FAA就普惠PW4000系列发动机发布替代适航指令征求意见稿，仅为既有AD的技术性补漏，影响124台在美注册发动机、直接合规成本约458万美元

[4910-13-P]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2026-11811; Project Identifier AD-2026-00667-E]
RIN 2120-AA64
Airworthiness Directives; Pratt & Whitney RTX Corporation (Type Certificate
Previously Held by Pratt & Whitney Division United Technologies Corporation)
Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD) 2026-0902, which applies to certain Pratt & Whitney RTX Corporation (PW) Model PW4074,
PW4074D, PW4077, PW4077D, PW4084D, PW4090, and PW4090-3 engines. AD
2026-09-02 requires repetitive angle ultrasonic scan inspections (AUSIs) of the highpressure compressor (HPC) 15th-stage disks, front turbine hubs, high-pressure turbine
(HPT) 1st-stage air seals, and HPT 2nd-stage hubs for crack indications, and removal
from service and replacement if necessary, and for certain serial numbers, removal from
service and replacement of the HPT 1st-stage air seal. Since the FAA issued AD 202609-02, the FAA was notified that a certain part number was omitted from AD 2026-09-02
and the applicability of the optional terminating action was matched to an unrelated
requirement. This proposed AD would require repetitive AUSIs of the HPC 15th-stage
disks, front turbine hubs, HPT 1st-stage air seals, and HPT 2nd-stage hubs for crack
indications, and removal from service and replacement if necessary, and for certain serial
numbers, removal from service and replacement of the HPT 1st-stage air seal. 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 [INSERT DATE 45
DAYS AFTER DATE OF PUBLICATION IN THE FEDERAL REGISTER].
ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43
and 11.45, by any of the following methods:

• Federal eRulemaking Portal: Go to regulations.gov. Follow the instructions for
submitting comments.
• Fax: (202) 493-2251.
• 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.
• 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 regulations.gov under Docket No. FAA2026-11811; 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:
• For PW material identified in this proposed AD, contact PW, 400 Main Street,
East Hartford, CT 06118; phone: (800) 565-0140; email: help24@prattwhitney.com;
website: connect.prattwhitney.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.
FOR FURTHER INFORMATION CONTACT: Molly Sturgis, Aviation Safety
Engineer, FAA, 2200 South 216th Street, Des Moines, WA 98198; phone: (562) 6275373; email: molly.a.sturgis@faa.gov.
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-2026-11811; Project Identifier AD-2026-00667-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 information as described in 14 CFR 11.35, the FAA will post all
comments received, without change, to regulations.gov, 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 Molly Sturgis,
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 issued AD 2026-09-02, Amendment 39-23322 (91 FR 30191, May 22,
2026) (AD 2026-09-02), for PW Model PW4074, PW4074D, PW4077, PW4077D,
PW4084D, PW4090, and PW4090-3 engines. AD 2026-09-02 was prompted by an
analysis of an event involving an International Aero Engines, LLC (IAE LLC) Model
PW1127GA-JM engine, which experienced an HPC 7th-stage integrally bladed rotor
(IBR-7) separation that resulted in an aborted takeoff. Following this event, the
manufacturer analysis found that the failure of the HPC IBR-7 was caused by a nickel
powdered metal anomaly, similar in nature to an anomaly previously observed. The
analysis also concluded that there is an increased risk of failure for additional nickel

