[Federal Register Volume 83, Number 119 (Wednesday, June 20, 2018)]
[Proposed Rules]
[Pages 28550-28553]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-13211]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0216; Product Identifier 1988-ANE-18-AD]
RIN 2120-AA64


Airworthiness Directives; Honeywell International Inc. Turboprop 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede Airworthiness Directive (AD) 88-12-10, 
which applies to certain Honeywell International Inc. (Honeywell) 
TPE331 turboprop engines. AD 88-12-10 requires reducing the life limit 
for certain second stage turbine rotors. Since we issued AD 88-12-10, 
we received a report that a TPE331-11U engine experienced an 
uncontained rotor separation. In addition, cracks were discovered 
through eddy current inspection (ECI) in the bore of the second stage 
turbine rotor assembly after publication of AD 88-12-10. This proposed 
AD would require removing certain second stage turbine rotors from 
service at a reduced life limit. We are proposing this AD to address 
the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by August 6, 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-
0216; 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-2018-0216; 
Product Identifier 1988-ANE-18-AD'' at the beginning of your comments. 
We specifically invite comments on the overall regulatory,

[[Page 28551]]

economic, environmental, and energy 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 88-12-10, Amendment 39-5910 (53 FR 19766, May 31, 
1988), (``AD 88-12-10''), for certain Honeywell TPE331 turboprop 
engines. AD 88-12-10 requires reducing the life limit for certain 
second stage turbine rotors. AD 88-12-10 resulted from the failure of a 
second stage turbine rotor due to crack growth from a bore initiation 
site induced by low cycle fatigue. We issued AD 88-12-10 to prevent 
failure of the second stage turbine rotor, leading to uncontained 
failure of the second stage turbine rotor.

Actions Since AD 88-12-10 Was Issued

    Since we issued AD 88-12-10, a TPE331-11U engine installed on an M7 
Aerospace LP SA227 airplane experienced an uncontained tri-hub rotor 
separation during climb on April 7, 2015. One of the three fragments 
from the second stage turbine rotor assembly, part number 3102106-6, 
came to rest inside the fuselage wall of the twin-engine airplane. In 
addition, second stage turbine rotor assembly cracks in the bore were 
discovered by ECI after publication of AD 88-12-10. This evidence 
supports higher stresses than originally calculated and supports the 
inability of the normal rotor inspection method, fluorescent penetrant 
inspection, to detect small cracks in the bore. In addition, we are 
adding the TPE331-8 and -10N model engines to the applicability of this 
AD because the design and material of its second stage turbine rotor 
are similar to those in the TPE331-10, -10R, -10U, -10UA, -10UF, -10UG, 
-10UGR, -10UR, and -11U model engines.

Related Service Information

    We reviewed Honeywell Service Bulletin (SB) TPE331-72-A2319, 
Revision 0, dated April 25, 2018 and TPE331-72-A2310, Revision 0, dated 
January 26, 2018. These SBs describe procedures for replacement of the 
second stage turbine rotor assembly installed on TPE331-8, -10, -10N, -
10R, -10U, -10UA, -10UF, -10UG, -10UGR, -10UR, and -11U model engines.

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 certain requirements of AD 88-12-10. 
This proposed AD would require removing certain second stage turbine 
rotors from service at a reduced life limit.

Differences Between This Proposed AD and the Service Information

    This NPRM proposes to allow certain rotors more time in service 
before their removal than is allowed by Honeywell SBs TPE331-72-A2310, 
Revision 0, dated January 26, 2018, and TPE331-72-A2319, Revision 0, 
dated April 25, 2018. The FAA finds that allowing an additional 100 
cycles in service before their removal provides a sufficient level of 
safety for applicable second stage turbine rotors that have been in 
service for 30 years after the publication of AD 88-12-10. In addition, 
the SB includes a calendar deadline of 5 years for removal of the 
applicable second stage turbine rotors that have exceeded their life-
limit of 3,000 cycles. The FAA is instead proposing a requirement to 
remove applicable rotors at the next access and prohibiting the 
installation of applicable rotors. We find that the calendar deadline 
is inconsistent with our compliance requirements.

Costs of Compliance

    We estimate that this proposed AD affects 100 engines installed on 
airplanes of U.S. registry.
    We estimate that 20 commercial engines and 80 general aviation 
engines will need this turbine rotor replacement to comply with this 
proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Scheduled rotor replacement...........  1 work-hour x $85 per             $7,500          $7,585        $379,250
                                         hour = $85.
Unscheduled rotor replacement.........  41 work-hours x $85 per            7,500          10,985         549,250
                                         hour = $3,485.
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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.
    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,

[[Page 28552]]

    (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) 
88-12-10, Amendment 39-5910 (53 FR 19766, May 31, 1988), 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-2018-0216; Product Identifier 1988-ANE-18-AD.

(a) Comments Due Date

    The FAA must receive comments on this AD action by August 6, 
2018.

(b) Affected ADs

    This AD replaces AD 88-12-10, Amendment 39-5910 (53 FR 19766, 
May 31, 1988) (``AD 88-12-10'').

(c) Applicability

    This AD applies to Honeywell International Inc. (Honeywell) 
TPE331-8, -10, -10N, -10R, -10U, -10UA, -10UF, -10UG, -10UGR, -10UR, 
and -11U turboprop engines with second stage turbine rotor 
assemblies, part number (P/Ns) 3102106-1, -6, and -8 or P/N 3101514-
1, -10 and -12, installed.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7250, Turbine 
Section.

(e) Unsafe Condition

    This AD was prompted by a report that a TPE331-11U engine 
installed on an M7 SA227 airplane experienced an uncontained rotor 
separation and the discovery of cracks in the bore of the second 
stage turbine rotor assembly after publication of AD 88-12-10. We 
are issuing this AD to prevent failure of the second stage turbine 
rotor. The unsafe condition, if not addressed, could result in 
uncontained release of the second stage turbine rotor, damage to the 
engine, and damage to the airplane.

(f) Compliance

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

(g) Required Actions

    (1) Remove from service the applicable second stage turbine 
rotor assembly, P/Ns 3102106-1, -6 and -8, according to the schedule 
in Table 1 to Paragraph (g)(1) of this AD:
[GRAPHIC] [TIFF OMITTED] TP20JN18.005

    (2) Remove from service the applicable second stage turbine 
rotor assembly, P/Ns 3101514-1, -10 and -12, per the schedule in 
Table 2 to Paragraph (g)(2) of this AD:

[[Page 28553]]

[GRAPHIC] [TIFF OMITTED] TP20JN18.006

(h) Definition

    For the purpose of this AD, ``next access'' is defined as when 
the applicable second stage turbine rotor assembly is removed from 
the engine.

(i) Installation Prohibition

    As of the effective date of this AD, do not install second stage 
turbine rotor assemblies, P/Ns 3102106-1, -6, and -8 and P/Ns 
3101514-1, -10, and -12 on any engine.

(j) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles ACO, 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.
    (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 
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 referenced 
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 14, 2018.
Robert J. Ganley,
Manager, Engine and Propeller Standards Branch, Aircraft Certification 
Service.
[FR Doc. 2018-13211 Filed 6-19-18; 8:45 am]
 BILLING CODE 4910-13-P


