Airworthiness Directives; Pratt & Whitney Turbofan Engines, 21190-21196 [2024-06433]
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Federal Register / Vol. 89, No. 60 / Wednesday, March 27, 2024 / Rules and Regulations
engine into the shop for maintenance
involving the separation of the H-flange.
(4) For the purposes of this AD, an ‘‘HPT
engine shop visit’’ is the induction of an
engine into the shop for maintenance
involving the separation of the M-flange.
(5) For the purposes of this AD, a ‘‘part
eligible for installation’’ is:
(i) An HPC IBR–7 having P/N 30G2307 or
30G4407 that has passed the AUSI required
by paragraph (h)(1) of this AD or is identified
as not affected by this AD in paragraph (c)(2)
of this AD, or later approved P/N.
(ii) An HPC IBR–8 having P/N 30G5608,
30G5908, or 30G8908 that has passed the
AUSI required by paragraph (h)(1) of this AD
or is identified as not affected by this AD in
paragraph (c)(2) of this AD, or later approved
P/N.
(iii) An HPT 1st-stage hub having P/N
30G7301 that has passed the AUSI required
by paragraph (h)(2) of this AD or is identified
as not affected by this AD in paragraph (c)(2)
of this AD, or later approved P/N.
(iv) An HPT 2nd-stage hub having P/N
30G6602 that has passed the AUSI required
by paragraph (h)(2) of this AD or is identified
as not affected by this AD in paragraph (c)(2)
of this AD, or later approved P/N.
(v) An HPC rear hub having P/N 30G8208
and is identified as not affected by this AD
in paragraph (c)(2) of this AD, or later
approved P/N.
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(j) Credit for Previous Actions
(1) This paragraph provides credit for the
actions specified in paragraph (g)(1) and (2)
of this AD, if those actions were performed
before the effective date of this AD using PW
Service Bulletin PW1000G–C–72–00–0188–
00A–930A–D, Issue No: 001, dated
September 13, 2021. This service information
is not incorporated by reference in this AD.
(2) This paragraph provides credit for the
actions specified in paragraph (h)(2) and (6)
of this AD, if those actions were performed
before the effective date of this AD using PW
Alert Service Bulletin PW ASB PW1000G–C–
72–00–0225–00A–930A–D, Issue No: 001,
dated November 3, 2023. This service
information is not incorporated by reference
in this AD.
(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 the AIR–520 Continued
Operational Safety Branch, send it to the
attention of the person identified in
paragraph (l)(1) 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
(1) For more information about this AD,
contact Carol Nguyen, Aviation Safety
Engineer, FAA, 2200 South 216th Street, Des
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Moines, WA 98198; phone: (781) 238–7655;
email: carol.nguyen@faa.gov.
(2) Service information identified in this
AD that is not incorporated by reference is
available at the address specified in
paragraph (m)(6) of this AD.
(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.
(3) The following service information was
approved for IBR on April 11, 2024.
(i) Pratt & Whitney Alert Service Bulletin
PW1000G–C–72–00–0224–00A–930A–D,
Issue No: 001, dated November 3, 2023.
(ii) Pratt & Whitney Alert Service Bulletin
PW1000G–C–72–00–0225–00A–930A–D,
Issue No: 002, dated December 12, 2023.
(iii) Pratt & Whitney Special Instruction
No. 198F–23, dated November 3, 2023.
(iv) Pratt & Whitney Special Instruction
No. 222F–23, Revision B, dated March 1,
2024.
(4) The following service information was
approved for IBR on August 28, 2023 (88 FR
56999, August 22, 2023).
(i) Pratt & Whitney Special Instruction No.
149F–23, dated August 4, 2023.
(ii) [Reserved]
(5) The following service information was
approved for IBR on November 7, 2022 (87
FR 59660, October 3, 2022; corrected October
24, 2022 (87 FR 64156)).
(i) Pratt & Whitney Service Bulletin
PW1000G–C–72–00–0188–00A–930A–D,
Issue No: 002, dated July 8, 2022.
(ii) [Reserved]
(6) For Pratt & Whitney service information
that is incorporated by reference, contact
International Aero Engines, LLC, 400 Main
Street, East Hartford, CT 06118; phone: (860)
565–0140; email: help24@pw.utc.com;
website: connect.prattwhitney.com.
(7) You may view this service information
that is incorporated by reference 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.
(8) You may view this material at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA,
visit www.archives.gov/federal-register/cfr/
ibr-locations or email fr.inspection@nara.gov.
