82 FR 56158 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 227 (November 28, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 227 (November 28, 2017)
| Page Range | 56158-56163 | |
| FR Document | 2017-23349 |
[Federal Register Volume 82, Number 227 (Tuesday, November 28, 2017)] [Rules and Regulations] [Pages 56158-56163] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-23349] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2017-0478; Product Identifier 2016-NM-174-AD; Amendment 39-19087; AD 2017-22-07] 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 certain Airbus Model A319 series airplanes; Model A320-211, -212, -214, -231, - 232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, - 213, -231, and -232 airplanes. This AD was prompted by a report of cracks on frame forks and outer skin on the forward and aft cargo compartment doors. This AD requires repetitive inspections of the frame forks, and corrective actions if necessary. This AD also includes optional modifications that constitute terminating action. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective January 2, 2018. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of January 2, 2018. ADDRESSES: For service information identified in this final rule, contact Airbus, Airworthiness Office--EIAS, 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 Standards Branch, 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-2017-0478. [[Page 56159]] 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-2017- 0478; 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: Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-227-1405; 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 certain Airbus Model A319 series airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. The NPRM published in the Federal Register on May 22, 2017 (82 FR 23160) (``the NPRM''). The NPRM was prompted by a report of cracks on frame forks and outer skin on the forward and aft cargo compartment doors. The NPRM proposed to require repetitive inspections of the frame forks, and corrective actions if necessary. The NPRM also included optional modifications that constitute terminating action. We are issuing this AD to detect and correct cracks on the frame forks and outer skin on the forward and aft cargo compartment doors, which could lead to reduced structural integrity and failure of the cargo compartment door, possible decompression of the airplane, and injury to occupants. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2016-0187, dated September 19, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Airbus Model A319 series airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. The MCAI states: During full scale fatigue test, cracks have been found on frame forks and outer skin on forward and aft cargo doors. To improve the fatigue behaviour of the frame forks, Airbus introduced modification (mod) 22948 in production, and issued inspection Service Bulletin (SB) A320-52-1032 and modification SB A320-52-1042, both recommended. Since those actions were taken, further improved cargo compartment doors have been introduced in production through Airbus mod 26213, on aeroplanes having [manufacturer serial number] MSN 0759 and up. This modification, which is not available for in- service retrofit, also includes provisions that exclude installation of pre-mod 26213 aft and forward compartment cargo doors on an aeroplane. In the frame of the Widespread Fatigue Damage (WFD) study, it has been determined that repetitive inspections are necessary for aft and forward cargo compartment doors on aeroplanes that do not (or no longer) embody mod 22948 (or SB A320-52-1042), and those that do not embody mod 26213. Failure to detect cracks would reduce the cargo door structural integrity. This condition, if not detected and corrected, could lead to cargo door failure, possibly resulting in decompression of the aeroplane and injury to occupants. To address this unsafe condition, Airbus issued SB A320-52-1171 to provide inspection instructions. This SB was later revised to correct the list of affected cargo doors. Airbus also issued SB A320-52-1170, introducing a door modification which constitutes terminating action for the repetitive special detailed inspection (SDI). For the reason described above, this [EASA] AD requires accomplishment of repetitive SDI by rototest of all frame forks in beam 4 area to detect cracks, and, depending on findings, accomplishment of applicable corrective action(s) [repair or replacement]. This AD also provides an optional [modification that constitutes] terminating action for the repetitive SDI required by this [EASA] AD. One of the optional modifications includes related investigative and corrective actions. The related investigative action is a high frequency eddy current (HFEC) rotating probe inspection for cracks, and the corrective action is a repair. 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-2017-0478. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA's response to each comment. Requests To Refer to Updated Service Information Delta Air Lines and United Airlines requested that we revise the NPRM to refer to Airbus Service Bulletin A320-52-1171, Revision 02, dated April 10, 2017. United Airlines mentioned that Airbus has made number of updates and clarifications in Airbus Service Bulletin A320- 52-1171, Revision 02, dated April 10, 2017. Additionally, United Airlines pointed out that EASA AD 2016-0187, dated September 19, 2016, quoted in the ``Discussion'' section of the NPRM, allows for use of later approved revisions. We agree with the commenters for the reasons provided. We have revised this AD to refer to Airbus Service Bulletin A320-52-1171, Revision 02, dated April 10, 2017. We have also redesignated paragraph (m) (of the proposed AD) as paragraph (m)(1) of this AD and added paragraph (m)(2) to provide credit for actions done before the effective date of this AD, if those actions were done using Airbus Service Bulletin A320-52-1171, Revision 01, dated September 5, 2016. Request To Clarify That Certain Service Information Cancels the Requirements of Certain Other Service Information United Airlines requested that we clarify that Airbus Service Bulletin A320-52-1171, Revision 02, dated April 10, 2017, cancels the requirements of Airbus Service Bulletin A320-52-1032. The commenter indicated that a statement regarding this subject would clarify the required actions for operators. The commenter also pointed out that a statement is listed in Airbus Service Bulletin A320-52-1171, Revision 02, dated April 10, 2017, that specifies the cancellation of the requirements of Airbus Service Bulletin A320-52-1032. We agree to clarify. Airbus Service Bulletin A320-52-1171, Revision 02, dated April 10, 2017, does include a statement indicating that the actions specified in Airbus Service Bulletin A320-52-1171, Revision 02, dated April 10, 2017, cancel the actions specified in Airbus Service Bulletin A320-52-1032. However, the actions specified in Airbus Service Bulletin A320-52-1032 are not required by any AD, and therefore, we do not