AD 2004-09-11 Airworthiness Directives; Boeing Model 767-200, -300, and -300F Series Airplanes

Models named: 767-200, -300, -300F series. Read the applicability below — it usually turns on serial or part numbers too.

Model 767-200, -300, and -300F series airplanes, line numbers 1 through 883 inclusive; certificated in any category.

Required as indicated, unless accomplished previously. To detect and correct cracks in the outer cylinder of the main landing gear (MLG), which could result in collapsed MLG and consequent reduced controllability of the airplane during takeoff and landing, accomplish the following: Service Bulletin References (a) The term “service bulletin,” as used in this AD, means the Accomplishment Instructions of Boeing Service Bulletin 767-32A0196, Revision 2, dated May 15, 2003. Inspection or Replacement and Corrective Actions (b) Within 18 months after the effective date of this AD, for both MLG, do the actions in either paragraph (b)(1) or (b)(2) of this AD. (1) Perform a gap measurement of the upper and lower joint gaps (includes measuring and recording upper and lower joint gaps twice); and an ultrasonic inspection of the outer cylinder of the main landing gear for cracks between the downlock fitting attach lugs, per Part 1 of the service bulletin. (2) Replace the outer cylinder of the main landing gear with a new or overhauled outer cylinder per Part 2 of the service bulletin. (c) If no crack is found during the inspection required by paragraph (b)(1) of this AD, before further flight, do the restoration (includes installing shims as applicable, electrical bracket, and cotter pins; and marking the main landing gear) per the service bulletin. (d) If any crack is found during the inspection required by paragraph (b)(1) of this AD: Before further flight, overhaul the outer cylinder of the MLG or replace the outer cylinder of the MLG with an interchangeable outer cylinder per Part 2 of the service bulletin, except as provided by paragraph (e) of this AD. (e) If any crack is found in the outer cylinder that cannot be removed within the repair limits specified in the service bulletin, during the overhaul specified in paragraph (d) of this AD, and the service bulletin specifies to contact Boeing for appropriate action: Before further flight, repair per 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 a Boeing Company Designated Engineering Representative 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. Note 1: When the outer cylinder is re-installed, attach the downlock fittings onto the outer cylinder as specified in the applicable Boeing Component Maintenance Manual (CMM), Document Number 161T1000, Section 32-11-19, Temporary Revision (TR) 32-61, dated March 26, 2002, or Section 32-11-19, pages 712 through 716, dated July 1, 2002, or dated July 1, 2003; or CMM Document Number 161T1000, Section 32-11-20, TR 32-62, dated March 26, 2002, or Section 32-11-20, pages 718 through 722, dated July 1, 2002, or dated July 1, 2003. Actions Accomplished Per Previous Issue of Service Bulletin (f) Accomplishment of the applicable actions before the effective date of this AD per Boeing Alert Service Bulletin 767-32A0196, dated August 1, 2002; or Boeing Service Bulletin 767-32A0196, Revision 1, dated September 26, 2002; are considered acceptable for compliance with the corresponding action specified in this AD. Parts Installation (g) As of the effective date of this AD, no person may install a MLG on any airplane, unless the outer cylinder of the MLG has been inspected and follow-on and corrective actions have been accomplished per Boeing Service Bulletin 767-32A0196, Revision 2, dated May 15, 2003; or unless the outer cylinder is new; or unless the outer cylinder has not been installed on any airplane since its last overhaul. Alternative Methods of Compliance (h) In accordance with 14 CFR 39.19, the Manager, Seattle ACO, FAA, is authorized to approve alternative methods of compliance for this AD. Incorporation by Reference (i) Unless otherwise specified in this AD, the actions shall be done in accordance with Boeing Service Bulletin 767-32A0196, Revision 2, dated May 15, 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, PO 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 Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. Effective Date (j) This amendment becomes effective on June 4, 2004. Issued in Renton, Washington, on April 20, 2004. Ali Bahrami, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 04-9590 Filed 4-29-04; 8:45 am] BILLING CODE 4910-13-P