Proposed Rule2026-18752
RIN 2120-AA64
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
September 14, 2026
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA proposes to adopt a new airworthiness directive (AD) for certain CFM International, S.A. (CFM) Model CFM56-5B, CFM56-5C, and CFM56-7B engines with a certain high-pressure turbine (HPT) inner stationary seal installed. This proposed AD was prompted by multiple reports of honeycomb separation from the surface of HPT inner stationary seals. This proposed AD would require initial and repetitive borescope inspections (BSIs) of the rotating air HPT front seal for cracks and, depending on the results, replacement with a part eligible for installation. This proposed AD would also require removal and replacement of the affected HPT inner stationary seal. This proposed AD would also require inspection of the affected HPT inner stationary seal for honeycomb separation and, depending on the results of the inspection, removal and replacement of the rotating air HPT front seal, HPT rotor blades, and No. 3 ball bearing. The FAA is proposing this AD to address the unsafe condition on these products.
Full Text
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<title>Federal Register, Volume 91 Issue 176 (Monday, September 14, 2026)</title>
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[Federal Register Volume 91, Number 176 (Monday, September 14, 2026)]
[Proposed Rules]
[Pages 58042-58046]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2026-18752]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2026-8803; Project Identifier AD-2026-00385-E]
RIN 2120-AA64
Airworthiness Directives; CFM International, S.A. Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for certain CFM International, S.A. (CFM) Model CFM56-5B, CFM56-5C, and
CFM56-7B engines with a certain high-pressure turbine (HPT) inner
stationary seal installed. This proposed AD was prompted by multiple
reports of honeycomb separation from the surface of HPT inner
stationary seals. This proposed AD would require initial and repetitive
borescope inspections (BSIs) of the rotating air HPT front seal for
cracks and, depending on the results, replacement with a part eligible
for installation. This proposed AD would also require removal and
replacement of the affected HPT inner stationary seal. This proposed AD
would also require inspection of the affected HPT inner stationary seal
for honeycomb separation and, depending on the results of the
inspection, removal and replacement of the rotating air HPT front seal,
HPT rotor blades, and No. 3 ball bearing. The FAA is proposing this AD
to address the unsafe condition on these products.
DATES: The FAA must receive comments on this proposed AD by October 29,
2026.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
<bullet> Federal eRulemaking Portal: Go to <a href="http://regulations.gov">regulations.gov</a>. Follow
the instructions for submitting comments.
<bullet> Fax: (202) 493-2251.
<bullet> Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590.
<bullet> Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
AD Docket: You may examine the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2026-8803; 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 NPRM, any comments received, and other
information. The street address for Docket Operations is listed above.
Material Incorporated by Reference:
<bullet> For CFM service material identified in this proposed AD,
contact CFM GE Aviation Fleet Support, 1 Neumann Way, M/D Room 285,
Cincinnati, OH 45125; phone: (877) 432-3272; email:
<a href="/cdn-cgi/l/email-protection#b6d7c0dfd7c2dfd9d898d0dad3d3c2c5c3c6c6d9c4c2f6d1d398d5d9db"><span class="__cf_email__" data-cfemail="dabbacb3bbaeb3b5b4f4bcb6bfbfaea9afaaaab5a8ae9abdbff4b9b5b7">[email protected]</span></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.
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#d8b9b4bda0bdb1f6acf6b5b9aaa9adbdbdb698beb9b9f6bfb7ae"><span class="__cf_email__" data-cfemail="53323f362b363a7d277d3e3221222636363d133532327d343c25">[email protected]</span></a>.
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any written relevant data, views, or
arguments about this proposal. Send your comments using a method listed
under the ADDRESSES section. Include ``Docket No. FAA-2026-8803;
Project Identifier AD-2026-00385-E'' at the beginning of your comments.
The most helpful comments reference a specific portion of the proposal,
explain the reason for any recommended change, and include supporting
data. The FAA will consider all comments received by the closing date
and may revise this proposal because of those comments.
Except for Confidential Business Information (CBI) as described in
the following paragraph, and other
[[Page 58043]]
information as described in 14 CFR 11.35, the FAA will post all
comments received, without change, to <a href="http://regulations.gov">regulations.gov</a>, including any
personal information you provide. The agency will also post a report
summarizing each substantive verbal contact received about this NPRM.
