82 FR 42957 - Airworthiness Directives; Honeywell International Inc. Turboprop and Turboshaft Engines
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 176 (September 13, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 176 (September 13, 2017)
| Page Range | 42957-42960 | |
| FR Document | 2017-19314 |
[Federal Register Volume 82, Number 176 (Wednesday, September 13, 2017)] [Proposed Rules] [Pages 42957-42960] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-19314] ----------------------------------------------------------------------- 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: [email protected]. 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: [email protected]. (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
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(2) Bombardier, Inc., Model CL–600–2D15 (2) For more information about this AD, DATES: We must receive comments on
(Regional Jet Series 705) airplanes and Model contact Aziz Ahmed, Aerospace Engineer, this proposed AD by October 30, 2017.
CL–600–2D24 (Regional Jet Series 900) Airframe and Mechanical Systems Section,
FAA, New York ACO Branch, 1600 Stewart ADDRESSES: You may send comments,
airplanes, serial numbers 15326 through
15370 inclusive. Avenue, Suite 410, Westbury, NY 11590; using the procedures found in 14 CFR
(3) Bombardier, Inc., Model CL–600–2E25 telephone: 516–228–7329; fax: 516–794– 11.43 and 11.45, by any of the following
(Regional Jet Series 1000) airplanes, serial 5531. methods:
numbers 19041 and 19042. (3) For service information identified in • Federal eRulemaking Portal: Go to
this AD, contact Bombardier, Inc., 400 Côte http://www.regulations.gov. Follow the
(d) Subject Vertu Road West, Dorval, Québec H4S 1Y9, instructions for submitting comments.
Air Transport Association (ATA) of Canada; Widebody Customer Response
Center North America toll-free telephone: 1–
• Fax: 202–493–2251.
America Code 27, Flight controls.
866–538–1247 or direct-dial telephone: 1– • Mail: U.S. Department of
(e) Reason 514–855–2999; fax: 514–855–7401; email: Transportation, Docket Operations, M–
This AD was prompted by a report of ac.yul@aero.bombardier.com; Internet: 30, West Building Ground Floor, Room
rudder yoke components that had not been http://www.bombardier.com. You may view W12–140, 1200 New Jersey Avenue SE.,
properly inspected at the supplier. We are this service information at the FAA, Washington, DC 20590.
issuing this AD to prevent a cracked rudder Transport Standards Branch, 1601 Lind • Hand Delivery: Deliver to Mail
yoke, which may affect rudder function on Avenue SW., Renton, WA. For information address above between 9 a.m. and 5
the affected side and could result in on the availability of this material at the
difficulties in maneuvering the airplane. FAA, call 425–227–1221. p.m., Monday through Friday, except
Federal holidays.
(f) Compliance Issued in Renton, Washington, on August For service information identified in
31, 2017.
Comply with this AD within the this NPRM, contact Honeywell
compliance times specified, unless already Dionne Palermo, International Inc., 111 S 34th Street,
done. Acting Director, System Oversight Division, Phoenix, AZ 85034–2802; phone: 800–
Aircraft Certification Service. 601–3099; Internet: https://
(g) Replacement of Left and Right Rudder
[FR Doc. 2017–19306 Filed 9–12–17; 8:45 am] myaerospace.honeywell.com/wps/
Yoke Assemblies
Within 6,600 flight hours after the effective
BILLING CODE 4910–13–P portal. You may view this service
date of this AD, replace the left and right information at the FAA, Engine and
rudder yoke assemblies, in accordance with Propeller Standards Branch, Policy and
the Accomplishment Instructions of DEPARTMENT OF TRANSPORTATION Innovation Division, 1200 District
Bombardier Service Bulletin 670BA–27–073, Avenue, Burlington, MA. For
dated November 23, 2016. Federal Aviation Administration
information on the availability of this
(h) Other FAA AD Provisions 14 CFR Part 39 material at the FAA, call 781–238–7125.
