Airworthiness Directives; Honeywell International Inc. Turboprop and Turboshaft Engines, 42957-42960 [2017-19314]

Download as PDF Federal Register / Vol. 82, No. 176 / Wednesday, September 13, 2017 / Proposed Rules (2) Bombardier, Inc., Model CL–600–2D15 (Regional Jet Series 705) airplanes and Model CL–600–2D24 (Regional Jet Series 900) airplanes, serial numbers 15326 through 15370 inclusive. (3) Bombardier, Inc., Model CL–600–2E25 (Regional Jet Series 1000) airplanes, serial numbers 19041 and 19042. (d) Subject Air Transport Association (ATA) of America Code 27, Flight controls. (e) Reason This AD was prompted by a report of rudder yoke components that had not been properly inspected at the supplier. We are issuing this AD to prevent a cracked rudder yoke, which may affect rudder function on the affected side and could result in difficulties in maneuvering the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. jstallworth on DSKBBY8HB2PROD with PROPOSALS (g) Replacement of Left and Right Rudder Yoke Assemblies Within 6,600 flight hours after the effective date of this AD, replace the left and right rudder yoke assemblies, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 670BA–27–073, dated November 23, 2016. (h) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, New York 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 ACO, send it to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone: 516–228–7300; fax: 516– 794–5531. 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, New York ACO Branch, FAA; or Transport Canada Civil Aviation (TCCA); or Bombardier Inc.’s TCCA Design Approval Organization (DAO). If approved by the DAO, the approval must include the DAO-authorized signature. (i) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) Canadian AD CF–2017–10, dated February 27, 2017, 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–2017–0811. VerDate Sep<11>2014 15:14 Sep 12, 2017 Jkt 241001 (2) For more information about this AD, contact Aziz Ahmed, Aerospace Engineer, Airframe and Mechanical Systems Section, FAA, New York ACO Branch, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone: 516–228–7329; fax: 516–794– 5531. (3) For service information identified in ˆ this AD, contact Bombardier, Inc., 400 Cote ´ Vertu Road West, Dorval, Quebec H4S 1Y9, Canada; Widebody Customer Response Center North America toll-free telephone: 1– 866–538–1247 or direct-dial telephone: 1– 514–855–2999; fax: 514–855–7401; email: ac.yul@aero.bombardier.com; Internet: http://www.bombardier.com. You may view this service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on August 31, 2017. Dionne Palermo, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2017–19306 Filed 9–12–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–9450; Product Identifier 2016–NE–25–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 adopt a new airworthiness directive (AD) for certain Honeywell International Inc. TPE331 turboprop and TSE331 turboshaft engines. This proposed AD was prompted by recent reports of failures of the direct drive fuel control gears and bearings in the hydraulic torque sensor gear assembly, part number (P/N) 3101726–3. This proposed AD would require initial and repetitive engine oil filter sampling and analysis of the affected engines. This proposed AD would also require inspection of hydraulic torque sensor gear assemblies that do not meet oil filter inspection requirements. This proposed AD would further require improved component overhaul procedures that would remove from service, by attrition, certain P/N hydraulic torque sensor gear assemblies. We are proposing this AD to correct the unsafe condition on these products. SUMMARY: PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 42957 We must receive comments on this proposed AD by October 30, 2017. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to 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, Policy and Innovation Division, 1200 District Avenue, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. DATES: 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–2016– 9450; 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, FAA, Los Angeles ACO Branch, Compliance and Airworthiness Division, 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– 2016–9450; Directorate Identifier 2016– NE–25–AD’’ at the beginning of your comments. We specifically invite E:\FR\FM\13SEP1.SGM 13SEP1 42958 Federal Register / Vol. 82, No. 176 / Wednesday, September 13, 2017 / Proposed Rules 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 We received reports of failures of the direct drive fuel control gears and bearings in the hydraulic torque sensor gear assembly, P/N 