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Rule2024-06433

Airworthiness Directives; Pratt & Whitney Turbofan Engines

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Published

March 27, 2024

Effective

April 11, 2024

Issuing agencies

Transportation DepartmentFederal Aviation Administration

Abstract

The FAA is adopting a new airworthiness directive (AD) for certain Pratt & Whitney (PW) Model PW1519G, PW1521G, PW1521GA, PW1521G- 3, PW1524G, PW1524G-3, PW1525G, PW1525G-3, PW1919G, PW1921G, PW1922G, PW1923G, and PW1923G-A engines. This AD was prompted by an updated 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 engine shutdown and aborted takeoff. This AD requires performing an angled ultrasonic inspection (AUSI) of certain high-pressure turbine (HPT) 1st-stage hubs, HPT 2nd-stage hubs, and HPC 8th-stage disks for cracks and, depending on the results of the inspections, replacing the HPT 1st-stage hubs, HPT 2nd-stage hubs, or HPC 8th-stage disks. This AD also requires accelerated replacement of certain HPC 7th-stage rotors, HPC 8th-stage disks, HPC rear hubs, HPT 1st-stage hubs, HPT 2nd-stage hubs, HPT 1st-stage air seals, HPT 2nd- stage air seals, HPT 1st-stage blade retaining plates, and HPT 2nd- stage blade retaining plates. 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 60 (Wednesday, March 27, 2024)</title>
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[Federal Register Volume 89, Number 60 (Wednesday, March 27, 2024)]
[Rules and Regulations]
[Pages 21190-21196]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2024-06433]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2023-2523; Project Identifier AD-2023-01086-E;
Amendment 39-22709; AD 2024-06-04]
RIN 2120-AA64

Airworthiness Directives; Pratt & Whitney Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Pratt & Whitney (PW) Model PW1519G, PW1521G, PW1521GA, PW1521G-
3, PW1524G, PW1524G-3, PW1525G, PW1525G-3, PW1919G, PW1921G, PW1922G,
PW1923G, and PW1923G-A engines. This AD was prompted by an updated
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 engine shutdown and aborted takeoff. This AD
requires performing an angled ultrasonic inspection (AUSI) of certain
high-pressure turbine (HPT) 1st-stage hubs, HPT 2nd-stage hubs, and HPC
8th-stage disks for cracks and, depending on the results of the
inspections, replacing the HPT 1st-stage hubs, HPT 2nd-stage hubs, or
HPC 8th-stage disks. This AD also requires accelerated replacement of
certain HPC 7th-stage rotors, HPC 8th-stage disks, HPC rear hubs, HPT
1st-stage hubs, HPT 2nd-stage hubs, HPT 1st-stage air seals, HPT 2nd-
stage air seals, HPT 1st-stage blade retaining plates, and HPT 2nd-
stage blade retaining plates. The FAA is issuing this AD to address the
unsafe condition on these products.

DATES: This AD is effective April 11, 2024.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of April 11,
2024.

ADDRESSES:
AD Docket: You may examine the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2023-2523; 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

[[Page 21191]]

Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590.
Material Incorporated by Reference:
<bullet> For Pratt & Whitney service information identified in this
AD, contact International Aero Engines, LLC, 400 Main Street, East
Hartford, CT 06118; phone: (860) 565-0140; email: <a href="/cdn-cgi/l/email-protection#751d10190547413505025b0001165b161a18">[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. It is
also available at <a href="http://regulations.gov">regulations.gov</a> under Docket No. FAA-2023-2523.

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#5e3d3f2c31327030392b273b301e383f3f70393128">[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 PW Model
PW1519G, PW1521G, PW1521GA, PW1521G-3, PW1524G, PW1524G-3, PW1525G,
PW1525G-3, PW1919G, PW1921G, PW1922G, PW1923G, and PW1923G-A engines.
The NPRM published in the Federal Register on January 9, 2024 (89 FR
1038). The NPRM was prompted by an incident involving an Airbus Model
A320neo airplane powered by IAE LLC Model PW1127GA-JM engines that
experienced a failure of the HPC IBR-7 resulting 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. The
analysis also concluded that there is an increased risk of failure for
additional nickel powdered metal parts in certain nickel powdered metal
production campaigns, and these parts 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, HPT 2nd-stage
hubs, and HPC 8th-stage disks for cracks and, depending on the results
of the inspections, replacing the HPT 1st-stage hubs, HPT 2nd-stage
hubs, or HPC 8th-stage disks. The FAA also proposed to require
accelerated replacement of certain HPC 7th-stage rotors, HPC 8th-stage
disks, HPC rear hubs, HPT 1st-stage air seals, HPT 2nd-stage air seals,
HPT 1st-stage hubs, HPT 2nd-stage hubs, HPT 1st-stage blade retaining
plates, and HPT 2nd-stage blade retaining plates. 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 five commenters. The commenters were
the Air Line Pilots Association, International (ALPA), Delta Air Lines,
Inc. (DAL), Lufthansa Technik AG (Lufthansa), PW, and Transport Canada
Civil Aviation (TCCA). ALPA supported the NPRM without change. DAL,
Lufthansa, PW, and TCCA requested changes to the proposed AD. The
following presents the comments received on the NPRM and the FAA's
response to each comment.

