Airworthiness Directives; General Electric Company CF6-45A, CF6-50A, CF6-50C, and CF6-50E Series Turbofan Engines, 75933-75934 [05-24341]

Download as PDF Federal Register / Vol. 70, No. 245 / Thursday, December 22, 2005 / Rules and Regulations The actions required by that AD are intended to prevent an ignition source for fuel vapor in the center wing fuel tank. That condition, if not corrected, could result in fire or explosion in the center wing fuel tank. Actions Since Issuance of Previous AD Since the issuance of that AD, Airbus ´ ´ notified the Direction Generale de l’Aviation Civile (DGAC), which is the airworthiness authority for France, and informed us that it had issued Service Bulletin A320–28–1104, dated December 2, 2003; Revision 01 dated December 8, 2004; and Revision 02 dated February 21, 2005. That service bulletin has been mandated by the European Aviation Safety Authority (EASA) AD F–2005–028 and FAA AD 2005–19–14. That service bulletin specifies inspections and the restoring of electrical bonding integrity in the center tank, including the bonding addressed by Airbus Service Bulletin A320–28–1067, Revision 02, dated January 27, 1997. Airbus states that Service Bulletin A320–28–1067, Revision 02, the service bulletin cited in AD 2005–19–16, is no longer required due to the issuance of Service Bulletin A320–28–1104, original version; Revision 01; and Revision 02. Accordingly, the DGAC canceled French AD F–2005–056 by issuing AD F–2005– 056 R1 on September 28, 2005. FAA’s Determination § 39.13 [Amended] 2. Section 39.13 is amended by adding an AD which removes amendment 39– 14281, to read as follows: I 2005–19–16 R1 Airbus: Amendment 39– 14429. FAA–2005–23400; Directorate Identifier 2005–NM–217–AD. Effective Date (a) This AD becomes effective December 22, 2005. Affected ADs (b) This action rescinds AD 2005–19–16. Applicability (c) This action applies to Airbus Model A320–111, –211, –212, –214, –231, –232, and –233 airplanes, certificated in any category; except those airplanes on which Airbus Modification 25513 has been accomplished in production. Issued in Renton, Washington, on December 8, 2005. Michael Zielinski, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–24343 Filed 12–21–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–22124; Directorate Identifier 2005–NE–21–AD; Amendment 39– 14427; AD 2005–26–06] RIN 2120–AA64 Since the issuance of AD 2005–19–16, we have determined that it is necessary to rescind that AD in order to prevent operators from performing unnecessary actions. Since this action rescinds a requirement to perform an unnecessary action, it has no adverse economic impact and imposes no additional burden on any person. Therefore, notice and public procedures hereon are unnecessary and the rescission may be made effective upon publication in the Federal Register. The Rescission Accordingly, pursuant to 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: cprice-sewell on PROD1PC66 with RULES 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. VerDate Aug<31>2005 15:00 Dec 21, 2005 Jkt 208001 Airworthiness Directives; General Electric Company CF6–45A, CF6–50A, CF6–50C, and CF6–50E Series Turbofan Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for General Electric Company (GE) CF6–45A, CF6– 50A, CF6–50C, and CF6–50E series turbofan engines. This AD requires removing from service pre-GE Service Bulletin (SB) No. CF6–50S/B 72–1268 configuration low pressure turbine (LPT) stage 2 interstage seal assemblies and stage 3 interstage seal assemblies. This AD also requires installing new or reworked configuration stage 2 interstage seal assemblies and stage 3 interstage seal assemblies. This AD results from reports of fan mid shaft separation, leading to separation of the LPT stage 1 disk, disk overspeed, and uncontained engine failure. We are issuing this AD to prevent uncontained PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 75933 engine failure and damage to the airplane. DATES: This AD becomes effective January 26, 2006. ADDRESSES: You can get the service information referenced in this 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. You may examine the AD docket on the Internet at https://dms.dot.gov or in Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC. 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: The FAA proposed to amend 14 CFR part 39 with a proposed airworthiness directive (AD). The proposed AD applies to GE CF6– 45A, CF6–50A, CF6–50C, and CF6–50E series turbofan engines. We published the proposed AD in the Federal Register on August 19, 2005 (70 FR 48660). That action proposed to require removing from service pre-GE SB No. CF6–50 S/ B 72–1268 configuration LPT stage 2 interstage seal assemblies and stage 3 interstage seal assemblies. That action also proposed to require installing new or reworked configuration stage 2 interstage seal assemblies and stage 3 interstage seal assemblies. Examining the AD Docket You may examine the docket that contains the AD, any comments received, and any final disposition in person at the Docket Management Facility Docket Office 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. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the three comments received. The commenters support the proposal. Conclusion We have carefully reviewed the available data, including the comments E:\FR\FM\22DER1.SGM 22DER1 75934 Federal Register / Vol. 70, No. 245 / Thursday, December 22, 2005 / Rules and Regulations received, and determined that air safety and the public interest require adopting the AD as proposed. Costs of Compliance There are about 2,079 CF6–45A, CF6– 50A, CF6–50C, and CF6–50E series turbofan engines of the affected design in the worldwide fleet. We estimate that 790 engines installed on airplanes of U.S. registry will be affected by this AD. We also estimate that it will take about 5 work hours per engine to rework the stage 2 interstage seal assembly and the stage 3 interstage seal assembly. The average labor rate is $65 per work hour. We estimate that 90% of the affected engines will have the parts reworked, and 10% will have new parts installed. A new stage 2 interstage seal assembly and new stage 3 interstage seal assembly will cost about $26,758 per engine. Based on these figures, we estimate the total cost of the AD to U.S. operators to be $2,344,957. 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. cprice-sewell on PROD1PC66 with RULES 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 VerDate Aug<31>2005 15:00 Dec 21, 2005 Jkt 208001 (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 Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation Administration amends 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 2005–26–06 General Electric Company: Amendment 39–14427. Docket No. FAA–2005–22124; Directorate Identifier. 2005–NE–21–AD. Effective Date (a) This airworthiness directive (AD) becomes effective January 26, 2006. Affected ADs (b) None. Applicability (c) This AD applies to General Electric Company (GE) CF6–45A, CF6–50A, CF6– 50C, and CF6–50E series turbofan engines. These engines are installed on, but not limited to, Boeing DC10 and 747 series airplanes, and Airbus Industrie A300 series airplanes. Unsafe Condition (d) This AD results from reports of fan mid shaft separation, leading to separation of the low pressure turbine (LPT) stage 1 disk, disk overspeed, and uncontained engine failure. We are issuing this AD to prevent uncontained engine failure and damage to the airplane. Compliance (e) You are responsible for having the actions required by this AD performed at the next disassembly of the LPT stage 2 interstage seal assembly and stage 3 interstage seal assembly from the LPT stator after the effective date of this AD, but no later than December 31, 2010, unless the actions have already been done. PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 Stage 2 Interstage Seal Assemblies (f) Remove from service the pre-GE Service Bulletin (SB) No. CF6–50 72–1268 configuration LPT stage 2 interstage seal assembly. (g) Install a new or reworked configuration LPT stage 2 interstage seal assembly, part number (P/N) 9198M81G05, 2092M13G01, 2092M13G02, or 2092M13G03, or other FAAapproved equivalent part. (h) Information on reworking the pre-SB No. CF6–50 S/B 72–1268 configuration stage 2 interstage seal assembly to the new configuration can be found in GE SB No. CF6–50 S/B 72–1268, dated December 16, 2004. Stage 3 Interstage Seal Assemblies (i) Remove from service the pre-SB No. CF6–50 S/B 72–1268 configuration stage 3 interstage seal assembly. (j) Install a new or reworked configuration LPT stage 3 interstage seal assembly, P/N 9044M29G17 or 2092M14G01, or other FAAapproved equivalent part. (k) Information on reworking the pre-SB No. CF6–50 S/B 72–1268 configuration stage 3 interstage seal assembly to the new configuration can be found in GE SB No. CF6–50 S/B 72–1268, dated December 16, 2004. Prohibition of Pre-SB No. CF6–50 S/B 72– 1268 Configurations (l) After the effective date of this AD, do not install pre-SB No. CF6–50 S/B 72–1268 configuration LPT stage 2 interstage seal assemblies or stage 3 interstage seal assemblies into any engine. Alternative Methods of Compliance (m) 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 (n) National Transportation Safety Board Safety Recommendation No. A–98–125, dated December 3, 1998, pertains to the subject of this AD. Material Incorporated by Reference (o) None. Issued in Burlington, Massachusetts, on December 14, 2005. Peter A. White, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 05–24341 Filed 12–21–05; 8:45 am] BILLING CODE 4910–13–P COMMODITY FUTURES TRADING COMMISSION 17 CFR Part 30 Foreign Futures and Options Transactions Commodity Futures Trading Commission. AGENCY: E:\FR\FM\22DER1.SGM 22DER1

