Airworthiness Directives; Honeywell International Inc. Turboprop and Turboshaft Engines, 29479-29483 [2018-13523]

Download as PDF Federal Register / Vol. 83, No. 122 / Monday, June 25, 2018 / Proposed Rules (i) Corrective Action for Any Discrepancy or Defect If any discrepancy or defect is detected during any inspection required by paragraph (h) of this AD: Before further flight, obtain corrective actions approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus Defense and Space S.A.’s EASA Design Organization Approval (DOA); and accomplish the corrective actions within the compliance time specified therein. If approved by the DOA, the approval must include the DOAauthorized signature. Accomplishment of a repair, as required by this paragraph, does not constitute terminating action for the repetitive inspections required by paragraph (h) of this AD. (j) Parts Installation Limitation As of the effective date of this AD, an affected part may be installed on any airplane provided that it is a new part or that, before installation, the visual inspection required by paragraph (h) of this AD has been accomplished on that part and the part passed the inspection (no discrepancy or defect detected), as required by paragraph (h) of this AD. amozie on DSK3GDR082PROD with PROPOSALS1 (k) Terminating Action for AD 2017–19–08 Accomplishing the actions required by this AD terminates all of the requirements of AD 2017–19–08. (l) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Section, Transport Standards 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 International Section, send it to the attention of the person identified in paragraph (m)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOCREQUESTS@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 Section, Transport Standards Branch, FAA; or EASA; or Airbus Defense and Space S.A.’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (m) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2018–0051, dated March 2, 2018, for related information. This MCAI may be found in the AD docket on the internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2018–0552. VerDate Sep<11>2014 16:25 Jun 22, 2018 Jkt 244001 (2) For more information about this AD, contact Shahram Daneshmandi, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax 206–231–3220. (3) For service information identified in this AD, contact Airbus Defense and Space, Services/Engineering support, Avenida de ´ Aragon 404, 28022 Madrid, Spain; telephone: +34 91 585 55 84; fax: +34 91 585 31 27; email: MTA.TechnicalService@ military.airbus.com. You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206–231–3195. Issued in Des Moines, Washington, on June 14, 2018. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018–13342 Filed 6–22–18; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–0479; Product Identifier 2016–NE–23–AD] RIN 2120–AA64 Airworthiness Directives; Honeywell International Inc. Turboprop and Turboshaft Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede Airworthiness Directive (AD) 2018–02– 14, which applies to certain Honeywell International Inc. (Honeywell) TPE331 turboprop and TSE331 turboshaft engines. AD 2018–02–14 requires inspection of the affected combustion chamber case assembly, replacement of those assemblies found cracked, and removal of affected assemblies on certain TPE331 and TSE331 engines. Since we issued AD 2018–02–14, we received comments to revise the applicability of that AD to include the TPE331–12B engine model, correct certain TPE engine model typographical errors, and to allow certain weld repair procedures. This proposed AD would expand the applicability of AD 2018– 02–14 to include the TPE331–12B engine model, correct certain engine model typographical errors, and allow certain weld repair procedures after approval. We are proposing this AD to SUMMARY: PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 29479 address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by August 9, 2018. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Honeywell International Inc., 111 S 34th Street, Phoenix, AZ 85034–2802; phone: 800– 601–3099; internet: https:// myaerospace.honeywell.com/wps/ portal. You may view this service information at the FAA, Engine and Propeller Standards Branch, 1200 District Avenue, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7759. 