Airworthiness Directives; Airbus Airplanes, 10411-10415 [2018-04727]

Download as PDF Federal Register / Vol. 83, No. 47 / Friday, March 9, 2018 / Proposed Rules paragraph (g) of this AD and all applicable corrective actions required by paragraph (h) of this AD, check the bolt preload, and do all applicable corrective actions, in accordance with paragraph 3.B., ‘‘Procedure,’’ of the Accomplishment Instructions of Bombardier Alert Service Bulletin A84–55–04, Revision C, dated May 3, 2016. Do all applicable corrective actions before further flight. Accomplishment of the actions required by paragraphs (l) and (m) of this AD, as applicable, terminates the requirements of this paragraph. (j) Retained Repetitive Inspection Interval, With New Terminating Action This paragraph restates the requirements of paragraph (j) of AD 2016–24–03, with new terminating action. Repeat the inspection and preload check required by paragraphs (g) and (i) of this AD at intervals not to exceed 3,600 flight hours or 18 months, whichever occurs first, except as provided by paragraph (k) of this AD. Accomplishment of the actions required by paragraphs (l) and (m) of this AD, as applicable, terminates the requirements of this paragraph. (k) Retained Optional Barrel Nut Replacement, With New Service Information This paragraph restates the provisions of paragraph (k) of AD 2016–24–03, with new service information. Inspection and replacement of all barrel nuts at the horizontal-stabilizer-to-vertical-stabilizer attachment joints, in accordance with paragraph 3.B., ‘‘Procedure,’’ of the Accomplishment Instructions of Bombardier Service Bulletin 84–55–08, Revision A, dated August 2, 2017, extends the next inspection required by paragraph (j) of this AD to within 6,000 flight hours or 36 months, whichever occurs first, after accomplishing the replacement. amozie on DSK30RV082PROD with PROPOSALS (l) New Requirement of This AD: Sealing Disk Installation Within 8,000 flight hours or 48 months, whichever occurs first, after the effective date of this AD, install a sealing disk at the midspar location of the vertical stabilizer in accordance with paragraph 3.B., ‘‘Procedure,’’ of the Accomplishment Instructions of Bombardier Service Bulletin 84–55–06, dated January 31, 2017. Accomplishment of the actions required by paragraphs (l) and (m) of this AD, as applicable, terminates the requirements of paragraphs (h), (i), and (j) of this AD. (m) New Requirement of This AD: Replacement of DSC228 Series Barrel Nuts For Bombardier, Inc., Model DHC–8–400, –401 and –402 airplanes, serial numbers 4001 through 4524 inclusive: Within 8,000 flight hours or 48 months, whichever occurs first, after the effective date of this AD, replace all DSC228 series barrel nuts at the horizontal-stabilizer-to-vertical-stabilizer attachment joints with B0203073 series barrel nuts in accordance with paragraph 3.B., ‘‘Procedure,’’ of the Accomplishment Instructions of Bombardier Service Bulletin 84–55–08, Revision A, dated August 2, 2017. Accomplishment of the actions required by paragraphs (l) and (m) of this AD, as VerDate Sep<11>2014 15:54 Mar 08, 2018 Jkt 244001 applicable, terminates the requirements of paragraphs (h), (i), and (j) of this AD. (n) Parts Installation Prohibition After modification of an airplane as required by paragraphs (l) and (m) of this AD, no person may install a DSC228 series barrel nut at the horizontal-stabilizer-to-verticalstabilizer attachment joint on the modified airplane. (o) Terminating Actions Accomplishment of the actions required by paragraphs (l) and (m) of this AD, as applicable, terminates the requirements of paragraphs (h), (i), and (j) of this AD. (p) Credit for Previous Actions (1) This paragraph provides credit for actions required by paragraphs (g)(1), (g)(2), (h)(1), (h)(1)(i), (h)(1)(ii), (h)(2), (h)(3), (h)(4), (i), and (k) of this AD, if those actions were performed before the effective date of this AD using the service information identified in paragraphs (p)(1)(i) through (p)(1)(iii) of this AD. (i) Bombardier Alert Service Bulletin A84– 55–04, dated May 21, 2015, which is not incorporated by reference in this AD. (ii) Bombardier Alert Service Bulletin A84– 55–04, Revision A, dated June 2, 2015, which is not incorporated by reference in this AD. (iii) Bombardier Alert Service Bulletin A84–55–04, Revision B, dated July 30, 2015, which is not incorporated by reference in this AD. (2) This paragraph provides credit for actions required by paragraphs (h)(1), (h)(1)(i), (h)(1)(ii), (h)(2), and (k) of this AD, if those actions were performed before the effective date of this AD using the service information identified in paragraphs (p)(2)(i) and (p)(2)(ii) of this AD. (i) Bombardier Service Bulletin 84–55–08, dated January 27, 2017, which is not incorporated by reference in this AD. (ii) Bombardier Alert Service Bulletin A84– 55–04, Revision C, dated May 3, 2016, which was incorporated by reference in AD 2016– 24–03. (q) Other FAA AD Provisions (1) Alternative Methods of Compliance (AMOCs): The Manager, New York ACO 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 manager of the certification office, send it to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7300; fax 516–794–5531. (i) 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. (ii) AMOCs approved previously for AD 2016–24–03 are approved as AMOCs for the corresponding provisions of this AD. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 10411 actions from a manufacturer, the action must be accomplished using a method approved by the Manager, New York ACO Branch, FAA; or Transport Canada Civil Aviation (TCCA); or Bombardier, Inc.’s TCCA Design Approval Organization (DAO). If approved by the DAO, the approval must include the DAO-authorized signature. (r) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) TCCA Airworthiness Directive CF–2015–13R1, dated June 26, 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–2018–0160. (2) For more information about this AD, contact Aziz Ahmed, Aerospace Engineer, Airframe and Mechanical Systems Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7329; fax 516–794–5531. (3) For service information identified in this AD, contact Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416–375–4000; fax 416–375–4539; email thd.qseries@aero.bombardier.com; internet http://www.bombardier.com. 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. Issued in Renton, Washington, on March 2, 2018. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018–04720 Filed 3–8–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0165; Product Identifier 2017–NM–122–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt 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 proposed AD was prompted by a report of a production quality deficiency on the SUMMARY: E:\FR\FM\09MRP1.SGM 09MRP1 10412 Federal Register / Vol. 83, No. 47 / Friday, March 9, 2018 / Proposed Rules inner retainer installed on link assemblies of the aft engine mount, which could result in failure of the retainer. This proposed AD would require modifying and re-identifying the aft engine mount assemblies. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by April 23, 2018. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For Airbus service information identified in this NPRM, 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 account.airworth-eas@airbus.com; internet http://www.airbus.com. For Goodrich Aerospace service information identified in this NPRM, contact Goodrich Corporation, Aerostructures, 850 Lagoon Drive, Chula Vista, CA 91910–2098; phone: 619–691– 2719; email: jan.lewis@goodrich.com; internet: http://www.goodrich.com/ TechPubs. 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. amozie on DSK30RV082PROD with PROPOSALS 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–2018– 0165; 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 NPRM, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, VerDate Sep<11>2014 15:54 Mar 08, 2018 Jkt 244001 International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3223. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2018–0165; Product Identifier 2017– NM–122–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this NPRM. We will consider all comments received by the closing date and may amend this NPRM based on those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this NPRM. Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2017–0251, dated December 15, 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: During in-service inspections, several aft engine mount inner retainers, fitted on aeroplanes equipped with CFM56–5A/5B engines, were found broken. Investigation identified that the main cause of crack initiation was the vibration dynamic effect that affects the retainers, and that the ‘‘dull’’ surface finish pitting is an aggravating factor when compared with the ‘‘bright’’ surface finishing. This condition, if not detected and corrected, could lead to in-flight loss of an aft engine mount link, possibly resulting in damage to the aeroplane and/or injury to persons on the ground. To address this potential unsafe condition, Airbus issued Alert Operators Transmission (AOT) A71N001–12 (later revised) and EASA issued AD 2013–0050 [which corresponds to FAA AD 2014–14–06, Amendment 39–17901 (79 FR 42655, July 23, 2014)], later superseded by EASA AD 2015–0021 [which corresponds to FAA AD 2016–14–09, Amendment 39–18590 (81 FR 44989, July 12, 2016) (‘‘AD 2016–14–09’’)], requiring repetitive detailed inspections (DET) of all aft PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 engine mount inner retainers and, depending on findings, their replacement. After EASA AD 2015–0021 was issued, a production quality deficiency was identified by Airbus and Goodrich Aerostructures, the engine mount retainer manufacturer, on the inner retainer, Part Number (P/N) 238–0252– 505, installed in the three link assemblies of the engine mount fitted on CFM56–5A/5B engines. Airbus issued AOT A71N011–15 and Service Bulletin (SB) A320–71–1070, providing a list of affected parts and applicable corrective actions. Consequently, EASA issued AD 2016–0010 (later revised), retaining the requirements of EASA AD 2015–0021, which was superseded, and in addition requiring the identification and replacement of all nonconforming aft engine mount