[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: ``9-ad-
[email protected]''. 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
----------------------------------------------------------------------------------------------------------------
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]
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