Airworthiness Directive · Amendment 39-19201 · Fuselage
The Boeing Company Airplanes
(1) This AD applies to all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes, certificated in any category.
(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) 2012-12-05, which applied to all The Boeing Company Model 737-100, -200, -200C, - 300, -400, and -500 series airplanes. AD 2012-12-05 required repetitive inspections for cracking under the stop fittings and intercostal flanges and for cracking of the intercostal web, attachment clips, stringer splice channels, frame, reinforcement angle, shear web, frame outer chord and inner chord; a one-time inspection to detect missing fasteners; repetitive inspections of the cargo barrier net fitting for cracking; repetitive inspections for cracking of the stringer S-15L aft intercostal; and repair or corrective action if necessary. For certain airplanes, this AD adds new repetitive inspections of certain areas of the frame inner chord, and applicable on-condition actions. This AD was prompted by reports of additional cracking in locations not covered by the inspections in AD 2012-12-05. We are issuing this AD to address the unsafe condition on these products.
This paragraph restates the requirements of paragraph (i) of AD 2012-12-05, with no changes. For all Model 737-100, -200, -200C, -300, -400, and -500 series airplanes, as identified in Boeing Alert Service Bulletin 737-53A1204, Revision 1, dated March 26, 2007: Before the accumulation of 15,000 total flight cycles, or within 4,500 flight cycles after November 1, 2005 (the effective date of AD 2005-20-03, Amendment 39-14296 (70 FR 56361, September 27, 2005) (“AD 2005-20-03”)), whichever occurs later: Do the inspections required by paragraphs (i) and (j) of this AD.
This paragraph restates the requirements of paragraph (j) of AD 2012-12-05, with no changes. For all Model 737-200C series airplanes, as identified in Boeing Alert Service Bulletin 737-53A1204, Revision 1, dated March 26, 2007: Before the accumulation of 15,000 total flight cycles, or within 4,500 flight cycles after September 9, 2009 (the effective date of AD 2009-16-14, Amendment 39-15987 (74 FR 38901, August 5, 2009) (“AD 2009-16-14”)), whichever occurs later, do the inspection required by paragraph (k) of this AD.
This paragraph restates the requirements of paragraph (k) of AD 2012-12-05, with no changes. For Group 1 airplanes identified in Boeing Alert Service Bulletin 737-53A1204, Revision 1, dated March 26, 2007: Perform a detailed inspection for cracking of the intercostal web, attachment clips, and stringer splice channels; and a high frequency eddy current (HFEC) inspection for cracking of the stringer splice channels located forward and aft of the forward entry door; and do all applicable corrective actions before further flight; in accordance with Parts 1 and 2 of the Work Instructions of Boeing Special Attention Service Bulletin 737-53-1204, dated June 19, 2003, or Boeing Alert Service Bulletin 737-53A1204, Revision 1, dated March 26, 2007; or in accordance with Parts 1, 2, 4, and 5 of the Work Instructions of Boeing Alert Service Bulletin 737-53A1204, Revision 2, dated June 24, 2010. After September 9, 2009 (the effective date of AD 2009-16-14), and until July 23, 2012 (the effective date of AD 2012-12-05), Boeing Alert Service Bulletin 737-53A1204, Revision 1, dated March 26, 2007; or Boeing Alert Service Bulletin 737-53A1204, Revision 2, dated June 24, 2010; may be used to accomplish the actions required by this paragraph. As of July 23, 2012, only Boeing Alert Service Bulletin 737-53A1204, Revision 2, dated June 24, 2010, may be used to accomplish the actions required by this paragraph.
This paragraph restates the requirements of paragraph (l) of AD 2012-12-05, with no changes. For Group 2 cargo airplanes identified in Boeing Alert Service Bulletin 737-53A1204, Revision 1, dated March 26, 2007: Perform a detailed inspection for cracking of the intercostal webs and attachment clips located forward of the forward entry door, and do all applicable corrective actions before further flight, in accordance with Part 3 of the Work Instructions of Boeing Special Attention Service Bulletin 737-53-1204, dated June 19, 2003, or Boeing Alert Service Bulletin 737-53A1204, Revision 1, dated March 26, 2007; or in accordance with Part 3 of Boeing Alert Service Bulletin 737-53A1204, Revision 2, dated June 24, 2010. After September 9, 2009 (the effective date of AD 2009-16-14), and until July 23, 2012 (the effective date of AD 2012-12-05), Boeing Alert Service Bulletin 737-53A1204, Revision 1, dated March 26, 2007; or Boeing Alert Service Bulletin 737-53A1204, Revision 2, dated June 24, 2010; may be used to accomplish the actions required by this paragraph. As of July 23, 2012, only Boeing Alert Service Bulletin 737-53A1204, Revision 2, dated June 24, 2010, may be used to accomplish the actions required by this paragraph.
This paragraph restates the requirements of paragraph (m) of AD 2012-12-05, with no changes. For Group 2 cargo airplanes identified in Boeing Alert Service Bulletin 737-53A1204, Revision 1, dated March 26, 2007: Perform a detailed inspection for cracking of the intercostal webs and attachment clips located aft of the forward entry door, and do all applicable corrective actions before further flight, in accordance with Part 4 of the Work Instructions of Boeing Alert Service Bulletin 737-53A1204, Revision 1, dated March 26, 2007; or in accordance with Part 3 of Boeing Alert Service Bulletin 737-53A1204, Revision 2, dated June 24, 2010. As of July 23, 2012 (the effective date of AD 2012-12-05), only Boeing Alert Service Bulletin 737-53A1204, Revision 2, dated June 24, 2010, may be used to accomplish the actions required by this paragraph.
