[Federal Register Volume 85, Number 23 (Tuesday, February 4, 2020)]
[Proposed Rules]
[Pages 6110-6115]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-02005]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0967; Product Identifier 2017-NE-35-AD]
RIN 2120-AA64


Airworthiness Directives; GE Aviation Czech s.r.o. Turboprop 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Supplemental Notice of proposed rulemaking (SNPRM); reopening 
of comment period.

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SUMMARY: The FAA is revising an earlier proposal for all GE Aviation 
Czech s.r.o. M601D-11, M601E-11, M601E-11A, M601E-11AS, M601E-11S, 
M601F, H80, H80-100, H80-200, H75-100, H75-200, H85-100, and H85-200 
turboprop engines. This action revises the notice of proposed 
rulemaking (NPRM) by revising the compliance time requirements for 
replacement of affected engine outlet system hardware. The FAA is 
proposing this airworthiness directive (AD) to address the unsafe 
condition on these products. At the request of some commenters, the FAA 
is reopening the comment period to allow the public the chance to 
comment on these changes.

DATES: The comment period for the NPRM published in the Federal 
Register on January 24, 2018 (83 FR 3287), is reopened.
    The FAA must receive comments on this SNPRM by March 20, 2020.

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 https://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 SNPRM, contact GE 
Aviation Czech s.r.o., Beranov[yacute]ch 65, 199 02 Praha 9--
Let[ncaron]any, Czech Republic; phone: +420 222 538 111; fax: +420 222 
538 222. 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.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0967; 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 SNPRM, the mandatory continuing airworthiness information (MCAI), 
the regulatory evaluation, any comments received, and other 
information. The street address for Docket Operations is listed above. 
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Barbara Caufield, Aerospace Engineer, 
ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; phone: 
781-238-7146; fax: 781-238-7199; email: [email protected].

SUPPLEMENTARY INFORMATION: 

Comments Invited

    The FAA invites 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-2017-0967; 
Product Identifier 2017-NE-35-AD'' at the beginning of your comments. 
The FAA specifically invites comments on the overall regulatory, 
economic, environmental, and energy aspects of this SNPRM. The FAA will 
consider all comments received by the closing date and may amend this 
SNPRM because of those comments.
    Except for Confidential Business Information (CBI) as described in 
the following paragraph, and other information as described in 14 CFR 
11.35, the FAA will post all comments received, without change, to 
https://www.regulations.gov, including any personal information you 
provide. The FAA will also post a report summarizing each substantive 
verbal contact received about this proposed AD.

Confidential Business Information

    Confidential Business Information (CBI) is commercial or financial 
information that is both customarily and actually treated as private by 
its owner. Under the Freedom of Information Act (FOIA) (5 U.S.C. 552), 
CBI is exempt from public disclosure. If your comments responsive to 
this SNPRM contain commercial or financial information that is 
customarily treated as private, that you actually treat as private, and 
that is relevant or

[[Page 6111]]

responsive to this SNPRM, it is important that you clearly designate 
the submitted comments as CBI. Please mark each page of your submission 
containing CBI as ``PROPIN.'' The FAA will treat such marked 
submissions as confidential under the FOIA, and they will not be placed 
in the public docket of this SNPRM. Submissions containing CBI should 
be sent to Barbara Caufield, Aerospace Engineer, ECO Branch, FAA, 1200 
District Avenue, Burlington, MA 01803. Any commentary that the FAA 
receives which is not specifically designated as CBI will be placed in 
the public docket for this rulemaking.

Discussion

    The FAA issued an NPRM to amend 14 CFR part 39 by adding an AD that 
would apply to all GE Aviation Czech s.r.o. M601D-11, M601E-11, M601E-
11A, M601E-11AS, M601E-11S, M601F, H75-100, H75-200, H80, H80-100, H80-
200, H85-100, and H85-200 turboprop engines. The NPRM published in the 
Federal Register on January 24, 2018 (83 FR 3287). The NPRM was 
prompted by a review by the manufacturer that identified the 
possibility of a power turbine (PT) rotor overspeed and the uncontained 
release of PT blades. The NPRM proposed to require installing a 
modified engine outlet system.
    The European Union Aviation Safety Agency (EASA), which is the 
Technical Agent for the Member States of the European Community, has 
issued EASA AD 2017-0151R1, dated December 5, 2018 (referred to after 
this as ``the MCAI''), to address the unsafe condition on these 
products. The MCAI states:

    A recent design review identified the possibility of failure of 
the power turbine (PT) or quill shaft splines.
    This condition, if not corrected, could lead to a PT rotor 
overspeed, with consequent release of PT blade(s), possibly 
resulting in high energy debris and damage to, and/or reduced 
control of, the aeroplane.
    To address this potential unsafe condition, GE Aviation Czech 
(GEAC) designed a modification (mod) of the engine outlet system and 
issued the ASB, later revised, providing instructions for 
modification of engines in service, and EASA issued AD 2017-0151, 
requiring modification of the affected engines, and prohibiting 
installation of pre-mod parts.
    Since that [EASA] AD was issued, GEAC completed a TBO extension 
program, and revised the ASB (now at Revision 03) and the applicable 
EMM accordingly.
    For the reasons stated above, this [EASA] AD is revised to 
include reference to the revised EMM.

