[Federal Register Volume 91, Number 11 (Friday, January 16, 2026)]
[Rules and Regulations]
[Pages 2068-2072]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2026-00838]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2025-0744; Project Identifier AD-2024-00586-T;
Amendment 39-23233; AD 2026-01-05]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
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 The Boeing Company Model 757-200 and -300 series airplanes.
This AD was prompted by cracking found during an inspection on an
airplane equipped with Aviation Partners Boeing (APB) scimitar blended
winglets. This AD requires performing a general visual inspection (GVI)
or maintenance records check of certain stringers for an approved
freeze plug repair, performing a high frequency eddy current (HFEC)
inspection of the same area for any crack common to a certain stringer
and a reinforcement strap, and applicable on-condition actions. The FAA
is issuing this AD to address the unsafe condition on these products.
DATES: This AD is effective February 20, 2026.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of February 20,
2026.
ADDRESSES:
AD Docket: You may examine the AD docket at regulations.gov under
Docket No. FAA-2025-0744; 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 APB material identified in this AD, contact Aviation
Partners Boeing, 2811 South 102nd St., Suite 200, Seattle, WA 98168;
phone 206-830-7699; email [email protected]; website
aviationpartnersboeing.com.
You may view this material at the FAA, Airworthiness
Products Section, Operational Safety Branch, 2200 South 216th St., Des
Moines, WA. For
[[Page 2069]]
information on the availability of this material at the FAA, call 206-
231-3195. It is also available at regulations.gov under Docket No. FAA-
2025-0744.
FOR FURTHER INFORMATION CONTACT: Sarah Illg, Aviation Safety Engineer,
FAA, 3960 Paramount Boulevard, Lakewood, CA 90712; phone: 206-231-3517;
email: [email protected].
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to certain The Boeing
Company Model 757-200 and -300 series airplanes. The NPRM was published
in the Federal Register on May 5, 2025 (90 FR 18930). The NPRM was
prompted by a report indicating a crack on a Model 757-200 airplane
equipped with APB scimitar blended winglets found during an HFEC
inspection during accomplishment of a 4C maintenance check. In the
NPRM, the FAA proposed to require a GVI or maintenance records check of
certain stringers for an approved freeze plug repair, an HFEC
inspection of the same area for any crack common to a certain stringer
and a reinforcement strap, and applicable on-condition actions. The FAA
is issuing this AD to address the potential for cracking on the right-
or left-wing lower stringer L-8 or L-6 vertical web flange at a
fastener common to the reinforcement strap.
Discussion of Final Airworthiness Directive
Comments
The FAA received comments from APB and Boeing who supported the
NPRM without change.
The FAA received additional comments from Delta Air Lines (Delta).
The following presents the comments received on the NPRM and the FAA's
response to each comment.
Request To Address Affected AD
Delta requested that the FAA add an exception to paragraph (h) of
the proposed AD stating the proposed AD and APB Service Bulletin AP757-
57-012 both serve as a method of compliance to AD 2020-01-18, Amendment
39-19824 (85 FR 5304, January 30, 2020); corrected February 26, 2020
(85 FR 10969) (AD 2020-01-18). Delta also requested that paragraph (b)
of the proposed AD be revised to reference AD 2020-01-18. Delta noted
that, among other actions, AD 2020-01-18 requires implementation of
airworthiness limitations (AWL) task 57-20-12, which is an inspection
of left- and right-hand lower wing stringers 6 and 8. Delta stated that
if a freeze plug is installed in accordance with APB Service Bulletin
AP757-57-012, it will no longer be feasible to accomplish AWL task 57-
20-12 because some of the material required to be inspected will be
removed and the installed freeze plug and retainer washer will cover up
the area required to be inspected. Delta concluded the proposed AD
would infringe upon the requirements of AD 2020-01-18.
The FAA agrees that installation of a freeze plug repair would
affect accomplishment of AWL task 57-20-12 as required by AD 2020-01-
18. However, the FAA disagrees with adding an exception to paragraph
(h) of this AD and referencing AD 2020-01-18 in paragraph (b) of this
AD. The FAA notes that an alternative method of compliance (AMOC) to AD
2020-01-18 was issued for Model 757-200 and -300 airplanes modified in
accordance with STC ST01518SE to allow accomplishment of AWL task 57-
20-12A, which supplements AWL task 57-20-12 but does not replace it.
