Airworthiness Directives; General Electric Company (GE) CF6-80C2A5F Turbofan Engines, 35366-35368 [E7-12490]

Download as PDF 35366 Proposed Rules Federal Register Vol. 72, No. 124 Thursday, June 28, 2007 This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules. DEPARTMENT OF TRANSPORTATION DEPARTMENT OF TRANSPORTATION RIN 2120–AA64 Federal Aviation Administration Airworthiness Directives; General Electric Company (GE) CF6–80C2A5F Turbofan Engines 14 CFR Parts 1, 101, 400, and 401 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–28172; Directorate Identifier 2007–NE–23–AD] Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: [Docket No. FAA–2007–27390; Notice No. 07–06] RIN 2120–AI88 Requirements for Amateur Rocket Activities; Correction Federal Aviation Administration (FAA), DOT. ACTION: Notice of Proposed Rule; correction. AGENCY: SUMMARY: This document corrects the docket number to a proposed rule published in the Federal Register of Thursday, June 14, 2007, regarding Requirements for Amateur Rocket Activities. The comment period will close September 12, 2007. FOR FURTHER INFORMATION CONTACT: Charles P. Brinkman, telephone: (202) 493–4562, or E-mail: phil.brinkman@faa.gov. DATES: rfrederick on PROD1PC67 with PROPOSALS Correction In proposed rule Requirements for Amateur Rocket Activities beginning on page 32816 in the Federal Register issue of June 14, 2007, make the following corrections. 1. On page 32816, in the first column, fourth line of the heading, ‘‘Docket No. FAA–2007–27310’’ should have read, ‘‘Docket No. FAA–2007–27390.’’ 2. On page 32816, in the first column, in the ADDRESSES paragraph, in the second and third lines, ‘‘Docket Number FAA–2007–27310’’ should have read ‘‘Docket Number FAA–2007–27390.’’ Issued in Washington, DC on June 21, 2007. Pamela Hamilton-Powell, Director, Office of Rulemaking. [FR Doc. E7–12463 Filed 6–27–07; 8:45 am] BILLING CODE 4910–13–P VerDate Aug<31>2005 14:52 Jun 27, 2007 Jkt 211001 SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for GE CF6–80C2A5F turbofan engines installed on Airbus A300 series airplanes. This proposed AD would require removing previous software versions from the engine electronic control unit (ECU). Engines with new version software will have increased margin to flameout. This proposed 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 proposing this AD to minimize the potential of an allengine flameout event caused by ice accretion and shedding during flight. DATES: We must receive any comments on this proposed AD by August 27, 2007. ADDRESSES: Use one of the following addresses to comment on this proposed AD. • DOT Docket Web site: Go to http://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to http://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 PO 00000 Frm 00001 Fmt 4702 Sfmt 4702 p.m., Monday through Friday, except Federal holidays. • Fax: (202) 493–2251. You can get the service information identified in this proposed 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. 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: Comments Invited We invite you to send us any written relevant data, views, or arguments regarding this proposal. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA– 2007–28712; Directorate Identifier 2007–NE–23–AD’’ in the subject line of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to http:// 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 proposed AD. Using the search function of the DOT 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 http:// dms.dot.gov. Examining the AD Docket You may examine the AD docket on the Internet at http://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. E:\FR\FM\28JNP1.SGM 28JNP1 Federal Register / Vol. 72, No. 124 / Thursday, June 28, 2007 / Proposed Rules The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is the same as the Mail address provided in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. rfrederick on PROD1PC67 with PROPOSALS Discussion GE CF6–80C2 and CF6–80E1 series turbofan engines continue to experience flameout events caused by 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 34 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 proposed AD addresses only the CF6–80C2A5F turbofan engines, installed on Airbus A300 series airplanes. We believe this model of CF6–80C2 engine is susceptible to flameouts caused by ice accretion and shedding into the engine during flight. Similar AD actions for other CF6–80C2 and CF6–80E1 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. CF6–80C2 S/B 73– 0352, dated February 7, 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 VerDate Aug<31>2005 14:52 Jun 27, 2007 Jkt 211001 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. FAA’s Determination and Requirements of the Proposed AD We have evaluated all pertinent information and identified an unsafe condition that is likely to exist or develop on other products of this same type design. We are proposing this AD, which would require removing certain software versions from the engine ECU. 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. 