Agencies

[Federal Register Volume 70, Number 245 (Thursday, December 22, 2005)]
[Rules and Regulations]
[Pages 75933-75934]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-24341]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-22124; Directorate Identifier 2005-NE-21-AD; 
Amendment 39-14427; AD 2005-26-06]
RIN 2120-AA64


Airworthiness Directives; General Electric Company CF6-45A, CF6-
50A, CF6-50C, and CF6-50E Series Turbofan Engines

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

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
General Electric Company (GE) CF6-45A, CF6-50A, CF6-50C, and CF6-50E 
series turbofan engines. This AD requires removing from service pre-GE 
Service Bulletin (SB) No. CF6-50S/B 72-1268 configuration low pressure 
turbine (LPT) stage 2 interstage seal assemblies and stage 3 interstage 
seal assemblies. This AD also requires installing new or reworked 
configuration stage 2 interstage seal assemblies and stage 3 interstage 
seal assemblies. This AD results from reports of fan mid shaft 
separation, leading to separation of the LPT stage 1 disk, disk 
overspeed, and uncontained engine failure. We are issuing this AD to 
prevent uncontained engine failure and damage to the airplane.

DATES: This AD becomes effective January 26, 2006.

ADDRESSES: You can get the service information referenced in this 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.
    You may examine the AD docket on the Internet at https://dms.dot.gov 
or in Room PL-401 on the plaza level of the Nassif Building, 400 
Seventh Street, SW., Washington, DC.

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: The FAA proposed to amend 14 CFR part 39 
with a proposed airworthiness directive (AD). The proposed AD applies 
to GE CF6-45A, CF6-50A, CF6-50C, and CF6-50E series turbofan engines. 
We published the proposed AD in the Federal Register on August 19, 2005 
(70 FR 48660). That action proposed to require removing from service 
pre-GE SB No. CF6-50 S/B 72-1268 configuration LPT stage 2 interstage 
seal assemblies and stage 3 interstage seal assemblies. That action 
also proposed to require installing new or reworked configuration stage 
2 interstage seal assemblies and stage 3 interstage seal assemblies.

Examining the AD Docket

    You may examine the docket that contains the AD, any comments 
received, and any final disposition in person at the Docket Management 
Facility Docket Office 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.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the three comments received. 
The commenters support the proposal.

Conclusion

    We have carefully reviewed the available data, including the 
comments

[[Page 75934]]

received, and determined that air safety and the public interest 
require adopting the AD as proposed.

Costs of Compliance

    There are about 2,079 CF6-45A, CF6-50A, CF6-50C, and CF6-50E series 
turbofan engines of the affected design in the worldwide fleet. We 
estimate that 790 engines installed on airplanes of U.S. registry will 
be affected by this AD. We also estimate that it will take about 5 work 
hours per engine to rework the stage 2 interstage seal assembly and the 
stage 3 interstage seal assembly. The average labor rate is $65 per 
work hour. We estimate that 90% of the affected engines will have the 
parts reworked, and 10% will have new parts installed. A new stage 2 
interstage seal assembly and new stage 3 interstage seal assembly will 
cost about $26,758 per engine. Based on these figures, we estimate the 
total cost of the AD to U.S. operators to be $2,344,957.

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, 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 adding the following new airworthiness 
directive:

2005-26-06 General Electric Company: Amendment 39-14427. Docket No. 
FAA-2005-22124; Directorate Identifier. 2005-NE-21-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective January 
26, 2006.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to General Electric Company (GE) CF6-45A, 
CF6-50A, CF6-50C, and CF6-50E series turbofan engines. These engines 
are installed on, but not limited to, Boeing DC10 and 747 series 
airplanes, and Airbus Industrie A300 series airplanes.

Unsafe Condition

    (d) This AD results from reports of fan mid shaft separation, 
leading to separation of the low pressure turbine (LPT) stage 1 
disk, disk overspeed, and uncontained engine failure. We are issuing 
this AD to prevent uncontained engine failure and damage to the 
airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed at the next disassembly of the LPT stage 2 interstage 
seal assembly and stage 3 interstage seal assembly from the LPT 
stator after the effective date of this AD, but no later than 
December 31, 2010, unless the actions have already been done.

Stage 2 Interstage Seal Assemblies

    (f) Remove from service the pre-GE Service Bulletin (SB) No. 
CF6-50 72-1268 configuration LPT stage 2 interstage seal assembly.
    (g) Install a new or reworked configuration LPT stage 2 
interstage seal assembly, part number (P/N) 9198M81G05, 2092M13G01, 
2092M13G02, or 2092M13G03, or other FAA-approved equivalent part.
    (h) Information on reworking the pre-SB No. CF6-50 S/B 72-1268 
configuration stage 2 interstage seal assembly to the new 
configuration can be found in GE SB No. CF6-50 S/B 72-1268, dated 
December 16, 2004.

Stage 3 Interstage Seal Assemblies

    (i) Remove from service the pre-SB No. CF6-50 S/B 72-1268 
configuration stage 3 interstage seal assembly.
    (j) Install a new or reworked configuration LPT stage 3 
interstage seal assembly, P/N 9044M29G17 or 2092M14G01, or other 
FAA-approved equivalent part.
    (k) Information on reworking the pre-SB No. CF6-50 S/B 72-1268 
configuration stage 3 interstage seal assembly to the new 
configuration can be found in GE SB No. CF6-50 S/B 72-1268, dated 
December 16, 2004.

Prohibition of Pre-SB No. CF6-50 S/B 72-1268 Configurations

    (l) After the effective date of this AD, do not install pre-SB 
No. CF6-50 S/B 72-1268 configuration LPT stage 2 interstage seal 
assemblies or stage 3 interstage seal assemblies into any engine.

Alternative Methods of Compliance

    (m) 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

    (n) National Transportation Safety Board Safety Recommendation 
No. A-98-125, dated December 3, 1998, pertains to the subject of 
this AD.

Material Incorporated by Reference

    (o) None.

    Issued in Burlington, Massachusetts, on December 14, 2005.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 05-24341 Filed 12-21-05; 8:45 am]
BILLING CODE 4910-13-P
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