Airworthiness Directives; General Electric Company Engines, 1361-1365 [2025-00208]
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Federal Register / Vol. 90, No. 5 / Wednesday, January 8, 2025 / Rules and Regulations
22907; Docket No. FAA–2024–2024;
Project Identifier MCAI–2024–00140–T.
(a) Effective Date
This airworthiness directive (AD) is
effective February 12, 2025.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all Airbus Defense and
Space S.A. (formerly known as
Construcciones Aeronauticas, S.A.) Model
CN–235, CN–235–200, and CN–235–300
airplanes, certificated in any category.
(d) Subject
Air Transport Association (ATA) of
America Code 32, Landing Gear.
(e) Unsafe Condition
This AD was prompted by a torn bulkhead
seal found jamming the nose landing gear
emergency cable pulley. Due to the similarity
of design, the main landing gear emergency
cable pulley could be exposed to the same
failure mode. The FAA is issuing this AD to
address this potential unsafe condition,
which could prevent the emergency
extension of the landing gears when required,
causing damage to the airplane and possible
injury to occupants.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Requirements
Except as specified in paragraphs (h) and
(i) of this AD: Comply with all required
actions and compliance times specified in,
and in accordance with, European Union
Aviation Safety Agency (EASA) AD 2024–
0054, dated February 26, 2024 (EASA AD
2024–0054).
(h) Exceptions to EASA AD 2024–0054
(1) Where EASA AD 2024–0054 refers to its
effective date, this AD requires using the
effective date of this AD.
(2) Where paragraph 3.1.1 of the Alert
Operators Transmission (AOT) specified in
EASA AD 2024–0054, states ‘‘each year (1
Year between 8 and 10 Years since
component installation) since the
inspection,’’ this AD requires replacing that
text with ‘‘within one year after the last
inspection’’.
(3) This AD does not adopt the ‘‘Remarks’’
section of EASA AD 2024–0054.
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(i) No Reporting Requirement
Although the material referenced in EASA
AD 2024–0054 specifies to submit certain
information to the manufacturer, this AD
does not include that requirement.
(j) 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.
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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 manager of the International Validation
Branch, mail it to the address identified in
paragraph (k) of this AD. Information may be
emailed to: 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 EASA; or Airbus Defense
and Space S.A.’s EASA Design Organization
Approval (DOA). If approved by the DOA,
the approval must include the DOAauthorized signature.
(k) Additional Information
For more information about this AD,
contact Shahram Daneshmandi, Aviation
Safety Engineer, FAA, 1600 Stewart Avenue,
Suite 410, Westbury, NY 11590; phone: 206–
231–3220; email: shahram.daneshmandi@
faa.gov.
(l) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference of
the material listed in this paragraph under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this material as
applicable to do the actions required by this
AD, unless this AD specifies otherwise.
(i) European Union Aviation Safety Agency
(EASA) AD 2024–0054, dated February 26,
2024.
(ii) [Reserved]
(3) For EASA material identified in this
AD, contact EASA, Konrad-Adenauer-Ufer 3,
50668 Cologne, Germany; telephone +49 221
8999 000; email ADs@easa.europa.eu;
website easa.europa.eu. You may find this
EASA AD on the EASA website at
ad.easa.europa.eu.
(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-locations or email fr.inspection@nara.gov.
Issued on December 4, 2024.
Victor Wicklund,
Deputy Director, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2025–00146 Filed 1–7–25; 8:45 am]
BILLING CODE 4910–13–P
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1361
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2024–0755; Project
Identifier AD–2023–00521–E; Amendment
39–22909; AD 2024–25–07]
RIN 2120–AA64
Airworthiness Directives; General
Electric Company Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for certain
General Electric Company (GE) Model
GEnx–1B64, GEnx–1B64/P1, GEnx–
1B64/P2, GEnx–1B67, GEnx–1B67/P1,
GEnx–1B67/P2, GEnx–1B70, GEnx–
1B70/75/P1, GEnx–1B70/75/P2, GEnx–
1B70/P1, GEnx–1B70/P2, GEnx–1B70C/
P1, GEnx–1B70C/P2, GEnx–1B74/75/P1,
GEnx–1B74/75/P2, GEnx–1B76/P2,
GEnx–1B76A/P2, GEnx–2B67, GEnx–
2B67B, and GEnx–2B67/P engines. This
AD was prompted by a manufacturer
evaluation that determined a lower life
limit may be necessary for certain stages
6–10 compressor rotor spools than
allowed by the engine shop manual
(ESM). This AD requires a one-time
inspection of the stages 6–10 spools for
previously accomplished blend repairs,
a one-time inspection of the blend
repairs on the stages 6–10 spools for
compliance with the updated allowable
limits, and replacement if necessary.
The FAA is issuing this AD to address
the unsafe condition on these products.
DATES: This AD is effective February 12,
2025.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of February 12, 2025.
ADDRESSES:
AD Docket: You may examine the AD
docket at regulations.gov under Docket
No. FAA–2024–0755; 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 GE material identified in this
AD, contact GE, 1 Neumann Way,
Cincinnati, OH 45215; phone: (513)
SUMMARY:
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552–3272; email: aviation.fleetsupport@
ge.com; website: ge.com.
• You may view this material at the
FAA, Airworthiness Products Section,
Operational Safety Branch, 1200 District
Avenue, Burlington, MA 01803. For
information on the availability of this
material at the FAA, call (817) 222–
5110. It is also available at
regulations.gov under Docket No. FAA–
2024–0755.
FOR FURTHER INFORMATION CONTACT:
Alexei Marqueen, Aviation Safety
Engineer, FAA, 2200 South 216th Street,
Des Moines, WA 98198; phone: (781)
238–7178; email: alexei.t.marqueen@
faa.gov.
