Airworthiness Directives; Airbus Helicopters (Type Certificate Previously Held by Eurocopter France) Helicopters, 58638-58641 [2019-23832]

Download as PDF 58638 Federal Register / Vol. 84, No. 212 / Friday, November 1, 2019 / Proposed Rules (d) Subject Air Transport Association (ATA) of America Code 54, Nacelles/Pylons. (e) Unsafe Condition This AD was prompted by a report of failure of a wing strut leak test due to a missing bolt on the firewall. The FAA is issuing this AD to address a hole in the firewall, which could allow flammable fluid leakage in the strut area. This leakage could overwhelm the drainage provision, enter the engine compartment, and result in an uncontrollable engine fire and consequent structural failure of the wing. khammond on DSKJM1Z7X2PROD with PROPOSALS (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Leak Test and Corrective Action Within 12 months after the effective date of this AD: Do a one-time leak (functional) test of the strut upper spar areas for the left and right wing struts, by doing the actions specified in paragraphs (g)(1) through (5) of this AD. A review of airplane maintenance records is acceptable in lieu of this test if it can be conclusively determined from that review that the leak test was previously accomplished and successfully completed. (1) Put a plug in the strut forward drain outlet (this drain outlet is labeled as ‘‘pylon strut’’). Put an empty container below the strut forward drain outlet to collect water drained through this outlet. (2) Apply 381 to 387 fluid ounces (11.3 to 11.4 liters) of water in 2.5 to 3.5 minutes, to the strut upper spar (strut areas between the forward and mid-vapor barriers). (3) Make sure that no leakage occurred after doing the action specified in paragraph (g)(2) of this AD. (4) Remove the plug from the strut forward drain outlet and make sure that the water is drained through the strut forward drain outlet only. (5) After 3 minutes from accomplishing the action specified in paragraph (g)(4) of this AD, measure the water collected in the container, and do the applicable actions specified in paragraphs (g)(5)(i) through (iii) of this AD. (i) If leaks were found, do corrective action before further flight using a method approved in accordance with the procedures specified in paragraph (h) of this AD. (ii) If no leaks were found and less than 354 fluid ounces (10.5 liters) of water is collected in the container, do corrective action before further flight using a method approved in accordance with the procedures specified in paragraph (h) of this AD. (ii) Before further flight after accomplishing any corrective action required by paragraph (g)(5)(i) or (ii) of this AD, repeat the actions specified in paragraphs (g)(1) through (5) of this AD until successful completion of the test (i.e., no leaks are found and 354 fluid ounces (10.5 liters) of water or more is measured in the container). Note 1 to paragraph (g): Additional guidance for performing the leak (functional) test can be found in Boeing Model 787 Aircraft Maintenance Manual (AMM), 54– 65–01, Strut Spar—Upper—Functional Test. VerDate Sep<11>2014 19:05 Oct 31, 2019 Jkt 250001 (h) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle ACO Branch, 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 certification office, send it to the attention of the person identified in paragraph (i)(1) of this AD. Information may be emailed to: 9ANM-Seattle-ACO-AMOC-Requests@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 Company Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO Branch, FAA, 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. (i) Related Information (1) For more information about this AD, contact Tak Kobayashi, Aerospace Engineer, Propulsion Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des Moines, WA 98198; phone and fax: 206–231–3553; email: takahisa.kobayashi@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. For information on the availability of this material at the FAA, call 206–231–3195. Issued in Des Moines, Washington, on October 24, 2019. Dionne Palermo, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2019–23788 Filed 10–31–19; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2019–0827; Product Identifier 2019–SW–014–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Helicopters (Type Certificate Previously Held by Eurocopter France) Helicopters Federal Aviation Administration (FAA), DOT. AGENCY: PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 Notice of proposed rulemaking (NPRM). ACTION: The FAA proposes to supersede Airworthiness Directive (AD) 2011–12–07 for Eurocopter France (now Airbus Helicopters) Model SA–365C, SA–365C1, SA–365C2, SA–365N, SA– 365N1, AS–365N2, AS 365 N3, and SA– 366G1 helicopters. AD 2011–12–07 currently requires repetitively inspecting the adhesive bead between the bushings and the Starflex star (Starflex) arms and the Starflex arm ends. Since the FAA issued AD 2011– 12–07, Airbus Helicopters has developed an improved Starflex. This proposed AD would retain the requirements of AD 2011–12–07 and revise the Applicability paragraph by omitting helicopters with the improved Starflex installed. The FAA is proposing this AD to address the unsafe condition on these products. DATES: The FAA must receive comments on this proposed AD by December 31, 2019. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your comments electronically. • Fax: 202–493–2251. • Mail: Send comments to the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590–0001. • Hand Delivery: Deliver to the ‘‘Mail’’ address between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. SUMMARY: 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–2019– 0827; or in person at Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the European Aviation Safety Agency (EASA) AD, the economic evaluation, any comments received and other information. The street address for Docket Operations is listed above. Comments will be available in the AD docket shortly after receipt. For service information identified in this proposed rule, contact Airbus Helicopters, 2701 N Forum Drive, Grand Prairie, TX 75052; telephone (972) 641– 0000 or (800) 232–0323; fax (972) 641– 3775; or at http:// www.helicopters.airbus.com/website/ en/ref/Technical-Support_73.html. You E:\FR\FM\01NOP1.SGM 01NOP1 Federal Register / Vol. 84, No. 212 / Friday, November 1, 2019 / Proposed Rules may view this service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N–321, Fort Worth, TX 76177. Matt Fuller, Senior Aviation Safety Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222–5110; email matthew.fuller@faa.gov. SUPPLEMENTARY INFORMATION: FOR FURTHER INFORMATION CONTACT: Comments Invited The FAA invites you to participate in this rulemaking by submitting written comments, data, or views. The FAA also invites comments relating to the economic, environmental, energy, or federalism impacts that might result from adopting the proposals in this document. The most helpful comments reference a specific portion of the proposal, explain the reason for any recommended change, and include supporting data. To ensure the docket does not contain duplicate comments, commenters should send only one copy of written comments, or if comments are filed electronically, commenters should submit only one time. The FAA will file in the docket all comments that the FAA receives, as well as a report summarizing each substantive public contact with FAA personnel concerning this proposed rulemaking. Before acting on this proposal, the FAA will consider all comments received on or before the closing date for comments. The FAA will consider comments filed after the comment period has closed if it is possible to do so without incurring expense or delay. The FAA may change this proposal in light of the comments received. khammond on DSKJM1Z7X2PROD with PROPOSALS Discussion The FAA issued AD 2011–12–07, Amendment 39–16714 (76 FR 35346, June 17, 2011) (‘‘AD 2011–12–07’’) for Eurocopter France (now Airbus Helicopters) Model SA–365C, SA– 365C1, SA–365C2, SA–365N, SA– 365N1, AS–365N2, AS 365 N3, and SA– 366G1 helicopters. AD 2011–12–07 requires repetitively inspecting the adhesive bead between the bushings and the Starflex arms for a crack, a gap, and loss of the adhesive bead, inspecting the Starflex arm ends for delamination, and replacing the Starflex if any of these conditions are found. AD 2011–12–07 was prompted by three cases of deterioration of a Starflex arm end. In two of these cases, the deterioration caused high amplitude VerDate Sep<11>2014 19:05 Oct 31, 2019 Jkt 250001 vibrations in flight, compelling the pilot to make a precautionary landing. The requirements of AD 2011–12–07 are intended to prevent failure of the Starflex, high-amplitude vibrations in flight, and subsequent loss of control of the helicopter. Actions Since AD 2011–12–07 Was Issued Since the FAA issued AD 2011–12– 07, Airbus Helicopters has developed new part-numbered Starflex, 365A31– 1212–00 and 365A31–1213–00, with different material. This change in material improves the reliability and technical performance of the Starflex, improves temperature-related behavior in the area of the Starflex arm ends, and increases dimension margins. Subsequently, Airbus Helicopters has extended the inspection interval of Starflex arm ends with these Starflex installed. Airbus Helicopters identifies helicopters with Starflex part number 365A31–1212–00 or 365A31–1213–00 installed as Modification (MOD) 0762C37. Accordingly, EASA, which is the Technical Agent for the Member States of the European Union, issued AD No. 2008–0165R1, dated June 30, 2017 (EASA AD 2008–0165R1), to address this unsafe condition for Airbus Helicopters Model SA 365 N, SA 365 N1, AS 365 N2, AS 365 N3, SA 365 C, SA 365 C1, SA 365 C2, SA 365 C3 and SA 366 G1 helicopters, except helicopters with MOD 0762C37 installed in production. EASA advises that the Airbus Helicopters Starflex manufactured with improved materials make the 10-hour repetitive inspections specified in the original issue of EASA AD 2008–0165R1 unnecessary. EASA AD 2008–0165R1 retains the repetitive inspections from the original issue