Airworthiness Directive · Amendment 39-22129 · Fuselage
The Boeing Company Airplanes
This AD applies to The Boeing Company Model 757-200, -200CB, and -300 series airplanes, certificated in any category, as identified in Boeing Alert Requirements Bulletin 757-53A0112 RB, Revision 1, dated June 17, 2022.
The FAA is superseding Airworthiness Directive (AD) 2019-23- 06, which applied to certain The Boeing Company Model 757-200, -200CB, and -300 series airplanes. AD 2019-23-06 required, depending on configuration, a general visual inspection for any previous repair, such as any reinforcing repair or local frame replacement repair, repetitive open hole high frequency eddy current (HFEC) inspections for any crack of the fuselage frame web fastener holes, on the left and right side of the airplane, and applicable on-condition actions. This AD was prompted by a determination that certain compliance times must be reduced. This AD requires the actions specified in AD 2019-23-06 with reduced compliances times for certain actions. The FAA is issuing this AD to address the unsafe condition on these products.
(1) For all airplanes except those identified in paragraphs (g)(2) through (4) of this AD: Except as specified by paragraph (h) of this AD, at the applicable times specified in the “Compliance” paragraph of Boeing Alert Requirements Bulletin 757-53A0112 RB, Revision 1, dated June 17, 2022, do all applicable actions identified in, and in accordance with, the Accomplishment Instructions of Boeing Alert Requirements Bulletin 757-53A0112 RB, Revision 1, dated June 17, 2022.
Note 1 to paragraph (g): Guidance for accomplishing the actions required by this AD can be found in Boeing Alert Service Bulletin 757-53A0112, Revision 1, dated June 17, 2022, which is referred to in Boeing Alert Requirements Bulletin 757-53A0112 RB, Revision 1, dated June 17, 2022.
(2) Except as specified by paragraph (h) of this AD: For airplanes on which Aviation Partners Boeing blended or scimitar blended winglets are installed in accordance with Supplemental Type Certificate (STC) ST01518SE, at the applicable times specified in paragraph 1.E., “Compliance” of Aviation Partners Boeing Alert Service Bulletin AP757-53-002, Revision 3, dated August 14, 2019, do all applicable actions identified in, and in accordance with, the Accomplishment Instructions of Boeing Alert Requirements Bulletin 757-53A0112 RB, dated November 16, 2018.
(3) Except as specified by paragraph (h) of this AD: For Group 1 airplanes that have been converted from a passenger to freighter configuration using VT Mobile Aerospace Engineering (MAE) Inc. STC ST03562AT, at the applicable times specified for Group 2 airplanes in the “Compliance” paragraph of Boeing Alert Requirements Bulletin 757-53A0112 RB, Revision 1, dated June 17, 2022, do all applicable Group 2 actions, as identified in, and in accordance with, the Accomplishment Instructions of Boeing Alert Requirements Bulletin 757-53A0112 RB, Revision 1, dated June 17, 2022.
(4) Except as specified by paragraph (h) of this AD: For Group 4 airplanes that have been converted from a passenger to freighter configuration using VT MAE Inc. STC ST03562AT, at the applicable times specified for Group 5 airplanes in the “Compliance” paragraph of Boeing Alert Requirements Bulletin 757-53A0112 RB, Revision 1, dated June 17, 2022, do all applicable Group 5 actions as identified in, and in accordance with, the Accomplishment Instructions of Boeing Alert Requirements Bulletin 757-53A0112 RB, Revision 1, dated June 17, 2022.
(1) Where the Condition and Compliance Time columns of the tables in the “Compliance” paragraph of Boeing Alert Requirements Bulletin 757-53A0112 RB, Revision 1, dated June 17, 2022, use the phrase “the original issue date of Requirements Bulletin 757-53A0112 RB,” this AD requires using “January 13, 2020 (the effective date of AD 2019-23-06).”
(2) Where the Condition and Compliance Time columns of the tables in the “Compliance” paragraph of Boeing Alert Requirements Bulletin 757-53A0112 RB, Revision 1, dated June 17, 2022, use the phrase “the Revision 1 date of Requirements Bulletin 757-53A0112 RB,” this AD requires using “the effective date of this AD.”
