Airworthiness Directives; General Electric (GE) CF6-80E1 Series Turbofan Engines, 45308-45310 [E7-15701]
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45308
Federal Register / Vol. 72, No. 156 / Tuesday, August 14, 2007 / Rules and Regulations
TABLE 2.—REQUIRED MATERIAL INCORPORATED BY REFERENCE
Airbus service information
Date
All Operators Telex A300–600–55A6032 .........................................................................................................................................
All Operators Telex A310–55A2033 .................................................................................................................................................
Service Bulletin A300–55–6039, including Appendix 01 ..................................................................................................................
Service Bulletin A310–55–2040, including Appendix 01 ..................................................................................................................
If you accomplish the optional actions
specified in this AD, you must use the
service documents identified in Table 3 of
June
June
June
June
23, 2004.
23, 2004.
7, 2006.
7, 2006.
this AD to perform those actions, unless the
AD specifies otherwise.
TABLE 3.—OPTIONAL MATERIAL INCORPORATED BY REFERENCE
Airbus service information
Date
Service Bulletin A300–55–6040 .......................................................................................................................................................
Service Bulletin A310–55–2041 .......................................................................................................................................................
(1) The Director of the Federal Register
approved the incorporation by reference of
the documents identified in Table 4 of this
June 5, 2006.
June 5, 2006.
AD in accordance with 5 U.S.C. 552(a) and
1 CFR part 51.
TABLE 4.—NEW MATERIAL INCORPORATED BY REFERENCE
Airbus service information
Service
Service
Service
Service
Bulletin
Bulletin
Bulletin
Bulletin
Date
A300–55–6039, including Appendix 01 ..................................................................................................................
A300–55–6040 .......................................................................................................................................................
A310–55–2040, including Appendix 01 ..................................................................................................................
A310–55–2041 .......................................................................................................................................................
(2) On February 3, 2006 (70 FR 77301,
December 30, 2005), the Director of the
Federal Register approved the incorporation
June
June
June
June
7,
5,
7,
5,
2006.
2006.
2006.
2006.
by reference of the service documents
identified in Table 5 of this AD.
TABLE 5.—MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE
Airbus service information
Date
All Operators Telex A300–600–55A6032 .........................................................................................................................................
All Operators Telex A310–55A2033 .................................................................................................................................................
(3) Contact Airbus, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France, for a
copy of this service information. You may
review copies at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington; 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.
sroberts on PROD1PC70 with RULES
Issued in Renton, Washington, on August
2, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–15589 Filed 8–13–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–21238; Directorate
Identifier 2005–NE–12–AD; Amendment 39–
15159; AD 2007–17–01]
RIN 2120–AA64
Airworthiness Directives; General
Electric (GE) CF6–80E1 Series
Turbofan Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD) for
General Electric (GE) CF6–80E1 series
VerDate Aug<31>2005
15:59 Aug 13, 2007
Jkt 211001
PO 00000
Frm 00004
Fmt 4700
Sfmt 4700
June 23, 2004.
June 23, 2004.
turbofan engines. That AD currently
requires removing electronic control
unit (ECU) software version E.1.M. or
earlier installed software, and installing
improved software for the ECU. This AD
requires removing software version
E.1.N or earlier from the engine ECU.
Engines with the new version software
will have increased margin to flameout.
This AD results from reports of engine
flameout events during flight, including
reports of events where all engines
simultaneously experienced a flameout
or other adverse operation. Although the
root cause investigation is not yet
complete, we believe that exposure to
ice crystals during flight is associated
with these flameout events. We are
issuing this AD to minimize the
potential of an all-engine flameout event
caused by ice accretion and shedding
during flight.
E:\FR\FM\14AUR1.SGM
14AUR1
Federal Register / Vol. 72, No. 156 / Tuesday, August 14, 2007 / Rules and Regulations
Effective August 29, 2007.
We must receive any comments on
this AD by October 15, 2007.
ADDRESSES: Use one of the following
addresses to comment on this 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.
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 the service
information identified in this AD.
FOR FURTHER INFORMATION CONTACT: John
Golinski, Aerospace Engineer, Engine
Certification Office, FAA, Engine and
Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803;
e-mail: john.golinski@faa.gov;
telephone: (781) 238–7135, fax: (781)
238–7199.
SUPPLEMENTARY INFORMATION: The FAA
amends 14 CFR part 39 by superseding
AD 2005–10–16, Amendment 39–14093
(70 FR 28806, May 19, 2005). That AD
requires improved software version
E.1.N to be installed into the ECU. That
AD was the result of an uncommanded
engine acceleration event caused by a
failure of the ECU digital interface unit.
