2016-25-09: 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\n\n\nSec. 39.13 (Amended) \n\n0 2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD) 2012-22-02, Amendment 39-17238 (77 FR 69739, November 21, 2012), and adding the following new AD: \n\n2016-25-09 The Boeing Company: Amendment 39-18735; Docket No. FAA- 2016-5598; Directorate Identifier 2016-NM-001-AD. \n\n(a) Effective Date \n\n\n\tThis AD is effective January 17, 2017. \n\n(b) Affected ADs \n\n\n\tThis AD replaces AD 2012-22-02, Amendment 39-17238 (77 FR 69739, November 21, 2012) (''AD 2012-22-02''). \n\n(c) Applicability \n\n\n\tThis AD applies to The Boeing Company Model 747-400, -400D, and -400F series airplanes, certificated in any category, as specified in Boeing Alert Service Bulletin 747-53A2784, Revision 2, dated August 20, 2015. \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 a determination that there were no inspection or repair procedures included in AD 2012-22-02 for airplanes with a station (STA) 320 crown frame web thickness less than 0.078 inch, or greater than or equal to 0.084 inch and less than or equal to 0.135 inch. We are issuing this AD to prevent complete fracture of the crown frame assembly, and consequent damage to the skin. Such damage could result in in-flight decompression of the airplane. \n\n(f) Compliance \n\n\n\tComply with this AD within the compliance times specified, unless already done. \n\n(g) Crown Frame Web Measurement for Certain Airplanes \n\n\n\tFor Group 1, Configuration 3 airplanes, identified in Boeing Alert Service Bulletin 747-53A2784, Revision 2, dated August 20, 2015: At the compliance time specified in table 1 of paragraph 1.E., ''Compliance,'' of Boeing Alert Service Bulletin 747-53A2784, Revision 2, dated August 20, 2015, measure the thickness of the crown frame web at STA 320, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747- 53A2784, Revision 2, dated August 20, 2015, except as required by paragraph (l)(2) of this AD. Do all related investigative and corrective actions at the applicable times specified in tables 2 and 3 of paragraph 1.E., ''Compliance,'' of Boeing Alert Service Bulletin 747-53A2784, Revision 2, dated August 20, 2015. \n\n(h) Inspections (Web With No Repair Doubler) and Related Investigative and Corrective Actions (Including Web Replacement) \n\n\n\tFor Group 1, Configuration 1 airplanes, identified in Boeing Alert Service Bulletin 747-53A2784, Revision 2, dated August 20, 2015: For airplanes with a web thickness less than 0.136 inch and no repair doubler installed on the web, at the time specified in table 2 of paragraph 1.E., ''Compliance,'' of Boeing Alert Service Bulletin 747-53A2784, Revision 2, dated August 20, 2015, do a detailed inspection for cracks and a general visual inspection for missing fasteners of the crown frame web at STA 320, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2784, Revision 2, dated August 20, 2015, except as specified in paragraph (l)(2) of this AD. Do the applicable related investigative and corrective actions at the applicable times specified in paragraph 1.E., ''Compliance,'' of Boeing Alert Service Bulletin 747-53A2784, Revision 2, dated August 20, 2015. \n\n(i) Inspection (Web With Repair Doubler) and Related Investigative and Corrective Actions (Including Web Replacement) \n\n\n\tFor Group 1, Configuration 1 airplanes, identified in Boeing Alert Service Bulletin 747-53A2784, Revision 2, dated August 20, 2015: For airplanes with a web thickness less than 0.136 inch and a repair doubler installed on the web, at the time specified in table 3 of paragraph 1.E., ''Compliance,'' of Boeing Alert Service Bulletin 747-53A2784, Revision 2, dated August 20, 2015, do a \n\n((Page 89373)) \n\ndetailed inspection for any crack in the upper chord and lower chord of the STA 320 crown frame, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747- 53A2784, Revision 2, dated August 20, 2015, except as specified in paragraph (l)(2) of this AD. Do the applicable related investigative and corrective actions at the applicable times specified in paragraph 1.E., ''Compliance,'' of Boeing Alert Service Bulletin 747-53A2784, Revision 2, dated August 20, 2015. \n\n(j) Web Replacement for Certain Airplanes \n\n\n\tFor Group 1, Configuration 2 airplanes, identified in Boeing Alert Service Bulletin 747-53A2784, Revision 2, dated August 20, 2015: At the applicable time specified in table 5 of paragraph 1.E., ''Compliance,'' of Boeing Alert Service Bulletin 747-53A2784, Revision 2, dated August 20, 2015, except as provided by paragraph (l)(1) of this AD, replace the web, including doing related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747- 53A2784, Revision 2, dated August 20, 2015, except as required by paragraph (l)(2) of this AD. Do all applicable related investigative and corrective actions before further flight. \n\n(k) Post-Replacement Repetitive Inspections of Replaced Web \n\n\n\tFollowing any web replacement required by this AD, at the time specified in paragraph 1.E., ''Compliance,'' of Boeing Alert Service Bulletin 747-53A2784, Revision 2, dated August 20, 2015: Do a detailed inspection for cracks of the web, upper chord, lower chord, and lower chord splice, and do all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2784, Revision 2, dated August 20, 2015, except as required by paragraph (l)(2) of this AD. Do all applicable corrective actions before further flight. If no crack is found, repeat the inspection thereafter at the intervals specified in paragraph 1.E., ''Compliance,'' of Boeing Alert Service Bulletin 747-53A2784, Revision 2, dated August 20, 2015. Accomplishment of the inspections required by AD 2009-19-05, Amendment 39-16022 (74 FR 48138, September 22, 2009), terminates the requirements of this paragraph. \n\n(l) Exceptions to the Service Information, With Updated Service Information \n\n\n\t(1) Where Boeing Alert Service Bulletin 747-53A2784, Revision 2, dated August 20, 2015, specifies a compliance time ''after the Revision 2 date of the service bulletin,'' this AD requires compliance within the specified compliance time after the effective date of this AD. \n\t(2) Where Boeing Alert ServiceBulletin 747-53A2784, Revision 2, dated August 20, 2015, specifies to contact Boeing for appropriate action, accomplish applicable actions before further flight using a method approved in accordance with the procedures specified in paragraph (n) of this AD. \n\n(m) Credit for Previous Actions \n\n\n\t(1) This paragraph provides credit for the actions required by paragraphs (h), (i), and (k) of this AD, if those actions were performed before December 26, 2012 (the effective date of AD 2012- 22-02), using Boeing Service Bulletin 747-53A2784, dated August 27, 2009. \n\t(2) This paragraph provides credit for the actions required by paragraphs (h), (i), and (k) of this AD, if those actions were performed before the effective date of this AD using Boeing Service Bulletin 747-53A2784, Revision 1, dated September 14, 2011. This service information was incorporated by reference in AD 2012-22-02. \n\n(n) 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 or local 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 (o)(1) of this AD. \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, modification, or alteration 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. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. \n\n(o) Related Information \n\n\n\t(1) For more information about this AD, contact Bill Ashforth, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057- 3356; phone: 425-917-6432; 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 (p)(3) and (p)(4) of this AD. \n\n(p) 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 Bulletin747-53A2784, Revision 2, dated August 20, 2015. \n\t(ii) Reserved. \n\t(3) For 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 the FAA, Transport Airplane Directorate, 1601 Lind Avenue 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.