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–2018– 0479; 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 NPRM, the regulatory evaluation, any comments received, and other information. The street address for Docket Operations (phone: 800–647–5527) is listed above. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Joseph Costa, Aerospace Engineer, Los Angeles ACO Branch, FAA, 3960 Paramount Blvd., Lakewood, CA 90712– 4137; phone: 562–627–5246; fax: 562– 627–5210; email: joseph.costa@faa.gov. 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–2018–0479; Product Identifier 2016–NE–23–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy E:\FR\FM\25JNP1.SGM 25JNP1 29480 Federal Register / Vol. 83, No. 122 / Monday, June 25, 2018 / Proposed Rules aspects of this NPRM. We will consider all comments received by the closing date and may amend this NPRM because of those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion We issued AD 2018–02–14, Amendment 39–19167 (83 FR 3263, January 24, 2018), (‘‘AD 2018–02–14’’), for certain Honeywell TPE331 turboprop and TSE331 turboshaft engines. AD 2018–02–14 requires inspection of the affected combustion chamber case assembly, replacement of those assemblies found cracked, and removal of affected assemblies on certain TPE331 and TSE331 engines. AD 2018–02–14 resulted from reports that combustion chamber case assemblies have cracked and ruptured. We issued AD 2018–02–14 to prevent failure of the combustion chamber case assembly. Actions Since AD 2018–02–14 Was Issued Since we issued AD 2018–02–14, we determined the need to revise sections of that AD. We received comments indicating that the TPE331–12B engine model was inadvertently omitted from that AD and that the TPE331–43–A, –43–BL, –47–A, –55–B, and –61–A engine models included typographical errors. We also received comments to revise the Compliance section, which disallows weld repairs on any combustion chamber case assemblies that are affected by that AD. We determined that allowing weld repair procedures of certain combustion chamber case assemblies with lower stresses may be accomplished if these procedures are approved by the Manager, Los Angeles ACO Branch. Related Service Information Under 1 CFR Part 51 We reviewed Honeywell Service Bulletin (SB) TPE331–72–2178, Revision 0, dated May 3, 2011 and Honeywell SB TPE331–72–2179, Revision 0, dated May 3, 2011. Honeywell SB TPE331–72–2178, Revision 0, describes procedures for inspection and removal of the affected combustion chamber case assemblies installed on all affected engines except for the TPE331–12B engine model. Honeywell SB TPE331–72–2179, Revision 0, describes procedures for inspection and removal of the affected combustion chamber case assemblies installed on the TPE331–12B engine model. 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 We reviewed Honeywell SBs TPE331– 72–2228, Revision 0, dated June 12, 2014; TPE331–72–2230, Revision 0, dated June 19, 2014; TPE331–72–2218, Revision 2, dated February 18, 2017; TPE331–72–2244, Revision 2, dated March 20 2017; TPE331–72–2235, Revision 2, dated February 18, 2017; TPE331–72–2281, Revision 0, dated July 22, 2016; TPE331–72–2294, Revision 0, dated December 22, 2016; TPE331–72– 2231, Revision 1, dated August 1, 2017; and TSE331–72–2245, Revision 0, dated November 11, 2016. These SBs provide guidance on replacement of the affected combustion chamber case assemblies. FAA’s Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements This proposed AD would retain all of the requirements of AD 2018–02–14. This proposed AD would revise the Applicability to include the TPE331– 12B engine model and to correct references to the TPE331–43–A, –43–BL, –47–A, –55–B, and –61–A engine models. This proposed AD would also allow weld repair procedures to the applicable combustion chamber case assemblies provided those procedures are approved by the Manager, Los Angeles ACO Branch. Costs of Compliance We estimate that this AD affects 5,644 engines installed on airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost On-wing inspection ............ 