[Federal Register Volume 83, Number 199 (Monday, October 15, 2018)]
[Rules and Regulations]
[Pages 51829-51832]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-22009]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-1116; Product Identifier 2016-NE-32-AD; Amendment 
39-19459; AD 2018-21-01]
RIN 2120-AA64


Airworthiness Directives; Honeywell International Inc. Turbofan 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2017-20-06 for 
certain Honeywell International Inc. (Honeywell) AS907-1-1A turbofan 
engines. AD 2017-20-06 required a one-time inspection of the second 
stage low-pressure turbine (LPT2) blades and, if the blades fail the 
inspection, the replacement of the blades with a part eligible for 
installation. This AD continues to 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. This AD was prompted 
by the need to clarify the Applicability and Compliance sections of AD 
2017-20-06. We are issuing this AD to address the unsafe condition on 
these products.

DATES: This AD is effective November 19, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of November 9, 
2017 (82 FR 46379, October 5, 2017).

ADDRESSES: For service information identified in this final rule, 
contact Honeywell International Inc., 111 S 34th Street, Phoenix, AZ 
85034-2802; phone: 800-601-3099; internet: https://myaerospace2.honeywell.com/wps/portal. You may view this service 
information at the FAA, Engine and Propeller Standards Branch, 1200 
District Avenue, Burlington, MA 01803. For information on the 
availability of this material at the FAA, call 781-238-7759. It is also 
available on the internet at http://www.regulations.gov by searching 
for and locating Docket No. FAA-2017-1116.

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-
1116; 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 final rule, the regulatory evaluation, any comments received, and 
other information. The address for Docket Operations (phone: 800-647-
5527) is U.S. Department of Transportation, Docket Operations, M-30, 
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, 
Washington, DC 20590.

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:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2017-20-06, Amendment 39-19063 (82 FR 46379, 
October 5, 2017), (``AD 2017-20-06''). AD 2017-20-06 applied to certain 
Honeywell International Inc. (Honeywell) AS907-1-1A turbofan engines. 
The NPRM published in the Federal Register on January 30, 2018 (83 FR 
4167). The NPRM was prompted by the need to clarify the Applicability 
and Compliance sections of AD 2017-20-06. The NPRM proposed to continue 
to require 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 issuing this AD to address the unsafe 
condition on these products.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM and 
the FAA's response to each comment.

Request To Align the Compliance Requirements With the Service Bulletin 
(SB)

    Bombardier Aerospace (Bombardier) requested that the compliance

[[Page 51830]]

requirements of the AD be aligned with Honeywell SB AS907-72-9067, 
Revision 1, dated March 20, 2017. Bombardier asked that we remove the 
requirements for measured wear requirements for recording of wear. 
Bombardier noted that Honeywell SB AS907-72-9067 requires contact 
between the LPT2 rotor blade Z-gap.
    We disagree. Honeywell SB AS907-72-9067, Revision 1, dated March 
20, 2017 and the compliance section of this AD provide the same 
guidance for measuring and recording wear with a borescope at the LPT2 
blade shroud Z-gap. Reported borescope inspections of high-time engines 
show that blade-to-blade contact at the Z-gap is difficult to measure 
with a borescope. The FAA and Honeywell agree that the measured wear 
limit of 0.005'', as defined by the Honeywell Light Maintenance Manual 
(LMM) AS907-1-1A, 72-00-00, is acceptable for this AD.
    Additionally, the FAA disagrees with the request to remove the 
requirement for recordings of the borescope inspection. We find that 
making these recordings with a clean digital image helps us to identify 
wear characteristics, severity, and cumulative damage of LPT2 blade 
assembly and to provide future borescope requirements for LPT blade 
maintenance. We did not change this AD.

Request To Revise Costs of Compliance

    Bombardier Aerospace requested that we align the cost estimates in 
this AD with the cost estimates in Honeywell's SB.
    We disagree. The slight differences in costs between the NPRM and 
Honeywell's SB reflect the additional recording requirements in this 
AD. We did not change this AD.

