[Federal Register Volume 70, Number 204 (Monday, October 24, 2005)]
[Proposed Rules]
[Pages 61398-61400]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 05-21174]


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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