[Federal Register Volume 59, Number 205 (Tuesday, October 25, 1994)]
[Unknown Section]
[Page 0]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 94-25192]
[[Page Unknown]]
[Federal Register: October 25, 1994]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 94-ANE-02; Amendment 39-9034; AD 94-20-06]
Airworthiness Directives; General Electric Company CF6-80C2
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 a repetitive oil quantity check after engine
start-up but prior to taxi, and installation of a flame arrestor plug
support (FAPS) in the aft end of the center vent tube as a terminating
action to the repetitive oil quantity checks. This amendment is
prompted by three reports of uncontained engine failure due to
separation of the fan mid shaft. The actions specified by this AD are
intended to prevent an uncontained engine failure and inflight engine
shutdown due to fuel contamination of the oil system.
DATES: Effective December 27, 1994.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of December 27, 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: Glorianne Messemer, Aerospace
Engineer, Engine Certification Office, FAA, Engine and Propeller
Directorate, 12 New England Executive Park, Burlington, MA 01803-5299;
telephone (617) 238-7132, fax (617) 238-7199.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) 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
May 2, 1994 (59 FR 22565). That action proposed to require a repetitive
oil quantity check after engine start-up but prior to taxi, and
installation of a flame arrestor plug support (FAPS) in the aft end of
the center vent tube (CVT) as a terminating action to the repetitive
oil quantity checks. The installation would be accomplished in
accordance with GE CF6-80C2 Service Bulletin (SB) No. 72-648, Revision
1, dated January 11, 1993, and GE CF6-80C2 SB No. 72-095, Revision 2,
dated January 11, 1993.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received.
One commenter supports the rule as proposed.
One commenter (the engine manufacturer) states that in the Summary
and Discussion sections the word ``and'' should be replaced with
``but'' to read ``* * * require a repetitive oil quantity check after
engine start up but prior to taxi.'' The commenter adds that the word
``and'' may cause some confusion and lead an operator to believe there
may be two checks. The FAA concurs and has revised this final rule
accordingly.
The commenter further states that in the Discussion section and
paragraphs (a) and (b) of the compliance section the phrase ``* * * if
the oil quantity indicates 5 gallons (20 quarts) or more'' should be
changed to ``* * * if the oil quantity indicates 5.5 gallons or more on
Boeing 747-200/300 aircraft or 22 units or more on all other
applications.'' The commenter notes that this change would avoid
unnecessary maintenance action. Operator feedback shows that there were
too many aircraft making unnecessary trips back to the gate. The
additional margin of 0.5 gallons and 2 units was established because
there was no contamination when the previous limit of 5 gallons (20
quarts) was exceeded. Both quarts and liters are used by different
operators, and in this situation the difference between quarts and
liters is negligible. The FAA concurs and has revised this final rule
accordingly.
The commenter further states that in paragraph (d) of the
compliance section the clause ``* * * replace the fan mid shaft
assembly, the mid fan duct assembly'' should be changed to ``* * *
replace the small diameter mid fan duct assembly (CVT).'' The commenter
notes that GE CF6-80C2 SB No. 72-095, Revision 2, dated January 11,
1993, introduces into production a new fan mid shaft assembly, mid fan
duct assembly (CVT), No. 6 bearing plug, preformed packing, and new
retaining ring. That SB also provides accomplishment instructions to
remove the small diameter CVT and replace it with a larger diameter CVT
that will accommodate the flame arrestor. The SB does not require
replacement of the fan mid shaft. The FAA concurs and has revised this
final rule accordingly.
The commenter further states that 14 center vent tube extension
hardware kits have been provided to the fleet. Installation of the CVT
extension in accordance with GE CF6-80C2 Service Evaluation Bulletin
(SEB) No. 72-628, dated July 15, 1993, should be an acceptable means of
compliance for this AD. The FAA concurs and has revised this final rule
accordingly by adding a new paragraph (f).
One commenter states that the oil quantity to initiate inspection
action should be 22 quarts instead of 20. The commenter notes that
operating experience on Boeing aircraft led to a revision in the Boeing
Operations Bulletin to use the 22 quart figure. The FAA concurs in
part. This final rule has been revised to refer to 22 units rather than
quarts, as described in a previous response.
