Airworthiness Directives; The Boeing Company Airplanes

[Federal Register Volume 91, Number 155 (Thursday, August 13, 2026)]
[Rules and Regulations]
[Pages 52223-52231]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2026-16504]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2026-0023; Project Identifier AD-2025-00427-T; 
Amendment 39-23436; AD 2026-16-06]
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 superseding Airworthiness Directive (AD) 2018-11-
14, which applied to certain The Boeing Company Model 767-300 and -300F 
series airplanes with certain winglets installed. AD 2018-11-14 
required high frequency eddy current (HFEC) inspections for cracking of 
the lower outboard wing skin and repair or modification if necessary. 
AD 2018-11-14 also required one of three follow-on actions: Repeating 
the HFEC inspections; modifying certain internal stringers and 
oversizing and plugging the existing fastener holes of the lower wing; 
or modifying the external doubler/tripler and doing repetitive post-
modification inspections. This AD was prompted by reports of fatigue 
cracking in the lower outboard wing skin at the inboard fastener of 
stringer L-9.5, and the lower outboard wing skin of stringer L-6.5, on 
airplanes with winglets installed per Supplemental Type Certificate 
(STC) ST01920SE. This AD was also prompted by a determination that, for 
certain airplanes, the area of the lower wing skin in the vicinity of 
the critical inboard end fasteners of installed repair doublers must be 
inspected. This AD continues to require the actions in AD 2018-11-14, 
adds to the applicability airplanes that have had STC ST01920SE 
installed and the STC winglets removed, and, for certain airplanes, 
requires repetitive internal and external HFEC inspections of the lower 
outboard wing skin common to the external doubler repair at stringer L-
9.5 and repair if necessary. The FAA is issuing this AD to address the 
unsafe condition on these products.

DATES: This AD is effective September 17, 2026.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of September 17, 
2026.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of July 
10, 2018 (83 FR 25885, June 5, 2018).

ADDRESSES: 
    AD Docket: You may examine the AD docket at regulations.gov under 
Docket No. FAA-2026-0023; 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 Aviation Partners Boeing material identified in this 
AD, contact Aviation Partners Boeing, 555 Andover Park West, Suite 200, 
Tukwila, Washington 98188; telephone 206-830-7699; email 
[email protected]; website aviationpartnersboeing.com.
    <bullet> 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. It is also available at regulations.gov under 
Docket No. FAA-2026-0023.

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 to supersede AD 2018-11-14, Amendment 39-19302 (83 FR 
25885, June 5, 2018) (AD 2018-11-14). AD 2018-11-14 applied to certain 
The Boeing Company Model 767-300 and -300F series airplanes with 
Aviation Partners Boeing (APB) winglets installed. The NPRM was 
published in the Federal Register on January 26, 2026 (91 FR 3084). The 
NPRM was prompted by reports of fatigue cracking in the lower outboard 
wing skin at the inboard fastener of stringer L-9.5, and the lower 
outboard wing skin of stringer L-6.5, on airplanes with winglets 
installed per STC ST01920SE. The NPRM was also prompted by a 
determination that, for certain airplanes, the area of the lower wing 
skin in the vicinity of the critical inboard end fasteners of installed 
repair doublers must be inspected. The FAA is issuing this AD to 
prevent fatigue cracking in the lower outboard wing skin. The

[[Page 52224]]

unsafe condition, if not addressed, could result in failure and 
subsequent separation of the wing and winglet and consequent reduced 
controllability of the airplane.

Discussion of Final Airworthiness Directive

Comments

    The FAA received comments from United Airlines and two commenters 
who supported the NPRM without change.
    The FAA received additional comments from five commenters, 
including APB, Boeing, Delta Air Lines (Delta), FedEx, and Obelisk Tech 
Systems Inc. The following presents the comments received on the NPRM 
and the FAA's response to each comment.

Request To Revise the Applicability

    Boeing requested that the FAA revise paragraph (c) of the proposed 
AD by adding that the AD is not applicable to Model 767-300 and -300F 
series airplanes on which STC ST01920SE has never been installed. 
Boeing noted that paragraph (c) of the proposed AD refers to paragraph 
1.A.1 of Aviation Partners Boeing Service Bulletin AP767-57-010, 
Revision 14, dated November 17, 2025; and AP767-57-014, Revision 3, 
dated November 17, 2025; for the airplane applicability, but the 
service information lists airplane groups based on which APB kits have 
been installed instead of identifying individual airplanes. Boeing also 
stated that the referenced service information is unavailable to 
operators who have not purchased the APB STC. Boeing concluded this 
places a burden on operators to demonstrate that they are not affected 
by the proposed AD.
    APB requested that the FAA revise paragraph (c) of the proposed AD 
by adding that the AD applies to Model 767-300 and -300F series 
airplanes with STC ST01920SE incorporated. APB stated this change 
addresses Boeing's request without adding an exemption to the 
applicability of the proposed rule.
    The FAA agrees to clarify the applicability. The effectivity 
(paragraph 1.A.1) of the referenced APB service information specifies 
it applies to Model 767-300 and -300F airplanes provisioned for blended 
winglets modified in accordance with STC ST01920SE, with or without 
winglets installed. Therefore, the FAA has revised paragraph (c) of 
this AD to clarify that this AD is applicable to Model 767-300 and -
300F airplanes provisioned for blended winglets modified in accordance 
with STC ST01920SE, with or without winglets installed.

Request To Reduce the Compliance Time

    Obelisk Tech Systems Inc. requested that the FAA reduce the 
compliance time of the proposed AD. The commenter stated that the 
affected airplanes are not airworthy, and that non-compliant airplanes 
must be grounded within 30 days and not be given an extended compliance 
period.
    Boeing requested that the FAA revise paragraph (k) of the proposed 
AD to require that the new requirements for Group 3 airplanes be 
accomplished within 3,000 flight cycles after the effective date of 
this AD. Boeing stated that the fleet finding showing additional 
inspection requirements were needed for Group 3 airplanes also showed 
the threshold to start the inspections was not adequate and should be 
reduced. Boeing asserted that limiting the threshold inspection to 
within 3,000 flight cycles after the effective date of the AD would 
adequately address this issue.
    The FAA does not agree to change the compliance time. The FAA has 
determined that the threshold and intervals identified in the APB 
service information for Group 3 airplanes is adequate for addressing 
the unsafe condition. APB has not provided the FAA with any new 
analysis that showed those thresholds and intervals need to be adjusted 
if the repairs were installed correctly. The grace period of 3,000 
flight cycles for those airplanes that are past the applicable 
thresholds identified in the service information is adequate. The FAA 
did not change this AD as a result of this comment.

Request To Clarify the Reporting Requirement

    Delta requested that the FAA clarify whether certain notes in the 
APB service information require operators to report all inspection 
findings at the specified inspection interval or to only report if 
cracks are found. Delta stated that those notes are not identified as 
Required for Compliance (RC).
    The FAA agrees that the notes in the APB service information that 
specify to report inspection results to APB are not identified as RC 
steps and, therefore, not required for compliance with this AD. If an 
operator wishes to voluntarily report findings, the FAA recommends they 
contact APB for clarification. The FAA did not change this AD as a 
result of this comment.

Request To Correct Certain Paragraph References

    APB and FedEx requested that the FAA correct a typographical error 
in paragraph (m)(1) of the proposed AD by replacing the reference to 
paragraph (o)(3) with paragraph (m)(3). The commenters also requested 
the reference to paragraph (o)(3) be removed from paragraphs (m)(2)(ii) 
and (m)(3)(ii) of the proposed AD. FedEx stated that paragraph (o)(3) 
is not defined in the NPRM.
    APB further requested that the FAA correct a typographical error in 
paragraph (m)(3) by replacing the reference to paragraph (m)(2)(ii) 
with paragraph (m)(3)(ii).
    The FAA agrees and has revised paragraphs (m)(1), (m)(2)(ii), 
(m)(3), and (m)(3)(ii) of this AD, accordingly.

