Airworthiness Directives; Airbus SAS Airplanes, 38953-38957 [2018-16576]

Download as PDF Federal Register / Vol. 83, No. 153 / Wednesday, August 8, 2018 / Rules and Regulations 147 to reduce the risk of uncoupling between the low-pressure (LP) fuel pump impeller and the high-pressure (HP) fuel pump shaft of the HP/LP pump and hydro-mechanical metering unit (HMU). We are issuing this AD to prevent failure of the HMU. The unsafe condition, if not corrected, could result in failure of the engine, in-flight shutdown, and loss of the helicopter. (k) Related Information DEPARTMENT OF TRANSPORTATION Comply with this AD within the compliance times specified, unless already done. (1) For more information about this AD, contact John Frost, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 781–238– 7756; fax: 781–238–7199; email: john.frost@ faa.gov. (2) Refer to European Aviation Safety Agency (EASA) AD 2017–0102, dated June 13, 2017, for more information. You may examine the EASA AD on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2009–0889. (g) Required Actions (l) Material Incorporated by Reference (1) Check the transmissible torque between the LP fuel pump impeller and the HP fuel pump shaft as follows: (i) For pre-Modification TU 147 HMUs, check the torque before accumulating 500 engine flight hours (FHs) since March 11, 2010 or before the next flight after the effective date of this AD, whichever occurs later. Use Paragraph 2.A. of Turbomeca Alert Mandatory Service Bulletin (MSB) A292 73 2830, Version B, dated July 10, 2009 to do the check. (ii) For HMUs that incorporated Modification TU 147 on or before March 31, 2010, and those HMUs not listed in Figure 2 or 3 of Turbomeca Alert MSB A292 73 2836, Version A, dated August 17, 2010, check the torque before the next flight after the effective date of this AD. Use Paragraph 2.A. of Turbomeca Alert MSB A292 73 2836, Version A, dated August 17, 2010, to do the check. (2) If the HMU does not pass the torque check, replace the HMU with a postModification TU 178 HMU before the next flight after the effective date of this AD. (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 the AD specifies otherwise. (3) The following service information was approved for IBR on March 11, 2010 (75 FR 5689, February 4, 2010). (i) Turbomeca Alert Mandatory Service Bulletin (MSB) No. A292 73 2830, Version B, dated July 10, 2009. (ii) Reserved. (4) The following service information was approved for IBR on March 20, 2012 (77 FR 8092, February 14, 2012). (i) Turbomeca Alert MSB No. A292 73 2836, Version A, dated August 17, 2010. (ii) Reserved. (5) For Safran Helicopter Engines, S.A, service information identified in this AD, contact Safran Helicopter Engines, S.A., 40220 Tarnos, France; phone: (33) 05 59 74 40 00; fax: (33) 05 59 74 45 15. (6) You may view this service information at FAA, Engine and Propeller Standards Branch, 1200 District Avenue, Burlington, MA 01803. For information on the availability of this material at the FAA, call 781–238–7759. (7) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. (f) Compliance (h) Mandatory Terminating Action Within 2,200 engine FHs or 72 months after the effective date of this AD, whichever occurs first, replace any pre-Modification TU 178 HMU with a post-Modification TU 178 configuration HMU. (i) Installation Prohibition After the effective date of this AD, do not install a pre-Modification TU 178 HMU on engines incorporating a post-Modification TU 178 HMU. amozie on DSK3GDR082PROD with RULES (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, ECO 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 the attention of the person identified in paragraph (k)(1) of this AD. You may email your request to: ANE-AD-AMOC@ faa.gov. (2) 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. VerDate Sep<11>2014 16:30 Aug 07, 2018 Jkt 244001 Issued in Burlington, Massachusetts, on July 31, 2018. Robert J. Ganley, Manager, Engine and Propeller Standards Branch, Aircraft Certification Service. [FR Doc. 2018–16652 Filed 8–7–18; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00003 Fmt 4700 38953 Sfmt 4700 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0640; Product Identifier 2018–NM–075–AD; Amendment 39–19343; AD 2018–16–03] RIN 2120–AA64 Airworthiness Directives; Airbus SAS Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for all Airbus SAS Model A319–133 airplanes and Model A321–232 airplanes. This AD requires modification and reidentification, or replacement, of certain engine fan cowl doors (FCDs) and installation of a placard in the flight deck. This AD was prompted by reports of in-service engine FCD losses, and the development of a new FCD front latch and keeper assembly that addresses this unsafe condition. We are issuing this AD to address the unsafe condition on these products. DATES: This AD becomes effective August 23, 2018. