AD 2005-07-08 Airworthiness Directives; Boeing Model 757-200 and -200PF Series Airplanes

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

This AD applies to Boeing Model 757-200 and -200PF series airplanes, certificated in any category, identified in Boeing Alert Service Bulletin 757-57A0063, dated June 26, 2003.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Repetitive Inspections and Tests (f) Within 18 months after the effective date of this AD: Do a detailed inspection and an audible tap test of the upper and lower skins of the trailing edge wedges on slats No. 2 through No. 4 inclusive and No. 7 through No. 9 inclusive, for evidence of damage or cracking, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 757-57A0063, dated June 26, 2003. Repeat the detailed inspection and audible tap test thereafter at intervals not to exceed 18 months. Note 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.” Related Investigative and Corrective Actions (g) If any damage or cracking is found during any inspection or audible tap test required by paragraph (f) of this AD: Before further flight, do the related investigative action, if applicable, and replace the affected part with a new trailing edge wedge assembly or repair the affected part, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 757-57A0063, dated June 26, 2003. Accomplishing the replacement terminates the repetitive inspections and audible tap tests required by paragraph (f) of this AD for that wedge assembly only. Actions Accomplished Previously (h) Previous accomplishment of all of the actions specified in the Accomplishment Instructions of Boeing Service Bulletin 757-57A0038, Revision 5, dated July 16, 1992; or Revision 6, dated November 10, 1994; in conjunction with the use of BMS 5-137 adhesive; is acceptable for compliance with the inspection requirements of paragraph (f) of this AD. Parts Installation (i) As of the effective date of this AD, no trailing edge wedge assembly having a part number listed in the “Existing Part Number” column of the table in paragraph 2.C.3. of Boeing Alert Service Bulletin 757-57A0063, dated June 26, 2003, may be installed on any airplane unless it has been inspected, tested, and had any necessary corrective actions accomplished in accordance with this AD. Optional Terminating Action (j) Replacing all trailing edge wedge assemblies with new, improved wedge assemblies in accordance with Part III of the Accomplishment Instructions of Boeing Alert Service Bulletin 757-57A0063, dated June 26, 2003, terminates the requirements of paragraph (f) of this AD. Alternative Methods of Compliance (AMOCs) (k)(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) 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 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 (l) You must use Boeing Alert Service Bulletin 757-57A0063, dated June 26, 2003, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approves the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. For copies of the service information, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207. For information on the availability of this material at the National Archives and Records Administration (NARA), call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html . You may view the AD docket at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL-401, Nassif Building, Washington, DC. Issued in Renton, Washington, on March 22, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-6259 Filed 3-30-05; 8:45 am] BILLING CODE 4910-13-P

This AD was prompted by a report of damage to the No. 4 leading edge slat. We are issuing this AD to prevent delamination of the leading edge slats, possible loss of pieces of the trailing edge wedge assembly during flight, reduction of the reduced maneuver and stall margins, and consequent reduced controllability of the airplane.