Airworthiness Directive · Amendment 39-19623 · Fuselage
The Boeing Company Airplanes
(1) This AD applies to The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 737-53A1360, dated June 21, 2018.
(2) Installation of Supplemental Type Certificate (STC) ST01219SE does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01219SE is installed, a “change in product” alternative method of compliance (AMOC) approval request is not necessary to comply with the requirements of 14 CFR 39.17.
We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by reports of cracking in the frame web, frame integral inboard chord, and fail-safe chord on multiple airplanes in multiple locations between stringers S-10 and S- 17 above the passenger floor, in addition to an evaluation by the design approval holder (DAH) indicating that certain fuselage frame splices are subject to widespread fatigue damage (WFD). This AD requires repetitive inspections of certain fuselage upper frames, side frames, fail-safe chords, inboard chords, frame webs, and stringers; an inspection for open tooling holes and the presence of repairs in certain inspection zones; and applicable on-condition actions. We are issuing this AD to address the unsafe condition on these products.
For airplanes identified as Group 1 in Boeing Alert Service Bulletin 737-53A1360, dated June 21, 2018: Within 120 days after the effective date of this AD, inspect the airplane and do all applicable on-condition actions using a method approved in accordance with the procedures specified in paragraph (k) of this AD.
For airplanes identified as Groups 2 through 9 in Boeing Alert Service Bulletin 737-53A1360, dated June 21, 2018, except as specified in paragraph (i) of this AD: At the applicable times specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-53A1360, dated June 21, 2018, do all applicable actions identified as “RC” (required for compliance) in, and in accordance with, the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1360, dated June 21, 2018.
(1) For purposes of determining compliance with the requirements of this AD: Where Boeing Alert Service Bulletin 737-53A1360, dated June 21, 2018, uses the phrase “the original issue date of this service bulletin,” this AD requires using “the effective date of this AD,” except where Boeing Alert Service Bulletin 737-53A1360, dated June 21, 2018, uses the phrase “the original issue date of this service bulletin” in a note or flag note.
(2) Where Boeing Alert Service Bulletin 737-53A1360, dated June 21, 2018, specifies contacting Boeing for repair instructions: This AD requires repair and applicable on-condition actions using a method approved in accordance with the procedures specified in paragraph (k) of this AD.
(3) Where Boeing Alert Service Bulletin 737-53A1360, dated June 21, 2018, specifies contacting Boeing for alternative inspections: This AD requires alternative inspections using a method approved in accordance with the procedures specified in paragraph (k) of this AD.
(4) For airplanes identified as Group 2 and Groups 4 through 9 in Boeing Alert Service Bulletin 737-53A1360, dated June 21, 2018, that have been modified to a cargo configuration: In addition to the actions required by paragraph (h) of this AD, the actions specified in Table 9, “Inspection of the Fuselage Frame Integral Inboard Chord and Web from STA 360 to STA 400, Right Side,” of Boeing Alert Service Bulletin 737-53A1360, dated June 21, 2018, must be done by doing all applicable actions identified as “RC” (required for compliance) in, and in accordance with, the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1360, dated June 21, 2018, at the applicable compliance times specified in Table 9, “Inspection of the Fuselage Frame Integral Inboard Chord and Web from STA 360 to STA 400, Right Side,” of Boeing Alert Service Bulletin 737-53A1360, dated June 21, 2018, except as specified in paragraphs (i)(1) and (i)(2) of this AD.
(1) Accomplishment of a preventative modification specified in Part 7 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1360, dated June 21, 2018, at a tooling hole location, terminates the repetitive inspections specified in Part 6 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1360, dated June 21, 2018, that are required by paragraph (h) of this AD, for that modified tooling hole location only.
(2) Accomplishment of a high frequency eddy current inspection specified in Part 9 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1360, dated June 21, 2018, terminates the repetitive inspections specified in Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1360, dated June 21, 2018, that are required by paragraph (h) of this AD, at the uppermost frame splice fastener location only.