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of August 3, 2017 (82 FR 29371, June 29, 2017). We must receive comments on this AD by September 24, 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 https://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: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this final rule, contact Airbus SAS, Airworthiness Office—EIAS, RondPoint Emile Dewoitine No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email SUMMARY: E:\FR\FM\08AUR1.SGM 08AUR1 38954 Federal Register / Vol. 83, No. 153 / Wednesday, August 8, 2018 / Rules and Regulations account.airworth-eas@airbus.com; internet https://www.airbus.com. 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 https:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 0640. Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 0640; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800–647–5527) is in the ADDRESSES section. 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: amozie on DSK3GDR082PROD with RULES The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2016–0053, dated March 14, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Model A319–131, –132, and –133 airplanes, Model A320–231, –232, and –233 airplanes, and Model A321–131, –231, and –232 airplanes. The MCAI states: Fan Cowl Door (FCD) losses during take-off were reported on aeroplanes equipped with IAE V2500 engines. Prompted by these ´ ´ occurrences, DGAC [Direction Generale de l’Aviation Civile] France issued AD 2000– 444–156(B), mandating FCD latch improvements. This [DGAC] AD was later superseded by [DGAC] AD 2001–381(B) [which corresponds to FAA AD 2003–18–06, Amendment 39–13297 (68 FR 53501, September 11, 2003)], requiring installation of additional fan cowl latch improvement by installing a hold open device. 16:30 Aug 07, 2018 Jkt 244001 You may examine the MCAI on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2018–0640. Related Service Information Under 1 CFR Part 51 Discussion VerDate Sep<11>2014 Since that [DGAC] AD was issued, further FCD in flight losses were experienced in service. Investigations confirmed that in all cases, the fan cowls were opened prior to the flight and were not correctly re-secured. During the pre-flight inspection, it was then not detected that the FCD were not properly latched. This condition, if not corrected, could lead to in-flight loss of a FCD, possibly resulting in damage to the aeroplane and/or injury to persons on the ground. Prompted by these recent events, new FCD front latch and keeper assembly were developed, having a specific key necessary to un-latch the FCD. This key cannot be removed unless the FCD front latch is safely closed. The key, after removal, must be stowed in the flight deck at a specific location, as instructed in the applicable Aircraft Maintenance Manual. Applicable Flight Crew Operating Manual has been amended accordingly. After modification, the FCD is identified with a different Part Number (P/N). For the reasons described above, this [EASA] AD retains the requirements of DGAC AD 2001–381(B), which is superseded, and requires modification and re-identification of FCD. Airbus has issued Service Bulletin A320–71–1069, Revision 01, including Appendix 01, dated April 28, 2016. This service information describes procedures for modifying the engine FCDs, installing placards, and reidentifying the FCDs with new part numbers. 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 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 issuing this AD because we evaluated all pertinent information and determined the unsafe condition exists and is likely to exist or develop on other products of these same type designs. PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 Differences Between This AD and the MCAI or Service Information The MCAI applies to Airbus SAS Model A319–131 and –132 airplanes; Model A320–231, –232, and –233 airplanes; and Model A321–131 and –231 airplanes, in addition to Model A319–133 airplanes and Model A321– 232 airplanes. The unsafe condition on Model A319–131 and –132 airplanes; Model A320–231, –232, and –233 airplanes; and Model A321–131 and –231 airplanes is already addressed in AD 2017–13–10, Amendment 39–18940 (82 FR 29371, June 29, 2017); therefore this AD only applies to Model A319– 133 airplanes and Model A321–232 airplanes. FAA’s Determination of the Effective Date There are currently no domestic operators of this product. Therefore, we find that notice and opportunity for prior public comment are unnecessary and that good cause exists for making this amendment effective in less than 30 days. Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2018–0640; Product Identifier 2018–NM–075–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD based on those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this AD. Costs of Compliance Currently, there are no affected U.S.registered airplanes. If an affected airplane is imported and placed on the U.S. Register in the future, we provide the following cost estimates to comply with this AD: E:\FR\FM\08AUR1.SGM 08AUR1 Federal Register / Vol. 83, No. 153 / Wednesday, August 8, 2018 / Rules and Regulations 38955 ESTIMATED COSTS FOR REQUIRED ACTIONS Labor cost Parts cost Cost per product 6 work-hours × $85 per hour = $510 ...................................................................................................................... $4,813 $5,323 Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes to the Director of the System Oversight Division. 