Airworthiness Directives; Airbus Airplanes, 33438-33441 [2016-12352]

Download as PDF 33438 Federal Register / Vol. 81, No. 102 / Thursday, May 26, 2016 / Proposed Rules Participation at the Public Meetings Commenters who wish to present oral statements at the July 7, 2016, public meeting should submit requests to the FAA no later than June 29, 2016. Requests should be submitted as described in the FOR FURTHER INFORMATION CONTACT section of this document and should include a written summary of oral remarks to be presented and an estimate of time needed for the presentation. Preferably, please submit requests via email to: Michael.Hughlett@faa.gov. Requests received after the dates specified above will be scheduled if there is time available during the meeting; however, the speakers’ names may not appear on the written agenda. To accommodate as many speakers as possible, the amount of time allocated to each speaker may be less than the amount of time requested to ensure various views can be heard. See ‘‘Public Meeting Procedures’’ below. The FAA may have available a projector and a computer capable of accommodating Word and PowerPoint presentations. Persons requiring any other kind of audiovisual equipment should notify the FAA when requesting to be placed on the agenda. The FAA will make every effort to accommodate all persons wishing to attend. Sign and oral interpretation can be made available at the meeting, as well as an assistive listening device, if requested 10 calendar days before the meeting. jstallworth on DSK7TPTVN1PROD with PROPOSALS Public Meeting Procedures A panel of representatives from the FAA will be present to facilitate the meeting in accordance with the following procedures: (1) The meeting is designed to facilitate the public comment process. The meeting will be informal and nonadversarial. No individual will be subject to cross-examination by any other participant. Government representatives on the panel may ask questions to clarify statements and to ensure an accurate record. Any statement made during the meetings by a panel member should not be construed as an official position of the government. (2) There will be no admission fees or other charges to attend or to participate in the public meeting. The meeting will be open to all persons, subject to availability of space in the meeting room. The FAA asks that participants sign in between 8:30 and 9:00 a.m. on the day of the meeting. The FAA will try to accommodate all speakers; however if available time does not allow this, speakers who have contacted the FAA VerDate Sep<11>2014 15:09 May 25, 2016 Jkt 238001 in advance will be allowed to speak first, others will be scheduled on a firstcome-first-served basis. The FAA reserves the right to exclude some speakers, if necessary, to obtain balanced viewpoints. The meeting may adjourn early if scheduled speakers complete their statements in less time than is scheduled for the meeting. (3) The FAA will prepare agendas of speakers and presenters and make the agendas available at the meeting. (4) Speaker time slots may be limited to 3-minute statements. If possible, the FAA will notify speakers if additional time is available. (5) The FAA will review and consider all material presented by participants at the public meeting. Position papers or materials presenting views or information related to the draft policy may be accepted at the discretion of the presiding officer and will be subsequently placed in the public docket. The FAA requests that presenters at the meeting provide at least 10 copies of all materials for distribution to the panel members. Presenters may provide other copies to the audience at their discretion. (6) We ask each person presenting comments to provide the technical basis to support the comments. The most helpful comments reference a specific portion of the policy statement and explain the reason for any recommended change. Issued in Fort Worth, Texas, on May 18, 2016. Jorge R. Castillo, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 2016–12526 Filed 5–25–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–6893; Directorate Identifier 2015–NM–181–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 A318–112 airplanes, A319–111, –112, –115, –132, and –133 airplanes, A320–214, –232, and –233 SUMMARY: PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 airplanes, and A321–211, –212, –213, –231, and –232 airplanes. This proposed AD was prompted by a quality control review on the final assembly line, which determined that the wrong aluminum alloy was used to manufacture several structural parts. This proposed AD would require a one-time eddy current conductivity measurements of certain cabin and cargo compartment structural parts to determine if an incorrect aluminum alloy was used, and replacement if necessary. We are proposing this AD to detect and replace structural parts made of incorrect aluminum alloy. This condition could result in reduced structural integrity of the airplane. DATES: We must receive comments on this proposed AD by July 11, 2016. 