Airworthiness Directives; General Electric Company CF6-50C Series Turbofan Engines, 62215-62217 [E9-28167]

Download as PDF Federal Register / Vol. 74, No. 227 / Friday, November 27, 2009 / Rules and Regulations 62215 DEPARTMENT OF TRANSPORTATION Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: (2) Use the inspection instructions in Thielert Service Bulletin No. TM TAE 125– 0017, Revision 2, dated February 22, 2008, to perform the inspection. (3) Thereafter, repetitively inspect the engine and engine oil for any evidence or pieces of broken piston cooling nozzles, within every additional 100 flight hours. (4) If any evidence of a failed cooling nozzle is found, replace the failed cooling nozzle before further flight. PART 39—AIRWORTHINESS DIRECTIVES Alternative Methods of Compliance (AMOCs) 1. The authority citation for part 39 continues to read as follows: (f) The Manager, Engine Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Airworthiness Directives; General Electric Company CF6–50C Series Turbofan Engines List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment ■ ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] Related Information 2. The FAA amends § 39.13 by adding the following new AD: ■ 2009–24–10 Thielert Aircraft Engines GmbH: Amendment 39–16102. Docket No. FAA–2009–0753; Directorate Identifier 2009–NE–31–AD. Effective Date (a) This airworthiness directive (AD) becomes effective January 4, 2010. Affected Airworthiness Directives (ADs) (b) None. Applicability (c) This AD applies to Thielert Aircraft Engines GmbH (TAE) model TAE 125–01 reciprocating engines, excluding engines that have been modified to TAE Design Modification No. 2007–001. These engines are installed in, but not limited to, Diamond Aircraft Industries Model DA42, Piper PA– 28–61 (Supplemental Type Certificate (STC) No. SA03303AT), Cessna 172F, 172G, 172H, 172I, 172K, 172L, 172M, 172N, 172P, 172R, 172S, F172F, F172G, F172H, F172K, F172L, F172M, F172N, and F172P (STC No. SA01303WI) airplanes. srobinson on DSKHWCL6B1PROD with RULES Reason (d) This AD results from mandatory continuing airworthiness information (MCAI) issued 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: In-flight engine shutdown incidents were reported on aircraft equipped with TAE–125– 01 engines. This was found to be mainly the result of operation over a long time period with broken piston cooling oil nozzles which caused thermal overload of the piston. We are issuing this AD to prevent engine in-flight shutdown, possibly resulting in reduced control of the aircraft. Actions and Compliance (e) Unless already done, do the following actions: (1) Within the next 110 flight hours, or during the next scheduled maintenance, whichever occurs first after the effective date of this AD, inspect the engine and engine oil for any evidence or pieces of broken piston cooling nozzles. VerDate Nov<24>2008 16:26 Nov 25, 2009 Jkt 220001 (g) Refer to European Aviation Safety Agency AD 2008–0016 R1, dated February 22, 2008, and Thielert Aircraft Engines GmbH, Platanenstrasse 14 D–09350, Lichtenstein, Germany, telephone: +49– 37204–696–0; fax: +49–37204–696–55; e-mail: info@centurion-engines.com, for related information. (h) Contact Jason Yang, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: jason.yang@faa.gov; telephone (781) 238–7747; fax (781) 238–7199, for more information about this AD. Material Incorporated by Reference (i) You must use Thielert Service Bulletin No. TM TAE 125–0017, Revision 2, dated February 22, 2008 to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Thielert Aircraft Engines GmbH, Platanenstrasse 14 D–09350, Lichtenstein, Germany, telephone: +49– 37204–696–0; fax: +49–37204–696–55; e-mail: info@centurion-engines.com. (3) You may review copies at the FAA, New England Region, 12 New England Executive Park, Burlington, MA; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Burlington, Massachusetts, on November 18, 2009. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E9–28166 Filed 11–25–09; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–24171; Directorate Identifier 2006–NE–08–AD; Amendment 39– 16093; AD 2007–11–18R1] RIN 2120–AA64 AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. SUMMARY: The FAA is revising an existing airworthiness directive (AD) for General Electric Company (GE) CF6– 50C series turbofan engines. That AD currently requires reworking certain forward fan stator cases and installing a fan module secondary containment shield. This AD requires the same actions but eliminates a certain service bulletin from the compliance method. This AD results from a review that shows that only one of the service bulletins referenced in the original AD is applicable as a compliance method. We are issuing this AD revision to eliminate a certain service bulletin from the compliance method and to prevent uncontained fan blade failures, which can result in separation of airplane hydraulic lines, damage to critical airplane systems, and possible loss of airplane control. DATES: This AD becomes effective January 4, 2010. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of January 4, 2010. ADDRESSES: You can get the service information identified in this AD from General Electric Company, GE– Aviation, Room 285, 1 Newmann Way, Cincinnati, OH 45215, telephone (513) 552–3272; fax (513) 552–3329; e-mail: geae.aoc@ge.com. The Docket Operations office is located at Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. FOR FURTHER INFORMATION CONTACT: James Rosa, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: james.rosa@faa.gov; telephone (781) 238–7152; fax (781) 238–7199. E:\FR\FM\27NOR1.SGM 27NOR1 62216 Federal Register / Vol. 74, No. 227 / Friday, November 27, 2009 / Rules and Regulations The FAA proposed to amend 14 CFR part 39 with a proposed AD. The proposed AD applies to GE CF6–50C series turbofan engines. We published the proposed AD in the Federal Register on June 24, 2009 (74 FR 30018). That action proposed to require reworking certain forward fan stator cases, installing a fan module secondary containment shield on Airbus A300 series airplanes, and eliminating GE Service Bulletin (SB) No. CF6–50 S/B 72–0986, Revision 2, dated March 21, 2007, as an acceptable compliance method. SUPPLEMENTARY INFORMATION: 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. 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. Request To Change Service Bulletin References One commenter, Airbus, requests that we reference the latest revision of GE SB No. CF6–50 S/B 72–0985 in the AD, which is Revision 3, dated August 22, 2007. We agree. We changed the SB references in the AD to Revision 3. Request To Remove European Aviation Safety Agency (EASA) AD Reference Airbus requests that we remove the reference to EASA AD 2004–0007 from the AD, as it has been cancelled by EASA. We agree and have removed the EASA AD reference. srobinson on DSKHWCL6B1PROD with RULES Request To Include GE SB No. CF6–50 S/B 72–0986 One commenter, Tradewinds Airlines, requests that we include GE SB No. CF6–50 S/B 72–0986 in the AD, as this will give credit for previous installation of required shields. We agree. If shields have been previously installed per GE SB No. CF6– 50 S/B 72–0986, CF6–50 S/B 72–0986, Revision 01, or CF6–50 S/B 72–0986, VerDate Nov<24>2008 16:26 Nov 25, 2009 Jkt 220001 Revision 02, credit will be allowed for that previous installation. 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 40 CF6–50C series turbofan engines installed on airplanes of U.S. registry. We also estimate that it will take about 2.5 work hours per engine to perform the actions, and that the average labor rate is $80 per work-hour. Required parts will cost about $9,451 per engine. Based on these figures, we estimate the total cost of the AD to U.S. operators to be $386,040. 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 PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 (3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a summary of the costs to comply with this AD and placed it in the AD Docket. You may get a copy of this summary at the address listed under ADDRESSES. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation Administration amends 14 CFR part 39 as follows: ■ PART 39—AIRWORTHINESS DIRECTIVES 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 removing Amendment 39–15075 (72 FR 30249, May 31, 2007), and by adding a new airworthiness directive, Amendment 39–16093, to read as follows: ■ 2007–11–18R1 General Electric Company: Amendment 39–16093. Docket No. FAA–2006–24171; Directorate Identifier 2006–NE–08–AD. Effective Date (a) This airworthiness directive (AD) becomes effective January 4, 2010. Affected ADs (b) This AD revises AD 2007–11–18, Amendment 39–15075. Applicability (c) This AD applies to General Electric Company (GE) CF6–50C, CF6–50C1, CF6– 50C2, and CF6–50C2R turbofan engines, with a forward fan stator case, part number (P/N) 9064M53G04, G05, G06, G07, G08, G09, G10, G12, or G13, or P/N 9173M37G01, G02, G03, G04, G05, or G06 installed. These engines are installed on, but not limited to, Airbus A300, McDonnell Douglas DC–10 series, and DC– 10–30F (KC–10A, KDC–10) airplanes. Unsafe Condition (d) This AD revision results from a review that shows that only one of the service bulletins referenced in the original AD is applicable as a compliance method. We are issuing this AD to eliminate a certain service bulletin from the compliance method and to prevent uncontained fan blade failures, which can result in separation of airplane hydraulic lines, damage to critical airplane systems, and possible loss of airplane control. E:\FR\FM\27NOR1.SGM 27NOR1 Federal Register / Vol. 74, No. 227 / Friday, November 27, 2009 / Rules and Regulations 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. (f) At the next engine shop visit after the effective date of this AD, but no later than June 30, 2010, rework the forward fan stator case and install the fan module secondary containment shield. (1) For engines on Airbus 300 series airplanes, use paragraph 3, Accomplishment Instructions, of GE Service Bulletin (SB) No. CF6–50 S/B 72–0985, Revision 3, dated August 22, 2007, to do the rework and installation. (2) Deleted. (g) The rework and installation specified in paragraph (f)(1) of this AD can also be done on-wing. Previous