Airworthiness Directives; Honeywell International Inc. Turboprop Engines, 15261-15266 [2014-06029]

Download as PDF Federal Register / Vol. 79, No. 53 / Wednesday, March 19, 2014 / Proposed Rules approval of a transaction, activity, or item. § 1211.4 Non-Objection Letters. (a) Authority. The Deputy Directors for Enterprise Regulation and for Federal Home Loan Bank Regulation, or their designees, may, in their discretion, issue to an Enterprise or to a Bank or the Office of Finance, respectively, a NonObjection Letter stating that FHFA does not object to a proposed transaction or activity for supervisory, regulatory, or policy reasons. The Director reserves the right to modify, rescind, or supersede a Non-Objection Letter, with such action being effective only on a prospective basis. (b) Requests. A regulated entity or the Office of Finance may request a NonObjection Letter in accordance with § 1211.6. § 1211.5 Regulatory Interpretations. (a) Authority. The General Counsel may, in his or her discretion, issue a Regulatory Interpretation to a regulated entity or the Office of Finance, providing guidance with respect to the application of any applicable statute, rule, regulation, or order to a proposed transaction or activity. The Director reserves the right to modify, rescind, or supersede a Regulatory Interpretation, with such action being effective only on a prospective basis. (b) Requests. A regulated entity or the Office of Finance may request a Regulatory Interpretation in accordance with § 1211.6. wreier-aviles on DSK5TPTVN1PROD with PROPOSALS § 1211.6 Submission requirements. Applications for a Waiver or Approval and requests for a Non-Objection Letter or Regulatory Interpretation shall comply with the requirements of this section and shall pertain to regulatory matters relating to the Banks or Enterprises, and not to conservatorship matters. (a) Filing. Each application or request shall be in writing. A Bank or the Office of Finance shall submit its filing to the Deputy Director for the Division of Federal Home Loan Bank Regulation, and an Enterprise shall submit its filing to the Deputy Director for Enterprise Regulation. Applications for regulatory interpretations shall be submitted also to the General Counsel. (b) Authorization. An application for a Waiver or Approval and a request for a Non-Objection Letter or Regulatory Interpretation shall be signed by the president of the regulated entity or by the chairperson of the board of directors of the Office of Finance, as appropriate. Applications for Waiver or Approval also shall be accompanied by a VerDate Mar<15>2010 15:37 Mar 18, 2014 Jkt 232001 resolution of the board of directors concurring in the substance and authorizing the filing of the application. (c) Information requirements. Each application or request shall contain: (1) The name of the requester, and the name, title, business address, telephone number, and business electronic mail address, if any, of the official filing the application or request on its behalf; (2) The name, business address, telephone number, and business electronic mail address, if any, of a contact person from whom FHFA staff may seek additional information if necessary; (3) The section numbers of the particular provisions of the applicable statutes or rules, regulations, policies, or orders to which the application or request relates; (4) Identification of the determination or relief requested, including any alternative relief requested if the primary relief is denied, and a clear statement of why such relief is needed; (5) A statement of the particular facts and circumstances giving rise to the application or request and identifying all relevant legal and factual issues; (6) References to all other relevant authorities, including the Authorizing Statutes, Safety and Soundness Act, FHFA rules, regulations, policies, and orders, judicial decisions, administrative decisions, relevant statutory interpretations, and policy statements; (7) References to any Waivers, NonObjection Letters, Approvals, or Regulatory Interpretations issued in the past in response to circumstances similar to those surrounding the request or application; (8) For any application or request involving interpretation of the Authorizing Statutes, Safety and Soundness Act, or FHFA regulations, a reasoned opinion of counsel supporting the relief or interpretation sought and distinguishing any adverse authority; (9) Any other non-duplicative, relevant supporting documentation; and (10) A certification by a person with knowledge of the facts that the representations made in the application or request are accurate and complete. The following form of certification is sufficient for this purpose: ‘‘I hereby certify that the statements contained in the submission are true and complete to the best of my knowledge. [Name and Title].’’ (d) Exceptions. In any given matter or class of matters, the Director, the Deputy Director for Federal Home Loan Bank Regulation, the Deputy Director for Enterprise Regulation, or the General Counsel, as appropriate, may accept an PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 15261 application or request that does not comply with the requirements of this section, for supervisory reasons or administrative efficiency. (e) Withdrawal. Once filed, an application or request may be withdrawn only upon written request, and only if FHFA has not yet acted on the application or request. Dated: March 13, 2014. Melvin L. Watt, Director, Federal Housing Finance Agency. [FR Doc. 2014–06033 Filed 3–18–14; 8:45 am] BILLING CODE 8070–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–23706; Directorate Identifier 2006–NE–03–AD] RIN 2120–AA64 Airworthiness Directives; Honeywell International Inc. Turboprop Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to supersede airworthiness directive (AD) 2006–15– 08, which applies to all Honeywell International Inc. TPE331–1, –2, –2UA, –3U, –3UW, –5, –5A, –5AB, –5B, –6, –6A, –10, –10AV, –10GP, –10GT, –10P, –10R, –10T, –10U, –10UA, –10UF, –10UG, –10UGR, –10UR, –11U, –12JR, –12UA, –12UAR, and –12UHR turboprop engines with certain part numbers (P/Ns) of Woodward fuel control unit (FCU) assemblies, installed. AD 2006–15–08 currently requires initial and repetitive dimensional inspections of the fuel control drive spline for wear, and replacement of the FCU and fuel pump. Since we issued AD 2006–15–08, we determined that additional FCU assembly P/Ns are affected, the compliance deadline and assembly replacement after removal for cause or overhaul are no longer required, and that cautionary engine operating information must be observed. This proposed AD was prompted by reports of loss of the fuel control drive, leading to engine overspeed, overtorque, overtemperature, uncontained rotor failure, and asymmetric thrust in multiengine airplanes. This proposed AD would require initial and repetitive dimensional inspections of the affected fuel control drive splines, and insertion of certain airplane operating procedures into the applicable flight manuals. We SUMMARY: E:\FR\FM\19MRP1.SGM 19MRP1 15262 Federal Register / Vol. 79, No. 53 / Wednesday, March 19, 2014 / Proposed Rules wreier-aviles on DSK5TPTVN1PROD with PROPOSALS are proposing this AD to prevent failure of the fuel control drive that could result in damage to the engine and airplane. DATES: We must receive comments on this proposed AD by May 19, 2014. 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 proposed AD, contact Honeywell International Inc., 111 S 34th Street, Phoenix, AZ 85034–2802; phone: 800– 601–3099; Internet: https:// myaerospace.honeywell.com/wps/ portal/!ut/. You may view this service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. 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–2006– 23706; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received and other information. The street address for the Docket Office (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Joseph Costa, Aerospace Engineer, Los Angeles Aircraft Certification Office, FAA, Transport Airplane Directorate, 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 VerDate Mar<15>2010 15:37 Mar 18, 2014 Jkt 232001 ADDRESSES section. Include ‘‘Docket No. FAA–2006–23706; Directorate Identifier 2006–NE–03–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD 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 On July 14, 2006, we issued AD 2006– 15–08, Amendment 39–14688 (71 FR 41121, July 20, 2006), for all Honeywell International Inc. TPE331 series turboprop engines with certain P/Ns of Woodward FCU assemblies installed. AD 2006–15–08 requires initial and repetitive dimensional inspections of the fuel control drive spline for wear that might cause replacement of the FCU and/or fuel pump assemblies. AD 2006–15–08 also requires the replacement of the FCU assembly when the FCU is removed for cause or overhaul, but not later than December 