Proposed Rule2026-01370
Airworthiness Directives; The Boeing Company Airplanes
Primary source
Metadata and text below are from the Federal Register, a public-domain U.S. government work. Always verify the official published version before relying on it for any legal matter.
Published
January 26, 2026
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA proposes to supersede Airworthiness Directive (AD) 2018-11-14, which applies to certain The Boeing Company Model 767-300 and -300F series airplanes. AD 2018-11-14 requires 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 requires 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. Since the FAA issued AD 2018-11-14, it was determined 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. In addition, it was determined that airplanes who have installed Supplemental Type Certificate (STC) ST01920SE and removed the STC winglets are also affected by the unsafe condition. This proposed AD would continue to require the actions in AD 2018-11-14, add airplanes to the applicability who have installed STC ST01920SE and removed the STC winglets, and, for certain airplanes, would require 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 proposing this AD to address the unsafe condition on these products.
Full Text
<html>
<head>
<title>Federal Register, Volume 91 Issue 16 (Monday, January 26, 2026)</title>
</head>
<body><pre>
[Federal Register Volume 91, Number 16 (Monday, January 26, 2026)]
[Proposed Rules]
[Pages 3084-3092]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2026-01370]
[[Page 3084]]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2026-0023; Project Identifier AD-2025-00427-T]
RIN 2120-AA64
Airworthiness Directives; The Boeing Company Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD)
2018-11-14, which applies to certain The Boeing Company Model 767-300
and -300F series airplanes. AD 2018-11-14 requires 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
requires 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. Since the FAA issued AD 2018-11-14, it was determined
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. In addition, it was determined that
airplanes who have installed Supplemental Type Certificate (STC)
ST01920SE and removed the STC winglets are also affected by the unsafe
condition. This proposed AD would continue to require the actions in AD
2018-11-14, add airplanes to the applicability who have installed STC
ST01920SE and removed the STC winglets, and, for certain airplanes,
would require 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 proposing this AD to
address the unsafe condition on these products.
DATES: The FAA must receive comments on this proposed AD by March 12,
2026.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
<bullet> Federal eRulemaking Portal: Go to <a href="http://regulations.gov">regulations.gov</a>. Follow
the instructions for submitting comments.
<bullet> Fax: 202-493-2251.
<bullet> Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590.
<bullet> Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
AD Docket: You may examine the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
Docket No. FAA-2026-0023; 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 NPRM, any comments received, and other
information. The street address for Docket Operations is listed above.
Material Incorporated by Reference:
<bullet> For Aviation Partners Boeing material identified in this
proposed AD, contact Aviation Partners Boeing, 2811 South 102nd St.,
Suite 200, Seattle, WA 98168; telephone 206-830-7699; email
<a href="/cdn-cgi/l/email-protection#d2b1b7a0a6bbb4bbb1b3a6bbbdbc92b3a4bbb3a6bbbdbca2b3a0a6bcb7a0a1fcb1bdbf"><span class="__cf_email__" data-cfemail="fc9f998e88959a959f9d88959392bc9d8a959d889593928c9d8e8892998e8fd29f9391">[email protected]</span></a>; website <a href="http://aviationpartnersboeing.com">aviationpartnersboeing.com</a>.
<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.
FOR FURTHER INFORMATION CONTACT: Sarah Illg, Aviation Safety Engineer,
FAA, 3960 Paramount Boulevard, Lakewood, CA 90712; phone: 206-231-3517;
email: <a href="/cdn-cgi/l/email-protection#dd8ebcafbcb5f39cf394b1b1ba9dbbbcbcf3bab2ab"><span class="__cf_email__" data-cfemail="02516370636a2c432c4b6e6e65426463632c656d74">[email protected]</span></a>.
SUPPLEMENTARY INFORMATION:
Comments Invited
The FAA invites you to send any written relevant data, views, or
arguments about this proposal. Send your comments using a method listed
under the ADDRESSES section. Include ``Docket No. FAA-2026-0023;
Project Identifier AD-2025-00427-T'' at the beginning of your comments.
The most helpful comments reference a specific portion of the proposal,
explain the reason for any recommended change, and include supporting
data. The FAA will consider all comments received by the closing date
and may amend the proposal because of those comments.
Except for Confidential Business Information (CBI) as described in
the following paragraph, and other information as described in 14 CFR
11.35, the FAA will post all comments received, without change, to
<a href="http://regulations.gov">regulations.gov</a>, including any personal information you provide. The
agency will also post a report summarizing each substantive verbal
contact received about this proposed AD.