inner retainers [EASA AD 2016–0010 R1 corresponds to FAA AD 2017–04–10, Amendment 39–18805 (82 FR 11791, February 27, 2017) (‘‘AD 2017– 04–10’’)]. After that [EASA] AD was issued, a new engine mount retainer was developed by Goodrich Aerostructures to improve the retainer efficiency. For retrofit purposes, Goodrich Aerostructures issued SB RA32071–164, and Airbus issued SB A320– 71–1071, providing instructions to modify and re-identify the engine mount assemblies as instructed in the Goodrich Aerostructures SB. Subsequently, it was observed that, on aeroplanes equipped with certain engines fitted with a Turbine Rear Frame (TRF) with 4 lugs configuration, the installation of the new engine mount retainers can lead to interference, and Goodrich Aerostructures revised SB RA32071–164, providing instructions not to install the new engine retainers on affected engines. Airbus SB A320–71–1071 is expected to be revised accordingly. For engines fitted with a TRF with 4 lugs, a new installation (potentially requiring different engine mount retainers) is being developed by Goodrich Aerospace and Airbus. Consequently, EASA issued AD 2017– 0138, retaining the requirements of EASA AD 2016–0010R1, which was superseded, and, except for aeroplanes equipped with engines fitted with a TRF with 4 lugs configuration, requiring modification and identification of aft engine mount assemblies as terminating action for the repetitive inspections of the retainers. That [EASA] AD also included additional instructions applicable to installation of engines fitted with a TRF with 4 lugs configuration. Since EASA AD 2017–0138 was issued, it was determined that installation of new engine mount assemblies must not be allowed for some specific engine configurations, and that installation of Goodrich Aerostructures SB RA32071–164 alone can be referred to, in order to accomplish the terminating action as required by that [EASA] AD. For the reason described above, this [EASA] AD retains the requirements of EASA AD 2017–0138, which is superseded, adds reference to Goodrich Aerostructures SB RA32071–164 * * *, and introduces new requirement for aeroplanes equipped with engines fitted with a TRF with 4 lugs configuration. E:\FR\FM\09MRP1.SGM 09MRP1 10413 Federal Register / Vol. 83, No. 47 / Friday, March 9, 2018 / Proposed Rules This NPRM would not supersede AD 2017–04–10. Rather, we have determined that a stand-alone AD would be more appropriate to address the changes in the MCAI. This NPRM would require modifying and reidentifying the aft engine mount assemblies. Accomplishment of the proposed actions would then terminate the repetitive detailed inspections required by paragraph (l) of AD 2016– 14–09, and serve as a method of compliance for the requirements of paragraph (g) of AD 2017–04–10. 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–2018– 0165. Related Service Information Under 1 CFR Part 51 FAA’s Determination and Requirements of This Proposed AD Airbus has issued Service Bulletin A320–71–1071, dated November 8, 2016. Goodrich Aerostructures has issued Service Bulletin RA32071–164, Revision 1, dated July 19, 2017. The service information describes procedures for modifying and reidentifying the aft engine mount retainer assembly. These documents are distinct since they apply to different airplane models in different configurations. 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. This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of these same type designs. Costs of Compliance We estimate that this proposed AD affects 500 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Labor cost Parts cost Modification and re-identification .................... 20 work-hours × $85 per hour = $1,700 ........ amozie on DSK30RV082PROD with PROPOSALS Authority for This Rulemaking Regulatory Findings 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 proposed 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. We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 this proposed regulation: 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. VerDate Sep<11>2014 15:54 Mar 08, 2018 Jkt 244001 List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 Cost per product $3,152 Cost on U.S. operators $4,852 $2,426,000 PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ Airbus: Docket No. FAA–2018–0165; Product Identifier 2017–NM–122–AD. (a) Comments Due Date We must receive comments by April 23, 2018. (b) Affected ADs This AD affects AD 2016–14–09, Amendment 39–18590 (81 FR 44989, July 12, 2016) (‘‘AD 2016–14–09’’); and AD 2017–04– 10, Amendment 39–18805 (82 FR 11791, February 27, 2017) (‘‘AD 2017–04–10’’). (c) Applicability This AD applies to the Airbus airplanes identified in paragraphs (c)(1) through (c)(4) of this AD, certificated in any category, all manufacturer serial numbers. (1) Model A318–111 and –112 airplanes. (2) Model A319–111, –112, –113, –114, and –115 airplanes. (3) Model A320–211, –212, –214, and –216 airplanes. (4) Model A321–111, –112, –211, –212, and –213 airplanes. (d) Subject Air Transport Association (ATA) of America Code 71, Powerplant. E:\FR\FM\09MRP1.SGM 09MRP1 10414 Federal Register / Vol. 83, No. 47 / Friday, March 