Credit (h) Previous credit is allowed for fan stator cases reworked and containment shields installed using GE SB No. CF6–50 S/B 72– 0985, dated December 2, 1991, Revision 1, dated September 15, 1998, or Revision 2, dated March 21, 2007, before the effective date of this AD. Credit is also allowed for fan stator cases reworked and containment shields installed using GE SB No. CF6–50 S/ B 72–0986, dated December 2, 1991, Revision 1, dated September 15, 1998, or Revision 2, dated march 21, 2007. Alternative Methods of Compliance (i) 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. srobinson on DSKHWCL6B1PROD with RULES Related Information (j) Deleted. (k) Contact James Rosa, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: james.rosa@faa.gov; telephone (781) 238–7152; fax (781) 238–7199, for more information about this AD. (l) Contact General Electric Company, GE– Aviation, Room 285, 1 Newmann Way, Cincinnati, OH 45215, telephone (513) 5523272; fax (513) 552–3329; e-mail: geae.aoc@ge.com, for a copy of the service information referenced in this AD. Material Incorporated by Reference (m) You must use GE Service Bulletin No. CF6–50 S/B 72–0985, Revision 3, dated August 22, 2007, to do the rework and installation required by this AD. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact General Electric Company, GE–Aviation, Room 285, 1 Newmann Way, Cincinnati, OH 45215, telephone (513) 552- 3272; fax (513) 552– 3329; e-mail: geae.aoc@ge.com, for a copy of this service information. You may review copies at the FAA, New England Region, 12 New England Executive Park, Burlington, MA; or at the National Archives and Records Administration (NARA). For information on VerDate Nov<24>2008 16:26 Nov 25, 2009 Jkt 220001 the availability of this material at NARA, call 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Burlington, Massachusetts, on November 16, 2009. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E9–28167 Filed 11–25–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0571; Directorate Identifier 2009–NM–004–AD; Amendment 39–16096; AD 2009–24–08] RIN 2120–AA64 AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. SUMMARY: We are adopting a new airworthiness directive (AD) for certain Boeing Model 777–200, –200LR, –300, and –300ER series airplanes. This AD requires inspections for scribe lines in the skin along lap joints, butt joints, certain external doublers, and the large cargo door hinges; and related investigative and corrective actions if necessary. This AD results from reports of scribe lines found at lap joints and butt joints, around external doublers, and at locations where external decals had been removed. We are issuing this AD to detect and correct scribe lines, which can develop into fatigue cracks in the skin. Undetected fatigue cracks can grow and cause sudden decompression of the airplane. DATES: This AD is effective January 4, 2010. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of January 4, 2010. ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124– 2207; telephone 206–544–5000, extension 1; fax 206–766–5680; e-mail me.boecom@boeing.com; Internet https://www.myboeingfleet.com. Examining the AD Docket You may examine the AD docket on the Internet at http:// Frm 00011 Fmt 4700 www.regulations.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 AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone 800–647–5527) is the Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Berhane Alazar, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6577; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: Airworthiness Directives; Boeing Model 777–200, –200LR, –300, and –300ER Series Airplanes PO 00000 62217 Sfmt 4700 Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an airworthiness directive (AD) that would apply to all Boeing Model 777 series airplanes. That NPRM was published in the Federal Register on June 25, 2009 (74 FR 30245). That NPRM proposed to require inspections for scribe lines in the skin along lap joints, butt joints, certain external doublers, and the large cargo door hinges; and related investigative and corrective actions if necessary. Comments We gave the public the opportunity to participate in developing this AD. We considered the comment received from the one commenter. Request To Eliminate Reporting Requirement for Negative Findings Boeing requests that we revise paragraph (k) of the NPRM to eliminate the requirement to report negative findings. Boeing states that this requirement deviates from Boeing Alert Service Bulletin 777–53A0054, dated August 7, 2008, in that the service bulletin specified that operators report findings of cracking. Boeing states that since the Model 777 fleet is young relative to the inspection thresholds, this reporting requirement may last for decades and it would involve hundreds of airplanes. Boeing states that after a period of time, the requirement would become redundant and is therefore an unnecessary burden. We agree with the commenter for the reasons provided. We revised paragraph (k) of the final rule to eliminate the requirement to report negative findings. E:\FR\FM\27NOR1.SGM 27NOR1

