Airworthiness Directive · Amendment 39-18192 · 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 737-53A1163, Revision 1, dated January 8, 2014.
(2) Installation of Supplemental Type Certificate (STC) ST01219SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/ebd1cec7b301293e86257cb30045557a/$FILE/ST01219SE.pdf http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/ebd1cec7b301293e86257cb30045557a/%24FILE/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 fatigue cracks found in the upper corners of the forward entry door skin cutout. This AD requires repetitive inspections for cracking in the upper corners of the forward entry door skin cutout, and repair if necessary. Accomplishment of this repair or a preventive modification terminates the repetitive inspections. We are issuing this AD to detect and correct cracking in the doorway upper corners, which could result in cabin depressurization.
(1) For airplanes identified in Boeing Alert Service Bulletin 737-53A1163, Revision 1, dated January 8, 2014, as Groups 1 and 2, Configuration 2, and Group 3: Before the accumulation of 27,000 total flight cycles, or within 4,500 flight cycles after the effective date of this AD, whichever occurs later, do an external detailed inspection for cracking of the skin assembly, and a low frequency eddy current (LFEC) inspection for cracking of the skin assembly and bear strap, and all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1163, Revision 1, dated January 8, 2014, except as required by paragraph (j) of this AD. Repeat the inspections thereafter at intervals not to exceed 4,500 flight cycles. Do all applicable corrective actions before further flight.
(2) For airplanes identified as Group 4 in Boeing Alert Service Bulletin 737-53A1163, Revision 1, dated January 8, 2014: Within 120 days after the effective date of this AD, do inspections of the skin assembly and bear strap and all applicable corrective actions using a method approved in accordance with the procedures specified in paragraph (m) of this AD.
(1) Accomplishment of the preventive change specified in Part II of the Accomplishment Instructions of Boeing Service Bulletin 737-53-1163, dated December 21, 1993; or the preventive modification specified in Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1163, Revision 1, dated January 8, 2014; terminates the inspection requirements specified in paragraph (g)(1) of this AD.
(2) Accomplishment of the repair specified in Part III of the Accomplishment Instructions of Boeing Service Bulletin 737-53-1163, dated December 21, 1993; or Part 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1163, Revision 1, dated January 8, 2014; terminates the inspection requirements specified in paragraph (g)(1) of this AD.
(3) For door corners that have a repair installed, as provided by Boeing, which inhibits the inspections required by paragraph (g)(1) of this AD, and approved before the effective date of this AD using FAA Form 8100-9, the inspection in paragraph (g)(1) of this AD is not required. Refer to the repair approval for any supplemental inspection of the repair area.
(1) For airplanes identified in Boeing Alert Service Bulletin 737-53A1163, Revision 1, dated January 8, 2014, as Groups 1 and 2, on which a repair or preventive modification has been installed in accordance with Boeing Service Bulletin 737-53-1163, dated December 21, 1993; or Boeing Alert Service Bulletin 737-53A1163, Revision 1, dated January 8, 2014: At the applicable time specified in table 3 of paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-53A1163, Revision 1, dated January 8, 2014, or within 4,500 flight cycles after the effective date of this AD, whichever occurs later, inspect the fuselage skin assembly, bear strap, and frame and sill outer chords, as applicable, for cracking, in accordance with table 3 of paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-53A1163, Revision 1, dated January 8, 2014. Repeat the inspection thereafter at the times specified in table 3 of paragraph 1.E., “Compliance” of Boeing Alert Service Bulletin 737-53A1163, Revision 1, dated January 8, 2014. If any crack is found during any inspection required by this paragraph, repair before further flight using a method approved in accordance with the procedures specified in paragraph (m) of this AD.
(2) The inspection requirement in paragraph (i)(1) of this AD does not apply to operators who have added the inspection program for this area specified in table 3 of paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-53A1163, Revision 1, dated January 8, 2014, in accordance with 14 CFR 121.1109(c)(2) or § 129.109(b)(2) to their FAA-approved maintenance program. These inspections may be used in support of compliance with 14 CFR 121.1109(c)(2) or § 129.109(b)(2).
If any cracking is found during any inspection required by this AD, and Boeing Alert Service Bulletin 737-53A1163, Revision 1, dated January 8, 2014, specifies to contact Boeing for appropriate action: Before further flight, repair the crack using a method approved in accordance with the procedures specified in paragraph (m) of this AD.
The Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1163, Revision 1, dated January 8, 2014, state that Group 1 and 2, Configuration 1 airplanes on which the repair or preventive modification has been installed as specified in Boeing Service Bulletin 737-53-1163, dated December 21, 1993, are not required to be inspected. However, this AD requires inspections of Group 1 and 2 airplanes, as identified in and in accordance with paragraph (i) of this AD, which correspond with table 3 of paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-53A1163, Revision 1, dated January 8, 2014.