SUPPLEMENTARY INFORMATION:
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Background
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain GE Model GEnx–1B64/
P1, GEnx–1B64/P2, GEnx–1B67, GEnx–
1B67/P1, GEnx–1B67/P2, GEnx–1B70,
GEnx–1B70/75/P1, GEnx–1B70/75/P2,
GEnx–1B70/P1, GEnx–1B70/P2, GEnx–
1B70C/P1, GEnx–1B70C/P2, GEnx–
1B74/75/P1, GEnx–1B74/75/P2, GEnx–
1B76/P2, GEnx–1B76A/P2, GEnx–2B67,
GEnx–2B67B, and GEnx–2B67/P
engines with certain stages 6–10 spool
installed. The NPRM published in the
Federal Register on March 25, 2024 (89
FR 20553). The NPRM was prompted by
a manufacturer evaluation which
determined that a lower life limit may
be necessary for certain stages 6–10
spools than that allowed in the engine
shop manual. In the NPRM, the FAA
proposed to require accomplishing a
one-time inspection of the stages 6–10
spools for previously accomplished
blend repairs, a one-time inspection of
the blend repairs on the stages 6–10
spools for compliance with the updated
allowable limits, and replacement, if
necessary, within compliance times
specified in GE GEnx–1B Service
Bulletin 72–0525, R00, dated October 4,
2023 (GEnx–1B SB 72–0525, R00), or
GEnx–2B Service Bulletin 72–0460,
R00, dated October 4, 2023 (GEnx–2B
SB 72–0460, R00). Depending on the
part numbers and serial numbers of the
affected stages 6–10 spools, the NPRM
proposed to require these actions to be
accomplished at the next piece-part
exposure after the effective date of the
proposed AD, or before the affected
stages 6–10 spool reaches the cyclic
removal threshold of up to 11,894 cycles
since new. The FAA is issuing this AD
to address the unsafe condition on these
products.
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Discussion of Final Airworthiness
Directive
Comments
The FAA received comments from
eight commenters. The commenters
were American Airlines, Air Line Pilots
Association, International (ALPA),
Boeing Commercial Airplanes (Boeing),
GE, Japan Airlines, Qatar Airways,
United Airlines, and United Parcel
Service (UPS). ALPA and Boeing
supported the NPRM without change.
The following presents the comments
received on the NPRM and the FAA’s
response to each comment.
Request for Clarification of Compliance
Time
Qatar Airways requested clarification
of the compliance threshold specified in
the NPRM. The commenter pointed out
that the compliance thresholds in the
service information specify that ‘‘at the
next piece-part exposure of the affected
6–10 spools, but before the affected 6–
10 spools reach the cycle since new
threshold for inspection listed in
paragraph 4., Appendix—A, Table 1,’’
whereas the NPRM expressed the
compliance time as ‘‘At the next piecepart exposure after the effective date of
this AD or before the affected stages 6–
10 spool reaches the cyclic removal
threshold specified in paragraph 4.,
Appendix-A, Table 1 of GEnx–1B 72–
0525, R00 or GEnx–2B SB 72–0460, R00,
as applicable.’’ The commentor stated
that the compliance time as written, is
unclear about when to take action and
which takes priority (next piece part or
cycle thresholds).
The FAA agrees that the compliance
time is unclear. Paragraph (g) of this AD
has been updated to state that the
required action is to be performed at
next piece part exposure or before the
spool reaches the cycle removal
thresholds, whichever occurs first.
Request To Update the Definition of
‘‘Part Eligible for Installation’’
American Airlines and UPS requested
that the FAA reword paragraph (h)(2) of
the proposed AD to allow installation of
an affected part, provided that the part
passes the required inspections. UPS
pointed out that in both paragraph (g) of
the proposed AD and the service
information, replacement of an affected
part is only required if a previously
accomplished blend repair is found and
is also not within the allowable limits.
However, the proposed definition
would prohibit installation of any
affected part, regardless of the
inspection results. In addition, UPS
requested that paragraph (h)(2) of the
proposed AD be reworded to redefine a
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‘‘part eligible for installation’’ as a stages
6–10 spool that does not have a P/N and
S/N defined in paragraph 4, Appendix
A, Table 1 of GEnx–1B 72–0525, R00 or
GEnx–2B 72–0460, R00, or a stages 6–
10 spool with a P/N and S/N that is
listed in paragraph 4, Appendix A,
Table 1 of GEnx–1B 72–0525, R00 or
GEnx–2B 72–0460 that has been
inspected and found to be within the
allowable limits.
The FAA agrees that a stages 6–10
spool that passes inspection does not
need to be removed from service.
Therefore, paragraph (h)(2) of this AD
has been updated to reflect this change.
Request To Revise the Summary
GE requested that the FAA revise the
SUMMARY of the NPRM to clarify that for
certain stages 6–10 compressor rotor
spools there is a potential life shortfall
to that specified in the ESM, instead of
an absolute or definite life shortfall. GE
stated that the evaluation of the repair
limits demonstrated that at the worst
size and location a stages 6–10 spool
would have an ultimate life lower than
that published in the ESM. However,
there is no evidence to show that any of
the affected stages 6–10 spools have a
repair at the worst size and location. GE
pointed out that for this reason, an
inspection is required to determine if
there is a possibility of the ultimate life
lower than that published in the ESM.
GE recommended adding the terms
‘‘may be’’ to the SUMMARY to clarify that
not all stages 6–10 spools will have a
lower life limit.
The FAA agrees that clarification is
necessary and has updated the SUMMARY
of this AD accordingly.
Request To Update the Required
Service Information
GE requested that the FAA update the
NPRM to specify the latest revision of
the service information. GE specified
the intention to revise GE GEnx–1B SB
72–0525, R00 and GEnx–2B SB 72–
0460, R00, and added that the updated
revisions will not change actions or
accomplishment instructions but will
add wording indicating hardware that
meets current ESM limits will not have
a lower limit than published in CH05.
