80 FR 73092 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 226 (November 24, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 226 (November 24, 2015)
| Page Range | 73092-73096 | |
| FR Document | 2015-28886 |
[Federal Register Volume 80, Number 226 (Tuesday, November 24, 2015)] [Rules and Regulations] [Pages 73092-73096] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-28886] ======================================================================= ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-0490; Directorate Identifier 2014-NM-018-AD; Amendment 39-18322; AD 2015-23-06] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are superseding Airworthiness Directive (AD) 2008-22-20 for certain Airbus Model A330-200, A330-300, and A340-300 series airplanes. AD 2008-22-20 required repetitive high frequency eddy current (HFEC) inspections for cracking, repair if necessary, and modification of the upper shell structure of the fuselage. This new AD shortens certain compliance times. This AD was prompted by a determination from a fatigue and damage tolerance evaluation that the compliance times must be reduced. We are issuing this AD to prevent fatigue cracking of the upper shell structure of the fuselage, which could result in reduced structural integrity of the airplane. DATES: This AD becomes effective December 29, 2015. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of December 29, 2015. The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of December 17, 2008 (73 FR 66747, November 12, 2008). ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail; [[Page 73093]] D=FAA-2015-0490; or in person at the Docket Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC. For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email [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-2015- 0490. FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2008-22-20, Amendment 39-15717 (73 FR 66747, November 12, 2008). AD 2008-22-20 applied to certain Airbus Model A330- 200, A330-300, and A340-300 series airplanes. The NPRM published in the Federal Register on March 17, 2015 (80 FR 13799). The NPRM was prompted by a determination from a fatigue and damage tolerance evaluation that the compliance times must be reduced. The NPRM also proposed to shorten certain compliance times. We are issuing this AD to prevent fatigue cracking of the upper shell structure of the fuselage, which could result in reduced structural integrity of the airplane. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014-0012R1, dated January 24, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Airbus Model A330-200, A330-300, and A340-300 series airplanes. The MCAI states: During fatigue tests (EF3) on the A340-600, damage was found in the longitudinal doubler at the Vertical Tail Plane (VTP) attachment cut out between Frame (FR) 80 and FR86. This damage occurred between 58,341 and 72,891 simulated flight cycles (FC). Due to the higher Design Service Goal and different design of the affected structural area (e.g. doubler thickness) for A330-200/- 300 and A340-300 airplane series, the damage assessment concluded that these airplanes may be also potentially affected. This condition, if not detected and corrected, could affect the structural integrity of the upper shell structure between FR80 and FR86. Prompted by these findings, EASA issued AD 2007-0284 [(http://ad.easa.europa.eu/blob/easa_ad_2007_0284_superseded.pdf/AD_2007-0284_1)] to require implementation of an inspection programme of this structural area using a high frequency eddy current (HFEC) method and a modification to improve the upper shell structure. Since that [EASA] AD was issued, in the frame of a new fatigue and damage tolerance evaluation, taking into account the airplane utilisation, the inspection threshold and intervals have been reassessed and the conclusion was that the thresholds and intervals for inspection, as well as the threshold for modifying the airplane, must be reduced. For the reason described above, this [EASA] AD retains the requirements of EASA AD 2007-0284, which is superseded and introduces redefined thresholds and intervals. This [EASA] AD is revised to clarify that, under some conditions, accomplishment of a repair constitutes terminating action for the repetitive inspections. One of the outcome of this clarification is the deletion of paragraph (5) of this [EASA] AD. You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2015-0490-0002. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM (80 FR 13799, March 17, 2015) and the FAA's response to each comment. Support for the NPRM (80 FR 13799, March 17, 2015) An anonymous commenter agreed with the safety benefit provided by the NPRM (80 FR 13799, March 17, 2015). Request for Revise Cost Delta requested that we revise the NPRM (80 FR 13799, March 17, 2015) to relay the heavy impact of accomplishing Airbus Service Bulletin A330-53-3160, Revision 03, dated January 6, 2012. Delta explained that the modification specified in Airbus Service Bulletin A330-53-3160, Revision 03, dated January 6, 2012, requires removal of the vertical stabilizer and the aft galley, which can heavily impact the operation. Delta reasoned that it has consulted with its maintenance organization and it is estimated to take 400 work-hours instead of 208 work-hours. We disagree with the request to revise this AD. We made the cost estimate based on the information provided in Airbus Service Bulletin A330-53-3160, Revision 03, dated January 6, 2012. The required work- hours defined in Airbus Service Bulletin A330-53-3160, Revision 03, dated January 6, 2012, are based on the direct labor cost to do the work. The need to remove and reinstall the aft galley depends on the airplane interior configuration and may differ from operator to operator. We are unable to determine all possible interior configurations and thus determine the maximum work-hours which may be required for any specific configuration. This estimate assumes that the work will be done by experienced personnel, and may need to be revised upwards to suit an operator's circumstances. The estimate does not include the time to prepare, plan, or inspect the work. We have made no changes to this AD in this regard. Conclusion We reviewed the available data and determined that air safety and the public interest require adopting this AD as proposed except for minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the NPRM (80 FR 13799, March 17, 2015) for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM (80 FR 13799, March 17, 2015). Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information. Airbus Service Bulletin A330-53-3159, Revision 02, dated March 29, 2010, describes procedures for a modification of the fuselage, which includes inspections (e.g., eddy current rotating probe test of fastener holes for cracking, high frequency eddy current (HFEC) inspections for cracking of the upper shell structure of the fuselage, and checks of the fastener position for clearance) and applicable corrective actions (e.g., repair and rework). Airbus Service Bulletin A330-53-3160, Revision 03, dated January 6, 2012, describes procedures for applicable actions, including an eddy current rotating probe test for cracking of the fastener holes and an HFEC inspection for cracks in the upper shell [[Page 73094]] of the fuselage (and including checks of the fastener position for clearance and applicable corrective actions (e.g., repair and rework)), and a modification of the airplane upper shell structure of the fuselage between FR80 and FR86. Airbus Service Bulletin A330-53-3168, Revision 02, dated December 21, 2011, describes procedures for a HFEC inspection for cracking of the upper shell structure of the fuselage between FR80 and FR86. Airbus Service Bulletin A340-53-4165, Revision 02, dated March 29, 2010, describes procedures for a modification of the fuselage, which includes inspections (e.g., eddy current rotating probe test of fastener holes for cracking, HFEC inspections for cracking of the upper shell structure of the fuselage, and checks of the fastener position for clearance) and applicable corrective actions (e.g., repair and rework). Airbus Service Bulletin A340-53-4172, Revision 01, dated July 8, 2009, describes procedures for inspections (e.g., rototest inspections of fastener holes for cracking, HFEC inspections for cracking of the upper shell structure of the fuselage, and checks of the fastener position for clearance) and modification of the airplane upper shell structure between FR80 and FR86 (including applicable corrective actions (e.g., repair and rework). Airbus Service Bulletin A340-53-4174, Revision 02, dated December 21, 2011, describes procedures for a HFEC inspection for cracking of the upper shell structure of the fuselage between FR80 and FR86. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section of this AD. Costs of Compliance We estimate that this AD affects 26 airplanes of U.S. registry. We also estimate that it will take about 208 work-hours per product to comply with the basic requirements (inspection and modification) of this AD. The average labor rate is $85 per work-hour. Required parts will cost about $28,360 per product. Based on these figures, we estimate the cost of this AD on U.S. operators to be $1,197,040, or $46,040 per product. We have received no definitive data that will enable us to provide cost estimates for the on-condition actions specified in this AD. According to the manufacturer, some of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ``Subtitle VII: Aviation Programs,'' describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in ``Subtitle VII, Part A, Subpart III, Section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: 1. Is not a ``significant regulatory action'' under Executive Order 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2015-0490; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800-647- 5527) is in the ADDRESSES section. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD) 2008-22-20, Amendment 39-15717 (73 FR 66747, November 12, 2008), and adding the following new AD: 2015-23-06 Airbus: Amendment 39-18322. Docket No. FAA-2015-0490; Directorate Identifier 2014-NM-018-AD. (a) Effective Date This AD becomes effective December 29, 2015. (b) Affected ADs This AD replaces AD 2008-22-20, Amendment 39-15717 (73 FR 66747, November 12, 2008). (c) Applicability This AD applies to Airbus Model A330-201, -202, -203, -223, - 243, -301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes; and Model A340-311, -312, and -313 airplanes; certificated in any category; all manufacturer serial numbers on which Airbus Modification 44205 has been embodied in production, except those on which Airbus Modification 52974 or 53223 has been embodied in production. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by the results of a fatigue and damage tolerance evaluation that concluded existing compliance times must be reduced. We are issuing this AD to prevent fatigue cracking of the upper shell structure of the fuselage, which could result in reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. [[Page 73095]] (g) Inspection for Airbus Model A330-300 and A340-300 Airplanes, Except Model A340-300 Weight Variant (WV) 027 Airplanes For Model A330-300 and A340-300 airplanes, except Model A340-300 WV 027 airplanes: At the applicable time specified in paragraph (g)(1) or (g)(2) of this AD, do a high frequency eddy current (HFEC) inspection for cracking of the upper shell structure between frame (FR) 80 and FR86, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53-3168, Revision 02, dated December 21, 2011; or Airbus Service Bulletin A340-53-4174, Revision 02, dated December 21, 2011; as applicable. Repeat the inspection thereafter at the applicable time specified in paragraph 1.E., ``COMPLIANCE,'' of Airbus Service Bulletin A330-53-3168, Revision 02, dated December 21, 2011; or Airbus Service Bulletin A340-53- 4174, Revision 02, dated December 21, 2011; as applicable. (1) For airplanes that, as of the effective date of this AD, have not been inspected in accordance with Airbus Service Bulletin A330-53-3168; or Airbus Service Bulletin A340-53-4174; as applicable: Inspect at the later of the times specified in paragraphs (g)(1)(i) and (g)(1)(ii) of this AD. (i) Before reaching the applicable threshold specified in paragraph 1.E., ``COMPLIANCE,'' of Airbus Service Bulletin A330-53- 3168, Revision 02, dated December 21, 2011; or Airbus Service Bulletin A340-53-4174, Revision 02, dated December 21, 2011; as applicable for airplane model, configuration, and utilization, since the airplane's first flight. (ii) Within the threshold defined in paragraph 1.E, ``COMPLIANCE,'' of Airbus Service Bulletin A330-53-3168, Revision 01, dated February 15, 2008; or Airbus Service Bulletin A340-53- 4174, Revision 01, dated February 15, 2008; as applicable for airplane model, configuration, and utilization since the airplane's first flight; or within 12 months after the effective date of this