specifically address Airbus Service Bulletin A320-52-1032 in this AD (except for the compliance time reference in paragraph (h)(4) of this AD). We have not changed this AD in this regard. [[Page 56160]] Request To Update the NPRM To Include Modifications 22948 and 26213 Delta Air Lines requested that we revise paragraphs (c) and (g) of the proposed AD to refer to Modifications 22948 and 26213. Specifically, Delta Air Lines requested that we include information that elaborates on the specific airplanes affected by the NPRM. Delta Air Lines pointed out that EASA AD 2016-0187, dated September 19, 2016, quoted in the ``Discussion'' section of the NPRM, and Airbus Service Bulletin A320-52-1042, Revision 2, dated January 14, 1997, already refer to the modifications. Delta Air Lines also mentioned that it has 40 forward and aft cargo compartment doors affected by the NPRM, which are pre-Modifications 22948 and 26213 and under manufacturer serial number 0758. We disagree to refer to Modifications 22948 and 26213 in paragraphs (c) and (g) of this AD; however, we agree that clarification is necessary. The applicability of this AD refers to the affected models having manufacturer serial numbers through 0758 inclusive; all airplanes having these serial numbers are affected by the identified unsafe condition. Airbus introduced modification 22948 in production, and issued Airbus Service Bulletin A320-52-1032 for recommended inspections and Airbus Service Bulletin A320-52-1042 for recommended modification 22948. Since that service information was issued, Airbus has introduced further improved forward and aft cargo compartment doors (modification 26213) in production on airplanes having manufacturer serial number 0759 and above; however, this modification is unavailable for in-service retrofit. Modification 26213 includes provisions that prohibit installation of earlier configurations of forward or aft cargo compartment doors (pre-modification 26213). Airplanes having manufacturer serial numbers 0759 and subsequent have modification 26213 installed in production. We have not changed this AD in this regard. Request To Include Instructions for Rotable Parts Delta Air Lines requested that we include instructions for rotable parts in paragraph (g) of the proposed AD. The commenter mentioned that forward or aft cargo compartment doors could be migrated from manufacturer serial number 0759 and above to airplanes that are affected, and asked if those airplanes are still affected. The commenter also requested that Airbus provide a list of manufacturer serial numbers that are affected by the proposed AD. We partially agree with the commenter. Airplanes originally delivered with the affected doors are subject to the requirements of this AD. Paragraph (h) of this AD only requires actions on affected doors. It is not physically possible to install the affected doors on serial numbers 0759 and above; therefore, parts rotability does not need to be addressed in this AD. In addition, paragraph (n) of this AD provides a parts installation limitation for the forward or aft cargo compartment doors for the airplanes identified in paragraph (c) of this AD. We have no practical method to provide a manufacturer serial number list of affected airplanes on which a non-affected door might have been installed or to predict an airplane configuration in the worldwide fleet. Therefore, we have not changed this AD in this regard. Request To Clarify Optional Terminating Actions United Airlines requested that we clarify the optional terminating actions specified in paragraph (j) of the proposed AD. The commenter requested we include a statement that specifies modification of all affected doors of an airplane in accordance with the requirements of paragraphs (j)(1), (j)(2), or (j)(3) of this AD constitutes terminating action. The commenter pointed out that EASA AD 2016-0187, dated September 19, 2016, quoted in the ``Discussion'' section of the NPRM, allows for modification of an airplane as specified in Airbus Service Bulletin A320-52-1042, Revision 2, dated January 14, 1997; or Airbus Service Bulletin A320-52-1170, dated September 5, 2016; and either is considered terminating action for the repetitive inspections. We agree that clarification is necessary. We have revised paragraph (j) of this AD to include introductory text with the statement: ``Modification of all affected doors of an airplane in accordance with the requirements of paragraph (j)(1), (j)(2), or (j)(3) of this AD constitutes terminating action . . . .'' Request To Include Compliance Times for Optional Terminating Actions Mr. Petit requested that we add compliance times for the optional terminating actions specified in the proposed AD. Mr. Petit indicated that 14 CFR 26.21 might require a mandatory terminating action before 56,300 flight cycles. Mr. Petit also recommended that the optional terminating action not be embodied before 21,700 flight cycles. We disagree with the commenter's request to include compliance times for the optional terminating action specified in this AD. 14 CFR 26.21 mandates the limit of validity (LOV) and does not specify compliance times for the optional terminating action specified in this AD. This AD mandates repetitive inspections of the frame forks as specified in the service information provided by the design approval holder (DAH) to meet the LOV. In addition, we do not include compliance times for optional actions in ADs because doing so would make the actions mandatory. We intend for the terminating actions in this AD to be optional, which aligns with the MCAI. Regarding the commenter's recommendation to prohibit accomplishing the optional terminating action before 21,700 flight cycles, the commenter provided no substantiation for this prohibition. We have received no data indicating that the optional terminating action should not be accomplished before 21,700 flight cycles. Therefore, we have not changed this AD in this regard. Clarification of Exception Paragraph (i)(2) of the proposed AD, which refers to Airbus Service Bulletin A320-52-1170, dated September 5, 2016, includes an exception as specified in paragraph (k) of the proposed AD. However, paragraph (k) of the proposed AD does not mention Airbus Service Bulletin A320- 52-1170, dated September 5, 2016. We have added Airbus Service Bulletin A320-52-1170, dated September 5, 2016, to the exception specified in paragraph (k) of this AD. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously and 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. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information. [[Page 56161]] Airbus Service Bulletin A320-52-1171, Revision 02, dated April 10, 2017, describes procedures for repetitive special detailed inspections of all frame forks in the beam 4 area of any affected door, and corrective actions. Airbus Service Bulletin A320-52-1042, Revision 2, dated January 14, 1997, describes procedures for modification of all affected forward and aft cargo compartment doors of an airplane. Airbus Service Bulletin A320-52-1170, dated September 5, 2016, describes modification of all affected forward and aft cargo compartment doors of an airplane, including related investigative and corrective actions. 