AD 2011-02-06

(a) This AD is effective March 1, 2011.

(b) None.

(c) This AD applies to The Boeing Company Model 767-300 series airplanes, certificated in any category, as identified in Boeing Special Attention Service Bulletin 767-53-0207, dated December 17, 2009.

(d) Air Transport Association (ATA) of America Code 53: Fuselage.

(e) This AD was prompted by reports of cracking found in the section 46 fuselage lower skin around the periphery of the very high frequency (VHF) antenna baseplate at station 1197 + 99. The Federal Aviation Administration is issuing this AD to detect and correct fatigue cracks in the fuselage skin and internal backup structure, which could result in rapid decompression of the airplane.

(f) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.

(g) Inspect for cracks in the fuselage skin and backup structure at the lower VHF antenna cutout at station 1197 + 99, between stringers 39L and 39R, by doing an external detailed inspection, with the antenna removed, of the fuselage structure at the lower aft VHF antenna cutout, and an internal detailed inspection of the backup structure. Do the inspections in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 767-53-0207, dated December 17, 2009. Do the inspections at the applicable time specified in paragraph 1.E., “Compliance,” of Boeing Special Attention Service Bulletin 767-53-0207, dated December 17, 2009, except as required by paragraphs (h) and (i) of this AD.

(1) If no crack is found, repeat the external detailed inspection, without removing the antenna, at intervals not to exceed 3,000 flight cycles.

(2) If any crack is found in the fuselage skin, repair before further flight, in accordance with Boeing Special Attention Service Bulletin 767-53-0207, dated December 17, 2009. Accomplishment of this repair terminates the repetitive external detailed inspections of the fuselage skin required by this AD.

(3) If any crack is found in the backup structure, before further flight, repair or replace the cracked part(s), in accordance with Boeing Special Attention Service Bulletin 767-53-0207, dated December 17, 2009.

(h) Where Boeing Special Attention Service Bulletin 767-53-0207, dated December 17, 2009, specifies a compliance time after the date on the service bulletin, this AD requires compliance within the specified time after the effective date of this AD.

(i) The internal detailed inspection specified in Boeing Special Attention Service Bulletin 767-53-0207, dated December 17, 2009, and required by paragraph (g) of this AD must be done at the later of the times specified in paragraphs (i)(1) and (i)(2) of this AD.

(1) Before the accumulation of 25,000 total flight cycles.

(2) At the applicable time specified in paragraph (i)(2)(i) or (i)(2)(ii) of this AD.

(i) If any fuselage skin crack is found during the external detailed inspection required by paragraph (g) of this AD: Within 3,000 flight cycles after the effective date of this AD.

(ii) If no fuselage skin crack is found during the external detailed inspection required by paragraph (g) of this AD: Within 6,000 flight cycles after the effective date of this AD.

(j)(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 the Related Information section of this AD. Information may be e-mailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.

(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.

(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.

(k) For more information about this AD, contact Berhane Alazar, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; phone: 425-917-6577; fax: 425-917-6590; e-mail: berhane.alazar@faa.gov.

(l) You must use Boeing Special Attention Service Bulletin 767-53-0207, dated December 17, 2009, to do the actions required by this AD, unless the AD specifies otherwise.

(1) The Director of the Federal Register approved the incorporation by reference of the service information under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P. O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-544-5000, extension 1; fax 206-766-5680; e-mail me.boecom@boeing.com; Internet https://www.myboeingfleet.com.

(3) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call 425-227-1221.

(4) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at an NARA facility, call 202-741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.