Airworthiness Directives; Airbus Airplanes, 26487-26490 [2015-10948]

Download as PDF Federal Register / Vol. 80, No. 89 / Friday, May 8, 2015 / Proposed Rules asabaliauskas on DSK5VPTVN1PROD with PROPOSALS (h) Retained Restrictions on Alternative Actions, Intervals, and/or CDCCLs, With a New Exception This paragraph restates the requirements of paragraph (k) of AD 2011–21–06, Amendment 39–16829 (76 FR 64788, October 19, 2011), with a new exception. Except as required by paragraph (i) of this AD, after accomplishing the revision required by paragraph (g) of this AD, no alternative actions (e.g., inspections), intervals, and/or CDCCLs may be used unless the actions, intervals, and/or CDCCLs are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (l) of this AD. (i) New Maintenance or Inspection Program Revision Within 90 days after the effective date of this AD: Revise the maintenance or inspection program, as applicable, by incorporating Subjects 05–10–10, ‘‘Airworthiness Limitations’’; 05–10–20, ‘‘Certification Maintenance Requirements’’; and 05–10–30, ‘‘Critical Design Configuration Control Limitations (CDCCL)—Fuel System’’; of Chapter 05, ‘‘Airworthiness Limitations,’’ of the BAE Systems (Operations) Limited J41 AMM, Revision 38, dated September 15, 2013. The initial compliance times for the tasks are at the applicable times specified in paragraphs (i)(1), (i)(2), and (i)(3) of this AD. Doing the actions required by this paragraph terminates the requirements of paragraph (g) of this AD. (1) For replacement tasks of life limited parts specified in Subject 05–10–10, ‘‘Airworthiness Limitations,’’ of Chapter 05, ‘‘Airworthiness Limitations,’’ of the BAE Systems (Operations) Limited J41 AMM, Revision 38, dated September 15, 2013: Prior to the applicable flight cycles (landings) or flight hours (flying hours) on the part specified in the ‘‘Mandatory Life Limits’’ column in Subject 05–10–10, or within 90 days after the effective date of this AD, whichever occurs later. (2) For structurally significant item tasks specified in Subject 05–10–10, ‘‘Airworthiness Limitations,’’ of Chapter 05, ‘‘Airworthiness Limitations,’’ of the BAE Systems (Operations) Limited J41 AMM, Revision 38, dated September 15, 2013: Prior to the accumulation of the applicable flight cycles specified in the ‘‘Initial Inspection’’ column in Subject 05–10–10, or within 90 days after the effective date of this AD, whichever occurs later. (3) For certification maintenance requirements tasks specified in Subject 05– 10–20, ‘‘Certification Maintenance Requirements,’’ of Chapter 05, ‘‘Airworthiness Limitations,’’ of the BAE Systems (Operations) Limited J41 AMM, Revision 38, dated September 15, 2013: Prior to the accumulation of the applicable flight hours specified in the ‘‘Time Between Checks’’ column in Subject 05–10–20, or within 90 days after the effective date of this AD, whichever occurs later; except for tasks that specify ‘‘first flight of the day’’ in the ‘‘Time Between Checks’’ column in Subject 05–10–20, the initial compliance time is the first flight of the next day after doing the revision required by paragraph (j) of this AD, VerDate Sep<11>2014 16:19 May 07, 2015 Jkt 235001 26487 or within 90 days the effective date of this AD, whichever occurs later. the approval must include the DOAauthorized signature. (j) New Restrictions on Alternative Actions, Intervals, and/or (CDCCLs) After the maintenance or inspection program, as applicable, has been revised as required by paragraph (i) of this AD, no alternative actions (e.g., inspections), intervals, and/or CDCCLs may be used unless the actions, intervals, and/or CDCCLs are approved as an AMOC in accordance with the procedures specified in paragraph (l) of this AD. (m) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014–0043, dated February 21, 2014, 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–2015–1279. (2) For service information identified in this AD, contact BAE SYSTEMS (Operations) Limited, Customer Information Department, Prestwick International Airport, Ayrshire, KA9 2RW, Scotland, United Kingdom; telephone +44 1292 675207; fax +44 1292 675704; email RApublications@ baesystems.com; Internet http:// www.baesystems.com/Businesses/ RegionalAircraft/index.htm. 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. (k) Credit for Previous Actions This paragraph restates the provisions of paragraph (j) of AD 2011–21–06, Amendment 39–16829 (76 FR 64788, October 19, 2011). This paragraph provides credit for actions required by paragraph (g) of this AD, if those actions were performed before November 23, 2011 (the effective date of AD 2011–21–06), in accordance with Subjects 05–10–10, ‘‘Airworthiness Limitations’’; 05–10–20, ‘‘Certification Maintenance Requirements’’; and 05–10–30, ‘‘Critical Design Configuration Control Limitations (CDCCL)—Fuel System’’; of Chapter 05, ‘‘Airworthiness Limitations,’’ of the BAE Systems (Operations) Limited Jetstream Series 4100 AMM, Revision 33, dated February 15, 2010; which are not incorporated by reference in this AD. (l) 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: 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. Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. (i) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. The AMOC approval letter must specifically reference this AD. (ii) AMOCs approved previously for AD 2011–21–06, Amendment 39–16829 (76 FR 64788, October 19, 2011), are not approved as AMOCs with this AD. (2) Contacting the Manufacturer: As of the effective date of this AD, 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 European Aviation Safety Agency (EASA); or BAE Systems (Operations) Limited’s EASA Design Organization Approval (DOA). If approved by the DOA, PO 00000 Frm 00019 Fmt 4702 Sfmt 4702 Issued in Renton, Washington, on April 29, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–11023 Filed 5–7–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–1277; Directorate Identifier 2014–NM–155–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Airbus Model A319, A320, and A321 series airplanes. This proposed