Airworthiness Directives; General Electric Company (GE) CF6-80C2D1F Turbofan Engines, 39039-39041 [E7-13835]

Download as PDF Federal Register / Vol. 72, No. 136 / Tuesday, July 17, 2007 / Proposed Rules 39039 Specification and issue date Title ITU–T Recommendation G.656 (2006) .... ITU–T Recommendation L.58 (2004) ....... TIA–598–C (2005) .................................... TIA/EIA–455–B (1998) .............................. Characteristics of a fibre and cable with non-zero dispersion for wideband optical transport. Construction, Installation and Protection of Cables and Other Elements of Outside Plant. Optical Fiber Cable Color Coding. Standard Test Procedure for Fiber Optic Fibers, Cables, Transducers, Sensors, Connecting and Terminating Devices, and Other Fiber Optic Components. Procedure to Measure Temperature Cycling Effects on Optical Fibers Optical Cable, and Other Passive Fiber Optic Components. TIA/EIA–455–3 .......................................... 5. Section 1755.902 and an undesignated center heading are added to read as follows: Fiber Optic Service Entrance Cables Dated: June 20, 2007. James M. Andrew, Administrator, Rural Utilities Service. [FR Doc. E7–13795 Filed 7–16–07; 8:45 am] BILLING CODE 3410–15–P rfrederick on PROD1PC67 with PROPOSALS § 1755.902 cables. Fiber optic service entrance This section covers the requirements for fiber optic service entrance cables intended for aerial installation either by attachment to a support strand or by an integrated self-supporting arrangement, for underground application by placement in a duct, or for buried installations by trenching, direct plowing, directional or pneumatic boring. Cable meeting this specification is recommended for fiber optic service entrances having 12 or fewer fibers with distances less than 100 meters (300 feet.) Service entrance cables shall meet the requirements of § 1755.900, except for any conflicting requirements with this section, in which case the following stipulations supersede requirements of § 1755.900: (a) Cable Detection. For detection purposes, the cable may have toning elements embedded or extruded with the outer jacket. (b) Tensile Rating. The cable shall have ratings that are no less than the tensile ratings indicated in paragraph 1.1.4, Tensile Rating, of Part 1 of the ICEA S–110–717 (ANSI/TIA 472F000). (c) Single Mode Cables. Unless otherwise specified by the purchaser, the single mode optical fibers used in service entrance cables shall meet the fiber attributes of Table 2/G.652, G.652.B attributes, of ITU–T Recommendation G.652. However, when the purchaser stipulates a low water peak fiber the optical fibers shall meet the fiber attributes of Table 4/ G.652, G.652.D attributes, of ITU–T Recommendation G.652. (d) Fiber Count. Unless otherwise specified by the purchaser, the service entrance cable shall contain 12 fibers or less. (e) Armor. A steel armor required in § 1755.900 for direct buried cable manufactured is optional, as required by the purchaser, for service entrance cable under this specification. VerDate Aug<31>2005 14:12 Jul 16, 2007 Jkt 211001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–28319; Directorate Identifier 2007–NE–27–AD] RIN 2120–AA64 Airworthiness Directives; General Electric Company (GE) CF6–80C2D1F Turbofan Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for GE CF6–80C2D1F turbofan engines, installed on McDonnell Douglas Corporation MD–11 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 September 17, 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 PO 00000 Frm 00022 Fmt 4702 Sfmt 4702 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– 2007–28319; Directorate Identifier 2007–NE–27–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 E:\FR\FM\17JYP1.SGM 17JYP1 39040 Federal Register / Vol. 72, No. 136 / Tuesday, July 17, 2007 / Proposed Rules 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. rfrederick on PROD1PC67 with PROPOSALS 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. 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 that are due to ice accretion and shedding into the engine during flight. Although the investigation is not yet complete, we believe that the ice accretion is caused by exposure to ice crystals during flight. Industry reports 35 airplane flameout events, including reports of multi-engine events where all engines on the airplane simultaneously experienced a flameout. Some of these events had high pressure compressor blade damage that may have been caused by impact with shedding ice. In all events, the engines restarted and continued to operate normally for the remainder of the flight. This proposed AD addresses only the CF6–80C2D1F turbofan engines, installed on McDonnell Douglas Corporation MD–11 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 CF–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 VerDate Aug<31>2005 14:12 Jul 16, 2007 Jkt 211001 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– 0351, dated April 11, 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 175 CF6–80C2D1F turbofan engines installed on McDonnell Douglas Corporation MD–11 series airplanes of U.S. registry. We estimate it would take about 3 workhours per ECU to perform the proposed actions if done at ECU shop visit, and 6 work-hours per ECU if done at engine shop visit. We estimate that 50% of the ECUs would be worked at ECU shop visit and the remaining 50% worked at engine shop visit. The average labor rate is $80 per work-hour. Based on these figures, we estimate the cost to U.S. operators to be $63,120. 