3101726–3. These failures are similar to previous failures in hydraulic torque sensor gear assemblies, P/Ns 3101726–1 and 3101726–2, that resulted in in-flight shutdowns and accidents in single and twin-engine airplanes. After recent failures of the hydraulic torque sensor gear assembly, P/N 3101726–3, installed in six engines, we re-performed oil filter analyses on samples taken prior to these failures. We found the wear metals, including, but not limited to, M50 steel platelets, in the engine oil filter samples. The FAA has found that the oil filter analysis for wear metals provides an effective means of identifying premature wear of the components in the hydraulic torque sensor gear assembly. This proposed AD would require initial and repetitive oil filter analysis for wear metals from the hydraulic torque sensor gear assembly. This AD also requires the use of later revisions of the hydraulic torque sensor gear assembly component overhaul manuals that provide improved maintenance instructions and removes from service, by attrition, hydraulic torque sensor gear assemblies, P/N 3101726–1 and certain P/N 3101726–2 of a pre-Series 9 configuration. This condition, if not corrected, could result in failure of the hydraulic torque sensor gear assembly, in-flight shutdown, and reduced control of the airplane. and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Related Service Information Under 1 CFR Part 51 Honeywell has issued Honeywell Service Information Letter (SIL) P331– 97, Revision 11, dated July 23, 2008. The SIL describes procedures for conducting the spectrometric oil and filter analysis program to sample and analyze metal particles in the engine lubricating system. 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. Proposed AD Requirements Other Related Service Information We reviewed the improved procedures and limitations in the Honeywell Torque Sensor Gear Assembly Overhaul Manual with Illustrated Parts List, 72–00–17, Revision 10, dated October 31, 2013, for the TPE331 and TSE331 torque sensor gear assemblies. We also reviewed Honeywell’s TPE331 Line Maintenance Training Manual which provides guidance for obtaining oil filter samples. In addition, we reviewed Honeywell Service Bulletins (SBs) TPE331–72– 0402, Revision 6, dated November 26, 1997; TPE331–72–0403, Revision 5, dated January 20, 1989; TPE331–72– 0404, Revision 8, dated September 13, 2016; TPE331–72–0823, Revision 3, dated September 13, 1996; TSE331–72– 5003, Revision 3, dated January 20, 1989; and TPE331–72–0180, Revision 36, dated April 7, 2016. The SBs address the inspection intervals for the oil and filter analysis for the affected TPE331 and TSE331 engines. FAA’s Determination We are proposing this AD because we evaluated all the relevant information This proposed AD requires initial and repetitive engine oil filter analysis of the affected TPE331 and TSE331 engines. This proposed AD also requires inspection of affected hydraulic torque sensor gear assemblies, and replacement or overhaul of those torque sensor gear assemblies that do not meet inspection requirements. This proposed AD restricts the use of earlier versions of the hydraulic sensor gear component overhaul manual. Differences Between This Proposed AD and the Service Information Honeywell service information does not recommend oil filter sampling and analysis and hydraulic torque sensor gear assembly inspection within specified times for applicable engines. Because of recent failures, this proposed AD defines specific time requirements for performing engine oil filter sampling and analysis for all applicable TPE331 and TSE331 engines and, if necessary, hydraulic torque sensor gear assembly inspections. This proposed AD would require the oil filter sample analysis, which is only part of Honeywell’s recommended spectrometric oil and oil filter analysis program. Costs of Compliance We estimate that this proposed AD affects 3,831 engines installed on airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: We estimate that 3,831 engines will require a records review to determine if they have an affected hydraulic torque sensor gear assembly installed. ESTIMATED COSTS Labor cost Records review ............................................... jstallworth on DSKBBY8HB2PROD with PROPOSALS Action 1 work-hour × $85 per hour = $85 ................. We estimate that 2,542 engines operating under Parts 121 or 135 and 544 engines operating under Part 91 will VerDate Sep<11>2014 15:14 Sep 12, 2017 Jkt 241001 Cost per product Parts cost $0 be required to perform oil filter sampling and analysis. PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 E:\FR\FM\13SEP1.SGM 13SEP1 $85 Cost on U.S. operators $325,635 Federal Register / Vol. 82, No. 176 / Wednesday, September 13, 2017 / Proposed Rules 42959 ESTIMATED COSTS Cost on U.S. operators Labor cost Oil filter sampling and analysis: Part 91 operators. Oil filter sampling and analysis: Part 121 and 135 operators. 