Airworthiness Directives; General Electric Company (GE) CF6-80 Series Turbofan Engines, 30956-30959 [E7-10588]
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30956
Federal Register / Vol. 72, No. 107 / Tuesday, June 5, 2007 / Rules and Regulations
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the Federal Aviation Administration
amends 14 CFR part 39 as follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
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:
I
2007–12–09 General Electric Company:
Amendment 39–15087. Docket No.
FAA–2006–26585; Directorate Identifier
2006–NE–44–AD.
alternative methods of compliance for this
AD if requested using the procedures found
in 14 CFR 39.19.
Related Information
(i) Contact Tara Chaidez, Aerospace
Engineer, Engine Certification Office, FAA,
Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; e-mail: tara.chaidez@faa.gov;
telephone (781) 238–7773, fax (781) 238–
7199, for more information about this AD.
Issued in Burlington, Massachusetts, on
May 30, 2007.
Robert Ganley,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E7–10746 Filed 6–4–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
Effective Date
(a) This airworthiness directive (AD)
becomes effective July 10, 2007.
[Docket No. FAA–2006–26488; Directorate
Identifier 2006–NE–43–AD; Amendment 39–
15077; AD 2007–11–20]
Affected ADs
(b) None.
RIN 2120–AA64
Applicability
(c) This AD applies to General Electric
Company (GE) CF34–10E2A1, CF34–10E5,
CF34–10E5A1, CF34–10E6, CF34–10E6A1,
and CF34–10E7 turbofan engines. These
engines are installed on, but not limited to,
Embraer ERJ–190 and –195 airplanes.
cprice-sewell on PROD1PC71 with RULES
Unsafe Condition
(d) This AD results from GE’s evaluation of
the effects to the combustor case due to
installing version 5.10 software in the fullauthority digital electronic control (FADEC),
and revising the combustor case published
life limit. We are issuing this AD to prevent
uncontained combustor case failure resulting
in an in-flight engine shutdown and possible
damage to the airplane.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
30 days after the effective date of this AD,
unless the actions have already been done.
(f) Revise the published life limit in the
Airworthiness Limitations Section of the
CF34–10E Engine Manual, for combustor
cases, part number (P/N) 2070M47G02 and
P/N 2070M47G03, from 39,600 cycles-sincenew (CSN) to 24,600 CSN.
(g) The requirements of this AD have been
met when the engine manual changes are
made and operators have modified their
continuous airworthiness maintenance plans
to reflect the Engine Maintenance Program
requirements specified in the GE CF34–10E
Engine Manual.
Alternative Methods of Compliance
(h) The Manager, Engine Certification
Office, has the authority to approve
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Airworthiness Directives; General
Electric Company (GE) CF6–80 Series
Turbofan Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for GE
CF6–80 series turbofan engines with
fuel shroud retaining rings, part number
(P/N) J204P0084, installed. This AD
requires replacing those retaining rings
with a more robust design fuel shroud
retaining snap ring. This AD results
from two events of external engine fuel
leakage and a subsequent under-cowl
engine fire. We are issuing this AD to
prevent an under-cowl engine fire and
damage to the airplane during an engine
high vibration event.
DATES: This AD becomes effective July
10, 2007. The Director of the Federal
Register approved the incorporation by
reference of certain publications listed
in the regulations as of July 10, 2007.
ADDRESSES: You can get the service
information identified in this AD from
General Electric Company via Lockheed
Martin Technology Services, 10525
Chester Road, Suite C, Cincinnati, Ohio
45215, telephone (513) 672–8400, fax
(513) 672–8422.
You may examine the AD docket on
the Internet at https://dms.dot.gov or in
Room PL–401 on the plaza level of the
SUMMARY:
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Nassif Building, 400 Seventh Street,
SW., Washington, DC.
FOR FURTHER INFORMATION CONTACT:
James Lawrence, Aerospace Engineer,
Engine Certification Office, FAA, Engine
and Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; e-mail: james.lawrence@faa.gov;
telephone: (781) 238–7176, fax: (781)
238–7199.
SUPPLEMENTARY INFORMATION: The FAA
proposed to amend 14 CFR part 39 with
a proposed AD. The proposed AD
applies to GE CF6–80 series turbofan
engines with fuel shroud retaining rings,
part number (P/N) J204P0084, installed.