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 88 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 ---------------------------------------------------------------------------------------------------------------- Special detailed inspection........ 25 work-hours x $85 per $0 $2,125 $187,000 hour = $2,125. ---------------------------------------------------------------------------------------------------------------- Optional Actions ---------------------------------------------------------------------------------------------------------------- Action Labor cost Parts cost Cost per product ---------------------------------------------------------------------------------------------------------------- Modification............................ 24 work-hours x $85 per Up to $240........... Up to $2,280. hour = $2,040. ---------------------------------------------------------------------------------------------------------------- We have received no definitive data that would enable us to provide cost estimates for the on-condition repairs and replacements specified in this AD. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ``Subtitle VII: Aviation Programs,'' describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in ``Subtitle VII, Part A, Subpart III, Section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes to the Director of the System Oversight Division. 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): 2017-22-07 Airbus: Amendment 39-19087; Docket No. FAA-2017-0478; Product Identifier 2016-NM-174-AD. (a) Effective Date This AD is effective January 2, 2018. (b) Affected ADs None. (c) Applicability This AD applies to Airbus Model A319-111, -112, -113, -114, - 115, -131, -132, and -133 airplanes; Model A320-211, -212, -214, - 231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes, certificated in any category, manufacturer serial numbers through 0758 inclusive. (d) Subject Air Transport Association (ATA) of America Code 52, Doors. (e) Reason This AD was prompted by a report of cracks on the frame forks and outer skin on the forward and aft cargo compartment doors. We are issuing this AD to detect and correct cracks on the frame forks and outer skin on the forward and aft cargo compartment doors, which could lead to reduced structural integrity and failure of the cargo compartment door, possible decompression of the airplane, and injury to occupants. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Definition of Affected Door For the purpose of this AD, an ``affected door'' is a forward or aft cargo compartment [[Page 56162]] door, having any part number listed in table 1 to paragraph (g) of this AD, except a cargo compartment door on which Airbus Service Bulletin A320-52-1042 or Airbus Service Bulletin A320-52-1170 is embodied. [GRAPHIC] [TIFF OMITTED] TR28NO17.017 (h) Repetitive Special Detailed Inspection of Frame Forks At the latest of the compliance times listed in paragraphs (h)(1) through (h)(4) of this AD: Do a special detailed inspection of all frame forks in the beam 4 area of any affected door as defined in paragraph (g) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1171, Revision 02, dated April 10, 2017, except as specified in paragraphs (k) and (l) of this AD. Repeat the inspection thereafter at intervals not to exceed 3,000 flight cycles. A review of the airplane delivery or maintenance records is acceptable to identify any affected door installed on the airplane, provided that the cargo compartment door part number can be conclusively determined from that review. (1) Before exceeding 37,500 flight cycles since first installation of the door on an airplane. (2) Within 900 flight cycles after the effective date of this AD, without exceeding 41,950 flight cycles since first installation of the door on an airplane. (3) Within 50 flight cycles after the effective date of this AD, for a door having reached or exceeded 41,900 flight cycles since first installation on an airplane. (4) Within 3,000 flight cycles since the last inspection of the door as specified in Airbus Service Bulletin A320-52-1032. (i) Corrective Actions If any crack is found during any inspection required by paragraph (h) of this AD, before further flight, do all applicable corrective actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1171, Revision 02, dated April 10, 2017, except as specified in paragraphs (k) and (l) of this AD. Accomplishment of applicable corrective actions does not constitute terminating action for the repetitive inspections. (j) Optional Terminating Action Modification of all affected doors of an airplane in accordance with the requirements of paragraph (j)(1), (j)(2), or (j)(3) of this AD, constitutes terminating action for the repetitive inspections specified in paragraph (h) of this AD for that airplane. (1) Modification of all affected doors of an airplane in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1042, Revision 2, dated January 14, 1997, constitutes terminating action for the repetitive inspections specified in paragraph (h) of this AD for that airplane, provided that, after modification, no affected door is re-installed on that airplane. (2) Modification of all affected doors of an airplane including accomplishment of all applicable related investigative and corrective actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-52-1170, dated September 5, 2016, except as specified in paragraph (k) of this AD, constitutes terminating action for the repetitive inspections specified in paragraph (h) of this AD for that airplane, provided that, after modification, no affected door is re-installed on that airplane. (3) Modification of all affected doors on an airplane, in case of finding damaged frame forks, as specified in an Airbus Repair Design Approval Sheet (RDAS), and done in accordance with a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA); constitutes terminating action for the repetitive inspection specified in paragraph (h) of this AD for that airplane, provided that, after modification, no affected door is re-installed on that airplane. (k) Exception to Service Information Where Airbus Service Bulletin A320-52-1170, dated September 5, 2016; or Airbus Service Bulletin A320-52-1171, Revision 02, dated April 10, 2017; specifies to contact Airbus for appropriate action, and specifies that action as ``RC'' (Required for Compliance): Before further flight, accomplish corrective actions in accordance with the procedures specified in paragraph (o)(2) of this AD. [[Page 56163]] (l) No Reporting Requirement Although Airbus Service Bulletin A320-52-1171, Revision 02, dated April 10, 2017, specifies to submit certain information to the manufacturer, and specifies that action as ``RC,'' this AD does not include that requirement. (m) Credit for Previous Actions (1) This paragraph provides credit for the actions required by paragraphs (h) and (i) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-52-1171, dated October 29, 2015, provided that it can be conclusively determined that any part number D52371000018 was also inspected as specified in paragraph (h) of this AD. (2) This paragraph provides credit for the actions required by paragraphs (h) and (i) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-52-1171, Revision 01, dated September 5, 2016. (n) Parts Installation Limitation As of the effective date of this AD, no person may install, on any airplane, an affected door specified in paragraph (g) of this AD, unless it has been inspected in accordance with the requirements of paragraph (h) of this AD and all applicable corrective actions have been done in accordance with paragraph (i) of this AD. (o) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Section, Transport Standards Branch, 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 Section, send it to the attention of the person identified in paragraph (p)(2) of this AD. 