Airworthiness Directive · Amendment 39-18920 · 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 737-53A1267, Revision 1, dated March 8, 2016 (“ASB 737-53A1267, R1”).
(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 superseding Airworthiness Directive (AD) 2007-26-04 for certain The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. AD 2007-26-04 required repetitive inspections for cracking of certain fasteners, and repair if necessary; and a preventive modification, which terminated the repetitive inspections. This AD removes the mandatory modification; adds repetitive inspections of the skin for cracking, a one-time inspection for defects of the production countersunk rivets, and corrective actions if necessary; and adds an optional skin trim-out repair, which will terminate certain inspections. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that certain skin panels are subject to widespread fatigue damage (WFD). We are issuing this AD to address the unsafe condition on these products.
For airplanes identified as Group 2 in ASB 737-53A1267, R1: Within 120 days after the effective date of this AD, inspect the airplane and do all applicable corrective actions using a method approved in accordance with the procedures specified in paragraph (k) of this AD.
For airplanes identified as Group 1 in ASB 737-53A1267, R1: Except as specified in paragraph (j)(1) of this AD, at the applicable time specified in paragraph 1.E. “Compliance” of ASB 737-53A1267, R1, do the applicable actions specified in paragraphs (h)(1) and (h)(2) of this AD; and do all applicable corrective actions; in accordance with the Accomplishment Instructions of ASB 737-53A1267, R1, except as specified in paragraph (j)(2) of this AD and as provided by paragraph (i) of this AD. Do all applicable corrective actions before further flight. Repeat the applicable inspections specified in paragraph (h)(1) of this AD thereafter at the applicable intervals specified paragraph 1.E., “Compliance,” of ASB 737-53A1267, R1, except as provided by paragraph (i) of this AD.
(1) Do detailed inspections and high frequency eddy current (HFEC) surface inspections of the skin around the fastener heads for any crack on the forward and aft fastener columns, left and right sides, at STA 259.5 circumferential butt splice, in accordance with Parts 1, 2, 6, 7, 8, and 9 of the Accomplishment Instructions of ASB 737-53A1267, R1, as applicable.
(2) Do a one-time detailed inspection for any defect of the production countersunk rivet heads on both forward and aft fastener columns, left and right sides, at STA 259.5 circumferential butt splice, in accordance with Part 3 of the Accomplishment Instructions of ASB 737-53A1267, R1.
(1) For airplanes identified as Group 1, Configuration 1, in ASB 737-53A1267, R1: Doing the skin trim-out repair specified in Part 5 of the Accomplishment Instructions of ASB 737-53A1267, R1, terminates the initial and repetitive inspections required by paragraph (h) of this AD that are specified in Part 1 of the Accomplishment Instructions of ASB 737-53A1267, R1, only; all other inspections required by paragraph (h) of this AD must be done, except as provided by paragraph (i)(2) of this AD.
(2) For airplanes identified as Group 1, Configuration 1 in ASB 737-53A1267, R1: Doing the skin repair specified in Part 4 of the Accomplishment Instructions of ASB 737-53A1267, R1, terminates the initial and repetitive inspections required by paragraph (h) of this AD that are specified in Part 1 and Part 2 of the Accomplishment Instructions of ASB 737-53A1267, R1, for the repaired area only; all other inspections required by paragraph (h) of this AD must be done, except as provided by paragraph (i)(1) of this AD.
(1) Where paragraph 1.E., “Compliance,” of ASB 737-53A1267, R1, specifies a compliance time “after the Revision 1 date of this service bulletin,” this AD requires compliance within the specified compliance time after the effective date of this AD.
(2) Although ASB 737-53A1267, R1, specifies to contact Boeing for appropriate action, and specifies that action as “RC” (Required for Compliance), this AD requires repair before further flight using a method approved in accordance with the procedures specified in paragraph (k) of this AD.
