Airworthiness Directives; CFM International, S.A. Engines, 26195-26198 [2025-11340]
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Federal Register / Vol. 90, No. 117 / Friday, June 20, 2025 / Rules and Regulations
the use potential of an uncalibrated torque
wrench when tightening the union fittings at
the pressure and return interfaces of all three
rudder hydraulic power control units (PCUs).
The FAA is issuing this AD to address union
fittings that could come loose and leak when
improperly torqued. The unsafe condition, if
not addressed, could result in the potential
loss of one or more hydraulic systems.
(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–
2024–13.
(h) Exception To Transport Canada AD CF–
2024–13
(1) Where Transport Canada AD CF–2024–
13 refers to its effective date, this AD requires
using the effective date of this AD.
(2) Where Transport Canada AD CF–2024–
13 refers to hours air time, this AD requires
using flight hours.
(3) Where the material referenced in
Transport Canada AD CF–2024–13 specifies
to ‘‘perform a visual inspection for
hydraulics leaks for all Rudder PCUs coil
tube fitting (Upper, Middle and Lower) in
accordance with to AMP BD500–A–J27–21–
01–01AAA–364B–A’’, this AD requires
replacing that text with ‘‘perform a visual
inspection for hydraulics leaks for all Rudder
PCUs coil tube fittings (Upper, Middle and
Lower) and do all applicable corrective
actions in accordance with AMP BD500–A–
J27–21–01–01AAA–364B–A. Do all
applicable corrective actions before further
flight except as specified in steps 13 and 22
of AMP BD500–A–J27–21–01–01AAA–364B–
A’’.
ddrumheller on DSK120RN23PROD with RULES1
(i) No Reporting Requirement
Although the material referenced in
Transport Canada AD CF–2024–13 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, 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 responsible Flight Standards Office, as
appropriate. If sending information directly
to the manager of AIR–520, Continued
Operational Safety Branch, send it to the
attention of the person identified in
paragraph (k) of this AD and email 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.
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(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, AIR–520, Continued
Operational Safety 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.
(k) Additional Information
For more information about this AD,
contact Brenda L. Buitrago, Aviation Safety
Engineer, FAA, 2200 South 216th St., Des
Moines, WA 98198; phone: 516–288–7368;
email: Brenda.L.Buitrago.Perez@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) Transport Canada AD CF–2024–13,
dated April 29, 2024.
(ii) [Reserved]
(3) For Transport Canada material
identified in this AD, contact Transport
Canada, 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 material 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-locations or email fr.inspection@nara.gov.
Issued on June 12, 2025.
Peter A. White,
Deputy Director, Integrated Certificate
Management Division, Aircraft Certification
Service.
[FR Doc. 2025–11385 Filed 6–18–25; 8:45 am]
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26195
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2024–2668; Project
Identifier AD–2024–00561–E; Amendment
39–23061; AD 2025–12–03]
RIN 2120–AA64
Airworthiness Directives; CFM
International, S.A. Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
The FAA is superseding
Airworthiness Directive (AD) 2023–09–
06, which applied to all CFM
International, S.A. Model (CFM) LEAP–
1A23, LEAP–1A24, LEAP–1A24E1,
LEAP–1A26, LEAP–1A26CJ, LEAP–
1A26E1, LEAP–1A29, LEAP–1A29CJ,
LEAP–1A30, LEAP–1A32, LEAP–1A33,
LEAP–1A33B2, and LEAP–1A35A
(LEAP–1A) engines. AD 2023–09–06
required replacement of certain highpressure turbine (HPT) rotor stage 1
disks (HPT stage 1 disks), forward outer
seals, and compressor rotor stages 6–10
spools. AD 2023–09–06 also prohibited
installation of an HPT stage 1 disk,
forward outer seal, or compressor rotor
stages 6–10 spool that has a part number
and serial number identified in the
service information onto any engine.
Since the FAA issued AD 2023–09–06,
the manufacturer identified additional
affected parts that were manufactured
from material suspected to have reduced
material properties due to iron
inclusion, which prompted this AD.
This AD retains the requirements to
replace certain HPT stage 1 disks,
forward outer seals, and compressor
rotor stages 6–10 spools and expands
the applicability to include additional
affected parts manufactured from the
same material suspected to have
reduced material properties due to iron
inclusion. The FAA is issuing this AD
to address the unsafe condition on these
products.
DATES: This AD is effective July 25,
2025.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of July 25, 2025.
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of June 23, 2023 (88 FR
32092, May 19, 2023).
ADDRESSES:
AD Docket: You may examine the AD
docket at regulations.gov under Docket
SUMMARY:
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Federal Register / Vol. 90, No. 117 / Friday, June 20, 2025 / Rules and Regulations
No. FAA–2024–2668; 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 CFM material identified in 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–
2024–2668.