powdered metal parts in certain nickel powdered metal production campaigns, and these
parts are susceptible to failure much earlier than previously determined. AD 2026-09-02
requires repetitive AUSIs of the HPC 15th-stage disks, front turbine hubs, HPT 1st-stage
air seals, and HPT 2nd-stage hubs for crack indications, and removal from service and
replacement if necessary, and for certain serial numbers, removal from service and
replacement of the HPT 1st-stage air seal. The FAA issued AD 2026-09-02 to prevent
failure of the HPC 15th-stage disk, front turbine hub, HPT 1st-stage air seal, and HPT
2nd-stage hub. The unsafe condition, if not addressed, could result in uncontained disk
failure, release of high energy debris, damage to the engine, damage to the airplane, and
possible loss of the airplane.
Actions Since AD 2026-09-02 Was Issued
Since the FAA issued AD 2026-09-02, the FAA has become aware that the
manufacturer revised PW Alert Service Bulletin (ASB) PW4G-112-A72-368, dated June
20, 2024 (PW ASB PW4G-112-A72-368) to include HPT 2nd-stage hub part number
(P/N) 53L402, which was not identified in PW ASB PW4G-112-A72-368 and
inadvertently omitted from AD 2026-09-02. Additionally, the applicability of the optional
terminating action was matched to paragraph (g)(1) of AD 2026-09-02, which is an
unrelated requirement.
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 PW ASB PW4G-112-A72-368, Revision No. 1, dated
September 20, 2024, which specifies procedures for performing repetitive AUSIs on
affected HPT 2nd-stage hubs.
This proposed AD would also require the following material, which the Director
of the Federal Register approved for incorporation by reference as of June 26, 2026 (91
FR 30191, May 22, 2026).

• PW ASB PW4G-112-A72-365, Revision No. 1, dated June 20, 2024, which
specifies procedures for performing repetitive AUSIs on affected HPC 15th-stage disks.
• PW ASB PW4G-112-A72-366, dated June 20, 2024, which specifies procedures
for performing repetitive AUSIs on affected HPT 1st-stage air seals.
• PW ASB PW4G-112-A72-367, dated June 20, 2024, which specifies procedures
for performing repetitive AUSIs on affected front turbine hubs.
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 repetitive AUSIs of the HPC 15th-stage disks,
front turbine hubs, HPT 1st-stage air seals, and HPT 2nd-stage hubs for crack indications,
and removal from service and replacement if necessary. This proposed AD would also
require, for certain serial numbers, removal from service and replacement of the HPT 1ststage air seal.
Costs of Compliance
The FAA estimates that this AD, if adopted as proposed, would affect 124
engines installed on airplanes of U.S. registry. The FAA estimates that 124 engines will
need AUSIs of the HPC 15th-stage disk, front turbine hub, HPT 2nd-stage hub, and HPT
1st-stage air seal; and 6 engines will need replacement of the HPT 1st-stage air seals.
The FAA estimates the following costs to comply with this proposed AD:

Estimated costs
Action

Labor Cost

Parts Cost

AUSI of HPC
15th-stage disk

4 work-hours ×
$85 per hour =
$340
5 work-hours ×
$85 per hour =
$425
5 work-hours ×
$85 per hour =
$425
5 work-hours ×
$85 per hour =
$425
1 work-hour x
$85 per hour =
$85

AUSI of front
turbine hub
AUSI of HPT
2nd-stage hub
AUSI of HPT
1st-stage air
seal
Replace certain
HPT 1st-stage
air seals (6
engines)

$0

Cost per
product
$340

Cost on U.S.
operators
$42,160

$0

$425

$52,700

$0

$425

$52,700

$0

$425

$52,700

$763,000

$763,085

$4,578,510

The FAA estimates the following costs to do any necessary replacements that
would be required based on the results of the proposed inspection. The agency has no
way of determining the number of engines that might need these replacements:
On-condition costs
Action
Replace HPC 15thstage disk
Replace front
turbine hub
Replace HPT 2ndstage hub
Replace HPT 1ststage air seal

Labor Cost
10 work-hours x
$85 per hour =
$850
10 work-hours x
$85 per hour =
$850
10 work-hours x
$85 per hour =
$850
10 work-hours x
$85 per hour =
$850