Confidential Business Information
CBI is commercial or financial information that is both customarily
and actually treated as private by its owner. Under the Freedom of
Information Act (FOIA) (5 U.S.C. 552), CBI is exempt from public
disclosure. If your comments responsive to this NPRM contain commercial
or financial information that is customarily treated as private, that
you actually treat as private, and that is relevant or responsive to
this NPRM, it is important that you clearly designate the submitted
comments as CBI. Please mark each page of your submission containing
CBI as ``PROPIN.'' The FAA will treat such marked submissions as
confidential under the FOIA, and they will not be placed in the public
docket of this NPRM. Submissions containing CBI should be sent to Sarah
Illg, Aviation Safety Engineer, FAA, 3960 Paramount Boulevard,
Lakewood, CA 90712; phone: 206-231-3517; email: <a href="/cdn-cgi/l/email-protection#a1f2c0d3c0c98fe08fe8cdcdc6e1c7c0c08fc6ced7"><span class="__cf_email__" data-cfemail="b8ebd9cad9d096f996f1d4d4dff8ded9d996dfd7ce">[email protected]</span></a>.
Any commentary that the FAA receives that is not specifically
designated as CBI will be placed in the public docket for this
rulemaking.
Background
The FAA issued AD 2018-11-14, Amendment 39-19302 (83 FR 25885, June
5, 2018) (AD 2018-11-14), for certain The Boeing Company Model 767-300
and -300F series airplanes. AD 2018-11-14 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.
AD 2018-11-14 requires HFEC inspections for cracking of the lower
outboard wing skin, and repair or modification if necessary. AD 2018-
11-14 also requires 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. The FAA issued AD 2018-11-14 to prevent fatigue cracking
in the lower outboard wing skin, which could result in failure and
subsequent separation of the wing and winglet and consequent reduced
controllability of the airplane.
Actions Since AD 2018-11-14 Was Issued
Since the FAA issued AD 2018-11-14, an operator found cracks in the
lower wing skin during a post-repair inspection of an affected
airplane. The post-repair inspection was an external surface HFEC
inspection and was not mandated by AD 2018-11-14, which refers to
Aviation Partners Boeing
[[Page 3085]]
Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017, as the
appropriate source of service information for accomplishing certain
inspections. The area of the lower wing skin in the vicinity of the
critical inboard end fasteners of previously installed repair doublers,
approved by the Boeing Commercial Airplanes Organization Designation
Authorization (ODA) and prior to the issuance of the Aviation Partners
Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017,
was inadvertently omitted from the internal HFEC inspection, for Group
3 airplanes, specified in Aviation Partners Boeing Service Bulletin
AP767-57-010, Revision 11, dated April 3, 2017, and could result in the
inadequate opportunity of crack detection at the critical fasteners.
The FAA determined 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 in order to address the
unsafe condition.
Aviation Partners Boeing issued Service Bulletin AP767-57-010,
Revision 14, dated November 17, 2025, to add the inspections at the
critical inboard end fasteners of installed repair doublers for Group 3
airplanes, and add one additional airplane to the list of affected
Group 3 airplanes.
In addition, the FAA determined that airplanes that have ever been
modified by STC ST01920SE are affected by the unsafe condition but not
all airplanes that were modified by STC ST01920SE were identified in
the applicability of AD 2018-11-14. AD 2018-11-14 identified airplanes
``with Aviation Partners Boeing winglets installed; as identified in
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. However, operators who
have modified their airplanes via STC ST01920SE and have removed the
STC winglets are also applicable.
Although the ``Effectivity'' of 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, only specify ``airplanes with blended winglets,'' the
bulletins also apply to the Group 1, 2, and 3 airplanes who have
installed STC ST01920SE and removed the STC winglets. The FAA has
revised the applicability of this proposed AD to refer to new Aviation
Partners Boeing service bulletins that have updated effectivity
statements that clarify all airplanes with STC ST01920SE are affected
and must do applicable actions to address the unsafe condition.
FAA's Determination
The FAA is issuing this NPRM after determining that the unsafe
condition described previously is likely to exist or develop on other
products of the same type design.
Material Incorporated by Reference Under 1 CFR Part 51
The FAA reviewed 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 proposed AD would also require 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.