4 work-hours × $85 per hour = $340 ....... $844 $1184 1 work-hour × $85 per hour = $85 ........... 211 296 We estimate that 242 engines will require that the hydraulic torque sensor Parts cost Cost per product Action $644,096 per year. 752,432 per year. gear assembly be overhauled during the first year of inspection. ESTIMATED OVERHAUL COSTS Action Labor cost Replace or overhaul hydraulic torque sensor gear assembly. 10 work-hours × $85 per hour = $850 ......................... We estimate that 217 engines will require hydraulic torque sensor gear assembly inspection after an Parts cost $10,000 Cost per product $10,850 unacceptable oil filter analysis during the first year of inspection. ON-CONDITION COSTS Action Labor cost Inspect and reassemble hydraulic torque sensor gear assembly. 5 work-hours × $85 per hour = $425 ........................... jstallworth on DSKBBY8HB2PROD with PROPOSALS Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency’s authority. 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. 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 VerDate Sep<11>2014 15:14 Sep 12, 2017 Jkt 241001 Parts cost Cost per product $3,000 $3,425 delegated the authority to issue ADs applicable to engines, propellers, and appliances to the Manager, Engine and Propeller Standards Branch, Policy and Innovation Division. List of Subjects in 14 CFR Part 39 Regulatory Findings The Proposed Amendment We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska 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. Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. 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 adding the following new airworthiness directive (AD): ■ Honeywell International Inc. (Type Certificate previously held by AlliedSignal, Garrett Engine Division; Garrett Turbine Engine Company; and AiResearch Manufacturing Company of Arizona): Docket No. FAA–2016–9450; Product Identifier 2016–NE–25–AD. (a) Comments Due Date We must receive comments by October 30, 2017. E:\FR\FM\13SEP1.SGM 13SEP1 42960 Federal Register / Vol. 82, No. 176 / Wednesday, September 13, 2017 / Proposed Rules (b) Affected ADs None. (c) Applicability This AD applies to Honeywell International Inc. (Honeywell) TPE331–1, –2, –2UA, –3U, –3UW, –5, –5B, –6, –6A, –8, –10, –10AV, –10N, –10P, –10R, –10T, –10U, –10UA, –10UF, –10UR model turboprop and TSE331–3U turboshaft engines with hydraulic torque sensor gear assemblies, part numbers (P/Ns) 3101726–1, –2, or –3, installed. (d) Subject Joint Aircraft System Component (JASC) Code 7210, Turbine Engine Reduction Gear. (e) Unsafe Condition This AD was prompted by recent reports of failures of the direct drive fuel control gears and bearings in the hydraulic torque sensor gear assembly, P/N 3101726–3. We are issuing this AD to prevent failure of the hydraulic torque sensor gear assembly, inflight shutdown, and reduced control of the airplane. jstallworth on DSKBBY8HB2PROD with PROPOSALS (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Oil Filter Sampling and Analysis (1) Obtain an initial engine oil filter sample of the affected engines within 150 hours time in service after the effective date of this AD. Guidance for obtaining oil filter samples can be found in Honeywell’s engine training manuals; for example, see the TPE331 Line Maintenance Training Manual. (2) Submit engine oil filter sample within 3 days of sampling to an ISO/IEC 17025accredited laboratory capable of performing analysis using ASTM D5185, Standard Test Method for Multielement Determination of Used and Unused Lubricating Oils and Base Oils by Inductively Coupled Plasma Atomic Emission Spectrometry (ICP–AES). A list of Honeywell-authorized laboratories capable of performing this analysis can be found in paragraph 1.D.(10) of Honeywell Service Information Letter (SIL) P331–97, Revision 11, dated July 23, 2008. (3) Perform an oil filter analysis for wear metals and evaluate filter contents using paragraphs 1.D.