    You may obtain further information by examining the MCAI in the AD 
docket on the internet at https://www.regulations.gov by searching for 
and locating Docket No. FAA-2017-0967.

Actions Since the NPRM Was Issued

    Since the FAA issued the NPRM, GE Aviation Czech s.r.o. has revised 
its service information. GE Aviation Czech s.r.o. published GE Aviation 
Alert Service Bulletin (ASB) ASB-M601E-72-00-00-0070[03], ASB-M601D-72-
00-00-0053[03], ASB-M601F-72-00-00-0036[03], ASB-M601T-72-00-00-
0029[03], ASB-M601Z-72-00-00-0039[03], ASB-H75-72-00-00-0011[03], ASB-
H80-72-00-00-0025[03], and ASB-H85-72-00-00-0007[03] (single document), 
dated July 24, 2018. In addition, EASA has revised its AD to 
incorporate changes from the revised ASB in EASA AD 2017-0151R1, dated 
December 5, 2018.

Comments

    The FAA gave the public the opportunity to comment on the NPRM. The 
following presents the comments received on the NPRM and the FAA's 
response to each comment.

Request To Exempt Part 137 Operators

    Thrush Aircraft, Inc., Swing Wing, Inc., and an individual 
commenter requested that the proposed rule exempt from its 
applicability section 14 CFR part 137 restricted category agricultural 
operators. The commenters stated that the proposed rule would have no 
significant effect on improving safety. They further commented that 
documented single engine uncontained events caused minor damage or 
penetrations to the engine nacelle and did not affect any primary 
structure of the aircraft or any aircraft systems.
    The FAA partially agrees. The FAA agrees with the commenter that 
there may be events in which an engine uncontainment does not have a 
hazardous effect on the aircraft or its occupant. There is still a risk 
of total loss of engine power and damage to the aircraft. The FAA 
disagrees with removing 14 CFR part 137 operators of restricted 
agricultural category aircraft from the applicability section of the 
proposed AD. The FAA considers an uncontained engine failure an unsafe 
condition regardless of the aircraft type on which the engine is 
installed.

Request To Consider Rule Significant

    Swing Wing, Inc., Thrush Aircraft, Inc., and an individual 
commenter requested that the FAA consider the proposed rule a 
significant regulatory action under Executive Order 12866 and a 
significant rule under the DOT Regulatory Policies and Procedures. The 
commenters stated that the cost to comply with the required actions of 
this AD will be much higher than what is shown in the economic costs 
section of the proposed AD since it did not consider lost revenue.
    The FAA disagrees. The estimated costs set forth in the NPRM and in 
this supplemental NPRM do not rise to the level of a ``Significant 
regulatory action'' as defined in Executive Order 12866 or under DOT 
Regulatory Policies and Procedures.

Request To Consider Rule Significant Effect on Small Businesses

    Swing Wing, Inc., Thrush Aircraft, Inc., and an individual 
commenter noted that the proposed rule would have a significant effect 
on small businesses. The commenters asked that the FAA therefore 
consider the economic impact of the proposed rule.
    In accordance with the Regulatory Flexibility Act, the FAA must 
perform a review to determine whether a rule will have a significant 
economic impact on a substantial number of small entities. Within this 
preamble, the FAA is publishing its initial Regulatory Flexibility 
Analysis.

Request To Delay Rule Implementation

    Swing Wing, Inc. and Thrush Aircraft, Inc. requested that the FAA 
delay implementation of this proposed rule by 24 to 36 months. The 
commenters requested that the FAA analyze the effective date of the AD 
to determine how it would affect 14 CFR part 137 operators. The 
commenters indicated that a delay of 24 to 36 months in the effective 
date would be commensurate with the compliance times in Table 1 of 
paragraph (g) as originally proposed by the engine manufacturer. The 
commenters further state that a delay of 24 to 36 months would allow 
operators to plan, schedule, and budget for accomplishing the required 
actions of the AD.
    The FAA disagrees. Delaying the implementation of the AD by 24 to 
36 months would not be consistent with the safety objectives of the 
rule.

