[Federal Register: November 2, 2005 (Volume 70, Number 211)]
[Rules and Regulations]
[Page 66250-66251]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr02no05-2]
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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:
DOT Docket web site: Go to http://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking web site: Go to http://www.regulations.gov
and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590-0001.
Fax: (202) 493-2251.
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]
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