Request To Clarify Unsafe Condition

DAL requested that the FAA update paragraph (e) of the proposed AD
or create a new paragraph to clarify why the HPC IBR-7 does not require
repetitive AUSIs. Delta noted that the HPC IBR-7 was the part that
originally separated during an event outlined in the proposed AD,
leading to engine shutdown and aborted takeoff, which prompted this AD.
The FAA disagrees with the request to update paragraph (e) or add a
paragraph to the AD that clarifies why there are no repetitive AUSIs
for the HPC IBR-7. The AUSI for the HPC IBR-7 was not available when
the NPRM was written and to address the unsafe condition quickly, the
FAA did not want to delay the issuance of this AD in order to add the
AUSI for the HPC IBR-7. Since this AD is considered an interim action,
the FAA will consider adding the AUSI for the HPC IBR-7 or other
actions in the future. The FAA did not change this AD as a result of
this comment.

Request To Update Definition for Parts Eligible for Installation

DAL requested that the FAA update paragraph (i)(3) of the proposed
AD to clarify installation eligibility for new/not service run HPC/HPT
hardware that is not currently installed on an engine. Delta stated
that HPC/HPT hardware scanned at production are scanned per the non-
destructive inspection procedure (NDIP) and may not list service
bulletin status so clarification is needed to determine hardware
eligibility based off service bulletin status as well as NDIP status.
The FAA disagrees with the request to update the definition of
parts eligible for installation to include new/not service run parts
because new parts inspected at production would not have the NDIP
listed in their paperwork. The service documents require the AUSI of
new parts prior to installation with no allowance for parts inspected
at production. The FAA did not change this AD as a result of this
comment.

Request To Update Definition of Engine Shop Visit and HPC Engine Shop
Visit

DAL requested that the FAA update the definitions for ``engine shop
visit'' and ``HPC engine shop visit'' in paragraph (i)(5) and (6) of
the proposed AD to provide clarity and avoid ambiguity. Delta noted
that the definition for ``engine shop visit'' includes the term
``pairs'' when defining separation of major mating engine flanges.
Delta stated that this does not clearly define what constitutes an
``engine shop visit,'' as the term ``pairs'' may be interpreted as
separation of two or more different lettered flanges. Delta also stated
that the phrase ``when the HPC rotor assembly is removed from the
engine'' used in the definition for an ``HPC engine shop visit'' does
not clearly describe the different scenarios that may constitute HPC
engine shop visits since the HPC rotor assembly can be at different
levels of exposure depending on the shop visit type.
The FAA partially agrees with the request. The FAA agrees to update
the definition of an ``HPC shop visit'' in paragraph (i)(6) of this AD
to: ``For the purposes of this AD, an `HPC engine shop visit' is when
the HPC rotor assembly is removed from the HPC module.'' The FAA
disagrees with the request to update the definition for an ``engine
shop visit'' because the definition used in this AD is standard and
taken from the World Airlines Technical Operations Glossary. The FAA
notes that the term ``pairs'' of major mating engine flanges refers to
the mating surfaces on each individual part of the bolted joint.

Request To Include Alert Service Bulletin (ASB) Issue Numbers in Tables

DAL requested that the FAA update Table 1 to Paragraph (g)(3) and
Table 2 to Paragraph (g)(7) of the proposed AD to include the issue
numbers of the ASBs that are listed in the Applicable (serial number)
S/N listing, Applicable service bulletin and the Table S/N is listed in
columns. DAL noted that certain ASBs, such as 72-00-0196 Issue 002,
were revised to include additional

[[Page 21192]]

serial numbers in the effectivity, so different ASB issue numbers
contain different serial number effectivity.
The FAA agrees with the request and has updated Table 1 to
paragraph (g)(3) and Table 2 to paragraph (g)(7) of this AD to include
the issue numbers of the applicable ASBs.

