Airworthiness Directive · Amendment 39-23280 · Wings
The Boeing Company Airplanes
This AD applies to The Boeing Company Model 767-200, -300, -300F, and -400ER series airplanes, certificated in any category, as identified in Boeing Alert Requirements Bulletin 767-57A0148 RB, dated October 10, 2024.
The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767-200, -300, -300F, and -400ER series airplanes. This AD was prompted by discovery of a crack at one of the forward lower fastener holes following replacement of a cracked underwing longeron (UWL) fitting. This AD requires performing an open hole high frequency eddy current (HFEC) inspection for cracks of the fastener holes common to the UWL fitting, upper drag splice angle, and lower drag splice angle, and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
Except as specified by paragraph (h) of this AD: At the applicable times specified in the “Compliance” paragraph of Boeing Alert Requirements Bulletin 767-57A0148 RB, dated October 10, 2024, do all applicable actions identified in, and in accordance with, the Accomplishment Instructions of Boeing Alert Requirements Bulletin 767-57A0148 RB, dated October 10, 2024.
Note 1 to paragraph (g): Guidance for accomplishing the actions required by this AD can be found in Boeing Alert Service Bulletin 767-57A0148, dated October 10, 2024, which is referred to in Boeing Alert Requirements Bulletin 767-57A0148 RB, dated October 10, 2024.
(1) Where the Compliance Time column of the tables in the “Compliance” paragraph of Boeing Alert Requirements Bulletin 767-57A0148 RB, dated October 10, 2024, refers to the original issue date of Requirements Bulletin 767-57A0148 RB, this AD requires using the effective date of this AD.
(2) Where the Compliance Time column of tables 3 and 4 in the “Compliance” paragraph of Boeing Alert Requirements Bulletin 767-57A0148 RB, dated October 10, 2024, specifies a compliance time of within 22,000 flight cycles or 80,000 flight hours after the replacement of the underwing longeron fitting, whichever occurs first, this AD requires that the compliance time be calculated from when replacement of the underwing longeron fitting was done using Boeing Alert Requirements Bulletin 767-57A0148 RB, dated October 10, 2024; or Boeing Alert Service Bulletin 767-57A0126, Revision 1, dated November 9, 2011; Revision 2, dated March 12, 2012; Revision 3, dated November 8, 2012; Revision 4, dated April 17, 2014; or Revision 5, dated April 7, 2016.
(3) Where Boeing Alert Requirements Bulletin 767-57A0148 RB, dated October 10, 2024, specifies contacting Boeing for repair instructions, this AD requires doing the repair using a method approved in accordance with the procedures specified in paragraph (i) of this AD.
(4) During application of any cap seal to a fastener, fastener head, and fastener threads and collars inside the tank, as required by this AD, the cap seal must be applied with a thickness equal to or greater than the dimensions specified in figure 1 to paragraph (h)(4) of this AD.
(5) Where Condition 3 (Action 2) of table 1 of the “Work Instructions” paragraph of Boeing Alert Requirements Bulletin 767-57A0148 RB, dated October 10, 2024, specifies to repeat the open hole high frequency eddy current (HFEC) inspection at any hole(s) using “figure 3” as the method of compliance, this AD requires, at oversize hole repair location(s), doing an open hole HFEC inspection of the fitting and the angles for any crack using “figure 35” as the method of compliance.
(6) Where the “Action” column of step 5 of figures 6, 8, and 10 of Boeing Alert Requirements Bulletin 767-57A0148 RB, dated October 10, 2024, specifies “FITTING, UNDERWING LONGERON, LH”, this AD requires replacing that text with “FITTING, UNDERWING LONGERON, RH”.
(7) Where step 15 of figures 15 through 28 of Boeing Alert Requirements Bulletin 767-57A0148 RB, dated October 10, 2024, specifies cap sealing fasteners (i.e., applying cap seal to wing tank fasteners internally with BMS 5-45), this AD requires cap sealing all fasteners installed in accordance with steps 8 and 11 of the applicable figure in Boeing Alert Requirements Bulletin 767-57A0148 RB, dated October 10, 2024.
(8) Where step 11 of figures 23 through 26 of Boeing Alert Requirements Bulletin 767-57A0148 RB, dated October 10, 2024, specifies installing a quantity of 8 fasteners, this AD requires installing 7 fasteners.
(9) Where the “Identification” column of step 9 of figures 23 through 26 of Boeing Alert Requirements Bulletin 767-57A0148 RB, dated October 10, 2024, specifies to install BACS40R021C032F, this AD requires installing BACS40R021C037F.
(10) Where the “Step” column of figure 34 of Boeing Alert Requirements Bulletin 767-57A0148 RB, dated October 10, 2024, refers to step 2, this AD requires reidentifying step 2 as an additional step 1 task.
