[Federal Register Volume 64, Number 3 (Wednesday, January 6, 1999)]
[Rules and Regulations]
[Pages 749-751]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-10]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-ANE-75-AD; Amendment 39-10968; AD 99-01-01]
RIN 2120-AA64
Airworthiness Directives; General Electric Company CF6-80C2
Series Turbofan Engines
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment adopts a new airworthiness directive (AD) that
is applicable to General Electric Company CF6-80C2 series turbofan
engines. This action requires a one-time visual inspection to ensure
the correct accessory gearbox (AGB) idler adapter inserts are
installed, and, if necessary, removal of AGB idler adapters with the
improper inserts. This amendment is prompted by a report of a failure
of a fuel tube flange connection due to improper AGB idler adapter
inserts that resulted in a high pressure fuel leak and engine fire. The
actions specified in this AD are intended to identify and remove AGB
idler adapters with improper inserts, which can result in an engine
fire and damage to the aircraft.
DATES: Effective January 21, 1999.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of January 21, 1999.
Comments for inclusion in the Rules Docket must be received on or
before March 8, 1999.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), New England Region, Office of the Regional
Counsel, Attention: Rules Docket No. 98-ANE-75-AD, 12 New England
Executive Park, Burlington, MA 01803-5299. Comments may also be sent
via the Internet using the following address: ``engineprop@faa.gov''. Comments sent via the Internet must contain the
docket number in the subject line.
The service information referenced in this AD may be obtained from
General Electric Aircraft Engines, c/o Commercial Technical
Publications, 1 Neumann Way, Rm. 230, Cincinnati, OH 45215-1988;
telephone (513) 552-2005, fax (513) 552-2816. This information may be
examined at the FAA, New England Region, Office of the Regional
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: Ian Dargin, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803-5299; telephone (781) 238-
7178, fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: The Federal Aviation Administration (FAA)
has received a report of an engine fire on an Airbus A300 aircraft with
General Electric Company (GE) Model CF6-80C2A5 turbofan engines
installed. The investigation into the cause of the fire identified a
high pressure fuel leak at the fuel cross-over tube to accessory
gearbox (AGB) idler adapter flange interface. The fuel leak occurred
due to shearing of the idler adapter threads by the threaded inserts,
allowing the inserts to pull out. This was attributed to incorrect
Service Bulletin (SB) instructions which created a situation where a
repair station installed improper inserts into the AGB idler adapter
housing at a previous maintenance shop visit.
The maintenance on the idler adapter was performed using GE SB 72-
743, dated August 25, 1994, that provided instructions for AGB idler
adapter rework on P/N 9395M78G06 adapters to improve the reliability
and correct a fuel leak problem that had been identified on engines in
revenue service. Idler adapters that were reworked were required to be
remarked to P/N 9395M78G08. The instructions in SB 72-743 were
incorrect and could have resulted in repair stations installing
improper inserts into the idler adapter. GE issued supplemental
instructions by way of Repair Document 032-273-S1, dated April 8, 1998,
which addresses the problem in SB 72-743 and has proven to be an
acceptable repair procedure. Furthermore, GE has published SB 72-743,
Revision 1, dated November 2, 1998, to cancel the rework of any AGB
idler adapter in accordance with the original issue of the SB.
Presently, the total number of GE CF6-80C2 engines that have
incorporated SB 72-743 and that could have improper inserts installed
is not known. Therefore, work performed using SB 72-743 by any repair
facility is suspect at this time. This condition, if not corrected, can
result in shearing of the idler adapter threads and pullout of the
threaded inserts from the AGB idler adapter which could result in a
high pressure fuel leak leading to a potential engine fire and damage
to the aircraft.
[[Page 750]]
The FAA has reviewed and approved the technical contents of GE CF6-
80C2 Alert Service Bulletins (ASB) 73-A283, Revision 2, dated November
18, 1998, Revision 1, dated October 30, 1998, and Original, dated
September 18, 1998. These ASBs describe procedures for a one-time
visual inspection on AGB idler adapters, P/N 9395M78G08, that had been
reworked from a P/N 9395M78G06 configuration, to ensure the correct AGB
idler adapter threaded inserts are installed, and if necessary, removal
of AGB idler adapters with the improper inserts.
Since an unsafe condition has been identified that is likely to
exist or develop on other engines of the same type design, this AD is
being issued to prevent an engine fire and damage to the aircraft. This
AD requires a one-time visual inspection to ensure the correct AGB
idler adapter threaded inserts are installed, and if necessary, removal
of the AGB idler adapters with the improper inserts. The actions are
required to be accomplished in accordance with the ASB described
previously.
Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity for prior
public comment hereon are impracticable, and that good cause exists for
making this amendment effective in less than 30 days.
Comments Invited
Although this action is in the form of a final rule that involves
requirements affecting flight safety and, thus, was not preceded by
notice and an opportunity for public comment, comments are invited on
this rule. Interested persons are invited to comment on this rule by
submitting such written data, views, or arguments as they may desire.