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: Deliver to Mail address above 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: 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–2016– 6893; 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. E:\FR\FM\26MYP1.SGM 26MYP1 Federal Register / Vol. 81, No. 102 / Thursday, May 26, 2016 / Proposed Rules 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–2016–6893; Directorate Identifier 2015–NM–181–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 jstallworth on DSK7TPTVN1PROD with PROPOSALS The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2015–0218, dated November 3, 2015 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus Model A318–112, A319–111, –112, –115, –132, and –133, A320–214, –232, and –233, and A321–211, –212, –213, –231, and –232 airplanes. The MCAI states: Following an Airbus quality control review on the final assembly line, it was discovered that wrong aluminum alloy were delivered by a supplier for several structural parts. The results of the investigations highlighted that 0.04% of the stock could be impacted by this wrong material. Structural investigations demonstrated the capability to sustain the static limits loads, and sufficient fatigue life up to a certain inspection threshold. This condition, if not detected and corrected, could reduce the structural integrity of the aeroplane. To address this potential unsafe condition, Airbus issued Service Bulletin (SB) A320– 53–1298 and SB A320–53–1299 to provide inspection instructions. For the reasons described above, this [EASA] AD requires a one-time Special Detailed Inspection (SDI) [eddy current conductivity measurements] of certain cabin and cargo compartment parts for material VerDate Sep<11>2014 15:09 May 25, 2016 Jkt 238001 identification and, depending on findings, replacement with serviceable parts. 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–2016– 6893. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletins A320–53–1298 and A320–53–1299, both dated February 16, 2015; both including Appendices 01, 02, and 03, dated February 16, 2015. The service information describes procedures for a one-time eddy current conductivity measurement of certain cabin and cargo compartment structural parts to determine if an incorrect aluminum alloy was used, and replacement of any affected part with a serviceable part. 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. 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 167 airplanes of U.S. registry. We also estimate that it would take about 1 work-hour 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 $14,195, or $85 per product. We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed AD. 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 available costs in our cost estimate. PO 00000 Frm 00016 Fmt 4702 Sfmt 4702 33439 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. E:\FR\FM\26MYP1.SGM 26MYP1 33440 § 39.13 Federal Register / Vol. 81, No. 102 / Thursday, May 26, 2016 / Proposed Rules [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ Airbus: Docket No. FAA–2016–6893; Directorate Identifier 2015–NM–181–AD. (a) Comments Due Date We must receive comments by July 11, 2016. (b) Affected ADs None. (c) Applicability This AD applies to the Airbus airplanes identified in paragraphs (c)(1) through (c)(4) of this AD, certificated in any category; manufacturer serial numbers 3586, 3588, 3589, 3590, 3595, 3604, 3608, 3614, 3615, 3620, 3632, 3634, 3638, 3647, 3651, 3657, 3660, 3661, 3663, 3671, 3675, 3680, 3683 through 3687 inclusive, 3689, 3691, 3694, 3700, 3702, 3704, 3705, 3710, 3720, 3727, 3728, 3733, 3735, 3742, 3744, 3746, 3754, 3757, 3759, 3763, 3768, 3770, 3772, 3774, 3775, 3779, 3788, 3790, 3794, 3797, 3799, 3801, 3803, 3808, 3810, 3818, 3822, 3824, 3826 through 4329 inclusive, 4331 through 6051 inclusive, 6053 through 6061 inclusive, 6063 through 6072 inclusive, 6074 through 6100 inclusive, 6102 through 6115 inclusive, 6117 through 6126 inclusive, 6128 through 6136 inclusive, 6138 through 6143 inclusive, 6145 through 6150 inclusive, 6152 through 6159 inclusive, 6161 and 6162. (1) Airbus Model A318–112 airplanes. (2) Airbus Model A319–111, –112, –115, –132, and –133 airplanes. (3) Airbus Model A320–214, –232, and –233 airplanes. (4) Airbus Model A321–211, –212, –213, –231, and –232 airplanes. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by a quality control review of the final assembly line which determined that the wrong aluminum alloy was used to manufacture several structural parts. We are issuing this AD to detect and correct structural parts made of incorrect aluminum alloy. This condition could result in reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) One-Time Measurement Within 6 years after the effective date of this AD, but not exceeding 12 years since the date of issuance of the original certificate of airworthiness or the date of issuance of the original export certificate of airworthiness: Do a one-time eddy current conductivity measurements (with 60kHz and 480kHz) of the cabin and cargo compartment structural parts identified in the ‘‘Affected P/N’’ column of table 1 to paragraphs (g) and (h) of this AD to determine if an incorrect aluminum alloy was used, in accordance with the Accomplishment