Airworthiness Directives; International Aero Engines, LLC Engines, 21181-21190 [2024-06419]
Download as PDF
<![CDATA[
Federal Register / Vol. 89, No. 60 / Wednesday, March 27, 2024 / Rules and Regulations
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Requirements
Except as specified in paragraph (h) of this
AD: Comply with all required actions and
compliance times specified in, and in
accordance with, Transport Canada AD CF–
2023–24.
(h) Exceptions to Transport Canada AD CF–
2023–24
(1) Where Transport Canada AD CF–2023–
24 refers to its effective date, this AD requires
using the effective date of this AD.
(2) Where Transport Canada AD CF–2023–
24 refers to ‘‘hours air time,’’ this AD requires
replacing those words with ‘‘flight hours.’’
(3) Where the service information specified
in Transport Canada AD CF–2023–24, in
steps 3.7.4.1 and 3.7.4.2, specifies using
‘‘screws (14),’’ this AD requires replacing
those words with ‘‘screws (18).’’
(4) Where the service information specified
in Transport Canada AD CF–2023–24, in step
3.7.7.1, specifies installing ‘‘harnesses
CPWTG2032 and CPWTH2034,’’ this AD
requires replacing those words with
‘‘harnesses CPYTG2039 and CPYTH2041.’’
khammond on DSKJM1Z7X2PROD with RULES
(i) Additional AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Validation 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
responsible Flight Standards Office, as
appropriate. If sending information directly
to the International Validation Branch, send
it to the attention of the person identified in
paragraph (j) of this AD. Information may be
emailed to: 9-AVS-AIR-730-AMOC@faa.gov.
Before using any approved AMOC, notify
your appropriate principal inspector, or
lacking a principal inspector, the manager of
the responsible Flight Standards Office.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain instructions
from a manufacturer, the instructions must
be accomplished using a method approved
by the Manager, International Validation
Branch, FAA; or Transport Canada; or Airbus
Canada Limited Partnership’s Transport
Canada Design Approval Organization
(DAO). If approved by the DAO, the approval
must include the DAO-authorized signature.
(j) Additional Information
For more information about this AD,
contact William Reisenauer, Aviation Safety
Engineer, FAA, 1600 Stewart Avenue, Suite
410, Westbury, NY 11590; phone: 516–228–
7300; email: 9-avs-nyaco-cos@faa.gov.
(k) 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.
VerDate Sep<11>2014
16:04 Mar 26, 2024
Jkt 262001
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) Transport Canada AD CF–2023–24,
dated April 6, 2023.
(ii) [Reserved]
(3) For Transport Canada AD CF–2023–24,
contact Transport Canada National Aircraft
Certification, 159 Cleopatra Drive, Nepean,
Ontario K1A 0N5, Canada; telephone 888–
663–3639; email TC.AirworthinessDirectivesConsignesdenavigabilite.TC@tc.gc.ca. You
may find this Transport Canada AD on the
Transport Canada website at tc.canada.ca/
en/aviation.
(4) You may view this material at the FAA,
Airworthiness Products Section, Operational
Safety Branch, 2200 South 216th St., Des
Moines, WA. For information on the
availability of this material at the FAA, call
206–231–3195.
(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-locationsoremailfr.inspection@nara.gov.
Issued on February 27, 2024.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2024–06477 Filed 3–26–24; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2023–2401; Project
Identifier AD–2023–01278–E; Amendment
39–22703; AD 2024–05–11]
RIN 2120–AA64
Airworthiness Directives; International
Aero Engines, LLC Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is superseding
Airworthiness Directive (AD) 2022–19–
15 for certain International Aero
Engines, LLC (IAE LLC) Model
PW1100G series engines; and AD 2023–
16–07 for certain IAE LLC Model
PW1100G series engines and PW1400G
series engines. AD 2022–19–15 required
an angled ultrasonic inspection (AUSI)
of the high-pressure turbine (HPT) 1ststage disk and HPT 2nd-stage disk, and
replacement, if necessary. AD 2023–16–
07 required an AUSI of the HPT 1ststage hub (also known as the HPT 1ststage disk) and HPT 2nd-stage hub (also
known as the HPT 2nd-stage disk) for
cracks, and replacement, if necessary,
which is terminating action for AD
2022–19–15. This AD was prompted by
SUMMARY:
PO 00000
Frm 00003
Fmt 4700
Sfmt 4700
21181
an investigation that determined an
increased risk of powdered metal
anomalies for all powdered metal parts
in certain powdered metal production
campaigns, which are susceptible to
failure significantly earlier than
previously determined. This AD retains
the AUSI requirement for certain HPT
1st-stage and HPT 2nd-stage hubs from
AD 2023–16–07. This AD requires
performing an AUSI of the HPT 1ststage hub, HPT 2nd-stage hub, highpressure compressor (HPC) 7th-stage
integrally bladed rotor (IBR–7), and HPC
8th-stage integrally bladed rotor (IBR–8)
for cracks, and replacing if necessary.
This AD also requires accelerated
replacement of the HPC IBR–7, HPC
IBR–8, HPC rear hub, HPT 1st-stage hub,
and HPT 2nd-stage hub. 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.
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of August 28, 2023 (88 FR
56999, August 22, 2023).
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of November 7, 2022 (87 FR
59660, October 3, 2022; corrected
October 24, 2022 (87 FR 64156)).
ADDRESSES:
AD Docket: You may examine the AD
docket at regulations.gov under Docket
No. FAA–2023–2401; or in person at
Docket Operations between 9 a.m. and
5 p.m., Monday through Friday, except
Federal holidays. The AD docket
contains this final rule, any comments
received, and other information. The
address for Docket Operations is U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE, Washington, DC
20590.
Material Incorporated by Reference:
• For Pratt & Whitney (PW) 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.
• 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
E:\FR\FM\27MRR1.SGM
27MRR1
21182
Federal Register / Vol. 89, No. 60 / Wednesday, March 27, 2024 / Rules and Regulations
on the availability of this material at the
FAA, call (817) 222–5110. It is also
available at regulations.gov under
Docket No. FAA–2023–2401.
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:
khammond on DSKJM1Z7X2PROD with RULES
Background
The FAA issued a notice of proposed
rulemaking (referred to herein as the
NPRM) to amend 14 CFR part 39 to
supersede AD 2022–19–15, Amendment
39–22184 (87 FR 59660, October 3,
2022; corrected October 24, 2022 (87 FR
64156)) (AD 2022–19–15); and AD
2023–16–07, Amendment 39–22526 (88
FR 56999, August 22, 2023) (AD 2023–
16–07). AD 2022–19–15 applied to
certain IAE LLC Model PW1122G–JM,
PW1124G1–JM, PW1124G–JM,
PW1127G1–JM, PW1127GA–JM,
PW1127G–JM, PW1129G–JM,
PW1130G–JM, PW1133GA–JM, and
PW1133G–JM engines. AD 2023–16–07
applied to certain IAE LLC Model
PW1122G–JM, PW1124G1–JM,
PW1124G–JM, PW1127G–JM,
PW1127G1–JM, PW1127GA–JM,
PW1129G–JM, PW1130G–JM,
PW1133G–JM, PW1133GA–JM,
PW1428G–JM, PW1428GA–JM,
PW1428GH–JM, PW1431G–JM,
PW1431GA–JM, and PW1431GH–JM
engines. The NPRM published in the
Federal Register on December 28, 2023
(88 FR 89627). The NPRM was
prompted by manufacturer analysis of
an HPC IBR–7 failure that determined it
was caused by a powdered metal
anomaly that is similar in nature to the
anomalies outlined in AD 2022–19–15.
The analysis concluded that there is an
increased risk of failure for additional
powdered metal parts in certain
powdered metal production campaigns,
including the HPC IBR–7 and HPC IBR–
8, and that all affected parts are
susceptible to failure significantly
earlier than previously determined. The
condition, if not addressed, could result
in uncontained hub failure, release of
high-energy debris, damage to the
engine, damage to the airplane, and loss
of the airplane.
To address the unsafe condition, the
FAA issued an NPRM (Docket No.
FAA–2023–2237; Project Identifier AD–
2023–01057–E) (referred to herein as the
previous NPRM) to supersede AD 2022–
19–15 and AD 2023–16–07, which was
published in the Federal Register on
December 12, 2023 (88 FR 86088).
However, after the previous NPRM was
issued, the FAA received information
VerDate Sep<11>2014
16:04 Mar 26, 2024
Jkt 262001
from PW that an error was inadvertently
included in the previous NPRM’s
compliance times for some of the HPT
1st-stage and 2nd-stage hubs, which
would have required removal
significantly later than necessary. Due to
the need to shorten the removal
timeframe, the FAA determined it was
necessary to withdraw the previous
NPRM and issue the NPRM for the
unsafe condition with the correct
compliance times.
In the NPRM, the FAA proposed to
continue to require performing an AUSI
of the HPT 1st-stage hub and HPT 2ndstage hub and replacing as necessary.
The NPRM proposed to require
performing an AUSI of the HPC IBR–7
and HPC IBR–8 for cracks and replacing
as necessary. The NPRM also proposed
to require accelerated replacement of
the HPC IBR–7, HPC IBR–8, HPC rear
hub, HPT 1st-stage hub, HPT 1st-stage
air seal, HPT 1st-stage blade retaining
plate, HPT 2nd-stage hub, HPT 2ndstage blade retaining plate, and HPT
2nd-stage rear seal. The FAA is issuing
this AD to address the unsafe condition
on these products.
Discussion of Final Airworthiness
Directive
Comments
The FAA received comments from 14
commenters, including the Air Line
Pilots Association, International
(ALPA); Air New Zealand; All Nippon
Airways CO., LTD. (ANA); Delta Air
Lines, Inc. (DAL); Hawaiian Airlines;
Hong Kong Express Airways Limited
(HK Express); InterGlobe Aviation
Limited (IndiGo); JetBlue Airways
(JetBlue); Lufthansa Group PW1100G–
JM Operators: Lufthansa, SWISS
International, Austrian, Lufthansa
Cityline (Lufthansa Group); Lufthansa
Technik AG; MTU Maintenance
Hannover GmbH; PW; United Airlines;
and Vietnam Airlines JSC. ALPA urged
the manufacturer to develop measures
to minimize the operational impact
these inspections will have on operators
but supported the proposed AD without
change. Thirteen commenters 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 Service Information
Three commenters, Delta, JetBlue, and
Lufthansa Technik AG requested that
the FAA revise paragraphs (h)(2), (h)(6),
and (m)(3)(ii) of the proposed AD to
refer to PW ASB PW1000G–C–72–00–
0225–00A–930A–D, Issue 002, dated
December 12, 2023, rather than PW ASB
PW1000G–C–72–00–0225–00A–930A–
PO 00000
Frm 00004
Fmt 4700
Sfmt 4700
D, Issue 001, dated November 3, 2023.
Lufthansa Technik AG noted that it
would be beneficial to use the latest SB
revision in sections (h), (i), and (j) of the
proposed AD.
The FAA agrees. PW Alert Service
Bulletin (ASB) PW1000G–C–72–00–
0225–00A–930A–D, Issue No: 002,
dated December 12, 2023, adds
alternative methods of AUSI compliance
to the Compliance section, adds service
information to the References section,
and removes unnecessary steps from the
Accomplishment Instructions. The FAA
revised this AD to refer to PW ASB
PW1000G–C–72–00–0225–00A–930A–
D, Issue No: 002, dated December 12,
2023. The FAA also revised paragraph
(j), Credit for Previous Actions, of this
AD to allow credit for certain actions
performed in accordance with PW ASB
PW1000G–C–72–00–0225–00A–930A–
D, Issue No: 001, dated November 3,
2023.
Request To Add Service Information
One commenter, Lufthansa Technik
AG, requested the addition of the
following documents to the Related
Service Information Under 1 CFR part
51 paragraph of the NPRM:
• Special Instruction (SI) 46F–23A,
dated April 4, 2023, which provides
instructions to inspect IBR–7 parts;
• SI 47F–23A, dated April 4, 2023,
which provides instructions to inspect
IBR–8 parts; and
• SI 169F–23B, dated October 11,
2023, and previous, which provides a
procedure to inspect all affected
hardware in-shop.
Lufthansa Technik AG noted that SI
169F–23B should be added to the
proposed AD to ensure that credit can
be taken from last accomplishment of
this SI.
The FAA disagrees. The Related
Service Information Under 1 CFR part
51 paragraph contains service
information that is incorporated by
reference in this AD, and the abovereferenced service information is not
incorporated by reference. The FAA did
not change this final rule as a result of
this comment.
Request To Allow Future Revisions of
Service Information
Three commenters, ANA, Hawaiian
Airlines, and HK Express Airways
requested the FAA add ‘‘or later’’ to SI
No. 222F–23 in the AD or to consider
not requiring a specific SI No. 222F–23
revision. The commenters noted that
this SI will be revised periodically and
suggested that the later revisions should
also be exempt from the proposed AD.
One commenter, ANA, also requested
that the FAA add the phrase ‘‘or later
E:\FR\FM\27MRR1.SGM
27MRR1
Federal Register / Vol. 89, No. 60 / Wednesday, March 27, 2024 / Rules and Regulations
khammond on DSKJM1Z7X2PROD with RULES
revision’’ to each service information
(Service Bulletin and PW Special
Instruction) stated in paragraph (m) of
the proposed AD.