31, 2012. AD 2006–15–08 was prompted by fuel control drive failures that resulted in a rapid, uncommanded, uncontrolled increase in fuel flow and overspeed of the engine during ground start. We issued AD 2006–15–08 to prevent failure of the fuel control drive, destructive overspeed that could result in uncontained rotor failure and damage to the airplane. Actions Since AD 2006–15–08 Was Issued Since we issued AD 2006–15–08, Amendment 39–14688 (71 FR 41121, July 20, 2006), we determined that additional FCU assembly P/Ns are affected, certain repetitive fuel control drive inspections are necessary, and that additional flight crew emergency procedures and warnings are required. The warnings are required to inform flight crew of the probable engine response(s) following a loss of drive between the engine driven fuel pump and fuel control governor system. These engine responses are dependent on the phase of operation (ground engine start, ground or flight operations). Also since we issued AD 2006–15–08, Amendment 39–14688 (71 FR 41121, July 20, 2006), we reviewed the inservice trends and engine in-flight shutdowns (IFSDs) caused by the PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 modified FCU and determined that the IFSD rate had not improved and the installation of the modified FCU assembly was not required. 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 require continued dimensional spline inspections required by AD 2006–15– 08, add new P/Ns of affected FCU assemblies that require dimensional spline inspections. This proposed AD would require insertion of uncommanded engine overspeed procedures into the Airplane Flight Manual, Pilot Operating Handbook, and or Manufacturer’s Operating Manual. This proposed AD would retain some but not all requirements of AD 2006– 15–08, (71 FR 41121, July 20, 2006), but would no longer require the installation of a modified FCU. Costs of Compliance We estimate that this proposed AD would affect 2,250 engines installed on airplanes of U.S. registry. We estimate that it would take 8 hours per engine to perform an FCU inspection, and three inspections will be required over the life of the product. The average labor rate is $85 per hour. Due to the more frequent inspections proposed by this AD, we estimate 10% of affected engines would require FCU assembly stub shaft replacement, fuel pump or fuel control repair. We also estimate that repairs should not exceed $10,000 per engine. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $6,307,044. 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 E:\FR\FM\19MRP1.SGM 19MRP1 Federal Register / Vol. 79, No. 53 / Wednesday, March 19, 2014 / Proposed Rules 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. (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. 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 to the extent that it justifies making a regulatory distinction, and 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. Amend § 39.13 by removing airworthiness directive (AD) 2006–15– 08, Amendment 39–14688 (71 FR ■ 15263 41121, July 20, 2006), and adding the following new AD: Honeywell International Inc.: Docket No. FAA–2006–23706; Directorate Identifier 2006–NE–03–AD. (a) Comments Due Date The FAA must receive comments on this AD action by May 19, 2014. (b) Affected ADs This AD supersedes AD 2006–15–08, Amendment 39–14688 (71 FR 41121, July 20, 2006). (c) Applicability This AD applies to all Honeywell International Inc. TPE331–1, –2, –2UA, –3U, –3UW, –5, –5A, –5AB, –5B, –6, –6A, –10, –10AV, –10GP, –10GT, –10P, –10R, –10T, –10U, –10UA, –10UF, –10UG, –10UGR, –10UR, –11U, –12JR, –12UA, –12UAR, and –12UHR turboprop engines with the part numbers (P/Ns) of Woodward fuel control unit (FCU) assemblies listed in Table 1 to paragraph (c) of this AD, installed. TABLE 1 TO PARAGRAPH (C)—AFFECTED FCU ASSEMBLY P/NS Group # Engine FCU Assembly P/Ns 1 ......................... TPE331–1, –2, and –2UA ....................... 2* ....................... 3 ......................... TPE331–1, –2, and –2UA ....................... TPE331–3U, –3UW, –5, –5A, –5AB, –5B, –6, –6A, –l0AV, –10GP, –10GT, –l0P, and –l0T. TPE331–3U, –3UW, –5, –5A, –5AB, –5B, –6, –6A, –l0AV, –10GP, –10GT, –l0P, and –l0T. TPE331–10, –l0R, –10U, –10UA, –10UF, –10UG, –10UGR, –10UR, –11U, –12JR, –12UA, –12UAR, and –12UHR. P/N 869199–13, –20, –21, –22, –23, –24, –25, –26, –27, –28, –29, –31, –32, –33, –34, and –35. P/N 869199–9, –10, –11, –12, –14, –16, –17, and –18. P/N 893561–7, –8, –9, –10, –11, –14, –15, –16, –20, –26, –27, and –29; or P/N 897770–1, –3, –7, –9, –10, –11, –12, –14, –15, –16, –25, –26, and –28. 