9, 2018 / Proposed Rules (e) Reason This AD was prompted by a report of a production quality deficiency on the inner retainer installed on link assemblies of the aft engine mount, which could result in failure of the retainer. We are issuing this AD to address non-conforming retainers of the aft engine mount. This condition could result in loss of the locking feature of the nuts of the inner and outer pins; loss of the pins will result in the aft mount engine link no longer being secured to the aft engine mount, possibly resulting in damage to the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Definitions (1) For the purpose of this AD: A Group 1 airplane has an aft engine mount assembly installed, having a part number (P/N) identified as ‘‘Old P/N’’ in figure 1 to paragraphs (g), (h), (i), (j), (k), and (l) of this AD. A Group 2 airplane does not have any aft engine mount assembly installed having a part number identified as ‘‘Old P/N’’ in figure 1 to paragraphs (g), (h), (i), (j), (k), and (l) of this AD. (2) For the purpose of this AD, a 4-lugs engine is a CFM56–5A1, CFM56–5A3, CFM56–5A4, CFM56–5A4/F, CFM56–5A5, or CFM56–5A5/F engine, fitted with a turbine rear frame (TRF) having a part number as identified in figure 2 to paragraph (g) of this AD. FIGURE 1 TO PARAGRAPHS (g), (h), (i), (j), (k), AND (l) OF THIS AD—PART RE-IDENTIFICATION Old P/N New P/N 238–0230–11 ..................... 238–0230–15 ..................... 238–0230–5 ....................... 642–2300–3 ....................... 238M0230–11 238M0230–15 238M0230–5 642–2300–11 FIGURE 2 TO PARAGRAPH (g) OF THIS AD—TRF WITH 4-LUGS CONFIGURATION amozie on DSK30RV082PROD with PROPOSALS Part No. 336–031–615–0 336–031–617–0 336–031–618–0 336–031–621–0 336–031–650–0 336–031–651–0 336–031–652–0 336–031–653–0 336–031–660–0 336–031–661–0 336–031–662–0 336–031–663–0 336–031–670–0 336–031–671–0 336–031–672–0 336–031–673–0 336–031–640–0 336–031–642–0 VerDate Sep<11>2014 15:54 Mar 08, 2018 (h) Modification For Group 1 airplanes: Within 48 months after the effective date of this AD, except for 4-lugs engines, modify the aft engine mount assembly, having a part number identified as ‘‘Old P/N’’ in figure 1 to paragraphs (g), (h), (i), (j), (k), and (l) of this AD, and re-identify it with the corresponding part number identified as ‘‘New P/N’’ in figure 1 to paragraphs (g), (h), (i), (j), (k), and (l) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 71–1071, dated November 8, 2016; or Goodrich Aerostructures Service Bulletin RA32071–164, Revision 1, dated July 19, 2017. (i) Other Acceptable Method of Compliance Replacement on an airplane of each aft engine mount assembly, identified as ‘‘Old P/N’’ in figure 1 to paragraphs (g), (h), (i), (j), (k), and (l) of this AD, with a corresponding aft engine mount assembly, identified as ‘‘New P/N’’ in figure 1 to paragraphs (g), (h), (i), (j), (k), and (l) of this AD, is an acceptable method to comply with the requirements of paragraph (h) of this AD for that airplane. (j) Identification of Certain Airplanes That Do Not Have Affected Parts An airplane on which Airbus modification 158435 has been embodied in production and on which it can be positively determined that no aft engine mount assembly, identified as ‘‘Old P/N’’ in figure 1 to paragraphs (g), (h), (i), (j), (k), and (l) of this AD, is installed, is considered a Group 2 airplane. A review of airplane maintenance records is acceptable to make this determination, if it can be conclusively determined that no aft engine mount assembly identified as ‘‘Old P/N’’ in figure 1 to paragraphs (g), (h), (i), (j), (k), and (l) of this AD is installed. Group 2 airplanes are not affected by the requirements of paragraph (h) of this AD. (k) Parts Installation Prohibition (1) For Group 1 airplanes: Do not install an aft engine mount assembly identified as ‘‘Old P/N’’ in figure 1 to paragraphs (g), (h), (i), (j), (k), and (l) of this AD on any airplane after modification of the airplane as required by paragraph (h) of this AD, or after any replacement specified in paragraph (i) of this AD. (2) For Group 2 airplanes: As of the effective date of this AD, do not install an aft engine mount assembly identified as ‘‘Old P/N’’ in figure 1 to paragraphs (g), (h), (i), (j), (k), and (l) of this AD on any airplane. (3) For airplanes equipped with a 4-lugs engine (left-hand (LH) or right-hand (RH) side): As of the effective date of this AD, do not modify any aft engine mount assembly identified as ‘‘Old P/N’’ in figure 1 to paragraphs (g), (h), (i), (j), (k), and (l) of this AD, as required by paragraph (h) of this AD, and do not install on an affected engine pylon (LH or RH) any aft engine mount assembly identified as ‘‘New P/N’’ in figure 1 to paragraphs (g), (h), (i), (j), (k), and (l) of this AD. (l) 4-Lugs Engine Installation (1) From the effective date of this AD, it is allowed to install or reinstall a 4-lugs engine Jkt 244001 PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 on an airplane (LH or RH) provided that the airplane is equipped with an aft engine mount assembly identified as ‘‘Old P/N’’ in figure 1 to paragraphs (g), (h), (i), (j), (k), and (l) of this AD on the affected