but does not apply to helicopters with the new Starflex. Also since the FAA issued AD 2011– 12–07, Eurocopter France changed its name to Airbus Helicopters. This proposed AD reflects that change and updates the contact information to obtain service documentation. FAA’s Determination These helicopters have been approved by EASA and are approved for operation in the United States. Pursuant to the FAA’s bilateral agreement with the European Union, EASA has notified the FAA of the unsafe condition described in its AD. The FAA is proposing this AD after evaluating all known relevant information and determined that an unsafe condition is likely to exist or develop on other helicopters of the same type designs. PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 58639 Related Service Information Under 1 CFR Part 51 The FAA reviewed one document that co-publishes four Airbus Helicopters Emergency Alert Service Bulletin (EASB) identification numbers: No. 05.00.51 for Model 365N-series helicopters, No. 05.35 for Model 366G1 helicopters, No. 05.28 for Model 365Cseries helicopters, and No. 05.00.21 for non FAA-type certificated military helicopters, all Revision 4 and dated November 20, 2014. EASB Nos. 05.00.51, 05.35, and 05.28 are proposed for incorporation by reference in this proposed AD. EASB No. 05.00.21 is not proposed for incorporation by reference in this proposed AD. This service information specifies visually inspecting the adhesive bead on the bushes of the Starflex arm ends for bonding failure of the bushes and distortion of the Starflex arm ends. This service information also specifies inspecting the leading edges and the trailing edges of the Starflex arm ends for delamination. 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. Other Related Service Information The FAA reviewed Airbus Helicopters Master Servicing Manual (MSM) AS 365 N for Model SA–365N helicopters, MSM AS 365 N1 for Model SA–365N1 helicopters, MSM AS 365 N2 for Model AS–365N2 helicopters, and MSM AS 365 N3 for Model AS 365 N3 helicopters, all Revision 7 and dated October 9, 2017. This service information provides a schedule of maintenance tasks for the helicopters. The FAA also reviewed one document that co-publishes four Eurocopter EASB identification numbers: No. 05.00.51 for Model 365N-series helicopters, No. 05.35 for Model 366G1 helicopters, No. 05.28 for Model 365C-series helicopters, and No. 05.00.21 for non FAA-type certificated military helicopters, all Revision 3 and dated August 18, 2008. This service information specifies the same Accomplishment Instructions as Revision 4, which is issued under the name Airbus Helicopters, although Revision 4 excludes helicopters that have MOD 0762C37 installed. Proposed AD Requirements This proposed AD would retain the requirements of AD 2011–12–07 to repetitively inspect the adhesive bead between the bushings and the Starflex arms for a crack, a gap, and loss of the adhesive bead, and repetitively inspect E:\FR\FM\01NOP1.SGM 01NOP1 58640 Federal Register / Vol. 84, No. 212 / Friday, November 1, 2019 / Proposed Rules the Starflex arm ends for delamination. However, this proposed AD would not apply to helicopters with MOD 0762C37 installed. Differences Between This Proposed AD and the EASA AD The EASA AD uses the word ‘‘check,’’ whereas this proposed AD uses the word ‘‘inspect’’ instead. In some ADs, the FAA uses the word ‘‘check’’ to designate specific actions that may be performed by the owner/operator (pilot). An ‘‘inspection’’ is a maintenance action that must be performed by a certificated person as specified in 14 CFR 43.3. Costs of Compliance The FAA estimates that this proposed AD affects 35 helicopters of U.S. Registry. The FAA estimates that operators may incur the following costs in order to comply with this AD. Labor costs are estimated at $85 per workhour. Inspecting the Starflex would take about 0.25 work-hour for an estimated cost of $21 per helicopter and $735 for the U.S. fleet per inspection cycle. Replacing the Starflex would take about 10 work-hours and parts would cost about $65,900 for an estimated cost of $66,750. khammond on DSKJM1Z7X2PROD with PROPOSALS 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. The FAA is 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 The FAA 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 VerDate Sep<11>2014 19:05 Oct 31, 2019 Jkt 250001 responsibilities among the various levels of government. For the reasons discussed, I certify this proposed regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Will not affect intrastate aviation in Alaska, and (3) 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. The FAA prepared an economic evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2011–12–07, Amendment 39–16714 (76 FR 35346, June 17, 2011), and adding the following new AD: ■ Airbus Helicopters (Type Certificate Previously Held by Eurocopter France): Docket No. FAA–2019–0827; Product Identifier 2019–SW–014–AD. (a) Applicability This AD applies to Airbus Helicopters (Type Certificate previously held by Eurocopter France) Model