We published the proposed AD in the
Federal Register on February 15, 2007
(72 FR 7355). That action proposed to
require replacing those retaining rings
with a more robust design fuel shroud
retaining snap ring.
Examining the AD Docket
You may examine the docket that
contains the AD, any comments
received, and any final disposition in
person at the Docket Management
Facility 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 DMS receives
them.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments received.
Comment That Table 1 Compliance
Schedule Is Somewhat Difficult To
Follow
One commenter, GE, states that the
Table 1 compliance schedule in the
proposed AD is somewhat difficult to
follow. The commenter states that the
table needs lines or spaces added, to
separate some of the items in it, for
clarity.
We agree that the Table 1 compliance
schedule in the proposed AD is difficult
to follow. We have deleted the Table 1
compliance schedule from this AD,
based on comments received on the
proposed AD, and which are discussed
in the paragraphs that follow.
Request To Reduce the AD
Applicability
GE requests that we reduce the AD
applicability to only engines with the
drainless manifold configuration, since
the drained manifold configuration is
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Federal Register / Vol. 72, No. 107 / Tuesday, June 5, 2007 / Rules and Regulations
not subjected to high internal pressure.
If a fuel supply tube leaks internally, the
shroud contains the fuel, preventing an
external leak. We agree and reduced the
AD applicability in the AD to only
engines with the drainless manifold
configuration.
Request To Clarify Applicability
GE requests that we clarify the
applicability to state that engines built
at the factory during production
assembly with the drainless manifold
configuration, are also subject to the
requirements of the AD. We agree and
made that clarification in the AD.
SB Compliance Credit for CF6–80C2
Series Engines
GE suggests that we add a note or
statement to the compliance section
verifying that CF6–80C2 series engine
operators that have complied with a
previous revision of SB No. CF6–80C2
S/B 73–0337, are in compliance with
the AD. We agree. We added the ‘‘SB
Compliance Credit for CF6–80C2 Series
Engines’’ paragraph to the AD.
Request To Revise the Compliance
Section
KLM Royal Dutch Airlines requests
that we revise the section of the
compliance that states ‘‘Comply with
this AD as soon as one or more fuel
shroud retaining rings are removed from
the engine’’ to, ‘‘Comply with this AD
during next engine shop visit for any
reason.’’ The commenter states that the
AD action should be only at enginelevel and not on-wing.
We agree that the AD action should be
only at engine-level and not on-wing.
That part of the proposed compliance
section was for engines that had not
incorporated GE SB No. CF6–80C2 S/B
73–0253 (which eliminates the fuel
drain system manifold and introduces a
new drainless fuel manifold). The result
is that this AD now applies to only the
drainless manifold configuration. In
addition, we deleted the Table 1
compliance schedule because it is no
longer needed, clarified compliance
paragraph (g), and clarified applicability
paragraphs (c) and (d) in this AD.
cprice-sewell on PROD1PC71 with RULES
Request To Change Nomenclature
All Nippon Airways requests that we
change the proposed AD nomenclature
for the rings being removed, from
‘‘retaining snap ring’’ to ‘‘retaining
ring’’. We agree. We confirmed that GE’s
SBs refer to the removed rings as
‘‘retaining rings’’ and to the rings being
installed as ‘‘snap rings.’’ We changed
the nomenclature in the AD to reflect
that which the SBs use.
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Reference Table of Fuel Manifold Part
Numbers Added
For reference, we added a Table under
paragraph (f) which lists fuel manifold
production part numbers.
Conclusion
We have carefully reviewed the
available data, including the comments
received, and determined that air safety
and the public interest require adopting
the AD with the changes described
previously. We have determined that
these changes will neither increase the
economic burden on any operator nor
increase the scope of the AD.
Costs of Compliance
We estimate that this AD will affect
853 CF6–80 series turbofan engines
installed on airplanes of U.S. registry.
We also estimate that it will take about
12.5 work-hours per engine to perform
the actions, and that the average labor
rate is $80 per work-hour. Required
parts will cost about $72 per engine.
Based on these figures, we estimate the
total cost of the AD to U.S. operators to
be $914,416.
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 AD will
not have federalism implications under
Executive Order 13132. This AD will
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 this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
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30957
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
(3) Will 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 summary of the costs
to comply with this AD and placed it in
the AD Docket. 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.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the Federal Aviation Administration
amends 14 CFR part 39 as follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
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:
I
2007–11–20 General Electric Company:
Amendment 39–15077. Docket No.
