AD 2005-07-12 Airworthiness Directives; Boeing Model 737-100, -200, -200C, -300, -400, and -500 Series Airplanes

Models named: 737-100, -200, -200C, -300, -400, -500 series. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes; certificated in any category; as identified in Boeing Alert Service Bulletin 737-53A1241, dated June 13, 2002.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Initial and Repetitive Inspections (f) Prior to the accumulation of 40,000 total flight cycles, or within 2,250 flight cycles after the effective date of this AD, whichever occurs later: Do a detailed inspection and an eddy current inspection to detect cracking of the frame web around the cutout for the doorstop intercostal strap at the aft side of the body station 291.5 frame at stringer 16R, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1241, dated June 13, 2002. If no cracking is found, repeat the inspections thereafter at intervals not to exceed 4,500 flight cycles. 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.” Corrective Action (g) If any crack is found during any inspection required by this AD, and the bulletin specifies to contact Boeing for appropriate action: Before further flight, repair the crack according to a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA; or according to data meeting the certification basis of the airplane approved by an Authorized Representative (AR) for the Boeing Delegation Option Authorization (DOA) Organization who has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the approval must specifically reference this AD. 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) An AMOC that provides an acceptable level of safety may be used for any inspection required by this AD, if it is approved by an AR for the Boeing DOA who has been authorized by the Manager, Seattle ACO, to make those findings. For an inspection method to be approved, the approval must specifically refer to this AD. Material Incorporated by Reference (i) You must use Boeing Alert Service Bulletin 737-53A1241, dated June 13, 2002, 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. To get copies of the service information, go to Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207. To view the AD docket, go to the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL-401, Nassif Building, Washington, DC. To review copies of the service information, go to 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 25, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. > [FR Doc. 05-6688 Filed 4-6-05; 8:45 am] BILLING CODE 4910-13-P

This AD was prompted by reports of fatigue cracks in the web of the body station 291.5 frame near the forward galley door. We are issuing this AD to detect and correct fatigue cracking of the aft frame and frame support structure of the forward galley door, which could result in a severed fuselage frame web, rapid decompression of the airplane, and possible loss of the forward galley door.