AD 95-10-17 Airworthiness Directives; Lockheed Model L-1011-385 Series Airplanes

Models named: L-1011-385 series. Read the applicability below — it usually turns on serial or part numbers too.

All Model L-1011-385 series airplanes, certificated in any category. Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (d) to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition; or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any airplane from the applicability of this AD.

Required as indicated, unless accomplished previously. To prevent reduced structural integrity of the fuselage shell due to fatigue cracking of the fuselage frames, accomplish the following: (a) Prior to the accumulation of 25,000 total landings, or within 25 days after the effective date of this AD, whichever occurs later: Perform either an external X-ray inspection, or both an internal close visual and an eddy current inspection, to detect cracking or severing of the fuselage frames at all fuselage frames where the frame outer flange attaches to the water line (WL) 280.6 longeron (upper stringerless sidewall longeron) on both the left- and right-hand sides of the airplane, in accordance with Lockheed Alert Service Bulletin 093-53-A271, dated April 25, 1995, including Attachments 1 and 2. (1) If no cracking or severing is found, no further action is required by paragraph (a) of this AD. (2) If any cracking or severing is found, prior to further flight, perform an inspection (using either an eddy current surface scan or a magneto-optic imager) to detect cracking of the adjacent frames and external skin, in accordance with the alert service bulletin. Prior to further flight, repair any cracking or severing found during any inspection required by paragraph (a) of this AD, in accordance with the alert service bulletin. (b) Except as provided by paragraph (c) of this AD, prior to the accumulation of 20,000 total landings, or within 120 days after the effective date of this AD, whichever occurs later: Perform either an external X-ray inspection, or both an internal close visual and an eddy current inspection, to detect cracking or severing of the fuselage frames between fuselage stations (FS) 589 to FS 749 (for the C1 door) and between FS 509 to FS 749 (for the C1A door) on the right-hand side of the airplane, in accordance with Lockheed Alert Service Bulletin 093-53-A271, dated April 25, 1995, including Attachments 1 and 2. If any cracking or severing is found, prior to further flight, perform an inspection to detect cracking of the fuselage frames at FS 1605 to FS 1745 on the left- and right-hand sides of the airplane, in accordance with the alert service bulletin. (1) If no cracking is found, no further action is required by paragraph (b) of this AD. (2) If any cracking is found, prior to further flight, perform an inspection (using either an eddy current surface scan or a magneto-optic imager) to detect cracking of the adjacent frames and external skin, in accordance with the alert service bulletin. Prior to further flight, repair any cracking or severing found during any inspection required by paragraph (b) of this AD, in accordance with the alert service bulletin. (c) Airplanes on which the inspection required by paragraph (a) of this AD is performed within the compliance time specified in paragraph (b) of this AD are not required to accomplish the inspection required by paragraph (b). (d) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Atlanta Aircraft Certification Office (ACO), FAA, Small Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta ACO. Note 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta ACO. (e) Special flight permits may be issued in accordance with Secs. 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (f) The inspections and repair shall be done in accordance with Lockheed Alert Service Bulletin 093-53-A271, dated April 25, 1995, including Attachments 1 and 2. (NOTE: Attachment 1 is undated.) 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 Lockheed Aeronautical Systems Support Company (LASSC), Field Support Department, Dept. 693, Zone 0755, 2251 Lake Park Drive, Smyrna, Georgia 30080. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Small Airplane Directorate, Atlanta Aircraft Certification Office, Campus Building, 1701 Columbia Avenue, Suite 2-160, College Park, Georgia; or at the Office of [[Page 26686]] the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment becomes effective on May 23, 1995. Issued in Renton, Washington, on May 10, 1995. James V. Devany, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 95-11974 Filed 5-17-95; 8:45 am] BILLING CODE 4910-13-U