Airworthiness Directives; General Electric Company (GE) CF6-80C2B Series Turbofan Engines, 31174-31176 [E7-10745]
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31174
Federal Register / Vol. 72, No. 108 / Wednesday, June 6, 2007 / Rules and Regulations
dated March 27, 2006; and Airbus Service
Bulletin A340–57–4087, Revision 01,
excluding Appendix 01, dated February 15,
2005; in accordance with 5 U.S.C. 552(a) and
1 CFR part 51.
(2) On October 27, 2005 (70 FR 59233,
October 12, 2005), the Director of the Federal
Register approved the incorporation by
reference of Airbus Service Bulletin A340–
57–4087, including Appendix 01, dated
November 21, 2003.
(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.
Issued in Renton, Washington, on May 25,
2007.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. E7–10754 Filed 6–5–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–25738; Directorate
Identifier 2006–NE–27–AD; Amendment 39–
15085; AD 2007–12–07]
RIN 2120–AA64
Airworthiness Directives; General
Electric Company (GE) CF6–80C2B
Series Turbofan Engines
Examining the AD Docket
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
rmajette on PROD1PC64 with RULES
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for GE
CF6–80C2B series turbofan engines with
electronic control units (ECUs),
installed on Boeing 747 and 767 series
airplanes. This AD requires installing
software version 8.2.Q1 to the engine
ECU, which increases the engine’s
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. Though the root cause
investigation is not yet complete, we
believe exposure to ice crystals during
flight is associated with these flameout
events. We are issuing this AD to
provide increased margin to flameout,
which will minimize the potential of an
VerDate Aug<31>2005
15:16 Jun 05, 2007
Jkt 211001
all-engine flameout event caused by ice
accretion and shedding during flight.
DATES: This AD becomes effective July
11, 2007. The Director of the Federal
Register approved the incorporation by
reference of certain publications listed
in the regulations as of July 11, 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: 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
proposed to amend 14 CFR part 39 with
a proposed AD. The proposed AD
applies to GE CF6–80C2B series
turbofan engines with ECUs, installed
on Boeing 747 and 767 series airplanes.
We published the proposed AD in the
Federal Register on October 24, 2006
(71 FR 62215). That action proposed to
require installing software version
8.2.Q1 to the engine ECU, which
increases the engine’s margin to
flameout.
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 Corrective Actions
Should Be Expanded
One commenter, the Airline Pilots
Association, International, states that
the corrective action should be
PO 00000
Frm 00004
Fmt 4700
Sfmt 4700
expanded in this AD to be fully
effective. The commenter states that the
prescribed modification addresses only
the flameout and restart issues, while
the problems of engine ice accretion and
compressor blade damage due to ice
shedding during operations, remain.
The commenter states that, due to the
severity of single- and dual-engine
flameout events, the FAA and GE must
examine the engine certification and
operating envelope to determine the
causes of ice accretions and compressor
blade damage while operating in an ice
crystal environment and continue to
develop a more comprehensive solution.
We do not agree. This AD considers
the ice accretion location, quantity, and
the potential of compressor blade
damage caused by impact with ice.
Paragraph (f) of this AD states that these
AD actions are interim actions due to
the on-going investigation, and that we
may take further rulemaking actions in
the future based on the results of the
investigation and field experience.
Request To Eliminate Certain Wording
Japan Airlines International (JAL)
requests that we eliminate ‘‘at the next
shop visit of the engine’’ in the
compliance section. Doing this would:
• Then allow operators to accomplish
the retrofit program on Boeing 767
series airplanes more aggressively; and
• Would facilitate completing the
program in the proposed 5-year
compliance period, without causing
aircraft on the ground (AOG) situations,
due to a shortage of spare ECUs.
JAL is concerned that there might be a
shortage of spare ECUs that could result
in grounded aircraft. JAL provided
information and data on their planned
retrofit for their fleet of Boeing 767 and
747 series airplanes.