Request To Revise APB's Address

    APB requested that the FAA revise paragraph (s)(5) of the proposed 
AD to reference APB's current address: 555 Andover Park West, Suite 
200, Tukwila, Washington 98188.
    The FAA agrees and has revised the ADDRESSES section and paragraph 
(s)(5) of this AD, accordingly.

Request To Require Other Methods of Compliance

    Obelisk Tech Systems Inc. requested that the FAA recognize 
commercial-off-the-shelf (COTS) alternatives and engage small defense 
contractors with COTS solutions. The commenter stated that true cost of 
compliance, which includes revenue lost, maintenance repair operations 
(MRO) scheduling, parts procurement, and management time, is 1,500 to 
3,300 percent above the FAA's disclosed estimate. The commenter further 
stated its drone-based nondestructive inspections (NDI) and artificial 
intelligence (AI) diagnostics reduce the per-airplane compliance time 
by 40 to 70 percent.
    Obelisk Tech Systems Inc. demands sole-source engagement under 41 
U.S.C. 3304(a)(1) and 10 U.S.C. 3204(a)(1) for drone-based NDI 
inspection, AI diagnostic technology, and compliance support via GSA 
commercial catalog. The commenter stated that it qualifies under the 
urgency exception of Federal Acquisitions Regulation (FAR) 6.302-2, and 
that the GSA catalog provides a compliant immediate procurement 
vehicle. The commenter also stated the ``DoD shall issue task orders to 
Obelisk for military Boeing AD compliance under OTA or rapid 
acquisition authority.'' Obelisk Tech Systems Inc. further stated that 
the proposed AD with understated expected harm and extended timeline 
violates State Farm, 463 U.S. 29 (1983).
    The FAA does not agree to revise this AD to require a different 
method of compliance. Under the provisions of

[[Page 52225]]

paragraph (q) of this AD, anyone may request an alternative method of 
compliance (AMOC) for accomplishing the inspections required by this 
AD. Alternative inspections methods may be allowed if they provide an 
acceptable level of safety. Further, operators are private entities 
that may engage with the businesses and technologies they choose to 
work with.
    The FAA infers that the commenter requests the FAA revise the Costs 
of Compliance section to account for indirect costs, such as airplane 
downtime, scheduling disruptions, and other administrative costs. The 
FAA recognizes that, in doing the actions required by an AD, operators 
might incur indirect costs in addition to the direct costs, but 
disagrees with revising the estimated costs. Since these costs vary 
significantly and the FAA lacks specific data on them, they are not 
included in the analysis. Additionally, the FAA considered the impact 
that this AD will have on affected operators and determined this AD 
will not trigger any downtime costs because the requirements of this AD 
can be performed during regularly scheduled maintenance. Since the FAA 
has assessed and disclosed the total known costs of the AD requirements 
in the Costs of Compliance section of the proposed AD, and the 
commenter did not provide additional cost data for the FAA to consider 
in its cost analysis, the FAA did not change this AD as a result of 
this comment.

Conclusion

    The FAA reviewed the relevant data, considered any comments 
received, and determined that air safety requires adopting 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 AP767-
57-010, Revision 14, dated November 17, 2025. This material specifies 
procedures, for Group 1 and 2 airplanes, for an HFEC inspection for 
cracking of the external surface of the lower outboard wing skin at 
stringer L-9.5, and on-condition actions that include repetitive HFEC 
inspections, modification by oversizing and plugging the existing 
fastener holes of the wing skin, repair (modification) of the stringer 
with new stringer, and repair (modification) of the stringer with 
external doubler/tripler; repetitive post-repair inspections for 
cracking, and repair. This material also specifies procedures, for 
Group 3 airplanes, for repetitive internal and external HFEC 
inspections of the lower outboard wing skin common to the external 
doubler repair at stringer L-9.5 and repair. In addition, the 
effectivity of Aviation Partners Boeing Service Bulletin AP767-57-010, 
Revision 14, dated November 17, 2025, was revised to specify airplanes 
provisioned for blended winglets modified in accordance with STC 
ST01920SE, with or without winglets installed.
    The FAA also reviewed Aviation Partners Boeing Service Bulletin 
AP767-57-014, Revision 3, dated November 17, 2025. This material does 
not change the procedures but does change the effectivity to specify 
airplanes provisioned for blended winglets modified in accordance with 
STC ST01920SE, with or without winglets installed.
    This AD also requires Aviation Partners Boeing Service Bulletin 
AP767-57-010, Revision 11, dated April 3, 2017; and Aviation Partners 
Boeing Service Bulletin AP767-57-014, Revision 1, dated April 12, 2017, 
which the Director of the Federal Register approved for incorporation 
by reference as of July 10, 2018 (83 FR 25885, June 5, 2018).
    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 195 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
----------------------------------------------------------------------------------------------------------------
HFEC inspections.................  6 work-hours x $85             $0  $510 per inspection   $99,450 per
                                    per hour = $510 per                cycle.                inspection cycle.
                                    inspection cycle.
Internal and external HFEC         3 work-hours x $85              0  $255 per inspection   $255 per inspection
 inspections (Group 3 airplanes).   per hour = $255 per                cycle.                cycle (1 airplane).
                                    inspection cycle.
----------------------------------------------------------------------------------------------------------------

    The FAA estimates the following costs to do any necessary repairs 
that would be required based on the results of the proposed inspection. 
The FAA has no way of determining the number of aircraft that might 
need these repairs:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                  Action                            Labor cost           Parts cost        Cost per product
----------------------------------------------------------------------------------------------------------------
Post-repair inspections..................  6 work-hours x $85 per hour           $0  $510 per inspection cycle.
                                            = $510.
Repair/modification......................  262 work-hours x $85 per               0  $22,270.
                                            hour = $22,270.
----------------------------------------------------------------------------------------------------------------

    The FAA has received no definitive data on which to base the cost 
estimates for on-condition repairs for the post-repair inspections 
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

[[Page 52226]]

detail the scope of the Agency's authority.
    The FAA is issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: General requirements. 
Under that section, Congress charges the FAA with promoting safe flight 
of civil aircraft in air commerce by prescribing regulations for 
practices, methods, and procedures the Administrator finds necessary 
for safety in air commerce. This regulation is within the scope of that 
authority because it addresses an unsafe condition that is likely to 
exist or develop on products identified in this rulemaking action.

Regulatory Findings

    This AD will not have federalism implications under Executive Order 
13132. This AD will not have a substantial direct effect on the States, 
on the relationship between the national government and the States, or 
on the distribution of power and responsibilities among the various 
levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Will not affect intrastate aviation in Alaska, and
    (3) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by:
0
a. Removing Airworthiness Directive (AD) 2018-11-14, Amendment 39-19302 
(83 FR 25885, June 5, 2018); and
0
b. Adding the following new AD:

2026-16-06 The Boeing Company: Amendment 39-23436; Docket No. FAA-
2026-0023; Project Identifier AD-2025-00427-T.

(a) Effective Date

    This airworthiness directive (AD) is effective September 17, 
2026.

(b) Affected ADs

    This AD replaces AD 2018-11-14, Amendment 39-19302 (83 FR 25885, 
June 5, 2018) (AD 2018-11-14).

