83 FR 26559 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 111 (June 8, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 111 (June 8, 2018)
| Page Range | 26559-26564 | |
| FR Document | 2018-12268 |
[Federal Register Volume 83, Number 111 (Friday, June 8, 2018)] [Rules and Regulations] [Pages 26559-26564] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2018-12268] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2017-1020; Product Identifier 2017-NM-114-AD; Amendment 39-19306; AD 2018-12-02] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for all Airbus Model A318-111 and -112 airplanes; Model A319-111, -112, -113, - 114, and -115 airplanes; Model A320-211, -212, -214, and -216 airplanes; and Model A321-111, -112, -211, -212, and -213 airplanes. This AD was prompted by a review of maintenance instructions for a blend repair of the snout diameter of the main beam assembly of the forward engine mount that would create an excessive gap between the bearing mono-ball and the snout. This AD requires modifying the main beam assembly of the forward engine mount. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective July 13, 2018. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of July 13, 2018. ADDRESSES: For Airbus 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. For Goodrich service information identified in this final rule, contact Goodrich Corporation, Aerostructures, 850 Lagoon Drive, Chula Vista, CA 91910-2098; phone: 619-691-2719; email: [email protected]; internet: http://www.goodrich.com/TechPubs. You may view this referenced service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206-231-3195. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-1020. 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- 1020; 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, 2200 South 216th St., Des Moines, WA 98198-6547; 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 all Airbus Model A318-111 and -112 airplanes; Model A319-111, -112, -113, -114, and -115 airplanes; Model A320-211, -212, -214, and -216 airplanes; and Model A321-111, -112, -211, -212, and -213 airplanes. The NPRM published in the Federal Register on October 24, 2017 (82 FR 49146) (``the NPRM''). The NPRM was prompted by a review of maintenance instructions for a blend repair of the snout diameter of the main beam assembly of the forward engine mount that would create an excessive gap between the bearing mono-ball and the snout. The NPRM proposed to require modifying the main beam assembly of the forward engine mount. We are issuing this AD to prevent in-flight failure of a forward engine mount, and consequent detachment of an engine, which could result in reduced controllability 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 AD 2017-0132R1, dated November 22, 2017 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for all Airbus Model A318-111 and -112 airplanes; Model A319-111, -112, -113, -114, and -115 airplanes; Model A320-211, -212, -214, and -216 airplanes; and Model A321-111, -112, - 211, -212, and -213 airplanes. The MCAI states: A review of maintenance instructions revealed that the Goodrich Aerospace CFM56-5B, Forward Engine Mount Component Maintenance Manual (CMM) 71-21-08, revision (rev.) 1 up to 46 (inclusive), repair 10 (Blend Repair-Beam Assembly Snout Diameter), provides instructions to blend the wear on the forward engine mount assembly, Part Number (P/N) 642-2000-9, 642-2000-13, or 642-2000-25, creating an excessive gap between the bearing mono-ball and the snout of the forward engine mount main beam assembly, P/N 642-2006-501, or P/N 642-2006-503. This condition, if not detected and corrected, could lead to in- flight failure of a forward engine mount and consequent detachment of an engine, possibly resulting in reduced control of the aeroplane and injury to persons on the ground. To address this potential unsafe condition, Airbus issued Service Bulletin (SB) A320-71-1065 and SB A320-71-1066, and [[Page 26560]] Goodrich Aerospace issued SB RA32071-159, providing instructions for an in-shop inspection(s) for the main beam snout and, depending on findings, applicable corrective action(s) and re-identification. Consequently, EASA issued AD 2017-0132, requiring replacement of the affected forward engine mount main beam assemblies. As the same main beam assemblies are certified for CFM56-5A engine installation, that [EASA] AD also applied to aeroplanes with that engine. Since that [EASA] AD was issued, it was determined that, for aeroplanes equipped with an affected forward engine mount main beam assembly, installation of an affected assembly can still be allowed until replacement, as required by this [EASA] AD. For the reason described above, this [EASA] AD is revised accordingly. Required actions include modifying the main beam assembly of the forward engine mount. The modification includes repairing, replacing, or reworking the main beam assembly. 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-2017-1020. 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. Support for the NPRM The Air Line Pilots Association, International (ALPA) and Jake Watson stated their support for the proposed AD. American Airlines (AAL) stated that it has no objection to the intent of the NPRM. Request To Use Revised Vendor Service Information AAL stated that the proposed AD should require Goodrich Aerospace Service Bulletin RA32071-159, Rev 1, dated July 25, 2017 (``SB RA32071- 159 Rev 1''), which corrects part number references, revises illustrations, and clarifies the procedure. Alternatively, AAL asserted that the proposed AD should allow the use of RA32071-159 Rev 1, or later revisions. AAL stated that Goodrich Aerospace Service Bulletin RA32071-159, dated November 20, 2016, is not useable due to multiple issues. We do not agree to require RA32071-159 Rev 1. Goodrich Aerospace Service Bulletin RA32071-159 is referenced as an additional source of guidance in Airbus Service Bulletin A320-71-1065, Revision 01, dated July 28, 2017; and Airbus Service Bulletin A320-71-1066, dated December 1, 2016; for inspecting and corrective actions. We acknowledge that RA32071-159 Rev 1 contains several improvements. Therefore, we recommend operators incorporate the latest approved service information. However, in paragraphs (g)(2)(ii) and (h) of this AD, we refer to ``Goodrich Aerospace Service Bulletin RA32071-159'' and not to any specific revision. Therefore, we have not changed this AD in this regard. Request To Exclude Certain Actions AAL stated that Goodrich Aerospace Service Bulletin RA32071-159 requires operators to ``fully disassemble the engine mount assembly'', which is not necessary for the dimensional inspection of the snout. AAL noted that, as long as the mount is not installed on the engine, the bearing assembly can be removed to expose the snout, clean, and measure the snout. AAL added that if an operator is forced to fully disassemble the mount, it will drive the mount to an overhaul, which is time consuming and costly. We infer that the commenter is asking that we exclude full disassembly of the engine mount assembly from the inspection specified in paragraph (h) of the proposed AD. We do not agree. Neither Airbus nor the state of design authority, EASA, has informed the FAA that the snout diameter can be conclusively measured without full disassembly of the engine mount