Parts Cost
$312,000

Cost per product
$312,850

$910,000

$910,850

$816,000

$816,850

$763,000

$763,850

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 that the 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
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 2026-09-02, Amendment 39-23322 (91 FR
30191, May 22, 2026); and

b. Adding the following new airworthiness directive:
Pratt & Whitney RTX Corporation (Type Certificate Previously Held by Pratt &
Whitney Division United Technologies Corporation): Docket No. FAA-2026-11811;
Project Identifier AD-2026-00667-E.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive (AD) by
[INSERT DATE 45 DAYS AFTER DATE OF PUBLICATION IN THE FEDERAL
REGISTER].
(b) Affected ADs
This AD replaces AD 2026-09-02, Amendment 39-23322 (91 FR 30191, May 22,
2026) (AD 2026-09-02).
(c) Applicability
This AD applies to all Pratt & Whitney RTX Corporation (PW) Model PW4074,
PW4074D, PW4077, PW4077D, PW4084D, PW4090, and PW4090-3 engines.
(d) Subject
Joint Aircraft System Component (JASC) Code 7250, Turbine Section; 7230,
Turbine Engine Compressor Section.
(e) Unsafe Condition
This AD was prompted by an analysis of an event involving an International Aero
Engines, LLC Model PW1127GA-JM engine, which experienced a high-pressure
compressor (HPC) 7th-stage integrally bladed rotor separation that resulted in an aborted
takeoff. The FAA is issuing this AD to prevent failure of the HPC 15th-stage disk, front
turbine hub, high-pressure turbine (HPT) 1st-stage air seal, and HPT 2nd-stage hub. The
unsafe condition, if not addressed, could result in uncontained disk failure, release of high
energy debris, damage to the engine, damage to the airplane, and possible loss of the
airplane.
(f) Compliance
Comply with this AD within the compliance times specified, unless already done.

(g) Required Actions
(1) For HPT 1st-stage air seals with a serial number identified in table 1 to
paragraph (g)(1) of this AD: At the next piece part opportunity after the effective date of
this AD, remove the HPT 1st-stage air seal from service and replace with a part eligible
for installation.
Table 1 to paragraph (g)(1) - HPT 1st-Stage Air Seals Affected Serial Numbers
Serial Number

Part Number (P/N)

CKLBME2702

50L663

CKLBME2703

50L663

CKLBME2704

50L663

CKLBME2705

50L663

CKLBME2711

50L663

CKLBMS8019

50L959

(2) At the next piece part opportunity after the effective date of this AD and
thereafter at every piece part opportunity, perform angle ultrasonic scan inspections
(AUSIs) of the HPC 15th-stage disk, front turbine hub, HPT 1st-stage air seal, and HPT
2nd-stage hub for crack indications in accordance with the applicable service material
specified in paragraph (g)(2)(i) through (iv) of this AD.
(i) For HPC 15th-stage disks: Accomplishment Instructions, paragraph 4.A or
4.B., of PW Alert Service Bulletin (ASB) PW4G-112-A72-365, Revision No. 1, dated
June 20, 2024.
(ii) For front turbine hubs: Accomplishment Instructions, paragraph 4.A or 4.B.,
of PW ASB PW4G-112-A72-367, dated June 20, 2024.
(iii) For HPT 1st-stage air seals: Accomplishment Instructions, paragraph 4.A or
4.B., of PW ASB PW4G-112-A72-366, dated June 20, 2024.
(iv) For HPT 2nd-stage hubs: Accomplishment Instructions, paragraph 4.A or
4.B., of PW ASB PW4G-112-A72-368, Revision No. 1, dated September 20, 2024.
(3) If during any inspection required by paragraph (g)(2) of this AD, any crack
indication is found, before further flight, remove the part from service and replace with a
part eligible for installation.