(c) Applicability

    This AD applies to The Boeing Company Model 767-300 and -300F 
series airplanes, certificated in any category, provisioned for 
blended winglets modified in accordance with Supplemental Type 
Certificate (STC) ST01920SE, with or without winglets installed.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Unsafe Condition

    This AD was prompted by reports of fatigue cracking in the lower 
outboard wing skin at the inboard fastener of stringer L-9.5, and 
the lower outboard wing skin of stringer L-6.5, on airplanes with 
winglets installed per Supplemental Type Certificate ST01920SE. This 
AD was also prompted by a determination that, for certain airplanes, 
the area of the lower wing skin in the vicinity of the critical 
inboard end fasteners of installed repair doublers must be 
inspected. The FAA is issuing this AD to prevent fatigue cracking in 
the lower outboard wing skin. The unsafe condition, if not 
addressed, could result in failure and subsequent separation of the 
wing and winglet and consequent reduced controllability of the 
airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Retained Repetitive Stringer L-9.5 Inspections, Modification, 
Repair (Modification), Repetitive Post-Repair Inspections, and Repair, 
With Revised Service Information

    This paragraph restates the requirements of paragraph (g) of AD 
2018-11-14, with revised service information.
    (1) For Group 1 and Group 2 airplanes, identified in Aviation 
Partners Boeing Service Bulletin AP767-57-010, Revision 11, dated 
April 3, 2017, with winglets installed: At the applicable time 
specified in paragraph 1.E., ``Compliance,'' of Aviation Partners 
Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 
2017, except as required by paragraph (j)(1) of this AD: Do a high 
frequency eddy current (HFEC) inspection for cracking of the lower 
outboard wing skin at stringer L-9.5, in accordance with Part 1 of 
the Accomplishment Instructions of Aviation Partners Boeing Service 
Bulletin AP767-57-010, Revision 11, dated April 3, 2017; or Revision 
14, dated November 17, 2025. As of the effective date of this AD, 
only Aviation Partners Boeing Service Bulletin AP767-57-010, 
Revision 14, dated November 17, 2025, may be used for performing the 
actions required by this paragraph.
    (i) For airplanes on which ``Condition 1'' is found, as defined 
in the Accomplishment Instructions of Aviation Partners Boeing 
Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017, 
during any inspection required by paragraph (g)(1) or (g)(1)(i)(A) 
of this AD: Do the applicable actions required by paragraph 
(g)(1)(i)(A), (g)(1)(i)(B), (g)(1)(i)(C), or (g)(1)(i)(D) of this 
AD.
    (A) Repeat the inspection specified in paragraph (g)(1) of this 
AD thereafter at the applicable times specified in paragraph 1.E., 
``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-
57-010, Revision 11, dated April 3, 2017.
    (B) Do the applicable actions required by paragraphs 
(g)(1)(i)(B)(1), (g)(1)(i)(B)(2), and (g)(1)(i)(B)(3) of this AD.
    (1) Before further flight, do actions (modifications and repair 
(modification)) in accordance with Part 2, Part 3, Part 4, and Part 
5, as applicable, of the Accomplishment Instructions of Aviation 
Partners Boeing Service Bulletin AP767-57-010, Revision 11, dated 
April 3, 2017; or Revision 14, dated November 17, 2025. As of the 
effective date of this AD, only Aviation Partners Boeing Service 
Bulletin AP767-57-010, Revision 14, dated November 17, 2025, may be 
used for performing the actions required by this paragraph.
    (2) For airplanes on which the repair (modification) specified 
in Part 5 of Aviation Partners Boeing Service Bulletin AP767-57-010 
was done: At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-
57-010, Revision 11, dated April 3, 2017, do a post-repair HFEC 
inspection for cracking, in accordance with Part 12 of the 
Accomplishment Instructions of Aviation Partners Boeing Service 
Bulletin AP767-57-010, Revision 11, dated April 3, 2017; or Revision 
14, dated November 17, 2025; and repeat the inspection thereafter at 
the applicable times specified in paragraph 1.E., ``Compliance,'' of 
Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, 
dated April 3, 2017. As of the effective date of this AD, only 
Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 14, 
dated November 17, 2025, may be used for performing the actions 
required by this paragraph.
    (3) If any crack is found during any inspection required by 
paragraph (g)(1)(i)(B)(2) of this AD, repair before further flight 
using a method approved in accordance with the procedures specified 
in paragraph (q) of this AD.
    (C) Do the actions required by paragraphs (g)(1)(i)(C)(1) and 
(g)(1)(i)(C)(2) of this AD, and do all applicable actions required 
by paragraph (g)(1)(i)(C)(3) of this AD.
    (1) Before further flight, repair (modify) in accordance with 
Part 8 of the Accomplishment Instructions of Aviation Partners 
Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 
2017; or Revision 14, dated November 17, 2025. As of the effective 
date of this AD, only Aviation Partners Boeing Service Bulletin 
AP767-57-010, Revision 14, dated November 17, 2025, may be used for 
performing the actions required by this paragraph.
    (2) At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Aviation

[[Page 52227]]

