82 FR 12401 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 41 (March 3, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 41 (March 3, 2017)
| Page Range | 12401-12405 | |
| FR Document | 2017-03951 |
[Federal Register Volume 82, Number 41 (Friday, March 3, 2017)] [Rules and Regulations] [Pages 12401-12405] From the Federal Register Online [www.thefederalregister.org] [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: [email protected]; 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: [email protected]. 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: [email protected]; 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
![Federal Register / Vol. 82, No. 41 / Friday, March 3, 2017 / Rules and Regulations 12401
Issued in Renton, Washington, on February www.regulations.gov by searching for instructions for a cold expansion of the foot
17, 2017. and locating Docket No. FAA–2016– attachment holes of certain fuselage frames,
Michael Kaszycki, 9298; or in person at the Docket and DGAC [Direction Générale de l’Aviation
Acting Manager, Transport Airplane Management Facility between 9 a.m. Civile] France issued AD F–2004–001 to
Directorate, Aircraft Certification Service. and 5 p.m., Monday through Friday, require this mod [which corresponds with
[FR Doc. 2017–03968 Filed 3–2–17; 8:45 am] except Federal holidays. The AD docket certain requirements in FAA AD 2004–23–
20, Amendment 39–13875 (69 FR 68779,
BILLING CODE 4910–13–P contains this AD, the regulatory
November 26, 2004)].
evaluation, any comments received, and
Since that [DGAC] AD was issued, Airbus
other information. The street address for released twelve other mods with
DEPARTMENT OF TRANSPORTATION the Docket Office (telephone 800–647– corresponding SBs, to complete the set of
5527) is Docket Management Facility, inspections and repairs in the frame of the
Federal Aviation Administration U.S. Department of Transportation, A300 WFD campaign. EASA issued AD
Docket Operations, M–30, West 2015–0115 to require ten of these mods
14 CFR Part 39 Building Ground Floor, Room W12–140, through section 3 of ALS [Airworthiness
[Docket No. FAA–2016–9298; Directorate 1200 New Jersey Avenue SE., Limitations Section] Part 2, and decision is
Identifier 2015–NM–161–AD; Amendment Washington, DC 20590. made to delete section 3 from ALS Part 2.
39–18811; AD 2017–05–01] FOR FURTHER INFORMATION CONTACT: Dan For the reasons described above, EASA
Rodina, Aerospace Engineer, issued AD 2015–0173, retaining the
RIN 2120–AA64 requirements of DGAC France AD F–2004–
International Branch, ANM–116,
Transport Airplane Directorate, FAA, 001, which was superseded, to require
Airworthiness Directives; Airbus implementation of the additional inspection,
Airplanes 1601 Lind Avenue SW., Renton, WA
modification and/or repair actions, as
98057–3356; telephone 425–227–2125;
AGENCY: Federal Aviation applicable to aeroplane model.
fax 425–227–1149. This [EASA] AD is revised to give credit
Administration (FAA), Department of SUPPLEMENTARY INFORMATION: for previous use of any earlier revision of an
Transportation (DOT).
Discussion affected Airbus SB, based on the fact that no
ACTION: Final rule. additional work is included in the later SB
We issued a notice of proposed revisions.