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:
ddrumheller on DSK120RN23PROD with RULES1
Background
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2023–09–06,
Amendment 39–22429 (88 FR 32092,
May 19, 2023), (AD 2023–09–06). AD
2023–09–06 applied to all CFM Model
LEAP–1A engines. The NPRM was
published in the Federal Register on
December 23, 2024 (89 FR 104462). The
NPRM was prompted by further analysis
by the manufacturer which identified
additional affected parts that were
manufactured from material suspected
to have reduced material properties due
to iron inclusion. In the NPRM, the FAA
proposed to require replacement of
certain HPT stage 1 disks, forward outer
seals, and compressor rotor stages 6–10
spools. In the NPRM, the FAA also
proposed to prohibit installation of an
HPT stage 1 disk, forward outer seal, or
compressor rotor stages 6–10 spool that
has a part number and serial number
identified in the material incorporated
by reference onto any engine. 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
three commenters. Commenters
included the Air Line Pilots
Association, International (ALPA), CFM
international, and StandardAero. ALPA
supported the NPRM without change.
The following presents the comments
received on the NPRM and the FAA’s
response to each comment.
Request To Update Service Material to
Latest Revision
CFM requested that the FAA update
the proposed AD to refer to the latest
revision of CFM Service Bulletin (SB)
LEAP–1A–72–00–0507–01A–930A–D.
CFM noted that CFM SB LEAP–1A–72–
00–0507–01A–930A–D, Issue 001, dated
January 24, 2024 (CFM SB LEAP–1A–
72–00–0507–01A–930A–D, Issue 001) is
being updated to include additional
affected HPT stage 1 disk serial numbers
in Tables 1 through 2.
The FAA agrees and has updated
paragraph (g)(4) of this AD to reference
CFM SB LEAP–1A–72–00–0507–01A–
930A–D, Issue 002, dated April 24, 2025
(CFM SB LEAP–1A–72–00–0507–01A–
930A–D, Issue 002). The FAA has also
updated the language in paragraph (g)(4)
of this AD to refer to ‘‘Tables 1 through
3’’ of CFM SB LEAP–1A–72–00–0507–
01A–930A–D, Issue 002 because Issue
002 includes an additional table with
affected parts. The FAA also added a
Credit for Previous Actions paragraph to
this AD, allowing operators to take
credit for required actions if
accomplished prior to the effective date
of this AD using CFM SB LEAP–1A–72–
00–0507–01A–930A–D, Issue 001. None
of the HPT stage 1 disk serial numbers
referenced in CFM SB LEAP–1A–72–
00–0507–01A–930A–D, Issue 002 are
included in any engine installed on
airplanes of U.S. Registry. Therefore,
this change imposes no additional
burden on operators who are required to
comply with this AD.
Request To Include Thrust Ratings
StandardAero requested that the FAA
revise the proposed AD to include XLR
thrust ratings and reference CFM SB
LEAP–1A–72–00–0529–01A–930A–D.
StandardAero noted that CFM recently
released CFM SB LEAP–1A–72–00–
0529–01A–930A–D, which prohibits the
installation of affected parts into any
XLR rated LEAP–1A engine.
StandardAero also mentioned that it
may be beneficial to expand the scope
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of the NPRM to ensure affected parts are
not installed into these engines at future
shop visits.
The FAA disagrees with the request
because the airworthiness limitations
section of the engine shop manual does
not allow for any of the affected part
serial numbers listed in CFM SB LEAP–
1A–72–00–0529–01A–93 0A–D to be
installed onto an XLR engine. The FAA
did not change this AD as a result of this
comment.
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.
Material Incorporated by Reference
Under 1 CFR Part 51
The FAA reviewed CFM SB LEAP–
1A–72–00–0507–01A–930A–D, Issue
002, dated April 24, 2025, which
identifies the part numbers and serial
numbers of HPT stage 1 disks, forward
outer seals, and compressor rotor stages
6–10 spools with potentially reduced
material properties and specifies
procedures for replacement of these
parts.
This AD also requires the following
material, which the Director of the
Federal Register approved for
incorporation by reference as of June 23,
2023 (88 FR 32092, May 19, 2023):
• CFM Service Bulletin LEAP–1A–
72–00–0470–01A–930A–D, Issue 003,
dated March 3, 2023.
• CFM Service Bulletin LEAP–1A–
72–00–0493–01A–930A–D, Issue 002,
dated November 17, 2022.
• CFM Service Bulletin LEAP–1A–
72–00–0496–01A–930A–D, Issue 001,
dated March 7, 2023.
This material 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.
Costs of Compliance
The FAA estimates that this AD
affects 42 engines installed on airplanes
of U.S. registry.
