[Federal Register: October 24, 2005 (Volume 70, Number 204)]
[Proposed Rules]
[Page 61398-61400]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr24oc05-16]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-22055; Directorate Identifier 2005-NE-31-AD]
RIN 2120-AA64
Airworthiness Directives; General Electric Company Model CF6-
80C2D1F Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD)
for General Electric Company Model CF6-80C2D1F turbofan engines. This
proposed AD would require modifying the latching system of the fan
reverser. This proposed AD results from 13 reports of released thrust
reverser hardware. We are proposing this AD to prevent release of the
thrust reverser cascade on landing, which could result in runway debris
and a possible hazard to other aircraft.
DATES: We must receive any comments on this proposed AD by November 23,
2005.
ADDRESSES: Use one of the following addresses to comment on this
proposed AD.
[[Page 61399]]
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.
You can get the service information identified in this proposed AD
from Middle River Aircraft Systems, Mail Point 46, 103 Chesapeake Park
Plaza, Baltimore, MD, 21220-4295, telephone: (410) 682-0094; fax: (410)
682-0100.
You may examine the comments on this proposed AD in the AD docket
on the Internet at http://dms.dot.gov.
FOR FURTHER INFORMATION CONTACT: James Lawrence, Aerospace Engineer,
Engine Certification Office, FAA, Engine & Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803-5299; telephone (781)
238-7176; fax (781) 238-7199.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send us any written relevant data, views, or
arguments regarding this proposal. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2005-22055;
Directorate Identifier 2005-NE-31-AD'' in the subject line of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments received by the closing date and may amend the
proposed AD in light of those comments.
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 proposed AD. Using the search function of the
DOT docket 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 proposal, 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 Docket Management Facility receives them.
Discussion
The FAA has received 13 reports of thrust reverser hardware
released on landing. The first event occurred in January 1997. With the
existing design for the forward lower latch, an operator can
inadvertently close a fan reverser half with the lower latch handle in
the closed position. When this happens, the barrel nut of the lower
latch assembly can ride over the clevis, mounted on the engine fan
case, without engaging the clevis. When it is in this position, the
lower latch assembly appears engaged when it isn't. Because the barrel
nut assembly of the lower latch might be spring-loaded against the
engine fan case, the fan cowl door can close without engaging the lower
latch assembly. All of the incidents occurred on CF6-80C2D1F engines
installed on McDonnell Douglas MD-11 airplanes. Investigations show the
design of those applications contributes to the failures of the fan
reversers. The Middle Rivers Aircraft Systems (MRAS) (a subsidiary of
the General Electric Company) issued four service bulletins to address
the problem. However, several operators of McDonnell Douglas MD-11
airplanes haven't incorporated the recommendations of those service
bulletins. As a result, three incidents occurred from March 2004
through October 2004. This condition, if not corrected, could result in
release of the thrust reverser cascade on landing, which could result
in runway debris and a possible hazard to other aircraft.
Relevant Service Information
We have reviewed and approved the technical contents of the
following MRAS service bulletins (SBs):
CF6-80C2 S/B 78-1068, Revision 2, dated May 16, 2005, and
CF6-80C2 S/B 78-1077, Revision 1, dated May 16, 2005, that describe
procedures for modifying the latching system of the fan reverser.
SB CF6-80C2 S/B 78-1078, Revision 1, dated May 16, 2005,
that describe procedures for replacing the existing L-shaped brackets
or the upper and lower ends of the upper latch operating cable.
SB CF6-80C2 S/B 78-1088, Revision 5, dated May 16, 2005,
that describe procedures for installing the new improved fan reverser
upper latch.
