[Federal Register: March 16, 2009 (Volume 74, Number 49)]
[Proposed Rules]
[Page 11043-11045]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr16mr09-18]
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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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[[Page 11043]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0018; Directorate Identifier 2009-NE-01-AD]
RIN 2120-AA64
Airworthiness Directives; General Electric Company CF6-80C2
Series Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), 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 (GE) CF6-80C2 series turbofan engines with
certain thrust reverser ballscrew gearbox assembly adjustable-length
end actuators installed. This proposed AD would require initial visual
inspections and repetitive replacements of the \3/8\-inch rod-ends
installed on the thrust reverser ballscrew gearbox assembly adjustable-
length end actuators, along with optional terminating action to those
repetitive replacements. This proposed AD would also require initial
visual inspections and replacements, if necessary, of the other
hardware connecting the thrust reverser transcowls to the engine. This
proposed AD results from reports of four failures of rod-ends on
certain thrust reverser ballscrew gearbox assembly adjustable-length
end actuators, leading to partial or complete separation of the
transcowl from the engine and airplane during thrust reversal. We are
proposing this AD to prevent loss of thrust control, asymmetric thrust,
increased stopping distance, and possibly hazardous debris on the
runway, which could result in unsafe landings.
DATES: We must receive any comments on this proposed AD by May 15,
2009.
ADDRESSES: Use one of the following addresses to comment on this
proposed AD.
Federal eRulemaking Portal: Go to http://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility, U.S. Department of
Transportation, 1200 New Jersey Avenue, SE., West Building Ground
Floor, Room W12-140, Washington, DC 20590-0001.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Fax: (202) 493-2251.
FOR FURTHER INFORMATION CONTACT: Christopher J. Richards, Aerospace
Engineer, Engine Certification Office, FAA, Engine & Propeller
Directorate, 12 New England Executive Park, Burlington, MA 01803; e-
mail: christopher.j.richards@faa.gov; telephone (781) 238-7133; 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-2009-0018; Directorate
Identifier 2009-NE-01-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://
www.regulations.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 Web site, anyone can find and read the comments in any
of our dockets, including, if provided, 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).
Examining the AD Docket
You may examine the AD docket on the Internet at http://
www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Operations office (telephone (800) 647-5527) is
the same as the Mail address provided in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
Discussion
Since January 2007, we received reports of four GE CF6-80C2 series
turbofan engine thrust reverser transcowls separating from the engine
and airplane during thrust reverser deployment while landing.
Investigation has revealed that the \3/8\-inch adjustable rod-ends on
the adjustable-length end actuators can fail in fatigue. When a rod-end
fails, additional load is put on the thrust reverser system center
drive unit (CDU). This additional load can cause the CDU clevis bracket
fasteners to fail or the CDU clevis pin to lose its retaining
capability, both causing separation of the transcowl from the engine
and airplane. This condition, if not corrected, could result in loss of
thrust control, asymmetric thrust, increased stopping distance, and
possibly hazardous debris on the runway, which could result in unsafe
landings.
Relevant Service Information
We have reviewed and approved the technical contents of Middle
River Aircraft Systems Alert Service Bulletin (ASB) No. CF6-80C2 S/B
78A1162, Revision 1, dated February 13, 2009. That ASB describes
procedures for inspecting ballscrew gearbox assembly adjustable-length
end actuator \3/8\-inch rod-ends and torsion arms, clevis fasteners,
clevis pins, and clevis pin retaining clips. That ASB also describes
procedures for replacing broken rod-ends, worn, damaged, or deformed
torsion arms, loose clevis fasteners, clevis pins that do not meet wear
limits, and loose clip retainer nuts and bolts.
[[Page 11044]]
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
initial and repetitive replacements of the \3/8\-inch rod-ends
installed on the thrust reverser ballscrew gearbox assembly adjustable-
length end actuators, along with optional terminating action to those
repetitive replacements. The proposed AD would also require an initial
visual inspection and replacement if necessary, of the other hardware
that connects the thrust reverser transcowl to the engine. 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 750 GE CF6-80C2
series turbofan engines installed on airplanes of U.S. registry. We
also estimate that it would take about 1.5 work-hours per engine to
perform the proposed inspection, 0.8 work-hour per engine to perform
the proposed rod-end replacement, and 24 work-hours per engine to
perform the proposed clevis bracket replacement. The average labor rate
is $80 per work-hour. Required rod-ends would cost about $168 per
engine. We estimate that 75 engines would require clevis bracket
replacement. Required replacement clevis brackets and associated labor
would cost about $826,500. Based on these figures, we estimate the
total cost of the proposed AD to U.S. operators to be $1,090,500.
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 AD:
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. 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, Incorporation by
reference, 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-2009-0018; Directorate
Identifier 2009-NE-01-AD.
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive
comments on this airworthiness directive (AD) action by May 15,
2009.
Affected ADs
(b) None.
Applicability
(c) This AD applies to General Electric Company (GE) CF6-80C2
series turbofan engines with thrust reverser ballscrew gearbox
assembly adjustable-length end actuators having \3/8\-inch rod-end,
part number (P/N) KBE6-59, MS21242S06, M81935/1-6, B15946-13, or
15946000-13, installed. These engines are installed on, but not
limited to, Airbus A300-600/R/F and A310-200/300, and Boeing 747-
200B/300/400/400D/400F, 767-200/300/300F/400ER, and MD-11 airplanes.