Agencies

[Federal Register Volume 74, Number 227 (Friday, November 27, 2009)]
[Rules and Regulations]
[Pages 62215-62217]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-28167]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24171; Directorate Identifier 2006-NE-08-AD; 
Amendment 39-16093; AD 2007-11-18R1]
RIN 2120-AA64


Airworthiness Directives; General Electric Company CF6-50C Series 
Turbofan Engines

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

ACTION: Final rule.

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

SUMMARY: The FAA is revising an existing airworthiness directive (AD) 
for General Electric Company (GE) CF6-50C series turbofan engines. That 
AD currently requires reworking certain forward fan stator cases and 
installing a fan module secondary containment shield. This AD requires 
the same actions but eliminates a certain service bulletin from the 
compliance method. This AD results from a review that shows that only 
one of the service bulletins referenced in the original AD is 
applicable as a compliance method. We are issuing this AD revision to 
eliminate a certain service bulletin from the compliance method and to 
prevent uncontained fan blade failures, which can result in separation 
of airplane hydraulic lines, damage to critical airplane systems, and 
possible loss of airplane control.

DATES: This AD becomes effective January 4, 2010. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in the regulations as of January 4, 2010.

ADDRESSES: You can get the service information identified in this AD 
from General Electric Company, GE-Aviation, Room 285, 1 Newmann Way, 
Cincinnati, OH 45215, telephone (513) 552-3272; fax (513) 552-3329; e-
mail: geae.aoc@ge.com.
    The Docket Operations office is located at Docket Management 
Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, 
SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-
0001.

FOR FURTHER INFORMATION CONTACT: James Rosa, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
james.rosa@faa.gov; telephone (781) 238-7152; fax (781) 238-7199.

[[Page 62216]]


SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 
with a proposed AD. The proposed AD applies to GE CF6-50C series 
turbofan engines. We published the proposed AD in the Federal Register 
on June 24, 2009 (74 FR 30018). That action proposed to require 
reworking certain forward fan stator cases, installing a fan module 
secondary containment shield on Airbus A300 series airplanes, and 
eliminating GE Service Bulletin (SB) No. CF6-50 S/B 72-0986, Revision 
2, dated March 21, 2007, as an acceptable compliance method.

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. 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.

Request To Change Service Bulletin References

    One commenter, Airbus, requests that we reference the latest 
revision of GE SB No. CF6-50 S/B 72-0985 in the AD, which is Revision 
3, dated August 22, 2007.
    We agree. We changed the SB references in the AD to Revision 3.

Request To Remove European Aviation Safety Agency (EASA) AD Reference

    Airbus requests that we remove the reference to EASA AD 2004-0007 
from the AD, as it has been cancelled by EASA.
    We agree and have removed the EASA AD reference.

Request To Include GE SB No. CF6-50 S/B 72-0986

    One commenter, Tradewinds Airlines, requests that we include GE SB 
No. CF6-50 S/B 72-0986 in the AD, as this will give credit for previous 
installation of required shields.
    We agree. If shields have been previously installed per GE SB No. 
CF6-50 S/B 72-0986, CF6-50 S/B 72-0986, Revision 01, or CF6-50 S/B 72-
0986, Revision 02, credit will be allowed for that previous 
installation.