The FAA disagrees with adding ‘‘or
later’’ or ‘‘or later revision’’ for service
information incorporated by reference
in this AD. Future revisions of the
service information have not yet been
published by the manufacturer or
reviewed by the FAA, and therefore
cannot be approved as required service
information. A request for an alternative
method of compliance (AMOC) can be
submitted to the FAA in accordance
with the requirements of paragraph (k)
of this AD if future revisions of the
service information referenced in this
AD are published. Additionally, if
future revisions of the service
information are published by the
manufacturer and approved by the FAA,
the FAA may consider further
rulemaking. The FAA did not change
this AD as a result of these comments.
Request To Exclude Unaffected Parts
Eleven commenters, ANA, DAL,
Hawaiian Airlines, HK Express Airways,
IndiGo, JetBlue, Lufthansa Group,
Lufthansa Technik AG, MTU
Maintenance Hannover GmbH, PW, and
United Airlines, recommended the FAA
exempt the HPC IBR–7, HPC IBR–8,
HPC Rear Hub, HPT 1st stage hub, and
HPT 2nd stage hub serial numbers listed
in Tables 1, 2, and 3 of PW SI No. 222F–
23 from the requirements set forth in the
proposed AD. PW explained that SI No.
222F–23 identifies specific part
numbers and serial numbers that were
manufactured outside the affected
population of material manufactured
from powdered metal addressed by the
proposed AD. PW requested modifying
the ‘‘Applicability’’ section of the
proposed AD to exclude parts which are
not in the affected population.
The FAA agrees. The FAA will revise
paragraph (c), Applicability, of this AD
to reference Tables 1, 2, and 3 of PW SI
No. 222F–23, Revision A, dated
February 13, 2024, which specifies part
numbers and serial numbers verified as
manufactured from powdered metal
campaigns produced prior to November
1, 2015, or after September 1, 2021, and
which are therefore outside the
population of material manufactured
from powdered metal addressed by this
AD. This change in the applicability
reduces the affected part numbers and
serial numbers.
Request Clarification on IBR–8 Part
Numbers
Lufthansa Technik AG commented
that two IBR–8 P/Ns, 30G3808 and
30G6308, are listed in the Illustrated
VerDate Sep<11>2014
16:04 Mar 26, 2024
Jkt 262001
Parts Catalog and in the airworthiness
limitations, but not in the proposed AD.
The commenter asked for clarification
that these part numbers do not require
AUSI and have no additional part
replacement but are not allowed for
reinstallation in accordance with
paragraph (i)(5) of the proposed AD. The
commenter suggested this could be due
to low life-limited part life.
For clarity, the FAA did not address
HPC IBR–8 having P/N 30G3808 and
30G6308 in this AD because the FAA
has determined that those parts are
either retired, out of service, or have
airworthiness limitations that are more
restrictive than the requirements of this
AD. The FAA did not change this AD
as a result of this comment.
Request To Modify Paragraph (g) of the
Proposed AD To Include Certain Part
Numbers
Lufthansa Technik AG requested that
the FAA review the inclusion of all four
affected HPT Stg 1 and Stg 2 part
numbers in paragraphs (g)(1) and (2) of
the proposed AD for completeness of
retaining the requirements of AD 2023–
16–07 with no change.
The FAA disagrees. Paragraph (g),
Retained Inspections from AD 2023–16–
07, With No Changes, of this AD applies
to certain part and serial numbers as
specified. The FAA did not change this
AD as a result of this comment.
Request To Modify the Compliance
Language in Paragraph (g) of the
Proposed AD
One commenter, ANA, requested to
change the required action specified in
paragraph (g) of the proposed AD from
‘‘perform an AUSI of the affected parts
within 30 days,’’ to ‘‘remove the affected
engine from service within 30 days, and
thereafter perform an AUSI of the
affected part before release to service.’’
The FAA disagrees. The commenter
provided no justification for the request,
and the FAA has determined that this
AD as written accomplishes the same
result requested by the commenter. The
FAA did not change this AD as a result
of this comment.
Request To Remove References to
Certain Parts
Two commenters, Air New Zealand
and PW, observed that Table 3 of the
proposed AD includes a reference to
components that are not affected by the
powdered metal issue and are not
referenced in PW SB PW1000G–C–72–
00–0224 and PW1000G–C–72–00–0225.
Air New Zealand suggested that
including these in the proposed AD
would create confusion and
unnecessary complexity when
PO 00000
Frm 00005
Fmt 4700
Sfmt 4700
21183
processing and showing compliance.
PW noted that the proposed AD would
not require accelerated replacement of
HPT 1st-stage front air seal, HPT 2ndstage rear air seal, HPT 1st-stage blade
retaining plate, and HPT 2nd-stage
blade retaining plate, and further noted
that these parts would be automatically
replaced with incorporation of the Block
D 1st and 2nd stage turbine disks. Air
New Zealand requested the removal of
the references to the HPT 1&2 air seals
and the HPT Stage 1 & 2 retaining
plates.
The FAA agrees. The FAA will
remove the references to HPT 1st-stage
front air seal, HPT 2nd-stage rear air
seal, HPT 1st-stage blade retaining plate,
and HPT 2nd-stage blade retaining plate
from this AD.
Request To Include Calculation for
Mixed Model Management
Three commenters, ANA, Lufthansa
Group, and Lufthansa Technik AG,
observed that a mixed model
management calculation as defined in
PW ASB PW1000G–C–72–00–0224–
00A–930A–D and PW ASB PW1000G–
C–72–00–0225–00A–930A–D is not
mentioned in the proposed AD.
Lufthansa Technik AG suggested that
this calculation is also referenced in SIL
17. Lufthansa Group noted that, without
a stated reference to the mixed model
management calculation, it is possible
that engines operated at any time at the
higher thrust rating must be treated as
such. The commenters requested that
the FAA state in the proposed AD that
mixed model management calculation
can be applied to address parts that
have operated in both Group 1 and
Group 2 engines.
The FAA agrees. The FAA will revise
paragraph (h), New Required Actions, of
this AD to address the calculation of
cyclic limits for part replacement and
AUSI compliance times for parts that
have been installed in a Group 1 and
Group 2 configuration as defined in the
note to Table 3 of the compliance
paragraph of PW ASB PW1000G–C–72–
00–0224–00A–930A–D, Issue No: 001
and PW1000G–C–72–00–0225–00A–
930A–D, Issue No: 002. The FAA has
not reviewed SIL 17 and will not
reference this service information in this
AD.
Request To Add a Cyclic Limit to
Paragraph (h)(1) of the Proposed AD
One commenter, Lufthansa Technik
AG, requested the FAA add a cyclic
limit to paragraph (h)(1) of the proposed
AD. The commenter noted that all
affected hardware is covered by the 100flight cycle (FC) timeframe in paragraph
(h)(9) of the proposed AD. The
E:\FR\FM\27MRR1.SGM
27MRR1
21184
Federal Register / Vol. 89, No. 60 / Wednesday, March 27, 2024 / Rules and Regulations
commenter suggested that, since there
are other unrelated issues in the HPC,
and as there is no cyclic limitation
planned for the AUSI of the HPC parts,
the FAA exclude the requirement to
perform an AUSI in accordance with
paragraph (h)(1) of the proposed AD
below 500 FCs since the last AUSI or
since new, unless the HPC rotor is
disassembled. The commenter
explained that this would remove the
need to inspect parts that were recently
installed but removed for access.
The FAA disagrees. The FAA cannot
account for all circumstances that
would require an engine shop visit.
Unusual engine shop visit
circumstances may be considered
through the provisions of paragraph (k),
Alternative Methods of Compliance, of
this AD. The FAA did not change this
AD as a result of this comment.
khammond on DSKJM1Z7X2PROD with RULES
Request To Clarify Discrepancy in
Compliance Times Between the
Proposed AD and the PW ASB
Two commenters, DAL and IndiGo,
noted a discrepancy between the
compliance times in the proposed AD
and those in the PW ASBs. IndiGo
requested that the FAA clarify if the
compliance timeline in the proposed
AD supersedes the compliance timeline
in the PW ASBs, and if the operators
can wait for the proposed AD to be
issued and follow the effective date
stated in the proposed AD. DAL
requested that the FAA add a paragraph
or revise paragraph (h)(2) to address the
100–FC drawdown periods in the
proposed AD and the discrepancy
between the compliance times of the AD
and the PW ASBs.
The FAA disagrees with adding a
paragraph. Operators are required to
comply within the compliance times
specified in this AD. However, how an
operator reacts to recommended actions
from the design approval holder (DAH)
should be spelled out in their approved
maintenance program and is not
governed by this AD. The FAA did not
change this AD as a result of this
comment.
Request To Adjust Compliance Time To
Account for Cycle Count
One commenter, Vietnam Airlines,
observed that the drawdown cycles for
mandated actions (such as part
replacement or inspection) shall be
contingent upon the cycle count
surpassing the compliance threshold
outlined in Table 1 to Paragraph (h)(2)
and Table 2 to Paragraph (h)(3) of the
proposed AD. The commenter suggested
that there should be distinctions in
treatment between an engine exceeding
the threshold by 1,000 cycles and one
VerDate Sep<11>2014
16:04 Mar 26, 2024
Jkt 262001
exceeding the threshold by 200 cycles.
Should the former exhibit a drawdown
period of 100 cycles, the commenter
recommended that the latter be
allocated a longer period for
compliance.
The FAA disagrees. The FAA
determined that a tiered drawdown is
not necessary because all parts
exceeding the compliance time or cycle
limit stated in Table 1 to paragraph
(h)(2) and Table 2 to paragraph (h)(3) of
this AD must be removed within 100
FCs after the effective date of this AD.
The FAA did not change this AD as a
result of this comment.
Request To Include Life Reduction for
Certain HPC Rear Hub
One commenter, ANA, noted that the
compliance times for HPC rear hub
having P/N 30G4008 are specified in
ASB PW1000G–C–72–00–0224–00A–
930A–D, but they are not included in
Table 3 of the proposed AD. Therefore,
the commenter observed, an engine may
be used beyond the compliance times
specified in ASB PW1000G–C–72–00–
0224–00A–930A–D. ANA requested that
the proposed AD be revised to include
the compliance times for P/N 30G4008
specified in ASB PW1000G–C–72–00–
0224–00A–930A–D.
The FAA disagrees. This AD requires
the removal of HPC rear hub having P/
N 30G4008 at either the next HPC
engine shop visit or the next HPT
engine shop visit, whichever occurs
first. The FAA determined that it is not
necessary to specify a compliance time
for HPC rear hub having P/N 30G4008
due to the cycle limits for the associated
HPC and HPT parts. The FAA did not
change this AD as a result of this
comment.
Request To Change ‘‘Crack’’ to ‘‘Defect’’
in Paragraph (h)(8) of the Proposed AD
One commenter, Lufthansa Technik
AG, observed that paragraph (h)(8) of
the proposed AD requires to remove
only parts found with a crack. The
commenter stated that due to AUSI
procedure, it cannot be determined if it
is a crack or just an anomaly. Therefore,
the commenter requested that the FAA
change the wording so that all parts
with defects will be removed from
service.
The FAA partially agrees. The FAA
does not agree with the wording
proposed by the commenter. The FAA
agrees to meet the commenter’s intent
by changing the wording of paragraph
(h)(9) of this AD from ‘‘if any crack is
found,’’ to ‘‘if any crack indication is
found.’’
PO 00000
Frm 00006
Fmt 4700
Sfmt 4700
Request To Include Reference to New
Parts
One commenter, Lufthansa Technik
AG, requested that the FAA change
paragraph (h)(9) of the proposed AD to
read ‘‘[. . .] 100 FCs or less since the
last AUSI OR NEW, (re-)inspection
[. . .].’’ The commenter explained that
this would allow also counting from
reinstallation of new hardware (where it
cannot be determined if the AUSI was
performed during production at OEM).
The FAA disagrees. Paragraph (h)(10)
of this AD applies to repetitive
inspections of affected parts installed
within the last 100 FCs. Parts that are
not included in paragraph (c),
Applicability, of this AD are not subject
to the repetitive AUSI requirement. The
FAA did not change this AD as a result
of this comment.
Request To Revise Heading of Table 1
to Paragraph (h)(2) of the Proposed AD
One commenter, Lufthansa Technik
AG, noted that it would avoid confusion
to reference HPT hub stage 1 and 2 only
in the heading of Table 1 to (h)(2). The
commenter requested that the FAA
include the part names in the header of
the table.
The FAA disagrees. The FAA has
determined that including the part
names in the header is not necessary
because paragraph (h)(2) specifies the
parts and part numbers subject to the
compliance time specified in Table 1 to
Paragraph (h)(2) of this AD. The FAA
did not change this AD as a result of this
comment.
Request To Reference AUSI Performed
in Service in Table 1 to (h)(2) of the
Proposed AD
One commenter, Lufthansa Technik
AG, suggested that the new production
parts inspection regime was updated
and that Table 1 to (h)(2) of the
proposed AD is not covering this AUSI
inspection at production. The
commenter requested that the second
column of Table 1 to (h)(2) of the
proposed AD be revised to state that this
reflects only ‘‘AUSI performed in
service prior to the effective date of this
AD.’’
The FAA disagrees. However, the
FAA has updated paragraph (c),
Applicability, of this AD to exempt
serial numbers listed in Tables 1, 2, and
3 of SI 222F–23, Revision A, which
includes parts subject to AUSI at
production.