SA–365C, SA– 365C1, SA–365C2, SA–365N, SA–365N1, AS–365N2, AS 365 N3, and SA–366G1 helicopters, certificated in any category, without Airbus Helicopters Modification 0762C37 (starflex arm part number (P/N) 365A31–1212–00 or P/N 365A31–1213–00) installed. (b) Unsafe Condition This AD defines the unsafe condition as failure of the Starflex star (Starflex) arm. This condition could result in high amplitude vibrations in flight and subsequent loss of control of the helicopter. (c) Affected ADs This AD replaces AD 2011–12–07, Amendment 39–16714 (76 FR 35346, June 17, 2011). PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 (d) Comments Due Date The FAA must receive comments by December 31, 2019. (e) Compliance You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. (f) Required Actions Within 10 hours time-in-service (TIS) and thereafter at intervals not to exceed 10 hours TIS: (1) Visually inspect the adhesive bead between the bushing and the Starflex arm for a crack, a gap, and loss of the adhesive bead, and inspect the Starflex arm ends for delamination in accordance with the Accomplishment Instructions, paragraphs 2.B.1. and 2.B.2. of Airbus Helicopters Emergency Alert Service Bulletin (EASB) No. 05.00.51, Revision 4, dated November 20, 2014 (EASB 05.00.51), EASB No. 05.35, Revision 4, dated November 20, 2014 (EASB 05.35), or EASB No. 05.28, Revision 4, dated November 20, 2014 (EASB 05.28), as applicable to your model helicopter. (2) If there is a crack in the shockproof paint around the entire adhesive bead where the Starflex arm joins the bushing (as shown in Figure 2 of EASB 05.00.51, EASB 05.35, or EASB 05.28, as applicable to your model helicopter), a gap between the adhesive bead and the bushing (as shown in Figure 3 of EASB 05.00.51, EASB 05.35, or EASB 05.28, as applicable to your model helicopter), delamination of a Starflex arm end (as shown in Figure 4 of EASB 05.00.51, EASB 05.35, or EASB 05.28, as applicable to your model helicopter), or loss of adhesive bead (as shown in Figure 5 of EASB 05.00.51, EASB 05.35, or EASB 05.28, as applicable to your model helicopter), replace the Starflex before further flight. (g) Credit for Previous Actions Actions accomplished before the effective date of this AD in accordance with the procedures specified in Eurocopter Emergency Alert Service Bulletin Nos. 05.00.51, 05.35, or 05.28, all Revision 3 and dated August 18, 2008, as applicable to your model helicopter, are considered acceptable for compliance with the corresponding actions specified in paragraph (f) of this AD as long as the last inspection was accomplished within the prior 10 hours TIS. (h) Alternative Methods of Compliance (AMOCs) (1) The Manager, Safety Management Section, Rotorcraft Standards Branch, FAA, may approve AMOCs for this AD. Send your proposal to: Matt Fuller, Senior Aviation Safety Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222–5110; email 9-ASWFTW-AMOC-Requests@faa.gov. (2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, the FAA suggests that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or E:\FR\FM\01NOP1.SGM 01NOP1 Federal Register / Vol. 84, No. 212 / Friday, November 1, 2019 / Proposed Rules certificate holding district office before operating any aircraft complying with this AD through an AMOC. (i) Additional Information (1) Airbus Helicopters Master Servicing Manual (MSM) AS 365 N, MSM AS 365 N1, MSM AS 365 N2, and MSM AS 365 N3, all Revision 7 and dated October 9, 2017; and Eurocopter Emergency Alert Service Bulletin Nos. 05.00.51, 05.35, 05.28, and 05.00.21, all Revision 3 and dated August 18, 2008, which are not incorporated by reference, contain additional information about the subject of this AD. For service information identified in this AD, contact Airbus Helicopters, 2701 N Forum Drive, Grand Prairie, TX 75052; telephone (972) 641–0000 or (800) 232–0323; fax (972) 641–3775; or at http:// www.helicopters.airbus.com/website/en/ref/ Technical-Support_73.html. You may view a copy of the service information at the FAA, Office of the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N– 321, Fort Worth, TX 76177. (2) The subject of this AD is addressed in European Aviation Safety Agency (EASA) AD No. 2008–0165R1, dated June 30, 2017. You may view the EASA AD on the internet at http://www.regulations.gov in the AD Docket. (j) Subject Joint Aircraft Service Component (JASC) Code: 6200, Main Rotor System. Issued in Fort Worth, Texas, on October 21, 2019. Lance T. Gant, Director, Compliance & Airworthiness Division, Aircraft Certification Service. [FR Doc. 2019–23832 Filed 10–31–19; 8:45 am] BILLING CODE 4910–13–P ENVIRONMENTAL PROTECTION AGENCY 40 CFR Part 52 [EPA–R09–OAR–2018–0562; FRL–10001– 51–Region 9] Clean Air Plans; 2008 8-Hour Ozone Nonattainment Area Requirements; Determination of Attainment by the Attainment Date; Imperial County, California Environmental Protection Agency (EPA). ACTION: Proposed rule. AGENCY: The Environmental Protection Agency (EPA) is proposing to approve two state implementation plan (SIP) revisions submitted by the State of California