Airworthiness Directives; Airbus SAS Airplanes, 51819-51823 [2018-21963]

Download as PDF Federal Register / Vol. 83, No. 199 / Monday, October 15, 2018 / Rules and Regulations of airworthiness; or within 7,500 flight hours or 36 months, whichever occurs first, after the most recent inspection was performed as specified in AWL No. 28–AWL–101; whichever is later. (h) Additional Acceptable Wire Types and Sleeving As an option, when accomplishing the actions required by paragraph (g) of this AD, the changes specified in paragraphs (h)(1) and (h)(2) of this AD are acceptable. (1) Where AWL No. 28–AWL–05 identifies wire types BMS 13–48, BMS 13–58, and BMS 13–60, the following wire types are acceptable: MIL–W–22759/16, SAE AS22759/16 (M22759/16), MIL–W–22759/32, SAE AS22759/32 (M22759/32), MIL–W– 22759/34, SAE AS22759/34 (M22759/34), MIL–W–22759/41, SAE AS22759/41 (M22759/41), MIL–W–22759/86, SAE AS22759/86 (M22759/86), MIL–W–22759/87, SAE AS22759/87 (M22759/87), MIL–W– 22759/92, and SAE AS22759/92 (M22759/ 92); and MIL–C–27500 and NEMA WC 27500 cables constructed from these military or SAE specification wire types, as applicable. (2) Where AWL No. 28–AWL–05 identifies TFE–2X Standard wall for wire sleeving, the following sleeving materials are acceptable: Roundit 2000NX and Varglas Type HO, HP, or HM. (i) No Alternative Actions, Intervals, and Critical Design Configuration Control Limitations (CDCCLs) Except as provided in paragraph (h) of this AD, after the maintenance or inspection program, as applicable, has been revised as required by paragraph (g) of this AD, no alternative actions (e.g., inspections), intervals, and CDCCLs may be used unless the actions, intervals, and CDCCLs are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (k) of this AD. khammond on DSK30JT082PROD with RULES (j) Terminating Actions for Certain AD Requirements Accomplishment of the revision required by paragraph (g) of this AD terminates the requirements specified in paragraphs (j)(1) through (j)(5) of this AD for that airplane: (1) The revision required by paragraphs (h) and (h)(1) of AD 2008–06–03. (2) All requirements of AD 2008–10–10 R1. (3) The revision required by paragraph (g) of AD 2008–17–15. (4) The revision required by paragraph (k) of AD 2011–18–03. (5) All requirements of AD 2013–15–17. (k) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle 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 the attention of the person identified in paragraph (l) of this AD. Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. VerDate Sep<11>2014 16:29 Oct 12, 2018 Jkt 247001 (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. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO Branch, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (l) Related Information For more information about this AD, contact Tak Kobayashi, Aerospace Engineer, Propulsion Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des Moines, WA 98198; phone and fax: 206–231–3553; email: takahisa.kobayashi@faa.gov. (m) 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 the AD specifies otherwise. (i) Boeing 737–600/700/700C/800/900/ 900ER Special Compliance Items/ Airworthiness Limitations, D626A001–9–04, Revision January 2017. (ii) Reserved. (3) For service information identified in this AD, 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. (4) 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. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Des Moines, Washington, on September 19, 2018. John P. Piccola, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018–21971 Filed 10–12–18; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 51819 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0358; Product Identifier 2017–NM–142–AD; Amendment 39–19463; AD 2018–21–05] RIN 2120–AA64 Airworthiness Directives; Airbus SAS Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain Airbus SAS Model A319–131, A319– 132, A319–133, A320–231, A320–232, A320–233, A321–131, A321–231, and A321–232 airplanes. This AD was prompted by reports of fan cowl door (FCD) losses during take-off. This AD requires modification and reidentification, or replacement, of certain FCDs, and installation of a placard in the flight deck. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective November 19, 2018. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of November 19, 2018. ADDRESSES: 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 account.airwortheas@airbus.com; internet http:// www.airbus.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 http://www.regulations.gov by searching for and locating Docket No. FAA–2018– 0358. SUMMARY: 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– 0358; 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 E:\FR\FM\15OCR1.SGM 15OCR1 51820 Federal Register / Vol. 83, No. 199 / Monday, October 15, 2018 / Rules and Regulations information. The address for Docket Operations (phone: 800–647–5527) is U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3223. SUPPLEMENTARY INFORMATION: khammond on DSK30JT082PROD with RULES Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Airbus SAS Model A319–131, A319–132, A319–133, A320– 231, A320–232, A320–233, A321–131, A321–231, and A321–232 airplanes. The NPRM published in the Federal Register on May 4, 2018 (83 FR 19648). The NPRM was prompted by reports of FCD losses during take-off. The NPRM proposed to require modification and reidentification, or replacement, of certain FCDs, and installation of a placard in the flight deck. We are issuing this AD to address inflight loss of an FCD, which could result in damage to the airplane and injury to persons on the ground. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2017–0178, dated September 15, 2017 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus SAS Model A319– 131, A319–132, A319–133, A320–231, A320–232, A320–233, A321–131, A321– 231, and A321–232 airplanes. The MCAI states: Fan Cowl Door (FCD) losses during take-off were reported on Airbus A320 family aeroplanes equipped with IAE [International Aero Engines] V2500 engines. Investigations confirmed that in all cases, the FCD were opened prior to the flight and were not correctly re-secured. During the pre-flight inspection, it was not detected that the FCD were not properly latched. This condition, if not corrected, could lead to in-flight loss of an FCD, possibly resulting in damage to the aeroplane and/or injury to persons on the ground. EASA issued AD 2016–0053 [which corresponds to FAA AD 2017–13–10, Amendment 39–18940 (82 FR 29371, June VerDate Sep<11>2014 16:29 Oct 12, 2018 Jkt 247001 29, 2017) (‘‘AD 2017–13–10’’)], requiring modification of the FCD installed on affected aeroplanes, and installation of a placard in the cockpit, in accordance with the instructions of Airbus Service Bulletin (SB) A320–71–1069 (which in turns refers to Goodrich SB V2500–NAC–71–0331 for FCD modification and re-identification). The monolithic FCDs, installed on aeroplanes embodying Short Brothers supplemental type certificate (STC) 10029547, are also affected by this potential unsafe condition. Consequently, the STC Holder, trading as Bombardier Short Brothers, developed a modification, similar to the one designed by Airbus, and issued SB V25MFC–71–1003. The modification consists of a new FCD front latch and keeper assembly, 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. The applicable Flight Crew Operating Manual has been amended accordingly. After modification, the FCD is identified with a different Part Number (P/N). Mixed FCD installation can be found on aeroplanes embodying [EASA] STC 10029547 (i.e., Monolithic FCD and standard production non-Monolithic FCD). For standard production non-Monolithic FCD, Bombardier Short Brothers SB V25MFC–71– 1003 specifies to accomplish the instructions of Goodrich SB V2500–NAC–71–0331, as applicable. For the reasons described above, this [EASA] AD requires modification and reidentification of FCD, and installation of a placard in the cockpit. 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– 0358. Comments We gave the public the opportunity to participate in developing this final rule. The following presents the comments received on the NPRM and the FAA’s response to each comment. Support for the NPRM The Air Line Pilots Association, International (ALPA) supported the NPRM. Request To Extend Compliance Time United Airlines (UAL) requested that the compliance time stated in the proposed AD be extended from 18 months to 36 months to match the compliance time stated in AD 2017–13– 10. UAL noted that both the proposed PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 AD and AD 2017–13–10 address the same unsafe condition, but on different FCDs. UAL added that it has a mixture of FCD configurations, which will be subject to different compliance times. We disagree with the commenter’s request to extend the compliance time to 36 months. We based the compliance time for this AD on the compliance time required by the EASA MCAI, which was determined by considering the urgency associated with the unsafe condition, the availability of required parts, and the practical aspect of accomplishing the required modification within a timeframe that corresponds to the normal scheduled maintenance for most affected operators. In addition, the manufacturer recommended that the service bulletin be accomplished no later than March 28, 2019. We have not changed this AD in this regard. Conclusion We reviewed the relevant data and determined that air safety and the public interest require adopting this final rule as proposed with the changes described previously and minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM for addressing the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this final rule. Related Service Information Under 1 CFR Part 51 Bombardier Short Brothers, PLC has issued Service Bulletin V25MFC–71– 1003, dated September 28, 2016. The service information describes procedures for installing modified latches on the left and right engine FCDs, and re-identifying the FCDs. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Costs of Compliance We estimate that this AD affects 557 airplanes of U.S. registry. We estimate the following costs to comply with this AD: E:\FR\FM\15OCR1.SGM 15OCR1 Federal Register / Vol. 83, No. 199 / Monday, October 15, 2018 / Rules and Regulations 51821 ESTIMATED COSTS Action Labor cost Modification and re-identification (or replacement), and placard installation. 8 work-hours × $85 per hour = $680 ............. 