1 work-hour × $85 per hour = $85 ...... We estimate the following costs to do any necessary replacements that would Parts cost Cost per product $0 $85 per inspection ..... be required based on the results of the proposed inspection. We estimate that Cost on U.S. operators $479,740 per inspection cycle. 158 engines will need this replacement during the first year of inspection. ON-CONDITION COSTS Labor cost Replacement of the combustion chamber case assembly ....... amozie on DSK3GDR082PROD with PROPOSALS1 Action 1 work-hour × $85 per hour = $85 .................. 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 VerDate Sep<11>2014 16:25 Jun 22, 2018 Jkt 244001 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 PO 00000 Frm 00016 Fmt 4702 Sfmt 4702 Parts cost $15,000 Cost per product $15,085 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 E:\FR\FM\25JNP1.SGM 25JNP1 Federal Register / Vol. 83, No. 122 / Monday, June 25, 2018 / Proposed Rules products identified in this rulemaking action. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to engines, propellers, and associated appliances to the Manager, Engine and Propeller Standards Branch, Policy and Innovation Division. Regulatory Findings We have 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 that the 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 amozie on DSK3GDR082PROD with PROPOSALS1 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 16:25 Jun 22, 2018 Jkt 244001 shutdown, and reduced control of the airplane. 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 29481 [Amended] (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Required Actions 2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2018–02–14, Amendment 39–19167 (83 FR 3263, January 24, 2018), and adding the following new AD: ■ This AD applies to Honeywell International Inc. (Honeywell) TPE331–1, –2, –2UA, –3U, –3UW, –5, –5A, –5AB, –5B, –6, –6A, –8, –10, –10AV, –10GP, –10GT, –10N, –10P, –10R, –10T, –10U, –10UA, –10UF, –10UG, –10UGR, –10UR, and –11U, –12B, –12JR, –12UA, –12UAR, –12UHR, –25AA, –25AB, –25DA, –25DB, –25FA, –43–A, –43–B, –47–A, –55–B, and –61–A turboprop engine models, including those engine models with a –L stamped after the model number (for example, –43–BL); and TSE331– 3U turboshaft engine models with combustion chamber case assemblies, part numbers (P/Ns) 869728–x, 893973–x, 3101668–x, and 3102613–x, where ‘‘x’’ denotes any dash number, installed. (1) For all affected engines: (i) Inspect all accessible areas of the combustion chamber case assembly, focusing on the weld joints, before accumulating 450 hours time in service (TIS) since last fuel nozzle inspection or within 50 hours TIS after the effective date of this AD, whichever occurs later. (ii) Perform the inspection in accordance with the Accomplishment Instructions, paragraphs 3.B.(1) through 3.B.(2), in Honeywell Service Bulletin (SB) TPE331–72– 2178, Revision 0, dated May 3, 2011, or SB TPE331–72–2179, Revision 0, dated May 3, 2011, as applicable to the affected engine model. (iii) Thereafter, repeat this inspection during scheduled fuel nozzle inspections at intervals not to exceed 450 hours TIS since the last fuel nozzle inspection. (2) For TPE331–3U, –3UW, –5, –5A, –5AB, –5B, –6, and –6A engine models with combustion chamber case assemblies, P/Ns 869728–1, 869728–3, or 893973–5, installed, and without the one-piece bleed pad with P3 boss; and for TPE331–1, –2, and –2UA engine models modified by National Flight Services, Inc., supplemental type certificate (STC) SE383CH, remove the combustion chamber case assembly from service at the next removal of the combustion chamber case assembly from the engine, not to exceed 3,700 hours TIS since last hot section inspection. (3) After the effective date of this AD, do not weld repair the applicable combustion chamber case assemblies unless the weld repair procedures are approved by the Manager, Los Angeles ACO Branch, and that approval specifically refers to this AD. (d) Subject (h) Definition Joint Aircraft System Component (JASC) Code 7240, Turbine Engine Combustion Section. (1) TPE331 engines modified by STC SE383CH may be defined as the ‘‘Super 1’’ and ‘‘Super 2’’ for the