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 Section, Transport Standards Branch, 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): Except as specified in paragraphs (k) and (l) of this AD: 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. (p) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2016-0187, dated September 19, 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-2017-0478. (2) For more information about this AD, contact Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-227-1405; fax: 425-227-1149. (3) 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. (i) Airbus Service Bulletin A320-52-1042, Revision 2, dated January 14, 1997 (pages 5, 9, and 19 through 22 of this document are identified as Revision 1, dated November 22, 1993). (ii) Airbus Service Bulletin A320-52-1170, dated September 5, 2016, including Appendices 01 and 02, dated September 5, 2016. (iii) Airbus Service Bulletin A320-52-1171, Revision 02, dated April 10, 2017. (3) For service information identified in this AD, contact Airbus, Airworthiness Office--EIAS, 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 Standards Branch, 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 October 17, 2017. Jeffrey E. Duven, Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2017-23349 Filed 11-27-17; 8:45 am] BILLING CODE 4910-13-P
![56158 Federal Register / Vol. 82, No. 227 / Tuesday, November 28, 2017 / Rules and Regulations
(f) Compliance (3) An AMOC that provides an acceptable Issued in Renton, Washington, on
Comply with this AD within the level of safety may be used for any repair, November 15, 2017.
compliance times specified, unless already modification, or alteration required by this Chris Spangenberg,
done. AD if it is approved by the Boeing
Acting Director, System Oversight Division,
Commercial Airplanes Organization
(g) For Group 1 Airplanes: Inspection and Aircraft Certification Service.
Designation Authorization (ODA) that has
Corrective Actions been authorized by the Manager, Los Angeles [FR Doc. 2017–25379 Filed 11–27–17; 8:45 am]
For airplanes identified as Group 1 in ACO Branch, to make those findings. To be BILLING CODE 4910–13–P
Boeing Alert Service Bulletin 737–57A1329, approved, the repair method, modification
dated January 16, 2017: Within 120 days after deviation, or alteration deviation must meet
the effective date of this AD, do an inspection the certification basis of the airplane, and the DEPARTMENT OF TRANSPORTATION
for cracking of the upper aft skin of the approval must specifically refer to this AD.
wings, and do all applicable corrective (4) Except as required by paragraph (i)(2) Federal Aviation Administration
actions, using a method approved in of this AD: For service information that
accordance with the procedures specified in contains steps that are labeled as RC, the 14 CFR Part 39
paragraph (j) of this AD. provisions of paragraphs (j)(4)(i) and (j)(4)(ii)
of this AD apply. [Docket No. FAA–2017–0478; Product
(h) For Groups 2 and 3 Airplanes: Repetitive (i) The steps labeled as RC, including Identifier 2016–NM–174–AD; Amendment
Inspections and Repair substeps under an RC step and any figures 39–19087; AD 2017–22–07]
For Groups 2 and 3 airplanes identified in identified in an RC step, must be done to
RIN 2120–AA64
Boeing Alert Service Bulletin 737–57A1329, comply with the AD. If a step or substep is
dated January 16, 2017: At the applicable labeled ‘‘RC Exempt,’’ then the RC
time specified in paragraph 1.E., requirement is removed from that step or
Airworthiness Directives; Airbus
‘‘Compliance,’’ of Boeing Alert Service substep. An AMOC is required for any Airplanes
Bulletin 737–57A1329, dated January 16, deviations to RC steps, including substeps AGENCY: Federal Aviation
2017, except as required by paragraph (i) of and identified figures.
this AD, do the applicable inspection for (ii) Steps not labeled as RC may be
Administration (FAA), Department of
cracking of the upper aft skin of the wings deviated from using accepted methods in Transportation (DOT).
from wing buttock line (WBL) 159 to WBL accordance with the operator’s maintenance ACTION: Final rule.
220, in accordance with the Work or inspection program without obtaining
Instructions of Boeing Alert Service Bulletin approval of an AMOC, provided the RC steps, We are adopting a new
SUMMARY:
737–57A1329, dated January 16, 2017. If any including substeps and identified figures, can airworthiness directive (AD) for certain
cracking is found, repair before further flight, still be done as specified, and the airplane Airbus Model A319 series airplanes;
in accordance with the procedures specified can be put back in an airworthy condition. Model A320–211, –212, –214, –231,
in paragraph (j) of this AD. Repeat the –232, and –233 airplanes; and Model
inspection thereafter at the applicable time (k) Related Information
For more information about this AD, A321–111, –112, –131, –211, –212,
specified in paragraph 1.E., ‘‘Compliance,’’ of
Boeing Alert Service Bulletin 737–57A1329, contact Payman Soltani, Aerospace Engineer, –213, –231, and –232 airplanes. This AD
dated January 16, 2017. Airframe Section, FAA, Los Angeles ACO was prompted by a report of cracks on
Branch, 3960 Paramount Boulevard, frame forks and outer skin on the
(i) Exceptions to the Service Information Lakewood, CA 90712–4137; phone: 562–627– forward and aft cargo compartment
(1) Where Boeing Alert Service Bulletin 5313; fax: 562–627–5210; email: doors. This AD requires repetitive
737–57A1329, dated January 16, 2017, payman.soltani@faa.gov. inspections of the frame forks, and
specifies a compliance time ‘‘after the corrective actions if necessary. This AD
original issue date of this service bulletin,’’ (l) Material Incorporated by Reference
(1) The Director of the Federal Register also includes optional modifications
paragraph (h) of this AD requires compliance
within the specified compliance time after approved the incorporation by reference that constitute terminating action. We
the effective date of this AD. (IBR) of the service information listed in this are issuing this AD to address the unsafe
(2) Although Boeing Alert Service Bulletin paragraph under 5 U.S.C. 552(a) and 1 CFR condition on these products.
