
[Federal Register Volume 82, Number 117 (Tuesday, June 20, 2017)]
[Proposed Rules]
[Pages 28028-28030]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-12561]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0034; Directorate Identifier 2016-NE-32-AD]
RIN 2120-AA64


Airworthiness Directives; Honeywell International Inc. Turbofan 
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) AS907-1-1A turbofan 
engines. This proposed AD was prompted by reports of loss of power due 
to failure of the second stage low-pressure turbine (LPT2) blade. This 
proposed AD would require a one-time inspection of the LPT2 blades and, 
if the blades fail the inspection, the replacement of the blades with a 
part eligible for installation. We are proposing this AD to correct the 
unsafe condition on these products.

DATES: We must receive comments on this proposed AD by August 4, 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-2017-
0034; 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: joseph.costa@faa.gov.

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-2017-0034; 
Directorate Identifier 2016-NE-32-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 received reports of a loss of power due to failure of the LPT2 
blade from high-cycle fatigue in the blade's dovetail region at similar 
times-in-service. The probable cause of this failure is wear and 
fretting of the LPT2 blade Z gap contact area at the blade tip shroud 
that leads to loss of dampening and increased vibration of the LPT2 
blade. This tip shroud condition in two new production engines with the 
same time-in-service, if not corrected, could result in failure of the 
LPT2 blades, failure of one or more engines, and loss of the airplane.

Related Service Information Under 1 CFR Part 51

    We reviewed Honeywell Service Bulletin (SB) AS907-72-9067, Revision

[[Page 28029]]

1, dated March 20, 2017. This SB describes procedures for inspecting 
the LPT2 blades. 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 SB AS907-72-9067, Revision 0, dated December 
12, 2016, which also describe procedures for inspecting the LPT2 
blades. We also reviewed the Honeywell Light Maintenance Manual, AS907-
1-1A, 72-00-00, Section 72-05-12, dated May 25, 2016, and Section 72-
55-03, dated September 27, 2011, which provide additional guidance for 
performing borescope inspections.

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 require a one-time borescope inspection of 
the LPT2 blades and, if the blades fail the inspection, replacement of 
the blades with an LPT2 rotor assembly eligible for installation.

Differences Between This Proposed AD and the Service Information

    Honeywell SB AS907-72-9067, Revision 1, dated March 20, 2017, 
recommends borescope inspections of the affected LPT2 blades with more 
than 8,000 hours-since-new (HSN) and recommends that these inspections 
be completed within 400 operating hours after the issuance of Honeywell 
SB AS907-72-9067, Revision 0, dated December 12, 2016. This NPRM would 
require inspections of affected LPT2 blades with more than 8,000 HSN 
and requires that these inspections be completed within 200 operating 
hours after the effective date of this AD. This NPRM includes a 
reporting requirement that Honeywell SB AS907-72-9067, Revision 1, 
dated March 20, 2017 does not.

Costs of Compliance

    We estimate that this proposed AD affects 40 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 per      Cost on U.S.
               Action                         Labor cost            Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Borescope inspection...............  10 work-hours x $85 per                  $0            $850         $34,000
                                      hour = $850.
Report results of inspection.......  1 work-hour x $85 per hour                0              85           3,400
                                      = 85.
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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 40 engines will need this replacement.

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                  Action                                Labor cost                 Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replacement of the LPT2 blade set.........  50 work-hours x $85 per hour =             $50,000          $54,250
                                             $4,250.
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Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a current valid OMB control number. The control 
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in 
the Costs of Compliance section of this document and includes time for 
reviewing instructions, as well as completing and reviewing the 
collection of information. Therefore, all reporting associated with 
this AD is mandatory. Comments concerning the accuracy of this burden 
and suggestions for reducing the burden should be directed to the FAA 
at 800 Independence Ave. SW., Washington, DC 20591. ATTN: Information 
Collection Clearance Officer, AES-200.

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

[[Page 28030]]

    (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.: Docket No. FAA-2017-0034; Directorate 
Identifier 2016-NE-32-AD.

(a) Comments Due Date

    We must receive comments by August 4, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Honeywell International Inc. (Honeywell) 
AS907-1-1A turbofan engines with second stage low-pressure turbine 
(LPT2) rotor blades, part number (P/N) 3035602-1, installed.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by reports of loss of power due to failure 
of the LPT2 blade. We are issuing this AD to prevent failure of the 
LPT2 blades, failure of one or more engines, and loss of the 
airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) For LPT2 rotor blades, P/N 3035602-1 that have more than 
8,000 hours since new on the effective date of this AD, perform a 
one-time borescope inspection for wear of the Z gap contact area at 
the blade tip shroud for each of the 62 LPT2 rotor blades within 200 
hours time in service after the effective date of this AD.
    (2) Use the Accomplishment Instructions, Paragraph 3.B.(1), of 
Honeywell Service Bulletin (SB) AS907-72-9067, Revision 1, dated 
March 20, 2017, to do the inspection.
    (3) If the measured wear and/or fretting of any Z gap contact 
area is greater than 0.005 inch, replace the LPT2 rotor assembly 
with a part eligible for installation before further flight.
    (4) Do the following actions within 200 hours time in service 
after the effective date of this AD:
    (i) Using a borescope make a clear digital image of the Z gap 
contact area at the blade tip shroud of the 62 LPT2 rotor blades.
    (ii) Identify the three Z gap contact areas with the greatest 
amount of wear and/or fretting.
    (iii) Record the blade position on the LPT2 rotor assembly and 
the measured wear of the three Z gap contact areas with the greatest 
amount of wear and/or fretting.
    (iv) Send the results to Honeywell at 
engine.reliability@honeywell.com within 30 days after completing 
these actions.

(g) Credit for Previous Actions

    You may take credit for the actions required by paragraphs 
(f)(1) and (4) of this AD, if you performed these actions before the 
effective date of this AD using Honeywell SB AS907-72-9067, Revision 
0, dated December 12, 2016.

(h) Paperwork Reduction Act Burden Statement

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to a penalty 
for failure to comply with a collection of information subject to 
the requirements of the Paperwork Reduction Act unless that 
collection of information displays a current valid OMB Control 
Number. The OMB Control Number for this information collection is 
2120-0056. Public reporting for this collection of information is 
estimated to be approximately 5 minutes per response, including the 
time for reviewing instructions, completing and reviewing the 
collection of information. All responses to this collection of 
information are mandatory. Comments concerning the accuracy of this 
burden and suggestions for reducing the burden should be directed to 
the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: 
Information Collection Clearance Officer, AES-200.

(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: 562-627-5246; fax: 562-627-5210; 
email: joseph.costa@faa.gov.
    (2) Honeywell SBs AS907-72-9067, Revision 0, dated December 12, 
2016 and AS907-72-9067, Revision 1, dated March 20, 2017, can be 
obtained from Honeywell International Inc., using the contact 
information in paragraph (j)(3) of this proposed AD.
    (3) For service information identified in this proposed 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/.
    (4) 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 June 13, 2017.
Robert J. Ganley,
Acting Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-12561 Filed 6-19-17; 8:45 am]
 BILLING CODE 4910-13-P