engine pylon (LH or RH). (2) For airplanes equipped with a 4-lugs engine (LH or RH), and on which, prior to the effective date of this AD, an aft engine mount assembly identified as ‘‘New P/N’’ in figure 1 to paragraphs (g), (h), (i), (j), (k), and (l) of this AD has been installed on the affected engine pylon (LH or RH), or on which the aft engine part assembly has been modified as specified in paragraph (h) of this AD: Within 30 days after the effective date of this AD, obtain repair instructions using 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), and accomplish those instructions accordingly. If approved by the DOA, the approval must include the DOA-authorized signature. (m) Terminating Action and Method of Compliance (1) Modification of an airplane as required by paragraph (h) of this AD, or as specified in paragraph (i) of this AD, constitutes terminating action for the repetitive detailed inspections required by paragraph (l) of AD 2016–14–09 for that airplane. (2) Modification of an airplane as required by paragraph (h) of this AD, or as specified in paragraph (i) of this AD, is a method of compliance with the requirements of paragraph (g) of AD 2017–04–10 for that airplane. (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 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: 9-ANM-116-AMOCREQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOAauthorized signature. (3) Required for Compliance (RC): If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply E:\FR\FM\09MRP1.SGM 09MRP1 Federal Register / Vol. 83, No. 47 / Friday, March 9, 2018 / Proposed Rules 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. DEPARTMENT OF TRANSPORTATION (o) Special Flight Permits AGENCY: Special flight permits, as described in Section 21.197 and Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199), are not allowed. (p) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2017–0251 dated December 15, 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–2018–0165. (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; telephone and fax 206– 231–3223. (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 account.airworth-eas@ airbus.com; internet http://www.airbus.com. (4) For Goodrich Aerospace service information identified in this AD, contact Goodrich Corporation, Aerostructures, 850 Lagoon Drive, Chula Vista, CA 91910–2098; phone: 619–691–2719; email: jan.lewis@ goodrich.com; internet: http:// www.goodrich.com/TechPubs. 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. Issued in Renton, Washington, on March 5, 2018. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018–04727 Filed 3–8–18; 8:45 am] amozie on DSK30RV082PROD with PROPOSALS BILLING CODE 4910–13–P VerDate Sep<11>2014 15:54 Mar 08, 2018 Jkt 244001 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0161; Product Identifier 2017–NM–088–AD] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc., Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). We propose to supersede Airworthiness Directive (AD) 2013–11– 12, which applies to certain Bombardier, Inc., Model BD–100–1A10 airplanes. AD 2013–11–12 requires inspecting for the correct serial number of a certain hydraulic system accumulator, and replacing affected hydraulic system accumulators with new or serviceable accumulators. Since we issued AD 2013–11–12, we have determined that certain other hydraulic system accumulators must be modified or replaced and life limits must be added. This proposed AD would expand the applicability and require modifying or replacing certain hydraulic brake system accumulators. This proposed AD would also require revising the maintenance or inspection program to add life limits for the accumulators. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by April 23, 2018. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Bombardier, Inc., ˆ 400 Cote-Vertu Road West, Dorval, ´ Quebec H4S 1Y9, Canada; telephone 514–855–5000; fax 514–855–7401; email thd.crj@aero.bombardier.com; internet http://www.bombardier.com. You may view this referenced service information at the FAA, Transport Standards SUMMARY: PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 10415 Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. 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–2018– 0161; 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Cesar Gomez, Aerospace Engineer, Airframe and Mechanical Systems Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516– 228–7318; fax 516–794–5531. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2018–0161; Product Identifier 2017– NM–088–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion We issued AD 2013–11–12, Amendment 39–17472 (78 FR 33206, June 4, 2013) (‘‘AD 2013–11–12’’), for certain Bombardier, Inc., Model BD– 100–1A10 airplanes. AD 2013–11–12 requires inspecting for the correct serial number of a certain hydraulic system accumulator, and replacing affected hydraulic system accumulators with new or serviceable accumulators. AD 2013–11–12 resulted from reports of failure of a screw cap or end cap of the hydraulic system accumulator while on the ground, which resulted in loss of E:\FR\FM\09MRP1.SGM 09MRP1