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. PO 00000 Frm 00023 Fmt 4702 Sfmt 4702 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: General Electric Company: Docket No. FAA– 2007–28319; Directorate Identifier 2007– NE–27–AD. E:\FR\FM\17JYP1.SGM 17JYP1 Federal Register / Vol. 72, No. 136 / Tuesday, July 17, 2007 / Proposed Rules Comments Due Date (a) The Federal Aviation Administration (FAA) must receive comments on this airworthiness directive (AD) action by September 17, 2007. Affected ADs (b) None. Applicability (c) This AD applies to General Electric Company (GE) CF6–80C2D1F turbofan engines, installed on McDonnell Douglas Corporation MD–11 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. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done. Interim Action (f) These actions are interim actions due to the on-going investigation, and we may take further rulemaking actions in the future based on the results of the investigation and field experience. Engine Electronic Control Unit (ECU) Software Removal (g) At the next shop visit of the engine or of the ECU, whichever occurs first, and not to exceed 60 months from the effective date of this AD, remove the following software versions from the ECUs: TABLE 1.—REMOVAL OF ECU SOFTWARE VERSIONS Software version (1) 8.5.A ........................... (2) 8.3.C ........................... (3) 8.3.D ........................... (4) 8.3.E ........................... rfrederick on PROD1PC67 with PROPOSALS (5) 8.3.F ........................... (6) 8.3.G ........................... (7) 8.3.H ........................... (8) 8.3.J ............................ Installed in ECU part No. 1851M51P01, 1851M51P02, 1851M52P01, 1851M52P02, 1851M53P01, 1851M53P02 1471M69P01, 1471M69P02, 1519M91P01 1519M91P02 1519M91P03, 1519M91P04 1519M91P05 1519M91P06, 1820M34P01 1519M91P07, 1820M34P02 1519M91P09, 1519M91P10, 1820M34P04, 1820M34P05 Previous Software Versions of ECU Software (h) For a period of 24 months after the effective date of this AD, once an ECU containing a software version not listed in Table 1 of this AD is installed on an engine, that ECU can be replaced with an ECU containing a previous version of software listed in Table 1. (i) Once the software version listed in Table 1 of this AD has been removed and new FAA-approved software version is installed in an ECU, reverting to those older software versions in that ECU is prohibited. (j) After 60 months from the effective date of this AD, use of an ECU with a software version listed in Table 1 of this AD is prohibited. Definitions (k) For the purposes of this AD: (1) Next shop visit of the ECU is when the ECU is removed from the engine for overhaul or maintenance after the effective date of this AD. (2) Next shop visit of the engine is when the engine is removed from the airplane for maintenance in which a major 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 shop visit of the engine: (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 (l) 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 (m) Special flight permits are not authorized. Related Information (n) 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– 0351, dated April 11, 2007. (o) Contact John Golinski, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: john.golinski@faa.gov; telephone: (781) 238–7135, fax: (781) 238– 7199, for more information about this AD. Issued in Burlington, Massachusetts, on July 11, 2007. Francis A. Favara, Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E7–13835 Filed 7–16–07; 8:45 am] DEPARTMENT OF LABOR Occupational Safety and Health Administration 29 CFR Part 1910 [Docket No. OSHA–2007–0032 (Formerly Docket No. OSHA–S031–2006–0665 and OSHA Docket No. S–031)] RIN 1218–AC09 Explosives Occupational Safety and Health Administration (OSHA), Department of Labor. AGENCY: ACTION: Proposed rule; close of comment period. SUMMARY: On April 13, 2007, the U.S. Department of Labor published a proposed rule entitled Explosives with a comment period that ended 7/12/2007. On July 9, 2007, the comment period was extended to 9/10/2007. At this time the U.S. Department of Labor is closing the comment period effective July 17, 2007. The Department intends to re-propose the Explosives NPRM at a later date in order to clarify the intent of the rulemaking. The comment period for the proposed rule published on April 13, 2007 (72 FR 18792) is closed effective July 17, 2007. DATES: For general information and press inquiries, contact Mr. Kevin Ropp, Office of Communications, Room N–3647, OSHA, U.S. Department of Labor, 200 Constitution Avenue, NW., Washington, DC 20210; telephone (202) 693–1999. For technical inquiries, contact Donald Pittenger, Directorate of Standards and Guidance, Room N–3609, OSHA, U.S. Department of Labor, 200 Constitution Avenue, NW., Washington, DC 20210; telephone (202) 693–2255 or fax (202) 693–1663. FOR FURTHER INFORMATION CONTACT: Signed at Washington, DC, on July 13, 2007. Edwin G. Foulke, Jr., Assistant Secretary of Labor for Occupational Safety and Health. [FR Doc. E7–13925 Filed 7–16–07; 8:45 am] BILLING CODE 4510–26–P BILLING CODE 4910–13–P VerDate Aug<31>2005 14:12 Jul 16, 2007 Jkt 211001 PO 00000 Frm 00024 Fmt 4702 Sfmt 4702 39041 E:\FR\FM\17JYP1.SGM 17JYP1

