Rule2025-00208
Airworthiness Directives; General Electric Company Engines
Primary source
Metadata and text below are from the Federal Register, a public-domain U.S. government work. Always verify the official published version before relying on it for any legal matter.
Published
January 8, 2025
Effective
February 12, 2025
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
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.
Full Text
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<title>Federal Register, Volume 90 Issue 5 (Wednesday, January 8, 2025)</title>
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[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 [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2025-00208]
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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.
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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 <a href="http://regulations.gov">regulations.gov</a> 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:
<bullet> For GE material identified in this AD, contact GE, 1
Neumann Way, Cincinnati, OH 45215; phone: (513)
[[Page 1362]]
552-3272; email: <a href="/cdn-cgi/l/email-protection#5332253a32273a3c3d7d353f363627202623233c2127136f32733b2136356e" http: ge.com">ge.com</a>">aviation.fleetsupport@<a href="http://ge.com">ge.com</a></a>; website: <a href="http://ge.com">ge.com</a>.
<bullet> 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
<a href="http://regulations.gov">regulations.gov</a> 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: <a href="/cdn-cgi/l/email-protection#7b1a171e031e12550f55161a090a0e1e1e153b1d1a1a551c140d"><span class="__cf_email__" data-cfemail="62030e071a070b4c164c0f0310131707070c220403034c050d14">[email protected]</span></a>.
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to certain 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: <a href="/cdn-cgi/l/email-protection#f7b6b9b2dab6b3dab6bab8b4b7919696d9909881"><span class="__cf_email__" data-cfemail="eaaba4afc7abaec7aba7a5a9aa8c8b8bc48d859c">[email protected]</span></a>.
(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: <a href="/cdn-cgi/l/email-protection#9bfaf7fee3fef2b5efb5f6fae9eaeefefef5dbfdfafab5fcf4ed"><span class="__cf_email__" data-cfemail="4928252c312c20673d6724283b383c2c2c27092f2828672e263f">[email protected]</span></a>.
(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:
<a href="/cdn-cgi/l/email-protection#315047585045585e5f1f575d545445424441415e4345710d5011594354570c" http: ge.com">ge.com</a>">aviation.fleetsupport@<a href="http://ge.com">ge.com</a></a>; website: <a href="http://ge.com">ge.com</a>.
(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 <a href="/cdn-cgi/l/email-protection#e4d885c48c968182d9" http: www.archives.gov federal-register cfr ibr-locationsoremailfr.inspection@nara.gov">www.archives.gov/federal-register/cfr/<span class="__cf_email__" data-cfemail="3d545f4f1051525e5c495452534e524f58505c54515b4f1354534e4d585e495452537d535c4f5c135a524b">[email protected]</span></a>"><a href="http://www.archives.gov/federal-register/cfr/ibr-locationsoremailfr.inspection@nara.gov">www.archives.gov/federal-register/cfr/<span class="__cf_email__" data-cfemail="e9808b9bc485868a889d8086879a869b8c848880858f9bc780879a998c8a9d808687a987889b88c78e869f">[email protected]</span></a></a>.
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
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This is legal information, not legal advice. Laws vary by jurisdiction and change frequently. Always verify current law with official sources and consult a licensed attorney in your jurisdiction for advice on your specific situation.