Airworthiness Directives; Airbus SAS Airplanes, 63399-63402 [2018-26474]

Download as PDF Federal Register / Vol. 83, No. 236 / Monday, December 10, 2018 / Rules and Regulations (a) Effective Date This AD is effective January 14, 2019. (b) Affected ADs None. (c) Applicability This AD applies to C Series Aircraft Limited Partnership (CSALP) (Type Certificate Previously Held by Bombardier, Inc.) airplanes, certificated in any category, identified in paragraphs (c)(1) and (c)(2) of this AD. (1) Model BD–500–1A10 airplanes, serial numbers 50001 and subsequent, equipped with blow-out panel part number D762213– 503, D762216–505, or D762209–503. (2) Model BD–500–1A11 airplanes, serial numbers 55001 and subsequent, equipped with blow-out panel part number D762213– 503, D762216–505, or D762209–503. (d) Subject Air Transport Association (ATA) of America Code 50, Cargo and accessory compartment. (e) Reason This AD was prompted by reports of dislodged cargo compartment blow-out panels. We are issuing this AD to address this condition, which could result in openings in the forward and aft cargo compartments. In the event of a cargo compartment fire, these unintended openings in the forward and aft cargo compartments would provide a path for smoke, fire, and Halon to enter the adjacent equipment bays, flight deck, and passenger cabin, which could delay smoke detection in the forward and aft cargo compartments and result in the forward and aft cargo compartments not being able to maintain the Halon concentration required for fire suppression. The cargo compartment fire may become uncontrollable if this condition is not addressed, which could result in the loss of controllability of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections of the Forward and Aft Cargo Compartment Blow-Out Panels and Re-Installation Within 7 days or 50 flight cycles, whichever occurs first, after the effective date of this AD, do a detailed inspection for any dislodged blow-out panel in the forward and aft cargo compartments, in accordance with C Series (Bombardier) Data Module BD500– A–J50–10–01–01AAA–310B–A, ‘‘Forward and aft cargo compartment blow-out panels— Visual check,’’ Issue 002, dated May 16, 2018. Re-install all dislodged forward and aft cargo compartment blow-out panels before further flight, in accordance with C Series (Bombardier) Data Module BD500–A–J50– 10–01–00AAA–521A–A, ‘‘Decompression panels dislodging—Return to basic configuration,’’ Issue 002, dated May 16, 2018. Thereafter, at intervals not to exceed 100 flight cycles, repeat the detailed inspection for any dislodged blow-out panel in the forward and aft cargo compartments. VerDate Sep<11>2014 16:14 Dec 07, 2018 Jkt 247001 (h) Reporting If any blow-out panel in the forward or aft cargo compartments is found dislodged during any inspection required by paragraph (g) of this AD, at the applicable time specified in paragraph (h)(1) or (h)(2) of this AD, report findings to the Bombardier customer response center (CRC) via email: crc_cseries@aero.bombardier.com. Reportable findings include the airplane serial number on which any dislodged blowout panel was found, the date of inspection, and the part number and location of each dislodged blow-out panel. (1) If the inspection was done on or after the effective date of this AD: Submit the report within 30 days after the inspection. (2) If the inspection was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD. (i) Paperwork Reduction Act Burden Statement A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120–0056. Public reporting for this collection of information is estimated to be approximately 1 hour per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW, Washington, DC 20591, Attn: Information Collection Clearance Officer, AES–200. (j) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, New York ACO Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the certification office, send it to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7300; fax 516–794–5531. 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, New York ACO Branch, FAA; or Transport Canada Civil Aviation PO 00000 Frm 00017 Fmt 4700 Sfmt 9990 63399 (TCCA); or C Series Aircraft Limited Partnership’s (CSALP’s) TCCA Design Approval Organization (DAO). If approved by the DAO, the approval must include the DAO-authorized signature. (k) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian AD CF–2018–15, dated June 6, 2018, 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–2018–0799. (2) For more information about this AD, contact Darren Gassetto, Aerospace Engineer, Mechanical Systems and Admin Services Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7323; fax 516 794 5531; email 9-avs-nyaco-cos@faa.gov. (l) 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) C Series (Bombardier) Data Module BD500–A–J50–10–01–00AAA–521A–A, ‘‘Decompression panels dislodging—Return to basic configuration,’’ Issue 002, dated May 16, 2018. (ii) C Series (Bombardier) Data Module BD500–A–J50–10–01–01AAA–310B–A, ‘‘Forward and aft cargo compartment blowout panels—Visual check,’’ Issue 002, dated May 16, 2018. (3) For service information identified in this AD, 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. (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 November 23, 2018. John P. Piccola, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018–26473 Filed 12–7–18; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\10DER1.SGM 10DER1 63400 Federal Register / Vol. 83, No. 236 / Monday, December 10, 2018 / Rules and Regulations DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0800; Product Identifier 2018–NM–107–AD; Amendment 39–19517; AD 2018–25–06] 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 all Airbus SAS Model A330–223F and Model A330–243F airplanes. This AD was prompted by a report of cracking at fastener holes located at a certain frame on the lower shell panel junction. This AD requires repetitive special detailed inspections (rototest) of certain fastener holes located at the lower shell junction of a certain frame on both left-hand (LH) and right-hand (RH) sides, and applicable related investigative and corrective actions. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective January 14, 2019. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of January 14, 2019. ADDRESSES: For service information identified in this final rule, contact Airbus SAS, Airworthiness Office— EAL, Rond-Point Emile Dewoitine No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330A340@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– 0800. 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– 0800; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. VerDate Sep<11>2014 16:14 Dec 07, 2018 Jkt 247001 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: Vladimir Ulyanov, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3229. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all Airbus SAS Model A330– 223F and Model A330–243F airplanes. The NPRM published in the Federal Register on September 21, 2018 (83 FR 47850). The NPRM was prompted by a report of cracking at fastener holes located at a certain frame on the lower shell panel junction. The NPRM proposed to require repetitive special detailed inspections (rototest) of certain fastener holes located at the lower shell junction of a certain frame on both LH and RH sides, and applicable related investigative and corrective actions. We are issuing this AD to address cracking at FR40 on the lower shell panel junction; such cracking could lead to reduced structural integrity of the fuselage. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2018–0146, dated July 12, 2018 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus SAS Model A330–223F and Model A330– 243F airplanes. The MCAI states: During embodiment of a frame (FR) 40 web repair on an A330 aeroplane, and during keel beam replacement on an A340 aeroplane, cracks were found on both left hand (LH) and right hand (RH) sides on internal strap, butt strap, keel beam fitting, or forward fitting FR40 flange. This condition, if not detected and corrected, could affect the structural integrity of the centre fuselage of the aeroplane. Prompted by these findings, Airbus issued SB [service bulletin] A330–53–3215, providing inspection instructions, and EASA issued AD 2014–0136 and, subsequently, AD 2017–0063 [which corresponds to FAA AD 2018–12–08, Amendment 39–19312 (83 FR 33821, July 18, 2018)] to require repetitive PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 special detailed inspection (SDI), (rototest), of 10 fastener holes located at the FR40 lower shell panel junction on both LH and RH sides and, depending on findings, accomplishment of applicable corrective action(s). After those ADs were issued, it has been determined that A330 Freighter aeroplanes are also affected by this potential unsafe condition. Consequently, Airbus published SB A330–53–3215 Revision 03 to expand the Effectivity of that SB to these aeroplanes. For the reason described above, this [EASA] AD requires repetitive SDI (rototest) of 10 fastener holes located at the FR40 lower shell panel junction on both LH and RH sides and, depending on findings, accomplishment of applicable corrective action(s) [which include oversizing, installing fasteners and repair; and accomplishment of applicable related investigative actions, which include a rototest inspection for cracking after oversizing]. 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– 0800. Comments We gave the public the opportunity to participate in developing this final rule. We received no comments on the NPRM or on the determination of the cost to the public. Conclusion We reviewed the relevant data 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 Airbus has issued Service Bulletin A330–53–3215, Revision 03, dated January 22, 2018. This service information describes procedures for repetitive rototest inspections of certain fastener holes, and related investigative and corrective actions if necessary. 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 5 airplanes of U.S. registry. We estimate the following costs to comply with this AD: E:\FR\FM\10DER1.SGM 10DER1 Federal Register / Vol. 83, No. 236 / Monday, December 10, 2018 / Rules and Regulations 63401 ESTIMATED COSTS Labor cost Parts cost Up to 42 work-hours × $85 per hour = $3,570 ............................................................ We estimate the following costs to do any necessary on-condition actions that would be required based on the results of any required actions. We have no way of determining the number of aircraft that might need these on-condition actions: ESTIMATED COSTS OF ON-CONDITION ACTIONS Labor cost 46 work-hours × $85 per hour = $3,910 Parts cost $3,690 Cost per product $7,600 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 VerDate Sep<11>2014 16:14 Dec 07, 2018 Jkt 247001 $0 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 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): ■ 2018–25–06 Airbus SAS: Amendment 39– 19517; Docket No. FAA–2018–0800; Product Identifier 2018–NM–107–AD. (a) Effective Date This AD is effective January 14, 2019. (b) Affected ADs None. (c) Applicability This AD applies to the airplanes, certificated in any category, identified in paragraphs (c)(1) and (c)(2) of this AD; all manufacturer serial numbers. (1) Airbus SAS Model A330–223F airplanes. (2) Airbus SAS Model A330–243F airplanes. PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 Cost per product Up to $3,570 ......... Cost on U.S. operators Up to $17,850. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by a report of cracking on both left-hand (LH) and righthand (RH) sides on the internal strap, butt strap, keel beam fitting, or forward fitting frame (FR) 40 flange. We are issuing this AD to address cracking at FR40 on the lower shell panel junction; such cracking could lead to reduced structural integrity of the fuselage. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Compliance Times for the Actions Required by Paragraph (h) of This AD Accomplish the actions required by paragraph (h) of this AD before exceeding the compliance time ‘‘threshold’’ defined in paragraph 1.E., ‘‘Compliance,’’ of Airbus Service Bulletin A330–53–3215, Revision 03, dated January 22, 2018 (‘‘A330–53–3215, R3’’), depending on airplane utilization and configuration and to be counted from airplane first flight, and, thereafter, at intervals not to exceed the compliance times defined in paragraph 1.E., ‘‘Compliance,’’ of A330–53–3215, R3, depending on airplane utilization and configuration. (h) Repetitive Inspections and Related Investigative and Corrective Actions At the applicable compliance times specified in paragraph (g) of this AD: Accomplish a special detailed inspection of the 10 fastener holes located at FR40 lower shell panel junction on both LH and RH sides, in accordance with the Accomplishment Instructions of A330–53– 3215, R3. (1) If, during any inspection required by the introductory text of paragraph (h) of this AD, any crack is detected, before further flight, accomplish all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of A330–53–3215, R3, except where A330–53–3215, R3 specifies to contact Airbus for repair instructions, and specifies that action as Required for Compliance (RC), this AD requires repair before further flight using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or European Aviation Safety Agency (EASA); or Airbus SAS’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (2) If, during any inspection required by the introductory text of paragraph (h) of this AD, the diameter of a fastener hole is found to be outside the tolerances of the transition E:\FR\FM\10DER1.SGM 10DER1 63402 Federal Register / Vol. 83, No. 236 / Monday, December 10, 2018 / Rules and Regulations fit as specified in A330–53–3215, R3, as applicable; and A330–53–3215, R3; specifies to contact Airbus for repair instructions, and specifies that action as ‘‘RC,’’ before further flight, repair using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus SAS’s EASA DOA. If approved by the DOA, the approval must include the DOAauthorized signature. (3) Accomplishment of corrective actions, as required by paragraph (h)(1) of this AD, does not constitute terminating action for the repetitive inspections required by the introductory text of paragraph (h) of this AD. (4) Accomplishment of a repair on an airplane, as required by paragraph (h)(2) of this AD, does not constitute terminating action for the repetitive inspections required by the introductory text of paragraph (h) of this AD for that airplane, unless the method approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus SAS’s EASA DOA indicates otherwise. (i) No Reporting Requirement Although A330–53–3215, R3, specifies to submit certain information to the manufacturer, and specifies that action as RC, this AD does not include that requirement. (j) Credit for Previous Actions This paragraph provides credit for the inspections required by the introductory text of paragraph (h) of this AD and the related investigative and corrective actions required by paragraph (h)(1) of this AD, if those actions were performed before the effective date of this AD, using Airbus Service Bulletin A330–53–3215, dated June 21, 2013; or Revision 01, dated April 17, 2014; or Revision 02, dated November 23, 2016. (k) 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 (l)(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 SAS’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): Except as specified by paragraphs (h)(1), (h)(2), and VerDate Sep<11>2014 16:14 Dec 07, 2018 Jkt 247001 (i) of this AD: If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (l) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2018–0146, dated July 12, 2018, 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–2018–0800. (2) For more information about this AD, contact Vladimir Ulyanov, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3229. (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (m)(3) and (m)(4) of this AD. (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 this AD specifies otherwise. (i) Airbus Service Bulletin A330–53–3215, Revision 03, dated January 22, 2018. (ii) [Reserved] (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAL, Rond-Point Emile Dewoitine No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330-A340@ airbus.com; internet http://www.airbus.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 November 23, 2018. John P. Piccola, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018–26474 Filed 12–7–18; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA–2018–0685; Airspace Docket No. 18–AGL–19] RIN 2120–AA66 Amendment of Class D Airspace; Detroit, MI Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: This action modifies Class D airspace at Coleman A. Young Municipal Airport (formerly Detroit City Airport), Detroit, MI, by changing the airspace designation to Detroit, MI, thereby removing the old airport name. The name and geographic coordinates of this airport are also updated to coincide with the FAA’s aeronautical database. This action is necessary to keep information current for the safety and management of aircraft within the national airspace system. DATES: Effective 0901 UTC, February 28, 2019. The Director of the Federal Register approves this incorporation by reference action under Title 1 Code of Federal Regulations part 51, subject to the annual revision of FAA Order 7400.11 and publication of conforming amendments. ADDRESSES: FAA Order 7400.11C, Airspace Designations and Reporting Points, and subsequent amendments can be viewed online at http://www.faa.gov/ air_traffic/publications/. For further information, you can contact the Airspace Policy Group, Federal Aviation Administration, 800 Independence Avenue SW, Washington, DC 20591; telephone: (202) 267–8783. The Order is also available for inspection at the National Archives and Records Administration (NARA). For information on the availability of FAA Order 7400.11C at NARA, call (202) 741–6030, or go to https:// www.archives.gov/federal-register/cfr/ ibr-locations.html. FAA Order 7400.11, Airspace Designations and Reporting Points, is published yearly and effective on September 15. FOR FURTHER INFORMATION CONTACT: Jeffrey Claypool, Federal Aviation Administration, Operations Support Group, Central Service Center, 10101 Hillwood Parkway, Fort Worth, TX 76177; telephone (817) 222–5711. SUPPLEMENTARY INFORMATION: SUMMARY: E:\FR\FM\10DER1.SGM 10DER1

