Airworthiness Directives; Honeywell International Inc. Turboprop and Turboshaft Engines, 28763-28766 [2018-13266]

Download as PDF 28763 Rules and Regulations Federal Register Vol. 83, No. 120 Thursday, June 21, 2018 This section of the FEDERAL REGISTER contains regulatory documents having general applicability and legal effect, most of which are keyed to and codified in the Code of Federal Regulations, which is published under 50 titles pursuant to 44 U.S.C. 1510. information on the availability of this material at the FAA, call 781–238–7759. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2016– 9450. Comments The Code of Federal Regulations is sold by the Superintendent of Documents. Examining the AD Docket Request To Revise Compliance Time for Resampling DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2016–9450; Product Identifier 2016–NE–25–AD; Amendment 39– 19317; AD 2018–13–05] RIN 2120–AA64 Airworthiness Directives; Honeywell International Inc. Turboprop and Turboshaft Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: FOR FURTHER INFORMATION CONTACT: We are adopting a new airworthiness directive (AD) for certain Honeywell International Inc. (Honeywell) TPE331 turboprop and TSE331 turboshaft engines. 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, part number (P/N) 3101726–3. This AD requires initial and repetitive engine oil filter sampling and analysis of the affected engines and inspections of certain hydraulic torque sensor gear assemblies. We are issuing this AD to address the unsafe condition on these products. SUMMARY: This AD is effective July 26, 2018. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of July 26, 2018. ADDRESSES: For service information identified in this final rule, 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 pmangrum on DSK30RV082PROD with RULES DATES: VerDate Sep<11>2014 14:07 Jun 20, 2018 Jkt 244001 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 Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, the regulatory evaluation, any comments received, and other information. The address for the Docket Operations (phone: 800–647–5527) is Docket Operations, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE, Washington, DC 20590. Joseph Costa, Aerospace Engineer, Los Angeles ACO Branch, FAA, 3960 Paramount Blvd., Lakewood, CA 90712– 4137; phone: 562–627–5246; fax: 562– 627–5210; email: joseph.costa@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Honeywell International Inc. TPE331 turboprop and TSE331 turboshaft engines. The NPRM published in the Federal Register on September 13, 2017 (82 FR 42957). The NPRM 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. The NPRM proposed to require initial and repetitive engine oil filter sampling and analysis of the affected engines. The NPRM also proposed to require inspection of the hydraulic torque sensor gear assemblies that do not meet oil filter inspection requirements and improved component overhaul procedures that would remove from service, by attrition, certain P/N hydraulic torque sensor gear assemblies. We are issuing this AD to address the unsafe condition on these products. PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 We gave the public the opportunity to participate in developing this final rule. The following presents the comments received on the NPRM and the FAA’s response to each comment. The National Agricultural Aviation Association (NAAA) commented that additional compliance time may be required for oil filter analysis resampling beyond the 25 hours timein-service proposed by the NPRM. The NAAA noted that the engine may reenter service after oil sampling. Therefore, the 25 hours time-in-service may be exceeded prior to the operators receiving notification from the laboratory that performed the oil filter analysis. We agree that the proposed compliance time may have resulted in operators exceeding the 25 hours timein-service before receiving the results of the oil filter analysis. We, therefore, revised the requirement time for resampling in this AD to 25 hours time in service after receiving notification from the accredited laboratory performing the oil filter analysis. We determined that allowing this additional time in service will improve the quality of the sample. We also clarified that if an inspection or resample is required, then the inspection must occur within 5 days after receiving notification from the laboratory that performed the oil filter analysis. Request To Revise Compliance Time for Initial Sample Honeywell requested that we increase the compliance time for obtaining an oil filter sample from 150 to 200 hours. Honeywell commented that Honeywell Service Bulletin (SB) TPE331–72–0180 indicates a 200-hours compliance time for TPE331–10 operators with at least 800 operating hours per year. Honeywell noted that this compliance time coincides with scheduled maintenance intervals for operators. We disagree. We are attempting to detect impending