[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: [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-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
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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
[email protected] 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: [email protected].
(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]
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