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Rule2024-12594

Airworthiness Directives; International Aero Engines, AG Engines

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Published

June 11, 2024

Effective

June 26, 2024

Issuing agencies

Transportation DepartmentFederal Aviation Administration

Abstract

The FAA is adopting a new airworthiness directive (AD) for certain International Aero Engines, AG (IAE AG) Model V2500 engines. This AD was prompted by an analysis of an event involving an International Aero Engines, LLC (IAE LLC) Model PW1127GA-JM engine, which experienced a high-pressure compressor (HPC) 7th-stage integrally bladed rotor (IBR-7) separation that resulted in an aborted takeoff. This AD requires performing an angled ultrasonic inspection (AUSI) of certain high-pressure turbine (HPT) 1st-stage hubs and HPT 2nd-stage hubs for cracks and replacing if necessary. This AD also requires accelerated replacement of certain HPT 1st-stage hubs and HPT 2nd-stage hubs. The FAA is issuing this AD to address the unsafe condition on these products.

Full Text

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<title>Federal Register, Volume 89 Issue 113 (Tuesday, June 11, 2024)</title>
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[Federal Register Volume 89, Number 113 (Tuesday, June 11, 2024)]
[Rules and Regulations]
[Pages 49094-49099]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2024-12594]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2024-0041; Project Identifier AD-2024-00032-E;
Amendment 39-22764; AD 2024-11-03]
RIN 2120-AA64

Airworthiness Directives; International Aero Engines, AG Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain International Aero Engines, AG (IAE AG) Model V2500 engines.
This AD was prompted by an analysis of an event involving an
International Aero Engines, LLC (IAE LLC) Model PW1127GA-JM engine,
which experienced a high-pressure compressor (HPC) 7th-stage integrally
bladed rotor (IBR-7) separation that resulted in an aborted takeoff.
This AD requires performing an angled ultrasonic inspection (AUSI) of
certain high-pressure turbine (HPT) 1st-stage hubs and HPT 2nd-stage
hubs for cracks and replacing if necessary. This AD also requires
accelerated replacement of certain HPT 1st-stage hubs and HPT 2nd-stage
hubs. The FAA is issuing this AD to address the unsafe condition on
these products.

DATES: This AD is effective June 26, 2024.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of June 26,
2024.

ADDRESSES:
AD Docket: You may examine the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2024-0041; 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, any comments received, and other
information. The address for Docket Operations 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.
Material Incorporated by Reference:
<bullet> For service information, contact International Aero
Engines, AG, 400 Main Street, East Hartford, CT 06118; phone: (860)
565-0140; email: <a href="/cdn-cgi/l/email-protection#6a020f061a585e2a1a1d441f1e0944090507">[email&#160;protected]</a>; website: <a href="http://connect.prattwhitney.com">connect.prattwhitney.com</a>.
<bullet> You may view this service information at the FAA,
Airworthiness Products Section, Operational Safety Branch, 1200
District Avenue, Burlington, MA 01803. For information on the
availability of this material at the FAA, call (817) 222-5110.

FOR FURTHER INFORMATION CONTACT: Carol Nguyen, Aviation Safety
Engineer, FAA, 2200 South 216th Street, Des Moines, WA 98198; phone:
(781) 238-7655; email: <a href="/cdn-cgi/l/email-protection#553634273a397b3b32202c303b153334347b323a23">[email&#160;protected]</a>.

SUPPLEMENTARY INFORMATION:

Background

The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to certain IAE AG Model
V2500 engines. The NPRM published in the Federal Register on February
5, 2024 (89 FR 7636). The NPRM was prompted by an event on December 24,
2022, when an Airbus Model A320neo airplane, powered by IAE LLC Model
PW1127GA-JM engines, experienced a failure of the HPC IBR-7 that
resulted in an engine shutdown and aborted take-off. Following this
event, the manufacturer conducted a records review of production and
field-returned parts and re-evaluated their engineering analysis
methodology. The new analysis found that the failure of the HPC IBR-7
was caused by a nickel powdered metal anomaly, similar in nature to an
anomaly previously observed on March 18, 2020, when an Airbus Model
A321-231 airplane, powered by IAE AG Model V2533-A5 engines,
experienced an uncontained HPT 1st-stage hub failure that resulted in
high-energy debris penetrating the engine cowling. The analysis also
concluded that there is an increased risk of failure for a
subpopulation of HPT 1st-stage hubs and HPT 2nd-stage hubs that were
manufactured from the same production campaign (a batch of nickel
powdered metal) as the HPT 1st-stage hub that failed on March 18, 2020;
these parts have a higher likelihood of containing the nickel powdered
metal anomaly and are susceptible to failure much earlier than
previously determined. In the NPRM, the FAA proposed to require
performing an AUSI of certain HPT 1st-stage hubs and HPT 2nd-stage hubs
and, depending on the results of the inspections, replacing the HPT
1st-stage hubs or HPT 2nd-stage hubs. The FAA also proposed to require
accelerated replacement of certain HPT 1st-stage hubs and HPT 2nd-stage
hubs. The FAA is issuing this AD to address the unsafe condition on
these products.

