Document ID: FAA-2016-9418-0006
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Honeywell International Inc. Turboprop and Turboshaft Engines
Posted Date: 2018-01-24T05:00Z

[Federal Register Volume 83, Number 16 (Wednesday, January 24, 2018)]
[Rules and Regulations]
[Pages 3263-3268]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-01228]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9418; Product Identifier 2016-NE-23-AD; Amendment 
39-19167; AD 2018-02-14]
RIN 2120-AA64

Airworthiness Directives; Honeywell International Inc. Turboprop 
and Turboshaft Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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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 reports that combustion 
chamber case assemblies have cracked and ruptured. This AD requires 
inspection of the affected combustion chamber case assembly, 
replacement of those assemblies found cracked, and removal of affected 
assemblies on certain TPE331 and TSE331 engines. We are issuing this AD 
to address the unsafe condition on these products.

DATES: This AD is effective February 28, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of February 28, 
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, 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-2016-9418.

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-
9418; 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 Docket Operations (phone: 800-647-
5527) is Document 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 TPE331 
turboprop and TSE331 turboshaft engines. The NPRM published in the 
Federal Register on April 19, 2017 (82 FR 18402). The NPRM was prompted 
by reports of three accidents involving combustion chamber case 
assembly ruptures. Investigations have shown numerous cracked and 
ruptured combustion chamber case assemblies resulting from high 
stresses in the as-designed weld joints and contributing factors due to 
repair weld quality, poor maintenance and inspection practices, and 
cycles-in-service. The NPRM proposed to require inspection, replacement 
of the affected combustion chamber case assemblies, and removal of 
affected assemblies on certain TPE331 turboprop and TSE331 turboshaft 
engines. 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 Internet Address

    Honeywell requested that its internet address be revised.
    We agree. We revised the internet address as requested by 
Honeywell.

Request To Revise Service Information

    Honeywell requested that we revise the service bulletins in this AD 
to reference the latest revisions.
    We agree. We revised the references in this AD to Honeywell Service 
Bulletins (SBs) TPE331-72-2218; TPE331-72-2235; and TPE331-72-2244 from 
Revision 1 to Revision 2. However, we did not update the references to 
the SB that is incorporated by reference since this SB is already at 
the latest revision.

Request To Revise Discussion of Proposed AD Requirements

    Honeywell requested that we reference the TSE331 turboshaft engine 
in the ``Proposed AD Requirements'' section of this final rule.
    We partially agree. We agree that we inadvertently omitted mention 
of the TSE331 turboshaft engines from the ``Proposed AD Requirements'' 
section in the NPRM. We disagree with making a change to this final 
rule because the ``Proposed AD Requirements'' section does not exist in 
this final rule AD. We did not change this AD.

Request To Revise Discussion of Removal and Replacement Times

    Honeywell requested changes to the Differences Between This 
Proposed AD and the Service Information section contained within the 
NPRM, recommending revision of the removal and replacement statement. 
Honeywell's referenced service bulletins in the NPRM recommend a 
revised compliance calendar deadline for certain redesigned combustion 
chamber case assemblies. Honeywell indicated the compliance deadline is 
March 31, 2021, for all redesigned combustion chamber case assemblies.
    We partially agree. We agree it would be appropriate to reference 
this calendar deadline in this discussion within the

[[Page 3264]]

NPRM. We do not agree to revise this final rule because this discussion 
does not exist in this final rule. Further explanation in this final 
rule is not necessary. We did not change this final rule.

Request To Revise Number of Affected Engines

    Honeywell indicated its records show 11,280 engines have been 
shipped with suspect combustion chamber case assemblies. Honeywell, 
therefore, requested we revise the number of engines accordingly within 
the Costs of Compliance section in this final rule.
    We disagree. We estimate costs based on the number of affected 
engines in the U.S. Registry. We estimate 50% of the engines Honeywell 
shipped are in the U.S. Registry. We did not change this final rule.

Request To Revise Applicability To Include TPE331-12B Engine

    Honeywell requested we revise the applicability of this AD to 
include the TPE331-12B engine. Honeywell commented this engine was used 
in military operations but now is operated commercially and has 
experienced similar cracks in its combustion chamber case assembly.
    We partially agree. The combustion chamber case assemblies 
installed on these engines are subject to the same cracking as those 
installed on the other affected TPE331 engines. However, in the 
interest of safety, we will proceed to publish this final rule without 
adding the TPE331-12B engine model. We will consider further rulemaking 
action to incorporate the TPE331-12B engines.