AD; whichever occurs first. (2) For airplanes that, as of the effective date of this AD, have been inspected in accordance with Airbus Service Bulletin A330- 53-3168; or Airbus Service Bulletin A340-53-4174; as applicable: Inspect at the later of the times specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD. (i) Within the applicable interval specified in paragraph 1.E., ``COMPLIANCE,'' of Airbus Service Bulletin A330-53-3168, Revision 02, dated December 21, 2011; or Airbus Service Bulletin A340-53- 4174, Revision 02, dated December 21, 2011; as applicable; to be counted from the last inspection. (ii) Within 12 months after the effective date of this AD without exceeding the intervals defined in paragraph 1.E, ``COMPLIANCE,'' of Airbus Service Bulletin A330-53-3168, Revision 01, dated February 15, 2008; or Airbus Service Bulletin A340-53- 4174, Revision 01, dated February 15, 2008; as applicable for airplane model, configuration, and utilization to be counted from the last inspection. (h) Corrective Action for Airbus Model A330-300 and A340-300 Airplanes, Except Model A340-300 WV 027 Airplanes If any crack is detected during any HFEC inspection required by the introductory text to paragraph (g) of this AD: 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). Accomplishment of a repair for a specific area, as required by this paragraph, is terminating action for the repetitive HFEC inspections required by the introductory text to paragraph (g) of this AD, as applicable, for that specific repaired area only. The need and definition of subsequent repetitive inspections (if any) for that specific repaired area will be defined in the applicable repair 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). (i) Optional Terminating Action For Airbus Model A330-300 and A340-300 airplanes, except Model A340-300 WV 027 airplanes: Modification, which includes inspections and applicable corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53-3159, Revision 02, dated March 29, 2010; or Airbus Service Bulletin A340- 53-4165, Revision 02, dated March 29, 2010; as applicable; terminates the repetitive HFEC inspections required by the introductory text to paragraph (g) of this AD, except where Airbus Service Bulletin A330-53-3159, Revision 02, dated March 29, 2010; or Airbus Service Bulletin A340-53-4165, Revision 02, dated March 29, 2010; as applicable; specifies to contact the manufacturer, repair using a method approved by the Manager, International Branch, ANM- 116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. (j) Inspection and Modification for Airbus Model A330-200 Airplanes Within the compliance times specified in paragraph (j)(1) or (j)(2) of this AD, whichever occurs later: Do all applicable actions, including an eddy current rotating probe test and an HFEC inspection for cracks, and modify the airplane upper shell structure between FR80 and FR86; in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53-3160, Revision 03, dated January 6, 2012. (1) Within the compliance times identified in paragraph 1.E., ``COMPLIANCE,'' of Airbus Service Bulletin A330-53-3160, Revision 03, dated January 6, 2012, as applicable for airplane configuration and utilization since the airplane's first flight. (2) Within 12 months after the effective date of this AD without exceeding the threshold defined in paragraph 1.E, ``COMPLIANCE,'' of Airbus Service Bulletin A330-53-3160, Revision 02, dated March 29, 2010, since the airplane's first flight. (k) Inspection and Modification for Airbus Model A340-300 Airplanes, Only WV 027 For Model A340-300 airplanes, WV 027 only: Before the accumulation of 14,200 total flight cycles from the airplane's first flight, do all applicable inspections and modify the airplane upper shell structure between FR80 and FR86; in accordance with the Accomplishment Instructions of Airbus Service Bulletin A340-53-4172, Revision 01, dated July 8, 2009. (l) Corrective Action for Airbus Model A330-200 Airplanes; and Model A340-300 Airplanes, only WV 027 If any crack is detected during the inspection required by the introductory text to paragraph (j) of this AD, or paragraph (k) of this AD, before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA; concurrently with modification required by paragraph the introductory text to paragraph (j) of this AD, or paragraph (k) of this AD. (m) Definition of ``Threshold'' and ``Interval'' (1) For the purposes of this AD, the term ``Threshold,'' as used in paragraph 1.E., ``COMPLIANCE,'' of the service information specified in paragraphs (m)(2)(i) through (m)(2)(vi) of this AD means the total flight cycles or flight hours accumulated since the airplane's first flight. (2) For the purposes of this AD, the term ``Interval'' as used in paragraph 1.E., ``COMPLIANCE,'' of the service information specified in paragraphs (m)(2)(i) through (m)(2)(vi) of this AD means the total flight cycles or flight hours accumulated since the last inspection, as applicable. (i) Airbus Service Bulletin A330-53-3168, dated September 19, 2007. (ii) Airbus Service Bulletin A330-53-3168, Revision 01, dated February 15, 2008. (iii) Airbus Service Bulletin A330-53-3168, Revision 02, dated December 21, 2011. (iv) Airbus Service Bulletin A340-53-4174, dated September 19, 2007. (v) Airbus Service Bulletin A340-53-4174, Revision 01, dated February 15, 2008. (vi) Airbus Service Bulletin A340-53-4174, Revision 02, dated December 21, 2011. (n) Credit for Previous Actions (1) For Model A330-300 and A340-300 airplanes, except Model A340-300 WV 027 airplanes: This paragraph provides credit for the modification specified in paragraph (i) of this AD, if those actions were performed before the effective date of this AD using the service information identified in paragraph (n)(1)(i), (n)(1)(ii), (n)(1)(iii), or (n)(1)(iv) of this AD, as applicable. This service information is not incorporated by reference in this AD. (i) Airbus Service Bulletin A330-53-3159, dated September 19, 2007. (ii) Airbus Service Bulletin A330-53-3159, Revision 01, dated June 15, 2009. (iii) Airbus Service Bulletin A340-53-4165, dated September 19, 2007. (iv) Airbus Service Bulletin A340-53-4165, Revision 01, dated June 17, 2009. (2) For Model A330-200 airplanes: This paragraph provides credit for the inspection [[Page 73096]] and modification required by the introductory text to paragraph (j) of this AD, if those actions were performed before the effective date of this AD using the service information identified in paragraph (n)(2)(i), (n)(2)(ii), or (n)(2)(iii) of this AD, as applicable. (i) Airbus Service Bulletin A330-53-3160, dated July 9, 2007, which was incorporated by reference in AD 2008-22-20, Amendment 39- 15717 (73 FR 66747, November 12, 2008). (ii) Airbus Service Bulletin A330-53-3160, Revision 01, dated April 28, 2009, which is not incorporated by reference in this AD. (iii) Airbus Service Bulletin A330-53-3160, Revision 02, dated March 29, 2010, which is not incorporated by reference in this AD. (3) For Model A340-300 airplanes, WV 027 only: This paragraph provides credit for the inspection and modification required by paragraph (k) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A340-53- 4172, dated July 10, 2007, which is was incorporated by reference in AD 2008-22-20, Amendment 39-15717 (73 FR 66747, November 12, 2008). (o) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. Information may be emailed to: [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. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: As of the effective date of this AD, for any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (p) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014-0012R1, dated January 24, 2014, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-0490. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (q)(3) and (q)(4) of this AD. (q) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (3) The following service information was approved for IBR on December 29, 2015. (i) Airbus Service Bulletin A330-53-3159, Revision 02, dated March 29, 2010. (ii) Airbus Service Bulletin A330-53-3160, Revision 03, dated January 6, 2012. (iii) Airbus Service Bulletin A330-53-3168, Revision 02, dated December 21, 2011. (iv) Airbus Service Bulletin A340-53-4165, Revision 02, dated March 29, 2010. (v) Airbus Service Bulletin A340-53-4172, Revision 01, dated July 8, 2009. (vi) Airbus Service Bulletin A340-53-4174, Revision 02, dated December 21, 2011. (4) The following service information was approved for IBR on December 17, 2008 (73 FR 66747, November 12, 2008). (i) Airbus Service Bulletin A330-53-3168, Revision 01, dated February 15, 2008. (ii) Airbus Service Bulletin A340-53-4174, Revision 01, dated February 15, 2008. (5) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email [email protected]; Internet http://www.airbus.com. (6) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. (7) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on October 30, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-28886 Filed 11-23-15; 8:45 am] BILLING CODE 4910-13-P
![73092 Federal Register / Vol. 80, No. 226 / Tuesday, November 24, 2015 / Rules and Regulations
V. Differences Between the Banks and amends part 1238 of title 12 of the Code stress test results for the severely
the Enterprises of Federal Regulations as follows: adverse scenario not earlier than
Section 1313(f) of the Safety and November 15 and not later than
PART 1238—STRESS TESTING OF November 30 of each year. The
Soundness Act requires the Director to
REGULATED ENTITIES summary may be published on the
consider the differences between the
Banks and the Enterprises whenever regulated entity’s Web site or in any
■ 1. The authority citation for part 1238
promulgating regulations that affect the other form that is reasonably accessible
continues to read as follows:
Banks. In developing the amendments to the public;
Authority: 12 U.S.C. 5365(i); 12 U.S.C.
to this rule, FHFA considered the 4513, 4526, 4612; and 12 U.S.C. 1426.
* * * * *
differences between the Banks and the Dated: November 11, 2015.
Enterprises, but also adhered to the ■ 2. Amend § 1238.3 by revising
paragraphs (a)(1) and (b) to read as Melvin L. Watt,
statutory mandate that the regulation be
follows: Director, Federal Housing Finance Agency.
‘‘consistent and comparable’’ with the
[FR Doc. 2015–29861 Filed 11–23–15; 8:45 am]
regulations of the other agencies. In § 1238.3 Annual stress test.
implementing the regulation, FHFA will BILLING CODE 8070–01–P
(a) * * *
define scenarios for the regulated (1) Shall complete an annual stress
entities, bearing in mind the key risk test of itself based on its data as of
exposures at each regulated entity. DEPARTMENT OF TRANSPORTATION
December 31 of the preceding calendar
In the final rule, FHFA requires
year; Federal Aviation Administration
different timeframes for reporting stress
test results for the Enterprises versus the * * * * *
Banks. For the Enterprises, FHFA sets (b) Scenarios provided by FHFA. In 14 CFR Part 39
the dates for reporting stress test results conducting its annual stress tests under
[Docket No. FAA–2015–0490; Directorate
to the regulator, the FRB, and the public this section, each regulated entity must
Identifier 2014–NM–018–AD; Amendment
in proximity to similar dates in the use scenarios provided by FHFA, which 39–18322; AD 2015–23–06]
other agencies’ rules for institutions shall be generally consistent with and
comparable to those established by the RIN 2120–AA64
with over $50 billion in assets.
Reporting dates for all the Banks, FRB, that reflect a minimum of three
sets of economic and financial Airworthiness Directives; Airbus
regardless of size, are set in proximity Airplanes
to similar dates for institutions with less conditions, including a baseline,
than $50 billion in assets. As a result, adverse, and severely adverse scenario. AGENCY: Federal Aviation
the Banks have over three additional Not later than 30 days after the FRB Administration (FAA), Department of
months to report results to FHFA, the publishes its scenarios, FHFA will issue Transportation (DOT).
FRB, and the public. to all regulated entities a description of ACTION: Final rule.
the baseline, adverse, and severely
VI. Paperwork Reduction Act adverse scenarios that each regulated SUMMARY: We are superseding
The final rule does not contain any entity shall use to conduct its annual Airworthiness Directive (AD) 2008–22–
collections of information pursuant to stress tests under this part. 20 for certain Airbus Model A330–200,
the Paperwork Reduction Act of 1995 ■ 3. Amend § 1238.5 by revising A330–300, and A340–300 series
(44 U.S.C. 3501, et seq.). Therefore, paragraph (a) to read as follows: airplanes. AD 2008–22–20 required
FHFA has not submitted any repetitive high frequency eddy current
§ 1238.5 Required report to FHFA and the
information to the Office of (HFEC) inspections for cracking, repair
FRB of stress test results and related
Management and Budget for review. information. if necessary, and modification of the
upper shell structure of the fuselage.