Similarly, an operator would need to submit a request for an AMOC to AD
2020-01-18 to address any freeze plug repair that affects
accomplishment AWL task 57-20-12. The FAA has not changed this AD in
this regard.
Request To Add Exception To Clarify Effectivity
Delta requested that the FAA add the following exception to
paragraph (h) of the proposed AD: Where paragraph 1.A.1 of APB Service
Bulletin AP757-57-012, Revision 1, dated October 17, 2024, states
``with winglets or wing tips installed,'' replace that text with ``with
winglets or wing tips installed or on which winglets have been
installed and subsequently removed.'' Delta stated that the effectivity
of the service bulletin does not mention airplanes on which winglets
were installed per Supplemental Type Certificate (STC) ST01518SE and
subsequently removed per APB Service Bulletin AP757-57-001, Revision 1,
dated May 18, 2012. Delta also stated it is unlikely that
accomplishment of APB Service Bulletin AP757-57-001 would restore an
airplane to a configuration where the unsafe condition of the proposed
AD does not exist.
The FAA agrees that the unsafe condition of this AD could exist on
airplanes modified per STC ST01518SE where winglets were never
installed, or winglets were installed and subsequently removed.
However, the FAA disagrees that an exception is needed to address
airplanes that had winglets installed per STC ST01518SE and
subsequently removed. The FAA clarifies that where the effectivity of
APB Service Bulletin AP757-57-012, Revision 1, dated October 17, 2024,
specifies ``or wing tips installed,'' that wording includes airplanes
that were modified per STC ST01518SE and either the winglets were never
installed, or winglets were installed and subsequently removed. The FAA
has not revised the AD in this regard.
Request To Correct Typographical Error
Delta requested that the FAA revise paragraph (h)(5) of the
proposed AD to ``or within 22 months'' to correct a typographical
error.
The FAA agrees and has revised paragraph (h)(5) of this AD
accordingly.
Request To Reference Tables for Existing Freeze Plug Repairs
Delta requested that the FAA add an exception to paragraph (h) of
the proposed AD to point to the appropriate tables for accomplishing
the repetitive surface HFEC inspections for airplanes with a freeze
plug repair done in accordance with APB Service Bulletin AP757-57-012,
Revision 1, dated October 17, 2024. Delta stated that, if a freeze plug
repair is accomplished (per condition 4.2, action 1), then condition
4.2, action 2 of tables 3, 6, 10, and 13 of paragraph 1.E.,
``Compliance,'' and tables 3 and 6 of paragraph 3.B., ``Work
Instructions,'' in the service bulletin specify accomplishing
repetitive surface HFEC inspections, but those tables are applicable to
inspection areas with no existing freeze plug repair. Delta asserted
that condition 4.2, action 2 of tables 3, 6, 10, and 13 in paragraph
1.E. of the service bulletin should specify accomplishing the
repetitive inspections per tables 2, 5, 9, and 12 of paragraph 1.E
because there is now a freeze plug. Similarly, Delta asserted that
condition 4.2, action 2 of tables 3 and 6 in paragraph 3.B. of the
service bulletin should specify accomplishing the repetitive
inspections per tables 2 and 5 of paragraph 3.B.
The FAA agrees that freeze plug repairs accomplished in accordance
with APB Service Bulletin AP757-57-012, Revision 1, dated October 17,
2024, should be considered as existing freeze plug repairs for
repetitive surface HFEC inspections on a per stringer, per wing basis.
However, no change is necessary to this AD because the FAA included
exceptions in the proposed AD that address Delta's request. Those
exceptions are in paragraphs (h)(7) and (8) of this AD, which specify
to use figures 3 and 8, respectively, to
[[Page 2070]]
accomplish the repetitive surface HFEC inspections for condition 4.2,
action 2 in tables 3 and 6, respectively, of the Accomplishment
Instructions of the service bulletin. The FAA notes that tables 2 and 5
of paragraph 3.B also refer to figures 3 and 8, respectively, for the
repetitive surface HFEC inspections. In addition, the FAA has
determined that tables 3, 6, 10, and 13 of paragraph 1.E. do not need
to be revised because those tables provide compliance times for
accomplishing the repetitive surface HFEC inspections, not the
instructions for accomplishing the repetitive inspections.
