AD 86-24-05 ACTIVE

86-24-05 ROLLS-ROYCE plc (formerly Rolls-Royce Limited): Amendment 39-5458. Applies to Rolls-Royce (R-R) RB211-22B and -524 series turbofan engines.

Compliance is required as indicated, unless already accomplished.

To prevent intermediate pressure compressor (IPC) rotor and turbine (IPT) disc uncontained failure, remove and inspect or retire from service IPC rotors and IPT disks which were oversped prior to August 13, 1982, using the laboratory inspection referred to in R-R Mandatory Service Bulletin (SB) RB.211-72-5887, Revision 2, dated August 23, 1985, or FAA approved equivalent as follows:

(a) For rotors and disks oversped in excess of 115 percent intermediate pressure rotor speed (N2) up to and including 120 percent N2:

(1) Inspect for cracks at the first engine shop visit after the effective date of this AD, after having accumulated 4,000 or more cycles since overspeed.

(2) Reinspect, thereafter, at intervals not to exceed 4,500 cycles in service.(3) Remove and retire cracked parts from service, prior to further flight, and replace with serviceable parts.

(b) Remove and retire from service rotors and disks oversped in excess of 120 percent N2 at the first engine shop visit after the effective date of this AD, after having accumulated 3,000 or more cycles since overspeed.

(c) Rotors and disks which have experienced multiple overspeeds are subject to the more stringent requirements of the applicable paragraphs (a) or (b) above for each of the overspeed events.

(d) Rotors and disks that have experienced an overspeed that was read on a gauge calibrated only to 110 percent N2, and in the absence of substantiating data as to the magnitude of the overspeed, must be considered as having oversped beyond 120 percent N2 and are subject to the requirements of paragraph (b) above.

NOTE: Shop visit is defined as the input of an engine into a repair shop where the subsequent engine maintenance entails one or more of the following:

(a) Separation of a major engine flange (lettered or numbered) other than flanges mating with major sections of the nacelle or reverser. Separation of flanges purely for purposes of shipment, without subsequent internal maintenance, is not a "shop visit".

(b) Removal of a disk, hub, or spool.

(c) Removal of a main or angle gearbox.

(d) Removal of fuel nozzles.

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 request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Engine Certification Office, Aircraft Certification Division, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803.

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.

R-R Mandatory SB RB.211-72-5887, identified and described in this document, 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 this document from the manufacturer may obtain copies upon request to Rolls-Royce plc, Technical Publications Department, P.O. Box 31, Derby DE2 8BJ, England. This document also may be examined at the Office of the Regional Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, Rules Docket Number 85-ANE-31, Room 311, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except Federal holidays.

This amendment becomes effective on December 20, 1986.