That condition, if not corrected, could
result in an undetected failure of the
ECU digital interface unit, leading to
uncommanded acceleration to the
overspeed limit without response to
throttle commands. The airplane could
then experience asymmetric thrust.
DATES:
simultaneously experienced a flameout.
Some of these events had high pressure
compressor blade damage that may have
been caused by impact with shedding
ice. In all events, the engines restarted
and continued to operate normally for
the remainder of the flight.
This AD addresses only the CF6–80E1
series turbofan engines, installed on
Airbus Industrie A330 series airplanes.
We believe the CF6–80E1 series
turbofan engines are susceptible to
flameouts caused by ice accretion and
shedding into the engine during flight.
Similar AD actions for CF6–80C2 series
engines may be forthcoming.
We view an all-engine flameout event
as an unsafe condition particularly for
low-altitude events, or other factors that
might result in the inability to restart
the engines and regain control of the
airplane. Since some aspects of this
problem are not completely understood,
this proposed AD is considered an
interim action due to GE’s on-going
investigation. Future AD action might
become necessary based on the results
of the investigation and field
experience. This condition of
insufficient margin to engine flameout
due to ice accretion and shedding
during flight, if not addressed, could
result in an all-engine flameout event
during flight.
sroberts on PROD1PC70 with RULES
Actions Since AD 2005–10–16 Was
Issued
Relevant Service Information
We have reviewed and approved the
technical contents of GE Service
Bulletin (SB) No. CF6–80E1 S/B 73–
0091, Revision 1, dated June 26, 2007.
That SB describes procedures for
removing certain software versions from
the ECU, and installing a software
version that is FAA-approved. The new
FAA-approved software version
described in the SB modifies the
variable bleed valve schedule, which
will provide an increased margin to
flameout. This increased margin is
expected to reduce the rate of flameout
occurrences due to ice accretion and
shedding during flight. The new FAAapproved software version incorporates
the software improvements required by
AD 2005–10–16, which prevent failure
of the ECU digital interface unit.
Since AD 2005–10–16 was issued, GE
CF6–80E1 and CF6–80C2 series
turbofan engines continue to experience
flameout events that are due to ice
accretion and shedding into the engine
during flight. Although the investigation
is not yet complete, we believe that the
ice accretion is caused by exposure to
ice crystals during flight. Industry
reports 35 airplane flameout events,
including reports of multi-engine events
where all engines on the airplane
FAA’s Determination and Requirements
of This AD
Although no airplanes that are
registered in the United States use these
CF6–80E1 series turbofan engines, the
possibility exists that the engines could
be used on airplanes that are registered
in the United States in the future. The
unsafe condition described previously is
likely to exist or develop on other CF6–
80E1 series turbofan engines of the same
type design. We are issuing this AD to
VerDate Aug<31>2005
15:59 Aug 13, 2007
Jkt 211001
PO 00000
Frm 00005
Fmt 4700
Sfmt 4700
45309
minimize the potential of an all-engine
flameout event caused by ice accretion
and shedding during flight. This AD
requires removing certain software
versions from the engine ECU.
FAA’s Determination of the Effective
Date
Since there are currently no domestic
operators of this engine model, notice
and opportunity for public comment
before issuing this AD are unnecessary.
A situation exists that allows the
immediate adoption of this regulation.
Interim Action
These actions are interim actions due
to the on-going investigation. We may
take further rulemaking actions in the
future, based on the results of the
investigation and field experience.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety and
was not preceded by notice and an
opportunity for public comment;
however, we invite you to send us any
written relevant data, views, or
arguments regarding this AD. Send your
comments to an address listed under
ADDRESSES. Include ‘‘AD Docket No.
FAA–2005–21238; Directorate Identifier
2005–NE–12–AD’’ in the subject line of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the rule that might suggest a
need to modify it.
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 AD. Using the
search function of the DMS 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 AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone (800) 647–5527) is
E:\FR\FM\14AUR1.SGM
14AUR1
45310
Federal Register / Vol. 72, No. 156 / Tuesday, August 14, 2007 / Rules and Regulations
provided in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
PART 39—AIRWORTHINESS
DIRECTIVES
TABLE 1.—REMOVAL OF ECU
SOFTWARE VERSIONS—Continued
1. The authority citation for part 39
continues to read as follows:
Software
version
Installed in ECU part No.