4* ....................... 5 ......................... P/N 893561–4, –5, –12, and –13 or P/N 897770–5, –8, and –13. P/N 897375–2, –3, –4, –5, –8, –9, –10, –11, –12, –13, –14, –15, –16, –17, –19, –21, –24, –25, –26, and –27; or P/N 897780–1, –2, –3, –4, –5, –6, –7, –8, –9, –10, –11, –14, –15, –16, –17, –18, –19, –20, –21, –22, –23, –24, –25, –26, –27, –30, –32, –34, –36, –37, and –38; or P/N 893561–17, –18, and –19. * New/added FCU assembly P/Ns (d) Unsafe Condition This AD was prompted by reports of loss of the fuel control drive, leading to engine overspeed and engine failure. We are issuing this AD to prevent damage to the engine, and damage to the airplane. wreier-aviles on DSK5TPTVN1PROD with PROPOSALS (e) Compliance Comply with this AD within the compliance times specified, unless already done. (1) Inspection of Engines with FCU Assembly P/Ns in Groups 2 and 4 For FCU assembly P/Ns in Groups 2 and 4 listed in Table 1 to paragraph (c) of this AD, at the next scheduled inspection of the fuel control drive, or within 500 hours-in-service VerDate Mar<15>2010 15:37 Mar 18, 2014 Jkt 232001 (HIS) after the effective date of this AD, whichever occurs first: (i) Inspect the fuel control drive spline for wear. (ii) Thereafter, re-inspect the fuel control drive within 1,000 HIS since-last-inspection (SLI) of the fuel control drive. (B) If on the effective date of this AD the FCU assembly has fewer than 950 HIS SLI, inspect the fuel control drive spline for wear before reaching 1,000 HIS. (ii) Thereafter, re-inspect the fuel control drive spline for wear within every 1,000 HIS SLI. (2) Inspection of Engines with FCU Assembly P/Ns in Groups 1, 3, and 5 (i) For FCU assembly P/Ns in Groups 1, 3, or 5 listed in Table 1 to paragraph (c) of this AD: (A) If on the effective date of this AD the FCU assembly has 950 or more HIS SLI, inspect the fuel control drive spline for wear within 50 HIS from the effective date of this AD. (3) Airplane Operating Procedures PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 Within 60 days after the effective date of this AD, insert the information in Figure 1 to paragraph (e) of this AD, into the Emergency Procedures Section of the Airplane Flight Manual (AFM), Pilot Operating Handbook (POH), and the Manufacturer’s Operating Manual (MOM). BILLING CODE 4910–13–P E:\FR\FM\19MRP1.SGM 19MRP1 VerDate Mar<15>2010 Federal Register / Vol. 79, No. 53 / Wednesday, March 19, 2014 / Proposed Rules 15:37 Mar 18, 2014 Jkt 232001 PO 00000 Frm 00008 Fmt 4702 Sfmt 4725 E:\FR\FM\19MRP1.SGM 19MRP1 EP19MR14.006</GPH> wreier-aviles on DSK5TPTVN1PROD with PROPOSALS 15264 BILLING CODE 4910–13–C wreier-aviles on DSK5TPTVN1PROD with PROPOSALS (f) Optional Terminating Action Replacing the affected FCU assembly with an FCU assembly P/N not listed in this AD is terminating action for the initial and repetitive inspections required by this AD, and for inserting the information in Figure 1 to paragraph (e) of this AD into the AFM, POH, and MOM. (g) Definitions For the purposes of this AD: (1) The ‘‘fuel control drive’’ is a series of mating splines located between the fuel pump and fuel control governor. VerDate Mar<15>2010 15:37 Mar 18, 2014 Jkt 232001 (2) The fuel control drive consists of four drive splines: the fuel pump internal spline, the fuel control external ‘‘quill shaft’’ spline, and the stub shaft internal and external splines. (h) Alternative Methods of Compliance (AMOCs) The Manager, Los Angeles Aircraft Certification Office, FAA, may approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 to make your request. (i) Related Information (1) For more information about this AD, contact Joseph Costa, Aerospace Engineer, PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 15265 Los Angeles Aircraft Certification Office, FAA, Transport Airplane Directorate, 3960 Paramount Blvd., Lakewood, CA 90712– 4137; phone: 562–627–5246; fax: 562–627– 5210; email: joseph.costa@faa.gov. (2) Honeywell International Inc., AFM, POH, and MOM, which are not incorporated by reference in this AD, can be obtained from Honeywell International Inc., using the contact information in paragraph (i)(4) of this AD. (3) Information pertaining to operating recommendations for affected engines after a fuel control drive failure is contained in Honeywell International