We partially agree. Eliminating the
proposed wording would result in a less
aggressive replacement program for the
total population of engines. JAL did not
provide any supporting data of how this
change would result in a more
aggressive compliance program for
engines installed on the Boeing 767
airplanes. Our risk assessment indicates
that the risk presented by this unsafe
condition can be successfully managed
within the current and expected parts
availability. Therefore, we did not
change the AD.
In reviewing JAL’s comment, we
noted that our intent could be clarified.
We changed the AD to clarify that ECUs
installed with previous versions of
software can be installed on an engine
for a period of time.
The added paragraph in the AD
discusses two possible conditions: (1)
Reverting to previous versions of
E:\FR\FM\06JNR1.SGM
06JNR1
Federal Register / Vol. 72, No. 108 / Wednesday, June 6, 2007 / Rules and Regulations
software in an ECU, and (2) versions of
software installed in ECUs that are
installed on an engine. Our risk
assessment indicates this change to the
AD is acceptable and manages the
unsafe condition.
Suggestion To Accelerate the
Compliance Schedule
One commenter, the National
Transportation Safety Board, suggests
that the compliance schedule be
accelerated as the software upgrade
program progresses.
We do not agree. Our risk assessment
indicates that the compromise to safety
that is the subject of this AD can be
adequately managed within the
compliance schedule this AD requires.
However, as also noted, we may have
other AD actions as we more fully
investigate the events leading to the AD.
We did not change the AD.
rmajette on PROD1PC64 with RULES
AD Clarifications
After we issued the proposed AD, our
review indicated that we should clarify
compliance and make the following
other needed updates.
We added a paragraph to the AD
compliance section to clarify our intent
for this AD. That paragraph now states
that after the effective date of this AD,
once software version 8.2.Q1 is installed
in an ECU, reverting to previous
versions of ECU software in that ECU is
prohibited.
We clarified the compliance
paragraphs by separating the actions
required for engines installed in Boeing
767 series airplanes from those installed
in Boeing 747 series airplanes.
We found that we inadvertently
described the inlet gearbox seal by
brand name. We now identify this seal
by its material name in this AD.
GE issued Service Bulletin No. CF6–
80C2 S/B 73–0339, Revision 1, which
includes changes in the compliance
section that make it consistent with this
AD. We now reference that Service
Bulletin Revision 1 in this AD.
We eliminated the paragraph that
stated that installation of later FAAapproved ECU software versions are an
acceptable alternative methods of
compliance (AMOC) to this AD. We will
approve future software versions as an
AMOC to this AD using the standard
AMOC process. Eliminating this
paragraph minimizes possible confusion
of using the process for requesting and
approving AMOCs.
Conclusion
We have carefully reviewed the
available data, including the comments
received, and determined that air safety
and the public interest require adopting
VerDate Aug<31>2005
15:16 Jun 05, 2007
Jkt 211001
the AD with the changes described
previously.
Costs of Compliance
We estimate that this AD will affect
293 CF6–80C2B series turbofan engines
with ECUs installed on Boeing 747 and
767 series airplanes of U.S. registry. It
will take about six work-hours per
engine to perform the actions (ECU
overhauls not included) and the average
labor rate is $80 per work-hour. Based
on these figures, we estimate the total
cost of the AD to U.S. operators to be
$283,740.
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.
PO 00000
Frm 00005
Fmt 4700
Sfmt 4700
31175
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
2007–12–07 General Electric Company:
Amendment 39–15085. Docket No.
FAA–2006–25738; Directorate Identifier
2006–NE–27–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective July 11, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to General Electric
Company (GE) CF6–80C2B1F, –80C2B2F,
–80C2B4F, –80C2B5F, –80C2B6F,
–80C2B6FA, –80C2B7F, and –80C2B8F
turbofan engines with electronic control
units (ECUs), installed on Boeing 747 and
767 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 provide increased margin to flameout,
which will minimize the potential of an allengine 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 ECU Software Installation for Boeing
767 Series Airplanes
(g) For Boeing 767 series airplanes:
E:\FR\FM\06JNR1.SGM
06JNR1
31176
Federal Register / Vol. 72, No. 108 / Wednesday, June 6, 2007 / Rules and Regulations
(1) All affected engines must have ECU
software version 8.2.Q1 installed at next
engine shop visit or ECU shop visit,
whichever occurs first, but no later than five
years after the effective date of this AD.