FAA–2006–26488; Directorate Identifier
2006–NE–43–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective July 10, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the following
General Electric Company (GE) CF6–80C2
series turbofan engines that have
incorporated GE Service Bulletin (SB) No.
CF6–80C2 S/B 73–0253, or were built with
the drainless manifold configuration at the
factory during production assembly, and,
have one or more fuel shroud retaining rings,
part number (P/N) J204P0084, installed:
CF6–80C2A1,
CF6–80C2A2,
CF6–80C2A3,
CF6–80C2A5,
CF6–80C2A8,
CF6–80C2A5F,
CF6–80C2B1,
CF6–80C2B2,
CF6–80C2B4,
CF6–80C2B6,
CF6–80C2B1F,
CF6–80C2B2F,
CF6–80C2B4F,
CF6–80C2B5F,
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Federal Register / Vol. 72, No. 107 / Tuesday, June 5, 2007 / Rules and Regulations
CF6–80C2B6F,
CF6–80C2B6FA,
CF6–80C2B7F,
CF6–80C2B8F,
CF6–80C2D1F,
CF6–80C2L1F.
(d) This AD also applies to GE CF6–
80E1A1, CF6–80E1A2, CF6–80E1A3, CF6–
80E1A4, and CF6–80E1A4B turbofan engines
that have incorporated GE SB No. CF6–80E1
S/B 73–0026, or were built with the drainless
manifold configuration at the factory during
production assembly, and, have one or more
fuel shroud retaining rings, P/N J204P0084,
installed.
(e) These engines are installed on, but not
limited to, Airbus A300, A310, A330, Boeing
747, 767, and McDonnell Douglas MD11
airplanes.
(f) For reference, the following Table 1 lists
fuel manifold production P/Ns.
TABLE 1.—REFERENCE OF FUEL
MANIFOLD PRODUCTION P/NS
TABLE 1.—REFERENCE OF FUEL MANIFOLD PRODUCTION P/NS—Continued
CF6–80 E1 Series Engines
Drained Fuel Manifold
P/N
(left
side)
Drainless Fuel
Manifold P/N (left
side)
1700M34G01 ............
1303M31G12.
Drained Fuel Manifold P/N (right
side)
Drainless Fuel
Manifold P/N (right
side)
1700M35G02 ............
1303M32G12.
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.
Unsafe Condition
(g) This AD results from two events of
external engine fuel leakage and a subsequent
under-cowl engine fire. We are issuing this
AD to prevent an under-cowl engine fire and
damage to the airplane during an engine high
vibration event.
Compliance
CF6–80C2 Series Engines
Drained Fuel Manifold
P/N
(left
side)
1303M31G04
1303M31G06
1303M31G07
1303M31G08
1303M31G10 ............
Drained Fuel
Manifold (right side)
1303M32G04
1303M32G06
1303M32G07
1303M32G08
1303M32G10 ............
(h) You are responsible for having the
actions required by this AD performed at the
next engine shop visit for any reason after the
effective date of this AD, unless the actions
have already been done.
Drainless Fuel
Manifold P/N (left
side)
Replacement of Fuel Shroud Retaining Snap
Rings
1303M31G12.
Drainless Fuel
Manifold P/N (right
side)
1303M32G12.
SB Compliance Credit for CF6–80C2 Series
Engines
(l) This AD requires no further action if the
fuel shroud retaining snap rings were
installed in the CF6–80C2 series engines
before the effective date of this AD using GE
SB No. CF6–80C2 S/B 73–0337, Revision 2,
dated January 11, 2007, Revision 1, dated
April 19, 2005, or the Original, dated
November 30, 2004.
(i) Replace any fuel shroud retaining rings,
P/N J204P0084, with a fuel shroud retaining
snap ring, P/N 2186M12P01. Each engine has
a total of 30 rings installed.
(j) For CF6–80C2 series engines, use
paragraphs 3.A. through 3.C.(1)(b)2, of GE SB
No. CF6–80C2 S/B 73–0337, Revision 3,
dated February 5, 2007, to do the
replacements.
(k) For CF6–80E1 series engines, use
paragraphs 3.A. through 3.C.(1)(b)2, of GE SB
No. CF6–80E1 S/B 73–0075, Revision 1,
dated November 27, 2006, to do the
replacements.
