[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:
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Document No. Pages Revision Date
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GE CF6-80C2
SB No. 72-614....... 1 1................... September 8, 1992.
2-12 Original............ July 2, 1992.
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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]
BILLING CODE 4910-13-P