Communications should identify the Rules Docket number and be submitted
in triplicate to the address specified under the caption ADDRESSES. All
communications received on or before the closing date for comments will
be considered, and this rule may be amended in light of the comments
received. Factual information that supports the commenter's ideas and
suggestions is extremely helpful in evaluating the effectiveness of the
AD action and determining whether additional rulemaking action would be
needed.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the rule. All comments submitted will be
available, both before and after the closing date for comments, in the
Rules Docket for examination by interested persons. A report that
summarizes each FAA-public contact concerned with the substance of this
AD will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this notice must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 98-ANE-75-AD.'' The postcard will be date stamped and
returned to the commenter.
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.
The FAA has determined that this regulation is an emergency
regulation that must be issued immediately to correct an unsafe
condition in aircraft, and is not a ``significant regulatory action''
under Executive Order 12866. It has been determined further that this
action involves an emergency regulation under DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979). If it is determined
that this emergency regulation otherwise would be significant under DOT
Regulatory Policies and Procedures, a final regulatory evaluation will
be prepared and placed in the Rules Docket. A copy of it, if filed, 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. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
99-01-01 General Electric Company: Amendment 39-10968 Docket 98-
ANE-75-AD.
Applicability: General Electric Company (GE) CF6-80C2 series
turbofan engines, with Accessory Gearbox (AGB) idler adapters, Part
Number (P/N) 9395M78G08 that had been reworked from a P/N 9395M78G06
configuration using GE CF6-80C2 Service Bulletin (SB) 72-743, dated
August 25, 1994, excluding those parts that were repaired by GE
Repair Document 032-273-S1, dated April 8, 1998. These engines are
installed on but not limited to Airbus A300 and A310 series, and
Boeing 747, 767, and MD-11 aircraft.
Note 1: Methods of determining if a P/N 9395M78G08 AGB idler
adapter had been reworked from a P/N 9395M78G06 configuration
include a record search or a visual inspection of the AGB idler
adapter part number in accordance with GE CF6-80C2 Alert Service
Bulletin (ASB) 73-A283, Revision 2, dated November 18, 1998,
Revision 1, dated October 30, 1998, or Original, dated September 18,
1998.
Note 2: This airworthiness directive (AD) applies to each engine
identified in the preceding applicability provision, regardless of
whether it has been modified, altered, or repaired in the area
subject to the requirements of this AD. For engines that have been
modified, altered, or repaired so that the performance of the
requirements of this AD is affected, the owner/operator must request
approval for an alternative method of compliance in accordance with
paragraph (c) of this AD. The request should include an assessment
of the effect of the modification, alteration, or repair on the
unsafe condition addressed by this AD; and, if the unsafe condition
has not been eliminated, the request should include specific
proposed actions to address it.
Compliance: Required as indicated, unless accomplished
previously.
To prevent an engine fuel leak, which can result in an engine
fire and damage to the aircraft, accomplish the following:
(a) Within 10 days after the effective date of this AD:
(1) Perform a visual inspection of AGB idler adapter inserts in
accordance with paragraph (2)(B) of the Accomplishment Instructions
of GE CF6-80C2 ASB 73-A283, Revision 2, dated November 18, 1998,
Revision 1, dated October 30, 1998, or Original, dated September 18,
1998.
(2) Remove the AGB adapter from service and replace with a
serviceable part those adapters with one or more inserts that are
flush with or extend past the back face of the casting.
(b) For the purpose of this AD, a serviceable part is defined as
any AGB idler adapter, except for P/Ns 9395M78G08 that had been
reworked from a P/N 9395M78G06 configuration having one or more
inserts flush with or extended past the back face of the casting, as
described in GE CF6-80-C2 ASB 73-A283, Revision 2, dated November
[[Page 751]]
18, 1998, Revision 1, dated October 30, 1998, or Original, dated
September 18, 1998.
(c) 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.
Operators shall submit their requests through an appropriate FAA
Principal Maintenance Inspector, who may add comments and then send
it to the Manager, Engine Certification Office.
Note 3: Information concerning the existence of approved
alternative methods of compliance with this airworthiness directive,
if any, may be obtained from the Engine Certification Office.
(d) 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.
(e) The actions required by this AD shall be done in accordance
with the following GE CF6-80C2 ASBs:
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Document No. Pages Revision Date
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73-A283........................ 1.................... 2.................... November 18, 1998.
2-4.................. 1.................... October 30, 1998.
5.................... Original............. September 18, 1998.
6-27................. 1.................... October 30, 1998.
Total pages: 27.
73-A283........................ 1-4.................. 1.................... October 30, 1998.
5.................... Original............. September 18, 1998.
6-27................. 1.................... October 30, 1998.
Total pages: 27
73-A283........................ 1-9.................. Original............. September 18, 1998.
Total pages: 9.............
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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,
c/o Commercial Technical Publications, 1 Neumann Way, Rm. 230,
Cincinnati, OH 45215-1988; telephone (513) 552-2005, fax (513) 552-
2816. Copies may be inspected at the FAA, New England Region, Office
of the Regional 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.
(f) This amendment becomes effective on January 21, 1999.
Issued in Burlington, Massachusetts, on December 23, 1998.
David A. Downey,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 99-10 Filed 1-5-99; 8:45 am]
BILLING CODE 4910-13-U