Request To Revise Compliance Time

    GE Aviation Czech s.r.o. requested the FAA revise the compliance 
time to remove the 6,600 engine equivalent cycles since new or since 
last overhaul requirement. GE Aviation Czech s.r.o. indicated it had 
held discussions with Thrush Aircraft, Inc. and EASA to remove the 
6,600 engine equivalent cycle removal requirement and EASA has revised 
their AD to do the same.
    The FAA agrees to remove the 6,600 engine equivalent cycles removal

[[Page 6112]]

requirement. GE Aviation Czech s.r.o. has revised its Service Bulletin 
to remove the 6,600 engine equivalent cycles removal requirement. EASA 
also published a revised AD 2017-0151R1, dated December 5, 2018, that 
removes the 6,600 engine equivalent cycles requirement. The FAA revised 
the compliance requirements in this proposed rule by removing the 6,600 
engine equivalent cycles removal requirement.

Revision To Compliance Requirement

    In addition, GE Aviation Czech s.r.o. and EASA revised the 
compliance time requirements in their ASB and AD, respectively, by 
adding a reference to removing affected parts within the compliance 
times identified in the Airworthiness Limitations Section (ALS) of the 
applicable engine manual. The FAA revised the compliance requirements 
in this proposed rule by adding a similar reference.

Revision to Cost Estimate

    The FAA reduced the number of estimated engines affected from 167 
in the NPRM to 42 in this SNPRM. The FAA is basing this estimate on the 
number of affected airplanes listed in the FAA's Aircraft Registry 
Database.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed GE Aviation ASB ASB-M601E-72-00-00-0070[03], ASB-
M601D-72-00-00-0053[03], ASB-M601F-72-00-00-0036[03], ASB-M601T-72-00-
00-0029[03], ASB-M601Z-72-00-00-0039[03], ASB-H75-72-00-00-0011[03], 
ASB-H80-72-00-00-0025[03], and ASB-H85-72-00-00-0007[03] (single 
document), dated July 24, 2018. The ASB describes procedures for 
removal and replacement of the engine outlet system hardware. 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.

FAA's Determination

    This product has been approved by the aviation authority of the 
Czech Republic and is approved for operation in the United States. 
Pursuant to our bilateral agreement with the European Community, EASA 
has notified us of the unsafe condition described in the MCAI and 
service information referenced above. The FAA is proposing this AD 
because the agency evaluated all information provided by EASA and 
determined the unsafe condition exists and is likely to exist or 
develop on other products of the same type design.

Proposed Requirements of This SNPRM

    This SNPRM would require replacement of the affected engine outlet 
system hardware.

Costs of Compliance

    The FAA estimates that this proposed AD affects 42 engines 
installed on airplanes of U.S. registry.
    The FAA estimates the following costs to comply with this proposed 
AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
               Action                         Labor cost            Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Replace exhaust system parts.......  64 work-hours x $85 per             $63,000         $68,440      $2,874,480
                                      hour = $5,440.
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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.
    The FAA is 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 Flexibility Determination

    The Regulatory Flexibility Act of 1980 (Pub. L. 96-354, codified as 
amended at 5 U.S.C. 601-612) (RFA) establishes ``as a principle of 
regulatory issuance that agencies shall endeavor, consistent with the 
objectives of the rule and of applicable statutes, to fit regulatory 
and informational requirements to the scale of the businesses, 
organizations, and governmental jurisdictions subject to regulation. To 
achieve this principle, agencies are required to solicit and consider 
flexible regulatory proposals and to explain the rationale for their 
actions to assure that such proposals are given serious 
consideration.'' Public Law 96-354, 2(b), Sept. 19, 1980. The RFA 
covers a wide-range of small entities, including small businesses, not-
for-profit organizations, and small governmental jurisdictions. 
Agencies must perform a review to determine whether a rule will have a 
significant economic impact on a substantial number of small entities. 
If the agency determines that it will, the agency must prepare a 
regulatory flexibility analysis as described in the RFA.
    Compliance cost of this proposed AD comes from the removal and 
replacement of the exhaust system parts. Estimated compliance cost per 
engine is identified below.
    Labor cost = 64 repair hours per engine * $85 Mean Hourly Wage = 
$5,440.
    Cost of Parts = $63,000 per engine (Source: GE Aviation Czech).
    $5,440 labor per engine + $63,000 parts per engine = $68,440 
compliance cost per engine.
    To estimate the revenue impacts of the proposed AD on these 38 
small operators, the FAA used the total estimated one-time costs of 
compliance per each engine ($68,440) and divided it by the estimated 
annual revenue of each entity ($700,000). The FAA determined all 38 
small businesses that would be affected by this proposed AD would 
experience impacts of approximately 9 percent of their annual revenue 
during the implementation of this AD ($68,440 / $700,000).