assembly. AAL did not provide any justification supported by approval from EASA; or Airbus's EASA Design Organization Approval (DOA) to allow deviation from the required for compliance section of the service information. However, under the provisions of paragraph (n) of this AD, we will consider requests for approval of an alternative method of compliance if sufficient data are submitted to substantiate that a deviation would provide an acceptable level of safety. We have made no change to this AD in this regard. Request To Compel Goodrich Aerospace To Use ``Required for Compliance (RC)'' Language in Goodrich Aerospace Service Bulletin RA32071-159 AAL also asked that the FAA compel Goodrich Aerospace to incorporate FAA Advisory Circular 20-176A, dated June 16, 2014, into Goodrich Aerospace Service Bulletin RA32071-159 for the purpose of ``. . . distinguishing which steps in an SB will have a direct effect on detecting, preventing, resolving, or eliminating the unsafe condition identified in an AD.'' AAL asserted that Goodrich Aerospace has had 7 years to evaluate and incorporate the best practices for drafting service bulletins related to ADs. We disagree with the commenter's request. FAA Advisory Circular 20- 176A, dated June 16, 2014, provides best practices for drafting service bulletins related to ADs. Although we recommend that the original equipment manufacturer (OEM) specify ``RC'' steps in service information, the FAA advisory circular is not mandatory, only a recommendation as best practices. We have not changed this AD in this regard. Request To Remove Revision Level for Vendor Service Information Delta Airlines (Delta) asked that the proposed AD not specify a revision level for Goodrich Aerospace Service Bulletin RA32071-159. Delta added that, if one must be specified, all revisions published prior to the effective date of the AD should be acceptable methods of compliance. We agree with the commenter's request that the revision level of Goodrich Aerospace Service Bulletin RA32071-159 not be specified. As previously explained, this AD does not specify a revision level for Goodrich Aerospace Service Bulletin RA32071-159. Therefore, no change to this AD is necessary in this regard. Request To Specify Confirmation That a Certain Discrepant Repair Has Never Been Installed Delta requested that paragraph (g)(1) of the proposed AD be revised to specify that maintenance records must confirm that Repair 10 of Component Maintenance Manual (CMM) 71-21-08, Revisions 1 through 46, has never been performed. Delta stated that, based on the NPRM and service information, it is clear that the discrepant repair is Repair 10 of CMM 71-21-08, Revisions 1 through 46. Delta added that paragraph (g)(1) of the proposed AD does not specify that maintenance records must show only that forward mount main beams have not been repaired per the discrepant Repair 10 of CMM 71-21-08, Revisions 1 through 46, which would classify them as affected main beams. We disagree with the commenter's request; however, we provide the following clarification. The intent of paragraph (g)(1) of this AD is that if no maintenance record exists then there is a possibility that the main beam has been repaired using Repair 10 of CMM 71-21-08 Revisions 1 through 46, and, therefore, qualifies as an ``affected main beam.'' We have not changed this AD in this regard. [[Page 26561]] Request To Apply Exceptions to Parts Without Maintenance Records of Repair History Delta asked that the exceptions in paragraphs (g)(2)(i) through (g)(2)(iii) of the proposed AD also apply to parts for which maintenance records are not available to confirm repair history. Delta stated that this will account for mounts that are not installed on-wing and future spare purchases. Delta added that paragraph (g)(2) of the proposed AD does not permit parts with unknown repair history to be excluded if the criteria in paragraphs (g)(2)(i) through (g)(2)(iii) of the proposed AD are met. Delta noted that paragraph (g)(1) of the proposed AD, parts with unknown repair history, are considered ``affected main beams'' and have the same compliance requirements as parts that have been repaired per discrepant Repair 10 of CMM 71-21-08, Revisions 1 through 46. We do not agree with the commenter's request. Exceptions in paragraphs (g)(2)(i) through (g)(2)(iii) of this AD are based on the fact that maintenance records exist. Therefore, these exceptions do not apply to parts with unknown repair history in paragraph (g)(1) of this AD. We have not changed this AD in this regard. Requests To Use Later Revisions of CMM Repairs Delta and Lufthansa Technik (Lufthansa) asked that we allow use of later revisions of the CMM repairs in paragraphs (g)(2)(ii) and (h) of the proposed AD. Delta noted that paragraph (g)(2)(ii) doesn't specify that a repair per the corrected Repair 10 of CMM 71-21-08, Revision 47 (and later), or Repair 21 of CMM 71-21-06, Revision 59 (and later), excludes forward mount main beams from the effectivity. Delta added that the dimensional requirements of corrected Repair 10 and Repair 21 are equivalent to the requirements of Goodrich Aerospace Service Bulletin RA32071-159, and ensure that any main beams repaired will meet the intent of the proposed AD. Delta stated that paragraph (h) of the proposed AD doesn't specify that a qualifying inspection can be done as specified in the instructions of the later revisions of CMMs 71-21-08 and 71-21-06 that introduced the corrected Repair 10 and Repair 21. Delta explained that CMM 71-21-08, Revision 48 (and later), and CMM 71-21-06, Revision 60 (and later), contain the correct snout diameters as specified in Repair 10 of CMM 71-21-08, Revision 47, and Repair 21 of CMM 71-21-06, Revision 59. Delta further noted that EASA AD 2017-0132R1, dated November 22, 2017, permits the use of later revisions of the CMMs with corrected Repairs 10 and 21. We disagree with the commenters' requests. We cannot use the phrase, ``or later approved revisions,'' in an AD when referring to the service document because doing so violates Office of the Federal Register (OFR) regulations for approval of materials ``incorporated by reference'' in rules. In general terms, we are required by these OFR regulations to either publish the service document contents as part of the actual AD language; or submit the service document to the OFR for approval as ``referenced'' material, in which case we may only refer to such material in the text of an AD. The AD may refer to the service document only if the OFR approved it for ``incorporation by reference.'' To allow operators to use later revisions of the referenced document (issued after publication of the AD), either we must revise the AD to reference specific later revisions, or operators must request approval to use later revisions as an alternative method of compliance (AMOC) with this AD under the provisions of paragraph (n) of this AD. We have not changed this AD in this regard. Request To Define Airplane Group Delta asked that paragraph (i) of the proposed AD clarify that airplanes on which the main beams have never been replaced are considered Group 2 airplanes. Delta stated that paragraph (i) of the proposed AD doesn't specify that airplanes on which the main beams have never been replaced (and thus never repaired) since aircraft delivery should be considered Group 2 airplanes. Delta added that an airplane