Request To Revise Compliance Time

    Honeywell, Council 331 (a TPE331 operators and maintenance group), 
and an individual operator requested a change to repetitive compliance 
time for the visual inspection of the combustion chamber case assembly 
and suggested a specified calendar date. The commenters noted 
compliance at 50 and 400 hours would not align with the fuel nozzle 
inspection interval and requested clarification.
    We partially agree. We interpret Honeywell's comment on the 50-hour 
initial compliance interval as a request to clarify the intent of the 
50-hour interval rather than as a request to change this AD. We used 
the 50-hour compliance interval and not a calendar date because a grace 
period is necessary to give operators time to comply with this AD.
    We agree the repetitive combustion chamber case assembly 
inspections should be aligned with the fuel nozzle inspections not to 
exceed 450 hours. We revised this AD to indicate repetitive visual 
inspection of the combustion chamber case assembly be performed before 
accumulating 450 hours since last fuel nozzle inspection.

Request To Note Ruptures of Additional Combustion Chamber Case 
Assemblies

    Honeywell requested this final rule note that combustion chamber 
case assembly ruptures occurred on parts other than those part numbers 
(P/Ns) mentioned in paragraph (g) of this AD. Honeywell indicated 
ruptures have occurred on other P/N combustor chamber case assemblies.
    We agree. Combustion chamber case assembly ruptures have occurred 
with other configurations other than those P/Ns mentioned in paragraph 
(g) of this AD. We agree the public should be aware of combustion 
chamber case assembly cracks that may propagate to failure or rupture 
if not properly inspected and maintained. We reviewed other combustion 
chamber case assembly configurations and determined the risk of rupture 
for P/N 3101668-x (``x'' denotes all dash numbers) is lower than those 
configurations identified in paragraph (g)(2) of this AD. We have 
adequately addressed more frequent inspections and removal from service 
of high risk and cracked combustion chamber case assemblies. We did not 
change this AD.

Request To Remove All Combustion Chamber Case Assemblies From Service

    Honeywell requested that we revise the Compliance section of this 
AD to require removal from service, at the next removal from the 
engine, all combustion chamber case assemblies other than the P/Ns 
listed in paragraph (g)(2) of this AD. In addition, Honeywell has 
performed a Continued Airworthiness Assessment, in accordance with 
Advisory Circular 39-8 and determined replacement of the combustion 
chamber case assemblies with redesigned assemblies is the only 
corrective action that would return the product to the level of safety 
intended by the original basis of certification.
    We disagree. This AD requires corrective actions that reduce the 
probability of combustion chamber case rupture. We identified in 
paragraph (g)(2) of this AD certain combustion chamber case assemblies 
with high stresses in the specified weld joint that showed higher 
incidents of cracking and rupture, a short crack propagation life, and 
poor crack detectability compared to other combustion chamber case 
assemblies. These combustion chamber case assemblies require 
replacement within the AD's specified compliance time. We did not 
change this AD.

Request To Clarify Identity of Supplemental Type Certificate (STC) 
Holder

    Honeywell requested we clarify that Honeywell is not the holder of 
the STC referenced in this AD.
    We agree. Indication of ownership of the subject STC may assist 
owners to identify the engine modification. We changed this AD by 
identifying National Flight Services Inc. as the holder of the STC 
SE383CH.

Request To Clarify Engines That Have Been Modified With Increased P3 
Pressures

    Honeywell requested we clarify paragraph (g) of this AD to describe 
how operators would determine that their engines have been modified 
with increased P3 pressures not under STC SE383CH.
    We agree that operators may be unable to determine that their 
engines have been modified with increased P3 case pressures. Therefore, 
we will limit the applicability of paragraph (g) of this AD to the 
referenced STC. We revised paragraph (g) of this AD by removing the 
phrase ``modified with increased P3 pressures, including, but not 
limited to . . .'' from this paragraph.''

Request To Limit Weld Repairs

    Honeywell requested we revise the compliance section of this AD to 
disallow any weld repairs on any combustion chamber case assemblies 
that are affected by this AD.
    We partially agree. We agree a weld repair is a sensitive process 
that may affect the fatigue life of the combustion chamber case 
assembly. We agree not to allow use of any weld repair procedures dated 
before the effective date of this AD. We will assess repair procedures 
of certain combustion chamber case assemblies with lower stresses on a 
case-by-case basis. We did not change this AD.

Request To Prohibit Installation of Weld-Repaired Combustion Chamber 
Case Assemblies

    Honeywell requested the compliance section be revised to prohibit 
installation of any applicable combustion chamber case assembly which 
has been weld repaired.
    We do not agree. In paragraphs (g)(2), (h) and (i) of this AD, we 
identified the combustion chamber case configurations with the highest 
risk of rupture. Prohibiting installation of all welded combustion 
chamber case assemblies is unnecessary because they

[[Page 3265]]

do not all create the same unsafe condition. We did not change this AD.