The FAA agrees and has revised this
AD to refer to GE GEnx–1B Service
Bulletin 72–0525, R01, dated June 10,
2024 (GEnx–1B SB 72–0525, R01), and
GEnx–2B Service Bulletin 72–0460,
R01, dated June 10, 2024 (GEnx–2B SB
72–0460, R01), as the appropriate source
of service information. Additionally, the
FAA has updated this AD to include
credit for the actions required by
paragraph (g) of this AD, if those actions
were done prior to the effective date of
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this AD using GE GEnx–1B SB 72–0525,
R00 and GEnx–2B SB 72–0460, R00.
Request To Clarify the Applicability of
ESM Life Limits
United Airlines requested that the
FAA include additional verbiage in the
service information and the proposed
AD that, in the case of an affected part
passing the inspection, that part retains
the ultimate life limit specified in the
ESM. United Airlines stated that
paragraph (g) of the proposed AD was
not specific about what actions to take
if the affected part passed the
inspection. However, the service
information specifies that no further
action is necessary. Also, paragraph
1.E.(3) of GEnx–1B SB 72–0525, R00
and GEnx–2B SB 72–0460, R00 states
that ‘‘affected 6–10 spools were found to
have life limit lower than ultimate life
limit.’’
The FAA disagrees with the request.
The life limits listed in the ESM are
mandatory and applicable regardless of
the actions required by this AD. Should
any affected part be found to have a
blend repair that is not in compliance
with the allowable limits specified in
the applicable service information, then
this AD requires removal from service
and replacement of that specific part.
However, this AD does not change the
life limits of parts that pass the
inspection. Therefore, the FAA has not
changed this AD in this regard.
Request To Specify the Affected Engine
Models in the Required Actions
Japan Airlines requested that the FAA
revise paragraph (g) of the proposed AD
to specify the affected engine models at
the beginning of each of the sentences,
to provide better clarity. Japan Airlines
referred to paragraph (g) of AD 2023–
17–08 as an example.
The FAA disagrees with the request.
AD 2023–17–08 specifies multiple
affected parts on both the GEnx–1B and
GEnx–2B Model engines, and therefore
the FAA used multiple paragraphs for
each affected part and each engine
model. In this AD, the only affected
parts are stages 6–10 spools, making it
unnecessary to specify engine models in
paragraph (g) of this AD.
Changes After the NPRM Was
Published
After the NPRM was published, the
FAA determined that Model GEnx–1B64
engines were inadvertently left out of
the applicability. None of these engines
with the affected stages 6–10 spools are
installed on airplanes on the U.S.
registry. This model has been added to
the applicability of the final rule in case
one of these engines with affected 6–10
spools are installed on an airplane
registered for operation in United States.
Adding this model to the applicability
does not increase the burden to U.S.
operators over the already proposed
requirements, so issuing a supplemental
notice of proposed rulemaking is
unnecessary.
Conclusion
The FAA reviewed the relevant data,
considered any comments received, and
determined that air safety requires
adopting this AD as proposed.
Accordingly, the FAA is issuing this AD
to address the unsafe condition on these
products. Except for minor editorial
changes, and any other changes
described previously, this AD is
adopted as proposed in the NPRM.
None of the changes will increase the
economic burden on any operator.
Material Incorporated by Reference
Under 1 CFR Part 51
The FAA reviewed GE GEnx–1B SB
72–0525, R01, and GEnx–2B SB 72–
0460, R01. This service information
identifies the part numbers and serial
numbers of affected stages 6–10 spools;
and specifies instructions for a one-time
inspection of the stages 6–10 spools for
previously accomplished blend repairs,
a one-time inspection of the blend
repairs on the stages 6–10 spools for
compliance with the updated allowable
limits, and replacement if necessary.
These documents are distinct since they
apply to different engine models.
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 ADDRESSES section.
Costs of Compliance
The FAA estimates that this AD
affects 6 engines installed on airplanes
of U.S. registry.
The FAA estimates the following
costs to comply with this AD:
ESTIMATED COSTS
Action
Labor cost
Inspect stages 6–10 spools ............................
Inspect previous blend repairs ........................
8 work-hours × $85 per hour = $680 .............
1 work-hours × $85 per hour = $85 ...............
The FAA estimates the following
costs to do any necessary replacements
that would be required based on the
Cost per
product
Parts cost
results of the inspections. The agency
has no way of determining the number
$0
0
Cost on U.S.
operators
$680
85
$4,080
510
of engines that might need this
replacement:
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ON-CONDITION COSTS
Action
Labor cost
Replace stages 6–10 spool ..........................................
8 work-hours × $85 per hour = $680 ...........................
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
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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
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Parts cost
$1,307,600
Cost per
product
$1,308,280
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
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Federal Register / Vol. 90, No. 5 / Wednesday, January 8, 2025 / Rules and Regulations
procedures the Administrator finds
necessary for safety in air commerce.
This regulation is within the scope of
that authority because it addresses an
unsafe condition that is likely to exist or
develop on products identified in this
rulemaking action.
Regulatory Findings
This AD will not have federalism
implications under Executive Order
13132. This AD will not have a
substantial direct effect on the States, on
the relationship between the national
government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Will not affect intrastate aviation
in Alaska, and
(3) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
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 adding
the following new airworthiness
directive:
■
2024–25–07 General Electric Company:
Amendment 39–22909; Docket No.
FAA–2024–0755; Project Identifier AD–
2023–00521–E.
(a) Effective Date
This airworthiness directive (AD) is
effective February 12, 2025.
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(b) Affected ADs
None.
