Airworthiness Directives; Airbus Airplanes, 26874-26877 [2017-12056]

Download as PDF 26874 Federal Register / Vol. 82, No. 111 / Monday, June 12, 2017 / Proposed Rules of the PBM can be conclusively determined from that review. (1) If the PBM is Rockwell Collins part number (P/N) 4260–0037–5: No further action is required by this paragraph. (2) If the PBM is Rockwell Collins P/N 4260–0037–3 or –4: Within 60 months after the effective date of this AD, install PBM P/ N 4260–0037–5, do the PBM installation test, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Service Bulletin B787– 81205–SB320028–00, Issue 001, dated October 31, 2016. Do all applicable corrective actions before further flight. asabaliauskas on DSKBBXCHB2PROD with PROPOSALS (h) Parts Installation Prohibition As of the effective date of this AD, no person may install on any airplane, a PBM having Rockwell Collins P/N 4260–0037–3 or –4. (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in paragraph (j)(1) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. (2) 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. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (i)(4)(i) and (i)(4)(ii) of this AD apply. (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. If a step or substep is labeled ‘‘RC Exempt,’’ then the RC requirement is removed from that step or substep. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled 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 RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. VerDate Sep<11>2014 16:49 Jun 09, 2017 Jkt 241001 (j) Related Information (1) For more information about this AD, contact Sean Schauer, Aerospace Engineer, Systems and Equipment Branch, ANM–130S, FAA, Seattle ACO, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917– 6479; fax: 425–917–6590; email: Sean.Schauer@faa.gov. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110–SK57, Seal Beach, CA 90740–5600; telephone: 562–797–1717; Internet: https:// www.myboeingfleet.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. Issued in Renton, Washington, on June 2, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–12058 Filed 6–9–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0533; Directorate Identifier 2016–NM–156–AD] Examining the AD Docket 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 all Airbus Model A300 B4–603 and A300 B4–622 airplanes; Model A300 B4–600R series airplanes; Model A300 C4–605R Variant F airplanes; Model A300 F4– 600R series airplanes; and Model A310– 203, A310–221, A310–222, A310–304, A310–322, A310–324, and A310–325 airplanes. This proposed AD was prompted by an evaluation by the design approval holder (DAH) that indicates that a section of the fuselage structure above the forward cargo door is subject to widespread fatigue damage (WFD). This proposed AD would require an inspection for cracks of the fastener and tooling holes at certain locations and a check of the diameter of the holes, and repair or modification of the affected fuselage structure if necessary. We are proposing this AD to address the unsafe condition on these products. SUMMARY: PO 00000 Frm 00016 Fmt 4702 We must receive comments on this proposed AD by July 27, 2017. 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 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 NRPM, contact Airbus SAS, Airworthiness Office–EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 44 51; email: continued.airworthiness-wb.external@ 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. DATES: Sfmt 4702 You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0533; 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: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–2125; 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–2017–0533; Directorate Identifier E:\FR\FM\12JNP1.SGM 12JNP1 Federal Register / Vol. 82, No. 111 / Monday, June 12, 2017 / Proposed Rules asabaliauskas on DSKBBXCHB2PROD with PROPOSALS 2016–NM–156–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 Structural fatigue damage is progressive. It begins as minute cracks, and those cracks grow under the action of repeated stresses. This can happen because of normal operational conditions and design attributes, or because of isolated situations or incidents such as material defects, poor fabrication quality, or corrosion pits, dings, or scratches. Fatigue damage can occur locally, in small areas or structural design details, or globally. Global fatigue damage is general degradation of large areas of structure with similar structural details and stress levels. Multiple-site damage is global damage that occurs in a large structural element such as a single rivet line of a