Discussion of Final Airworthiness Directive

Comments

The FAA received comments from 14 commenters, including the Air
Line Pilots Association, International (ALPA); JetBlue Airways
(JetBlue); Lufthansa Technik AG (Lufthansa); MTU Maintenance Hannover
GmbH; MTU Maintenance Zhuhai Co. Ltd; Pratt & Whitney (PW); Turkish
Engine Center (TEC); United Airlines; five anonymous commenters; and an
individual commenter. ALPA, United Airlines, the individual commenter,
and one anonymous commenter supported the proposed AD without change.
Ten commenters requested changes to the proposed AD. The following
presents the comments received on the NPRM and the FAA's response to
each comment.

[[Page 49095]]

Request To Clarify Affected Parts

Two anonymous commenters requested that the FAA clarify if HPT hubs
that were produced before 2020 are part of the affected subpopulation
if they were installed in January of 2019 or February of 2019 and had
not accumulated more than 1,200 flight cycles (FCs).
The FAA clarifies that the affected population was manufactured
from the same production campaign (a batch of nickel powdered metal) as
the HPT 1st-stage hub that failed on March 18, 2020. The FAA notes that
those affected parts are defined by serial number within the service
information documents that are incorporated by reference in this AD.
The FAA did not change this AD as a result of these comments.

Request To Clarify AUSI for Parts Removed From Service

An anonymous commenter requested that the FAA change the proposed
AD to clarify if removal of the affected part from service and
replacement with a part eligible for installation is an acceptable
alternative to performing the AUSI required by paragraph (g)(1) of the
proposed AD. The commenter noted that affected parts may be proactively
replaced or found unserviceable before the AUSI is required.
The FAA disagrees with the request to change the AD because the
AUSI required by paragraph (g)(1) of the proposed AD only applies to
``affected parts.'' If the part has been replaced with a part
``eligible for installation,'' then it is not an ``affected part'' and
the AUSI is not required. The FAA did not change this AD as a result of
this comment.

Request To Clarify Start Date for FC Accumulation

An anonymous commenter requested that the FAA clarify the point or
date from which FCs should be counted in order to remain compliant with
the proposed AD. The commenter noted that in Table 1 to Paragraph
(g)(1) of the proposed AD, the AUSI compliance times are specified in
terms of FCs, and for the HPT 1st-stage hub with Part Number (P/N)
2A5001, the compliance requirement is based on 100 FCs from a specific
reference point.
The FAA clarifies that the FC count for AUSI compliance times
begins on the effective date of this AD. The FAA has also changed the
fourth column header of Table 1 to Paragraph (g)(1), Table 2 to
Paragraph (g)(4), and Table 3 to Paragraph (g)(5) of this AD to read as
follows: ``Flight cycle (FC) limit from the effective date of this
AD.''

Request To Account for Inability To Obtain Special Instruction

JetBlue requested that the FAA do one of the following:
(1) remove the reference to PW Special Instruction No. 189F-23,
dated November 20, 2023 (PW SI No. 189F-23), from the effectivity of
the affected parts listed in Table 1 to Paragraph (g)(1) and Table 2 to
Paragraph (g)(4) of this AD; or
(2) have IAE LLC revise IAE AG Non-Modification Service Bulletin
(NMSB) V2500-ENG-72-0720, dated November 20, 2023 (V2500-ENG-72-0720)
to provide the list of the affected P/Ns and serial numbers of the hubs
mentioned in PW SI No. 189F-23; or
(3) list all affected hubs within the AD.
JetBlue noted that they were unable to obtain PW SI No. 189F-23
from IAE LLC because it relates to a military program and there are
concerns about the inadvertent release of data.
The FAA disagrees with the request because PW SI No. 189F-23
applies to the V2531-E5 engine model only, and therefore IAE only
provides PW SI No. 189F-23 to those owning or operating the product.
The FAA notes that material that is incorporated by reference in
airworthiness directives can be accessed by the means identified in the
ADDRESSES section. For clarity, the FAA added the phrase ``which only
applies to the IAE AG V2531-E5 Model engine'' at the end of each
reference to the service bulletin, except for paragraph (l), Material
Incorporated by Reference, of the final rule.