Request To Add Airworthiness
Limitation to Table 2 to Paragraph
(h)(3) of the Proposed AD
One commenter, Lufthansa Technik
AG, noted that in Table 2 to paragraph
E:\FR\FM\27MRR1.SGM
27MRR1
Federal Register / Vol. 89, No. 60 / Wednesday, March 27, 2024 / Rules and Regulations
(h)(3) of the proposed AD, for Group 1
engines, the 1st-Stage Hub P/N 30G4201
or 30G6201 with AUSI performed refers
to 3,800 FCs since the last AUSI. The
commenter also noted that for Group 2
engines, the 1st-Stage Hub P/N 30G4201
or 30G6201 with AUSI performed refers
to 2,800 FCs since the last AUSI. The
commenter observed that the part needs
removal within the airworthiness
limitation. The commenter requested
that the FAA add a statement similar to
the 2nd-stage hubs.
The FAA disagrees. The FAA has
determined that adding such a
statement is unnecessary because the
existing airworthiness limitations are
more restrictive. The FAA did not
change this AD as a result of this
comment.
khammond on DSKJM1Z7X2PROD with RULES
Request To Make Changes to Tables
Three commenters, HK Express
Airways, JetBlue, and Lufthansa
Technik AG, expressed that the lack of
borderlines in Table 2 for paragraph
(h)(3) and Table 3 for paragraph (h)(4)
of the proposed AD is confusing.
Lufthansa Technik AG notes that on the
first look, it seems that the compliance
time for part removal at next HPT shop
visit is applicable to one row only, but
in fact should be applicable for all parts
listed below. The commenters requested
that the FAA complete the engine group
and compliance time boxes for each line
item listed in Table 2 and Table 3 of the
proposed AD.
The FAA agrees. The FAA has revised
Table 2 to paragraph (h)(3) and Table 3
to paragraph (h)(4) of this AD to
complete the engine group and
compliance time columns for each line
item.
Request To Provide Additional Cycles
for Alternate Climb Operations
One commenter, JetBlue, stated that
JetBlue has been operating with the
Alternate Climb modification on the
fleet. The commenter explained that the
Alternate Climb modification is
performed pre-delivery and decreases
work/stress on the engine during the
entire climb duration, which effectively
alleviates stress/fatigue. The commenter
requested that the FAA analyze the data
to check the feasibility of providing
additional cycles for the Alternate
Climb modification to meet the
proposed AD timelines.
The FAA disagrees. Operators can
submit a request for an AMOC to the
FAA in accordance with the
requirements of paragraph (k) of this AD
with the data that shows the
modification provides an acceptable
level of safety. The FAA did not change
this AD in response to this comment.
VerDate Sep<11>2014
16:04 Mar 26, 2024
Jkt 262001
Request To Modify Definition for Part
Eligible for Installation
One commenter, HK Express Airways,
noted that PW SI 222F–23 identifies
parts exempted from repetitive AUSI
and early retirement carrying the same
part number, and the commenter
observed that the proposed AD did not
mention this SI in paragraph (i). HK
Express Airways requested adding
reference to SI 222F–23 to the definition
of ‘‘part eligible for installation,’’ so the
parts listed in the SI are deemed to be
eligible for installation. The commenter
also noted that SI 222F–23 will be
updated quarterly by PW, therefore the
AD should not fix the SI version.
The FAA agrees to revise the
definition of ‘‘part eligible for
installation’’ in paragraph (i) of this AD
to reference part serial numbers
identified in Tables 1, 2, and 3 of SI
222F–23, Revision A. The FAA does not
agree to include an undated reference to
SI 222F–23. Future revisions of service
information have not yet been published
by the manufacturer or reviewed by the
FAA, and therefore cannot be approved
as required service information. A
request for an AMOC can be submitted
to the FAA in accordance with
paragraph (k) of this AD if future
revisions of the service information
referenced in this AD are published.
Additionally, if future revisions of the
service information are published by the
manufacturer and approved by the FAA,
the FAA may consider further
rulemaking.
Request To Clarify if Newly Produced
Parts Are Eligible for Installation
Three commenters, DAL, HK Express
Airways, and Lufthansa Technik AG,
observed that the proposed AD did not
address newly produced parts carrying
the same part number in the definition
of ‘‘part eligible for installation’’ in
paragraph (i)(5) of the proposed AD.
Therefore, the commenters reasoned,
the proposed AD does not define
installation eligibility for any new/not
service run HPC/HPT hardware that is
not currently installed on a Group 1 or
Group 2 engine. The commenters
requested that paragraph (i)(5) of the
proposed AD be revised to add
installation eligibility for new
production parts.
The FAA agrees. If the newly
produced parts are manufactured from
powdered metal material produced
prior to November 1, 2015, or after
September 1, 2021, as identified in the
original manufacturing records or in
Tables 1, 2, and 3 of SI No. 222F–23,
Revision A, those parts are not affected
by this AD. The FAA revised the
PO 00000
Frm 00007
Fmt 4700
Sfmt 4700
21185
definition of ‘‘part eligible for
installation’’ in paragraph (i)(5) of this
AD to reference parts identified as not
affected by this AD in paragraph (c)(2)
of this AD. Therefore, parts identified in
Tables 1, 2, and 3 of SI No. 222F–23,
Revision A, will meet the definition of
‘‘part eligible for installation.’’ To meet
the updated definition of ‘‘part eligible
for installation,’’ affected parts need to
be inspected in accordance with this
AD. Unaffected parts can be installed
without performing the requirements of
this AD.
Request To Clarify Meaning of
Induction as Used in Paragraph (i),
Definitions, of the Proposed AD
One commenter, ANA, asked the FAA
to clarify that the definition of
‘‘induction’’ in paragraph (i) of the
proposed AD is the timing when the
engine disassembly is started. ANA
asked the FAA to clarify a particular
situation to have a correct
understanding. ANA noted that, in
terms of paragraph (h)(1) and (2) of the
proposed AD, if an engine is already in
shop for maintenance involving the
separation H-flange or M-flange, then
assembly has already been started at the
effective date of this AD. The
commenter asked if an angled ultrasonic
scan inspection should therefore not be
performed in this shop visit.
The FAA agrees to clarify. The FAA
does not have a set definition for
induction. Reference your approved
maintenance program to determine what
ADs apply to your engines during an
engine shop visit. In the example
provided, if the engine were already at
an engine shop visit on the effective
date of this AD, the requirements of
paragraphs (h)(1) and (2) would apply at
the next engine shop visit after the
effective date of this AD. The FAA did
not change this AD in response to this
comment.
Request To Include 2nd-Stage HPT
Retaining Plates in Paragraph (i),
Definitions, of the Proposed AD
One commenter, Lufthansa Technik
AG, requested that the FAA include
2nd-stage HPT retaining plates in the
definition of parts eligible for
installation.
The FAA disagrees. The FAA revised
this final rule to remove references to
HPT retaining plates in response to
another comment. The FAA did not
change this AD in response to this
comment.
E:\FR\FM\27MRR1.SGM
27MRR1
21186
Federal Register / Vol. 89, No. 60 / Wednesday, March 27, 2024 / Rules and Regulations
Request To Identify Previous AUSI
Service Information in Paragraph (j),
Credit for Previous Actions, of the
Proposed AD
One commenter, Lufthansa Technik
AG, observed that, in addition to the
credit for paragraphs (g)(1) and (2) of the
proposed AD, it should be required to
note down which procedures qualify as
‘‘AUSI performed’’ for cyclic
requirements under paragraphs (h)(2)
with table 1 and (h)(8) of the proposed
AD to correctly determine the remaining
life and if the AUSI was performed prior
to AD eÄectivity. The commenter listed
the following service information: For
HPT hubs in accordance with (h)(2) and
(8) of the proposed AD:
• SI 169F–23;
• SB PW1000G–C–72–00–0188–00A–
930A–D, Issue 1 dated September 13,
2021; and
• PW1000G–C–72–00–0188–00A–
930A–D, Issue 2 dated July 8, 2022.
For HPC parts in accordance with
paragraph (h)(8) of the proposed AD:
• SI 46F–23; and
• SI 47F–23.
The FAA infers that the commenter
requested that the FAA add the service
information identified to paragraph (j),
Credit for Previous Actions, of this AD.
The FAA disagrees. PW SB PW1000G–
C–72–00–0188–00A–930A–D, Issue No:
001, dated September 13, 2021, is
referenced in paragraph (j), Credit for
Previous Actions, of this AD. The FAA
revised paragraph (j), Credit for Previous
Actions, of this AD to include PW ASB
PW1000G–C–72–00–0225–00A–930A–
D, Issue No. 001, dated November 3,
2023, which provides methods for AUSI
that may have been previously used, in
response to a separate comment. The
FAA did not change this AD in response
to this comment.
khammond on DSKJM1Z7X2PROD with RULES
Request To Add Special Flights Permit
Paragraph
One commenter, HK Express Airways,
noted that according to PW, nonrevenue maintenance or check flights
are permitted if the aircraft is required
to re-locate to base maintenance
facilities for storage or engine removal
after the compliance time. The
commenter requested that the FAA add
a paragraph to the proposed AD to
clearly state that non-revenue
maintenance flights are permitted
within the proposed AD.
The FAA disagrees because 14 CFR
39.23 allows for special flight permits
unless specified as limited or prohibited
in the AD. The FAA did not change this
AD in response to this comment.
VerDate Sep<11>2014
16:04 Mar 26, 2024
Jkt 262001
Additional Change Made to the
Applicability
Since the NPRM published, the FAA
determined the need to add IAE LLC
Models PW1127G1A–JM and
PW1127G1B–JM to paragraph (c),
Applicability, in this AD. These engine
models were recently certificated but
are not in production yet. The FAA
revised the applicability of this AD to
include these additional engine models.
None of the engines added to the
applicability of this AD are on the U.S.
Register. Additional notice and
opportunity for public comment before
issuing this AD are therefore
unnecessary. Since there are no
additional engines on the U.S. registry,
no changes have been made to the Costs
of Compliance paragraph in this final
rule.
Updated Service Information for
Paragraph (c)(2) of the Applicability
Since the NPRM comment period
closed, PW updated SI 222F–23,
Revision A, to add additional part
numbers and serial numbers verified as
manufactured from powdered metal
campaigns produced prior to November
1, 2015, or after September 1, 2021, and
which are therefore outside the
population of material manufactured
from powdered metal addressed by this
AD. For this reason, the FAA updated
paragraph (c)(2) of the Applicability to
reference Tables 1, 2, and 3 of PW SI
No. 222F–23, Revision B, dated March
1, 2024. This change to the applicability
of this AD reduces the affected part
numbers and serial numbers.
Conclusion
The FAA reviewed the relevant data,
considered any comments received, and
determined that air safety requires
adopting the 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–C–72–00–
0224–00A–930A–D, Issue No: 001,
dated November 3, 2023, which
specifies procedures for performing an
AUSI for cracks on affected HPC IBR–
7 and HPC IBR–8;
• PW ASB PW1000G–C–72–00–
0225–00A–930A–D, Issue No: 002,
dated December 12, 2023, which
PO 00000
Frm 00008
Fmt 4700
Sfmt 4700
specifies procedures for performing an
AUSI for cracks on affected HPT 1ststage hubs and HPT 2nd-stage hubs;
• PW SI No. 198F–23, dated
November 3, 2023, which specifies the
list of affected HPT 1st-stage hubs and
HPT 2nd-stage hubs, identified by part
number and serial number, installed on
certain IAE LLC engines;
• PW SI No. 222F–23, Revision B,
dated March 1, 2024, which specifies
the list of part numbers and serial
numbers that were manufactured
outside of the affected population of
material manufactured from powdered
metal;
• PW Service Bulletin PW1000G–C–
72–00–0188–00A–930A–D, Issue No:
002, dated July 8, 2022, which was
previously approved for incorporation
by reference on November 7, 2022 (87
FR 59660, October 3, 2022; corrected
October 24, 2022 (87 FR 64156)). This
service information specifies procedures
for performing an AUSI for cracks on
affected HPT 1st-stage hubs and HPT
2nd-stage hubs; and
• PW SI No. 149F–23, dated August
4, 2023, which was previously approved
for incorporation by reference on
August 28, 2023 (88 FR 56999, August
22, 2023). This service information
specifies the list of affected HPT 1ststage hubs and HPT 2nd-stage hubs,
identified by part number and serial
number, installed on certain IAE LLC
engines.
This service information is reasonably
available because the interested parties
have access to it through their normal
course of business or by the means
identified in the ADDRESSES section.
Interim Action
The FAA considers this AD to be an
interim action. The unsafe condition is
still under investigation by the
manufacturer and, depending on the
results of that investigation, the FAA
may consider further rulemaking action.
Justification for Determination of the
Effective Date
Section 553(d) of the Administrative
Procedure Act (APA) (5 U.S.C. 551 et
seq.) authorizes agencies to make rules
effective in less than thirty days, upon
a finding of ‘‘good cause.’’ The FAA has
found that the risk to the flying public
justifies a shortened effective date for
this rule due to powdered metal
anomalies in HPT 1st-stage hub, HPT
2nd-stage hub, HPC IBR–7, 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
E:\FR\FM\27MRR1.SGM
27MRR1
Federal Register / Vol. 89, No. 60 / Wednesday, March 27, 2024 / Rules and Regulations
certain parts is within 100 flight cycles
after the effective date of this AD, which
is on average one calendar month of
operation. The longer these parts remain
in service, the higher the probability of
failure. Additionally, the FAA did not
receive any adverse comments or useful
information about this AD from U.S.
operators that necessitates waiting 30
days for this AD to become effective.