SUMMARY: We are adopting a new rulemaking (NPRM) to amend 14 CFR
airworthiness directive (AD) for all part 39 by adding an AD that would Required actions include an
Airbus Model A300 series airplanes. apply to all Airbus Model A300 series inspection to determine if certain
This AD was prompted by an evaluation airplanes. The NPRM published in the modifications have been done. For
by the design approval holder (DAH) Federal Register on October 26, 2016 airplanes on which the specified
that indicates that a section of the wing (81 FR 74354) (‘‘the NPRM’’). The modifications have not been done, this
and aft fuselage is subject to widespread NPRM was prompted by an evaluation AD requires accomplishing those
fatigue damage (WFD). This AD requires by the DAH that indicates that a section modifications, including doing related
an inspection to determine if certain of the wing and aft fuselage is subject to investigative and corrective actions if
modifications have been done. We are WFD. The NPRM proposed to require an necessary. Depending on airplane
issuing this AD to address the unsafe inspection to determine if certain configuration, the compliance times for
condition on these products. modifications have been done. For modifying the airplane structure range
DATES: This AD is effective April 7, airplanes on which the specified between 13,300 flight cycles and 48,000
2017. modifications have not been done, this flight cycles since first flight of the
The Director of the Federal Register AD requires accomplishing those airplane. You may examine the MCAI in
approved the incorporation by reference modifications, including doing related the AD docket on the Internet at http://
of certain publications listed in this AD investigative and corrective actions if www.regulations.gov by searching for
as of April 7, 2017. necessary. We are issuing this AD to and locating Docket No. FAA–2016–
ADDRESSES: For service information prevent reduced structural integrity of 9298.
identified in this final rule, contact these airplanes due to the failure of
Comments
Airbus SAS, Airworthiness Office– certain structural components.
EAW, 1 Rond Point Maurice Bellonte, The European Aviation Safety Agency We gave the public the opportunity to
31707 Blagnac Cedex, France; (EASA), which is the Technical Agent participate in developing this AD. We
telephone: +33 5 61 93 36 96; fax: +33 for the Member States of the European received no comments on the NPRM or
5 61 93 44 51; email: Union, has issued EASA AD 2015– on the determination of the cost to the
continued.airworthiness-wb.external@ 0173R1, dated August 31, 2016, public.
airbus.com; Internet http:// (referred to after this as the Mandatory
Continuing Airworthiness Information, Conclusion
www.airbus.com. You may view this
referenced service information at the or ‘‘the MCAI’’), to correct an unsafe
condition for all Airbus Model A300 We reviewed the relevant data and
FAA, Transport Airplane Directorate, determined that air safety and the
1601 Lind Avenue SW., Renton, WA. series airplanes. The MCAI states:
public interest require adopting this AD
For information on the availability of A widespread fatigue damage (WFD) as proposed except for minor editorial
this material at the FAA, call 425–227– analysis conducted on A300 aeroplanes
changes. We have determined that these
1221. It is also available on the Internet identified areas which are susceptible to
minor changes:
mstockstill on DSK3G9T082PROD with RULES
at http://www.regulations.gov by crack development.
searching for and locating Docket No.
This condition, if not corrected, could • Are consistent with the intent that
affect the structural integrity of the was proposed in the NPRM for
FAA–2016–9298. aeroplane. correcting the unsafe condition; and
Examining the AD Docket To address this issue, Airbus developed a
modification (mod) to reinforce the structure • Do not add any additional burden
You may examine the AD docket on of the aeroplane. Airbus issued Service upon the public than was already
the Internet at http:// Bulletin (SB) A300–53–0271 to provide proposed in the NPRM.
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![Federal Register / Vol. 82, No. 41 / Friday, March 3, 2017 / Rules and Regulations 12403
air commerce by prescribing regulations List of Subjects in 14 CFR Part 39 and B4–203 airplanes, certificated in any
for practices, methods, and procedures category, all manufacturer serial numbers.
Air transportation, Aircraft, Aviation
the Administrator finds necessary for safety, Incorporation by reference, (d) Subject
safety in air commerce. This regulation Safety.
is within the scope of that authority Air Transport Association (ATA) of
Adoption of the Amendment America Code 53, Fuselage.
because it addresses an unsafe condition
that is likely to exist or develop on Accordingly, under the authority (e) Reason
products identified in this rulemaking delegated to me by the Administrator, This AD was prompted by an evaluation by
action. the FAA amends 14 CFR part 39 as the design approval holder that indicates that
Regulatory Findings follows: a section of the wing and aft fuselage is
subject to widespread fatigue damage. We are
We determined that this AD will not PART 39—AIRWORTHINESS issuing this AD to prevent reduced structural
have federalism implications under DIRECTIVES integrity of these airplanes due to the failure
Executive Order 13132. This AD will of certain structural components.
