Airworthiness Directives; General Electric Company (GE) CF6-80C2 and CF6-80E1 Series Turbofan Engines, 51388-51391 [E7-17682]
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51388
Federal Register / Vol. 72, No. 173 / Friday, September 7, 2007 / Proposed Rules
Service Bulletin A310–53–2125, including
Appendix 01, dated January 9, 2007, at the
applicable compliance times listed in Table
1 (threshold) or Table 2 (grace period) of this
AD, whichever occurs later.
TABLE 1.—COMPLIANCE THRESHOLDS
Whichever occurs first after the effective date of this AD
Airbus model
Accumulated time since
first flight (in flight cycles)
A310–200 .........................................................................................................................
A310–300 with an average flight time (AFT) ≤ to 4 hours ..............................................
A310–300 with an AFT > 4 hours ....................................................................................
Accumulated time since
first flight (in flight hours)
41,500
33,000
20,500
83,500
93,500
102,000
TABLE 2.—GRACE PERIODS
Whichever occurs first after the
effective date of this AD
Airbus model
Flight cycles
A310–200 .........................................................................................................................................................
A310–300 with an average flight time (AFT) ≤ 4 hours ..................................................................................
A310–300 with an AFT > 4 hours ....................................................................................................................
FAA AD Differences
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Note: This AD differs from the MCAI and/
or service information as follows:
No differences.
Other FAA AD Provisions
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
Send information to ATTN: Tom Stafford,
Aerospace Engineer, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone (425)
227–1622; fax (425) 227–1149. Before using
any approved AMOC on any airplane to
which the AMOC applies, notify your
appropriate principal inspector (PI) in the
FAA Flight Standards District Office (FSDO),
or lacking a PI, your local FSDO.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act,
the Office of Management and Budget (OMB)
has approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(h) Refer to MCAI European Aviation
Safety Agency Airworthiness Directive 2007–
0111, dated April 25, 2007; and Airbus
Service Bulletin A310–53–2125, dated
January 9, 2007; for related information.
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Issued in Renton, Washington, on August
28, 2007.
Stephen P. Boyd,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. E7–17686 Filed 9–6–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–28413; Directorate
Identifier 2007–NE–25–AD]
RIN 2120–AA64
Airworthiness Directives; General
Electric Company (GE) CF6–80C2 and
CF6–80E1 Series Turbofan Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for GE
CF6–80C2 and CF6–80E1 series
turbofan engines with fuel manifold part
numbers (P/Ns) 1303M31G12 and
1303M32G12 installed. This proposed
AD would require removing and
discarding the loop clamps that
assemble the fuel manifold to the
compressor rear frame (CRF) friction
damper brackets, visually inspecting the
fuel manifold for wear at each clamp
location, and replacing the clamps with
new, zero-time parts. This proposed AD
results from fuel manifold vibration
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1,500
1,200
740
Flight hours
3,000
3,400
3,600
during engine operation that causes the
loop clamps that assemble the manifold
to the CRF to deteriorate. Fourteen fuel
leak events occurred over the past
several years. We are proposing this AD
to prevent fuel leaks during engine
operation that could result in an undercowl fire.
DATES: We must receive any comments
on this proposed AD by November 6,
2007.
ADDRESSES: Use one of the following
addresses to comment on this proposed
AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• 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.
You may examine the comments on
this proposed AD in the AD docket on
the Internet at https://dms.dot.gov., or in
Room W12–140 on the ground floor of
the West Building, 1200 New Jersey
Avenue, SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Robert Green, Aerospace Engineer,
Engine Certification Office, FAA, Engine
and Propeller Directorate, 12 New
England Executive Park, Burlington, MA
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Federal Register / Vol. 72, No. 173 / Friday, September 7, 2007 / Proposed Rules
01803; telephone (781) 238–7754; 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–
2007–28413; Directorate Identifier
2007–NE–25–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 https://
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.). 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 https://
dms.dot.gov.
pwalker on PROD1PC71 with PROPOSALS
Examining the AD Docket
You may examine the AD docket on
the Internet at https://dms.dot.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
During a pre-flight inspection in
November 2002, a manifold fuel leak
was found on a CF6–80C2B1F turbofan
engine. This fuel leak resulted from fuel
manifold vibration during engine
operation, which caused the loop
clamps that assemble the manifold to
the CRF to deteriorate. The cushion on
the loop clamp wore away resulting in
the metal strip of the clamp rubbing into
the fuel manifold. A fuel leak resulted.