compressor modification of the TPE331–1 and the TPE331–2, –2U, and –2UA engine models, respectively. (2) Figures 1 and 2 to paragraph (h) of this AD illustrate the appearance of combustion chamber case assembly, P/N 893973–5, without and with, respectively, the one-piece bleed pad with the P3 boss. Honeywell International Inc. (Type Certificate previously held by AlliedSignal Inc., Garrett Engine Division; Garrett Turbine Engine Company; and AiResearch Manufacturing Company of Arizona): Docket No. FAA–2018–0479; Product Identifier 2016–NE–23–AD. (a) Comments Due Date The FAA must receive comments on this AD action by August 9, 2018. (b) Affected ADs This AD replaces AD 2018–02–14, Amendment 39–19167 (83 FR 3263, January 24, 2018). (c) Applicability (e) Unsafe Condition This AD was prompted by reports that combustion chamber case assemblies have cracked and ruptured. We are issuing this AD to prevent failure of the combustion chamber case assembly. The unsafe condition, if not addressed, could result in failure of the combustion chamber case assembly, in-flight PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 BILLING CODE 4910–13–P E:\FR\FM\25JNP1.SGM 25JNP1 29482 Federal Register / Vol. 83, No. 122 / Monday, June 25, 2018 / Proposed Rules amozie on DSK3GDR082PROD with PROPOSALS1 (i) Installation Prohibition After the effective date of this AD, do not install a combustion chamber case assembly, P/N 869728–1, 869728–3, or 893973–5, in TPE331–3U, –3UW, –5, –5A, –5AB, –5B, –6, and –6A engine models or in TPE331–1, –2, and –2UA engine models modified by National Flight Services, Inc., STC SE383CH, unless the combustion chamber case assembly has a one-piece bleed pad with P3 boss. VerDate Sep<11>2014 16:25 Jun 22, 2018 Jkt 244001 (1) The Manager, Los Angeles 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 (k)(1) of this AD. Information may be emailed to: 9ANM-LAACO-AMOC-REQUESTS@faa.gov. (2) Before using any approved AMOC, notify your appropriate principal inspector, PO 00000 Frm 00018 Fmt 4702 Sfmt 4702 or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (k) Related Information (1) For more information about this AD, contact Joseph Costa, Aerospace Engineer, Los Angeles ACO Branch, FAA, 3960 Paramount Blvd., Lakewood, CA 90712– 4137; phone: 562–627–5246; fax: 562–627– 5210; email: joseph.costa@faa.gov. (2) For service information identified in this AD, contact AD, contact Honeywell International Inc., 111 S 34th Street, Phoenix, AZ 85034–2802; phone: 800–601–3099; internet: https://myaerospace.honeywell E:\FR\FM\25JNP1.SGM 25JNP1 EP25JN18.007</GPH> (j) Alternative Methods of Compliance (AMOCs) EP25JN18.006</GPH> BILLING CODE 4910–13–C Federal Register / Vol. 83, No. 122 / Monday, June 25, 2018 / Proposed Rules .com/wps/portal. You may view this service information at the FAA, Engine and Propeller Standards Branch, 1200 District Avenue, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7759. Issued in Burlington, Massachusetts, on June 19, 2018. Robert J. Ganley, Manager, Engine and Propeller Standards Branch, Aircraft Certification Service. [FR Doc. 2018–13523 Filed 6–22–18; 8:45 am] BILLING CODE 4910–13–P ENVIRONMENTAL PROTECTION AGENCY 40 CFR Part 52 [EPA–R09–OAR–2018–0233; FRL–9979– 35—Region 9] Air Plan Approval; California; San Diego County Air Pollution Control District; Stationary Source Permits and Exemptions Environmental Protection Agency (EPA). ACTION: Proposed rule. AGENCY: The Environmental Protection Agency (EPA) is proposing to approve and conditionally approve revisions to the San Diego County Air Pollution Control District’s (SDAPCD or ‘‘District’’) portion of the California State Implementation Plan (SIP). These revisions concern the District’s New Source Review (NSR) permitting program for new and modified sources of air pollution under section 110(a)(2)(C) and part D of title I of the Clean Air Act (CAA). This action updates the SDAPCD’s applicable SIP with current SDAPCD permitting rules. We are taking comments on this proposal and plan to follow with a final action. SUMMARY: Any comments must arrive by July 25, 2018. ADDRESSES: Submit your comments, identified by Docket ID No. EPA–R09– OAR–2018–0233 at http:// www.regulations.gov, or via email to R9AirPermits@epa.gov. For comments submitted at Regulations.gov, follow the online instructions for submitting comments. Once submitted, comments cannot be removed or edited from Regulations.gov. For either manner of submission, 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 http://www2.epa.gov/dockets/ commenting-epa-dockets. FOR FURTHER INFORMATION CONTACT: YaTing Tsai, EPA Region IX, (415) 972– 3328, Tsai.Ya-Ting@epa.gov. SUPPLEMENTARY INFORMATION: Throughout this document, ‘‘we,’’ ‘‘us’’ and ‘‘our’’ refer to the EPA. DATES: Table of Contents I. The State’s Submittal A. What rules did the State submit? 