This paragraph restates the requirements of paragraph (n) of AD 2012-12-05, with no changes. Repeat the inspections required by paragraphs (i), (j), and (k) of this AD thereafter at intervals not to exceed 6,000 flight cycles after the previous inspection, or within 3,000 flight cycles after September 9, 2009, whichever occurs later.
This paragraph restates the requirements of paragraph (o) of AD 2012-12-05, with no changes. Do the actions required by paragraphs (g), (h), (i), (j), (k), and (l) of this AD by accomplishing all the applicable actions specified in the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737-53-1204, dated June 19, 2003; Boeing Alert Service Bulletin 737-53A1204, Revision 1, dated March 26, 2007; or Boeing Alert Service Bulletin 737-53A1204, Revision 2, dated June 24, 2010; except as provided by paragraphs (m)(1) and (m)(2) of this AD. After September 9, 2009 (the effective date of AD 2009-16-14), and until July 23, 2012 (the effective date of AD 2012-12-05), Boeing Alert Service Bulletin 737-53A1204, Revision 1, dated March 26, 2007; or Boeing Alert Service Bulletin 737-53A1204, Revision 2, dated June 24, 2010; may be used to accomplish the actions required by this paragraph. As of July 23, 2012, only Boeing Alert Service Bulletin 737-53A1204, Revision 2, dated June 24, 2010, may be used to accomplish the actions required by this paragraph.
(1) Where Boeing Special Attention Service Bulletin 737-53-1204, dated June 19, 2003; Boeing Alert Service Bulletin 737-53A1204, Revision 1, dated March 26, 2007; or Boeing Alert Service Bulletin 737-53A1204, Revision 2, dated June 24, 2010; specifies to contact Boeing for repair instructions: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (s) of this AD.
(2) Where Boeing Special Attention Service Bulletin 737-53-1204, dated June 19, 2003; or Boeing Alert Service Bulletin 737-53A1204, Revision 1, dated March 26, 2007; specifies a compliance time relative to the date of a service bulletin, this AD requires compliance relative to September 9, 2009 (the effective date of AD 2009-16-14). Where Boeing Special Attention Service Bulletin 737-53-1204, dated June 19, 2003; or Boeing Alert Service Bulletin 737-53A1204, Revision 1, dated March 26, 2007; specifies a compliance time relative to the date of the initial release of a service bulletin, this AD requires compliance relative to November 1, 2005 (the effective date of AD 2005-20-03).
This paragraph restates exceptions to Boeing Alert Service Bulletin 737-53A1204, Revision 2, dated June 24, 2010, specified in paragraph (r) of AD 2012-12-05, with no changes.
(1) The access and restoration instructions identified in the Work Instructions of Boeing Alert Service Bulletin 737-53A1204, Revision 2, dated June 24, 2010, are not required by this AD. Operators may perform those actions in accordance with approved maintenance procedures.
(2) The use of Boeing Drawing 65-88700 is not allowed when accomplishing the actions required by this AD in accordance with the Work Instructions of Boeing Alert Service Bulletin 737-53A1204, Revision 2, dated June 24, 2010.
This paragraph restates the requirements of paragraph (s) of AD 2012-12-05, with no changes. For Group 2 airplanes identified in Boeing Alert Service Bulletin 737-53A1204, Revision 2, dated June 24, 2010: Before the accumulation of 15,000 total flight cycles, or within 4,500 flight cycles after July 23, 2012 (the effective date of AD 2012-12-05), whichever occurs later, do initial detailed and HFEC inspections for cracking of the S-15L aft intercostal between body station (BS) 348.2 and BS 360, and do a detailed inspection of the cargo barrier net fitting at the intercostal, in accordance with Figure 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1204, Revision 2, dated June 24, 2010. If any cracking is found, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (s) of this AD. Repeat the inspections thereafter at intervals not to exceed 6,000 flight cycles.
(1) For airplanes identified as Group 1 and Group 3 in Boeing Alert Service Bulletin 737-53A1240, Revision 2, dated November 2, 2016: Except as required by paragraph (q) of this AD, at the applicable times specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-53A1240, Revision 2, dated November 2, 2016, do all applicable actions identified as “RC” (required for compliance) in, and in accordance with, the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1240, Revision 2, dated November 2, 2016.
(2) For airplanes identified as Group 2 in Boeing Alert Service Bulletin 737-53A1240, Revision 2, dated November 2, 2016: Within 120 days after the effective date of this AD, do actions to correct the unsafe condition using a method approved in accordance with the procedures specified in paragraph (s) of this AD.
(1) Where Boeing Alert Service Bulletin 737-53A1240, Revision 2, dated November 2, 2016, uses the phrase “after the Revision 2 date of this service bulletin,” for purposes of determining compliance with the requirements of this AD, the phrase “after the effective date of this AD” must be used.
(2) Where Boeing Alert Service Bulletin 737-53A1240, Revision 2, dated November 2, 2016, specifies contacting Boeing, and specifies that action as RC: This AD requires using a method approved in accordance with the procedures specified in paragraph(s) of this AD.