The high surface temperature of the CRF
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during engine operation could have
ignited the leaking fuel resulting in an
under-cowl fire.
In 2003, GE issued service bulletins
for the CF6–80C2 and CF6–80E1series
turbofan engines recommending
repetitive visual inspection of the fuel
manifolds at intervals of 4,500 flighthours (FH). Despite these
recommendations, five fuel leak events
occurred in 2006; one resulting in an
under-cowl fire on a CF6–80C2B6F
turbofan engine. There have been three
additional fuel leak events to date in
2007. A total of thirteen CF6–80C2
series turbofan engine fuel leaks
(November 2002 through May 2007) and
one CF6–80E1 fuel leak (January 2007)
have been reported. Five of the recent
events occurred within the 4,500 FH
since the last inspection.
Because of the increased number of
fuel leak events and the low FH
intervals since the last inspection, this
proposed AD would reduce the initial
re-inspection FH interval, and would
require replacing the fuel manifold loop
clamps with new, zero-time parts at
each inspection. This proposed AD is
necessary to prevent fuel leaks during
engine operation that could result in an
under-cowl fire.
Differences Between the Proposed AD
and the Manufacturer’s Service
Information
In the manufacturer’s original service
bulletins, GE recommends inspecting
the fuel manifold for wear at 4,500 FH.
However, the service bulletins do not
recommend replacing the loop clamps
at each inspection.
Because recent field events involving
fuel leaks indicate a reduced inspection
interval is required, this AD would
require removing loop clamps and
inspecting the fuel manifold according
to the following schedule:
• For engines previously inspected
using GEAE service bulletins, SB 73–
0226, dated March 5, 2003, for CF6–
80C2 engines; or SB 73–0061, dated
April 14, 2003, for CF6–80E1 engines,
within 1,750 FH since-last-inspection.
• If used loop clamps or clamps of
unknown heritage were installed at last
shop visit, within 1,750 FH since-lastshop-visit.
• For first-run engines and engines
with zero-time, new loop clamps
installed at last shop visit, within 7,500
FH.
• For affected engines that have
already exceeded the 1,750 FH initial
inspection threshold, within 4,500 FH
of the last inspection or 4 months after
the effective date of the AD, whichever
comes first.
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51389
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 removing and
discarding the loop clamps that
assemble the fuel manifold to the
compressor rear frame damper (CRF)
friction damper brackets, visually
inspecting the fuel manifold for wear at
each loop clamp location, and replacing
the clamps with new, zero-time parts.
Costs of Compliance
We estimate that this proposed AD
would affect 350 CF6–80C2 series
turbofan engines installed on airplanes
of U.S. registry. We also estimate that it
would take about 4 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 $162 per engine. Based on these
figures, we estimate the total cost of the
proposed AD to U.S. operators for one
manifold visual inspection and loop
clamp replacement to be $168,700.
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:
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Federal Register / Vol. 72, No. 173 / Friday, September 7, 2007 / Proposed Rules
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, 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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
General Electric Company: Docket No. FAA–
2007–28413; Directorate Identifier 2007–
NE–25–AD.
Comments Due Date
(a) The Federal Aviation Administration
(FAA) must receive comments on this
airworthiness directive (AD) action by
November 6, 2007.
Affected ADs
(b) None.
manifold P/N’s 1303M31G12 and
1303M32G12. These engines are installed on
Airbus A330 airplanes.
Unsafe Condition
(d) This AD results from fuel manifold
vibration during engine operation that causes
the clamps that assemble the manifold to the
compressor rear frame (CRF) to deteriorate.
We are issuing this AD to prevent fuel leaks.
The high surface temperature of the CRF
could ignite the leaking fuel resulting in an
under-cowl fire.