737–57A1329, dated January 16, 2017, part 51. DATES: This AD is effective January 2,
specifies to contact Boeing for repair (2) You must use this service information 2018.
instructions, and specifies that action as as applicable to do the actions required by
The Director of the Federal Register
‘‘RC’’ (Required for Compliance), this AD this AD, unless the AD specifies otherwise.
(i) Boeing Alert Service Bulletin 737– approved the incorporation by reference
requires repair in accordance with the
procedures specified in paragraph (j) of this 57A1329, dated January 16, 2017. of certain publications listed in this AD
AD. (ii) Reserved. as of January 2, 2018.
(3) For service information identified in ADDRESSES: For service information
(j) Alternative Methods of Compliance this AD, contact Boeing Commercial
(AMOCs) identified in this final rule, contact
Airplanes, Attention: Contractual & Data Airbus, Airworthiness Office—EIAS,
(1) The Manager, Los Angeles ACO Branch, Services (C&DS), 2600 Westminster Blvd.,
1 Rond Point Maurice Bellonte, 31707
FAA, has the authority to approve AMOCs MC 110–SK57, Seal Beach, CA 90740;
for this AD, if requested using the procedures telephone 562–797–1717; Internet https:// Blagnac Cedex, France; telephone: +33 5
found in 14 CFR 39.19. In accordance with www.myboeingfleet.com. 61 93 36 96; fax: +33 5 61 93 44 51;
14 CFR 39.19, send your request to your (4) You may view this service information email: account.airworth-eas@
principal inspector or local Flight Standards at the FAA, Transport Standards Branch, airbus.com; Internet: http://
District Office, as appropriate. If sending 1601 Lind Avenue SW., Renton, WA. For www.airbus.com. You may view this
information directly to the manager of the information on the availability of this referenced service information at the
certification office, send it to the attention of material at the FAA, call 425–227–1221. FAA, Transport Standards Branch, 1601
jstallworth on DSKBBY8HB2PROD with RULES
the person identified in paragraph (k) of this (5) You may view this service information Lind Avenue SW., Renton, WA. For
AD. Information may be emailed to: 9-ANM- that is incorporated by reference at the
information on the availability of this
LAACO-AMOC-Requests@faa.gov. National Archives and Records
(2) Before using any approved AMOC, Administration (NARA). For information on material at the FAA, call 425–227–1221.
notify your appropriate principal inspector, the availability of this material at NARA, call It is also available on the Internet at
or lacking a principal inspector, the manager 202–741–6030, or go to: http:// http://www.regulations.gov by searching
of the local flight standards district office/ www.archives.gov/federal-register/cfr/ibr- for and locating Docket No. FAA–2017–
certificate holding district office. locations.html. 0478.
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Examining the AD Docket Model A321–111, –112, –131, –211, Requests To Refer to Updated Service
You may examine the AD docket on –212, –213, –231, and –232 airplanes. Information
the Internet at http:// The MCAI states:
Delta Air Lines and United Airlines
www.regulations.gov by searching for During full scale fatigue test, cracks have
requested that we revise the NPRM to
and locating Docket No. FAA–2017– been found on frame forks and outer skin on
forward and aft cargo doors. refer to Airbus Service Bulletin A320–
0478; or in person at the Docket
Management Facility between 9 a.m. To improve the fatigue behaviour of the 52–1171, Revision 02, dated April 10,
and 5 p.m., Monday through Friday, frame forks, Airbus introduced modification 2017. United Airlines mentioned that
except Federal holidays. The AD docket (mod) 22948 in production, and issued Airbus has made number of updates and
inspection Service Bulletin (SB) A320–52– clarifications in Airbus Service Bulletin
contains this AD, the regulatory
1032 and modification SB A320–52–1042, A320–52–1171, Revision 02, dated April
evaluation, any comments received, and both recommended.
other information. The street address for 10, 2017. Additionally, United Airlines
Since those actions were taken, further
the Docket Office (telephone: 800–647– pointed out that EASA AD 2016–0187,
improved cargo compartment doors have
5527) is Docket Management Facility, been introduced in production through dated September 19, 2016, quoted in the
U.S. Department of Transportation, Airbus mod 26213, on aeroplanes having ‘‘Discussion’’ section of the NPRM,
Docket Operations, M–30, West [manufacturer serial number] MSN 0759 and allows for use of later approved
Building Ground Floor, Room W12–140, up. This modification, which is not available revisions.
1200 New Jersey Avenue SE., for in-service retrofit, also includes We agree with the commenters for the
Washington, DC 20590. provisions that exclude installation of pre-
reasons provided. We have revised this
mod 26213 aft and forward compartment
FOR FURTHER INFORMATION CONTACT: AD to refer to Airbus Service Bulletin
cargo doors on an aeroplane.