(4) and (5) of Honeywell SIL P331–97, Revision 11, dated July 23, 2008. Guidelines for interpreting analysis results can be found in paragraph (8) of Honeywell SIL P331–97. (4) For those engines where the oil filter analysis indicates the need for an inspection or resample, as specified in Figures 1, 2 or 3 of the Honeywell SIL P331–97, Revision 11, dated July 23, 2008, accomplish the following: (i) If Figures 1, 2, or 3 indicate an inspection is required, within 5 days, inspect the torque sensor gear assembly using paragraph (g)(5) of this AD. (ii) If Figures 1, 2, or 3 indicate a resample is required, perform a repeat oil filter sample and analysis, within 25 hours time in service from the previous sample, to evaluate for wear metals in accordance with paragraphs (g)(1), (2) and (3) of this AD. VerDate Sep<11>2014 15:14 Sep 12, 2017 Jkt 241001 (A) If the resample indicates a second resample or inspection is required, within 5 days, inspect the hydraulic torque sensor gear assembly using paragraph (g)(5) of this AD. (B) Reserved. (5) Inspect the hydraulic torque sensor gear assembly using the following steps: (i) Remove bearings, P/Ns 358893–1, 3103035–1, 3103585–1 or 70100168–1, from the assembled spur gear and fuel control drive gearshaft and inspect or replace. Guidance for performing the inspection can be found in Section 70–00–00, Standard Practices of the applicable TPE331 engine maintenance manual. For example, see paragraph 5., ‘‘Bearing Inspection,’’ on pages 11–12 of Honeywell Maintenance Manual 70–00–00, TPE331–10 (Report No. 72–00– 27), dated February 29, 2000. (ii) Visually inspect the gearshaft teeth for scoring, pitting, chipping, metal deposits or corner breakage. Visual defects on gear teeth are acceptable if defects cannot be felt using a 0.031 inch diameter stylus. No corner breakage is allowed. (iii) For any hydraulic torque sensor gear assembly that fails the inspection required by paragraph (g)(5) of this AD, remove the affected hydraulic torque sensor gear assembly and, before further flight, replace with a part eligible for installation. (6) Thereafter, repeat the steps identified in paragraphs (g)(1) through (5) of this AD every additional 150 hours time in service after last oil filter sampling. (h) Hydraulic Torque Sensor Gear Assembly Overhaul After the effective date of this AD, do not use the Honeywell Torque Sensor Gear Assembly Overhaul Manual with Illustrated Parts List, 72–00–17, Revision No. 9, dated, July 20, 1992, or earlier versions, to overhaul TPE331 or TSE331 hydraulic torque sensor gear assemblies, P/Ns 3101726–1, –2, or –3. (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, FAA, Los Angeles ACO Branch, Compliance and Airworthiness Division, 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 Los Angeles ACO Branch, send it to the attention of the person identified in paragraph (j)(1) of this AD. (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. (j) Related Information (1) For more information about this AD, contact Joseph Costa, Aerospace Engineer, FAA, Los Angeles ACO Branch, Compliance and Airworthiness Division, 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 proposed AD, contact Honeywell PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 International Inc., 111 S 34th Street, Phoenix, AZ 85034–2802; phone: 800–601–3099; Internet: https:// myaerospace.honeywell.com/wps/portal. (3) You may view this service information at the FAA, Engine and Propeller Standards Branch, Policy and Innovation Division, 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 September 7, 2017. Robert J. Ganley, Manager, Engine and Propeller Standards Branch, Aircraft Certification Service. [FR Doc. 2017–19314 Filed 9–12–17; 8:45 am] BILLING CODE 4910–13–P CONSUMER PRODUCT SAFETY COMMISSION 16 CFR Parts 1420 [CPSC Docket No. 2017–0032] Amendment to Standard for All-Terrain Vehicles; Notice of Proposed Rulemaking Consumer Product Safety Commission. ACTION: Notice of proposed rulemaking. AGENCY: The Consumer Product Safety Improvement Act of 2008 (CPSIA) required the Consumer Product Safety Commission (CPSC or the Commission) to publish, as a mandatory consumer product safety standard, the American National Standard for Four-Wheel AllTerrain Vehicles Equipment Configuration, and Performance Requirements, developed by the Specialty Vehicle Institute of America (ANSI/SVIA 1–2007). CPSC published that mandatory consumer product safety standard on November 14, 2008. ANSI/ SVIA issued a 2017 edition of its standard in June 2017. In accordance with the CPSIA, CPSC proposes to amend the Commission’s mandatory ATV standard to reference the 2017 edition of the ANSI/SVIA standard. DATES: Submit comments by November 27, 2017. ADDRESSES: Comments related to the proposed rule, identified by Docket No. CPSC–2017–0032, may be submitted electronically or in writing: Electronic Submissions: Submit electronic comments to the Federal eRulemaking Portal at: http:// www.regulations.gov. Follow the instructions for submitting comments. The Commission does not accept comments submitted by email, except through www.regulations.gov. The Commission encourages you to submit electronic comments by using the SUMMARY: E:\FR\FM\13SEP1.SGM 13SEP1

