Airworthiness Directive · Amendment 39-17874 · Wings
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/0/2C6E3DBDDD36F91C862576A4005D64E2?OpenDocument&Highlight=st01219se) 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) 2014-03-06 for all the Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. AD 2014-03-06 required repetitive inspections for cracking of the aft support fitting for the main landing gear (MLG) beam, and the rear spar upper chord and rear spar web in the area of rear spar station (RSS) 224.14; and repair if necessary. This AD clarifies two paragraph references. This AD was prompted by a determination that two paragraph references were in error. We are issuing this AD to detect and correct cracking of the aft support fitting for the main landing gear (MLG) beam, and the rear spar upper chord and rear spar web in the area of rear spar station (RSS) 224.14, which could grow and result in a fuel leak and possible fire.
This paragraph restates the actions required by paragraph (g) of AD 2014-03-06, Amendment 39-17743 (79 FR 12368, March 5, 2014) with no changes. For airplanes identified in Group 1 of Boeing Special Attention Service Bulletin 737-57-1318, dated May 15, 2013: At the applicable time specified in paragraph 1.E., “Compliance,” of Boeing Special Attention Service Bulletin 737-57-1318, dated May 15, 2013, except as required by paragraph (i) of this AD, do inspections and applicable corrective actions using a method approved in accordance with the procedures specified in paragraph (j) of this AD.
This paragraph restates the actions required by the introductory text of paragraph (h) of AD 2014-03-06, Amendment 39-17743 (79 FR 12368, March 5, 2014) with no changes. For airplanes identified in Groups 2 through 7 of Boeing Special Attention Service Bulletin 737-57-1318, dated May 15, 2013: At the applicable time specified in paragraph 1.E., “Compliance,” of Boeing Special Attention Service Bulletin 737-57-1318, dated May 15, 2013, except as required by paragraph (i) of this AD, do high frequency eddy current inspections to detect cracking of the aft support fitting for the MLG beam, and the rear spar upper chord and rear spar web in the area of rear spar station 224.14, as applicable, in accordance with Option 1, 2, or 3 of the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737-57-1318, dated May 15, 2013.
(1) This paragraph restates the actions required by paragraph (h)(1) of AD 2014-03-06, Amendment 39-17743 (79 FR 12368, March 5, 2014) with no changes. If no crack is found, repeat the inspection thereafter at the time specified in paragraph 1.E., “Compliance,” of Boeing Special Attention Service Bulletin 737-57-1318, dated May 15, 2013, as applicable. Accomplishment of the inspection of the 12 fastener holes (locations 1-12) in accordance with Option 2, Action 3; or Option 3, Action 3; as specified in note (b) of tables 2 through 5 of paragraph 1.E., “Compliance,” of Boeing Special Attention Service Bulletin 737-57-1318, dated May 15, 2013; terminates only the corresponding inspections that include note (b) in the “Repeat Interval” column of the applicable table.
(2) This paragraph restates the actions required by paragraph (h)(2) of AD 2014-03-06, Amendment 39-17743 (79 FR 12368, March 5, 2014), with revised paragraph references to the introductory text of paragraph (h) and to paragraph (h)(1) of this AD to mandate corrective actions. If any crack is found during any inspection required by the introductory text of paragraph (h) or by paragraph (h)(1) of this AD, repair before further flight using a method approved in accordance with the procedures specified in paragraph (j) of this AD.
This paragraph restates the actions required by paragraph (i) of AD 2014-03-06, Amendment 39-17743 (79 FR 12368, March 5, 2014), with no changes. Where Boeing Special Attention Service Bulletin 737-57-1318, dated May 15, 2013, specifies a compliance time “after the original issue date of this service bulletin,” this AD requires compliance within the specified compliance time after April 9, 2014 (the effective date of AD 2014-03-06).