The economic analysis in the proposed rule included all 1,570
engines in the fleet. The manufacturer has advised the FAA that this
number is overly conservative and that there are only approximately 300
engines installed on aircraft of U.S. registry. Out of the 300 engines,
an estimated 96% have accomplished the requirements of this AD. The
economic analysis of this final rule has been revised accordingly.
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 changes described
previously. The FAA has determined that these changes will neither
increase the economic burden on any operator nor increase the scope of
the AD.
The FAA estimates that 300 engines installed on aircraft of U.S.
registry will be affected by this AD, that it will take approximately 8
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 $2,316 per engine. Out of the 300 engines, the
manufacturer has advised the FAA that 96% of the fleet have
accomplished the requirements of this AD. Based on these figures, the
total cost impact of the AD on U.S. operators is estimated to be
$33,072.
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 part 39 of
the Federal Aviation Regulations (14 CFR part 39) 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:
94-20-06 General Electric Company: Amendment 39-9034. Docket 94-ANE-
02.
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 engine failure and inflight engine
shutdown due to fuel contamination of the oil system, accomplish the
following:
(a) Before each flight, perform an oil quantity inspection for
fuel contamination at least 30 seconds after the engine reaches
stabilized idle but prior to taxi. If the oil quantity indicates 5.5
gallons or more on Boeing 747-200/300 aircraft or 22 units or more
on all other applications, maintenance investigation is required
prior to takeoff.
(b) If the oil quantity indicates 5.5 gallons or more on Boeing
747-200/300 aircraft or 22 units or more on all other applications,
flush and troubleshoot the oil system for fuel contamination prior
to further flight.
(c) For engines with No. 6 bearing plug, Part Number (P/N)
1375M78G01, replace the No. 6 bearing plug with center vent tube
(CVT) flame arrestor plug support (FAPS) in accordance with GE CF6-
80C2 Service Bulletin (SB) No. 72-648, Revision 1, dated January 11,
1993, prior to January 23, 1995.
(d) For engines with No. 6 bearing plug, P/N 9362M36G01, replace
the small diameter mid fan duct assembly CVT and the retaining ring,
in accordance with GE CF6-80C2 SB No. 72-095, Revision 2, dated
January 11, 1993, and replace the No. 6 bearing plug with CVT FAPS
in accordance with GE CF6-80C2 SB No. 72-648, Revision 1, dated
January 11, 1993, prior to January 23, 1995.
(e) Installation of the CVT FAPS in accordance with paragraphs
(c) or (d) of this AD, constitutes terminating action for paragraphs
(a) and (b) of this AD.
(f) Installation of the center vent tube extension in accordance
with GE CF6-80C2 Service Evaluation Bulletin (SEB) No. 72-628, dated
July 15, 1993, constitutes an acceptable means of compliance with
this AD.
(g) The oil quantity inspection required by paragraph (a) of
this AD may be performed by the pilot. The checks must be recorded
in accordance with Federal Aviation Regulation (FAR) Section 43.9,
and records maintained by the owner/operator as required by FAR
Section 121.380(a)(2)(v), or 91.417(a)(2)(v), as applicable.
(h) An alternative method of compliance or adjustment of the
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
alternative methods of compliance with this airworthiness directive,
if any, may be obtained from the Engine Certification Office.
(i) Special flight permits may be issued in accordance with
sections 21.197 and 21.199 of the Federal Aviation Regulations (14
CFR 21.197 and 21.199) to operate the aircraft to a location where
the requirements of this AD can be accomplished.
(j) The replacement of the CVT FAPS shall be done in accordance
with the following service bulletins:
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Document No. Pages Revision Date
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GE CF6-80C2, SB No. 72- 1-15 2 January 11, 1993.
095.
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Total pages......... 15
=========
GE CF6-80C2, SB No. 72- 1-16 1 January 11, 1993.
648.
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Total pages......... 16
=========
GE CF6-80C2, SEB No. 72- 1-13 Original July 15, 1993.
628.
---------
Total pages......... 13
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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.
(k) This amendment becomes effective on December 27, 1994.
Issued in Burlington, Massachusetts, on September 23, 1994.
Mark C. Fulmer,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 94-25192 Filed 10-24-94; 8:45 am]
BILLING CODE 4910-13-P
