85-10-05 R1 ROLLS-ROYCE LIMITED: Amendment 39-5063 as amended by Amendment 39-5239. Applies to Rolls-Royce RB211-22B and RB211-524B, -524C, and -524D series turbofan engines.
Compliance is required as indicated unless already accomplished.
To prevent an internal oil fire, failure of the low compressor rotor shaft, and subsequent low turbine rotor overspeed leading to an uncontained rotor failure, accomplish the following:
Prior to December 31, 1987, incorporate low pressure rotor location bearing area modifications as specified in Rolls-Royce Mandatory SB RB211-72-6847, Revision 2, dated March 30, 1984, or FAA approved equivalent.
Upon request, an alternate means of compliance may be approved by the Manager, Engine Certification Office, Aircraft Certification Division, New England Region, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803.
Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished.
Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Engine Certification Office, New England Region, may adjust the compliance time specified in this AD.
The manufacturer's SB identified and described in this directive is incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received the SB from the manufacturer may obtain copies upon request to Rolls-Royce Limited, Technical Publications Department, P.O. Box 31, Derby DE2 8BJ, England. The SB may also be examined at the office of the Regional Counsel, New England Region, Federal Aviation Administration, Rules Docket No. 84-ANE-14, 12 New England Executive Park, Burlington, Massachusetts 01803, weekdays between the hours of 8:00 a.m. and 4:30 p.m. except Federal holidays.
Amendment 39-5063 became effective on July 23, 1985.This Amendment 39-5239 becomes effective on March 28, 1986.