80-13-05 R1: (HPC) Rotor Stage 1 And 2 Disk Assembly

80-13-05 R1 ROLLS-ROYCE, LTD: Amendment 39-3804 as amended by Amendment 39-4742. Applies to Rolls-Royce RB211-22B turbofan engines. Compliance required as indicated, unless already accomplished. To preclude possible high pressure compressor (HPC) rotor stage 1 and 2 disk assembly failure, remove from service all HPC rotor stage 1 and 2 disk assemblies, listed by part number and serial number in Appendices 1 and 2 of Rolls-Royce Alert Service Bulletin No. RB211-72-A5722, Revision 3, dated April 17, 1981, in accordance with the following compliance schedule: 1. For disk assemblies listed in Appendix 1: a. After July 31, 1980, no disk assemblies may exceed 7,000 flight cycles. b. After December 31, 1980, no disk assemblies may exceed 6,000 flight cycles. c. All remaining disk assemblies by April 30, 1981. 2. For disk assemblies listed in Appendix 2: a. After the effective date of this amendment, no disk assemblies may exceed 9,000 flight cycles. NOTE: For the purpose of this AD, a flight cycle is considered to be an engine operating sequence from takeoff to landing. Replace with an FAA-approved, serviceable HPC rotor stage 1 and 2 disk assembly. The manufacturer's Alert Service Bulletin identified and described in this directive is incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a). All persons affected by this directive who have not already received the service bulletin from the manufacturer may obtain copies upon request to Technical Publications Department, Rolls-Royce, Ltd., Derby, England DE2 8BJ. The service bulletin may also be examined at Federal Aviation Administration, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, Massachusetts. Amendment 39-3804 became effective upon publication in the Federal Register. This Amendment 39-4742 becomes effective November 28, 1983.