Partners Boeing Service Bulletin AP767-57-010, Revision 11, dated 
April 3, 2017, do a post-repair HFEC inspection for cracking, in 
accordance with Part 9 of the Accomplishment Instructions of 
Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, 
dated April 3, 2017; or Revision 14, dated November 17, 2025; and 
repeat the inspection thereafter at the applicable times specified 
in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing 
Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017. As 
of the effective date of this AD, only Aviation Partners Boeing 
Service Bulletin AP767-57-010, Revision 14, dated November 17, 2025, 
may be used for performing the actions required by this paragraph.
    (3) If any crack is found during any inspection required by 
paragraph (g)(1)(i)(C)(2) of this AD, repair before further flight 
using a method approved in accordance with the procedures specified 
in paragraph (q) of this AD.
    (D) Do the actions required by paragraphs (g)(1)(i)(D)(1) and 
(g)(1)(i)(D)(2) of this AD, and do all applicable actions required 
by paragraph (g)(1)(i)(D)(3) of this AD.
    (1) Before further flight, repair (modify) in accordance with 
Part 11 of the Accomplishment Instructions of Aviation Partners 
Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 
2017; or Revision 14, dated November 17, 2025. As of the effective 
date of this AD, only Aviation Partners Boeing Service Bulletin 
AP767-57-010, Revision 14, dated November 17, 2025, may be used for 
performing the actions required by this paragraph.
    (2) At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-
57-010, Revision 11, dated April 3, 2017, do a post-repair HFEC 
inspection for cracking, in accordance with Part 13 of the 
Accomplishment Instructions of Aviation Partners Boeing Service 
Bulletin AP767-57-010, Revision 11, dated April 3, 2017; or Revision 
14, dated November 17, 2025; and repeat the inspection thereafter at 
the applicable times specified in paragraph 1.E., ``Compliance,'' of 
Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, 
dated April 3, 2017; except as required by paragraph (j)(4) of this 
AD. As of the effective date of this AD, only Aviation Partners 
Boeing Service Bulletin AP767-57-010, Revision 14, dated November 
17, 2025, may be used for performing the actions required by this 
paragraph.
    (3) If any crack is found during any inspection required by 
paragraph (g)(1)(i)(D)(2) of this AD, repair before further flight 
using a method approved in accordance with the procedures specified 
in paragraph (q) of this AD.
    (ii) For airplanes on which ``Condition 2'' is found, as defined 
in the Accomplishment Instructions of Aviation Partners Boeing 
Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017, 
during any inspection required by paragraph (g)(1) or (g)(1)(i)(A) 
of this AD: Do the actions required by paragraph (g)(1)(ii)(A) or 
(g)(1)(ii)(B) of this AD.
    (A) Do the actions required by paragraphs (g)(1)(ii)(A)(1) and 
(g)(1)(ii)(A)(2) of this AD, and do all applicable actions required 
by paragraph (g)(1)(ii)(A)(3) of this AD.
    (1) Before further flight, repair (modify) in accordance with 
Part 8 of the Accomplishment Instructions of Aviation Partners 
Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 
2017; or Revision 14, dated November 17, 2025. As of the effective 
date of this AD, only Aviation Partners Boeing Service Bulletin 
AP767-57-010, Revision 14, dated November 17, 2025, may be used for 
performing the actions required by this paragraph.
    (2) At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-
57-010, Revision 11, dated April 3, 2017, do a post-repair HFEC 
inspection for cracking, in accordance with Part 9 of the 
Accomplishment Instructions of Aviation Partners Boeing Service 
Bulletin AP767-57-010, Revision 11, dated April 3, 2017; or Revision 
14, dated November 17, 2025; and repeat the inspection thereafter at 
the applicable times specified in paragraph 1.E., ``Compliance.'' of 
Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, 
dated April 3, 2017. As of the effective date of this AD, only 
Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 14, 
dated November 17, 2025, may be used for performing the actions 
required by this paragraph.
    (3) If any crack is found during any inspection required by 
paragraph (g)(1)(ii)(A)(2) of this AD, repair before further flight 
using a method approved in accordance with the procedures specified 
in paragraph (q) of this AD.
    (B) Do the actions required by paragraphs (g)(1)(ii)(B)(1) and 
(g)(1)(ii)(B)(2) of this AD, and do all applicable actions required 
by paragraph (g)(1)(ii)(B)(3) of this AD.
    (1) Before further flight, repair (modify) in accordance with 
Part 11 of the Accomplishment Instructions of Aviation Partners 
Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 
2017; or Revision 14, dated November 17, 2025. As of the effective 
date of this AD, only Aviation Partners Boeing Service Bulletin 
AP767-57-010, Revision 14, dated November 17, 2025, may be used for 
performing the actions required by this paragraph.
    (2) At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-
57-010, Revision 11, dated April 3, 2017, do a post-repair HFEC 
inspection for cracking, in accordance with Part 13 of the 
Accomplishment Instructions of Aviation Partners Boeing Service 
Bulletin AP767-57-010, Revision 11, dated April 3, 2017; or Revision 
14, dated November 17, 2025; and repeat the inspection thereafter at 
the applicable times specified in paragraph 1.E., ``Compliance,'' of 
Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, 
dated April 3, 2017; except as required by paragraph (j)(4) of this 
AD. As of the effective date of this AD, only Aviation Partners 
Boeing Service Bulletin AP767-57-010, Revision 14, dated November 
17, 2025, may be used for performing the actions required by this 
paragraph.
    (3) If any crack is found during any inspection required by 
paragraph (g)(1)(ii)(B)(2) of this AD, repair before further flight 
using a method approved in accordance with the procedures specified 
in paragraph (q) of this AD.
    (iii) For airplanes on which ``Condition 3'' is found, as 
defined in the Accomplishment Instructions of Aviation Partners 
Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 
2017, during the actions specified in paragraph (g)(1)(i)(B)(1) of 
this AD: Do the actions required by paragraph (g)(1)(iii)(A) or 
(g)(1)(iii)(B) of this AD.
    (A) Do the actions required by paragraphs (g)(1)(iii)(A)(1) and 
(g)(1)(iii)(A)(2) of this AD, and do all applicable actions required 
by paragraph (g)(1)(iii)(A)(3) of this AD.
    (1) Before further flight, repair (modify) in accordance with 
Part 8 of the Accomplishment Instructions of Aviation Partners 
Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 
2017; or Revision 14, dated November 17, 2025. As of the effective 
date of this AD, only Aviation Partners Boeing Service Bulletin 
AP767-57-010, Revision 14, dated November 17, 2025, may be used for 
performing the actions required by this paragraph.
    (2) At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-
57-010, Revision 11, dated April 3, 2017, do a post-repair HFEC 
inspection for cracking, in accordance with Part 9 of the 
Accomplishment Instructions of Aviation Partners Boeing Service 
Bulletin AP767-57-010, Revision 11, dated April 3, 2017; or Revision 
14, dated November 17, 2025; and repeat the inspection thereafter at 
the applicable times specified in paragraph 1.E., ``Compliance,'' of 
Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, 
dated April 3, 2017. As of the effective date of this AD, only 
Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 14, 
dated November 17, 2025, may be used for performing the actions 
required by this paragraph.
    (3) If any crack is found during any inspection required by 
paragraph (g)(1)(iii)(A)(2) of this AD, repair before further flight 
using a method approved in accordance with the procedures specified 
in paragraph (q) of this AD.
    (B) Do the actions required by paragraphs (g)(1)(iii)(B)(1) and 
(g)(1)(iii)(B)(2) of this AD, and do all applicable actions required 
by paragraph (g)(1)(iii)(B)(3) of this AD.
    (1) Before further flight, repair (modify) in accordance with 
Part 11 of the Accomplishment Instructions of Aviation Partners 
Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 
2017; or Revision 14, dated November 17, 2025. As of the effective 
date of this AD, only Aviation Partners Boeing Service Bulletin 
AP767-57-010, Revision 14, dated November 17, 2025, may be used for 
performing the actions required by this paragraph.
    (2) At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-
57-010, Revision 11, dated April 3, 2017, do a post-repair HFEC 
inspection for cracking, in accordance with Part 13 of the 
Accomplishment Instructions of Aviation Partners Boeing Service 
Bulletin AP767-57-

[[Page 52228]]

010, Revision 11, dated April 3, 2017; or Revision 14, dated 
November 17, 2025; and repeat the inspection thereafter at the 
applicable times specified in paragraph 1.E., ``Compliance,'' of 
Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, 
dated April 3, 2017; except as required by paragraph (j)(4) of this 
AD. As of the effective date of this AD, only Aviation Partners 
Boeing Service Bulletin AP767-57-010, Revision 14, dated November 
17, 2025, may be used for performing the actions required by this 
paragraph.
    (3) If any crack is found during any inspection required by 
paragraph (g)(1)(iii)(B)(2) of this AD, repair before further flight 
using a method approved in accordance with the procedures specified 
in paragraph (q) of this AD.
    (iv) For airplanes on which ``Condition 4'' is found, as defined 
in the Accomplishment Instructions of Aviation Partners Boeing 
Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017, 
during any action specified in paragraph (g)(1)(i)(C)(1), 
(g)(1)(i)(D)(1), (g)(1)(ii)(A)(1), (g)(1)(ii)(B)(1), 
(g)(1)(iii)(A)(1), and (g)(1)(iii)(B)(1) of this AD: Repair before 
further flight using a method approved in accordance with the 
procedures specified in paragraph (q) of this AD.
    (2) For Group 3 airplanes, identified in Aviation Partners 
Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 
2017, with winglets installed: At the applicable time specified in 
paragraph 1.E., ``Compliance'' of Aviation Partners Boeing Service 
Bulletin AP767-57-010, Revision 11, dated April 3, 2017, or within 6 
months after July 10, 2018 (the effective date of AD 2018-11-14), 
whichever occurs later, do an HFEC inspection for cracking of the 
lower outboard wing skin at stringer L-9.5, in accordance with Part 
7 of the Accomplishment Instructions of Aviation Partners Boeing 
Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017. 
Repeat the inspections thereafter at the applicable time specified 
in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing 
Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017. If 
any cracking is found during any inspection, repair before further 
flight using a method approved in accordance with the procedures 
specified in paragraph (q) of this AD. An approved repair terminates 
the repetitive inspections required by paragraph (g)(2) of this AD 
for the repaired area only. Doing the initial inspections required 
by paragraph (k) of this AD terminates the inspections required by 
paragraph (g)(2) of this AD.
    (3) Group 4 airplanes, identified in Aviation Partners Boeing 
Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017, 
with winglets installed, are not affected by the actions required by 
paragraph (g) of this AD.