The FAA estimates the following
costs to comply with this AD:
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Federal Register / Vol. 90, No. 117 / Friday, June 20, 2025 / Rules and Regulations
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ESTIMATED COSTS
Action
Labor cost
Parts cost
Cost per
product
Replace HPT stage 1 disk (42 affected parts) ..
Replace forward outer seal (24 affected parts)
Replace compressor rotor stages 6–10 spool
(15 affected parts).
8 work-hours × $85 per hour = $680 ...
8 work-hours × $85 per hour = $680 ...
8 work-hours × $85 per hour = $680 ...
$215,635 (pro-rated) ......
$47,500 (pro-rated) ........
$37,660 (pro-rated) ........
$216,315
48,180
38,340
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
The FAA is issuing this rulemaking
under the authority described in
Subtitle VII, Part A, Subpart III, Section
44701: General requirements. Under
that section, Congress charges the FAA
with promoting safe flight of civil
aircraft in air commerce by prescribing
regulations for practices, methods, and
procedures the Administrator finds
necessary for safety in air commerce.
This regulation is within the scope of
that authority because it addresses an
unsafe condition that is likely to exist or
develop on products identified in this
rulemaking action.
Regulatory Findings
This AD will not have federalism
implications under Executive Order
13132. This AD will not have a
substantial direct effect on the States, on
the relationship between the national
government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866,
(2) Will not affect intrastate aviation
in Alaska, and
(3) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
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
AD 2023–09–06, Amendment 39–22429
(88 FR 32092, May 19, 2023); and
■ b. Adding the following new
airworthiness directive:
■
■
2025–12–03 CFM International, S.A.:
Amendment 39–23061; Docket No. FAA–
2024–2668; Project Identifier AD–2024–
00561–E.
(a) Effective Date
This airworthiness directive (AD) is
effective July 25, 2025.
(b) Affected ADs
This AD replaces AD 2023–09–06,
Amendment 39–22429 (88 FR 32092, May 19,
2023) (AD 2023–09–06).
(c) Applicability
This AD applies to CFM International, S.A.
Model (CFM) LEAP–1A23, LEAP–1A24,
LEAP–1A24E1, LEAP–1A26, LEAP–1A26CJ,
LEAP–1A26E1, LEAP–1A29, LEAP–1A29CJ,
LEAP–1A30, LEAP–1A32, LEAP–1A33,
LEAP–1A33B2, and LEAP–1A35A engines.
(d) Subject
Joint Aircraft System Component (JASC)
Code 7230, Turbine Engine Compressor
Section; 7250, Turbine Section.
The Amendment
(e) Unsafe Condition
This AD was prompted by a manufacturer
investigation that revealed that certain highpressure turbine (HPT) rotor stage 1 disks
(HPT stage 1 disks), forward outer seals, and
compressor rotor stages 6–10 spools were
manufactured from material suspected to
have reduced material properties due to iron
inclusion. The FAA is issuing this AD to
prevent fracture and consequent uncontained
failure of certain HPT stage 1 disks, forward
outer seals, and compressor rotor stages 6–10
spools. The unsafe condition, if not
addressed, could result in uncontained
debris release, damage to the engine, and
damage to the airplane.
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
List of Subjects in 14 CFR Part 39
ddrumheller on DSK120RN23PROD with RULES1
PART 39—AIRWORTHINESS
DIRECTIVES
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
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Cost on U.S.
operators
$9,085,230
1,156,320
575,100
(g) Required Actions
(1) For engines with an installed HPT stage
1 disk, forward outer seal, or compressor
rotor stages 6–10 spool having a part number
(P/N) and serial number (S/N) identified in
Compliance, paragraph 3.E., Tables 1 through
9, of CFM Service Bulletin (SB) LEAP–1A–
72–00–0496–01A–930A–D, Issue 001, dated
March 7, 2023 (CFM SB LEAP–1A–72–00–
0496–01A–930A–D, Issue 001): At the next
piece-part exposure of the HPT stage 1 disk,
forward outer seal, or compressor rotor stages
6–10 spool, as applicable, or before
exceeding the applicable cycles since new
(CSN) threshold identified in Compliance,
paragraph 3.E., Tables 1 through 9, of CFM
SB LEAP–1A–72–00–0496–01A–930A–D,
Issue 1, whichever occurs first after June 23,
2023 (the effective date of AD 2023–09–06);
or if the applicable CSN threshold has been
exceeded as of June 23, 2023 (the effective
date of AD 2023–09–06), within 50 flight
cycles (FCs) from June 23, 2023 (the effective
date of AD 2023–09–06); remove the HPT
stage 1 disk, forward outer seal, or
compressor rotor stages 6–10 spool, as
applicable, from service and replace with a
part eligible for installation.