AD was prompted by fatigue testing that determined fatigue damage could appear on clips, shear webs, and angles at certain rear fuselage sections and certain frames. This proposed AD is intended to complete certain mandated programs intended to support the airplane reaching its limit of validity (LOV) of the engineering data that support the established structural maintenance program. This proposed AD would require replacing the clips, the shear webs, and angles, including doing all applicable related investigative SUMMARY: E:\FR\FM\08MYP1.SGM 08MYP1 26488 Federal Register / Vol. 80, No. 89 / Friday, May 8, 2015 / Proposed Rules actions, and repair if necessary. We are proposing this AD to prevent fatigue damage on the clips, shear webs, and angles, which could affect the structural integrity of the airplane. DATES: We must receive comments on this proposed AD by June 22, 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–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 proposed AD, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. 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. asabaliauskas on DSK5VPTVN1PROD with PROPOSALS Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 1277; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; fax 425–227–1149. SUPPLEMENTARY INFORMATION: VerDate Sep<11>2014 16:19 May 07, 2015 Jkt 235001 Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2015–1277; Directorate Identifier 2014–NM–155–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion As described in FAA Advisory Circular 120-104 (http://www.faa.gov/ documentLibrary/media/Advisory_ Circular/120-104.pdf), several programs have been developed to support initiatives that will ensure the continued airworthiness of aging airplane structure. The last element of those initiatives is the requirement to establish a limit of validity (LOV) of the engineering data that support the structural maintenance program under 14 CFR 26.21. This proposed AD is the result of an assessment of the previously established programs by the DAH during the process of establishing the LOV for Airbus Model A319, A320, and A321 series airplanes. The actions specified in this proposed AD are necessary to complete certain programs to ensure the continued airworthiness of aging airplane structure and to support an airplane reaching its LOV. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014–0177, dated July 25, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus Model A319, A320, and A321 series airplanes. The MCAI states: During the A320 fatigue test campaign for Extended Service Goal (ESG), it was determined that fatigue damage could appear on the clips, shear webs and angles at rear fuselage section 19, on Frame (FR) 72 and FR74. This condition, if not detected and corrected, could affect the structural integrity of the aeroplane. To address this potential unsafe condition, Airbus developed a modification, which has PO 00000 Frm 00020 Fmt 4702 Sfmt 4702 been published through Airbus Service Bulletin (SB) A320–53–1266 for in-service application to allow aeroplanes to operate up to the new ESG limit. For the reasons described above, this [EASA] AD requires replacement of the affected clips, shear webs and angles at rear fuselage section 19, FR72 and FR74 [including all applicable related investigative actions and repair if any cracking is found]. Related investigative actions include rotating probe testing for cracking of the fastener holes and high frequency eddy current inspections for cracking of the stringers. 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–2015– 1277. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A320–53–1266, Revision 01, dated June 20, 2013. This service information describes procedures for replacing clips, shear webs, and angles at rear fuselage section 19, FR72 and FR74. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. 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 of this NPRM. FAA’s Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of these same type designs. Costs of Compliance We estimate that this proposed AD affects 44 airplanes of U.S. registry. We also estimate that it would take about 110 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $411,400, or $9,350 per product. We have received no definitive data on the costs of required parts. According to the manufacturer, some of the costs of this proposed AD may be covered under warranty, thereby E:\FR\FM\08MYP1.SGM 08MYP1 Federal Register / Vol. 80, No. 89 / Friday, May 8, 2015 / Proposed Rules reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. 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. 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 asabaliauskas on DSK5VPTVN1PROD with PROPOSALS We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: VerDate Sep<11>2014 16:19 May 07, 2015 Jkt 235001 § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ Airbus: Docket No. FAA–2015–1277; Directorate Identifier 2014–NM–155–AD. (a) Comments Due Date We must receive comments by June 22, 2015. (b) Affected ADs None. (c) Applicability This AD applies to the airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in any category, all manufacturer serial numbers, except those on which Airbus Modification 30975 has been embodied in production. (1) Airbus Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes. (2) Airbus Model A320–211, –212, –214, –231, –232, and –233 airplanes. (3) Airbus Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by fatigue testing that determined fatigue damage could appear on clips, shear webs, and angles at certain rear fuselage sections and certain frames. This AD is intended to complete certain mandated programs intended to support the airplane reaching its limit of validity (LOV) of the engineering data that support the established structural maintenance program. We are issuing this AD to prevent fatigue damage on the clips, shear webs, and angles, which could affect the structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Replacement At the later of the times specified in paragraphs (g)(1) and (g)(2) of this AD: Replace the clips, shear webs, and angles at rear fuselage section 19, frame (FR)72 and FR74, and do all applicable related investigative actions before further flight, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 53–1266, Revision 01, dated June 20, 2013. If any crack is found during any related investigative action required by this AD: Before further flight, repair using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation PO 00000 Frm 00021 Fmt 4702 Sfmt 4702 26489 Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). (1) Before exceeding 48,000 flight cycles or 96,000 flight hours, whichever occurs first since the airplane’s first flight. (2) Within 30 days after the effective date of this AD. (h) Additional Replacement for Airplanes on Which the Replacement Required by Paragraph (g) of This AD Is Done Before 30,000 Flight Cycles or 60,000 Flight Hours For airplanes on which the replacement of clips, shear webs, and angles specified in Airbus Service Bulletin A320–53–1266 is done before accumulating 30,000 flight cycles or 60,000 flight hours, whichever occurred first since the airplane’s first flight: Within 30,000 flight cycles or 60,000 flight hours, whichever occurs first after that replacement, do the replacement specified in paragraph (g) of this AD. (i) Credit for Previous Actions Except as required by paragraph (h) of this AD: This paragraph provides credit for the replacement required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320–53–1266, dated January 11, 2013, which is not incorporated by reference in this AD. (j) 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: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; fax 425–227–1149. Information may be emailed to: 9-ANM-116AMOC-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. (k) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014–0177, dated July 25, 2014, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by E:\FR\FM\08MYP1.SGM 08MYP1 26490 Federal Register / Vol. 80, No. 89 / Friday, May 8, 2015 / Proposed Rules searching for and locating Docket No. FAA– 2015–1277. (2) For service information identified in this AD, contact Airbus, Airworthiness Office—EIAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@ airbus.com; Internet http://www.airbus.com. 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. Issued in Renton, Washington, on April 29, 2015. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–10948 Filed 5–7–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–0929; Directorate Identifier 2014–NM–218–AD] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc. Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Bombardier, Inc. Model BD–100–1A10 (Challenger 300) airplanes. This proposed AD was prompted by multiple reports of chafing found on an electrical wiring harness in the aft equipment bay, caused by contact between the wiring harness and a neighboring hydraulic line. This proposed AD would require an inspection, repair if necessary, and modification of the wiring harness installation to ensure that the wiring harness routing is correct and a minimum clearance between the wire and the hydraulic line is maintained. We are proposing this AD to detect and correct chafing on an electrical wiring harness, which could cause an electrical short circuit or lead to a malfunction of the flight control system, the engine indication system, or the hydraulic power control system, and adversely affect the continued safe operation and landing of the airplane. DATES: We must receive comments on this proposed AD by June 22, 2015. ADDRESSES: You may send comments, using the procedures found in 14 CFR asabaliauskas on DSK5VPTVN1PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 16:19 May 07, 2015 Jkt 235001 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–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 proposed AD, contact Bombardier, ˆ 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. 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– 0929; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Assata Dessaline, Aerospace Engineer, Avionics and Service Branch, ANE–172, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone: 516– 228–7301; fax: 516–794–5531. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2015–0929; Directorate Identifier 2014–NM–218–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, PO 00000 Frm 00022 Fmt 4702 Sfmt 4702 economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion Transport Canada Civil Aviation (TCCA), which is the aviation authority for Canada, has issued Canadian Airworthiness Directive CF–2014–32, dated September 8, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Bombardier, Inc. Model BD– 100–1A10 (Challenger 300) airplanes. The MCAI states: There have been multiple in-service reports of chafing found on an electrical wiring harness in the aft equipment bay. An investigation determined that the chafing was attributed to contact between the wiring harness and a neighboring hydraulic line. This chafing could cause an electrical short circuit or lead to a malfunction of the flight control system, the engine indication system, or the hydraulic power control system; which could adversely affect the continued safe operation and landing of the aeroplane. This [Canadian] AD mandates the inspection [general visual inspection], rectification as required [repair of damage (including wear and chafing)], and modification of the wiring harness installation to ensure the correct wiring routing and a minimum clearance between the wire and the hydraulic line is maintained. 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–2015– 0929. Related Service Information Under 1 CFR Part 51 Bombardier, Inc. has issued Service Bulletin 100–24–24, dated June 6, 2014. The service information describes procedures for an inspection, repair if necessary, and modification to reroute wiring harness installation to prevent contact with the hydraulic line. 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 of this NPRM. E:\FR\FM\08MYP1.SGM 08MYP1