Inc., Operating Information Letter (OIL) OI331–12R6, dated E:\FR\FM\19MRP1.SGM 19MRP1 EP19MR14.007</GPH> Federal Register / Vol. 79, No. 53 / Wednesday, March 19, 2014 / Proposed Rules 15266 Federal Register / Vol. 79, No. 53 / Wednesday, March 19, 2014 / Proposed Rules May 26, 2009, for multi-engine airplanes; and in OIL OI331–18R4, dated May 26, 2009, for single-engine airplanes. Information on fuel control drive spline inspection can be found in Section 72–00–00 of the applicable TPE331 maintenance manuals. These Honeywell International Inc., OILs and the TPE331 maintenance manuals, which are not incorporated by reference in this AD, can be obtained from Honeywell International Inc., using the contact information in paragraph (i)(4) of this AD. (4) For service information identified in this AD, contact Honeywell International Inc., 111 S. 34th Street, Phoenix, AZ 85034– 2802; Internet: https:// myaerospace.honeywell.com/wps/portal/!ut; phone: 800–601–3099. (5) You may view this service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. DEPARTMENT OF TRANSPORTATION You may send comments 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: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Airbus SAS, Airworthiness Office—EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Federal Aviation Administration Examining the AD Docket Issued in Burlington, Massachusetts, on March 10, 2014. Colleen M. D’Alessandro, Assistant Directorate Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2014–06029 Filed 3–18–14; 8:45 am] BILLING CODE 4910–13–P 14 CFR Part 39 [Docket No. FAA–2014–0143; Directorate Identifier 2012–NM–113–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for all Airbus Model A300 B4–603, B4–620, B4–622, B4–605R, B4–622R; F4–605R, F4–622R and C4–605R variant F airplanes. This proposed AD was prompted by reports of cracks in the frame base fittings connecting the frame lower positions to the center wing box. This proposed AD would require repetitive detailed inspections of the lower frame fittings, related investigative actions, and corrective actions if necessary. We are proposing this AD to detect and correct cracking on the lower frame fittings, which could reduce the structural integrity of the airplane. wreier-aviles on DSK5TPTVN1PROD with PROPOSALS SUMMARY: We must receive comments on this proposed AD by May 5, 2014. DATES: VerDate Mar<15>2010 15:37 Mar 18, 2014 Jkt 232001 ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0143; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone (425) 227–2125; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2014–0143; Directorate Identifier 2012–NM–113–AD’’ at the beginning of your comments. We specifically invite PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion The European Aviation Safety Agency (EASA), which is the technical agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2012–0103, dated June 11, 2012 (corrected June 19, 2012) (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: During maintenance checks, cracks were discovered by A300 and A300–600 operators in the frame [base] feet fittings, connecting the frame lower positions to the centre wing box. These occurrences were followed by a dedicated sampling inspection programme carried out by Airbus. During this sampling programme, 22 A300–600 aeroplanes were found with cracks on the lower fittings of frame 44 to frame 46 left hand (LH) and right hand (RH) side. This condition, if not detected and corrected, could affect the structural integrity of the fuselage of all aeroplanes operated up to the extended service goal (ESG). For the reasons described above, this [EASA] AD requires repetitive detailed visual inspections [for discrepancies (cracking)] of the lower frame fittings between frame 41 and frame 46 and, depending on findings, accomplishment of a repair. This [EASA] AD has been republished to correct Note 2 in Appendix 1. Related investigative actions include doing a rotating probe inspection for cracking of the crack stop hole. Corrective actions include repairing or replacing cracking and cracked base fittings. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov by searching for and locating it in Docket No. FAA– 2014–0143. Relevant Service Information Airbus has issued Mandatory Service Bulletin A300–53–6111, Revision 05, including Appendix 01, dated January 28, 2013. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. E:\FR\FM\19MRP1.SGM 19MRP1