on which the forward mounts have never been replaced since aircraft delivery will not have the discrepant Repair 10 of CMM 71-21-08, Revisions 1 through 46. We do not agree to revise paragraph (i) of this AD; however, we have clarified the airplane group as follows. Paragraph (i) of this AD specifies Group 2 airplanes are airplanes on which an affected main beam has not been installed as of the effective date of this AD. Therefore, airplanes with main beams that have never been replaced since aircraft delivery might be considered Group 2 airplanes, if the original main beam is not an affected main beam as defined in paragraph (g) of this AD. However, if for example, an airplane with main beams that have never been replaced does not have maintenance records to conclusively confirm the part has never been repaired, as specified in paragraph (g)(1) of this AD, then it is a Group 1 airplane. We have not changed this AD in this regard. Request To Change ``Modify'' to ``Inspect and Disposition'' Delta asked that the proposed AD use the language ``inspect and disposition'' instead of ``modify'' to describe the action required by paragraph (j) of the proposed AD. Additionally, Delta asked that the proposed AD specify that replacement of a forward mount assembly containing an affected main beam with a forward mount assembly that contains an AD-compliant main beam is an acceptable means of compliance. Delta stated that paragraph (j) of the proposed AD uses the term ``modify'' to describe compliance with the requirements of the inspection and repair of the mounts. Delta added that, based on the instructions in the service information, the intent of the work instructions is to inspect affected main beams and disposition based on inspection findings; the dispositions range from scrapping the main beam to blending, based on measured snout diameter. Delta noted that the replacement of a forward mount assembly that contains an affected main beam with a forward mount assembly with an AD-compliant main beam meets the intent of the proposed AD to remove affected main beams from service. We partially agree. We do not agree to replace ``modify'' with ``inspect and disposition,'' because corrective action cannot be defined by the term ``disposition,'' which is open to interpretation. Operators must follow the instructions in the Airbus service information referenced in paragraph (j) of this AD for the applicable method of compliance. However, we acknowledge that, while the Accomplishment Instructions of Airbus Service Bulletin A320-71-1066, dated December 1, 2016, specify to do a ``Modification of the FWD Engine Mount Assembly on Engine 1 and Engine 2,'' the Accomplishment Instructions of Airbus Service Bulletin A320-71-1065, Revision 01, dated July 28, 2017, specify to do inspections and applicable corrective actions. Therefore, we have changed paragraph (j) of this AD to replace ``modify'' with ``modify, including doing all applicable inspections and corrective actions.'' Request To Include Goodrich Aerospace Service Bulletin for the Required Modification Lufthansa requested that we include Goodrich Aerospace Service Bulletin [[Page 26562]] RA32071-159 in paragraph (j) of the proposed AD to ``make it more clear.'' We do not agree. The commenter provided no explanation of what is unclear in paragraph (j) or how adding the Goodrich Aerospace service bulletin will clarify the requirements of paragraph (j). Therefore, we have not changed this AD in this regard. Requests To Provide Credit for Previous Actions Done Using Other Service Information Delta and Lufthansa asked that the proposed AD include credit for doing previous actions by accomplishing Goodrich Aerospace Service Bulletin RA32071-159; Repair 10 of CMM 71-21-08, Revision 47 (and later); or Repair 21 of CMM 71-21-06, Revision 59 (and later). Delta stated that paragraph (l) of the proposed AD includes credit for previous actions only for compliance with Airbus Service Bulletin A320- 71-1065, Revision 01, dated July 28, 2017. Delta asserted that the intent of the proposed AD is met by the accomplishment of Goodrich Aerospace Service Bulletin RA32071-159; Repair 10 of CMM 71-21-08, Revision 47 (and later); or Repair 21 of CMM 71-21-06, Revision 59 (and later); due to the correction of the inspection and repair requirements. We do not agree with the commenter's request. Goodrich Aerospace Service Bulletin RA32071-159 is referenced in the airplane level Airbus service information as a secondary document; therefore, it is not an alternate for the instructions in the airplane level service information. All of the steps in paragraph 3.C. of Airbus Service Bulletin A320-71-1065, Revision 01, dated July 28, 2017, are required for compliance and must be done to comply with this AD. If not done before the effective date of this AD, paragraph (f) of this AD states that you must comply with the actions in the AD, ``unless already done.'' Regarding future revisions of CMM repairs, we may not refer to any document that does not yet exist. To allow operators to use later revisions of a required document (issued after publication of the AD), either we must revise the AD to reference specific later revisions, or operators must request approval to use later revisions as an alternative method of compliance with the requirements of an AD under the provisions of the AMOC paragraph of the AD. However, as explained previously, the identified CMM repairs are not required for accomplishment of any action in this AD; therefore, no change to this AD is necessary in this regard. Request To Change Parts Installation Prohibition Delta asked that paragraph (m) of the proposed AD, ``Parts Installation Prohibition,'' be changed to permit the same allowance to install an affected main beam onto an aircraft equipped with an affected forward engine mount assembly within the compliance windows defined in paragraph (j) of the proposed AD. Delta stated that paragraph (m) of the proposed AD prohibits the installation of an affected main beam on any airplane after the effective date of the AD. Delta further points out that the parallel EASA AD 2017-0132R1, dated November 22, 2017, permits the installation of an affected main beam onto an aircraft equipped with an affected forward engine mount assembly within the compliance times defined in paragraph (j) of the proposed AD. We agree with the commenter's request. After the NPRM was issued, EASA issued AD 2017-0132R1, dated November 22, 2017, which revised its parts installation requirement. We have revised paragraph (m) of this AD to match the EASA AD. In addition, we have revised this AD to refer to EASA AD 2017-0132R1, dated November 22, 2017. 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, with 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 Service Bulletin A320-71-1065, Revision 01, dated July 28, 2017. This service information describes procedures for modifying the main beam assembly of the forward engine mount. The modification includes, among other things, repair or replacement of the main beam assembly. Airbus has also issued Service Bulletin A320-71-1066, dated December 1, 2016. This service information describes procedures for modifying the main beam assembly of the forward engine mount. The modification includes, among other things, rework of the main beam assembly. 