[Federal Register Volume 70, Number 211 (Wednesday, November 2, 2005)]
[Rules and Regulations]
[Pages 66250-66251]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-21805]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-22701; Directorate Identifier 2005-NE-37-AD; 
Amendment 39-14356; AD 2005-22-12]
RIN 2120-AA64


Airworthiness Directives; General Electric Company 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 adopting a new airworthiness directive (AD) for 
General Electric Company (GE) CF6-80E1 series turbofan engines 
installed on Airbus Industrie A330 series airplanes. This AD requires a 
check of the holding torque of the thrust reverser actuation system 
(TRAS) locks, and if necessary a visual inspection of the TRAS lock 
flexible drive shafts, within 10 flight cycles after all aborted 
takeoffs in which the thrust reverser was deployed. This AD results 
from reports of operators finding several damaged TRAS lock flexible 
drive shafts during inspections and checks of the drive shafts. We are 
issuing this AD to prevent inadvertent in-flight deployment of the 
thrust reverser, which can result in loss of control of the airplane.

DATES: This AD becomes effective December 2, 2005.
    We must receive any comments on this AD by January 3, 2006.

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 20590-0001.
    <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 Middle River Aircraft Systems, Mail Point 46, 103 
Chesapeake Park Plaza, Baltimore, MD, 21220-4295, attn: Warranty 
Support, telephone: (410) 682-0094, fax: (410) 682-0100 for the alert 
service bulletin identified in this AD. 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 temporary revision identified in this AD. Contact 
Airbus, 1 Rond Point Maurice Bellionte, 31707 Blagnac Cedex, France, 
for the Airbus A330 manual information identified in this AD.

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

SUPPLEMENTARY INFORMATION: The FAA issued AD 2002-10-08 (67 FR 36090, 
May 23, 2002) on May 9, 2002. That AD requires initial and repetitive 
thrust reverser inspections and checks. That AD resulted from reports 
of service-induced hardware deterioration that reduces the overall 
thrust reverser system protection against inadvertent deployment, which 
can result in loss of control of the airplane. Since we issued that AD, 
we received reports of operators finding several damaged TRAS lock 
flexible drive shafts. The operators found these damaged shafts while 
complying with the torque check specified in AD 2002-10-08. 
Investigation and analysis by GE and the FAA revealed that high end-of-
stroke impact caused the damage. End-of-stroke impact is highest when 
the thrust reverser is commanded to deploy during an aborted take-off. 
The TRAS lock flexible drive shaft attaches the upper end actuator to 
the TRAS lock. When the system is commanded to deploy, the TRAS lock 
rotates to allow movement of the thrust reverser. At the end of the 
deployment stroke, the actuation system end-actuator hits its hard 
stop, while the TRAS lock continues to rotate. The TRAS lock then 
transmits its rotating inertia to the TRAS lock flexible drive shafts. 
This transmission of inertia can cause twisting, shearing, or bird 
caging of the drive shafts, leading to loss of the holding torque in 
the TRAS lock. Loss of holding torque reduces the effectiveness of the 
lock and if not corrected, can increase the probability of an in-flight 
inadvertent deployment of the thrust reverser, which can result in loss 
of control of the airplane.

FAA's Determination and Requirements of This AD

    Although this affected engine model is not used on any airplanes 
that are registered in the United States, the possibility exists that 
this engine model could be used on airplanes registered in the United 
States in the future. We are issuing this AD to prevent inadvertent in-
flight deployment of the thrust reverser, which can result in loss of 
control of the airplane. This AD requires performing a check of the 
holding torque of the TRAS locks, and if necessary a visual inspection 
of the TRAS lock flexible drive shafts, within 10 flight cycles after 
all aborted takeoffs in which the thrust reverser was deployed. This AD 
also requires replacing any damaged flexible drive shafts or locks.

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.

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-2005-22701; 
Directorate Identifier 2005-NE-37-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

[[Page 66251]]

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 Docket Management 
Facility Docket Offices 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.

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, 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 adding the following new airworthiness 
directive:

2005-22-12 General Electric Company: Amendment 39-14356. Docket No. 
FAA-2005-22701; Directorate Identifier 2005-NE-37-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective December 
2, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to General Electric Company (GE) CF6-80E1 
series turbofan engines. These engines are installed on, but not 
limited to, Airbus Industrie A330 series airplanes.

Unsafe Condition

    (d) This AD results from reports of operators finding several 
damaged thrust reverser actuation system (TRAS) lock flexible drive 
shafts during inspections and checks of the drive shafts. We are 
issuing this AD to prevent inadvertent in-flight deployment of the 
thrust reverser, which can result in loss of control of the 
airplane.

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.
    (f) Within 10 flight cycles after all aborted takeoffs in which 
the thrust reverser was deployed, do the following:
    (1) Perform a check of the holding torque of the TRAS locks.
    (2) Based on the results of the holding torque check, perform a 
visual inspection of the TRAS lock flexible drive shafts if 
necessary.
    (3) Replace any damaged flexible drive shafts or locks.
    (g) Information on performing a check of the holding torque of 
the TRAS locks, and a visual inspection of the TRAS lock flexible 
drive shafts, can be found in the Airbus A330 Aircraft Maintenance 
Manual, Task 72-00-00-200-850.

Alternative Methods of Compliance

    (h) 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

    (i) Middle River Aircraft Systems Alert Service Bulletin No. 
CF6-80E1 S/B 78A5097, dated June 14, 2005, and General Electric CF6-
80E1 Series Engine Manual Temporary Revision No. 05-0049, dated 
August 24, 2005, pertain to the subject of this AD.

    Issued in Burlington, Massachusetts, on October 27, 2005.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 05-21805 Filed 11-1-05; 8:45 am]
BILLING CODE 4910-13-P