Agencies

[Federal Register Volume 82, Number 176 (Wednesday, September 13, 2017)]
[Proposed Rules]
[Pages 42957-42960]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-19314]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9450; Product Identifier 2016-NE-25-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 adopt a new airworthiness directive (AD) for 
certain Honeywell International Inc. TPE331 turboprop and TSE331 
turboshaft engines. This proposed AD was prompted by recent reports of 
failures of the direct drive fuel control gears and bearings in the 
hydraulic torque sensor gear assembly, part number (P/N) 3101726-3. 
This proposed AD would require initial and repetitive engine oil filter 
sampling and analysis of the affected engines. This proposed AD would 
also require inspection of hydraulic torque sensor gear assemblies that 
do not meet oil filter inspection requirements. This proposed AD would 
further require improved component overhaul procedures that would 
remove from service, by attrition, certain P/N hydraulic torque sensor 
gear assemblies. We are proposing this AD to correct the unsafe 
condition on these products.

DATES: We must receive comments on this proposed AD by October 30, 
2017.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to 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, Policy and Innovation Division, 1200 District Avenue, 
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-2016-
9450; 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, FAA, 
Los Angeles ACO Branch, Compliance and Airworthiness Division, 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-2016-9450; 
Directorate Identifier 2016-NE-25-AD'' at the beginning of your 
comments. We specifically invite

[[Page 42958]]

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

    We received reports of failures of the direct drive fuel control 
gears and bearings in the hydraulic torque sensor gear assembly, P/N 
3101726-3. These failures are similar to previous failures in hydraulic 
torque sensor gear assemblies, P/Ns 3101726-1 and 3101726-2, that 
resulted in in-flight shutdowns and accidents in single and twin-engine 
airplanes.
    After recent failures of the hydraulic torque sensor gear assembly, 
P/N 3101726-3, installed in six engines, we re-performed oil filter 
analyses on samples taken prior to these failures. We found the wear 
metals, including, but not limited to, M50 steel platelets, in the 
engine oil filter samples. The FAA has found that the oil filter 
analysis for wear metals provides an effective means of identifying 
premature wear of the components in the hydraulic torque sensor gear 
assembly.
    This proposed AD would require initial and repetitive oil filter 
analysis for wear metals from the hydraulic torque sensor gear 
assembly. This AD also requires the use of later revisions of the 
hydraulic torque sensor gear assembly component overhaul manuals that 
provide improved maintenance instructions and removes from service, by 
attrition, hydraulic torque sensor gear assemblies, P/N 3101726-1 and 
certain P/N 3101726-2 of a pre-Series 9 configuration. This condition, 
if not corrected, could result in failure of the hydraulic torque 
sensor gear assembly, in-flight shutdown, and reduced control of the 
airplane.

Related Service Information Under 1 CFR Part 51

    Honeywell has issued Honeywell Service Information Letter (SIL) 
P331-97, Revision 11, dated July 23, 2008. The SIL describes procedures 
for conducting the spectrometric oil and filter analysis program to 
sample and analyze metal particles in the engine lubricating system. 
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 the improved procedures and limitations in the 
Honeywell Torque Sensor Gear Assembly Overhaul Manual with Illustrated 
Parts List, 72-00-17, Revision 10, dated October 31, 2013, for the 
TPE331 and TSE331 torque sensor gear assemblies. We also reviewed 
Honeywell's TPE331 Line Maintenance Training Manual which provides 
guidance for obtaining oil filter samples. In addition, we reviewed 
Honeywell Service Bulletins (SBs) TPE331-72-0402, Revision 6, dated 
November 26, 1997; TPE331-72-0403, Revision 5, dated January 20, 1989; 
TPE331-72-0404, Revision 8, dated September 13, 2016; TPE331-72-0823, 
Revision 3, dated September 13, 1996; TSE331-72-5003, Revision 3, dated 
January 20, 1989; and TPE331-72-0180, Revision 36, dated April 7, 2016. 
The SBs address the inspection intervals for the oil and filter 
analysis for the affected TPE331 and TSE331 engines.