Request To Adjust Compliance Times

JetBlue requested that the FAA adjust the compliance times for
Table 1 to Paragraph (g)(1), Table 2 to Paragraph (g)(4), and Table 3
to Paragraph (g)(5) of this AD to match the drawdown period of IAE AG
NMSB V2500-ENG-72-0720. JetBlue noted that IAE AG NMSB V2500-ENG-72-
0720 provides an additional 200 FCs and is based on an effective date
of January 1, 2024, while the proposed AD provides 200 FCs less and is
based on the effective date of the AD. JetBlue also noted that it
planned the engine removal schedule based on the drawdown of IAE AG
NMSB V2500-ENG-72-0720, including working with the engine shops for
induction slots and spare engines (including obtaining lease engines).
The FAA disagrees with the request because the drawdown times for
IAE AG NMSB V2500-ENG-72-0720 started on January 1, 2024, and the FAA
reduced the compliance time for the AUSIs required by this AD in order
to better align with the control program. The FAA did not change this
AD as a result of this comment.

Comment Regarding Low Cost Estimate

JetBlue commented that the estimated cost of compliance provided in
the proposed AD is not realistic and would be only achievable for a new
engine or engine just returning to the shop. JetBlue also noted that
the estimated cost would have great financial impact on operators, and
the manufacturer is not providing a support program to address this.
The FAA disagrees that the estimated cost in the AD is unrealistic.
The FAA based its estimated cost of compliance on the work-hours and
parts costs from the manufacturer to perform the required actions. The
commenter did not provide specifics on which cost estimates were
incorrect and what would be considered realistic. The FAA did not
change this AD as a result of this comment.

Comment Regarding Parts Eligible for Installation

Lufthansa commented that parts considered eligible for installation
should not be limited to the disk S/Ns that are not listed in V2500-
ENG-72-0720 or PW SI No. 189F-23. Lufthansa noted that disk S/Ns listed
in those documents that have passed AUSI are also eligible for
installation and need to be removed within 4,000 FCs from
accomplishment of the AUSI or at the next HPT module removal after the
AUSI.
The FAA agrees to change paragraph (h)(1) of this AD to include
parts that were not removed from service as a result of the required
actions of this AD as ``parts eligible for installation.''

Request To Redefine AUSI Inspected Part Installation Date

TEC requested that the FAA change the definition of the date that
an AUSI inspected part was installed in paragraph (h)(5) of the
proposed AD from ``the date of the authorized release certification for
the shop visit at which the part was first installed after the AUSI was
performed'' to ``the HPT hub release certificate date.'' TEC noted that
it is possible for two HPT hubs to be inspected on the same date and be
installed on different engines. Since release dates of these engines
can differ, it is possible for different replacement compliance times
to apply to parts that were inspected on the same day.
The FAA disagrees with the request to change the definition of the
date that an AUSI inspected part was installed. The FAA acknowledges
that AUSI

[[Page 49096]]

compliance times will vary depending on when the AUSI inspected part
was installed, and this was taken into consideration in order to manage
shop visit capacity. The FAA did not change this AD as a result of this
comment.

Request To Revise Paragraph (g)(1) of the Proposed AD

MTU Maintenance Hannover GmbH and PW requested that the FAA revise
paragraph (g)(1) of the proposed AD to remove mention of AUSI inspected
parts installed on or after November 1, 2023. MTU Maintenance Hannover
GmbH requested that the phrase ``or the AUSI inspected part was
installed on or after November 1, 2023'' be removed from paragraph
(g)(1) of the proposed AD entirely, and PW requested that the FAA
change the language from ``or the AUSI inspected part was installed on
or after November 1, 2023'' to ``before November 1, 2023.'' JetBlue,
MTU Maintenance Hannover GmbH, and PW all noted that the current
language in paragraph (g)(1) of the proposed AD could cause an early
engine removal by requiring a second AUSI inspection on hubs that had
been previously AUSI inspected.
The FAA agrees to revise paragraph (g)(1) of this AD to prevent the
potential requirement of performing a second AUSI on hubs that had an
AUSI performed on or after November 1, 2023.