(2) Within 24 months after the effective
date of this AD, at least one of the airplane’s
affected engines must have ECU software
version 8.2.Q1 installed.
(3) Do the software installations specified
in paragraphs (g)(1) and (g)(2) of this AD
using paragraphs 3.A. through 3.B.(3)(f)4. of
the Accomplishment Instructions of GE
Service Bulletin No. CF6–80C2 S/B 73–0339,
Revision 1, dated April 24, 2007.
Engine ECU Software Installation for Boeing
747 Series Airplanes
(h) For Boeing 747 series airplanes:
(1) All affected engines must have ECU
software version 8.2.Q1 installed at next
engine shop visit or ECU shop visit,
whichever occurs first, but no later than five
years after the effective date of this AD.
(2) Do the software installations specified
in paragraph (h)(1) of this AD using
paragraphs 3.A. through 3.B.(3)(f)4. of the
Accomplishment Instructions of GE Service
Bulletin No. CF6–80C2 S/B 73–0339,
Revision 1, dated April 24, 2007.
rmajette on PROD1PC64 with RULES
Reverting to Previous Software Versions of
ECU Software
(i) After the effective date of this AD:
(1) Once software version 8.2.Q1 is
installed in an ECU, reverting to previous
versions of ECU software in that ECU is
prohibited.
(2) For a period of 24 months after the
effective date of this AD, once an ECU
containing software version 8.2.Q1 is
installed on an engine, that ECU can be
replaced with an ECU containing a previous
software version. The calendar time
requirements in paragraphs (g) and (h) of this
AD are not to be exceeded.
(3) After 24 months from the effective date
of this AD, once an ECU containing software
version 8.2.Q1 is installed on an engine, if
the ECU needs to be replaced for any reason,
it must only be replaced by another ECU
containing version 8.2.Q1 software.
Definitions
(j) For the purposes of this AD:
(1) Next shop visit of the engine ECU is
when the ECU is removed from the engine for
overhaul or for maintenance.
(2) Next shop visit of the engine is when
the engine is removed from the airplane for
maintenance in which a major engine flange
is disassembled after the effective date of this
AD. The following engine maintenance
actions, either separately or in combination
with each other, are not considered a next
engine shop visit:
(i) Removal of the upper high pressure
compressor (HPC) stator case solely for airfoil
maintenance.
(ii) Module-level inspection of the HPC
rotor stages 3–9 spool.
(iii) Replacement of stage 5 HPC variable
stator vane bushings or lever arms.
(iv) Removal of the accessory gearbox.
(v) Replacement of the inlet gearbox
polytetrafluoroethylene seal.
VerDate Aug<31>2005
15:16 Jun 05, 2007
Jkt 211001
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) Under 14 CFR part 39.23, special flight
permits are prohibited.
Material Incorporated by Reference
(m) You must use General Electric
Company Service Bulletin No. CF6–80C2
S/B 73–0339, Revision 1, dated April 24,
2007, to perform the installation required by
this AD. The Director of the Federal Register
approved the incorporation by reference of
this service bulletin 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.
Issued in Burlington, Massachusetts, on
May 30, 2007.
Robert Ganley,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E7–10745 Filed 6–5–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF HOMELAND
SECURITY
U.S. Customs and Border Protection
DEPARTMENT OF THE TREASURY
19 CFR Part 12
[CBP Dec. 07–27]
RIN 1505–AB79
Extension of Import Restrictions
Imposed on Archaeological and
Ethnological Materials From Peru
AGENCIES: U.S. Customs and Border
Protection, Department of Homeland
Security; Department of the Treasury.
ACTION: Final rule.
SUMMARY: This document amends U.S.
