Airworthiness Directives; Airbus Airplanes, 5020-5023 [2015-01174]

Download as PDF 5020 Federal Register / Vol. 80, No. 20 / Friday, January 30, 2015 / Rules and Regulations ANE–170, FAA; or Transport Canada Civil Aviation (TCCA); or Bombardier, Inc.’s TCCA Design Approval Organization (DAO). The initial compliance time for the operational test is within 100 flight hours after the effective date of this AD. Note 1 to paragraph (h) of this AD: Bombardier Task 27–41–00–101, Operational Test (BITE) of the Horizontal Stabilizer Trim Controls System (HSTCS), provides guidance for the operational test specified in paragraph (h) of this AD. Bombardier Task 27–41–00– 101 is included in the Bombardier Challenger 604 Time Limits/Maintenance Checks (TLMC) Manual; and in the Bombardier Challenger 605 TLMC Manual. (i) No Alternative Actions or Intervals After the maintenance or inspection program has been revised, as required by paragraph (h) of this AD, no alternative actions (e.g., inspections) or intervals may be used unless the actions or intervals are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (m)(1) of this AD. (j) HSTA Replacement For airplanes equipped with a HSTA having P/N 604–92305–3 (vendor P/N 845401) or P/N 604–92305–5 (vendor P/N 8454–2): Within 3,000 flight hours or 26 months after the effective date of this AD, whichever occurs first, replace any HSTA having P/N 604–92305–3 (vendor P/N 845401) or P/N 604–92305–5 (vendor P/N 8454–2) with a HSTA having P/N 604– 92305–7 (vendor P/N 8454–3), in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 604–27–032, Revision 02, dated April 22, 2014; or Bombardier Service Bulletin 605–27–002, Revision 02, dated April 22, 2014; as applicable. rljohnson on DSK4SPTVN1PROD with RULES (k) Credit for Previous Actions This paragraph provides credit for the actions required by paragraph (j) of this AD if those actions were performed before the effective date of this AD using the service information identified in paragraphs (k)(1) through (k)(4) of this AD, as applicable. This service information is not incorporated by reference in this AD. (1) Bombardier Service Bulletin 604–27– 032, dated September 10, 2012. (2) Bombardier Service Bulletin 604–27– 032, Revision 01, dated April 29, 2013. (3) Bombardier Service Bulletin 605–27– 002, dated September 10, 2012. (4) Bombardier Service Bulletin 605–27– 002, Revision 01, April 29, 2013. (l) Parts Installation Prohibition As of the effective date of this AD, no person may install any HSTA having P/N 604–92305–3 (vendor P/N 8454–1) or 604– 92305–5 (vendor P/N 8454–2) on any airplane. (m) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, New York ACO, ANE–170, FAA, has the authority to approve VerDate Sep<11>2014 14:34 Jan 29, 2015 Jkt 235001 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 ACO, send it to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO, 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. The AMOC approval letter must specifically reference this AD. (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, ANE–170; or TCCA; or Bombardier, Inc.’s TCCA Design DAO. If approved by the DAO, the approval must include the DAO-authorized signature. the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. (n) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian Airworthiness Directive CF–2013–18 dated July 16, 2013, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov/ #!documentDetail;D=FAA-2014-0231-0002. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (o)(3) and (o)(4) of this AD. Airworthiness Directives; Airbus Airplanes (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 Service Bulletin 604–27– 032, Revision 02, dated April 22, 2014. (ii) Bombardier Service Bulletin 605–27– 002, Revision 02, dated April 22, 2014. (iii) Bombardier Temporary Revision 604/ 37, dated May 21, 2013, to the Bombardier Challenger CL–604 Airplane Flight Manual, PSP 604–1. (iv) Bombardier Temporary Revision 605/ 18, dated May 21, 2013, to the Bombardier Challenger CL–605 Airplane Flight Manual, PSP 605–1. (3) For service information identified in ˆ this AD, contact Bombardier, Inc., 400 Cote ´ Vertu Road West, Dorval, Quebec H4S 1Y9, Canada; telephone 514–855–5000; fax 514– 855–7401; email thd.crj@ aero.bombardier.com; Internet http:// www.bombardier.com. (4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on PO 00000 Frm 00018 Fmt 4700 Sfmt 4700 Issued in Renton, Washington, on January 11, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–01171 Filed 1–29–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–0079; Directorate Identifier 2013–NM–091–AD; Amendment 39–18085; AD 2015–02–18] RIN 2120–AA64 Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for all Airbus Model A330–201, –202, –203, –301, –302, and –303 airplanes. This AD requires a one-time ultrasonic inspection for fractures of all aft mountpylon bolts of each engine. This AD was prompted by a report of one bolt on the aft engine mount upper beam found totally broken. We are issuing this AD to detect and correct fracture of the aft mount-pylon bolts, which could result in failure of the engine mount and consequent detachment of the engine. DATES: This AD becomes effective February 17, 2015. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of February 17, 2015. We must receive comments on this AD by March 16, 2015. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– SUMMARY: E:\FR\FM\30JAR1.SGM 30JAR1 Federal Register / Vol. 80, No. 20 / Friday, January 30, 2015 / Rules and Regulations 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 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. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. 