Request To Edit Service Bulletin References

Lufthansa requested that the FAA merge paragraph (g)(1) of the
proposed AD with paragraph (g)(4)(i) of the proposed AD and paragraph
(g)(2) of the proposed AD with paragraph (g)(4)(ii) of the proposed AD
and refer to ASBs PW1000G-A-72-00-0204 and PW1000G-A-72-00-0205, as
applicable. Lufthansa noted that all of the ASBs referenced in these
paragraphs refer to NDIP-1260 for 8th-stage discs, NDIP-1254 for 1st-
stage hubs, and NDIP-1257 for 2nd-stage hubs. Lufthansa also noted that
this aligns with the PW ASB set-up, which requires inspections during
shop visits in accordance with ASBs PW1000G-A-72-00-0204 and PW1000G-A-
72-00-0205 for all less affected hardware and stricter inspections for
parts more affected and listed in ASBs PW1000G-A-72-00-0196 and
PW1000G-A-72-00-0197 only.
The FAA disagrees with the request to merge steps within paragraph
(g) of this AD. The FAA notes that several service information
documents are referenced within paragraph (g) of this AD in order to
account for both initial AUSI and repetitive AUSIs. The FAA did not
change this AD as a result of this comment.

Request To Clarify 100 Flight Cycle Threshold

TCCA requested that the FAA clarify the intention of the condition
``or within 100 FCs after the effective date of this AD'' that is
proposed in paragraph (g)(3) of the proposed AD and to clarify if it is
related to the intent of paragraph (g)(13) of the proposed AD.
For clarification, the intention of the condition ``or within 100
FCs after the effective date of this AD'' is to provide a grace period
for affected parts that are over the cycle limits listed in Table 1 to
Paragraph (g)(3) of this AD, and the condition is not related to
paragraph (g)(13) of this AD. The FAA did not change this AD as a
result of this comment.

Request To Add Definition for Affected Part

TCCA requested that the FAA update the proposed AD by adding a
definition for ``affected part'' in order to avoid misinterpretation
since there are multiple parts with different part numbers and a
subpopulation of part SNs and inspection thresholds involved.
The FAA disagrees with the request to add a definition for
``affected part'' to this AD because the affected parts and part
numbers are already specified within paragraph (g) of this AD. The FAA
did not change this AD as a result of this comment.

Request To Update Number of Affected U.S. Products

PW requested that the FAA update the NPRM by changing the number of
engines installed on airplanes of U.S. registry from 430 to 121.
The FAA agrees and has updated the number of engines installed on
airplanes of U.S. registry from 430 to 121 in the Cost of Compliance
paragraph of this final rule and updated the estimated costs
accordingly.

Request To Incorporate Updated Service Information

PW requested that the FAA incorporate PW Special Instruction (SI)
No. 240F-23A, dated February 7, 2024, into the final rule. PW noted
that they have refined this SI, which lists a limited number of
affected HPT hubs by S/N, and this information has already been
provided to affected operators.
The FAA agrees with the request and has updated this final rule to
reference PW SI No. 240F-23A, dated February 7, 2024, in paragraphs (h)
and (m)(2)(ix) of this AD.