Agencies

[Federal Register Volume 83, Number 236 (Monday, December 10, 2018)]
[Rules and Regulations]
[Pages 63399-63402]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-26474]



[[Page 63400]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0800; Product Identifier 2018-NM-107-AD; Amendment 
39-19517; AD 2018-25-06]
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 all 
Airbus SAS Model A330-223F and Model A330-243F airplanes. This AD was 
prompted by a report of cracking at fastener holes located at a certain 
frame on the lower shell panel junction. This AD requires repetitive 
special detailed inspections (rototest) of certain fastener holes 
located at the lower shell junction of a certain frame on both left-
hand (LH) and right-hand (RH) sides, and applicable related 
investigative and corrective actions. We are issuing this AD to address 
the unsafe condition on these products.

DATES: This AD is effective January 14, 2019.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of January 14, 
2019.

ADDRESSES: For service information identified in this final rule, 
contact Airbus SAS, Airworthiness Office--EAL, Rond-Point Emile 
Dewoitine No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 
96; fax +33 5 61 93 45 80; 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-
0800.

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-
0800; 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: Vladimir Ulyanov, Aerospace Engineer, 
International Section, Transport Standards Branch, FAA, 2200 South 
216th St., Des Moines, WA 98198; telephone and fax 206-231-3229.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to all Airbus SAS Model A330-
223F and Model A330-243F airplanes. The NPRM published in the Federal 
Register on September 21, 2018 (83 FR 47850). The NPRM was prompted by 
a report of cracking at fastener holes located at a certain frame on 
the lower shell panel junction. The NPRM proposed to require repetitive 
special detailed inspections (rototest) of certain fastener holes 
located at the lower shell junction of a certain frame on both LH and 
RH sides, and applicable related investigative and corrective actions.
    We are issuing this AD to address cracking at FR40 on the lower 
shell panel junction; such cracking could lead to reduced structural 
integrity of the fuselage.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2018-0146, dated July 12, 2018 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus SAS Model 
A330-223F and Model A330- 243F airplanes. The MCAI states:

    During embodiment of a frame (FR) 40 web repair on an A330 
aeroplane, and during keel beam replacement on an A340 aeroplane, 
cracks were found on both left hand (LH) and right hand (RH) sides 
on internal strap, butt strap, keel beam fitting, or forward fitting 
FR40 flange.
    This condition, if not detected and corrected, could affect the 
structural integrity of the centre fuselage of the aeroplane.
    Prompted by these findings, Airbus issued SB [service bulletin] 
A330-53-3215, providing inspection instructions, and EASA issued AD 
2014-0136 and, subsequently, AD 2017-0063 [which corresponds to FAA 
AD 2018-12-08, Amendment 39-19312 (83 FR 33821, July 18, 2018)] to 
require repetitive special detailed inspection (SDI), (rototest), of 
10 fastener holes located at the FR40 lower shell panel junction on 
both LH and RH sides and, depending on findings, accomplishment of 
applicable corrective action(s).
    After those ADs were issued, it has been determined that A330 
Freighter aeroplanes are also affected by this potential unsafe 
condition. Consequently, Airbus published SB A330-53-3215 Revision 
03 to expand the Effectivity of that SB to these aeroplanes.
    For the reason described above, this [EASA] AD requires 
repetitive SDI (rototest) of 10 fastener holes located at the FR40 
lower shell panel junction on both LH and RH sides and, depending on 
findings, accomplishment of applicable corrective action(s) [which 
include oversizing, installing fasteners and repair; and 
accomplishment of applicable related investigative actions, which 
include a rototest inspection for cracking after oversizing].

    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-
0800.

Comments

    We gave the public the opportunity to participate in developing 
this final rule. We received no comments on the NPRM or on the 
determination of the cost to the public.

Conclusion

    We reviewed the relevant data 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

    Airbus has issued Service Bulletin A330-53-3215, Revision 03, dated 
January 22, 2018. This service information describes procedures for 
repetitive rototest inspections of certain fastener holes, and related 
investigative and corrective actions if necessary. 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 5 airplanes of U.S. registry. We 
estimate the following costs to comply with this AD:

[[Page 63401]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
            Labor cost                Parts cost           Cost per product           Cost on  U.S. operators
----------------------------------------------------------------------------------------------------------------
Up to 42 work-hours x $85 per hour              $0  Up to $3,570.................  Up to $17,850.
 = $3,570.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary on-condition 
actions that would be required based on the results of any required 
actions. We have no way of determining the number of aircraft that 
might need these on-condition actions:

                 Estimated Costs of On-Condition Actions
------------------------------------------------------------------------
                                                               Cost per
                   Labor cost                     Parts cost    product
------------------------------------------------------------------------
46 work-hours x $85 per hour = $3,910...........     $3,690      $7,600
------------------------------------------------------------------------

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):

2018-25-06 Airbus SAS: Amendment 39-19517; Docket No. FAA-2018-0800; 
Product Identifier 2018-NM-107-AD.

(a) Effective Date

    This AD is effective January 14, 2019.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the airplanes, certificated in any category, 
identified in paragraphs (c)(1) and (c)(2) of this AD; all 
manufacturer serial numbers.
    (1) Airbus SAS Model A330-223F airplanes.
    (2) Airbus SAS Model A330-243F airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Reason

    This AD was prompted by a report of cracking on both left-hand 
(LH) and right-hand (RH) sides on the internal strap, butt strap, 
keel beam fitting, or forward fitting frame (FR) 40 flange. We are 
issuing this AD to address cracking at FR40 on the lower shell panel 
junction; such cracking could lead to reduced structural integrity 
of the fuselage.

(f) Compliance

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

(g) Compliance Times for the Actions Required by Paragraph (h) of This 
AD

    Accomplish the actions required by paragraph (h) of this AD 
before exceeding the compliance time ``threshold'' defined in 
paragraph 1.E., ``Compliance,'' of Airbus Service Bulletin A330-53-
3215, Revision 03, dated January 22, 2018 (``A330-53-3215, R3''), 
depending on airplane utilization and configuration and to be 
counted from airplane first flight, and, thereafter, at intervals 
not to exceed the compliance times defined in paragraph 1.E., 
``Compliance,'' of A330-53-3215, R3, depending on airplane 
utilization and configuration.

