AD 2000-11-10

Rolls-Royce plc (R-R) Model RB211-22B and -524 series turbofan engines, not incorporating new intermediate pressure (IP) compressor stage 6-7 rotor shafts assemblies with redesigned stage 6 disks in accordance with R-R Service Bulletin (SB) No. RB.211-72-9993, dated August 26, 1994. These engines are installed on but not limited to Boeing 747 series and 767 series, and Lockheed L-1011 series aircraft.

Note 1:

This airworthiness directive (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 (e) 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.

Required as indicated, unless previously accomplished.

To prevent an uncontained engine failure due to rupture of an IP compressor stage 6-7 rotor shaft, accomplish the following:

(a) For IP compressor stage 6-7 rotor shafts that have not been reworked in accordance with SB RB.211-72-9594, Revision 8, dated January 14, 1999, Revision 7, dated September 16, 1994, Revision 6, dated August 12, 1994, or Revision 5, dated February 12, 1993, remove the rotor shafts prior to exceeding the life limits established in Table 1 of this AD under sub-title “Pre SB72-9594” and replace with serviceable parts.

(b) Remove from service IP stage 6-7 rotor shafts that have been reworked in accordance with R-R SB RB.211-72-9594, Revision 8, dated January 14, 1999, Revision 7, dated September 16, 1994, Revision 6, dated August 12, 1994, or Revision 5, dated February 12, 1993, prior to exceeding the new, reduced cyclic life listed in Table 1 of this AD under the sub-title “Post SB72-9594” and replace with serviceable parts.

(c) Remove from service IP compressor stage 6-7 rotor shafts that have been reworked in accordance with R-R SB RB.211-72-9618, dated August 7, 1992, prior to exceeding the new, reduced cyclic life limits listed in Table 1 of this AD under the sub-title “Post SB72-9618” and replace with serviceable parts.

(d) IP compressor stage 6-7 rotor shaft rework in accordance with R-R SB RB.211-72-9594 can only be accomplished when the cyclic life of the part falls within the rework bands established in Table 1 of this AD. To accomplish rework of IP compressor stage 6-7 rotor shafts prior to reaching the lower limit of the rework bands specified in Table 1 of this AD, the part must be artificially aged to the cyclic life which defines the lower limit of the applicable rework bands in Table 1 of this AD.

Note 2:

For example, if the lower limit of the rework band is 8,000 cycles, and the part is reworked at 7,000 cycles, the part must be artificially aged by adding 1,000 cycles to the cycles since new recorded on the part; i.e., on return to service the cycles since new on this part would be 8,000 cycles.

(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. Operators shall submit their request through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office.

Note 3:

Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Engine Certification Office.

(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 aircraft to a location where the requirements of this AD can be accomplished.

(g) The actions of this AD shall be done in accordance with the following R-R Service Bulletins:

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, P.O. Box 31, Derby, DE24 8BJ, UK, telephone 011-44-1332-242424. 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.

(h) This amendment becomes effective on August 7, 2000.