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–2015– 0079; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone 425–227–1138; fax 425–227–1149. SUPPLEMENTARY INFORMATION: Discussion rljohnson on DSK4SPTVN1PROD with RULES The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2013–0094, dated April 15, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus Model A330–201, –202, –203, –301, –302, and –303 airplanes. The MCAI states: During a scheduled replacement of a CF6– 80E1 engine #1 on an A330 aeroplane, one bolt on the aft engine mount upper beam was found totally broken. That bolt is one of the four bolts that attach the upper beam to the pylon. The subsequent analyses of the broken bolt and the upper beam identified the following: —a fatigue origin area with crack propagation from the boundary of the bolt, VerDate Sep<11>2014 14:34 Jan 29, 2015 Jkt 235001 —a spiral groove with cold work and microstructural distortion underlying that extended axially along the shank, and —a score mark on counter-bore edge of the upper beam. The preliminary root-cause investigation shows that an unusual contact with the counter-bore edge of the beam induced a significant groove on the bolt during its installation in production. It is suspected that this groove led to a fatigue crack initiation and subsequent quick propagation leading to the complete fracture of the bolt. As the root-cause is still under investigation, including the installation sequence specific to this aeroplane—engine model, the other A330 propulsion systems are not affected. This condition, if not detected and corrected, could lead, in conjunction with a second fractured bolt, to the loss of engine mount structural integrity and potential engine detachment in flight as the remaining bolts would not be able to sustain the residual fatigue and limit loads. For the reasons described above, this [EASA] AD requires a one-time ultrasonic inspection of the four aft mount-pylon bolts of both engines for detection of completely sheared [fractured] bolts through the bolt section and, depending on finding, accomplishment of applicable corrective actions [repair]. This [EASA] AD is considered as an interim action, pending the results of the ongoing investigations, and further AD action may follow. You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2015–0079. Related Service Information Airbus has issued Alert Operators Transmission (AOT) A71L002–13, dated April 8, 2013. The service information describes procedures to perform a onetime ultrasonic inspection for fractures of all aft mount-pylon bolts of each engine. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. FAA’s Determination and Requirements of This AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are issuing this AD because we evaluated all pertinent information and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 5021 FAA’s Determination of the Effective Date Since there are currently no domestic operators of this product, notice and opportunity for public comment before issuing this AD are unnecessary. Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2015–0079; Directorate Identifier 2013–NM–091– AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD based on those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this AD. Costs of Compliance We estimate that this AD affects 0 airplanes of U.S. registry. We also estimate that it will take about 3 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD on U.S. operators to be $255 per product. We have received no definitive data that would enable us to provide cost estimates for the on-condition action specified in this AD. We have no way of determining the number of aircraft that might need this action. Paperwork Reduction Act A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to 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 control number for the collection of information required by this AD is 2120–0056. The paperwork cost associated with this AD has been detailed in the Costs of Compliance section of this document and includes time for reviewing instructions, as well as completing and reviewing the collection of information. E:\FR\FM\30JAR1.SGM 30JAR1 5022 Federal Register / Vol. 80, No. 20 / Friday, January 30, 2015 / Rules and Regulations Therefore, all reporting associated with this AD is 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. Authority for This Rulemaking Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. rljohnson on DSK4SPTVN1PROD with RULES List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: VerDate Sep<11>2014 14:34 Jan 29, 2015 Jkt 235001 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): ■ 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. Adoption of the Amendment PART 39—AIRWORTHINESS DIRECTIVES 2015–02–18 Airbus: Amendment 39–18085. Docket No. FAA–2015–0079; Directorate Identifier 2013–NM–091–AD. (a) Effective Date This AD becomes effective February 17, 2015. (b) Affected ADs None. (c) Applicability This AD applies to Airbus Model A330– 201, –202, –203, –301, –302, and –303 airplanes, certificated in any category, all manufacturer serial numbers. (d) Subject Air Transport Association (ATA) of America Code 71, Powerplant. (e) Reason This AD was prompted by a report of one bolt on the aft engine mount upper beam found totally broken. We are issuing this AD to detect and correct fracture of the aft mount-pylon bolts, which could result in failure of the engine mount and consequent detachment of the engine. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Bolt Inspection Within 1,000 flight hours after the effective date of this AD, do a one-time ultrasonic inspection for fractures of all aft mount-pylon bolts of each engine, in accordance with Airbus Alert Operators Transmission (AOT) A71L002–13, dated April 8, 2013. If any fracture is detected, repair before further flight using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). (h) Reporting Submit a report of the findings (both positive and negative) of the inspection required by paragraph (g) of this AD to Airbus, at the applicable time specified in paragraph (h)(1) or (h)(2) of this AD. Send the report to the contact for inspection results specified in paragraph 7, ‘‘REPORTING,’’ of Airbus AOT A71L002–13, dated April 8, 2013. (1) If the inspection was done on or after the effective date of this AD: Submit the report within 30 days after the inspection. PO 00000 Frm 00020 Fmt 4700 Sfmt 4700 (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) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, 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 Branch, send it to ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057– 3356; telephone 425–227–1138; fax 425–227– 1149. Information may be emailed to: 9ANM-116-AMOC-REQUESTS@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. The AMOC approval letter must specifically reference this AD. (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 Branch, ANM– 116, Transport Airplane Directorate, FAA; or the EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Reporting Requirements: 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 5 minutes 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) Related Information Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2013–0094, dated April 15, 2013, for related information. You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2015–0079. E:\FR\FM\30JAR1.SGM 30JAR1 Federal Register / Vol. 80, No. 20 / Friday, January 30, 2015 / Rules and Regulations (k) 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 Alert Operators Transmission A71L002–13, dated April 8, 2013. (ii) Reserved. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 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 Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (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 Renton, Washington, on January 15, 2015. John P. Piccola, Jr., Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–01174 Filed 1–29–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0622; Directorate Identifier 2014–NM–009–AD; Amendment 39–18080; AD 2015–02–13] RIN 2120–AA64 Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (Embraer) Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for all Empresa Brasileira de Aeronautica S.A. (Embraer) Model EMB–135ER, –135KE, –135KL, –135LR, –145, –145ER, –145MR, –145LR, –145XR, –145MP, and –145EP airplanes. This AD was prompted by a determination of the need to revise the airplane airworthiness limitations related to the pylon yokes I and II, and the skin panel rljohnson on DSK4SPTVN1PROD with RULES SUMMARY: VerDate Sep<11>2014 14:34 Jan 29, 2015 Jkt 235001 of the windshield pillar. This AD requires revising the maintenance or inspection program, as applicable. We are issuing this AD to prevent fatigue cracking of various structural elements, which could affect the structural integrity of the airplane. DATES: This AD becomes effective March 6, 2015. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of March 6, 2015. ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov/ #!docketDetail;D=FAA-2014-0622; or in person at the Docket Management Facility, U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC. For service information identified in this AD, contact Empresa Brasileira de Aeronautica S.A. (Embraer), Technical Publications Section (PC 060), Av. Brigadeiro Faria Lima, 2170—Putim— ˜ 12227–901 Sao Jose dos Campos—SP— Brasil; telephone +55 12 3927–5852 or +55 12 3309–0732; fax +55 12 3927– 7546; email distrib@embraer.com.br; Internet http://www.flyembraer.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. FOR FURTHER INFORMATION CONTACT: Todd Thompson, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1175; fax 425–227–1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to all Embraer Model EMB –135ER, –135KE, –135KL, –135LR, –145, –145ER, –145MR, –145LR, –145XR, –145MP, and –145EP airplanes. The NPRM published in the Federal Register on September 4, 2014 (79 FR 52588). ˆ The Agencia Nacional de Aviacao ¸˜ Civil (ANAC), which is the aviation authority for Brazil, has issued Brazilian Airworthiness Directive 2014–01–01, dated January 20, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Embraer Model EMB –135ER, PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 5023 –135KE, –135KL, –135LR, –145, –145ER, –145MR, –145LR, –145XR, –145MP, and –145EP airplanes. The MCAI states: This [Brazilian] AD was prompted by a new revision to the airworthiness limitations requirements [related to the pylon yokes I and II, and the skin panel of the windshield pillar] of the Maintenance Review Board Report. We are issuing this [Brazilian] AD to ensure that fatigue cracking of various structural elements is detected and corrected. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov/ #!documentDetail;D=FAA-2014-06220002. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (79 FR 52588, September 4, 2014) 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 AD 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 (79 FR 52588, September 4, 2014) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (79 FR 52588, September 4, 2014). Related Service Information We reviewed EMBRAER EMB145 Temporary Revision 15–3, dated August 26, 2013, to the Airworthiness Limitation Requirements of the EMBRAER EMB145 Maintenance Review Board Report MRB 145/1150; and EMBRAER EMB145 Temporary Revision 15–4, dated August 26, 2013, to the Airworthiness Limitation Requirements of the EMBRAER EMB145 Maintenance Review Board Report MRB–145/1150. The service information describes airworthiness limitations related to inspections of certain fuselage or pylon components. You can find this information at http:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0622. Costs of Compliance We estimate that this AD affects 688 airplanes of U.S. registry. We also estimate that it will take about 1 work-hour per product to comply with the basic requirements of this AD. The average labor rate is $85 E:\FR\FM\30JAR1.SGM 30JAR1