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 500 airplanes of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Modification.................. Up to 76 work-hours $778 Up to $7,238........ Up to $3,619,000. x $85 per hour = $6,460. ---------------------------------------------------------------------------------------------------------------- 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. [[Page 26563]] 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): 2018-12-02 Airbus: Amendment 39-19306; Docket No. FAA-2017-1020; Product Identifier 2017-NM-114-AD. (a) Effective Date This AD is effective July 13, 2018. (b) Affected ADs None. (c) Applicability This AD applies to all Airbus Model A318-111 and -112 airplanes; Model A319-111, -112, -113, -114, and -115 airplanes; Model A320- 211, -212, -214, and -216 airplanes; and Model A321-111, -112, -211, -212, and -213 airplanes; certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 71, Powerplant. (e) Reason This AD was prompted by a review of maintenance instructions for a blend repair of the diameter of the snout of the main beam assembly of the forward engine mount that would create an excessive gap between the bearing mono-ball and the snout. We are issuing this AD to prevent in-flight failure of a forward engine mount, and consequent detachment of an engine, which could result in reduced controllability of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Definition of Affected Parts For the purposes of this AD: An ``affected main beam'' is any main beam assembly of the forward engine mount, part number (P/N) 642-2006-501 or P/N 642-2006-503, identified in paragraph (g)(1) or (g)(2) of this AD. (1) Any part for which no maintenance records are available to confirm the part has never been repaired. (2) Any part that was repaired as specified in Repair 10, of Goodrich Aerospace Component Maintenance Manual (CMM) 71-21-08, Revisions 1 through 46, except for parts identified in paragraphs (g)(2)(i), (g)(2)(ii), and (g)(2)(iii) of this AD. (i) Any part on which a qualifying inspection identified in paragraph (h) of this AD has been done and there were no findings (the inspection was passed). (ii) Any part on which a qualifying inspection identified in paragraph (h) of this AD has been done and that part has been repaired as specified in Goodrich Aerospace Service Bulletin RA32071-159. (iii) Any part that has been repaired in accordance with other instructions 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). (h) Definition of Qualifying Inspection For the purposes of this AD: ``A qualifying inspection'' is an inspection done as specified in Goodrich Aerospace Service Bulletin RA32071-159; or for CFM56-5B engines, an inspection done as specified in Repair 10 of Goodrich Aerospace CMM 71-21-08, Revision 47; or for CFM56-5A engines, an inspection done as specified in Repair 21 of Goodrich Aerospace CMM 71-21-06, Revision 59. (i) Definition of Airplane Groups For the purposes of this AD: ``Group 1 airplanes'' are airplanes on which an affected main beam has been installed as of the effective date of this AD. ``Group 2 airplanes'' are airplanes on which an affected main beam has not been installed as of the effective date of this AD; this includes airplanes with an original certificate of airworthiness or original export certificate of airworthiness that was issued after the effective date of this AD. (j) Modification of Affected Main Beam Assemblies For Group 1 airplanes as identified in paragraph (i) of this AD: At the earliest of the compliance times specified in paragraphs (j)(1), (j)(2), and (j)(3) of this AD, modify, including doing all applicable inspections and corrective actions, for each affected main beam identified in paragraph (g) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-71- 1065, Revision 01, dated July 28, 2017; or Airbus Service Bulletin A320-71-1066, dated December 1, 2016; as applicable; except as required by paragraph (k) of this AD. (1) Within 48 months after the effective date of this AD. (2) Within 10,000 flight cycles after the effective date of this AD. (3) Within 15,000 flight hours after the effective date of this AD. (k) Exception to Service Information Where Airbus Service Bulletin A320-71-1065, Revision 01, dated July 28, 2017, specifies to contact a manufacturer 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 (n)(2) of this AD. (l) Credit for Previous Actions This paragraph provides credit for the actions required by paragraph (j) of this AD involving Airbus Service Bulletin A320-71- 1065, Revision 01, dated July 28, 2017, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320-71-1065, dated December 1, 2016. (m) Parts Installation Prohibition Do not install on any airplane an affected main beam or a forward engine mount assembly equipped with an affected main beam, as specified in paragraph (m)(1) or (m)(2) of this AD, as applicable. (1) For Group 1 airplanes: After modification of the airplane as required by paragraph (j) of this AD. (2) For Group 2 airplanes: As of the effective date of this AD. (n) 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 [[Page 26564]] directly to the manager of the International Section, send it to the attention of the person identified in paragraph (o)(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 required by paragraph (k) 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. (o) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2017-0132R1, dated November 22, 2017, 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-2017-1020. (2) For more information about this AD, contact Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198-6547; telephone 425-227-1405; fax 425-227-1149. (3) Airbus service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (p)(4) and (p)(5) of this AD. (4) Goodrich service information identified in this AD that is not incorporated by reference is available at Goodrich Corporation, Aerostructures, 850 Lagoon Drive, Chula Vista, CA 91910-2098; phone: 619-691-2719; email: [email protected]; internet: http://www.goodrich.com/TechPubs. (p) 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 A320-71-1065, Revision 01, dated July 28, 2017. (ii) Airbus Service Bulletin A320-71-1066, dated December 1, 2016. (3) For Airbus 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) For Goodrich service information identified in this final rule, contact Goodrich Corporation, Aerostructures, 850 Lagoon Drive, Chula Vista, CA 91910-2098; phone: 619-691-2719; email: [email protected]; internet: http://www.goodrich.com/TechPubs. (5) You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206-231-3195. (6) 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 Des Moines, Washington, on May 29, 2018. Jeffrey E. Duven, Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018-12268 Filed 6-7-18; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 83, No. 111 / Friday, June 8, 2018 / Rules and Regulations 26559
5313; fax: 562–627–5210; email: and Model A321–111, –112, –211, –212, 216th St., Des Moines, WA 98198–6547;
payman.soltani@faa.gov. and –213 airplanes. This AD was telephone 425–227–1405; fax 425–227–
(2) Service information identified in this prompted by a review of maintenance 1149.
AD that is not incorporated by reference is instructions for a blend repair of the
available at the addresses specified in SUPPLEMENTARY INFORMATION:
paragraphs (l)(3) and (l)(4) of this AD.