Sanjay Ralhan, Aerospace Engineer, In the frame of the Widespread Fatigue A320–52–1171, Revision 02, dated April
International Section, Transport Damage (WFD) study, it has been determined 10, 2017. We have also redesignated
Standards Branch, FAA, 1601 Lind that repetitive inspections are necessary for paragraph (m) (of the proposed AD) as
Avenue SW., Renton, WA 98057–3356; aft and forward cargo compartment doors on paragraph (m)(1) of this AD and added
telephone: 425–227–1405; fax: 425– aeroplanes that do not (or no longer) embody paragraph (m)(2) to provide credit for
227–1149. mod 22948 (or SB A320–52–1042), and those actions done before the effective date of
SUPPLEMENTARY INFORMATION: that do not embody mod 26213. Failure to
this AD, if those actions were done
detect cracks would reduce the cargo door
Discussion structural integrity.
using Airbus Service Bulletin A320–52–
This condition, if not detected and 1171, Revision 01, dated September 5,
We issued a notice of proposed
corrected, could lead to cargo door failure, 2016.
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would possibly resulting in decompression of the
aeroplane and injury to occupants.
Request To Clarify That Certain Service
apply to certain Airbus Model A319 Information Cancels the Requirements
To address this unsafe condition, Airbus
series airplanes; Model A320–211, –212, issued SB A320–52–1171 to provide of Certain Other Service Information
–214, –231, –232, and –233 airplanes; inspection instructions. This SB was later
and Model A321–111, –112, –131, –211, revised to correct the list of affected cargo United Airlines requested that we
–212, –213, –231, and –232 airplanes. doors. Airbus also issued SB A320–52–1170, clarify that Airbus Service Bulletin
The NPRM published in the Federal introducing a door modification which A320–52–1171, Revision 02, dated April
Register on May 22, 2017 (82 FR 23160) constitutes terminating action for the 10, 2017, cancels the requirements of
(‘‘the NPRM’’). The NPRM was repetitive special detailed inspection (SDI). Airbus Service Bulletin A320–52–1032.
prompted by a report of cracks on frame For the reason described above, this The commenter indicated that a
forks and outer skin on the forward and [EASA] AD requires accomplishment of statement regarding this subject would
repetitive SDI by rototest of all frame forks
aft cargo compartment doors. The clarify the required actions for
in beam 4 area to detect cracks, and,
NPRM proposed to require repetitive depending on findings, accomplishment of operators. The commenter also pointed
inspections of the frame forks, and applicable corrective action(s) [repair or out that a statement is listed in Airbus
corrective actions if necessary. The replacement]. This AD also provides an Service Bulletin A320–52–1171,
NPRM also included optional optional [modification that constitutes] Revision 02, dated April 10, 2017, that
modifications that constitute terminating action for the repetitive SDI specifies the cancellation of the
terminating action. We are issuing this required by this [EASA] AD. requirements of Airbus Service Bulletin
AD to detect and correct cracks on the A320–52–1032.
frame forks and outer skin on the One of the optional modifications
forward and aft cargo compartment includes related investigative and We agree to clarify. Airbus Service
doors, which could lead to reduced corrective actions. The related Bulletin A320–52–1171, Revision 02,
structural integrity and failure of the investigative action is a high frequency dated April 10, 2017, does include a
cargo compartment door, possible eddy current (HFEC) rotating probe statement indicating that the actions
decompression of the airplane, and inspection for cracks, and the corrective specified in Airbus Service Bulletin
injury to occupants. action is a repair. You may examine the A320–52–1171, Revision 02, dated April
The European Aviation Safety Agency MCAI in the AD docket on the Internet 10, 2017, cancel the actions specified in
(EASA), which is the Technical Agent at http://www.regulations.gov by Airbus Service Bulletin A320–52–1032.
for the Member States of the European searching for and locating Docket No. However, the actions specified in
Union, has issued EASA AD 2016–0187, FAA–2017–0478. Airbus Service Bulletin A320–52–1032
jstallworth on DSKBBY8HB2PROD with RULES
dated September 19, 2016 (referred to Comments are not required by any AD, and
after this as the Mandatory Continuing therefore, we do not specifically address
Airworthiness Information, or ‘‘the We gave the public the opportunity to Airbus Service Bulletin A320–52–1032
MCAI’’), to correct an unsafe condition participate in developing this AD. The in this AD (except for the compliance
for certain Airbus Model A319 series following presents the comments time reference in paragraph (h)(4) of this
airplanes; Model A320–211, –212, –214, received on the NPRM and the FAA’s AD). We have not changed this AD in
–231, –232, and –233 airplanes; and response to each comment. this regard.
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• Airbus Service Bulletin A320–52– aft cargo compartment doors of an have access to it through their normal
1171, Revision 02, dated April 10, 2017, airplane. course of business or by the means
describes procedures for repetitive • Airbus Service Bulletin A320–52– identified in the ADDRESSES section.
special detailed inspections of all frame 1170, dated September 5, 2016,
forks in the beam 4 area of any affected describes modification of all affected Costs of Compliance
door, and corrective actions. forward and aft cargo compartment We estimate that this AD affects 88
• Airbus Service Bulletin A320–52– doors of an airplane, including related
airplanes of U.S. registry.
1042, Revision 2, dated January 14, investigative and corrective actions.
1997, describes procedures for This service information is reasonably We estimate the following costs to
modification of all affected forward and available because the interested parties comply with this AD:
ESTIMATED COSTS
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
Special detailed inspection ..... 25 work-hours × $85 per hour = $2,125 ................................ $0 $2,125 $187,000
OPTIONAL ACTIONS
Cost per
Action Labor cost Parts cost product
Modification ............................. 24 work-hours × $85 per hour = $2,040 ........................................................... Up to $240 ..... Up to $2,280.