Request To Provide Instructions for Inspections of Areas With a Freeze
Plug Repair
Delta requested that the FAA add an exception to paragraph (h) of
the proposed AD to provide instructions on how to comply with the
surface HFEC inspections specified in APB Service Bulletin AP757-57-
012, Revision 1, dated October 17, 2024, for areas that have a freeze
plug repair. Delta also stated that the HFEC inspection areas shown in
figure 3 of the service bulletin could be concealed by freeze plug
repairs in the inspection area, which makes the surface HFEC inspection
not possible as written in the service bulletin. Delta noted there are
no instructions for removal of the fastener and retainer washer in
areas with a freeze plug installed and referred to an email from APB
that clarified such instructions.
The FAA agrees to clarify the instructions for accomplishing a
surface HFEC inspection in an area with a freeze plug repair. The
freeze plug retainer washer does not need to be removed. It is
acceptable to perform the surface HFEC inspection around the
circumference of the retainer washer. Accordingly, the FAA has added a
new exception to paragraph (h)(9) of this AD to require the surface
HFEC inspection of the applicable lower stringer vertical web flange
around each fastener, including any washers or freeze plug retainer
washers (washer removal is not required) for any crack.
Request To Clarify Sealant Requirements
Delta requested that the FAA add an exception to paragraph (h) of
the proposed AD to clarify that figures 3 and 8 of APB Service Bulletin
AP757-57-012, Revision 1, dated October 17, 2024, require applying
Boeing Material Specification (BMS) 5-45 or BMS 5-168 sealant. Delta
stated that step 4 of those figures list BMS 5-45 and BMS 5-168 in
separate substeps, which could be misinterpreted to mean that both
sealants need to be applied.
The FAA agrees that only one sealant must be applied under step 4
of figures 3 and 8 of the service bulletin. The FAA has added a new
exception in paragraph (h)(10) of this AD accordingly.
Request To Clarify Retainer Washer Requirements
Delta requested that the FAA add an exception to paragraph (h) of
the proposed AD to clarify the requirement for the retainer washer in
flag note (e) of figures 6 and 11 of APB Service Bulletin AP757-57-012,
Revision 1, dated October 17, 2024. Delta stated the flag note
specifies that the retainer washer must have a 0.15-0.20-inch overlap
with the freeze plug, which can be interpreted as the washer needs to
overlap the freeze plug as opposed to overlapping the surrounding
structure. Delta asserted that the wording in the service bulletin does
not appear to provide a requirement for the outer diameter of the
retainer washer. Delta requested that the requirement instead state
that the retainer washer must be fabricated with a 0.15-0.20-inch
diameter greater than a freeze plug.
The FAA agrees to clarify the requirement for retainer washer
fabrication of in flag note (e) of figures 6 and 11 in the service
bulletin. The FAA has added a new exception in paragraph (h)(12) to
clarify the retainer washer must have a 0.15-0.20-inch radius greater
than the freeze plug.
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 Aviation Partners Boeing Service Bulletin AP757-
57-012 Revision 1, dated October 17, 2024. This material specifies
procedures for performing a GVI or maintenance records check of the
lower stringer L-6 and lower stringer L-8 vertical web flange, between
WS 397.50 and WS 403 for an approved freeze plug repair; a surface HFEC
inspection for cracking of the wing lower stringer L-6 and lower
stringer L-8 vertical web flange, common to the reinforcement strap
attach fasteners located between WS 397.50 and WS 403.00; and
applicable on-condition actions. The on-condition actions include
repetitive surface HFEC inspections for cracking, crack length
measurement, a surface HFEC inspection of the lower stringer L-6 or L-8
vertical web flange around each of the four fasteners for cracks, crack
removal, freeze plug repair, and crack repair.
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 156 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Left- and Right-wing GVI and HFEC 7 work-hours x $85 $0 Up to $595......... Up to $92,820.
Inspection. per hour = $595.
----------------------------------------------------------------------------------------------------------------
The FAA has received no definitive data on which to base the cost
estimates for the on-condition actions specified in this AD.
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.
[[Page 2071]]
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 adding the following new airworthiness
directive:
2026-01-05 The Boeing Company: Amendment 39-23233; Docket No. FAA-
2025-0744; Project Identifier AD-2024-00586-T.
