AD 92-04-08

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AD Number:
92-04-08
Document Type:
AD Final Rules
Docket Number:
91-ANE-58
Subject Heading:
GENERAL ELECTRIC COMPANY Model (GE) CF6-80A Series Engines
Subject:
Stage 1 Disk/Shafts
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
03/27/1992
Make:
General Electric Company
Model:
CF6-80A | CF6-80A1 | CF6-80A2 | CF6-80A3
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Superseded AD: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Superseded By: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: 92-04-08
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   91-ANE-58

AMENDMENT:   39-8179

AD NUMBER:   92-04-08

SUBJECT HEADING:   GENERAL ELECTRIC COMPANY Model (GE) CF6-80A Series Engines

ACTION:  

SUMMARY:  

DATES:   Effective March 27, 1992.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:   92-04-08 GENERAL ELECTRIC COMPANY: Amendment No. 39-8179, Docket No. 91-ANE-58.
Applicability: General Electric Company (GE) CF6-80A series turbofan engines installed on, but not limited to, Airbus A310 and Boeing 767 aircraft.
Compliance: Required as indicated, unless previously accomplished.
To prevent an uncontained engine failure, an inflight engine shutdown, and damage to the aircraft, accomplish the following:
(a) Prior to further flight, after the effective date of this AD, remove from service CF6-80A high pressure turbine rotor (HPTR) stage 1 disk/shafts identified by the following part number (P/N) and serial number (S/N):

PART NUMBER	SERIAL NUMBER
9362M58	MPOP8483
9362M58	MPOS1676

Prior to returning affected engines to service replace with a serviceable part.
(b) Eddy current and fluorescent penetrant inspect, CF6-80A HPTR stage 1 disk/shafts identified by the following P/N and S/N, in accordance with the Accomplishment Instructions of GE CF6-80A Service Bulletin (SB) 72-605, dated December 20, 1991, within the next 400 cycles in service (CIS) after the effective date of this AD, not to exceed 3,400 total CIS since last chrome plating repair procedure:

PART NUMBER	SERIAL NUMBER
9234M67	MPOP2707
9234M67	MPON6442
9234M67	MPOP7075
9362M58	MPOS4048

(c) Remove from service CF6-80A HPTR stage 1 disk/shafts which exceed the serviceable limits defined in Paragraphs 2.C.(6) and 2.D. of the Accomplishment Instructions of GE CF6-80A SB 72-605, dated December 20, 1991.
(d) 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.
(e) Upon submission of substantiating data by an owner or operator through an FAA Inspector (maintenance, avionics, or operations, as appropriate), an alternate method of compliance with the requirements of this AD or adjustments to the compliance times specified in this AD may be approved by the Manager, Engine Certification Office, Engine & Propeller Directorate, Aircraft Certification Service, 12 New England Executive Park, Burlington, Massachusetts 01803-5299.
(f) The inspections shall be done in accordance with the following General Electric document:

Document No.	Page No.	Issue	Date
GE CF6-80A	1-29	Original	Dec. 20, 1991
SB 72-605			
Total Pages: 29			

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 General Electric Aircraft Engines, CF6 Distribution Clerk, Room 132, 111 Merchant Street, Cincinnati, Ohio 45246. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, Room 311, 12 New England Executive Park, Burlington, Massachusetts, or at the Office of the Federal Register, 1100 L Street, NW, Room 8401, Washington, DC.
(g) This amendment (39-8179, AD 92-04-08) becomes effective on March 27, 1992.

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