Airworthiness Directives; Airbus Airplanes, 23199-23202 [2016-08953]

Download as PDF Lhorne on DSK5TPTVN1PROD with PROPOSALS Federal Register / Vol. 81, No. 76 / Wednesday, April 20, 2016 / Proposed Rules SW., Washington, DC 20585–0121. Telephone: (202) 287–6307. Email: Johanna.Jochum@Hq.Doe.Gov. SUPPLEMENTARY INFORMATION: On January 20, 2016, ASRAC met and unanimously passed the recommendation to form a Circulator Pumps Working Group. The purpose of the working group is to discuss and, if possible, reach consensus regarding definitions, test procedures, and energy conservation standards, to form the basis of proposed energy conservation standards and test procedures. The Working Group consists of representatives of parties having a defined stake in the outcome of the proposed standards, and will consult as appropriate with a range of experts on technical issues. Per the ASRAC Charter, the Working Group is expected to make a concerted effort to negotiate a final term sheet by September 30, 2016. This document announces the next series of meetings for this working group. DOE will host public meetings and webinars on the below dates. • Wednesday, May 4, 2016 at 9:00 a.m. to 5:00 p.m. EST at 955 L’Enfant Plaza, Room 8037B, SW., Washington, DC • Thursday, May 5, 2016 from 8:00 a.m. to 3:00 p.m. EST at 955 L’Enfant Plaza, Room 8037B, SW., Washington, DC • Thursday, June 16, 2016 at 9:00 a.m. to 5:00 p.m. EST at Navigant Offices, 1200 19th St NW., #700, Washington, DC • Friday, June 17, 2016 at 8:00 a.m. to 3:00 p.m. EST at 955 L’Enfant Plaza, Room 8037B, SW., Washington, DC • Tuesday, July 12, 2016 at 9:00 a.m. to 5:00 p.m. EST at 955 L’Enfant Plaza, Room 8037B, SW., Washington, DC • Wednesday, July 13, 2016 at 8:00 a.m. to 3:00 p.m. EST at 955 L’Enfant Plaza, Room 8037B, SW., Washington, DC • Wednesday, August 10, 2016 at 9:00 a.m. to 5:00 p.m. EST at 955 L’Enfant Plaza, Room 8037B, SW., Washington, DC • Thursday, August 11, 2016 at 8:00 a.m. to 3:00 p.m. EST at 950 L’Enfant Plaza, Room 6097, SW., Washington, DC • Wednesday, September 7, 2016 at 9:00 a.m. to 5:00 p.m. EST at 955 L’Enfant Plaza, Room 8037B, SW., Washington, DC • Thursday, September 8, 2016 at 8:00 a.m. to 3:00 p.m. EST at 950 L’Enfant Plaza, Room 6097, SW., Washington, DC • Wednesday, September 28, 2016 at 9:00 a.m. to 5:00 p.m. EST at 950 VerDate Sep<11>2014 14:51 Apr 19, 2016 Jkt 238001 L’Enfant Plaza, Room 6097, SW., Washington, DC • Thursday, September 29, 2016 at 8:00 a.m. to 3:00 p.m. EST at 950 L’Enfant Plaza, Room 6097, SW., Washington, DC Members of the public are welcome to observe the business of the meeting and, if time allows, may make oral statements during the specified period for public comment. To attend the meeting and/or to make oral statements regarding any of the items on the agenda, email asrac@ee.doe.gov. In the email, please indicate your name, organization (if appropriate), citizenship, and contact information. Please note that foreign nationals participating in the public meeting are subject to advance security screening procedures which require advance notice prior to attendance at the public meeting. If you are a foreign national, and wish to participate in the public meeting, please inform DOE as soon as possible by contacting Ms. Regina Washington at (202) 586–1214 or by email: Regina.Washington@ee.doe.gov so that the necessary procedures can be completed. Anyone attending the meeting will be required to present a government photo identification, such as a passport, driver’s license, or government identification. Due to the required security screening upon entry, individuals attending should arrive early to allow for the extra time needed. Due to the REAL ID Act implemented by the Department of Homeland Security (DHS) recent changes have been made regarding ID requirements for individuals wishing to enter Federal buildings from specific states and U.S. territories. Driver’s licenses from the following states or territory will not be accepted for building entry and one of the alternate forms of ID listed below will be required. DHS has determined that regular driver’s licenses (and ID cards) from the following jurisdictions are not acceptable for entry into DOE facilities: Alaska, Louisiana, New York, American Samoa, Maine, Oklahoma, Arizona, Massachusetts, Washington, and Minnesota. Acceptable alternate forms of PhotoID include: U.S. Passport or Passport Card; an Enhanced Driver’s License or Enhanced ID-Card issued by the states of Minnesota, New York or Washington (Enhanced licenses issued by these states are clearly marked Enhanced or Enhanced Driver’s License); A military ID or other Federal government issued Photo-ID card. Docket: The docket is available for review at www.regulations.gov, PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 23199 including Federal Register documents, public meeting attendee lists and transcripts, comments, and other supporting