AD 2005-18-08 Airworthiness Directives; Boeing Model 737-100, -200, -200C, and -300 Series Airplanes

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

This AD applies to Boeing Model 737-100, -200, -200C, and -300 series airplanes, certificated in any category; line numbers 1 through 1670 inclusive.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Inspection (f) Prior to the accumulation of 15,000 total flight cycles, or within 3,000 flight cycles after the effective date of this AD, whichever occurs later: Perform a detailed inspection to detect cracking of the retaining pin lugs of the support fitting of the MLG beam, or elongation of a bolt hole in a lug, in accordance with the Accomplishment Instructions, Part I: Inspection, of Boeing Special Attention Service Bulletin 737-57-1267, dated August 8, 2002. If no cracked lug or elongated bolt hole is found, repeat the inspection thereafter at intervals not to exceed 12,000 flight cycles, until the actions specified in paragraph (h) of this AD are accomplished. 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 mirrors magnifying lenses, etc. may be necessary. Surface cleaning and elaborate procedures may be required.” Corrective Action (g) If any cracked lug or elongated bolt hole is found during any inspection required by paragraph (f) of this AD, before further flight, do paragraph (g)(1) or (g)(2) of this AD. (1) Rework the fitting in accordance with the Accomplishment Instructions, Part II: Rework, of Boeing Special Attention Service Bulletin 737-57-1267, dated August 8, 2002. (2) Replace the fitting in accordance with the Accomplishment Instructions, Part III—Fitting Replacement, of Boeing Service Bulletin 737-57-1216, Revision 2, dated May 6, 1999, and install a retaining bolt, castellated nut, and cotter pin in accordance with Boeing Service Bulletin 737-57A1260, Revision 2, dated October 18, 2001. Replacing the fitting in accordance with the Accomplishment Instructions, Part III—Fitting Replacement, of Boeing Service Bulletin 737-57-1216, dated December 17, 1992, or Revision 1, dated September 23, 1993; and replacing the retaining bolt, self-locking nut, and associated hardware of the support beam for the MLG with a new bolt, castellated nut, and new hardware; in accordance with Boeing Service Bulletin 737-57A1260, Revision 2, dated October 18, 2001; prior to the effective date of this AD are acceptable methods of compliance with the requirements of this paragraph. Optional Terminating Action (h) Reworking or replacing the fitting in accordance with paragraph (g)(1) or (g)(2) of this AD constitutes terminating action for the inspections required by paragraph (f) of this AD. Repair (i) If any cracking is found during any inspection required by this AD, and the service bulletin specifies to contact Boeing for appropriate action: Before further flight, repair in accordance with a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA; or per data meeting the type certification basis of the airplane approved by an Authorized Representative (AR) for the Boeing DOA Organization who has been authorized by the Manager, Seattle ACO, to make such findings. For a repair method to be approved, the approval must specifically reference this AD. Parts Installation (j) As of the effective date of this AD: With the exception of a new support fitting of the MLG; (i.e., a fitting that has been reworked or replaced as required by paragraph (g) of this AD), all retaining pin lugs of the support fitting, and bolt holes of the lugs must be inspected in accordance with this AD before being installed on any airplane. Alternative Methods of Compliance (AMOCs) (k)(1) The Manager, Seattle 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 corrective actions per data meeting the type certification basis of the airplane approved by a Boeing DOA Organization AR 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 reference this AD. Material Incorporated by Reference (l) You must use Boeing Special Attention Service Bulletin 737-57-1267, dated August 8, 2002; Boeing Service Bulletin 737-57-1216, Revision 2, dated May 6, 1999; and Boeing Service Bulletin 737-57A1260, Revision 2, dated October 18, 2001; as applicable, 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 these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get copies of the service information, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207. To view an 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 August 24, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-17461 Filed 9-2-05; 8:45 am] BILLING CODE 4910-13-P

This AD was prompted by reports of discrepancies of the lugs on the support fitting of the main landing gear (MLG) beam. We are issuing this AD to prevent separation of the support beam of the MLG from the rear spar, which could cause cracking of the MLG support fitting and a consequent leak in the wing fuel tank or collapse of the MLG.