(3) Where Boeing Alert Requirements Bulletin 757-53A0112 RB, Revision 1, dated June 17, 2022, specifies contacting Boeing for repair instructions or for alternative inspections: This AD requires doing the repair, or doing the alternative inspections and applicable on-condition actions using a method approved in accordance with the procedures specified in paragraph (j) of this AD.
(4) Where the Condition and Compliance Time columns of the tables in the “Compliance” paragraph of Aviation Partners Boeing Alert Service Bulletin AP757-53-002, Revision 3, dated August 14, 2019, use the phrase “the original issue date of this service bulletin,” this AD requires using “January 13, 2020 (the effective date of AD 2019-23-06).”
(5) Where Aviation Partners Boeing Alert Service Bulletin AP757-53-002, Revision 3, dated August 14, 2019, specifies contacting Boeing for repair instructions or for alternative inspections: This AD requires doing the repair, or doing the alternative inspections and applicable on-condition actions using a method approved in accordance with the procedures specified in paragraph (j) of this AD.
(6) For Group 1 airplanes, as identified in Aviation Partners Boeing Alert Service Bulletin AP757-53-002, Revision 3, dated August 14, 2019, with less than 34,500 total flight cycles as of the effective date of this AD that have accomplished any eddy current inspection specified in Revision 1 or Revision 2 of Aviation Partners Boeing Alert Service Bulletin AP757-53-001 with no cracking found and have not accomplished any inspection specified in Revision 2 or Revision 3 of Aviation Partners Boeing Alert Service Bulletin AP757-53-002: The compliance time for the initial open hole high frequency eddy current (HFEC) inspection of the STA 1640 fuselage frame web fastener holes common to the S-14L and S-14R intercostal tee clip for any crack is at the applicable time specified in paragraph (h)(6)(i) or (ii) of this AD, whichever occurs later.
(i) Within 1,200 flight cycles after the most recent inspection was done in accordance with Revision 1 or Revision 2 of Aviation Partners Boeing Alert Service Bulletin AP757-53-001.
(ii) Within 500 flight cycles after the effective date of this AD not to exceed 5,600 flight cycles after the most recent inspection was done in accordance with Revision 1 or Revision 2 of Aviation Partners Boeing Alert Service Bulletin AP757-53-001.
(7) For Group 1 airplanes, as identified in Aviation Partners Boeing Alert Service Bulletin AP757-53-002, Revision 3, dated August 14, 2019, with 34,500 total flight cycles or more as of the effective date of this AD that have accomplished any eddy current inspection in accordance with Revision 1 or Revision 2 of Aviation Partners Boeing Alert Service Bulletin AP757-53-001 with no cracking found and have not accomplished any inspection specified in Revision 2 or Revision 3 of Aviation Partners Boeing Alert Service Bulletin AP757-53-002: The compliance time for the initial open hole HFEC inspection of the STA 1640 fuselage frame web fastener holes common to the S-14L and S-14R intercostal tee clip for any crack is at the applicable time specified in paragraph (h)(7)(i) or (ii) of this AD, whichever occurs later:
(i) Within 1,200 flight cycles after the most recent eddy current inspection was done in accordance with Revision 1 or Revision 2 of Aviation Partners Boeing Alert Service Bulletin AP757-53-001.
(ii) Prior to the accumulation of 35,000 total flight cycles, or within 30 days after the effective date of this AD, whichever occurs later.
(8) For Group 3 airplanes, as identified in Aviation Partners Boeing Alert Service Bulletin AP757-53-002, Revision 3, dated August 14, 2019, that as of the effective date of this AD have accomplished any eddy current inspection in accordance with Revision 1 or Revision 2 of Aviation Partners Boeing Alert Service Bulletin AP757 53-001, with no cracking found: The compliance time for the initial open hole HFEC inspection of the STA 1640 fuselage frame web fastener holes common to the S-14L and S-14R intercostal tee clip for any crack is at the applicable time specified in paragraph (h)(8)(i) or (ii) of this AD, whichever occurs later.
(i) Within 1,350 flight cycles after the most recent eddy current inspection was done as specified in Revision 1 or Revision 2 of Aviation Partners Boeing Alert Service Bulletin AP757-53-001.
(ii) Within 500 flight cycles after the effective date of this AD not to exceed 3,250 flight cycles after the most recent inspection was done in accordance with Revision 1 or Revision 2 of Aviation Partners Boeing Alert Service Bulletin AP757-53-001.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
Aircraft
