[Federal Register Volume 72, Number 104 (Thursday, May 31, 2007)]
[Proposed Rules]
[Pages 30300-30302]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E7-10512]
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Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
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Federal Register / Vol. 72, No. 104 / Thursday, May 31, 2007 /
Proposed Rules
[[Page 30300]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-25239; Directorate Identifier 2006-NE-23-AD]
RIN 2120-AA64
Airworthiness Directives; General Electric Company Aircraft
Engine Group (GEAE) CF6-45A Series, CF6-50A, CF6-50C Series and CF6-50E
Series 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 GEAE CF6-45A, 45A2, -50A, -50C, -50CA, -50C1, -50C2, -50C2B, -
50C2D, -50C2F, -50C2R, -50E, -50E1, -50E2, and -50E2B turbofan engines.
This proposed AD would require replacing the compressor discharge
pressure (CDP) restoring spring assembly on certain main engine
controls (MECs) or re-marking MECs that already incorporate GEAE
Service Bulletin (SB) No. CF6-50 S/B 73-0119, dated March 21, 2005.
This proposed AD results from reports of five events involving
fractured CDP restoring spring assemblies. We are proposing this AD to
prevent loss of engine thrust control that could lead to loss of
control of the airplane.
DATES: We must receive any comments on this proposed AD by July 30,
2007.
ADDRESSES: Use one of the following addresses to comment on this
proposed 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.
You can get the service information identified in this proposed AD
from General Electric Company via GE-Aviation, Attn: Distributions, 111
Merchant St., Room 230, Cincinnati, Ohio 45246; telephone (513) 552-
3272; fax (513) 552-3329.
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: Tara Chaidez, Aerospace Engineer,
Engine Certification Office, FAA, Engine & Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803; telephone (781) 238-
7773; 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-2006-25239;
Directorate Identifier 2006-NE-23-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 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.).
Examining the AD Docket
You may examine the docket that contains the proposal, any comments
received and, any final disposition in person at the DOT 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
We received reports of five field events since 2002, which involved
fractured CDP restoring spring assemblies. Four events resulted in in-
flight shutdowns, and one event occurred during ground operation and
resulted in an engine shutdown.
Before 1996, the manufacturer of the spring assemblies welded some
spring assemblies such that the gap between the spring and the curved
spring seat exceeded 0.002 inch. Analysis shows that spring assemblies
with gaps greater than 0.002 inch have high stresses in the spring and
can fatigue in the heat affected zone of the weld.
Fracture of the spring assembly could cause excessive fuel flow
from the MEC, which could result in an uncommanded increase in engine
thrust with loss of throttle control. This condition, if not corrected,
could result in loss of engine thrust control that could lead to loss
of control of the airplane.
Relevant Service Information
We have reviewed and approved the technical contents of GEAE SB No.
CF6-50 S/B 73-0119, Revision 02, dated March 9, 2007, that describes
procedures for replacing the CDP restoring spring assembly and re-
marking the MEC data plate, and GEAE SB No. CF6-50 S/B 73-0120, dated
March 21, 2007 that describes procedures for replacing the CDP
restoring spring assembly.
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,
[[Page 30301]]
which would require replacing the CDP restoring spring assembly on
certain MECs and re-marking MECs that already incorporate GEAE SB No.
CF6-50 S/B 73-0119, dated March 21, 2005 or GEAE SB No. CF6-50 S/B 73-
0119, Revision 01, dated May 26, 2006. The proposed AD would require
you to use the service information described previously to perform
these actions.
Costs of Compliance
We estimate that this proposed AD would affect 756 GEAE CF6-45A, -
50C, and -50E series turbofan engines installed on airplanes of U.S.
registry. We also estimate that it would take about 40 work-hours per
engine to perform the proposed actions, and that the average labor rate
is $80 per work-hour. Required parts would cost about $1,787 per
engine. Based on these figures, we estimate the total cost of the
proposed AD to U.S. operators to be $3,770,172.
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 Company: Docket No. FAA-2006-25239; Directorate
Identifier 2006-NE-23-AD.
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive
comments on this airworthiness directive (AD) action by July 30,
2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to General Electric Company Aircraft Engine
Group (GEAE) CF6-45A, 45A2, -50A, -50C, -50CA, -50C1, -50C2, -50C2B,
-50C2D -50C2F, -50C2R, -50E, -50E1, -50E2, and -50E2B turbofan
engines that have a main engine control (MEC) with a part number (P/
N) specified in Table 1 of this AD installed. These engines are
installed on, but not limited to, Airbus A300 series airplanes,
McDonnell Douglas DC-10, KC-10, and MD-10 series airplanes, and
Boeing 747 series airplanes.