35367 on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the proposed 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. Would 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 regulatory evaluation of the estimated costs to comply with this proposed AD. You may get a copy of this summary at the address listed under ADDRESSES. List of Subjects in 14 CFR Part 39 Costs of Compliance We estimate that this proposed AD would affect 81 CF6–80C2A5F turbofan engines installed on Airbus A300 series airplanes of U.S. registry. We also estimate it would take about 3.5 workhours per ECU to perform the proposed 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. Air transportation, Aircraft, Aviation safety, Safety. 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. Authority: 49 U.S.C. 106(g), 40113, 44701. Regulatory Findings We have determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 The Proposed Amendment Under the authority delegated to me by the Administrator, the Federal Aviation Administration proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: General Electric Company: Docket No. FAA– 2007–28172; Directorate Identifier 2007– NE–23–AD. Comments Due Date (a) The Federal Aviation Administration (FAA) must receive comments on this airworthiness directive (AD) action by August 27, 2007. Affected ADs (b) None. Applicability (c) This AD applies to General Electric Company (GE) CF6–80C2A5F turbofan engines, installed on Airbus A300 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, due to ice accretion and shedding during flight. Exposure to ice crystals during flight is believed to be associated with these flameout events. E:\FR\FM\28JNP1.SGM 28JNP1 35368 Federal Register / Vol. 72, No. 124 / Thursday, June 28, 2007 / Proposed Rules Compliance DEPARTMENT OF TRANSPORTATION (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 (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 rfrederick on PROD1PC67 with PROPOSALS (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 dated February 7, 2007. (n) Contact John Golinski, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; email: john.golinski@faa.gov; telephone: (781) 238–7135, fax: (781) 238– 7199, for more information about this AD. Issued in Burlington, Massachusetts, on June 22, 2007. Francis A. Favara, Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E7–12490 Filed 6–27–07; 8:45 am] 14:52 Jun 27, 2007 Jkt 211001 [Docket No. FAA–2007–28379; Directorate Identifier 2007–NM–077–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Model A300 Series Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). Previous Software Versions of ECU Software VerDate Aug<31>2005 14 CFR Part 39 AGENCY: (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. BILLING CODE 4910–13–P Federal Aviation Administration SUMMARY: We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: [T]he FAA has published SFAR 88 (Special Federal Aviation Regulation 88). * * * Under this regulation, all holders of type certificates for passenger transport aircraft * * * are required to conduct a design review against explosion risks. This Airworthiness Directive (AD), which renders mandatory the modification of the fuel pump wiring against short circuit, is a consequence of this design review. The unsafe condition is chafing of the fuel pump cables, which could result in short circuits leading to fuel pump failure, intermittent operation, arcing, and possible fuel tank explosion. The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI. DATES: We must receive comments on this proposed AD by July 30, 2007. ADDRESSES: You may send comments by any of the following methods: • DOT Docket Web Site: Go to http://dms.dot.gov and follow the instructions for sending your comments electronically. • Fax: (202) 493–2251. • Mail: Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590– 0001. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. • Federal eRulemaking Portal: http:// www.regulations.gov. Follow the instructions for submitting comments. PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 Examining the AD Docket You may examine the AD docket on the Internet at http://dms.dot.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone (800) 647– 5227) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Tom Stafford, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1622; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Streamlined Issuance of AD The FAA is implementing a new process for streamlining the issuance of ADs related to MCAI. This streamlined process will allow us to adopt MCAI safety requirements in a more efficient manner and will reduce safety risks to the public. This process continues to follow all FAA AD issuance processes to meet legal, economic, Administrative Procedure Act, and Federal Register requirements. We also continue to meet our technical decision-making responsibilities to identify and correct unsafe conditions on U.S.-certificated products. This proposed AD references the MCAI and related service information that we considered in forming the engineering basis to correct the unsafe condition. The proposed AD contains text copied from the MCAI and for this reason might not follow our plain language principles. Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2007–28379; Directorate Identifier 2007–NM–077–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to http:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each E:\FR\FM\28JNP1.SGM 28JNP1

