Airworthiness Directives; General Electric (GE) CF6-80E1 Series Turbofan Engines

[Federal Register Volume 72, Number 156 (Tuesday, August 14, 2007)]
[Rules and Regulations]
[Pages 45308-45310]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E7-15701]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-21238; Directorate Identifier 2005-NE-12-AD; 
Amendment 39-15159; AD 2007-17-01]
RIN 2120-AA64


Airworthiness Directives; General Electric (GE) CF6-80E1 Series 
Turbofan Engines

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

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD) for General Electric (GE) CF6-80E1 series turbofan engines. That 
AD currently requires removing electronic control unit (ECU) software 
version E.1.M. or earlier installed software, and installing improved 
software for the ECU. This AD requires removing software version E.1.N 
or earlier from the engine ECU. Engines with the new version software 
will have increased margin to flameout. This AD results from reports of 
engine flameout events during flight, including reports of events where 
all engines simultaneously experienced a flameout or other adverse 
operation. Although the root cause investigation is not yet complete, 
we believe that exposure to ice crystals during flight is associated 
with these flameout events. We are issuing this AD to minimize the 
potential of an all-engine flameout event caused by ice accretion and 
shedding during flight.

[[Page 45309]]


DATES: Effective August 29, 2007.
    We must receive any comments on this AD by October 15, 2007.

ADDRESSES: Use one of the following addresses to comment on this AD.
    <bullet> DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
    <bullet> Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
    <bullet> Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
    <bullet> Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    <bullet> Fax: (202) 493-2251.
    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 the service 
information identified in this AD.

FOR FURTHER INFORMATION CONTACT: John Golinski, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; e-mail: 
[email protected]; telephone: (781) 238-7135, fax: (781) 238-7199.

SUPPLEMENTARY INFORMATION: The FAA amends 14 CFR part 39 by superseding 
AD 2005-10-16, Amendment 39-14093 (70 FR 28806, May 19, 2005). That AD 
requires improved software version E.1.N to be installed into the ECU. 
That AD was the result of an uncommanded engine acceleration event 
caused by a failure of the ECU digital interface unit. That condition, 
if not corrected, could result in an undetected failure of the ECU 
digital interface unit, leading to uncommanded acceleration to the 
overspeed limit without response to throttle commands. The airplane 
could then experience asymmetric thrust.

Actions Since AD 2005-10-16 Was Issued

    Since AD 2005-10-16 was issued, GE CF6-80E1 and CF6-80C2 series 
turbofan engines continue to experience flameout events that are due to 
ice accretion and shedding into the engine during flight. Although the 
investigation is not yet complete, we believe that the ice accretion is 
caused by exposure to ice crystals during flight. Industry reports 35 
airplane flameout events, including reports of multi-engine events 
where all engines on the airplane simultaneously experienced a 
flameout. Some of these events had high pressure compressor blade 
damage that may have been caused by impact with shedding ice. In all 
events, the engines restarted and continued to operate normally for the 
remainder of the flight.
    This AD addresses only the CF6-80E1 series turbofan engines, 
installed on Airbus Industrie A330 series airplanes. We believe the 
CF6-80E1 series turbofan engines are susceptible to flameouts caused by 
ice accretion and shedding into the engine during flight. Similar AD 
actions for CF6-80C2 series engines may be forthcoming.
    We view an all-engine flameout event as an unsafe condition 
particularly for low-altitude events, or other factors that might 
result in the inability to restart the engines and regain control of 
the airplane. Since some aspects of this problem are not completely 
understood, this proposed AD is considered an interim action due to 
GE's on-going investigation. Future AD action might become necessary 
based on the results of the investigation and field experience. This 
condition of insufficient margin to engine flameout due to ice 
accretion and shedding during flight, if not addressed, could result in 
an all-engine flameout event during flight.

Relevant Service Information

    We have reviewed and approved the technical contents of GE Service 
Bulletin (SB) No. CF6-80E1 S/B 73-0091, Revision 1, dated June 26, 
2007. That SB describes procedures for removing certain software 
versions from the ECU, and installing a software version that is FAA-
approved. The new FAA-approved software version described in the SB 
modifies the variable bleed valve schedule, which will provide an 
increased margin to flameout. This increased margin is expected to 
reduce the rate of flameout occurrences due to ice accretion and 
shedding during flight. The new FAA-approved software version 
incorporates the software improvements required by AD 2005-10-16, which 
prevent failure of the ECU digital interface unit.

FAA's Determination and Requirements of This AD

    Although no airplanes that are registered in the United States use 
these CF6-80E1 series turbofan engines, the possibility exists that the 
engines could be used on airplanes that are registered in the United 
States in the future. The unsafe condition described previously is 
likely to exist or develop on other CF6-80E1 series turbofan engines of 
the same type design. We are issuing this AD to minimize the potential 
of an all-engine flameout event caused by ice accretion and shedding 
during flight. This AD requires removing certain software versions from 
the engine ECU.