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 430 engines installed on
airplanes of U.S. registry. The FAA
estimates that 366 engines will need
21187
replacement of the HPT 1st-stage hub;
351 engines will need replacement of
the HPT 2nd-stage hub; 408 engines will
need replacement of the HPC IBR–7; 368
engines will need replacement of the
HPC IBR–8; and 283 engines will need
replacement of the HPC rear hub.
The FAA estimates the following
costs to comply with this AD:
ESTIMATED COSTS
Labor cost
AUSI of HPT 1st-stage hub, HPT 2nd-stage hub,
HPC IBR–7, and HPC IBR–8 for cracks.
Replace HPT 1st-stage hub .....................................
Replace HPT 2nd-stage hub ....................................
Replace HPC IBR–7 .................................................
Replace HPC IBR–8 .................................................
Replace HPC rear hub .............................................
80 work-hours ×$85 per hour = $6,800 ...
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.
khammond on DSKJM1Z7X2PROD with RULES
Parts cost
(average
pro-rated cost)
Action
Regulatory Findings
The FAA has determined that this AD
will not have federalism implications
under Executive Order 13132. This AD
will not have a substantial direct effect
on the States, on the relationship
between the national government and
the States, or on the distribution of
power and responsibilities among the
various levels of government.
For the reasons discussed above, I
certify that this AD:
VerDate Sep<11>2014
16:04 Mar 26, 2024
Jkt 262001
Cost per
product
Cost on U.S.
operators
$0
$6,800
$2,924,000
......
......
......
......
......
56,000
62,000
82,000
93,000
132,000
56,850
62,850
82,850
93,850
132,850
20,807,100
$22,060,350
33,802,800
34,536,800
37,596,550
(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
10
10
10
10
10
work-hours
work-hours
work-hours
work-hours
work-hours
×$85
×$85
×$85
×$85
×$85
per
per
per
per
per
hour
hour
hour
hour
hour
=
=
=
=
=
$850
$850
$850
$850
$850
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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by:
■ a. Removing Airworthiness Directive
2022–19–15, Amendment 39–22184 (87
FR 59660, October 3, 2022; corrected
October 24, 2022 (87 FR 64156)); and
Airworthiness Directive 2023–16–07,
Amendment 39–22526 (88 FR 56999,
August 22, 2023); and
■ b. Adding the following new
airworthiness directive:
■
2024–05–11 International Aero Engines,
LLC: Amendment 39–22703; Docket No.
FAA–2023–2401; Project Identifier AD–
2023–01278–E.
PO 00000
Frm 00009
Fmt 4700
Sfmt 4700
This airworthiness directive (AD) is
effective April 11, 2024.
(b) Affected ADs
(1) This AD replaces AD 2022–19–15,
Amendment 39–22184 (87 FR 59660, October
3, 2022; corrected October 24, 2022 (87 FR
64156)).
(2) This AD replaces AD 2023–16–07,
Amendment 39–22526 (88 FR 56999, August
22, 2023) (AD 2023–16–07).
(c) Applicability
(1) This AD applies to International Aero
Engines, LLC (IAE LLC) Model PW1122G–
JM, PW1124G1–JM, PW1124G–JM,
PW1127G–JM, PW1127G1–JM, PW1127G1A–
JM, PW1127G1B–JM, PW1127GA–JM,
PW1129G–JM, PW1130G–JM, PW1133G–JM,
PW1133GA–JM, PW1428G–JM, PW1428GA–
JM, PW1428GH–JM, PW1431G–JM,
PW1431GA–JM, and PW1431GH–JM engines
with an installed:
(i) High-pressure compressor (HPC) 7thstage integrally bladed rotor (IBR–7) having
part number (P/N) 30G2307 or 30G4407;
(ii) HPC 8th-stage integrally bladed rotor
(IBR–8) having P/N 30G5608, 30G5908, or
30G8908;
(iii) HPC rear hub having P/N 30G4008 or
30G8208;
(iv) High-pressure turbine (HPT) 1st-stage
hub having P/N 30G4201, 30G6201, or
30G7301; or
(v) HPT 2nd-stage hub having P/N
30G3902, 30G5502, or 30G6602.
(2) This AD does not apply to parts
identified in paragraphs (c)(1)(i) through (v)
of this AD if those parts were manufactured
from powdered metal material produced
prior to November 1, 2015, or after
September 1, 2021, as identified by part
serial number in Tables 1, 2, and 3 of PW
Special Instruction (SI) No. 222F–23,
Revision B, dated March 1, 2024 (PW SI No.
222F–23, Revision B) or in the original
manufacturing records for the part.
E:\FR\FM\27MRR1.SGM
27MRR1
21188
Federal Register / Vol. 89, No. 60 / Wednesday, March 27, 2024 / Rules and Regulations
(3) If the original manufacturing records do
not identify the production date of the
powdered metal used to make the parts
identified in paragraphs (c)(1)(i) through (v)
of this AD, and the part serial number is not
listed in Tables 1, 2, and 3 of PW SI No.
222F–23, Revision B, then the part is subject
to the requirements of this AD.
(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 analysis of
an event involving an IAE LLC Model
PW1127GA–JM engine, which experienced
failure of an HPC IBR–7 that resulted in an
engine shutdown and aborted takeoff. The
FAA is issuing this AD to prevent failure of
the HPT 1st-stage hub, HPT 2nd-stage hub,
HPC IBR–7, and HPC IBR–8. The unsafe
condition, if not addressed, could result in
uncontained hub failure, release of highenergy debris, damage to the engine, damage
to the airplane, and loss of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Inspections From AD 2023–16–
07, With No Changes
(1) This paragraph restates the
requirements of paragraph (g)(1) of AD 2023–
16–07. For Group 1 and Group 2 engines
with an installed HPT 1st-stage hub having
part number (P/N) 30G7301 and a serial
number (S/N) listed in Tables 1, 2, 3, or 4 of
PW Special Instruction (SI) No. 149F–23,
dated August 4, 2023 (PW SI No. 149F–23),
within 30 days after August 28, 2023 (the
effective date of AD 2023–16–07), perform an
AUSI of the HPT 1st-stage hubs for cracks in
accordance with the Accomplishment
Instructions, paragraph 9.A. or 9.B., as
applicable, of Pratt & Whitney (PW) Service
Bulletin PW1000G–C–72–00–0188–00A–
930A–D, Issue No: 002, dated July 8, 2022
(PW1000G–C–72–00–0188–00A–930A–D,
Issue No: 002).
(2) This paragraph restates the
requirements of paragraph (g)(2) of AD 2023–
16–07. For Group 1 and Group 2 engines
with an installed HPT 2nd-stage hub having
P/N 30G6602 and an S/N listed in Tables 1,
2, 3, or 4 of PW SI No. 149F–23, within 30
days after August 28, 2023 (the effective date
of AD 2023–16–07), perform an AUSI of the
HPT 2nd-stage hubs for cracks in accordance
with the Accomplishment Instructions,
paragraph 9.C. or 9.D., as applicable, of
PW1000G–C–72–00–0188–00A–930A–D,
Issue No: 002.
(h) New Required Actions
(1) For Group 1 and Group 2 engines with
an affected HPC IBR–7 having P/N 30G2307
or 30G4407, or an affected HPC IBR–8 having
P/N 30G5608, 30G5908, or 30G8908, at the
next HPC engine shop visit and thereafter at
every HPC engine shop visit, perform an
angled ultrasonic scan inspection (AUSI) of
the affected HPC IBR–7 or HPC IBR–8, as
applicable, for cracks in accordance with the
Accomplishment Instructions, paragraph
4.E.(1) or 4.E.(2), of PW Alert Service Bulletin
(ASB) PW1000G–C–72–00–0224–00A–930A–
D, Issue No: 001, dated November 3, 2023
(PW ASB PW1000G–C–72–00–0224–00A–
930A–D, Issue No: 001).
(2) For Group 1 and Group 2 engines with
an affected HPT 1st-stage hub having P/N
30G7301 or an HPT 2nd-stage hub having P/
N 30G6602, before exceeding the applicable
compliance time in Table 1 to paragraph
(h)(2) of this AD, except as required by
paragraphs (g)(1) and (2) and paragraph (h)(7)
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
1.D.(7)(a) or 1.D.(7)(b) of PW ASB PW1000G–
C–72–00–0225–00A–930A–D, Issue No: 002,
dated December 12, 2023 (PW ASB
PW1000G–C–72–00–0225–00A–930A–D,
Issue No: 002). Thereafter, repeat the AUSI at
the applicable interval in Table 1 to
paragraph (h)(2) of this AD.
TABLE 1 TO PARAGRAPH (h)(2)—AUSI COMPLIANCE TIMES
Engine
group
AUSI performed
prior to effective
date of this AD
1 .............
No ..........................
1 .............
Yes .........................
2 .............
No ..........................
2 .............
Yes .........................
Compliance time
Repetitive interval
Before accumulating 3,800 cycles since new (CSN)
or within 100 flight cycles (FCs) after the effective
date of this AD, whichever occurs later.
At the next HPT engine shop visit, not to exceed
3,800 FCs since the previous AUSI, or within 100
FCs after the effective date of this AD, whichever
occurs later.
Before accumulating 2,800 CSN or within 100 FCs
after the effective date of this AD, whichever occurs later.
At the next HPT engine shop visit, not to exceed
2,800 FCs since the previous AUSI, or within 100
FCs after the effective date of this AD, whichever
occurs later.
(3) For Group 1 and Group 2 engines with
an affected part listed in Table 2 to paragraph
(h)(3) of this AD, at the next HPT engine shop
visit not to exceed the applicable cyclic limit
Thereafter at each HPT engine shop visit or before
exceeding 3,800 FCs from the last AUSI of the affected hub, whichever occurs first.
Thereafter at each HPT engine shop visit or before
exceeding 3,800 FCs from the last AUSI of the affected hub, whichever occurs first.
Thereafter at each HPT engine shop visit or before
exceeding 2,800 FCs from the last angled AUSI of
the affected hub, whichever occurs first.
Thereafter at each HPT engine shop visit or before
exceeding 2,800 FCs from the last AUSI of the affected hub, whichever occurs first.
specified in Table 2 to paragraph (h)(3) of
this AD, or 100 FCs after the effective date
of the AD, whichever occurs later, except as
required by paragraphs (h)(6) and (8) of this
AD, remove the affected part from service
and replace with a part eligible for
installation.
khammond on DSKJM1Z7X2PROD with RULES
TABLE 2 TO PARAGRAPH (h)(3)—PART REPLACEMENT COMPLIANCE TIMES
Engine
group
AUSI performed
prior to effective
date of this AD
Part name
1 .............
Yes .........................
HPT 1st-stage hub ..
1 .............
No ..........................
HPT 1st-stage hub ..
1 .............
Yes .........................
HPT 2nd-stage hub
VerDate Sep<11>2014
16:04 Mar 26, 2024
Jkt 262001
PO 00000
Part No.
30G4201 or
30G6201.
30G4201 or
30G6201.
30G3902 or
30G5502.
Frm 00010
Fmt 4700
Cyclic limit
3,800 FCs since last AUSI.
3,800 CSN.
3,800 FCs since last AUSI or 7,000 CSN, whichever comes
first.
Sfmt 4700
E:\FR\FM\27MRR1.SGM
27MRR1
Federal Register / Vol. 89, No. 60 / Wednesday, March 27, 2024 / Rules and Regulations
21189
TABLE 2 TO PARAGRAPH (h)(3)—PART REPLACEMENT COMPLIANCE TIMES—Continued
Engine
group
AUSI performed
prior to effective
date of this AD
1 .............
No ..........................
HPT 2nd-stage hub
2 .............
Yes .........................
HPT 1st-stage hub ..
2 .............
No ..........................
HPT 1st-stage hub ..
2 .............
Yes .........................
HPT 2nd-stage hub
2 .............
No ..........................
HPT 2nd-stage hub
Part name
(4) For Group 1 and Group 2 engines with
an affected part listed in Table 3 to paragraph
(h)(4) of this AD, before exceeding the
Part No.
30G3902 or
30G5502.
30G4201 or
30G6201.
30G4201 or
30G6201.
30G3902 or
30G5502.
30G3902 or
30G5502.
Cyclic limit
3,800 CSN.
2,800 FCs since last AUSI.
2,800 CSN.
2,800 FCs since last AUSI or 5,000 CSN, whichever comes
first.
2,800 CSN.
applicable compliance times specified in
Table 3 to paragraph (h)(4) of this AD,
remove the affected part from service and
replace with a part eligible for installation.
khammond on DSKJM1Z7X2PROD with RULES
TABLE 3 TO PARAGRAPH (h)(4)—PART REPLACEMENT COMPLIANCE TIMES
Engine
group
Part name
Part No.
1 and 2 ...
HPC rear hub .........
30G4008 ................
1 .............
HPC rear hub .........
30G8208 ................
1 .............
HPC IBR–7 ............
1 .............
HPC IBR–8 ............
1 .............
HPT 1st-stage hub
30G2307 or
30G4407.
30G5608 or
30G5908 or
30G8908.
30G7301 ................
1 .............
HPT 2nd-stage hub
30G6602 ................
2 .............
HPC rear hub .........
30G8208 ................
2 .............
HPC IBR–7 ............
2 .............
HPC IBR–8 ............
2 .............
HPT 1st-stage hub
30G2307 or
30G4407.
30G5608 or
30G5908 or
30G8908.
30G7301 ................
2 .............
HPT 2nd-stage hub
30G6602 ................