(h) Definitions
For the purpose of this AD:
(1) A “piece part opportunity” is one of the conditions specified in paragraph
(h)(1)(i) through (iv).
(i) The HPC 15th-stage disk is removed from the engine and all blades are
removed.
(ii) The front turbine hub is removed from the engine and all blades are removed.
(iii) The HPT 2nd-stage hub is removed from the engine and all blades are
removed.
(iv) The HPT 1st-stage air seal is fully disassembled from the engine.
(2) A “part eligible for installation” is:
(i) An HPC 15th-stage disk having P/N 51S115, 51S315, 55H615, or 56H015 that
has passed the angle ultrasonic scan inspection (AUSI) required by paragraph (g)(2)(i) of
this AD.
(ii) An HPC 15th-stage disk having P/N 51S115 or 56H015 that has a certificate
of conformance that shows compliance with Non-Destructive Inspection Procedure
(NDIP)-1276.
(iii) An HPC 15th-stage disk having P/N 51S315 or 55H615 that has a certificate
of conformance that shows compliance with NDIP-1289.
(iv) A front turbine hub having P/N 55L801 or 55L901 that has passed the AUSI
required by paragraph (g)(2)(ii) of this AD.
(v) A front turbine hub having P/N 55L801 that has a certificate of conformance
that shows compliance with NDIP-1273.
(vi) A front turbine hub having P/N 55L901 that has a certificate of conformance
that shows compliance with NDIP-1288.
(vii) An HPT 1st-stage air seal having P/N 50L663 or 50L959 that has passed the
AUSI required by paragraph (g)(2)(iii) of this AD.
(viii) An HPT 1st-stage air seal having P/N 50L663 that has a certificate of
conformance that shows compliance with NDIP-1286.

(ix) An HPT 1st-stage air seal having P/N 50L959 that has a certificate of
conformance that shows compliance with NDIP-1287.
(x) An HPT 2nd-stage hub having P/N 53L202, 53L402, or 54L802 that has
passed the AUSI required by paragraph (g)(2)(iv) of this AD.
(xi) An HPT 2nd-stage hub having P/N 53L202 that has a certificate of
conformance that shows compliance with NDIP-1274.
(xii) An HPT 2nd-stage hub having P/N 53L402 or 54L802 that has a certificate
of conformance that shows compliance with NDIP-1275.
(xiii) Any HPC 15th-stage disk, front turbine hub, HPT 1st-stage air seal, or HPT
2nd-stage hub that is new, zero-time, and that has an FAA Form 8130-3 from the original
equipment manufacturer for new production dated July 1, 2025, or later.
(i) Optional Terminating Action - Airworthiness Limitations Section (ALS) Revision
Revising the ALS of the existing engine manual and the operator’s existing
approved maintenance program or inspection program, as applicable, by incorporating
the information in figure 1 to paragraph (i) of this AD, constitutes terminating action for
the actions required by paragraphs (g)(2) and (3) of this AD.

Figure 1 to Paragraph (i) - ALS Additional Inspections
Engine Manuals
P/N 51A345 and 51A751

Chapter / Section 05-10-00
PW4000 SERIES ENGINE
MANUAL ENGINE AIRWORTHINESS
LIMITATIONS - TIME
LIMITS

B. Parts
Requiring
Inspection
DESCRIPTION
Seal - Air, HPT
1st-Stage

CIR MANUAL 51A750
INSPECTION Check-02
Update to include

Hub, Turbine
Front Assembly
(1st-Stage)

TASK 72-52-05-200-001.
1. Non-Destructive Inspection Turbine Front Hub (Stage 1)
Angle Ultrasonic Inspection
(1) Do an Angle Ultrasonic
Inspection for Assembly P/N 55L221
or Detail P/N 55L801 by NDIP-1273
and for Assembly P/N 55L521 or
Detail P/N 55L901 by NDIP-1288.

TASK 72-52-19-200-001.
1. Non-Destructive Inspection - Stage
1 HPT Airseal
Angle Ultrasonic Inspection
(1) Do an Angle Ultrasonic
Inspection for P/N 50L663 by NDIP1286 and for P/N 50L959 by NDIP1287.

P/N 51A345
TASK 05-10-01-990-004.
5. Critical Life Limited
Part Inspection and Critical
Part Inspection.
P/N 51A751
TASK 05-10-01-990-007.
5. Critical Life Limited
Part Inspection and Critical
Part Inspection.
Chapter / Section 05-10-00
PW4000 SERIES ENGINE
MANUAL ENGINE AIRWORTHINESS
LIMITATIONS - TIME
LIMITS
P/N 51A345
TASK 05-10-01-990-004.
5. Critical Life Limited
Part Inspection and Critical
Part Inspection.
P/N 51A751
TASK 05-10-01-990-007
5. Critical Life Limited
Part Inspection and Critical
Part Inspection.