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 the following service information:
<bullet> PW ASB PW1000G-A-72-00-0196-00A-930A-D, Issue No: 002,
dated November 30, 2023, and PW ASB PW1000G-A-72-00-0141-00B-930A-D,
Issue No: 002, dated November 30, 2023. This service information
specifies a list of affected HPT 1st-stage hubs and HPT 2nd-stage hubs
that are identified by serial number (S/N) and installed on certain PW
engines; and instructions for performing an AUSI on affected HPT 1st-
stage hubs and HPT 2nd-stage hubs.
<bullet> PW ASB PW1000G-A-72-00-0197-00A-930A-D, Issue No: 004,
dated November 30, 2023, and PW ASB PW1000G-A-72-00-0142-00B-930A-D,
Issue No: 004, dated November 30, 2023. This service information
specifies a list of affected HPC 8th-stage disks that are identified by
S/N and installed on certain PW engines; and instructions for
performing an AUSI on affected HPC 8th-stage disks.
<bullet> PW ASB PW1000G-A-72-00-0204-00A-930A-D, Issue No: 001,
dated November 30, 2023, and PW ASB PW1000G-A-72-00-0150-00B-930A-D,
Issue No: 001, dated November 30, 2023, which specifies procedures for
performing repetitive AUSIs on affected HPC 8th-stage disks.
<bullet> PW ASB PW1000G-A-72-00-0205-00A-930A-D, Issue No: 001,
dated November 30, 2023, and PW ASB PW1000G-A-72-00-0151-00B-930A-D,
Issue No: 001, dated November 30, 2023, which specify procedures for
performing repetitive AUSIs on affected HPT 1st-stage hubs and HPT 2nd-
stage hubs.
<bullet> PW SI No. 240F-23A, dated February 7, 2024, which
specifies a list of affected HPT 1st-stage hubs and HPT 2nd-stage hubs
that are identified by S/N and installed on certain PW 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. This 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 hub, HPT
2nd-stage hub, and HPC IBR-8 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 compliance time for replacement of certain parts is
within 100 flight cycles after the effective date of this AD, which

[[Page 21193]]

is on average one calendar month of operation. 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 121 engines installed on
airplanes of U.S. registry. The FAA estimates that 121 engines will
need the AUSI of the HPT 1st-stage hub, HPT 2nd-stage hub, and HPC 8th-
stage disk; 121 engines will need replacement of the HPT 1st-stage hub;
121 engines will need replacement of the HPT 2nd-stage hub; 121 engines
will need replacement of the HPC 7th-stage rotor; 121 engines will need
replacement of the HPC 8th-stage disk; 121 engines would need
replacement of the HPC rear hub; 121 engines will need replacement of
the HPT 1st-stage air seal; 121 engines will need replacement of the
HPT 2nd-stage air seal; 121 engines will need replacement of the HPT
1st-stage blade retaining plate; and 121 engines will need replacement
of the HPT 2nd-stage blade retaining plate.
The FAA estimates the following costs to comply with this AD:

Estimated Costs
----------------------------------------------------------------------------------------------------------------
Parts cost
Action Labor cost (average pro- Cost per Cost on U.S.
rated cost) product operators
----------------------------------------------------------------------------------------------------------------
Perform AUSI of HPT 1st-stage hub, HPT 60 work-hours x $85 per $0 $5,100 $617,100
2nd-stage hub, and HPC 8th-stage disk. hour = $5,100.
Replace HPT 1st-stage hub.............. 10 work-hours x 85 per 49,500 50,350 6,092,350
hour = 850.
Replace HPT 2nd-stage hub.............. 10 work-hours x 85 per 25,500 26,350 3,188,350
hour = 850.
Replace HPC 7th-stage rotor............ 10 work-hours x 85 per 48,000 48,850 5,910,850
hour = 850.
Replace HPC 8th-stage disk............. 10 work-hours x 85 per 35,500 36,350 4,398,350
hour = 850.
Replace HPC rear hub................... 10 work-hours x 85 per 83,000 83,850 10,145,850
hour = 850.
Replace HPT 1st-stage air seal......... 10 work-hours x 85 per 21,000 21,850 2,643,850
hour = 850.
Replace HPT 2nd-stage air seal......... 10 work-hours x 85 per 36,000 36,850 4,458,850
hour = 850.
Replace HPT 1st-stage blade retaining 10 work-hours x 85 per 34,000 34,850 4,216,850
plate. hour = 850.
Replace HPT 2nd-stage blade retaining 10 work-hours x 85 per 13,000 13,850 1,675,850
plate. hour = 850.
----------------------------------------------------------------------------------------------------------------

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:

2024-06-04 Pratt & Whitney: Amendment 39-22709; Docket No. FAA-2023-
2523; Project Identifier AD-2023-01086-E.

(a) Effective Date

This airworthiness directive (AD) is effective April 11, 2024.

(b) Affected ADs

None.

Pratt & Whitney (PW) Model PW1519G, PW1521G, PW1521GA, PW1521G-
3, PW1524G, PW1524G-3, PW1525G, PW1525G-3, PW1919G, PW1921G,
PW1922G, PW1923G, and PW1923G-A engines.

(d) Subject

Joint Aircraft System Component (JASC) Code 7230, Turbine Engine
Compressor Section; 7250, Turbine Section.