(5) For affected parts that have been
operated in a Group 1 and Group 2
configuration, calculate part replacement and
AUSI times required by paragraphs (h)(2)
through (4) using the note to Table 3 of the
compliance paragraph of PW ASB PW1000G–
C–72–00–0224–00A–930A–D, Issue No: 001
or PW ASB PW1000G–C–72–00–0225–00A–
930A–D, Issue No: 002, as applicable, which
addresses calculating mixed model cycles.
(6) For Group 1 and Group 2 engines with
an installed HPT 1st-stage hub having P/N
30G6201 or an HPT 2nd-stage hub having P/
N 30G5502 and an S/N listed in Tables 1, 2,
3, or 4 of PW SI No. 149F–23 that has not
had an AUSI performed before the effective
date of this AD, before further flight, remove
the affected hub from service.
(7) For Group 1 and Group 2 engines with
an installed HPT 1st-stage hub having P/N
30G7301 or an HPT 2nd-stage hub having P/
N 30G6602 with an S/N listed in Tables 1,
VerDate Sep<11>2014
16:04 Mar 26, 2024
Jkt 262001
Compliance time
At the next HPC shop visit or HPT shop visit, whichever occurs first after the effective
date of this AD.
Before accumulating 7,000 CSN or within 100 FCs after the effective date of this AD,
whichever occurs later.
Before accumulating 7,000 CSN or within 100 FCs after the effective date of this AD,
whichever occurs later.
Before accumulating 7,000 CSN or within 100 FCs after the effective date of this AD,
whichever occurs later.
Before accumulating 7,000
whichever occurs later.
Before accumulating 7,000
whichever occurs later.
Before accumulating 5,000
whichever occurs later.
Before accumulating 5,000
whichever occurs later.
Before accumulating 5,000
whichever occurs later.
CSN or within 100 FCs after the effective date of this AD,
CSN or within 100 FCs after the effective date of this AD,
CSN or within 100 FCs after the effective date of this AD,
CSN or within 100 FCs after the effective date of this AD,
CSN or within 100 FCs after the effective date of this AD,
Before accumulating 5,000 CSN or within 100 FCs after the effective date of this AD,
whichever occurs later.
Before accumulating 5,000 CSN or within 100 FCs after the effective date of this AD,
whichever occurs later.
2, 3, or 4 of PW SI No. 198F–23, dated
November 3, 2023 (PW SI No. 198F–23),
within 100 FC after the effective date of this
AD, perform an AUSI of the affected hub for
cracks in accordance with the
Accomplishment Instructions, paragraph
1.D.(7)(a) or 1.D.(7)(b) of PW ASB PW1000G–
C–72–00–0225–00A–930A–D, Issue No: 002.
(8) For Group 1 and Group 2 engines with
an installed HPT 1st-stage hub having P/N
30G6201 or an HPT 2nd-stage hub having P/
N 30G5502 with an S/N listed in Tables 1,
2, 3, or 4 of PW SI No. 198F–23, within 100
FC after the effective date of this AD, remove
the hub from service and replace with a part
eligible for installation.
(9) If any crack indication is found during
any AUSI required by this AD, before further
flight, remove the affected part from service
and replace with a part eligible for
installation.
PO 00000
Frm 00011
Fmt 4700
Sfmt 4700
(10) 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.
(i) Definitions
(1) For the purposes of this AD, ‘‘Group 1
engines’’ are IAE LLC Model PW1122G–JM,
PW1124G1–JM, PW1124G–JM, PW1127G–
JM, PW1127G1–JM, PW1127G1A–JM,
PW1127G1B–JM, and PW1127GA–JM
engines.
(2) For the purposes of this AD, ‘‘Group 2
engines’’ are IAE LLC Model PW1129G–JM,
PW1130G–JM, PW1133G–JM, PW1133GA–
JM, PW1428G–JM, PW1428GA–JM,
PW1428GH–JM, PW1431G–JM, PW1431GA–
JM, and PW1431GH–JM engines.
(3) For the purposes of this AD, an ‘‘HPC
engine shop visit’’ is the induction of an
E:\FR\FM\27MRR1.SGM
27MRR1
21190
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.
khammond on DSKJM1Z7X2PROD with RULES
(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
VerDate Sep<11>2014
16:04 Mar 26, 2024
Jkt 262001
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
PO 00000
Frm 00012
Fmt 4700
Sfmt 4700
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:
E:\FR\FM\27MRR1.SGM
27MRR1
]]>Agencies
[Federal Register Volume 89, Number 60 (Wednesday, March 27, 2024)]
[Rules and Regulations]
[Pages 21181-21190]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2024-06419]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2023-2401; Project Identifier AD-2023-01278-E;
Amendment 39-22703; AD 2024-05-11]
RIN 2120-AA64
Airworthiness Directives; International Aero Engines, LLC Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2022-19-15
for certain International Aero Engines, LLC (IAE LLC) Model PW1100G
series engines; and AD 2023-16-07 for certain IAE LLC Model PW1100G
series engines and PW1400G series engines. AD 2022-19-15 required an
angled ultrasonic inspection (AUSI) of the high-pressure turbine (HPT)
1st-stage disk and HPT 2nd-stage disk, and replacement, if necessary.
AD 2023-16-07 required an AUSI of the HPT 1st-stage hub (also known as
the HPT 1st-stage disk) and HPT 2nd-stage hub (also known as the HPT
2nd-stage disk) for cracks, and replacement, if necessary, which is
terminating action for AD 2022-19-15. This AD was prompted by an
investigation that determined an increased risk of powdered metal
anomalies for all powdered metal parts in certain powdered metal
production campaigns, which are susceptible to failure significantly
earlier than previously determined. This AD retains the AUSI
requirement for certain HPT 1st-stage and HPT 2nd-stage hubs from AD
2023-16-07. This AD requires performing an AUSI of the HPT 1st-stage
hub, HPT 2nd-stage hub, high-pressure compressor (HPC) 7th-stage
integrally bladed rotor (IBR-7), and HPC 8th-stage integrally bladed
rotor (IBR-8) for cracks, and replacing if necessary. This AD also
requires accelerated replacement of the HPC IBR-7, HPC IBR-8, HPC rear
hub, HPT 1st-stage hub, and HPT 2nd-stage hub. 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.
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of August
28, 2023 (88 FR 56999, August 22, 2023).
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of
November 7, 2022 (87 FR 59660, October 3, 2022; corrected October 24,
2022 (87 FR 64156)).
ADDRESSES:
AD Docket: You may examine the AD docket at regulations.gov under
Docket No. FAA-2023-2401; or in person at Docket Operations between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD
docket contains this final rule, any comments received, and other
information. The address for Docket Operations is U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.
Material Incorporated by Reference:
For Pratt & Whitney (PW) service information that is
incorporated by reference, 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 that is incorporated
by reference at the FAA, Airworthiness Products Section, Operational
Safety Branch, 1200 District Avenue, Burlington, MA 01803. For
information
[[Page 21182]]
on the availability of this material at the FAA, call (817) 222-5110.
It is also available at regulations.gov under Docket No. FAA-2023-2401.
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 (referred to herein
as the NPRM) to amend 14 CFR part 39 to supersede AD 2022-19-15,
Amendment 39-22184 (87 FR 59660, October 3, 2022; corrected October 24,
2022 (87 FR 64156)) (AD 2022-19-15); and AD 2023-16-07, Amendment 39-
22526 (88 FR 56999, August 22, 2023) (AD 2023-16-07). AD 2022-19-15
applied to certain IAE LLC Model PW1122G-JM, PW1124G1-JM, PW1124G-JM,
PW1127G1-JM, PW1127GA-JM, PW1127G-JM, PW1129G-JM, PW1130G-JM, PW1133GA-
JM, and PW1133G-JM engines. AD 2023-16-07 applied to certain IAE LLC
Model PW1122G-JM, PW1124G1-JM, PW1124G-JM, PW1127G-JM, PW1127G1-JM,
PW1127GA-JM, PW1129G-JM, PW1130G-JM, PW1133G-JM, PW1133GA-JM, PW1428G-
JM, PW1428GA-JM, PW1428GH-JM, PW1431G-JM, PW1431GA-JM, and PW1431GH-JM
engines. The NPRM published in the Federal Register on December 28,
2023 (88 FR 89627). The NPRM was prompted by manufacturer analysis of
an HPC IBR-7 failure that determined it was caused by a powdered metal
anomaly that is similar in nature to the anomalies outlined in AD 2022-
19-15. The analysis concluded that there is an increased risk of
failure for additional powdered metal parts in certain powdered metal
production campaigns, including the HPC IBR-7 and HPC IBR-8, and that
all affected parts are susceptible to failure significantly earlier
than previously determined. The condition, if not addressed, could
result in uncontained hub failure, release of high-energy debris,
damage to the engine, damage to the airplane, and loss of the airplane.
To address the unsafe condition, the FAA issued an NPRM (Docket No.
FAA-2023-2237; Project Identifier AD-2023-01057-E) (referred to herein
as the previous NPRM) to supersede AD 2022-19-15 and AD 2023-16-07,
which was published in the Federal Register on December 12, 2023 (88 FR
86088). However, after the previous NPRM was issued, the FAA received
information from PW that an error was inadvertently included in the
previous NPRM's compliance times for some of the HPT 1st-stage and 2nd-
stage hubs, which would have required removal significantly later than
necessary. Due to the need to shorten the removal timeframe, the FAA
determined it was necessary to withdraw the previous NPRM and issue the
NPRM for the unsafe condition with the correct compliance times.
In the NPRM, the FAA proposed to continue to require performing an
AUSI of the HPT 1st-stage hub and HPT 2nd-stage hub and replacing as
necessary. The NPRM proposed to require performing an AUSI of the HPC
IBR-7 and HPC IBR-8 for cracks and replacing as necessary. The NPRM
also proposed to require accelerated replacement of the HPC IBR-7, HPC
IBR-8, HPC rear hub, HPT 1st-stage hub, HPT 1st-stage air seal, HPT
1st-stage blade retaining plate, HPT 2nd-stage hub, HPT 2nd-stage blade
retaining plate, and HPT 2nd-stage rear seal. The FAA is issuing this
AD to address the unsafe condition on these products.
Discussion of Final Airworthiness Directive
Comments
The FAA received comments from 14 commenters, including the Air
Line Pilots Association, International (ALPA); Air New Zealand; All
Nippon Airways CO., LTD. (ANA); Delta Air Lines, Inc. (DAL); Hawaiian
Airlines; Hong Kong Express Airways Limited (HK Express); InterGlobe
Aviation Limited (IndiGo); JetBlue Airways (JetBlue); Lufthansa Group
PW1100G-JM Operators: Lufthansa, SWISS International, Austrian,
Lufthansa Cityline (Lufthansa Group); Lufthansa Technik AG; MTU
Maintenance Hannover GmbH; PW; United Airlines; and Vietnam Airlines
JSC. ALPA urged the manufacturer to develop measures to minimize the
operational impact these inspections will have on operators but
supported the proposed AD without change. Thirteen commenters 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 Service Information
Three commenters, Delta, JetBlue, and Lufthansa Technik AG
requested that the FAA revise paragraphs (h)(2), (h)(6), and (m)(3)(ii)
of the proposed AD to refer to PW ASB PW1000G-C-72-00-0225-00A-930A-D,
Issue 002, dated December 12, 2023, rather than PW ASB PW1000G-C-72-00-
0225-00A-930A-D, Issue 001, dated November 3, 2023. Lufthansa Technik
AG noted that it would be beneficial to use the latest SB revision in
sections (h), (i), and (j) of the proposed AD.
The FAA agrees. PW Alert Service Bulletin (ASB) PW1000G-C-72-00-
0225-00A-930A-D, Issue No: 002, dated December 12, 2023, adds
alternative methods of AUSI compliance to the Compliance section, adds
service information to the References section, and removes unnecessary
steps from the Accomplishment Instructions. The FAA revised this AD to
refer to PW ASB PW1000G-C-72-00-0225-00A-930A-D, Issue No: 002, dated
December 12, 2023. The FAA also revised paragraph (j), Credit for
Previous Actions, of this AD to allow credit for certain actions
performed in accordance with PW ASB PW1000G-C-72-00-0225-00A-930A-D,
Issue No: 001, dated November 3, 2023.
Request To Add Service Information
One commenter, Lufthansa Technik AG, requested the addition of the
following documents to the Related Service Information Under 1 CFR part
51 paragraph of the NPRM:
Special Instruction (SI) 46F-23A, dated April 4, 2023,
which provides instructions to inspect IBR-7 parts;
SI 47F-23A, dated April 4, 2023, which provides
instructions to inspect IBR-8 parts; and
SI 169F-23B, dated October 11, 2023, and previous, which
provides a procedure to inspect all affected hardware in-shop.
Lufthansa Technik AG noted that SI 169F-23B should be added to the
proposed AD to ensure that credit can be taken from last accomplishment
of this SI.
The FAA disagrees. The Related Service Information Under 1 CFR part
51 paragraph contains service information that is incorporated by
reference in this AD, and the above-referenced service information is
not incorporated by reference. The FAA did not change this final rule
as a result of this comment.
Request To Allow Future Revisions of Service Information
Three commenters, ANA, Hawaiian Airlines, and HK Express Airways
requested the FAA add ``or later'' to SI No. 222F-23 in the AD or to
consider not requiring a specific SI No. 222F-23 revision. The
commenters noted that this SI will be revised periodically and
suggested that the later revisions should also be exempt from the
proposed AD. One commenter, ANA, also requested that the FAA add the
phrase ``or later
[[Page 21183]]
revision'' to each service information (Service Bulletin and PW Special
Instruction) stated in paragraph (m) of the proposed AD.