Agencies

[Federal Register Volume 83, Number 47 (Friday, March 9, 2018)]
[Proposed Rules]
[Pages 10411-10415]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-04727]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0165; Product Identifier 2017-NM-122-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt 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 proposed AD was prompted by a report of a production quality 
deficiency on the

[[Page 10412]]

inner retainer installed on link assemblies of the aft engine mount, 
which could result in failure of the retainer. This proposed AD would 
require modifying and re-identifying the aft engine mount assemblies. 
We are proposing this AD to address the unsafe condition on these 
products.

DATES: We must receive comments on this proposed AD by April 23, 2018.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For Airbus service information identified in this NPRM, 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 Aerospace service information identified in this NPRM, 
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 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.

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-2018-
0165; 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 NPRM, the regulatory evaluation, any comments received, 
and other information. The street address for the Docket Operations 
office (telephone 800-647-5527) is in the ADDRESSES section. Comments 
will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, 
International Section, Transport Standards Branch, FAA, 2200 South 
216th St., Des Moines, WA 98198; telephone and fax 206-231-3223.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2018-0165; 
Product Identifier 2017-NM-122-AD'' at the beginning of your comments. 
We specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this NPRM. We will consider all 
comments received by the closing date and may amend this NPRM based on 
those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this NPRM.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2017-0251, dated December 15, 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:

    During in-service inspections, several aft engine mount inner 
retainers, fitted on aeroplanes equipped with CFM56-5A/5B engines, 
were found broken. Investigation identified that the main cause of 
crack initiation was the vibration dynamic effect that affects the 
retainers, and that the ``dull'' surface finish pitting is an 
aggravating factor when compared with the ``bright'' surface 
finishing.
    This condition, if not detected and corrected, could lead to in-
flight loss of an aft engine mount link, possibly resulting in 
damage to the aeroplane and/or injury to persons on the ground.
    To address this potential unsafe condition, Airbus issued Alert 
Operators Transmission (AOT) A71N001-12 (later revised) and EASA 
issued AD 2013-0050 [which corresponds to FAA AD 2014-14-06, 
Amendment 39-17901 (79 FR 42655, July 23, 2014)], later superseded 
by EASA AD 2015-0021 [which corresponds to FAA AD 2016-14-09, 
Amendment 39-18590 (81 FR 44989, July 12, 2016) (``AD 2016-14-
09'')], requiring repetitive detailed inspections (DET) of all aft 
engine mount inner retainers and, depending on findings, their 
replacement.
    After EASA AD 2015-0021 was issued, a production quality 
deficiency was identified by Airbus and Goodrich Aerostructures, the 
engine mount retainer manufacturer, on the inner retainer, Part 
Number (P/N) 238-0252-505, installed in the three link assemblies of 
the engine mount fitted on CFM56-5A/5B engines. Airbus issued AOT 
A71N011-15 and Service Bulletin (SB) A320-71-1070, providing a list 
of affected parts and applicable corrective actions.
    Consequently, EASA issued AD 2016-0010 (later revised), 
retaining the requirements of EASA AD 2015-0021, which was 
superseded, and in addition requiring the identification and 
replacement of all non-conforming aft engine mount inner retainers 
[EASA AD 2016-0010 R1 corresponds to FAA AD 2017-04-10, Amendment 
39-18805 (82 FR 11791, February 27, 2017) (``AD 2017-04-10'')].
    After that [EASA] AD was issued, a new engine mount retainer was 
developed by Goodrich Aerostructures to improve the retainer 
efficiency. For retrofit purposes, Goodrich Aerostructures issued SB 
RA32071-164, and Airbus issued SB A320-71-1071, providing 
instructions to modify and re-identify the engine mount assemblies 
as instructed in the Goodrich Aerostructures SB. Subsequently, it 
was observed that, on aeroplanes equipped with certain engines 
fitted with a Turbine Rear Frame (TRF) with 4 lugs configuration, 
the installation of the new engine mount retainers can lead to 
interference, and Goodrich Aerostructures revised SB RA32071-164, 
providing instructions not to install the new engine retainers on 
affected engines. Airbus SB A320-71-1071 is expected to be revised 
accordingly. For engines fitted with a TRF with 4 lugs, a new 
installation (potentially requiring different engine mount 
retainers) is being developed by Goodrich Aerospace and Airbus.
    Consequently, EASA issued AD 2017-0138, retaining the 
requirements of EASA AD 2016-0010R1, which was superseded, and, 
except for aeroplanes equipped with engines fitted with a TRF with 4 
lugs configuration, requiring modification and identification of aft 
engine mount assemblies as terminating action for the repetitive 
inspections of the retainers. That [EASA] AD also included 
additional instructions applicable to installation of engines fitted 
with a TRF with 4 lugs configuration.
    Since EASA AD 2017-0138 was issued, it was determined that 
installation of new engine mount assemblies must not be allowed for 
some specific engine configurations, and that installation of 
Goodrich Aerostructures SB RA32071-164 alone can be referred to, in 
order to accomplish the terminating action as required by that 
[EASA] AD.
    For the reason described above, this [EASA] AD retains the 
requirements of EASA AD 2017-0138, which is superseded, adds 
reference to Goodrich Aerostructures SB RA32071-164 * * *, and 
introduces new requirement for aeroplanes equipped with engines 
fitted with a TRF with 4 lugs configuration.