(e) Unsafe Condition

This AD was prompted by an updated analysis of an event
involving an International Aero Engines, LLC Model PW1127GA-JM
engine, which experienced a high-pressure compressor (HPC) 7th-stage
integrally bladed rotor separation 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, HPT 2nd-
stage hub, and HPC 8th-stage disk. 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
possible loss of the airplane.

(f) Compliance

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

[[Page 21194]]

(g) Required Actions

(1) For PW1500G engines with an installed HPC 8th-stage disk
having part number (P/N) 30G7208, at the next HPC engine shop visit,
except as required by paragraph (g)(3) of this AD, perform an angled
ultrasonic inspection (AUSI) of the affected HPC 8th-stage disk for
cracks in accordance with the Accomplishment Instructions, paragraph
8., of PW Alert Service Bulletin (ASB) PW1000G-A-72-00-0197-00A-
930A-D, Issue No: 004, dated November 30, 2023 (PW1000G-A-72-00-
0197-00A-930A-D, Issue No: 004).
(2) For PW1500G engines with an installed HPT 1st-stage hub
having P/N 30G8501 or an installed HPT 2nd-stage hub having P/N
30G7202, at the next engine shop visit, except as required by
paragraph (g)(3) of this AD, perform an AUSI of the affected HPT
1st-stage hub or HPT 2nd-stage hub, as applicable, for cracks in
accordance with the Accomplishment Instructions, paragraph 8.A. or
8.B., of PW ASB PW1000G-A-72-00-0196-00A-930A-D, Issue No: 002,
dated November 30, 2023 (PW1000G-A-72-00-0196-00A-930A-D, Issue No:
002).
(3) For PW1500G engines with an installed part, P/N and serial
number (S/N) listed in Table 1 to paragraph (g)(3) of this AD with
no AUSI performed prior to the effective date of this AD, within the
applicable compliance time listed in Table 1 to paragraph (g)(3) of
this AD or within 100 flight cycles (FCs) after the effective date
of this AD, whichever occurs later, perform an AUSI of the affected
part for cracks in accordance with the applicable service bulletin
listed in Table 1 to paragraph (g)(3) of this AD.

Table 1 to Paragraph (g)(3)--AUSI Compliance Times
----------------------------------------------------------------------------------------------------------------
Applicable service
Part Applicable S/N listing Compliance time bulletin (see paragraph
(m)(2) of this AD)
----------------------------------------------------------------------------------------------------------------
HPC 8th-stage disk P/N 30G7208....... Table 1 of PW ASB Next HPC engine shop Accomplishment
PW1000G-A-72-00-0197-0 visit not to exceed Instructions,
0A-930A-D, Issue No: 10,000 part cycles paragraph 8., of PW
004. since new (CSN). ASB PW1000G-A-72-00-
0197-00A-930A-D, Issue
No: 004.
HPT 1st-stage hub P/N 30G8501........ Table 2 of PW ASB Next engine shop visit Accomplishment
PW1000G-A-72-00-0196-0 not to exceed 5,000 Instructions,
0A-930A-D, Issue No: part CSN. paragraph 8.A. of PW
002. ASB PW1000G-A-72-00-
0196-00A-930A-D, Issue
No: 002.
HPT 2nd-stage hub P/N 30G7202........ Table 3 of PW ASB Next engine shop visit Accomplishment
PW1000G-A-72-00-0196-0 not to exceed 5,000 Instructions,
0A-930A-D, Issue No: part CSN. paragraph 8.B, of PW
002. ASB PW1000G-A-72-00-
0196-00A-930A-D, Issue
No: 002.
HPT 1st-stage hub P/N 30G8501........ Table 4 of PW ASB Next engine shop visit Accomplishment
PW1000G-A-72-00-0196-0 not to exceed 4,000 Instructions,
0A-930A-D, Issue No: part CSN. paragraph 8.A, of PW
002. ASB PW1000G-A-72-00-
0196-00A-930A-D, Issue
No: 002.
HPT 2nd-stage hub P/N 30G7202........ Table 5 of PW ASB Next engine shop visit Accomplishment
PW1000G-A-72-00-0196-0 not to exceed 4,000 Instructions,
0A-930A-D, Issue No: part CSN. paragraph 8.B., of PW
002. ASB PW1000G-A-72-00-
0196-00A-930A-D, Issue
No: 002.
----------------------------------------------------------------------------------------------------------------

