[Federal Register Volume 82, Number 176 (Wednesday, September 13, 2017)]
[Proposed Rules]
[Pages 42957-42960]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-19314]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-9450; Product Identifier 2016-NE-25-AD]
RIN 2120-AA64
Airworthiness Directives; Honeywell International Inc. Turboprop
and Turboshaft Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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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
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Cost per Cost on U.S.
Action Labor cost Parts cost product operators
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Records review........................ 1 work-hour x $85 per $0 $85 $325,635
hour = $85.
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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
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Cost per
Action Labor cost Parts cost product Cost on U.S. operators
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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.
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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
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Cost per
Action Labor cost Parts cost product
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Replace or overhaul hydraulic torque sensor 10 work-hours x $85 per hour = $10,000 $10,850
gear assembly. $850.
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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
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Cost per
Action Labor cost Parts cost product
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Inspect and reassemble hydraulic torque sensor 5 work-hours x $85 per hour = $3,000 $3,425
gear assembly. $425.
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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