Request To Add Further Information on Combustion Chamber Assembly 
Failures

    Perimeter Aviation LP (Perimeter) requested we add information to 
this AD regarding the number of failures of combustion chamber 
assemblies with or without the one-piece bleed pad. Perimeter requested 
further information on how these failures relate to the P/N 3101668-12 
combustion chamber assembly.
    We agree. We note that five of the six combustion chamber case 
assemblies that ruptured were assemblies without the one-piece bleed 
pad. P/N 3101668-x has the one-piece bleed pad with P3 boss, which 
demonstrated significantly reduced cracking between the P3 and bleed 
boss; therefore, this combustion chamber case assembly is not affected 
by this AD. No further changes are needed. We did not change this AD.

Request To Add More Frequent Inspections

    Hancock Enterprises, Inc. and Council 331 requested we require more 
frequent visual inspections and/or fluorescent penetrant inspections 
during the combustion chamber case assembly's removal. They recommended 
allowing the assembly be re-installed and replaced with an updated part 
at the next overhaul or continuous airworthiness maintenance. Council 
331 cited the non-destructive testing experience of these combustion 
chamber case assemblies.
    We disagree. We do not believe more frequent inspections would 
maintain an adequate level of safety. Allowing the most difficult-to-
inspect and highest risk combustion chamber case assemblies back into 
service would allow excessive risk. Although we agree more frequent 
visual inspections would improve the probability of detecting cracks, 
thereby reducing the risk of a rupture, the FAA believes the 
probability of crack detection for a visual inspection of an installed 
combustion chamber case assembly is generally low and will not maintain 
an acceptable level of safety. We did not change this AD.

Request To Add Terminating Action

    Council 331 requested that compliance with one of the service 
bulletins listed in ``Other Related Service Information'' provide 
terminating action for the proposed AD. Terminating action in the AD 
will provide added incentive to operators in removing from service 
suspect parts with a documented history of failure. Council 331 
commented that, as drafted, the new redesign combustion chamber case 
assembly does not eliminate the AD's compliance requirements. There 
have been no known failures of the new redesign combustion chamber case 
assembly.
    We partially agree. We agree lower stress and improved reliability 
should eliminate the need for repetitive visual inspection. We also 
agree to limiting the ADs applicability to only the suspect 
configurations should provide adequate safety. We therefore changed the 
Applicability section of this AD to refer only to engines ``with 
combustion chamber case assemblies, part numbers (P/Ns) 869728-x, 
893973-x, 3101668-x, and 3102613-x, where ``x'' denotes any dash 
number, installed.''
    We do not agree it is necessary to specify terminating action in 
this AD. This AD only applies to the specified engine models with the 
specific P/N combustor chamber case assemblies installed. Therefore, a 
terminating action for new combustor chamber assemblies is unnecessary. 
We did not change this AD.

Revision to Engine Operating Time Limit

    After further review, we revised the engine operating time limit in 
paragraph (g)(2) of this AD to ``not to exceed 3,700 hours time-in-
service since last hot section inspection.'' This is equivalent to 
removal of the combustion chamber case assemblies at their next removal 
from the engine, which was specified in the NPRM.

Revision to Installation Prohibition

    After further review, we revised the Installation Prohibition, 
paragraph (i) of this AD, to limit this prohibition against 
installation of affected combustion chamber case assemblies in certain 
engine models. This clarification makes this prohibition consistent 
with paragraph (g)(2) of 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 SB TPE331-72-2178, Revision 0, dated May 3, 
2011. Honeywell SB TPE331-72-2178 describe procedures for inspection 
and removal of the affected combustion chamber case assemblies 
installed on all affected engines except for the TPE331-12B engine. 
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

    Honeywell has also issued SBs TPE331-72-2228, Revision 0, dated 
June 12, 2014; TPE331-72-2230, Revision 0, dated June 19, 2014; TPE331-
72-2218, Revision 2, dated February 18, 2017; TPE331-72-2244, Revision 
2, dated March 20 2017; TPE331-72-2235, Revision 2, dated February 18, 
2017; TPE331-72-2281, Revision 0, dated July 22, 2016; TPE331-72-2294, 
Revision 0, dated December 22, 2016; and TSE331-72-2245, Revision 0, 
dated November 11, 2016. These SBs provide guidance on replacement of 
the affected combustion chamber case assemblies.

Costs of Compliance

    We estimate that this AD affects 5,644 engines installed on 
airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                  Cost on U.S.
           Action                 Labor cost       Parts cost          Cost per product            operators
----------------------------------------------------------------------------------------------------------------
On-wing inspection..........  1 work-hour x $85              $0  $85 per inspection..........  $479,740 per
                               per hour = $85.                                                  inspection
                                                                                                cycle.
----------------------------------------------------------------------------------------------------------------

[[Page 3266]]

    We estimate the following costs to do any necessary replacements 
that would be required based on the results of the proposed inspection. 
We estimate that 158 engines will need this replacement during the 
first year of inspection.