Customs and Border Protection (CBP)
regulations to reflect the extension of
import restrictions on archaeological
material and certain ethnological
materials originating in Peru which
were imposed by Treasury Decision
(T.D.) 97–50 and extended by T.D. 02–
PO 00000
Frm 00006
Fmt 4700
Sfmt 4700
30. The Assistant Secretary for
Educational and Cultural Affairs, United
States Department of State, has
determined that conditions continue to
warrant the imposition of import
restrictions. Accordingly, the
restrictions will remain in effect for an
additional 5 years, and the CBP
regulations are being amended to
indicate this second extension. These
restrictions are being extended pursuant
to determinations of the United States
Department of State made under the
terms of the Convention on Cultural
Property Implementation Act in
accordance with the United Nations
Educational, Scientific and Cultural
Organization (UNESCO) Convention on
the Means of Prohibiting and Preventing
the Illicit Import, Export and Transfer of
Ownership of Cultural Property. T.D.
97–50 contains the Designated List of
archaeological and ethnological
materials that describes the articles to
which the restrictions apply.
DATES: Effective Date: June 9, 2007.
FOR FURTHER INFORMATION CONTACT: For
legal aspects, George F. McCray, Esq.,
Chief, Intellectual Property Rights and
Restricted Merchandise Branch, (202)
572–8710. For operational aspects,
Michael Craig, Chief, Other Government
Agencies Branch, (202) 344–1684.
SUPPLEMENTARY INFORMATION:
Background
Pursuant to the provisions of the 1970
United Nations Educational, Scientific
and Cultural Organization (UNESCO)
Convention, codified into U.S. law as
the Convention on Cultural Property
Implementation Act (Pub. L. 97–446, 19
U.S.C. 2601 et seq.), the United States
entered into a bilateral agreement with
the Republic of Peru on June 9, 1997,
concerning the imposition of import
restrictions on pre-Columbian
archaeological materials of Peru dating
to the Colonial period and certain
Colonial ethnological material from
Peru. On June 11, 1997, the former
United States Customs Service
published T.D. 97–50 in the Federal
Register (62 FR 31713), which amended
19 CFR 12.104g(a) to reflect the
imposition of these restrictions, and
included a list designating the types of
archaeological and ethnological
materials covered by the restrictions.
Import restrictions listed in 19 CFR
12.104g(a) are ‘‘effective for no more
than five years beginning on the date on
which the agreement enters into force
with respect to the United States. This
period can be extended for additional
periods not to exceed five years if it is
determined that the factors which
justified the initial agreement still
E:\FR\FM\06JNR1.SGM
06JNR1
Agencies
[Federal Register Volume 72, Number 108 (Wednesday, June 6, 2007)]
[Rules and Regulations]
[Pages 31174-31176]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-10745]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-25738; Directorate Identifier 2006-NE-27-AD;
Amendment 39-15085; AD 2007-12-07]
RIN 2120-AA64
Airworthiness Directives; General Electric Company (GE) CF6-80C2B
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
CF6-80C2B series turbofan engines with electronic control units (ECUs),
installed on Boeing 747 and 767 series airplanes. This AD requires
installing software version 8.2.Q1 to the engine ECU, which increases
the engine's 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. Though the root cause investigation is not yet complete, we
believe exposure to ice crystals during flight is associated with these
flameout events. We are issuing this AD to provide increased margin to
flameout, which will minimize the potential of an all-engine flameout
event caused by ice accretion and shedding during flight.
DATES: This AD becomes effective July 11, 2007. The Director of the
Federal Register approved the incorporation by reference of certain
publications listed in the regulations as of July 11, 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: 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 proposed to amend 14 CFR part 39
with a proposed AD. The proposed AD applies to GE CF6-80C2B series
turbofan engines with ECUs, installed on Boeing 747 and 767 series
airplanes. We published the proposed AD in the Federal Register on
October 24, 2006 (71 FR 62215). That action proposed to require
installing software version 8.2.Q1 to the engine ECU, which increases
the engine's margin to flameout.
