
0369, Revision 03, dated September 1, 2010, has not been embodied: 
Modify the rear fuselage, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-53-0369, Revision 03, 
dated September 1, 2010.
    (vii) For airplanes on which Airbus Service Bulletin A300-53-
0375, Revision 01, dated June 24, 2013, has not been embodied: 
Modify the forward fuselage, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-53-0375, Revision 01, 
dated June 24, 2013.
    (viii) For airplanes on which Airbus Service Bulletin A300-53-
0393, dated September 27, 2013, has not been embodied: Modify the 
fuselage frame, in accordance with the Accomplishment Instructions 
of Airbus Service Bulletin A300-53-0393, dated September 27, 2013.
    (ix) For airplanes on which Airbus Service Bulletin A300-57-
0203, Revision 04, dated February 18, 2015, has not been embodied: 
Modify the outer wing, and do all applicable related investigative 
and corrective actions, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-57-0203, Revision 04, 
dated February 18, 2015.
    (x) For airplanes on which Airbus Service Bulletin A300-57-0258, 
dated September 30, 2014, has not been embodied: Modify the wing 
structure and do all applicable related investigative and corrective 
actions, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A300-57-0258, dated September 30, 2014.
    (xi) For airplanes on which Airbus Service Bulletin A300-57-
0259, dated September 30, 2014, has not been embodied: Modify the 
wing structure, and do all applicable related investigative and 
corrective actions, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-57-0259, dated 
September 30, 2014.
    (2) If it is determined that Airbus Service Bulletin A300-53-
0374, Revision 04 dated July 5, 2013 (mod 12794) has not been 
embodied: Within the compliance time specified in paragraphs 
(h)(2)(i), (h)(2)(ii), (h)(2)(iii), and (h)(2)(iv) of this AD, as 
applicable, modify the rear fuselage, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-53-0374, 
Revision 04, dated July 5, 2013, except as required by paragraph (i) 
of this AD.
    (i) For Model A300 B2 and A300 B4-100 airplanes, fuselage frame 
(FR) 55: Within 31,300 flight cycles since first flight of the 
airplane, or within 4 months after the effective date of this AD, 
whichever occurs later.
    (ii) For Model A300 B2 and A300 B4-100 airplanes, FR 58: Within 
49,700 flight cycles since first flight of the airplane, or within 4 
months after the effective date of this AD, whichever occurs later.
    (iii) For Model A300 B4-200 airplanes, FR 55: Within 33,600 
flight cycles since first flight of the airplane, or within 4 months 
after the effective date of this AD, whichever occurs later.
    (iv) For Model A300 B4-200 airplanes, FR 58: Within 55,800 
flight cycles since first flight of the airplane, or within 4 months 
after the effective date of this AD, whichever occurs later.
    (3) If it is determined that Airbus Service Bulletin A300-53-
0373, Revision 03, dated September 1, 2010 (mod 12796) has not been 
embodied: Within the compliance time specified in paragraphs 
(h)(3)(i), (h)(3)(ii), and (h)(3)(iii) of this AD, as applicable, 
modify the rear fuselage, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-53-0373, Revision 03, 
dated September 1, 2010, except as required by paragraph (i) of this 
AD.
    (i) For Model A300 B2 airplanes: Within 42,700 flight cycles 
since first flight of the airplane, or within 4 months after the 
effective date of this AD, whichever occurs later.
    (ii) For Model A300 B4-100 airplanes: Within 41,700 flight 
cycles since first flight of the airplane, or within 4 months after 
the effective date of this AD, whichever occurs later.
    (iii) For Model A300 B4-200 airplanes: Within 47,900 flight 
cycles since first flight of the airplane, or within 4 months after 
the effective date of this AD, whichever occurs later.

(i) Exception to the Service Information

    Where any service information identified in table 1 to 
paragraphs (g), (h), and (i) of this AD specifies to contact the 
manufacturer for instructions or solutions, 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).

(j) Terminating Action for Certain Requirements in AD 2004-23-20

    Accomplishing the modification required by paragraph (h)(1)(iii) 
of this AD terminates the modification required by paragraph (i) of 
AD 2004-23-20 for that airplane only.

(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: Dan Rodina, 
Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-1405; fax 425-227-2125. 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: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or 
Airbus's EASA DOA. If approved by the DOA, the approval must include 
the DOA-authorized signature.
    (3) Required for Compliance (RC): If any service information 
contains procedures or tests that are identified as RC, those 
procedures and tests must be done to comply with this AD; any 
procedures or tests that are not identified as RC are recommended. 
Those procedures and tests that are not identified as RC may be 
deviated from using accepted methods in accordance with the 
operator's maintenance or inspection program without obtaining 
approval of an AMOC, provided the procedures and tests identified as 
RC can be done and the airplane can be put back in an airworthy 
condition. Any substitutions or changes to procedures or tests 
identified as RC require approval of an AMOC.

(l) Related Information

    Refer to Mandatory Continuing Airworthiness Information (MCAI) 
EASA AD 2015-0173R1, dated August 31, 2016, 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-
2016-9298.

(m) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) Airbus Service Bulletin A300-53-0239, Revision 02, dated 
March 6, 2000.
    (ii) Airbus Service Bulletin A300-53-247, Revision 2, dated July 
20, 1990.
    (iii) Airbus Service Bulletin A300-53-0271, Revision 05, dated 
June 21, 2013.
    (iv) Airbus Service Bulletin A300-53-0366, dated April 7, 2005.
    (v) Airbus Service Bulletin A300-53-0368, dated April 7, 2005.
    (vi) Airbus Service Bulletin A300-53-0369, Revision 03, dated 
September 1, 2010.
    (vii) Airbus Service Bulletin A300-53-0373, Revision 03, dated 
September 1, 2010.

[[Page 12405]]

    (viii) Airbus Service Bulletin A300-53-0374, Revision 04, dated 
July 5, 2013.
    (ix) Airbus Service Bulletin A300-53-0375, Revision 01, dated 
June 24, 2013.
    (x) Airbus Service Bulletin A300-53-0393, dated September 27, 
2013.
    (xi) Airbus Service Bulletin A300-57-0203, Revision 04, dated 
February 18, 2015.
    (xii) Airbus Service Bulletin A300-57-0258, dated September 30, 
2014.
    (xiii) Airbus Service Bulletin A300-57-0259, dated September 30, 
2014.
    (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: continued.airworthiness-wb.external@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 February 16, 2017.
Thomas Groves,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-03951 Filed 3-2-17; 8:45 am]
 BILLING CODE 4910-13-P