2006-24-02: Stringer fastener locations

2006-24-02 Boeing: Amendment 39-14831. Docket No. FAA-2006-24877; Directorate Identifier 2005-NM-253-AD. \n\nEffective Date \n\n\t(a) This AD becomes effective December 27, 2006. \n\nAffected ADs \n\n\t(b) This AD supersedes AD 90-26-10. \n\nApplicability \n\n\t(c) This AD applies to Boeing Model 747-100, 747-100B, 747-200B, 747-200C, 747-200F, 747SR, and 747SP series airplanes, certificated in any category; line numbers 001 through 430 inclusive. \n\nUnsafe Condition \n\n\t(d) This AD results from a report of cracking discovered in a skin lap joint that was previously inspected using the eddy current method. We are issuing this AD to prevent rapid decompression of the airplane due to disbonding and subsequent cracking of the skin panels. \n\nCompliance \n\n\t(e) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. \n\nRestatement of Certain Requirements of AD 90-26-10 \n\nInspections(f) Prior to the accumulation of 12,000 flight cycles or within the next 1,000 flight cycles after January 22, 1991 (the effective date of AD 90-26-10), whichever occurs later, unless previously accomplished within the last 1,000 flight cycles, conduct an external detailed and external high frequency eddy current (HFEC) inspection for cracks of the fuselage skin from body station (BS) 220 to BS 520, left- and right-hand sides of the airplane between stringers (S)-6 and S-14, excluding the skin lap joints, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2321, dated October 31, 1989; or Revision 7, dated October 27, 2005. After the effective date of this AD, only Revision 7 may be used. Doing the inspections in this paragraph in accordance with Revision 7 of the service bulletin eliminates the need for doing the actions in paragraph (k) of this AD. Repeat the inspections thereafter at intervals not to exceed 2,000 flight cycles until the terminating modification in paragraph (g) of this AD is done, except as provided by paragraph (h) of this AD. \n\n\tNote 1: For the purposes of this AD, a detailed inspection is: "An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.'' \n\nTerminating Modification \n\n\t(g) For airplanes line numbers 001 through 200 inclusive, prior to the accumulation of 20,000 total flight cycles, or within 48 months after the January 22, 1991, whichever occurs later: Perform the terminating modification of the skin panel from BS 340 to BS 520, S-6 to S-14, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2321, dated October 31, 1989; or Revision 7, dated October 27, 2005. After the effective date of this AD, only Revision 7 may be used. The modification consists of replacing the skin panel with a new skin panel which was manufactured utilizing the improved hot phosphoric acid anodize bonding process. \n\n\t(h) Replacement of the skin panel required by paragraph (g) of this AD constitutes terminating action for the inspections from BS 340 to BS 520 required by paragraphs (f) and (k) of this AD. The inspections from BS 220 to BS 340 required by paragraph (f) of this AD are to be continued. \n\nAdjustments for Cabin Differential Pressure \n\n\t(i) Before the effective date of this AD: Flight cycles conducted at 2.0 pounds per square inch (psi) or less cabin differential pressure need not be counted for the purpose of this airworthiness directive. \n\n\t(j) Before the effective date of this AD: For Model 747SR airplanes only, the threshold and repetitive inspection intervals specified herein may be multiplied by the 1.2 adjustment factor based on continued mixed operation at lower cabin pressure differentials. \n\nNew Requirements of This AD \n\nAdditional Inspection of Skins With Alodine-Coated Rivets \n\n\t(k) For airplanes identified in Figure 9 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2321, Revision 7, dated October 27, 2005, as requiring additional inspection: Within 150 flight cycles after the effective date of this AD, do the inspection in paragraph (k)(1) or (k)(2) of this AD in accordance with the Accomplishment Instructions of the service bulletin. \n\n\t(1) Do an external detailed inspection for cracking of Area 1, and repeat the inspection thereafter at intervals not to exceed 150 flight cycles until one of the actions in paragraph (k)(1)(i), (k)(1)(ii), or (k)(1)(iii) is accomplished. Repeat the inspection of Area 1 thereafter in accordance with the requirements of paragraph (f) of this AD. \n\n\t(i) The inspection in accordance with paragraph (k)(1) of this AD has been done seven times. If this option is used: Within 150 flight cycles after the seventh inspection, do the inspection required by paragraph (k)(2) of this AD. \n\n\t(ii) The inspection in accordance with paragraph (k)(2) has been accomplished. \n\n\t(iii) The inspections in accordance with paragraph (f) of this AD has been accomplished once in accordance with Revision 7 of the service bulletin.\n \n\t(2) Do an external HFEC inspection for cracking of Area 1 in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747-53A2321, Revision 7, dated October 27, 2005. Repeat the inspection of Area 1 thereafter in accordance with the requirements of paragraph (f) of this AD. \n\nRepair \n\n\t(l) If any crack is found during any inspection required by this AD: Before further flight, repair in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747- 53A2321, dated October 31, 1989; or Revision 7, dated October 27, 2005. After the effective date of this AD, only Revision 7 of the service bulletin may be used. Where Revision 7 of the service bulletin specifies to contact Boeing for repair instructions: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (n) of this AD. \n\nAdjustments to Compliance Time: Cabin Differential Pressure \n\n\t(m) For the purposes of calculating the compliance threshold and repetitive interval for actions required by paragraphs (f), (g), and (k) of this AD, on or after the effective date of this AD: All flight cycles, including the number of flight cycles in which cabin differential pressure is at 2.0 psi or less, must be counted when determining the number of flight cycles that have occurred on the airplane, and a 1.2 adjustment factor may not be used. However, for airplanes on which the repetitive interval for the actions required by paragraphs (f) and (k) of this AD have been calculated in accordance with paragraph (i) or (j) of this AD by excluding thenumber of flight cycles in which cabin differential pressure is at 2.0 pounds psi or less, or by using a 1.2 adjustment factor: Continue to adjust the repetitive interval in accordance with paragraph (i) or (j) of this AD until the next inspections required by paragraph (f) or (k) of this AD are accomplished. Thereafter, no adjustment to compliance times based on paragraph (i) or (j) of this AD is allowed. \n\nAlternative Methods of Compliance (AMOCs) \n\n\t(n)(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. \n\n\t(2) Before using any AMOC approved in accordance with Sec. 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. \n\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 byan 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. \n\n\t(4) AMOCs approved previously in accordance with AD 90-26-10 are acceptable for compliance with the requirements of this AD, provided that any alternative terminating action was not based upon inspection results using sliding probe low-frequency eddy current (LFEC), sliding probe HFEC, or mid-frequency eddy current (MFEC) inspection method; and provided that any alternative method future inspections did not incorporate sliding probe LFEC or MFEC inspection method. \n\nMaterial Incorporated by Reference \n\n\t(o) You must use Boeing Alert Service Bulletin 747-53A2321, dated October 31, 1989; and Boeing Alert Service Bulletin 747- 53A2321, Revision 7, dated October 27, 2005; as applicable; to perform theactions that are required by this AD, unless the AD specifies otherwise. (Only the first page of Boeing Alert Service Bulletin 747-53A2321, dated October 31, 1989, contains the document issue date; no other page of this document contains this information.) The Director of the Federal Register approved the incorporation by reference of these documents 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 Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., Room PL-401, Nassif Building, Washington, DC; on the Internet at http://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html .