Confidential Business Information
CBI is commercial or financial information that is both customarily
and actually treated as private by its owner. Under the Freedom of
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public
disclosure. If your comments responsive to this NPRM contain commercial
or financial information that is customarily treated as private, that
you actually treat as private, and that is relevant or responsive to
this NPRM, it is important that you clearly designate the submitted
comments as CBI. Please mark each page of your submission containing
CBI as ``PROPIN.'' The FAA will treat such marked submissions as
confidential under the FOIA, and they will not be placed in the public
docket of this NPRM. Submissions containing CBI should be sent to
Alexei Marqueen, Aviation Safety Engineer, FAA, 2200 South 216th
Street, Des Moines, WA 98198. Any commentary that the FAA receives
which is not specifically designated as CBI will be placed in the
public docket for this rulemaking.
Background
The FAA was notified by the manufacturer of multiple reports of
honeycomb separation from the surface of HPT inner stationary seals. A
manufacturer investigation revealed that the affected HPT inner
stationary seal may not have gone through the correct braze repair
process, which could lead to a localized separation of the replaced
honeycomb. This separation could affect the life of the HPT forward
outer seal because missing honeycomb can induce a vibratory response in
the HPT forward outer seal resulting in crack initiation in the seal
teeth that propagate radially. This condition, if not addressed, could
result in uncontained part release, damage to the engine, and damage to
the airplane.
FAA's Determination
The FAA is issuing this NPRM after determining that the unsafe
condition described previously is likely to exist or develop on other
products of the same type design.
Material Incorporated by Reference Under 1 CFR Part 51
The FAA reviewed the following service material:
<bullet> CFM Service Bulletin (SB) SB CFM56-7B S/B 72-1096,
Revision 01, dated January 21, 2026.
<bullet> CFM SB CFM56-5B S/B 72-1129, Revision 01, dated January
21, 2026.
<bullet> CFM SB CFM56-5C S/B 72-0813, Revision 01, dated June 9,
2026.
This service material, differentiated by engine model, specifies
procedures for performing a BSI of the rotating air HPT front seal for
cracks and other damage.
The FAA also reviewed the following service material:
<bullet> CFM SB CFM56-5C S/B 72-0811, Revision 02, dated January
19, 2026.
<bullet> CFM SB CFM56-7B S/B 72-1093, Revision 02, dated January
19, 2026.
<bullet> CFM SB CFM56-5B S/B 72-1125, Revision 02, dated January
19, 2026.
This service material, differentiated by engine model, specifies
procedures for inspecting the HPT inner stationary seal for honeycomb
separation.
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.
Proposed AD Requirements in This NPRM
This proposed AD would require initial and repetitive BSIs of the
rotating air HPT front seal for cracks and other damage and, depending
on the results, replacement with a part eligible for installation. This
proposed AD would also require removal and replacement of the affected
HPT inner stationary seal. This proposed AD would also require
inspection of the affected HPT inner stationary seal for honeycomb
separation and, depending on the results of the inspection, removal and
replacement of the rotating air HPT front seal, HPT rotor blades, and
No. 3 ball bearing.
Costs of Compliance
The FAA estimates that this AD, if adopted as proposed, would
affect 39 engines installed on airplanes of U.S. registry.
The FAA estimates the following costs to comply with this proposed
AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
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BSI of rotating air HPT front seal.... 8 work-hours x $85 per $0 $680 $26,520
hour = $680.
Replacement of HPT inner stationary 8 work-hours x $85 per 173,700 174,380 6,800,820
seal. hour = $680.
Inspection of HPT inner stationary 8 work-hours x $85 per 0 680 26,520
seal. hour = $680.
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The FAA estimates the following costs to do any necessary
replacements that would be required based on the results of the
proposed inspections. The agency has no way of determining the number
of engines that might need these replacements:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Replacement of rotating air HPT front seal.... 8 work-hours x $85 per hour = $601,400 $602,080
$680.
Replacement of HPT rotor blades (set)......... 8 work-hours x $85 per hour = 2,019,320 2,020,000
$680.