Issued on March 8, 2024.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2024–06419 Filed 3–22–24; 11:15 am]
BILLING CODE 4910–13–P
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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
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
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 highpressure 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 8thstage disks, HPC rear hubs, HPT 1ststage 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 regulations.gov 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
SUMMARY:
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Federal Register / Vol. 89, No. 60 / Wednesday, March 27, 2024 / Rules and Regulations
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE, Washington, DC
20590.
Material Incorporated by Reference:
• 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:
help24@pw.utc.com; website:
connect.prattwhitney.com.
• 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 regulations.gov 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: carol.nguyen@faa.gov.
SUPPLEMENTARY INFORMATION:
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 2ndstage 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.
Background
Request To Clarify Unsafe Condition
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
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.
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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 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
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21191
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
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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.
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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
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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:
• 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
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performing an AUSI on affected HPT
1st-stage hubs and HPT 2nd-stage hubs.
• 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.
• 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.
• 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.
• 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
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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 8thstage disk; 121 engines would need
21193
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
Labor cost
Perform AUSI of HPT 1st-stage hub, HPT 2ndstage hub, and HPC 8th-stage disk.
Replace HPT 1st-stage hub .....................................
Replace HPT 2nd-stage hub ....................................
Replace HPC 7th-stage rotor ...................................
Replace HPC 8th-stage disk ....................................
Replace HPC rear hub .............................................
Replace HPT 1st-stage air seal ................................
Replace HPT 2nd-stage air seal ..............................
Replace HPT 1st-stage blade retaining plate ...........
Replace HPT 2nd-stage blade retaining plate .........
60 work-hours × $85 per hour = $5,100 ..
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.
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Parts cost
(average
pro-rated cost)
Action
$5,100
$617,100
.........
.........
.........
.........
.........
.........
.........
.........
.........
49,500
25,500
48,000
35,500
83,000
21,000
36,000
34,000
13,000
50,350
26,350
48,850
36,350
83,850
21,850
36,850
34,850
13,850
6,092,350
3,188,350
5,910,850
4,398,350
10,145,850
2,643,850
4,458,850
4,216,850
1,675,850
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.
(a) Effective Date
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
(d) Subject
The Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
(e) Unsafe Condition
10
10
10
10
10
10
10
10
10
×
×
×
×
×
×
×
×
×
85
85
85
85
85
85
85
85
85
per
per
per
per
per
per
per
per
per
hour
hour
hour
hour
hour
hour
hour
hour
hour
=
=
=
=
=
=
=
=
=
850
850
850
850
850
850
850
850
850
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
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
■
Jkt 262001
work-hours
work-hours
work-hours
work-hours
work-hours
work-hours
work-hours
work-hours
work-hours
PART 39—AIRWORTHINESS
DIRECTIVES
§ 39.13
16:04 Mar 26, 2024
Cost on U.S.
operators
$0
Regulatory Findings
VerDate Sep<11>2014
Cost per
product
[Amended]
2. The FAA amends § 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.
PO 00000
Frm 00015
Fmt 4700
Sfmt 4700
This airworthiness directive (AD) is
effective April 11, 2024.
(b) Affected ADs
None.
(c) Applicability
Pratt & Whitney (PW) Model PW1519G,
PW1521G, PW1521GA, PW1521G–3,
PW1524G, PW1524G–3, PW1525G,
PW1525G–3, PW1919G, PW1921G,
PW1922G, PW1923G, and PW1923G–A
engines.
Joint Aircraft System Component (JASC)
Code 7230, Turbine Engine Compressor
Section; 7250, Turbine Section.
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.
E:\FR\FM\27MRR1.SGM
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Federal Register / Vol. 89, No. 60 / Wednesday, March 27, 2024 / Rules and Regulations
(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 1ststage 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
Part
Applicable S/N listing
HPC 8th-stage disk P/
N 30G7208.
Table 1 of PW ASB PW1000G–A–72–00–
0197–00A–930A–D, Issue No: 004.
HPT 1st-stage hub P/
N 30G8501.
Table 2 of PW ASB PW1000G–A–72–00–
0196–00A–930A–D, Issue No: 002.
Next HPC engine shop visit not to
exceed 10,000 part cycles since
new (CSN).
Next engine shop visit not to exceed
5,000 part CSN.
HPT 2nd-stage hub P/
N 30G7202.
Table 3 of PW ASB PW1000G–A–72–00–
0196–00A–930A–D, Issue No: 002.
Next engine shop visit not to exceed
5,000 part CSN.
HPT 1st-stage hub P/
N 30G8501.
Table 4 of PW ASB PW1000G–A–72–00–
0196–00A–930A–D, Issue No: 002.
Next engine shop visit not to exceed
4,000 part CSN.
HPT 2nd-stage hub P/
N 30G7202.
