AD 2005-20-13 Airworthiness Directives; Boeing Model 727 Airplanes

Models named: 727, 727C, 727-100, 727-100C, 727-200, 727-200F series. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to all Boeing Model 727, 727C, 727-100, 727-100C, 727-200, and 727-200F series airplanes, certificated in any category.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Service Bulletin Reference (f) The term “service bulletin,” as used in this AD, means the Accomplishment Instructions of Boeing Alert Service Bulletin 727-53A0227, dated September 16, 2004. Inspections (g) Before the accumulation of 40,000 total flight cycles, or within 3,500 flight cycles after the effective date of this AD, whichever occurs later: Do a one-time general visual inspection of the lower lobe frames to find open holes between stringer 17L and stringer 17R of body section 43, record their locations, and keep these records for future reference when accomplishing the actions in this AD; and do a high-frequency eddy current (HFEC) inspection for cracks of all open holes, including lining holes. Repeat the HFEC inspection at intervals not to exceed 3,500 flight cycles until the optional terminating action in paragraph (i) of this AD is accomplished. Do all inspections in accordance with the service bulletin. Corrective Action (h) If any crack is found during any inspection required by paragraph (g) or (j) of this AD: Before further flight, do the applicable corrective action in paragraph (h)(1) or (h)(2) of this AD. (1) If the crack is less than 0.063 inch in length, do the corrective action and related investigative action in Figure 6 of the service bulletin. (2) If the crack is 0.063 inch in length or greater, repair the crack using a method approved in accordance with paragraph (k) of this AD. Chapters 51-40-3 and 53-10-4 of the Boeing 727 Structural Repair Manual (SRM) are approved methods. Except for these SRMs, for a repair method to be approved, the approval must specifically reference this AD. Optional Terminating Action (i) Installing rivets in all open tooling holes, and all unused lining holes, according to Part 2 of the Work Instructions of the service bulletin terminates the repetitive inspection requirements of paragraph (g) of this AD only for those holes plugged with rivets. Terminating action for the repetitive inspection requirements of paragraph (g) of this AD is not permitted for all lining holes without installed rivets, except as provided by paragraph (j) of this AD. Extended Intervals for Repetitive HFEC Inspections (j) For open holes that are in use for lining installation only: Doing the applicable actions in Table 1 of this AD extends the intervals of the repetitive HFEC inspections required by paragraph (g) of this AD. Table 1.—Extended Intervals for Repetitive HFEC Inspections If the modification specified in paragraph C. of AD 90-20-14— Then— (1) Was done before the effective date of this AD Do the initial HFEC inspection required by paragraph (g) of this AD at the time specified in that paragraph. Do the repetitive HFEC inspections required by paragraph (g) of this AD thereafter at intervals not to exceed 20,000 flight cycles. (2) Has not been done before the effective date of this AD Do the modification specified in paragraph C. of AD 90-20-14 at the same time as the initial HFEC inspection required by paragraph (g) of this AD, and repeat the HFEC inspection thereafter at intervals not to exceed 20,000 flight cycles. AMOCs (k)(1) The Manager, Seattle Aircraft Certification Office (ACO), has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) The inspection methods specified in paragraph (g) of this AD are AMOCs to the inspection methods required by paragraph A. of AD 90-20-14, amendment 39-6730. Inspection thresholds and repetitive intervals are not included in or affected by this AMOC. All other provisions of AD 90-20-14 that are not specifically mentioned above remain fully applicable and must be met. (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. (4) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Material Incorporated by Reference (l) You must use Boeing Alert Service Bulletin 727-53A0227, dated September 16, 2004, 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 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 . Issued in Renton, Washington, on September 26, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-19842 Filed 10-4-05; 8:45 am] BILLING CODE 4910-13-P

This AD was prompted by reports of cracks at open tooling holes in the lower lobe frames of body section 43. We are issuing this AD to detect and correct cracks in the frames, which could result in cracks in the skin panels and rapid decompression of the airplane.