Agencies

[Federal Register Volume 79, Number 53 (Wednesday, March 19, 2014)]
[Proposed Rules]
[Pages 15261-15266]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-06029]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-23706; Directorate Identifier 2006-NE-03-AD]
RIN 2120-AA64


Airworthiness Directives; Honeywell International Inc. Turboprop 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede airworthiness directive (AD) 2006-15-
08, which applies to all Honeywell International Inc. TPE331-1, -2, -
2UA, -3U, -3UW, -5, -5A, -5AB, -5B, -6, -6A, -10, -10AV, -10GP, -10GT, 
-10P, -10R, -10T, -10U, -10UA, -10UF, -10UG, -10UGR, -10UR, -11U, -
12JR, -12UA, -12UAR, and -12UHR turboprop engines with certain part 
numbers (P/Ns) of Woodward fuel control unit (FCU) assemblies, 
installed. AD 2006-15-08 currently requires initial and repetitive 
dimensional inspections of the fuel control drive spline for wear, and 
replacement of the FCU and fuel pump. Since we issued AD 2006-15-08, we 
determined that additional FCU assembly P/Ns are affected, the 
compliance deadline and assembly replacement after removal for cause or 
overhaul are no longer required, and that cautionary engine operating 
information must be observed. This proposed AD was prompted by reports 
of loss of the fuel control drive, leading to engine overspeed, 
overtorque, overtemperature, uncontained rotor failure, and asymmetric 
thrust in multi-engine airplanes. This proposed AD would require 
initial and repetitive dimensional inspections of the affected fuel 
control drive splines, and insertion of certain airplane operating 
procedures into the applicable flight manuals. We

[[Page 15262]]

are proposing this AD to prevent failure of the fuel control drive that 
could result in damage to the engine and airplane.

DATES: We must receive comments on this proposed AD by May 19, 2014.

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 proposed AD, contact 
Honeywell International Inc., 111 S 34th Street, Phoenix, AZ 85034-
2802; phone: 800-601-3099; Internet: https://myaerospace.honeywell.com/wps/portal/!ut/. You may view this service information at the FAA, 
Engine & Propeller Directorate, 12 New England Executive Park, 
Burlington, MA. For information on the availability of this material at 
the FAA, call 781-238-7125.

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-2006-
23706; or in person at the Docket Management Facility between 9 a.m. 
and 5 p.m., Monday through Friday, except Federal holidays. The AD 
docket contains this proposed AD, the regulatory evaluation, any 
comments received and other information. The street address for the 
Docket Office (phone: 800-647-5527) is in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Joseph Costa, Aerospace Engineer, Los 
Angeles Aircraft Certification Office, FAA, Transport Airplane 
Directorate, 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-2006-
23706; Directorate Identifier 2006-NE-03-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD 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

    On July 14, 2006, we issued AD 2006-15-08, Amendment 39-14688 (71 
FR 41121, July 20, 2006), for all Honeywell International Inc. TPE331 
series turboprop engines with certain P/Ns of Woodward FCU assemblies 
installed. AD 2006-15-08 requires initial and repetitive dimensional 
inspections of the fuel control drive spline for wear that might cause 
replacement of the FCU and/or fuel pump assemblies. AD 2006-15-08 also 
requires the replacement of the FCU assembly when the FCU is removed 
for cause or overhaul, but not later than December 31, 2012. AD 2006-
15-08 was prompted by fuel control drive failures that resulted in a 
rapid, uncommanded, uncontrolled increase in fuel flow and overspeed of 
the engine during ground start. We issued AD 2006-15-08 to prevent 
failure of the fuel control drive, destructive overspeed that could 
result in uncontained rotor failure and damage to the airplane.

Actions Since AD 2006-15-08 Was Issued

    Since we issued AD 2006-15-08, Amendment 39-14688 (71 FR 41121, 
July 20, 2006), we determined that additional FCU assembly P/Ns are 
affected, certain repetitive fuel control drive inspections are 
necessary, and that additional flight crew emergency procedures and 
warnings are required. The warnings are required to inform flight crew 
of the probable engine response(s) following a loss of drive between 
the engine driven fuel pump and fuel control governor system. These 
engine responses are dependent on the phase of operation (ground engine 
start, ground or flight operations).
    Also since we issued AD 2006-15-08, Amendment 39-14688 (71 FR 
41121, July 20, 2006), we reviewed the in-service trends and engine in-
flight shutdowns (IFSDs) caused by the modified FCU and determined that 
the IFSD rate had not improved and the installation of the modified FCU 
assembly was not required.

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 require continued dimensional spline 
inspections required by AD 2006-15-08, add new P/Ns of affected FCU 
assemblies that require dimensional spline inspections. This proposed 
AD would require insertion of uncommanded engine overspeed procedures 
into the Airplane Flight Manual, Pilot Operating Handbook, and or 
Manufacturer's Operating Manual. This proposed AD would retain some but 
not all requirements of AD 2006-15-08, (71 FR 41121, July 20, 2006), 
but would no longer require the installation of a modified FCU.