Proposed AD Requirements in This NPRM
This proposed AD would retain all of the requirements of AD 2018-
11-14, add airplanes that have ever been modified by STC ST01920SE and
removed the STC winglets to the applicability, and for certain
airplanes, would require 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.
Costs of Compliance
The FAA estimates that this AD, if adopted as proposed, would
affect 195 airplanes of U.S. registry. The FAA estimates the following
costs to comply with this proposed AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Parts Cost on U.S.
Action Labor cost 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:
[[Page 3086]]
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 proposed 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.
The FAA is issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, General requirements.
Under that section, Congress charges the FAA with promoting safe flight
of civil aircraft in air commerce by prescribing regulations for
practices, methods, and procedures the Administrator finds necessary
for safety in air commerce. This regulation is within the scope of that
authority because it addresses an unsafe condition that is likely to
exist or develop on products identified in this rulemaking action.
Regulatory Findings
The FAA has determined that this proposed AD would not have
federalism implications under Executive Order 13132. This proposed AD
would not have a substantial direct effect on the States, on the
relationship between the national government and the States, or on the
distribution of power and responsibilities among the various levels of
government.
For the reasons discussed above, I certify that the proposed
regulation:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866,
(2) Would not affect intrastate aviation in Alaska, and
(3) Would not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
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:
The Boeing Company: Docket No. FAA-2026-0023; Project Identifier AD-
2025-00427-T.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) by March 12, 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, as specified in
paragraph 1.A.1 of Aviation 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.
(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.
[[Page 3087]]
(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 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
[[Page 3088]]
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 AP767-57-010, 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-
[[Page 3089]]
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, AIR-520, Continued Operational Safety
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.
(j) Retained Exceptions to Service Information Specifications With No
Changes
This paragraph retains the exceptions 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
[[Page 3090]]
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; 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 (o)(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) Except as required by paragraph (o)(3) of this AD 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.
(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
[[Page 3091]]
paragraphs (m)(3)(i) and (m)(2)(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) Except as required by paragraph (o)(3) of this AD 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.
(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 Commercial Airplanes Organization
Designation Authorization (ODA) that has been authorized by the
Manager, AIR-520, Continued Operational Safety 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 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: <a href="/cdn-cgi/l/email-protection#3a7b7775797a5c5b5b145d554c"><span class="__cf_email__" data-cfemail="783935373b381e1919561f170e">[email protected]</span></a>. 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 Company Organization Designation
Authorization (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) Related 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: <a href="/cdn-cgi/l/email-protection#c390a2b1a2abed82ed8aafafa483a5a2a2eda4acb5"><span class="__cf_email__" data-cfemail="3b685a495a53157a157257575c7b5d5a5a155c544d">[email protected]</span></a>.
(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 [DATE 35 DAYS
AFTER PUBLICATION OF THE FINAL RULE].
(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, 2811 South 102nd St., Suite 200,
Seattle, WA 98168; telephone 206-830-7699; email
<a href="/cdn-cgi/l/email-protection#16757364627f707f7577627f79785677607f77627f797866776462787364653875797b"><span class="__cf_email__" data-cfemail="2e4d4b5c5a4748474d4f5a4741406e4f58474f5a4741405e4f5c5a404b5c5d004d4143">[email protected]</span></a>; website
<a href="http://aviationpartnersboeing.com">aviationpartnersboeing.com</a>.
(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.
[[Page 3092]]
(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 <a href="http://www.archives.gov/federal-register/cfr/ibr-locations">www.archives.gov/federal-register/cfr/ibr-locations</a> or email <a href="/cdn-cgi/l/email-protection#2147530f484f5251444255484e4f614f4053400f464e57"><span class="__cf_email__" data-cfemail="ed8b9fc384839e9d888e99848283ad838c9f8cc38a829b">[email protected]</span></a>.
Issued on January 21, 2026.
Peter A. White,
Deputy Director, Integrated Certificate Management Division, Aircraft
Certification Service.
[FR Doc. 2026-01370 Filed 1-23-26; 8:45 am]
BILLING CODE 4910-13-P
</pre><script data-cfasync="false" src="/cdn-cgi/scripts/5c5dd728/cloudflare-static/email-decode.min.js"></script></body>
</html>Indexed from Federal Register on January 26, 2026.
This is legal information, not legal advice. Laws vary by jurisdiction and change frequently. Always verify current law with official sources and consult a licensed attorney in your jurisdiction for advice on your specific situation.