AD 2007-17-13 Airworthiness Directives; Boeing Model 747-100, -200B, -200C, and -200F Series Airplanes

Models named: 747-100, -200B, -200C, -200F series. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Boeing Model 747-100, -200B, -200C, and -200F series airplanes, certificated in any category; as identified in Boeing Alert Service Bulletin 747-53A2673, dated February 8, 2007.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Inspections/Corrective Actions (f) Before the accumulation of 20,000 total flight cycles, or within 1,500 flight cycles after the effective date of this AD, whichever is later: Perform a high frequency eddy current (HFEC) inspection for cracks in the fuselage skin at the cutout of the bulk cargo door light, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2673, dated February 8, 2007. Repeat the inspection thereafter at intervals not to exceed 3,000 flight cycles. (1) If no crack is found: Repeat the inspection required by paragraph (f) of this AD at the time specified. (2) If any crack is found that is 2.0 inches or less in length from the edge of the light cutout forward lower corner: Before further flight, do all the corrective actions (including an additional HFEC inspection for cracks) in accordance with Part 2 of the Accomplishment Instructions of the service bulletin. Accomplishing the actions specified in Part 2 of the service bulletin ends the repetitive inspections required by paragraph (f) of this AD. (3) If any crack is found during the inspection required by paragraph (f) of this AD that is more than 2.0 inches in total length from the edge of the light cutout forward lower corner, or is at a location other than the light cutout forward lower corner: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (g)(2) of this AD. Alternative Methods of Compliance (AMOCs) (g)(1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD, if it is approved by an Authorized Representative for the Boeing Commercial Airplanes Delegation Option Authorization Organization who 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. (3) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. Material Incorporated by Reference (h) You must use Boeing Alert Service Bulletin 747-53A2673, dated February 8, 2007, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207, for a copy of this service information. You may review copies at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or 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. Issued in Renton, Washington, on August 14, 2007. Stephen P. Boyd, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7-16420 Filed 8-27-07; 8:45 am] BILLING CODE 4910-13-P

This AD results from a report of a 2-inch crack through the fuselage skin and internal bonded doubler at the cutout of the bulk cargo door light. We are issuing this AD to detect and correct cracks in the fuselage skin at the cutout of the bulk cargo door light, which could result in reduced structural integrity of the fuselage at the bulk cargo door and consequent rapid decompression of the fuselage.