AD 2026-16-06 Airworthiness Directives; The Boeing Company Airplanes

Models named: 767-300, -300F series. Read the applicability below — it usually turns on serial or part numbers too.

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.

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

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 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- 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.

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.

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