■ 1. The authority citation for part 39
not have a substantial direct effect on
continues to read as follows: (f) Compliance
the States, on the relationship between
the national government and the States, Authority: 49 U.S.C. 106(g), 40113, 44701. Comply with this AD within the
or on the distribution of power and compliance times specified, unless already
§ 39.13 [Amended] done.
responsibilities among the various
levels of government. ■ 2. The FAA amends § 39.13 by adding
(g) Verification of Embodied Modifications
the following new airworthiness
For the reasons discussed above, I Within 4 months after the effective date of
directive (AD):
certify that this AD: this AD, verify whether the Airbus
2017–05–01 Airbus: Amendment 39–18811;
1. Is not a ‘‘significant regulatory Docket No. FAA–2016–9298; Directorate
modifications specified in table 1 to
action’’ under Executive Order 12866; Identifier 2015–NM–161–AD. paragraphs (g), (h), and (i) of this AD, as
2. Is not a ‘‘significant rule’’ under the applicable to airplane model, have been
(a) Effective Date embodied on the airplane, in accordance
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); This AD is effective April 7, 2017. with the Accomplishment Instructions of the
applicable Airbus service bulletin specified
3. Will not affect intrastate aviation in (b) Affected ADs
in table 1 to paragraphs (g), (h), and (i) of this
Alaska; and This AD affects AD 2004–23–20, AD. A review of the airplane maintenance
4. Will not have a significant Amendment 39–13875 (69 FR 68779,
records is acceptable to accomplish the
November 26, 2004) (‘‘AD 2004–23–20’’).
economic impact, positive or negative, verification required by this paragraph,
on a substantial number of small entities (c) Applicability provided those records can be used to
under the criteria of the Regulatory This AD applies to Airbus Model A300 B2– conclusively determine whether the
Flexibility Act. 1A, B2–1C, B2K–3C, B2–203, B4–2C, B4–103, modifications have been embodied.
TABLE 1 TO PARAGRAPHS (g), (h), AND (i) OF THIS AD—AIRBUS MODIFICATION AND APPLICABLE SERVICE BULLETIN
Set Airbus modification Applicable Airbus 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 and (i) of this AD, or within 4 months after Service Bulletin A300–53–0239, Revision 02,
Which Have Not Been Embodied the effective date of this AD, whichever dated March 6, 2000.
If, during the verification required by occurs later, do the applicable actions (ii) For airplanes on which Airbus Service
paragraph (g) of this AD, it is determined that specified in paragraphs (h)(1)(i) through Bulletin A300–53–247, Revision 2, dated July
any modification has not been embodied, do (h)(1)(xi) of this AD, except as required by 20, 1990, has not been embodied: Modify the
the applicable actions specified in paragraph (i) of this AD. Do all applicable fuselage upper door frame structure by doing
paragraphs (h)(1), (h)(2), and (h)(3) of this eddy current inspections for cracks of the
related investigative and corrective actions
AD. structure specified in Airbus Service Bulletin
before further flight.
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(1) If it is determined that any Airbus A300–53–247, Revision 2, dated July 20,
(i) For airplanes on which Airbus Service 1990, and a structural modification or repair,
modification, specified in the applicable
Bulletin A300–53–0239, Revision 02, dated as applicable, in accordance with the
Airbus Service Bulletin, identified in ‘‘Set
1A’’ of table 1 to paragraphs (g), (h), and (i) March 6, 2000, has not been embodied: Accomplishment Instructions of Airbus
of this AD is not embodied: Within the Modify the longitudinal junction and do all Service Bulletin A300–53–247, Revision 2,
applicable compliance time specified in the applicable related investigative and dated July 20, 1990.