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 requires initial and repetitive engine oil filter 
analysis of the affected TPE331 and TSE331 engines. This proposed AD 
also requires inspection of affected hydraulic torque sensor gear 
assemblies, and replacement or overhaul of those torque sensor gear 
assemblies that do not meet inspection requirements. This proposed AD 
restricts the use of earlier versions of the hydraulic sensor gear 
component overhaul manual.

Differences Between This Proposed AD and the Service Information

    Honeywell service information does not recommend oil filter 
sampling and analysis and hydraulic torque sensor gear assembly 
inspection within specified times for applicable engines. Because of 
recent failures, this proposed AD defines specific time requirements 
for performing engine oil filter sampling and analysis for all 
applicable TPE331 and TSE331 engines and, if necessary, hydraulic 
torque sensor gear assembly inspections. This proposed AD would require 
the oil filter sample analysis, which is only part of Honeywell's 
recommended spectrometric oil and oil filter analysis program.

Costs of Compliance

    We estimate that this proposed AD affects 3,831 engines installed 
on airplanes of U.S. registry. We estimate the following costs to 
comply with this proposed AD:
    We estimate that 3,831 engines will require a records review to 
determine if they have an affected hydraulic torque sensor gear 
assembly installed.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Records review........................  1 work-hour x $85 per                 $0             $85        $325,635
                                         hour = $85.
----------------------------------------------------------------------------------------------------------------

    We estimate that 2,542 engines operating under Parts 121 or 135 and 
544 engines operating under Part 91 will be required to perform oil 
filter sampling and analysis.

[[Page 42959]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                       Cost per
             Action                  Labor cost       Parts cost        product        Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Oil filter sampling and          4 work-hours x               $844           $1184  $644,096 per year.
 analysis: Part 91 operators.     $85 per hour =
                                  $340.
Oil filter sampling and          1 work-hour x $85             211             296  752,432 per year.
 analysis: Part 121 and 135       per hour = $85.
 operators.
----------------------------------------------------------------------------------------------------------------

    We estimate that 242 engines will require that the hydraulic torque 
sensor gear assembly be overhauled during the first year of inspection.

                                            Estimated Overhaul Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replace or overhaul hydraulic torque sensor     10 work-hours x $85 per hour =           $10,000         $10,850
 gear assembly.                                  $850.
----------------------------------------------------------------------------------------------------------------

    We estimate that 217 engines will require hydraulic torque sensor 
gear assembly inspection after an unacceptable oil filter analysis 
during the first year of inspection.

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Inspect and reassemble hydraulic torque sensor  5 work-hours x $85 per hour =             $3,000          $3,425
 gear assembly.                                  $425.
----------------------------------------------------------------------------------------------------------------

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.
    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 
appliances to the Manager, Engine and Propeller Standards Branch, 
Policy and Innovation Division.

Regulatory Findings

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

Honeywell International Inc. (Type Certificate previously held by 
AlliedSignal, Garrett Engine Division; Garrett Turbine Engine 
Company; and AiResearch Manufacturing Company of Arizona): Docket 
No. FAA-2016-9450; Product Identifier 2016-NE-25-AD.

(a) Comments Due Date

    We must receive comments by October 30, 2017.

[[Page 42960]]

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Honeywell International Inc. (Honeywell) 
TPE331-1, -2, -2UA, -3U, -3UW, -5, -5B, -6, -6A, -8, -10, -10AV, -
10N, -10P, -10R, -10T, -10U, -10UA, -10UF, -10UR model turboprop and 
TSE331-3U turboshaft engines with hydraulic torque sensor gear 
assemblies, part numbers (P/Ns) 3101726-1, -2, or -3, installed.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7210, Turbine Engine 
Reduction Gear.