documents/materials. All documents in the docket are listed in the www.regulations.gov index. However, not all documents listed in the index may be publicly available, such as information that is exempt from public disclosure. Issued in Washington, DC, on April 14, 2016. Kathleen B. Hogan, Deputy Assistant Secretary for Energy Efficiency, Energy Efficiency and Renewable Energy. [FR Doc. 2016–09126 Filed 4–19–16; 8:45 am] BILLING CODE 6450–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–5591; Directorate Identifier 2014–NM–193–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede Airworthiness Directive (AD) 2005–15– 07, for certain Airbus Model A320–111 airplanes and Model A320–200 series airplanes. AD 2005–15–07 currently requires installing insulator and cable ties to the electrical cables of the S routes at the gaps in the raceway in the wing trailing edge and the wing tip and wing root areas. Since we issued AD 2005–15–07, we have received reports of wire chafing in the left-hand wing trailing edge. This proposed AD would require additional modifications in the trailing edges of both wings. This proposed AD would also remove airplanes from the applicability. We are proposing this AD to prevent wire chafing in the trailing edge of the wings, which could result in a short circuit in the vicinity of the fuel tanks, consequently resulting in a potential source of ignition in a fuel tank vapor space and consequent fuel tank explosion. SUMMARY: We must receive comments on this proposed AD by June 6, 2016. ADDRESSES: You may send comments by any of the following methods: DATES: E:\FR\FM\20APP1.SGM 20APP1 23200 Federal Register / Vol. 81, No. 76 / Wednesday, April 20, 2016 / Proposed Rules • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, 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 https://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 https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 5591; 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: Lhorne on DSK5TPTVN1PROD with PROPOSALS 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–2016–5591; Directorate Identifier 2014–NM–193–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy VerDate Sep<11>2014 14:51 Apr 19, 2016 Jkt 238001 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 https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion On July 13, 2005, we issued AD 2005– 15–07, Amendment 39–14196 (70 FR 43024, July 26, 2005) (‘‘AD 2005–15– 07’’). AD 2005–15–07 requires actions intended to address an unsafe condition on certain Airbus Model A320–111 airplanes and Model A320–200 series airplanes. Since we issued AD 2005–15–07, we have received reports of wire chafing in the left-hand wing trailing edge. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014–0198, dated September 5, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus Model A320–211, –212, and –231 airplanes. The MCAI states: Prompted by an accident * * *, the FAA published Special Federal Aviation Regulation (SFAR) 88 [(66 FR 23086, May 7, 2001)], and the Joint Aviation Authorities (JAA) published Interim Policy INT/POL/25/ 12. Prompted by that regulation, the results of an Airbus review of the A320 type design identified, on certain aeroplanes, a possible ignition source in fuel tank vapour space(s). That condition, if not corrected, could result in a fuel tank explosion and consequent loss of the aeroplane. It was, therefore, decided to modify the cable routes of the wing trailing edge, aft of the rear spar and wing tip of those aeroplanes, to be applied in service in accordance with the instructions of Airbus Service Bulletin (SB) A320–24–1062 Revision 05. Following that decision, DGAC France issued AD F–2004–173 (EASA approval number 2004–10570) to require that modification. After that AD was issued, it was found that additional work, introduced by Airbus SB A320–24–1062 Revision 05, was not included as part of the normal accomplishment instructions, which meant that the additional work might not be accomplished. Consequently, EASA issued AD 2008–0051, retaining the requirements of DGAC France AD F–2004–173 [which corresponds to FAA AD 2005–15–07, Amendment 39–14196 (70 FR 43024, July 26, 2005)], which was superseded, and required the accomplishment of the additional work in accordance with the instructions of Airbus PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 SB A320–24–1062 Revision 06. EASA AD 2008–0051 was revised to reduce the Applicability and to add a clarification to paragraph (2). After EASA AD 2008–0051R1 was issued, some operators reported wire chafing in the left hand wing trailing edge. Investigation established that the wire chafing, initiated at raceway gaps, was either due to maintenance action(s), or to structure vibrations. Prompted by these findings, Airbus developed two modifications to prevent any further wire chafing by introducing an additional protection at