29483 B. Are there other versions of these rules? C. What is the purpose of the submitted rule revisions? II. The EPA’s Evaluation and Action A. How is the EPA evaluating the rules? B. Do the rules meet the evaluation criteria? C. Proposed Action and Public Comment III. Incorporation by Reference IV. Statutory and Executive Order Reviews I. The State’s Submittal A. What rules did the State submit? Table 1 lists the rules addressed by this proposal with the dates when they were adopted by the SDAPCD and submitted by the California Air Resources Board (CARB), which is the governor’s designee for California SIP submittals. Collectively, these submittals generally constitute the SDAPCD’s current program for preconstruction review and permitting of new or modified stationary sources under its jurisdiction. The rule revisions that are the subject of this action represent a comprehensive revision to the SDAPCD’s preconstruction review and permitting program and are intended to satisfy the requirements under part D of title I of the Act (nonattainment NSR or NNSR) as well as the general preconstruction review requirements under section 110(a)(2)(C) of the Act (minor NSR). The SDAPCD does not implement a SIP-approved prevention of significant deterioration (PSD) permitting program and has not submitted the rules in this action for purposes of the PSD program; therefore, we are not evaluating whether this SIP submittal satisfies PSD program requirements at 40 CFR 51.166. TABLE 1—SUBMITTED RULES Adopted date amozie on DSK3GDR082PROD with PROPOSALS1 Rule No. Rule title 11 .............................. 20 .............................. 20.1 ........................... 20.2 * ......................... 20.3 * ......................... 20.4 * ......................... 20.6 ........................... 24 .............................. Exemptions from Rule 10 Permit Requirements .............................................................. Standards for Granting Permits ........................................................................................ New Source Review—General Provisions ....................................................................... New Source Review—Non-Major Stationary Sources ..................................................... New Source Review—Major Stationary Sources and PSD Stationary Sources ............. New Source Review—Portable Emission Units ............................................................... Standards for Permit to Operate Air Quality Analysis ...................................................... Temporary Permit to Operate ........................................................................................... 05/11/2016 06/10/1986 04/27/2016 04/27/2016 04/27/2016 04/27/2016 04/27/2016 06/29/2016 Submitted date 08/22/2016 11/21/1986 06/17/2016 06/17/2016 06/17/2016 06/17/2016 06/17/2016 08/22/2016 * The following subsections of the Rules 20.2–20.4 were not submitted to the EPA for inclusion in the San Diego SIP: Rule 20.2 Subsections (d)(2)(i)(B), (d)(2)(v), (d)(2)(vi)(B) and (d)(3); Rule 20.3 Subsections (d)(1)(vi), (d)(2)(i)(B), (d)(2)(v), (d)(2)(vi)(B) and (d)(3); and Rule 20.4 Subsections (b)(2), (b)(3), (d)(1)(iii), (d)(2)(i)(B), (d)(2)(iv), (d)(2)(v)(B), (d)(3) and (d)(5). On October 14, 2016, the EPA determined that the submittal of Rules VerDate Sep<11>2014 16:25 Jun 22, 2018 Jkt 244001 20.1, 20.2, 20.3, 20.4 and 20.6 met the completeness criteria in 40 CFR part 51 PO 00000 Frm 00019 Fmt 4702 Sfmt 4702 appendix V, which must be met before formal EPA review. On September 27, E:\FR\FM\25JNP1.SGM 25JNP1