[[Page 10413]]


    This NPRM would not supersede AD 2017-04-10. Rather, we have 
determined that a stand-alone AD would be more appropriate to address 
the changes in the MCAI. This NPRM would require modifying and re-
identifying the aft engine mount assemblies. Accomplishment of the 
proposed actions would then terminate the repetitive detailed 
inspections required by paragraph (l) of AD 2016-14-09, and serve as a 
method of compliance for the requirements of paragraph (g) of AD 2017-
04-10. 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-2018-0165.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A320-71-1071, dated November 8, 
2016. Goodrich Aerostructures has issued Service Bulletin RA32071-164, 
Revision 1, dated July 19, 2017. The service information describes 
procedures for modifying and re-identifying the aft engine mount 
retainer assembly. These documents are distinct since they apply to 
different airplane models in different configurations.
    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.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of these 
same type designs.

Costs of Compliance

    We estimate that this proposed AD affects 500 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
               Action                         Labor cost            Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Modification and re-identification.  20 work-hours x $85 per              $3,152          $4,852      $2,426,000
                                      hour = $1,700.
----------------------------------------------------------------------------------------------------------------

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 proposed 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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed 
regulation:
    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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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):

Airbus: Docket No. FAA-2018-0165; Product Identifier 2017-NM-122-AD.

(a) Comments Due Date

    We must receive comments by April 23, 2018.

(b) Affected ADs

    This AD affects AD 2016-14-09, Amendment 39-18590 (81 FR 44989, 
July 12, 2016) (``AD 2016-14-09''); and AD 2017-04-10, Amendment 39-
18805 (82 FR 11791, February 27, 2017) (``AD 2017-04-10'').

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs 
(c)(1) through (c)(4) of this AD, certificated in any category, all 
manufacturer serial numbers.
    (1) Model A318-111 and -112 airplanes.
    (2) Model A319-111, -112, -113, -114, and -115 airplanes.
    (3) Model A320-211, -212, -214, and -216 airplanes.
    (4) Model A321-111, -112, -211, -212, and -213 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 71, Powerplant.

[[Page 10414]]

(e) Reason

    This AD was prompted by a report of a production quality 
deficiency on the inner retainer installed on link assemblies of the 
aft engine mount, which could result in failure of the retainer. We 
are issuing this AD to address non-conforming retainers of the aft 
engine mount. This condition could result in loss of the locking 
feature of the nuts of the inner and outer pins; loss of the pins 
will result in the aft mount engine link no longer being secured to 
the aft engine mount, possibly resulting in damage to the airplane.

(f) Compliance

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

(g) Definitions

    (1) For the purpose of this AD: A Group 1 airplane has an aft 
engine mount assembly installed, having a part number (P/N) 
identified as ``Old P/N'' in figure 1 to paragraphs (g), (h), (i), 
(j), (k), and (l) of this AD. A Group 2 airplane does not have any 
aft engine mount assembly installed having a part number identified 
as ``Old P/N'' in figure 1 to paragraphs (g), (h), (i), (j), (k), 
and (l) of this AD.
    (2) For the purpose of this AD, a 4-lugs engine is a CFM56-5A1, 
CFM56-5A3, CFM56-5A4, CFM56-5A4/F, CFM56-5A5, or CFM56-5A5/F engine, 
fitted with a turbine rear frame (TRF) having a part number as 
identified in figure 2 to paragraph (g) of this AD.

Figure 1 to Paragraphs (g), (h), (i), (j), (k), and (l) of this AD--Part
                            Re-Identification
------------------------------------------------------------------------
                Old P/N                              New P/N
------------------------------------------------------------------------
238-0230-11............................  238M0230-11
238-0230-15............................  238M0230-15
238-0230-5.............................  238M0230-5
642-2300-3.............................  642-2300-11
------------------------------------------------------------------------


   Figure 2 to Paragraph (g) of This AD--TRF With 4-Lugs Configuration
------------------------------------------------------------------------
                                Part No.
-------------------------------------------------------------------------
                               336-031-615-0
                               336-031-617-0
                               336-031-618-0
                               336-031-621-0
                               336-031-650-0
                               336-031-651-0
                               336-031-652-0
                               336-031-653-0
                               336-031-660-0
                               336-031-661-0
                               336-031-662-0
                               336-031-663-0
                               336-031-670-0
                               336-031-671-0
                               336-031-672-0
                               336-031-673-0
                               336-031-640-0
                               336-031-642-0
------------------------------------------------------------------------

(h) Modification

    For Group 1 airplanes: Within 48 months after the effective date 
of this AD, except for 4-lugs engines, modify the aft engine mount 
assembly, having a part number identified as ``Old P/N'' in figure 1 
to paragraphs (g), (h), (i), (j), (k), and (l) of this AD, and re-
identify it with the corresponding part number identified as ``New 
P/N'' in figure 1 to paragraphs (g), (h), (i), (j), (k), and (l) of 
this AD, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A320-71-1071, dated November 8, 2016; or 
Goodrich Aerostructures Service Bulletin RA32071-164, Revision 1, 
dated July 19, 2017.