snout diameter of the main beam
assembly of the forward engine mount Discussion
(l) Material Incorporated by Reference that would create an excessive gap We issued a notice of proposed
(1) The Director of the Federal Register between the bearing mono-ball and the rulemaking (NPRM) to amend 14 CFR
approved the incorporation by reference snout. This AD requires modifying the part 39 by adding an AD that would
(IBR) of the service information listed in this main beam assembly of the forward apply to all Airbus Model A318–111
paragraph under 5 U.S.C. 552(a) and 1 CFR engine mount. We are issuing this AD and –112 airplanes; Model A319–111,
part 51. to address the unsafe condition on these
(2) You must use this service information –112, –113, –114, and –115 airplanes;
as applicable to do the actions required by
products. Model A320–211, –212, –214, and –216
this AD, unless the AD specifies otherwise. DATES: This AD is effective July 13, airplanes; and Model A321–111, –112,
(i) Boeing Alert Requirements Bulletin 2018. –211, –212, and –213 airplanes. The
737–57A1337 RB, dated September 14, 2017. The Director of the Federal Register NPRM published in the Federal
(ii) Reserved. approved the incorporation by reference Register on October 24, 2017 (82 FR
(3) For service information identified in of certain publications listed in this AD 49146) (‘‘the NPRM’’). The NPRM was
this AD, contact Boeing Commercial as of July 13, 2018. prompted by a review of maintenance
Airplanes, Attention: Contractual & Data instructions for a blend repair of the
ADDRESSES: For Airbus service
Services (C&DS), 2600 Westminster Blvd.,
MC 110–SK57, Seal Beach, CA 90740–5600; information identified in this final rule, snout diameter of the main beam
telephone 562–797–1717; internet https:// contact Airbus, Airworthiness Office– assembly of the forward engine mount
www.myboeingfleet.com. EIAS, 1 Rond Point Maurice Bellonte, that would create an excessive gap
(4) You may view this service information 31707 Blagnac Cedex, France; between the bearing mono-ball and the
at the FAA, Transport Standards Branch, telephone: +33 5 61 93 36 96; fax: +33 snout. The NPRM proposed to require
2200 South 216th St., Des Moines, WA. For 5 61 93 44 51; email: account.airworth- modifying the main beam assembly of
information on the availability of this eas@airbus.com; internet: http:// the forward engine mount. We are
material at the FAA, call 206–231–3195. issuing this AD to prevent in-flight
www.airbus.com. For Goodrich service
(5) You may view this service information failure of a forward engine mount, and
that is incorporated by reference at the information identified in this final rule,
National Archives and Records contact Goodrich Corporation, consequent detachment of an engine,
Administration (NARA). For information on Aerostructures, 850 Lagoon Drive, Chula which could result in reduced
the availability of this material at NARA, call Vista, CA 91910–2098; phone: 619–691– controllability of the airplane.
202–741–6030, or go to: http:// 2719; email: jan.lewis@goodrich.com; The European Aviation Safety Agency
www.archives.gov/federal-register/cfr/ibr- internet: http://www.goodrich.com/ (EASA), which is the Technical Agent
locations.html. TechPubs. You may view this for the Member States of the European
Issued in Des Moines, Washington, on May referenced service information at the Union, has issued EASA AD 2017–
31, 2018. FAA, Transport Standards Branch, 2200 0132R1, dated November 22, 2017
Michael Kaszycki, South 216th St., Des Moines, WA. For (referred to after this as the Mandatory
Acting Director, System Oversight Division, information on the availability of this Continuing Airworthiness Information,
Aircraft Certification Service. material at the FAA, call 206–231–3195. or ‘‘the MCAI’’), to correct an unsafe
[FR Doc. 2018–12279 Filed 6–7–18; 8:45 am] It is also available on the internet at condition for all Airbus Model A318–
BILLING CODE 4910–13–P http://www.regulations.gov by searching 111 and –112 airplanes; Model A319–
for and locating Docket No. FAA–2017– 111, –112, –113, –114, and –115
1020. airplanes; Model A320–211, –212, –214,
DEPARTMENT OF TRANSPORTATION and –216 airplanes; and Model A321–
Examining the AD Docket 111, –112, –211, –212, and –213
Federal Aviation Administration You may examine the AD docket on airplanes. The MCAI states:
the internet at http:// A review of maintenance instructions
14 CFR Part 39 www.regulations.gov by searching for revealed that the Goodrich Aerospace
and locating Docket No. FAA–2017– CFM56–5B, Forward Engine Mount
[Docket No. FAA–2017–1020; Product
Identifier 2017–NM–114–AD; Amendment
1020; or in person at the Docket Component Maintenance Manual (CMM) 71–
39–19306; AD 2018–12–02] Management Facility between 9 a.m. 21–08, revision (rev.) 1 up to 46 (inclusive),
and 5 p.m., Monday through Friday, repair 10 (Blend Repair-Beam Assembly
RIN 2120–AA64 except Federal holidays. The AD docket Snout Diameter), provides instructions to
contains this AD, the regulatory blend the wear on the forward engine mount
Airworthiness Directives; Airbus assembly, Part Number (P/N) 642–2000–9,
evaluation, any comments received, and 642–2000–13, or 642–2000–25, creating an
Airplanes other information. The street address for excessive gap between the bearing mono-ball
AGENCY: Federal Aviation the Docket Office (telephone 800–647– and the snout of the forward engine mount
Administration (FAA), Department of 5527) is Docket Management Facility, main beam assembly, P/N 642–2006–501, or
Transportation (DOT). U.S. Department of Transportation, P/N 642–2006–503.
ACTION: Final rule.
Docket Operations, M–30, West This condition, if not detected and
Building Ground Floor, Room W12–140, corrected, could lead to in-flight failure of a
amozie on DSK3GDR082PROD with RULES
1200 New Jersey Avenue SE, forward engine mount and consequent
SUMMARY: We are adopting a new
Washington, DC 20590. detachment of an engine, possibly resulting
airworthiness directive (AD) for all in reduced control of the aeroplane and
Airbus Model A318–111 and –112 FOR FURTHER INFORMATION CONTACT: injury to persons on the ground.
airplanes; Model A319–111, –112, –113, Sanjay Ralhan, Aerospace Engineer, To address this potential unsafe condition,
–114, and –115 airplanes; Model A320– International Section, Transport Airbus issued Service Bulletin (SB) A320–
211, –212, –214, and –216 airplanes; Standards Branch, FAA, 2200 South 71–1065 and SB A320–71–1066, and
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![26560 Federal Register / Vol. 83, No. 111 / Friday, June 8, 2018 / Rules and Regulations
Goodrich Aerospace issued SB RA32071– that RA32071–159 Rev 1 contains practices for drafting service bulletins
159, providing instructions for an in-shop several improvements. Therefore, we related to ADs.
inspection(s) for the main beam snout and, recommend operators incorporate the
depending on findings, applicable corrective We disagree with the commenter’s
latest approved service information. request. FAA Advisory Circular 20–
action(s) and re-identification.