Compliance
Applicability
(c) This AD applies to:
(1) GE CF6–80C2A1, –80C2A2, –80C2A3,
–80C2A5, –80C2A8, –80C2A5F, –80C2B1,
–80C2B2, –80C2B4, –80C2B6, –80C2B1F,
–80C2B1F1, –80C2B1F2, –80C2B2F,
–80C2B3F, –80C2B4F, –80C2B5F, –80C2B6F,
–80C2B6FA, –80C2B7F, –80C2B8F,
–80C2D1F, –80C2L1F, –80C2K1F turbofan
engine models configured with fuel manifold
part numbers (P/Ns) 1303M31G12 and
1303M32G12. These engines are installed on,
but not limited to Boeing 747, 767, MD11,
and Airbus A300 and A310 airplanes.
(2) This AD also applies to GE CF6–
80E1A1, –80E1A2, –80E1A3, –80E1A4,
–80E1A4/B turbofan engine models with fuel
(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.
Removal and Replacement of Loop Clamps
and Fuel Manifold Inspection Compliance
Times
(f) Remove and discard the loop clamps,
P/N J1220G10, that assemble the fuel
manifold to the Compressor Rear Frame
friction damper brackets, inspect the fuel
manifold for wear at each clamp location as
specified in paragraph (g) of this AD, and
replace the loop clamps with new, zero-time
parts at each inspection. Use the following
schedule in Table 1 of this AD:
TABLE 1.—INSPECTION SCHEDULE FOR INITIAL INSPECTIONS
If:
Then replace clamps and inspect within:
(1) The engine was previously inspected using GEAE service bulletins,
SB 73–0226, dated March 5, 2003, for CF6–80C2 engines; or SB
73–0061, dated April 14, 2003, for CF6–80E1 engines.
(2) Used loop clamps or clamps of unknown heritage were installed at
last shop visit.
(3) The engine is a first-run engine or is an engine with zero-time, new
loop clamps previously installed.
(4) The engine has already exceeded the 1,750 FH initial inspection
threshold.
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Inspection of Fuel Manifold P/Ns
1303M31G12 and 1303M32G12
(g) Remove any tape applied to clamp
locations. Visually inspect the full
circumference of the manifold at each clamp
location.
(h) If the fuel manifold shows any signs of
wear, determine the depth of the wear as
follows:
(1) Measure the outside diameter of the
tube using a pinpoint micrometer adjacent to
the worn area.
(2) Measure the worn area at the smallest
diameter.
(3) Subtract the measurement of the worn
tube diameter from the unworn diameter
measurement. Allowable wear is 0.0035 inch.
(i) Before further flight, replace fuel
manifolds with wear greater than 0.010 inch.
(ii) Replace fuel manifolds with wear
greater than 0.0035 inch, but less than 0.010
inch, within 50 flight cycles.
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1,750 flight hours (FH) time-since-last-inspection (TSLI).
1,750 FH time-since-last-shop-visit.
7,500 FH since zero-time, new loop clamps were installed.
4,500 FH TSLI, or 4 months after the effective date of this AD, whichever occurs first.
Revise Air Carrier’s Continuous
Airworthiness Maintenance Program
(CAMP) and Airworthiness Limitation
Section (ALS)
(i) Within 30 days of the effective date of
this AD, revise the air carrier’s approved
CAMP and ALS of Chapter 5 in the CF6–
80C2 and CF6–80E1 Instructions for
Continued Airworthiness to add:
(1) Repetitive inspections of fuel
manifolds, P/Ns 1303M31G12 and
1303M32G12, as detailed in paragraphs (g)
and (h) of this AD, at 7,500 FH intervals.
(2) Mandatory removal of loop clamps, P/
N J1220G10, that assemble the fuel manifold,
P/Ns 1303M31G12 and 1303M32G12, to the
Compressor Rear Frame friction damper
brackets, at each inspection.
(3) Replacement of loop clamps, P/N
J1220G10, with new, zero-time parts, at each
inspection.
Alternative Methods of Compliance
(j) The Manager, Engine Certification
Office, has the authority to approve
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alternative methods of compliance for this
AD if requested using the procedures found
in 14 CFR 39.19.