[[Page 6113]]

Initial Regulatory Flexibility Analysis

    Under Section 603(b) and (c) of the RFA, the initial analysis must 
address the following six areas:
    (1) Description of reasons the agency is considering the action;
    (2) Statement of the legal basis and objectives for the proposed 
rule;
    (3) Description of the record keeping and other compliance 
requirements of the proposed rule;
    (4) All federal rules that may duplicate, overlap, or conflict with 
the proposed rule;
    (5) Description and an estimated number of small entities to which 
the proposed rule will apply; and
    (6) Describe alternatives considered.

Reasons the Agency Is Considering the Action

    This proposed AD was prompted by a review by the manufacturer that 
identified the possibility of a PT overspeed and the uncontained 
release of PT blades. The FAA is proposing this AD to prevent 
uncontained release of the PT blades. This proposed AD would require 
installing a modified engine outlet system. The unsafe condition, if 
not addressed, could result in failure of the PT blades, uncontained 
release of the blades, damage to the engine, and damage to the 
airplane.

Legal Basis and Objectives for the Proposed Rule

    The FAA's legal basis for this proposed AD is discussed in detail 
under the ``Authority for this Rulemaking'' section.

Description and an Estimated Number of Small Entities to Which the 
Proposed Rule Would Apply

    This proposed AD would apply to all GE Aviation Czech s.r.o. M601D-
11, M601E-11, M601E-11A, M601E-11AS, M601E-11S, M601F, H75-100, H75-
200, H80, H80-100, H80-200, H85-100, and H85-200 turboprop engines. 
These engines are typically installed on airplanes that are owned and 
operated by aerial application businesses, which is a small segment of 
the aviation industry. These airplanes, also known as ``crop-dusters,'' 
spread fertilizer, insecticides, fungicides, and weed killers.\1\
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    \1\ ``Flying Low Is Flying High As Demand for Crop-Dusters 
Soars'', by Jonathan Welsh, updated Aug. 14, 2009: https://www.wsj.com/articles/SB125020758399330769. Accessed on July 26, 
2019.
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    The FAA searched the 2018 Aircraft Registration database that 
contains the records of all U.S. Civil Aircraft maintained by the FAA's 
Aircraft Registration Branch and identified 42 airplanes with GE H80 
series engines or equivalent turboprop engines installed. The Aircraft 
Registration database shows that 38 companies own these 42 airplanes--4 
companies own 2 airplanes, while the remaining 34 companies own 1 
airplane each. Based on these registration records, the FAA assumes 
that approximately each entity or business owned one airplane.
    By using the Small Business Administration (SBA)'s size standards 
and the North American Industry Classification System (NAICS) code 
classifications, the FAA is able to determine whether a business is 
small or not. These entities would operate under NAICS code 115112, 
Soil Preparation, Planting, and Cultivating. The size standards for 
this NAICS code as provided by SBA's Size Standards Table \2\ is $7.5 
million in annual revenues. Therefore, entities generating less than 
$7.5 million in annual revenues would be treated as small businesses 
for the purposes of this analysis.
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    \2\ https://www.sba.gov/sites/default/files/files/Size_Standards_Table.pdf Accessed on July 26, 2019.
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    The FAA assumes that all 38 operators above that would be affected 
by this proposed AD are small businesses because $700,000 annual 
revenue for a first-class, used turbine agricultural aviation plane \3\ 
is a reasonable industry estimate. On average, entities operating in 
the aerial application industry would generate approximately $700,000 
each year ($700,000 x 1 crop-duster airplane), which is below $7.5 
million revenue size standards for NAICS code 115112. Therefore, the 
FAA assumes all 38 registered company owners or operators to be small 
entities.
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    \3\ ``How much does it cost?'' by Bill Lavender, April 3, 2017. 
https://agairupdate.com/how-much-does-it-cost/ Accessed on July 26, 
2019.
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Record-Keeping and Other Compliance Requirements of the Proposed Rule

    There are no record-keeping costs associated with this proposed 
rule.

Duplicative, Overlapping, or Conflicting Federal Rules

    There are no relevant Federal rules that may duplicate, overlap, or 
conflict with this proposed rule.

Alternatives to the Proposed AD

    There is no direct safety alternative to the modification of the 
engine outlet system. The modification addresses a safety issue aimed 
at preventing an uncontained release of the PT blades.