(c) Applicability
This AD applies to General Electric
Company (GE) Model GEnx–1B64, GEnx–
1B64/P1, GEnx–1B64/P2, GEnx–1B67, GEnx–
1B67/P1, GEnx–1B67/P2, GEnx–1B70, GEnx–
1B70/75/P1, GEnx–1B70/75/P2, GEnx–1B70/
P1, GEnx–1B70/P2, GEnx–1B70C/P1, GEnx–
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1B70C/P2, GEnx–1B74/75/P1, GEnx–1B74/
75/P2, GEnx–1B76/P2, GEnx–1B76A/P2,
GEnx–2B67, GEnx–2B67B, and GEnx–2B67/P
engines with an installed:
(1) Stages 6–10 compressor rotor spool
(stages 6–10 spool) having a part number (P/
N) and serial number (S/N) listed in
paragraph 4, Appendix—A, Table 1 of GE
GEnx–1B Service Bulletin 72–0525, R01,
dated June 10, 2024 (GEnx–1B SB 72–0525,
R01); or
(2) Stages 6–10 spool having a P/N and S/
N listed in paragraph 4, Appendix—A, Table
1 of GE GEnx–2B Service Bulletin 72–0460,
R01, dated June 10, 2024 (GEnx–2B SB 72–
0460, R01).
(h) Definition
For the purposes of this AD:
(1) A ‘‘piece-part exposure’’ is when the
stages 6–10 spool is disassembled from the
high-pressure compressor rotor assembly.
(2) A ‘‘part eligible for installation’’ is
either a stages 6–10 spool that does not have
a P/N and S/N identified in paragraph 4,
Appendix—A, Table 1 of GEnx–1B 72–0525,
R01 or GEnx–2B 72–0460, R01, or a stages 6–
10 spool that does have a P/N and S/N
identified in paragraph 4, Appendix—A,
Table 1 of GEnx–1B 72–0525, R01 or GEnx–
2B 72–0460, R01, provided that the affected
part is not removed in accordance with
paragraph (g)(3) of this AD.
(d) Subject
(i) Credit for Previous Actions
You may take credit for the actions
required by paragraph (g) of this AD if you
performed those actions before the effective
date of this AD using GE GEnx–1B Service
Bulletin 72–0525, R00, dated October 4,
2023, or GEnx–2B Service Bulletin 72–0460,
R00, dated October 4, 2023.
Joint Aircraft System Component (JASC)
Code 7230, Turbine Engine Compressor
Section.
(e) Unsafe Condition
This AD was prompted by a manufacturer
evaluation which determined that a lower
life limit may be necessary for certain stages
6–10 spools than that allowed in the engine
shop manual. The FAA is issuing this AD to
prevent fracture and potential uncontained
failure of the stages 6–10 spools. The unsafe
condition, if not addressed, could result in
uncontained debris release, damage to the
engine, and damage to the aircraft.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions
At the next piece-part exposure after the
effective date of this AD or before the affected
stages 6–10 spool reaches the cyclic removal
threshold specified in paragraph 4.,
Appendix—A, Table 1 of GEnx–1B 72–0525,
R01 or GEnx–2B SB 72–0460, R01, as
applicable, whichever occurs first, do the
following actions:
(1) Inspect the stages 6–10 spool for
previously accomplished blend repairs in
accordance with the Accomplishment
Instructions, paragraph 3.B.(1) of GEnx–1B
SB 72–0525, R01 or GEnx–2B SB 72–0460,
R01, as applicable.
(2) If during any inspection required by
paragraph (g)(1) of this AD, any stages 6–10
spool is found to have a previously
accomplished blend repair, before further
flight, inspect the blend repair for
compliance with the allowable limits in
accordance with the Accomplishment
Instructions, paragraph 3.B.(2) of GEnx–1B
SB 72–0525, R01 or GEnx–2B SB 72–0460,
R01, as applicable.
(3) If during any inspection required by
paragraph (g)(2) of this AD, any stages 6–10
spool is found to have a previously
accomplished blend repair that is not within
the allowable limits, before further flight,
remove the stages 6–10 spool from service
and replace with a part eligible for
installation in accordance with the
Accomplishment Instructions, paragraph
3.B.(2)(a)1 or 3.B.(2)(b)1 of GEnx–1B SB 72–
0525, R01 or GEnx–2B SB 72–0460, R01, as
applicable.
PO 00000
Frm 00010
Fmt 4700
Sfmt 4700
(j) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, AIR–520 Continued
Operational Safety Branch, FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the AIR–520 Continued
Operational Safety Branch, send it to the
attention of the person identified in
paragraph (k) of this AD and email to: ANEAD-AMOC@faa.gov.
(2) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(k) Related Information
For more information about this AD,
contact Alexei Marqueen, Aviation Safety
Engineer, FAA, 2200 South 216th Street, Des
Moines, WA 98198; phone: (781) 238–7178;
email: alexei.t.marqueen@faa.gov.
(l) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the material listed in this paragraph
under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this material as
applicable to do the actions required by this
AD, unless the AD specifies otherwise.
(i) GE GEnx–1B Service Bulletin 72–0525,
R01, dated June 10, 2024.
(ii) GE GEnx–2B Service Bulletin 72–0460,
R01, dated June 10, 2024.
(3) For GE material identified in this AD,
contact GE 1 Neumann Way, Cincinnati, OH
45215; phone: (513) 552–3272; email:
aviation.fleetsupport@ge.com; website:
ge.com.
(4) You may view this material at 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.
E:\FR\FM\08JAR1.SGM
08JAR1
Federal Register / Vol. 90, No. 5 / Wednesday, January 8, 2025 / Rules and Regulations
(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 December 6, 2024.
Peter A. White,
Deputy Director, Integrated Certificate
Management Division, Aircraft Certification
Service.