Replacement of No. 3 ball bearing............. 8 work-hours x $85 per hour = 70,460 71,140
$680.
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[[Page 58044]]
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
The FAA is issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: General requirements.
Under that section, Congress charges the FAA with promoting safe flight
of civil aircraft in air commerce by prescribing regulations for
practices, methods, and procedures the Administrator finds necessary
for safety in air commerce. This regulation is within the scope of that
authority because it addresses an unsafe condition that is likely to
exist or develop on products identified in this rulemaking action.
Regulatory Findings
The FAA determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 this proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Would not affect intrastate aviation in Alaska, and
(3) Would 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 Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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:
CFM International, S.A.: Docket No. FAA-2026-8803; Project
Identifier AD-2026-00385-E.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by October 29, 2026.
(b) Affected ADs
None.
(c) Applicability
This AD applies to CFM International, S.A. (CFM) Model engines
identified in table 1 to paragraph (c) of this AD with an installed
high-pressure turbine (HPT) inner stationary seal, part number (P/N)
1808M56G01, with a serial number (S/N) listed in Paragraph 4.,
APPENDIX--A, Table 3, of CFM Service Bulletin (SB) CFM56-5B S/B 72-
1125, Revision 02, dated January 19, 2026 (CFM56-5B S/B 72-1125
R02); Paragraph 4., APPENDIX--A, Table 3, of CFM SB CFM56-5C S/B 72-
0811, Revision 02, dated January 19, 2026 (CFM56-5C S/B 72-0811
R02); or Paragraph 4., APPENDIX--A, Table 3, of CFM SB CFM56-7B S/B
72-1093, Revision 02, dated January 19, 2026 (CFM56-7B S/B 72-1093
R02).
Table 1 to Paragraph (c)--CFM Model Engines
------------------------------------------------------------------------
Make Model
------------------------------------------------------------------------
CFM.......................... CFM56-5B1, CFM56-5B1/2P, CFM56-5B1/3,
CFM56-5B1/P, CFM56-5B2, CFM56-5B2/2P,
CFM56-5B2/3, CFM56-5B2/P, CFM56-5B3/2P,
CFM56-5B3/2P1, CFM56-5B3/3, CFM56-5B3/
3B1, CFM56-5B3/P, CFM56-5B3/P1, CFM56-
5B4, CFM56-5B4/2P, CFM56-5B4/2P1, CFM56-
5B4/3, CFM56-5B4/3B1, CFM56-5B4/P, CFM56-
5B4/P1, CFM56-5B5, CFM56-5B5/3, CFM56-
5B5/P, CFM56-5B6, CFM56-5B6/2P, CFM56-
5B6/3, CFM56-5B6/P, CFM56-5B7, CFM56-5B7/
3, CFM56-5B7/P, CFM56-5B8/3, CFM56-5B8/
P, CFM56-5B9/2P, CFM56-5B9/3, CFM56-5B9/
P.
CFM.......................... CFM56-5C2, CFM56-5C2/4, CFM56-5C2/F,
CFM56-5C2/F4, CFM56-5C2/G, CFM56-5C2/G4,
CFM56-5C2/P, CFM56-5C3/F, CFM56-5C3/F4,
CFM56-5C3/G, CFM56-5C3/G4, CFM56-5C3/P,
CFM56-5C4, CFM56-5C4/1, CFM56-5C4/P,
CFM56-5C4/1P.
CFM.......................... CFM56-7B20, CFM56-7B20/2, CFM56-7B20/3,
CFM56-7B20E, CFM56-7B22, CFM56-7B22/2,
CFM56-7B22/3, CFM56-7B22/3B1, CFM56-7B22/
B1, CFM56-7B22E, CFM56-7B22E/B1, CFM56-
7B24, CFM56-7B24/2, CFM56-7B24/3, CFM56-
7B24/3B1, CFM56-7B24/B1, CFM56-7B24E,
CFM56-7B24E/B1, CFM56-7B26, CFM56-7B26/
2, CFM56-7B26/3, CFM56-7B26/3B1, CFM56-
7B26/3B2, CFM56-7B26/3B2F, CFM56-7B26/
3F, CFM56-7B26/B1, CFM56-7B26/B2, CFM56-
7B26E, CFM56-7B26E/B1, CFM56-7B26E/B2,
CFM56-7B26E/B2F, CFM56-7B26E/F, CFM56-
7B27, CFM56-7B27/2, CFM56-7B27/3, CFM56-
7B27/3B1, CFM56-7B27/3B1F, CFM56-7B27/
3B3, CFM56-7B27/3F, CFM56-7B27/B1, CFM56-
7B27/B3, CFM56-7B27A, CFM56-7B27A/3,
CFM56-7B27AE, CFM56-7B27E, CFM56-7B27E/
B1, CFM56-7B27E/B1F, CFM56-7B27E/B3,
CFM56-7B27E/F.