VII. Regulatory Flexibility Act (a) Report required for stress tests. On
This new AD shortens certain
The final rule applies only to the or before May 20 of each year, the
compliance times. This AD was
regulated entities, which do not come Enterprises must report the results of
prompted by a determination from a
within the meaning of small entities as the stress tests required under § 1238.3
fatigue and damage tolerance evaluation
defined in the Regulatory Flexibility Act to FHFA, and to the FRB, in accordance
that the compliance times must be
(see 5 U.S.C. 601(6)). Therefore, in with paragraph (b) of this section; and
reduced. We are issuing this AD to
accordance with section 605(b) of the on or before August 31 of each year, the
prevent fatigue cracking of the upper
Regulatory Flexibility Act (5 U.S.C. Banks must report the results of the
shell structure of the fuselage, which
605(b)), the General Counsel of FHFA stress tests required under § 1238.3 to
could result in reduced structural
certifies that this final rule will not have FHFA, and to the FRB, in accordance
integrity of the airplane.
a significant economic impact on a with paragraph (b) of this section;
DATES: This AD becomes effective
substantial number of small entities. * * * * *
December 29, 2015.
■ 4. Amend § 1238.7 by revising
List of Subjects in 12 CFR Part 1238 The Director of the Federal Register
paragraph (a) to read as follows: approved the incorporation by reference
Administrative practice and
procedure, Capital, Federal Home Loan § 1238.7 Publication of results by of certain publications listed in this AD
Banks, Government-sponsored regulated entities. as of December 29, 2015.
enterprises, Regulated entities, (a) Public disclosure of results The Director of the Federal Register
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Reporting and recordkeeping required for stress tests of regulated approved the incorporation by reference
requirements, Stress test. entities. The Enterprises must disclose of certain other publications listed in
publicly a summary of the stress test this AD as of December 17, 2008 (73 FR
Authority and Issuance results for the severely adverse scenario 66747, November 12, 2008).
For the reasons stated in the not earlier than August 1 and not later ADDRESSES: You may examine the AD
preamble, and under the authority of 12 than August 15 of each year. Each Bank docket on the Internet at http://
U.S.C. 4513, 4526, and 5365(i), FHFA must disclose publicly a summary of the www.regulations.gov/#!docketDetail;
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![Federal Register / Vol. 80, No. 226 / Tuesday, November 24, 2015 / Rules and Regulations 73093
D=FAA-2015-0490; or in person at the attachment cut out between Frame (FR) 80 Delta reasoned that it has consulted
Docket Management Facility, U.S. and FR86. This damage occurred between with its maintenance organization and it
Department of Transportation, Docket 58,341 and 72,891 simulated flight cycles is estimated to take 400 work-hours
(FC).
Operations, M–30, West Building instead of 208 work-hours.
Due to the higher Design Service Goal and
Ground Floor, Room W12–140, 1200 different design of the affected structural area
We disagree with the request to revise
New Jersey Avenue SE., Washington, (e.g. doubler thickness) for A330–200/–300 this AD. We made the cost estimate
DC. and A340–300 airplane series, the damage based on the information provided in
For service information identified in assessment concluded that these airplanes Airbus Service Bulletin A330–53–3160,
this AD, contact Airbus SAS, may be also potentially affected. Revision 03, dated January 6, 2012. The
Airworthiness Office—EAL, 1 Rond This condition, if not detected and required work-hours defined in Airbus
Point Maurice Bellonte, 31707 Blagnac corrected, could affect the structural integrity Service Bulletin A330–53–3160,
Cedex, France; telephone +33 5 61 93 36 of the upper shell structure between FR80 Revision 03, dated January 6, 2012, are
and FR86.
96; fax +33 5 61 93 45 80; email Prompted by these findings, EASA issued
based on the direct labor cost to do the
airworthiness.A330–A340@airbus.com; AD 2007–0284 [(http://ad.easa.europa.eu/ work. The need to remove and reinstall
Internet http://www.airbus.com. You blob/easa_ad_2007_0284_superseded.pdf/ the aft galley depends on the airplane
may view this referenced service AD_2007-0284_1)] to require implementation interior configuration and may differ
information at the FAA, Transport of an inspection programme of this structural from operator to operator. We are unable
Airplane Directorate, 1601 Lind Avenue area using a high frequency eddy current to determine all possible interior
SW., Renton, WA. For information on (HFEC) method and a modification to configurations and thus determine the
the availability of this material at the improve the upper shell structure. maximum work-hours which may be
Since that [EASA] AD was issued, in the
FAA, call 425–227–1221. It is also frame of a new fatigue and damage tolerance
required for any specific configuration.
available on the Internet at http:// evaluation, taking into account the airplane This estimate assumes that the work
www.regulations.gov by searching for utilisation, the inspection threshold and will be done by experienced personnel,
and locating Docket No. FAA–2015– intervals have been reassessed and the and may need to be revised upwards to
0490. conclusion was that the thresholds and suit an operator’s circumstances. The
intervals for inspection, as well as the estimate does not include the time to
FOR FURTHER INFORMATION CONTACT:
threshold for modifying the airplane, must be prepare, plan, or inspect the work. We
Vladimir Ulyanov, Aerospace Engineer, reduced.
International Branch, ANM–116, have made no changes to this AD in this
For the reason described above, this
Transport Airplane Directorate, FAA, regard.
[EASA] AD retains the requirements of EASA
1601 Lind Avenue SW., Renton, WA AD 2007–0284, which is superseded and Conclusion
98057–3356; telephone 425–227–1138; introduces redefined thresholds and
intervals. We reviewed the available data and
fax 425–227–1149.