Differences Between the Proposed AD and the Manufacturer's Service
Information
Middle River Aircraft Systems SB's CF6-80C2 S/B 78-1068, Revision
2, dated May 16, 2005; CF6-80C2 S/B 78-1077, Revision 1, dated May 16,
2005; and CF6-80C2 S/B 78-1078, Revision 1, dated May 16, 2005; apply
to CF6-80C2 series engines. This proposed AD applies to the CF6-80C2D1F
engine installed on the McDonnell Douglas MD-11 airplanes only.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other products
of this same type design. We are proposing this AD, which would
require:
Modifying the latching system of the fan reverser at the
next normally scheduled maintenance period, or within 1,200 flight
hours time-in-service (TIS) after the effective date of the proposed
AD, whichever occurs first; and
Replacing the existing L-shaped support brackets of the
upper and lower ends of the upper latch operating cable at the next
normally scheduled maintenance period, or within 6,000 flight hours TIS
after the effective date of the proposed AD, whichever occurs first;
and
Installing the new improved fan reverser upper latch at
the next normally scheduled maintenance period, or within 6,000 flight
hours TIS after the effective date of the proposed AD, whichever occurs
first.
The proposed AD would require you to use the service information
described previously to perform these actions.
Costs of Compliance
There are about 339 General Electric Company CF6-80C2D1F2 turbofan
engines of the affected design in the worldwide fleet. We estimate that
this proposed AD would affect 138 engines installed on airplanes of
U.S. registry. We also estimate that it would take
[[Page 61400]]
approximately 19 work hours per engine to perform the proposed actions,
and that the average labor rate is $65 per work hour. Required parts
would cost approximately $6,644 per engine. Based on these figures, we
estimate the total cost of the proposed AD to U.S. operators to be
$1,087,302.
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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 proposed
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. Would 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 regulatory evaluation of the estimated costs to
comply with this proposed AD. See the ADDRESSES section for a location
to examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Under the authority delegated to me by the Administrator, the
Federal Aviation Administration proposes to amend 14 CFR part 39 as
follows:
PART 39--AIRWORTHINESS DIRECTIVES
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]
2. The FAA amends Sec. 39.13 by adding the following new
airworthiness directive:
General Electric Corporation: Docket No. FAA-2005-22055; Directorate
Identifier 2005-NE-31-AD.
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive
comments on this airworthiness directive (AD) action by November 23,
2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to General Electric Company Model CF6-
80C2D1F turbofan engines. These engines are installed on, but not
limited to, McDonnell Douglas Corporation MD-11 airplanes.
Unsafe Condition
(d) This AD results from 13 reports of released thrust reverser
hardware. We are issuing this AD to prevent release of the thrust
reverser cascade on landing, which could result in runway debris and
a possible hazard to other aircraft.
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.
Modifying the Latching System of the Fan Reverser
(f) At the next normally scheduled maintenance period or within
1,200 flight hours time-in-service (TIS) after the effective date of
this AD, whichever occurs first, modify the latching system of the
fan reverser. Use the Accomplishment Instructions of Middle River
Aircraft Systems (MRAS) service bulletins (SBs) CF6-80C2 S/B 78-
1068, Revision 2, or CF6-80C2 S/B 78-1077, Revision 1, both dated
May 16, 2005 to modify the latch assembly.
Replacing the L-Shaped Support Brackets
(g) At the next normally scheduled maintenance period or within
6,000 flight hours TIS after the effective date of this AD,
whichever occurs first, replace the existing L-shaped support
brackets of the upper and lower ends of the upper latch operating
cable with improved T-shaped support brackets. Use the
Accomplishment Instructions of MRAS SB CF6-80C2 S/B 78-1078,
Revision 1, dated May 16, 2005 to replace the support brackets.
Installing the Improved Upper Latch of the Fan Reverser
(h) At the next normally scheduled maintenance period or within
6,000 flight hours TIS after the effective date of this AD,
whichever occurs first, install the improved upper latch of the fan
reverser. Use the Accomplishment Instructions of MRAS SB CF6-80C2 S/
B 78-1088, Revision 5, dated May 16, 2005 to install the upper
latch.
Alternative Methods of Compliance
(i) 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
(j) None.
Issued in Burlington, Massachusetts, on October 13, 2005.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 05-21174 Filed 10-21-05; 8:45 am]
BILLING CODE 4910-13-P