applicable Airbus Service Bulletin identified corrective actions, in accordance with the (iii) For airplanes on which Airbus Service
in ‘‘Set 1A’’ of table 1 to paragraphs (g), (h), Accomplishment Instructions of Airbus Bulletin A300–53–0271, Revision 05, dated
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![Federal Register / Vol. 82, No. 41 / Friday, March 3, 2017 / Rules and Regulations 12405
(viii) Airbus Service Bulletin A300–53– an unsafe condition on an aviation for the specified products and was
0374, Revision 04, dated July 5, 2013. product. The MCAI describes the unsafe based on mandatory continuing
(ix) Airbus Service Bulletin A300–53– condition as certain combinations of the airworthiness information (MCAI)
0375, Revision 01, dated June 24, 2013. aileron counterweight and the attaching originated by an aviation authority of
(x) Airbus Service Bulletin A300–53–0393,
dated September 27, 2013.
parts possibly resulting in reduced another country. The MCAI states:
(xi) Airbus Service Bulletin A300–57– thread engagement and leading to The proper installation of the aileron
0203, Revision 04, dated February 18, 2015. disconnection of the aileron counterweight requires a combination,
(xii) Airbus Service Bulletin A300–57– counterweight from the aileron. We are peculiar to each aileron, of anchor nut types,
0258, dated September 30, 2014. issuing this AD to require actions to bolt types, number of washers, and the
(xiii) Airbus Service Bulletin A300–57– address the unsafe condition on these definition of the bolt torque. Some
0259, dated September 30, 2014. products. combinations of counterweight and attaching
(3) For service information identified in parts, which could result in reduced thread
DATES: This AD is effective April 7, engagement, have been reported on a PC–6
this AD, contact Airbus SAS, Airworthiness
Office–EAW, 1 Rond Point Maurice Bellonte, 2017. aeroplane.
31707 Blagnac Cedex, France; telephone: +33 The Director of the Federal Register This condition, if not detected and
5 61 93 36 96; fax: +33 5 61 93 44 51; email: approved the incorporation by reference corrected, may lead to a disconnection of the
continued.airworthiness-wb.external@ of a certain publication listed in the AD aileron counterweight from the aileron,
airbus.com; Internet http://www.airbus.com. as of April 7, 2017. possibly resulting in reduced control of the
(4) You may view this service information aeroplane.
ADDRESSES: You may examine the AD
at the FAA, Transport Airplane Directorate, To address this potential unsafe condition,
docket on the Internet at http:// Pilatus issued Service Bulletin (SB) No. 57–
1601 Lind Avenue SW., Renton, WA. For www.regulations.gov by searching for 006 (hereafter referred to as ‘the SB’ in this
information on the availability of this
material at the FAA, call 425–227–1221.
and locating Docket No. FAA–2016– AD) to provide inspection instructions.
(5) You may view this service information 9357; or in person at Document For the reason described above, this AD
Management Facility, U.S. Department requires identification and inspection of the
that is incorporated by reference at the
of Transportation, Docket Operations, affected aileron mass-balance counterweight
National Archives and Records
M–30, West Building Ground Floor, attachment parts and, depending on findings,
Administration (NARA). For information on
accomplishment of applicable corrective
the availability of this material at NARA, call Room W12–140, 1200 New Jersey action(s).
202–741–6030, or go to: http:// Avenue SE., Washington, DC 20590.
www.archives.gov/federal-register/cfr/ibr- For service information identified in The MCAI can be found in the AD
locations.html. this AD, contact Pilatus Aircraft Ltd., docket on the Internet at: https://www.
Customer Technical Support (MCC), regulations.gov/document?D=FAA-
Issued in Renton, Washington, on February 2016-9357-0002.
