Airworthiness Directive · Amendment 39-18943 · 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 737-53A1354, dated December 2, 2016.
(2) Installation of Supplemental Type Certificate (STC) ST01219SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/ebd1cec7b301293e86257cb30045557a/$FILE/ST01219SE.pdf) 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 frame web cracking at certain locations. This AD requires repetitive inspections in certain locations of the frame web, and corrective action if necessary. We are issuing this AD to address the unsafe condition on these products.
For airplanes identified as Group 1 in Boeing Alert Service Bulletin 737-53A1354, dated December 2, 2016: Within 120 days after the effective date of this AD, accomplish actions to correct the unsafe condition (e.g. inspections, repairs, and corrective actions), using a method approved in accordance with the procedures specified in paragraph (j) of this AD.
For airplanes identified as Group 2 in Boeing Alert Service Bulletin 737-53A1354, dated December 2, 2016: At the applicable times specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-53A1354, dated December 2, 2016, except as required by paragraph (i)(1) of this AD: Do the inspections specified in paragraphs (h)(1), (h)(2), and (h)(3) of this AD, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1354, dated December 2, 2016, except as required by paragraph (i)(2) of this AD. Repeat the inspections thereafter at the applicable times specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-53A1354, dated December 2, 2016. Do all applicable corrective actions before further flight.
(1) Do high frequency eddy current (HFEC), detailed, and general visual inspections for cracking of the left side section 41 lower lobe frames, between STA 268.25 and STA 360.
(2) Do detailed and general visual inspections for cracking of the right side section 41 lower lobe frames, between STA 268.25 and STA 360.
(3) Do an HFEC inspection for cracking of the right side STA 312, STA 328, and STA 344, section 41 lower lobe frames.
(1) Where paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-53A1354, dated December 2, 2016, specifies a compliance time “after the original date of this service bulletin,” this AD requires compliance within the specified compliance time after the effective date of this AD.
(2) Where Boeing Alert Service Bulletin 737-53A1354, dated December 2, 2016, specifies to contact Boeing for repair instructions, and specifies that action as Required for Compliance (RC), this AD requires repair before further flight using a method approved in accordance with the procedures specified in paragraph (j) of this AD.