to meet Clean Air Act (CAA or ‘‘Act’’) requirements for the 2008 ozone national ambient air quality standards (NAAQS) in the Imperial County nonattainment area, as follows. The EPA proposes to approve the ‘‘Imperial County 2017 State Implementation Plan for the 2008 8- khammond on DSKJM1Z7X2PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 19:05 Oct 31, 2019 Jkt 250001 Hour Ozone Standard’’ (‘‘Imperial Ozone Plan’’ or ‘‘Plan’’) and the portions of the ‘‘2018 Updates to the California State Implementation Plan’’ (‘‘2018 SIP Update’’) that address the requirement for a reasonable further progress (RFP) demonstration for the Imperial County for the 2008 ozone standards. In addition, the EPA is proposing to determine, based on a separate demonstration submitted by the State of California, that the Imperial County nonattainment area would have attained the 2008 ozone NAAQS by the ‘‘Moderate’’ area attainment date of July 20, 2018, but for emissions emanating from outside of the United States, and therefore would no longer be subject to the CAA requirements pertaining to reclassification upon failure to attain. If we finalize these proposed actions, the Imperial County nonattainment area would remain classified as a Moderate nonattainment area for the 2008 ozone NAAQS. DATES: Any comments must arrive by December 2, 2019. ADDRESSES: Submit your comments, identified by Docket ID No. EPA–R09– OAR–2018–0562, at https:// www.regulations.gov. For comments submitted at Regulations.gov, follow the online instructions for submitting comments. Once submitted, comments cannot be edited or removed from Regulations.gov. The EPA may publish any comment received to its public docket. Do not submit electronically any information you consider to be Confidential Business Information (CBI) or other information whose disclosure is restricted by statute. Multimedia submissions (audio, video, etc.) must be accompanied by a written comment. The written comment is considered the official comment and should include discussion of all points you wish to make. The EPA will generally not consider comments or comment contents located outside of the primary submission (i.e., on the web, cloud, or other file sharing system). For additional submission methods, please contact the person identified in the FOR FURTHER INFORMATION CONTACT section. For the full EPA public comment policy, information about CBI or multimedia submissions, and general guidance on making effective comments, please visit https://www.epa.gov/dockets/ commenting-epa-dockets. FOR FURTHER INFORMATION CONTACT: Rory Mays, Air Planning Office (AIR–2), EPA Region IX, (415) 972–3227, mays.rory@ epa.gov. SUPPLEMENTARY INFORMATION: Throughout this document, ‘‘we,’’ ‘‘us,’’ and ‘‘our’’ refer to the EPA. The EPA PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 58641 proposes to approve the portions of the Imperial Ozone Plan that address the requirements for emissions statements, a base year emissions inventory, a reasonably available control measures (RACM) demonstration, a demonstration of attainment of the standards by the applicable attainment date but for emissions emanating from outside of the United States, and motor vehicle emission budgets. The EPA proposes that the requirements for contingency measures for failing to meet RFP would be moot if we finalize our proposed determination that Imperial County has met its 2017 RFP targets. The EPA also proposes that contingency measures for failing to attain the standards would not be required if we finalize our proposed approval of the State’s demonstrations of attainment by the attainment date but for international emissions. The EPA proposes to approve the portions of the 2018 SIP Update that address the requirement for a reasonable further progress (RFP) demonstration for the Imperial County for the 2008 ozone standards. Table of Contents I. Background A. Ozone Standards, Area Designations, and SIPs B. Imperial County Ozone Nonattainment Area II. Imperial Ozone Plan and 2018 SIP Update A. Overarching Requirements B. Requirements for International Border Areas C. Summary of the Imperial Ozone Plan and 2018 SIP Update D. Emissions Statement Certification E. Emissions Inventories F. Reasonably Available Control Measures Demonstration G. Demonstration of Attainment but for International Emissions H. Rate of Progress and Reasonable Further Progress Demonstration I. Motor Vehicle Emission Budgets J. Contingency Measures K. Other Requirements III. Imperial County Ozone Determination of Attainment but for International Emissions A. Statutory and Regulatory Requirements B. Summary of State’s Submission C. EPA Review of State’s Submission IV. Proposed Action V. Statutory and Executive Order Reviews I. Background A. Ozone Standards, Area Designations, and SIPs Ground-level ozone pollution is formed from the reaction of volatile organic compounds (VOC) and oxides of nitrogen (NOX) in the presence of sunlight. These two pollutants, referred to as ozone precursors, are emitted by many types of sources, including on- E:\FR\FM\01NOP1.SGM 01NOP1