(h) Retained Repetitive Stringer L-6.5 Inspections, Repair 
(Modification), Repetitive Post-Repair Inspections, and Repair With No 
Changes

    This paragraph restates the requirements of paragraph (h) of AD 
2018-11-14, with no changes.
    (1) For airplanes, identified in Aviation Partners Boeing 
Service Bulletin AP767-57-014, Revision 1, dated April 12, 2017, 
with winglets installed: At the applicable time specified in 
paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service 
Bulletin AP767-57-014, Revision 1, dated April 12, 2017, except as 
required by paragraph (j)(2) of this AD: Do an HFEC inspection for 
cracking of stringer L-6.5 of the lower outboard wing skin, in 
accordance with Part 1 of Aviation Partners Boeing Service Bulletin 
AP767-57-014, Revision 1, dated April 12, 2017; or Aviation Partners 
Boeing Service Bulletin AP767-57-014, Revision 3, dated November 17, 
2025. If no cracking is found, repeat the inspection thereafter at 
the applicable times specified in paragraph 1.E., ``Compliance,'' of 
Aviation Partners Boeing Service Bulletin AP767-57-014, Revision 1, 
dated April 12, 2017, except as provided by paragraph (h)(3) of this 
AD. As of the effective date of this AD, only Aviation Partners 
Boeing Service Bulletin AP767-57-014, Revision 3, dated November 17, 
2025, may be used for performing the actions required by this 
paragraph.
    (2) If any crack is found during any inspection required by 
paragraph (h)(1) of this AD, do the actions required by paragraphs 
(h)(2)(i) and (h)(2)(ii) of this AD, and do all applicable actions 
required by paragraph (h)(2)(iii) of this AD.
    (i) Before further flight, repair (modify) stringer L-6.5, in 
accordance with Part 2 of the Accomplishment Instructions of 
Aviation Partners Boeing Service Bulletin AP767-57-014, Revision 1, 
dated April 12, 2017; or Aviation Partners Boeing Service Bulletin 
AP767-57-014, Revision 3, dated November 17, 2025. As of the 
effective date of this AD, only Aviation Partners Boeing Service 
Bulletin AP767-57-014, Revision 3, dated November 17, 2025, may be 
used for performing the actions required by this paragraph.
    (ii) Except as required by paragraph (j)(3) of this AD: At the 
applicable time specified in paragraph 1.E., ``Compliance,'' of 
Aviation Partners Boeing Service Bulletin AP767-57-014, Revision 1, 
dated April 12, 2017, except as required by paragraph (j)(2) of this 
AD, do an HFEC post-repair inspection for cracking, in accordance 
with Part 3 of the Accomplishment Instructions of Aviation Partners 
Boeing Service Bulletin AP767-57-014, Revision 1, dated April 12, 
2017; or Aviation Partners Boeing Service Bulletin AP767-57-014, 
Revision 3, dated November 17, 2025, and repeat the inspection 
thereafter at the applicable times specified in paragraph 1.E., 
``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-
57-014, Revision 1, dated April 12, 2017. As of the effective date 
of this AD, only Aviation Partners Boeing Service Bulletin AP767-57-
014, Revision 3, dated November 17, 2025, may be used for performing 
the actions required by this paragraph.
    (iii) If any crack is found during any inspection required by 
paragraph (h)(2)(ii) of this AD, repair before further flight using 
a method approved in accordance with the procedures specified in 
paragraph (q) of this AD.
    (3) As an option to the repetitive inspections required by 
paragraph (h)(1) of this AD, do the actions required by paragraphs 
(h)(3)(i) and (h)(3)(ii) of this AD, and do all applicable actions 
required by paragraph (h)(3)(iii) of this AD.
    (i) Before further flight after accomplishing the most recent 
inspection required by paragraph (h)(1) of this AD, repair (modify) 
stringer L-6.5, in accordance with Part 2 of the Accomplishment 
Instructions of Aviation Partners Boeing Service Bulletin AP767-57-
014, Revision 1, dated April 12, 2017; or Aviation Partners Boeing 
Service Bulletin AP767-57-014, Revision 3, dated November 17, 2025. 
As of the effective date of this AD, only Aviation Partners Boeing 
Service Bulletin AP767-57-014, Revision 3, dated November 17, 2025, 
may be used for performing the actions required by this paragraph.
    (ii) Except as required by paragraph (j)(3) of this AD: At the 
applicable time specified in paragraph 1.E., ``Compliance,'' of 
Aviation Partners Boeing Service Bulletin AP767-57-014, Revision 1, 
dated April 12, 2017, except as required by paragraph (j)(2) of this 
AD, do a post-repair HFEC inspection for cracking, in accordance 
with Part 3 of the Accomplishment Instructions of Aviation Partners 
Boeing Service Bulletin AP767-57-014, Revision 1, dated April 12, 
2017; or Aviation Partners Boeing Service Bulletin AP767-57-014, 
Revision 3, dated November 17, 2025, and repeat the inspection 
thereafter at the applicable times specified in paragraph 1.E., 
``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-
57-014, Revision 1, dated April 12, 2017. As of the effective date 
of this AD, only Aviation Partners Boeing Service Bulletin AP767-57-
014, Revision 3, dated November 17, 2025, may be used for performing 
the actions required by this paragraph.
    (iii) If any crack is found during any inspection required by 
paragraph (h)(3)(ii) of this AD, repair before further flight using 
a method approved in accordance with the procedures specified in 
paragraph (q) of this AD.

(i) Retained Repair Approval, With New Service Information References

    This paragraph restates the repair approval specified in 
paragraph (i) of AD 2018-11-14, with new service information 
references. Repairs of the lower outboard wing skin that were 
approved after June 15, 2017, and before July 10, 2018 (the 
effective date of AD 2018-11-14), by the Boeing Commercial Airplanes 
Organization Designation Authorization (ODA) that has been 
authorized by the Manager, Seattle ACO Branch, FAA, are approved for 
the applicable repairs required by paragraphs (g) and (h) of this 
AD. The ODA repairs will have post installation inspection 
requirements in lieu of the post-inspection instructions specified 
in Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 
11, dated April 3, 2017; Aviation Partners Boeing Service Bulletin 
AP767-57-010, Revision 14, dated November 17, 2025; Aviation 
Partners Boeing Service Bulletin AP767-57-014, Revision 1, dated 
April 12, 2017; and Aviation Partners Boeing Service Bulletin AP767-
57-014, Revision 3, dated November 17, 2025.