Related Information
(n) Contact James Lawrence, Aerospace
Engineer, Engine Certification Office, FAA,
Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; e-mail: james.lawrence@faa.gov;
telephone (781) 238–7176; fax (781) 238–
7199, for more information about this AD.
Material Incorporated by Reference
(o) You must use the General Electric
Company service information specified in
Table 2 of this AD to perform the
replacements required by this AD. The
Director of the Federal Register approved the
incorporation by reference of the documents
listed in Table 2 of this AD in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51.
Contact General Electric Company via
Lockheed Martin Technology Services, 10525
Chester Road, Suite C, Cincinnati, Ohio
45215, telephone (513) 672–8400, fax (513)
672–8422, for a copy of this service
information. You may review copies at the
FAA, New England Region, Office of the
Regional Counsel, 12 New England Executive
Park, Burlington, MA; or at the National
Archives and Records Administration
(NARA). For information on the availability
of this material at NARA, call 202–741–6030,
or go to: https://www.archives.gov/federalregister/cfr/ibr-locations.html.
TABLE 2.—INCORPORATION BY REFERENCE
Page
CF6–80C2 S/B 73–0337 ......................................................................................................
Total Pages: 13
CF6–80E1 S/B 73–0075 ......................................................................................................
Total Pages: 13
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Service Bulletin No.
All ................
3
February 5, 2007.
All ................
1
November 27, 2006.
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Revision
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30959
Federal Register / Vol. 72, No. 107 / Tuesday, June 5, 2007 / Rules and Regulations
Issued in Burlington, Massachusetts, on
May 24, 2007.
Francis A. Favara,
Manager, Engine and Propeller Directorate,
Aircraft Certification Service.
[FR Doc. E7–10588 Filed 6–4–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–27713; Directorate
Identifier 2006–NM–240–AD; Amendment
39–15079; AD 2007–12–01]
RIN 2120–AA64
Airworthiness Directives; Bombardier
Model DHC–8–100, DHC–8–200, and
DHC–8–300 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for certain
Bombardier Model DHC–8–100, DHC–
8–200, and DHC–8–300 series airplanes.
This AD requires, for certain airplanes,
modification of the upper bearing of the
main landing gear (MLG) shock strut.
This AD also requires, for certain
airplanes, revising the de Havilland
DHC–8 Maintenance Program Manual to
include the MLG shock strut servicing
task. This AD results from reports of
over-extension of the MLG shock strut
piston, which allows the torque links to
go over-center and rest on the piston.
We are issuing this AD to prevent loss
in shock absorption during touchdown
and failure of the shock strut housing,
which could result in a subsequent loss
of directional control.
SUMMARY:
This AD becomes effective July
10, 2007.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of July 10, 2007.
ADDRESSES: You may examine the AD
docket on the Internet at https://
dms.dot.gov or in person at the Docket
Management Facility, U.S. Department
of Transportation, 400 Seventh Street,
SW., Nassif Building, Room PL–401,
Washington, DC.
Contact Bombardier, Inc., Bombardier
Regional Aircraft Division, 123 Garratt
Boulevard, Downsview, Ontario M3K
1Y5, Canada, for service information
identified in this AD.
FOR FURTHER INFORMATION CONTACT:
Mazdak Hobbi, Aerospace Engineer,
Airframe and Propulsion Branch, ANE–
171, FAA, New York Aircraft
Certification Office, 1600 Stewart
Avenue, Suite 410, Westbury, New York
11590; telephone (516) 228–7330; fax
(516) 794–5531.
SUPPLEMENTARY INFORMATION:
March 29, 2007 (72 FR 14721). That
NPRM proposed to require, for certain
airplanes, modification of the upper
bearing of the main landing gear (MLG)
shock strut. That NPRM proposed to
also require, for certain airplanes,
revising the de Havilland DHC–8
Maintenance Program Manual to
include the MLG shock strut servicing
task.
Examining the Docket
You may examine the airworthiness
directive (AD) docket on the Internet at
https://dms.dot.gov or in person at the
Docket Management Facility office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The Docket Management Facility office
(telephone (800) 647–5227) is located on
the plaza level of the Nassif Building at
the street address stated in the
ADDRESSES section.
We have revised this action to clarify
the appropriate procedure for notifying
the principal inspector before using any
approved AMOC on any airplane to
which the AMOC applies.