[FR Doc. 2025–00208 Filed 1–7–25; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2024–1898; Project
Identifier AD–2023–01013–E; Amendment
39–22904; AD 2024–25–02]
RIN 2120–AA64
Airworthiness Directives; CFM
International, S.A. Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for certain
CFM International, S.A. (CFM) Model
LEAP–1B engines. This AD was
prompted by a report of a quality escape
involving certain high-pressure
compressor (HPC) stage 2 seals
manufactured without detailed finish
machining, which could result in
deeper rubs and mechanical damage to
the seal teeth of the stage 3–4
compressor rotor blisk (stage 3–4 blisk)
of the mating compressor rotor during
initial operation. This AD requires a
visual inspection of the HPC stage 2
seal, a visual inspection of the forward
arm seal teeth of the stage 3–4 blisk, an
eddy current inspection (ECI) of the
forward arm seal teeth of the stage 3–4
blisk, and replacement of the HPC stage
2 seal and the stage 3–4 blisk, if
necessary. The FAA is issuing this AD
to address the unsafe condition on these
products.
DATES: This AD is effective February 12,
2025.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of February 12, 2025.
ADDRESSES:
AD Docket: You may examine the AD
docket at regulations.gov under Docket
No. FAA–2024–1898; or in person at
Docket Operations between 9 a.m. and
5 p.m., Monday through Friday, except
lotter on DSK11XQN23PROD with RULES1
SUMMARY:
VerDate Sep<11>2014
15:49 Jan 07, 2025
Jkt 265001
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 CFM material identified in this
AD, contact CFM, GE Aviation Fleet
Support, 1 Neumann Way, M/D Room
285, Cincinnati, OH 45215; phone: (877)
432–3272; email: aviation.fleetsupport@
ge.com.
• You may view this material at the
FAA, Airworthiness Products Section,
Operational Safety Branch, 1200 District
Avenue, Burlington, MA 01803. For
information on the availability of this
material at the FAA, call (817) 222–
5110. It is also available at
regulations.gov under Docket No. FAA–
2024–1898.
FOR FURTHER INFORMATION CONTACT:
Mehdi Lamnyi, Aviation Safety
Engineer, FAA, 2200 South 216th Street,
Des Moines, WA 98198; phone: (781)
238–7743; email: mehdi.lamnyi@
faa.gov.
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain CFM Model LEAP–1B
engines. The NPRM published in the
Federal Register on July 29, 2024 (89 FR
60838). The NPRM was prompted by a
report of a quality escape involving
certain HPC stage 2 seals manufactured
without detailed finish machining,
which could result in deeper rubs and
mechanical damage to the seal teeth of
the stage 3–4 blisk of the mating
compressor rotor during initial
operation. In the NPRM, the FAA
proposed to require a visual inspection
of the HPC stage 2 seal, a visual
inspection of the forward arm seal teeth
of the stage 3–4 blisk, an ECI of the
forward arm seal teeth of the stage 3–4
blisk, and replacement of the HPC stage
2 seal and the stage 3–4 blisk, if
necessary. 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 six
commenters. The commenters were The
Boeing Company (Boeing), CFM,
Ryanair, StandardAero, Southwest
Airlines (SWA), and United Airlines
PO 00000
Frm 00011
Fmt 4700
Sfmt 4700
1365
(UAL). Boeing concurred with the
contents of the NPRM and
StandardAero expressed support for the
NPRM. The following presents the
comments received on the NPRM and
the FAA’s response to each comment.
Request To Remove Certain Engine
Serial Numbers (ESNs) From the
Applicability
CFM and Ryanair requested that the
FAA remove certain ESNs from the
applicability of the proposed AD or
include replacement of the HPC stage 2
seal and the stage 3–4 blisk with new
parts as an option for complying with
the proposed AD. Both commenters
stated that certain ESNs had already
replaced the HPC stage 2 seal and the
stage 3–4 blisk with new parts. Both
commenters also pointed out that by
replacing the HPC stage 2 seal and the
stage 3–4 blisk with new parts, the
unsafe condition is mitigated for those
engines, but not as specified in the
required actions of the proposed AD.
Since this is a quality escape issue
and limited to the parts originally
installed on the engine, the FAA agrees
for the reasons provided and has
removed ESNs 60A676 and 60A669
from the applicability of this AD.
Request for Clarification of Difference
With the Service Information
StandardAero and UAL requested that
the FAA provide clarification regarding
why the borescope inspection (BSI)
specified in the required service
information is not required by the
NPRM. StandardAero pointed out that
the NPRM does not address why the BSI
is not required. StandardAero also
mentioned that the European Union
Aviation Safety Agency (EASA) has a
corresponding proposed AD (EASA
PAD 24–108), which discussed and
inferred that the BSIs have already been
completed on all affected engines.
StandardAero specifically requested
that the FAA confirm that the BSIs have
been completed on all the ESNs that are
specified in the service information, and
that the ESNs specified in the NPRM are
those that require additional action due
to the BSI results. UAL pointed out that
the service information contains
Required for Compliance (RC) steps for
a BSI. UAL requested clarification of
whether those steps are required by the
NPRM and whether the BSI is
acceptable for verifying the condition of
the HPC stage 2 seal and the stage 3–4
blisk.
The FAA acknowledges the difference
between the actions required by this AD
and those specified in the service
information. The engine manufacturer
has provided the FAA with evidence
E:\FR\FM\08JAR1.SGM
08JAR1
]]>Agencies
[Federal Register Volume 90, Number 5 (Wednesday, January 8, 2025)]
[Rules and Regulations]
[Pages 1361-1365]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2025-00208]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2024-0755; Project Identifier AD-2023-00521-E;
Amendment 39-22909; AD 2024-25-07]
RIN 2120-AA64
Airworthiness Directives; General Electric Company Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain General Electric Company (GE) Model GEnx-1B64, GEnx-1B64/P1,
GEnx-1B64/P2, GEnx-1B67, GEnx-1B67/P1, GEnx-1B67/P2, GEnx-1B70, GEnx-
1B70/75/P1, GEnx-1B70/75/P2, GEnx-1B70/P1, GEnx-1B70/P2, GEnx-1B70C/P1,
GEnx-1B70C/P2, GEnx-1B74/75/P1, GEnx-1B74/75/P2, GEnx-1B76/P2, GEnx-
1B76A/P2, GEnx-2B67, GEnx-2B67B, and GEnx-2B67/P engines. This AD was
prompted by a manufacturer evaluation that determined a lower life
limit may be necessary for certain stages 6-10 compressor rotor spools
than allowed by the engine shop manual (ESM). This AD requires a one-
time inspection of the stages 6-10 spools for previously accomplished
blend repairs, a one-time inspection of the blend repairs on the stages
6-10 spools for compliance with the updated allowable limits, and
replacement if necessary. The FAA is issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective February 12, 2025.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of February 12,
2025.