Request To Revise Paragraph (g)(2) of the AD

MTU Maintenance Hannover GmbH and PW requested that the FAA revise
paragraph (g)(2) of the proposed AD to clarify the required actions for
engines with AUSI inspected parts that were installed on or after
November 1, 2023. MTU Maintenance Hannover GmbH requested that the FAA
revise paragraph (g)(2) to read as follows: ``For engines with an AUSI
inspected part installed on or after November 1, 2023 or for parts
inspected in accordance with paragraph (g)(1) of this AD, within 4,000
FCs from accomplishment of the AUSI required by paragraph (g)(1) of
this AD or at the next HPT module removal after the AUSI required by
paragraph (g)(1) of this AD, whichever occurs first, remove the part
from service and replace with a part eligible for installation.'' PW
requested that the FAA revise paragraph (g)(2) of the proposed AD to
read as follows: ``For parts inspected in accordance with paragraph
(g)(1) of this AD, or for parts previously AUSI inspected and installed
on or after November 1, 2023, within 4,000 FCs from accomplishment of
the AUSI required by paragraph (g)(1) of this AD or at the next HPT
module removal after the AUSI required by paragraph (g)(1) of this AD,
whichever occurs first, remove the part from service and replace with a
part eligible for installation.'' PW noted that the intent is to
inspect everything, and any part inspected after November 1, 2023 will
be removed at 4,000 FCs.
The FAA agrees to revise paragraph (g)(2) of this AD to clarify the
required actions for engines with AUSI inspected parts that were
installed on or after November 1, 2023.

Request To Clarify Compliance Time for High-Thrust Engines

MTU Maintenance Zhuhai Co. Ltd requested that the FAA clarify the
part replacement compliance time in Table 2 to Paragraph (g)(4) of the
proposed AD for a part not previously operated in a high-thrust engine
model that has its engine rating changed to a high-thrust rating
without any disassembly or removal of the HPT module.
The FAA clarifies that after the initial flight in the newly rated
high-thrust engine, the part is considered to have previously operated
in a high-thrust engine and it will be required to use the lower cycle
limits. For example, the HPT 1st-stage hub will need to be removed at
1,800 FCs after the effective date of the AD because it is now
operating in a high-thrust engine. The FAA notes that the removal or
non-removal of the HPT module at shop visit would not have an effect on
this scenario as these are considered the new replacement cycle limits
for the affected parts on the effective date of the AD. The FAA has
revised paragraph (h)(3) of this AD by removing the second instance of
the word ``previously'' from the definition in order to avoid potential
misinterpretation.

Conclusion

The FAA reviewed the relevant data, considered any comments
received, and determined that air safety requires adopting this AD as
proposed. Accordingly, the FAA is issuing this AD to address the unsafe
condition on these products. Except for minor editorial changes, and
any other changes described previously, this AD is adopted as proposed
in the NPRM. None of the changes will increase the economic burden on
any operator.

Related Service Information Under 1 CFR Part 51

The FAA reviewed IAE AG NMSB V2500-ENG-72-0720, dated November 20,
2023; and PW Special Instruction No. 189F-23, dated November 20, 2023,
which only applies to the IAE AG V2531-E5 Model engine. This service
information specifies procedures for performing an AUSI for cracks on
affected HPT 1st-stage hubs and HPT 2nd-stage hubs. This service
information also specifies the list of affected HPT 1st-stage hubs and
HPT 2nd-stage hubs, identified by part number and serial number,
installed on certain IAE AG engines. 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.

Interim Action

The FAA considers this AD to be an interim action. The unsafe
condition is still under investigation by the manufacturer and,
depending on the results of that investigation, the FAA may consider
further rulemaking action.

Justification for Determination of the Effective Date

Section 553(d) of the Administrative Procedure Act (APA) (5 U.S.C.
551 et seq.) authorizes agencies to make rules effective in less than
thirty days, upon a finding of ``good cause.'' The FAA has found that
the risk to the flying public justifies a shortened effective date for
this rule due to powdered metal anomalies in HPT 1st-stage hubs and HPT
2nd-stage hubs that could lead to premature fracture and uncontained
failure, which could lead to the release of high-energy debris, damage
to the engine, damage to the airplane, and loss of the airplane. The
longer these parts remain in service, the higher the probability of
failure. Accordingly, the FAA finds that good cause exists pursuant to
5 U.S.C. 553(d) for making this amendment effective in less than 30
days.

