[Federal Register Volume 82, Number 74 (Wednesday, April 19, 2017)]
[Proposed Rules]
[Pages 18402-18406]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-07779]
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Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
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Federal Register / Vol. 82, No. 74 / Wednesday, April 19, 2017 /
Proposed Rules
[[Page 18402]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-9418; Directorate Identifier 2016-NE-23-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. (Honeywell) TPE331 turboprop and
TSE331 turboshaft engines. This proposed AD was prompted by reports
that combustion chamber case assemblies have cracked and ruptured. This
proposed AD would require inspection of the affected combustion chamber
case assembly, replacement of those assemblies found cracked, and
removal of affected assemblies on certain TPE331 engines. We are
proposing this AD to correct the unsafe condition on these products.
DATES: We must receive comments on this proposed AD by June 5, 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/!ut/. You may view this service information at the FAA, Engine &
Propeller Directorate, 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-
9418; 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, Los
Angeles Aircraft Certification Office, FAA, Transport Airplane
Directorate, 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 proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2016-9418;
Directorate Identifier 2016-NE-23-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD 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 proposed AD.
Discussion
We have received reports of three accidents involving combustion
chamber case assembly ruptures. Investigations have shown numerous
cracked 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. From 1979 to 2016, twenty-four of these cracked combustion
chamber case assemblies have propagated to rupture. This condition, if
not corrected, could result in failure of the combustion chamber case
assembly, in-flight shutdown, and reduced control of the airplane.
Related Service Information Under 1 CFR Part 51
We reviewed Honeywell Service Bulletin (SB) TPE331-72-2178,
Revision 0, dated May 3, 2011. The SB describes procedures for
inspection and removal of the affected combustion chamber case
assemblies. 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 1, dated July 13, 2016; TPE331-72-2244, Revision 1,
dated July 20, 2016; TPE331-72-2235, Revision 1, dated July 21, 2016;
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.
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.
[[Page 18403]]
Proposed AD Requirements
This proposed AD would require inspection, replacement of the
affected combustion chamber case assemblies, and removal of affected
assemblies on certain TPE331 turboprop engines.
Differences Between This Proposed AD and the Service Information
This AD proposes inspection and replacement of high-stressed
combustion chamber case assemblies and those chamber case assemblies
found cracked at scheduled routine inspections. Honeywell SBs TPE331-
72-2228, Revision 0, dated June 12, 2014; TPE331-72-2230, Revision 0,
dated June 19, 2014; TPE331-72-2218, Revision 1, dated July 13, 2016;
TPE331-72-2244, Revision 1, dated July 20, 2016; TPE331-72-2235,
Revision 1, dated July 21, 2016; 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, recommend the
removal and replacement of the combustion chamber case assembly at next
removal from the engine, but no later than March 31, 2021 or December
31, 2021, depending on the respective engine.
Costs of Compliance
We estimate that this proposed AD affects 5,644 engines installed
on airplanes of U.S. registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
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Cost on U.S.
Action Labor cost Parts cost Cost per product operators
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On-wing inspection.............. 1 work-hour x $85 $0 $85 per inspection. $479,740 per
per hour = $85. inspection.
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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
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Cost per
Action Labor cost Parts cost product
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Replacement of the combustion chamber 1 work-hour x $85 per hour = $15,000 $15,085
assembly. $85.
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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.
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 Inc., Garrett Engine Division; Garrett Turbine Engine
Company; and AiResearch Manufacturing Company of Arizona): Docket
No. FAA-2016-9418; Directorate Identifier 2016-NE-23-AD.
(a) Comments Due Date
We must receive comments by June 5, 2017.
(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.
(d) Subject
Joint Aircraft System Component (JASC) Code 7240, Turbine Engine
Combustion Section.
[[Page 18404]]
(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, in-flight
shutdown, and reduced control of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(1) For all affected engines:
(i) Inspect all accessible areas, of the combustion chamber case
assembly, focusing on the weld joints, at the next scheduled fuel
nozzle inspection or replacement, before accumulating 400 hours
since last fuel nozzle inspection, or within 50 hours in service
after the effective date of this AD, whichever occurs later.
(ii) Thereafter, repeat this inspection before accumulating an
additional 400 hours since last inspection of the combustion chamber
case assembly.
(iii) Use the Accomplishment Instructions, paragraph 3.B.(1)
through 3.B.(2), in Honeywell Service Bulletin TPE331-72-2178,
Revision 0, dated May 3, 2011, to do the inspection.
(2) For TPE331-3U, -3UW, -5, -5A, -5AB, -5B, -6, -6A engines
with combustion chamber case assemblies, part numbers (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
with increased P3 pressures, including, but not limited to, engines
modified by 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.
(3) For 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, -11U, -12JR, -12UA, -12UAR, -
12UHR model turboprop and TSE331-3U model turboshaft engines, after
the effective date of this AD do not weld repair the combustion
chamber case assembly using procedures dated before the effective
date of this AD.
(g) Definitions
(1) ``Modified with increased P3 pressures'' is defined as an
engine modification including, but not limited to, TPE331 model
engines modified by STC SE383CH (commonly referred to as the ``Super
1'' and ``Super 2'' for the compressor modification of the TPE331-1
and the TPE331-2, -2U, and -2UA engines, respectively).
(2) Figures 1 and 2 to paragraph (g) 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.
[[Page 18405]]
[GRAPHIC] [TIFF OMITTED] TP19AP17.000
(h) 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 an
engine, unless the combustion chamber case assembly has a one-piece
bleed pad with P3 boss.
(i) Alternative Methods of Compliance (AMOCs)
The Manager, Los Angeles Aircraft Certification Office, FAA, may
approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19
to make your request.
(j) Related Information
(1) For more information about this proposed AD, contact Joseph
Costa, Aerospace Engineer, Los Angeles Aircraft Certification
Office, FAA, Transport Airplane Directorate, 3960 Paramount Blvd.,
Lakewood, CA 90712-4137; phone: 562-627-
[[Page 18406]]
5246; fax: 562-627-5210; email: [email protected].
(2) For 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/!ut/.
(3) You may view this service information at the FAA, Engine &
Propeller Directorate, 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 April 6, 2017.
Carlos A. Pestana,
Acting Manager, Engine & Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 2017-07779 Filed 4-18-17; 8:45 am]
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