lap splice joining two large skin panels. Global damage can also occur in multiple elements such as adjacent frames or stringers. Multiple-sitedamage and multiple-element-damage cracks are typically too small initially to be reliably detected with normal inspection methods. Without intervention, these cracks will grow, and eventually compromise the structural integrity of the airplane, in a condition known as WFD. As an airplane ages, WFD will likely occur, and will certainly occur if the airplane is operated long enough without any intervention. The FAA’s WFD final rule (75 FR 69746, November 15, 2010) became effective on January 14, 2011. The WFD rule requires certain actions to prevent structural failure due to WFD throughout the operational life of certain existing transport category airplanes and all transport category airplanes that will be certificated in the future. For existing and future airplanes subject to the WFD rule, the rule requires that DAHs establish a limit of validity (LOV) of the engineering data that support the structural maintenance program. Operators affected by the WFD VerDate Sep<11>2014 16:49 Jun 09, 2017 Jkt 241001 rule may not fly an airplane beyond its LOV, unless an extended LOV is approved. The WFD rule (75 FR 69746, November 15, 2010) does not require identifying and developing maintenance actions if the DAHs can show that such actions are not necessary to prevent WFD before the airplane reaches the LOV. Many LOVs, however, do depend on accomplishment of future maintenance actions. As stated in the WFD rule, any maintenance actions necessary to reach the LOV will be mandated by airworthiness directives through separate rulemaking actions. In the context of WFD, this action is necessary to enable DAHs to propose LOVs that allow operators the longest operational lives for their airplanes, and still ensure that WFD will not occur. This approach allows for an implementation strategy that provides flexibility to DAHs in determining the timing of service information development (with FAA approval), while providing operators with certainty regarding the LOV applicable to their airplanes. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive AD 2016–0178, dated September 12, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Model A300 series airplanes. The MCAI states: In the frame of the Widespread Fatigue Damage (WFD) analysis, some structural areas were identified as requiring embodiment of a structural modification. This condition, if not corrected, could reduce the fuselage structural integrity. To address this unsafe condition, Airbus issued Service Bulletin (SB) A310–53–2145 and SB A300–53–6187 to provide instructions for structural reinforcement of the fuselage frames (FR) between FR20 Right Hand side (RH) and FR25 RH and the frame couplings between stringer (STGR) 20 RH and STGR23 RH, hereafter collectively referred to as ‘the affected fuselage structure’ in this [EASA] AD. For the reason described above, this [EASA] AD requires accomplishment of a one-time special detailed inspection (SDI) of the fastener and tooling holes, and modification of the affected fuselage structure. The required actions include a rototest inspection for cracks of the fastener and tooling holes at certain locations and a check of the diameter of the holes, and repair or modification of PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 26875 the affected fuselage structure if necessary. 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–2017– 0533. Related Service Information Under 1 CFR Part 51 Airbus issued the following service information: • Airbus Service Bulletin A300–53– 6187, Revision 00, dated May 31, 2016. This service information describes procedures for a rototest inspection for cracks of the fastener and tooling holes at certain locations, a check of the diameter of the holes, repair, and modification of the affected fuselage structure by reinforcing the frames between right hand FR 20 RH and FR 25 RH, or FR 21 RH and FR 25 RH, depending on the configuration; and reinforcing the frame couplings between stringer STGR 20 RH and STGR 23 RH. • Airbus Service Bulletin A310–53– 2145, Revision 00, dated May 31, 2016. This service information describes procedures for a rototest inspection for cracks of the fastener and tooling holes at certain locations, a check of the diameter of the holes, repair, and modification of the affected fuselage structure by reinforcing the frames between right hand FR20 RH and FR25 RH; and reinforcing the frame couplings between STGR 20 RH and STGR 23 RH. 