The FAA disagrees with adding ``or later'' or ``or later revision''
for service information incorporated by reference in this AD. Future
revisions of the service information have not yet been published by the
manufacturer or reviewed by the FAA, and therefore cannot be approved
as required service information. A request for an alternative method of
compliance (AMOC) can be submitted to the FAA in accordance with the
requirements of paragraph (k) of this AD if future revisions of the
service information referenced in this AD are published. Additionally,
if future revisions of the service information are published by the
manufacturer and approved by the FAA, the FAA may consider further
rulemaking. The FAA did not change this AD as a result of these
comments.
Request To Exclude Unaffected Parts
Eleven commenters, ANA, DAL, Hawaiian Airlines, HK Express Airways,
IndiGo, JetBlue, Lufthansa Group, Lufthansa Technik AG, MTU Maintenance
Hannover GmbH, PW, and United Airlines, recommended the FAA exempt the
HPC IBR-7, HPC IBR-8, HPC Rear Hub, HPT 1st stage hub, and HPT 2nd
stage hub serial numbers listed in Tables 1, 2, and 3 of PW SI No.
222F-23 from the requirements set forth in the proposed AD. PW
explained that SI No. 222F-23 identifies specific part numbers and
serial numbers that were manufactured outside the affected population
of material manufactured from powdered metal addressed by the proposed
AD. PW requested modifying the ``Applicability'' section of the
proposed AD to exclude parts which are not in the affected population.
The FAA agrees. The FAA will revise paragraph (c), Applicability,
of this AD to reference Tables 1, 2, and 3 of PW SI No. 222F-23,
Revision A, dated February 13, 2024, which specifies part numbers and
serial numbers verified as manufactured from powdered metal campaigns
produced prior to November 1, 2015, or after September 1, 2021, and
which are therefore outside the population of material manufactured
from powdered metal addressed by this AD. This change in the
applicability reduces the affected part numbers and serial numbers.
Request Clarification on IBR-8 Part Numbers
Lufthansa Technik AG commented that two IBR-8 P/Ns, 30G3808 and
30G6308, are listed in the Illustrated Parts Catalog and in the
airworthiness limitations, but not in the proposed AD. The commenter
asked for clarification that these part numbers do not require AUSI and
have no additional part replacement but are not allowed for
reinstallation in accordance with paragraph (i)(5) of the proposed AD.
The commenter suggested this could be due to low life-limited part
life.
For clarity, the FAA did not address HPC IBR-8 having P/N 30G3808
and 30G6308 in this AD because the FAA has determined that those parts
are either retired, out of service, or have airworthiness limitations
that are more restrictive than the requirements of this AD. The FAA did
not change this AD as a result of this comment.
Request To Modify Paragraph (g) of the Proposed AD To Include Certain
Part Numbers
Lufthansa Technik AG requested that the FAA review the inclusion of
all four affected HPT Stg 1 and Stg 2 part numbers in paragraphs (g)(1)
and (2) of the proposed AD for completeness of retaining the
requirements of AD 2023-16-07 with no change.
The FAA disagrees. Paragraph (g), Retained Inspections from AD
2023-16-07, With No Changes, of this AD applies to certain part and
serial numbers as specified. The FAA did not change this AD as a result
of this comment.
Request To Modify the Compliance Language in Paragraph (g) of the
Proposed AD
One commenter, ANA, requested to change the required action
specified in paragraph (g) of the proposed AD from ``perform an AUSI of
the affected parts within 30 days,'' to ``remove the affected engine
from service within 30 days, and thereafter perform an AUSI of the
affected part before release to service.''
The FAA disagrees. The commenter provided no justification for the
request, and the FAA has determined that this AD as written
accomplishes the same result requested by the commenter. The FAA did
not change this AD as a result of this comment.
Request To Remove References to Certain Parts
Two commenters, Air New Zealand and PW, observed that Table 3 of
the proposed AD includes a reference to components that are not
affected by the powdered metal issue and are not referenced in PW SB
PW1000G-C-72-00-0224 and PW1000G-C-72-00-0225. Air New Zealand
suggested that including these in the proposed AD would create
confusion and unnecessary complexity when processing and showing
compliance. PW noted that the proposed AD would not require accelerated
replacement of HPT 1st-stage front air seal, HPT 2nd-stage rear air
seal, HPT 1st-stage blade retaining plate, and HPT 2nd-stage blade
retaining plate, and further noted that these parts would be
automatically replaced with incorporation of the Block D 1st and 2nd
stage turbine disks. Air New Zealand requested the removal of the
references to the HPT 1&2 air seals and the HPT Stage 1 & 2 retaining
plates.
The FAA agrees. The FAA will remove the references to HPT 1st-stage
front air seal, HPT 2nd-stage rear air seal, HPT 1st-stage blade
retaining plate, and HPT 2nd-stage blade retaining plate from this AD.
Request To Include Calculation for Mixed Model Management
Three commenters, ANA, Lufthansa Group, and Lufthansa Technik AG,
observed that a mixed model management calculation as defined in PW ASB
PW1000G-C-72-00-0224-00A-930A-D and PW ASB PW1000G-C-72-00-0225-00A-
930A-D is not mentioned in the proposed AD. Lufthansa Technik AG
suggested that this calculation is also referenced in SIL 17. Lufthansa
Group noted that, without a stated reference to the mixed model
management calculation, it is possible that engines operated at any
time at the higher thrust rating must be treated as such. The
commenters requested that the FAA state in the proposed AD that mixed
model management calculation can be applied to address parts that have
operated in both Group 1 and Group 2 engines.
The FAA agrees. The FAA will revise paragraph (h), New Required
Actions, of this AD to address the calculation of cyclic limits for
part replacement and AUSI compliance times for parts that have been
installed in a Group 1 and Group 2 configuration as defined in the note
to Table 3 of the compliance paragraph of PW ASB PW1000G-C-72-00-0224-
00A-930A-D, Issue No: 001 and PW1000G-C-72-00-0225-00A-930A-D, Issue
No: 002. The FAA has not reviewed SIL 17 and will not reference this
service information in this AD.
Request To Add a Cyclic Limit to Paragraph (h)(1) of the Proposed AD
One commenter, Lufthansa Technik AG, requested the FAA add a cyclic
limit to paragraph (h)(1) of the proposed AD. The commenter noted that
all affected hardware is covered by the 100-flight cycle (FC) timeframe
in paragraph (h)(9) of the proposed AD. The
[[Page 21184]]
commenter suggested that, since there are other unrelated issues in the
HPC, and as there is no cyclic limitation planned for the AUSI of the
HPC parts, the FAA exclude the requirement to perform an AUSI in
accordance with paragraph (h)(1) of the proposed AD below 500 FCs since
the last AUSI or since new, unless the HPC rotor is disassembled. The
commenter explained that this would remove the need to inspect parts
that were recently installed but removed for access.
The FAA disagrees. The FAA cannot account for all circumstances
that would require an engine shop visit. Unusual engine shop visit
circumstances may be considered through the provisions of paragraph
(k), Alternative Methods of Compliance, of this AD. The FAA did not
change this AD as a result of this comment.
Request To Clarify Discrepancy in Compliance Times Between the Proposed
AD and the PW ASB
Two commenters, DAL and IndiGo, noted a discrepancy between the
compliance times in the proposed AD and those in the PW ASBs. IndiGo
requested that the FAA clarify if the compliance timeline in the
proposed AD supersedes the compliance timeline in the PW ASBs, and if
the operators can wait for the proposed AD to be issued and follow the
effective date stated in the proposed AD. DAL requested that the FAA
add a paragraph or revise paragraph (h)(2) to address the 100-FC
drawdown periods in the proposed AD and the discrepancy between the
compliance times of the AD and the PW ASBs.
The FAA disagrees with adding a paragraph. Operators are required
to comply within the compliance times specified in this AD. However,
how an operator reacts to recommended actions from the design approval
holder (DAH) should be spelled out in their approved maintenance
program and is not governed by this AD. The FAA did not change this AD
as a result of this comment.
Request To Adjust Compliance Time To Account for Cycle Count
One commenter, Vietnam Airlines, observed that the drawdown cycles
for mandated actions (such as part replacement or inspection) shall be
contingent upon the cycle count surpassing the compliance threshold
outlined in Table 1 to Paragraph (h)(2) and Table 2 to Paragraph (h)(3)
of the proposed AD. The commenter suggested that there should be
distinctions in treatment between an engine exceeding the threshold by
1,000 cycles and one exceeding the threshold by 200 cycles. Should the
former exhibit a drawdown period of 100 cycles, the commenter
recommended that the latter be allocated a longer period for
compliance.
The FAA disagrees. The FAA determined that a tiered drawdown is not
necessary because all parts exceeding the compliance time or cycle
limit stated in Table 1 to paragraph (h)(2) and Table 2 to paragraph
(h)(3) of this AD must be removed within 100 FCs after the effective
date of this AD. The FAA did not change this AD as a result of this
comment.
Request To Include Life Reduction for Certain HPC Rear Hub
One commenter, ANA, noted that the compliance times for HPC rear
hub having P/N 30G4008 are specified in ASB PW1000G-C-72-00-0224-00A-
930A-D, but they are not included in Table 3 of the proposed AD.
Therefore, the commenter observed, an engine may be used beyond the
compliance times specified in ASB PW1000G-C-72-00-0224-00A-930A-D. ANA
requested that the proposed AD be revised to include the compliance
times for P/N 30G4008 specified in ASB PW1000G-C-72-00-0224-00A-930A-D.
The FAA disagrees. This AD requires the removal of HPC rear hub
having P/N 30G4008 at either the next HPC engine shop visit or the next
HPT engine shop visit, whichever occurs first. The FAA determined that
it is not necessary to specify a compliance time for HPC rear hub
having P/N 30G4008 due to the cycle limits for the associated HPC and
HPT parts. The FAA did not change this AD as a result of this comment.
Request To Change ``Crack'' to ``Defect'' in Paragraph (h)(8) of the
Proposed AD
One commenter, Lufthansa Technik AG, observed that paragraph (h)(8)
of the proposed AD requires to remove only parts found with a crack.
The commenter stated that due to AUSI procedure, it cannot be
determined if it is a crack or just an anomaly. Therefore, the
commenter requested that the FAA change the wording so that all parts
with defects will be removed from service.
The FAA partially agrees. The FAA does not agree with the wording
proposed by the commenter. The FAA agrees to meet the commenter's
intent by changing the wording of paragraph (h)(9) of this AD from ``if
any crack is found,'' to ``if any crack indication is found.''
Request To Include Reference to New Parts
One commenter, Lufthansa Technik AG, requested that the FAA change
paragraph (h)(9) of the proposed AD to read ``[. . .] 100 FCs or less
since the last AUSI OR NEW, (re-)inspection [. . .].'' The commenter
explained that this would allow also counting from reinstallation of
new hardware (where it cannot be determined if the AUSI was performed
during production at OEM).
The FAA disagrees. Paragraph (h)(10) of this AD applies to
repetitive inspections of affected parts installed within the last 100
FCs. Parts that are not included in paragraph (c), Applicability, of
this AD are not subject to the repetitive AUSI requirement. The FAA did
not change this AD as a result of this comment.
Request To Revise Heading of Table 1 to Paragraph (h)(2) of the
Proposed AD
One commenter, Lufthansa Technik AG, noted that it would avoid
confusion to reference HPT hub stage 1 and 2 only in the heading of
Table 1 to (h)(2). The commenter requested that the FAA include the
part names in the header of the table.
The FAA disagrees. The FAA has determined that including the part
names in the header is not necessary because paragraph (h)(2) specifies
the parts and part numbers subject to the compliance time specified in
Table 1 to Paragraph (h)(2) of this AD. The FAA did not change this AD
as a result of this comment.
Request To Reference AUSI Performed in Service in Table 1 to (h)(2) of
the Proposed AD
One commenter, Lufthansa Technik AG, suggested that the new
production parts inspection regime was updated and that Table 1 to
(h)(2) of the proposed AD is not covering this AUSI inspection at
production. The commenter requested that the second column of Table 1
to (h)(2) of the proposed AD be revised to state that this reflects
only ``AUSI performed in service prior to the effective date of this
AD.''
The FAA disagrees. However, the FAA has updated paragraph (c),
Applicability, of this AD to exempt serial numbers listed in Tables 1,
2, and 3 of SI 222F-23, Revision A, which includes parts subject to
AUSI at production.
Request To Add Airworthiness Limitation to Table 2 to Paragraph (h)(3)
of the Proposed AD
One commenter, Lufthansa Technik AG, noted that in Table 2 to
paragraph
[[Page 21185]]
(h)(3) of the proposed AD, for Group 1 engines, the 1st-Stage Hub P/N
30G4201 or 30G6201 with AUSI performed refers to 3,800 FCs since the
last AUSI. The commenter also noted that for Group 2 engines, the 1st-
Stage Hub P/N 30G4201 or 30G6201 with AUSI performed refers to 2,800
FCs since the last AUSI. The commenter observed that the part needs
removal within the airworthiness limitation. The commenter requested
that the FAA add a statement similar to the 2nd-stage hubs.
The FAA disagrees. The FAA has determined that adding such a
statement is unnecessary because the existing airworthiness limitations
are more restrictive. The FAA did not change this AD as a result of
this comment.