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] ■ 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 amozie on DSK3GDR082PROD with RULES Regulatory Findings 2018–16–03 Airbus SAS: Amendment 39– 19343; Docket No. FAA–2018–0640; Product Identifier 2018–NM–075–AD. VerDate Sep<11>2014 16:30 Aug 07, 2018 Jkt 244001 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 (a) Effective Date This AD becomes effective August 23, 2018. (b) Affected ADs None. (c) Applicability This AD applies to Airbus SAS Model A319–133 airplanes and Model A321–232 airplanes, certificated in any category, all manufacturer serial numbers. (d) Subject Air Transport Association (ATA) of America Code 71, Powerplant. (e) Reason This AD was prompted by reports of inservice engine fan cowl door (FCD) losses, and the development of a new FCD front latch and keeper assembly that addresses this unsafe condition. We are issuing this AD to address in-flight loss of an engine FCD and possible consequent damage to the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Modification Within 36 months after the effective date of this AD, do the actions specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 71–1069, Revision 01, including Appendix 01, dated April 28, 2016. (1) Modify the left-hand and right-hand engine FCDs on engines 1 and 2. (2) Install a placard that specifies the FCD keys stowage location in the flight deck on the box located at the bottom of panel 120VU or at the bottom of the coat stowage, as applicable to airplane configuration. (3) Re-identify both engine FCDs with the new part numbers, as specified in figure 1 to paragraphs (g), (j), and (k) of this AD. E:\FR\FM\08AUR1.SGM 08AUR1 Federal Register / Vol. 83, No. 153 / Wednesday, August 8, 2018 / Rules and Regulations (h) Missing FCD Keys or Placard Flights with one or both FCD keys missing from the stowage location in the fight deck, or with the placard (that specifies the FCD keys stowage location) missing or damaged, are permitted for a period not to exceed 10 calendar days from the date of discovery. (i) Alternative Location of FCD Keys and Placard amozie on DSK3GDR082PROD with RULES As an option to paragraph (g)(2) of this AD, an alternative location for the key stowage in the flight deck and installation of a placard for identification of that stowage location are permitted as specified in the operator’s FAAaccepted maintenance or inspection program, provided the keys can be retrieved from that flight deck location when needed and the placard installation is done within 36 months after the effective date of this AD. (j) Optional Compliance by Replacement or Installation (1) Replacing an engine FCD having a part number listed as ‘‘Old Part Number’’ in figure 1 to paragraphs (g), (j), and (k) of this AD with an FCD having the corresponding part number listed as ‘‘New Part Number’’ in figure 1 to paragraphs (g), (j), and (k) of this AD is an acceptable method of compliance with the requirements of paragraphs (g)(1) and (g)(3) of this AD for that engine FCD only. (2) An airplane on which Airbus Modification 157516 has been embodied in production is compliant with the requirements of paragraphs (g)(1) and (g)(3) of this AD, provided no engine FCD having a part number identified as ‘‘Old Part Number’’ in figure 1 to paragraphs (g), (j), and (k) of this AD is installed on that airplane. (3) An airplane on which Airbus Modification 157718 has been embodied in VerDate Sep<11>2014 16:30 Aug 07, 2018 Jkt 244001 production is compliant with the requirements of paragraph (g)(2) of this AD. (4) Installation on an engine of a right-hand and left-hand engine FCD having a part number approved after the effective date of this AD is a method of compliance with the requirements of paragraphs (g)(1) and (g)(3) of this AD for that engine only, provided the part number is approved, and the installation is accomplished 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). If approved by the DOA, the approval must include the DOA-authorized signature. (k) Parts Installation Limitations (1) For an airplane with an engine FCD installed having a part number identified as ‘‘Old Part Number’’ in figure 1 to paragraphs (g), (j), and (k) of this AD: After modification of that airplane as required by paragraph (g) of this AD, do not install an engine FCD, having a part number identified as ‘‘Old Part Number’’ in figure 1 to paragraphs (g), (j), and (k) of this AD. (2) For an airplane that does not have an engine FCD installed having a part number identified as ‘‘Old Part Number’’ in figure 1 to paragraphs (g), (j), and (k) of this AD: On or after the effective date of this AD, do not install an engine FCD having a part number identified as ‘‘Old Part Number’’ in figure 1 to paragraphs (g), (j), and (k) of this AD. (l) Credit for Previous Actions This paragraph provides credit for actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320–71–1069, dated December 18, 2015. PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 (m) 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 (n)(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. (n) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2016–0053, dated March 14, 2016, for related information. You may examine the MCAI on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA– 2018–0640. (2) For more information about this AD, contact Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards E:\FR\FM\08AUR1.SGM 08AUR1 ER08AU18.002</GPH> 38956 Federal Register / Vol. 83, No. 153 / Wednesday, August 8, 2018 / Rules and Regulations Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206– 231–3223. (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (o)(4) and (o)(5) of this AD. (o) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (3) The following service information was approved for IBR on August 3, 2017 (82 FR 29371, June 29, 2017). (i) Airbus Service Bulletin A320–71–1069, Revision 01, including Appendix 01, dated April 28, 2016. (ii) Reserved. (4) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EIAS, Rond-Point Emile Dewoitine No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ airbus.com; internet https://www.airbus.com. (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: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Des Moines, Washington, on July 23, 2018. James Cashdollar, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018–16576 Filed 8–7–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0276; Product Identifier 2017–NM–079–AD; Amendment 39–19346; AD 2018–16–06] RIN 2120–AA64 amozie on DSK3GDR082PROD with RULES Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747–100, SUMMARY: VerDate Sep<11>2014 16:30 Aug 07, 2018 Jkt 244001 –100B, –100B SUD, –200B, –200C, –200F, –300, –400, –400D, 747SP, and 747SR, and 747–8 series airplanes. This AD was prompted by reports indicating that additional areas of Boeing Material Specification (BMS) 8–39 flexible urethane foam were found during an inspection required by a related AD. This AD requires inspecting for BMS 8– 39 flexible urethane foam insulation in the floor panel assemblies and the power drive unit (PDU) cover assemblies, doing applicable oncondition actions, modifying certain dripshields, and replacing BMS 8–39 foam strips on certain dripshields with BMS 8–371 foam strips. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective September 12, 2018. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of September 12, 2018. ADDRESSES: For service information identified in this final rule, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110–SK57, Seal Beach, CA 90740–5600; telephone 562–797–1717; internet https://www.myboeingfleet.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. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2018– 0276. Examining the AD Docket You may examine the AD docket on the internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 0276; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, the regulatory evaluation, any comments received, and other information. The address for Docket Operations (phone: 800–647–5527) is Docket Operations, 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: Scott Craig, Aerospace Engineer, Cabin Safety and Environmental Systems Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des Moines, WA 98198; phone and fax: 206–231–3566; email: Michael.S.Craig@faa.gov. PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 38957 SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain The Boeing Company Model 747–100, –100B, –100B SUD, –200B, –200C, –200F, –300, –400, –400D, 747SP, and 747SR, and 747–8 series airplanes. The NPRM published in the Federal Register on April 17, 2018 (83 FR 16796). The NPRM was prompted by reports indicating that additional areas of BMS 8–39 flexible urethane foam were found during an inspection required by a related AD. The NPRM proposed to require inspecting for BMS 8–39 flexible urethane foam insulation in the floor panel assemblies and the PDU cover assemblies, doing applicable oncondition actions, modifying certain dripshields, and replacing BMS 8–39 foam strips on certain dripshields with BMS 8–371 foam strips. We are issuing this AD to address BMS 8–39 flexible urethane foam in certain areas, which, if exposed to an ignition source, could cause an uncontrolled fire leading to loss of control of the airplane. Comments We gave the public the opportunity to participate in developing this final rule. We have considered the comment received. Boeing stated that it had no objection to the NPRM. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this final rule as proposed, except for minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM for addressing the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. Related Service Information Under 1 CFR Part 51 We reviewed the following Boeing service information. • Boeing Special Attention Service Bulletin 747–53–2877, dated August 5, 2014, which describes procedures for performing a general visual inspection for BMS 8–39 flexible urethane foam insulation in the floor panel assemblies and the PDU cover assemblies, and applicable on-condition actions. • Boeing Special Attention Service Bulletin 747–25–3646, Revision 1, dated E:\FR\FM\08AUR1.SGM 08AUR1