------------------------------------------------------------------------
(d) Subject
Joint Aircraft System Component (JASC) Code 7230, Turbine Engine
Compressor Section.
(e) Unsafe Condition
This AD was prompted by multiple reports of honeycomb separation
from the surface of HPT inner stationary seals. The FAA is issuing
this AD to prevent failure of the HPT inner stationary seal and the
rotating air HPT front seal. The unsafe condition, if not addressed,
could result in uncontained part 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) Definitions
For the purpose of this AD:
(1) Group 1 engines are CFM Model CFM56-5B engines with a
rotating air HPT front seal (HPT front seal) installed having P/N
1795M36P01 or P/N 1795M36P02, and an HPT inner stationary seal
installed having P/N 1808M56G01, with an S/N listed in Paragraph 4.,
APPENDIX--A, Table 1, of CFM56-5B S/B 72-1129, Revision 01, dated
January 21, 2026 (CFM56-5B S/B 72-1129, Revision 01).
(2) Group 2 engines are CFM Model CFM56-5B engines with an HPT
front seal installed having P/N 1795M36P01 or P/N 1795M36P02, and an
HPT inner stationary seal installed having P/N 1808M56G01, with an
S/N listed in Paragraph 4., APPENDIX--A, Table 2, of CFM56-5B S/B
72-1129, Revision 01.
[[Page 58045]]
(3) Group 3 engines are CFM Model CFM56-5C engines with an
installed HPT inner stationary seal, P/N 1808M56G01, with an S/N
listed in Paragraph 4., APPENDIX--A, Table 1, of CFM56-5C S/B 72-
0813, Revision 01, dated June 9, 2026 (CFM56-5C S/B 72-0813,
Revision 01).
(4) Group 4 engines are CFM Model CFM56-7B engines with an HPT
front seal installed having P/N 1795M36P02, and an HPT inner
stationary seal installed having P/N 1808M56G01, with an S/N listed
in Paragraph 4., APPENDIX--A, Table 1, of CFM56-7B S/B 72-1096
Revision 01, dated January 21, 2026 (CFM56-7B S/B 72-1096, Revision
01).
(5) Group 5 engines are CFM Model CFM56-7B engines with an HPT
front seal installed having P/N 1795M36P02 and an HPT inner
stationary seal installed having P/N 1808M56G01, with an S/N listed
in Paragraph 4., APPENDIX--A, Table 2, of CFM56-7B S/B 72-1096
Revision 01.
(6) An ``engine shop visit'' is the induction of an engine into
the shop for maintenance involving the separation of pairs of major
mating engine case flanges, except for the following situations,
which do not constitute an engine shop visit:
(i) Separation of engine flanges solely for the purpose of
transportation of the engine without subsequent maintenance.
(ii) Separation of engine flanges solely for the purpose of
replacing the fan or propulsor without subsequent maintenance.
(7) An ``HPT inner stationary seal that is eligible for
installation'' is an HPT inner stationary seal:
(i) That is not listed in Table 3 of CFM56-5B S/B 72-1125 R02;
Table 3 of CFM56-5C S/B 72-0811 R02; or Table 3 CFM56-7B S/B 72-1093
R02; or
(ii) With P/N 1808M56G01 and an S/N listed in Table 3 of CFM56-
5B S/B 72-1125 R02; Table 3 of CFM56-5C S/B 72-0811 R02; or Table 3
CFM56-7B S/B 72-1093 R02, that has been repaired as specified in
CFM56--5B Engine Shop Manual (ESM), 72--41--03, REPAIR 003; CFM56--
5C ESM, 72--41--03, REPAIR 003; or CFM56--7B ESM, 72--41--03, REPAIR
003, after the repair date listed in Paragraph 4., APPENDIX--A,
Table 3 of CFM56-5B S/B 72-1125 R02, CFM56-5C S/B 72-0811 R02, or
CFM56-7B S/B 72-1093 R02, as applicable by engine model.
