Airworthiness Directives; Honeywell International Inc. Turboprop Engines, 17412-17415 [2016-06936]

Download as PDF 17412 Proposed Rules Federal Register Vol. 81, No. 60 Tuesday, March 29, 2016 This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules. 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) 2015–12– 04, which applies to all Honeywell International Inc. (Honeywell) 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 Woodward fuel control unit (FCU) assemblies, installed. AD 2015– 12–04 currently requires initial and repetitive dimensional inspections of the affected fuel control drives and insertion of certain airplane operating procedures into the applicable flight manuals. This proposed AD would correct compliance requirements and relax the inspection interval. We are proposing this AD to prevent failure of the fuel control drive, damage to the engine, and damage to the airplane. DATES: We must receive comments on this proposed AD by May 31, 2016. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room mstockstill on DSK4VPTVN1PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 16:52 Mar 28, 2016 Jkt 238001 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. You may view this service information at the FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2006– 23706. 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 NPRM. 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 NPRM. We will consider PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 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 NPRM. Discussion On June 5, 2015, we issued AD 2015– 12–04, Amendment 39–18177, (80 FR 34534, June 17, 2015) (‘‘AD 2015–12– 04’’), for 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 Woodward FCU assemblies, installed. AD 2015–12–04 requires initial and repetitive dimensional inspections of the affected fuel control drives and insertion of certain airplane operating procedures into the applicable flight manuals. AD 2015–12–04 resulted from reports of loss of the fuel control drive, leading to engine overspeed, overtorque, overtemperature, uncontained rotor failure, and asymmetric thrust in multiengine airplanes. We issued AD 2015– 12–04 to prevent failure of the fuel control drive, damage to the engine, and damage to the airplane. Actions Since AD 2015–12–04 Was Issued We received a request to change compliance time from 50 hours to 100 hours for fuel control part numbers affected by paragraph (e)(2) of this AD. We concluded that because the number of fuel control drives in-service that had not completed an initial inspection was small, changing the compliance time to 100 hours would not add additional risk of fuel control drive failure and, therefore, is appropriate. We also received reports that some airplanes do not use the condition lever to shut down the engine, and so could not comply with the AD. We concluded that references to a condition lever were inappropriate. This proposed AD eliminates references to a condition lever. E:\FR\FM\29MRP1.SGM 29MRP1 Federal Register / Vol. 81, No. 60 / Tuesday, March 29, 2016 / Proposed Rules Related Service Information We reviewed Honeywell Operating Information Letter (OIL) OI331–12R6, dated May 26, 2009, for multi-engine airplanes; and OIL OI331–18R4, dated May 26, 2009, for single-engine airplanes and Honeywell TPE331 maintenance manuals. The service information describes procedures for conducting fuel control drive inspections and engine shutdown. FAA’s Determination We are proposing this NPRM because we information evaluated all the relevant 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 NPRM would increase the inspection time limits for the FCU assembly from 50 to 100 hours-inservice in Compliance paragraph (e)(2) of this AD. This NPRM would also delete reference to the condition lever. Costs of Compliance We estimate that this proposed AD affects 2,250 engines installed on airplanes of U.S. registry. We also estimate that it would take about 8 hours per engine to comply with this proposed AD. The average labor rate is $85 per hour. We estimate that 10% of affected engines will require FCU assembly stub shaft replacement and fuel pump or fuel control repair. We also estimate that repairs will cost about $10,000 per engine. Based on these figures, we estimate the cost of this AD on U.S. operators to be $525,587 per year. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We 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. 17413 List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing airworthiness directive (AD) 2015–12–04, Amendment 39–18177 (80 FR 34534, June 17, 2015) (‘‘AD 2015– 12–04’’), 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 31, 2016. (b) Affected ADs This AD replaces AD 2015–12–04. (c) Applicability This AD applies to all Honeywell International Inc. (Honeywell) 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 Woodward fuel control unit (FCU) assemblies with Honeywell part numbers (P/ Ns) as 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, –10P, and –10T. TPE331–3U, –3UW, –5, –5B, –6, –6A, and –10T. 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, –29; and P/N 897770–1, –3, –7, –9, –10, –11, –12, –14, –15, –16, –25, –26, and –28. mstockstill on DSK4VPTVN1PROD with PROPOSALS 4 ................... 