Instructions of Airbus Service Bulletins A320–53–1298, dated February 16, 2015, including Appendices 01, 02, and 03, dated February 16, 2015 (for cabin parts); and A320–53– 1299, dated February 16, 2015, including Appendices 01, 02, and 03, dated February 16, 2015 (for cargo parts). TABLE 1 TO PARAGRAPHS (g) AND (h) OF THIS AD—PARTS TO BE INSPECTED/INSTALLED Affected P/N D5347120720000 D5347120720100 D5347120920000 D5347120920100 D5347118820400 D5347717620000 D5357020620000 D5358526421200 D5358526421400 D5358526421000 D5358513120001 Acceptable replacement P/N ...................................................................... ...................................................................... ...................................................................... ...................................................................... ...................................................................... ...................................................................... ...................................................................... ...................................................................... ...................................................................... ...................................................................... ...................................................................... jstallworth on DSK7TPTVN1PROD with PROPOSALS (h) Replacement If during the inspection required by paragraph (g) of this AD, any affected part having a part number (P/N) specified in table 1 to paragraphs (g) and (h) of this AD is found to have a measured value greater than that specified in Figure A–GFAAA, Sheet 02, ‘‘Inspection Flowchart,’’ of the applicable service information identified in paragraph (g) of this AD: Before further flight, replace with an acceptable replacement part having a P/N specified in table 1 to paragraphs (g) and (h) of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletins A320–53–1298, dated February 16, 2015, including Appendices 01, 02, and 03, dated February 16, 2015 (for cabin parts); and A320–53–1299, dated February 16, 2015, including Appendices 01, 02, and 03, dated February 16, 2015 (for cargo parts). (i) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane VerDate Sep<11>2014 15:09 May 25, 2016 Jkt 238001 D5347120720051 D5347120720151 D5347120920051 D5347120920151 D5347118820451 D5347717620051 D5357020620051 D5358526421251 D5358526421400 D5358526421051 D5358513120051 ...................................................................... ...................................................................... ...................................................................... ...................................................................... ...................................................................... ...................................................................... ...................................................................... ...................................................................... ...................................................................... ...................................................................... ...................................................................... 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: 9ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 Area Cabin. Cabin. Cabin. Cabin. Cabin. Cargo. Cargo. Cargo. Cargo. Cargo. Cargo. (EASA); or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (j) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2015–0218, dated November 3, 2015, 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–2016–6893. E:\FR\FM\26MYP1.SGM 26MYP1 Federal Register / Vol. 81, No. 102 / Thursday, May 26, 2016 / Proposed Rules (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 May 17, 2016. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–12352 Filed 5–25–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF ENERGY Federal Energy Regulatory Commission 18 CFR Part 40 [Docket No. RM16–7–000] Disturbance Control Standard— Contingency Reserve for Recovery From a Balancing Contingency Event Reliability Standard Federal Energy Regulatory Commission, DOE. ACTION: Notice of proposed rulemaking. AGENCY: The Federal Energy Regulatory Commission proposes to approve Reliability Standard BAL–002– 2 (Disturbance Control Standard— Contingency Reserve for Recovery from a Balancing Contingency Event) submitted by the North American Electric Reliability Corporation (NERC). Proposed Reliability Standard BAL– 002–2 is designed to ensure that applicable entities balance resources and demand and return their Area Control Error to defined values following a Reportable Balancing Contingency Event. In addition, the Commission proposes to direct NERC to modify Reliability Standard BAL–002–2 to address concerns related to the possible extension or delay of the periods for Area Control Error recovery and contingency reserve restoration. The Commission also proposes to direct NERC to address a reliability gap regarding megawatt losses above the most severe single contingency. DATES: Comments are due July 25, 2016. ADDRESSES: Comments, identified by docket