(8) A ``rotating air HPT front seal that is eligible for
installation'' is any rotating air HPT front seal that was not
removed from service as a result of paragraph (h)(2) of this AD or
as a result of paragraph (h)(5)(i) of this AD.
(9) ``HPT rotor blades eligible for installation'' are new HPT
rotor blades with zero flight hours since new or HPT rotor blades
that have been inspected and returned to a serviceable condition
using FAA-approved maintenance procedures.
(10) A ``No. 3 ball bearing eligible for installation'' is any
No. 3 ball bearing that was not removed from service as a result of
paragraph (h)(5)(iii) of this AD.
(h) Required Actions
(1) Within the applicable time specified in paragraphs (h)(1)(i)
through (v) of this AD, perform repetitive borescope inspections
(BSI) of the HPT front seal in accordance with the Accomplishment
Instructions, paragraph 3.B of CFM56-5B S/B 72-1129, Revision 01;
CFM56-5C S/B 72-0813, Revision 01; or CFM56-7B S/B 72-1096, Revision
01, as applicable by engine model.
(i) For Group 1 engines, within 400 flight cycles (FCs) after
the effective date of this AD and thereafter at intervals not to
exceed 800 FCs.
(ii) For Group 2 engines, within 300 FCs after the effective
date of this AD and thereafter at intervals not to exceed 800 FCs.
(iii) For Group 3 engines, within 125 FCs after the effective
date of this AD and thereafter at intervals not to exceed 250 FCs.
(iv) For Group 4 engines, within 400 FCs after the effective
date of this AD and thereafter at intervals not to exceed 800 FCs.
(v) For Group 5 engines, within 300 FCs after the effective date
of this AD and thereafter at intervals not to exceed 800 FCs.
(2) If during any BSI required by paragraph (h)(1) of this AD
any crack is detected, before further flight, remove the rotating
air HPT front seal from service and replace with a rotating air HPT
front seal that is eligible for installation.
(3) At the next engine shop visit after the effective date of
this AD, remove the affected HPT inner stationary seal and replace
it with an HPT inner stationary seal that is eligible for
installation.
(4) After removing the affected HPT inner stationary seal
required by paragraph (h)(3) of this AD, inspect the removed HPT
inner stationary seal for honeycomb separation in accordance with
the Accomplishment Instructions, paragraph 3.C.(1), of CFM56-5B S/B
72-1125 R02; CFM56-5C S/B 72-0811 R02; or CFM56-7B S/B 72-1093 R02,
as applicable by engine model.
(5) If honeycomb separation is found during the inspection
required by paragraph (h)(4) of this AD, before further flight:
(i) Remove the rotating air HPT front seal from service and
replace with a rotating air HPT front seal that is eligible for
installation.
(ii) Remove the HPT rotor blades and replace them with HPT rotor
blades eligible for installation.
(iii) Remove the No. 3 ball bearing from service and replace
with a No. 3 ball bearing eligible for installation.
(i) Terminating Action
Accomplishing the actions in paragraphs (h)(3) through (5) of
this AD constitutes terminating action for the repetitive BSIs of
the HPT front seal required by paragraph (h)(1) of this AD.
(j) Installation Prohibition
(1) After the effective date of this AD, do not reinstall any
rotating air HPT front seal that was removed as a result of
paragraphs (h)(2) or (h)(5)(i) of this AD on any engine.
(2) After the effective date of this AD, do not reinstall any
No. 3 ball bearing that was removed as a result of paragraph
(h)(5)(iii) of this AD on any engine.
(k) No Reporting Requirement
Although the service material specifies to submit certain
information to the manufacturer, this AD does not require that
action.