(4) Thereafter at each piece-part exposure of the affected part
for PW1500G engines with an installed HPC 8th-stage disk having P/N
30G7208, an installed HPT 1st-stage hub having P/N 30G8501, or an
installed HPT 2nd-stage hub having P/N 30G7202, do the following:
(i) Perform an AUSI of the affected HPC 8th-stage disk for
cracks in accordance with the Accomplishment Instructions, paragraph
5.B., PW ASB PW1000G-A-72-00-0204-00A-930A-D, Issue No: 001, dated
November 30, 2023.
(ii) Perform an AUSI of the affected HPT 1st-stage hub and HPT
2nd-stage hub, as applicable, for cracks in accordance with the
Accomplishment Instructions, paragraph 7.A. or 7.B., of PW ASB
PW1000G-A-72-00-0205-00A-930A-D, Issue No: 001, dated November 30,
2023.
(5) For PW1900G engines with an installed HPC 8th-stage disk
having P/N 30G7208, at the next HPC engine shop visit, except as
required by paragraph (g)(7) of this AD, perform an AUSI of the
affected HPC 8th-stage disk for cracks in accordance with the
Accomplishment Instructions, paragraph 8., of Pratt & Whitney PW ASB
PW1000G-A-72-00-0142-00B-930A-D, Issue No: 004, dated November 30,
2023 (PW1000G-A-72-00-0142-00B-930A-D, Issue No: 004).
(6) For PW1900G engines with an installed HPT 1st-stage hub
having P/N 30G8501 or an installed HPT 2nd-stage hub having P/N
30G7202, at the next engine shop visit, except as required by
paragraph (g)(7) of this AD, perform an AUSI of the affected HPT
1st-stage hub and HPT 2nd-stage hub, as applicable, for cracks in
accordance with the Accomplishment Instructions, paragraph 8.A. or
8.B., of PW ASB PW1000G-A-72-00-0141-00B-930A-D, Issue No: 002,
dated November 30, 2023 (PW1000G-A-72-00-0141-00B-930A-D, Issue No:
002).
(7) For PW1900G engines with an installed part, P/N and S/N
listed in Table 2 to paragraph (g)(7) of this AD, with no AUSI
performed prior to the effective date of this AD, within the
compliance time listed in Table 2 to paragraph (g)(7) of this AD or
within 100 FCs after the effective date of this AD, whichever occurs
later, perform an AUSI of the affected parts for cracks in
accordance with the applicable service bulletin listed in Table 2 to
paragraph (g)(7) of this AD.

Table 2 to Paragraph (g)(7)--AUSI Compliance Times
----------------------------------------------------------------------------------------------------------------
Applicable service
Part Table S/N is listed in Compliance time bulletin (see paragraph
(m)(2) of this AD)
----------------------------------------------------------------------------------------------------------------
HPC 8th-stage disk having P/N 30G7208 Table 1 of PW ASB Next HPC engine shop Accomplishment
PW1000G-A-72-00-0142-0 visit not to exceed Instructions,
0B-930A-D, Issue No: 10,000 part CSN. paragraph 8., of PW
004. ASB PW1000G-A-72-00-
0142-00B-930A-D, Issue
No: 004.
HPT 1st-stage hub having P/N 30G8501. Table 2 of PW ASB Next engine shop visit Accomplishment
PW1000G-A-72-00-0141-0 not to exceed 5,000 Instructions,
0B-930A-D, Issue No: part CSN. paragraph 8.A., of PW
002. ASB PW1000G-A-72-00-
0141-00B-930A-D, Issue
No: 002.
HPT 2nd-stage hub having P/N 30G7202. Table 3 of PW ASB Next engine shop visit Accomplishment
PW1000G-A-72-00-0141-0 not to exceed 5,000 Instructions,
0B-930A-D, Issue No: part CSN. paragraph 8.B, of PW
002. ASB PW1000G-A-72-00-
0141-00B-930A-D, Issue
No: 002.
HPT 1st-stage hub having P/N 30G8501. Table 4 of PW ASB Next engine shop visit Accomplishment
PW1000G-A-72-00-0141-0 not to exceed 4,000 Instructions,
0B-930A-D, Issue No: part CSN. paragraph 8.A., of PW
002. ASB PW1000G-A-72-00-
0141-00B-930A-D, Issue
No: 002.
HPT 2nd-stage hub having P/N 30G7202. Table 5 of PW ASB Next engine shop visit Accomplishment
PW1000G-A-72-00-0141-0 not to exceed 4,000 Instructions,
0B-930A-D, Issue No: part CSN. paragraph 8.B., of PW
002. ASB PW1000G-A-72-00-
0141-00B-930A-D, Issue
No: 002.
----------------------------------------------------------------------------------------------------------------