raceway gaps and a new cable standard in the trailing edges of both wings. Airbus published SB A320–92– 1049 and SB A320–92–1052 to make these modifications available for in-service application. At the time of incorporation of Airbus SB A320–24–1062, these two modifications were considered recommended only. EASA recently determined that this condition, if not corrected, could lead to a short circuit on 115 volts in the vicinity of fuel tanks, consequently creating another risk of ignition source in a fuel tank vapour space. For the reasons described above, this [EASA] AD retains the requirements of EASA AD 2008–0051R1, which is superseded, and requires modifications to install the additional anti-chafing protection and the new cable standard. This proposed AD also removes Model A320–214, –232, and –233 airplanes from the applicability because those airplane models have been modified in production or in service. You may examine the MCAI in the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 5591. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletins A320–92–1049, Revision 01, dated November 28, 2011; A320–92–1052, dated December 5, 2007; and A320–24– 1062, Revision 07, dated November 28, 2011. Airbus Service Bulletin A320–92– 1049, Revision 01, dated November 28, 2011, describes procedures to install the additional anti-chafing protection. Airbus Service Bulletin A320–92– 1052, dated December 5, 2007, describes procedures to replace the current electrical cable with the new standard one. Airbus A320–24–1062, Revision 07, dated November 28, 2011, describes procedures to install insulator and cable ties to the electrical cables of the S routes at the gaps in the raceway in the wing trailing edge and the wing tip and wing root areas. This service information is reasonably available because the interested parties have access to it through their normal E:\FR\FM\20APP1.SGM 20APP1 Federal Register / Vol. 81, No. 76 / Wednesday, April 20, 2016 / Proposed Rules Authority for This Rulemaking course of business or by the means identified in the ADDRESSES section. 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 the same type design. Difference Between This Proposed AD and the MCAI or Service Information The MCAI specifies a compliance time of 72 months for modifying the trailing edges of both wings. However, this proposed AD would require a compliance time of 60 months to be consistent with the 60-month compliance time for installing the insulator and cable ties to the electrical cables of the S routes at the gaps in the raceway in the wing trailing edge and the wing tip and wing root areas specified in AD 2005–15–07. This difference has been coordinated with EASA. Lhorne on DSK5TPTVN1PROD with PROPOSALS Costs of Compliance We estimate that this proposed AD affects 47 airplanes of U.S. registry. The actions required by AD 2005–15– 07, and retained in this proposed AD take about 35 work-hours per product, at an average labor rate of $85 per workhour. Required parts cost about $0 per product. Based on these figures, the estimated cost of the actions that are required by AD 2005–15–07 is $2,975 per product. We also estimate that it would take about 76 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost about $13,000 per product. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $914,620, or $19,460 per product. According to the manufacturer, some of the costs of this proposed AD may be covered under warranty, thereby 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. VerDate Sep<11>2014 14:51 Apr 19, 2016 Jkt 238001 § 39.13 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. 23201 ■ 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2005–15–07, Amendment 39–14196 (70 FR 43024, July 26, 2005), and adding the following new AD: Airbus: Docket No. FAA–2016–5591; Directorate Identifier 2014–NM–193–AD. (a) Comments Due Date We must receive comments by June 6, 2016. (b) Affected ADs This AD replaces AD 2005–15–07, Amendment 39–14196 (70 FR 43024, July 26, 2005) (‘‘AD 2005–15–07’’). (c) Applicability This AD applies to Airbus Model A320– 211, –212, and –231 airplanes, certificated in any category, all manufacturer serial numbers except those on which Airbus Modification 22626 has been embodied in production. (d) Subject Air Transport Association (ATA) of America Code 24, Electrical Power; and Code 92. (e) Reason This AD was prompted by reports of wire chafing in the left-hand wing trailing edge. We are issuing this AD to prevent wire chafing in the trailing edge of the wings, which could result in a short circuit in the vicinity of the fuel tanks, consequently resulting in a potential source of ignition in a fuel tank vapor space and consequent fuel tank explosion. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Modification This paragraph restates the requirements of paragraph (f) of AD 2005–15–07, with revised service information. Within 60 months after August 30, 2005 (the effective date of AD 2005–15–07), install insulator and cable ties to the electrical cables of the S routes at the gaps in the raceway in the wing trailing edge and the wing tip and wing root areas, in accordance with Airbus Service Bulletin A320–24–1062, Revision 05, dated June 27, 2002; or the Accomplishment Instructions of Airbus Service Bulletin A320–24–1062, Revision 07, dated November 28, 2011. As of the effective date of this AD, only Airbus Service Bulletin A320–24–1062, Revision 07, dated November 28, 2011, may be used. (h) New Requirement of This AD: Modification of Trailing Edges Within 60 months after the effective date of this AD, modify the trailing edges of both wings by accomplishing the actions specified in paragraphs (h)(1) and (h)(2) of this AD. (1) Install the additional anti-chafing protection in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–92–1049, Revision 01, dated November 28, 2011. E:\FR\FM\20APP1.SGM 20APP1 23202 Federal Register / Vol. 81, No. 76 / Wednesday, April 20, 2016 / Proposed Rules (2) Replace the current electrical cable with the new standard one in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–92–1052, dated December 5, 2007. During the replacement, ensure that the anti-chafing protection specified in Airbus Service Bulletin A320– 92–1049, as required by paragraph (h)(1) of this AD, remains in place. (i) Additional Modification For airplanes on which the installation specified in Airbus Service Bulletin A320– 24–1062, Revision 05, dated June 27, 2002, has been done: Within 60 months after the effective date of this AD, install insulators and cable ties, in accordance with ‘‘Modification—Additional Work (Introduced at Revision No. 06)’’ of the Accomplishment Instructions of Airbus Service Bulletin A320– 24–1062, Revision 07, dated November 28, 2011. Lhorne on DSK5TPTVN1PROD with PROPOSALS (j) Credit for Previous Actions (1) This paragraph provides credit for actions required by paragraphs (g) and (i) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320–24–1062, Revision 06, dated June 26, 2007, which is not incorporated by reference in this AD. (2) This paragraph provides credit for actions required by paragraph (h) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320–92–1049, dated July 23, 2007, which is not incorporated by reference in this AD. (k) 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: 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 Airbus’s EASA Design Organization Approval (DOA). If approved by VerDate Sep<11>2014 14:51 Apr 19, 2016 Jkt 238001 the DOA, the approval must include the DOA-authorized signature. (l) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014–0198, dated September 5, 2014, for related information. This MCAI may be found in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA–2016–5591. (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 https://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 4, 2016. Jeffrey E. Duven, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–08953 Filed 4–19–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–5593; Directorate Identifier 2015–NM–184–AD] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc. Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede Airworthiness Directive (AD) 2015–02– 23, for certain Bombardier, Inc. Model CL–600–1A11 (CL–600), CL–600–2A12 (CL–601), and CL–600–2B16 (CL–601– 3A, and CL–601–3R Variants) airplanes. AD 2015–02–23 currently requires repetitive inspections for fractured or incorrectly oriented fasteners on the inboard flap hinge-box forward fittings on both wings, and replacement of all fasteners if necessary. The preamble to AD 2015–02–23 explains that we consider the requirements interim action and are considering further rulemaking. We now have determined that further rulemaking is indeed necessary, and that replacement of the fasteners is necessary. This proposed AD would require terminating action to replace the fasteners on the inboard flap SUMMARY: PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 hinge-box forward fittings on both wings. We are proposing this AD to detect and correct incorrectly oriented or fractured fasteners, which could result in detachment of the flap hingebox and the flap surface, and consequent reduced controllability of the airplane. DATES: We must receive comments on this proposed AD by June 6, 2016. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Bombardier, Inc., ˆ 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 https://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 https:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 5593; 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: Aziz Ahmed, Aerospace Engineer, Airframe and Mechanical Systems Branch, ANE– 171, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7329; fax 516–794–5531. SUPPLEMENTARY INFORMATION: E:\FR\FM\20APP1.SGM 20APP1