ADDRESSES:
AD Docket: You may examine the AD docket at regulations.gov under
Docket No. FAA-2024-0755; 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 GE material identified in this AD, contact GE, 1
Neumann Way, Cincinnati, OH 45215; phone: (513)
[[Page 1362]]
552-3272; email: ge.com">aviation.fleetsupport@ge.com; website: ge.com.
You may view this material at the FAA, Airworthiness
Products Section, Operational Safety Branch, 1200 District Avenue,
Burlington, MA 01803. For information on the availability of this
material at the FAA, call (817) 222-5110. It is also available at
regulations.gov under Docket No. FAA-2024-0755.
FOR FURTHER INFORMATION CONTACT: Alexei Marqueen, Aviation Safety
Engineer, FAA, 2200 South 216th Street, Des Moines, WA 98198; phone:
(781) 238-7178; email: [email protected].
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to certain GE Model GEnx-
1B64/P1, GEnx-1B64/P2, GEnx-1B67, GEnx-1B67/P1, GEnx-1B67/P2, GEnx-
1B70, GEnx-1B70/75/P1, GEnx-1B70/75/P2, GEnx-1B70/P1, GEnx-1B70/P2,
GEnx-1B70C/P1, GEnx-1B70C/P2, GEnx-1B74/75/P1, GEnx-1B74/75/P2, GEnx-
1B76/P2, GEnx-1B76A/P2, GEnx-2B67, GEnx-2B67B, and GEnx-2B67/P engines
with certain stages 6-10 spool installed. The NPRM published in the
Federal Register on March 25, 2024 (89 FR 20553). The NPRM was prompted
by a manufacturer evaluation which determined that a lower life limit
may be necessary for certain stages 6-10 spools than that allowed in
the engine shop manual. In the NPRM, the FAA proposed to require
accomplishing a one-time inspection of the stages 6-10 spools for
previously accomplished blend repairs, a one-time inspection of the
blend repairs on the stages 6-10 spools for compliance with the updated
allowable limits, and replacement, if necessary, within compliance
times specified in GE GEnx-1B Service Bulletin 72-0525, R00, dated
October 4, 2023 (GEnx-1B SB 72-0525, R00), or GEnx-2B Service Bulletin
72-0460, R00, dated October 4, 2023 (GEnx-2B SB 72-0460, R00).
Depending on the part numbers and serial numbers of the affected stages
6-10 spools, the NPRM proposed to require these actions to be
accomplished at the next piece-part exposure after the effective date
of the proposed AD, or before the affected stages 6-10 spool reaches
the cyclic removal threshold of up to 11,894 cycles since new. 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 eight commenters. The commenters
were American Airlines, Air Line Pilots Association, International
(ALPA), Boeing Commercial Airplanes (Boeing), GE, Japan Airlines, Qatar
Airways, United Airlines, and United Parcel Service (UPS). ALPA and
Boeing supported the NPRM without change. The following presents the
comments received on the NPRM and the FAA's response to each comment.
Request for Clarification of Compliance Time
Qatar Airways requested clarification of the compliance threshold
specified in the NPRM. The commenter pointed out that the compliance
thresholds in the service information specify that ``at the next piece-
part exposure of the affected 6-10 spools, but before the affected 6-10
spools reach the cycle since new threshold for inspection listed in
paragraph 4., Appendix--A, Table 1,'' whereas the NPRM expressed the
compliance time as ``At the next piece-part exposure after the
effective date of this AD or before the affected stages 6-10 spool
reaches the cyclic removal threshold specified in paragraph 4.,
Appendix-A, Table 1 of GEnx-1B 72-0525, R00 or GEnx-2B SB 72-0460, R00,
as applicable.'' The commentor stated that the compliance time as
written, is unclear about when to take action and which takes priority
(next piece part or cycle thresholds).
The FAA agrees that the compliance time is unclear. Paragraph (g)
of this AD has been updated to state that the required action is to be
performed at next piece part exposure or before the spool reaches the
cycle removal thresholds, whichever occurs first.
Request To Update the Definition of ``Part Eligible for Installation''
American Airlines and UPS requested that the FAA reword paragraph
(h)(2) of the proposed AD to allow installation of an affected part,
provided that the part passes the required inspections. UPS pointed out
that in both paragraph (g) of the proposed AD and the service
information, replacement of an affected part is only required if a
previously accomplished blend repair is found and is also not within
the allowable limits. However, the proposed definition would prohibit
installation of any affected part, regardless of the inspection
results. In addition, UPS requested that paragraph (h)(2) of the
proposed AD be reworded to redefine a ``part eligible for
installation'' as a stages 6-10 spool that does not have a P/N and S/N
defined in paragraph 4, Appendix A, Table 1 of GEnx-1B 72-0525, R00 or
GEnx-2B 72-0460, R00, or a stages 6-10 spool with a P/N and S/N that is
listed in paragraph 4, Appendix A, Table 1 of GEnx-1B 72-0525, R00 or
GEnx-2B 72-0460 that has been inspected and found to be within the
allowable limits.
The FAA agrees that a stages 6-10 spool that passes inspection does
not need to be removed from service. Therefore, paragraph (h)(2) of
this AD has been updated to reflect this change.
