Airworthiness Directive · Amendment 39-18214 · 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 737-53A1108, Revision 7, dated July 7, 2014.
(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) 98-22-10 for certain The Boeing Company Model 737-100, -200, -200C, and -300 series airplanes. AD 98-22-10 required repetitive inspections for cracking of the aft frame and frame support structure of the forward service doorway, and repair if necessary. AD 98-22-10 also provided an optional terminating action for the repetitive inspection requirements of that AD. This new AD requires new inspections and adds airplanes to the applicability; for certain airplanes, this new AD provides an optional preventive modification, which terminates the repetitive inspections. This AD was prompted by reports of fatigue cracking of the aft frame and frame support structure of the forward service doorway around the six doorstop fittings, and a determination that inspections are needed in additional locations and that additional airplanes might be subject to the identified unsafe condition. We are issuing this AD to detect and correct fatigue cracking of the aft frame and frame support structure of the forward service doorway around the six doorstop fittings, which could result in door deflection and loss of pressurization.
At the applicable times specified in tables 1 through 6 of paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-53A1108, Revision 7, dated July 7, 2014, except as required by paragraph (k)(1) of this AD: Do detailed inspections of the frame web between body station (STA) 332.1 and STA 344, intercostal T-brackets, intercostal T-chords, intercostals, and stringers, as applicable; do high frequency eddy current (HFEC) inspections for cracking of door stop intercostal T-brackets, intercostal web, door stop intercostal T-chords, intercostals, and stringers, as applicable; and do all applicable related investigative and corrective actions; in accordance with Parts 2 and 4 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1108, Revision 7, dated July 7, 2014, except as required by paragraphs (k)(2) through (k)(4) of this AD. Do all applicable related investigative and corrective actions before further flight. Repeat the inspections at the applicable times specified in tables 1 through 6 of paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-53A1108, Revision 7, dated July 7, 2014, until the terminating action specified in paragraph (h) of this AD is done.
For Group 1, Configuration 1; Group 1, Configuration 2; Group 2; Group 3; Group 4, Configuration 1; and Group 4, Configuration 2 airplanes identified in Boeing Alert Service Bulletin 737-53A1108, Revision 7, dated July 7, 2014: Accomplishment of a preventive modification in accordance with Part 5 of Boeing Alert Service Bulletin 737-53A1108, Revision 7, dated July 7, 2014, terminates the repetitive inspections required by paragraph (g) of this AD.
For Group 5 airplanes identified in Boeing Alert Service Bulletin 737-53A1108, Revision 7, dated July 7, 2014: Within 120 days after the effective date of this AD, inspect and repair any cracking using a method approved in accordance with the procedures specified in paragraph (m) of this AD. Repair any cracking, before further flight.
The post preventive modification inspections specified in tables 9 through 12 in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-53A1108, Revision 6, dated January 9, 2014; and Boeing Alert Service Bulletin 737-53A1108, Revision 7, dated July 7, 2014; are not required by this AD.
Note 1 to paragraph (j) of this AD: Tables 9 through 12 in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-53A1108, Revision 6, dated January 9, 2014; and Boeing Alert Service Bulletin 737-53A1108, Revision 7, dated July 7, 2014; specify that post preventive modification inspections may be used in support of compliance with section 121.1109(c)(2) or 129.109(b)(2) of the Federal Aviation Regulations (14 CFR 121.1109(c)(2) or 14 CFR 129.109(b)(2)). The corresponding actions specified in the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1108, Revision 6, dated January 9, 2014; and Boeing Alert Service Bulletin 737-53A1108, Revision 7, dated July 7, 2014; are not required by this AD.
(1) Where Boeing Alert Service Bulletin 737-53A1108, Revision 7, dated July 7, 2014, specifies a compliance time “after the issue date of Revision 6 of this service bulletin,” this AD requires compliance within the specified time after the effective date of this AD.
(2) Where Boeing Alert Service Bulletin 737-53A1108, Revision 7, dated July 7, 2014, specifies to contact Boeing for repair instructions: Before further flight, repair the cracking using a method approved in accordance with the procedures specified in paragraph (m) of this AD.
(3) Where Boeing Alert Service Bulletin 737-53A1108, Revision 7, dated July 7, 2014, specifies accomplishment of a preventative modification in accordance with “Revision 6 of this service bulletin,” this AD requires accomplishment of those actions to be done in accordance with Boeing Alert Service Bulletin 737-53A1108, Revision 7, dated July 7, 2014.
(4) Where table 4 in paragraph 1.E, “Compliance,” of Boeing Alert Service Bulletin 737-53A1108, Revision 7, dated July 7, 2014, specifies repairing a condition identified as any crack found in “an intercostal,” this AD requires repairing a condition identified as any crack found in “an intercostal or attaching stringers.”