Request To Make Changes to Tables
Three commenters, HK Express Airways, JetBlue, and Lufthansa
Technik AG, expressed that the lack of borderlines in Table 2 for
paragraph (h)(3) and Table 3 for paragraph (h)(4) of the proposed AD is
confusing. Lufthansa Technik AG notes that on the first look, it seems
that the compliance time for part removal at next HPT shop visit is
applicable to one row only, but in fact should be applicable for all
parts listed below. The commenters requested that the FAA complete the
engine group and compliance time boxes for each line item listed in
Table 2 and Table 3 of the proposed AD.
The FAA agrees. The FAA has revised Table 2 to paragraph (h)(3) and
Table 3 to paragraph (h)(4) of this AD to complete the engine group and
compliance time columns for each line item.
Request To Provide Additional Cycles for Alternate Climb Operations
One commenter, JetBlue, stated that JetBlue has been operating with
the Alternate Climb modification on the fleet. The commenter explained
that the Alternate Climb modification is performed pre-delivery and
decreases work/stress on the engine during the entire climb duration,
which effectively alleviates stress/fatigue. The commenter requested
that the FAA analyze the data to check the feasibility of providing
additional cycles for the Alternate Climb modification to meet the
proposed AD timelines.
The FAA disagrees. Operators can submit a request for an AMOC to
the FAA in accordance with the requirements of paragraph (k) of this AD
with the data that shows the modification provides an acceptable level
of safety. The FAA did not change this AD in response to this comment.
Request To Modify Definition for Part Eligible for Installation
One commenter, HK Express Airways, noted that PW SI 222F-23
identifies parts exempted from repetitive AUSI and early retirement
carrying the same part number, and the commenter observed that the
proposed AD did not mention this SI in paragraph (i). HK Express
Airways requested adding reference to SI 222F-23 to the definition of
``part eligible for installation,'' so the parts listed in the SI are
deemed to be eligible for installation. The commenter also noted that
SI 222F-23 will be updated quarterly by PW, therefore the AD should not
fix the SI version.
The FAA agrees to revise the definition of ``part eligible for
installation'' in paragraph (i) of this AD to reference part serial
numbers identified in Tables 1, 2, and 3 of SI 222F-23, Revision A. The
FAA does not agree to include an undated reference to SI 222F-23.
Future revisions of service information have not yet been published by
the manufacturer or reviewed by the FAA, and therefore cannot be
approved as required service information. A request for an AMOC can be
submitted to the FAA in accordance with paragraph (k) of this AD if
future revisions of the service information referenced in this AD are
published. Additionally, if future revisions of the service information
are published by the manufacturer and approved by the FAA, the FAA may
consider further rulemaking.
Request To Clarify if Newly Produced Parts Are Eligible for
Installation
Three commenters, DAL, HK Express Airways, and Lufthansa Technik
AG, observed that the proposed AD did not address newly produced parts
carrying the same part number in the definition of ``part eligible for
installation'' in paragraph (i)(5) of the proposed AD. Therefore, the
commenters reasoned, the proposed AD does not define installation
eligibility for any new/not service run HPC/HPT hardware that is not
currently installed on a Group 1 or Group 2 engine. The commenters
requested that paragraph (i)(5) of the proposed AD be revised to add
installation eligibility for new production parts.
The FAA agrees. If the newly produced parts are manufactured from
powdered metal material produced prior to November 1, 2015, or after
September 1, 2021, as identified in the original manufacturing records
or in Tables 1, 2, and 3 of SI No. 222F-23, Revision A, those parts are
not affected by this AD. The FAA revised the definition of ``part
eligible for installation'' in paragraph (i)(5) of this AD to reference
parts identified as not affected by this AD in paragraph (c)(2) of this
AD. Therefore, parts identified in Tables 1, 2, and 3 of SI No. 222F-
23, Revision A, will meet the definition of ``part eligible for
installation.'' To meet the updated definition of ``part eligible for
installation,'' affected parts need to be inspected in accordance with
this AD. Unaffected parts can be installed without performing the
requirements of this AD.
Request To Clarify Meaning of Induction as Used in Paragraph (i),
Definitions, of the Proposed AD
One commenter, ANA, asked the FAA to clarify that the definition of
``induction'' in paragraph (i) of the proposed AD is the timing when
the engine disassembly is started. ANA asked the FAA to clarify a
particular situation to have a correct understanding. ANA noted that,
in terms of paragraph (h)(1) and (2) of the proposed AD, if an engine
is already in shop for maintenance involving the separation H-flange or
M-flange, then assembly has already been started at the effective date
of this AD. The commenter asked if an angled ultrasonic scan inspection
should therefore not be performed in this shop visit.
The FAA agrees to clarify. The FAA does not have a set definition
for induction. Reference your approved maintenance program to determine
what ADs apply to your engines during an engine shop visit. In the
example provided, if the engine were already at an engine shop visit on
the effective date of this AD, the requirements of paragraphs (h)(1)
and (2) would apply at the next engine shop visit after the effective
date of this AD. The FAA did not change this AD in response to this
comment.
Request To Include 2nd-Stage HPT Retaining Plates in Paragraph (i),
Definitions, of the Proposed AD
One commenter, Lufthansa Technik AG, requested that the FAA include
2nd-stage HPT retaining plates in the definition of parts eligible for
installation.
The FAA disagrees. The FAA revised this final rule to remove
references to HPT retaining plates in response to another comment. The
FAA did not change this AD in response to this comment.
[[Page 21186]]
Request To Identify Previous AUSI Service Information in Paragraph (j),
Credit for Previous Actions, of the Proposed AD
One commenter, Lufthansa Technik AG, observed that, in addition to
the credit for paragraphs (g)(1) and (2) of the proposed AD, it should
be required to note down which procedures qualify as ``AUSI performed''
for cyclic requirements under paragraphs (h)(2) with table 1 and (h)(8)
of the proposed AD to correctly determine the remaining life and if the
AUSI was performed prior to AD e[fflig]ectivity. The commenter listed
the following service information: For HPT hubs in accordance with
(h)(2) and (8) of the proposed AD:
SI 169F-23;
SB PW1000G-C-72-00-0188-00A-930A-D, Issue 1 dated
September 13, 2021; and
PW1000G-C-72-00-0188-00A-930A-D, Issue 2 dated July 8,
2022.
For HPC parts in accordance with paragraph (h)(8) of the proposed
AD:
SI 46F-23; and
SI 47F-23.
The FAA infers that the commenter requested that the FAA add the
service information identified to paragraph (j), Credit for Previous
Actions, of this AD. The FAA disagrees. PW SB PW1000G-C-72-00-0188-00A-
930A-D, Issue No: 001, dated September 13, 2021, is referenced in
paragraph (j), Credit for Previous Actions, of this AD. The FAA revised
paragraph (j), Credit for Previous Actions, of this AD to include PW
ASB PW1000G-C-72-00-0225-00A-930A-D, Issue No. 001, dated November 3,
2023, which provides methods for AUSI that may have been previously
used, in response to a separate comment. The FAA did not change this AD
in response to this comment.
Request To Add Special Flights Permit Paragraph
One commenter, HK Express Airways, noted that according to PW, non-
revenue maintenance or check flights are permitted if the aircraft is
required to re-locate to base maintenance facilities for storage or
engine removal after the compliance time. The commenter requested that
the FAA add a paragraph to the proposed AD to clearly state that non-
revenue maintenance flights are permitted within the proposed AD.
The FAA disagrees because 14 CFR 39.23 allows for special flight
permits unless specified as limited or prohibited in the AD. The FAA
did not change this AD in response to this comment.
Additional Change Made to the Applicability
Since the NPRM published, the FAA determined the need to add IAE
LLC Models PW1127G1A-JM and PW1127G1B-JM to paragraph (c),
Applicability, in this AD. These engine models were recently
certificated but are not in production yet. The FAA revised the
applicability of this AD to include these additional engine models.
None of the engines added to the applicability of this AD are on the
U.S. Register. Additional notice and opportunity for public comment
before issuing this AD are therefore unnecessary. Since there are no
additional engines on the U.S. registry, no changes have been made to
the Costs of Compliance paragraph in this final rule.
Updated Service Information for Paragraph (c)(2) of the Applicability
Since the NPRM comment period closed, PW updated SI 222F-23,
Revision A, to add additional part numbers and serial numbers verified
as manufactured from powdered metal campaigns produced prior to
November 1, 2015, or after September 1, 2021, and which are therefore
outside the population of material manufactured from powdered metal
addressed by this AD. For this reason, the FAA updated paragraph (c)(2)
of the Applicability to reference Tables 1, 2, and 3 of PW SI No. 222F-
23, Revision B, dated March 1, 2024. This change to the applicability
of this AD reduces the affected part numbers and serial numbers.
Conclusion
The FAA reviewed the relevant data, considered any comments
received, and determined that air safety requires adopting the 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-C-72-00-0224-00A-930A-D, Issue No: 001,
dated November 3, 2023, which specifies procedures for performing an
AUSI for cracks on affected HPC IBR-7 and HPC IBR-8;
PW ASB PW1000G-C-72-00-0225-00A-930A-D, Issue No: 002,
dated December 12, 2023, which specifies procedures for performing an
AUSI for cracks on affected HPT 1st-stage hubs and HPT 2nd-stage hubs;
PW SI No. 198F-23, dated November 3, 2023, which specifies
the list of affected HPT 1st-stage hubs and HPT 2nd-stage hubs,
identified by part number and serial number, installed on certain IAE
LLC engines;
PW SI No. 222F-23, Revision B, dated March 1, 2024, which
specifies the list of part numbers and serial numbers that were
manufactured outside of the affected population of material
manufactured from powdered metal;
PW Service Bulletin PW1000G-C-72-00-0188-00A-930A-D, Issue
No: 002, dated July 8, 2022, which was previously approved for
incorporation by reference on November 7, 2022 (87 FR 59660, October 3,
2022; corrected October 24, 2022 (87 FR 64156)). This service
information specifies procedures for performing an AUSI for cracks on
affected HPT 1st-stage hubs and HPT 2nd-stage hubs; and
PW SI No. 149F-23, dated August 4, 2023, which was
previously approved for incorporation by reference on August 28, 2023
(88 FR 56999, August 22, 2023). This service information specifies the
list of affected HPT 1st-stage hubs and HPT 2nd-stage hubs, identified
by part number and serial number, installed on certain IAE LLC engines.
This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.
Interim Action
The FAA considers this AD to be an interim action. The unsafe
condition is still under investigation by the manufacturer and,
depending on the results of that investigation, the FAA may consider
further rulemaking action.
Justification for Determination of the Effective Date
Section 553(d) of the Administrative Procedure Act (APA) (5 U.S.C.
551 et seq.) authorizes agencies to make rules effective in less than
thirty days, upon a finding of ``good cause.'' The FAA has found that
the risk to the flying public justifies a shortened effective date for
this rule due to powdered metal anomalies in HPT 1st-stage hub, HPT
2nd-stage hub, HPC IBR-7, 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
[[Page 21187]]
certain parts is within 100 flight cycles after the effective date of
this AD, which is on average one calendar month of operation. The
longer these parts remain in service, the higher the probability of
failure. Additionally, the FAA did not receive any adverse comments or
useful information about this AD from U.S. operators that necessitates
waiting 30 days for this AD to become effective. 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 430 engines installed on
airplanes of U.S. registry. The FAA estimates that 366 engines will
need replacement of the HPT 1st-stage hub; 351 engines will need
replacement of the HPT 2nd-stage hub; 408 engines will need replacement
of the HPC IBR-7; 368 engines will need replacement of the HPC IBR-8;
and 283 engines will need replacement of the HPC rear hub.
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
----------------------------------------------------------------------------------------------------------------
AUSI of HPT 1st-stage hub, HPT 2nd- 80 work-hours x$85 per $0 $6,800 $2,924,000
stage hub, HPC IBR-7, and HPC IBR-8 hour = $6,800.
for cracks.
Replace HPT 1st-stage hub.............. 10 work-hours x$85 per 56,000 56,850 20,807,100
hour = $850.
Replace HPT 2nd-stage hub.............. 10 work-hours x$85 per 62,000 62,850 $22,060,350
hour = $850.
Replace HPC IBR-7...................... 10 work-hours x$85 per 82,000 82,850 33,802,800
hour = $850.
Replace HPC IBR-8...................... 10 work-hours x$85 per 93,000 93,850 34,536,800
hour = $850.
Replace HPC rear hub................... 10 work-hours x$85 per 132,000 132,850 37,596,550
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
The FAA has determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) 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:
0
a. Removing Airworthiness Directive 2022-19-15, Amendment 39-22184 (87
FR 59660, October 3, 2022; corrected October 24, 2022 (87 FR 64156));
and Airworthiness Directive 2023-16-07, Amendment 39-22526 (88 FR
56999, August 22, 2023); and
0
b. Adding the following new airworthiness directive:
2024-05-11 International Aero Engines, LLC: Amendment 39-22703;
Docket No. FAA-2023-2401; Project Identifier AD-2023-01278-E.
(a) Effective Date
This airworthiness directive (AD) is effective April 11, 2024.
(b) Affected ADs
(1) This AD replaces AD 2022-19-15, Amendment 39-22184 (87 FR
59660, October 3, 2022; corrected October 24, 2022 (87 FR 64156)).
(2) This AD replaces AD 2023-16-07, Amendment 39-22526 (88 FR
56999, August 22, 2023) (AD 2023-16-07).