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 the same type design. Costs of Compliance We estimate that this proposed AD affects 132 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: E:\FR\FM\12JNP1.SGM 12JNP1 26876 Federal Register / Vol. 82, No. 111 / Monday, June 12, 2017 / Proposed Rules ESTIMATED COSTS Action Labor cost Inspection, check, repair, and modification .... 45 work-hours × $85 per hour = $3,825 ........ 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. asabaliauskas on DSKBBXCHB2PROD with PROPOSALS 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: VerDate Sep<11>2014 16:49 Jun 09, 2017 Jkt 241001 Parts cost $2,360 Cost per product $6,185 Cost on U.S. operators $816,420 PART 39—AIRWORTHINESS DIRECTIVES Airbus Service Bulletin A310–53–2145, Revision 00, dated May 31, 2016; as applicable. 1. The authority citation for part 39 continues to read as follows: (h) Repair of Detected Cracks If any condition specified in paragraph (h)(1) or (h)(2) of this AD is found, prior to further flight, repair in accordance with 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). Concurrently with the repair, unless the approved repair instructions specify otherwise, modify the affected structure, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300– 53–6187, Revision 00, dated May 31, 2016; or Airbus Service Bulletin A310–53–2145, Revision 00, dated May 31, 2016; as applicable. (1) Any crack is found during the rototest inspection required by paragraph (g) of this AD. (2) Any hole diameter is greater than or equal to the maximum starting hole diameter specified in the Accomplishment Instructions of Airbus Service Bulletin A300– 53–6187, Revision 00, dated May 31, 2016; or Airbus Service Bulletin A310–53–2145, Revision 00, dated May 31, 2016; as applicable, is found during the check required by paragraph (g) of this AD. ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new Airworthiness Directive (AD): ■ Airbus: Docket No. FAA–2017–0533; Directorate Identifier 2016–NM–156–AD. (a) Comments Due Date We must receive comments by July 27, 2017. (b) Affected ADs None. (c) Applicability This AD applies to Airbus airplanes identified in paragraphs (c)(1) through (c)(5) of this AD, certificated in any category, all manufacturer serial numbers. (1) Model A300 B4–603 and A300 B4–622 airplanes. (2) Model A300 B4–605R and A300 B4– 622R airplanes. (3) Model A300 F4–605R and A300 F4– 622R airplanes. (4) Model A300 C4–605R Variant F airplanes. (5) Model A310–203, –221, –222, –304, –322, –324, and –325 airplanes. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by an evaluation by the design approval holder that indicates that a section of the fuselage structure above the forward cargo door is subject to widespread fatigue damage. We are issuing this AD to prevent reduced structural integrity of these airplanes due to the failure of certain structural components. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Check and Rototest Inspection of Affected Fastener and Tooling Holes Before exceeding 42,500 flight cycles since the first flight of the airplane, do a check of the diameter of the fastener holes and tooling holes and a rototest inspection for cracks of all holes of removed fasteners and the tooling holes at the locations specified in, and in accordance with, the Accomplishment Instructions of Airbus Service Bulletin A300– 53–6187, Revision 00, dated May 31, 2016; or PO 00000 Frm 00018 Fmt 4702 Sfmt 4702 (i) Modification If, during the actions required by paragraph (g) of this AD, no crack is found and the hole diameter is less than the maximum starting hole diameter specified in the Accomplishment Instructions of Airbus Service Bulletin A300–53–6187, Revision 00, dated May 31, 2016; or Airbus Service Bulletin A310–53–2145, Revision 00, dated May 31, 2016; as applicable, before further flight, modify the affected fuselage structure, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300– 53–6187, Revision 00, dated May 31, 2016; or Airbus Service Bulletin A310–53–2145, Revision 00, dated May 31, 2016; as applicable. (j) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the International Branch, send it to the attention of the person E:\FR\FM\12JNP1.SGM 12JNP1 Federal Register / Vol. 82, No. 111 / Monday, June 12, 2017 / Proposed Rules identified in paragraph (k)(2) of this AD. 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. (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 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. asabaliauskas on DSKBBXCHB2PROD with PROPOSALS (k) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2016–0178, dated September 12, 2016, for related information. You may examine the MCAI on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2017–0533. (2) For more information about this AD, contact Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; fax 425–227–2125. Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 44 51; email: continued.airworthinesswb.external@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 June 2, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–12056 Filed 6–9–17; 8:45 am] BILLING CODE 4910–13–P VerDate Sep<11>2014 16:49 Jun 09, 2017 Jkt 241001 DEPARTMENT OF LABOR Office of Labor-Management Standards 29 CFR Parts 405 and 406 RIN 1245–AA07 Rescission of Rule Interpreting ‘‘Advice’’ Exemption in Section 203(c) of the Labor-Management Reporting and Disclosure Act Office of Labor-Management Standards, Department of Labor. ACTION: Notice of proposed rulemaking; request for comments. AGENCY: This Notice of Proposed Rulemaking proposes to rescind the regulations established in the final rule titled ‘‘Interpretation of the ‘Advice’ Exemption in Section 203(c) of the Labor-Management Reporting and Disclosure Act,’’ effective April 15, 2016. DATES: Comments must be received on or before August 11, 2017. ADDRESSES: You may submit comments, identified by RIN 1245–AA07, only by the following method: Internet—Federal eRulemaking Portal. Electronic comments may be submitted through https:// www.regulations.gov. To locate the proposed rule, use key words such as ‘‘Labor-Management Standards’’ or ‘‘Advice Exemption’’ to search documents accepting comments. Follow the instructions for submitting comments. Please be advised that comments received will be posted without change to https:// www.regulations.gov, including any personal information provided. The Paperwork Reduction Act section of this preamble provides information about additional comment opportunities for the associated information collection requirements. FOR FURTHER INFORMATION CONTACT: Andrew Davis, Chief of the Division of Interpretations and Standards, Office of Labor-Management Standards, U.S. Department of Labor, 200 Constitution Avenue NW., Room N–5609, Washington, DC 20210, (202) 693–0123 (this is not a toll-free number), (800) 877–8339 (TTY/TDD). SUPPLEMENTARY INFORMATION: SUMMARY: I. Statutory Authority The Department’s statutory authority is set forth in sections 203 and 208 of the LMRDA, 29 U.S.C. 432, 438. Section 208 of the LMRDA provides that the Secretary of Labor shall have authority to issue, amend, and rescind rules and PO 00000 Frm 00019 Fmt 4702 Sfmt 4702 26877 regulations prescribing the form and publication of reports required to be filed under Title II of the Act and such other reasonable rules and regulations as he may find necessary to prevent the circumvention or evasion of the reporting requirements. 29 U.S.C. 438. Section 203, discussed in more detail below, sets out the substantive reporting obligations. The Secretary has delegated his authority under the LMRDA to the Director of the Office of LaborManagement Standards and permitted redelegation of such authority. See Secretary’s Order 03–2012 (Oct. 19, 2012), published at 77 FR 69375 (Nov. 16, 2012). II. Background A. Introduction The proposal to rescind the March 24, 2016 Rule is part of the Department’s continuing effort to fairly effectuate the reporting requirements of the LMRDA. The LMRDA generally reflects obligations of unions and employers to conduct labor-management relations in a manner that protects the rights of employees to exercise their right to choose whether to be represented by a union for purposes of collective bargaining. The LMRDA’s reporting provisions promote these rights by requiring unions, employers, and labor relations consultants to publicly disclose information about certain financial transactions, agreements, and arrangements. The Department believes that a fair and transparent government regulatory regime must consider and balance the interests of labor relations consultants, employers, labor organizations, their members, and the public. Any change to a labor relations consultant’s recordkeeping, reporting and business practices must be based on a demonstrated and significant need for information, consideration of the burden associated with such reporting, and any increased costs associated with the change. B. The LMRDA’s Reporting Requirements In enacting the LMRDA in 1959, a bipartisan Congress sought to protect the rights and interests of employees, labor organizations and the public generally as they relate to the activities of labor organizations, employers, labor relations consultants, and their officers, employees, and representatives. Section 203(a) of the LMRDA, 29 U.S.C. 433(a), requires employers to report to the Department of Labor ‘‘any agreement or arrangement with a labor relations consultant or other E:\FR\FM\12JNP1.SGM 12JNP1

