Airworthiness Directives; General Electric Company (GE) CF6-45 and CF6-50 Series Turbofan Engines, 19259-19261 [05-7387]

Download as PDF Federal Register / Vol. 70, No. 70 / Wednesday, April 13, 2005 / Rules and Regulations SUMMARY: The FAA is adopting a new airworthiness directive (AD) for GE CF6–45 and CF6–50 series turbofan engines. This AD requires reviewing accumulated cyclic-life records of 10 Citation life-limited rotating parts, correcting those records, and removing from I The authority citation for these special service parts that exceed the low-cycleconditions is as follows: fatigue (LCF) life limits published in the Authority: 49 U.S.C. 106(g), 40113 and Engine Manual Chapter 5, 44701; 14 CFR 21.16 and 21.101; and 14 CFR Airworthiness Limitations Section 11.38 and 11.19. (ALS). This AD results from an error in The Special Conditions a tracking database that subtracted flight cycles of certain serial number (SN) I Accordingly, pursuant to the authority parts from the actual accumulated delegated to me by the Administrator, cycles. We are issuing this AD to the following special conditions are prevent rotating parts that may have issued as part of the type certification exceeded their LCF life limit from basis for the Twin Commander Aircraft Models 690C, 690D, 695, 695A, and 695B failing, leading to uncontained engine failure. modified by Twin Commander Aircraft LLC. to add a digital Air Data computer. DATES: This AD becomes effective April 1. Protection of Electrical and 28, 2005. We must receive any comments on Electronic Systems from High Intensity this AD by June 13, 2005. Radiated Fields (HIRF). Each system that performs critical functions must be ADDRESSES: Use one of the following designed and installed to ensure that the addresses to comment on this AD. • DOT Docket Web site: Go to operations, and operational capabilities https://dms.dot.gov and follow the of these systems to perform critical instructions for sending your comments functions, are not adversely affected electronically. when the airplane is exposed to high • Government-wide rulemaking Web intensity radiated electromagnetic fields site: Go to https://www.regulations.gov external to the airplane. and follow the instructions for sending 2. For the purpose of these special your comments electronically. conditions, the following definition • Mail: Docket Management Facility; applies: Critical Functions: Functions U.S. Department of Transportation, 400 whose failure would contribute to, or Seventh Street, SW., Nassif Building, cause, a failure condition that would Room PL–401, Washington, DC 20590– prevent the continued safe flight and 001. landing of the airplane. • Fax: (202) 493–2251. Issued in Kansas City, Missouri on April 1, • Hand Delivery: Room PL–401 on 2005. the plaza level of the Nassif Building, David R. Showers, 400 Seventh Street, SW., Washington, Acting Manager, Small Airplane Directorate, DC, between 9 a.m. and 5 p.m., Monday Aircraft Certification Service. through Friday, except Federal holidays. [FR Doc. 05–7430 Filed 4–12–05; 8:45 am] FOR FURTHER INFORMATION CONTACT: BILLING CODE 4910–13–P Karen Curtis, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New DEPARTMENT OF TRANSPORTATION England Executive Park, Burlington, MA 01803; telephone (781) 238–7192; fax Federal Aviation Administration (781) 238–7199. SUPPLEMENTARY INFORMATION: In March 14 CFR Part 39 of 2005, GE informed us that a records review of a certain engine revealed that [Docket No. FAA–2005–20932; Directorate Identifier 2005–NE–11–AD; Amendment 39– the number of cycles accumulated on 14056; AD 2005–08–04] that engine, and its life-limited rotating parts, were recorded incorrectly in the RIN 2120–AA64 operator’s database in 1989. GE has advised us that the engine and rotating Airworthiness Directives; General parts actually have more cycles Electric Company (GE) CF6–45 and accumulated than currently recorded. CF6–50 Series Turbofan Engines Upon further investigation, GE has confirmed that that engine was affected AGENCY: Federal Aviation by an error in a tracking database that Administration (FAA), DOT. subtracted flight cycles from the actual ACTION: Final rule; request for accumulated cycles on a total of 32 comments. rotating parts. PART 23—AIRWORTHINESS STANDARDS; NORMAL, UTILITY, ACROBATIC, AND COMMUTER CATEGORY AIRPLANES VerDate jul<14>2003 16:30 Apr 12, 2005 Jkt 205001 PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 19259 GE advises that 22 of the 32 affected rotating parts are in the control of a foreign operator, and under the jurisdiction of the Direction Generale de L’Aviation Civile (DGAC), which is the airworthiness authority for France. The DGAC advises that there are three of the 32 parts installed on foreign registered airplanes, but not under the jurisdiction of the DGAC. The location, current cycle count, and corrected cycle count are known for these 25 parts. None of these 25 parts have exceeded their LCF life limit. GE advises that they do not know the locations or current cycle counts of the remaining seven affected rotating parts. These seven parts could be in service with accumulated cyclic life exceeding their LCF life limit. We are including the three parts mentioned previously with the seven parts, as being affected by this AD, to ensure their cyclic lives get corrected. This condition, if not corrected, could result in failure of rotating parts that may have exceeded their LCF life limit, leading to uncontained engine failure. FAA’s Determination and Requirements of This AD The unsafe condition described previously is likely to exist or develop on other GE CF6–45 and CF6–50 series turbofan engines of the same type design. For that reason, we are issuing this AD to prevent rotating parts that may have exceeded their LCF life limit, from failing, leading to uncontained engine failure. This AD requires: • Reviewing the engine records within 10 days after the effective date of this AD, for the existence of rotating parts listed by SN in this AD; and • Correcting the records for those parts; and • Within 100 cycles-in-service after the effective date of this AD, removing from service those parts exceeding their LCF life limits. FAA’s Determination of the Effective Date Since an unsafe condition exists that requires the immediate adoption of this AD, we have found that notice and opportunity for public comment before issuing this AD are impracticable, and that good cause exists for making this amendment effective in less than 30 days. Comments Invited This AD is a final rule that involves requirements affecting flight safety and was not preceded by notice and an opportunity for public comment; however, we invite you to send us any written relevant data, views, or arguments regarding this AD. Send your E:\FR\FM\13APR1.SGM 13APR1 19260 Federal Register / Vol. 70, No. 70 / Wednesday, April 13, 2005 / Rules and Regulations comments to an address listed under ADDRESSES. Include ‘‘AD Docket No. FAA–2005–20932; Directorate Identifier 2005–NE–11–AD’’ in the subject line of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the rule that might suggest a need to modify it. We will post all comments we receive, without change, to https:// 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 AD. Using the search function of the DMS 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 https://dms.dot.gov. Examining the AD Docket You may examine the docket that contains the AD, any comments received, and any final disposition in person at the DMS Docket Offices between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone (800) 647– 5227) is located on the plaza level of the Department of Transportation Nassif Building at the street address stated in ADDRESSES. Comments will be available in the AD docket shortly after the DMS receives them. 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 the regulation: 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. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a summary of the costs to comply with this AD and placed it in the AD Docket. You may get a copy of this summary at the address listed under ADDRESSES. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. Adoption of the Amendment Under the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I 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: I 2005–08–04 General Electric Company: Amendment 39–14056. Docket No. FAA–2005–20932; Directorate Identifier 2005–NE–11–AD. Effective Date (a) This airworthiness directive (AD) becomes effective April 28, 2005. Affected ADs (b) None. Applicability (c) This AD applies to General Electric Company (GE) CF6–45 and CF6–50 series turbofan engines. These engines are installed on, but not limited to, Boeing DC–10, 747 series, and Airbus Industrie A300 series airplanes. Unsafe Condition (d) This AD results from an error in a tracking database that subtracted flight cycles of certain serial number (SN) parts from the actual accumulated cycles. We are issuing this AD to prevent rotating parts that may have exceeded their low-cycle fatigue (LCF) life limit from failing, leading to uncontained engine failure. 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. Records Check (f) Within 10 days after the effective date of this AD, do the following: (1) Check the engine records for the part numbers (P/Ns) and SNs listed in Table 1 of this AD. (2) Make the required cycle and hour corrections for those parts. TABLE 1.—ROTATING PARTS REQUIRING CYCLIC LIFE CORRECTION Required cycle correction P/N SN Part name 9051M71P17 ...................... 9079M63P17 ...................... 9234M35P01 ...................... 9128M81G03 ..................... 9080M27P04 ...................... (9080M28G10) ................... 9061M21P03 ...................... 9061M70G01 ..................... 9185M75G01 ..................... 9045M86P10 ...................... MPOA0748 ......................... MPOC7054 ........................ MPOU3470 ........................ APV01489 .......................... MPOA0853 ......................... ............................................ SNE01254 .......................... KLA00801 .......................... MPOH4228 ........................ CAN01080 .......................... Disk, Fan Stage 1 ........................................................... Shaft, Compressor Rotor Rear ....................................... Shaft, Forward High Pressure Turbine (HPT) Rotor ...... Shaft, HPT Rotor Rear ................................................... Shaft, Fan Forward ......................................................... (Shaft, Fan Forward-Balanced). Disk, Low Pressure Turbine (LPT) Rotor Stage 1 ......... Tube, LPT Air ................................................................. Spool, Fan Rotor Stage 2–4 .......................................... Adapter, Tube ................................................................. VerDate jul<14>2003 16:30 Apr 12, 2005 Jkt 205001 PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 E:\FR\FM\13APR1.SGM 13APR1 Required hour correction +2,429 +2,429 +2,429 +2,429 +2,429 +15,936 +15,936 +15,936 +15,936 +15,936 +1,224 +2,429 +2,429 +2,429 +5,708 +15,936 +15,936 +15,936 19261 Federal Register / Vol. 70, No. 70 / Wednesday, April 13, 2005 / Rules and Regulations TABLE 1.—ROTATING PARTS REQUIRING CYCLIC LIFE CORRECTION—Continued Required cycle correction P/N SN Part name 9061M26P20 ...................... PMOA0508 ......................... Shaft, LPT Rear .............................................................. (3) After correcting the cycles and hours, remove from service any rotating parts listed in Table 1 of this AD that exceed their LCF life limit, within 100 cycles-in-service after the effective date of this AD. (g) After the effective date of this AD, do not install any part listed in Table 1 of this AD into any engine, unless the cycles and hours have been corrected as specified in paragraph (f) of this AD. (h) After the effective date of this AD, do not install any engine unless the records check specified in paragraph (f) of this AD has been performed. 