Related Information
(k) GE service bulletins GEAE CF6–80C2 S/
B 73–0226, dated March 5, 2003, and GEAE
CF6–80E1 S/B 73–0061, dated April 14,
2003; and the following General Electric
engine manuals pertain to the subject of this
AD: CF6–80C2 Engine Manual GEK 92451;
CF6–80C2L1F Engine Manual GEK 112213;
CF6–80C2K1F Engine Manual GEK 112721;
and CF6–80E1 Engine Manual GEK 99376.
(l) Contact Robert Green, Aerospace
Engineer, Engine Certification Office, FAA,
Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA,
01803; e-mail: robert.green@faa.gov;
telephone (781) 238–7754; fax (781) 238–
7199, for more information about this AD.
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Federal Register / Vol. 72, No. 173 / Friday, September 7, 2007 / Proposed Rules
Issued in Burlington, Massachusetts, on
August 30, 2007.
Thomas A. Boudreau,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E7–17682 Filed 9–6–07; 8:45 am]
Comments Invited
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2006–28778; Airspace
Docket No. 07–AGL–6]
Proposed Establishment of Class E5
Airspace; Prairie Du Sac, WI
Federal Aviation
Administration (FAA), DOT.
AGENCY:
ACTION:
Notice of proposed rulemaking.
SUMMARY: This action proposes to
establish Class E airspace at Prairie Du
Sac, WI. Additional controlled airspace
is necessary to accommodate aircraft
using a new Area Navigation (RNAV)
Global Positioning System (GPS)
Instrument Approach Procedure (IAP) at
Sauk-Prairie Airport. The FAA is
proposing this action to enhance the
safety and management of aircraft
operations at Sauk-Prairie Airport,
Prairie Du Sac, WI.
Comments must be received on
or before October 1, 2007.
DATES:
Send comments on this
proposal to the Docket Management
System, U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590. You must
identify the docket number FAA–2007–
28778/Airspace Docket No. 07–AGL–6,
at the beginning of your comments. You
may also submit comments on the
Internet at https://dms.dot.gov You may
review the public docket containing the
proposal, any comments received, and
any final disposition in person in the
Dockets Office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The Docket Office
(telephone 1–800–647–5527) is on the
ground floor of the building at the above
address.
pwalker on PROD1PC71 with PROPOSALS
ADDRESSES:
FOR FURTHER INFORMATION CONTACT:
Grant Nichols, System Support, DOT
Regional Headquarters Building, Federal
Aviation Administration, 901 Locust,
Kansas City, MO 64106; at telephone
number (816) 329–2522.
SUPPLEMENTARY INFORMATION:
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Interested parties are invited to
participate in this proposal rulemaking
by submitting such written data, views,
or arguments, as they may desire.
Comments that provide the factual basis
supporting the views and suggestions
presented are particularly helpful in
developing reasoned regulatory
decisions on the proposal. Comments
are specifically invited on the overall
regulatory, aeronautical, economic,
environmental, and energy-related
aspects of the proposal.
Communications should identify both
docket umbers and be submitted in
triplicate to the address listed above.
Commenters wishing the FAA to
acknowledge receipt of their comments
on this notice must submit with those
comments a self-addressed, stamped
postcard on which the following
statement is made: ‘‘Comments to
Docket No. FAA–2007–28778/Airspace
Docket No. 07–AGL–6.’’ The postcard
will be date/time stamped and returned
to the commenter.
Availability of NPRM’s
An electronic copy of this document
may be downloaded through the
internet at https://dms.dot.gov. Recently
published rulemaking documents can
also be accessed through the FAA’s Web
page at https://www.faa.gov or the
Superintendent of Document’s Web
page at https://www.access.gpo.gov/nara.
Additionally, any person may obtain
a copy of this notice by submitting a
request to the Federal Aviation
Administration (FAA), Office of Air
Traffic Airspace Management, ATA–
400, 800 Independence Avenue, SW.,
Washington, DC 20591, or by calling
(202) 267–8783. Communications must
identify both docket numbers for this
notice. Persons interested in being
placed on a mailing list for future copies
of NPRMs should contact the FAA’s
Office of Rulemaking (202) 267–9677, to
request a copy of Advisory Circular No.
11–2A, Notice of Proposed Rulemaking
Distribution System, which describes
the application procedure.