Agencies

[Federal Register Volume 72, Number 124 (Thursday, June 28, 2007)]
[Proposed Rules]
[Pages 35366-35368]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-12490]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28172; Directorate Identifier 2007-NE-23-AD]
RIN 2120-AA64


Airworthiness Directives; General Electric Company (GE) CF6-
80C2A5F Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for GE CF6-80C2A5F turbofan engines installed on Airbus A300 series 
airplanes. This proposed AD would require removing previous software 
versions from the engine electronic control unit (ECU). Engines with 
new version software will have increased margin to flameout. This 
proposed 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 proposing this AD to minimize the potential of an all-engine 
flameout event caused by ice accretion and shedding during flight.

DATES: We must receive any comments on this proposed AD by August 27, 
2007.

ADDRESSES: Use one of the following addresses to comment on this 
proposed AD.
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://
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.
    You can get the service information identified in this proposed 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.

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:

Comments Invited

    We invite you to send us any written relevant data, views, or 
arguments regarding this proposal. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2007-28712; 
Directorate Identifier 2007-NE-23-AD'' in the subject line of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments received by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to http://
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 proposed AD. Using the search function of the 
DOT 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 http://dms.dot.gov.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://
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.

[[Page 35367]]

The AD docket contains this proposed AD, the regulatory evaluation, any 
comments received, and other information. The street address for the 
Docket Operations office (telephone (800) 647-5527) is the same as the 
Mail address provided in the ADDRESSES section. Comments will be 
available in the AD docket shortly after receipt.

Discussion

    GE CF6-80C2 and CF6-80E1 series turbofan engines continue to 
experience flameout events caused by 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 34 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 proposed AD addresses only the CF6-80C2A5F turbofan engines, 
installed on Airbus A300 series airplanes. We believe this model of 
CF6-80C2 engine is susceptible to flameouts caused by ice accretion and 
shedding into the engine during flight. Similar AD actions for other 
CF6-80C2 and CF6-80E1 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. CF6-80C2 S/B 73-0352, dated February 7, 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.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to exist or develop on other products 
of this same type design. We are proposing this AD, which would require 
removing certain software versions from the engine ECU.

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.

Costs of Compliance

    We estimate that this proposed AD would affect 81 CF6-80C2A5F 
turbofan engines installed on Airbus A300 series airplanes of U.S. 
registry. We also estimate it would take about 3.5 work-hours per ECU 
to perform the proposed 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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 the proposed 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. Would 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 regulatory evaluation of the estimated costs to 
comply with this proposed AD. 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.

The Proposed Amendment

    Under the authority delegated to me by the Administrator, the 
Federal Aviation Administration proposes to amend 14 CFR part 39 as 
follows:

PART 39--AIRWORTHINESS DIRECTIVES

    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]

    2. The FAA amends Sec.  39.13 by adding the following new 
airworthiness directive:

General Electric Company: Docket No. FAA-2007-28172; Directorate 
Identifier 2007-NE-23-AD.

Comments Due Date

    (a) The Federal Aviation Administration (FAA) must receive 
comments on this airworthiness directive (AD) action by August 27, 
2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to General Electric Company (GE) CF6-80C2A5F 
turbofan engines, installed on Airbus A300 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, due to ice accretion and shedding during flight. 
Exposure to ice crystals during flight is believed to be associated 
with these flameout events.

[[Page 35368]]

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 dated February 7, 
2007.
    (n) Contact John Golinski, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; email: 
john.golinski@faa.gov; telephone: (781) 238-7135, fax: (781) 238-
7199, for more information about this AD.

    Issued in Burlington, Massachusetts, on June 22, 2007.
Francis A. Favara,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
 [FR Doc. E7-12490 Filed 6-27-07; 8:45 am]
BILLING CODE 4910-13-P