Table 1.--Affected Woodward and GEAE P/Ns for MECs by Engine Model
Series
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Engine model series Woodward P/N GEAE P/N
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CF6-50A, -50C, -50CA, -50C1, - 8062-275 9070M55P42
50C2, -50C2B, -50C2D, -50C2F, - 8062-279 9070M55P44
50C2R............................ 8062-287 9070M55P49
8062-289 9070M55P51
8062-819 9070M55P101
8062-822 9070M55P102
8062-824 9070M55P103
8062-823 9070M55P104
8062-826 9070M55P105
8062-827 9070M55P106
8062-828 9070M55P107
8062-829 9070M55P108
CF6-45A, -45A2, -50E, -50E1, - 8062-276 9187M29P10
50E2, -50E2B..................... 8062-280 9187M29P11
8062-290 9187M29P14
8062-291 9187M29P15
8062-817 9187M29P100
8062-820 9187M29P101
8062-896 9187M29P22
8062-897 9187M29P23
8062-898 9187M29P20
8062-899 9187M29P21
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[[Page 30302]]
(d) This AD results from reports of five events involving
fractured compressor discharge pressure (CDP) restoring spring
assembly. We are issuing this AD to prevent loss of engine thrust
control that could lead to 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.
Replacing the CDP Restoring Spring Assembly on CF6-50A Engines and -50C
Series Engines
(f) For CF6-50A model engines and -50C series engines that have
an MEC that has a P/N listed in Table 1 of this AD, replace the CDP
restoring spring assembly as follows in Table 2 of this AD:
Table 2.--Compliance Schedule for CF6-50A and -50C Engines
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If the CDP restoring spring assembly
in your MEC Then By Use
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(1) Was already replaced using GEAE Re-mark the MEC........ The next time the MEC Paragraph 3.A. of the
CF6-50 S/B 73-0119, dated March 21, is routed for repair Accomplishment
2005. such as the next MEC Instructions of SB No.
shop visit. CF6-50 S/B 73-0119,
Revision 02, dated
March 9, 2007.
(2) Was already replaced within Replace the spring The first MEC shop Paragraph 3.A. of the
10,000 or fewer hours time-in- assembly and re-mark visit or engine shop Accomplishment
service (TIS) before the effective the MEC. visit after the MEC Instructions of SB No.
date of this AD, and the replacement exceeds 10,000 hours CF6-50 S/B 73-0119,
spring assembly (P/N 3018-248) had TIS, but do not exceed Revision 02, dated
zero hours TIS. 20,000 hours TIS. March 9, 2007.
(3) Has more then 10,000 hours TIS... Replace the spring The next MEC shop visit Paragraph 3.A. of the
assembly and re-mark or engine shop visit Accomplishment
the MEC. whichever occurs first. Instructions of SB No.
CF6-50 S/B 73-0119,
Revision 02, dated
March 9, 2007.
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Replacing the CDP Restoring Spring Assembly on CF6-45A and -50E Series
Engines
(g) For CF6-45A series and -50E series engines that have an MEC
that has a P/N listed in Table 1 of this AD, replace the CDP
restoring spring assembly as follows in Table 3 of this AD:
Table 3.--Compliance Schedule for CF6-45A and -50E Engines
----------------------------------------------------------------------------------------------------------------
If the CDP restoring spring assembly
in your MEC Then By Use
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(1) Was already replaced within Replace the spring The first MEC shop Paragraph 3.A. of the
10,000 or fewer hours time-in- assembly and re-mark visit or engine shop Accomplishment
service (TIS) before the effective the MEC. visit after the MEC Instructions of SB No.
date of this AD, and the replacement exceeds 10,000 hours CF6-50 S/B 73-0120,
spring assembly (P/N 3018-248) had TIS, but do not exceed dated March 21, 2007.
zero hours TIS. 20,000 hours TIS.
(2) Has more then 10,000 hours TIS... Replace the spring The next MEC shop visit Paragraph 3.A. of the
assembly and re-mark or engine shop visit Accomplishment
the MEC. whichever occurs first. Instructions of SB No.
CF6-50 S/B 73-0120,
dated March 21, 2007.
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Definition
(h) For the purpose of this AD, a shop visit is induction of the
engine or MEC into the shop for any cause.
Installation Prohibition
(i) After the effective date of the AD, do not install an MEC
that:
(1) Has not complied with SB No. CF6-50 S/B 73-0119, Revision
02, dated March 9, 2007 or earlier revision, or SB No. CF6-50 S/B
73-0120, dated March 21, 2007, or,
(2) Has not had the CDP restoring spring replaced with a spring
assembly, P/N 3018-248, or FAA-approved equivalent spring assembly,
within the previous 10,000 hours of MEC operation.
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.
Issued in Burlington, Massachusetts, on May 23, 2007.
Fran A. Favara,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. E7-10512 Filed 5-30-07; 8:45 am]
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