Agencies

[Federal Register Volume 72, Number 136 (Tuesday, July 17, 2007)]
[Proposed Rules]
[Pages 39039-39041]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-13835]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-28319; Directorate Identifier 2007-NE-27-AD]
RIN 2120-AA64


Airworthiness Directives; General Electric Company (GE) CF6-
80C2D1F 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 CF6-80C2D1F turbofan engines, installed on McDonnell Douglas 
Corporation MD-11 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 September 
17, 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-2007-28319; 
Directorate Identifier 2007-NE-27-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

[[Page 39040]]

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. 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 that are due to ice accretion and shedding 
into the engine during flight. Although the investigation is not yet 
complete, we believe that the ice accretion is caused by exposure to 
ice crystals during flight. Industry reports 35 airplane flameout 
events, including reports of multi-engine events where all engines on 
the airplane simultaneously experienced a flameout. Some of these 
events had high pressure compressor blade damage that may have been 
caused by impact with shedding ice. In all events, the engines 
restarted and continued to operate normally for the remainder of the 
flight.
    This proposed AD addresses only the CF6-80C2D1F turbofan engines, 
installed on McDonnell Douglas Corporation MD-11 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 CF-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 73-0351, dated April 11, 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 175 CF6-80C2D1F 
turbofan engines installed on McDonnell Douglas Corporation MD-11 
series airplanes of U.S. registry. We estimate it would take about 3 
work-hours per ECU to perform the proposed actions if done at ECU shop 
visit, and 6 work-hours per ECU if done at engine shop visit. We 
estimate that 50% of the ECUs would be worked at ECU shop visit and the 
remaining 50% worked at engine shop visit. The average labor rate is 
$80 per work-hour. Based on these figures, we estimate the cost to U.S. 
operators to be $63,120. 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-2007-28319; Directorate 
Identifier 2007-NE-27-AD.

[[Page 39041]]

Comments Due Date

    (a) The Federal Aviation Administration (FAA) must receive 
comments on this airworthiness directive (AD) action by September 
17, 2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to General Electric Company (GE) CF6-80C2D1F 
turbofan engines, installed on McDonnell Douglas Corporation MD-11 
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.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified unless the 
actions have already been done.

Interim Action

    (f) These actions are interim actions due to the on-going 
investigation, and we may take further rulemaking actions in the 
future based on the results of the investigation and field 
experience.

Engine Electronic Control Unit (ECU) Software Removal

    (g) At the next shop visit of the engine or of the ECU, 
whichever occurs first, and not to exceed 60 months from the 
effective date of this AD, remove the following software versions 
from the ECUs:

               Table 1.--Removal of ECU Software Versions
------------------------------------------------------------------------
          Software version                 Installed in ECU part No.
------------------------------------------------------------------------
(1) 8.5.A...........................  1851M51P01, 1851M51P02,
                                       1851M52P01, 1851M52P02,
                                       1851M53P01, 1851M53P02
(2) 8.3.C...........................  1471M69P01, 1471M69P02, 1519M91P01
(3) 8.3.D...........................  1519M91P02
(4) 8.3.E...........................  1519M91P03, 1519M91P04
(5) 8.3.F...........................  1519M91P05
(6) 8.3.G...........................  1519M91P06, 1820M34P01
(7) 8.3.H...........................  1519M91P07, 1820M34P02
(8) 8.3.J...........................  1519M91P09, 1519M91P10,
                                       1820M34P04, 1820M34P05
------------------------------------------------------------------------

Previous Software Versions of ECU Software

    (h) For a period of 24 months after the effective date of this 
AD, once an ECU containing a software version not listed in Table 1 
of this AD is installed on an engine, that ECU can be replaced with 
an ECU containing a previous version of software listed in Table 1.
    (i) Once the software version listed in Table 1 of this AD has 
been removed and new FAA-approved software version is installed in 
an ECU, reverting to those older software versions in that ECU is 
prohibited.
    (j) After 60 months from the effective date of this AD, use of 
an ECU with a software version listed in Table 1 of this AD is 
prohibited.

Definitions

    (k) For the purposes of this AD:
    (1) Next shop visit of the ECU is when the ECU is removed from 
the engine for overhaul or maintenance after the effective date of 
this AD.
    (2) Next shop visit of the engine is when the engine is removed 
from the airplane for maintenance in which a major 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 shop visit of the engine:
    (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

    (l) 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

    (m) Special flight permits are not authorized.

Related Information

    (n) 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 73-0351, dated April 11, 
2007.
    (o) Contact John Golinski, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
john.golinski@faa.gov; telephone: (781) 238-7135, fax: (781) 238-
7199, for more information about this AD.

    Issued in Burlington, Massachusetts, on July 11, 2007.
Francis A. Favara,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
 [FR Doc. E7-13835 Filed 7-16-07; 8:45 am]
BILLING CODE 4910-13-P