We have received no definitive data Regulatory Findings § 39.13 [Amended]
that would enable us to provide cost ■ 2. The FAA amends § 39.13 by adding
We determined that this AD will not
estimates for the on-condition repairs the following new airworthiness
have federalism implications under
and replacements specified in this AD. directive (AD):
Executive Order 13132. This AD will
Authority for This Rulemaking not have a substantial direct effect on 2017–22–07 Airbus: Amendment 39–19087;
the States, on the relationship between Docket No. FAA–2017–0478; Product
Title 49 of the United States Code the national government and the States, Identifier 2016–NM–174–AD.
specifies the FAA’s authority to issue or on the distribution of power and (a) Effective Date
rules on aviation safety. Subtitle I, responsibilities among the various
section 106, describes the authority of This AD is effective January 2, 2018.
levels of government.
the FAA Administrator. ‘‘Subtitle VII: For the reasons discussed above, I (b) Affected ADs
Aviation Programs,’’ describes in more certify that this AD: None.
detail the scope of the Agency’s 1. Is not a ‘‘significant regulatory (c) Applicability
authority. action’’ under Executive Order 12866; This AD applies to Airbus Model A319–
We are issuing this rulemaking under 2. Is not a ‘‘significant rule’’ under the 111, –112, –113, –114, –115, –131, –132, and
the authority described in ‘‘Subtitle VII, DOT Regulatory Policies and Procedures –133 airplanes; Model A320–211, –212, –214,
Part A, Subpart III, Section 44701: (44 FR 11034, February 26, 1979); –231, –232, and –233 airplanes; and Model
General requirements.’’ Under that 3. Will not affect intrastate aviation in A321–111, –112, –131, –211, –212, –213,
section, Congress charges the FAA with –231, and –232 airplanes, certificated in any
Alaska; and category, manufacturer serial numbers
promoting safe flight of civil aircraft in 4. Will not have a significant
air commerce by prescribing regulations through 0758 inclusive.
economic impact, positive or negative,
for practices, methods, and procedures on a substantial number of small entities (d) Subject
the Administrator finds necessary for under the criteria of the Regulatory Air Transport Association (ATA) of
safety in air commerce. This regulation Flexibility Act. America Code 52, Doors.
is within the scope of that authority (e) Reason
because it addresses an unsafe condition List of Subjects in 14 CFR Part 39
that is likely to exist or develop on This AD was prompted by a report of
Air transportation, Aircraft, Aviation cracks on the frame forks and outer skin on
products identified in this rulemaking safety, Incorporation by reference, the forward and aft cargo compartment doors.
action. Safety. We are issuing this AD to detect and correct
This AD is issued in accordance with cracks on the frame forks and outer skin on
authority delegated by the Executive Adoption of the Amendment the forward and aft cargo compartment doors,
Director, Aircraft Certification Service, which could lead to reduced structural
Accordingly, under the authority
integrity and failure of the cargo
as authorized by FAA Order 8000.51C. delegated to me by the Administrator, compartment door, possible decompression
In accordance with that order, issuance the FAA amends 14 CFR part 39 as of the airplane, and injury to occupants.
of ADs is normally a function of the follows:
jstallworth on DSKBBY8HB2PROD with RULES
Compliance and Airworthiness (f) Compliance
Division, but during this transition PART 39—AIRWORTHINESS Comply with this AD within the
period, the Executive Director has DIRECTIVES compliance times specified, unless already
done.
delegated the authority to issue ADs
applicable to transport category ■ 1. The authority citation for part 39 (g) Definition of Affected Door
airplanes to the Director of the System continues to read as follows: For the purpose of this AD, an ‘‘affected
Oversight Division. Authority: 49 U.S.C. 106(g), 40113, 44701. door’’ is a forward or aft cargo compartment
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![Federal Register / Vol. 82, No. 227 / Tuesday, November 28, 2017 / Rules and Regulations 56163
(l) No Reporting Requirement with the operator’s maintenance or DEPARTMENT OF TRANSPORTATION
Although Airbus Service Bulletin A320– inspection program without obtaining
52–1171, Revision 02, dated April 10, 2017, approval of an AMOC, provided the Federal Aviation Administration
specifies to submit certain information to the procedures and tests identified as RC can be
manufacturer, and specifies that action as done and the airplane can be put back in an
airworthy condition. Any substitutions or
14 CFR Part 39
‘‘RC,’’ this AD does not include that
requirement. changes to procedures or tests identified as [Docket No. FAA–2017–0933; Product
RC require approval of an AMOC. Identifier 2017–SW–051–AD; Amendment
(m) Credit for Previous Actions 39–19106; AD 2017–24–02]
(p) Related Information
(1) This paragraph provides credit for the
(1) Refer to Mandatory Continuing RIN 2120–AA64
actions required by paragraphs (h) and (i) of
this AD, if those actions were performed Airworthiness Information (MCAI) EASA AD
before the effective date of this AD using 2016–0187, dated September 19, 2016, for Airworthiness Directives; Airbus
Airbus Service Bulletin A320–52–1171, related information. This MCAI may be Helicopters Deutschland GmbH
dated October 29, 2015, provided that it can found in the AD docket on the Internet at Helicopters
be conclusively determined that any part http://www.regulations.gov by searching for
number D52371000018 was also inspected as and locating Docket No. FAA–2017–0478. AGENCY: Federal Aviation
specified in paragraph (h) of this AD. (2) For more information about this AD, Administration (FAA), Department of
(2) This paragraph provides credit for the contact Sanjay Ralhan, Aerospace Engineer, Transportation (DOT).
actions required by paragraphs (h) and (i) of International Section, Transport Standards
ACTION: Final rule; request for
this AD, if those actions were performed Branch, FAA, 1601 Lind Avenue SW.,
Renton, WA 98057–3356; telephone: 425– comments.
before the effective date of this AD using
Airbus Service Bulletin A320–52–1171, 227–1405; fax: 425–227–1149.