Table 5 of PW ASB PW1000G–A–72–00–
0196–00A–930A–D, Issue No: 002.
Next engine shop visit not to exceed
4,000 part CSN.
(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–
Applicable service bulletin
(see paragraph (m)(2) of this AD)
Compliance time
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 8thstage 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-
Accomplishment Instructions, paragraph 8., of PW
ASB PW1000G–A–72–00–0197–00A–930A–D,
Issue No: 004.
Accomplishment Instructions, paragraph 8.A. of PW
ASB PW1000G–A–72–00–0196–00A–930A–D,
Issue No: 002.
Accomplishment Instructions, paragraph 8.B, of PW
ASB PW1000G–A–72–00–0196–00A–930A–D,
Issue No: 002.
Accomplishment Instructions, paragraph 8.A, of PW
ASB PW1000G–A–72–00–0196–00A–930A–D,
Issue No: 002.
Accomplishment Instructions, paragraph 8.B., of PW
ASB PW1000G–A–72–00–0196–00A–930A–D,
Issue No: 002.
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
khammond on DSKJM1Z7X2PROD with RULES
Part
Table S/N is listed in
HPC 8th-stage disk
Table 1 of PW ASB PW1000G–A–72–00–
having P/N 30G7208.
0142–00B–930A–D, Issue No: 004.
Next HPC engine shop visit not to
exceed 10,000 part CSN.
HPT 1st-stage hub
Table 2 of PW ASB PW1000G–A–72–00–
having P/N 30G8501.
0141–00B–930A–D, Issue No: 002.
Next engine shop visit not to exceed
5,000 part CSN.
HPT 2nd-stage hub
Table 3 of PW ASB PW1000G–A–72–00–
having P/N 30G7202.
0141–00B–930A–D, Issue No: 002.
Next engine shop visit not to exceed
5,000 part CSN.
HPT 1st-stage hub
Table 4 of PW ASB PW1000G–A–72–00–
having P/N 30G8501.
0141–00B–930A–D, Issue No: 002.
Next engine shop visit not to exceed
4,000 part CSN.
HPT 2nd-stage hub
Table 5 of PW ASB PW1000G–A–72–00–
having P/N 30G7202.
0141–00B–930A–D, Issue No: 002.
Next engine shop visit not to exceed
4,000 part CSN.
VerDate Sep<11>2014
16:04 Mar 26, 2024
Jkt 262001
PO 00000
Applicable service bulletin
(see paragraph (m)(2) of this AD)
Compliance time
Frm 00016
Fmt 4700
Sfmt 4700
Accomplishment Instructions, paragraph 8., of PW
ASB PW1000G–A–72–00–0142–00B–930A–D,
Issue No: 004.
Accomplishment Instructions, paragraph 8.A., of PW
ASB PW1000G–A–72–00–0141–00B–930A–D,
Issue No: 002.
Accomplishment Instructions, paragraph 8.B, of PW
ASB PW1000G–A–72–00–0141–00B–930A–D,
Issue No: 002.
Accomplishment Instructions, paragraph 8.A., of PW
ASB PW1000G–A–72–00–0141–00B–930A–D,
Issue No: 002.
Accomplishment Instructions, paragraph 8.B., of PW
ASB PW1000G–A–72–00–0141–00B–930A–D,
Issue No: 002.
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Federal Register / Vol. 89, No. 60 / Wednesday, March 27, 2024 / Rules and Regulations
(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
khammond on DSKJM1Z7X2PROD with RULES
HPC 7th-stage rotor ..............................
HPC 8th-stage disk ...............................
HPC rear hub ........................................
HPT 1st-stage hub ................................
HPT 2nd-stage hub ...............................
HPT 1st-stage air seal ..........................
HPT 2nd-stage air seal .........................
HPT 1st-stage blade retaining plate .....
HPT 2nd-stage blade retaining plate ....
30G3307
30G3248
30G2902
30G5701
30G5002
30G3132
30G3451
30G1692
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 1ststage 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/
VerDate Sep<11>2014
16:04 Mar 26, 2024
Jkt 262001
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 ‘‘piecepart 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
PO 00000
Frm 00017
Fmt 4700
Sfmt 4700
21195
(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: carol.nguyen@faa.gov.
(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.
E:\FR\FM\27MRR1.SGM
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Federal Register / Vol. 89, No. 60 / Wednesday, March 27, 2024 / Rules and Regulations
(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:
help24@pw.utc.com; website:
connect.prattwhitney.com.
(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 www.archives.gov/federal-register/cfr/
ibr-locations or email fr.inspection@nara.gov.