The Proposal
This action proposes to amend Title
14, Code of Federal Regulations (14
CFR) part 71, by establishing Class E
airspace extending upward from 700
feet above the surface at Sauk-Prairie
Airport, Prairie Du Sac, WI. aAnew
RNAV (GPS) IAP has made this action
necessary for the safety of IFR
operations at Sauk-Prairie Airport,
Prairie Du Sac, WI. This area would be
depicted on appropriate aeronautical
charts.
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51391
Class E airspace areas extending
upward from 700 feet or more above the
surface of the earth are published in
Paragraph 6005 of FAA Order 7400.9P,
dated September 1, 2006, and effective
September 15, 2006, which is
incorporated by reference in 14 CFR
71.1. The Class E airspace designations
listed in this document would be
published subsequently in the Order.
The FAA has determined that this
proposed regulation only involves an
established body of technical
regulations for which frequent and
routine amendments are necessary to
keep them operationally current. It,
therefore, (1) Is not a ‘‘significant
regulatory action’’ under Executive
Order 12866; (2) is not a ‘‘significant
rule’’ under DOT Regulatory Policies
and Procedures (44 FR 11034; February
26, 1979); and (3) does not warrant
preparation of a Regulatory Evaluation
as the anticipated impact is so minimal.
Since this is a routine matter that will
only affect air traffic procedures and air
navigation, it is certified that this rule,
when promulgated, will not have a
significant economic impact on a
substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 71
Airspace, Incorporation by reference,
Navigation (Air).
The Proposed Amendment
In consideration of the foregoing, the
Federal Aviation Administration
proposes to amend 14 CFR part 71 as
follows:
PART 71—DESIGNATION OF CLASS A,
CLASS B, CLASS C, CLASS D, AND
CLASS E AIRSPACE AREAS;
AIRWAYS; ROUTES; AND REPORTING
POINTS
1. The authority citation for part 71
continues to read as follows:
Authority: 49 U.S.C. 106(g); 40103, 40113,
40120; E.O. 10854, 24 FR 9565, 3 CFR 1959–
1963 Comp., p. 389.
§ 71.1
[Amended]
2. The incorporation by reference in
14 CFR 71.1 of Federal Aviation
Administration Order 7400.9P, Airspace
Designations and Reporting Points,
dated September 1, 2006, and effective
September 15, 2006, is amended as
follows:
Paragraph 6005 Class E Airspace Areas
Extending Upward From 700 Feet or More
Above the Surface of the Earth.
*
*
*
*
*
AGL E5 Prairie Du Sac, WI [New]
Sauk-Prairie Airport, Prairie Du Sac, WI
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]]>Agencies
[Federal Register Volume 72, Number 173 (Friday, September 7, 2007)]
[Proposed Rules]
[Pages 51388-51391]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-17682]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-28413; Directorate Identifier 2007-NE-25-AD]
RIN 2120-AA64
Airworthiness Directives; General Electric Company (GE) CF6-80C2
and CF6-80E1 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 GE CF6-80C2 and CF6-80E1 series turbofan engines with fuel manifold
part numbers (P/Ns) 1303M31G12 and 1303M32G12 installed. This proposed
AD would require removing and discarding the loop clamps that assemble
the fuel manifold to the compressor rear frame (CRF) friction damper
brackets, visually inspecting the fuel manifold for wear at each clamp
location, and replacing the clamps with new, zero-time parts. This
proposed AD results from fuel manifold vibration during engine
operation that causes the loop clamps that assemble the manifold to the
CRF to deteriorate. Fourteen fuel leak events occurred over the past
several years. We are proposing this AD to prevent fuel leaks during
engine operation that could result in an under-cowl fire.
DATES: We must receive any comments on this proposed AD by November 6,
2007.
ADDRESSES: Use one of the following addresses to comment on this
proposed AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
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.
You may examine the comments on this proposed AD in the AD docket
on the Internet at https://dms.dot.gov., or in Room W12-140 on the
ground floor of the West Building, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Robert Green, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA
[[Page 51389]]
01803; telephone (781) 238-7754; 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-2007-28413;
Directorate Identifier 2007-NE-25-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 https://
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.). 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 https://dms.dot.gov.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
dms.dot.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
During a pre-flight inspection in November 2002, a manifold fuel
leak was found on a CF6-80C2B1F turbofan engine. This fuel leak
resulted from fuel manifold vibration during engine operation, which
caused the loop clamps that assemble the manifold to the CRF to
deteriorate. The cushion on the loop clamp wore away resulting in the
metal strip of the clamp rubbing into the fuel manifold. A fuel leak
resulted. The high surface temperature of the CRF during engine
operation could have ignited the leaking fuel resulting in an under-
cowl fire.