FAA's Determination of the Effective Date

    Since there are currently no domestic operators of this engine 
model, notice and opportunity for public comment before issuing this AD 
are unnecessary. A situation exists that allows the immediate adoption 
of this regulation.

Interim Action

    These actions are interim actions due to the on-going 
investigation. We may take further rulemaking actions in the future, 
based on the results of the investigation and field experience.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment; however, we invite you to send us any written relevant data, 
views, or arguments regarding this AD. Send your comments to an address 
listed under ADDRESSES. Include ``AD Docket No. FAA-2005-21238; 
Directorate Identifier 2005-NE-12-AD'' in the subject line of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify it.
    We will post all comments we receive, without change, to http://dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this AD. Using the search function of the DMS Web 
site, anyone can find and read the comments in any of our dockets, 
including the name of the individual who sent the comment (or signed 
the comment on behalf of an association, business, labor union, etc.). 
You may review the DOT's complete Privacy Act Statement in the Federal 
Register published on April 11, 2000 (65 FR 19477-78) or you may visit 
http://dms.dot.gov.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://dms.dot.gov; or in person at the Docket Operations office between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD 
docket contains this AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Operations office (telephone (800) 647-5527) is

[[Page 45310]]

provided in the ADDRESSES section. Comments will be available in the AD 
docket shortly after receipt.

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 the 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, Safety.

Adoption of the Amendment

0
Under 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

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 removing Amendment 39-14093 (70 FR 
28806, May 19, 2005), and by adding a new airworthiness directive, 
Amendment 39-15159, to read as follows:

2007-17-01 General Electric Company: Amendment 39-15159. Docket No. 
FAA-2005-21238; Directorate Identifier 2005-NE-12-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective August 
29, 2007.

Affected ADs

    (b) This AD supersedes AD 2005-10-16.

Applicability

    (c) This AD applies to General Electric Company (GE) CF6-80E1A1, 
CF6-80E1A2, CF6-80E1A3, CF6-80E1A4, and CF6-80E1A4/B turbofan 
engines, installed on Airbus Industrie A330 series airplanes.

Unsafe Condition

    (d) This AD results from reports of engine flameout events 
during flight, including reports of events where all engines 
simultaneously experienced a flameout or other adverse operation. We 
are issuing this AD to minimize the potential of an all-engine 
flameout event caused by ice accretion and shedding during flight. 
Exposure to ice crystals during flight is believed to be associated 
with these flameout events.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified unless the 
actions have already been done.

Interim Action

    (f) These actions are interim actions due to the on-going 
investigation, and we may take further rulemaking actions in the 
future based on the results of the investigation and field 
experience.

Engine Electronic Control Unit (ECU) Software Removal

    (g) Before January 31, 2008, remove the following software 
versions from the ECUs:

               Table 1.--Removal of ECU Software Versions
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         Software version                Installed in ECU part No.
------------------------------------------------------------------------
(1) E.1.D........................  1799M99P01
(2) E.1.F........................  1799M99P03
(3) E.1.G........................  1799M99P04
(4) E.1.H........................  1799M99P05
(5) E.1.I........................  1799M99P06, 1799M99P07, 1851M74P01,
                                    1851M80P01
(6) E.1.J........................  1799M99P08, 1799M99P09, 1851M74P02,
                                    1851M80P02
(7) E.1.K........................  1799M99P10, 1851M74P03, 1851M80P03,
                                    1960M84P01
(8) E.1.L........................  1799M99P11, 1851M74P04, 1851M80P04,
                                    1960M84P02
(9) E.1.M........................  1799M99P12, 1851M74P05, 1851M80P05,
                                    1960M84P03
(10) E.1.N.......................  1799M99P13, 1851M74P06, 1851M80P06,
                                    1960M84P04, 2043M29P01, 2043M29P02
------------------------------------------------------------------------

Previous Software Versions of ECU Software

    (h) Until January 31, 2008, once an ECU containing a software 
version not listed in Table 1 of this AD is installed on an engine, 
that ECU can be replaced with an ECU containing a previous version 
of software listed in Table 1.
    (i) Once the software version listed in Table 1 of this AD has 
been removed and new FAA-approved software version is installed in 
an ECU, reverting to those older software versions in that ECU is 
prohibited.
    (j) After January 31, 2008, use of an ECU with a software 
version listed in Table 1 of this AD is prohibited.

Alternative Methods of Compliance

    (k) 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.

Special Flight Permits

    (l) Special flight permits are not authorized.

Related Information

    (m) Information on removing ECU software and installing new 
software, which provides increased margin to flameout, can be found 
in GE Service Bulletin No. CF6-80E1 S/B 73-0091, Revision 1, dated 
June 26, 2007.
    (n) Contact John Golinski, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
[email protected]; telephone: (781) 238-7135, fax: (781) 238-
7199, for more information about this AD.

    Issued in Burlington, Massachusetts, on August 6, 2007.
Francis A. Favara,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
 [FR Doc. E7-15701 Filed 8-13-07; 8:45 am]
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