(e) Unsafe Condition

    This AD was prompted by recent reports of failures of the direct 
drive fuel control gears and bearings in the hydraulic torque sensor 
gear assembly, P/N 3101726-3. We are issuing this AD to prevent 
failure of the hydraulic torque sensor gear 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) Oil Filter Sampling and Analysis

    (1) Obtain an initial engine oil filter sample of the affected 
engines within 150 hours time in service after the effective date of 
this AD. Guidance for obtaining oil filter samples can be found in 
Honeywell's engine training manuals; for example, see the TPE331 
Line Maintenance Training Manual.
    (2) Submit engine oil filter sample within 3 days of sampling to 
an ISO/IEC 17025-accredited laboratory capable of performing 
analysis using ASTM D5185, Standard Test Method for Multielement 
Determination of Used and Unused Lubricating Oils and Base Oils by 
Inductively Coupled Plasma Atomic Emission Spectrometry (ICP-AES). A 
list of Honeywell-authorized laboratories capable of performing this 
analysis can be found in paragraph 1.D.(10) of Honeywell Service 
Information Letter (SIL) P331-97, Revision 11, dated July 23, 2008.
    (3) Perform an oil filter analysis for wear metals and evaluate 
filter contents using paragraphs 1.D.(4) and (5) of Honeywell SIL 
P331-97, Revision 11, dated July 23, 2008. Guidelines for 
interpreting analysis results can be found in paragraph (8) of 
Honeywell SIL P331-97.
    (4) For those engines where the oil filter analysis indicates 
the need for an inspection or resample, as specified in Figures 1, 2 
or 3 of the Honeywell SIL P331-97, Revision 11, dated July 23, 2008, 
accomplish the following:
    (i) If Figures 1, 2, or 3 indicate an inspection is required, 
within 5 days, inspect the torque sensor gear assembly using 
paragraph (g)(5) of this AD.
    (ii) If Figures 1, 2, or 3 indicate a resample is required, 
perform a repeat oil filter sample and analysis, within 25 hours 
time in service from the previous sample, to evaluate for wear 
metals in accordance with paragraphs (g)(1), (2) and (3) of this AD.
    (A) If the resample indicates a second resample or inspection is 
required, within 5 days, inspect the hydraulic torque sensor gear 
assembly using paragraph (g)(5) of this AD.
    (B) Reserved.
    (5) Inspect the hydraulic torque sensor gear assembly using the 
following steps:
    (i) Remove bearings, P/Ns 358893-1, 3103035-1, 3103585-1 or 
70100168-1, from the assembled spur gear and fuel control drive 
gearshaft and inspect or replace. Guidance for performing the 
inspection can be found in Section 70-00-00, Standard Practices of 
the applicable TPE331 engine maintenance manual. For example, see 
paragraph 5., ``Bearing Inspection,'' on pages 11-12 of Honeywell 
Maintenance Manual 70-00-00, TPE331-10 (Report No. 72-00-27), dated 
February 29, 2000.
    (ii) Visually inspect the gearshaft teeth for scoring, pitting, 
chipping, metal deposits or corner breakage. Visual defects on gear 
teeth are acceptable if defects cannot be felt using a 0.031 inch 
diameter stylus. No corner breakage is allowed.
    (iii) For any hydraulic torque sensor gear assembly that fails 
the inspection required by paragraph (g)(5) of this AD, remove the 
affected hydraulic torque sensor gear assembly and, before further 
flight, replace with a part eligible for installation.
    (6) Thereafter, repeat the steps identified in paragraphs (g)(1) 
through (5) of this AD every additional 150 hours time in service 
after last oil filter sampling.

(h) Hydraulic Torque Sensor Gear Assembly Overhaul

    After the effective date of this AD, do not use the Honeywell 
Torque Sensor Gear Assembly Overhaul Manual with Illustrated Parts 
List, 72-00-17, Revision No. 9, dated, July 20, 1992, or earlier 
versions, to overhaul TPE331 or TSE331 hydraulic torque sensor gear 
assemblies, P/Ns 3101726-1, -2, or -3.

(i) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, FAA, Los Angeles ACO Branch, Compliance and 
Airworthiness Division, 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 Los Angeles 
ACO Branch, send it to the attention of the person identified in 
paragraph (j)(1) of this AD.
    (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.

(j) Related Information

    (1) For more information about this AD, contact Joseph Costa, 
Aerospace Engineer, FAA, Los Angeles ACO Branch, Compliance and 
Airworthiness Division, 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 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.
    (3) You may view this service information at the FAA, Engine and 
Propeller Standards Branch, Policy and Innovation Division, 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 September 7, 2017.
Robert J. Ganley,
Manager, Engine and Propeller Standards Branch, Aircraft Certification 
Service.
[FR Doc. 2017-19314 Filed 9-12-17; 8:45 am]
 BILLING CODE 4910-13-P