Costs of Compliance

The FAA estimates that this AD affects 116 engines installed on
airplanes of U.S. registry. The FAA estimates that 40 engines need an
AUSI of the HPT 1st-stage hub; 40 engines need an AUSI of the HPT 2nd-
stage hub; 67 engines need replacement of the HPT 1st-stage hub; and 49
engines need replacement of the HPT 2nd-stage hub.
The FAA estimates the following costs to comply with this AD:

[[Page 49097]]

Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
AUSI of HPT 1st-stage hub............. 5 work-hours x $85 per $0 $425 $17,000
hour = $425.
AUSI of HPT 2nd-stage hub............. 5 work-hours x $85 per 0 425 17,000
hour = $8,500.
Replace HPT 1st-stage hub............. 100 work-hours x $85 per 460,000 468,500 31,389,500
hour = $8,500.
Replace HPT 2nd-stage hub............. 100 work-hours x $85 per 360,000 368,500 18,056,500
hour = $8,500.
----------------------------------------------------------------------------------------------------------------

The FAA has included all known costs in its cost estimate.
According to the manufacturer, however, some of the costs of this AD
may be covered under warranty, thereby reducing the cost impact on
affected operators.

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.

Regulatory Findings

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) Will not affect intrastate aviation in Alaska, and
(3) 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 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 adding the following new airworthiness
directive:

2024-11-03 International Aero Engines, AG: Amendment 39-22764;
Docket No. FAA-2024-0041; Project Identifier AD-2024-00032-E.

(a) Effective Date

This airworthiness directive (AD) is effective June 26, 2024.

(b) Affected ADs

This AD is related to AD 2022-02-09, Amendment 39-21906 (87 FR
7029, February 8, 2022) (AD 2022-02-09).

This AD applies to International Aero Engines, AG (IAE AG) Model
V2522-A5, V2524-A5, V2525-D5, V2527-A5, V2527E-A5, V2527M-A5, V2528-
D5, V2530-A5, V2531-E5, and V2533-A5 engines.

(d) Subject

Joint Aircraft System Component (JASC) Code 7230, Turbine
Engine.

(e) Unsafe Condition

This AD was prompted by an analysis of an event involving an
International Aero Engines, LLC Model PW1127GA-JM engine, which
experienced failure of a high-pressure compressor 7th-stage
integrally bladed rotor that resulted in an engine shutdown and
aborted takeoff. The FAA is issuing this AD to prevent failure of
the high-pressure turbine (HPT) 1st-stage hub and HPT 2nd-stage hub.
The unsafe condition, if not addressed, could result in uncontained
hub failure, release of high-energy debris, damage to the engine,
damage to the airplane, and loss of the airplane.

(f) Compliance

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

(g) Required Actions

(1) For engines with an installed part, part number (P/N), and
serial number (S/N) listed in Table 1 to paragraph (g)(1) of this
AD, with no angled ultrasonic inspection (AUSI) performed, at the
next engine shop visit after the effective date of this AD before
exceeding the applicable cycle limit specified in Table 1 to
paragraph (g)(1) of this AD, perform an AUSI of the affected parts
for cracks in accordance with the applicable service information
listed in Table 1 to paragraph (g)(1) of this AD.

[[Page 49098]]