5 ................... VerDate Sep<11>2014 16:52 Mar 28, 2016 Jkt 238001 PO 00000 P/N 893561–4, –5, –12, –13; and 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, –27; and 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, –38; and P/N 893561–17, –18, and –19. Frm 00002 Fmt 4702 Sfmt 4702 E:\FR\FM\29MRP1.SGM 29MRP1 Federal Register / Vol. 81, No. 60 / Tuesday, March 29, 2016 / Proposed Rules (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 failure of the fuel control drive, damage to the engine, and damage to the airplane. (e) Compliance Comply with this AD within the compliance times specified, unless already done. mstockstill on DSK4VPTVN1PROD with PROPOSALS (1) Inspection of Engines With FCU Assembly P/Ns in Groups 2 or 4 For FCU assembly P/Ns in Groups 2 or 4 listed in Table 1 to paragraph (c) of this AD: (f) Optional Terminating Action Replacing the affected FCU assembly with an FAA-approved FCU assembly not listed in this AD by P/N is terminating action for the VerDate Sep<11>2014 16:52 Mar 28, 2016 Jkt 238001 (i) At the next scheduled inspection of the fuel control drive, or within 500 hours-inservice (HIS) after the effective date of this AD, whichever occurs first, inspect the fuel control drive for wear. (ii) Thereafter, re-inspect the fuel control drive within every 1,000 HIS since-lastinspection (SLI). (ii) If on the effective date of this AD the FCU assembly has fewer than 900 HIS SLI, inspect the fuel control drive for wear within 1,000 HIS. (iii) Thereafter, re-inspect the fuel control drive for wear within every 1,000 HIS SLI. (2) Inspection of Engines With FCU Assembly P/Ns in Groups 1, 3, or 5 For FCU assembly P/Ns in Groups 1, 3, or 5 listed in Table 1 to paragraph (c) of this AD: (i) If on the effective date of this AD the FCU assembly has 900 or more HIS SLI, inspect the fuel control drive for wear within 100 HIS after the effective date of this AD. 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 applicable Airplane Flight Manual (AFM), Pilot Operating Handbook (POH), or the Manufacturer’s Operating Manual (MOM). 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 PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 (3) Airplane Operating Procedures For the purposes of this AD: E:\FR\FM\29MRP1.SGM 29MRP1 EP29MR16.000</GPH> 17414 Federal Register / Vol. 81, No. 60 / Tuesday, March 29, 2016 / Proposed Rules (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) Information pertaining to operating recommendations for affected engines after a fuel control drive failure is contained in Honeywell Operating Information Letter (OIL) OI331–12R6, dated May 26, 2009, for multi-engine airplanes; and OIL OI331–18R4, dated May 26, 2009, for single-engine airplanes. Information on fuel control drive inspection can be found in Section 72–00–00 of the applicable TPE331 maintenance manuals. These Honeywell OILs and the TPE331 maintenance manuals can be obtained from Honeywell using the contact information in paragraph (i)(3) of this proposed AD. (3) For service information identified in this AD, contact Honeywell International Inc., 111 S. 34th Street, Phoenix, AZ 85034– 2802; phone: 800–601–3099; Internet: https://myaerospace.honeywell.com/wps/ portal. (4) You may view this service information at the FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. We propose to adopt a new airworthiness directive (AD) for all The Boeing Company Model 737–600, –700, –700C, –800, –900, and 900ER series airplanes. This proposed AD was prompted by an evaluation by the design approval holder (DAH) indicating that the S–14L and S–14R lap splices are subject to widespread fatigue damage (WFD). This proposed AD would require repetitive low frequency eddy current inspections for cracking in the lower fastener row of the S–14L and S–14R lap splices and repair if necessary. We are proposing this AD to detect and correct widespread cracking in the S–14L and S–14R lap splices that could rapidly link up and result in possible rapid decompression and reduced structural integrity of the airplane. SUMMARY: [Docket No. FAA–2016–5034; Directorate Identifier 2015–NM–172–AD] We must receive comments on this proposed AD by May 13, 2016. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206– 766–5680; Internet https:// www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 5034. RIN 2120–AA64 Examining the AD Docket Issued in Burlington, Massachusetts, on March 15, 2016. Ann C. Mollica, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 2016–06936 Filed 3–28–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 mstockstill on DSK4VPTVN1PROD with PROPOSALS Notice of proposed rulemaking (NPRM). ACTION: Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. AGENCY: VerDate Sep<11>2014 16:52 Mar 28, 2016 Jkt 238001 DATES: You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 5034; or in person at the Docket PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 17415 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: Jason Deutschman, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6595; fax: 425–917–6590; email: Jason.deutschman@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2016–5034; Directorate Identifier 2015– NM–172–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 Structural fatigue damage is progressive. It begins as minute cracks, and those cracks grow under the action of repeated stresses. This can happen because of normal operational conditions and design attributes, or because of isolated situations or incidents such as material defects, poor fabrication quality, or corrosion pits, dings, or scratches. Fatigue damage can occur locally, in small areas or structural design details, or globally. Global fatigue damage is general degradation of large areas of structure with similar structural details and stress levels. Multiple-site damage is global damage that occurs in a large structural element such as a single rivet line of a lap splice joining two large skin panels. Global damage can also occur in multiple elements such as adjacent frames or stringers. Multiple-site- E:\FR\FM\29MRP1.SGM 29MRP1