Agencies

[Federal Register Volume 81, Number 76 (Wednesday, April 20, 2016)]
[Proposed Rules]
[Pages 23199-23202]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-08953]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-5591; Directorate Identifier 2014-NM-193-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede Airworthiness Directive (AD) 2005-15-
07, for certain Airbus Model A320-111 airplanes and Model A320-200 
series airplanes. AD 2005-15-07 currently requires installing insulator 
and cable ties to the electrical cables of the S routes at the gaps in 
the raceway in the wing trailing edge and the wing tip and wing root 
areas. Since we issued AD 2005-15-07, we have received reports of wire 
chafing in the left-hand wing trailing edge. This proposed AD would 
require additional modifications in the trailing edges of both wings. 
This proposed AD would also remove airplanes from the applicability. We 
are proposing this AD to prevent wire chafing in the trailing edge of 
the wings, which could result in a short circuit in the vicinity of the 
fuel tanks, consequently resulting in a potential source of ignition in 
a fuel tank vapor space and consequent fuel tank explosion.

DATES: We must receive comments on this proposed AD by June 6, 2016.

ADDRESSES: You may send comments by any of the following methods:

[[Page 23200]]

     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this NPRM, 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 https://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 https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
5591; 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-2016-5591; 
Directorate Identifier 2014-NM-193-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 https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On July 13, 2005, we issued AD 2005-15-07, Amendment 39-14196 (70 
FR 43024, July 26, 2005) (``AD 2005-15-07''). AD 2005-15-07 requires 
actions intended to address an unsafe condition on certain Airbus Model 
A320-111 airplanes and Model A320-200 series airplanes.
    Since we issued AD 2005-15-07, we have received reports of wire 
chafing in the left-hand wing trailing edge.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2014-0198, dated September 5, 2014 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A320-211, -212, and -231 airplanes. The MCAI states:

    Prompted by an accident * * *, the FAA published Special Federal 
Aviation Regulation (SFAR) 88 [(66 FR 23086, May 7, 2001)], and the 
Joint Aviation Authorities (JAA) published Interim Policy INT/POL/
25/12.
    Prompted by that regulation, the results of an Airbus review of 
the A320 type design identified, on certain aeroplanes, a possible 
ignition source in fuel tank vapour space(s). That condition, if not 
corrected, could result in a fuel tank explosion and consequent loss 
of the aeroplane.
    It was, therefore, decided to modify the cable routes of the 
wing trailing edge, aft of the rear spar and wing tip of those 
aeroplanes, to be applied in service in accordance with the 
instructions of Airbus Service Bulletin (SB) A320-24-1062 Revision 
05. Following that decision, DGAC France issued AD F-2004-173 (EASA 
approval number 2004-10570) to require that modification.
    After that AD was issued, it was found that additional work, 
introduced by Airbus SB A320-24-1062 Revision 05, was not included 
as part of the normal accomplishment instructions, which meant that 
the additional work might not be accomplished. Consequently, EASA 
issued AD 2008-0051, retaining the requirements of DGAC France AD F-
2004-173 [which corresponds to FAA AD 2005-15-07, Amendment 39-14196 
(70 FR 43024, July 26, 2005)], which was superseded, and required 
the accomplishment of the additional work in accordance with the 
instructions of Airbus SB A320-24-1062 Revision 06. EASA AD 2008-
0051 was revised to reduce the Applicability and to add a 
clarification to paragraph (2).
    After EASA AD 2008-0051R1 was issued, some operators reported 
wire chafing in the left hand wing trailing edge. Investigation 
established that the wire chafing, initiated at raceway gaps, was 
either due to maintenance action(s), or to structure vibrations.
    Prompted by these findings, Airbus developed two modifications 
to prevent any further wire chafing by introducing an additional 
protection at raceway gaps and a new cable standard in the trailing 
edges of both wings. Airbus published SB A320-92-1049 and SB A320-
92-1052 to make these modifications available for in-service 
application. At the time of incorporation of Airbus SB A320-24-1062, 
these two modifications were considered recommended only.
    EASA recently determined that this condition, if not corrected, 
could lead to a short circuit on 115 volts in the vicinity of fuel 
tanks, consequently creating another risk of ignition source in a 
fuel tank vapour space.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2008-0051R1, which is superseded, and 
requires modifications to install the additional anti-chafing 
protection and the new cable standard.

    This proposed AD also removes Model A320-214, -232, and -233 
airplanes from the applicability because those airplane models have 
been modified in production or in service. You may examine the MCAI in 
the AD docket on the Internet at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2016-5591.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletins A320-92-1049, Revision 01, 
dated November 28, 2011; A320-92-1052, dated December 5, 2007; and 
A320-24-1062, Revision 07, dated November 28, 2011.
    Airbus Service Bulletin A320-92-1049, Revision 01, dated November 
28, 2011, describes procedures to install the additional anti-chafing 
protection.
    Airbus Service Bulletin A320-92-1052, dated December 5, 2007, 
describes procedures to replace the current electrical cable with the 
new standard one.
    Airbus A320-24-1062, Revision 07, dated November 28, 2011, 
describes procedures to install insulator and cable ties to the 
electrical cables of the S routes at the gaps in the raceway in the 
wing trailing edge and the wing tip and wing root areas.
    This service information is reasonably available because the 
interested parties have access to it through their normal

[[Page 23201]]

course of business or by the means identified in the ADDRESSES section.

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 the same 
type design.

Difference Between This Proposed AD and the MCAI or Service Information

    The MCAI specifies a compliance time of 72 months for modifying the 
trailing edges of both wings. However, this proposed AD would require a 
compliance time of 60 months to be consistent with the 60-month 
compliance time for installing the insulator and cable ties to the 
electrical cables of the S routes at the gaps in the raceway in the 
wing trailing edge and the wing tip and wing root areas specified in AD 
2005-15-07. This difference has been coordinated with EASA.

Costs of Compliance

    We estimate that this proposed AD affects 47 airplanes of U.S. 
registry.
    The actions required by AD 2005-15-07, and retained in this 
proposed AD take about 35 work-hours per product, at an average labor 
rate of $85 per work-hour. Required parts cost about $0 per product. 
Based on these figures, the estimated cost of the actions that are 
required by AD 2005-15-07 is $2,975 per product.
    We also estimate that it would take about 76 work-hours per product 
to comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Required parts would cost about 
$13,000 per product. Based on these figures, we estimate the cost of 
this proposed AD on U.S. operators to be $914,620, or $19,460 per 
product.
    According to the manufacturer, some of the costs of this proposed 
AD may be covered under warranty, thereby 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 removing Airworthiness Directive (AD) 
2005-15-07, Amendment 39-14196 (70 FR 43024, July 26, 2005), and adding 
the following new AD:

Airbus: Docket No. FAA-2016-5591; Directorate Identifier 2014-NM-
193-AD.