Request To Revise the Summary
GE requested that the FAA revise the SUMMARY of the NPRM to clarify
that for certain stages 6-10 compressor rotor spools there is a
potential life shortfall to that specified in the ESM, instead of an
absolute or definite life shortfall. GE stated that the evaluation of
the repair limits demonstrated that at the worst size and location a
stages 6-10 spool would have an ultimate life lower than that published
in the ESM. However, there is no evidence to show that any of the
affected stages 6-10 spools have a repair at the worst size and
location. GE pointed out that for this reason, an inspection is
required to determine if there is a possibility of the ultimate life
lower than that published in the ESM. GE recommended adding the terms
``may be'' to the SUMMARY to clarify that not all stages 6-10 spools
will have a lower life limit.
The FAA agrees that clarification is necessary and has updated the
SUMMARY of this AD accordingly.
Request To Update the Required Service Information
GE requested that the FAA update the NPRM to specify the latest
revision of the service information. GE specified the intention to
revise GE GEnx-1B SB 72-0525, R00 and GEnx-2B SB 72-0460, R00, and
added that the updated revisions will not change actions or
accomplishment instructions but will add wording indicating hardware
that meets current ESM limits will not have a lower limit than
published in CH05.
The FAA agrees and has revised this AD to refer to GE GEnx-1B
Service Bulletin 72-0525, R01, dated June 10, 2024 (GEnx-1B SB 72-0525,
R01), and GEnx-2B Service Bulletin 72-0460, R01, dated June 10, 2024
(GEnx-2B SB 72-0460, R01), as the appropriate source of service
information. Additionally, the FAA has updated this AD to include
credit for the actions required by paragraph (g) of this AD, if those
actions were done prior to the effective date of
[[Page 1363]]
this AD using GE GEnx-1B SB 72-0525, R00 and GEnx-2B SB 72-0460, R00.
Request To Clarify the Applicability of ESM Life Limits
United Airlines requested that the FAA include additional verbiage
in the service information and the proposed AD that, in the case of an
affected part passing the inspection, that part retains the ultimate
life limit specified in the ESM. United Airlines stated that paragraph
(g) of the proposed AD was not specific about what actions to take if
the affected part passed the inspection. However, the service
information specifies that no further action is necessary. Also,
paragraph 1.E.(3) of GEnx-1B SB 72-0525, R00 and GEnx-2B SB 72-0460,
R00 states that ``affected 6-10 spools were found to have life limit
lower than ultimate life limit.''
The FAA disagrees with the request. The life limits listed in the
ESM are mandatory and applicable regardless of the actions required by
this AD. Should any affected part be found to have a blend repair that
is not in compliance with the allowable limits specified in the
applicable service information, then this AD requires removal from
service and replacement of that specific part. However, this AD does
not change the life limits of parts that pass the inspection.
Therefore, the FAA has not changed this AD in this regard.
Request To Specify the Affected Engine Models in the Required Actions
Japan Airlines requested that the FAA revise paragraph (g) of the
proposed AD to specify the affected engine models at the beginning of
each of the sentences, to provide better clarity. Japan Airlines
referred to paragraph (g) of AD 2023-17-08 as an example.
The FAA disagrees with the request. AD 2023-17-08 specifies
multiple affected parts on both the GEnx-1B and GEnx-2B Model engines,
and therefore the FAA used multiple paragraphs for each affected part
and each engine model. In this AD, the only affected parts are stages
6-10 spools, making it unnecessary to specify engine models in
paragraph (g) of this AD.
Changes After the NPRM Was Published
After the NPRM was published, the FAA determined that Model GEnx-
1B64 engines were inadvertently left out of the applicability. None of
these engines with the affected stages 6-10 spools are installed on
airplanes on the U.S. registry. This model has been added to the
applicability of the final rule in case one of these engines with
affected 6-10 spools are installed on an airplane registered for
operation in United States. Adding this model to the applicability does
not increase the burden to U.S. operators over the already proposed
requirements, so issuing a supplemental notice of proposed rulemaking
is unnecessary.
Conclusion
The FAA reviewed the relevant data, considered any comments
received, and determined that air safety requires adopting this AD as
proposed. Accordingly, the FAA is issuing this AD to address the unsafe
condition on these products. Except for minor editorial changes, and
any other changes described previously, this AD is adopted as proposed
in the NPRM. None of the changes will increase the economic burden on
any operator.
Material Incorporated by Reference Under 1 CFR Part 51
The FAA reviewed GE GEnx-1B SB 72-0525, R01, and GEnx-2B SB 72-
0460, R01. This service information identifies the part numbers and
serial numbers of affected stages 6-10 spools; and specifies
instructions for a one-time inspection of the stages 6-10 spools for
previously accomplished blend repairs, a one-time inspection of the
blend repairs on the stages 6-10 spools for compliance with the updated
allowable limits, and replacement if necessary. These documents are
distinct since they apply to different engine models.
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 ADDRESSES section.
Costs of Compliance
The FAA estimates that this AD affects 6 engines installed on
airplanes of U.S. registry.
The FAA estimates the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Inspect stages 6-10 spools............ 8 work-hours x $85 per $0 $680 $4,080
hour = $680.
Inspect previous blend repairs........ 1 work-hours x $85 per 0 85 510
hour = $85.
----------------------------------------------------------------------------------------------------------------
The FAA estimates the following costs to do any necessary
replacements that would be required based on the results of the
inspections. The agency has no way of determining the number of engines
that might need this replacement:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Replace stages 6-10 spool..................... 8 work-hours x $85 per hour = $1,307,600 $1,308,280
$680.
----------------------------------------------------------------------------------------------------------------
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
[[Page 1364]]
procedures the Administrator finds necessary for safety in air
commerce. This regulation is within the scope of that authority because
it addresses an unsafe condition that is likely to exist or develop on
products identified in this rulemaking action.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Will not affect intrastate aviation in Alaska, and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive:
2024-25-07 General Electric Company: Amendment 39-22909; Docket No.
FAA-2024-0755; Project Identifier AD-2023-00521-E.
