Airworthiness Directives; General Electric Company (GE) CT58 Series Turboshaft Engines, 63629-63630 [E8-25442]

Download as PDF Federal Register / Vol. 73, No. 208 / Monday, October 27, 2008 / Rules and Regulations 63629 Sandy K. Baruah, Acting Administrator. [FR Doc. E8–25324 Filed 10–24–08; 8:45 am] BILLING CODE 8025–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–0808; Directorate Identifier 2008–NE–18–AD; Amendment 39– 15712; AD 2008–22–16] RIN 2120–AA64 Airworthiness Directives; General Electric Company (GE) CT58 Series Turboshaft Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. sroberts on PROD1PC70 with RULES AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain GE CT58 series turboshaft engines. This AD requires recalculating the lives of certain part numbered compressor spools using a new repetitive heavy lift (RHL) multiplying factor. This AD results from reports of cracks originating from the inner faces of the locking screw holes in the compressor spool. We are issuing this AD to prevent cracks due to RHL missions. Cracks could result in an uncontained rotor burst and damage to, or loss of, the helicopter and serious injuries to any person onboard. DATES: This AD becomes effective December 1, 2008. ADDRESSES: You can get the service information identified in this AD from GE Aircraft Engines Customer Support Center, M/D 285, 1 Neumann Way, Evendale, OH 45215; telephone (513) 552–3272; fax (513) 552–3329; e-mail GEAE.csc@ae.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: Christopher J. Richards, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: VerDate Aug<31>2005 17:05 Oct 24, 2008 Jkt 214001 christopher.j.richards@faa.gov; telephone (781) 238–7133; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 with a proposed AD. The proposed AD applies to certain GE CT58 series turboshaft engines. We published the proposed AD in the Federal Register on July 23, 2008 (73 FR 42724). That action proposed to require recalculating the cycles on certain compressor spools using new RHL mission multipliers within 30 days after the effective date of the proposed AD. 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. Examining the AD Docket (12) Final agency action. The decision of the hearing official is the final agency decision for the purposes of judicial review under the Administrative Procedure Act (5 U.S.C. 701 et seq.). * * * * * Regulatory Findings 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. 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. Comments We provided the public the opportunity to participate in the development of this AD. We received no comments on the proposal or on the determination of the cost to the public. Conclusion We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. Costs of Compliance We estimate that this proposed AD will affect 89 engines installed on helicopters of U.S. registry. We also estimate that it will take about 0.5 workhour per engine to perform the proposed actions, and that the average labor rate is $80 per work-hour. Prorated life lost for the compressor spools will cost about $16,972 per engine. Based on these figures, we estimate the total cost of this AD to U.S. operators to be $1,514,068. 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: ■ 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. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: ■ 2008–22–16 General Electric Company (GE): Amendment 39–15712. Docket No. FAA–2008–0808; Directorate Identifier 2008–NE–18–AD. E:\FR\FM\27OCR1.SGM 27OCR1 63630 Federal Register / Vol. 73, No. 208 / Monday, October 27, 2008 / Rules and Regulations Effective Date AD if requested using the procedures found in 14 CFR 39.19. (a) This airworthiness directive (AD) becomes effective December 1, 2008. Affected ADs (b) None. Applicability (c) This AD applies to GE CT58 series turboshaft engines with a compressor spool, part number (P/N) 5920T82G07, 6010T57G07, or 6010T57G08, installed. These engines are installed on, but not limited to, Sikorsky S–61A, S–61L, S–61N, S–61R, S–62, and Columbia 107–II helicopters. Unsafe Condition (d) This AD results from reports of cracks originating from the inner faces of the locking screw holes in the compressor spool. We are issuing this AD to prevent cracks due to repetitive heavy lift (RHL) missions. Cracks could result in an uncontained rotor burst and damage to, or loss of, the helicopter and serious injuries to any person onboard. Related Information (l) GE Alert Service Bulletin CT58 S/B 72– A0162, Revision 12, dated April 17, 2008, pertains to the subject of this AD. (m) Contact Christopher J. Richards, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: christopher.j.richards@faa.gov; telephone (781) 238–7133; fax (781) 238–7199, for more information about this AD. Material Incorporated by Reference (n) None. Issued in Burlington, Massachusetts, on October 20, 2008. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E8–25442 Filed 10–24–08; 8:45 am] BILLING CODE 4910–13–P 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. Recalculating Compressor Spool Cycles (f) Within 30 days after the effective date of this AD, recalculate the life of compressor spools, P/N 5920T82G07, 6010T57G07, or 6010T57G08, using an RHL mission multiplying factor of both 3.7 cycles per hour and 6.0 cycles per hour. GE Alert Service Bulletin CT58 S/B 72–A0162, Revision 12, dated April 17, 2008, contains information on calculating life cycles for the compressor spools. sroberts on PROD1PC70 with RULES Removing Compressor Spools Based on the New Recalculated Cycles (g) Before January 1, 2010, remove the compressor spools, P/N 5920T82G07, 6010T57G07, or 6010T57G08, at the earlier of when: (1) The compressor spool reaches its part life limit as calculated using an RHL multiplying factor of 3.7, or (2) You can see the spool at shop visit after it has reached its part life limit using an RHL multiplying factor of 6.0. (h) On January 1, 2010 and thereafter, remove the engine before the compressor spool exceeds its part life limit as calculated using an RHL multiplying factor of 6.0. (i) As of January 1, 2010, don’t use an RHL multiplying factor of 3.7 to calculate the life of the compressor spool. Installation Prohibition (j) After the effective date of this AD, don’t install any engine that has a compressor spool installed that meets or exceeds the life limits as calculated in paragraph (g)(1) through (g)(2) or (h) of this AD. Alternative Methods of Compliance (k) The Manager, Engine Certification Office, has the authority to approve alternative methods of compliance for this VerDate Aug<31>2005 18:13 Oct 24, 2008 Jkt 214001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 417 [Docket No. FAA–2000–7953; Amendment No. 417] RIN 2120–AG37 Licensing and Safety Requirements for Launch Federal Aviation Administration, DOT. ACTION: Final rule; technical amendment. AGENCY: SUMMARY: This action corrects reference errors that appeared in a final rule the FAA published in the Federal Register on August 25, 2006. The final rule amended commercial space transportation regulations governing the launch of expendable launch vehicles. In that final rule, the FAA inadvertently referenced incorrect sections. The intent of this action is to correct this minor error in the regulation to ensure the requirement is clear and accurate. DATES: Effective October 27, 2008. FOR FURTHER INFORMATION CONTACT: ´ Rene Rey, Licensing and Safety Division, AST–200, Federal Aviation Administration, 800 Independence Avenue, SW., Washington, DC 20591; telephone (202) 267–7538; e-mail Rene.Rey@faa.gov. For questions regarding legal interpretation, contact Laura Montgomery, AGC–200, (202) 267–3150; e-mail laura.montgomery@faa.gov. SUPPLEMENTARY INFORMATION: On August 25, 2006, the FAA published a final rule PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 in the Federal Register (71 FR 50537) that, among other changes, amended § 417.25(c)(3). The FAA inadvertently referenced incorrect sections in 14 CFR 417.25(c)(3). As published, this provision requires a post launch report to identify any flight environment not consistent with the maximum predicted environment as required by § 417.307(b) and any measured wind profiles not consistent with the predictions used for the launch, as required by § 417.217(d)(2). These references are incorrect. They should refer launch operators to Appendix D 417.7(b) and Appendix A 417.7(g)(3), respectively. This amendment will not impose any additional restrictions on operators affected by these regulations. Technical Amendment This technical amendment corrects the references in § 417.25(c)(3). Justification for Immediate Adoption Because this action merely corrects a reference made in the published rule, the FAA finds that notice and public comment under 5 U.S.C. 553(b) is not necessary. For the same reason, the FAA finds good cause exists under 5 U.S.C. 553(d) for making this rule effective upon publication. List of Subjects in 14 CFR Part 417 Aviation safety, Reporting and recordkeeping requirements, Rockets, Space transportation and exploration. ■ Accordingly, Title 14 of the Code of Federal Regulations (CFR) part 417 is amended as follows: PART 417—LAUNCH SAFETY 1. The authority citation for part 417 continues to read as follows: ■ Authority: 49 U.S.C. 70101–70121. 2. Amend § 417.25 by revising paragraph (c)(3) to read as follows: ■ § 417.25 Post launch report. (c) * * * (3) For the launch of launch vehicle flown with a flight safety system, identify any flight environment not consistent with the maximum predicted environment as required by D 417.7(b) and any measured wind profiles not consistent with the predictions used for the launch, as required by § 417.7(g)(3); and * * * * * Issued in Washington, DC on October 22, 2008. Pamela Hamilton-Powell, Director, Office of Rulemaking. [FR Doc. E8–25506 Filed 10–24–08; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\27OCR1.SGM 27OCR1