[[Page 52229]]

(j) Retained Exceptions to Service Information Specifications With No 
Changes

    This paragraph retains the exceptions specified in paragraph (j) 
of AD 2018-11-14, with no changes.
    (1) Where paragraph 1.E., ``Compliance,'' of Aviation Partners 
Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 
2017, specifies a compliance time ``after the issue date of Revision 
11 of this service bulletin,'' this AD requires compliance within 
the specified compliance time after July 10, 2018 (the effective 
date of AD 2018-11-14).
    (2) Where paragraph 1.E., ``Compliance,'' of Aviation Partners 
Boeing Service Bulletin AP767-57-014, Revision 1, dated April 12, 
2017, specifies a compliance time ``after the initial issue date of 
this service bulletin,'' this AD requires compliance within the 
specified compliance time after July 10, 2018 (the effective date of 
AD 2018-11-14).
    (3) For Condition 1 and Condition 2 airplanes: Where paragraph 
1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin 
AP767-57-014, Revision 1, dated April 12, 2017, specifies a 
compliance time for accomplishing the Part 3 HFEC inspection of 18 
months ``after the initial issue date of this service bulletin,'' 
the required compliance time is 6,000 flight cycles or 18,000 flight 
hours, whichever occurs first, after doing the Part 2 repair.
    (4) For airplanes on which a stringer L-9.5 replacement was 
accomplished per Part 11 of Aviation Partners Boeing Service 
Bulletin AP767-57-010, Revision 11, dated April 3, 2017: Where 
Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, 
dated April 3, 2017, specifies repeating the post-repair HFEC 
inspection ``in Part 9,'' this AD requires repeating the post-repair 
HFEC inspection in Part 13.

(k) New Requirements for Group 3 Airplanes

    For Group 3 airplanes identified in Aviation Partners Boeing 
Service Bulletin AP767-57-010, Revision 14, dated November 17, 2025: 
At the applicable time specified in paragraph 1.E., ``Compliance,'' 
of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 
14, dated November 17, 2025, or within 3,000 flight cycles after the 
effective date of this AD, whichever occurs later, do the initial 
internal and external HFEC inspections of the lower outboard wing 
skin common to the external doubler repair at stringer L-9.5, in 
accordance with Part 7 of the Accomplishment Instructions of 
Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 14, 
dated November 17, 2025. Repeat the inspections thereafter at the 
applicable time specified in paragraph 1.E., ``Compliance,'' of 
Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 14, 
dated November 17, 2025. If any cracking is found during any 
inspection, repair before further flight using a method approved in 
accordance with the procedures specified in paragraph (q) of this 
AD. Doing the initial inspections required by this paragraph 
terminates the inspections required by paragraph (g)(2) of this AD.

(l) New Repetitive Stringer L-9.5 Inspections, Modification, Repair 
(Modification), Repetitive Post-Repair Inspections, and Repair

    (1) For Group 1 and Group 2 airplanes identified in Aviation 
Partners Boeing Service Bulletin AP767-57-010, Revision 14, dated 
November 17, 2025, without winglets installed: At the applicable 
time specified in paragraph 1.E., ``Compliance,'' of Aviation 
Partners Boeing Service Bulletin AP767-57-010, Revision 14, dated 
November 17, 2025, except as required by paragraph (o)(1) of this 
AD: Do a HFEC inspection for cracking of the lower outboard wing 
skin at stringer L-9.5, in accordance with Part 1 of the 
Accomplishment Instructions of Aviation Partners Boeing Service 
Bulletin AP767-57-010, Revision 14, dated November 17, 2025.
    (i) For airplanes on which ``Condition 1'' is found, as defined 
in the Accomplishment Instructions of Aviation Partners Boeing 
Service Bulletin AP767-57-010, Revision 14, dated November 17, 2025, 
during any inspection required by paragraph (l)(1) or (l)(1)(i)(A) 
of this AD: Do the applicable actions required by paragraph 
(l)(1)(i)(A), (l)(1)(i)(B), (l)(1)(i)(C), or (l)(1)(i)(D) of this 
AD.
    (A) Repeat the inspection specified in paragraph (l)(1) of this 
AD thereafter at the applicable times specified in paragraph 1.E., 
``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-
57-010, Revision 14, dated November 17, 2025.
    (B) Do the applicable actions required by paragraphs 
(l)(1)(i)(B)(1), (l)(1)(i)(B)(2), and (l)(1)(i)(B)(3) of this AD.
    (1) Before further flight, do actions (modifications and repair 
(modification)) in accordance with Part 2, Part 3, Part 4, and Part 
5, as applicable, of the Accomplishment Instructions of Aviation 
Partners Boeing Service Bulletin AP767-57-010, Revision 14, dated 
November 17, 2025.
    (2) For airplanes on which the repair (modification) specified 
in Part 5 of Aviation Partners Boeing Service Bulletin AP767-57-010 
was done: At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-
57-010, Revision 14, dated November 17, 2025, do a post-repair HFEC 
inspection for cracking, in accordance with Part 12 of the 
Accomplishment Instructions of Aviation Partners Boeing Service 
Bulletin AP767-57-010, Revision 14, dated November 17, 2025; and 
repeat the inspection thereafter at the applicable times specified 
in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing 
Service Bulletin AP767-57-010, Revision 14, dated November 17, 2025.
    (3) If any crack is found during any inspection required by 
paragraph (l)(1)(i)(B)(2) of this AD, repair before further flight 
using a method approved in accordance with the procedures specified 
in paragraph (q) of this AD.
    (C) Do the actions required by paragraphs (l)(1)(i)(C)(1) and 
(l)(1)(i)(C)(2) of this AD, and do all applicable actions required 
by paragraph (l)(1)(i)(C)(3) of this AD.
    (1) Before further flight, repair (modify) in accordance with 
Part 8 of the Accomplishment Instructions of Aviation Partners 
Boeing Service Bulletin AP767-57-010, Revision 14, dated November 
17, 2025.
    (2) At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-
57-010, Revision 14, dated November 17, 2025, do a post-repair HFEC 
inspection for cracking, in accordance with Part 9 of the 
Accomplishment Instructions of Aviation Partners Boeing Service 
Bulletin AP767-57-010, Revision 14, dated November 17, 2025; and 
repeat the inspection thereafter at the applicable times specified 
in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing 
Service Bulletin AP767-57-010, Revision 14, dated November 17, 2025.
    (3) If any crack is found during any inspection required by 
paragraph (l)(1)(i)(C)(2) of this AD, repair before further flight 
using a method approved in accordance with the procedures specified 
in paragraph (q) of this AD.
    (D) Do the actions required by paragraphs (l)(1)(i)(D)(1) and 
(l)(1)(i)(D)(2) of this AD, and do all applicable actions required 
by paragraph (l)(1)(i)(D)(3) of this AD.
    (1) Before further flight, repair (modify) in accordance with 
Part 11 of the Accomplishment Instructions of Aviation Partners 
Boeing Service Bulletin AP767-57-010, Revision 14, dated November 
17, 2025.
    (2) At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-
57-010, Revision 14, dated November 17, 2025, do a post-repair HFEC 
inspection for cracking, in accordance with Part 13 of the 
Accomplishment Instructions of Aviation Partners Boeing Service 
Bulletin AP767-57-010, Revision 14, dated November 17, 2025; and 
repeat the inspection thereafter at the applicable times specified 
in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing 
Service Bulletin AP767-57-010, Revision 14, dated November 17, 2025.
    (3) If any crack is found during any inspection required by 
paragraph (l)(1)(i)(D)(2) of this AD, repair before further flight 
using a method approved in accordance with the procedures specified 
in paragraph (q) of this AD.
    (ii) For airplanes on which ``Condition 2'' is found, as defined 
in the Accomplishment Instructions of Aviation Partners Boeing 
Service Bulletin AP767-57-010, Revision 14, dated November 17, 2025, 
during any inspection required by paragraph (l)(1) or (l)(1)(i)(A) 
of this AD: Do the actions required by paragraph (l)(1)(ii)(A) or 
(l)(1)(ii)(B) of this AD.
    (A) Do the actions required by paragraphs (l)(1)(ii)(A)(1) and 
(l)(1)(ii)(A)(2) of this AD, and do all applicable actions required 
by paragraph (l)(1)(ii)(A)(3) of this AD.
    (1) Before further flight, repair (modify) in accordance with 
Part 8 of the Accomplishment Instructions of Aviation Partners 
Boeing Service Bulletin AP767-57-010, Revision 14, dated November 
17, 2025.
    (2) At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-
57-010, Revision 14, dated November 17, 2025, do a post-repair HFEC 
inspection for cracking, in accordance with Part 9 of the 
Accomplishment Instructions of Aviation Partners Boeing Service 
Bulletin AP767-57-010, Revision 14, dated November 17, 2025;