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) General Electric Company Alert Service Bulletin No. CF6–50 S/B 72–A1275, dated March 24, 2005, pertains to the subject of this AD. Material Incorporated by Reference (k) None. Issued in Burlington, Massachusetts, on April 7, 2005. Jay J. Pardee, Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 05–7387 Filed 4–12–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF HEALTH AND HUMAN SERVICES Food and Drug Administration 21 CFR Part 520 Oral Dosage Form New Animal Drugs; Dichlorophene and Toluene Capsules AGENCY: Food and Drug Administration, HHS. ACTION: The Food and Drug Administration (FDA) is amending the animal drug regulations that reflect approval of a new animal drug application (NADA) for dichlorophene and toluene capsules used in dogs and cats for removal of certain intestinal parasites. In a notice published elsewhere in this issue of the Federal Register, FDA is withdrawing approval of the NADA. SUMMARY: 16:30 Apr 12, 2005 This rule is effective April 25, 2005. Jkt 205001 +2,429 +15,936 DEPARTMENT OF HEALTH AND HUMAN SERVICES FOR FURTHER INFORMATION CONTACT: Pamela K. Esposito, Center for Veterinary Medicine (HFV–212), Food and Drug Administration, 7519 Standish Pl., Rockville, MD 20855, 301–827– 7818; e-mail: pesposit@cvm.fda.gov. Food and Drug Administration Natchez Animal Supply Co., 201 John R. Junkin Dr., Natchez, MS 39120, has requested that FDA withdraw approval of NADA 121–557 for THR Worm (dichlorophene and toluene) Capsules used in dogs and cats for removal of certain intestinal parasites. This action is requested because the product is no longer manufactured or marketed. The animal drug regulations are amended to reflect the withdrawal of approval. This rule does not meet the definition of ‘‘rule’’ in 5 U.S.C. 804(3)(A) because it is a rule of ‘‘particular applicability.’’ Therefore, it is not subject to the congressional review requirements in 5 U.S.C. 801–808. AGENCY: SUPPLEMENTARY INFORMATION: 21 CFR Part 520 Oral Dosage Form New Animal Drugs; Ivermectin Meal; Change of Sponsor Food and Drug Administration, HHS. ACTION: Final rule. SUMMARY: The Food and Drug Administration (FDA) is amending the animal drug regulations to reflect a change of sponsor for a new animal drug application (NADA) from Merial Ltd. to Farnam Companies, Inc. DATES: This rule is effective April 13, 2005. FOR FURTHER INFORMATION CONTACT: David R. Newkirk, Center for Veterinary Medicine (HFV–100), Food and Drug Administration, 7500 Standish Pl., Rockville, MD 20855, 301–827–6967, email: david.newkirk@fda.gov. SUPPLEMENTARY INFORMATION: Merial List of Subjects in 21 CFR Part 520 Ltd., 3239 Satellite Blvd., Bldg. 500, Duluth, GA 30096–4640, has informed Animal drugs. FDA that it has transferred ownership I Therefore, under the Federal Food, of, and all rights and interest in, NADA Drug, and Cosmetic Act and under 141–241 for ZIMECTERIN–EZ authority delegated to the Commissioner (ivermectin) 0.6% w/w for Horses to of Food and Drugs and redelegated to the Farnam Companies, Inc., 301 West Osborn, Phoenix, AZ 85013–3928. Center for Veterinary Medicine, 21 CFR This rule does not meet the definition part 520 is amended as follows: of ‘‘rule’’ in 5 U.S.C. 804(3)(A) because PART 520—ORAL DOSAGE FORM it is a rule of ‘‘particular applicability.’’ NEW ANIMAL DRUGS Therefore, it is not subject to the congressional review requirements in 5 I 1. The authority citation for 21 CFR U.S.C. 801–808. part 520 continues to read as follows: List of Subjects in 21 CFR Part 520 Authority: 21 U.S.C. 360b. § 520.580 Final rule. VerDate jul<14>2003 DATES: Required hour correction [Amended] 2. Section 520.580 is amended in paragraph (b)(1) by removing ‘‘049968,’’. I Dated: March 31, 2005. Catherine P. Beck, Acting Director, Center for Veterinary Medicine. [FR Doc. 05–7337 Filed 4–12–05; 8:45 am] BILLING CODE 4160–01–S PO 00000 Animal drugs. Therefore, under the Federal Food, Drug, and Cosmetic Act and under authority delegated to the Commissioner of Food and Drugs and redelegated to the Center for Veterinary Medicine, 21 CFR part 520 is amended as follows: I PART 520—ORAL DOSAGE FORM NEW ANIMAL DRUGS 1. The authority citation for 21 CFR part 520 continues to read as follows: I Authority: 21 U.S.C. 360b. Frm 00009 Fmt 4700 Sfmt 4700 E:\FR\FM\13APR1.SGM 13APR1