number, may be filed in the following ways: • Electronic Filing through http:// www.ferc.gov. Documents created jstallworth on DSK7TPTVN1PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 15:09 May 25, 2016 Jkt 238001 electronically using word processing software should be filed in native applications or print-to-PDF format and not in a scanned format. • Mail/Hand Delivery: Those unable to file electronically may mail or handdeliver comments to: Federal Energy Regulatory Commission, Secretary of the Commission, 888 First Street NE., Washington, DC 20426. Instructions: For detailed instructions on submitting comments and additional information on the rulemaking process, see the Comment Procedures Section of this document. FOR FURTHER INFORMATION CONTACT: Enakpodia Agbedia (Technical Information), Office of Electric Reliability, Division of Reliability Standards, Federal Energy Regulatory Commission, 888 First Street NE., Washington, DC 20426, Telephone: (202) 502–6750, Enakpodia.Agbedia@ ferc.gov. Mark Bennett (Legal Information), Office of the General Counsel, Federal Energy Regulatory Commission, 888 First Street NE., Washington, DC 20426, Telephone: (202) 502–8524, Mark.Bennett@ferc.gov. SUPPLEMENTARY INFORMATION: 1. Under section 215 of the Federal Power Act (FPA),1 the Commission proposes to approve proposed Reliability Standard BAL–002–2 (Disturbance Control Standard—Contingency Reserve for Recovery from a Balancing Contingency Event). The North American Electric Reliability Corporation (NERC), the Commission-certified Electric Reliability Organization (ERO), submitted proposed Reliability Standard BAL–002–2 for Commission approval. Proposed Reliability Standard BAL– 002–2 applies to balancing authorities and reserve sharing groups. Proposed Reliability Standard BAL–002–2 is designed to ensure that these entities are able to recover from system contingencies by deploying adequate reserves to return their Area Control Error (ACE) to defined values and by replacing the capacity and energy lost due to generation or transmission equipment outages.2 In addition, the Commission proposes to approve eight new and revised definitions proposed 1 16 U.S.C. 824(o). Proposed Reliability Standard BAL–002–2 is available on the Commission’s eLibrary document retrieval system in Docket No. RM16–7–000 and on the NERC Web site, www.nerc.com. 2 ACE is the instantaneous difference between a balancing authority’s Net Actual and Scheduled Interchange, taking into account the effects of Frequency Bias, correction for meter error, and Automatic Time Error Correction, if operating in that mode. NERC Glossary of Terms Used in NERC Reliability Standards at 7 (updated April 20, 2016). PO 00000 Frm 00018 Fmt 4702 Sfmt 4702 33441 by NERC for inclusion in the NERC Glossary of Terms Used in NERC Reliability Standards (NERC Glossary) and to retire currently-effective Reliability Standard BAL–002–1 immediately prior to the effective date of proposed Reliability Standard BAL– 002–2. The Commission also proposes to approve, with certain modifications, the associated violation risk factors and violation severity levels, and implementation plan. 2. Pursuant to section 215(d)(5) of the FPA,3 the Commission proposes to direct NERC to modify Reliability Standard BAL–002–2 to address concerns related to the possible extension or delay of the periods for ACE recovery and contingency reserve restoration. The Commission also proposes to direct NERC to address a reliability gap regarding megawatt losses above the most severe single contingency. I. Background A. Mandatory Reliability Standards and Order No. 693 Directives 3. Section 215 of the FPA requires a Commission-certified Electric Reliability Organization (ERO) to develop mandatory and enforceable Reliability Standards that are subject to Commission review and approval. The Commission may approve, by rule or order, a proposed Reliability Standard or modification to a Reliability Standard if it determines that the Standard is just, reasonable, not unduly discriminatory or preferential and in the public interest.4 Once approved, the Reliability Standards may be enforced by NERC, subject to Commission oversight, or by the Commission independently.5 Pursuant to section 215 of the FPA, the Commission established a process to select and certify an ERO,6 and subsequently certified NERC.7 4. On March 16, 2007, the Commission issued Order No. 693, approving 83 of the 107 Reliability Standards filed by NERC, including Reliability Standard BAL–002–0.8 In 3 16 U.S.C. 824o(d)(5). 824o(d)(2). 5 Id. 824o(e). 6 Rules Concerning Certification of the Electric Reliability Organization; and Procedures for the Establishment, Approval, and Enforcement of Electric Reliability Standards, Order No. 672, FERC Stats. & Regs. ¶ 31,204, order on reh’g, Order No. 672–A, FERC Stats. & Regs. ¶ 31,212 (2006). 7 North American Electric Reliability Corp., 116 FERC ¶ 61,062, order on reh’g and compliance, 117 FERC ¶ 61,126 (2006), aff’d sub nom. Alcoa, Inc. v. FERC, 564 F.3d 1342 (D.C. Cir. 2009). 8 Mandatory Reliability Standards for the BulkPower System, Order No. 693, FERC Stats. & Regs. 4 Id. E:\FR\FM\26MYP1.SGM Continued 26MYP1

