AD 2007-16-13 Airworthiness Directives; Boeing Model 757-200, -200PF, and -200CB Series Airplanes

Models named: 757-200, -200PF, -200CB series. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Boeing Model 757-200, -200PF, and -200CB series airplanes; certificated in any category; line numbers 1 through 1048 inclusive; powered by Rolls-Royce engines.

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 757-54A0047, Revision 3, dated June 27, 2007. One-Time Inspection and Repair (g) For airplanes identified in paragraphs (g)(1) and (g)(2) of this AD: Within 90 days after the effective date of this AD, do a high frequency eddy current (HFEC) inspection for cracking of the four critical fastener holes in the horizontal flange and, before further flight, do all applicable repairs, in accordance with Part IV of the Accomplishment Instructions of the alert service bulletin, except as required by paragraph (k) of this AD. (1) Airplanes on which findings on the horizontal or vertical fasteners or the shims led to a rejection of any fastener during the actions specified in Boeing Alert Service Bulletin 757-54A0047, dated November 13, 2003; or Boeing Service Bulletin 757-54A0047, Revision 1, dated March 24, 2005. (2) Airplanes that had equivalent findings prior to Boeing Alert Service Bulletin 757-54A0047, dated November 13, 2003, except for findings on airplanes identified as Group 1, Configuration 2 in the alert service bulletin that were prior to the incorporation of Boeing Service Bulletin 757-54-0035. Repetitive Inspections and Repair (h) At the applicable times specified in paragraph 1.E., “Compliance,” of the alert service bulletin, except as required by paragraphs (i) and (j) of this AD: Do the inspections specified in paragraphs (h)(1), (h)(2), and (h)(3) of this AD and, before further flight, do all applicable related investigative actions and repairs, by doing all the actions specified in Parts I and II of the Accomplishment Instructions of the alert service bulletin, except as required by paragraph (k) of this AD. (1) Do detailed inspections of the shim installations between the vertical flange and bulkhead to determine if there are signs of movement. (2) Do detailed inspections of the four fasteners in the vertical flange to determine if there are signs of movement or if there are gaps under the head or collar. (3) Do detailed inspections of the fasteners that hold the strut to the horizontal flange of the strut-to-diagonal brace fitting to determine if there are signs of movement or if there are gaps under the head or collar. Exceptions to Alert Service Bulletin Procedures (i) Where the alert service bulletin specifies a compliance time relative to “the date on this service bulletin,” this AD requires compliance within the corresponding specified time relative to the effective date of this AD. (j) Where the alert service bulletin specifies a compliance time relative to the “date of issuance of airworthiness certificate,” this AD requires compliance within the corresponding time relative to the date of issuance of the original standard airworthiness certificate or the date of issuance of the original export certificate of airworthiness. (k) If any crack is found during any inspection required by this AD, and the alert service bulletin specifies to contact Boeing for appropriate action: Before further flight, repair the crack using a method approved in accordance with the procedures specified in paragraph (o) of this AD Credit for Actions Done Using Previous Service Information (l) Actions done before the effective date of this AD in accordance with Boeing Service Bulletin 757-54A0047, Revision 1, dated March 24, 2005; and Boeing Alert Service Bulletin 757-54A0047, Revision 2, dated January 31, 2007; are considered acceptable for compliance with the corresponding actions specified in this AD. (m) An inspection and corrective actions done before June 29, 2005 (the effective date of AD 2005-12-04), in accordance with paragraph (b) or (c), as applicable, of AD 2004-12-07, are acceptable for compliance with the initial inspection requirement of paragraph (h) of this AD. An Acceptable Method of Compliance With Certain Requirements of AD 2004-12-07 (n) Accomplishing the actions specified in this AD terminates the requirements specified in paragraphs (b) and (c) of AD 2004-12-07. Alternative Methods of Compliance (AMOCs) (o)(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. (4) AMOCs approved previously in accordance with AD 2004-12-07 are approved as AMOCs for the corresponding provisions of this AD. (5) AMOCs approved previously in accordance with AD 2005-12-04 are approved as AMOCs for the corresponding provisions of this AD. Material Incorporated by Reference (p) You must use Boeing Alert Service Bulletin 757-54A0047, Revision 3, dated June 27, 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 July 31, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7-15419 Filed 8-8-07; 8:45 am] BILLING CODE 4910-13-P

This AD results from reports of cracking in the pylon under bolts that appear to be undamaged during the existing AD inspections. We are issuing this AD to detect and correct cracks, loose and broken bolts, and shim migration in the joint between the aft torque bulkhead and the strut-to-diagonal brace fitting, which could result in damage to the strut and consequent separation of the strut and engine from the airplane.