torque sensor failures using set response times and reduced oil filter sampling and analysis intervals. We find, therefore, that the 150-hour compliance time meets the safety objectives of this AD. Further, we did not receive any comments from part 121 E:\FR\FM\21JNR1.SGM 21JNR1 28764 Federal Register / Vol. 83, No. 120 / Thursday, June 21, 2018 / Rules and Regulations Request To Update Service Information or part 135 operators indicating a concern with the inspection interval of 150 hours. We did not change this AD. Request To Revise Number of Resampling Tests NAAA and Copperstate Turbine Engine Company commented that a single resampling allowance that may lead to a gearbox inspection is too stringent. They indicated that oil filter resampling experience has shown that multiple resampling tests may be necessary. NAAA commented that the source of the contamination may not always be the material caused by the torque sensor failure. In this situation, NAAA indicated that another resampling, without the inspection, may be warranted. NAAA commented that the sample analysis should guide maintenance personnel in the proper direction without having to tear down an engine unnecessarily. We partially agree. We agree that some wear elements, such as silver and aluminum, found during the initial oil filter analysis could permit more than one resampling before a required gearbox inspection. We also agree because these elements or alloys may not cause accelerated wear and possible failure of the torque sensor assembly. We disagree with changing the AD because the commenters have not produced evidence that the presence of certain elements may not contribute to the failure of the torque sensor. We will consider AMOC requests to allow additional oil filter resamples before requiring a gearbox inspection provided we receive acceptable technical justification. We did not change this AD. Honeywell requested that we revise our reference to the service bulletin to refer to the latest revision. We agree. We updated the reference in the Other Related Service Information paragraph in this AD to Revision 38 of Honeywell SB TPE331–72–0180. Request To Clarify Differences Paragraph Honeywell requested that we clarify the ‘‘Differences Between This Proposed AD and the Service Information’’ section in the NPRM. We disagree. The referenced paragraph does not exist in the final rule and the compliance requirements were clearly defined in the NPRM. We did not change this AD. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this final rule with the changes described previously and minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this final rule. Related Service Information Under 1 CFR Part 51 We reviewed 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 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 38, dated August 15, 2017. The SBs address the inspection intervals for the oil and filter analysis for the affected TPE331 and TSE331 engines. Costs of Compliance We estimate that this AD affects 3,831 engines installed on airplanes of U.S. registry. We estimate the following costs to comply with this 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 Action Labor cost Records review ............................................... 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 Cost per product Parts cost $0 Cost on U.S. operators $85 $325,635 be required to perform oil filter sampling and analysis. pmangrum on DSK30RV082PROD with RULES ESTIMATED COSTS Cost per product 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 $1,184 $644,096 per year. 1 work-hour × $85 per hour = $85 ............. 211 296 $752,432 per year. VerDate Sep<11>2014 14:07 Jun 20, 2018 Jkt 244001 PO 00000 Frm 00002 Fmt 4700 Parts cost Cost on U.S. operators Action Sfmt 4700 E:\FR\FM\21JNR1.SGM 21JNR1 28765 Federal Register / Vol. 83, No. 120 / Thursday, June 21, 2018 / Rules and Regulations 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 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 Cost per product $10,000 $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 pmangrum on DSK30RV082PROD with RULES Paperwork Reduction Act A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB control number. The control number for the collection of information required by this AD is 2120–0056. The paperwork cost associated with this AD has been detailed in the Costs of Compliance section of this document and includes time for reviewing instructions, as well as completing and reviewing the collection of information. Therefore, all reporting associated with this AD is mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at 800 Independence Ave. SW, Washington, DC 20591. ATTN: Information Collection Clearance Officer, AES–200. 