Costs of Compliance

    We estimate that this proposed AD would affect 2,250 engines 
installed on airplanes of U.S. registry. We estimate that it would take 
8 hours per engine to perform an FCU inspection, and three inspections 
will be required over the life of the product. The average labor rate 
is $85 per hour. Due to the more frequent inspections proposed by this 
AD, we estimate 10% of affected engines would require FCU assembly stub 
shaft replacement, fuel pump or fuel control repair. We also estimate 
that repairs should not exceed $10,000 per engine. Based on these 
figures, we estimate the cost of this proposed AD on U.S. operators to 
be $6,307,044.

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

[[Page 15263]]

is within the scope of that authority because it addresses an unsafe 
condition that is likely to exist or develop on products identified in 
this rulemaking action.

Regulatory Findings

    We 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 to the extent 
that it justifies making a regulatory distinction, 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. Amend Sec.  39.13 by removing airworthiness directive (AD) 2006-15-
08, Amendment 39-14688 (71 FR 41121, July 20, 2006), and adding the 
following new AD:

Honeywell International Inc.: Docket No. FAA-2006-23706; Directorate 
Identifier 2006-NE-03-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by May 19, 2014.

(b) Affected ADs

    This AD supersedes AD 2006-15-08, Amendment 39-14688 (71 FR 
41121, July 20, 2006).

(c) Applicability

    This AD applies to all Honeywell International Inc. TPE331-1, -
2, -2UA, -3U, -3UW, -5, -5A, -5AB, -5B, -6, -6A, -10, -10AV, -10GP, 
-10GT, -10P, -10R, -10T, -10U, -10UA, -10UF, -10UG, -10UGR, -10UR, -
11U, -12JR, -12UA, -12UAR, and -12UHR turboprop engines with the 
part numbers (P/Ns) of Woodward fuel control unit (FCU) assemblies 
listed in Table 1 to paragraph (c) of this AD, installed.

          Table 1 to Paragraph (c)--Affected FCU Assembly P/Ns
------------------------------------------------------------------------
     Group               Engine            FCU Assembly P/Ns
------------------------------------------------------------------------
1........................  TPE331-1, -2, and -  P/N 869199-13, -20, -21,
                            2UA.                 -22, -23, -24, -25, -
                                                 26, -27, -28, -29, -31,
                                                 -32, -33, -34, and -35.
2*.......................  TPE331-1, -2, and -  P/N 869199-9, -10, -11,
                            2UA.                 12, -14, -16, -17, and
                                                 18.
3........................  TPE331-3U, -3UW, -   P/N 893561-7, -8, -9, -
                            5, -5A, -5AB, -5B,   10, -11, -14, -15, -16,
                            -6, -6A, -l0AV, -    -20, -26, -27, and -29;
                            10GP, -10GT, -l0P,   or P/N 897770-1, -3, -
                            and -l0T.            7, -9, -10, -11, -12, -
                                                 14, -15, -16, -25, -26,
                                                 and -28.
4*.......................  TPE331-3U, -3UW, -   P/N 893561-4, -5, -12,
                            5, -5A, -5AB, -5B,   and -13 or P/N 897770-
                            -6, -6A, -l0AV, -    5, -8, and -13.
                            10GP, -10GT, -l0P,
                            and -l0T.
5........................  TPE331-10, -l0R, -   P/N 897375-2, -3, -4, -
                            10U, -10UA, -10UF,   5, -8, -9, -10, -11, -
                            -10UG, -10UGR, -     12, -13, -14, -15, -16,
                            10UR, -11U, -12JR,   -17, -19, -21, -24, -
                            -12UA, -12UAR, and   25, -26, and -27; or P/
                            -12UHR.              N 897780-1, -2, -3, -4,
                                                 -5, -6, -7, -8, -9, -
                                                 10, -11, -14, -15, -16,
                                                 -17, -18, -19, -20, -
                                                 21, -22, -23, -24, -25,
                                                 -26, -27, -30, -32, -
                                                 34, -36, -37, and -38;
                                                 or P/N 893561-17, -18,
                                                 and -19.
------------------------------------------------------------------------
* New/added FCU assembly P/Ns

(d) Unsafe Condition

    This AD was prompted by reports of loss of the fuel control 
drive, leading to engine overspeed and engine failure. We are 
issuing this AD to prevent damage to the engine, and damage to the 
airplane.