Table 1 to Paragraph (g)(1)--AUSI Compliance Times
----------------------------------------------------------------------------------------------------------------
Applicable
Previously operated Flight cycle (FC) service
Part Table S/N is in high-thrust model limit from the information (see
listed in engine effective date of paragraph (l)(2)
this AD of this AD)
----------------------------------------------------------------------------------------------------------------
HPT 1st-stage hub P/N 2A5001... Table 1 of IAE AG Yes.................. 100 FCs.......... Accomplishment
Non-Modification Instructions,
Service Bulletin paragraph 5., of
V2500-ENG-72-0720 IAE AG NMSB
, dated November V2500-ENG-72-072
20, 2023 (IAE AG 0.
NMSB V2500-ENG-72-
0720).
HPT 1st-stage hub P/N 2A5001... Table 1 of Pratt & Yes.................. 100 FCs.......... Accomplishment
Whitney (PW) Instructions,
Special paragraph 5., of
Instruction No. PW SI No. 189F-
189F-23, dated 23, which only
November 20, 2023 applies to the
(PW SI No. 189F- IAE AG V2531-E5
23), which only Model engine.
applies to the
IAE AG V2531-E5
Model engine.
HPT 1st-stage hub P/N 2A5001... Table 1 of IAE AG No................... 700 FCs.......... Accomplishment
NMSB V2500-ENG-72- Instructions,
0720. paragraph 5., of
IAE AG NMSB
V2500-ENG-72-072
0.
HPT 2nd-stage hub P/N 2A4802... Table 2 of IAE AG Yes.................. 800 FCs.......... Accomplishment
NMSB V2500-ENG-72- Instructions,
0720. paragraph 6., of
IAE AG NMSB
V2500-ENG-72-072
0.
HPT 2nd-stage hub P/N 2A4802... Table 2 PW SI No. Yes.................. 800 FCs.......... Accomplishment
189F-23, which Instructions,
only applies to paragraph 6., of
the IAE AG V2531- PW SI No. 189F-
E5 Model engine. 23, which only
applies to the
IAE AG V2531-E5
Model engine.
HPT 2nd-stage hub P/N 2A4802... Table 2 of IAE AG No................... 1100 FCs......... Accomplishment
NMSB V2500-ENG-72- Instructions,
0720. paragraph 6., of
IAE AG NMSB
V2500-ENG-72-072
0.
----------------------------------------------------------------------------------------------------------------

(2) For parts inspected in accordance with paragraph (g)(1) of
this AD, or for AUSI inspected parts installed on or after November
1, 2023, within 4,000 FCs from accomplishment of the AUSI or at the
next HPT module removal after the AUSI, whichever occurs first,
remove the part from service and replace with a part eligible for
installation.
(3) If any crack is found during the inspections required by
paragraphs (g)(1) of this AD, before further flight, remove the
affected part from service and replace with a part eligible for
installation.
(4) For engines with an AUSI inspected part installed prior to
November 1, 2023, having a P/N and S/N listed in Table 2 to
paragraph (g)(4) of this AD, at the next HPT module removal after
the effective date of this AD, but before exceeding the applicable
cycle limit specified in Table 2 to paragraph (g)(4) of this AD,
remove the affected part from service and replace with a part
eligible for installation.

Table 2 to Paragraph (g)(4)--Part Replacement Compliance Times
----------------------------------------------------------------------------------------------------------------
Previously operated Flight cycle limit from
Part Table S/N is listed in in high-thrust model the effective date of
engine this AD
----------------------------------------------------------------------------------------------------------------
HPT 1st-stage hub P/N 2A5001...... Table 1 of IAE AG NMSB Yes.................. 1,800 FCs.
V2500-ENG-72-0720.
HPT 1st-stage hub P/N 2A5001...... Table 1 of PW SI No. 189F- Yes.................. 1,800 FCs.
23, which only applies to
the IAE AG V2531-E5 Model
engine.
HPT 1st-stage hub P/N 2A5001...... Table 1 of IAE AG NMSB No................... 2,800 FCs.
V2500-ENG-72-0720.
HPT 2nd-stage hub P/N 2A4802...... Table 2 of IAE AG NMSB Yes.................. 3,400 FCs.
V2500-ENG-72-0720.
HPT 2nd-stage hub P/N 2A4802...... Table 2 of PW SI No. 189F- Yes.................. 3,400 FCs.
23, which only applies to
the IAE AG V2531-E5 Model
engine.
HPT 2nd-stage hub P/N 2A4802...... Table 2 of IAE AG NMSB No................... 3,800 FCs.
V2500-ENG-72-0720.
----------------------------------------------------------------------------------------------------------------

(5) For engines with an installed part that has a P/N and S/N
listed in Table 3 to paragraph (g)(5) of this AD, at the next HPT
module removal after the effective date of this AD, but before
exceeding the applicable cycle limit specified in Table 3 to
paragraph (g)(5) of this AD, remove the affected part from service
and replace with a part eligible for installation.

