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

[Federal Register Volume 70, Number 96 (Thursday, May 19, 2005)]
[Rules and Regulations]
[Pages 28806-28808]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-9887]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-21238; Directorate Identifier 2005-NE-12-AD; 
Amendment 39-14093; AD 2005-10-16]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
General Electric (GE) CF6-80E1 series turbofan engines that have an 
electronic control unit (ECU) with software version E.1.M. or earlier 
installed. This AD requires installing improved software for the ECU. 
This AD results from an uncommanded engine acceleration event caused by 
a failure of the ECU digital interface unit (DIU). We are issuing this 
AD to prevent an undetected failure of the ECU DIU, which could result 
in uncommanded acceleration to the overspeed limit without response to 
throttle commands. The airplane could then experience asymmetric 
thrust.

DATES: This AD becomes effective June 3, 2005. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in the regulations as of June 3, 2005.
    We must receive any comments on this AD by July 18, 2005.

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: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590-001.
    <bullet> Fax: (202) 493-2251.
    <bullet> Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    Contact General Electric Company via Lockheed Martin Technology 
Services, Lockheed Martin Technical Services,

[[Page 28807]]

Distribution Center, 1330 Kemper Meadow Drive, Suite 110-C, Cincinnati, 
Ohio 45240, telephone (513) 672-8400; fax (513) 672-8422, or E-mail: 
[email protected] for the service information identified in 
this AD; or
    Sign on to the GEAE Customer Web Center (CWC): https://customer.geae.com.

FOR FURTHER INFORMATION CONTACT: Karen Curtis, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; telephone (781) 238-
7192; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: In June 2003, a CF6-80E1 engine experienced 
an uncommanded acceleration and did not respond to throttle commands 
during cruise. The pilot shut down the engine by switching off the 
master lever. GE investigated the uncommanded acceleration and 
confirmed that failure of the ECU DIU caused the event. This failure 
corrupted all the digital interfaces with the airplane, ECU pressure 
subsystem, and opposite ECU channel. The ECU used a default ambient 
pressure value, which scheduled fuel flow to a higher than intended 
value. In addition, the DIU failure corrupted the channel-health and 
channel-activity data communication between channels and allowed the 
failed channel to remain active while the healthy channel became 
active. The existing ECU software logic did not detect and record the 
DIU fault and did not ensure control of the engine by the healthy 
channel. Failure of the DIU, if not detected, could result in an 
uncommanded engine acceleration to the overspeed limit, without 
response to throttle commands. The airplane may then experience 
asymmetric thrust.

Relevant Service Information

    We have reviewed and approved the technical contents of GE Aircraft 
Engines CF6-80E1 Service Bulletin (SB) 73-0070, dated June 22, 2004, 
and SB 73-0070, Revision 01, dated March 21, 2005, that describe 
procedures for uploading new software E.1.N. to the ECU.

FAA's Determination and Requirements of This AD

    Although no airplanes that are registered in the United States use 
these engines, the possibility exists that these 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 GE CF6-80E series turbofan engines of the same type design 
that have an ECU with software version E.1.M or earlier installed. We 
are issuing this AD to prevent undetected failure of the ECU DIU. This 
AD requires installing improved ECU software version E.1.N at the next 
ECU exposure. You must use the service information described previously 
to perform the actions required by this AD.

FAA's Determination of the Effective Date

    Since there are currently no domestic operators of these GE CF6-
80E1 series turbofan engines, notice and opportunity for public comment 
before issuing this AD are unnecessary. A situation exists that allows 
the immediate adoption of this regulation.

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. 2005-10-16, 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 docket that contains the AD, any comments 
received, and any final disposition in person at the DMS Docket Offices 
between 9:00 a.m. and 5:00 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.

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 the regulation:
    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, Incorporation by 
reference, 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:

[[Page 28808]]

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:

2005-10-16 General Electric Company: Amendment 39-14093. Docket No. 
FAA-2005-21238; Directorate Identifier 2005-NE-12-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective June 3, 
2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to all General Electric (GE) CF6-80E1 series 
turbofan engines with electronic control unit (ECU) part numbers (P/
N's) 1799M99P12, 1851M74P05, 1851M80P05, and 1960M84P03 or earlier 
installed. These (GE) CF6-80E1 series engines are installed on, but 
not limited to, Airbus Industrie (AI) A330 airplanes.

Unsafe Condition

    (d) This AD results from an uncommanded engine acceleration 
event caused by a failure of the ECU digital interface unit (DIU). 
We are issuing this AD to prevent undetected failure of the ECU DIU, 
which could result in uncommanded acceleration to the overspeed 
limit without response to throttle commands. The airplane could then 
experience asymmetric thrust.

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.

GE CF6-80E1A4/B Engines

    (f) For GE CF6-80E1A4/B engines with ECU's that already have 
software version E.1.N installed, no further action is required.

All Other CF6-80E1 Series Turbofan Engines

    (g) At next ECU exposure, upload improved software version 
E.1.N. Use the Accomplishment Instructions of either of GE Aircraft 
Engines CF6-80E1 Service Bulletin (SB) 73-0070, dated June 22, 2004, 
or SB 73-0070, Revision 01, dated March 21, 2005.
    (h) For the purposes of this AD, the next ECU exposure is 
defined as the next removal of the ECU for repair, or the next 
engine shop visit, whichever occurs sooner.
    (i) After the effective date of this AD, do not install any ECU 
that has a software version earlier than E.1.N onto any engine.

Alternative Methods of Compliance

    (j) 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

    (k) None.

Material Incorporated by Reference

    (l) You must use of General Electric (GE) Aircraft Engines CF6-
80E1 Service Bulletin (SB) 73-0070, dated June 22, 2004, or SB 73-
0070, Revision 01, dated March 21, 2005 to install the updated 
software required by this AD. The Director of the Federal Register 
approved the incorporation by reference of this service bulletin in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact General 
Electric Company via Lockheed Martin Technology Services, Lockheed 
Martin Technical Services, Distribution Center, 1330 Kemper Meadow 
Drive, Suite 110-C, Cincinnati, Ohio 45240, telephone (513) 672-
8400; fax (513) 672-8422, or e-mail: [email protected] 
for the service information identified in this AD; or
    Go to the GEAE Customer Web Center (CWC): https://customer.geae.com. You may review copies at the Docket Management 
Facility; U.S. Department of Transportation, 400 Seventh Street, 
SW., Nassif Building, Room PL-401, Washington, DC 20590-001, on the 
Internet at http://dms.dot.gov, 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/code_of_federal_regulations/ibr_locations.html.

    Issued in Burlington, Massachusetts, on May 12, 2005.
Robert Ganley,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 05-9887 Filed 5-18-05; 8:45 am]
BILLING CODE 4910-13-P

The complete text was extracted from the official GovInfo HTML edition for this publication. Acquired 2026-10-09T03:55:15.558651+00:00. Text extraction preserves the recorded source wording; it does not determine current requirements.

Open the captured official edition

Source SHA-256

96f8ddd404b8421dabc49c8264700b11a4c8ab2e8791aa3fbc8235c1f09a0a0e

Text SHA-256

0e140c751b8aec931601b40a06bd96f87682ec6b747b374d4b2c46be069f9ea2