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

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


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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.

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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.
    <bullet> DOT Docket Web site: Go to  http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
    <bullet> Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
    <bullet> Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590-001.
    <bullet> Fax: (202) 493-2251.
    <bullet> 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:
    <bullet> 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
    <bullet> Correcting the records for those parts; and
    <bullet> 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 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 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 
http://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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