(6) E.1.J ......
1799M99P08, 1799M99P09,
1851M74P02, 1851M80P02
1799M99P10, 1851M74P03,
1851M80P03, 1960M84P01
1799M99P11, 1851M74P04,
1851M80P04, 1960M84P02
1799M99P12, 1851M74P05,
1851M80P05, 1960M84P03
1799M99P13, 1851M74P06,
1851M80P06, 1960M84P04,
2043M29P01, 2043M29P02
I
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 the
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.
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
2. The FAA amends § 39.13 by
removing Amendment 39–14093 (70 FR
28806, May 19, 2005), and by adding a
new airworthiness directive,
Amendment 39–15159, to read as
follows:
I
2007–17–01 General Electric Company:
Amendment 39–15159. Docket No.
FAA–2005–21238; Directorate Identifier
2005–NE–12–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective August 29, 2007.
Affected ADs
(b) This AD supersedes AD 2005–10–16.
Applicability
(c) This AD applies to General Electric
Company (GE) CF6–80E1A1, CF6–80E1A2,
CF6–80E1A3, CF6–80E1A4, and CF6–
80E1A4/B turbofan engines, installed on
Airbus Industrie A330 series airplanes.
Unsafe Condition
(d) This AD results from reports of engine
flameout events during flight, including
reports of events where all engines
simultaneously experienced a flameout or
other adverse operation. We are issuing this
AD to minimize the potential of an all-engine
flameout event caused by ice accretion and
shedding during flight. Exposure to ice
crystals during flight is believed to be
associated with these flameout events.
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.
Interim Action
(f) These actions are interim actions due to
the on-going investigation, and we may take
further rulemaking actions in the future
based on the results of the investigation and
field experience.
Engine Electronic Control Unit (ECU)
Software Removal
(g) Before January 31, 2008, remove the
following software versions from the ECUs:
TABLE 1.—REMOVAL OF ECU
SOFTWARE VERSIONS
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
sroberts on PROD1PC70 with RULES
Adoption of the Amendment
VerDate Aug<31>2005
15:59 Aug 13, 2007
Jkt 211001
Software
version
(1)
(2)
(3)
(4)
(5)
E.1.D ......
E.1.F ......
E.1.G .....
E.1.H ......
E.1.I .......
PO 00000
Frm 00006
Under the authority delegated to me
by the Administrator, the Federal
Aviation Administration amends part 39
of the Federal Aviation Regulations (14
CFR part 39) as follows:
I
[Amended]
Installed in ECU part No.
1799M99P01
1799M99P03
1799M99P04
1799M99P05
1799M99P06, 1799M99P07,
1851M74P01, 1851M80P01
Fmt 4700
Sfmt 4700
(7) E.1.K ......
(8) E.1.L ......
(9) E.1.M .....
(10) E.1.N ....
Previous Software Versions of ECU Software
(h) Until January 31, 2008, once an ECU
containing a software version not listed in
Table 1 of this AD is installed on an engine,
that ECU can be replaced with an ECU
containing a previous version of software
listed in Table 1.
(i) Once the software version listed in
Table 1 of this AD has been removed and
new FAA-approved software version is
installed in an ECU, reverting to those older
software versions in that ECU is prohibited.
(j) After January 31, 2008, use of an ECU
with a software version listed in Table 1 of
this AD is prohibited.
Alternative Methods of Compliance
(k) 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.
Special Flight Permits
(l) Special flight permits are not
authorized.
Related Information
(m) Information on removing ECU software
and installing new software, which provides
increased margin to flameout, can be found
in GE Service Bulletin No. CF6–80E1 S/B 73–
0091, Revision 1, dated June 26, 2007.
(n) Contact John Golinski, Aerospace
Engineer, Engine Certification Office, FAA,
Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; e-mail: john.golinski@faa.gov;
telephone: (781) 238–7135, fax: (781) 238–
7199, for more information about this AD.
Issued in Burlington, Massachusetts, on
August 6, 2007.
Francis A. Favara,
Manager, Engine and Propeller Directorate,
Aircraft Certification Service.