DATES:
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would
apply to certain Bombardier Model
DHC–8–100, DHC–8–200, and DHC–8–
300 series airplanes. That NPRM was
published in the Federal Register on
Comments
We provided the public the
opportunity to participate in the
development of this AD. We received no
comments on the NPRM or on the
determination of the cost to the public.
Clarification of Part Number
We have revised paragraph (i)(2) of
this final rule to correct a typographical
error, which resulted in an incorrect
part number. Paragraph (i)(2) should
have read ‘‘* * * 10129–5 or 10129–
553.’’
Clarification of Alternative Method of
Compliance (AMOC) Paragraph
Conclusion
We have carefully reviewed the
available data and determined that air
safety and the public interest require
adopting the AD with the changes
described previously. We have
determined that these changes will
neither increase the economic burden
on any operator nor increase the scope
of the AD.
Costs of Compliance
The following table provides the
estimated costs for U.S. operators to
comply with this AD.
ESTIMATED COSTS
Action
Work hours
cprice-sewell on PROD1PC71 with RULES
Modification ........................................................
Manual Revision ................................................
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.
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15:27 Jun 04, 2007
Jkt 211001
Average
labor rate
per hour
4
1
$80
80
Parts
$274
0
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
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Number of U.S.registered
airplanes
Cost per
airplane
$594
80
Up to 135 .........
135 ...................
Fleet cost
Up to $80,190.
$10,800.
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.
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Agencies
[Federal Register Volume 72, Number 107 (Tuesday, June 5, 2007)]
[Rules and Regulations]
[Pages 30956-30959]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-10]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-26488; Directorate Identifier 2006-NE-43-AD;
Amendment 39-15077; AD 2007-11-20]
RIN 2120-AA64
Airworthiness Directives; General Electric Company (GE) CF6-80
Series Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for GE
CF6-80 series turbofan engines with fuel shroud retaining rings, part
number (P/N) J204P0084, installed. This AD requires replacing those
retaining rings with a more robust design fuel shroud retaining snap
ring. This AD results from two events of external engine fuel leakage
and a subsequent under-cowl engine fire. We are issuing this AD to
prevent an under-cowl engine fire and damage to the airplane during an
engine high vibration event.
DATES: This AD becomes effective July 10, 2007. The Director of the
Federal Register approved the incorporation by reference of certain
publications listed in the regulations as of July 10, 2007.
ADDRESSES: You can get the service information identified in this AD
from General Electric Company via Lockheed Martin Technology Services,
10525 Chester Road, Suite C, Cincinnati, Ohio 45215, telephone (513)
672-8400, fax (513) 672-8422.
You may examine the AD docket on the Internet at https://dms.dot.gov
or in Room PL-401 on the plaza level of the Nassif Building, 400
Seventh Street, SW., Washington, DC.
FOR FURTHER INFORMATION CONTACT: James Lawrence, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803; e-mail:
james.lawrence@faa.gov; telephone: (781) 238-7176, fax: (781) 238-7199.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39
with a proposed AD. The proposed AD applies to GE CF6-80 series
turbofan engines with fuel shroud retaining rings, part number (P/N)
J204P0084, installed. We published the proposed AD in the Federal
Register on February 15, 2007 (72 FR 7355). That action proposed to
require replacing those retaining rings with a more robust design fuel
shroud retaining snap ring.
Examining the AD Docket
You may examine the docket that contains the AD, any comments
received, and any final disposition in person at the Docket Management
Facility 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 DMS receives them.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments received.
Comment That Table 1 Compliance Schedule Is Somewhat Difficult To
Follow
One commenter, GE, states that the Table 1 compliance schedule in
the proposed AD is somewhat difficult to follow. The commenter states
that the table needs lines or spaces added, to separate some of the
items in it, for clarity.
We agree that the Table 1 compliance schedule in the proposed AD is
difficult to follow. We have deleted the Table 1 compliance schedule
from this AD, based on comments received on the proposed AD, and which
are discussed in the paragraphs that follow.
Request To Reduce the AD Applicability
GE requests that we reduce the AD applicability to only engines
with the drainless manifold configuration, since the drained manifold
configuration is
[[Page 30957]]
not subjected to high internal pressure. If a fuel supply tube leaks
internally, the shroud contains the fuel, preventing an external leak.
We agree and reduced the AD applicability in the AD to only engines
with the drainless manifold configuration.
Request To Clarify Applicability
GE requests that we clarify the applicability to state that engines
built at the factory during production assembly with the drainless
manifold configuration, are also subject to the requirements of the AD.