Agencies

[Federal Register Volume 80, Number 89 (Friday, May 8, 2015)]
[Proposed Rules]
[Pages 26487-26490]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-10948]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-1277; Directorate Identifier 2014-NM-155-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Airbus Model A319, A320, and A321 series airplanes. This 
proposed AD was prompted by fatigue testing that determined fatigue 
damage could appear on clips, shear webs, and angles at certain rear 
fuselage sections and certain frames. This proposed AD is intended to 
complete certain mandated programs intended to support the airplane 
reaching its limit of validity (LOV) of the engineering data that 
support the established structural maintenance program. This proposed 
AD would require replacing the clips, the shear webs, and angles, 
including doing all applicable related investigative

[[Page 26488]]

actions, and repair if necessary. We are proposing this AD to prevent 
fatigue damage on the clips, shear webs, and angles, which could affect 
the structural integrity of the airplane.

DATES: We must receive comments on this proposed AD by June 22, 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-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 proposed AD, contact 
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 
93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. 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-
1277; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Operations office (telephone 800-647-5527) is in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; 
fax 425-227-1149.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2015-1277; 
Directorate Identifier 2014-NM-155-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    As described in FAA Advisory Circular 120-104 (http://www.faa.gov/documentLibrary/media/Advisory_Circular/120-104.pdf), several programs 
have been developed to support initiatives that will ensure the 
continued airworthiness of aging airplane structure. The last element 
of those initiatives is the requirement to establish a limit of 
validity (LOV) of the engineering data that support the structural 
maintenance program under 14 CFR 26.21. This proposed AD is the result 
of an assessment of the previously established programs by the DAH 
during the process of establishing the LOV for Airbus Model A319, A320, 
and A321 series airplanes. The actions specified in this proposed AD 
are necessary to complete certain programs to ensure the continued 
airworthiness of aging airplane structure and to support an airplane 
reaching its LOV.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2014-0177, dated July 25, 2014 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A319, A320, and A321 series airplanes. The MCAI states:

    During the A320 fatigue test campaign for Extended Service Goal 
(ESG), it was determined that fatigue damage could appear on the 
clips, shear webs and angles at rear fuselage section 19, on Frame 
(FR) 72 and FR74.
    This condition, if not detected and corrected, could affect the 
structural integrity of the aeroplane.
    To address this potential unsafe condition, Airbus developed a 
modification, which has been published through Airbus Service 
Bulletin (SB) A320-53-1266 for in-service application to allow 
aeroplanes to operate up to the new ESG limit.
    For the reasons described above, this [EASA] AD requires 
replacement of the affected clips, shear webs and angles at rear 
fuselage section 19, FR72 and FR74 [including all applicable related 
investigative actions and repair if any cracking is found].

