Airworthiness Directives; General Electric Company (GE) CF6-80 Series Turbofan Engines

[Federal Register Volume 72, Number 107 (Tuesday, June 5, 2007)]
[Rules and Regulations]
[Pages 30956-30959]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E7-10588]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-26488; Directorate Identifier 2006-NE-43-AD; 
Amendment 39-15077; AD 2007-11-20]
RIN 2120-AA64


Airworthiness Directives; General Electric Company (GE) CF6-80 
Series Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for GE 
CF6-80 series turbofan engines with fuel shroud retaining rings, part 
number (P/N) J204P0084, installed. This AD requires replacing those 
retaining rings with a more robust design fuel shroud retaining snap 
ring. This AD results from two events of external engine fuel leakage 
and a subsequent under-cowl engine fire. We are issuing this AD to 
prevent an under-cowl engine fire and damage to the airplane during an 
engine high vibration event.

DATES: This AD becomes effective July 10, 2007. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in the regulations as of July 10, 2007.

ADDRESSES: You can get the service information identified in this AD 
from General Electric Company via Lockheed Martin Technology Services, 
10525 Chester Road, Suite C, Cincinnati, Ohio 45215, telephone (513) 
672-8400, fax (513) 672-8422.
    You may examine the AD docket on the Internet at http://dms.dot.gov 
or in Room PL-401 on the plaza level of the Nassif Building, 400 
Seventh Street, SW., Washington, DC.

FOR FURTHER INFORMATION CONTACT: James Lawrence, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; e-mail: 
[email protected]; telephone: (781) 238-7176, fax: (781) 238-7199.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 
with a proposed AD. The proposed AD applies to GE CF6-80 series 
turbofan engines with fuel shroud retaining rings, part number (P/N) 
J204P0084, installed. We published the proposed AD in the Federal 
Register on February 15, 2007 (72 FR 7355). That action proposed to 
require replacing those retaining rings with a more robust design fuel 
shroud retaining snap ring.

Examining the AD Docket

    You may examine the docket that contains the AD, any comments 
received, and any final disposition in person at the Docket Management 
Facility between 9 a.m. and 5 p.m., Monday through Friday, except 
Federal holidays. The Docket Office (telephone (800) 647-5227) is 
located on the plaza level of the Department of Transportation Nassif 
Building at the street address stated in ADDRESSES. Comments will be 
available in the AD docket shortly after the DMS receives them.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments received.

Comment That Table 1 Compliance Schedule Is Somewhat Difficult To 
Follow

    One commenter, GE, states that the Table 1 compliance schedule in 
the proposed AD is somewhat difficult to follow. The commenter states 
that the table needs lines or spaces added, to separate some of the 
items in it, for clarity.
    We agree that the Table 1 compliance schedule in the proposed AD is 
difficult to follow. We have deleted the Table 1 compliance schedule 
from this AD, based on comments received on the proposed AD, and which 
are discussed in the paragraphs that follow.

Request To Reduce the AD Applicability

    GE requests that we reduce the AD applicability to only engines 
with the drainless manifold configuration, since the drained manifold 
configuration is

[[Page 30957]]

not subjected to high internal pressure. If a fuel supply tube leaks 
internally, the shroud contains the fuel, preventing an external leak. 
We agree and reduced the AD applicability in the AD to only engines 
with the drainless manifold configuration.

Request To Clarify Applicability

    GE requests that we clarify the applicability to state that engines 
built at the factory during production assembly with the drainless 
manifold configuration, are also subject to the requirements of the AD. 
We agree and made that clarification in the AD.

SB Compliance Credit for CF6-80C2 Series Engines

    GE suggests that we add a note or statement to the compliance 
section verifying that CF6-80C2 series engine operators that have 
complied with a previous revision of SB No. CF6-80C2 S/B 73-0337, are 
in compliance with the AD. We agree. We added the ``SB Compliance 
Credit for CF6-80C2 Series Engines'' paragraph to the AD.

