[Federal Register Volume 59, Number 61 (Wednesday, March 30, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-5939]


[[Page Unknown]]

[Federal Register: March 30, 1994]


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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39

[Docket No. 93-ANE-42; Amendment 39-8851; AD 94-06-03]

 

Airworthiness Directives; General Electric Company CF6 Series 
Turbofan Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to General Electric Company (GE) CF6-80C2 series turbofan 
engines, that requires an inspection for cracks in the stage 1 high 
pressure turbine (HPT) disk rim bolt holes, and replacement, if 
necessary, with serviceable parts. This amendment is prompted by a 
report of an uncontained stage 1 HPT disk failure which resulted in an 
aborted takeoff. The actions specified by this AD are intended to 
prevent an uncontained stage 1 HPT disk failure, which could result in 
an inflight engine shutdown, rejected takeoff, or damage to the 
aircraft.

DATES: Effective April 29, 1994.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of April 29, 1994.

ADDRESSES: The service information referenced in this AD may be 
obtained from General Electric Aircraft Engines, CF6 Distribution 
Clerk, room 132, 111 Merchant Street, Cincinnati, OH 45246. This 
information may be examined at the Federal Aviation Administration 
(FAA), New England Region, Office of the Assistant Chief Counsel, 12 
New England Executive Park, Burlington, MA; or at the Office of the 
Federal Register, 800 North Capitol Street NW., suite 700, Washington, 
DC.

FOR FURTHER INFORMATION CONTACT: Robert J. Ganley, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803-5299; telephone (617) 
238-7138; fax (617) 238-7199.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations to include an airworthiness directive (AD) that is 
applicable to General Electric Company (GE) CF6-80C2 series turbofan 
engines was published in the Federal Register on September 24, 1993 (58 
FR 49944). That action proposed to require an eddy current inspection 
for cracks in the stage 1 HPT disk rim bolt holes, and replacement, if 
necessary, with serviceable parts in accordance with GE CF6-80C2 
Service Bulletin (SB) No. 72-614, Revision 1, dated September 8, 1992.
    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.
    Two commenters support the rule as proposed.
    The FAA has determined that the compliance end date of December 31, 
1993, noted in compliance paragraph (a)(3) of the Notice of Proposed 
Rulemaking (NPRM) is inconsistent with the anticipated publication date 
of this amendment, and as such may place an undue burden on operators. 
The NPRM proposed a compliance period of 100 days to accomplish the 
required actions based on the anticipated publication date of the AD at 
the time the NPRM was published. Therefore, the compliance end date in 
compliance paragraph (a)(3) of this final rule has been revised to 130 
days after date of publication in the Federal Register. This time 
period is comprised of the 30 day period after publication and prior to 
the effective date plus 100 days.
    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the change described 
previously. The FAA has determined that this change will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.
    There are approximately 66 GE CF6-80C2 series turbofan engines of 
the affected design in the worldwide fleet. The FAA estimates that one 
engine of the affected design is installed on an aircraft of U.S. 
registry will be affected by this AD, that it will take approximately 
232 work hours per engine to accomplish the required actions, and that 
the average labor rate is $55 per work hour. Required parts will cost 
approximately $172,500 per engine. Based on these figures, the total 
cost impact of the AD on U.S. operators is estimated to be $185,260.
    The regulations adopted herein will not have substantial direct 
effects on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government. Therefore, in 
accordance with Executive Order 12612, it is determined that this final 
rule does not have sufficient federalism implications to warrant the 
preparation of a Federalism Assessment.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) will not have a 
significant economic impact, positive or negative, on a substantial 
number of small entities under the criteria of the Regulatory 
Flexibility Act. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the Rules Docket at the location provided under the caption 
ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends 14 CFR part 
39 of the Federal Aviation Regulations as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C. 
106(g); and 14 CFR 11.89.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

94-06-03 General Electric Company: Amendment 39-8851. Docket 93-ANE-
42.