Agencies

[Federal Register Volume 83, Number 153 (Wednesday, August 8, 2018)]
[Rules and Regulations]
[Pages 38953-38957]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-16576]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0640; Product Identifier 2018-NM-075-AD; Amendment 
39-19343; AD 2018-16-03]
RIN 2120-AA64


Airworthiness Directives; Airbus SAS Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Airbus SAS Model A319-133 airplanes and Model A321-232 airplanes. This 
AD requires modification and re-identification, or replacement, of 
certain engine fan cowl doors (FCDs) and installation of a placard in 
the flight deck. This AD was prompted by reports of in-service engine 
FCD losses, and the development of a new FCD front latch and keeper 
assembly that addresses this unsafe condition. We are issuing this AD 
to address the unsafe condition on these products.

DATES: This AD becomes effective August 23, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of August 3, 
2017 (82 FR 29371, June 29, 2017).
    We must receive comments on this AD by September 24, 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 https://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: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this final rule, contact 
Airbus SAS, Airworthiness Office--EIAS, Rond-Point Emile Dewoitine No: 
2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 
61 93 44 51; email

[[Page 38954]]

[email protected]; internet https://www.airbus.com. 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 https://www.regulations.gov by 
searching for and locating Docket No. FAA-2018-0640.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0640; or in person at the Docket Operations office between 9 a.m. and 5 
p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The street address for the Docket Operations office 
(telephone 800-647-5527) is in the ADDRESSES section. 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:

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2016-0053, dated March 14, 2016 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for all Airbus Model A319-131, -132, and -
133 airplanes, Model A320-231, -232, and -233 airplanes, and Model 
A321-131, -231, and -232 airplanes. The MCAI states:

    Fan Cowl Door (FCD) losses during take-off were reported on 
aeroplanes equipped with IAE V2500 engines. Prompted by these 
occurrences, DGAC [Direction G[eacute]n[eacute]rale de l'Aviation 
Civile] France issued AD 2000-444-156(B), mandating FCD latch 
improvements. This [DGAC] AD was later superseded by [DGAC] AD 2001-
381(B) [which corresponds to FAA AD 2003-18-06, Amendment 39-13297 
(68 FR 53501, September 11, 2003)], requiring installation of 
additional fan cowl latch improvement by installing a hold open 
device.
    Since that [DGAC] AD was issued, further FCD in flight losses 
were experienced in service. Investigations confirmed that in all 
cases, the fan cowls were opened prior to the flight and were not 
correctly re-secured. During the pre-flight inspection, it was then 
not detected that the FCD were not properly latched.
    This condition, if not corrected, could lead to in-flight loss 
of a FCD, possibly resulting in damage to the aeroplane and/or 
injury to persons on the ground.
    Prompted by these recent events, new FCD front latch and keeper 
assembly were developed, having a specific key necessary to un-latch 
the FCD. This key cannot be removed unless the FCD front latch is 
safely closed. The key, after removal, must be stowed in the flight 
deck at a specific location, as instructed in the applicable 
Aircraft Maintenance Manual. Applicable Flight Crew Operating Manual 
has been amended accordingly. After modification, the FCD is 
identified with a different Part Number (P/N).
    For the reasons described above, this [EASA] AD retains the 
requirements of DGAC AD 2001-381(B), which is superseded, and 
requires modification and re-identification of FCD.

