AD 91-07-17

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AD Number:
91-07-17
Document Type:
AD Final Rules
Docket Number:
90-ANE-23
Subject Heading:
GENERAL ELECTRIC COMPANY Model CT58-140-1 Engines
Subject:
Gas Generator
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
04/26/1991
Make:
General Electric Company
Model:
CT58-140-1
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Superseded AD: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Superseded By: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: 91-07-17
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   90-ANE-23

AMENDMENT:   39-6954

AD NUMBER:   91-07-17

SUBJECT HEADING:   GENERAL ELECTRIC COMPANY Model CT58-140-1 Engines

ACTION:  

SUMMARY:  

DATES:   Effective April 26, 1991.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   91-07-17 GENERAL ELECTRIC COMPANY: Amendment 39-6954. Docket No. 90-ANE-23.
Applicability: General Electric Company (GE) CT58-140-1 turboshaft engines overhauled by H&S Aviation, Division 3 (Formerly Hants and Sussex), Portsmouth, England, between March 14, 1989, and August 21, 1989, installed on, but not limited to, Sikorsky S-61 and Boeing V107 aircraft. The affected parts are identified by part number (P/N) and serial number (S/N) and are installed in engines with S/N, as follows:

Engine S/N	Part Name	P/N	Part	S/N
295235	Stage 1 forward cooling plate	37C30005P101	BJWTMS	7732
	Stage 1 aft cooling plate	3002T25P01	BJWTMS	6649
	Stage 2 forward cooling plate	000T88P02	ASVA	3663
	Stage 2 aft cooling plate	3002T27P01	ASVA	0125
	Power Turbine (PT) wheel & shaft	5002T30P01	GAT	59510
295206	Stage 1 turbine wheel	4002T17P02	GATBK	483
	Stage 2 turbine wheel	4002T96P02	GATFE	352
280326	Stage 2 turbine wheel	4002T96P02	GATL	2835
	PT wheel and shaft	5002T30P01	GAT	59722
280218	PT wheel and shaft	5002T30P01	GAT	59692
280294	Stage 1 forward cooling plate	37C300055P101	BJWTMS	7663
	Stage 1 aft cooling plate	3002T25P01	5778	5778
	Stage 2 forward cooling plate	3000T88P02	BJWTMS	5951
	Stage 2 aft cooling plate	3002T27P01	BJWTMS	7356
	Stage 2 turbine wheel	4002T96P02	GATEL	092

Compliance: Required as indicated, unless already accomplished.
To prevent failure of suspect gas generator (GG) turbine rotor parts and power turbine (PT) wheels, which may have a reduced low cycle fatigue life due to inadvertent shotpeening which could result in an uncontained engine failure, remove and inspect all surfaces of GG turbine rotor parts and PT wheels identified above by 20x microscope as follows:
(a) Part S/N BJWTMS 7732, BJWTMS 6649, ASVA 3663, ASVA 0125, and GAT 59510, prior to accumulating 5,853 cycles since new (CSN).
(b) Part S/N GATBK 483, and GATFE 352, prior to accumulating 5,249 CSN.
(c) Part S/N GATL 2835, prior to accumulating 10,792 CSN.
(d) Part S/N GAT 59722, prior to accumulating 10,856 CSN.
(e) Part S/N GAT 59692, prior to accumulating 9,660 CSN.
(f) Part S/N BJWTMS 7663, BJWTMS 5778, BJWTMS 5951, BJWTMS 7356, and GATEL 092, prior to accumulating 5,696 CSN.
(g) Remove from service parts found with evidence of shotpeening and replace with a serviceable part. Reidentify parts found with no evidence of shotpeening prior to return to service.
NOTE: GE Alert Service Bulletin CT58 A72-173 (CEB-275), contains information in reference to paragraphs (a) through (g) above.
(h) 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.
(i) 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, Engine Certification Office, ANE-140, Engine and Propeller Directorate, Aircraft Certification Service, FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803-5299.
All persons affected by this directive who have not already received the appropriate alert service bulletin from the manufacturer may obtain copies upon request to GE Aircraft Engines, 1000 Western Avenue, Lynn, Massachusetts 01910. These documents may be examined at the FAA, New England Region, Office of the Assistant Chief Counsel, Room 311, 12 New England Executive Park, Burlington, Massachusetts.
This amendment (39-6954, AD 91-07-17) becomes effective on April 26, 1991.

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