AD 2003-14-21 Airworthiness Directives; Lockheed Martin Models L-1011 Airplanes and Rolls-Royce plc RB211 Series Turbofan Engines

This airworthiness directive (AD) is applicable to Lockheed Martin models L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15, and L-1011-385-3 airplanes and Rolls-Royce plc (RR) RB211-22B-02, RB211-524B-02, RB211-524B-B-02, RB211-524B3-02, RB211-524B4-02, and RB211-524B4-D-02 series turbofan engines.

Compliance with this AD is required as indicated, unless already done. To prevent undetected fires originating within the high speed gearbox (HSGB) from breaching the HSGB case, which could result in engine damage and increased difficulty in extinguishing a fire, and to prevent undetected low pressure (LP) compressor shaft location bearing failure, which could result in LP compressor and turbine shaft assembly failure, turbine overspeed, and possible uncontained engine failure, do the following: Requirements for All Applicable Airplanes and Engines (a) Incorporate the following service bulletins concurrently or before accomplishing the requirements of RR Mandatory Service Bulletin (MSB) RB.211-72-C963, dated December 4, 2001, or RR MSB RB.211-72-C863, dated February 15, 2002, whichever is applicable, as specified in paragraphs (b) through (d) of this AD: (1) Install a new design engine front bearing housing assembly in accordance with RR SB RB.211-72-6149, Revision 9, dated November 24, 1999. (2) Install a revised gearbox breather assembly in accordance with RR SB RB.211-72-C178, Revision 1, dated March 9, 2001. (3) Install overheat detectors in the gearbox breather duct assembly, in accordance with RR SB RB.211-77-C144, Revision 1, dated February 13, 2002. (4) Modify airplane instrument panels and consoles with the installation of the engine failure indicators, failure lenses, and marker, in accordance with Lockheed Martin SB 093-77-060, Revision 1, dated June 30, 2003. RB211-524B-02 and RB211-524B-B-02 Engines (b) Within three months after the effective date of this AD, for RB211-524B-02 and RB211-524B-B-02 engines, do the following: (1) Install an LP compressor shaft extreme axial movement detector system in accordance with RR MSB RB.211-72-C963, dated December 4, 2001. (2) Replace existing speed probe loom electrical support assembly, located on the engine front bearing housing assembly, with speed probe loom electrical support assembly P/N FW15212, in accordance with 3.A. Accomplishment Instructions of RR MSB RB.211-71-E047, dated August 2, 2002. RB211-22B-02 Engines (c) Within three years after the effective date of this AD, for RB211-22B-02 engines, install an LP compressor shaft extreme axial movement detector system in accordance with RR MSB RB.211-72-C863, dated February 15, 2002. RB211-524B3-02, RB211-524B4-02, and RB211-524B4-D-02 Engines (d) Within four years after the effective date of this AD, for RB211-524B3-02, RB211-524B4-02, and RB211-524B4-D-02 engines, install an LP compressor shaft extreme axial movement detector system in accordance with RR MSB RB.211-72-C963, dated December 4, 2001. Alternative Methods of Compliance (e) 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, Engine Certification Office (ECO) for engines or Manager, Atlanta Aircraft Certification Office (ACO) for airplanes. Operators must submit their request through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, ECO, or Manager, ACO. Note 1: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the ECO or ACO. Special Flight Permits (f) Special flight permits may be issued in accordance with §§ 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 done. Note 2: The subject of this AD is addressed in CAA airworthiness directive AD 006-12-2001, AD 003-08-2002, and AD 006-02-2002. Documents That Have Been Incorporated by Reference (g) The actions in this AD must be done in accordance with the following Rolls-Royce plc service bulletins and Lockheen Martin service bulletin: Document No. Pages Revision Date RB.211-72-6149 All 9 Nov. 24, 1999. Total pages: 72 RB.211-77-C144 All 1 Feb. 13, 2002. Total pages: 57 RB.211-72-C963 All Original Dec. 4, 2001. Total pages: 75 RB.211-71-E047 All Original Aug. 2, 2002. Total pages: 6 RB.211-72-C863 All Original Feb. 15, 2002. Total pages: 75 Lockheed Martin 093-77-060 1 1 Jun. 30, 2003.   2-4 Original Apr. 11, 2002.   5 1 Jun. 30, 2003.   6-10 Original Apr. 11, 2002. Total pages: 10 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 Rolls-Royce plc, PO Box 31, Derby, England, DE248BJ; telephone: 011-44-1332-242-424; fax: 011-44-1332-245-418 and Lockheed Martin & Logistics Center, 120 Orion Street, Greenville, South Carolina 29605. Copies may be inspected at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. Effective Date (h) This amendment becomes effective on August 25, 2003. Issued in Burlington, Massachusetts, on July 10, 2003. Francis A. Favara, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 03-17949 Filed 7-18-03; 8:45 am] BILLING CODE 4910-13-P