Exemption
(d) GE CF6-80C2 series turbofan engines that have completed the
initial compliance actions in Middle River Aircraft Systems (MRAS)
Alert Service Bulletin (ASB) No. CF6-80C2 S/B 78A1162, dated
December 30, 2008, or ASB No. CF6-80C2 S/B 78A1162, Revision 1,
dated February 13, 2009:
(1) Are allowed to take credit for accomplishing paragraphs (g)
and (h) of this AD; however
(2) All \3/8\-inch rod-ends, including those on engines which
satisfy paragraph (d) of this AD, are subject to the replacement
requirements in paragraph (i) of this AD.
Unsafe Condition
(e) This AD results from reports of four failures of rod-ends on
certain thrust reverser ballscrew gearbox assembly adjustable-length
end actuators, leading to partial or complete separation of the
transcowl from the engine and airplane during thrust reversal. We
are issuing this AD to prevent loss of thrust control, asymmetric
thrust, increased stopping distance, and possibly hazardous debris
on the runway, which could result in unsafe landings.
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Visual Inspection and Fastening Hardware Replacements
(g) Within 500 flight cycles after the effective date of this
AD, do the following:
(1) Inspect all translating cowl clevis pin retaining clips and
associated fastening hardware, including those on the center drive
unit (CDU), to ensure they are properly assembled and securely
fastened in place. If a retaining clip is not completely covering
the clevis pin and firmly attached to the clevis, remove and replace
the fastening hardware. Use paragraphs 3.B.(2)(b) and 3.B.(2)(c) of
MRAS ASB No. CF6-80C2 S/B 78A1162, Revision 1, dated February 13,
2009, to do the inspections.
(2) Remove and inspect all clevis pins for physical damage or
significant corrosion. Use paragraphs 3.C.(1) through 3.C.(3) of
MRAS ASB No. CF6-80C2 S/B 78A1162, Revision 1, dated February 13,
2009, to do the removals, inspections, and part disposition as
necessary.
(3) Inspect the clevis brackets and four clevis fasteners at
each of the clevis brackets (upper, center, and lower) for
structural integrity. Use paragraphs 3.F.(1)(a) and 3.F.(1)(b) of
MRAS ASB No. CF6-80C2 S/B 78A1162, Revision 1, dated February 13,
2009, to do the inspections.
(4) If loose or missing clevis fasteners are found, remove and
replace the clevis
[[Page 11045]]
fasteners. Use paragraphs 3.F.(2)(a) through 3.F(2)(c) of MRAS ASB
No. CF6-80C2 S/B 78A1162, Revision 1, dated February 13, 2009, to do
the replacements.
Initial Rod-End Replacements
(h) For all \3/8\-inch translating cowl adjustable-length
actuator rod-ends, P/N KBE6-59, MS21242S06, B15946-13, 15946000-13,
or M81935/1-6 having more than 600 flight cycles-since-new on the
effective date of this AD, replace them with P/N M81935/1-6, zero
time rod-ends within 500 flight cycles after the effective date of
this AD. Use paragraphs 3.E.(2) through 3.E.(7) of MRAS ASB No. CF6-
80C2 S/B 78A1162, Revision 1, dated February 13, 2009, to do the
replacements.
Repetitive \3/8\-inch Rod-End Replacements
(i) Repetitively replace \3/8\-inch translating cowl adjustable-
length actuator rod-ends, P/N M81935/1-6, that were installed as
specified in paragraph (h) of this AD, before they accumulate 11,000
flight cycles, with a zero time \3/8\-inch adjustable-length rod-
end, P/N M81935/1-6. Use paragraphs 3.E.(2) through 3.E.(7) of MRAS
ASB No. CF6-80C2 S/B 78A1162, Revision 1, dated February 13, 2009,
to do the replacements.
Optional Terminating Action
(j) As an optional terminating action to the repetitive \3/8\-
inch rod-end replacements required by this AD, replace the \3/8\-
inch adjustable rod-ends with either a fixed length rod-end, P/N
3238726-1, -2, or MS9560-08, or a 7/16-inch adjustable rod-end, P/N
3238729-1. Use paragraph 3.E.(1) of MRAS ASB No. CF6-80C2 S/B
78A1162, Revision 1, dated February 13, 2009, to do the
replacements.
Installation Prohibition
(k) Rod-ends removed to comply with this AD are not eligible for
installation on any aircraft.
Previous Credit
(l) Inspections and replacements and optional terminating action
performed before the effective date of this AD using MRAS ASB No.
CF6-80C2 S/B 78A1162, dated December 30, 2008, satisfy the required
initial actions and optional terminating action of this AD.
Alternative Methods of Compliance
(m) 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
(n) Contact Christopher J. Richards, Aerospace Engineer, Engine
Certification Office, FAA, Engine & Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; e-mail:
christopher.j.richards@faa.gov; telephone (781) 238-7133; fax (781)
238-7199, for more information about this AD.
(o) Contact Middle River Aircraft Systems, Mail Point 46, 103
Chesapeake Park Plaza, Baltimore, MD 21220, attn: Warranty Support;
telephone (410) 682-0094; fax (410) 682-0100, for a copy of the
service information identified in this AD.
Issued in Burlington, Massachusetts, on March 9, 2009.
Francis A. Favara,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. E9-5575 Filed 3-13-09; 8:45 am]
BILLING CODE 4910-13-P