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 Corrective Actions Should Be Expanded
One commenter, the Airline Pilots Association, International,
states that the corrective action should be expanded in this AD to be
fully effective. The commenter states that the prescribed modification
addresses only the flameout and restart issues, while the problems of
engine ice accretion and compressor blade damage due to ice shedding
during operations, remain. The commenter states that, due to the
severity of single- and dual-engine flameout events, the FAA and GE
must examine the engine certification and operating envelope to
determine the causes of ice accretions and compressor blade damage
while operating in an ice crystal environment and continue to develop a
more comprehensive solution.
We do not agree. This AD considers the ice accretion location,
quantity, and the potential of compressor blade damage caused by impact
with ice. Paragraph (f) of this AD states that these AD actions are
interim actions due to the on-going investigation, and that we may take
further rulemaking actions in the future based on the results of the
investigation and field experience.
Request To Eliminate Certain Wording
Japan Airlines International (JAL) requests that we eliminate ``at
the next shop visit of the engine'' in the compliance section. Doing
this would:
Then allow operators to accomplish the retrofit program on
Boeing 767 series airplanes more aggressively; and
Would facilitate completing the program in the proposed 5-
year compliance period, without causing aircraft on the ground (AOG)
situations, due to a shortage of spare ECUs.
JAL is concerned that there might be a shortage of spare ECUs that
could result in grounded aircraft. JAL provided information and data on
their planned retrofit for their fleet of Boeing 767 and 747 series
airplanes.
We partially agree. Eliminating the proposed wording would result
in a less aggressive replacement program for the total population of
engines. JAL did not provide any supporting data of how this change
would result in a more aggressive compliance program for engines
installed on the Boeing 767 airplanes. Our risk assessment indicates
that the risk presented by this unsafe condition can be successfully
managed within the current and expected parts availability. Therefore,
we did not change the AD.
In reviewing JAL's comment, we noted that our intent could be
clarified. We changed the AD to clarify that ECUs installed with
previous versions of software can be installed on an engine for a
period of time.
The added paragraph in the AD discusses two possible conditions:
(1) Reverting to previous versions of
[[Page 31175]]
software in an ECU, and (2) versions of software installed in ECUs that
are installed on an engine. Our risk assessment indicates this change
to the AD is acceptable and manages the unsafe condition.
Suggestion To Accelerate the Compliance Schedule
One commenter, the National Transportation Safety Board, suggests
that the compliance schedule be accelerated as the software upgrade
program progresses.
We do not agree. Our risk assessment indicates that the compromise
to safety that is the subject of this AD can be adequately managed
within the compliance schedule this AD requires. However, as also
noted, we may have other AD actions as we more fully investigate the
events leading to the AD. We did not change the AD.
AD Clarifications
After we issued the proposed AD, our review indicated that we
should clarify compliance and make the following other needed updates.
We added a paragraph to the AD compliance section to clarify our
intent for this AD. That paragraph now states that after the effective
date of this AD, once software version 8.2.Q1 is installed in an ECU,
reverting to previous versions of ECU software in that ECU is
prohibited.
We clarified the compliance paragraphs by separating the actions
required for engines installed in Boeing 767 series airplanes from
those installed in Boeing 747 series airplanes.
We found that we inadvertently described the inlet gearbox seal by
brand name. We now identify this seal by its material name in this AD.
GE issued Service Bulletin No. CF6-80C2 S/B 73-0339, Revision 1,
which includes changes in the compliance section that make it
consistent with this AD. We now reference that Service Bulletin
Revision 1 in this AD.
We eliminated the paragraph that stated that installation of later
FAA-approved ECU software versions are an acceptable alternative
methods of compliance (AMOC) to this AD. We will approve future
software versions as an AMOC to this AD using the standard AMOC
process. Eliminating this paragraph minimizes possible confusion of
using the process for requesting and approving AMOCs.
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.
Costs of Compliance
We estimate that this AD will affect 293 CF6-80C2B series turbofan
engines with ECUs installed on Boeing 747 and 767 series airplanes of
U.S. registry. It will take about six work-hours per engine to perform
the actions (ECU overhauls not included) and the average labor rate is
$80 per work-hour. Based on these figures, we estimate the total cost
of the AD to U.S. operators to be $283,740.