Request To Revise the Compliance Section

    KLM Royal Dutch Airlines requests that we revise the section of the 
compliance that states ``Comply with this AD as soon as one or more 
fuel shroud retaining rings are removed from the engine'' to, ``Comply 
with this AD during next engine shop visit for any reason.'' The 
commenter states that the AD action should be only at engine-level and 
not on-wing.
    We agree that the AD action should be only at engine-level and not 
on-wing. That part of the proposed compliance section was for engines 
that had not incorporated GE SB No. CF6-80C2 S/B 73-0253 (which 
eliminates the fuel drain system manifold and introduces a new 
drainless fuel manifold). The result is that this AD now applies to 
only the drainless manifold configuration. In addition, we deleted the 
Table 1 compliance schedule because it is no longer needed, clarified 
compliance paragraph (g), and clarified applicability paragraphs (c) 
and (d) in this AD.

Request To Change Nomenclature

    All Nippon Airways requests that we change the proposed AD 
nomenclature for the rings being removed, from ``retaining snap ring'' 
to ``retaining ring''. We agree. We confirmed that GE's SBs refer to 
the removed rings as ``retaining rings'' and to the rings being 
installed as ``snap rings.'' We changed the nomenclature in the AD to 
reflect that which the SBs use.

Reference Table of Fuel Manifold Part Numbers Added

    For reference, we added a Table under paragraph (f) which lists 
fuel manifold production part numbers.

Conclusion

    We have carefully reviewed the available data, including the 
comments received, and determined that air safety and the public 
interest require adopting the AD with the changes described previously. 
We have determined that these changes will neither increase the 
economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

    We estimate that this AD will affect 853 CF6-80 series turbofan 
engines installed on airplanes of U.S. registry. We also estimate that 
it will take about 12.5 work-hours per engine to perform the actions, 
and that the average labor rate is $80 per work-hour. Required parts 
will cost about $72 per engine. Based on these figures, we estimate the 
total cost of the AD to U.S. operators to be $914,416.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect 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.
    For the reasons discussed above, I certify that this AD:
    (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.
    We prepared a summary of the costs to comply with this AD and 
placed it in the AD Docket. You may get a copy of this summary at the 
address listed under ADDRESSES.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the Federal Aviation Administration amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive:

2007-11-20 General Electric Company: Amendment 39-15077. Docket No. 
FAA-2006-26488; Directorate Identifier 2006-NE-43-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective July 10, 
2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to the following General Electric Company 
(GE) CF6-80C2 series turbofan engines that have incorporated GE 
Service Bulletin (SB) No. CF6-80C2 S/B 73-0253, or were built with 
the drainless manifold configuration at the factory during 
production assembly, and, have one or more fuel shroud retaining 
rings, part number (P/N) J204P0084, installed:

CF6-80C2A1,
CF6-80C2A2,
CF6-80C2A3,
CF6-80C2A5,
CF6-80C2A8,
CF6-80C2A5F,
CF6-80C2B1,
CF6-80C2B2,
CF6-80C2B4,
CF6-80C2B6,
CF6-80C2B1F,
CF6-80C2B2F,
CF6-80C2B4F,
CF6-80C2B5F,

[[Page 30958]]

CF6-80C2B6F,
CF6-80C2B6FA,
CF6-80C2B7F,
CF6-80C2B8F,
CF6-80C2D1F,
CF6-80C2L1F.

    (d) This AD also applies to GE CF6-80E1A1, CF6-80E1A2, CF6-
80E1A3, CF6-80E1A4, and CF6-80E1A4B turbofan engines that have 
incorporated GE SB No. CF6-80E1 S/B 73-0026, or were built with the 
drainless manifold configuration at the factory during production 
assembly, and, have one or more fuel shroud retaining rings, P/N 
J204P0084, installed.
    (e) These engines are installed on, but not limited to, Airbus 
A300, A310, A330, Boeing 747, 767, and McDonnell Douglas MD11 
airplanes.
    (f) For reference, the following Table 1 lists fuel manifold 
production P/Ns.

          Table 1.--Reference of Fuel Manifold Production P/Ns
------------------------------------------------------------------------
 
------------------------------------------------------------------------
                         CF6-80C2 Series Engines
------------------------------------------------------------------------
   Drained Fuel Manifold P/N (left      Drainless Fuel Manifold P/N
                side)                 (left side)
------------------------------------------------------------------------
1303M31G04
1303M31G06
1303M31G07
1303M31G08
1303M31G10..........................  1303M31G12.
------------------------------------------------------------------------
 Drained Fuel Manifold (right side)     Drainless Fuel Manifold P/N
                                      (right side)
------------------------------------------------------------------------
1303M32G04
1303M32G06
1303M32G07
1303M32G08
1303M32G10..........................  1303M32G12.
------------------------------------------------------------------------
                        CF6-80 E1 Series Engines
------------------------------------------------------------------------
   Drained Fuel Manifold P/N (left      Drainless Fuel Manifold P/N
                side)                 (left side)
------------------------------------------------------------------------
1700M34G01..........................  1303M31G12.
------------------------------------------------------------------------
  Drained Fuel Manifold P/N (right      Drainless Fuel Manifold P/N
                side)                 (right side)
------------------------------------------------------------------------
1700M35G02..........................  1303M32G12.
------------------------------------------------------------------------

