AD 2004-18-08 Airworthiness Directives; Boeing Model 727, 727C, 727-100, -100C, and -200 Series Airplanes

Models named: 727, 727C, 727-100, -100C, -200 series. Read the applicability below — it usually turns on serial or part numbers too.

Model 727, 727C, 727-100, -100C, and -200 series airplanes, line numbers 1 through 887 inclusive; certificated in any category.

Required as indicated, unless accomplished previously. To detect and correct cracks and corrosion on the attach fitting holes of the forward trunnion attach fittings of the main landing gear (MLG), which could result in the collapse of the MLG, accomplish the following: Service Bulletin References (a) The term “service bulletin,” as used in this AD, means Boeing Alert Service Bulletin 727-57A0132, Revision 3, dated March 20, 2003. Initial Inspection (b) Perform an inspection of the forward trunnion attach fittings of the MLG to determine the part number (P/N) of the attach fitting, in accordance with “Part 1” of the Accomplishment Instructions of the service bulletin, at the latest of the times specified in paragraphs (b)(1), (b)(2), and (b)(3) of this AD: (1) Prior to airplanes reaching 240 months old since the date of issuance of the original Airworthiness Certificate or the date of issuance of the original Export Certificate of Airworthiness; or (2) Within 18 months after the effective date of this AD; or (3) Within 120 months after the last inspection/rework/repair of the attach fitting per Boeing Service Bulletin 727-57A0132, dated June 28, 1974, Revision 1, dated October 31, 1975, or Revision 2, dated April 24, 1981; or Boeing Alert Service Bulletin 727-57A0132, Revision 3, dated March 20, 2003. Corrective Actions (c) If, during the inspection required by paragraph (b) of this AD, both attach fittings are found to have P/N 65-19296-9, -10, -13, or -14; P/N 65-99909-1724 or -1727; P/N 65-19296U13 or P/N 65-19296U14 (attach fitting made of 7075-T73511 or 7050-T7451 aluminum); no further action is required by this paragraph. (d) If, during the inspection required by paragraph (b) of this AD, any attach fitting is found to have P/N 65-19296-1 through -8 inclusive (attach fitting made of 7079-T6 aluminum): Before further flight, perform the actions in paragraphs (d)(1) and (d)(2) of this AD, as applicable. (1) Do detailed and high frequency eddy current inspections of the attach fitting holes for cracks and corrosion, repair any crack or corrosion found, and rework the attach fitting holes, in accordance with Figures 4 and 5 of the service bulletin, except as provided by paragraph (d)(2) of this AD. (2) If the attach fitting hole cannot be reworked or repaired in accordance with Figures 4 and 5 of the service bulletin: Before further flight, replace the attach fitting with a new attach fitting that has P/N 65-19296-9, -10, -13, or -14, P/N 65-99909-1724 or -1727, P/N 65-19296U13, or P/N 65-19296U14, in accordance with paragraph 7 of “Part II” of the Accomplishment Instructions of the service bulletin. Accomplishment of this replacement is terminating action for that fitting. Terminating Action (e) Within 120 months after the effective date of this AD, replace attach fittings that have P/N 65-19296-1 through -8 (attach fittings made of 7079-T6 aluminum) with new attach fittings that have P/N 65-19296-9, -10, -13, or -14, P/N 65-99909-1724 or -1727, P/N 65-19296U13, or P/N 65-19296U14 (attach fittings made of 7075-T73511 or 7050-T7451 aluminum), in accordance with paragraph 7 of “Part II” of the Accomplishment Instructions of the service bulletin. Replacement of all attach fittings made of 7079-T6 aluminum with new attach fittings made of 7075-T73511 or 7050-T7451 aluminum terminates the requirements of paragraph (d) of this AD. Parts Installation (f) As of the effective date of this AD, no person shall install, on any airplane, an attach fitting, P/N 65-19296-1, -2, -3, -4, -5, -6, -7, or -8 (attach fitting made of 7079-T6 aluminum), unless it has been inspected/reworked/repaired in accordance with paragraph (d) of this AD. Alternative Methods of Compliance (g)(1) In accordance with 14 CFR 39.19, the Manager, Seattle Aircraft Certification Office, FAA, is authorized to approve alternative methods of compliance (AMOCs) for this AD. (2) An AMOC that provides an acceptable level of safety may be used for any rework/repair required by this AD, if it is approved by a Boeing Company Designated Engineering Representative (DER) who has been authorized by the Manager, Seattle ACO, to make such findings. For a rework/repair method to be approved, the approval must specifically reference this AD. Incorporation by Reference (h) The actions shall be done in accordance with Boeing Alert Service Bulletin 727-57A0132, Revision 3, dated March 20, 2003. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. Effective Date (i) This amendment becomes effective on October 13, 2004. Issued in Renton, Washington, on August 26, 2004. Kevin M. Mullin, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 04-20205 Filed 9-7-04; 8:45 am] BILLING CODE 4910-13-P