[[Page 21195]]

(8) Thereafter at each piece-part exposure of the affected part
for PW1900G engines with an installed HPC 8th-stage disk having P/N
30G7208, or an installed HPT 1st-stage hub having P/N 30G8501, or an
installed HPT 2nd-stage hub having P/N 30G7202, do the following:
(i) Perform an AUSI of the affected HPC 8th-stage disk for
cracks in accordance with the Accomplishment Instructions, paragraph
5.B., of PW ASB PW1000G-A-72-00-0150-00B-930A-D, Issue No: 001,
dated November 30, 2023.
(ii) Perform an AUSI of the affected HPT 1st-stage hub and HPT
2nd-stage hub, as applicable, for cracks in accordance with the
Accomplishment Instructions, paragraph 7.A. or 7.B., of PW ASB
PW1000G-A-72-00-0151-00B-930A-D, Issue No: 001, dated November 30,
2023.
(9) If any crack is found during the inspections required by
paragraph (g) of this AD, before further flight, remove the affected
part from service and replace with a part eligible for installation.
(10) For engines with an installed part and P/N listed in Table
3 to paragraph (g)(10) of this AD having 3,300 CSN or less on the
effective date of this AD, before the part accumulates 4,000 CSN or
at the next engine shop visit after the effective date of this AD,
whichever occurs first, remove the part from service and replace
with a part eligible for installation.

Table 3 to Paragraph (g)(10)--Part Numbers
------------------------------------------------------------------------
Part name P/N
------------------------------------------------------------------------
HPC 7th-stage rotor......................................... 30G3307
HPC 8th-stage disk.......................................... 30G3248
HPC rear hub................................................ 30G2902
HPT 1st-stage hub........................................... 30G5701
HPT 2nd-stage hub........................................... 30G5002
HPT 1st-stage air seal...................................... 30G3132
HPT 2nd-stage air seal...................................... 30G3451
HPT 1st-stage blade retaining plate......................... 30G1692
HPT 2nd-stage blade retaining plate......................... 30G1698
------------------------------------------------------------------------

(11) For engines with an installed part and P/N listed in Table
3 to paragraph (g)(10) of this AD having more than 3,300 CSN on the
effective date of this AD, at the next engine shop visit or within
700 FCs after the effective date of this AD, whichever occurs first,
remove the part from service and replace it with a part eligible for
installation.
(12) For engines with an installed HPT 1st-stage hub having P/N
30G8501 or an installed HPT 2nd-stage hub having P/N 30G7202 and an
S/N listed in Table 1 of PW Special Instruction (SI) No. 240F-23A,
dated February 7, 2024, within 100 FCs from the effective date of
this AD, remove the hub from service and replace it with a part
eligible for installation.
(13) If an affected part has accumulated 100 FCs or less since
the last AUSI, reinspection is not required provided that the part
was not damaged during removal from the engine.

(h) Installation Prohibition

After the effective date of this AD, do not install an HPT 1st-
stage hub having P/N 30G8501 or an HPT 2nd-stage hub having P/N
30G7202 and an S/N listed in Table 1 of PW SI No. 240F-23A, dated
February 7, 2024, in any engine.