Agencies

[Federal Register Volume 83, Number 122 (Monday, June 25, 2018)]
[Proposed Rules]
[Pages 29479-29483]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-13523]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0479; Product Identifier 2016-NE-23-AD]
RIN 2120-AA64


Airworthiness Directives; Honeywell International Inc. Turboprop 
and Turboshaft Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede Airworthiness Directive (AD) 2018-02-
14, which applies to certain Honeywell International Inc. (Honeywell) 
TPE331 turboprop and TSE331 turboshaft engines. AD 2018-02-14 requires 
inspection of the affected combustion chamber case assembly, 
replacement of those assemblies found cracked, and removal of affected 
assemblies on certain TPE331 and TSE331 engines. Since we issued AD 
2018-02-14, we received comments to revise the applicability of that AD 
to include the TPE331-12B engine model, correct certain TPE engine 
model typographical errors, and to allow certain weld repair 
procedures. This proposed AD would expand the applicability of AD 2018-
02-14 to include the TPE331-12B engine model, correct certain engine 
model typographical errors, and allow certain weld repair procedures 
after approval. We are proposing this AD to address the unsafe 
condition on these products.

DATES: We must receive comments on this proposed AD by August 9, 2018.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, contact Honeywell 
International Inc., 111 S 34th Street, Phoenix, AZ 85034-2802; phone: 
800-601-3099; internet: https://myaerospace.honeywell.com/wps/portal. 
You may view this service information at the FAA, Engine and Propeller 
Standards Branch, 1200 District Avenue, Burlington, MA. For information 
on the availability of this material at the FAA, call 781-238-7759.

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-2018-
0479; 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 NPRM, the regulatory evaluation, any comments received, and other 
information. The street address for Docket Operations (phone: 800-647-
5527) is listed above. Comments will be available in the AD docket 
shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Joseph Costa, Aerospace Engineer, Los 
Angeles ACO Branch, FAA, 3960 Paramount Blvd., Lakewood, CA 90712-4137; 
phone: 562-627-5246; fax: 562-627-5210; email: [email protected].

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-2018-0479; 
Product Identifier 2016-NE-23-AD'' at the beginning of your comments. 
We specifically invite comments on the overall regulatory, economic, 
environmental, and energy

[[Page 29480]]

aspects of this NPRM. We will consider all comments received by the 
closing date and may amend this NPRM because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    We issued AD 2018-02-14, Amendment 39-19167 (83 FR 3263, January 
24, 2018), (``AD 2018-02-14''), for certain Honeywell TPE331 turboprop 
and TSE331 turboshaft engines. AD 2018-02-14 requires inspection of the 
affected combustion chamber case assembly, replacement of those 
assemblies found cracked, and removal of affected assemblies on certain 
TPE331 and TSE331 engines. AD 2018-02-14 resulted from reports that 
combustion chamber case assemblies have cracked and ruptured. We issued 
AD 2018-02-14 to prevent failure of the combustion chamber case 
assembly.

Actions Since AD 2018-02-14 Was Issued

    Since we issued AD 2018-02-14, we determined the need to revise 
sections of that AD. We received comments indicating that the TPE331-
12B engine model was inadvertently omitted from that AD and that the 
TPE331-43-A, -43-BL, -47-A, -55-B, and -61-A engine models included 
typographical errors. We also received comments to revise the 
Compliance section, which disallows weld repairs on any combustion 
chamber case assemblies that are affected by that AD. We determined 
that allowing weld repair procedures of certain combustion chamber case 
assemblies with lower stresses may be accomplished if these procedures 
are approved by the Manager, Los Angeles ACO Branch.