The following provisions also apply to this Examining the AD Docket
AD: [Docket No. FAA–2016–9450; Product
(1) Alternative Methods of Compliance Identifier 2016–NE–25–AD] You may examine the AD docket on
(AMOCs): The Manager, New York ACO RIN 2120–AA64 the Internet at http://
Branch, FAA, has the authority to approve www.regulations.gov by searching for
AMOCs for this AD, if requested using the Airworthiness Directives; Honeywell and locating Docket No. FAA–2016–
procedures found in 14 CFR 39.19. In International Inc. Turboprop and 9450; or in person at the Docket
accordance with 14 CFR 39.19, send your Turboshaft Engines Management Facility between 9 a.m.
request to your principal inspector or local
Flight Standards District Office, as
and 5 p.m., Monday through Friday,
AGENCY: Federal Aviation
appropriate. If sending information directly except Federal holidays. The AD docket
Administration (FAA), DOT.
to the manager of the ACO, send it to ATTN: contains this proposed AD, the
ACTION: Notice of proposed rulemaking regulatory evaluation, any comments
Program Manager, Continuing Operational
Safety, FAA, New York ACO Branch, 1600 (NPRM). received, and other information. The
Stewart Avenue, Suite 410, Westbury, NY SUMMARY: We propose to adopt a new street address for the Docket Office
11590; telephone: 516–228–7300; fax: 516– (phone: 800–647–5527) is in the
794–5531. Before using any approved AMOC, airworthiness directive (AD) for certain
Honeywell International Inc. TPE331 ADDRESSES section. Comments will be
notify your appropriate principal inspector,
or lacking a principal inspector, the manager turboprop and TSE331 turboshaft available in the AD docket shortly after
of the local flight standards district office/ engines. This proposed AD was receipt.
certificate holding district office. prompted by recent reports of failures of FOR FURTHER INFORMATION CONTACT:
(2) Contacting the Manufacturer: For any the direct drive fuel control gears and Joseph Costa, Aerospace Engineer, FAA,
requirement in this AD to obtain corrective bearings in the hydraulic torque sensor Los Angeles ACO Branch, Compliance
actions from a manufacturer, the action must gear assembly, part number (P/N) and Airworthiness Division, 3960
be accomplished using a method approved Paramount Blvd., Lakewood, CA 90712–
3101726–3. This proposed AD would
by the Manager, New York ACO Branch,
FAA; or Transport Canada Civil Aviation require initial and repetitive engine oil 4137; phone: 562–627–5246; fax: 562–
(TCCA); or Bombardier Inc.’s TCCA Design filter sampling and analysis of the 627–5210; email: joseph.costa@faa.gov.
Approval Organization (DAO). If approved by affected engines. This proposed AD SUPPLEMENTARY INFORMATION:
the DAO, the approval must include the would also require inspection of
DAO-authorized signature. hydraulic torque sensor gear assemblies Comments Invited
jstallworth on DSKBBY8HB2PROD with PROPOSALS
(i) Related Information that do not meet oil filter inspection We invite you to send any written
requirements. This proposed AD would relevant data, views, or arguments about
(1) Refer to Mandatory Continuing
further require improved component this NPRM. Send your comments to an
Airworthiness Information (MCAI) Canadian
AD CF–2017–10, dated February 27, 2017, for overhaul procedures that would remove address listed under the ADDRESSES
related information. This MCAI may be from service, by attrition, certain P/N section. Include ‘‘Docket No. FAA–
found in the AD docket on the Internet at hydraulic torque sensor gear assemblies. 2016–9450; Directorate Identifier 2016–
http://www.regulations.gov by searching for We are proposing this AD to correct the NE–25–AD’’ at the beginning of your
and locating Docket No. FAA–2017–0811. unsafe condition on these products. comments. We specifically invite
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ESTIMATED COSTS
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
Oil filter sampling and analysis: Part 91 4 work-hours × $85 per hour = $340 ....... $844 $1184 $644,096 per year.
operators.
Oil filter sampling and analysis: Part 121 1 work-hour × $85 per hour = $85 ........... 211 296 752,432 per year.
and 135 operators.