Agencies

[Federal Register Volume 80, Number 20 (Friday, January 30, 2015)]
[Rules and Regulations]
[Pages 5020-5023]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-01174]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0079; Directorate Identifier 2013-NM-091-AD; 
Amendment 39-18085; AD 2015-02-18]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule; request for comments.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Airbus Model A330-201, -202, -203, -301, -302, and -303 airplanes. This 
AD requires a one-time ultrasonic inspection for fractures of all aft 
mount-pylon bolts of each engine. This AD was prompted by a report of 
one bolt on the aft engine mount upper beam found totally broken. We 
are issuing this AD to detect and correct fracture of the aft mount-
pylon bolts, which could result in failure of the engine mount and 
consequent detachment of the engine.

DATES: This AD becomes effective February 17, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of February 17, 
2015.
    We must receive comments on this AD by March 16, 2015.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-

[[Page 5021]]

30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue 
SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, 
except Federal holidays.
    For service information identified in this AD, contact Airbus SAS, 
Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 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. You may view this referenced service information at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, call 
425-227-1221.

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-2015-
0079; or in person at the Docket Operations office between 9 a.m. and 5 
p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the regulatory evaluation, any comments received, and 
other information. The street address for the Docket Operations office 
(telephone 800-647-5527) is in the ADDRESSES section. Comments will be 
available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone 425-227-
1138; fax 425-227-1149.

SUPPLEMENTARY INFORMATION:

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2013-0094, dated April 15, 2013 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A330-201, -202, -203, -301, -302, and -303 airplanes. The MCAI states:

    During a scheduled replacement of a CF6-80E1 engine #1 on an 
A330 aeroplane, one bolt on the aft engine mount upper beam was 
found totally broken. That bolt is one of the four bolts that attach 
the upper beam to the pylon.
    The subsequent analyses of the broken bolt and the upper beam 
identified the following:

--a fatigue origin area with crack propagation from the boundary of 
the bolt,
--a spiral groove with cold work and microstructural distortion 
underlying that extended axially along the shank, and
--a score mark on counter-bore edge of the upper beam.

    The preliminary root-cause investigation shows that an unusual 
contact with the counter-bore edge of the beam induced a significant 
groove on the bolt during its installation in production. It is 
suspected that this groove led to a fatigue crack initiation and 
subsequent quick propagation leading to the complete fracture of the 
bolt.
    As the root-cause is still under investigation, including the 
installation sequence specific to this aeroplane--engine model, the 
other A330 propulsion systems are not affected.
    This condition, if not detected and corrected, could lead, in 
conjunction with a second fractured bolt, to the loss of engine 
mount structural integrity and potential engine detachment in flight 
as the remaining bolts would not be able to sustain the residual 
fatigue and limit loads.
    For the reasons described above, this [EASA] AD requires a one-
time ultrasonic inspection of the four aft mount-pylon bolts of both 
engines for detection of completely sheared [fractured] bolts 
through the bolt section and, depending on finding, accomplishment 
of applicable corrective actions [repair].
    This [EASA] AD is considered as an interim action, pending the 
results of the ongoing investigations, and further AD action may 
follow.