This [EASA] AD is revised to clarify that, determined that air safety and the
SUPPLEMENTARY INFORMATION: public interest require adopting this AD
under some conditions, accomplishment of a
Discussion repair constitutes terminating action for the as proposed except for minor editorial
repetitive inspections. One of the outcome of changes. We have determined that these
We issued a notice of proposed this clarification is the deletion of paragraph minor changes:
rulemaking (NPRM) to amend 14 CFR (5) of this [EASA] AD. • Are consistent with the intent that
part 39 to supersede AD 2008–22–20,
You may examine the MCAI in the was proposed in the NPRM (80 FR
Amendment 39–15717 (73 FR 66747,
AD docket on the Internet at http:// 13799, March 17, 2015) for correcting
November 12, 2008). AD 2008–22–20
www.regulations.gov/#!documentDetail; the unsafe condition; and
applied to certain Airbus Model A330– • Do not add any additional burden
200, A330–300, and A340–300 series D=FAA-2015-0490-0002.
upon the public than was already
airplanes. The NPRM published in the Comments proposed in the NPRM (80 FR 13799,
Federal Register on March 17, 2015 (80 We gave the public the opportunity to March 17, 2015).
FR 13799). The NPRM was prompted by participate in developing this AD. The
a determination from a fatigue and Related Service Information Under 1
following presents the comments
damage tolerance evaluation that the CFR Part 51
received on the NPRM (80 FR 13799,
compliance times must be reduced. The March 17, 2015) and the FAA’s response Airbus has issued the following
NPRM also proposed to shorten certain to each comment. service information.
compliance times. We are issuing this • Airbus Service Bulletin A330–53–
AD to prevent fatigue cracking of the Support for the NPRM (80 FR 13799, 3159, Revision 02, dated March 29,
upper shell structure of the fuselage, March 17, 2015) 2010, describes procedures for a
which could result in reduced structural An anonymous commenter agreed modification of the fuselage, which
integrity of the airplane. with the safety benefit provided by the includes inspections (e.g., eddy current
The European Aviation Safety Agency NPRM (80 FR 13799, March 17, 2015). rotating probe test of fastener holes for
(EASA), which is the Technical Agent cracking, high frequency eddy current
for the Member States of the European Request for Revise Cost (HFEC) inspections for cracking of the
Union, has issued EASA Airworthiness Delta requested that we revise the upper shell structure of the fuselage,
Directive 2014–0012R1, dated January NPRM (80 FR 13799, March 17, 2015) to and checks of the fastener position for
24, 2014 (referred to after this as the relay the heavy impact of accomplishing clearance) and applicable corrective
Mandatory Continuing Airworthiness Airbus Service Bulletin A330–53–3160, actions (e.g., repair and rework).
mstockstill on DSK4VPTVN1PROD with RULES
Information, or ‘‘the MCAI’’), to correct Revision 03, dated January 6, 2012. • Airbus Service Bulletin A330–53–
an unsafe condition for certain Airbus Delta explained that the modification 3160, Revision 03, dated January 6,
Model A330–200, A330–300, and A340– specified in Airbus Service Bulletin 2012, describes procedures for
300 series airplanes. The MCAI states: A330–53–3160, Revision 03, dated applicable actions, including an eddy
During fatigue tests (EF3) on the A340–600, January 6, 2012, requires removal of the current rotating probe test for cracking
damage was found in the longitudinal vertical stabilizer and the aft galley, of the fastener holes and an HFEC
doubler at the Vertical Tail Plane (VTP) which can heavily impact the operation. inspection for cracks in the upper shell
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![73094 Federal Register / Vol. 80, No. 226 / Tuesday, November 24, 2015 / Rules and Regulations
of the fuselage (and including checks of cost impact on affected individuals. We office (telephone 800–647–5527) is in
the fastener position for clearance and do not control warranty coverage for the ADDRESSES section.
applicable corrective actions (e.g., repair affected individuals. As a result, we
and rework)), and a modification of the have included all costs in our cost List of Subjects in 14 CFR Part 39
airplane upper shell structure of the estimate. Air transportation, Aircraft, Aviation
fuselage between FR80 and FR86. safety, Incorporation by reference,
• Airbus Service Bulletin A330–53– Authority for This Rulemaking
Safety.
3168, Revision 02, dated December 21, Title 49 of the United States Code
2011, describes procedures for a HFEC specifies the FAA’s authority to issue Adoption of the Amendment
inspection for cracking of the upper rules on aviation safety. Subtitle I,
shell structure of the fuselage between section 106, describes the authority of Accordingly, under the authority
FR80 and FR86. the FAA Administrator. ‘‘Subtitle VII: delegated to me by the Administrator,
• Airbus Service Bulletin A340–53– Aviation Programs,’’ describes in more the FAA amends 14 CFR part 39 as
4165, Revision 02, dated March 29, detail the scope of the Agency’s follows:
2010, describes procedures for a authority.
modification of the fuselage, which PART 39—AIRWORTHINESS
We are issuing this rulemaking under DIRECTIVES
includes inspections (e.g., eddy current the authority described in ‘‘Subtitle VII,
rotating probe test of fastener holes for Part A, Subpart III, Section 44701:
cracking, HFEC inspections for cracking General requirements.’’ Under that ■ 1. The authority citation for part 39
of the upper shell structure of the section, Congress charges the FAA with continues to read as follows:
fuselage, and checks of the fastener promoting safe flight of civil aircraft in Authority: 49 U.S.C. 106(g), 40113, 44701.