(a) Comments Due Date

    We must receive comments by June 6, 2016.

(b) Affected ADs

    This AD replaces AD 2005-15-07, Amendment 39-14196 (70 FR 43024, 
July 26, 2005) (``AD 2005-15-07'').

(c) Applicability

    This AD applies to Airbus Model A320-211, -212, and -231 
airplanes, certificated in any category, all manufacturer serial 
numbers except those on which Airbus Modification 22626 has been 
embodied in production.

(d) Subject

    Air Transport Association (ATA) of America Code 24, Electrical 
Power; and Code 92.

(e) Reason

    This AD was prompted by reports of wire chafing in the left-hand 
wing trailing edge. We are issuing this AD to prevent wire chafing 
in the trailing edge of the wings, which could result in a short 
circuit in the vicinity of the fuel tanks, consequently resulting in 
a potential source of ignition in a fuel tank vapor space and 
consequent fuel tank explosion.

(f) Compliance

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

(g) Retained Modification

    This paragraph restates the requirements of paragraph (f) of AD 
2005-15-07, with revised service information. Within 60 months after 
August 30, 2005 (the effective date of AD 2005-15-07), install 
insulator and cable ties to the electrical cables of the S routes at 
the gaps in the raceway in the wing trailing edge and the wing tip 
and wing root areas, in accordance with Airbus Service Bulletin 
A320-24-1062, Revision 05, dated June 27, 2002; or the 
Accomplishment Instructions of Airbus Service Bulletin A320-24-1062, 
Revision 07, dated November 28, 2011. As of the effective date of 
this AD, only Airbus Service Bulletin A320-24-1062, Revision 07, 
dated November 28, 2011, may be used.

(h) New Requirement of This AD: Modification of Trailing Edges

    Within 60 months after the effective date of this AD, modify the 
trailing edges of both wings by accomplishing the actions specified 
in paragraphs (h)(1) and (h)(2) of this AD.
    (1) Install the additional anti-chafing protection in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A320-92-1049, Revision 01, dated November 28, 2011.

[[Page 23202]]

    (2) Replace the current electrical cable with the new standard 
one in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A320-92-1052, dated December 5, 2007. During the 
replacement, ensure that the anti-chafing protection specified in 
Airbus Service Bulletin A320-92-1049, as required by paragraph 
(h)(1) of this AD, remains in place.

(i) Additional Modification

    For airplanes on which the installation specified in Airbus 
Service Bulletin A320-24-1062, Revision 05, dated June 27, 2002, has 
been done: Within 60 months after the effective date of this AD, 
install insulators and cable ties, in accordance with 
``Modification--Additional Work (Introduced at Revision No. 06)'' of 
the Accomplishment Instructions of Airbus Service Bulletin A320-24-
1062, Revision 07, dated November 28, 2011.

(j) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by 
paragraphs (g) and (i) of this AD, if those actions were performed 
before the effective date of this AD using Airbus Service Bulletin 
A320-24-1062, Revision 06, dated June 26, 2007, which is not 
incorporated by reference in this AD.
    (2) This paragraph provides credit for actions required by 
paragraph (h) of this AD, if those actions were performed before the 
effective date of this AD using Airbus Service Bulletin A320-92-
1049, dated July 23, 2007, which is not incorporated by reference in 
this AD.

(k) 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: 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 Airbus's EASA Design Organization Approval (DOA). If 
approved by the DOA, the approval must include the DOA-authorized 
signature.

(l) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2014-0198, dated September 5, 
2014, for related information. This MCAI may be found in the AD 
docket on the Internet at https://www.regulations.gov by searching 
for and locating Docket No. FAA-2016-5591.
    (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 https://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 4, 2016.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-08953 Filed 4-19-16; 8:45 am]
 BILLING CODE 4910-13-P
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