(2) For engines with an installed forward
outer seal having a P/N and S/N identified
in Compliance, paragraph 3.E., Tables 1
through 2, of CFM SB LEAP–1A–72–00–
0470–01A–930A–D, Issue 003, dated March
3, 2023 (CFM SB LEAP–1A–72–00–0470–
01A–930A–D, Issue 003): At the next piecepart exposure of the forward outer seal, or
before exceeding the applicable CSN
threshold identified in Compliance,
paragraph 3.E., Tables 1 through 2, of CFM
SB LEAP–1A–72–00–0470–01A–930A–D,
Issue 003, whichever occurs first after June
23, 2023 (the effective date of AD 2023–09–
06); or if the applicable CSN threshold has
been exceeded as of June 23, 2023 (the
effective date of AD 2023–09–06), within 50
FCs from June 23, 2023 (the effective date of
AD 2023–09–06); remove the forward outer
seal from service and replace with a part
eligible for installation.
(3) For engines with an installed HPT stage
1 disk having a P/N and S/N identified in
Compliance, paragraph 3.E., Tables 1 through
2, of CFM SB LEAP–1A–72–00–0493–01A–
930A–D, Issue 002, dated November 17, 2022
(CFM SB LEAP–1A–72–00–0493–01A–930A–
D, Issue 002): At the next piece-part exposure
of the HPT stage 1 disk, or before exceeding
the applicable CSN threshold identified in
Compliance, paragraph 3.E., Tables 1 through
2, of CFM SB LEAP–1A–72–00–0493–01A–
930A–D, Issue 002, whichever occurs first
after June 23, 2023 (the effective date of AD
2023–09–06); or if the applicable CSN
threshold has been exceeded as of June 23,
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2023 (the effective date of AD 2023–09–06),
within 50 FCs from June 23, 2023 (the
effective date of AD 2023–09–06), remove the
HPT stage 1 disk from service and replace
with a part eligible for installation.
(4) For engines with an installed HPT stage
1 disk having a P/N and S/N identified in
Compliance, paragraph 3.E., Tables 1 through
3, of CFM SB LEAP–1A–72–00–0507–01A–
930A–D, Issue 002, dated April 24, 2025
(CFM SB LEAP–1A–72–00–0507–01A–930A–
D, Issue 002): At the next piece-part exposure
of the HPT stage 1 disk, or before exceeding
the applicable CSN threshold identified in
Compliance, paragraph 3.E., Tables 1 through
3, of CFM SB LEAP–1A–72–00–0507–01A–
930A–D, Issue 002, whichever occurs first
after the effective date of this AD; or if the
applicable CSN threshold has been exceeded
as of the effective date of this AD, within 50
FCs from the effective date of this AD;
remove the HPT stage 1 disk from service and
replace with a part eligible for installation.
(h) Definition
For the purpose of this AD, a ‘‘part eligible
for installation’’ is an HPT stage 1 disk,
forward outer seal, or compressor rotor stages
6–10 spool that does not have a P/N and S/
N identified in the service information listed
in paragraphs (g)(1) through (4) of this AD.
(i) Installation Prohibition
After the effective date of this AD, do not
install an HPT stage 1 disk, forward outer
seal, or compressor rotor stages 6–10 spool
that has a P/N and S/N identified in the
service information listed in paragraphs (g)(1)
through (4) of this AD on any engine.
(j) Credit for Previous Actions
You may take credit for the actions
required by paragraph (g)(4) of this AD if you
performed those actions before the effective
date of this AD using CFM SB LEAP–1A–72–
00–0507–01A–930A–D, Issue 001, dated
January 24, 2024.
ddrumheller on DSK120RN23PROD with RULES1
(k) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, AIR–520 Continued
Operational Safety Branch, FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector
or local Flight Standards District Office, as
appropriate. If sending information directly
to the manager of AIR–520 Continued
Operational Safety Branch, send it to the
attention of the person identified in
paragraph (l)(1) of this AD and email to:
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.
(l) Additional Information
(1) For more information about this AD,
contact Mehdi Lamnyi, Aviation Safety
Engineer, FAA, 2200 South 216th Street, Des
Moines, WA 98198; phone: (781) 238–7743;
email: mehdi.lamnyi@faa.gov.
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(2) CFM material that is not incorporated
by reference is available at the address
specified in paragraph (m)(5) of this AD.
(m) 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.
(3) The following material was approved
for IBR on July 25, 2025.
(i) CFM Service Bulletin LEAP–1A–72–00–
0507–01A–930A–D, Issue 002, dated April
24, 2025.
(ii) [Reserved]
(4) The following material was approved
for IBR on June 23, 2023 (88 FR 32092, May
19, 2023).
(i) CFM Service Bulletin LEAP–1A–72–00–
0470–01A–930A–D, Issue 003, dated March
3, 2023.
(ii) CFM Service Bulletin LEAP–1A–72–
00–0493–01A–930A–D, Issue 002, dated
November 17, 2022.