In 2003, GE issued service bulletins for the CF6-80C2 and CF6-
80E1series turbofan engines recommending repetitive visual inspection
of the fuel manifolds at intervals of 4,500 flight-hours (FH). Despite
these recommendations, five fuel leak events occurred in 2006; one
resulting in an under-cowl fire on a CF6-80C2B6F turbofan engine. There
have been three additional fuel leak events to date in 2007. A total of
thirteen CF6-80C2 series turbofan engine fuel leaks (November 2002
through May 2007) and one CF6-80E1 fuel leak (January 2007) have been
reported. Five of the recent events occurred within the 4,500 FH since
the last inspection.
Because of the increased number of fuel leak events and the low FH
intervals since the last inspection, this proposed AD would reduce the
initial re-inspection FH interval, and would require replacing the fuel
manifold loop clamps with new, zero-time parts at each inspection. This
proposed AD is necessary to prevent fuel leaks during engine operation
that could result in an under-cowl fire.
Differences Between the Proposed AD and the Manufacturer's Service
Information
In the manufacturer's original service bulletins, GE recommends
inspecting the fuel manifold for wear at 4,500 FH. However, the service
bulletins do not recommend replacing the loop clamps at each
inspection.
Because recent field events involving fuel leaks indicate a reduced
inspection interval is required, this AD would require removing loop
clamps and inspecting the fuel manifold according to the following
schedule:
For engines previously inspected using GEAE service
bulletins, SB 73-0226, dated March 5, 2003, for CF6-80C2 engines; or SB
73-0061, dated April 14, 2003, for CF6-80E1 engines, within 1,750 FH
since-last-inspection.
If used loop clamps or clamps of unknown heritage were
installed at last shop visit, within 1,750 FH since-last-shop-visit.
For first-run engines and engines with zero-time, new loop
clamps installed at last shop visit, within 7,500 FH.
For affected engines that have already exceeded the 1,750
FH initial inspection threshold, within 4,500 FH of the last inspection
or 4 months after the effective date of the AD, whichever comes first.
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
removing and discarding the loop clamps that assemble the fuel manifold
to the compressor rear frame damper (CRF) friction damper brackets,
visually inspecting the fuel manifold for wear at each loop clamp
location, and replacing the clamps with new, zero-time parts.
Costs of Compliance
We estimate that this proposed AD would affect 350 CF6-80C2 series
turbofan engines installed on airplanes of U.S. registry. We also
estimate that it would take about 4 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 $162 per engine. Based on these
figures, we estimate the total cost of the proposed AD to U.S.
operators for one manifold visual inspection and loop clamp replacement
to be $168,700.
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:
[[Page 51390]]
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, 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-2007-28413; Directorate
Identifier 2007-NE-25-AD.
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive
comments on this airworthiness directive (AD) action by November 6,
2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to:
(1) GE CF6-80C2A1, -80C2A2, -80C2A3, -80C2A5, -80C2A8, -80C2A5F,
-80C2B1, -80C2B2, -80C2B4, -80C2B6, -80C2B1F, -80C2B1F1, -80C2B1F2,
-80C2B2F, -80C2B3F, -80C2B4F, -80C2B5F, -80C2B6F, -80C2B6FA, -
80C2B7F, -80C2B8F, -80C2D1F, -80C2L1F, -80C2K1F turbofan engine
models configured with fuel manifold part numbers (P/Ns) 1303M31G12
and 1303M32G12. These engines are installed on, but not limited to
Boeing 747, 767, MD11, and Airbus A300 and A310 airplanes.
(2) This AD also applies to GE CF6-80E1A1, -80E1A2, -80E1A3, -
80E1A4, -80E1A4/B turbofan engine models with fuel manifold P/N's
1303M31G12 and 1303M32G12. These engines are installed on Airbus
A330 airplanes.