Agencies

[Federal Register Volume 84, Number 212 (Friday, November 1, 2019)]
[Proposed Rules]
[Pages 58638-58641]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-23832]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0827; Product Identifier 2019-SW-014-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters (Type Certificate 
Previously Held by Eurocopter France) Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD) 
2011-12-07 for Eurocopter France (now Airbus Helicopters) Model SA-
365C, SA-365C1, SA-365C2, SA-365N, SA-365N1, AS-365N2, AS 365 N3, and 
SA-366G1 helicopters. AD 2011-12-07 currently requires repetitively 
inspecting the adhesive bead between the bushings and the Starflex star 
(Starflex) arms and the Starflex arm ends. Since the FAA issued AD 
2011-12-07, Airbus Helicopters has developed an improved Starflex. This 
proposed AD would retain the requirements of AD 2011-12-07 and revise 
the Applicability paragraph by omitting helicopters with the improved 
Starflex installed. The FAA is proposing this AD to address the unsafe 
condition on these products.

DATES: The FAA must receive comments on this proposed AD by December 
31, 2019.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Docket: Go to http://www.regulations.gov. Follow the online instructions for sending your 
comments electronically.
     Fax: 202-493-2251.
     Mail: Send comments to the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590-0001.
     Hand Delivery: Deliver to the ``Mail'' address between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.

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-2019-
0827; or in person at Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The AD docket contains 
this proposed AD, the European Aviation Safety Agency (EASA) AD, the 
economic evaluation, any comments received and other information. The 
street address for Docket Operations is listed above. Comments will be 
available in the AD docket shortly after receipt.
    For service information identified in this proposed rule, contact 
Airbus Helicopters, 2701 N Forum Drive, Grand Prairie, TX 75052; 
telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; or at 
http://www.helicopters.airbus.com/website/en/ref/Technical-Support_73.html. You

[[Page 58639]]

may view this service information at the FAA, Office of the Regional 
Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort 
Worth, TX 76177.

FOR FURTHER INFORMATION CONTACT: Matt Fuller, Senior Aviation Safety 
Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 
10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-5110; 
email [email protected].

SUPPLEMENTARY INFORMATION:

Comments Invited

    The FAA invites you to participate in this rulemaking by submitting 
written comments, data, or views. The FAA also invites comments 
relating to the economic, environmental, energy, or federalism impacts 
that might result from adopting the proposals in this document. The 
most helpful comments reference a specific portion of the proposal, 
explain the reason for any recommended change, and include supporting 
data. To ensure the docket does not contain duplicate comments, 
commenters should send only one copy of written comments, or if 
comments are filed electronically, commenters should submit only one 
time.
    The FAA will file in the docket all comments that the FAA receives, 
as well as a report summarizing each substantive public contact with 
FAA personnel concerning this proposed rulemaking. Before acting on 
this proposal, the FAA will consider all comments received on or before 
the closing date for comments. The FAA will consider comments filed 
after the comment period has closed if it is possible to do so without 
incurring expense or delay. The FAA may change this proposal in light 
of the comments received.

Discussion

    The FAA issued AD 2011-12-07, Amendment 39-16714 (76 FR 35346, June 
17, 2011) (``AD 2011-12-07'') for Eurocopter France (now Airbus 
Helicopters) Model SA-365C, SA-365C1, SA-365C2, SA-365N, SA-365N1, AS-
365N2, AS 365 N3, and SA-366G1 helicopters. AD 2011-12-07 requires 
repetitively inspecting the adhesive bead between the bushings and the 
Starflex arms for a crack, a gap, and loss of the adhesive bead, 
inspecting the Starflex arm ends for delamination, and replacing the 
Starflex if any of these conditions are found. AD 2011-12-07 was 
prompted by three cases of deterioration of a Starflex arm end. In two 
of these cases, the deterioration caused high amplitude vibrations in 
flight, compelling the pilot to make a precautionary landing. The 
requirements of AD 2011-12-07 are intended to prevent failure of the 
Starflex, high-amplitude vibrations in flight, and subsequent loss of 
control of the helicopter.

Actions Since AD 2011-12-07 Was Issued

    Since the FAA issued AD 2011-12-07, Airbus Helicopters has 
developed new part-numbered Starflex, 365A31-1212-00 and 365A31-1213-
00, with different material. This change in material improves the 
reliability and technical performance of the Starflex, improves 
temperature-related behavior in the area of the Starflex arm ends, and 
increases dimension margins. Subsequently, Airbus Helicopters has 
extended the inspection interval of Starflex arm ends with these 
Starflex installed. Airbus Helicopters identifies helicopters with 
Starflex part number 365A31-1212-00 or 365A31-1213-00 installed as 
Modification (MOD) 0762C37.
    Accordingly, EASA, which is the Technical Agent for the Member 
States of the European Union, issued AD No. 2008-0165R1, dated June 30, 
2017 (EASA AD 2008-0165R1), to address this unsafe condition for Airbus 
Helicopters Model SA 365 N, SA 365 N1, AS 365 N2, AS 365 N3, SA 365 C, 
SA 365 C1, SA 365 C2, SA 365 C3 and SA 366 G1 helicopters, except 
helicopters with MOD 0762C37 installed in production. EASA advises that 
the Airbus Helicopters Starflex manufactured with improved materials 
make the 10-hour repetitive inspections specified in the original issue 
of EASA AD 2008-0165R1 unnecessary. EASA AD 2008-0165R1 retains the 
repetitive inspections from the original issue but does not apply to 
helicopters with the new Starflex.
    Also since the FAA issued AD 2011-12-07, Eurocopter France changed 
its name to Airbus Helicopters. This proposed AD reflects that change 
and updates the contact information to obtain service documentation.