(iii) CFM Service Bulletin LEAP–1A–72–
00–0496–01A–930A–D, Issue 001, dated
March 7, 2023.
(5) For CFM material identified in this AD,
contact CFM International, S.A., GE Aviation
Fleet Support, 1 Neumann Way, M/D Room
285, Cincinnati, OH 45215; phone: (877)
432–3272; email: aviation.fleetsupport@
ge.com.
(6) 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.
(7) 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 June 10, 2025.
Peter A. White,
Deputy Director, Integrated Certificate
Management Division, Aircraft Certification
Service.
[FR Doc. 2025–11340 Filed 6–18–25; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2025–0350; Project
Identifier MCAI–2023–00877–R; Amendment
39–23064; AD 2025–12–06]
RIN 2120–AA64
Airworthiness Directives; Airbus
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
PO 00000
Frm 00006
Fmt 4700
Sfmt 4700
The FAA is adopting a new
airworthiness directive (AD) for all
Airbus Helicopters Model AS332L1
helicopters. This AD was prompted by
a determination that new or more
restrictive airworthiness limitations are
necessary. This AD requires revising the
airworthiness limitations section (ALS)
of the existing maintenance manual
(MM) or instructions for continued
airworthiness (ICAs) and the existing
approved maintenance or inspection
program, as applicable. The FAA is
issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective July 25,
2025.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of July 25, 2025.
ADDRESSES:
AD Docket: You may examine the AD
docket at regulations.gov under Docket
No. FAA–2025–0350; or in person at
Docket Operations between 9 a.m. and
5 p.m., Monday through Friday, except
Federal holidays. The AD docket
contains this final rule, the mandatory
continuing airworthiness information
(MCAI), any comments received, and
other information. The 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 European Union Aviation
Safety Agency (EASA) material
identified in this AD, contact EASA,
Konrad-Adenauer-Ufer 3, 50668
Cologne, Germany; phone: +49 221 8999
000; email: ADs@easa.europa.eu;
website: easa.europa.eu. You may find
the EASA material on the EASA website
at ad.easa.europa.eu.
• You may view this material at the
FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood
Parkway, Room 6N–321, Fort Worth, TX
76177. 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–2025–0350.
FOR FURTHER INFORMATION CONTACT:
Adam Hein, Aviation Safety Engineer,
FAA, 1600 Stewart Avenue, Suite 410,
Westbury, NY 11590; phone: (316) 946–
4116; email: adam.hein@faa.gov.
SUPPLEMENTARY INFORMATION:
SUMMARY:
Background
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to all Airbus Helicopters Model
E:\FR\FM\20JNR1.SGM
20JNR1
]]>Agencies
[Federal Register Volume 90, Number 117 (Friday, June 20, 2025)]
[Rules and Regulations]
[Pages 26195-26198]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2025-11340]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2024-2668; Project Identifier AD-2024-00561-E;
Amendment 39-23061; AD 2025-12-03]
RIN 2120-AA64
Airworthiness Directives; CFM International, S.A. Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2023-09-
06, which applied to all CFM International, S.A. Model (CFM) LEAP-1A23,
LEAP-1A24, LEAP-1A24E1, LEAP-1A26, LEAP-1A26CJ, LEAP-1A26E1, LEAP-1A29,
LEAP-1A29CJ, LEAP-1A30, LEAP-1A32, LEAP-1A33, LEAP-1A33B2, and LEAP-
1A35A (LEAP-1A) engines. AD 2023-09-06 required replacement of certain
high-pressure turbine (HPT) rotor stage 1 disks (HPT stage 1 disks),
forward outer seals, and compressor rotor stages 6-10 spools. AD 2023-
09-06 also prohibited installation of an HPT stage 1 disk, forward
outer seal, or compressor rotor stages 6-10 spool that has a part
number and serial number identified in the service information onto any
engine. Since the FAA issued AD 2023-09-06, the manufacturer identified
additional affected parts that were manufactured from material
suspected to have reduced material properties due to iron inclusion,
which prompted this AD. This AD retains the requirements to replace
certain HPT stage 1 disks, forward outer seals, and compressor rotor
stages 6-10 spools and expands the applicability to include additional
affected parts manufactured from the same material suspected to have
reduced material properties due to iron inclusion. The FAA is issuing
this AD to address the unsafe condition on these products.
DATES: This AD is effective July 25, 2025.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of July 25,
2025.
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of June
23, 2023 (88 FR 32092, May 19, 2023).
ADDRESSES:
AD Docket: You may examine the AD docket at regulations.gov under
Docket
[[Page 26196]]
No. FAA-2024-2668; 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 CFM material identified in AD, contact CFM, GE
Aviation Fleet Support, 1 Neumann Way, M/D Room 285, Cincinnati, OH
45215; phone: (877) 432-3272; email: [email protected].
