Airworthiness Directive · Amendment 39-18026 · Fuselage
The Boeing Company Airplanes
(1) This AD applies to The Boeing Company airplanes, certificated in any category, identified in paragraphs (c)(1)(i) and (c)(1)(ii) of this AD.
(i) Model 737-100, -200, -200C, -300, -400, and -500 series airplanes, as identified in Boeing Alert Service Bulletin 737-53A1197, dated August 25, 2006.
(ii) Model 737-300, -400, and -500 series airplanes, as identified in Boeing Alert Service Bulletin 737-53A1188, Revision 3, dated September 6, 2013.
(2) Installation of Supplemental Type Certificate (STC) ST01219SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/ebd1cec7b301293e86257cb30045557a/$FILE/ST01219SE.pdf) does not affect the ability to accomplish the actions required by this AD. For airplanes on which STC ST01219SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/ebd1cec7b301293e86257cb30045557a/$FILE/ST01219SE.pdf) is installed, therefore, 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) 2008-17-03 for certain The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. AD 2008-17-03 required repetitive inspections to detect fuselage frame cracking, and corrective action if necessary. AD 2008-17-03 also provided for optional terminating action (repair/ preventive change) for the repetitive inspections. This new AD adds airplanes to the applicability, but does not provide terminating action for the newly added airplanes. This AD was prompted by reports of cracks found at the cutout in the web of body station frame 303.9 inboard of stringer 16L, as well as a new report of cracking found on an airplane not identified in the applicability of AD 2008-17-03. We are issuing this AD to detect and correct fuselage frame cracking, which could prevent the left forward entry door from sealing correctly, and could cause in-flight decompression of the airplane.
This paragraph restates the requirements of paragraph (f) of AD 2008-17-03, Amendment 39-15641 (73 FR 48288, August 19, 2008), with revised service information and airplane groupings. For airplanes identified as Group 1 in Boeing Alert Service Bulletin 737-53A1188, Revision 3, dated September 6, 2013: Do detailed and high frequency eddy current (HFEC) inspections in the web and doubler around the slotted holes in the frame web at stringers 15L and 16L, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1188, Revision 2, dated May 9, 2007; or Boeing Alert Service Bulletin 737-53A1188, Revision 3, dated September 6, 2013, except as provided by paragraph (j)(4) of this AD. Do the inspections at the applicable time specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-53A1188, Revision 3, dated September 6, 2013. Do all applicable corrective actions before further flight in accordance with Boeing Alert Service Bulletin 737-53A1188, Revision 2, dated May 9, 2007; or Boeing Alert Service Bulletin 737-53A1188, Revision 3, dated September 6, 2013; except as provided by paragraph (j)(3) of this AD. Repeat the inspections at intervals not to exceed 4,500 flight cycles, until accomplishment of the repair/preventive change in accordance with Boeing Alert Service Bulletin 737-53A1188, Revision 2, dated May 9, 2007; or Boeing Alert Service Bulletin 737-53A1188, Revision 3, dated September 6, 2013; which terminates the repetitive inspection requirements for the airplanes identified in this paragraph. A repair/preventive change done using Boeing Alert Service Bulletin 737-53A1188, dated April 9, 1998; or Boeing Alert Service Bulletin 737-53A1188, Revision 1, dated March 18, 1999; does not terminate the repetitive inspections, but the repetitive inspections may be terminated after the existing kit is replaced with a new kit in accordance with paragraph 3.B., Part II, step 3, or Part III, step 3, of Boeing Alert Service Bulletin 737-53A1188, Revision 2, dated May 9, 2007. As of the effective date of this AD, only Boeing Alert Service Bulletin 737-53A1188, Revision 3, dated September 6, 2013, may be used to do the actions required by this paragraph.
Note 1 to paragraph (g) of this AD: Airplanes identified as Group 1 in Boeing Alert Service Bulletin 737-53A1188, Revision 3, dated September 6, 2013, are the same as those identified in Boeing Alert Service Bulletin 737-53A1188, Revision 2, dated May 9, 2007.
This paragraph restates the requirements of paragraph (g) of AD 2008-17-03, Amendment 39-15641 (73 FR 48288, August 19, 2008). For airplanes identified in Boeing Alert Service Bulletin 737-53A1197, dated August 25, 2006: Do an ultrasound inspection of the slot-shaped cutout in the web for the door stop strap at stringer 16L, an HFEC inspection of the web along the upper and lower edges of the doubler around the doorstop strap at stringer 16L, and a detailed inspection of the web around the doubler for the cutout at stringer 16L, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1197, dated August 25, 2006, except as provided by paragraph (j)(4) of this AD. Do the inspections at the applicable time specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-53A1197, dated August 25, 2006, except as provided by paragraph (j)(2) of this AD. Do all applicable corrective actions before further flight in accordance with Boeing Alert Service Bulletin 737-53A1197, dated August 25, 2006, except as provided by paragraph (j)(3) of this AD. Repeat the inspections at intervals not to exceed 4,500 flight cycles, until accomplishment of the repair/preventive change in accordance with Boeing Alert Service Bulletin 737-53A1197, dated August 25, 2006, which terminates the repetitive inspections.
For airplanes identified as Group 2 in Boeing Alert Service Bulletin 737-53A1188, Revision 3, dated September 6, 2013: At the applicable times specified in Table 3 of paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-53A1188, Revision 3, dated September 6, 2013, except as required by paragraph (j)(1) of this AD: Do detailed and HFEC inspections for cracking in the web of the body station 303.9 frame at stringer 15L, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1188, Revision 3, dated September 6, 2013, except as required by paragraphs (j)(3) and (j)(4) of this AD. Do all applicable corrective actions before further flight. Repeat the inspection thereafter at the applicable time specified in Table 3 of paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-53A1188, Revision 3, dated September 6, 2013. Accomplishment of a repair using a method approved in accordance with the procedures specified in paragraph (k) of this AD terminates the repetitive inspections required by this paragraph for the area covered by the repair.
(1) Where Boeing Alert Service Bulletin 737-53A1188, Revision 3, dated September 6, 2013, specifies a compliance time “after the Revision 3 date 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 737-53A1197, dated August 25, 2006, specifies a compliance time “After the Date of this Service Bulletin,” this AD requires compliance for paragraph (h) of this AD within the specified time after September 23, 2008 (the effective date of AD 2008-17-03, Amendment 39-15641 (73 FR 48288, August 19, 2008)). For the initial inspection, the grace period for airplanes that have exceeded the specified threshold is extended to 4,500 flight cycles after September 23, 2008 (the effective date of AD 2008-17-03).
(3) Where Boeing Alert Service Bulletin 737-53A1188, Revision 2, dated May 9, 2007; Boeing Alert Service Bulletin 737-53A1188, Revision 3, dated September 6, 2013; and Boeing Alert Service Bulletin 737-53A1197, dated August 25, 2006; specify to contact Boeing for appropriate action, including repair of damage outside the scope of the service information, repair using a method approved in accordance with the procedures specified in paragraph (k) of this AD.
(4) This AD does not require the specific access and restoration instructions identified in the Work Instructions of Boeing Alert Service Bulletin 737-53A1188, Revision 3, dated September 6, 2013; and Boeing Alert Service Bulletin 737-53A1197, dated August 25, 2006. Operators may perform those actions in accordance with approved maintenance procedures.