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 40 CF6-50C series turbofan 
engines installed on airplanes of U.S. registry. We also estimate that 
it will take about 2.5 work hours per engine to perform the actions, 
and that the average labor rate is $80 per work-hour. Required parts 
will cost about $9,451 per engine. Based on these figures, we estimate 
the total cost of the AD to U.S. operators to be $386,040.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and
    (3) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a summary of the costs to comply with this AD and 
placed it in the AD Docket. You may get a copy of this summary at the 
address listed under ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the Federal Aviation Administration amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Amendment 39-15075 (72 FR 
30249, May 31, 2007), and by adding a new airworthiness directive, 
Amendment 39-16093, to read as follows:

2007-11-18R1 General Electric Company: Amendment 39-16093. Docket 
No. FAA-2006-24171; Directorate Identifier 2006-NE-08-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective January 
4, 2010.

Affected ADs

    (b) This AD revises AD 2007-11-18, Amendment 39-15075.

Applicability

    (c) This AD applies to General Electric Company (GE) CF6-50C, 
CF6-50C1, CF6-50C2, and CF6-50C2R turbofan engines, with a forward 
fan stator case, part number (P/N) 9064M53G04, G05, G06, G07, G08, 
G09, G10, G12, or G13, or P/N 9173M37G01, G02, G03, G04, G05, or G06 
installed. These engines are installed on, but not limited to, 
Airbus A300, McDonnell Douglas DC-10 series, and DC-10-30F (KC-10A, 
KDC-10) airplanes.

Unsafe Condition

    (d) This AD revision results from a review that shows that only 
one of the service bulletins referenced in the original AD is 
applicable as a compliance method. We are issuing this AD to 
eliminate a certain service bulletin from the compliance method and 
to prevent uncontained fan blade failures, which can result in 
separation of airplane hydraulic lines, damage to critical airplane 
systems, and possible loss of airplane control.

[[Page 62217]]

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.
    (f) At the next engine shop visit after the effective date of 
this AD, but no later than June 30, 2010, rework the forward fan 
stator case and install the fan module secondary containment shield.
    (1) For engines on Airbus 300 series airplanes, use paragraph 3, 
Accomplishment Instructions, of GE Service Bulletin (SB) No. CF6-50 
S/B 72-0985, Revision 3, dated August 22, 2007, to do the rework and 
installation.
    (2) Deleted.
    (g) The rework and installation specified in paragraph (f)(1) of 
this AD can also be done on-wing.

Previous Credit

    (h) Previous credit is allowed for fan stator cases reworked and 
containment shields installed using GE SB No. CF6-50 S/B 72-0985, 
dated December 2, 1991, Revision 1, dated September 15, 1998, or 
Revision 2, dated March 21, 2007, before the effective date of this 
AD. Credit is also allowed for fan stator cases reworked and 
containment shields installed using GE SB No. CF6-50 S/B 72-0986, 
dated December 2, 1991, Revision 1, dated September 15, 1998, or 
Revision 2, dated march 21, 2007.

Alternative Methods of Compliance

    (i) 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.

Related Information

    (j) Deleted.
    (k) Contact James Rosa, Aerospace Engineer, Engine Certification 
Office, FAA, Engine and Propeller Directorate, 12 New England 
Executive Park, Burlington, MA 01803; e-mail: james.rosa@faa.gov; 
telephone (781) 238-7152; fax (781) 238-7199, for more information 
about this AD.
    (l) Contact General Electric Company, GE-Aviation, Room 285, 1 
Newmann Way, Cincinnati, OH 45215, telephone (513) 552- 3272; fax 
(513) 552-3329; e-mail: geae.aoc@ge.com, for a copy of the service 
information referenced in this AD.

Material Incorporated by Reference

    (m) You must use GE Service Bulletin No. CF6-50 S/B 72-0985, 
Revision 3, dated August 22, 2007, to do the rework and installation 
required by this AD. The Director of the Federal Register approved 
the incorporation by reference of this service bulletin in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact General 
Electric Company, GE-Aviation, Room 285, 1 Newmann Way, Cincinnati, 
OH 45215, telephone (513) 552- 3272; fax (513) 552-3329; e-mail: 
geae.aoc@ge.com, for a copy of this service information. You may 
review copies at the FAA, New England Region, 12 New England 
Executive Park, Burlington, MA; or at the National Archives and 
Records Administration (NARA). For information on the availability 
of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Burlington, Massachusetts, on November 16, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E9-28167 Filed 11-25-09; 8:45 am]
BILLING CODE 4910-13-P