Agencies

[Federal Register Volume 81, Number 102 (Thursday, May 26, 2016)]
[Proposed Rules]
[Pages 33438-33441]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-12352]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-6893; Directorate Identifier 2015-NM-181-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 A318-112 airplanes, A319-111, -112, -115, -132, 
and -133 airplanes, A320-214, -232, and -233 airplanes, and A321-211, -
212, -213, -231, and -232 airplanes. This proposed AD was prompted by a 
quality control review on the final assembly line, which determined 
that the wrong aluminum alloy was used to manufacture several 
structural parts. This proposed AD would require a one-time eddy 
current conductivity measurements of certain cabin and cargo 
compartment structural parts to determine if an incorrect aluminum 
alloy was used, and replacement if necessary. We are proposing this AD 
to detect and replace structural parts made of incorrect aluminum 
alloy. This condition could result in reduced structural integrity of 
the airplane.

DATES: We must receive comments on this proposed AD by July 11, 2016.

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: Deliver to Mail address above 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: 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-2016-
6893; 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.

[[Page 33439]]


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-2016-6893; 
Directorate Identifier 2015-NM-181-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

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2015-0218, dated November 3, 2015 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A318-112, A319-111, -112, -115, -132, and -133, A320-214, -232, and -
233, and A321-211, -212, -213, -231, and -232 airplanes. The MCAI 
states:

    Following an Airbus quality control review on the final assembly 
line, it was discovered that wrong aluminum alloy were delivered by 
a supplier for several structural parts. The results of the 
investigations highlighted that 0.04% of the stock could be impacted 
by this wrong material.
    Structural investigations demonstrated the capability to sustain 
the static limits loads, and sufficient fatigue life up to a certain 
inspection threshold.
    This condition, if not detected and corrected, could reduce the 
structural integrity of the aeroplane.
    To address this potential unsafe condition, Airbus issued 
Service Bulletin (SB) A320-53-1298 and SB A320-53-1299 to provide 
inspection instructions.
    For the reasons described above, this [EASA] AD requires a one-
time Special Detailed Inspection (SDI) [eddy current conductivity 
measurements] of certain cabin and cargo compartment parts for 
material identification and, depending on findings, replacement with 
serviceable parts.

    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-2016-
6893.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletins A320-53-1298 and A320-53-1299, 
both dated February 16, 2015; both including Appendices 01, 02, and 03, 
dated February 16, 2015. The service information describes procedures 
for a one-time eddy current conductivity measurement of certain cabin 
and cargo compartment structural parts to determine if an incorrect 
aluminum alloy was used, and replacement of any affected part with a 
serviceable part. 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.

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 167 airplanes of U.S. 
registry.
    We also estimate that it would take about 1 work-hour 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 $14,195, or $85 
per product.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD.
    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 available 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.

[[Page 33440]]

Sec.  39.13  [Amended]

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

Airbus: Docket No. FAA-2016-6893; Directorate Identifier 2015-NM-
181-AD.

(a) Comments Due Date

    We must receive comments by July 11, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs 
(c)(1) through (c)(4) of this AD, certificated in any category; 
manufacturer serial numbers 3586, 3588, 3589, 3590, 3595, 3604, 
3608, 3614, 3615, 3620, 3632, 3634, 3638, 3647, 3651, 3657, 3660, 
3661, 3663, 3671, 3675, 3680, 3683 through 3687 inclusive, 3689, 
3691, 3694, 3700, 3702, 3704, 3705, 3710, 3720, 3727, 3728, 3733, 
3735, 3742, 3744, 3746, 3754, 3757, 3759, 3763, 3768, 3770, 3772, 
3774, 3775, 3779, 3788, 3790, 3794, 3797, 3799, 3801, 3803, 3808, 
3810, 3818, 3822, 3824, 3826 through 4329 inclusive, 4331 through 
6051 inclusive, 6053 through 6061 inclusive, 6063 through 6072 
inclusive, 6074 through 6100 inclusive, 6102 through 6115 inclusive, 
6117 through 6126 inclusive, 6128 through 6136 inclusive, 6138 
through 6143 inclusive, 6145 through 6150 inclusive, 6152 through 
6159 inclusive, 6161 and 6162.
    (1) Airbus Model A318-112 airplanes.
    (2) Airbus Model A319-111, -112, -115, -132, and -133 airplanes.
    (3) Airbus Model A320-214, -232, and -233 airplanes.
    (4) Airbus Model A321-211, -212, -213, -231, and -232 airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by a quality control review of the final 
assembly line which determined that the wrong aluminum alloy was 
used to manufacture several structural parts. We are issuing this AD 
to detect and correct structural parts made of incorrect aluminum 
alloy. This condition could result in reduced structural integrity 
of the airplane.