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replacement of the combustion chamber assembly  1 work-hour x $85 per hour = $85         $15,000         $15,085
----------------------------------------------------------------------------------------------------------------

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):

2018-02-14 Honeywell International Inc. (Type Certificate previously 
held by AlliedSignal Inc., Garrett Engine Division; Garrett Turbine 
Engine Company; and AiResearch Manufacturing Company of Arizona): 
Amendment 39-19167; Docket No. FAA-2016-9418; Product Identifier 
2016-NE-23-AD.

(a) Effective Date

    This AD is effective February 28, 2018.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Honeywell International Inc. (Honeywell) 
TPE331-1, -2, -2UA, -3U, -3UW, -5, -5A, -5AB, -5B, -6, -6A, -8, -10, 
-10AV, -10GP, -10GT, -10N, -10P, -10R, -10T, -10U, -10UA, -10UF, -
10UG, -10UGR, -10UR, and -11U, -12JR, -12UA, -12UAR, -12UHR, -25AA, 
-25AB, -25DA, -25DB, -25FA, -43A, -43BL, -47A, -55B, and -61A model 
turboprop engines, and TSE331-3U model turboshaft engines with 
combustion chamber case assemblies, part numbers (P/Ns) 869728-x, 
893973-x, 3101668-x, and 3102613-x, where ``x'' denotes any dash 
number, installed.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7240, Turbine Engine 
Combustion Section.

(e) Unsafe Condition

    This AD was prompted by reports that combustion chamber case 
assemblies have cracked and ruptured. We are issuing this AD to 
prevent failure of the combustion chamber case assembly. The unsafe 
condition, if not addressed, could result in failure of the 
combustion chamber, in-flight shutdown, and reduced control of the 
airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Required Actions

    (1) For all affected engines:
    (i) Inspect all accessible areas of the combustion chamber case 
assembly, focusing on the weld joints, before accumulating 450 hours 
in service since last fuel nozzle inspection or within 50 hours in 
service after the effective date of this AD, whichever occurs later.
    (ii) Do the inspection in accordance with the Accomplishment 
Instructions, paragraphs 3.B.(1) through 3.B.(2), in Honeywell 
Service Bulletin TPE331-72-2178, Revision 0, dated May 3, 2011.
    (iii) Thereafter, repeat this inspection during scheduled fuel 
nozzle inspections at intervals not to exceed 450 hours.
    (2) For TPE331-3U, -3UW, -5, -5A, -5AB, -5B, -6, and -6A engines 
with combustion chamber case assemblies, P/Ns 869728-1, 869728-3, or 
893973-5, installed, and without the one-piece bleed pad with P3 
boss; and for TPE331-1, -2, and -2UA engines modified by National 
Flight Services, Inc., supplemental type certificate (STC) SE383CH, 
remove the combustion chamber case assembly from service at the next 
removal of the combustion chamber case from the engine, not to 
exceed 3,700 hours time-in-service since last hot section 
inspection.
    (3) As of the effective date of this AD, do not weld repair the 
applicable combustion chamber case assemblies using procedures dated 
before the effective date of this AD.

(h) Definition

    TPE331 model engines modified by STC SE383CH may be defined as 
the ``Super 1'' and ``Super 2'' for the compressor modification of 
the TPE331-1 and the TPE331-2, -2U, and -2UA engines, respectively. 
Figures 1 and 2 to paragraph (h) of this AD illustrate the 
appearance of combustion chamber case assembly, P/N

[[Page 3267]]

893973-5, without and with, respectively, the one-piece bleed pad 
with the P3 boss.
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[GRAPHIC] [TIFF OMITTED] TR24JA18.002

[GRAPHIC] [TIFF OMITTED] TR24JA18.003

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(i) Installation Prohibition

    After the effective date of this AD, do not install a combustion 
chamber case assembly, P/N 869728-1, 869728-3, or 893973-5, in 
TPE331-3U, -3UW, -5, -5A, -5AB, -5B, -6, and -6A engines or in 
TPE331-1, -2, and -2UA engines modified by National Flight Services, 
Inc., STC SE383CH, unless the combustion chamber case assembly has a 
one-piece bleed pad with P3 boss.

[[Page 3268]]

(j) 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 (k) 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.

(k) 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].

(l) 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 Bulletin TPE331-72-2178, Revision 0, dated 
May 3, 2011.
    (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 the FAA, Engine and 
Propeller Standards Branch, 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 January 17, 2018.
Robert J. Ganley,
Manager, Engine and Propeller Standards Branch, Aircraft Certification 
Service.
[FR Doc. 2018-01228 Filed 1-23-18; 8:45 am]
BILLING CODE 4910-13-P