(a) Effective Date
This airworthiness directive (AD) is effective February 20,
2026.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company Model 757-200 and -300
series airplanes, certificated in any category, as specified in
paragraph 1.A.1 of Aviation Partners Boeing Service Bulletin AP757-
57-012, Revision 1, dated October 17, 2024.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Unsafe Condition
This AD was prompted by an operator reporting a crack on a Model
757-200 airplane equipped with Aviation Partners Boeing scimitar
blended winglets. The FAA is issuing this AD to address the
potential for cracking on the right- or left-wing lower stringer L-8
or L-6 vertical web flange at a fastener common to the reinforcement
strap. The unsafe condition, if not addressed, could result in the
inability of a principal structural element to sustain limit loads,
which could adversely affect the structural integrity of the
airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Required Actions
Except as specified in paragraphs (h) and (i) of this AD: At the
applicable times specified in paragraph 1.E., ``Compliance,'' of
Aviation Partners Boeing Service Bulletin AP757-57-012, Revision 1,
dated October 17, 2024, do all applicable actions identified as
``RC'' (required for compliance) in, and in accordance with, the
Accomplishment Instructions of Aviation Partners Boeing Service
Bulletin AP757-57-012, Revision 1, dated October 17, 2024.
(h) Exceptions to Service Bulletin Specifications
(1) Where the Compliance Time columns of the tables in
``Compliance'' paragraph of Aviation Partners Boeing Service
Bulletin AP757-57-012, Revision 1, dated October 17, 2024, refer to
the original issue date of this Service Bulletin, this AD requires
using the effective date of this AD.
(2) Where Table 2 and Table 3 of the ``Compliance'' paragraph of
Aviation Partners Boeing Service Bulletin AP757-57-012, Revision 1,
dated October 17, 2024, specify Action 1 without a compliance time,
for this AD, the compliance time is before 9,500 flight cycles after
the blended winglet installation, within 3,000 flight cycles after
the effective date of this AD, or within 24 months after the
effective date of this AD, whichever occurs later.
(3) Where Table 5 and Table 6 of the ``Compliance'' paragraph of
Aviation Partners Boeing Service Bulletin AP757-57-012, Revision 1,
dated October 17, 2024, specify Action 1 without a compliance time,
for this AD, the compliance time is before 8,000 flight cycles after
the blended winglet installation, within 3,000 flight cycles after
the effective date of this AD, or within 24 months after the
effective date of this AD, whichever occurs later.
(4) Where Table 9 and Table 10 of the ``Compliance'' paragraph
of Aviation Partners Boeing Service Bulletin AP757-57-012, Revision
1, dated October 17, 2024, specify Action 1 without a compliance
time, for this AD, the compliance time is before 9,500 flight cycles
after the blended winglet installation, within 3,000 flight cycles
after the effective date of this AD, or within 22 months after the
effective date of this AD, whichever occurs later.
(5) Where Table 12 and Table 13 of the ``Compliance'' paragraph
of Aviation Partners Boeing Service Bulletin AP757-57-012, Revision
1, dated October 17, 2024, specify Action 1 without a compliance
time, for this AD, the compliance time is before 8,000 flight cycles
after the blended winglet installation, within 3,000 flight cycles
after the effective date of this AD, or within 22 months after the
effective date of this AD, whichever occurs later.
(6) Where Condition 2 of Table 6 in the Accomplishment
Instructions of Aviation Partners Boeing Service Bulletin AP757-57-
012, Revision 1, dated October 17, 2024, includes ``remove crack''
as part of the actions, the action ``remove crack'' is not required
by this AD for Condition 2 of Table 6.
(7) Where Action 2 of Condition 4.2 in Table 3 of the
Accomplishment Instructions of Aviation Partners Boeing Service
Bulletin AP757-57-012, Revision 1, dated October 17, 2024, does not
include a method of compliance for the inspection, for this AD, the
method of compliance is Figure 3 of the Accomplishment Instructions
of Aviation Partners Boeing Service Bulletin AP757-57-012, Revision
1, dated October 17, 2024.
(8) Where Action 2 of Condition 4.2 in Table 6 of the
Accomplishment Instructions of Aviation Partners Boeing Service
Bulletin AP757-57-012, Revision 1, dated October 17, 2024, does not
include a method of compliance for the inspection, for this AD, the
method of compliance is Figure 8 of the Accomplishment Instructions
of Aviation Partners Boeing Service Bulletin AP757-57-012, Revision
1, dated October 17, 2024.