[FR Doc. E7–15701 Filed 8–13–07; 8:45 am]
BILLING CODE 4910–13–P
E:\FR\FM\14AUR1.SGM
14AUR1
]]>Agencies
[Federal Register Volume 72, Number 156 (Tuesday, August 14, 2007)]
[Rules and Regulations]
[Pages 45308-45310]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-15701]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-21238; Directorate Identifier 2005-NE-12-AD;
Amendment 39-15159; AD 2007-17-01]
RIN 2120-AA64
Airworthiness Directives; General Electric (GE) CF6-80E1 Series
Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD) for General Electric (GE) CF6-80E1 series turbofan engines. That
AD currently requires removing electronic control unit (ECU) software
version E.1.M. or earlier installed software, and installing improved
software for the ECU. This AD requires removing software version E.1.N
or earlier from the engine ECU. Engines with the new version software
will have increased margin to flameout. This AD results from reports of
engine flameout events during flight, including reports of events where
all engines simultaneously experienced a flameout or other adverse
operation. Although the root cause investigation is not yet complete,
we believe that exposure to ice crystals during flight is associated
with these flameout events. We are issuing this AD to minimize the
potential of an all-engine flameout event caused by ice accretion and
shedding during flight.
[[Page 45309]]
DATES: Effective August 29, 2007.
We must receive any comments on this AD by October 15, 2007.
ADDRESSES: Use one of the following addresses to comment on this 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.
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 the service
information identified in this AD.
FOR FURTHER INFORMATION CONTACT: John Golinski, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803; e-mail:
john.golinski@faa.gov; telephone: (781) 238-7135, fax: (781) 238-7199.
SUPPLEMENTARY INFORMATION: The FAA amends 14 CFR part 39 by superseding
AD 2005-10-16, Amendment 39-14093 (70 FR 28806, May 19, 2005). That AD
requires improved software version E.1.N to be installed into the ECU.
That AD was the result of an uncommanded engine acceleration event
caused by a failure of the ECU digital interface unit. That condition,
if not corrected, could result in an undetected failure of the ECU
digital interface unit, leading to uncommanded acceleration to the
overspeed limit without response to throttle commands. The airplane
could then experience asymmetric thrust.
Actions Since AD 2005-10-16 Was Issued
Since AD 2005-10-16 was issued, GE CF6-80E1 and CF6-80C2 series
turbofan engines continue to experience flameout events that are due to
ice accretion and shedding into the engine during flight. Although the
investigation is not yet complete, we believe that the ice accretion is
caused by exposure to ice crystals during flight. Industry reports 35
airplane flameout events, including reports of multi-engine events
where all engines on the airplane simultaneously experienced a
flameout. Some of these events had high pressure compressor blade
damage that may have been caused by impact with shedding ice. In all
events, the engines restarted and continued to operate normally for the
remainder of the flight.
This AD addresses only the CF6-80E1 series turbofan engines,
installed on Airbus Industrie A330 series airplanes. We believe the
CF6-80E1 series turbofan engines are susceptible to flameouts caused by
ice accretion and shedding into the engine during flight. Similar AD
actions for CF6-80C2 series engines may be forthcoming.
We view an all-engine flameout event as an unsafe condition
particularly for low-altitude events, or other factors that might
result in the inability to restart the engines and regain control of
the airplane. Since some aspects of this problem are not completely
understood, this proposed AD is considered an interim action due to
GE's on-going investigation. Future AD action might become necessary
based on the results of the investigation and field experience. This
condition of insufficient margin to engine flameout due to ice
accretion and shedding during flight, if not addressed, could result in
an all-engine flameout event during flight.
Relevant Service Information
We have reviewed and approved the technical contents of GE Service
Bulletin (SB) No. CF6-80E1 S/B 73-0091, Revision 1, dated June 26,
2007. That SB describes procedures for removing certain software
versions from the ECU, and installing a software version that is FAA-
approved. The new FAA-approved software version described in the SB
modifies the variable bleed valve schedule, which will provide an
increased margin to flameout. This increased margin is expected to
reduce the rate of flameout occurrences due to ice accretion and
shedding during flight. The new FAA-approved software version
incorporates the software improvements required by AD 2005-10-16, which
prevent failure of the ECU digital interface unit.
FAA's Determination and Requirements of This AD
Although no airplanes that are registered in the United States use
these CF6-80E1 series turbofan engines, the possibility exists that the
engines could be used on airplanes that are registered in the United
States in the future. The unsafe condition described previously is
likely to exist or develop on other CF6-80E1 series turbofan engines of
the same type design. We are issuing this AD to minimize the potential
of an all-engine flameout event caused by ice accretion and shedding
during flight. This AD requires removing certain software versions from
the engine ECU.
FAA's Determination of the Effective Date
Since there are currently no domestic operators of this engine
model, notice and opportunity for public comment before issuing this AD
are unnecessary. A situation exists that allows the immediate adoption
of this regulation.