Agencies

[Federal Register Volume 70, Number 70 (Wednesday, April 13, 2005)]
[Rules and Regulations]
[Pages 19259-19261]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-7387]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-20932; Directorate Identifier 2005-NE-11-AD; 
Amendment 39-14056; AD 2005-08-04]
RIN 2120-AA64


Airworthiness Directives; General Electric Company (GE) CF6-45 
and CF6-50 Series Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for GE 
CF6-45 and CF6-50 series turbofan engines. This AD requires reviewing 
accumulated cyclic-life records of 10 life-limited rotating parts, 
correcting those records, and removing from service parts that exceed 
the low-cycle-fatigue (LCF) life limits published in the Engine Manual 
Chapter 5, Airworthiness Limitations Section (ALS). This AD results 
from an error in a tracking database that subtracted flight cycles of 
certain serial number (SN) parts from the actual accumulated cycles. We 
are issuing this AD to prevent rotating parts that may have exceeded 
their LCF life limit from failing, leading to uncontained engine 
failure.

DATES: This AD becomes effective April 28, 2005.
    We must receive any comments on this AD by June 13, 2005.

ADDRESSES: Use one of the following addresses to comment on this AD.
     DOT Docket Web site: Go to  https://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590-001.
     Fax: (202) 493-2251.
     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.

FOR FURTHER INFORMATION CONTACT: Karen Curtis, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; telephone (781) 238-
7192; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: In March of 2005, GE informed us that a 
records review of a certain engine revealed that the number of cycles 
accumulated on that engine, and its life-limited rotating parts, were 
recorded incorrectly in the operator's database in 1989. GE has advised 
us that the engine and rotating parts actually have more cycles 
accumulated than currently recorded. Upon further investigation, GE has 
confirmed that that engine was affected by an error in a tracking 
database that subtracted flight cycles from the actual accumulated 
cycles on a total of 32 rotating parts.
    GE advises that 22 of the 32 affected rotating parts are in the 
control of a foreign operator, and under the jurisdiction of the 
Direction Generale de L'Aviation Civile (DGAC), which is the 
airworthiness authority for France. The DGAC advises that there are 
three of the 32 parts installed on foreign registered airplanes, but 
not under the jurisdiction of the DGAC. The location, current cycle 
count, and corrected cycle count are known for these 25 parts. None of 
these 25 parts have exceeded their LCF life limit. GE advises that they 
do not know the locations or current cycle counts of the remaining 
seven affected rotating parts. These seven parts could be in service 
with accumulated cyclic life exceeding their LCF life limit. We are 
including the three parts mentioned previously with the seven parts, as 
being affected by this AD, to ensure their cyclic lives get corrected. 
This condition, if not corrected, could result in failure of rotating 
parts that may have exceeded their LCF life limit, leading to 
uncontained engine failure.

FAA's Determination and Requirements of This AD

    The unsafe condition described previously is likely to exist or 
develop on other GE CF6-45 and CF6-50 series turbofan engines of the 
same type design. For that reason, we are issuing this AD to prevent 
rotating parts that may have exceeded their LCF life limit, from 
failing, leading to uncontained engine failure. This AD requires:
     Reviewing the engine records within 10 days after the 
effective date of this AD, for the existence of rotating parts listed 
by SN in this AD; and
     Correcting the records for those parts; and
     Within 100 cycles-in-service after the effective date of 
this AD, removing from service those parts exceeding their LCF life 
limits.

FAA's Determination of the Effective Date

    Since an unsafe condition exists that requires the immediate 
adoption of this AD, we have found that notice and opportunity for 
public comment before issuing this AD are impracticable, and that good 
cause exists for making this amendment effective in less than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment; however, we invite you to send us any written relevant data, 
views, or arguments regarding this AD. Send your

[[Page 19260]]

comments to an address listed under ADDRESSES. Include ``AD Docket No. 
FAA-2005-20932; Directorate Identifier 2005-NE-11-AD'' in the subject 
line of your comments. We specifically invite comments on the overall 
regulatory, economic, environmental, and energy aspects of the rule 
that might suggest a need to modify it.
    We will post all comments we receive, without change, to https://
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 AD. Using the search function of the DMS 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 
https://dms.dot.gov.

Examining the AD Docket

    You may examine the docket that contains the AD, any comments 
received, and any final disposition in person at the DMS Docket Offices 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Office (telephone (800) 647-5227) is located on 
the plaza level of the Department of Transportation Nassif Building at 
the street address stated in ADDRESSES. Comments will be available in 
the AD docket shortly after the DMS receives them.

