AD 2005-08-15 Airworthiness Directives; Boeing Model 707 Airplanes and Model 720 and 720B Series Airplanes

Models named: 707-100 long body, -200, -100B long body, -100B short body series, 707-300, -300B, -300C, -400 series, 720, 720B series. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Boeing Model 707-100 long body, -200, -100B long body, and -100B short body series airplanes; Model 707-300, -300B, -300C, and -400 series airplanes; and Model 720 and 720B series airplanes; certificated in any category; having line numbers 1 through 1012 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 3,500 total flight hours, or within 18 months after the effective date of this AD, whichever occurs later: Do a detailed inspection for cracking of the front spar fitting of the inboard and outboard nacelles according to the Accomplishment Instructions of Boeing Alert Service Bulletin A3514, dated July 29, 2004. Repeat the inspection thereafter at intervals not to exceed 700 flight hours. Note 1: There is no terminating action at this time for the repetitive inspections required by paragraph (f) of this AD. Replacement (g) If any cracking is found during any inspection required by paragraph (f) of this AD: Before further flight, replace the cracked front spar fitting with a new fitting, according to the Accomplishment Instructions of Boeing Alert Service Bulletin A3514, dated July 29, 2004. Parts Installation (h) As of the effective date of this AD, no person may install, on any airplane, a front spar fitting having a part number other than the part numbers specified in paragraph 2.C.2. of Boeing Alert Service Bulletin A3514, dated July 29, 2004. Alternative Methods of Compliance (AMOCs) (i)(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 that is required by this AD, if it is approved by an Authorized Representative for the Boeing DOA 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 (j) You must use Boeing Alert Service Bulletin A3514, dated July 29, 2004, 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, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207. To view the AD docket, contact 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, contact 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 April 13, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-7996 Filed 4-22-05; 8:45 am] BILLING CODE 4910-13-P

This AD was prompted by a report indicating that a crack was found in a front spar fitting that had been replaced as part of the modification required by AD 2001-17-24. We are issuing this AD to detect and correct this cracking, which could result in reduced structural integrity of the engine nacelle, and consequent separation of an engine from the airplane.