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-2024-2668.
FOR FURTHER INFORMATION CONTACT: Mehdi Lamnyi, Aviation Safety
Engineer, FAA, 2200 South 216th Street, Des Moines, WA 98198; phone:
(781) 238-7743; email: [email protected].
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2023-09-06, Amendment 39-22429 (88 FR
32092, May 19, 2023), (AD 2023-09-06). AD 2023-09-06 applied to all CFM
Model LEAP-1A engines. The NPRM was published in the Federal Register
on December 23, 2024 (89 FR 104462). The NPRM was prompted by further
analysis by the manufacturer which identified additional affected parts
that were manufactured from material suspected to have reduced material
properties due to iron inclusion. In the NPRM, the FAA proposed to
require replacement of certain HPT stage 1 disks, forward outer seals,
and compressor rotor stages 6-10 spools. In the NPRM, the FAA also
proposed to prohibit installation of an HPT stage 1 disk, forward outer
seal, or compressor rotor stages 6-10 spool that has a part number and
serial number identified in the material incorporated by reference onto
any engine. 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 three commenters. Commenters
included the Air Line Pilots Association, International (ALPA), CFM
international, and StandardAero. ALPA supported the NPRM without
change. The following presents the comments received on the NPRM and
the FAA's response to each comment.
Request To Update Service Material to Latest Revision
CFM requested that the FAA update the proposed AD to refer to the
latest revision of CFM Service Bulletin (SB) LEAP-1A-72-00-0507-01A-
930A-D. CFM noted that CFM SB LEAP-1A-72-00-0507-01A-930A-D, Issue 001,
dated January 24, 2024 (CFM SB LEAP-1A-72-00-0507-01A-930A-D, Issue
001) is being updated to include additional affected HPT stage 1 disk
serial numbers in Tables 1 through 2.
The FAA agrees and has updated paragraph (g)(4) of this AD to
reference CFM SB LEAP-1A-72-00-0507-01A-930A-D, Issue 002, dated April
24, 2025 (CFM SB LEAP-1A-72-00-0507-01A-930A-D, Issue 002). The FAA has
also updated the language in paragraph (g)(4) of this AD to refer to
``Tables 1 through 3'' of CFM SB LEAP-1A-72-00-0507-01A-930A-D, Issue
002 because Issue 002 includes an additional table with affected parts.
The FAA also added a Credit for Previous Actions paragraph to this AD,
allowing operators to take credit for required actions if accomplished
prior to the effective date of this AD using CFM SB LEAP-1A-72-00-0507-
01A-930A-D, Issue 001. None of the HPT stage 1 disk serial numbers
referenced in CFM SB LEAP-1A-72-00-0507-01A-930A-D, Issue 002 are
included in any engine installed on airplanes of U.S. Registry.
Therefore, this change imposes no additional burden on operators who
are required to comply with this AD.
Request To Include Thrust Ratings
StandardAero requested that the FAA revise the proposed AD to
include XLR thrust ratings and reference CFM SB LEAP-1A-72-00-0529-01A-
930A-D. StandardAero noted that CFM recently released CFM SB LEAP-1A-
72-00-0529-01A-930A-D, which prohibits the installation of affected
parts into any XLR rated LEAP-1A engine. StandardAero also mentioned
that it may be beneficial to expand the scope of the NPRM to ensure
affected parts are not installed into these engines at future shop
visits.
The FAA disagrees with the request because the airworthiness
limitations section of the engine shop manual does not allow for any of
the affected part serial numbers listed in CFM SB LEAP-1A-72-00-0529-
01A-93 0A-D to be installed onto an XLR engine. The FAA did not change
this AD as a result of this comment.
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.
Material Incorporated by Reference Under 1 CFR Part 51
The FAA reviewed CFM SB LEAP-1A-72-00-0507-01A-930A-D, Issue 002,
dated April 24, 2025, which identifies the part numbers and serial
numbers of HPT stage 1 disks, forward outer seals, and compressor rotor
stages 6-10 spools with potentially reduced material properties and
specifies procedures for replacement of these parts.
This AD also requires the following material, which the Director of
the Federal Register approved for incorporation by reference as of June
23, 2023 (88 FR 32092, May 19, 2023):
CFM Service Bulletin LEAP-1A-72-00-0470-01A-930A-D, Issue
003, dated March 3, 2023.
CFM Service Bulletin LEAP-1A-72-00-0493-01A-930A-D, Issue
002, dated November 17, 2022.
CFM Service Bulletin LEAP-1A-72-00-0496-01A-930A-D, Issue
001, dated March 7, 2023.
This material 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.
Costs of Compliance
The FAA estimates that this AD affects 42 engines installed on
airplanes of U.S. registry.
