[Federal Register Volume 83, Number 180 (Monday, September 17, 2018)]
[Rules and Regulations]
[Pages 46853-46857]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-20142]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0479; Product Identifier 2016-NE-23-AD; Amendment 
39-19369; AD 2018-17-15]
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 superseding Airworthiness Directive (AD) 2018-02-14 for 
certain Honeywell International Inc. (Honeywell) TPE331 turboprop and 
TSE331 turboshaft engines. AD 2018-02-14 required 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. This AD retains the inspection and 
replacement requirements in AD 2018-02-04; revises the Applicability to 
add the TPE331-12 engine model and the related inspection action, 
correct references to certain engine models; and revises compliance to 
allow certain weld repair procedures. This AD was prompted by comments 
to revise the applicability and required actions of AD 2018-02-14 to 
include the TPE331-12B engine model, correct certain TPE engine model 
typographical errors, and to allow certain weld repair procedures. We 
are issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective October 22, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of October 22, 
2018.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of 
February 28, 2018 (83 FR 3263, January 24, 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; website: 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 01803. 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-2018-0479.

Examining the AD Docket

    You may examine the AD docket on the internet at http://www.regulations.govby searching for and locating Docket No. FAA-2018-
0479; 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

[[Page 46854]]

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 to supersede AD 2018-02-14, Amendment 39-19167 (83 FR 3263, 
January 24, 2018), (``AD 2018-02-14''). AD 2018-02-14 applied to 
certain Honeywell TPE331 turboprop and TSE331 turboshaft engines. The 
NPRM published in the Federal Register on June 25, 2018 (83 FR 29479). 
The NPRM was prompted by comments to revise the applicability and 
required actions of AD 2018-02-14 to include the TPE331-12B engine 
model, correct certain TPE engine model typographical errors, and to 
allow certain weld repair procedures. The NPRM proposed to continue to 
require the inspection and replacement of the affected combustion 
chamber case assembly on certain TPE331 and TSE331 engines. The NPRM 
also proposed to revise the Applicability to include the TPE331-12B 
engine model and the related inspection action, correct references to 
the TPE331-43-A, -43-BL, -47-A, -55-B, and -61-A engine models, and to 
allow weld repair procedures to the applicable combustion chamber case 
assemblies provided those procedures are approved by the Manager, Los 
Angeles ACO Branch. 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 AD. We received no comments on the NPRM or on the determination of 
the cost to the public.

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting this AD as proposed except for 
minor editorial changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for addressing the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    We reviewed Honeywell Service Bulletin (SB) TPE331-72-2178, 
Revision 0, dated May 3, 2011 and Honeywell SB TPE331-72-2179, Revision 
0, dated May 3, 2011. Honeywell SB TPE331-72-2178, Revision 0, 
describes procedures for inspection and removal of the affected 
combustion chamber case assemblies installed on all affected engines 
except for the TPE331-12B engine model. Honeywell SB TPE331-72-2179, 
Revision 0, describes procedures for inspection and removal of the 
affected combustion chamber case assemblies installed on the TPE331-12B 
engine model. 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 Honeywell 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; TPE331-72-2231, Revision 1, dated 
August 1, 2017; 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
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                                                                                                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.
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    We estimate the following costs to do any necessary replacements 
that would be required based on the results of the inspection. We 
estimate that 158 engines will need this replacement during the first 
year of inspection.

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

[[Page 46855]]

    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

    We have determined that 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 removing Airworthiness Directive (AD) 
2018-02-14, Amendment 39-19167 (83 FR 3263, January 24, 2018), and 
adding the following new AD:

2018-17-15 Honeywell International Inc. (Type Certificate previously 
held by AlliedSignal Inc., Garrett Engine Division; Garrett Turbine 
Engine Company; and AiResearch Manufacturing Company of Arizona): 
Amendment 39-19369; Docket No. FAA-2018-0479; Product Identifier 
2016-NE-23-AD.

(a) Effective Date

    This AD is effective October 22, 2018.

(b) Affected ADs

    This AD replaces AD 2018-02-14, Amendment 39-19167 (83 FR 3263, 
January 24, 2018).

(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, -12B, -12JR, -12UA, -12UAR, -12UHR, -
25AA, -25AB, -25DA, -25DB, -25FA, -43-A, -43-B, -47-A, -55-B, and -
61-A turboprop engine models, including those engine models with a -
L stamped after the model number (for example, -43-BL); and TSE331-
3U turboshaft engine models 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 case 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) 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 
time in service (TIS) since last fuel nozzle inspection or within 50 
hours TIS after the effective date of this AD, whichever occurs 
later.
    (ii) Perform the inspection in accordance with the 
Accomplishment Instructions, paragraphs 3.B.(1) through 3.B.(2), in 
Honeywell Service Bulletin (SB) TPE331-72-2178, Revision 0, dated 
May 3, 2011, or SB TPE331-72-2179, Revision 0, dated May 3, 2011, as 
applicable to the affected engine model.
    (iii) Thereafter, repeat this inspection during scheduled fuel 
nozzle inspections at intervals not to exceed 450 hours TIS since 
the last fuel nozzle inspection.
    (2) For TPE331-3U, -3UW, -5, -5A, -5AB, -5B, -6, and -6A engine 
models 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 engine models 
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 assembly from the engine, not to exceed 3,700 hours TIS since 
last hot section inspection.
    (3) After the effective date of this AD, do not weld repair the 
applicable combustion chamber case assemblies unless the weld repair 
procedures are approved by the Manager, Los Angeles ACO Branch, and 
that approval specifically refers to this AD.

(h) Definition

    (1) TPE331 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 engine models, 
respectively.
    (2) Figures 1 and 2 to paragraph (h) of this AD illustrate the 
appearance of combustion chamber case assembly, P/N 893973-5, 
without and with, respectively, the one-piece bleed pad with the P3 
boss.
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[GRAPHIC] [TIFF OMITTED] TR17SE18.000

[GRAPHIC] [TIFF OMITTED] TR17SE18.001

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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 engine models or in 
TPE331-1, -2, and -2UA engine models modified by National Flight 
Services, Inc., STC SE383CH, unless the combustion chamber case 
assembly has a one-piece bleed pad with P3 boss.

(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. You may email 
your request to: [email protected].
    (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.

[[Page 46857]]

    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (3) The following service information was approved for IBR on 
October 22, 2018.
    (i) Honeywell International Inc. (Honeywell) Service Bulletin 
(SB) TPE331-72-2179, Revision 0, dated May 3, 2011.
    (ii) Reserved.
    (4) The following service information was approved for IBR on 
February 28, 2018 (83 FR 3263, January 24, 2018).
    (i) Honeywell SB TPE331-72-2178, Revision 0, dated May 3, 2011.
    (ii) Reserved.
    (5) For service information identified in this AD, contact 
Honeywell International Inc., 111 S 34th Street, Phoenix, AZ 85034-
2802; phone: 800-601-3099; website: https://myaerospace.honeywell.com/wps/portal.
    (6) You may view this service information at FAA, Engine and 
Propeller Standards Branch, 1200 District Avenue, Burlington, MA 
01803. For information on the availability of this material at the 
FAA, call 781-238-7759.
    (7) 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 September 5, 2018.
Robert J. Ganley,
Manager, Engine and Propeller Standards Branch, Aircraft Certification 
Service.
[FR Doc. 2018-20142 Filed 9-14-18; 8:45 am]
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