We agree and made that clarification in the AD.
SB Compliance Credit for CF6-80C2 Series Engines
GE suggests that we add a note or statement to the compliance
section verifying that CF6-80C2 series engine operators that have
complied with a previous revision of SB No. CF6-80C2 S/B 73-0337, are
in compliance with the AD. We agree. We added the ``SB Compliance
Credit for CF6-80C2 Series Engines'' paragraph to the AD.
Request To Revise the Compliance Section
KLM Royal Dutch Airlines requests that we revise the section of the
compliance that states ``Comply with this AD as soon as one or more
fuel shroud retaining rings are removed from the engine'' to, ``Comply
with this AD during next engine shop visit for any reason.'' The
commenter states that the AD action should be only at engine-level and
not on-wing.
We agree that the AD action should be only at engine-level and not
on-wing. That part of the proposed compliance section was for engines
that had not incorporated GE SB No. CF6-80C2 S/B 73-0253 (which
eliminates the fuel drain system manifold and introduces a new
drainless fuel manifold). The result is that this AD now applies to
only the drainless manifold configuration. In addition, we deleted the
Table 1 compliance schedule because it is no longer needed, clarified
compliance paragraph (g), and clarified applicability paragraphs (c)
and (d) in this AD.
Request To Change Nomenclature
All Nippon Airways requests that we change the proposed AD
nomenclature for the rings being removed, from ``retaining snap ring''
to ``retaining ring''. We agree. We confirmed that GE's SBs refer to
the removed rings as ``retaining rings'' and to the rings being
installed as ``snap rings.'' We changed the nomenclature in the AD to
reflect that which the SBs use.
Reference Table of Fuel Manifold Part Numbers Added
For reference, we added a Table under paragraph (f) which lists
fuel manifold production part numbers.
Conclusion
We have carefully reviewed the available data, including the
comments received, and determined that air safety and the public
interest require adopting the AD with the changes described previously.
We have determined that these changes will neither increase the
economic burden on any operator nor increase the scope of the AD.
Costs of Compliance
We estimate that this AD will affect 853 CF6-80 series turbofan
engines installed on airplanes of U.S. registry. We also estimate that
it will take about 12.5 work-hours per engine to perform the actions,
and that the average labor rate is $80 per work-hour. Required parts
will cost about $72 per engine. Based on these figures, we estimate the
total cost of the AD to U.S. operators to be $914,416.
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 AD will not have federalism
implications under Executive Order 13132. This AD will 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 this AD:
(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) Will 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 summary of the costs to comply with this AD and
placed it in the AD Docket. 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.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the Federal Aviation Administration amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
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]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive:
2007-11-20 General Electric Company: Amendment 39-15077. Docket No.
FAA-2006-26488; Directorate Identifier 2006-NE-43-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective July 10,
2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to the following General Electric Company
(GE) CF6-80C2 series turbofan engines that have incorporated GE
Service Bulletin (SB) No. CF6-80C2 S/B 73-0253, or were built with
the drainless manifold configuration at the factory during
production assembly, and, have one or more fuel shroud retaining
rings, part number (P/N) J204P0084, installed:
CF6-80C2A1,
CF6-80C2A2,
CF6-80C2A3,
CF6-80C2A5,
CF6-80C2A8,
CF6-80C2A5F,
CF6-80C2B1,
CF6-80C2B2,
CF6-80C2B4,
CF6-80C2B6,
CF6-80C2B1F,
CF6-80C2B2F,
CF6-80C2B4F,
CF6-80C2B5F,
[[Page 30958]]
CF6-80C2B6F,
CF6-80C2B6FA,
CF6-80C2B7F,
CF6-80C2B8F,
CF6-80C2D1F,
CF6-80C2L1F.
(d) This AD also applies to GE CF6-80E1A1, CF6-80E1A2, CF6-
80E1A3, CF6-80E1A4, and CF6-80E1A4B turbofan engines that have
incorporated GE SB No. CF6-80E1 S/B 73-0026, or were built with the
drainless manifold configuration at the factory during production
assembly, and, have one or more fuel shroud retaining rings, P/N
J204P0084, installed.
(e) These engines are installed on, but not limited to, Airbus
A300, A310, A330, Boeing 747, 767, and McDonnell Douglas MD11
airplanes.
(f) For reference, the following Table 1 lists fuel manifold
production P/Ns.
