Document ID: FAA-2018-0479-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Honeywell International Inc. Turboprop and Turboshaft Engines
Posted Date: 2018-06-25T04:00Z

[Federal Register Volume 83, Number 122 (Monday, June 25, 2018)]
[Proposed Rules]
[Pages 29479-29483]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-13523]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0479; Product 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 supersede Airworthiness Directive (AD) 2018-02-
14, which applies to certain Honeywell International Inc. (Honeywell) 
TPE331 turboprop and TSE331 turboshaft engines. AD 2018-02-14 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. Since we issued AD 
2018-02-14, we received comments to revise the applicability of that AD 
to include the TPE331-12B engine model, correct certain TPE engine 
model typographical errors, and to allow certain weld repair 
procedures. This proposed AD would expand the applicability of AD 2018-
02-14 to include the TPE331-12B engine model, correct certain engine 
model typographical errors, and allow certain weld repair procedures 
after approval. We are proposing this AD to address the unsafe 
condition on these products.

DATES: We must receive comments on this proposed AD by August 9, 2018.

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. 
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.

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-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 NPRM, the regulatory evaluation, any comments received, and other 
information. The street address for Docket Operations (phone: 800-647-
5527) is listed above. Comments will be available in the AD docket 
shortly after receipt.

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: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2018-0479; 
Product Identifier 2016-NE-23-AD'' at the beginning of your comments. 
We specifically invite comments on the overall regulatory, economic, 
environmental, and energy

[[Page 29480]]

aspects of this NPRM. We will consider all comments received by the 
closing date and may amend this NPRM 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 issued AD 2018-02-14, Amendment 39-19167 (83 FR 3263, January 
24, 2018), (``AD 2018-02-14''), for certain Honeywell TPE331 turboprop 
and TSE331 turboshaft engines. AD 2018-02-14 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. AD 2018-02-14 resulted from reports that 
combustion chamber case assemblies have cracked and ruptured. We issued 
AD 2018-02-14 to prevent failure of the combustion chamber case 
assembly.

Actions Since AD 2018-02-14 Was Issued

    Since we issued AD 2018-02-14, we determined the need to revise 
sections of that AD. We received comments indicating that the TPE331-
12B engine model was inadvertently omitted from that AD and that the 
TPE331-43-A, -43-BL, -47-A, -55-B, and -61-A engine models included 
typographical errors. We also received comments to revise the 
Compliance section, which disallows weld repairs on any combustion 
chamber case assemblies that are affected by that AD. We determined 
that allowing weld repair procedures of certain combustion chamber case 
assemblies with lower stresses may be accomplished if these procedures 
are approved by the Manager, Los Angeles ACO Branch.

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.

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.

Proposed AD Requirements

    This proposed AD would retain all of the requirements of AD 2018-
02-14. This proposed AD would revise the Applicability to include the 
TPE331-12B engine model and to correct references to the TPE331-43-A, -
43-BL, -47-A, -55-B, and -61-A engine models. This proposed AD would 
also allow weld repair procedures to the applicable combustion chamber 
case assemblies provided those procedures are approved by the Manager, 
Los Angeles ACO Branch.

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                 $0  $85 per inspection........  $479,740 per
                                    $85 per hour =                                                inspection
                                    $85.                                                          cycle.
----------------------------------------------------------------------------------------------------------------

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

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

[[Page 29481]]

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

    We have 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 that the 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, 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 removing Airworthiness Directive (AD) 
2018-02-14, Amendment 39-19167 (83 FR 3263, January 24, 2018), and 
adding the following new 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-2018-0479; Product Identifier 2016-NE-23-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by August 9, 
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.
BILLING CODE 4910-13-P

[[Page 29482]]

[GRAPHIC] [TIFF OMITTED] TP25JN18.006

[GRAPHIC] [TIFF OMITTED] TP25JN18.007

BILLING CODE 4910-13-C

(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)(1) of this AD. Information 
may be emailed 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

    (1) 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].
    (2) For service information identified in this AD, contact AD, 
contact Honeywell International Inc., 111 S 34th Street, Phoenix, AZ 
85034-2802; phone: 800-601-3099; internet: https://
myaerospace.honeywell

[[Page 29483]]

.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.

    Issued in Burlington, Massachusetts, on June 19, 2018.
Robert J. Ganley,
Manager, Engine and Propeller Standards Branch, Aircraft Certification 
Service.
[FR Doc. 2018-13523 Filed 6-22-18; 8:45 am]
BILLING CODE 4910-13-P