AD 89-23-12

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AD Number:
89-23-12
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
ALLISON GAS TURBINE DIVISION, GENERAL MOTORS CORPORATION Model 250-C28B and -C28C Engines
Subject:
Turbine Nozzle Assembly
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
10/29/1989
Make:
Rolls-Royce Corporation
Model:
250-C28B | 250-C28C
Product Type:
Engine
Product Subtype:
Affected AD:
Superseded AD:
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39
Comments:
AIRWORTHINESS DIRECTIVES FINAL RULES: 89-23-12
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-6345

AD NUMBER:   89-23-12

SUBJECT HEADING:   ALLISON GAS TURBINE DIVISION, GENERAL MOTORS CORPORATION Model 250-C28B and -C28C Engines

ACTION:  

SUMMARY:  

DATES:   Effective October 29, 1989.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   89-23-12 ALLISON GAS TURBINE DIVISION, GENERAL MOTORS CORPORATION (Allison, formerly Detroit Diesel Allison): Amendment 39-6345.
Applicability: Allison Model 250-C28B and -C28C engines, with P/N 6898952 second stage turbine nozzle assembly, installed in aircraft certificated in any category except those with the following turbine assembly serial numbers:


Engine Model	Turbine Serial Number
250-C28B	CAT 70498, CAT 70499
	CAT 70502, CAT 70513 and subsequent
250-C28C	CAT 28010 and subsequent

Compliance: Required as indicated, unless already accomplished.
To prevent failure of the second stage turbine nozzle which can lead to rubbing contact between the nozzle diaphragm and the second stage turbine wheel possibly resulting in an uncontained turbine wheel failure, accomplish the following:
(a) Within the next 100 hours time-in-service after the effective date of this AD, or at the next turbine repair or overhaul, whichever occurs first, but not later than November 30, 1989, perform the following:
Modify and reidentify second stage turbine nozzle, P/N 6898952, into P/N 23001942, in accordance with Allison Commercial Engine Alert Bulletin CEB-A-72-2044, Revision 4, dated May 1, 1989.
NOTE: Existing Model 250-C28B and -28C engines which have incorporated Allison Commercial Engine Alert Bulletin CEB-A-72-2044, Revision 4, dated May 1, 1989, or prior issues of CEB-72-2044, or engines which have incorporated P/N 23001942 are already in compliance with this AD.
(b) 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.
(c) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, an alternate method of compliance with the requirements of this AD or adjustments to the compliance schedule specified in this AD may be approved by the Manager, Chicago Aircraft Certification Office, Federal Aviation Administration, 2300 East Devon Avenue, Des Plaines, Illinois 60018.
The second stage turbine nozzle modification shall be done in accordance with Allison Commercial Engine Alert Bulletin CEB-A-72-2044, Revision 4, dated May 1, 1989. 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 Allison Gas Turbine Division, General Motors Corporation, P.O. Box 420, Indianapolis, Indiana 46206-0420. Copies may be inspected at the Regional Rules Docket, Office of the Assistant Chief Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Room 311, Burlington, Massachusetts 01803, or at the Office of the Federal Register, 1100 L Street, N.W., Room 8301, Washington, D.C. 20591.
This amendment (39-6345, AD 89-23-12) becomes effective on October 29, 1989.

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