(f) Compliance

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

(g) One-Time Measurement

    Within 6 years after the effective date of this AD, but not 
exceeding 12 years since the date of issuance of the original 
certificate of airworthiness or the date of issuance of the original 
export certificate of airworthiness: Do a one-time eddy current 
conductivity measurements (with 60kHz and 480kHz) of the cabin and 
cargo compartment structural parts identified in the ``Affected P/
N'' column of table 1 to paragraphs (g) and (h) of this AD to 
determine if an incorrect aluminum alloy was used, in accordance 
with the Accomplishment Instructions of Airbus Service Bulletins 
A320-53-1298, dated February 16, 2015, including Appendices 01, 02, 
and 03, dated February 16, 2015 (for cabin parts); and A320-53-1299, 
dated February 16, 2015, including Appendices 01, 02, and 03, dated 
February 16, 2015 (for cargo parts).

  Table 1 to Paragraphs (g) and (h) of This AD--Parts To Be Inspected/
                                Installed
------------------------------------------------------------------------
                                      Acceptable
          Affected P/N              replacement P/N          Area
------------------------------------------------------------------------
D5347120720000..................  D5347120720051....  Cabin.
D5347120720100..................  D5347120720151....  Cabin.
D5347120920000..................  D5347120920051....  Cabin.
D5347120920100..................  D5347120920151....  Cabin.
D5347118820400..................  D5347118820451....  Cabin.
D5347717620000..................  D5347717620051....  Cargo.
D5357020620000..................  D5357020620051....  Cargo.
D5358526421200..................  D5358526421251....  Cargo.
D5358526421400..................  D5358526421400....  Cargo.
D5358526421000..................  D5358526421051....  Cargo.
D5358513120001..................  D5358513120051....  Cargo.
------------------------------------------------------------------------

(h) Replacement

    If during the inspection required by paragraph (g) of this AD, 
any affected part having a part number (P/N) specified in table 1 to 
paragraphs (g) and (h) of this AD is found to have a measured value 
greater than that specified in Figure A-GFAAA, Sheet 02, 
``Inspection Flowchart,'' of the applicable service information 
identified in paragraph (g) of this AD: Before further flight, 
replace with an acceptable replacement part having a P/N specified 
in table 1 to paragraphs (g) and (h) of this AD, in accordance with 
the Accomplishment Instructions of Airbus Service Bulletins A320-53-
1298, dated February 16, 2015, including Appendices 01, 02, and 03, 
dated February 16, 2015 (for cabin parts); and A320-53-1299, dated 
February 16, 2015, including Appendices 01, 02, and 03, dated 
February 16, 2015 (for cargo parts).

(i) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it to ATTN: 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 
European Aviation Safety Agency (EASA); or Airbus's EASA DOA. If 
approved by the DOA, the approval must include the DOA-authorized 
signature.
    (3) Required for Compliance (RC): If any service information 
contains procedures or tests that are identified as RC, those 
procedures and tests must be done to comply with this AD; any 
procedures or tests that are not identified as RC are recommended. 
Those procedures and tests that are not identified as RC may be 
deviated from using accepted methods in accordance with the 
operator's maintenance or inspection program without obtaining 
approval of an AMOC, provided the procedures and tests identified as 
RC can be done and the airplane can be put back in an airworthy 
condition. Any substitutions or changes to procedures or tests 
identified as RC require approval of an AMOC.

(j) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2015-0218, dated November 3, 2015, 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-2016-6893.

[[Page 33441]]

    (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 May 17, 2016.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-12352 Filed 5-25-16; 8:45 am]
 BILLING CODE 4910-13-P