We estimate that 242 engines will gear assembly be overhauled during the
require that the hydraulic torque sensor first year of inspection.
ESTIMATED OVERHAUL COSTS
Cost per
Action Labor cost Parts cost product
Replace or overhaul hydraulic torque sensor gear as- 10 work-hours × $85 per hour = $850 ......................... $10,000 $10,850
sembly.
We estimate that 217 engines will unacceptable oil filter analysis during
require hydraulic torque sensor gear the first year of inspection.
assembly inspection after an
ON-CONDITION COSTS
Cost per
Action Labor cost Parts cost product
Inspect and reassemble hydraulic torque sensor gear 5 work-hours × $85 per hour = $425 ........................... $3,000 $3,425
assembly.
Authority for This Rulemaking delegated the authority to issue ADs List of Subjects in 14 CFR Part 39
applicable to engines, propellers, and
Title 49 of the United States Code appliances to the Manager, Engine and Air transportation, Aircraft, Aviation
specifies the FAA’s authority to issue Propeller Standards Branch, Policy and safety, Incorporation by reference,
rules on aviation safety. Subtitle I, Innovation Division. Safety.
section 106, describes the authority of
the FAA Administrator. Subtitle VII: Regulatory Findings The Proposed Amendment
Aviation Programs, describes in more Accordingly, under the authority
We determined that this proposed AD
detail the scope of the Agency’s delegated to me by the Administrator,
would not have federalism implications
authority. the FAA proposes to amend 14 CFR part
under Executive Order 13132. This
We are issuing this rulemaking under proposed AD would not have a 39 as follows:
the authority described in Subtitle VII, substantial direct effect on the States, on
Part A, Subpart III, Section 44701: the relationship between the national PART 39—AIRWORTHINESS
‘‘General requirements.’’ Under that Government and the States, or on the DIRECTIVES
section, Congress charges the FAA with distribution of power and
promoting safe flight of civil aircraft in responsibilities among the various ■ 1. The authority citation for part 39
air commerce by prescribing regulations levels of government. continues to read as follows:
for practices, methods, and procedures
For the reasons discussed above, I Authority: 49 U.S.C. 106(g), 40113, 44701.
the Administrator finds necessary for
certify this proposed regulation:
safety in air commerce. This regulation § 39.13 [Amended]
is within the scope of that authority (1) Is not a ‘‘significant regulatory
because it addresses an unsafe condition action’’ under Executive Order 12866, ■ 2. The FAA amends § 39.13 by adding
that is likely to exist or develop on (2) Is not a ‘‘significant rule’’ under the following new airworthiness
products identified in this rulemaking the DOT Regulatory Policies and directive (AD):
action. Procedures (44 FR 11034, February 26, Honeywell International Inc. (Type
This AD is issued in accordance with 1979), Certificate previously held by
jstallworth on DSKBBY8HB2PROD with PROPOSALS
authority delegated by the Executive (3) Will not affect intrastate aviation AlliedSignal, Garrett Engine Division;
Director, Aircraft Certification Service, in Alaska to the extent that it justifies Garrett Turbine Engine Company; and
as authorized by FAA Order 8000.51C. making a regulatory distinction, and AiResearch Manufacturing Company of
Arizona): Docket No. FAA–2016–9450;
In accordance with that order, issuance (4) Will not have a significant Product Identifier 2016–NE–25–AD.
of ADs is normally a function of the economic impact, positive or negative,
Compliance and Airworthiness on a substantial number of small entities (a) Comments Due Date
Division, but during this transition under the criteria of the Regulatory We must receive comments by October 30,
period, the Executive Director has Flexibility Act. 2017.
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(b) Affected ADs (A) If the resample indicates a second International Inc., 111 S 34th Street, Phoenix,
None. resample or inspection is required, within 5 AZ 85034–2802; phone: 800–601–3099;
days, inspect the hydraulic torque sensor Internet: https://
(c) Applicability gear assembly using paragraph (g)(5) of this myaerospace.honeywell.com/wps/portal.