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 and associated appliances to the Director of the System Oversight Division. khammond on DSK30JT082PROD with RULES Regulatory Findings 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 VerDate Sep<11>2014 16:29 Oct 12, 2018 Jkt 247001 Parts cost 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] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ 2018–21–05 Airbus SAS: Amendment 39– 19463; Docket No. FAA–2018–0358; Product Identifier 2017–NM–142–AD. (a) Effective Date This AD is effective November 19, 2018. PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 $1,500 Cost per product $2,180 Cost on U.S. operators $1,214,260 (b) Affected ADs None. (c) Applicability This AD applies to Airbus SAS Model A319–131, A319–132, A319–133, A320–231, A320–232, A320–233, A321–131, A321–231, and A321–232 airplanes, certificated in any category, if modified by Bombardier Short Brothers, PLC Supplemental Type Certificate (STC) ST03076NY. (d) Subject Air Transport Association (ATA) of America Code 71, Powerplant. (e) Reason This AD was prompted by reports of fan cowl door (FCD) losses during takeoff. We are issuing this AD to prevent in-flight loss of an FCD, which could result in damage to the airplane and injury to persons on the ground. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Modification and Re-Identification of FCDs Within 18 months after the effective date of this AD: Do the modification and reidentification specified in paragraphs (g)(1) and (g)(2) of this AD. (1) Modify each left-hand (LH) and righthand (RH) FCD having a part number listed as ‘‘Old Part Number’’ in table 1 to paragraphs (g), (h), and (l) of this AD, in accordance with the Accomplishment Instructions of Bombardier Short Brothers Service Bulletin V25MFC–71–1003, dated September 28, 2016. (2) Re-identify each modified FCD with the part number listed as ‘‘New Part Number’’ in table 1 to paragraphs (g), (h), and (l) of this AD, in accordance with the Accomplishment Instructions of Bombardier Short Brothers Service Bulletin V25MFC–71–1003, dated September 28, 2016. E:\FR\FM\15OCR1.SGM 15OCR1 Federal Register / Vol. 83, No. 199 / Monday, October 15, 2018 / Rules and Regulations khammond on DSK30JT082PROD with RULES (h) Optional Compliance by Replacement or Installation (1) Replacement of the FCDs having a part number listed as ‘‘Old Part Number’’ in table 1 to paragraphs (g), (h), and (l) of this AD, with the FCDs having the corresponding part number listed as ‘‘New Part Number’’ in table 1 to paragraphs (g), (h), and (l) of this AD, is acceptable for compliance with the requirements of paragraph (g) of this AD. (2) Installation on an engine of a LH and RH FCD having a part number approved after the effective date of this AD is acceptable for compliance with the requirements of paragraph (g) of this AD for that engine only, provided the conditions specified in paragraphs (h)(2)(i) and (h)(2)(ii) of this AD are met. (i) The part number is approved using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Bombardier Short Brothers, PLC’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOAauthorized signature. (ii) The installation is accomplished using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Bombardier Short Brothers, PLC’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (i) Placard Installation For airplanes on which Airbus SAS modification 157718 has not been embodied in production: Within 18 months after the effective date of this AD, install a placard that specifies the FCD keys stowage location in the flight deck on the box located at the bottom of the 120VU panel, or at the bottom of the coat stowage, as applicable to airplane configuration, using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Bombardier Short Brothers, PLC’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (j) 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 VerDate Sep<11>2014 16:29 Oct 12, 2018 Jkt 247001 keys stowage location) missing or damaged, are permitted for a period not to exceed 10 calendar days from the date of discovery. (k) Alternate Location of FCD Keys and Placard As an option to paragraph (i) of this AD, an alternate 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 18 months after the effective date of this AD. (l) Parts Installation Prohibition No person may install on any airplane an FCD with a part number identified as ‘‘Old Part Number’’ in table 1 to paragraphs (g), (h), and (l) of this AD, after the time specified in paragraph (l)(1) or (l)(2) of this AD, as applicable. (1) For any airplane with an installed FCD having a part number identified as ‘‘Old Part Number’’ in table 1 to paragraphs (g), (h), and (l) of this AD: After modification of that airplane as required by paragraph (g) of this AD or as specified in paragraph (h) of this AD. (2) For any airplane without an installed FCD having a part number identified as ‘‘Old Part Number’’ in table 1 to paragraphs (g), (h), and (l) of this AD: After the effective date of this AD. (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 PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 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 Bombardier Short Brothers, PLC’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 2017–0178, dated September 