    Related investigative actions include rotating probe testing for 
cracking of the fastener holes and high frequency eddy current 
inspections for cracking of the stringers. 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-2015-1277.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A320-53-1266, Revision 01, dated 
June 20, 2013. This service information describes procedures for 
replacing clips, shear webs, and angles at rear fuselage section 19, 
FR72 and FR74. The actions described in this service information are 
intended to correct the unsafe condition identified in the MCAI. 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 of this NPRM.

FAA's Determination and Requirements of This Proposed AD

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

Costs of Compliance

    We estimate that this proposed AD affects 44 airplanes of U.S. 
registry.
    We also estimate that it would take about 110 work-hours per 
product to comply with the basic requirements of this proposed AD. The 
average labor rate is $85 per work-hour. Based on these figures, we 
estimate the cost of this proposed AD on U.S. operators to be $411,400, 
or $9,350 per product.
    We have received no definitive data on the costs of required parts.
    According to the manufacturer, some of the costs of this proposed 
AD may be covered under warranty, thereby

[[Page 26489]]

reducing the cost impact on affected individuals. We do not control 
warranty coverage for affected individuals. As a result, we have 
included all costs in our cost estimate.

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

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

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

Airbus: Docket No. FAA-2015-1277; Directorate Identifier 2014-NM-
155-AD.

(a) Comments Due Date

    We must receive comments by June 22, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the airplanes identified in paragraphs 
(c)(1), (c)(2), and (c)(3) of this AD, certificated in any category, 
all manufacturer serial numbers, except those on which Airbus 
Modification 30975 has been embodied in production.
    (1) Airbus Model A319-111, -112, -113, -114, -115, -131, -132, 
and -133 airplanes.
    (2) Airbus Model A320-211, -212, -214, -231, -232, and -233 
airplanes.
    (3) Airbus Model A321-111, -112, -131, -211, -212, -213, -231, 
and -232 airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by fatigue testing that determined fatigue 
damage could appear on clips, shear webs, and angles at certain rear 
fuselage sections and certain frames. This AD is intended to 
complete certain mandated programs intended to support the airplane 
reaching its limit of validity (LOV) of the engineering data that 
support the established structural maintenance program. We are 
issuing this AD to prevent fatigue damage on the clips, shear webs, 
and angles, which could affect the structural integrity of the 
airplane.

(f) Compliance

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

(g) Replacement

    At the later of the times specified in paragraphs (g)(1) and 
(g)(2) of this AD: Replace the clips, shear webs, and angles at rear 
fuselage section 19, frame (FR)72 and FR74, and do all applicable 
related investigative actions before further flight, in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A320-53-1266, Revision 01, dated June 20, 2013. If any crack is 
found during any related investigative action required by this AD: 
Before further flight, repair 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).
    (1) Before exceeding 48,000 flight cycles or 96,000 flight 
hours, whichever occurs first since the airplane's first flight.
    (2) Within 30 days after the effective date of this AD.

(h) Additional Replacement for Airplanes on Which the Replacement 
Required by Paragraph (g) of This AD Is Done Before 30,000 Flight 
Cycles or 60,000 Flight Hours

    For airplanes on which the replacement of clips, shear webs, and 
angles specified in Airbus Service Bulletin A320-53-1266 is done 
before accumulating 30,000 flight cycles or 60,000 flight hours, 
whichever occurred first since the airplane's first flight: Within 
30,000 flight cycles or 60,000 flight hours, whichever occurs first 
after that replacement, do the replacement specified in paragraph 
(g) of this AD.

(i) Credit for Previous Actions

    Except as required by paragraph (h) of this AD: This paragraph 
provides credit for the replacement required by paragraph (g) of 
this AD, if those actions were performed before the effective date 
of this AD using Airbus Service Bulletin A320-53-1266, dated January 
11, 2013, which is not incorporated by reference in this AD.

(j) 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: Sanjay 
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-1405; 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.

(k) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2014-0177, dated July 25, 2014, 
for related information. This MCAI may be found in the AD docket on 
the Internet at http://www.regulations.gov by

[[Page 26490]]

searching for and locating Docket No. FAA-2015-1277.
    (2) For service information identified in this AD, contact 
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 
61 93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. 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.

    Issued in Renton, Washington, on April 29, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-10948 Filed 5-7-15; 8:45 am]
 BILLING CODE 4910-13-P