(l) Credit for Previous Actions
You may take credit for the initial BSI specified in paragraph
(h)(1) of this AD if you performed that BSI before the effective
date of this AD using CFM SB CFM56-5C S/B 72-0813, Revision 00,
dated July 15, 2025, CFM56-5B S/B 72-1129 Revision 00, dated July
10, 2025, or CFM56-7B S/B 72-1096 Revision 00, dated July 10, 2025.
You may take credit for the actions specified in paragraphs
(h)(3) through (5) of this AD if you performed those actions before
the effective date of this AD using CFM56-5B S/B 72-1125 Revision
00, dated January 28, 2025; CFM56-5B S/B 72-1125 Revision 01, dated
July 10, 2025; CFM56-5C S/B 72-0811 Revision 00, dated January 28,
2025; CFM56-5C S/B 72-0811 Revision 01, dated July 10, 2025; CFM56-
7B S/B 72-1093 Revision 00, dated January 28, 2025; or CFM56-7B S/B
72-1093 Revision 01, dated July 10, 2025.
(m) 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 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 (n)(1) of this AD and email to: <a href="/cdn-cgi/l/email-protection#5c1d11131f1c3a3d3d723b332a"><span class="__cf_email__" data-cfemail="0f4e42404c4f696e6e21686079">[email protected]</span></a>. 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.
(n) Additional Information
(1) 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#27464b425f424e0953094a465556524242496741464609404851"><span class="__cf_email__" data-cfemail="1a7b767f627f73346e34777b686b6f7f7f745a7c7b7b347d756c">[email protected]</span></a>.
(2) For material identified in this AD that is not incorporated
by reference, contact CFM GE Aviation Fleet Support, 1 Neumann Way,
M/D Room 285, Cincinnati, OH 45125; phone: (877) 432-3272; email:
<a href="/cdn-cgi/l/email-protection#3657405f57425f595818505a535342454346465944427651531855595b"><span class="__cf_email__" data-cfemail="85e4f3ece4f1eceaebabe3e9e0e0f1f6f0f5f5eaf7f1c5e2e0abe6eae8">[email protected]</span></a>.
(o) 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) CFM Service Bulletin (SB) CFM56-5B S/B 72-1125, Revision 02,
dated January 19, 2026.
(ii) CFM SB CFM56-5B S/B 72-1129, Revision 01, dated January 21,
2026.
(iii) CFM SB CFM56-5C S/B 72-0811, Revision 02, dated January
19, 2026.
(iv) CFM SB CFM56-5C S/B 72-0813, Revision 01, dated June 9,
2026.
(v) CFM SB CFM56-7B S/B 72-1093, Revision 02, dated January 19,
2026.
[[Page 58046]]
(vi) CFM SB CFM56-7B S/B 72-1096, Revision 01, dated January 21,
2026.
(3) For CFM material identified in this AD, contact CFM GE
Aviation Fleet Support, 1 Neumann Way, M/D Room 285, Cincinnati, OH
45125; phone: (877) 432-3272; email: <a href="/cdn-cgi/l/email-protection#cfaeb9a6aebba6a0a1e1a9a3aaaabbbcbabfbfa0bdbb8fa8aae1aca0a2"><span class="__cf_email__" data-cfemail="4e2f38272f3a2721206028222b2b3a3d3b3e3e213c3a0e292b602d2123">[email protected]</span></a>.
(4) 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.
(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="http://www.archives.gov/federal-register/cfr/ibr-locations">www.archives.gov/federal-register/cfr/ibr-locations</a> or email <a href="/cdn-cgi/l/email-protection#f89e8ad691968b889d9b8c919796b896998a99d69f978e"><span class="__cf_email__" data-cfemail="6e081c4007001d1e0b0d1a0701002e000f1c0f40090118">[email protected]</span></a>.
Issued on September 10, 2026.
Brian Knaup,
Acting Deputy Director, Integrated Certificate Management Division,
Aircraft Certification Service.
[FR Doc. 2026-18752 Filed 9-11-26; 8:45 am]
BILLING CODE 4910-13-P
</pre><script data-cfasync="false" src="/cdn-cgi/scripts/5c5dd728/cloudflare-static/email-decode.min.js"></script></body>
</html>Indexed from Federal Register on September 14, 2026.
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.