position for clearance) and applicable air commerce by prescribing regulations
corrective actions (e.g., repair and § 39.13 [Amended]
for practices, methods, and procedures
rework). the Administrator finds necessary for
• Airbus Service Bulletin A340–53– ■ 2. The FAA amends § 39.13 by
safety in air commerce. This regulation removing Airworthiness Directive (AD)
4172, Revision 01, dated July 8, 2009, is within the scope of that authority
describes procedures for inspections 2008–22–20, Amendment 39–15717 (73
because it addresses an unsafe condition FR 66747, November 12, 2008), and
(e.g., rototest inspections of fastener that is likely to exist or develop on
holes for cracking, HFEC inspections for adding the following new AD:
products identified in this rulemaking
cracking of the upper shell structure of action. 2015–23–06 Airbus: Amendment 39–18322.
the fuselage, and checks of the fastener Docket No. FAA–2015–0490; Directorate
position for clearance) and modification Regulatory Findings Identifier 2014–NM–018–AD.
of the airplane upper shell structure We determined that this AD will not (a) Effective Date
between FR80 and FR86 (including have federalism implications under
applicable corrective actions (e.g., repair This AD becomes effective December 29,
Executive Order 13132. This AD will 2015.
and rework). not have a substantial direct effect on
• Airbus Service Bulletin A340–53– the States, on the relationship between (b) Affected ADs
4174, Revision 02, dated December 21, the national government and the States, This AD replaces AD 2008–22–20,
2011, describes procedures for a HFEC or on the distribution of power and Amendment 39–15717 (73 FR 66747,
inspection for cracking of the upper responsibilities among the various November 12, 2008).
shell structure of the fuselage between levels of government.
FR80 and FR86. (c) Applicability
For the reasons discussed above, I
This service information is reasonably This AD applies to Airbus Model A330–
certify that this AD:
available because the interested parties 201, –202, –203, –223, –243, –301, –302,
1. Is not a ‘‘significant regulatory
have access to it through their normal –303, –321, –322, –323, –341, –342, and –343
action’’ under Executive Order 12866;
course of business or by the means airplanes; and Model A340–311, –312, and
identified in the ADDRESSES section of 2. Is not a ‘‘significant rule’’ under the
–313 airplanes; certificated in any category;
this AD. DOT Regulatory Policies and Procedures all manufacturer serial numbers on which
(44 FR 11034, February 26, 1979); Airbus Modification 44205 has been
Costs of Compliance 3. Will not affect intrastate aviation in embodied in production, except those on
We estimate that this AD affects 26 Alaska; and which Airbus Modification 52974 or 53223
airplanes of U.S. registry. We also 4. Will not have a significant has been embodied in production.
estimate that it will take about 208 economic impact, positive or negative,
on a substantial number of small entities (d) Subject
work-hours per product to comply with
the basic requirements (inspection and under the criteria of the Regulatory Air Transport Association (ATA) of
modification) of this AD. The average Flexibility Act. America Code 53, Fuselage.
labor rate is $85 per work-hour. Examining the AD Docket (e) Reason
Required parts will cost about $28,360 This AD was prompted by the results of a
per product. Based on these figures, we You may examine the AD docket on
fatigue and damage tolerance evaluation that
estimate the cost of this AD on U.S. the Internet at http://
concluded existing compliance times must be
operators to be $1,197,040, or $46,040 www.regulations.gov/#!docket
reduced. We are issuing this AD to prevent
per product. Detail;D=FAA-2015-0490; or in person
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fatigue cracking of the upper shell structure
We have received no definitive data at the Docket Management Facility of the fuselage, which could result in
that will enable us to provide cost between 9 a.m. and 5 p.m., Monday reduced structural integrity of the airplane.
estimates for the on-condition actions through Friday, except Federal holidays.
specified in this AD. The AD docket contains this AD, the (f) Compliance
According to the manufacturer, some regulatory evaluation, any comments Comply with this AD within the
of the costs of this AD may be covered received, and other information. The compliance times specified, unless already
under warranty, thereby reducing the street address for the Docket Operations done.
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![73096 Federal Register / Vol. 80, No. 226 / Tuesday, November 24, 2015 / Rules and Regulations
and modification required by the (2) Service information identified in this DEPARTMENT OF TRANSPORTATION
introductory text to paragraph (j) of this AD, AD that is not incorporated by reference is
if those actions were performed before the available at the addresses specified in Federal Aviation Administration
effective date of this AD using the service paragraphs (q)(3) and (q)(4) of this AD.
information identified in paragraph (n)(2)(i), 14 CFR Part 39
(n)(2)(ii), or (n)(2)(iii) of this AD, as (q) Material Incorporated by Reference
applicable. (1) The Director of the Federal Register [Docket No. FAA–2015–0682; Directorate
(i) Airbus Service Bulletin A330–53–3160, approved the incorporation by reference Identifier 2014–NM–074–AD; Amendment
dated July 9, 2007, which was incorporated
(IBR) of the service information listed in this 39–18329; AD 2015–23–12]
by reference in AD 2008–22–20, Amendment
39–15717 (73 FR 66747, November 12, 2008). paragraph under 5 U.S.C. 552(a) and 1 CFR
(ii) Airbus Service Bulletin A330–53–3160, part 51. RIN 2120–AA64
Revision 01, dated April 28, 2009, which is (2) You must use this service information
not incorporated by reference in this AD. as applicable to do the actions required by Airworthiness Directives; ATR—GIE
(iii) Airbus Service Bulletin A330–53– this AD, unless this AD specifies otherwise. Avions de Transport Régional
3160, Revision 02, dated March 29, 2010, (3) The following service information was Airplanes
which is not incorporated by reference in this approved for IBR on December 29, 2015.
AD. AGENCY: Federal Aviation
(i) Airbus Service Bulletin A330–53–3159,
(3) For Model A340–300 airplanes, WV 027 Administration (FAA), Department of
Revision 02, dated March 29, 2010.
only: This paragraph provides credit for the Transportation (DOT).