FAA's Determination

    These helicopters have been approved by EASA and are approved for 
operation in the United States. Pursuant to the FAA's bilateral 
agreement with the European Union, EASA has notified the FAA of the 
unsafe condition described in its AD. The FAA is proposing this AD 
after evaluating all known relevant information and determined that an 
unsafe condition is likely to exist or develop on other helicopters of 
the same type designs.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed one document that co-publishes four Airbus 
Helicopters Emergency Alert Service Bulletin (EASB) identification 
numbers: No. 05.00.51 for Model 365N-series helicopters, No. 05.35 for 
Model 366G1 helicopters, No. 05.28 for Model 365C-series helicopters, 
and No. 05.00.21 for non FAA-type certificated military helicopters, 
all Revision 4 and dated November 20, 2014. EASB Nos. 05.00.51, 05.35, 
and 05.28 are proposed for incorporation by reference in this proposed 
AD. EASB No. 05.00.21 is not proposed for incorporation by reference in 
this proposed AD.
    This service information specifies visually inspecting the adhesive 
bead on the bushes of the Starflex arm ends for bonding failure of the 
bushes and distortion of the Starflex arm ends. This service 
information also specifies inspecting the leading edges and the 
trailing edges of the Starflex arm ends for delamination.
    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.

Other Related Service Information

    The FAA reviewed Airbus Helicopters Master Servicing Manual (MSM) 
AS 365 N for Model SA-365N helicopters, MSM AS 365 N1 for Model SA-
365N1 helicopters, MSM AS 365 N2 for Model AS-365N2 helicopters, and 
MSM AS 365 N3 for Model AS 365 N3 helicopters, all Revision 7 and dated 
October 9, 2017. This service information provides a schedule of 
maintenance tasks for the helicopters.
    The FAA also reviewed one document that co-publishes four 
Eurocopter EASB identification numbers: No. 05.00.51 for Model 365N-
series helicopters, No. 05.35 for Model 366G1 helicopters, No. 05.28 
for Model 365C-series helicopters, and No. 05.00.21 for non FAA-type 
certificated military helicopters, all Revision 3 and dated August 18, 
2008. This service information specifies the same Accomplishment 
Instructions as Revision 4, which is issued under the name Airbus 
Helicopters, although Revision 4 excludes helicopters that have MOD 
0762C37 installed.

Proposed AD Requirements

    This proposed AD would retain the requirements of AD 2011-12-07 to 
repetitively inspect the adhesive bead between the bushings and the 
Starflex arms for a crack, a gap, and loss of the adhesive bead, and 
repetitively inspect

[[Page 58640]]

the Starflex arm ends for delamination. However, this proposed AD would 
not apply to helicopters with MOD 0762C37 installed.

Differences Between This Proposed AD and the EASA AD

    The EASA AD uses the word ``check,'' whereas this proposed AD uses 
the word ``inspect'' instead. In some ADs, the FAA uses the word 
``check'' to designate specific actions that may be performed by the 
owner/operator (pilot). An ``inspection'' is a maintenance action that 
must be performed by a certificated person as specified in 14 CFR 43.3.

Costs of Compliance

    The FAA estimates that this proposed AD affects 35 helicopters of 
U.S. Registry. The FAA estimates that operators may incur the following 
costs in order to comply with this AD. Labor costs are estimated at $85 
per work-hour.
    Inspecting the Starflex would take about 0.25 work-hour for an 
estimated cost of $21 per helicopter and $735 for the U.S. fleet per 
inspection cycle. Replacing the Starflex would take about 10 work-hours 
and parts would cost about $65,900 for an estimated cost of $66,750.

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.
    The FAA is 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

    The FAA 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, I certify this proposed regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Will not affect intrastate aviation in Alaska, and
    (3) 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.
    The FAA prepared an economic evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2011-12-07, Amendment 39-16714 (76 FR 35346, June 17, 2011), and adding 
the following new AD:

Airbus Helicopters (Type Certificate Previously Held by Eurocopter 
France): Docket No. FAA-2019-0827; Product Identifier 2019-SW-014-
AD.

(a) Applicability

    This AD applies to Airbus Helicopters (Type Certificate 
previously held by Eurocopter France) Model SA-365C, SA-365C1, SA-
365C2, SA-365N, SA-365N1, AS-365N2, AS 365 N3, and SA-366G1 
helicopters, certificated in any category, without Airbus 
Helicopters Modification 0762C37 (starflex arm part number (P/N) 
365A31-1212-00 or P/N 365A31-1213-00) installed.