Regulatory Findings

    The FAA 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, and
    (2) Will not affect intrastate aviation in Alaska.

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):

GE Aviation Czech s.r.o. (Type Certificate previously held by WALTER 
Engines a.s., Walter a.s., and MOTORLET a.s.): Docket No. FAA-2017-
0967; Product Identifier 2017-NE-35-AD.

(a) Comments Due Date

    The FAA must receive comments by March 20, 2020.

(b) Affected ADs

    None.

(c) Applicability

    (1) This AD applies to all GE Aviation Czech s.r.o. M601D-11, 
M601E-11, M601E-11A, M601E-11AS, M601E-11S, M601F, H75-100, H75-200, 
H80, H80-100, H80-200, H85-100, and H85-200 turboprop engines.
    (2) These engines are known to be installed on, but not limited 
to, Thrush Aircraft, Inc. (formerly Quality, Ayres, Rockwell) S-2R, 
PZL ``Warszawa-Ok[eogon]cie'' PZL-106 (Kruk), Air Tractor AT-300, 
AT-400 and AT-500 series, Allied Ag Cat Productions, Inc. (formerly 
Schweizer, Grumman American) G-164 series, RUAG (formerly Dornier) 
Do 28 and Aircraft Industries (formerly LET) L-410 airplanes.

[[Page 6114]]

(d) Subject

    Joint Aircraft System Component (JASC) Code 7810, Engine 
Collector/Tailpipe/Nozzle.

(e) Unsafe Condition

    This AD was prompted by a review by the manufacturer that 
identified the possibility of a power turbine (PT) overspeed and the 
uncontained release of PT blades. The FAA is issuing this AD to 
prevent uncontained release of the PT blades. The unsafe condition, 
if not addressed, could result in failure of the PT blades, 
uncontained release of the blades, 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) After the effective date of this AD, replace the parts 
listed in Tables 2 through 5 to paragraph (g) of this AD with the 
parts identified in Planning Information, Paragraph 1.5, Sections I 
through IV, respectively in GE Aviation Alert Service Bulletin (ASB) 
ASB-M601E-72-00-00-0070 [03], ASB-M601D-72-00-00-0053 [03], ASB-
M601F-72-00-00-0036 [03], ASB-M601T-72-00-00-0029 [03], ASB-M601Z-
72-00-00-0039 [03], ASB-H75-72-00-00-0011 [03], ASB-H80-72-00-00-
0025 [03], and ASB-H85-72-00-00-0007 [03] (single document), dated 
July 24, 2018, using the criteria below, whichever occurs first:
    (i) During the next engine shop visit,
    (ii) within the compliance time identified in the applicable 
Airworthiness Limitations Section of the existing maintenance manual 
for the affected engine model, or
    (iii) within the compliance time, in years after the effective 
date of this AD, shown in Table 1 of this AD.
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[[Page 6115]]


[GRAPHIC] [TIFF OMITTED] TP04FE20.002

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    (2) [Reserved]

(h) Installation Prohibition

    (1) Do not install any part with a P/N listed in Tables 2through 
5 to paragraph (g) of this AD on any engine after that engine has 
been modified as required by paragraph (g)(1) of this AD.
    (2) After the effective date of this AD, do not install a part 
with a P/N listed in Tables 2 through 5 of this AD on any engine 
manufactured on or after September 1, 2017.

(i) Definition

    For the purpose of this AD, an engine shop visit is when the 
engine is overhauled or rebuilt, or the PT is disassembled.

(j) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, ECO 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 
ECO Branch, send it to the attention of the person identified in 
paragraph (k)(1) 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

    (1) For more information about this AD, contact Barbara 
Caufield, Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, 
Burlington, MA 01803; phone: 781-238-7146; fax: 781-238-7199; email: 
[email protected].
    (2) Refer to European Union Aviation Safety Agency (EASA) AD 
2017-0151R1, dated December 5, 2018, for more information. You may 
examine the EASA AD in the AD docket on the internet at https://www.regulations.gov by searching for and locating it in Docket No. 
FAA-2017-0967.
    (3) For service information identified in this AD, contact GE 
Aviation Czech s.r.o., Beranov[yacute]ch 65, 199 02 Praha 9--
Let[ncaron]any, Czech Republic; phone: +420 222 538 111; fax: +420 
222 538 222. You may view this referenced 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.

    Issued in Burlington, Massachusetts, on January 29, 2020.
Robert J. Ganley,
Manager, Engine and Propeller Standards Branch, Aircraft Certification 
Service.
[FR Doc. 2020-02005 Filed 2-3-20; 8:45 am]
 BILLING CODE 4910-13-P