[[Page 49099]]

Table 3 to Paragraph (g)(5)--Part Replacement Compliance Times
----------------------------------------------------------------------------------------------------------------
Previously operated Flight cycle limit from
Part Table S/N is listed in in high-thrust model the effective date of
engine this AD
----------------------------------------------------------------------------------------------------------------
HPT 1st-stage hub P/N 2A5001...... Table 3 of IAE AG NMSB Yes.................. 1,800 FCs.
V2500-ENG-72-0720.
HPT 1st-stage hub P/N 2A5001...... Table 3 of IAE AG NMSB No................... 2,800 FCs.
V2500-ENG-72-0720.
HPT 2nd-stage hub P/N 2A4802...... Table 4 of IAE AG NMSB Yes.................. 3,400 FCs.
V2500-ENG-72-0720.
HPT 2nd-stage hub P/N 2A4802...... Table 4 of IAE AG NMSB No................... 3,800 FCs.
V2500-ENG-72-0720.
----------------------------------------------------------------------------------------------------------------

(h) Definitions

(1) For the purposes of this AD, a ``part eligible for
installation'' is an HPT 1st-stage disk or HPT 2nd-stage disk having
an S/N that is not listed in IAE AG NMSB V2500-ENG-72-0720 or PW SI
No. 189F-23, or an HPT 1st-stage disk or HPT 2nd-stage disk that was
not removed from service per the requirements of this AD.
(2) For the purposes of this AD, an ``HPT module removal'' is
when the HPT rotor and stator assembly are removed from the engine.
(3) For the purposes of this AD, ``Previously operated in high-
thrust model engine'' refers to HPT 1st-stage hubs or HPT 2nd-stage
hubs that have operated in an IAE AG Model V2527E-A5, V2527M-A5,
V2528-D5, V2530-A5, V2531-E5, or V2533-A5 engine for any duration.
(4) For the purposes of this AD, an ``engine shop visit'' is the
induction of an engine into the shop for maintenance involving the
separation of pairs of major mating engine flanges, H-P, except for
the following situations, which do not constitute an engine shop
visit:
(i) Separation of engine flanges solely for the purposes of
transportation without subsequent engine maintenance.
(ii) Engine removal for the purpose of performing field
maintenance activities at a maintenance facility in lieu of
performing them on-wing.
(5) For the purposes of this AD, the date that an AUSI inspected
part was installed is the date of the authorized release
certification for the shop visit at which the part was first
installed after the AUSI was performed.

(i) Terminating Action to AD 2022-02-09

Compliance with paragraph (g)(1) of this AD satisfies the
requirements of AD 2022-02-09.

(j) Alternative Methods of Compliance (AMOCs)

(1) The Manager, AIR-520 Continued Operational Safety 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 AIR-520 Continued
Operational Safety Branch, send it to the attention of the person
identified in paragraph (k) 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) Additional Information

For more information about this AD, contact Carol Nguyen,
Aviation Safety Engineer, FAA, 2200 South 216th Street, Des Moines,
WA 98198; phone: (781) 238-7655; email: <a href="/cdn-cgi/l/email-protection#9af9fbe8f5f6b4f4fdefe3fff4dafcfbfbb4fdf5ec">[email&#160;protected]</a>.

(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.
(i) International Aero Engines AG (IAE AG) Non-Modification
Service Bulletin V2500-ENG-72-0720, dated November 20, 2023.
(ii) Pratt & Whitney (PW) Special Instruction No. 189F-23, dated
November 20, 2023.
(3) For IAE AG and PW service information, contact International
Aero Engines, AG, 400 Main Street, East Hartford, CT 06118; phone:
(860) 565-0140; email: <a href="/cdn-cgi/l/email-protection#1c7479706c2e285c6c6b3269687f327f7371">[email&#160;protected]</a>; website:
<a href="http://connect.prattwhitney.com">connect.prattwhitney.com</a>.
(4) You may view this service information at the FAA,
Airworthiness Products Section, Operational Safety Branch, 1200
District Avenue, Burlington, MA 01803. For information on the
availability of this material at the FAA, call (817) 222-5110.
(5) You may view this material at the National Archives and
Records Administration (NARA). For information on the availability
of this material at NARA, visit <a href="http://www.archives.gov/federal-register/cfr/ibr-locations">www.archives.gov/federal-register/cfr/ibr-locations</a> or email <a href="/cdn-cgi/l/email-protection#f29480dc9b9c81829791869b9d9cb29c938093dc959d84">[email&#160;protected]</a>.

Issued on May 31, 2024.
Suzanne Masterson,
Deputy Director, Integrated Certificate Management Division, Aircraft
Certification Service.
[FR Doc. 2024-12594 Filed 6-10-24; 8:45 am]
BILLING CODE 4910-13-P

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