AD 2001-23-02 Airworthiness Directives; Rolls-Royce plc RB211 Turbofan Engines

Rolls-Royce plc model (RR) RB211-535E4-37 and RB211-535E4-B-37 turbofan engines, with the following high pressure (HP) turbine disks installed: part number (P/N) UL10323, with serial numbers (SN's) CQDY6070 and higher; P/N UL27680, with any serial number; and P/N UL27681, with any serial number. RR model B211-535C-37 turbofan engines, with the following HP turbine disks installed: P/N LK80622, with SN LQDY6316 and higher; P/N LK80623, with SN CQDY5945 and higher; and P/N UL28267, with any serial number. RR model RB211-535E4-B-75 turbofan engines with the following HP turbine disks installed: P/N UL10323, with SN CQDY6070 and higher; and P/N UL27680, with any serial number. RR model RB211-22B-02 turbofan engines with the following HP turbine disks installed: P/N LK80622, with SN LQDY6316 and higher; P/N LK80623, with SN CQDY5945 and higher; and P/N UL28267, having any serial number. These engines are installed on but not limited to Boeing 757, Tupolev Tu204, and Lockheed L-1011 series airplanes. Note 1: This AD applies to each engine 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 engines that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (c) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.

Compliance with this AD is required as indicated, unless already done. To prevent possible high pressure (HP) turbine disk failure, which could result in an uncontained engine failure and damage to the airplane, accomplish the following: Inspection for All Except Model RB211-22B-02 (a) For model RB211-535E4-37, RB211-535E4-B-37, RB211-535C-37, and RB211-535E4-B-75 engines, conduct a one-time inspection of the HP turbine disks identified in Section A. (1) and (2), of RR SB No. RB.211-72-C817, Revision 2, dated March 7, 2001, for cracks on the rear face of the cooling air holes. (1) For disk life at or below 13,700 cycles on the effective date of this AD, inspect at the earlier of the following : (i) At the next shop visit when the HP turbine blades have been removed from the disk; or (ii) Prior to exceeding 14,500 cycles-in-service (CIS) since new. (2) For disk life above 13,700 cycles on the effective date of this AD, inspect at the earliest of the following: (i) Prior to reaching 15,300 CIS since new; or (ii) Within 800 cycles after the effective date of this AD; or (iii) At the next shop visit when the HP turbine blades have been removed from the disk. (3) Inspect the HP turbine disk for cracks on the rear face of the cooling air holes in accordance with the Accomplishment Instructions, Section 3 of RR SB No. RB.211-72-C817, Revision 1, dated January 24, 2000; or RR SB No. RB.211-72-C817, Revision 2, dated March 7, 2001. (4) Replace any cracked HP turbine disk with a serviceable part. Inspections for Model RB211-22b-02 (b) For model RB211-22B-02 engines, conduct a one-time inspection of the HP turbine disks identified in Section A. of RR SB No. RB.211-72-C877, Revision 1, dated March 7, 2001, for cracks on the rear face of the cooling air holes. (1) For disk life at or below 11,000 CIS on the effective date of this AD, inspect at the earlier of the following: (i) At the next shop visit when the HP turbine blades have been removed from the disk; or (ii) Prior to exceeding 11,000 CIS since new. (2) HP turbine disks with more than 11,000 CIS on the effective date of this AD must be inspected within 300 CIS after the effective date of this AD. (3) Inspect the HP turbine disk for cracks on the rear face of the cooling air holes in accordance with the Accomplishment Instructions outlined in Section 3 of RR SB No. RB.211-72-C877, dated January 29, 2000, or RR SB No. RB.211-72-C877, Revision 1, dated March 7, 2001. (4) Replace any cracked HP turbine disk with a serviceable part. Alternative Methods of Compliance (c) 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). Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, ECO. Note 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the ECO. Ferry Flights (d) Special flight permits may be issued in accordance with sections 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. Documents That Have Been Incorporated by Reference (e) The inspection must be done in accordance with the following Rolls-Royce mandatory service bulletins:   Document No. Pages Revision Date MSB RB.211-72-C817 1 1 Jan. 24, 2000.   2-7 Original Dec. 14, 1999.   8-11 1 Jan. 24, 2000.   12-21 Original Dec. 14, 1999. Total pages: 21 MSB RB.211-72-C817 All 2 Mar. 7, 2001. Total pages: 6 MSB RB.211-72-C877 All Original Jan. 29, 2000. Total pages: 17 MSB RB.211-72-C877 All 1 Mar. 7, 2001. Total pages: 5 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; telephone: International Access Code 011, Country Code 44, 1332-249428, fax: International Access Code 011, Country Code 44, 1332-249223. Copies may be inspected, by appointment, 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. Note 3: The subject of this AD is addressed in Civil Aviation Authority (CAA) Airworthiness Directives 003-12-99 and 004-01-2000. Effective Date (f) This amendment becomes effective on December 24, 2001. Issued in Burlington, Massachusetts, on November 5, 2001. Mark C. Fulmer, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 01-28418 Filed 11-16-01; 8:45 am] BILLING CODE 4910-13-U