Consequently, EASA issued AD 2017– However, in paragraphs (g)(2)(ii) and (h) 176A, dated June 16, 2014, provides
0132, requiring replacement of the affected of this AD, we refer to ‘‘Goodrich best practices for drafting service
forward engine mount main beam Aerospace Service Bulletin RA32071–
bulletins related to ADs. Although we
assemblies. As the same main beam 159’’ and not to any specific revision.
assemblies are certified for CFM56–5A recommend that the original equipment
Therefore, we have not changed this AD
engine installation, that [EASA] AD also manufacturer (OEM) specify ‘‘RC’’ steps
in this regard.
applied to aeroplanes with that engine. in service information, the FAA
Since that [EASA] AD was issued, it was Request To Exclude Certain Actions advisory circular is not mandatory, only
determined that, for aeroplanes equipped AAL stated that Goodrich Aerospace a recommendation as best practices. We
with an affected forward engine mount main have not changed this AD in this regard.
beam assembly, installation of an affected
Service Bulletin RA32071–159 requires
assembly can still be allowed until operators to ‘‘fully disassemble the Request To Remove Revision Level for
replacement, as required by this [EASA] AD. engine mount assembly’’, which is not Vendor Service Information
For the reason described above, this necessary for the dimensional
[EASA] AD is revised accordingly. inspection of the snout. AAL noted that, Delta Airlines (Delta) asked that the
Required actions include modifying as long as the mount is not installed on proposed AD not specify a revision level
the main beam assembly of the forward the engine, the bearing assembly can be for Goodrich Aerospace Service Bulletin
engine mount. The modification removed to expose the snout, clean, and RA32071–159. Delta added that, if one
includes repairing, replacing, or measure the snout. AAL added that if an must be specified, all revisions
reworking the main beam assembly. You operator is forced to fully disassemble published prior to the effective date of
may examine the MCAI in the AD the mount, it will drive the mount to an the AD should be acceptable methods of
docket on the internet at http:// overhaul, which is time consuming and compliance.
www.regulations.gov by searching for costly.
We infer that the commenter is asking We agree with the commenter’s
and locating Docket No. FAA–2017– request that the revision level of
1020. that we exclude full disassembly of the
engine mount assembly from the Goodrich Aerospace Service Bulletin
Comments inspection specified in paragraph (h) of RA32071–159 not be specified. As
We gave the public the opportunity to the proposed AD. We do not agree. previously explained, this AD does not
participate in developing this AD. The Neither Airbus nor the state of design specify a revision level for Goodrich
following presents the comments authority, EASA, has informed the FAA Aerospace Service Bulletin RA32071–
received on the NPRM and the FAA’s that the snout diameter can be 159. Therefore, no change to this AD is
response to each comment. conclusively measured without full necessary in this regard.
disassembly of the engine mount
Support for the NPRM Request To Specify Confirmation That
assembly. AAL did not provide any
a Certain Discrepant Repair Has Never
The Air Line Pilots Association, justification supported by approval from
Been Installed
International (ALPA) and Jake Watson EASA; or Airbus’s EASA Design
stated their support for the proposed Organization Approval (DOA) to allow Delta requested that paragraph (g)(1)
AD. American Airlines (AAL) stated deviation from the required for of the proposed AD be revised to specify
that it has no objection to the intent of compliance section of the service that maintenance records must confirm
the NPRM. information. However, under the that Repair 10 of Component
provisions of paragraph (n) of this AD, Maintenance Manual (CMM) 71–21–08,
Request To Use Revised Vendor Service we will consider requests for approval
Information Revisions 1 through 46, has never been
of an alternative method of compliance performed. Delta stated that, based on
AAL stated that the proposed AD if sufficient data are submitted to the NPRM and service information, it is
should require Goodrich Aerospace substantiate that a deviation would clear that the discrepant repair is Repair
Service Bulletin RA32071–159, Rev 1, provide an acceptable level of safety. 10 of CMM 71–21–08, Revisions 1
dated July 25, 2017 (‘‘SB RA32071–159 We have made no change to this AD in through 46. Delta added that paragraph
Rev 1’’), which corrects part number this regard. (g)(1) of the proposed AD does not
references, revises illustrations, and specify that maintenance records must
clarifies the procedure. Alternatively, Request To Compel Goodrich
Aerospace To Use ‘‘Required for show only that forward mount main
AAL asserted that the proposed AD
Compliance (RC)’’ Language in beams have not been repaired per the
should allow the use of RA32071–159
Goodrich Aerospace Service Bulletin discrepant Repair 10 of CMM 71–21–08,
Rev 1, or later revisions. AAL stated that
RA32071–159 Revisions 1 through 46, which would
Goodrich Aerospace Service Bulletin
AAL also asked that the FAA compel classify them as affected main beams.
RA32071–159, dated November 20,
2016, is not useable due to multiple Goodrich Aerospace to incorporate FAA We disagree with the commenter’s
issues. Advisory Circular 20–176A, dated June request; however, we provide the
We do not agree to require RA32071– 16, 2014, into Goodrich Aerospace following clarification. The intent of
159 Rev 1. Goodrich Aerospace Service Service Bulletin RA32071–159 for the paragraph (g)(1) of this AD is that if no
Bulletin RA32071–159 is referenced as purpose of ‘‘. . . distinguishing which maintenance record exists then there is
amozie on DSK3GDR082PROD with RULES
an additional source of guidance in steps in an SB will have a direct effect a possibility that the main beam has
Airbus Service Bulletin A320–71–1065, on detecting, preventing, resolving, or been repaired using Repair 10 of CMM
Revision 01, dated July 28, 2017; and eliminating the unsafe condition 71–21–08 Revisions 1 through 46, and,
Airbus Service Bulletin A320–71–1066, identified in an AD.’’ AAL asserted that therefore, qualifies as an ‘‘affected main
dated December 1, 2016; for inspecting Goodrich Aerospace has had 7 years to beam.’’ We have not changed this AD in
and corrective actions. We acknowledge evaluate and incorporate the best this regard.
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![Federal Register / Vol. 83, No. 111 / Friday, June 8, 2018 / Rules and Regulations 26563
This AD is issued in accordance with (c) Applicability main beam has been installed as of the
authority delegated by the Executive This AD applies to all Airbus Model A318– effective date of this AD. ‘‘Group 2 airplanes’’
Director, Aircraft Certification Service, 111 and –112 airplanes; Model A319–111, are airplanes on which an affected main
–112, –113, –114, and –115 airplanes; Model beam has not been installed as of the
as authorized by FAA Order 8000.51C. effective date of this AD; this includes
In accordance with that order, issuance A320–211, –212, –214, and –216 airplanes;
and Model A321–111, –112, –211, –212, and airplanes with an original certificate of
of ADs is normally a function of the airworthiness or original export certificate of
–213 airplanes; certificated in any category.