(3) Service information identified in this SUMMARY: We are adopting a new
Revision 01, dated September 5, 2016. airworthiness directive (AD) for Airbus
AD that is not incorporated by reference is
(n) Parts Installation Limitation available at the addresses specified in Helicopters Deutschland GmbH (Airbus
As of the effective date of this AD, no paragraphs (q)(3) and (q)(4) of this AD. Helicopters) Model MBB–BK 117 D–2
person may install, on any airplane, an (q) Material Incorporated by Reference
helicopters. This AD requires amending
affected door specified in paragraph (g) of the rotorcraft flight manual to establish
this AD, unless it has been inspected in (1) The Director of the Federal Register a minimum airspeed limitation for the
accordance with the requirements of approved the incorporation by reference
(IBR) of the service information listed in this autopilot cruise height mode. This AD
paragraph (h) of this AD and all applicable is prompted by two reports of
paragraph under 5 U.S.C. 552(a) and 1 CFR
corrective actions have been done in uncommanded helicopter climbs and
part 51.
accordance with paragraph (i) of this AD.
(2) You must use this service information descents. The actions of this AD are
(o) Other FAA AD Provisions as applicable to do the actions required by intended to address an unsafe condition
The following provisions also apply to this this AD, unless this AD specifies otherwise. on these products.
AD: (i) Airbus Service Bulletin A320–52–1042,
DATES: This AD becomes effective
(1) Alternative Methods of Compliance Revision 2, dated January 14, 1997 (pages 5,
9, and 19 through 22 of this document are December 13, 2017.
(AMOCs): The Manager, International The Director of the Federal Register
Section, Transport Standards Branch, FAA, identified as Revision 1, dated November 22,
1993). approved the incorporation by reference
has the authority to approve AMOCs for this
AD, if requested using the procedures found (ii) Airbus Service Bulletin A320–52–1170, of certain documents listed in this AD
in 14 CFR 39.19. In accordance with 14 CFR dated September 5, 2016, including as of December 13, 2017.
39.19, send your request to your principal Appendices 01 and 02, dated September 5, We must receive comments on this
inspector or local Flight Standards District 2016. AD by January 29, 2018.
Office, as appropriate. If sending information (iii) Airbus Service Bulletin A320–52–
ADDRESSES: You may send comments by
directly to the International Section, send it 1171, Revision 02, dated April 10, 2017.
(3) For service information identified in any of the following methods:
to the attention of the person identified in
this AD, contact Airbus, Airworthiness • Federal eRulemaking Docket: Go to
paragraph (p)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOC- Office—EIAS, 1 Rond Point Maurice http://www.regulations.gov. Follow the
REQUESTS@faa.gov. Before using any Bellonte, 31707 Blagnac Cedex, France; online instructions for sending your
approved AMOC, notify your appropriate telephone: +33 5 61 93 36 96; fax: +33 5 61 comments electronically.
principal inspector, or lacking a principal 93 44 51; email: account.airworth-eas@ • Fax: 202–493–2251.
inspector, the manager of the local flight airbus.com; Internet: http://www.airbus.com. • Mail: Send comments to the U.S.
standards district office/certificate holding (4) You may view this service information
Department of Transportation, Docket
district office. at the FAA, Transport Standards Branch,
1601 Lind Avenue SW., Renton, WA. For Operations, M–30, West Building
(2) Contacting the Manufacturer: For any Ground Floor, Room W12–140, 1200
requirement in this AD to obtain corrective information on the availability of this
material at the FAA, call 425–227–1221. New Jersey Avenue SE., Washington,
actions from a manufacturer, the action must
be accomplished using a method approved (5) You may view this service information DC 20590–0001.
by the Manager, International Section, that is incorporated by reference at the • Hand Delivery: Deliver to the
Transport Standards Branch, FAA; or EASA; National Archives and Records ‘‘Mail’’ address between 9 a.m. and 5
or Airbus’s EASA DOA. If approved by the Administration (NARA). For information on p.m., Monday through Friday, except
DOA, the approval must include the DOA- the availability of this material at NARA, call Federal holidays.
authorized signature. 202–741–6030, or go to: http://
(3) Required for Compliance (RC): Except www.archives.gov/federal-register/cfr/ibr- Examining the AD Docket
as specified in paragraphs (k) and (l) of this locations.html.
You may examine the AD docket on
jstallworth on DSKBBY8HB2PROD with RULES
AD: If any service information contains Issued in Renton, Washington, on October the Internet at http://
procedures or tests that are identified as RC, 17, 2017. www.regulations.gov by searching for
those procedures and tests must be done to Jeffrey E. Duven,
comply with this AD; any procedures or tests and locating Docket No. FAA–2017–
Director, System Oversight Division, Aircraft 0933; or in person at the Docket
that are not identified as RC are
Certification Service. Operations Office between 9 a.m. and 5
recommended. Those procedures and tests
that are not identified as RC may be deviated [FR Doc. 2017–23349 Filed 11–27–17; 8:45 am] p.m., Monday through Friday, except
from using accepted methods in accordance BILLING CODE 4910–13–P Federal holidays. The AD docket
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Document Created: 2017-11-28 01:51:15
Document Modified: 2017-11-28 01:51:15
| 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 January 2, 2018. | |
| Contact | Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-227-1405; fax: 425- 227-1149. | |
| FR Citation | 82 FR 56158 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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