[Federal Register Volume 72, Number 196 (Thursday, October 11, 2007)]
[Rules and Regulations]
[Pages 57848-57850]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E7-20036]


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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: 
[email protected]; 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: 
[email protected]; 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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