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–2018–0358. (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. (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. (i) Bombardier Short Brothers Service Bulletin V25MFC–71–1003, dated September 28, 2016. (ii) Reserved. (3) For service information identified in this AD, contact Bombardier Short Brothers, PLC, Airworthiness, P.O. Box 241, Airport Road, Belfast, BT3 9DZ Northern Ireland; telephone +44(0)2890–462469; fax +44(0)2890–468444; email michael.mulholland@aero.bombardier.com; internet http://www.bombardier.com. (4) 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. E:\FR\FM\15OCR1.SGM 15OCR1 ER15OC18.000</GPH> 51822 Federal Register / Vol. 83, No. 199 / Monday, October 15, 2018 / Rules and Regulations (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Des Moines, Washington, on September 20, 2018. John P. Piccola, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018–21963 Filed 10–12–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0546; Product Identifier 2017–NM–171–AD; Amendment 39–19461; AD 2018–21–03] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc., Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD–700–1A10 and BD–700–1A11 airplanes. This AD was prompted by reports of multiple inflight departures of the aft belly fairing access panels. This AD requires modification of the aft belly fairing access panels. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective November 19, 2018. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of November 19, 2018. ADDRESSES: For service information identified in this final rule, contact Bombardier, Inc., 400 Coˆte Vertu Road West, Dorval, Que´bec 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 service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2018– 0546. khammond on DSK30JT082PROD with RULES SUMMARY: VerDate Sep<11>2014 16:29 Oct 12, 2018 Jkt 247001 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– 0546; 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 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: Andrea Jimenez, Aerospace Engineer, Airframe and Propulsion Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7330; fax 516–794–5531; email 9-avs-nyaco-cos@ faa.gov. 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 Bombardier, Inc., Model BD–700–1A10 and BD–700–1A11 airplanes. The NPRM published in the Federal Register on June 20, 2018 (83 FR 28553). The NPRM was prompted by reports of multiple in-flight departures of the aft belly fairing access panels. The NPRM proposed to require modification of the aft belly fairing access panels. We are issuing this AD to address inflight departures of the aft belly fairing access panels, which could result in runway hazards or hazards to people on the ground. Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian AD CF–2017–31, dated September 22, 2017 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Bombardier, Inc., Model BD–700–1A10 and BD–700– 1A11 airplanes. The MCAI states: There have been multiple in-service occurrences where operators reported inflight departure of the aft belly fairing access panels, 185CL and/or 186CR. There has been no damage reported to the affected aircraft to date, however departure of the panels in any phase of flight could create runway hazards or a hazard to persons and property on the ground. Bombardier Inc. has issued Service Bulletins (SBs) to incorporate new selflocking nutplates with associated hardware (retaining rings and studs) to improve PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 51823 fastener engagement. A bracket has also been added to provide two additional panel attachment points. This [Canadian] AD requires the incorporation of these design changes to prevent departure of the two aft belly fairing access panels in flight and the associated risk on the ground. 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– 0546. Comments We gave the public the opportunity to participate in developing this final rule. The following presents the comment received on the NPRM and the FAA’s response to that comment. Request To Include Additional Document in Credit for Previous Actions Paragraph Bombardier requested that paragraph (h) of the proposed AD, ‘‘Credit for Previous Actions,’’ be revised to include Bombardier Service Request for Product Support Action 124026 (‘‘SRPSA 124026’’). The requester noted that Canadian AD CF–2017–31, dated September 22, 2017, included a statement that incorporation of the actions described in Bombardier SRPSA 124026 on an airplane satisfies the intent of the Canadian AD. The commenter also noted that Bombardier SRPSA 124026 was utilized on a U.S.registered airplane having number N211PB and serial number 9378. We agree with the commenter’s request for the reasons provided by the commenter. We have added paragraph (h)(2) to this AD to provide credit for airplanes on which Bombardier SRPSA 124026 has been incorporated. Conclusion We reviewed the relevant data, considered the comment received, and determined that air safety and the public interest require adopting this final rule with the change described previously, and minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM for addressing the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this final rule. E:\FR\FM\15OCR1.SGM 15OCR1