Agencies

[Federal Register Volume 82, Number 111 (Monday, June 12, 2017)]
[Proposed Rules]
[Pages 26874-26877]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-12056]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0533; Directorate Identifier 2016-NM-156-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 all 
Airbus Model A300 B4-603 and A300 B4-622 airplanes; Model A300 B4-600R 
series airplanes; Model A300 C4-605R Variant F airplanes; Model A300 
F4-600R series airplanes; and Model A310-203, A310-221, A310-222, A310-
304, A310-322, A310-324, and A310-325 airplanes. This proposed AD was 
prompted by an evaluation by the design approval holder (DAH) that 
indicates that a section of the fuselage structure above the forward 
cargo door is subject to widespread fatigue damage (WFD). This proposed 
AD would require an inspection for cracks of the fastener and tooling 
holes at certain locations and a check of the diameter of the holes, 
and repair or modification of the affected fuselage structure if 
necessary. We are proposing this AD to address the unsafe condition on 
these products.

DATES: We must receive comments on this proposed AD by July 27, 2017.

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 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 NRPM, contact Airbus 
SAS, Airworthiness Office-EAW, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 
44 51; email: continued.airworthiness-wb.external@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.

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-2017-
0533; 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: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; 
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-2017-0533; 
Directorate Identifier

[[Page 26875]]

2016-NM-156-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

    Structural fatigue damage is progressive. It begins as minute 
cracks, and those cracks grow under the action of repeated stresses. 
This can happen because of normal operational conditions and design 
attributes, or because of isolated situations or incidents such as 
material defects, poor fabrication quality, or corrosion pits, dings, 
or scratches. Fatigue damage can occur locally, in small areas or 
structural design details, or globally. Global fatigue damage is 
general degradation of large areas of structure with similar structural 
details and stress levels. Multiple-site damage is global damage that 
occurs in a large structural element such as a single rivet line of a 
lap splice joining two large skin panels. Global damage can also occur 
in multiple elements such as adjacent frames or stringers. Multiple-
site-damage and multiple-element-damage cracks are typically too small 
initially to be reliably detected with normal inspection methods. 
Without intervention, these cracks will grow, and eventually compromise 
the structural integrity of the airplane, in a condition known as WFD. 
As an airplane ages, WFD will likely occur, and will certainly occur if 
the airplane is operated long enough without any intervention.
    The FAA's WFD final rule (75 FR 69746, November 15, 2010) became 
effective on January 14, 2011. The WFD rule requires certain actions to 
prevent structural failure due to WFD throughout the operational life 
of certain existing transport category airplanes and all transport 
category airplanes that will be certificated in the future. For 
existing and future airplanes subject to the WFD rule, the rule 
requires that DAHs establish a limit of validity (LOV) of the 
engineering data that support the structural maintenance program. 
Operators affected by the WFD rule may not fly an airplane beyond its 
LOV, unless an extended LOV is approved.
    The WFD rule (75 FR 69746, November 15, 2010) does not require 
identifying and developing maintenance actions if the DAHs can show 
that such actions are not necessary to prevent WFD before the airplane 
reaches the LOV. Many LOVs, however, do depend on accomplishment of 
future maintenance actions. As stated in the WFD rule, any maintenance 
actions necessary to reach the LOV will be mandated by airworthiness 
directives through separate rulemaking actions.
    In the context of WFD, this action is necessary to enable DAHs to 
propose LOVs that allow operators the longest operational lives for 
their airplanes, and still ensure that WFD will not occur. This 
approach allows for an implementation strategy that provides 
flexibility to DAHs in determining the timing of service information 
development (with FAA approval), while providing operators with 
certainty regarding the LOV applicable to their airplanes.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive AD 2016-0178, dated September 12, 2016 
(referred to after this as the Mandatory Continuing Airworthiness 
Information, or ``the MCAI''), to correct an unsafe condition for all 
Airbus Model A300 series airplanes. The MCAI states:

    In the frame of the Widespread Fatigue Damage (WFD) analysis, 
some structural areas were identified as requiring embodiment of a 
structural modification.
    This condition, if not corrected, could reduce the fuselage 
structural integrity.
    To address this unsafe condition, Airbus issued Service Bulletin 
(SB) A310-53-2145 and SB A300-53-6187 to provide instructions for 
structural reinforcement of the fuselage frames (FR) between FR20 
Right Hand side (RH) and FR25 RH and the frame couplings between 
stringer (STGR) 20 RH and STGR23 RH, hereafter collectively referred 
to as `the affected fuselage structure' in this [EASA] AD.
    For the reason described above, this [EASA] AD requires 
accomplishment of a one-time special detailed inspection (SDI) of 
the fastener and tooling holes, and modification of the affected 
fuselage structure.

    The required actions include a rototest inspection for cracks of 
the fastener and tooling holes at certain locations and a check of the 
diameter of the holes, and repair or modification of the affected 
fuselage structure if necessary. 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-2017-0533.

Related Service Information Under 1 CFR Part 51

    Airbus issued the following service information:
     Airbus Service Bulletin A300-53-6187, Revision 00, dated 
May 31, 2016. This service information describes procedures for a 
rototest inspection for cracks of the fastener and tooling holes at 
certain locations, a check of the diameter of the holes, repair, and 
modification of the affected fuselage structure by reinforcing the 
frames between right hand FR 20 RH and FR 25 RH, or FR 21 RH and FR 25 
RH, depending on the configuration; and reinforcing the frame couplings 
between stringer STGR 20 RH and STGR 23 RH.
     Airbus Service Bulletin A310-53-2145, Revision 00, dated 
May 31, 2016. This service information describes procedures for a 
rototest inspection for cracks of the fastener and tooling holes at 
certain locations, a check of the diameter of the holes, repair, and 
modification of the affected fuselage structure by reinforcing the 
frames between right hand FR20 RH and FR25 RH; and reinforcing the 
frame couplings between STGR 20 RH and STGR 23 RH.
    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 the same 
type design.