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:
2007-12-07 General Electric Company: Amendment 39-15085. Docket No.
FAA-2006-25738; Directorate Identifier 2006-NE-27-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective July 11,
2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to General Electric Company (GE) CF6-
80C2B1F, -80C2B2F, -80C2B4F, -80C2B5F, -80C2B6F, -80C2B6FA, -
80C2B7F, and -80C2B8F turbofan engines with electronic control units
(ECUs), installed on Boeing 747 and 767 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 provide increased margin to flameout, which
will 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 ECU Software Installation for Boeing 767 Series Airplanes
(g) For Boeing 767 series airplanes:
[[Page 31176]]
(1) All affected engines must have ECU software version 8.2.Q1
installed at next engine shop visit or ECU shop visit, whichever
occurs first, but no later than five years after the effective date
of this AD.
(2) Within 24 months after the effective date of this AD, at
least one of the airplane's affected engines must have ECU software
version 8.2.Q1 installed.
(3) Do the software installations specified in paragraphs (g)(1)
and (g)(2) of this AD using paragraphs 3.A. through 3.B.(3)(f)4. of
the Accomplishment Instructions of GE Service Bulletin No. CF6-80C2
S/B 73-0339, Revision 1, dated April 24, 2007.
Engine ECU Software Installation for Boeing 747 Series Airplanes
(h) For Boeing 747 series airplanes:
(1) All affected engines must have ECU software version 8.2.Q1
installed at next engine shop visit or ECU shop visit, whichever
occurs first, but no later than five years after the effective date
of this AD.
(2) Do the software installations specified in paragraph (h)(1)
of this AD using paragraphs 3.A. through 3.B.(3)(f)4. of the
Accomplishment Instructions of GE Service Bulletin No. CF6-80C2 S/B
73-0339, Revision 1, dated April 24, 2007.
Reverting to Previous Software Versions of ECU Software
(i) After the effective date of this AD:
(1) Once software version 8.2.Q1 is installed in an ECU,
reverting to previous versions of ECU software in that ECU is
prohibited.
(2) For a period of 24 months after the effective date of this
AD, once an ECU containing software version 8.2.Q1 is installed on
an engine, that ECU can be replaced with an ECU containing a
previous software version. The calendar time requirements in
paragraphs (g) and (h) of this AD are not to be exceeded.
(3) After 24 months from the effective date of this AD, once an
ECU containing software version 8.2.Q1 is installed on an engine, if
the ECU needs to be replaced for any reason, it must only be
replaced by another ECU containing version 8.2.Q1 software.
Definitions
(j) For the purposes of this AD:
(1) Next shop visit of the engine ECU is when the ECU is removed
from the engine for overhaul or for maintenance.
(2) Next shop visit of the engine is when the engine is removed
from the airplane for maintenance in which a major engine flange is
disassembled after the effective date of this AD. The following
engine maintenance actions, either separately or in combination with
each other, are not considered a next engine shop visit:
(i) Removal of the upper high pressure compressor (HPC) stator
case solely for airfoil maintenance.
(ii) Module-level inspection of the HPC rotor stages 3-9 spool.
(iii) Replacement of stage 5 HPC variable stator vane bushings
or lever arms.
(iv) Removal of the accessory gearbox.
(v) Replacement of the inlet gearbox polytetrafluoroethylene
seal.
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) Under 14 CFR part 39.23, special flight permits are
prohibited.
Material Incorporated by Reference
(m) You must use General Electric Company Service Bulletin No.
CF6-80C2 S/B 73-0339, Revision 1, dated April 24, 2007, to perform
the installation required by this AD. The Director of the Federal
Register approved the incorporation by reference of this service
bulletin 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.
Issued in Burlington, Massachusetts, on May 30, 2007.
Robert Ganley,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E7-10745 Filed 6-5-07; 8:45 am]
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