The FAA estimates the following costs to comply with this AD:
[[Page 26197]]
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Replace HPT stage 1 disk (42 8 work-hours x $85 $215,635 (pro-rated)............. $216,315 $9,085,230
affected parts). per hour = $680.
Replace forward outer seal (24 8 work-hours x $85 $47,500 (pro-rated).............. 48,180 1,156,320
affected parts). per hour = $680.
Replace compressor rotor stages 8 work-hours x $85 $37,660 (pro-rated).............. 38,340 575,100
6-10 spool (15 affected parts). 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 the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
The FAA is issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: General requirements.
Under that section, Congress charges the FAA with promoting safe flight
of civil aircraft in air commerce by prescribing regulations for
practices, methods, and procedures the Administrator finds necessary
for safety in air commerce. This regulation is within the scope of that
authority because it addresses an unsafe condition that is likely to
exist or develop on products identified in this rulemaking action.
Regulatory Findings
This AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States,
on the relationship between the national government and the States, or
on the distribution of power and responsibilities among the various
levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Will not affect intrastate aviation in Alaska, and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by:
0
a. Removing Airworthiness Directive AD 2023-09-06, Amendment 39-22429
(88 FR 32092, May 19, 2023); and
0
b. Adding the following new airworthiness directive:
2025-12-03 CFM International, S.A.: Amendment 39-23061; Docket No.
FAA-2024-2668; Project Identifier AD-2024-00561-E.
(a) Effective Date
This airworthiness directive (AD) is effective July 25, 2025.
(b) Affected ADs
This AD replaces AD 2023-09-06, Amendment 39-22429 (88 FR 32092,
May 19, 2023) (AD 2023-09-06).
(c) Applicability
This AD applies to CFM International, S.A. Model (CFM) LEAP-
1A23, LEAP-1A24, LEAP-1A24E1, LEAP-1A26, LEAP-1A26CJ, LEAP-1A26E1,
LEAP-1A29, LEAP-1A29CJ, LEAP-1A30, LEAP-1A32, LEAP-1A33, LEAP-
1A33B2, and LEAP-1A35A engines.
(d) Subject
Joint Aircraft System Component (JASC) Code 7230, Turbine Engine
Compressor Section; 7250, Turbine Section.
(e) Unsafe Condition
This AD was prompted by a manufacturer investigation that
revealed that certain high-pressure turbine (HPT) rotor stage 1
disks (HPT stage 1 disks), forward outer seals, and compressor rotor
stages 6-10 spools were manufactured from material suspected to have
reduced material properties due to iron inclusion. The FAA is
issuing this AD to prevent fracture and consequent uncontained
failure of certain HPT stage 1 disks, forward outer seals, and
compressor rotor stages 6-10 spools. The unsafe condition, if not
addressed, could result in uncontained debris release, damage to the
engine, and damage to the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
(1) For engines with an installed HPT stage 1 disk, forward
outer seal, or compressor rotor stages 6-10 spool having a part
number (P/N) and serial number (S/N) identified in Compliance,
paragraph 3.E., Tables 1 through 9, of CFM Service Bulletin (SB)
LEAP-1A-72-00-0496-01A-930A-D, Issue 001, dated March 7, 2023 (CFM
SB LEAP-1A-72-00-0496-01A-930A-D, Issue 001): At the next piece-part
exposure of the HPT stage 1 disk, forward outer seal, or compressor
rotor stages 6-10 spool, as applicable, or before exceeding the
applicable cycles since new (CSN) threshold identified in
Compliance, paragraph 3.E., Tables 1 through 9, of CFM SB LEAP-1A-
72-00-0496-01A-930A-D, Issue 1, whichever occurs first after June
23, 2023 (the effective date of AD 2023-09-06); or if the applicable
CSN threshold has been exceeded as of June 23, 2023 (the effective
date of AD 2023-09-06), within 50 flight cycles (FCs) from June 23,
2023 (the effective date of AD 2023-09-06); remove the HPT stage 1
disk, forward outer seal, or compressor rotor stages 6-10 spool, as
applicable, from service and replace with a part eligible for
installation.
(2) For engines with an installed forward outer seal having a P/
N and S/N identified in Compliance, paragraph 3.E., Tables 1 through
2, of CFM SB LEAP-1A-72-00-0470-01A-930A-D, Issue 003, dated March
3, 2023 (CFM SB LEAP-1A-72-00-0470-01A-930A-D, Issue 003): At the
next piece-part exposure of the forward outer seal, or before
exceeding the applicable CSN threshold identified in Compliance,
paragraph 3.E., Tables 1 through 2, of CFM SB LEAP-1A-72-00-0470-
01A-930A-D, Issue 003, whichever occurs first after June 23, 2023
(the effective date of AD 2023-09-06); or if the applicable CSN
threshold has been exceeded as of June 23, 2023 (the effective date
of AD 2023-09-06), within 50 FCs from June 23, 2023 (the effective
date of AD 2023-09-06); remove the forward outer seal from service
and replace with a part eligible for installation.