Agencies

[Federal Register Volume 81, Number 60 (Tuesday, March 29, 2016)]
[Proposed Rules]
[Pages 17412-17415]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-06936]


========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

========================================================================


Federal Register / Vol. 81, No. 60 / Tuesday, March 29, 2016 / 
Proposed Rules

[[Page 17412]]



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) 2015-12-
04, which applies to all Honeywell International Inc. (Honeywell) 
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 Woodward fuel control unit (FCU) assemblies, installed. AD 
2015-12-04 currently requires initial and repetitive dimensional 
inspections of the affected fuel control drives and insertion of 
certain airplane operating procedures into the applicable flight 
manuals. This proposed AD would correct compliance requirements and 
relax the inspection interval. We are proposing this AD to prevent 
failure of the fuel control drive, damage to the engine, and damage to 
the airplane.

DATES: We must receive comments on this proposed AD by May 31, 2016.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this 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. You may view this service information at the FAA, Engine & 
Propeller Directorate, 1200 District Avenue, Burlington, MA. For 
information on the availability of this material at the FAA, call 781-
238-7125. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2006-
23706.

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 NPRM. 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 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 NPRM.

Discussion

    On June 5, 2015, we issued AD 2015-12-04, Amendment 39-18177, (80 
FR 34534, June 17, 2015) (``AD 2015-12-04''), for 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 Woodward FCU assemblies, installed. AD 2015-12-04 
requires initial and repetitive dimensional inspections of the affected 
fuel control drives and insertion of certain airplane operating 
procedures into the applicable flight manuals. AD 2015-12-04 resulted 
from reports of loss of the fuel control drive, leading to engine 
overspeed, overtorque, overtemperature, uncontained rotor failure, and 
asymmetric thrust in multi-engine airplanes. We issued AD 2015-12-04 to 
prevent failure of the fuel control drive, damage to the engine, and 
damage to the airplane.

Actions Since AD 2015-12-04 Was Issued

    We received a request to change compliance time from 50 hours to 
100 hours for fuel control part numbers affected by paragraph (e)(2) of 
this AD. We concluded that because the number of fuel control drives 
in-service that had not completed an initial inspection was small, 
changing the compliance time to 100 hours would not add additional risk 
of fuel control drive failure and, therefore, is appropriate.
    We also received reports that some airplanes do not use the 
condition lever to shut down the engine, and so could not comply with 
the AD. We concluded that references to a condition lever were 
inappropriate. This proposed AD eliminates references to a condition 
lever.

[[Page 17413]]

Related Service Information

    We reviewed Honeywell Operating Information Letter (OIL) OI331-
12R6, dated May 26, 2009, for multi-engine airplanes; and OIL OI331-
18R4, dated May 26, 2009, for single-engine airplanes and Honeywell 
TPE331 maintenance manuals. The service information describes 
procedures for conducting fuel control drive inspections and engine 
shutdown.

FAA's Determination

    We are proposing this NPRM because we information evaluated all the 
relevant 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 NPRM would increase the inspection time limits for the FCU 
assembly from 50 to 100 hours-in-service in Compliance paragraph (e)(2) 
of this AD. This NPRM would also delete reference to the condition 
lever.

Costs of Compliance

    We estimate that this proposed AD affects 2,250 engines installed 
on airplanes of U.S. registry. We also estimate that it would take 
about 8 hours per engine to comply with this proposed AD. The average 
labor rate is $85 per hour. We estimate that 10% of affected engines 
will require FCU assembly stub shaft replacement and fuel pump or fuel 
control repair. We also estimate that repairs will cost about $10,000 
per engine. Based on these figures, we estimate the cost of this AD on 
U.S. operators to be $525,587 per year.