Agencies

[Federal Register Volume 83, Number 199 (Monday, October 15, 2018)]
[Rules and Regulations]
[Pages 51819-51823]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-21963]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0358; Product Identifier 2017-NM-142-AD; Amendment 
39-19463; AD 2018-21-05]
RIN 2120-AA64


Airworthiness Directives; Airbus SAS Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Airbus SAS Model A319-131, A319-132, A319-133, A320-231, A320-232, 
A320-233, A321-131, A321-231, and A321-232 airplanes. This AD was 
prompted by reports of fan cowl door (FCD) losses during take-off. This 
AD requires modification and re-identification, or replacement, of 
certain FCDs, and installation of a placard in the flight deck. We are 
issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective November 19, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of November 19, 
2018.

ADDRESSES: 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 [email protected]; 
internet http://www.airbus.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 http://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0358.

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-
0358; 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

[[Page 51820]]

information. The address for Docket Operations (phone: 800-647-5527) is 
U.S. Department of Transportation, Docket Operations, M-30, West 
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, 
Washington, DC 20590.

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

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to certain Airbus SAS Model 
A319-131, A319-132, A319-133, A320-231, A320-232, A320-233, A321-131, 
A321-231, and A321-232 airplanes. The NPRM published in the Federal 
Register on May 4, 2018 (83 FR 19648). The NPRM was prompted by reports 
of FCD losses during take-off. The NPRM proposed to require 
modification and re-identification, or replacement, of certain FCDs, 
and installation of a placard in the flight deck.
    We are issuing this AD to address in-flight loss of an FCD, which 
could result in damage to the airplane and injury to persons on the 
ground.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2017-0178, dated September 15, 2017 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for certain Airbus SAS Model A319-131, 
A319-132, A319-133, A320-231, A320-232, A320-233, A321-131, A321-231, 
and A321-232 airplanes. The MCAI states:

    Fan Cowl Door (FCD) losses during take-off were reported on 
Airbus A320 family aeroplanes equipped with IAE [International Aero 
Engines] V2500 engines. Investigations confirmed that in all cases, 
the FCD were opened prior to the flight and were not correctly re-
secured. During the pre-flight inspection, it was not detected that 
the FCD were not properly latched.
    This condition, if not corrected, could lead to in-flight loss 
of an FCD, possibly resulting in damage to the aeroplane and/or 
injury to persons on the ground.
    EASA issued AD 2016-0053 [which corresponds to FAA AD 2017-13-
10, Amendment 39-18940 (82 FR 29371, June 29, 2017) (``AD 2017-13-
10'')], requiring modification of the FCD installed on affected 
aeroplanes, and installation of a placard in the cockpit, in 
accordance with the instructions of Airbus Service Bulletin (SB) 
A320-71-1069 (which in turns refers to Goodrich SB V2500-NAC-71-0331 
for FCD modification and re-identification).
    The monolithic FCDs, installed on aeroplanes embodying Short 
Brothers supplemental type certificate (STC) 10029547, are also 
affected by this potential unsafe condition. Consequently, the STC 
Holder, trading as Bombardier Short Brothers, developed a 
modification, similar to the one designed by Airbus, and issued SB 
V25MFC-71-1003. The modification consists of a new FCD front latch 
and keeper assembly, 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. The applicable Flight Crew Operating Manual has 
been amended accordingly. After modification, the FCD is identified 
with a different Part Number (P/N).
    Mixed FCD installation can be found on aeroplanes embodying 
[EASA] STC 10029547 (i.e., Monolithic FCD and standard production 
non-Monolithic FCD). For standard production non-Monolithic FCD, 
Bombardier Short Brothers SB V25MFC-71-1003 specifies to accomplish 
the instructions of Goodrich SB V2500-NAC-71-0331, as applicable.
    For the reasons described above, this [EASA] AD requires 
modification and re-identification of FCD, and installation of a 
placard in the cockpit.