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
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2024–0472; Project
Identifier MCAI–2024–00095–E; Amendment
39–22707; AD 2024–06–02]
RIN 2120–AA64
Airworthiness Directives; GE Aviation
Czech s.r.o. (Type Certificate
Previously Held by WALTER Engines
a.s., Walter a.s., and MOTORLET a.s.)
Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for all GE
Aviation Czech s.r.o. (GEAC) (type
certificate previously held by WALTER
Engines a.s., Walter a.s., and
MOTORLET a.s.) Model M601D–11,
M601E–11, M601E–11A, M601E–11AS,
M601E–11S, and M601F engines. This
AD was prompted by a report of a crack
on the centrifugal compressor case
mount pad weld area, caused by a nonconforming welding (lack of welding
penetration). This AD requires a onetime detailed visual inspection of the
compressor case pad welds for any
crack, and replacement of the
compressor case if necessary, as
specified in a European Union Aviation
Safety Agency (EASA) AD, which is
incorporated by reference (IBR). The
FAA is issuing this AD to address the
unsafe condition on these products.
khammond on DSKJM1Z7X2PROD with RULES
SUMMARY:
VerDate Sep<11>2014
16:04 Mar 26, 2024
Jkt 262001
This AD is effective April 11,
2024.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of April 11, 2024.
The FAA must receive comments on
this AD by May 13, 2024.
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
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.
AD Docket: You may examine the AD
docket at regulations.gov under Docket
No. FAA–2024–0472; or in person at
Docket Operations between 9 a.m. and
5 p.m., Monday through Friday, except
Federal holidays. The AD docket
contains this final rule, the mandatory
continuing airworthiness information
(MCAI), any comments received, and
other information. The street address for
Docket Operations is listed above.
Material Incorporated by Reference:
• For service information identified
in this final rule, contact EASA, KonradAdenauer-Ufer 3, 50668 Cologne,
Germany; phone: +49 221 8999 000;
email: ADs@easa.europa.eu; website:
easa.europa.eu. You may find this
material on the EASA website at
ad.easa.europa.eu.
• 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 regulations.gov under
Docket No. FAA–2024–0472.
FOR FURTHER INFORMATION CONTACT:
Barbara Caufield, Aviation Safety
Engineer, FAA, 1600 Stewart Avenue,
Suite 410, Westbury, NY 11590; phone:
(781) 238–7146; email:
barbara.caufield@faa.gov.
SUPPLEMENTARY INFORMATION:
DATES:
Comments Invited
The FAA invites you to send any
written data, views, or arguments about
this final rule. Send your comments to
an address listed under ADDRESSES.
Include ‘‘Docket No. FAA–2024–0472;
PO 00000
Frm 00018
Fmt 4700
Sfmt 4700
Project Identifier MCAI–2024–00095–E’’
at the beginning of your comments. The
most helpful comments reference a
specific portion of the final rule, explain
the reason for any recommended
change, and include supporting data.
The FAA will consider all comments
received by the closing date and may
amend this final rule 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
regulations.gov, including any personal
information you provide. The agency
will also post a report summarizing each
substantive verbal contact received
about this final rule.
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 AD contain
commercial or financial information
that is customarily treated as private,
that you actually treat as private, and
that is relevant or responsive to this AD,
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 AD. Submissions containing CBI
should be sent to Barbara Caufield,
Aviation Safety Engineer, FAA, 1600
Stewart Avenue, Suite 410, Westbury,
NY 11590. Any commentary that the
FAA receives which is not specifically
designated as CBI will be placed in the
public docket for this rulemaking.
Background
EASA, which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2024–
0040–E, dated February 8, 2024, (EASA
AD 2024–0040–E) (also referred to as
the MCAI), to correct an unsafe
condition on GEAC Model M601D,
M601D–1, M601D–2, M601D–11,
M601D–11NZ, M601E, M601E–11,
M601E–11A, M601E–11AS, M601E–
11S, M601E–21, M601F, M601FS, and
M601Z engines. The MCAI states that a
crack was found on the centrifugal
compressor case mount pad weld area of
an engine, which led to an unscheduled
engine removal. Further investigation
identified a non-conforming welding in
the location of the failure (lack of
E:\FR\FM\27MRR1.SGM
27MRR1
]]>Agencies
[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 [www.gpo.gov]
[FR Doc No: 2024-06433]
-----------------------------------------------------------------------
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 regulations.gov 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:
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: [email protected];
website: connect.prattwhitney.com.
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 regulations.gov 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: [email protected].
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:
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.
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.
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.
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.
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.
(c) Applicability
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: [email protected].
(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: [email protected]; website:
connect.prattwhitney.com.
(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 www.archives.gov/federal-register/cfr/ibr-locations or email [email protected].
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