(h) Repetitive Inspections and Related Investigative and Corrective 
Actions

    At the applicable compliance times specified in paragraph (g) of 
this AD: Accomplish a special detailed inspection of the 10 fastener 
holes located at FR40 lower shell panel junction on both LH and RH 
sides, in accordance with the Accomplishment Instructions of A330-
53-3215, R3.
    (1) If, during any inspection required by the introductory text 
of paragraph (h) of this AD, any crack is detected, before further 
flight, accomplish all applicable related investigative and 
corrective actions, in accordance with the Accomplishment 
Instructions of A330-53-3215, R3, except where A330-53-3215, R3 
specifies to contact Airbus for repair instructions, and specifies 
that action as Required for Compliance (RC), this AD requires repair 
before further flight using a method approved by the Manager, 
International Section, Transport Standards Branch, FAA; or European 
Aviation Safety Agency (EASA); or Airbus SAS's EASA Design 
Organization Approval (DOA). If approved by the DOA, the approval 
must include the DOA-authorized signature.
    (2) If, during any inspection required by the introductory text 
of paragraph (h) of this AD, the diameter of a fastener hole is 
found to be outside the tolerances of the transition

[[Page 63402]]

fit as specified in A330-53-3215, R3, as applicable; and A330-53-
3215, R3; specifies to contact Airbus for repair instructions, and 
specifies that action as ``RC,'' before further flight, repair using 
a method approved by the Manager, International Section, Transport 
Standards Branch, FAA; or EASA; or Airbus SAS's EASA DOA. If 
approved by the DOA, the approval must include the DOA-authorized 
signature.
    (3) Accomplishment of corrective actions, as required by 
paragraph (h)(1) of this AD, does not constitute terminating action 
for the repetitive inspections required by the introductory text of 
paragraph (h) of this AD.
    (4) Accomplishment of a repair on an airplane, as required by 
paragraph (h)(2) of this AD, does not constitute terminating action 
for the repetitive inspections required by the introductory text of 
paragraph (h) of this AD for that airplane, unless the method 
approved by the Manager, International Section, Transport Standards 
Branch, FAA; or EASA; or Airbus SAS's EASA DOA indicates otherwise.

(i) No Reporting Requirement

    Although A330-53-3215, R3, specifies to submit certain 
information to the manufacturer, and specifies that action as RC, 
this AD does not include that requirement.

(j) Credit for Previous Actions

    This paragraph provides credit for the inspections required by 
the introductory text of paragraph (h) of this AD and the related 
investigative and corrective actions required by paragraph (h)(1) of 
this AD, if those actions were performed before the effective date 
of this AD, using Airbus Service Bulletin A330-53-3215, dated June 
21, 2013; or Revision 01, dated April 17, 2014; or Revision 02, 
dated November 23, 2016.

(k) 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 (l)(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 SAS's 
EASA DOA. If approved by the DOA, the approval must include the DOA-
authorized signature.
    (3) Required for Compliance (RC): Except as specified by 
paragraphs (h)(1), (h)(2), and (i) of this AD: If any service 
information contains procedures or tests that are identified as RC, 
those procedures and tests must be done to comply with this AD; any 
procedures or tests that are not identified as RC are recommended. 
Those procedures and tests that are not identified as RC may be 
deviated from using accepted methods in accordance with the 
operator's maintenance or inspection program without obtaining 
approval of an AMOC, provided the procedures and tests identified as 
RC can be done and the airplane can be put back in an airworthy 
condition. Any substitutions or changes to procedures or tests 
identified as RC require approval of an AMOC.

(l) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2018-0146, dated July 12, 2018, 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-2018-0800.
    (2) For more information about this AD, contact Vladimir 
Ulyanov, Aerospace Engineer, International Section, Transport 
Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; 
telephone and fax 206-231-3229.
    (3) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (m)(3) and (m)(4) of this AD.

(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 this AD specifies otherwise.
    (i) Airbus Service Bulletin A330-53-3215, Revision 03, dated 
January 22, 2018.
    (ii) [Reserved]
    (3) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAL, Rond-Point Emile Dewoitine 
No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax 
+33 5 61 93 45 80; email [email protected]; 
internet http://www.airbus.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/ibr-locations.html.

    Issued in Des Moines, Washington, on November 23, 2018.
John P. Piccola,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-26474 Filed 12-7-18; 8:45 am]
 BILLING CODE 4910-13-P