AD 2006-06-05 Airworthiness Directives; Boeing Model 720 and 720B Series Airplanes

Models named: 720, 720B series. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to all Boeing Model 720 and 720B 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. Repetitive Inspections (f) Within 30 days after the effective date of this AD: Do detailed and high-frequency eddy current (HFEC) inspections for any crack, corrosion, or sign of damage (e.g., finish scratches, blistering, or signs of fuel leaking) of the front spar upper chords under the fairing web; and repair if necessary; by accomplishing all the actions specified in Boeing Multi-Operator Message (MOM) 1-151636045-1, dated January 17, 2006. If any crack, corrosion, or sign of damage is found, do all applicable repairs before further flight. Repeat the inspections thereafter at intervals not to exceed 12 months. Where the MOM specifies to contact Boeing for repair instructions: Before further flight, repair using a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA. For a repair method to be approved by the Manager, Seattle ACO, as required by this paragraph, the Manager's approval letter must specifically refer to this AD. 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.” Instructions for Oversizing Fasteners (g) Where Boeing MOM 1-151636045-1, dated January 17, 2006, specifies to contact Boeing for appropriate action if it is necessary to oversize fasteners during restoration: Before further flight, oversize the fasteners using a method approved in accordance with a method 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. Alternative Methods of Compliance (AMOCs) (h)(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) 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 (i) You must use Boeing Multi-Operator Message (MOM) 1-151636045-1, dated January 17, 2006, 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 March 7, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06-2545 Filed 3-16-06; 8:45 am] BILLING CODE 4910-13-U

This AD results from a report that inspections required by previous AD action are inadequate for Boeing Model 720 and 720B series airplanes. We are issuing this AD to detect and correct any crack, corrosion, or sign of damage (e.g., finish scratches, blistering, or signs of fuel leaking) of the front spar upper chords under the fairing web, which could result in structural failure of the wing.