Revision to Applicability

    The intent of the NPRM was to limit the applicability of this AD to 
affected blades that have more than 8,000 hours since new on November 
9, 2017 (the effective date of AD 2017-20-06). We therefore revised the 
applicability to refer to ``November 9, 2017,'' instead of ``the 
effective date of this AD.''

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD as proposed.

Related Service Information Under 1 CFR Part 51

    We reviewed Honeywell SB AS907-72-9067, Revision 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 describes procedures for inspecting the LPT2 
blades. We also reviewed the Honeywell LMM 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.

Costs of Compliance

    We estimate that this AD affects 40 engines installed on airplanes 
of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     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.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements 
that would be required based on the results of the 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.
----------------------------------------------------------------------------------------------------------------

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 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 currently 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 1 hour per response, including the time for reviewing 
instructions, searching existing data sources, gathering and 
maintaining the data needed, completing and reviewing the collection of 
information. All responses to this collection of information are 
mandatory. Send comments regarding this burden estimate or any other 
aspect of this collection of information, including suggestions for 
reducing this burden to: Information Collection Clearance Officer, 
Federal Aviation Administration, 10101 Hillwood Parkway, Fort Worth, TX 
76177-1524.

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

[[Page 51831]]

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 AD will not have federalism 
implications under Executive Order 13132. This AD will 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 this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under 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.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 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) 
2017-20-06, Amendment 39-19063 (82 FR 46379, October 5, 2017), and 
adding the following new AD:

2018-21-01 Honeywell International Inc.: Amendment 39-19459; Docket 
No. FAA-2017-1116; Product Identifier 2016-NE-32-AD.

(a) Effective Date

    This AD is effective November 19, 2018.

(b) Affected ADs

    This AD replaces AD 2017-20-06, Amendment 39-19063 (82 FR 46379, 
October 5, 2017).

(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 3035602-1, installed, that have 
more than 8,000 hours since new on November 9, 2017 (the effective 
date of AD 2017-20-06).

(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. The unsafe condition, if not corrected, could result in 
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.

(g) Required Actions

    Within 200 hours time in service after the effective date of 
this AD, do the following:
    (1) 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. 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.
    (2) 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.
    (3) 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, 
and do the following:
    (i) Identify the three Z gap contact areas with the greatest 
amount of wear and/or fretting.
    (ii) 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.
    (iii) Send the results to Honeywell at 
[email protected] within 30 days after completing 
these actions.

(h) Credit for Previous Actions

    You may take credit for the actions required by paragraphs 
(g)(1) and (2) 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.

(i) 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 currently 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 1 hour per response, including the 
time for reviewing instructions, searching existing data sources, 
gathering and maintaining the data needed, completing and reviewing 
the collection of information. All responses to this collection of 
information are mandatory. Send comments regarding this burden 
estimate or any other aspect of this collection of information, 
including suggestions for reducing this burden to: Information 
Collection Clearance Officer, Federal Aviation Administration, 10101 
Hillwood Parkway, Fort Worth, TX 76177-1524.

(j) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles ACO Branch, FAA, may 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 
Los Angeles ACO Branch, send it to the attention of the person 
identified in paragraph (k) of this AD. You may email your request 
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

    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].

(l) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (3) The following service information was approved for IBR on 
November 9, 2017 (82 FR 46379, October 5, 2017).
    (i) Honeywell Service Bulletin AS907-72-9067, Revision 1, dated 
March 20, 2017.
    (ii) Reserved.

[[Page 51832]]

    (4) For Honeywell service information identified in this AD, 
contact Honeywell International Inc., 111 S 34th Street, Phoenix, AZ 
85034-2802; phone: 800-601-3099; internet: https://myaerospace2.honeywell.com/wps/portal.
    (5) You may view this service information at FAA, Engine and 
Propeller Standards Branch, 1200 District Avenue, Burlington, MA 
01803. For information on the availability of this material at the 
FAA, call 781-238-7759.
    (6) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Burlington, Massachusetts, on October 3, 2018.
Robert J. Ganley,
Manager, Engine and Propeller Standards Branch, Aircraft Certification 
Service.
[FR Doc. 2018-22009 Filed 10-12-18; 8:45 am]
 BILLING CODE 4910-13-P