    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-
0358.

Comments

    We gave the public the opportunity to participate in developing 
this final rule. The following presents the comments received on the 
NPRM and the FAA's response to each comment.

Support for the NPRM

    The Air Line Pilots Association, International (ALPA) supported the 
NPRM.

Request To Extend Compliance Time

    United Airlines (UAL) requested that the compliance time stated in 
the proposed AD be extended from 18 months to 36 months to match the 
compliance time stated in AD 2017-13-10. UAL noted that both the 
proposed AD and AD 2017-13-10 address the same unsafe condition, but on 
different FCDs. UAL added that it has a mixture of FCD configurations, 
which will be subject to different compliance times.
    We disagree with the commenter's request to extend the compliance 
time to 36 months. We based the compliance time for this AD on the 
compliance time required by the EASA MCAI, which was determined by 
considering the urgency associated with the unsafe condition, the 
availability of required parts, and the practical aspect of 
accomplishing the required modification within a timeframe that 
corresponds to the normal scheduled maintenance for most affected 
operators. In addition, the manufacturer recommended that the service 
bulletin be accomplished no later than March 28, 2019. We have not 
changed this AD in this regard.

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting this final rule as proposed with 
the changes described previously and minor editorial changes. We have 
determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for addressing the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this final 
rule.

Related Service Information Under 1 CFR Part 51

    Bombardier Short Brothers, PLC has issued Service Bulletin V25MFC-
71-1003, dated September 28, 2016. The service information describes 
procedures for installing modified latches on the left and right engine 
FCDs, and re-identifying the FCDs. This service information is 
reasonably available because the interested parties have access to it 
through their normal course of business or by the means identified in 
the ADDRESSES section.

Costs of Compliance

    We estimate that this AD affects 557 airplanes of U.S. registry. We 
estimate the following costs to comply with this AD:

[[Page 51821]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Modification and re-identification (or  8 work-hours x $85 per            $1,500          $2,180      $1,214,260
 replacement), and placard               hour = $680.
 installation.
----------------------------------------------------------------------------------------------------------------

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 and 
associated appliances to the Director of the System Oversight Division.

Regulatory Findings

    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):

2018-21-05 Airbus SAS: Amendment 39-19463; Docket No. FAA-2018-0358; 
Product Identifier 2017-NM-142-AD.

(a) Effective Date

    This AD is effective November 19, 2018.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus SAS Model A319-131, A319-132, A319-
133, A320-231, A320-232, A320-233, A321-131, A321-231, and A321-232 
airplanes, certificated in any category, if modified by Bombardier 
Short Brothers, PLC Supplemental Type Certificate (STC) ST03076NY.

(d) Subject

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

(e) Reason

    This AD was prompted by reports of fan cowl door (FCD) losses 
during takeoff. We are issuing this AD to prevent in-flight loss of 
an FCD, which could result in damage to the airplane and injury to 
persons on the ground.