(3) For engines with an installed HPT stage 1 disk having a P/N
and S/N identified in Compliance, paragraph 3.E., Tables 1 through
2, of CFM SB LEAP-1A-72-00-0493-01A-930A-D, Issue 002, dated
November 17, 2022 (CFM SB LEAP-1A-72-00-0493-01A-930A-D, Issue 002):
At the next piece-part exposure of the HPT stage 1 disk, or before
exceeding the applicable CSN threshold identified in Compliance,
paragraph 3.E., Tables 1 through 2, of CFM SB LEAP-1A-72-00-0493-
01A-930A-D, Issue 002, whichever occurs first after June 23, 2023
(the effective date of AD 2023-09-06); or if the applicable CSN
threshold has been exceeded as of June 23,
[[Page 26198]]
2023 (the effective date of AD 2023-09-06), within 50 FCs from June
23, 2023 (the effective date of AD 2023-09-06), remove the HPT stage
1 disk from service and replace with a part eligible for
installation.
(4) For engines with an installed HPT stage 1 disk having a P/N
and S/N identified in Compliance, paragraph 3.E., Tables 1 through
3, of CFM SB LEAP-1A-72-00-0507-01A-930A-D, Issue 002, dated April
24, 2025 (CFM SB LEAP-1A-72-00-0507-01A-930A-D, Issue 002): At the
next piece-part exposure of the HPT stage 1 disk, or before
exceeding the applicable CSN threshold identified in Compliance,
paragraph 3.E., Tables 1 through 3, of CFM SB LEAP-1A-72-00-0507-
01A-930A-D, Issue 002, whichever occurs first after the effective
date of this AD; or if the applicable CSN threshold has been
exceeded as of the effective date of this AD, within 50 FCs from the
effective date of this AD; remove the HPT stage 1 disk from service
and replace with a part eligible for installation.
(h) Definition
For the purpose of this AD, a ``part eligible for installation''
is an HPT stage 1 disk, forward outer seal, or compressor rotor
stages 6-10 spool that does not have a P/N and S/N identified in the
service information listed in paragraphs (g)(1) through (4) of this
AD.
(i) Installation Prohibition
After the effective date of this AD, do not install an HPT stage
1 disk, forward outer seal, or compressor rotor stages 6-10 spool
that has a P/N and S/N identified in the service information listed
in paragraphs (g)(1) through (4) of this AD on any engine.
(j) Credit for Previous Actions
You may take credit for the actions required by paragraph (g)(4)
of this AD if you performed those actions before the effective date
of this AD using CFM SB LEAP-1A-72-00-0507-01A-930A-D, Issue 001,
dated January 24, 2024.
(k) Alternative Methods of Compliance (AMOCs)
(1) The Manager, AIR-520 Continued Operational Safety Branch,
FAA, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. In accordance with 14
CFR 39.19, send your request to your principal inspector or local
Flight Standards District Office, as appropriate. If sending
information directly to the manager of AIR-520 Continued Operational
Safety Branch, send it to the attention of the person identified in
paragraph (l)(1) 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.
(l) Additional Information
(1) For more information about this AD, contact Mehdi Lamnyi,
Aviation Safety Engineer, FAA, 2200 South 216th Street, Des Moines,
WA 98198; phone: (781) 238-7743; email: [email protected].
(2) CFM material that is not incorporated by reference is
available at the address specified in paragraph (m)(5) of this AD.
(m) 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.
(3) The following material was approved for IBR on July 25,
2025.
(i) CFM Service Bulletin LEAP-1A-72-00-0507-01A-930A-D, Issue
002, dated April 24, 2025.
(ii) [Reserved]
(4) The following material was approved for IBR on June 23, 2023
(88 FR 32092, May 19, 2023).
(i) CFM Service Bulletin LEAP-1A-72-00-0470-01A-930A-D, Issue
003, dated March 3, 2023.
(ii) CFM Service Bulletin LEAP-1A-72-00-0493-01A-930A-D, Issue
002, dated November 17, 2022.
(iii) CFM Service Bulletin LEAP-1A-72-00-0496-01A-930A-D, Issue
001, dated March 7, 2023.
(5) For CFM material identified in this AD, contact CFM
International, S.A., GE Aviation Fleet Support, 1 Neumann Way, M/D
Room 285, Cincinnati, OH 45215; phone: (877) 432-3272; email:
[email protected].
(6) 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.
(7) 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 June 10, 2025.
Peter A. White,
Deputy Director, Integrated Certificate Management Division, Aircraft
Certification Service.
[FR Doc. 2025-11340 Filed 6-18-25; 8:45 am]
BILLING CODE 4910-13-P