Agencies

[Federal Register Volume 73, Number 208 (Monday, October 27, 2008)]
[Rules and Regulations]
[Pages 63629-63630]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-25442]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0808; Directorate Identifier 2008-NE-18-AD; 
Amendment 39-15712; AD 2008-22-16]
RIN 2120-AA64


Airworthiness Directives; General Electric Company (GE) CT58 
Series Turboshaft Engines

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

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain GE CT58 series turboshaft engines. This AD requires 
recalculating the lives of certain part numbered compressor spools 
using a new repetitive heavy lift (RHL) multiplying factor. This AD 
results from reports of cracks originating from the inner faces of the 
locking screw holes in the compressor spool. We are issuing this AD to 
prevent cracks due to RHL missions. Cracks could result in an 
uncontained rotor burst and damage to, or loss of, the helicopter and 
serious injuries to any person onboard.

DATES: This AD becomes effective December 1, 2008.

ADDRESSES: You can get the service information identified in this AD 
from GE Aircraft Engines Customer Support Center, M/D 285, 1 Neumann 
Way, Evendale, OH 45215; telephone (513) 552-3272; fax (513) 552-3329; 
e-mail GEAE.csc@ae.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: Christopher J. Richards, Aerospace 
Engineer, Engine Certification Office, FAA, Engine & Propeller 
Directorate, 12 New England Executive Park, Burlington, MA 01803; e-
mail: christopher.j.richards@faa.gov; telephone (781) 238-7133; fax 
(781) 238-7199.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 
with a proposed AD. The proposed AD applies to certain GE CT58 series 
turboshaft engines. We published the proposed AD in the Federal 
Register on July 23, 2008 (73 FR 42724). That action proposed to 
require recalculating the cycles on certain compressor spools using new 
RHL mission multipliers within 30 days after the effective date of the 
proposed AD.

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 received no comments on the proposal or on 
the determination of the cost to the public.

Conclusion

    We have carefully reviewed the available data and determined that 
air safety and the public interest require adopting the AD as proposed.

Costs of Compliance

    We estimate that this proposed AD will affect 89 engines installed 
on helicopters of U.S. registry. We also estimate that it will take 
about 0.5 work-hour per engine to perform the proposed actions, and 
that the average labor rate is $80 per work-hour. Prorated life lost 
for the compressor spools will cost about $16,972 per engine. Based on 
these figures, we estimate the total cost of this AD to U.S. operators 
to be $1,514,068.

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:

2008-22-16 General Electric Company (GE): Amendment 39-15712. Docket 
No. FAA-2008-0808; Directorate Identifier 2008-NE-18-AD.

[[Page 63630]]

Effective Date

    (a) This airworthiness directive (AD) becomes effective December 
1, 2008.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to GE CT58 series turboshaft engines with a 
compressor spool, part number (P/N) 5920T82G07, 6010T57G07, or 
6010T57G08, installed. These engines are installed on, but not 
limited to, Sikorsky S-61A, S-61L, S-61N, S-61R, S-62, and Columbia 
107-II helicopters.

Unsafe Condition

    (d) This AD results from reports of cracks originating from the 
inner faces of the locking screw holes in the compressor spool. We 
are issuing this AD to prevent cracks due to repetitive heavy lift 
(RHL) missions. Cracks could result in an uncontained rotor burst 
and damage to, or loss of, the helicopter and serious injuries to 
any person onboard.

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.

Recalculating Compressor Spool Cycles

    (f) Within 30 days after the effective date of this AD, 
recalculate the life of compressor spools, P/N 5920T82G07, 
6010T57G07, or 6010T57G08, using an RHL mission multiplying factor 
of both 3.7 cycles per hour and 6.0 cycles per hour. GE Alert 
Service Bulletin CT58 S/B 72-A0162, Revision 12, dated April 17, 
2008, contains information on calculating life cycles for the 
compressor spools.

Removing Compressor Spools Based on the New Recalculated Cycles

    (g) Before January 1, 2010, remove the compressor spools, P/N 
5920T82G07, 6010T57G07, or 6010T57G08, at the earlier of when:
    (1) The compressor spool reaches its part life limit as 
calculated using an RHL multiplying factor of 3.7, or
    (2) You can see the spool at shop visit after it has reached its 
part life limit using an RHL multiplying factor of 6.0.
    (h) On January 1, 2010 and thereafter, remove the engine before 
the compressor spool exceeds its part life limit as calculated using 
an RHL multiplying factor of 6.0.
    (i) As of January 1, 2010, don't use an RHL multiplying factor 
of 3.7 to calculate the life of the compressor spool.

Installation Prohibition

    (j) After the effective date of this AD, don't install any 
engine that has a compressor spool installed that meets or exceeds 
the life limits as calculated in paragraph (g)(1) through (g)(2) or 
(h) of this AD.

Alternative Methods of Compliance

    (k) 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

    (l) GE Alert Service Bulletin CT58 S/B 72-A0162, Revision 12, 
dated April 17, 2008, pertains to the subject of this AD.
    (m) Contact Christopher J. Richards, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
christopher.j.richards@faa.gov; telephone (781) 238-7133; fax (781) 
238-7199, for more information about this AD.

Material Incorporated by Reference

    (n) None.

    Issued in Burlington, Massachusetts, on October 20, 2008.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E8-25442 Filed 10-24-08; 8:45 am]
BILLING CODE 4910-13-P