(a) Effective Date
This airworthiness directive (AD) is effective February 12,
2025.
(b) Affected ADs
None.
(c) Applicability
This AD applies to General Electric Company (GE) Model GEnx-
1B64, GEnx-1B64/P1, GEnx-1B64/P2, GEnx-1B67, GEnx-1B67/P1, GEnx-
1B67/P2, GEnx-1B70, GEnx-1B70/75/P1, GEnx-1B70/75/P2, GEnx-1B70/P1,
GEnx-1B70/P2, GEnx-1B70C/P1, GEnx-1B70C/P2, GEnx-1B74/75/P1, GEnx-
1B74/75/P2, GEnx-1B76/P2, GEnx-1B76A/P2, GEnx-2B67, GEnx-2B67B, and
GEnx-2B67/P engines with an installed:
(1) Stages 6-10 compressor rotor spool (stages 6-10 spool)
having a part number (P/N) and serial number (S/N) listed in
paragraph 4, Appendix--A, Table 1 of GE GEnx-1B Service Bulletin 72-
0525, R01, dated June 10, 2024 (GEnx-1B SB 72-0525, R01); or
(2) Stages 6-10 spool having a P/N and S/N listed in paragraph
4, Appendix--A, Table 1 of GE GEnx-2B Service Bulletin 72-0460, R01,
dated June 10, 2024 (GEnx-2B SB 72-0460, R01).
(d) Subject
Joint Aircraft System Component (JASC) Code 7230, Turbine Engine
Compressor Section.
(e) Unsafe Condition
This AD was prompted by a manufacturer evaluation which
determined that a lower life limit may be necessary for certain
stages 6-10 spools than that allowed in the engine shop manual. The
FAA is issuing this AD to prevent fracture and potential uncontained
failure of the stages 6-10 spools. The unsafe condition, if not
addressed, could result in uncontained debris release, damage to the
engine, and damage to the aircraft.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
At the next piece-part exposure after the effective date of this
AD or before the affected stages 6-10 spool reaches the cyclic
removal threshold specified in paragraph 4., Appendix--A, Table 1 of
GEnx-1B 72-0525, R01 or GEnx-2B SB 72-0460, R01, as applicable,
whichever occurs first, do the following actions:
(1) Inspect the stages 6-10 spool for previously accomplished
blend repairs in accordance with the Accomplishment Instructions,
paragraph 3.B.(1) of GEnx-1B SB 72-0525, R01 or GEnx-2B SB 72-0460,
R01, as applicable.
(2) If during any inspection required by paragraph (g)(1) of
this AD, any stages 6-10 spool is found to have a previously
accomplished blend repair, before further flight, inspect the blend
repair for compliance with the allowable limits in accordance with
the Accomplishment Instructions, paragraph 3.B.(2) of GEnx-1B SB 72-
0525, R01 or GEnx-2B SB 72-0460, R01, as applicable.
(3) If during any inspection required by paragraph (g)(2) of
this AD, any stages 6-10 spool is found to have a previously
accomplished blend repair that is not within the allowable limits,
before further flight, remove the stages 6-10 spool from service and
replace with a part eligible for installation in accordance with the
Accomplishment Instructions, paragraph 3.B.(2)(a)1 or 3.B.(2)(b)1 of
GEnx-1B SB 72-0525, R01 or GEnx-2B SB 72-0460, R01, as applicable.
(h) Definition
For the purposes of this AD:
(1) A ``piece-part exposure'' is when the stages 6-10 spool is
disassembled from the high-pressure compressor rotor assembly.
(2) A ``part eligible for installation'' is either a stages 6-10
spool that does not have a P/N and S/N identified in paragraph 4,
Appendix--A, Table 1 of GEnx-1B 72-0525, R01 or GEnx-2B 72-0460,
R01, or a stages 6-10 spool that does have a P/N and S/N identified
in paragraph 4, Appendix--A, Table 1 of GEnx-1B 72-0525, R01 or
GEnx-2B 72-0460, R01, provided that the affected part is not removed
in accordance with paragraph (g)(3) of this AD.
(i) Credit for Previous Actions
You may take credit for the actions required by paragraph (g) of
this AD if you performed those actions before the effective date of
this AD using GE GEnx-1B Service Bulletin 72-0525, R00, dated
October 4, 2023, or GEnx-2B Service Bulletin 72-0460, R00, dated
October 4, 2023.
(j) Alternative Methods of Compliance (AMOCs)
(1) The Manager, AIR-520 Continued Operational Safety Branch,
FAA, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. In accordance with 14
CFR 39.19, send your request to your principal inspector or local
Flight Standards District Office, as appropriate. If sending
information directly to the manager of the AIR-520 Continued
Operational Safety Branch, send it to the attention of the person
identified in paragraph (k) of this AD and email to: [email protected].
(2) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(k) Related Information
For more information about this AD, contact Alexei Marqueen,
Aviation Safety Engineer, FAA, 2200 South 216th Street, Des Moines,
WA 98198; phone: (781) 238-7178; email: [email protected].
(l) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the material listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this material as applicable to do the actions
required by this AD, unless the AD specifies otherwise.
(i) GE GEnx-1B Service Bulletin 72-0525, R01, dated June 10,
2024.
(ii) GE GEnx-2B Service Bulletin 72-0460, R01, dated June 10,
2024.
(3) For GE material identified in this AD, contact GE 1 Neumann
Way, Cincinnati, OH 45215; phone: (513) 552-3272; email:
ge.com">aviation.fleetsupport@ge.com; website: ge.com.
(4) You may view this material at 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.
[[Page 1365]]
(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/[email protected]">www.archives.gov/federal-register/cfr/[email protected].
Issued on December 6, 2024.
Peter A. White,
Deputy Director, Integrated Certificate Management Division, Aircraft
Certification Service.
[FR Doc. 2025-00208 Filed 1-7-25; 8:45 am]
BILLING CODE 4910-13-P