Compliance and Airworthiness airworthiness that was issued after the
Division, but during this transition (d) Subject effective date of this AD.
period, the Executive Director has Air Transport Association (ATA) of (j) Modification of Affected Main Beam
delegated the authority to issue ADs America Code 71, Powerplant. Assemblies
applicable to transport category (e) Reason For Group 1 airplanes as identified in
airplanes to the Director of the System paragraph (i) of this AD: At the earliest of the
This AD was prompted by a review of
Oversight Division. maintenance instructions for a blend repair compliance times specified in paragraphs
Regulatory Findings of the diameter of the snout of the main beam (j)(1), (j)(2), and (j)(3) of this AD, modify,
assembly of the forward engine mount that including doing all applicable inspections
We determined that this AD will not would create an excessive gap between the and corrective actions, for each affected main
have federalism implications under bearing mono-ball and the snout. We are beam identified in paragraph (g) of this AD,
Executive Order 13132. This AD will issuing this AD to prevent in-flight failure of in accordance with the Accomplishment
not have a substantial direct effect on a forward engine mount, and consequent Instructions of Airbus Service Bulletin A320–
the States, on the relationship between detachment of an engine, which could result 71–1065, Revision 01, dated July 28, 2017; or
in reduced controllability of the airplane. Airbus Service Bulletin A320–71–1066,
the national government and the States, dated December 1, 2016; as applicable;
or on the distribution of power and (f) Compliance except as required by paragraph (k) of this
responsibilities among the various Comply with this AD within the AD.
levels of government. compliance times specified, unless already (1) Within 48 months after the effective
For the reasons discussed above, I done. date of this AD.
certify that this AD: (2) Within 10,000 flight cycles after the
(g) Definition of Affected Parts effective date of this AD.
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866, For the purposes of this AD: An ‘‘affected (3) Within 15,000 flight hours after the
2. Is not a ‘‘significant rule’’ under the main beam’’ is any main beam assembly of effective date of this AD.
the forward engine mount, part number (P/
DOT Regulatory Policies and Procedures (k) Exception to Service Information
N) 642–2006–501 or P/N 642–2006–503,
(44 FR 11034, February 26, 1979), identified in paragraph (g)(1) or (g)(2) of this Where Airbus Service Bulletin A320–71–
3. Will not affect intrastate aviation in AD. 1065, Revision 01, dated July 28, 2017,
Alaska, and (1) Any part for which no maintenance specifies to contact a manufacturer for
4. Will not have a significant records are available to confirm the part has appropriate action, and specifies that action
economic impact, positive or negative, never been repaired. as ‘‘RC’’ (Required for Compliance): Before
on a substantial number of small entities (2) Any part that was repaired as specified further flight, accomplish corrective actions
under the criteria of the Regulatory in Repair 10, of Goodrich Aerospace in accordance with the procedures specified
Flexibility Act. Component Maintenance Manual (CMM) 71– in paragraph (n)(2) of this AD.
21–08, Revisions 1 through 46, except for
(l) Credit for Previous Actions
List of Subjects in 14 CFR Part 39 parts identified in paragraphs (g)(2)(i),
(g)(2)(ii), and (g)(2)(iii) of this AD. This paragraph provides credit for the
Air transportation, Aircraft, Aviation actions required by paragraph (j) of this AD
(i) Any part on which a qualifying
safety, Incorporation by reference, inspection identified in paragraph (h) of this involving Airbus Service Bulletin A320–71–
Safety. AD has been done and there were no findings 1065, Revision 01, dated July 28, 2017, if
(the inspection was passed). those actions were performed before the
Adoption of the Amendment effective date of this AD using Airbus Service
(ii) Any part on which a qualifying
Accordingly, under the authority inspection identified in paragraph (h) of this Bulletin A320–71–1065, dated December 1,
delegated to me by the Administrator, AD has been done and that part has been 2016.
the FAA amends 14 CFR part 39 as repaired as specified in Goodrich Aerospace (m) Parts Installation Prohibition
follows: Service Bulletin RA32071–159.
(iii) Any part that has been repaired in Do not install on any airplane an affected
accordance with other instructions approved main beam or a forward engine mount
PART 39—AIRWORTHINESS assembly equipped with an affected main
DIRECTIVES by the Manager, International Section,
Transport Standards Branch, FAA; or the beam, as specified in paragraph (m)(1) or
European Aviation Safety Agency (EASA); or (m)(2) of this AD, as applicable.
■ 1. The authority citation for part 39 (1) For Group 1 airplanes: After
Airbus’s EASA Design Organization
continues to read as follows: modification of the airplane as required by
Approval (DOA).
Authority: 49 U.S.C. 106(g), 40113, 44701. paragraph (j) of this AD.
(h) Definition of Qualifying Inspection (2) For Group 2 airplanes: As of the
§ 39.13 [Amended] For the purposes of this AD: ‘‘A qualifying effective date of this AD.
■ 2. The FAA amends § 39.13 by adding inspection’’ is an inspection done as (n) Other FAA AD Provisions
specified in Goodrich Aerospace Service
the following new airworthiness The following provisions also apply to this
Bulletin RA32071–159; or for CFM56–5B
directive (AD): engines, an inspection done as specified in AD:
2018–12–02 Airbus: Amendment 39–19306; Repair 10 of Goodrich Aerospace CMM 71– (1) Alternative Methods of Compliance
Docket No. FAA–2017–1020; Product 21–08, Revision 47; or for CFM56–5A (AMOCs): The Manager, International
amozie on DSK3GDR082PROD with RULES
Identifier 2017–NM–114–AD. engines, an inspection done as specified in Section, Transport Standards Branch, FAA,
Repair 21 of Goodrich Aerospace CMM 71– has the authority to approve AMOCs for this
(a) Effective Date 21–06, Revision 59. AD, if requested using the procedures found
This AD is effective July 13, 2018. in 14 CFR 39.19. In accordance with 14 CFR
(i) Definition of Airplane Groups 39.19, send your request to your principal
(b) Affected ADs For the purposes of this AD: ‘‘Group 1 inspector or local Flight Standards District
None. airplanes’’ are airplanes on which an affected Office, as appropriate. If sending information
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![26564 Federal Register / Vol. 83, No. 111 / Friday, June 8, 2018 / Rules and Regulations
directly to the manager of the International (3) For Airbus service information of a certain publication listed in this AD
Section, send it to the attention of the person identified in this AD, contact Airbus, as of June 25, 2018.
identified in paragraph (o)(2) of this AD. Airworthiness Office–EIAS, 1 Rond Point We must receive comments on this
Information may be emailed to: 9-ANM-116- Maurice Bellonte, 31707 Blagnac Cedex,
AMOC-REQUESTS@faa.gov. Before using
AD by July 23, 2018.