Related Service Information Under 1 CFR Part 51

    We reviewed Honeywell Service Bulletin (SB) TPE331-72-2178, 
Revision 0, dated May 3, 2011 and Honeywell SB TPE331-72-2179, Revision 
0, dated May 3, 2011. Honeywell SB TPE331-72-2178, Revision 0, 
describes procedures for inspection and removal of the affected 
combustion chamber case assemblies installed on all affected engines 
except for the TPE331-12B engine model. Honeywell SB TPE331-72-2179, 
Revision 0, describes procedures for inspection and removal of the 
affected combustion chamber case assemblies installed on the TPE331-12B 
engine model. 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

    We reviewed Honeywell SBs TPE331-72-2228, Revision 0, dated June 
12, 2014; TPE331-72-2230, Revision 0, dated June 19, 2014; TPE331-72-
2218, Revision 2, dated February 18, 2017; TPE331-72-2244, Revision 2, 
dated March 20 2017; TPE331-72-2235, Revision 2, dated February 18, 
2017; TPE331-72-2281, Revision 0, dated July 22, 2016; TPE331-72-2294, 
Revision 0, dated December 22, 2016; TPE331-72-2231, Revision 1, dated 
August 1, 2017; and TSE331-72-2245, Revision 0, dated November 11, 
2016. These SBs provide guidance on replacement of the affected 
combustion chamber case assemblies.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD would retain all of the requirements of AD 2018-
02-14. This proposed AD would revise the Applicability to include the 
TPE331-12B engine model and to correct references to the TPE331-43-A, -
43-BL, -47-A, -55-B, and -61-A engine models. This proposed AD would 
also allow weld repair procedures to the applicable combustion chamber 
case assemblies provided those procedures are approved by the Manager, 
Los Angeles ACO Branch.

Costs of Compliance

    We estimate that this AD affects 5,644 engines installed on 
airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:


                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                   Cost on U.S.
              Action                  Labor cost       Parts cost         Cost per product          operators
----------------------------------------------------------------------------------------------------------------
On-wing inspection...............  1 work-hour x                 $0  $85 per inspection........  $479,740 per
                                    $85 per hour =                                                inspection
                                    $85.                                                          cycle.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements 
that would be required based on the results of the proposed inspection. 
We estimate that 158 engines will need this replacement during the 
first year of inspection.

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replacement of the combustion chamber case      1 work-hour x $85 per hour = $85         $15,000         $15,085
 assembly.
----------------------------------------------------------------------------------------------------------------

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

[[Page 29481]]

products identified in this rulemaking action.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to engines, propellers, and 
associated appliances to the Manager, Engine and Propeller Standards 
Branch, Policy and Innovation Division.

Regulatory Findings

    We have 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 that the proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13   [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2018-02-14, Amendment 39-19167 (83 FR 3263, January 24, 2018), and 
adding the following new AD:

Honeywell International Inc. (Type Certificate previously held by 
AlliedSignal Inc., Garrett Engine Division; Garrett Turbine Engine 
Company; and AiResearch Manufacturing Company of Arizona): Docket 
No. FAA-2018-0479; Product Identifier 2016-NE-23-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by August 9, 
2018.

(b) Affected ADs

    This AD replaces AD 2018-02-14, Amendment 39-19167 (83 FR 3263, 
January 24, 2018).

(c) Applicability

    This AD applies to Honeywell International Inc. (Honeywell) 
TPE331-1, -2, -2UA, -3U, -3UW, -5, -5A, -5AB, -5B, -6, -6A, -8, -10, 
-10AV, -10GP, -10GT, -10N, -10P, -10R, -10T, -10U, -10UA, -10UF, -
10UG, -10UGR, -10UR, and -11U, -12B, -12JR, -12UA, -12UAR, -12UHR, -
25AA, -25AB, -25DA, -25DB, -25FA, -43-A, -43-B, -47-A, -55-B, and -
61-A turboprop engine models, including those engine models with a -
L stamped after the model number (for example, -43-BL); and TSE331-
3U turboshaft engine models with combustion chamber case assemblies, 
part numbers (P/Ns) 869728-x, 893973-x, 3101668-x, and 3102613-x, 
where ``x'' denotes any dash number, installed.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7240, Turbine Engine 
Combustion Section.

(e) Unsafe Condition

    This AD was prompted by reports that combustion chamber case 
assemblies have cracked and ruptured. We are issuing this AD to 
prevent failure of the combustion chamber case assembly. The unsafe 
condition, if not addressed, could result in failure of the 
combustion chamber case assembly, in-flight shutdown, and reduced 
control of the airplane.