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 VerDate Sep<11>2014 14:07 Jun 20, 2018 Jkt 244001 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 associated appliances to the Manager, Engine and Propeller Standards Branch, Policy and Innovation Division. Regulatory Findings Frm 00003 Fmt 4700 Cost per product $3,000 $3,425 List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 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 adding the following new airworthiness directive (AD): ■ This AD will not have federalism implications under Executive Order 13132. This AD will 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 this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. PO 00000 Parts cost Sfmt 4700 2018–13–05 Honeywell International Inc. (Type Certificate previously held by AlliedSignal, Garrett Engine Division; Garrett Turbine Engine Company; and AiResearch Manufacturing Company of Arizona): Amendment 39–19317; Docket No. FAA–2016–9450; Product Identifier 2016–NE–25–AD. (a) Effective Date This AD is effective July 26, 2018. (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. E:\FR\FM\21JNR1.SGM 21JNR1 28766 Federal Register / Vol. 83, No. 120 / Thursday, June 21, 2018 / Rules and Regulations (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. The unsafe condition, if not addressed, could result in failure of the hydraulic torque sensor gear assembly, in-flight shutdown, and reduced control of the airplane. pmangrum on DSK30RV082PROD with RULES (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. You can find guidance for obtaining oil filter samples in Honeywell’s engine training manuals; for example, see the TPE331 Line Maintenance Training Manual. (2) Submit the 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). You can find a list of Honeywell-authorized laboratories capable of performing this analysis 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 after receiving notification from the laboratory that performed the analysis, inspect the torque sensor gear assembly using paragraph (g)(4)(iii) 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 after receiving notification from the laboratory that performs the analysis 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 after receiving notification from the laboratory that performed the analysis, inspect the hydraulic torque sensor gear assembly using paragraph (g)(4)(iii) of this AD. VerDate Sep<11>2014 14:07 Jun 20, 2018 Jkt 244001 (B) Reserved. (iii) Inspect the hydraulic torque sensor gear assembly using the following steps: (A) 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. (B) 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. (5) Thereafter, repeat the steps identified in paragraphs (g)(1) through (4) of this AD every additional 150 hours time in service after last oil filter sampling. (6) For any hydraulic torque sensor gear assembly that fails the inspection required by paragraph (g) of this AD, remove the affected hydraulic torque sensor gear assembly and, before further flight, replace with a part eligible for installation. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Honeywell Service Information Letter P331–97, Revision 11, dated July 23, 2008. (ii) Reserved. (3) For Honeywell 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 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 781–238–7759. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. (h) Hydraulic Torque Sensor Gear Assembly Overhaul [FR Doc. 2018–13266 Filed 6–20–18; 8:45 am] 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, Los Angeles ACO Branch, FAA has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the certification office, send it to the attention of the person identified in paragraph (j) 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 For more information about this AD, contact Joseph Costa, Aerospace Engineer, Los Angeles ACO Branch, FAA, 3960 Paramount Blvd., Lakewood, CA 90712– 4137; phone: 562–627–5246; fax: 562–627– 5210; email: joseph.costa@faa.gov. (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 Issued in Burlington, Massachusetts, on June 14, 2018. Robert J. Ganley, Manager, Engine and Propeller Standards Branch, Aircraft Certification Service. BILLING CODE 4910–13–P DEPARTMENT OF HOMELAND SECURITY Coast Guard 33 CFR Part 165 [Docket Number USCG–2018–0333] RIN 165–AA00 Safety Zones; Marine Events Held in the Captain of the Port Long Island Sound Zone Coast Guard, DHS. Temporary final rule. AGENCY: ACTION: The Coast Guard is establishing nine temporary safety zones for fireworks displays within the Captain of the Port (COTP) Long Island Sound (LIS) Zone. This temporary final rule is necessary to provide for the safety of life on navigable waters during these events. Entry into, transit through, mooring or anchoring within these limited access areas is prohibited unless authorized by the COTP LIS. DATES: This rule is effective without actual notice from June 21, 2018 through July 15, 2018. For the purposes of enforcement, actual notice will be used from May 27, 2018, through June 21, 2018. ADDRESSES: To view documents mentioned in this preamble as being SUMMARY: E:\FR\FM\21JNR1.SGM 21JNR1