(9) Where flag notes (b) and (c) of Figure 3 and Figure 8 of the
Accomplishment Instructions of Aviation Partners Boeing Service
Bulletin AP757-57-012, Revision 1, dated October 17, 2024, specify
doing a surface high frequency eddy current (HFEC) inspection of the
applicable lower stringer vertical web flange ``around each of the
four fasteners for any crack'', this AD requires replacing that text
with ``around each fastener, including any washers or freeze plug
retainer washers (washer removal is not required) for any crack''.
(10) Where Step 4 of Figure 3 and Figure 8 of the Accomplishment
Instructions of Aviation Partners Boeing Service Bulletin AP757-57-
012, Revision 1, dated October 17, 2024, specifies applying both BMS
5-45 and BMS 5-168 sealants, this AD requires application of either
BMS 5-45 or BMS 5-168 sealant.
(11) Where flag note (b) of Figure 5 and Figure 10 of the
Accomplishment Instructions of Aviation Partners Boeing
[[Page 2072]]
Service Bulletin AP757-57-012, Revision 1, dated October 17, 2024,
specifies ``Maximum hole diameter 0.80 inch'', this AD requires
replacing that text with ``Maximum hole diameter 0.80 inch. Do an
open-hole HFEC inspection of the hole in the stringer in accordance
with 757 NDT Manual Part 6, 51-00-04, 51-00-11, or 51-00-16''.
(12) Where flag note (e) of Figure 6 and Figure 11 of the
Accomplishment Instructions of Aviation Partners Boeing Service
Bulletin AP757-57-012, Revision 1, dated October 17, 2024, specifies
``The retainer washer must have 0.15-0.20 inch overlap with the
freeze plug'', this AD requires replacing that text with ``The
retainer washer must have a 0.15-0.20-inch radius greater than the
freeze plug''.
(13) Where Aviation Partners Boeing Service Bulletin AP757-57-
012, Revision 1, dated October 17, 2024, specifies contacting
Aviation Partners Boeing for repair instructions: This AD requires
repair using a method approved in accordance with the procedures
specified in paragraph (j) of this AD.
(i) No Reporting Requirement
Although Aviation Partners Boeing Service Bulletin AP757-57-012,
Revision 1, dated October 17, 2024, specifies to report existing
repairs, this AD does not require any report.
(j) Alternative Methods of Compliance (AMOCs)
(1) The Manager, West Certification 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 the certification office, send it to the attention of
the person identified in paragraph (k) of this AD. Information may
be emailed to: [email protected]. Before using any approved AMOC, notify
your appropriate principal inspector, or lacking a principal
inspector, the manager of the responsible Flight Standards Office.
(2) Except as specified by paragraph (g) of this AD: For
material that contains steps that are labeled as Required for
Compliance (RC), the provisions of paragraphs (j)(2)(i) and (ii) of
this AD apply.
(i) The steps labeled as RC, including substeps under an RC step
and any figures identified in an RC step, must be done to comply
with the AD. If a step or substep is labeled ``RC Exempt,'' then the
RC requirement is removed from that step or substep. An AMOC is
required for any deviations to RC steps, including substeps and
identified figures.
(ii) Steps not labeled as RC may be deviated from using accepted
methods in accordance with the operator's maintenance or inspection
program without obtaining approval of an AMOC, provided the RC
steps, including substeps and identified figures, can still be done
as specified, and the airplane can be put back in an airworthy
condition.
(k) Additional Information
For more information about this AD, contact Sarah Illg, Aviation
Safety Engineer, FAA, 3960 Paramount Boulevard, Lakewood, CA 90712;
phone: 206-231-3517; email: [email protected].
(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 the AD specifies otherwise.
(i) Aviation Partners Boeing Service Bulletin AP757-57-012,
Revision 1, dated October 17, 2024.
(ii) [Reserved]
(3) For Aviation Partners Boeing material identified in this AD,
contact Aviation Partners Boeing, 2811 South 102nd St., Suite 200,
Seattle, WA 98168; phone 206-830-7699; email
[email protected]; website aviationpartnersboeing.com.
(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 [email protected].
Issued on January 12, 2026.
Steven W. Thompson,
Acting Deputy Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2026-00838 Filed 1-15-26; 8:45 am]
BILLING CODE 4910-13-P