You may examine the MCAI on the Internet at http://www.regulations.gov 
by searching for and locating Docket No. FAA-2015-0079.

Related Service Information

    Airbus has issued Alert Operators Transmission (AOT) A71L002-13, 
dated April 8, 2013. The service information describes procedures to 
perform a one-time ultrasonic inspection for fractures of all aft 
mount-pylon bolts of each engine. The actions described in this service 
information are intended to correct the unsafe condition identified in 
the MCAI.

FAA's Determination and Requirements of This AD

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

FAA's Determination of the Effective Date

    Since there are currently no domestic operators of this product, 
notice and opportunity for public comment before issuing this AD are 
unnecessary.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2015-0079; Directorate 
Identifier 2013-NM-091-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this AD based on 
those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this AD.

Costs of Compliance

    We estimate that this AD affects 0 airplanes of U.S. registry.
    We also estimate that it will take about 3 work-hours per product 
to comply with the basic requirements of this AD. The average labor 
rate is $85 per work-hour. Based on these figures, we estimate the cost 
of this AD on U.S. operators to be $255 per product.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition action specified in this AD. We 
have no way of determining the number of aircraft that might need this 
action.

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to 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 control 
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in 
the Costs of Compliance section of this document and includes time for 
reviewing instructions, as well as completing and reviewing the 
collection of information.

[[Page 5022]]

Therefore, all reporting associated with this AD is 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.

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.

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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

Sec.  39.13  [Amended]

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

2015-02-18 Airbus: Amendment 39-18085. Docket No. FAA-2015-0079; 
Directorate Identifier 2013-NM-091-AD.

(a) Effective Date

    This AD becomes effective February 17, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A330-201, -202, -203, -301, -
302, and -303 airplanes, certificated in any category, all 
manufacturer serial numbers.

(d) Subject

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

(e) Reason

    This AD was prompted by a report of one bolt on the aft engine 
mount upper beam found totally broken. We are issuing this AD to 
detect and correct fracture of the aft mount-pylon bolts, which 
could result in failure of the engine mount and consequent 
detachment of the engine.

(f) Compliance

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

(g) Bolt Inspection

    Within 1,000 flight hours after the effective date of this AD, 
do a one-time ultrasonic inspection for fractures of all aft mount-
pylon bolts of each engine, in accordance with Airbus Alert 
Operators Transmission (AOT) A71L002-13, dated April 8, 2013. If any 
fracture is detected, repair before further flight using a method 
approved by the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; or the European Aviation Safety Agency 
(EASA); or Airbus's EASA Design Organization Approval (DOA).

(h) Reporting

    Submit a report of the findings (both positive and negative) of 
the inspection required by paragraph (g) of this AD to Airbus, at 
the applicable time specified in paragraph (h)(1) or (h)(2) of this 
AD. Send the report to the contact for inspection results specified 
in paragraph 7, ``REPORTING,'' of Airbus AOT A71L002-13, dated April 
8, 2013.
    (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) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, 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 Branch, send it to ATTN: Vladimir 
Ulyanov, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, 
Washington 98057-3356; telephone 425-227-1138; fax 425-227-1149. 
Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@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. The AMOC approval letter must specifically reference this 
AD.
    (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 
Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; 
or Airbus's EASA DOA. If approved by the DOA, the approval must 
include the DOA-authorized signature.
    (3) Reporting Requirements: 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 5 
minutes 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) Related Information

    Refer to Mandatory Continuing Airworthiness Information (MCAI) 
EASA Airworthiness Directive 2013-0094, dated April 15, 2013, for 
related information. You may examine the MCAI on the Internet at 
http://www.regulations.gov by searching for and locating Docket No. 
FAA-2015-0079.

[[Page 5023]]

 (k) 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 Alert Operators Transmission A71L002-13, dated April 
8, 2013.
    (ii) Reserved.
    (3) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 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 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.
    (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 Renton, Washington, on January 15, 2015.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-01174 Filed 1-29-15; 8:45 am]
BILLING CODE 4910-13-P