Agencies

[Federal Register Volume 83, Number 120 (Thursday, June 21, 2018)]
[Rules and Regulations]
[Pages 28763-28766]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-13266]



========================================================================
Rules and Regulations
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains regulatory documents 
having general applicability and legal effect, most of which are keyed 
to and codified in the Code of Federal Regulations, which is published 
under 50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by the Superintendent of Documents. 

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


Federal Register / Vol. 83, No. 120 / Thursday, June 21, 2018 / Rules 
and Regulations

[[Page 28763]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9450; Product Identifier 2016-NE-25-AD; Amendment 
39-19317; AD 2018-13-05]
RIN 2120-AA64


Airworthiness Directives; Honeywell International Inc. Turboprop 
and Turboshaft Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Honeywell International Inc. (Honeywell) TPE331 turboprop and TSE331 
turboshaft engines. 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, part number (P/N) 3101726-3. This AD 
requires initial and repetitive engine oil filter sampling and analysis 
of the affected engines and inspections of certain hydraulic torque 
sensor gear assemblies. We are issuing this AD to address the unsafe 
condition on these products.

DATES: This AD is effective July 26, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of July 26, 
2018.

ADDRESSES: For service information identified in this final rule, 
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-
238-7759. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9450.

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 Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The AD docket contains 
this final rule, the regulatory evaluation, any comments received, and 
other information. The address for the Docket Operations (phone: 800-
647-5527) is Docket Operations, U.S. Department of Transportation, 
Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 
New Jersey Avenue SE, Washington, DC 20590.

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

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to certain Honeywell 
International Inc. TPE331 turboprop and TSE331 turboshaft engines. The 
NPRM published in the Federal Register on September 13, 2017 (82 FR 
42957). The NPRM 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. The NPRM proposed to require 
initial and repetitive engine oil filter sampling and analysis of the 
affected engines. The NPRM also proposed to require inspection of the 
hydraulic torque sensor gear assemblies that do not meet oil filter 
inspection requirements and improved component overhaul procedures that 
would remove from service, by attrition, certain P/N hydraulic torque 
sensor gear assemblies. We are issuing this AD to address the unsafe 
condition on these products.

Comments

    We gave the public the opportunity to participate in developing 
this final rule. The following presents the comments received on the 
NPRM and the FAA's response to each comment.

Request To Revise Compliance Time for Resampling

    The National Agricultural Aviation Association (NAAA) commented 
that additional compliance time may be required for oil filter analysis 
resampling beyond the 25 hours time-in-service proposed by the NPRM. 
The NAAA noted that the engine may re-enter service after oil sampling. 
Therefore, the 25 hours time-in-service may be exceeded prior to the 
operators receiving notification from the laboratory that performed the 
oil filter analysis.
    We agree that the proposed compliance time may have resulted in 
operators exceeding the 25 hours time-in-service before receiving the 
results of the oil filter analysis. We, therefore, revised the 
requirement time for resampling in this AD to 25 hours time in service 
after receiving notification from the accredited laboratory performing 
the oil filter analysis. We determined that allowing this additional 
time in service will improve the quality of the sample. We also 
clarified that if an inspection or resample is required, then the 
inspection must occur within 5 days after receiving notification from 
the laboratory that performed the oil filter analysis.

Request To Revise Compliance Time for Initial Sample

    Honeywell requested that we increase the compliance time for 
obtaining an oil filter sample from 150 to 200 hours. Honeywell 
commented that Honeywell Service Bulletin (SB) TPE331-72-0180 indicates 
a 200-hours compliance time for TPE331-10 operators with at least 800 
operating hours per year. Honeywell noted that this compliance time 
coincides with scheduled maintenance intervals for operators.
    We disagree. We are attempting to detect impending torque sensor 
failures using set response times and reduced oil filter sampling and 
analysis intervals. We find, therefore, that the 150-hour compliance 
time meets the safety objectives of this AD. Further, we did not 
receive any comments from part 121

[[Page 28764]]

or part 135 operators indicating a concern with the inspection interval 
of 150 hours. We did not change this AD.

Request To Revise Number of Resampling Tests

    NAAA and Copperstate Turbine Engine Company commented that a single 
resampling allowance that may lead to a gearbox inspection is too 
stringent. They indicated that oil filter resampling experience has 
shown that multiple resampling tests may be necessary. NAAA commented 
that the source of the contamination may not always be the material 
caused by the torque sensor failure. In this situation, NAAA indicated 
that another resampling, without the inspection, may be warranted. NAAA 
commented that the sample analysis should guide maintenance personnel 
in the proper direction without having to tear down an engine 
unnecessarily.
    We partially agree. We agree that some wear elements, such as 
silver and aluminum, found during the initial oil filter analysis could 
permit more than one resampling before a required gearbox inspection. 
We also agree because these elements or alloys may not cause 
accelerated wear and possible failure of the torque sensor assembly. We 
disagree with changing the AD because the commenters have not produced 
evidence that the presence of certain elements may not contribute to 
the failure of the torque sensor. We will consider AMOC requests to 
allow additional oil filter resamples before requiring a gearbox 
inspection provided we receive acceptable technical justification. We 
did not change this AD.

Request To Update Service Information

    Honeywell requested that we revise our reference to the service 
bulletin to refer to the latest revision.
    We agree. We updated the reference in the Other Related Service 
Information paragraph in this AD to Revision 38 of Honeywell SB TPE331-
72-0180.

