2014-22-06: Fuselage

Adoption of the Amendment \n\n\n\tAccordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: \n\nPART 39--AIRWORTHINESS DIRECTIVES \n\n0 1. The authority citation for part 39 continues to read as follows: \n\n\n\tAuthority: 49 U.S.C. 106(g), 40113, 44701. \n\nSec. 39.13 (Amended) \n\n0 2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD) 2005-07-12, Amendment 39-14036 (70 FR 17596, April 7, 2005), and adding the following new AD: \n\n2014-22-06 The Boeing Company: Amendment 39-18011 ; Docket No. FAA- 2013-0836; Directorate Identifier 2013-NM-126-AD. \n\n(a) Effective Date \n\n\n\tThis AD is effective December 17, 2014. \n\n(b) Affected ADs \n\n\n\tThis AD replaces AD 2005-07-12, Amendment 39-14036 (70 FR 17596, April 7, 2005). \n\n(c) Applicability \n\n\n\t(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 BoeingAlert Service Bulletin 737- 53A1241, Revision 1, dated June 11, 2013. \n\t(2) Installation of Supplemental Type Certificate (STC) ST01219SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/ rgstc.nsf/0/082838ee177dbf62862576a4005cdfc0/$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. \n\n(d) Subject \n\n\n\tAir Transport Association (ATA) of America Code 53, Fuselage. \n\n(e) Unsafe Condition \n\n\n\tThis AD was prompted by reports of new findings of cracking at various locations of the stations (STA) 277 to STA 291.5 frames and intercostals, including webs, chords, clips, and shear ties, between stringers 7R and 17R. We are issuing this AD to detect \n\n((Page 67047)) \n\nand correct fatigue cracking of the aft frame and frame support structure of the forward galley door, which could result in a severed fuselage frame web, rapid decompression of the airplane, and possible loss of the forward galley door. \n\n(f) Compliance \n\n\n\tComply with this AD within the compliance times specified, unless already done. \n\n(g) Group 1 Airplanes: Inspections and Corrective Actions \n\n\n\tFor airplanes identified as Group 1 in Boeing Alert Service Bulletin 737-53A1241, Revision 1, dated June 11, 2013: Within 120 days after the effective date of this AD, do inspections for cracking from STA 277 to STA 328, stringer 7R to 17R of the forward galley door cutout, using a method approved in accordance with the procedures specified in paragraph (m) of this AD. Do all applicable corrective actions before further flight using a method approved in accordance with the procedures specified in paragraph (m) of this AD. \n\n(h) Group 2 and Group 3 Airplanes: Inspections and Corrective Actions \n\n\n\t(1) For airplanes identified as Group 2 and Group 3 in Boeing Alert Service Bulletin 737-53A1241, Revision 1, dated June 11, 2013: Except as provided by paragraph (k)(2) of this AD, at the applicable times specified in tables 1 and 2 in paragraph 1.E, ''Compliance,'' of Boeing Alert Service Bulletin 737-53A1241, Revision 1, dated June 11, 2013, do detailed and surface high frequency eddy current (HFEC) inspections, as applicable, for cracking in the forward galley door cutout, in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1241, Revision 1, dated June 11, 2013. Repeat the detailed and surface HFEC inspections thereafter at the applicable intervals specified in tables 1 and 2 in paragraph 1.E, ''Compliance,'' of Boeing Alert Service Bulletin 737-53A1241, Revision 1, dated June 11, 2013. If any crack is found, before further flight, do all applicable corrective actions in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1241,Revision 1, dated June 11, 2013, except as required by paragraph (k)(1) of this AD. Accomplishment of a repair specified in Steps 1.a., 2.a., 6.a., or 6.b. of Part 2, of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1241, Revision 1, dated June 11, 2013, as applicable, and except as required by paragraph (k)(1) of this AD, terminates the inspections required by this paragraph for the repaired area(s) only. \n\t(2) Removal and replacement of a cracked part, in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1241, Revision 1, dated June 11, 2013, does not terminate the repetitive inspections required by paragraph (h)(1) of this AD. \n\n(i) Terminating Action \n\n\n\tThe inspections required by paragraph (h)(1) of this AD may be terminated at areas with repairs installed prior to the effective date of this AD, provided the repairs meet the conditions specified in note 11 or note 13 of paragraph 3.A., ''General Information,'' of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1241, Revision 1, dated June 11, 2013. \n\n(j) Optional Terminating Action \n\n\n\tAccomplishment of the preventive modification on the STA 291.5 frame web, in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1241, Revision 1, dated June 11, 2013, terminates the inspections required by paragraph (h)(1) of this AD for the area that is common to the preventive modification. \n\n\n\t(k) Exceptions to the Service Information \n\n\n\t(1) Where Boeing Alert Service Bulletin 737-53A1241, Revision 1, dated June 11, 2013, specifies to contact Boeing for a corrective action: Before further flight, do the applicable action using a method approved in accordance with the procedures specified in paragraph (m) of this AD. \n\t(2) Where paragraph 1.E., ''Compliance,'' of Boeing Alert Service Bulletin 737-53A1241, Revision 1, dated June 11, 2013, specifies a compliance time''after the date on Revision 1 of this service bulletin,'' this AD requires compliance within the specified compliance time after the effective date of this AD. \n\t(3) The title to each page of figure 5 of Boeing Alert Service Bulletin 737-53A1241, Revision 1, dated June 11, 2013, is incorrect and refers to ''Stringer 16R'' when it should refer to ''Stringer 14R.'' \n\n(l) Credit for Previous Actions \n\n\n\tThis paragraph provides credit for the actions specified in paragraph (h)(1) of this AD, if those actions were performed before the effective date of this AD using Boeing Alert Service Bulletin 737-53A1241, dated June 13, 2002, which is not incorporated by reference in this AD. \n\n(m) Alternative Methods of Compliance (AMOCs) \n\n\n\t(1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector orlocal Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in paragraph (n)(1) of this AD. Information may be emailed to: [email protected]. \n\t(2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. \n\t(3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. \n\t(4) AMOCs approved for the actions specified in AD 2005-07-12, Amendment 39-14036(70 FR 17596, April 7, 2005), are approved as AMOCs for the corresponding provisions of this AD. \n\n(n) Related Information \n\n\n\t(1) For more information about this AD, contact Alan Pohl, Aerospace Engineer, Airframe Branch, ANM-120S, FAA Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6450; fax: 425-917-6590; email: [email protected]. \n\t(2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (o)(3) and (o)(4) of this AD. \n\n(o) Material Incorporated by Reference \n\n\n\t(1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. \n\t(2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. \n\t(i) Boeing Alert Service Bulletin 737-53A1241, Revision 1, dated June11, 2013. (ii) Reserved. \n\t(3) For Boeing service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P. O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. \n\t(4) You may view this service information at FAA, Transport Airplane Directorate, 1601 Lind Ave. SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. \n\t(5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.