(i) Definitions

(1) For the purposes of this AD, ``PW1500G'' engines are PW
Model PW1519G, PW1521G, PW1521GA, PW1521G-3, PW1524G, PW1524G-3,
PW1525G, and PW1525G-3 engines.
(2) For the purposes of this AD, ``PW1900G'' engines are PW
Model PW1919G, PW1921G, PW1922G, PW1923G, and PW1923G-A engines.
(3) For the purposes of this AD, a ``part eligible for
installation'' is:
(i) Any HPC 7th-stage rotor, P/N 30G5307 or later approved P/N.
(ii) Any HPC 8th-stage disk, P/N 30G7208, that has passed the
AUSI required by paragraph (g) of this AD or later approved P/N.
(iii) Any HPC rear hub, P/N 30G7308 or later approved P/N.
(iv) Any HPT 1st-stage hub, P/N 30G8501, that has passed the
AUSI required by paragraph (g) of this AD or later approved P/N.
(v) Any HPT 2nd-stage hub, P/N 30G7202, that has passed the AUSI
required by paragraph (g) of this AD or later approved P/N.
(vi) Any HPT 1st-stage air seal, P/N 30G5195 or later approved
P/N.
(vii) Any HPT 2nd-stage air seal, P/N 30G5196 or later approved
P/N.
(viii) Any HPT 1st-stage blade retaining plate, P/N 30G5193 or
later approved P/N.
(ix) Any HPT 2nd-stage blade retaining plate, P/N 30G5194 or
later approved P/N.
(4) For the purposes of this AD, a ``piece-part exposure'' is
when the part is disassembled from the rotor assembly.
(5) 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, except for the
following situations, which do not constitute an engine shop visit.
(i) The separation of engine flanges solely for the purposes of
transportation without subsequent engine maintenance.
(ii) Fan case maintenance or replacement.
(6) For the purposes of this AD, an ``HPC engine shop visit'' is
when the HPC rotor assembly is removed from the HPC module.

(j) Credit for Previous Actions

This paragraph provides credit for the initial AUSI of the HPC
8th-stage disk, HPT 1st-stage hub and HPT 2nd-stage hub specified in
paragraph (g)(1), (2), (4) and (5) of this AD, if the initial AUSI
was performed before the effective date of this AD using the
following service information.
(1) PW ASB PW1000G-A-72-00-0196-00A-930A-D, Issue No: 001, dated
March 16, 2023; or
(2) PW ASB PW1000G-A-72-00-0197-00A-930A-D, Issue No: 001, dated
March 22, 2023; or
(3) PW ASB PW1000G-A-72-00-0197-00A-930A-D, Issue No: 002, dated
June 19, 2023; or
(4) PW ASB PW1000G-A-72-00-0197-00A-930A-D, Issue No: 003, dated
August 14, 2023; or
(5) PW ASB PW1000G-A-72-00-0141-00B-930A-D, Issue No: 001, dated
March 16, 2023; or
(6) PW ASB PW1000G-A-72-00-0142-00B-930A-D, Issue No: 001, dated
March 22, 2023; or
(7) PW ASB PW1000G-A-72-00-0142-00B-930A-D, Issue No: 002, dated
June 19, 2023.; or
(8) PW ASB PW1000G-A-72-00-0142-00B-930A-D, Issue No: 003, dated
August 14, 2023.

(k) 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 AIR-520 Continued Operational
Safety Branch, send it to the attention of the person identified in
paragraph (l) 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.

(l) 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#9ffcfeedf0f3b1f1f8eae6faf1dff9fefeb1f8f0e9">[email&#160;protected]</a>.

(m) 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) Pratt & Whitney (PW) Alert Service Bulletin (ASB) PW1000G-A-
72-00-0141-00B-930A-D, Issue No: 002, dated November 30, 2023.
(ii) PW ASB PW1000G-A-72-00-0142-00B-930A-D, Issue No: 004,
dated November 30, 2023.
(iii) PW ASB PW1000G-A-72-00-0150-00B-930A-D, Issue No: 001,
dated November 30, 2023.
(iv) PW ASB PW1000G-A-72-00-0151-00B-930A-D, Issue No: 001,
dated November 30, 2023.
(v) PW ASB PW1000G-A-72-00-0196-00A-930A-D, Issue No: 002, dated
November 30, 2023.
(vi) PW ASB PW1000G-A-72-00-0197-00A-930A-D, Issue No: 004,
dated November 30, 2023.
(vii) PW ASB PW1000G-A-72-00-0204-00A-930A-D, Issue No: 001,
dated November 30, 2023.
(viii) PW ASB PW1000G-A-72-00-0205-00A-930A-D, Issue No: 001,
dated November 30, 2023.
(ix) PW Special Instruction No. 240F-23A, dated February 7,
2024.

[[Page 21196]]

(3) For PW service information identified in this AD, contact
International Aero Engines, LLC, 400 Main Street, East Hartford, CT
06118; phone: (860) 565-0140; email: <a href="/cdn-cgi/l/email-protection#93fbf6ffe3a1a7d3e3e4bde6e7f0bdf0fcfe">[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#2e485c0047405d5e4b4d5a4741406e404f5c4f00494158">[email&#160;protected]</a>.

Issued on March 21, 2024.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2024-06433 Filed 3-22-24; 4:15 pm]
BILLING CODE 4910-13-P

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