AD 2006-09-03 Airworthiness Directives; Boeing Model 727, 727C, 727-100, and 727-100C Series Airplanes

Models named: 727, 727C, 727-100, 727-100C 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 and 727-100C 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 “alert service bulletin,” as used in this AD, means Boeing Alert Service Bulletin 727-53A0228, dated March 24, 2005. Repetitive Inspections (g) Accomplish the applicable inspections for any cracks (including stop-drilled, trimmed-out, or repaired cracks) in the body skin and bear strap at the upper and lower hinge cutouts of the mid-cabin galley doorway, along the upper fastener row of the stringer 14R lap splice, and in the doorstop fitting adjacent to the upper hinge cutout, as specified in Table 1 of paragraph 1.E. “Compliance” of the alert service bulletin. Accomplish the inspections at the applicable compliance time specified in Table 1 of paragraph 1.E.; except, where Table 1 specifies a compliance time relative to the date of the release of the alert service bulletin, this AD requires compliance relative to the effective date of this AD. Accomplish the inspections by doing all the applicable actions specified in the Accomplishment Instructions of the alert service bulletin. Inspections of door stop fittings made of 7075 material having part number (P/N) 65-23674-7 are not required. Repeat the applicable inspection at the applicable repeat interval specified in Table 1 of paragraph 1.E. of the alert service bulletin. Corrective Action (h) If any cracking is found during any inspection required by paragraph (g) of this AD, repair the cracking and repeat the inspection at the applicable compliance time specified in Table 1 of paragraph 1.E. “Compliance” of the alert service bulletin. Do the repair by doing all the applicable actions specified in the Accomplishment Instructions of the alert service bulletin. Where the alert service bulletin specifies to report cracking to Boeing for repair instructions: Before further flight, repair any cracking according to a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA; or using a method approved in accordance with paragraph (j)(3) of this AD. Optional Terminating Action (i) Replacement of the doorstop fitting with a fitting made of 7075 material having P/N 65-23674-7, in accordance with the Accomplishment Instructions of the alert service bulletin, terminates the repetitive inspections of that fitting, as required by paragraph (g) of this AD. Alternative Methods of Compliance (AMOCs) (j)(1) The Manager, Seattle 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 Figures 9 through 12 of the alert service bulletin, as required by paragraph (g) of this AD, at the thresholds and intervals specified in paragraph (g), are approved as a method of compliance (MOC) to paragraph (b) of AD 98-11-03 and 98-11-03 R1, for the inspections of Structurally Significant Item F-16A, Supplemental Structural Inspection Document D6-48040-1, affected by the repair or modification. The MOC applies only to the areas inspected in accordance with Boeing Alert Service Bulletin 727-53A0228, dated March 24, 2005. All provisions of AD 98-11-03 R1 that are not specifically referenced in this paragraph remain fully applicable and must be complied with. (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 14 CFR 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 (k) You must use Boeing Alert Service Bulletin 727-53A0228, dated March 24, 2005, 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 April 17, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06-3890 Filed 4-25-06; 8:45 am] BILLING CODE 4910-13-P

This AD results from reports of skin and bear strap cracking at the upper and lower hinge cutout and along the upper fastener row of the stringer 14R lap splice, and cracking in the doorstop fitting adjacent to the upper hinge cutout. There are also reports of cracking on airplanes previously modified in production to resist such cracking. We are issuing this AD to find and fix fatigue cracking of the fuselage, which could result in reduced structural integrity and consequent rapid decompression of the airplane.