Unsafe Condition
(d) This AD results from fuel manifold vibration during engine
operation that causes the clamps that assemble the manifold to the
compressor rear frame (CRF) to deteriorate. We are issuing this AD
to prevent fuel leaks. The high surface temperature of the CRF could
ignite the leaking fuel resulting in an under-cowl fire.
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.
Removal and Replacement of Loop Clamps and Fuel Manifold Inspection
Compliance Times
(f) Remove and discard the loop clamps, P/N J1220G10, that
assemble the fuel manifold to the Compressor Rear Frame friction
damper brackets, inspect the fuel manifold for wear at each clamp
location as specified in paragraph (g) of this AD, and replace the
loop clamps with new, zero-time parts at each inspection. Use the
following schedule in Table 1 of this AD:
Table 1.--Inspection Schedule for Initial Inspections
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Then replace clamps and inspect
If: within:
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(1) The engine was previously inspected 1,750 flight hours (FH) time-
using GEAE service bulletins, SB 73- since-last-inspection (TSLI).
0226, dated March 5, 2003, for CF6-
80C2 engines; or SB 73-0061, dated
April 14, 2003, for CF6-80E1 engines.
(2) Used loop clamps or clamps of 1,750 FH time-since-last-shop-
unknown heritage were installed at visit.
last shop visit.
(3) The engine is a first-run engine or 7,500 FH since zero-time, new
is an engine with zero-time, new loop loop clamps were installed.
clamps previously installed.
(4) The engine has already exceeded the 4,500 FH TSLI, or 4 months
1,750 FH initial inspection threshold. after the effective date of
this AD, whichever occurs
first.
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Inspection of Fuel Manifold P/Ns 1303M31G12 and 1303M32G12
(g) Remove any tape applied to clamp locations. Visually inspect
the full circumference of the manifold at each clamp location.
(h) If the fuel manifold shows any signs of wear, determine the
depth of the wear as follows:
(1) Measure the outside diameter of the tube using a pinpoint
micrometer adjacent to the worn area.
(2) Measure the worn area at the smallest diameter.
(3) Subtract the measurement of the worn tube diameter from the
unworn diameter measurement. Allowable wear is 0.0035 inch.
(i) Before further flight, replace fuel manifolds with wear
greater than 0.010 inch.
(ii) Replace fuel manifolds with wear greater than 0.0035 inch,
but less than 0.010 inch, within 50 flight cycles.
Revise Air Carrier's Continuous Airworthiness Maintenance Program
(CAMP) and Airworthiness Limitation Section (ALS)
(i) Within 30 days of the effective date of this AD, revise the
air carrier's approved CAMP and ALS of Chapter 5 in the CF6-80C2 and
CF6-80E1 Instructions for Continued Airworthiness to add:
(1) Repetitive inspections of fuel manifolds, P/Ns 1303M31G12
and 1303M32G12, as detailed in paragraphs (g) and (h) of this AD, at
7,500 FH intervals.
(2) Mandatory removal of loop clamps, P/N J1220G10, that
assemble the fuel manifold, P/Ns 1303M31G12 and 1303M32G12, to the
Compressor Rear Frame friction damper brackets, at each inspection.
(3) Replacement of loop clamps, P/N J1220G10, with new, zero-
time parts, at each inspection.
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) GE service bulletins GEAE CF6-80C2 S/B 73-0226, dated March
5, 2003, and GEAE CF6-80E1 S/B 73-0061, dated April 14, 2003; and
the following General Electric engine manuals pertain to the subject
of this AD: CF6-80C2 Engine Manual GEK 92451; CF6-80C2L1F Engine
Manual GEK 112213; CF6-80C2K1F Engine Manual GEK 112721; and CF6-
80E1 Engine Manual GEK 99376.
(l) Contact Robert Green, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA, 01803; e-mail:
robert.green@faa.gov; telephone (781) 238-7754; fax (781) 238-7199,
for more information about this AD.
[[Page 51391]]
Issued in Burlington, Massachusetts, on August 30, 2007.
Thomas A. Boudreau,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E7-17682 Filed 9-6-07; 8:45 am]
BILLING CODE 4910-13-P
