AD 2007-15-07 Airworthiness Directives; Boeing Model 747-100, 747-100B, 747-200B, 747-200C, 747-200F, 747-300, 747SR, and 747SP Series Airplanes

Models named: 747-100, 747-100B, 747-200B, 747-200C, 747-200F, 747-300, 747SR, 747SP series. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Boeing Model 747-100, 747-100B, 747-200B, 747-200C, 747-200F, 747-300, 747SR, and 747SP series airplanes, certificated in any category; as identified in Boeing Alert Service Bulletin 747-53A2542, dated February 16, 2006.

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 and Corrective Actions (f) For any airplane that has not had external skin doublers installed around the left- or right-side Number 3 flight deck window in accordance with Boeing Service Bulletin 747-53-2272, Revision 18, dated May 16, 2002, or an earlier revision: Do the applicable actions described in paragraphs (f)(1) and (f)(2) of this AD. Do all the actions in and in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2542, dated February 16, 2006. Do the actions at the compliance times specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 747-53A2542, dated February 16, 2006, on the side(s) of the airplane on which the doubler installation has not been done; except where the service bulletin specifies compliance times after the date on the service bulletin, this AD requires compliance times after the effective date of this AD. Installing external skin doublers around the left- or right-side Number 3 flight deck windows in accordance with Boeing Service Bulletin 747-53-2272, Revision 18, or an earlier revision, ends the repetitive high-frequency eddy current (HFEC) inspections required by this paragraph on the side of the airplane on which the doublers are installed. After the effective date of this AD, only Boeing Service Bulletin 747-53-2272, Revision 18, may be used to install the external skin doublers around the left- and right-side Number 3 flight deck windows. (1) Do a HFEC inspection for cracks of the fuselage skin at stringer 5, between body stations 340 and 350; and do all applicable corrective actions before further flight. (2) Repeat the HFEC inspection thereafter at the applicable interval specified in paragraph 1.E. of Boeing Alert Service Bulletin 747-53A2542, dated February 16, 2006. Credit for Actions of Alternative AD (g) For Group 1 airplanes only: External skin doublers installed around the left- or right-side Number 3 flight deck windows in accordance with the requirements of AD 90-06-06, amendment 39-6490, end the repetitive HFEC inspections required by paragraph (f) of this AD on the side of the airplane on which the doublers are installed. Terminating Action (h) For Group 2 airplanes only: Before accumulating 24,000 total flight cycles, or within 250 flight cycles after the effective date of the AD, whichever occurs later, install external skin doublers around the left- and right-side Number 3 flight deck windows; in accordance with a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA. Boeing Service Bulletin 747-53-2272, Revision 17, dated November 18, 1999, and Revision 18, dated May 16, 2002, describe one approved method of compliance for doing the required actions. After the effective date of this AD, only Revision 18 is acceptable as an approved method of compliance. Accomplishing this action ends the repetitive inspections required by paragraph (f) of this AD. Alternative Methods of Compliance (AMOCs) (i)(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) 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. (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 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, and the approval must specifically refer to this AD. Material Incorporated by Reference (j) You must use Boeing Alert Service Bulletin 747-53A2542, dated February 16, 2006, 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 July 15, 2007. Stephen P. Boyd, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7-14140 Filed 7-27-07; 8:45 am] BILLING CODE 4910-13-P

This AD results from reports of fatigue cracks in the fuselage skin near stringer 5 between body stations 340 and 350. We are issuing this AD to detect and correct fatigue cracking of the fuselage skin near stringer 5. Cracks in this area could join together and result in in-flight depressurization of the airplane.