(i) Other Acceptable Method of Compliance

    Replacement on an airplane of each aft engine mount assembly, 
identified as ``Old P/N'' in figure 1 to paragraphs (g), (h), (i), 
(j), (k), and (l) of this AD, with a corresponding aft engine mount 
assembly, identified as ``New P/N'' in figure 1 to paragraphs (g), 
(h), (i), (j), (k), and (l) of this AD, is an acceptable method to 
comply with the requirements of paragraph (h) of this AD for that 
airplane.

(j) Identification of Certain Airplanes That Do Not Have Affected Parts

    An airplane on which Airbus modification 158435 has been 
embodied in production and on which it can be positively determined 
that no aft engine mount assembly, identified as ``Old P/N'' in 
figure 1 to paragraphs (g), (h), (i), (j), (k), and (l) of this AD, 
is installed, is considered a Group 2 airplane. A review of airplane 
maintenance records is acceptable to make this determination, if it 
can be conclusively determined that no aft engine mount assembly 
identified as ``Old P/N'' in figure 1 to paragraphs (g), (h), (i), 
(j), (k), and (l) of this AD is installed. Group 2 airplanes are not 
affected by the requirements of paragraph (h) of this AD.

(k) Parts Installation Prohibition

    (1) For Group 1 airplanes: Do not install an aft engine mount 
assembly identified as ``Old P/N'' in figure 1 to paragraphs (g), 
(h), (i), (j), (k), and (l) of this AD on any airplane after 
modification of the airplane as required by paragraph (h) of this 
AD, or after any replacement specified in paragraph (i) of this AD.
    (2) For Group 2 airplanes: As of the effective date of this AD, 
do not install an aft engine mount assembly identified as ``Old P/
N'' in figure 1 to paragraphs (g), (h), (i), (j), (k), and (l) of 
this AD on any airplane.
    (3) For airplanes equipped with a 4-lugs engine (left-hand (LH) 
or right-hand (RH) side): As of the effective date of this AD, do 
not modify any aft engine mount assembly identified as ``Old P/N'' 
in figure 1 to paragraphs (g), (h), (i), (j), (k), and (l) of this 
AD, as required by paragraph (h) of this AD, and do not install on 
an affected engine pylon (LH or RH) any aft engine mount assembly 
identified as ``New P/N'' in figure 1 to paragraphs (g), (h), (i), 
(j), (k), and (l) of this AD.

 (l) 4-Lugs Engine Installation

    (1) From the effective date of this AD, it is allowed to install 
or reinstall a 4-lugs engine on an airplane (LH or RH) provided that 
the airplane is equipped with an aft engine mount assembly 
identified as ``Old P/N'' in figure 1 to paragraphs (g), (h), (i), 
(j), (k), and (l) of this AD on the affected engine pylon (LH or 
RH).
    (2) For airplanes equipped with a 4-lugs engine (LH or RH), and 
on which, prior to the effective date of this AD, an aft engine 
mount assembly identified as ``New P/N'' in figure 1 to paragraphs 
(g), (h), (i), (j), (k), and (l) of this AD has been installed on 
the affected engine pylon (LH or RH), or on which the aft engine 
part assembly has been modified as specified in paragraph (h) of 
this AD: Within 30 days after the effective date of this AD, obtain 
repair instructions using 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), and accomplish those instructions 
accordingly. If approved by the DOA, the approval must include the 
DOA-authorized signature.

(m) Terminating Action and Method of Compliance

    (1) Modification of an airplane as required by paragraph (h) of 
this AD, or as specified in paragraph (i) of this AD, constitutes 
terminating action for the repetitive detailed inspections required 
by paragraph (l) of AD 2016-14-09 for that airplane.
    (2) Modification of an airplane as required by paragraph (h) of 
this AD, or as specified in paragraph (i) of this AD, is a method of 
compliance with the requirements of paragraph (g) of AD 2017-04-10 
for that airplane.

(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 
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): If any service information 
contains procedures or tests that are identified as RC, those 
procedures and tests must be done to comply

[[Page 10415]]

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) Special Flight Permits

    Special flight permits, as described in Section 21.197 and 
Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197 
and 21.199), are not allowed.

(p) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2017-0251 dated December 15, 
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-2018-0165.
    (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; telephone 
and fax 206-231-3223.
    (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 Aerospace service information identified in 
this AD, 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 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.

    Issued in Renton, Washington, on March 5, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-04727 Filed 3-8-18; 8:45 am]
 BILLING CODE 4910-13-P