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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.

(d) SUBJECT

    Joint Aircraft System Component (JASC)  Code 7210,  Turbine Engine Re-
    duction 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 re-
     peat 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 follow-
      ing 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 inspec-
    tion  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 in-
    spector, 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.

(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 Honey-
    well 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.

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: joseph.costa@faa.gov.
PREAMBLE 

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: 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.

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
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

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

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

Action Labor cost Parts cost Cost per product Cost on U.S. operators
Oil filter sampling and analysis: Part 91 operators 4 work-hours x $85 per hour = $340 $844 $1,184 $644,096 per year
Oil filter sampling and analysis: Part 121 and 135 operators 1 work-hour x $85 per hour = $85 211 296 $752,432 per year

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

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

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

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

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]

2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):