France; telephone: +33 5 61 93 36 96; fax:
any approved AMOC, notify your appropriate +33 5 61 93 44 51; email: account.airworth- ADDRESSES: You may send comments,
principal inspector, or lacking a principal eas@airbus.com; internet: http:// using the procedures found in 14 CFR
inspector, the manager of the local flight www.airbus.com. 11.43 and 11.45, by any of the following
standards district office/certificate holding (4) For Goodrich service information methods:
district office. identified in this final rule, contact Goodrich • Federal eRulemaking Portal: Go to
(2) Contacting the Manufacturer: For any Corporation, Aerostructures, 850 Lagoon
requirement in this AD to obtain corrective
http://www.regulations.gov. Follow the
Drive, Chula Vista, CA 91910–2098; phone: instructions for submitting comments.
actions from a manufacturer, the action must 619–691–2719; email: jan.lewis@
be accomplished using a method approved • Fax: 202–493–2251.
goodrich.com; internet: http://
by the Manager, International Section, www.goodrich.com/TechPubs. • Mail: U.S. Department of
Transport Standards Branch, FAA; or EASA; (5) You may view this service information Transportation, Docket Operations,
or Airbus’s EASA DOA. If approved by the at the FAA, Transport Standards Branch, M–30, West Building Ground Floor,
DOA, the approval must include the DOA- 2200 South 216th St., Des Moines, WA. For Room W12–140, 1200 New Jersey
authorized signature. information on the availability of this Avenue SE, Washington, DC 20590.
(3) Required for Compliance (RC): Except material at the FAA, call 206–231–3195. • Hand Delivery: Deliver to Mail
as required by paragraph (k) of this AD: If any (6) You may view this service information
service information contains procedures or address above between 9 a.m. and 5
that is incorporated by reference at the p.m., Monday through Friday, except
tests that are identified as RC, those National Archives and Records
procedures and tests must be done to comply Federal holidays.
Administration (NARA). For information on
with this AD; any procedures or tests that are the availability of this material at NARA, call
For service information identified in
not identified as RC are recommended. Those 202–741–6030, or go to: http:// this final rule, contact Boeing
procedures and tests that are not identified Commercial Airplanes, Attention:
www.archives.gov/federal-register/cfr/ibr-
as RC may be deviated from using accepted Contractual & Data Services (C&DS),
locations.html.
methods in accordance with the operator’s
Issued in Des Moines, Washington, on May
2600 Westminster Blvd., MC 110 SK57,
maintenance or inspection program without
obtaining approval of an AMOC, provided 29, 2018. Seal Beach, CA 90740–5600; telephone
the procedures and tests identified as RC can Jeffrey E. Duven,
562 797 1717; internet https://
be done and the airplane can be put back in www.myboeingfleet.com. You may view
Director, System Oversight Division, Aircraft
an airworthy condition. Any substitutions or Certification Service.
this service information at the FAA,
changes to procedures or tests identified as Transport Standards Branch, 2200
RC require approval of an AMOC. [FR Doc. 2018–12268 Filed 6–7–18; 8:45 am]
South 216th St., Des Moines, WA. For
BILLING CODE 4910–13–P
(o) Related Information information on the availability of this
(1) Refer to Mandatory Continuing
material at the FAA, call 206–231–3195.
Airworthiness Information (MCAI) EASA AD It is also available on the internet at
DEPARTMENT OF TRANSPORTATION
2017–0132R1, dated November 22, 2017, for http://www.regulations.gov by searching
related information. This MCAI may be Federal Aviation Administration for and locating Docket No. FAA–2018–
found in the AD docket on the internet at 0507.
http://www.regulations.gov by searching for
14 CFR Part 39 Examining the AD Docket
and locating Docket No. FAA–2017–1020.
(2) For more information about this AD, [Docket No. FAA–2018–0507; Product You may examine the AD docket on
contact Sanjay Ralhan, Aerospace Engineer, Identifier 2018–NM–027–AD; Amendment the internet at http://
International Section, Transport Standards 39–19308; AD 2018–12–04]
Branch, FAA, 2200 South 216th St., Des
www.regulations.gov by searching for
Moines, WA 98198–6547; telephone 425– RIN 2120–AA64 and locating Docket No. FAA–2018–
227–1405; fax 425–227–1149. 0507; or in person at Docket Operations
(3) Airbus service information identified in Airworthiness Directives; The Boeing between 9 a.m. and 5 p.m., Monday
this AD that is not incorporated by reference Company Airplanes through Friday, except Federal holidays.
is available at the addresses specified in The AD docket contains this final rule,
paragraphs (p)(4) and (p)(5) of this AD. AGENCY: Federal Aviation
Administration (FAA), DOT. the regulatory evaluation, any
(4) Goodrich service information identified comments received, and other
in this AD that is not incorporated by ACTION: Final rule; request for
reference is available at Goodrich
information. The street address for
comments.
Corporation, Aerostructures, 850 Lagoon Docket Operations (phone: 800–647–
Drive, Chula Vista, CA 91910–2098; phone: SUMMARY: We are adopting a new 5527) is in the ADDRESSES section.
619–691–2719; email: jan.lewis@ airworthiness directive (AD) for certain Comments will be available in the AD
goodrich.com; internet: http:// The Boeing Company Model 777–300ER docket shortly after receipt.
www.goodrich.com/TechPubs. series airplanes. This AD requires FOR FURTHER INFORMATION CONTACT:
(p) Material Incorporated by Reference replacing the water filter assembly in Stanley Chen, Aerospace Engineer,
(1) The Director of the Federal Register certain steam ovens. This AD was Cabin Safety and Environmental
approved the incorporation by reference prompted by a report that water can Systems Section, FAA, Seattle ACO
(IBR) of the service information listed in this enter the steam oven cavity and become Branch, 2200 South 216th St., Des
paragraph under 5 U.S.C. 552(a) and 1 CFR heated and then released when the oven Moines, WA 98198; phone and fax: 206–
part 51. door is opened. We are issuing this AD 231–3565; email: stanley.chen@faa.gov.
amozie on DSK3GDR082PROD with RULES
(2) You must use this service information to address the unsafe condition on these SUPPLEMENTARY INFORMATION:
as applicable to do the actions required by
products.
this AD, unless this AD specifies otherwise. Discussion
(i) Airbus Service Bulletin A320–71–1065, DATES: This AD is effective June 25,
Revision 01, dated July 28, 2017. 2018. We have received a report that
(ii) Airbus Service Bulletin A320–71–1066, The Director of the Federal Register members of the cabincrew on a Model
dated December 1, 2016. approved the incorporation by reference 787 airplane were injured when hot
VerDate Sep<11>2014 16:08 Jun 07, 2018 Jkt 244001 PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 E:\FR\FM\08JNR1.SGM 08JNR1](https://thefederalregister.org/doc/83_FR_26670/page/6.svg)
Document Created: 2018-06-08 01:21:54
Document Modified: 2018-06-08 01:21:54
| 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 July 13, 2018. | |
| Contact | Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198-6547; telephone 425-227-1405; fax 425- 227-1149. | |
| FR Citation | 83 FR 26559 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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