Chapter / Section 05-10-00
PW4000 SERIES ENGINE
MANUAL ENGINE AIRWORTHINESS
LIMITATIONS - TIME
LIMITS

Hub, Turbine
Rear Assembly
(2nd-Stage)

TASK 72-52-06-200-001.
1. Non-Destructive Inspection Turbine Intermediate Hub (Stage 2)
Angle Ultrasonic Inspection
(1) Do an Angle Ultrasonic
Inspection for Assembly P/N 53L232
and Detail P/N 53L202 by NDIP1274 and for Assembly P/N 53L332
and Detail P/N 53L402 or Assembly
P/N 54L832 or 54L932 and Detail
P/N 54L802 by NDIP-1275.

HPC Disk 15thStage

TASK 72-35-92-200-001.
1. Non-Destructive Inspection - HPC
Disk 15th-Stage
Angle Ultrasonic Inspection
(1) Do an Angle Ultrasonic
Inspection for P/N 55H615 and P/N
51S315 by NDIP-1289.
TASK 72-35-92-200-001-A.
1. Non-Destructive Inspection - HPC
Disk 15th-Stage
Angle Ultrasonic Inspection
(1) Do an Angle Ultrasonic
Inspection for P/N 56H015 and P/N
51S115 by NDIP-1276.

P/N 51A345
TASK 05-10-01-990-004.
5. Critical Life Limited
Part Inspection and Critical
Part Inspection.
P/N 51A751
TASK 05-10-01-990-007.
5. Critical Life Limited
Part Inspection and Critical
Part Inspection.
Chapter / Section 05-10-00
PW4000 SERIES ENGINE
MANUAL ENGINE AIRWORTHINESS
LIMITATIONS - TIME
LIMITS
P/N 51A345
TASK 05-10-01-990-004.
5. Critical Life Limited
Part Inspection and Critical
Part Inspection.
P/N 51A751
TASK 05-10-01-990-007.
5. Critical Life Limited
Part Inspection and Critical
Part Inspection.

(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:
AMOC@faa.gov.
(2) Before using any approved AMOC, notify your appropriate principal
inspector, or lacking a principal inspector, the manager of the local flight standards
district office/certificate holding district office.
(k) Additional Information
For more information about this AD, contact Molly Sturgis, Aviation Safety
Engineer, FAA, 2200 South 216th Street, Des Moines, WA 98198; phone: (562) 6275373; email: molly.a.sturgis@faa.gov.
(l) Material Incorporated by Reference
(1) The Director of the Federal Register approved the incorporation by reference
(IBR) of the material listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this material as applicable to do the actions required by this AD,
unless the AD specifies otherwise.
(3) The following material was approved for IBR on [DATE 35 DAYS AFTER
PUBLICATION OF THE FINAL RULE].
(i) Pratt & Whitney RTX Corporation (PW) Alert Service Bulletin (ASB) PW4G112-A72-368, Revision No. 1, dated September 20, 2024.
(ii) [Reserved]
(4) The following material was approved for IBR on June 26, 2026 (91 FR 30191,
May 22, 2026).
(i) PW ASB PW4G-112-A72-365, Revision No. 1, dated June 20, 2024.
(ii) PW ASB PW4G-112-A72-366, dated June 20, 2024.
(iii) PW ASB PW4G-112-A72-367, dated June 20, 2024.

(5) For PW material identified in this AD, contact PW, 400 Main Street, East
Hartford, CT, 06118; phone: (800) 565-0140; email: help24@prattwhitney.com; website:
connect.prattwhitney.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 October 14, 2026.

Lona C. Saccomando,
Acting Deputy Director, Integrated Certificate Management Division,
Aircraft Certification Service.
[FR Doc. 2026-21298 Filed: 10/16/2026 8:45 am; Publication Date: 10/19/2026]