(c) Applicability
(1) This AD applies to International Aero Engines, LLC (IAE LLC)
Model PW1122G-JM, PW1124G1-JM, PW1124G-JM, PW1127G-JM, PW1127G1-JM,
PW1127G1A-JM, PW1127G1B-JM, PW1127GA-JM, PW1129G-JM, PW1130G-JM,
PW1133G-JM, PW1133GA-JM, PW1428G-JM, PW1428GA-JM, PW1428GH-JM,
PW1431G-JM, PW1431GA-JM, and PW1431GH-JM engines with an installed:
(i) High-pressure compressor (HPC) 7th-stage integrally bladed
rotor (IBR-7) having part number (P/N) 30G2307 or 30G4407;
(ii) HPC 8th-stage integrally bladed rotor (IBR-8) having P/N
30G5608, 30G5908, or 30G8908;
(iii) HPC rear hub having P/N 30G4008 or 30G8208;
(iv) High-pressure turbine (HPT) 1st-stage hub having P/N
30G4201, 30G6201, or 30G7301; or
(v) HPT 2nd-stage hub having P/N 30G3902, 30G5502, or 30G6602.
(2) This AD does not apply to parts identified in paragraphs
(c)(1)(i) through (v) of this AD if those parts were manufactured
from powdered metal material produced prior to November 1, 2015, or
after September 1, 2021, as identified by part serial number in
Tables 1, 2, and 3 of PW Special Instruction (SI) No. 222F-23,
Revision B, dated March 1, 2024 (PW SI No. 222F-23, Revision B) or
in the original manufacturing records for the part.
[[Page 21188]]
(3) If the original manufacturing records do not identify the
production date of the powdered metal used to make the parts
identified in paragraphs (c)(1)(i) through (v) of this AD, and the
part serial number is not listed in Tables 1, 2, and 3 of PW SI No.
222F-23, Revision B, then the part is subject to the requirements of
this AD.
(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 analysis of an event involving an IAE
LLC Model PW1127GA-JM engine, which experienced failure of an HPC
IBR-7 that resulted in an engine shutdown and aborted takeoff. The
FAA is issuing this AD to prevent failure of the HPT 1st-stage hub,
HPT 2nd-stage hub, HPC IBR-7, and HPC IBR-8. The unsafe condition,
if not addressed, could result in uncontained hub failure, release
of high-energy debris, damage to the engine, damage to the airplane,
and loss of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Inspections From AD 2023-16-07, With No Changes
(1) This paragraph restates the requirements of paragraph (g)(1)
of AD 2023-16-07. For Group 1 and Group 2 engines with an installed
HPT 1st-stage hub having part number (P/N) 30G7301 and a serial
number (S/N) listed in Tables 1, 2, 3, or 4 of PW Special
Instruction (SI) No. 149F-23, dated August 4, 2023 (PW SI No. 149F-
23), within 30 days after August 28, 2023 (the effective date of AD
2023-16-07), perform an AUSI of the HPT 1st-stage hubs for cracks in
accordance with the Accomplishment Instructions, paragraph 9.A. or
9.B., as applicable, of Pratt & Whitney (PW) Service Bulletin
PW1000G-C-72-00-0188-00A-930A-D, Issue No: 002, dated July 8, 2022
(PW1000G-C-72-00-0188-00A-930A-D, Issue No: 002).
(2) This paragraph restates the requirements of paragraph (g)(2)
of AD 2023-16-07. For Group 1 and Group 2 engines with an installed
HPT 2nd-stage hub having P/N 30G6602 and an S/N listed in Tables 1,
2, 3, or 4 of PW SI No. 149F-23, within 30 days after August 28,
2023 (the effective date of AD 2023-16-07), perform an AUSI of the
HPT 2nd-stage hubs for cracks in accordance with the Accomplishment
Instructions, paragraph 9.C. or 9.D., as applicable, of PW1000G-C-
72-00-0188-00A-930A-D, Issue No: 002.
(h) New Required Actions
(1) For Group 1 and Group 2 engines with an affected HPC IBR-7
having P/N 30G2307 or 30G4407, or an affected HPC IBR-8 having P/N
30G5608, 30G5908, or 30G8908, at the next HPC engine shop visit and
thereafter at every HPC engine shop visit, perform an angled
ultrasonic scan inspection (AUSI) of the affected HPC IBR-7 or HPC
IBR-8, as applicable, for cracks in accordance with the
Accomplishment Instructions, paragraph 4.E.(1) or 4.E.(2), of PW
Alert Service Bulletin (ASB) PW1000G-C-72-00-0224-00A-930A-D, Issue
No: 001, dated November 3, 2023 (PW ASB PW1000G-C-72-00-0224-00A-
930A-D, Issue No: 001).
(2) For Group 1 and Group 2 engines with an affected HPT 1st-
stage hub having P/N 30G7301 or an HPT 2nd-stage hub having P/N
30G6602, before exceeding the applicable compliance time in Table 1
to paragraph (h)(2) of this AD, except as required by paragraphs
(g)(1) and (2) and paragraph (h)(7) 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 1.D.(7)(a) or 1.D.(7)(b) of PW ASB PW1000G-C-72-00-0225-
00A-930A-D, Issue No: 002, dated December 12, 2023 (PW ASB PW1000G-
C-72-00-0225-00A-930A-D, Issue No: 002). Thereafter, repeat the AUSI
at the applicable interval in Table 1 to paragraph (h)(2) of this
AD.
Table 1 to Paragraph (h)(2)--AUSI Compliance Times
------------------------------------------------------------------------
AUSI performed prior to
Engine group effective date of this Compliance time Repetitive
AD interval
------------------------------------------------------------------------
1........... No...................... Before Thereafter at
accumulating each HPT
3,800 cycles engine shop
since new visit or
(CSN) or before
within 100 exceeding
flight cycles 3,800 FCs from
(FCs) after the last AUSI
the effective of the
date of this affected hub,
AD, whichever whichever
occurs later. occurs first.
1........... Yes..................... At the next HPT Thereafter at
engine shop each HPT
visit, not to engine shop
exceed 3,800 visit or
FCs since the before
previous AUSI, exceeding
or within 100 3,800 FCs from
FCs after the the last AUSI
effective date of the
of this AD, affected hub,
whichever whichever
occurs later. occurs first.
2........... No...................... Before Thereafter at
accumulating each HPT
2,800 CSN or engine shop
within 100 FCs visit or
after the before
effective date exceeding
of this AD, 2,800 FCs from
whichever the last
occurs later. angled AUSI of
the affected
hub, whichever
occurs first.
2........... Yes..................... At the next HPT Thereafter at
engine shop each HPT
visit, not to engine shop
exceed 2,800 visit or
FCs since the before
previous AUSI, exceeding
or within 100 2,800 FCs from
FCs after the the last AUSI
effective date of the
of this AD, affected hub,
whichever whichever
occurs later. occurs first.
------------------------------------------------------------------------
(3) For Group 1 and Group 2 engines with an affected part listed
in Table 2 to paragraph (h)(3) of this AD, at the next HPT engine
shop visit not to exceed the applicable cyclic limit specified in
Table 2 to paragraph (h)(3) of this AD, or 100 FCs after the
effective date of the AD, whichever occurs later, except as required
by paragraphs (h)(6) and (8) of this AD, remove the affected part
from service and replace with a part eligible for installation.
Table 2 to Paragraph (h)(3)--Part Replacement Compliance Times
----------------------------------------------------------------------------------------------------------------
AUSI performed prior to
Engine group effective date of this AD Part name Part No. Cyclic limit
----------------------------------------------------------------------------------------------------------------
1................ Yes.......................... HPT 1st-stage hub... 30G4201 or 30G6201. 3,800 FCs since
last AUSI.
1................ No........................... HPT 1st-stage hub... 30G4201 or 30G6201. 3,800 CSN.
1................ Yes.......................... HPT 2nd-stage hub... 30G3902 or 30G5502. 3,800 FCs since
last AUSI or 7,000
CSN, whichever
comes first.
[[Page 21189]]
1................ No........................... HPT 2nd-stage hub... 30G3902 or 30G5502. 3,800 CSN.
2................ Yes.......................... HPT 1st-stage hub... 30G4201 or 30G6201. 2,800 FCs since
last AUSI.
2................ No........................... HPT 1st-stage hub... 30G4201 or 30G6201. 2,800 CSN.
2................ Yes.......................... HPT 2nd-stage hub... 30G3902 or 30G5502. 2,800 FCs since
last AUSI or 5,000
CSN, whichever
comes first.
2................ No........................... HPT 2nd-stage hub... 30G3902 or 30G5502. 2,800 CSN.
----------------------------------------------------------------------------------------------------------------
(4) For Group 1 and Group 2 engines with an affected part listed
in Table 3 to paragraph (h)(4) of this AD, before exceeding the
applicable compliance times specified in Table 3 to paragraph (h)(4)
of this AD, remove the affected part from service and replace with a
part eligible for installation.
Table 3 to Paragraph (h)(4)--Part Replacement Compliance Times
----------------------------------------------------------------------------------------------------------------
Engine group Part name Part No. Compliance time
----------------------------------------------------------------------------------------------------------------
1 and 2............. HPC rear hub.................... 30G4008......................... At the next HPC shop
visit or HPT shop
visit, whichever
occurs first after
the effective date of
this AD.
1................... HPC rear hub.................... 30G8208......................... Before accumulating
7,000 CSN or within
100 FCs after the
effective date of
this AD, whichever
occurs later.
1................... HPC IBR-7....................... 30G2307 or 30G4407.............. Before accumulating
7,000 CSN or within
100 FCs after the
effective date of
this AD, whichever
occurs later.
1................... HPC IBR-8....................... 30G5608 or 30G5908 or 30G8908... Before accumulating
7,000 CSN or within
100 FCs after the
effective date of
this AD, whichever
occurs later.
1................... HPT 1st-stage hub............... 30G7301......................... Before accumulating
7,000 CSN or within
100 FCs after the
effective date of
this AD, whichever
occurs later.
1................... HPT 2nd-stage hub............... 30G6602......................... Before accumulating
7,000 CSN or within
100 FCs after the
effective date of
this AD, whichever
occurs later.
2................... HPC rear hub.................... 30G8208......................... Before accumulating
5,000 CSN or within
100 FCs after the
effective date of
this AD, whichever
occurs later.
2................... HPC IBR-7....................... 30G2307 or 30G4407.............. Before accumulating
5,000 CSN or within
100 FCs after the
effective date of
this AD, whichever
occurs later.
2................... HPC IBR-8....................... 30G5608 or 30G5908 or 30G8908... Before accumulating
5,000 CSN or within
100 FCs after the
effective date of
this AD, whichever
occurs later.
2................... HPT 1st-stage hub............... 30G7301......................... Before accumulating
5,000 CSN or within
100 FCs after the
effective date of
this AD, whichever
occurs later.
2................... HPT 2nd-stage hub............... 30G6602......................... Before accumulating
5,000 CSN or within
100 FCs after the
effective date of
this AD, whichever
occurs later.
----------------------------------------------------------------------------------------------------------------
(5) For affected parts that have been operated in a Group 1 and
Group 2 configuration, calculate part replacement and AUSI times
required by paragraphs (h)(2) through (4) using the note to Table 3
of the compliance paragraph of PW ASB PW1000G-C-72-00-0224-00A-930A-
D, Issue No: 001 or PW ASB PW1000G-C-72-00-0225-00A-930A-D, Issue
No: 002, as applicable, which addresses calculating mixed model
cycles.
(6) For Group 1 and Group 2 engines with an installed HPT 1st-
stage hub having P/N 30G6201 or an HPT 2nd-stage hub having P/N
30G5502 and an S/N listed in Tables 1, 2, 3, or 4 of PW SI No. 149F-
23 that has not had an AUSI performed before the effective date of
this AD, before further flight, remove the affected hub from
service.
(7) For Group 1 and Group 2 engines with an installed HPT 1st-
stage hub having P/N 30G7301 or an HPT 2nd-stage hub having P/N
30G6602 with an S/N listed in Tables 1, 2, 3, or 4 of PW SI No.
198F-23, dated November 3, 2023 (PW SI No. 198F-23), within 100 FC
after the effective date of this AD, perform an AUSI of the affected
hub for cracks in accordance with the Accomplishment Instructions,
paragraph 1.D.(7)(a) or 1.D.(7)(b) of PW ASB PW1000G-C-72-00-0225-
00A-930A-D, Issue No: 002.
(8) For Group 1 and Group 2 engines with an installed HPT 1st-
stage hub having P/N 30G6201 or an HPT 2nd-stage hub having P/N
30G5502 with an S/N listed in Tables 1, 2, 3, or 4 of PW SI No.
198F-23, within 100 FC after the effective date of this AD, remove
the hub from service and replace with a part eligible for
installation.
(9) If any crack indication is found during any AUSI required by
this AD, before further flight, remove the affected part from
service and replace with a part eligible for installation.
(10) 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.
(i) Definitions
(1) For the purposes of this AD, ``Group 1 engines'' are IAE LLC
Model PW1122G-JM, PW1124G1-JM, PW1124G-JM, PW1127G-JM, PW1127G1-JM,
PW1127G1A-JM, PW1127G1B-JM, and PW1127GA-JM engines.
(2) For the purposes of this AD, ``Group 2 engines'' are IAE LLC
Model PW1129G-JM, PW1130G-JM, PW1133G-JM, PW1133GA-JM, PW1428G-JM,
PW1428GA-JM, PW1428GH-JM, PW1431G-JM, PW1431GA-JM, and PW1431GH-JM
engines.
(3) For the purposes of this AD, an ``HPC engine shop visit'' is
the induction of an
[[Page 21190]]
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.
(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 Moines,
WA 98198; phone: (781) 238-7655; email: [email protected].
(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:
[email protected]; 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 [email protected].
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