    You may examine the MCAI on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0640.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A320-71-1069, Revision 01, 
including Appendix 01, dated April 28, 2016. This service information 
describes procedures for modifying the engine FCDs, installing 
placards, and re-identifying the FCDs with new part numbers. 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 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 issuing this AD because we 
evaluated all pertinent information and determined the unsafe condition 
exists and is likely to exist or develop on other products of these 
same type designs.

Differences Between This AD and the MCAI or Service Information

    The MCAI applies to Airbus SAS Model A319-131 and -132 airplanes; 
Model A320-231, -232, and -233 airplanes; and Model A321-131 and -231 
airplanes, in addition to Model A319-133 airplanes and Model A321-232 
airplanes. The unsafe condition on Model A319-131 and -132 airplanes; 
Model A320-231, -232, and -233 airplanes; and Model A321-131 and -231 
airplanes is already addressed in AD 2017-13-10, Amendment 39-18940 (82 
FR 29371, June 29, 2017); therefore this AD only applies to Model A319-
133 airplanes and Model A321-232 airplanes.

FAA's Determination of the Effective Date

    There are currently no domestic operators of this product. 
Therefore, we find that notice and opportunity for prior public comment 
are unnecessary and that good cause exists for making this amendment 
effective in less than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2018-0640; Product 
Identifier 2018-NM-075-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this AD based on 
those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this AD.

Costs of Compliance

    Currently, there are no affected U.S.-registered airplanes. If an 
affected airplane is imported and placed on the U.S. Register in the 
future, we provide the following cost estimates to comply with this AD:

[[Page 38955]]



                  Estimated Costs for Required Actions
------------------------------------------------------------------------
                                                             Cost per
              Labor cost                   Parts cost        product
------------------------------------------------------------------------
6 work-hours x $85 per hour = $510....          $4,813           $5,323
------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII: Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to transport category airplanes to 
the Director of the System Oversight Division.

Regulatory Findings

    We determined that this AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2018-16-03 Airbus SAS: Amendment 39-19343; Docket No. FAA-2018-0640; 
Product Identifier 2018-NM-075-AD.

(a) Effective Date

    This AD becomes effective August 23, 2018.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus SAS Model A319-133 airplanes and Model 
A321-232 airplanes, certificated in any category, all manufacturer 
serial numbers.

(d) Subject

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

(e) Reason

    This AD was prompted by reports of in-service engine fan cowl 
door (FCD) losses, and the development of a new FCD front latch and 
keeper assembly that addresses this unsafe condition. We are issuing 
this AD to address in-flight loss of an engine FCD and possible 
consequent damage to the airplane.

(f) Compliance

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

(g) Modification

    Within 36 months after the effective date of this AD, do the 
actions specified in paragraphs (g)(1), (g)(2), and (g)(3) of this 
AD, in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A320-71-1069, Revision 01, including Appendix 01, 
dated April 28, 2016.
    (1) Modify the left-hand and right-hand engine FCDs on engines 1 
and 2.
    (2) Install a placard that specifies the FCD keys stowage 
location in the flight deck on the box located at the bottom of 
panel 120VU or at the bottom of the coat stowage, as applicable to 
airplane configuration.
    (3) Re-identify both engine FCDs with the new part numbers, as 
specified in figure 1 to paragraphs (g), (j), and (k) of this AD.