[[Page 52230]]

and repeat the inspection thereafter at the applicable times 
specified in paragraph 1.E., ``Compliance.'' of Aviation Partners 
Boeing Service Bulletin AP767-57-010, Revision 14, dated November 
17, 2025.
    (3) If any crack is found during any inspection required by 
paragraph (l)(1)(ii)(A)(2) of this AD, repair before further flight 
using a method approved in accordance with the procedures specified 
in paragraph (q) of this AD.
    (B) Do the actions required by paragraphs (l)(1)(ii)(B)(1) and 
(l)(1)(ii)(B)(2) of this AD, and do all applicable actions required 
by paragraph (l)(1)(ii)(B)(3) of this AD.
    (1) Before further flight, repair (modify) in accordance with 
Part 11 of the Accomplishment Instructions of Aviation Partners 
Boeing Service Bulletin AP767-57-010, Revision 14, dated November 
17, 2025.
    (2) At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-
57-010, Revision 14, dated November 17, 2025, do a post-repair HFEC 
inspection for cracking, in accordance with Part 13 of the 
Accomplishment Instructions of Aviation Partners Boeing Service 
Bulletin AP767-57-010, Revision 14, dated November 17, 2025; and 
repeat the inspection thereafter at the applicable times specified 
in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing 
Service Bulletin AP767-57-010, Revision 14, dated November 17, 2025.
    (3) If any crack is found during any inspection required by 
paragraph (l)(1)(ii)(B)(2) of this AD, repair before further flight 
using a method approved in accordance with the procedures specified 
in paragraph (q) of this AD.
    (iii) For airplanes on which ``Condition 3'' is found, as 
defined in the Accomplishment Instructions of Aviation Partners 
Boeing Service Bulletin AP767-57-010, Revision 14, dated November 
17, 2025, during the actions specified in paragraph (l)(1)(i)(B)(1) 
of this AD: Do the actions required by paragraph (l)(1)(iii)(A) or 
(l)(1)(iii)(B) of this AD.
    (A) Do the actions required by paragraphs (l)(1)(iii)(A)(1) and 
(l)(1)(iii)(A)(2) of this AD, and do all applicable actions required 
by paragraph (l)(1)(iii)(A)(3) of this AD.
    (1) Before further flight, repair (modify) in accordance with 
Part 8 of the Accomplishment Instructions of Aviation Partners 
Boeing Service Bulletin AP767-57-010, Revision 14, dated November 
17, 2025.
    (2) At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-
57-010, Revision 14, dated November 17, 2025, do a post-repair HFEC 
inspection for cracking, in accordance with Part 9 of the 
Accomplishment Instructions of Aviation Partners Boeing Service 
Bulletin AP767-57-010, Revision 14, dated November 17, 2025; and 
repeat the inspection thereafter at the applicable times specified 
in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing 
Service Bulletin AP767-57-010, Revision 14, dated November 17, 2025.
    (3) If any crack is found during any inspection required by 
paragraph (l)(1)(iii)(A)(2) of this AD, repair before further flight 
using a method approved in accordance with the procedures specified 
in paragraph (q) of this AD.
    (B) Do the actions required by paragraphs (l)(1)(iii)(B)(1) and 
(l)(1)(iii)(B)(2) of this AD, and do all applicable actions required 
by paragraph (l)(1)(iii)(B)(3) of this AD.
    (1) Before further flight, repair (modify) in accordance with 
Part 11 of the Accomplishment Instructions of Aviation Partners 
Boeing Service Bulletin AP767-57-010, Revision 14, dated November 
17, 2025.
    (2) At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-
57-010, Revision 14, dated November 17, 2025, do a post-repair HFEC 
inspection for cracking, in accordance with Part 13 of the 
Accomplishment Instructions of Aviation Partners Boeing Service 
Bulletin AP767-57-010, Revision 14, dated November 17, 2025; and 
repeat the inspection thereafter at the applicable times specified 
in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing 
Service Bulletin AP767-57-010, Revision 14, dated November 17, 2025.
    (3) If any crack is found during any inspection required by 
paragraph (l)(1)(iii)(B)(2) of this AD, repair before further flight 
using a method approved in accordance with the procedures specified 
in paragraph (q) of this AD.
    (iv) For airplanes on which ``Condition 4'' is found, as defined 
in the Accomplishment Instructions of Aviation Partners Boeing 
Service Bulletin AP767-57-010, Revision 14, dated November 17, 2025, 
during any action specified in paragraph (l)(1)(i)(C)(1), 
(l)(1)(i)(D)(1), (l)(1)(ii)(A)(1), (l)(1)(ii)(B)(1), 
(l)(1)(iii)(A)(1), and (l)(1)(iii)(B)(1) of this AD: Repair before 
further flight using a method approved in accordance with the 
procedures specified in paragraph (q) of this AD.
    (2) Group 4 airplanes identified in Aviation Partners Boeing 
Service Bulletin AP767-57-010, Revision 14, dated November 17, 2025, 
without winglets installed, are not affected by the actions required 
by paragraph (l) of this AD.

(m) New Repetitive Stringer L-6.5 Inspections, Repair (Modification), 
Repetitive Post-Repair Inspections, and Repair

    (1) For airplanes identified in Aviation Partners Boeing Service 
Bulletin AP767-57-014, Revision 3, dated November 17, 2025, without 
winglets installed: At the applicable time specified in paragraph 
1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin 
AP767-57-014, Revision 3, dated November 17, 2025, except as 
required by paragraph (o)(2) of this AD, do an HFEC inspection for 
cracking of stringer L-6.5 of the lower outboard wing skin, in 
accordance with Part 1 of Aviation Partners Boeing Service Bulletin 
AP767-57-014, Revision 3, dated November 17, 2025. If no cracking is 
found, repeat the inspection thereafter at the applicable times 
specified in paragraph 1.E., ``Compliance'' of Aviation Partners 
Boeing Service Bulletin AP767-57-014, Revision 3, dated November 17, 
2025, except as provided by paragraph (m)(3) of this AD.
    (2) If any crack is found during any inspection required by 
paragraph (m)(1) of this AD, do the actions required by paragraphs 
(m)(2)(i) and (m)(2)(ii) of this AD, and do all applicable actions 
required by paragraph (m)(2)(iii) of this AD.
    (i) Before further flight, repair (modify) stringer L-6.5, in 
accordance with Part 2 of the Accomplishment Instructions of 
Aviation Partners Boeing Service Bulletin AP767-57-014, Revision 3, 
dated November 17, 2025.
    (ii) At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-
57-014, Revision 3, dated November 17, 2025, except as required by 
paragraph (o)(2) of this AD, do an HFEC post-repair inspection for 
cracking, in accordance with Part 3 of the Accomplishment 
Instructions of Aviation Partners Boeing Service Bulletin AP767-57-
014, Revision 3, dated November 17, 2025, and repeat the inspection 
thereafter at the applicable times specified in paragraph 1.E., 
``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-
57-014, Revision 3, dated November 17, 2025, except as required by 
paragraph (o)(2) of this AD.
    (iii) If any crack is found during any inspection required by 
paragraph (m)(2)(ii) of this AD, repair before further flight using 
a method approved in accordance with the procedures specified in 
paragraph (q) of this AD.
    (3) As an option to the repetitive inspections required by 
paragraph (m)(1) of this AD, do the actions required by paragraphs 
(m)(3)(i) and (ii) of this AD, and do all applicable actions 
required by paragraph (m)(3)(iii) of this AD.
    (i) Before further flight after accomplishing the most recent 
inspection required by paragraph (m)(1) of this AD, repair (modify) 
stringer L-6.5, in accordance with Part 2 of the Accomplishment 
Instructions of Aviation Partners Boeing Service Bulletin AP767-57-
014, Revision 3, dated November 17, 2025.
    (ii) At the applicable time specified in paragraph 1.E., 
``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-
57-014, Revision 3, dated November 17, 2025, except as required by 
paragraph (o)(2) of this AD, do a post-repair HFEC inspection for 
cracking, in accordance with Part 3 of the Accomplishment 
Instructions of Aviation Partners Boeing Service Bulletin AP767-57-
014, Revision 3, dated November 17, 2025, and repeat the inspection 
thereafter at the applicable times specified in paragraph 1.E., 
``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-
57-014, Revision 3, dated November 17, 2025, except as required by 
paragraph (o)(2) of this AD.
    (iii) If any crack is found during any inspection required by 
paragraph (m)(3)(ii) of this AD, repair before further flight using 
a method approved in accordance with the procedures specified in 
paragraph (q) of this AD.

