[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]


 ========================================================================
 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.
 
 ========================================================================
 

  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).

-----------------------------------------------------------------------

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
----------------------------------------------------------------------------------------------------------------
                                                                                                 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.
----------------------------------------------------------------------------------------------------------------

    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          1 work-hour x $85 per hour =            $15,000          $15,085
 assembly.                                      $85.
----------------------------------------------------------------------------------------------------------------

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]
 BILLING CODE 4910-13-P