16, 2017. P.O. Box 992, CH–6371 Stans,
Switzerland; phone: +41 (0)41 619 3333; Comments
Thomas Groves,
fax: +41 (0)41 619 7311; email:
Acting Manager, Transport Airplane supportPC12@pilatus-aircraft.com; We gave the public the opportunity to
Directorate, Aircraft Certification Service. participate in developing this AD. The
Internet: http://www.pilatus-
[FR Doc. 2017–03951 Filed 3–2–17; 8:45 am]
aircraft.com. You may view this following presents the comment
BILLING CODE 4910–13–P referenced service information at the received on the proposal and the FAA’s
FAA, Small Airplane Directorate, 901 response to the comment.
Locust, Kansas City, Missouri 64106. Request for Clarification on the Unsafe
DEPARTMENT OF TRANSPORTATION For information on the availability of Condition
Federal Aviation Administration this material at the FAA, call (816) 329–
Lukas Owens stated that in the event
4148. It is also available on the Internet
of loss of the ailerons, some degree of
14 CFR Part 39 at http://www.regulations.gov by
roll control is available by using the
searching for Docket No. FAA–2016–
[Docket No. FAA–2016–9357; Directorate secondary effect of rudder. The
9357.
Identifier 2016–CE–030–AD; Amendment requester stated that while not an
39–18798; AD 2017–04–03] FOR FURTHER INFORMATION CONTACT: efficient way to turn the aircraft, a pilot
Doug Rudolph, Aerospace Engineer, has at least some directional control and
RIN 2120–AA64 FAA, Small Airplane Directorate, 901 that short or rapid bursts of power may
Locust, Room 301, Kansas City, increase the effectiveness of the rudder
Airworthiness Directives; Pilatus
Missouri 64106; telephone: (816) 329– to some degree, acting as a form of
Aircraft Ltd. Airplanes
4059; fax: (816) 329–4090; email: torque and slipstream effect. The
AGENCY: Federal Aviation doug.rudolph@faa.gov. requester asked why the AD change is
Administration (FAA), Department of SUPPLEMENTARY INFORMATION: needed or how it is justified.
Transportation (DOT). We infer that the commenter, in
Discussion
ACTION: Final rule. addition to asking why the AD action is
We issued a notice of proposed necessary and how it is justified,
SUMMARY: We are adopting a new rulemaking (NPRM) to amend 14 CFR believes the AD action is not needed
airworthiness directive (AD) for Pilatus part 39 by adding an AD that would and is not justified. However, the
Aircraft Ltd. Models PC–6, PC–6–H1, apply to Pilatus Aircraft Ltd. Models commenter does not present solutions
PC–6–H2, PC–6/350, PC–6/350–H1, PC– PC–6, PC–6–H1, PC–6–H2, PC–6/350, that address the unsafe condition of the
6/350–H2, PC–6/A, PC–6/A–H1, PC–6/ PC–6/350–H1, PC–6/350–H2, PC–6/A, mass balance weight potentially
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A–H2, PC–6/B–H2, PC–6/B1–H2, PC–6/ PC–6/A–H1, PC–6/A–H2, PC–6/B–H2, separating from the airplane. For this
B2–H2, PC–6/B2–H4, PC–6/C–H2, and PC–6/B1–H2, PC–6/B2–H2, PC–6/B2– reason, we have not changed this AD
PC–6/C1–H2 airplanes. This AD results H4, PC–6/C–H2, and PC–6/C1–H2 based on this comment.
from mandatory continuing airplanes. The NPRM was published in
airworthiness information (MCAI) the Federal Register on November 4, Conclusion
issued by an aviation authority of 2016 (81 FR 76883). The NPRM We reviewed the relevant data,
another country to identify and correct proposed to correct an unsafe condition considered the comment received, and
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Document Created: 2018-02-01 14:45:37
Document Modified: 2018-02-01 14:45:37
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective April 7, 2017. | |
| 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. | |
| FR Citation | 82 FR 12401 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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