(n) Repair Approval for Paragraphs (l) and (m) of This AD

    Repairs of the lower outboard wing skin that were approved after 
June 15, 2017, and before July 10, 2018 (the effective date of AD 
2018-11-14), by the Boeing ODA that has been authorized by the 
Manager, AIR-770, West Certification Branch, FAA, are approved for 
the applicable repairs required by paragraphs (l) and (m) of this 
AD. The ODA repairs will have post installation inspection 
requirements in lieu of the post-inspection instructions specified 
in Aviation

[[Page 52231]]

Partners Boeing Service Bulletin AP767-57-010, Revision 14, dated 
November 17, 2025; and Aviation Partners Boeing Service Bulletin 
AP767-57-014, Revision 3, dated November 17, 2025.

(o) New Exceptions to Service Information Specifications

    (1) Where paragraph 1.E., ``Compliance,'' of Aviation Partners 
Boeing Service Bulletin AP767-57-010, Revision 14, dated November 
17, 2025, specifies a compliance time ``the effective date of AD 
2018-11-14,'' this AD requires compliance within the specified 
compliance time after the effective date of this AD.
    (2) Where paragraph 1.E., ``Compliance,'' of Aviation Partners 
Boeing Service Bulletin AP767-57-014, Revision 3, dated November 17, 
2025, specifies a compliance time ``Within 18 months after the 
effective date of AD 2018-11-14,'' this AD requires compliance 
within the specified compliance time after the effective date of 
this AD.

(p) Credit for Previous Actions

    (1) This paragraph provides credit for the actions specified in 
paragraph (g) of this AD, if those actions were performed before the 
effective date of this AD using Aviation Partners Boeing Service 
Bulletin AP767-57-010, Revision 12, dated June 21, 2018; or Aviation 
Partners Boeing Service Bulletin AP767-57-010, Revision 13, dated 
November 5, 2024.
    (2) This paragraph provides credit for the actions specified in 
paragraph (h) of this AD, if those actions were performed before the 
effective date of this AD using Aviation Partners Boeing Service 
Bulletin AP767-57-014, Revision 2, dated July 9, 2018.
    (3) This paragraph provides credit for the actions specified in 
paragraph (k) of this AD, if those actions were performed before the 
effective date of this AD using Aviation Partners Boeing Service 
Bulletin AP767-57-010, Revision 13, dated November 5, 2024.
    (4) For Group 1 and 2 airplanes identified in Aviation Partners 
Boeing Service Bulletin AP767-57-010, Revision 14, dated November 
17, 2025: This paragraph provides credit for the actions specified 
in paragraph (l) of this AD, if those actions were performed before 
the effective date of this AD using Aviation Partners Boeing Service 
Bulletin AP767-57-010, Revision 11, dated April 3, 2017; Aviation 
Partners Boeing Service Bulletin AP767-57-010, Revision 12, dated 
June 21, 2018; or Aviation Partners Boeing Service Bulletin AP767-
57-010, Revision 13, dated November 5, 2024.
    (5) This paragraph provides credit for the actions specified in 
paragraph (m) of this AD, if those actions were performed before the 
effective date of this AD using Aviation Partners Boeing Service 
Bulletin AP767-57-014, Revision 1, dated April 12, 2017; or Aviation 
Partners Boeing Service Bulletin AP767-57-014, Revision 2, dated 
July 9, 2018.

(q) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, AIR-770, 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 (r) 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) An AMOC that provides an acceptable level of safety may be 
used for any repair, modification, or alteration required by this AD 
if it is approved by The Boeing ODA that has been authorized by the 
Manager, AIR-770, West Certification Branch, FAA, to make those 
findings. To be approved, the repair method, modification deviation, 
or alteration deviation must meet the certification basis of the 
airplane, and the approval must specifically refer to this AD.
    (3) AMOCs approved for AD 2018-11-14 are approved as AMOCs for 
the corresponding provisions of paragraphs (g) and (h) of this AD.
    (4) Except as required by paragraphs (g)(1)(i)(B)(3), 
(g)(1)(i)(C)(3), (g)(1)(i)(D)(3), (g)(1)(ii)(A)(3), 
(g)(1)(ii)(B)(3), (g)(1)(iii)(A)(3), (g)(1)(iii)(B)(3), (g)(1)(iv), 
(g)(2), (h)(2)(iii), (h)(3)(iii), (k), (l)(1)(i)(B)(3), 
(l)(1)(i)(C)(3), (l)(1)(i)(D)(3), (l)(1)(ii)(A)(3), 
(l)(1)(ii)(B)(3), (l)(1)(iii)(A)(3), (l)(1)(iii)(B)(3), (l)(1)(iv), 
(l)(2), (m)(2)(iii), and (m)(3)(iii), of this AD: For material that 
contains steps that are labeled as Required for Compliance (RC), the 
provisions of paragraphs (q)(4)(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.

(r) 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].

(s) 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 this AD specifies otherwise.
    (3) The following material was approved for IBR on September 17, 
2026.
    (i) Aviation Partners Boeing Service Bulletin AP767-57-010, 
Revision 14, dated November 17, 2025.
    (ii) Aviation Partners Boeing Service Bulletin AP767-57-014, 
Revision 3, dated November 17, 2025.
    (4) The following material was approved for IBR on July 10, 2018 
(83 FR 25885, June 5, 2018).
    (i) Aviation Partners Boeing Service Bulletin AP767-57-010, 
Revision 11, dated April 3, 2017.
    (ii) Aviation Partners Boeing Service Bulletin AP767-57-014, 
Revision 1, dated April 12, 2017.
    (5) For Aviation Partners Boeing material identified in this AD, 
contact Aviation Partners Boeing, 555 Andover Park West, Suite 200, 
Tukwila, Washington 98188; telephone 206-830-7699; email 
[email protected]; website 
aviationpartnersboeing.com.
    (6) 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.
    (7) You may view this material at the National Archives and 
Records Administration (NARA). For information on the availability 
of this material at NARA, visit www.archives.gov/federal-register/cfr/ibr-locations or email [email protected].

    Issued on August 5, 2026.
Steven W. Thompson,
Acting Deputy Director, Compliance & Airworthiness Division, Aircraft 
Certification Service.
[FR Doc. 2026-16504 Filed 8-12-26; 8:45 am]
BILLING CODE 4910-13-P

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