[[Page 38956]]

[GRAPHIC] [TIFF OMITTED] TR08AU18.002

(h) Missing FCD Keys or Placard

    Flights with one or both FCD keys missing from the stowage 
location in the fight deck, or with the placard (that specifies the 
FCD keys stowage location) missing or damaged, are permitted for a 
period not to exceed 10 calendar days from the date of discovery.

(i) Alternative Location of FCD Keys and Placard

    As an option to paragraph (g)(2) of this AD, an alternative 
location for the key stowage in the flight deck and installation of 
a placard for identification of that stowage location are permitted 
as specified in the operator's FAA-accepted maintenance or 
inspection program, provided the keys can be retrieved from that 
flight deck location when needed and the placard installation is 
done within 36 months after the effective date of this AD.

(j) Optional Compliance by Replacement or Installation

    (1) Replacing an engine FCD having a part number listed as ``Old 
Part Number'' in figure 1 to paragraphs (g), (j), and (k) of this AD 
with an FCD having the corresponding part number listed as ``New 
Part Number'' in figure 1 to paragraphs (g), (j), and (k) of this AD 
is an acceptable method of compliance with the requirements of 
paragraphs (g)(1) and (g)(3) of this AD for that engine FCD only.
    (2) An airplane on which Airbus Modification 157516 has been 
embodied in production is compliant with the requirements of 
paragraphs (g)(1) and (g)(3) of this AD, provided no engine FCD 
having a part number identified as ``Old Part Number'' in figure 1 
to paragraphs (g), (j), and (k) of this AD is installed on that 
airplane.
    (3) An airplane on which Airbus Modification 157718 has been 
embodied in production is compliant with the requirements of 
paragraph (g)(2) of this AD.
    (4) Installation on an engine of a right-hand and left-hand 
engine FCD having a part number approved after the effective date of 
this AD is a method of compliance with the requirements of 
paragraphs (g)(1) and (g)(3) of this AD for that engine only, 
provided the part number is approved, and the installation is 
accomplished 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). If approved by the DOA, the approval must include the DOA-
authorized signature.

(k) Parts Installation Limitations

    (1) For an airplane with an engine FCD installed having a part 
number identified as ``Old Part Number'' in figure 1 to paragraphs 
(g), (j), and (k) of this AD: After modification of that airplane as 
required by paragraph (g) of this AD, do not install an engine FCD, 
having a part number identified as ``Old Part Number'' in figure 1 
to paragraphs (g), (j), and (k) of this AD.
    (2) For an airplane that does not have an engine FCD installed 
having a part number identified as ``Old Part Number'' in figure 1 
to paragraphs (g), (j), and (k) of this AD: On or after the 
effective date of this AD, do not install an engine FCD having a 
part number identified as ``Old Part Number'' in figure 1 to 
paragraphs (g), (j), and (k) of this AD.

(l) Credit for Previous Actions

    This paragraph provides credit for actions required by paragraph 
(g) of this AD, if those actions were performed before the effective 
date of this AD using Airbus Service Bulletin A320-71-1069, dated 
December 18, 2015.

(m) 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 (n)(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.

(n) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2016-0053, dated March 14, 2016, for related 
information. You may examine the MCAI on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-
2018-0640.
    (2) For more information about this AD, contact Sanjay Ralhan, 
Aerospace Engineer, International Section, Transport Standards

[[Page 38957]]

Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone 
and fax 206-231-3223.
    (3) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (o)(4) and (o)(5) of this AD.

(o) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (3) The following service information was approved for IBR on 
August 3, 2017 (82 FR 29371, June 29, 2017).
    (i) Airbus Service Bulletin A320-71-1069, Revision 01, including 
Appendix 01, dated April 28, 2016.
    (ii) Reserved.
    (4) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EIAS, Rond-Point Emile Dewoitine 
No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax 
+33 5 61 93 44 51; email [email protected]; internet 
https://www.airbus.com.
    (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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Des Moines, Washington, on July 23, 2018.
James Cashdollar,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-16576 Filed 8-7-18; 8:45 am]
 BILLING CODE 4910-13-P
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