(ii) Airbus Service Bulletin A330–53–3160,
inspection and modification required by ACTION: Final rule.
Revision 03, dated January 6, 2012.
paragraph (k) of this AD, if those actions
were performed before the effective date of (iii) Airbus Service Bulletin A330–53–
SUMMARY: We are adopting a new
this AD using Airbus Service Bulletin A340– 3168, Revision 02, dated December 21, 2011.
airworthiness directive (AD) for all
53–4172, dated July 10, 2007, which is was (iv) Airbus Service Bulletin A340–53–
ATR—GIE Avions de Transport
incorporated by reference in AD 2008–22–20, 4165, Revision 02, dated March 29, 2010.
(v) Airbus Service Bulletin A340–53–4172,
Régional Model ATR42 and ATR72
Amendment 39–15717 (73 FR 66747,
November 12, 2008). Revision 01, dated July 8, 2009.
airplanes. This AD was prompted by
(vi) Airbus Service Bulletin A340–53–
new occurrences of certain cracked
(o) Other FAA AD Provisions main landing gear (MLG) rear hinge
4174, Revision 02, dated December 21, 2011.
The following provisions also apply to this (4) The following service information was pins. This AD requires identifying the
AD: serial number and part number of the
approved for IBR on December 17, 2008 (73
(1) Alternative Methods of Compliance MLG rear hinge pins, and replacing pins
(AMOCs): The Manager, International FR 66747, November 12, 2008).
(i) Airbus Service Bulletin A330–53–3168, or the MLG if necessary. We are issuing
Branch, ANM–116, Transport Airplane this AD to detect and correct cracked
Directorate, FAA, has the authority to Revision 01, dated February 15, 2008.
approve AMOCs for this AD, if requested (ii) Airbus Service Bulletin A340–53–4174, rear hinge pins, which could lead to
using the procedures found in 14 CFR 39.19. Revision 01, dated February 15, 2008. MLG structural failure, possibly
In accordance with 14 CFR 39.19, send your (5) For service information identified in resulting in collapse of the MLG and
request to your principal inspector or local this AD, contact Airbus SAS, Airworthiness consequent injury to the occupants of
Flight Standards District Office, as Office—EAL, 1 Rond Point Maurice Bellonte, the airplane.
appropriate. If sending information directly 31707 Blagnac Cedex, France; telephone +33 DATES: This AD becomes effective
to the International Branch, send it to ATTN: 5 61 93 36 96; fax +33 5 61 93 45 80; email December 29, 2015. The Director of the
Vladimir Ulyanov, Aerospace Engineer,
airworthiness.A330-A340@airbus.com; Federal Register approved the
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind Internet http://www.airbus.com. incorporation by reference of certain
Avenue SW., Renton, WA 98057–3356; (6) You may view this service information publications listed in this AD as of
telephone 425–227–1138; fax 425–227–1149. at the FAA, Transport Airplane Directorate, December 29, 2015.
Information may be emailed to: 9-ANM-116- 1601 Lind Avenue SW., Renton, WA. For ADDRESSES: You may examine the AD
AMOC-REQUESTS@faa.gov. Before using information on the availability of this docket on the Internet at http://www.
any approved AMOC, notify your appropriate material at the FAA, call 425–227–1221. regulations.gov/#!docketDetail;D=FAA-
principal inspector, or lacking a principal (7) You may view this service information
inspector, the manager of the local flight
2015-0682; or in person at the Docket
that is incorporated by reference at the
standards district office/certificate holding Management Facility, U.S. Department
National Archives and Records
district office. The AMOC approval letter of Transportation, Docket Operations,
Administration (NARA). For information on
must specifically reference this AD. M–30, West Building Ground Floor,
the availability of this material at NARA, call
(2) Contacting the Manufacturer: As of the Room W12–140, 1200 New Jersey
202–741–6030, or go to: http://
effective date of this AD, for any requirement Avenue SE., Washington, DC.
in this AD to obtain corrective actions from www.archives.gov/federal-register/cfr/ibr-
locations.html.
For service information identified in
a manufacturer, the action must be this AD, contact ATR—GIE Avions de
accomplished using a method approved by Issued in Renton, Washington, on October Transport Régional, 1, Allée Pierre
the Manager, International Branch, ANM– 30, 2015.
116, Transport Airplane Directorate, FAA; or
Nadot, 31712 Blagnac Cedex, France;
the EASA; or Airbus’s EASA DOA. If Michael Kaszycki, telephone +33 (0) 5 62 21 62 21; fax +33
approved by the DOA, the approval must Acting Manager, Transport Airplane (0) 5 62 21 67 18; email
include the DOA-authorized signature. Directorate, Aircraft Certification Service. continued.airworthiness@atr.fr; Internet
[FR Doc. 2015–28886 Filed 11–23–15; 8:45 am] http://www.aerochain.com. You may
(p) Related Information
view this referenced service information
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BILLING CODE 4910–13–P
(1) Refer to Mandatory Continuing at the FAA, Transport Airplane
Airworthiness Information (MCAI) EASA Directorate, 1601 Lind Avenue SW.,
Airworthiness Directive 2014–0012R1, dated
January 24, 2014, for related information.
Renton, WA. For information on the
This MCAI may be found in the AD docket availability of this material at the FAA,
on the Internet at http://www.regulations.gov call 425–227–1221. It is also available
by searching for and locating Docket No. on the Internet at http://
FAA–2015–0490. www.regulations.gov by searching for
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Document Created: 2015-12-14 14:09:19
Document Modified: 2015-12-14 14:09:19
| 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 becomes effective December 29, 2015. | |
| Contact | Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. | |
| FR Citation | 80 FR 73092 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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