[Federal Register: October 11, 2007 (Volume 72, Number 196)]
[Rules and Regulations]
[Page 57848-57850]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr11oc07-4]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-28172; Directorate Identifier 2007-NE-23-AD;
Amendment 39-15224; AD 2007-21-06]
RIN 2120-AA64
Airworthiness Directives; General Electric Company (GE) CF6-
80C2A5F Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for GE
CF6-80C2A5F turbofan engines installed on, but not limited to, Airbus
A300F4-605R airplanes. This AD requires removing previous software
versions from the engine electronic control unit (ECU). Engines with
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.
DATES: This AD becomes effective November 15, 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.
The Docket Operations office is located at U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC 20590-0001.
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 CF6-80C2A5F turbofan
engines installed on Airbus A300 series airplanes. We published the
proposed AD in the Federal Register on June 28, 2007 (72 FR 35366).
That action proposed to require removing previous software versions
from the engine ECU. Engines with new version software will have
increased margin to flameout.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov
or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. Follow the online instructions for accessing the docket. 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 provided in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments received.
Applicability Clarification
One commenter, Airbus, points out that CF6-80C2A5F engines are
installed on Airbus A300-600 series airplanes, and not on Airbus A300
series airplanes, as we stated in the proposed AD. We agree that the
applicability needs clarification. However, to be more accurate, we
changed the AD to state that the CF6-80C2A5F engines are installed on,
but not limited to, Airbus A300F4-605R airplanes.
Request To Exclude Airplanes
Airbus requests that we exclude airplanes that have incorporated
modification number (No.) 13270, from the AD applicability. Airbus did
not provide any technical rationale, information, or explanation
regarding the content of modification No. 13270, or why airplanes with
modification No. 13270 should be excluded from the AD.
We do not agree. We believe that modification No. 13270 might be an
Airbus design change for removing previous versions of software from
engines and incorporating new software. We state in the AD that the
actions are required unless previously done. Airbus airplanes that have
previously incorporated the actions of this AD by following the GE
Service Bulletin, or any other document, such as Airbus modification
No. 13270, have satisfied the requirements of this AD, and no
[[Page 57849]]
further action is required. We did not change the AD.
Request To Add Airbus Service Bulletin Reference
Airbus requests that we add a reference to Airbus Service Bulletin
No. A300-73-6032, dated May 23, 2007 as another source of information
on the subject. Airbus provided no explanation for adding the
reference.
We do not agree. The AD requirements are for the GE CF6-80C2A5F
turbofan engine, and not the airplane. Airbus did not send us a copy of
their Service Bulletin, so we do not know the contents of it. We did
not change the AD.
Update of Service Bulletin Reference
In the related material paragraph, the proposed AD referenced GE
software upgrade Service Bulletin No. CF6-80C2 S/B 73-0352, dated
February 7, 2007. GE has since revised that Service Bulletin and we
updated the reference to Service Bulletin No. CF6-80C2 S/B 73-0352,
Revision 1, dated September 12, 2007, in that paragraph.
Request for Additional Information
Airbus requests that we provide additional information to them on
the number of engine flameout reports defined in the proposed AD.
We do not agree. GE has stated that they will continue to
periodically update the airplane manufacturers on the root cause
investigation and any revenue service flameout events. We did not
change the AD.
Request for Differences Between GE Service Bulletin and AD To Be
Reconciled
KLM Royal Dutch Airlines states that the proposed AD statements
regarding prohibition of installing ECUs with pre GE Service Bulletin
No. 73-0352 software after 24 months of AD effective date, is different
from the GE Service Bulletin requirement. The commenter requests that
differences between the Service Bulletin and the AD be reconciled.
We do not agree. Both the AD and Service Bulletin compliance
program identify 24 months as the calendar time cap for incorporating
the software change. The AD requires that the new software be installed
after 24 months. The Service Bulletin does not provide this statement
but recommends the actions of the Service Bulletin be done within 24
months of the original issue date of the SB. We believe the intent of
the AD and SB are the same, and that the AD program is appropriate for
balancing the actions to address the unsafe condition and impact to the
fleet. We did not change the AD.
Proposed AD Allows for No Exemptions
KLM Royal Dutch Airlines states that, unlike AD 2007-12-07 (Boeing
747 and 767 ECU fleet) the proposed AD allows for no exemptions. The
commenter requests that we allow for exemptions, to make the AD in line
with other ADs for CF6-80C2 engine applications.
We do not agree. The AD actions for AD 2007-12-07 were developed
specifically for the affected fleet of CF6-80C2 engines installed on
Boeing 747 and 767 airplanes. That action considers the number of
affected engines, available resources, risk of unsafe condition, and
other factors. The actions identified in this AD are specific to the
CF6-80C2 engines installed on Airbus A300F4-605R airplanes, and are
appropriate for balancing the actions needed to address the unsafe
condition and impact to the fleet. We did not change the AD.
Request To Rewrite All of the CF6-80 Ice Accretion ADs
KLM Royal Dutch Airlines requests that we rewrite all of the
compliance requirements and determination definitions for all of the
CF6-80 ice accretion ADs, to make them identical. The commenter did not
provide any justification for this change.
We do not agree. We developed the AD compliance programs for the
icing inclement weather threat for the various fleets of CF6-80C2 and
CF6-80E1 engines. These AD programs are different relative to
corrective actions, due to several factors, including risk of unsafe
condition, fleet size, and available resources. We believe having a
tailored compliance plan for each population of CF6 engine provides the
best approach of mitigating the risk of an unsafe condition and
minimizing the impact to the respective fleet. We did not change the
AD.
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 81 CF6-80C2A5F turbofan
engines installed on Airbus A300F4-605R airplanes of U.S. registry. We
also estimate it will take about 3.5 work-hours per ECU to perform the
actions. The average labor rate is $80 per work-hour. Based on these
figures, we estimate the cost to U.S. operators to be $22,680. Our cost
estimate is exclusive of warranty coverage.
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, 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:
[[Page 57850]]
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:
2007-21-06 General Electric Company: Amendment 39-15224. Docket No.
FAA-2007-28172; Directorate Identifier 2007-NE-23-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective November
15, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to General Electric Company (GE) CF6-80C2A5F
turbofan engines, installed on, but not limited to, Airbus A300F4-
605R 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, due to 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 Removal
(g) Within 24 months after the effective date of this AD, remove
software version 8.4.E or older versions, from the engine ECUs, part
numbers 1797M63P01, 1797M63P02, 1797M63P03, 1797M63P04, 1797M63P05,
1820M99P01, 1820M99P02, 1820M99P03, 1820M99P04, and 1820M99P05.
Previous Software Versions of ECU Software
(h) You may use an ECU installed on an engine with a software
version of 8.4.E or older for no longer than 24 months after the
effective date of this AD.
(i) Once software version 8.4.E or older has been removed and
new FAA-approved software version is installed in an ECU, reverting
to version 8.4.E or older of ECU software in that ECU is prohibited.
(j) After 24 months from the effective date of this AD, use of
an ECU with a software version of 8.4.E or older 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. CF6-80C2 S/B 73-0352, Revision 1, dated
September 12, 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.
Material Incorporated by Reference
(o) None.
Issued in Burlington, Massachusetts, on October 4, 2007.
Thomas A. Boudreau,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E7-20036 Filed 10-10-07; 8:45 am]
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