Costs of Compliance

    We estimate that this proposed AD affects 132 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

[[Page 26876]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
               Action                         Labor cost            Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Inspection, check, repair, and       45 work-hours x $85 per              $2,360          $6,185        $816,420
 modification.                        hour = $3,825.
----------------------------------------------------------------------------------------------------------------

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13   [Amended]

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

Airbus: Docket No. FAA-2017-0533; Directorate Identifier 2016-NM-
156-AD.

(a) Comments Due Date

    We must receive comments by July 27, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus airplanes identified in paragraphs 
(c)(1) through (c)(5) of this AD, certificated in any category, all 
manufacturer serial numbers.
    (1) Model A300 B4-603 and A300 B4-622 airplanes.
    (2) Model A300 B4-605R and A300 B4-622R airplanes.
    (3) Model A300 F4-605R and A300 F4-622R airplanes.
    (4) Model A300 C4-605R Variant F airplanes.
    (5) Model A310-203, -221, -222, -304, -322, -324, and -325 
airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by an evaluation by the design approval 
holder that indicates that a section of the fuselage structure above 
the forward cargo door is subject to widespread fatigue damage. We 
are issuing this AD to prevent reduced structural integrity of these 
airplanes due to the failure of certain structural components.

(f) Compliance

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

(g) Check and Rototest Inspection of Affected Fastener and Tooling 
Holes

    Before exceeding 42,500 flight cycles since the first flight of 
the airplane, do a check of the diameter of the fastener holes and 
tooling holes and a rototest inspection for cracks of all holes of 
removed fasteners and the tooling holes at the locations specified 
in, and in accordance with, the Accomplishment Instructions of 
Airbus Service Bulletin A300-53-6187, Revision 00, dated May 31, 
2016; or Airbus Service Bulletin A310-53-2145, Revision 00, dated 
May 31, 2016; as applicable.

(h) Repair of Detected Cracks

    If any condition specified in paragraph (h)(1) or (h)(2) of this 
AD is found, prior to further flight, repair in accordance with 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). 
Concurrently with the repair, unless the approved repair 
instructions specify otherwise, modify the affected structure, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-53-6187, Revision 00, dated May 31, 2016; or Airbus 
Service Bulletin A310-53-2145, Revision 00, dated May 31, 2016; as 
applicable.
    (1) Any crack is found during the rototest inspection required 
by paragraph (g) of this AD.
    (2) Any hole diameter is greater than or equal to the maximum 
starting hole diameter specified in the Accomplishment Instructions 
of Airbus Service Bulletin A300-53-6187, Revision 00, dated May 31, 
2016; or Airbus Service Bulletin A310-53-2145, Revision 00, dated 
May 31, 2016; as applicable, is found during the check required by 
paragraph (g) of this AD.

(i) Modification

    If, during the actions required by paragraph (g) of this AD, no 
crack is found and the hole diameter is less than the maximum 
starting hole diameter specified in the Accomplishment Instructions 
of Airbus Service Bulletin A300-53-6187, Revision 00, dated May 31, 
2016; or Airbus Service Bulletin A310-53-2145, Revision 00, dated 
May 31, 2016; as applicable, before further flight, modify the 
affected fuselage structure, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A300-53-6187, Revision 00, 
dated May 31, 2016; or Airbus Service Bulletin A310-53-2145, 
Revision 00, dated May 31, 2016; as applicable.

(j) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the manager of the International Branch, send it to the 
attention of the person

[[Page 26877]]

identified in paragraph (k)(2) of this AD. 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.
    (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 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.

(k) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2016-0178, dated September 12, 2016, for related 
information. You may examine the MCAI on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-
2017-0533.
    (2) For more information about this AD, contact Dan Rodina, 
Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-1405; fax 425-227-2125. Information may be 
emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov.
    (3) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; 
fax: +33 5 61 93 44 51; email: continued.airworthiness-wb.external@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 June 2, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-12056 Filed 6-9-17; 8:45 am]
 BILLING CODE 4910-13-P
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