This AD applies to Honeywell AD. (3) You may view this service information
International Inc. (Honeywell) TPE331–1, –2, (B) Reserved. at the FAA, Engine and Propeller Standards
–2UA, –3U, –3UW, –5, –5B, –6, –6A, –8, –10, (5) Inspect the hydraulic torque sensor gear Branch, Policy and Innovation Division, 1200
–10AV, –10N, –10P, –10R, –10T, –10U, assembly using the following steps: District Avenue, Burlington, MA. For
–10UA, –10UF, –10UR model turboprop and (i) Remove bearings, P/Ns 358893–1, information on the availability of this
TSE331–3U turboshaft engines with 3103035–1, 3103585–1 or 70100168–1, from material at the FAA, call 781–238–7125.
hydraulic torque sensor gear assemblies, part the assembled spur gear and fuel control
drive gearshaft and inspect or replace. Issued in Burlington, Massachusetts, on
numbers (P/Ns) 3101726–1, –2, or –3, September 7, 2017.
installed. Guidance for performing the inspection can
be found in Section 70–00–00, Standard Robert J. Ganley,
(d) Subject Practices of the applicable TPE331 engine Manager, Engine and Propeller Standards
Joint Aircraft System Component (JASC) maintenance manual. For example, see Branch, Aircraft Certification Service.
Code 7210, Turbine Engine Reduction Gear. paragraph 5., ‘‘Bearing Inspection,’’ on pages [FR Doc. 2017–19314 Filed 9–12–17; 8:45 am]
11–12 of Honeywell Maintenance Manual
(e) Unsafe Condition 70–00–00, TPE331–10 (Report No. 72–00– BILLING CODE 4910–13–P
This AD was prompted by recent reports of 27), dated February 29, 2000.
failures of the direct drive fuel control gears (ii) Visually inspect the gearshaft teeth for
and bearings in the hydraulic torque sensor scoring, pitting, chipping, metal deposits or CONSUMER PRODUCT SAFETY
gear assembly, P/N 3101726–3. We are corner breakage. Visual defects on gear teeth COMMISSION
issuing this AD to prevent failure of the are acceptable if defects cannot be felt using
hydraulic torque sensor gear assembly, in- a 0.031 inch diameter stylus. No corner 16 CFR Parts 1420
flight shutdown, and reduced control of the breakage is allowed.
airplane. (iii) For any hydraulic torque sensor gear [CPSC Docket No. 2017–0032]
assembly that fails the inspection required by
(f) Compliance Amendment to Standard for All-Terrain
paragraph (g)(5) of this AD, remove the
Comply with this AD within the affected hydraulic torque sensor gear Vehicles; Notice of Proposed
compliance times specified, unless already assembly and, before further flight, replace Rulemaking
done. with a part eligible for installation.
(6) Thereafter, repeat the steps identified in AGENCY: Consumer Product Safety
(g) Oil Filter Sampling and Analysis
paragraphs (g)(1) through (5) of this AD every Commission.
(1) Obtain an initial engine oil filter sample additional 150 hours time in service after last ACTION: Notice of proposed rulemaking.
of the affected engines within 150 hours time oil filter sampling.