Request To Clarify Differences Paragraph

    Honeywell requested that we clarify the ``Differences Between This 
Proposed AD and the Service Information'' section in the NPRM.
    We disagree. The referenced paragraph does not exist in the final 
rule and the compliance requirements were clearly defined in the NPRM. 
We did not change this AD.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this final rule with the changes described previously and minor 
editorial changes. We have determined that these minor changes:
     [Agr]re consistent with the intent that was proposed in 
the NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this final 
rule.

Related Service Information Under 1 CFR Part 51

    We reviewed 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 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 38, dated August 15, 2017. The SBs address 
the inspection intervals for the oil and filter analysis for the 
affected TPE331 and TSE331 engines.

Costs of Compliance

    We estimate that this AD affects 3,831 engines installed on 
airplanes of U.S. registry. We estimate the following costs to comply 
with this 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.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                         Cost per
             Action                   Labor cost        Parts cost        product       Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Oil filter sampling and           4 work-hours x $85            $844          $1,184  $644,096 per year.
 analysis: Part 91 operators.      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.
----------------------------------------------------------------------------------------------------------------


[[Page 28765]]

    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.
----------------------------------------------------------------------------------------------------------------

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a current valid OMB control number. The control 
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in 
the Costs of Compliance section of this document and includes time for 
reviewing instructions, as well as completing and reviewing the 
collection of information. Therefore, all reporting associated with 
this AD is mandatory. Comments concerning the accuracy of this burden 
and suggestions for reducing the burden should be directed to the FAA 
at 800 Independence Ave. SW, Washington, DC 20591. ATTN: Information 
Collection Clearance Officer, AES-200.

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

Regulatory Findings

    This AD will not have federalism implications under Executive Order 
13132. This AD will 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 this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 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):

2018-13-05 Honeywell International Inc. (Type Certificate previously 
held by AlliedSignal, Garrett Engine Division; Garrett Turbine 
Engine Company; and AiResearch Manufacturing Company of Arizona): 
Amendment 39-19317; Docket No. FAA-2016-9450; Product Identifier 
2016-NE-25-AD.

(a) Effective Date

    This AD is effective July 26, 2018.

(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.

[[Page 28766]]

(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. The unsafe 
condition, if not addressed, could result in 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. You can find guidance for obtaining oil filter samples in 
Honeywell's engine training manuals; for example, see the TPE331 
Line Maintenance Training Manual.
    (2) Submit the 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). You can find a list of Honeywell-authorized laboratories 
capable of performing this analysis 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 after receiving notification from the laboratory that 
performed the analysis, inspect the torque sensor gear assembly 
using paragraph (g)(4)(iii) 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 after receiving notification from the laboratory 
that performs the analysis 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 after receiving notification from the 
laboratory that performed the analysis, inspect the hydraulic torque 
sensor gear assembly using paragraph (g)(4)(iii) of this AD.
    (B) Reserved.
    (iii) Inspect the hydraulic torque sensor gear assembly using 
the following steps:
    (A) 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.
    (B) 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.
    (5) Thereafter, repeat the steps identified in paragraphs (g)(1) 
through (4) of this AD every additional 150 hours time in service 
after last oil filter sampling.
    (6) For any hydraulic torque sensor gear assembly that fails the 
inspection required by paragraph (g) of this AD, remove the affected 
hydraulic torque sensor gear assembly and, before further flight, 
replace with a part eligible for installation.

(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, Los Angeles ACO Branch, FAA has the authority 
to approve AMOCs for this AD, if requested using the procedures 
found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your 
request to your principal inspector or local Flight Standards 
District Office, as appropriate. If sending information directly to 
the manager of the certification office, send it to the attention of 
the person identified in paragraph (j) 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

    For more information about this AD, contact Joseph Costa, 
Aerospace Engineer, Los Angeles ACO Branch, FAA, 3960 Paramount 
Blvd., Lakewood, CA 90712-4137; phone: 562-627-5246; fax: 562-627-
5210; email: [email protected].

(k) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Honeywell Service Information Letter P331-97, Revision 11, 
dated July 23, 2008.
    (ii) Reserved.
    (3) For Honeywell 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 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 781-238-7759.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Burlington, Massachusetts, on June 14, 2018.
Robert J. Ganley,
Manager, Engine and Propeller Standards Branch, Aircraft Certification 
Service.
[FR Doc. 2018-13266 Filed 6-20-18; 8:45 am]
 BILLING CODE 4910-13-P