Unsafe Condition

    (g) This AD results from two events of external engine fuel 
leakage and a subsequent under-cowl engine fire. We are issuing this 
AD to prevent an under-cowl engine fire and damage to the airplane 
during an engine high vibration event.

Compliance

    (h) You are responsible for having the actions required by this 
AD performed at the next engine shop visit for any reason after the 
effective date of this AD, unless the actions have already been 
done.

Replacement of Fuel Shroud Retaining Snap Rings

    (i) Replace any fuel shroud retaining rings, P/N J204P0084, with 
a fuel shroud retaining snap ring, P/N 2186M12P01. Each engine has a 
total of 30 rings installed.
    (j) For CF6-80C2 series engines, use paragraphs 3.A. through 
3.C.(1)(b)2, of GE SB No. CF6-80C2 S/B 73-0337, Revision 3, dated 
February 5, 2007, to do the replacements.
    (k) For CF6-80E1 series engines, use paragraphs 3.A. through 
3.C.(1)(b)2, of GE SB No. CF6-80E1 S/B 73-0075, Revision 1, dated 
November 27, 2006, to do the replacements.

SB Compliance Credit for CF6-80C2 Series Engines

    (l) This AD requires no further action if the fuel shroud 
retaining snap rings were installed in the CF6-80C2 series engines 
before the effective date of this AD using GE SB No. CF6-80C2 S/B 
73-0337, Revision 2, dated January 11, 2007, Revision 1, dated April 
19, 2005, or the Original, dated November 30, 2004.

Alternative Methods of Compliance

    (m) The Manager, Engine Certification Office, has the authority 
to approve alternative methods of compliance for this AD if 
requested using the procedures found in 14 CFR 39.19.

Related Information

    (n) Contact James Lawrence, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
[email protected]; telephone (781) 238-7176; fax (781) 238-
7199, for more information about this AD.

Material Incorporated by Reference

    (o) You must use the General Electric Company service 
information specified in Table 2 of this AD to perform the 
replacements required by this AD. The Director of the Federal 
Register approved the incorporation by reference of the documents 
listed in Table 2 of this AD in accordance with 5 U.S.C. 552(a) and 
1 CFR part 51. Contact General Electric Company via Lockheed Martin 
Technology Services, 10525 Chester Road, Suite C, Cincinnati, Ohio 
45215, telephone (513) 672-8400, fax (513) 672-8422, for a copy of 
this service information. You may review copies at the FAA, New 
England Region, Office of the Regional Counsel, 12 New England 
Executive Park, Burlington, MA; or at the National Archives and 
Records Administration (NARA). For information on the availability 
of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

                                      Table 2.--Incorporation by Reference
----------------------------------------------------------------------------------------------------------------
        Service Bulletin No.                    Page              Revision                   Date
----------------------------------------------------------------------------------------------------------------
CF6-80C2 S/B 73-0337................  All.....................            3  February 5, 2007.
    Total Pages: 13
CF6-80E1 S/B 73-0075................  All.....................            1  November 27, 2006.
    Total Pages: 13
----------------------------------------------------------------------------------------------------------------



[[Page 30959]]

    Issued in Burlington, Massachusetts, on May 24, 2007.
Francis A. Favara,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
 [FR Doc. E7-10588 Filed 6-4-07; 8:45 am]
BILLING CODE 4910-13-P

The complete text was extracted from the official GovInfo HTML edition for this publication. Acquired 2026-10-09T03:38:10.572666+00:00. Text extraction preserves the recorded source wording; it does not determine current requirements.

Open the captured official edition

Source SHA-256

7473f0e2045f48ed6cd0adc20d656a6906544d09ba56a0216c6a14d41f7fb3c7

Text SHA-256

9d05909b0f8e67eae69f44b05d47b876cb2b835e565e4294080bd977944fa1ff