Interim Action
These actions are interim actions due to the on-going
investigation. We may take further rulemaking actions in the future,
based on the results of the investigation and field experience.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety and was not preceded by notice and an opportunity for public
comment; however, we invite you to send us any written relevant data,
views, or arguments regarding this AD. Send your comments to an address
listed under ADDRESSES. Include ``AD Docket No. FAA-2005-21238;
Directorate Identifier 2005-NE-12-AD'' in the subject line of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify it.
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 AD. Using the search function of the DMS 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 AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Operations office (telephone (800) 647-5527) is
[[Page 45310]]
provided in the ADDRESSES section. Comments will be available in the AD
docket shortly after receipt.
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 the 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, Safety.
Adoption of the Amendment
0
Under the authority delegated to me by the Administrator, the Federal
Aviation Administration amends part 39 of the Federal Aviation
Regulations (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 removing Amendment 39-14093 (70 FR
28806, May 19, 2005), and by adding a new airworthiness directive,
Amendment 39-15159, to read as follows:
2007-17-01 General Electric Company: Amendment 39-15159. Docket No.
FAA-2005-21238; Directorate Identifier 2005-NE-12-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective August
29, 2007.
Affected ADs
(b) This AD supersedes AD 2005-10-16.
Applicability
(c) This AD applies to General Electric Company (GE) CF6-80E1A1,
CF6-80E1A2, CF6-80E1A3, CF6-80E1A4, and CF6-80E1A4/B turbofan
engines, installed on Airbus Industrie A330 series airplanes.
Unsafe Condition
(d) This AD results from reports of engine flameout events
during flight, including reports of events where all engines
simultaneously experienced a flameout or other adverse operation. We
are issuing this AD to minimize the potential of an all-engine
flameout event caused by ice accretion and shedding during flight.
Exposure to ice crystals during flight is believed to be associated
with these flameout events.
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.
Interim Action
(f) These actions are interim actions due to the on-going
investigation, and we may take further rulemaking actions in the
future based on the results of the investigation and field
experience.
Engine Electronic Control Unit (ECU) Software Removal
(g) Before January 31, 2008, remove the following software
versions from the ECUs:
Table 1.--Removal of ECU Software Versions
------------------------------------------------------------------------
Software version Installed in ECU part No.
------------------------------------------------------------------------
(1) E.1.D........................ 1799M99P01
(2) E.1.F........................ 1799M99P03
(3) E.1.G........................ 1799M99P04
(4) E.1.H........................ 1799M99P05
(5) E.1.I........................ 1799M99P06, 1799M99P07, 1851M74P01,
1851M80P01
(6) E.1.J........................ 1799M99P08, 1799M99P09, 1851M74P02,
1851M80P02
(7) E.1.K........................ 1799M99P10, 1851M74P03, 1851M80P03,
1960M84P01
(8) E.1.L........................ 1799M99P11, 1851M74P04, 1851M80P04,
1960M84P02
(9) E.1.M........................ 1799M99P12, 1851M74P05, 1851M80P05,
1960M84P03
(10) E.1.N....................... 1799M99P13, 1851M74P06, 1851M80P06,
1960M84P04, 2043M29P01, 2043M29P02
------------------------------------------------------------------------
Previous Software Versions of ECU Software
(h) Until January 31, 2008, once an ECU containing a software
version not listed in Table 1 of this AD is installed on an engine,
that ECU can be replaced with an ECU containing a previous version
of software listed in Table 1.
(i) Once the software version listed in Table 1 of this AD has
been removed and new FAA-approved software version is installed in
an ECU, reverting to those older software versions in that ECU is
prohibited.
(j) After January 31, 2008, use of an ECU with a software
version listed in Table 1 of this AD is prohibited.
Alternative Methods of Compliance
(k) 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.
Special Flight Permits
(l) Special flight permits are not authorized.
Related Information
(m) Information on removing ECU software and installing new
software, which provides increased margin to flameout, can be found
in GE Service Bulletin No. CF6-80E1 S/B 73-0091, Revision 1, dated
June 26, 2007.
(n) Contact John Golinski, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; e-mail:
john.golinski@faa.gov; telephone: (781) 238-7135, fax: (781) 238-
7199, for more information about this AD.
Issued in Burlington, Massachusetts, on August 6, 2007.
Francis A. Favara,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. E7-15701 Filed 8-13-07; 8:45 am]
BILLING CODE 4910-13-P