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 the regulation:
    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. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a summary of the costs to comply with this AD and 
placed it in the AD Docket. You may get a copy of this summary at the 
address listed under ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

Adoption of the Amendment

0
Under the authority delegated to me by the Administrator, the Federal 
Aviation Administration amends part 39 of the Federal Aviation 
Regulations (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 adding the following new airworthiness 
directive:

2005-08-04 General Electric Company: Amendment 39-14056. Docket No. 
FAA-2005-20932; Directorate Identifier 2005-NE-11-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective April 
28, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to General Electric Company (GE) CF6-45 and 
CF6-50 series turbofan engines. These engines are installed on, but 
not limited to, Boeing DC-10, 747 series, and Airbus Industrie A300 
series airplanes.

Unsafe Condition

    (d) This AD results from an error in a tracking database that 
subtracted flight cycles of certain serial number (SN) parts from 
the actual accumulated cycles. We are issuing this AD to prevent 
rotating parts that may have exceeded their low-cycle fatigue (LCF) 
life limit from failing, leading to uncontained engine failure.

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.

Records Check

    (f) Within 10 days after the effective date of this AD, do the 
following:
    (1) Check the engine records for the part numbers (P/Ns) and SNs 
listed in Table 1 of this AD.
    (2) Make the required cycle and hour corrections for those 
parts.

                            Table 1.--Rotating Parts Requiring Cyclic Life Correction
----------------------------------------------------------------------------------------------------------------
                                                                                          Required     Required
                 P/N                             SN                   Part name            cycle         hour
                                                                                         correction   correction
----------------------------------------------------------------------------------------------------------------
9051M71P17..........................  MPOA0748...............  Disk, Fan Stage 1......       +2,429      +15,936
9079M63P17..........................  MPOC7054...............  Shaft, Compressor Rotor       +2,429      +15,936
                                                                Rear.
9234M35P01..........................  MPOU3470...............  Shaft, Forward High           +2,429      +15,936
                                                                Pressure Turbine (HPT)
                                                                Rotor.
9128M81G03..........................  APV01489...............  Shaft, HPT Rotor Rear..       +2,429      +15,936
9080M27P04..........................  MPOA0853...............  Shaft, Fan Forward.....       +2,429      +15,936
(9080M28G10)........................  .......................  (Shaft, Fan Forward-
                                                                Balanced).
9061M21P03..........................  SNE01254...............  Disk, Low Pressure            +1,224       +5,708
                                                                Turbine (LPT) Rotor
                                                                Stage 1.
9061M70G01..........................  KLA00801...............  Tube, LPT Air..........       +2,429      +15,936
9185M75G01..........................  MPOH4228...............  Spool, Fan Rotor Stage        +2,429      +15,936
                                                                2-4.
9045M86P10..........................  CAN01080...............  Adapter, Tube..........       +2,429      +15,936

[[Page 19261]]

 
9061M26P20..........................  PMOA0508...............  Shaft, LPT Rear........       +2,429      +15,936
----------------------------------------------------------------------------------------------------------------

    (3) After correcting the cycles and hours, remove from service 
any rotating parts listed in Table 1 of this AD that exceed their 
LCF life limit, within 100 cycles-in-service after the effective 
date of this AD.
    (g) After the effective date of this AD, do not install any part 
listed in Table 1 of this AD into any engine, unless the cycles and 
hours have been corrected as specified in paragraph (f) of this AD.
    (h) After the effective date of this AD, do not install any 
engine unless the records check specified in paragraph (f) of this 
AD has been performed.

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) General Electric Company Alert Service Bulletin No. CF6-50 
S/B 72-A1275, dated March 24, 2005, pertains to the subject of this 
AD.

Material Incorporated by Reference

    (k) None.

    Issued in Burlington, Massachusetts, on April 7, 2005.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 05-7387 Filed 4-12-05; 8:45 am]
BILLING CODE 4910-13-P
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