    Applicability: General Electric Company (GE) CF6-80C2 series 
turbofan engines installed on but not limited to Airbus A300 and 
A310 series, Boeing 747 and 767 series, and McDonnell Douglas MD-11 
series aircraft.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent an uncontained stage 1 high pressure turbine (HPT) 
disk failure, which could result in an inflight engine shutdown, 
rejected takeoff, or damage to the aircraft, accomplish the 
following: (a) Eddy current inspect (ECI) for cracks stage 1 HPT 
disks, Part Numbers 9392M23G10, 9392M23G12, and 9392M23G21, with 
serial numbers listed in paragraph 1.A. of GE CF6-80C2 Service 
Bulletin (SB) No. 72-614, Revision 1, dated September 8, 1992, in 
accordance with the accomplishment instructions of GE CF6-80C2 SB 
No. 72-614, Revision 1, dated September 8, 1992, as follows: (1) For 
disks which have accumulated less than 3,000 cycles since new (CSN) 
on the effective date of this AD, ECI the rim bolt holes at the next 
engine shop visit after accumulating 3,000 CSN, or prior to 
accumulating 4,500 CSN, whichever occurs earlier.
    (2) For disks which have accumulated 3,000 CSN or more, but less 
than 4,000 CSN on the effective date of this AD, ECI the rim bolt 
holes at the next engine shop visit, or prior to accumulating 4,500 
CSN, whichever occurs earlier.
    (3) For disks which have accumulated 4,000 CSN or more, but less 
than 9,500 CSN on the effective date of this AD, ECI the rim bolt 
holes at the next engine shop visit, or prior to August 8, 1994, 
whichever occurs earlier.
    (4) For disks which have accumulated 9,500 CSN or more on the 
effective date of this AD, ECI the rim bolt holes at the next engine 
shop visit.
    (b) Remove from service disks found cracked, and replace with 
serviceable parts. Inspect replacement disks in accordance with 
paragraph (a) of this AD, if applicable.
    (c) Disks referenced in paragraph (a) of this AD that have been 
inspected in accordance with the procedures outlined in GE CF6-80C2 
All Operators Wire 92-80C-16, dated April 22, 1992, or GE CF6-80C2 
SB No. 72-614, dated July 2, 1992, prior to the effective date of 
this AD, and whose CSN at the time of inspection was 3,000 CSN, or 
more, meet the inspection requirements of paragraph (a) of this AD.
    (d) For the purpose of this AD, an engine shop visit is defined 
as the induction of an engine into a shop for maintenance involving 
the separation of any major flange.
    (e) An alternative method of compliance or adjustment of the 
initial compliance time, that provides an acceptable level of 
safety, may be used if approved by the Manager, Engine Certification 
Office. The request should be forwarded through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, Engine Certification Office.

    Note: Information concerning the existence of approved alternate 
methods of compliance with this airworthiness directive, if any, may 
be obtained from the Engine Certification Office.

    (f) Special flight permits may be issued in accordance with FAR 
21.197 and 21.199 to operate the aircraft to a location where the 
requirements of this AD can be accomplished.
    (g) The modification and inspection shall be done in accordance 
with the following service bulletin: 

------------------------------------------------------------------------
    Document No.      Pages         Revision                Date        
------------------------------------------------------------------------
GE CF6-80C2                                                             
SB No. 72-614.......       1  1...................  September 8, 1992.  
                        2-12  Original............  July 2, 1992.       
                     --------                                           
  Total pages.......      12                                            
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    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, OH 45246. Copies may be inspected at the FAA, New 
England Region, Office of the Assistant Chief Counsel, 12 New 
England Executive Park, Burlington, MA; or at the Office of the 
Federal Register, 800 North Capitol Street NW., suite 700, 
Washington, DC.
    (h) This amendment becomes effective on April 29, 1994.

    Issued in Burlington, Massachusetts, on March 7, 1994.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 94-5939 Filed 3-29-94; 8:45 am]
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