(f) Compliance

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

(g) Required Actions

    (1) For all affected engines:
    (i) Inspect all accessible areas of the combustion chamber case 
assembly, focusing on the weld joints, before accumulating 450 hours 
time in service (TIS) since last fuel nozzle inspection or within 50 
hours TIS after the effective date of this AD, whichever occurs 
later.
    (ii) Perform the inspection in accordance with the 
Accomplishment Instructions, paragraphs 3.B.(1) through 3.B.(2), in 
Honeywell Service Bulletin (SB) TPE331-72-2178, Revision 0, dated 
May 3, 2011, or SB TPE331-72-2179, Revision 0, dated May 3, 2011, as 
applicable to the affected engine model.
    (iii) Thereafter, repeat this inspection during scheduled fuel 
nozzle inspections at intervals not to exceed 450 hours TIS since 
the last fuel nozzle inspection.
    (2) For TPE331-3U, -3UW, -5, -5A, -5AB, -5B, -6, and -6A engine 
models with combustion chamber case assemblies, P/Ns 869728-1, 
869728-3, or 893973-5, installed, and without the one-piece bleed 
pad with P3 boss; and for TPE331-1, -2, and -2UA engine models 
modified by National Flight Services, Inc., supplemental type 
certificate (STC) SE383CH, remove the combustion chamber case 
assembly from service at the next removal of the combustion chamber 
case assembly from the engine, not to exceed 3,700 hours TIS since 
last hot section inspection.
    (3) After the effective date of this AD, do not weld repair the 
applicable combustion chamber case assemblies unless the weld repair 
procedures are approved by the Manager, Los Angeles ACO Branch, and 
that approval specifically refers to this AD.

(h) Definition

    (1) TPE331 engines modified by STC SE383CH may be defined as the 
``Super 1'' and ``Super 2'' for the compressor modification of the 
TPE331-1 and the TPE331-2, -2U, and -2UA engine models, 
respectively.
    (2) Figures 1 and 2 to paragraph (h) of this AD illustrate the 
appearance of combustion chamber case assembly, P/N 893973-5, 
without and with, respectively, the one-piece bleed pad with the P3 
boss.
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[GRAPHIC] [TIFF OMITTED] TP25JN18.006

[GRAPHIC] [TIFF OMITTED] TP25JN18.007

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(i) Installation Prohibition

    After the effective date of this AD, do not install a combustion 
chamber case assembly, P/N 869728-1, 869728-3, or 893973-5, in 
TPE331-3U, -3UW, -5, -5A, -5AB, -5B, -6, and -6A engine models or in 
TPE331-1, -2, and -2UA engine models modified by National Flight 
Services, Inc., STC SE383CH, unless the combustion chamber case 
assembly has a one-piece bleed pad with P3 boss.

(j) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles 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 (k)(1) of this AD. Information 
may be emailed to: [email protected].
    (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.

(k) Related Information

    (1) For more information about this AD, contact Joseph Costa, 
Aerospace Engineer, Los Angeles ACO Branch, FAA, 3960 Paramount 
Blvd., Lakewood, CA 90712-4137; phone: 562-627-5246; fax: 562-627-
5210; email: [email protected].
    (2) For service information identified in this AD, contact AD, 
contact Honeywell International Inc., 111 S 34th Street, Phoenix, AZ 
85034-2802; phone: 800-601-3099; internet: https://
myaerospace.honeywell

[[Page 29483]]

.com/wps/portal. You may view this service information at the FAA, 
Engine and Propeller Standards Branch, 1200 District Avenue, 
Burlington, MA. For information on the availability of this material 
at the FAA, call 781-238-7759.

    Issued in Burlington, Massachusetts, on June 19, 2018.
Robert J. Ganley,
Manager, Engine and Propeller Standards Branch, Aircraft Certification 
Service.
[FR Doc. 2018-13523 Filed 6-22-18; 8:45 am]
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