in service after the effective date of this AD. SUMMARY: The Consumer Product Safety
Guidance for obtaining oil filter samples can (h) Hydraulic Torque Sensor Gear Assembly
be found in Honeywell’s engine training Overhaul Improvement Act of 2008 (CPSIA)
manuals; for example, see the TPE331 Line After the effective date of this AD, do not
required the Consumer Product Safety
Maintenance Training Manual. use the Honeywell Torque Sensor Gear Commission (CPSC or the Commission)
(2) Submit engine oil filter sample within Assembly Overhaul Manual with Illustrated to publish, as a mandatory consumer
3 days of sampling to an ISO/IEC 17025- Parts List, 72–00–17, Revision No. 9, dated, product safety standard, the American
accredited laboratory capable of performing July 20, 1992, or earlier versions, to overhaul National Standard for Four-Wheel All-
analysis using ASTM D5185, Standard Test TPE331 or TSE331 hydraulic torque sensor Terrain Vehicles Equipment
Method for Multielement Determination of gear assemblies, P/Ns 3101726–1, –2, or –3. Configuration, and Performance
Used and Unused Lubricating Oils and Base
Oils by Inductively Coupled Plasma Atomic (i) Alternative Methods of Compliance Requirements, developed by the
Emission Spectrometry (ICP–AES). A list of (AMOCs) Specialty Vehicle Institute of America
Honeywell-authorized laboratories capable of (1) The Manager, FAA, Los Angeles ACO (ANSI/SVIA 1–2007). CPSC published
performing this analysis can be found in Branch, Compliance and Airworthiness that mandatory consumer product safety
paragraph 1.D.(10) of Honeywell Service Division, has the authority to approve standard on November 14, 2008. ANSI/
Information Letter (SIL) P331–97, Revision AMOCs for this AD, if requested using the SVIA issued a 2017 edition of its
11, dated July 23, 2008. procedures found in 14 CFR 39.19. In standard in June 2017. In accordance
(3) Perform an oil filter analysis for wear accordance with 14 CFR 39.19, send your with the CPSIA, CPSC proposes to
metals and evaluate filter contents using request to your principal inspector or local
paragraphs 1.D.(4) and (5) of Honeywell SIL
amend the Commission’s mandatory
Flight Standards District Office, as
P331–97, Revision 11, dated July 23, 2008. appropriate. If sending information directly ATV standard to reference the 2017
Guidelines for interpreting analysis results to the manager of the Los Angeles ACO edition of the ANSI/SVIA standard.
can be found in paragraph (8) of Honeywell Branch, send it to the attention of the person DATES: Submit comments by November
SIL P331–97. identified in paragraph (j)(1) of this AD. 27, 2017.
(4) For those engines where the oil filter (2) Before using any approved AMOC, ADDRESSES: Comments related to the
analysis indicates the need for an inspection notify your appropriate principal inspector,
or resample, as specified in Figures 1, 2 or or lacking a principal inspector, the manager
proposed rule, identified by Docket No.
3 of the Honeywell SIL P331–97, Revision 11, of the local flight standards district office/ CPSC–2017–0032, may be submitted
dated July 23, 2008, accomplish the certificate holding district office. electronically or in writing:
following: Electronic Submissions: Submit
(i) If Figures 1, 2, or 3 indicate an (j) Related Information electronic comments to the Federal
jstallworth on DSKBBY8HB2PROD with PROPOSALS
inspection is required, within 5 days, inspect (1) For more information about this AD, eRulemaking Portal at: http://
the torque sensor gear assembly using contact Joseph Costa, Aerospace Engineer, www.regulations.gov. Follow the
paragraph (g)(5) of this AD. FAA, Los Angeles ACO Branch, Compliance instructions for submitting comments.
(ii) If Figures 1, 2, or 3 indicate a resample and Airworthiness Division, 3960 Paramount
is required, perform a repeat oil filter sample Blvd., Lakewood, CA 90712–4137; phone: The Commission does not accept
and analysis, within 25 hours time in service 562–627–5246; fax: 562–627–5210; email: comments submitted by email, except
from the previous sample, to evaluate for joseph.costa@faa.gov. through www.regulations.gov. The
wear metals in accordance with paragraphs (2) For service information identified in Commission encourages you to submit
(g)(1), (2) and (3) of this AD. this proposed AD, contact Honeywell electronic comments by using the
VerDate Sep<11>2014 15:14 Sep 12, 2017 Jkt 241001 PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 E:\FR\FM\13SEP1.SGM 13SEP1](https://thefederalregister.org/doc/82_FR_43133/page/4.svg)
Document Created: 2017-09-13 00:09:05
Document Modified: 2017-09-13 00:09:05
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by October 30, 2017. | |
| 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: [email protected] | |
| FR Citation | 82 FR 42957 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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