Authority for This Rulemaking

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

Regulatory Findings

    We 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. The FAA amends Sec.  39.13 by removing airworthiness directive (AD) 
2015-12-04, Amendment 39-18177 (80 FR 34534, June 17, 2015) (``AD 2015-
12-04''), 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 31, 2016.

(b) Affected ADs

    This AD replaces AD 2015-12-04.

(c) Applicability

    This AD applies to all Honeywell International Inc. (Honeywell) 
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 Woodward fuel control unit (FCU) assemblies with 
Honeywell part numbers (P/Ns) as 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, -5, - P/N 893561-7, -8, -9, -
                         5A, -5AB, -5B, -6, -   10, -11, -14, -15, -16,
                         6A, -l0AV, -10GP, -    20, -26, -27, -29; and
                         10GT, -10P, and -10T. P/N 897770-1, -3, -7, -9,
                                                -10, -11, -12, -14, -15,
                                                -16, -25, -26, and -28.
4.....................  TPE331-3U, -3UW, -5, - P/N 893561-4, -5, -12, -
                         5B, -6, -6A, and -     13; and
                         10T.                  P/N 897770-5, -8, and -
                                                13.
5.....................  TPE331-10, -l0R, -     P/N 897375-2, -3, -4, -5,
                         10U, -10UA, -10UF, -   -8, -9, -10, -11, -12, -
                         10UG, -10UGR, -10UR,   13, -14, -15, -16, -17,
                         -11U, -12JR, -12UA, -  19, -21, -24, -25, -26,
                         12UAR, and -12UHR.     27; and
                                               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,
                                                -38; and
                                               P/N 893561-17, -18, and -
                                                19.
------------------------------------------------------------------------


[[Page 17414]]

(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 failure of the fuel control drive, 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 or 4

    For FCU assembly P/Ns in Groups 2 or 4 listed in Table 1 to 
paragraph (c) of this AD:
    (i) 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, inspect the fuel control drive for 
wear.
    (ii) Thereafter, re-inspect the fuel control drive within every 
1,000 HIS since-last-inspection (SLI).

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

    For FCU assembly P/Ns in Groups 1, 3, or 5 listed in Table 1 to 
paragraph (c) of this AD:
    (i) If on the effective date of this AD the FCU assembly has 900 
or more HIS SLI, inspect the fuel control drive for wear within 100 
HIS after the effective date of this AD.
    (ii) If on the effective date of this AD the FCU assembly has 
fewer than 900 HIS SLI, inspect the fuel control drive for wear 
within 1,000 HIS.
    (iii) Thereafter, re-inspect the fuel control drive 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 applicable Airplane Flight 
Manual (AFM), Pilot Operating Handbook (POH), or the Manufacturer's 
Operating Manual (MOM).
[GRAPHIC] [TIFF OMITTED] TP29MR16.000

(f) Optional Terminating Action

    Replacing the affected FCU assembly with an FAA-approved FCU 
assembly not listed in this AD by P/N 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:

[[Page 17415]]

    (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) Information pertaining to operating recommendations for 
affected engines after a fuel control drive failure is contained in 
Honeywell Operating Information Letter (OIL) OI331-12R6, dated May 
26, 2009, for multi-engine airplanes; and OIL OI331-18R4, dated May 
26, 2009, for single-engine airplanes. Information on fuel control 
drive inspection can be found in Section 72-00-00 of the applicable 
TPE331 maintenance manuals. These Honeywell OILs and the TPE331 
maintenance manuals can be obtained from Honeywell using the contact 
information in paragraph (i)(3) of this proposed AD.
    (3) For service information identified in this AD, contact 
Honeywell International Inc., 111 S. 34th Street, Phoenix, AZ 85034-
2802; phone: 800-601-3099; Internet: https://myaerospace.honeywell.com/wps/portal.
    (4) You may view this service information at the FAA, Engine & 
Propeller Directorate, 1200 District Avenue, Burlington, MA. For 
information on the availability of this material at the FAA, call 
781-238-7125.

    Issued in Burlington, Massachusetts, on March 15, 2016.
Ann C. Mollica,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2016-06936 Filed 3-28-16; 8:45 am]
 BILLING CODE 4910-13-P