Table 1.--Reference of Fuel Manifold Production P/Ns
------------------------------------------------------------------------
------------------------------------------------------------------------
CF6-80C2 Series Engines
------------------------------------------------------------------------
Drained Fuel Manifold P/N (left Drainless Fuel Manifold P/N
side) (left side)
------------------------------------------------------------------------
1303M31G04
1303M31G06
1303M31G07
1303M31G08
1303M31G10.......................... 1303M31G12.
------------------------------------------------------------------------
Drained Fuel Manifold (right side) Drainless Fuel Manifold P/N
(right side)
------------------------------------------------------------------------
1303M32G04
1303M32G06
1303M32G07
1303M32G08
1303M32G10.......................... 1303M32G12.
------------------------------------------------------------------------
CF6-80 E1 Series Engines
------------------------------------------------------------------------
Drained Fuel Manifold P/N (left Drainless Fuel Manifold P/N
side) (left side)
------------------------------------------------------------------------
1700M34G01.......................... 1303M31G12.
------------------------------------------------------------------------
Drained Fuel Manifold P/N (right Drainless Fuel Manifold P/N
side) (right side)
------------------------------------------------------------------------
1700M35G02.......................... 1303M32G12.
------------------------------------------------------------------------
Unsafe Condition
(g) This AD results from two events of external engine fuel
leakage and a subsequent under-cowl engine fire. We are issuing this
AD to prevent an under-cowl engine fire and damage to the airplane
during an engine high vibration event.
Compliance
(h) You are responsible for having the actions required by this
AD performed at the next engine shop visit for any reason after the
effective date of this AD, unless the actions have already been
done.
Replacement of Fuel Shroud Retaining Snap Rings
(i) Replace any fuel shroud retaining rings, P/N J204P0084, with
a fuel shroud retaining snap ring, P/N 2186M12P01. Each engine has a
total of 30 rings installed.
(j) For CF6-80C2 series engines, use paragraphs 3.A. through
3.C.(1)(b)2, of GE SB No. CF6-80C2 S/B 73-0337, Revision 3, dated
February 5, 2007, to do the replacements.
(k) For CF6-80E1 series engines, use paragraphs 3.A. through
3.C.(1)(b)2, of GE SB No. CF6-80E1 S/B 73-0075, Revision 1, dated
November 27, 2006, to do the replacements.
SB Compliance Credit for CF6-80C2 Series Engines
(l) This AD requires no further action if the fuel shroud
retaining snap rings were installed in the CF6-80C2 series engines
before the effective date of this AD using GE SB No. CF6-80C2 S/B
73-0337, Revision 2, dated January 11, 2007, Revision 1, dated April
19, 2005, or the Original, dated November 30, 2004.
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 James Lawrence, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; e-mail:
james.lawrence@faa.gov; telephone (781) 238-7176; fax (781) 238-
7199, for more information about this AD.
Material Incorporated by Reference
(o) You must use the General Electric Company service
information specified in Table 2 of this AD to perform the
replacements required by this AD. The Director of the Federal
Register approved the incorporation by reference of the documents
listed in Table 2 of this AD in accordance with 5 U.S.C. 552(a) and
1 CFR part 51. Contact General Electric Company via Lockheed Martin
Technology Services, 10525 Chester Road, Suite C, Cincinnati, Ohio
45215, telephone (513) 672-8400, fax (513) 672-8422, for a copy of
this service information. You may review copies at the FAA, New
England Region, Office of the Regional Counsel, 12 New England
Executive Park, Burlington, MA; or at the National Archives and
Records Administration (NARA). For information on the availability
of this material at NARA, call 202-741-6030, or go to: https://
www.archives.gov/federal-register/cfr/ibr-locations.html.
Table 2.--Incorporation by Reference
----------------------------------------------------------------------------------------------------------------
Service Bulletin No. Page Revision Date
----------------------------------------------------------------------------------------------------------------
CF6-80C2 S/B 73-0337................ All..................... 3 February 5, 2007.
Total Pages: 13
CF6-80E1 S/B 73-0075................ All..................... 1 November 27, 2006.
Total Pages: 13
----------------------------------------------------------------------------------------------------------------
[[Page 30959]]
Issued in Burlington, Massachusetts, on May 24, 2007.
Francis A. Favara,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. E7-10588 Filed 6-4-07; 8:45 am]
BILLING CODE 4910-13-P