(b) Unsafe Condition

    This AD defines the unsafe condition as failure of the Starflex 
star (Starflex) arm. This condition could result in high amplitude 
vibrations in flight and subsequent loss of control of the 
helicopter.

(c) Affected ADs

    This AD replaces AD 2011-12-07, Amendment 39-16714 (76 FR 35346, 
June 17, 2011).

(d) Comments Due Date

    The FAA must receive comments by December 31, 2019.

(e) Compliance

    You are responsible for performing each action required by this 
AD within the specified compliance time unless it has already been 
accomplished prior to that time.

 (f) Required Actions

    Within 10 hours time-in-service (TIS) and thereafter at 
intervals not to exceed 10 hours TIS:
    (1) Visually inspect the adhesive bead between the bushing and 
the Starflex arm for a crack, a gap, and loss of the adhesive bead, 
and inspect the Starflex arm ends for delamination in accordance 
with the Accomplishment Instructions, paragraphs 2.B.1. and 2.B.2. 
of Airbus Helicopters Emergency Alert Service Bulletin (EASB) No. 
05.00.51, Revision 4, dated November 20, 2014 (EASB 05.00.51), EASB 
No. 05.35, Revision 4, dated November 20, 2014 (EASB 05.35), or EASB 
No. 05.28, Revision 4, dated November 20, 2014 (EASB 05.28), as 
applicable to your model helicopter.
    (2) If there is a crack in the shockproof paint around the 
entire adhesive bead where the Starflex arm joins the bushing (as 
shown in Figure 2 of EASB 05.00.51, EASB 05.35, or EASB 05.28, as 
applicable to your model helicopter), a gap between the adhesive 
bead and the bushing (as shown in Figure 3 of EASB 05.00.51, EASB 
05.35, or EASB 05.28, as applicable to your model helicopter), 
delamination of a Starflex arm end (as shown in Figure 4 of EASB 
05.00.51, EASB 05.35, or EASB 05.28, as applicable to your model 
helicopter), or loss of adhesive bead (as shown in Figure 5 of EASB 
05.00.51, EASB 05.35, or EASB 05.28, as applicable to your model 
helicopter), replace the Starflex before further flight.

 (g) Credit for Previous Actions

    Actions accomplished before the effective date of this AD in 
accordance with the procedures specified in Eurocopter Emergency 
Alert Service Bulletin Nos. 05.00.51, 05.35, or 05.28, all Revision 
3 and dated August 18, 2008, as applicable to your model helicopter, 
are considered acceptable for compliance with the corresponding 
actions specified in paragraph (f) of this AD as long as the last 
inspection was accomplished within the prior 10 hours TIS.

(h) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Section, Rotorcraft Standards 
Branch, FAA, may approve AMOCs for this AD. Send your proposal to: 
Matt Fuller, Senior Aviation Safety Engineer, Safety Management 
Section, Rotorcraft Standards Branch, FAA, 10101 Hillwood Pkwy., 
Fort Worth, TX 76177; telephone (817) 222-5110; email [email protected].
    (2) For operations conducted under a 14 CFR part 119 operating 
certificate or under 14 CFR part 91, subpart K, the FAA suggests 
that you notify your principal inspector, or lacking a principal 
inspector, the manager of the local flight standards district office 
or

[[Page 58641]]

certificate holding district office before operating any aircraft 
complying with this AD through an AMOC.

(i) Additional Information

    (1) Airbus Helicopters Master Servicing Manual (MSM) AS 365 N, 
MSM AS 365 N1, MSM AS 365 N2, and MSM AS 365 N3, all Revision 7 and 
dated October 9, 2017; and Eurocopter Emergency Alert Service 
Bulletin Nos. 05.00.51, 05.35, 05.28, and 05.00.21, all Revision 3 
and dated August 18, 2008, which are not incorporated by reference, 
contain additional information about the subject of this AD. For 
service information identified in this AD, contact Airbus 
Helicopters, 2701 N Forum Drive, Grand Prairie, TX 75052; telephone 
(972) 641-0000 or (800) 232-0323; fax (972) 641-3775; or at http://www.helicopters.airbus.com/website/en/ref/Technical-Support_73.html. 
You may view a copy of the service information at the FAA, Office of 
the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 
6N-321, Fort Worth, TX 76177.
    (2) The subject of this AD is addressed in European Aviation 
Safety Agency (EASA) AD No. 2008-0165R1, dated June 30, 2017. You 
may view the EASA AD on the internet at http://www.regulations.gov 
in the AD Docket.

(j) Subject

    Joint Aircraft Service Component (JASC) Code: 6200, Main Rotor 
System.

    Issued in Fort Worth, Texas, on October 21, 2019.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2019-23832 Filed 10-31-19; 8:45 am]
BILLING CODE 4910-13-P