(f) Compliance

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

(g) Modification and Re-Identification of FCDs

    Within 18 months after the effective date of this AD: Do the 
modification and re-identification specified in paragraphs (g)(1) 
and (g)(2) of this AD.
    (1) Modify each left-hand (LH) and right-hand (RH) FCD having a 
part number listed as ``Old Part Number'' in table 1 to paragraphs 
(g), (h), and (l) of this AD, in accordance with the Accomplishment 
Instructions of Bombardier Short Brothers Service Bulletin V25MFC-
71-1003, dated September 28, 2016.
    (2) Re-identify each modified FCD with the part number listed as 
``New Part Number'' in table 1 to paragraphs (g), (h), and (l) of 
this AD, in accordance with the Accomplishment Instructions of 
Bombardier Short Brothers Service Bulletin V25MFC-71-1003, dated 
September 28, 2016.

[[Page 51822]]

[GRAPHIC] [TIFF OMITTED] TR15OC18.000

(h) Optional Compliance by Replacement or Installation

    (1) Replacement of the FCDs having a part number listed as ``Old 
Part Number'' in table 1 to paragraphs (g), (h), and (l) of this AD, 
with the FCDs having the corresponding part number listed as ``New 
Part Number'' in table 1 to paragraphs (g), (h), and (l) of this AD, 
is acceptable for compliance with the requirements of paragraph (g) 
of this AD.
    (2) Installation on an engine of a LH and RH FCD having a part 
number approved after the effective date of this AD is acceptable 
for compliance with the requirements of paragraph (g) of this AD for 
that engine only, provided the conditions specified in paragraphs 
(h)(2)(i) and (h)(2)(ii) of this AD are met.
    (i) The part number is approved using a method approved by the 
Manager, International Section, Transport Standards Branch, FAA; or 
the European Aviation Safety Agency (EASA); or Bombardier Short 
Brothers, PLC's EASA Design Organization Approval (DOA). If approved 
by the DOA, the approval must include the DOA-authorized signature.
    (ii) The installation is accomplished using a method approved by 
the Manager, International Section, Transport Standards Branch, FAA; 
or EASA; or Bombardier Short Brothers, PLC's EASA DOA. If approved 
by the DOA, the approval must include the DOA-authorized signature.

(i) Placard Installation

    For airplanes on which Airbus SAS modification 157718 has not 
been embodied in production: Within 18 months after the effective 
date of this AD, install a placard that specifies the FCD keys 
stowage location in the flight deck on the box located at the bottom 
of the 120VU panel, or at the bottom of the coat stowage, as 
applicable to airplane configuration, using a method approved by the 
Manager, International Section, Transport Standards Branch, FAA; or 
EASA; or Bombardier Short Brothers, PLC's EASA DOA. If approved by 
the DOA, the approval must include the DOA-authorized signature.

(j) 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.

(k) Alternate Location of FCD Keys and Placard

    As an option to paragraph (i) of this AD, an alternate 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 18 
months after the effective date of this AD.

(l) Parts Installation Prohibition

    No person may install on any airplane an FCD with a part number 
identified as ``Old Part Number'' in table 1 to paragraphs (g), (h), 
and (l) of this AD, after the time specified in paragraph (l)(1) or 
(l)(2) of this AD, as applicable.
    (1) For any airplane with an installed FCD having a part number 
identified as ``Old Part Number'' in table 1 to paragraphs (g), (h), 
and (l) of this AD: After modification of that airplane as required 
by paragraph (g) of this AD or as specified in paragraph (h) of this 
AD.
    (2) For any airplane without an installed FCD having a part 
number identified as ``Old Part Number'' in table 1 to paragraphs 
(g), (h), and (l) of this AD: After the effective date of this AD.

(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 Bombardier 
Short Brothers, PLC'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 2017-0178, dated September 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-2018-0358.
    (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.

(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.
    (i) Bombardier Short Brothers Service Bulletin V25MFC-71-1003, 
dated September 28, 2016.
    (ii) Reserved.
    (3) For service information identified in this AD, contact 
Bombardier Short Brothers, PLC, Airworthiness, P.O. Box 241, Airport 
Road, Belfast, BT3 9DZ Northern Ireland; telephone +44(0)2890-
462469; fax +44(0)2890-468444; email 
[email protected]; internet http://www.bombardier.com.
    (4) 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.

[[Page 51823]]

    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Des Moines, Washington, on September 20, 2018.
John P. Piccola,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-21963 Filed 10-12-18; 8:45 am]
 BILLING CODE 4910-13-P