(e) Compliance

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

(1) Inspection of Engines with FCU Assembly P/Ns in Groups 2 and 4

    For FCU assembly P/Ns in Groups 2 and 4 listed in Table 1 to 
paragraph (c) of this AD, at the next scheduled inspection of the 
fuel control drive, or within 500 hours-in-service (HIS) after the 
effective date of this AD, whichever occurs first:
    (i) Inspect the fuel control drive spline for wear.
    (ii) Thereafter, re-inspect the fuel control drive within 1,000 
HIS since-last-inspection (SLI) of the fuel control drive.

(2) Inspection of Engines with FCU Assembly P/Ns in Groups 1, 3, and 5

    (i) For FCU assembly P/Ns in Groups 1, 3, or 5 listed in Table 1 
to paragraph (c) of this AD:
    (A) If on the effective date of this AD the FCU assembly has 950 
or more HIS SLI, inspect the fuel control drive spline for wear 
within 50 HIS from the effective date of this AD.
    (B) If on the effective date of this AD the FCU assembly has 
fewer than 950 HIS SLI, inspect the fuel control drive spline for 
wear before reaching 1,000 HIS.
    (ii) Thereafter, re-inspect the fuel control drive spline for 
wear within every 1,000 HIS SLI.

(3) Airplane Operating Procedures

    Within 60 days after the effective date of this AD, insert the 
information in Figure 1 to paragraph (e) of this AD, into the 
Emergency Procedures Section of the Airplane Flight Manual (AFM), 
Pilot Operating Handbook (POH), and the Manufacturer's Operating 
Manual (MOM).
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(f) Optional Terminating Action

    Replacing the affected FCU assembly with an FCU assembly P/N not 
listed in this AD is terminating action for the initial and 
repetitive inspections required by this AD, and for inserting the 
information in Figure 1 to paragraph (e) of this AD into the AFM, 
POH, and MOM.

(g) Definitions

    For the purposes of this AD:
    (1) The ``fuel control drive'' is a series of mating splines 
located between the fuel pump and fuel control governor.
    (2) The fuel control drive consists of four drive splines: the 
fuel pump internal spline, the fuel control external ``quill shaft'' 
spline, and the stub shaft internal and external splines.

(h) Alternative Methods of Compliance (AMOCs)

    The Manager, Los Angeles Aircraft Certification Office, FAA, may 
approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 
to make your request.

(i) Related Information

    (1) For more information about this AD, contact Joseph Costa, 
Aerospace Engineer, Los Angeles Aircraft Certification Office, FAA, 
Transport Airplane Directorate, 3960 Paramount Blvd., Lakewood, CA 
90712-4137; phone: 562-627-5246; fax: 562-627-5210; email: 
joseph.costa@faa.gov.
    (2) Honeywell International Inc., AFM, POH, and MOM, which are 
not incorporated by reference in this AD, can be obtained from 
Honeywell International Inc., using the contact information in 
paragraph (i)(4) of this AD.
    (3) Information pertaining to operating recommendations for 
affected engines after a fuel control drive failure is contained in 
Honeywell International Inc., Operating Information Letter (OIL) 
OI331-12R6, dated

[[Page 15266]]

May 26, 2009, for multi-engine airplanes; and in OIL OI331-18R4, 
dated May 26, 2009, for single-engine airplanes. Information on fuel 
control drive spline inspection can be found in Section 72-00-00 of 
the applicable TPE331 maintenance manuals. These Honeywell 
International Inc., OILs and the TPE331 maintenance manuals, which 
are not incorporated by reference in this AD, can be obtained from 
Honeywell International Inc., using the contact information in 
paragraph (i)(4) of this AD.
    (4) For service information identified in this AD, contact 
Honeywell International Inc., 111 S. 34th Street, Phoenix, AZ 85034-
2802; Internet: https://myaerospace.honeywell.com/wps/portal/!ut; 
phone: 800-601-3099.
    (5) You may view this service information at the FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, 
MA. For information on the availability of this material at the FAA, 
call 781-238-7125.

    Issued in Burlington, Massachusetts, on March 10, 2014.
Colleen M. D'Alessandro,
Assistant Directorate Manager, Engine & Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2014-06029 Filed 3-18-14; 8:45 am]
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