Airworthiness Directives; General Electric Company CF34-10E Series Turbofan Engines, 30955-30956 [E7-10746]

Download as PDF 30955 Rules and Regulations Federal Register Vol. 72, No. 107 Tuesday, June 5, 2007 This section of the FEDERAL REGISTER contains regulatory documents having general applicability and legal effect, most of which are keyed to and codified in the Code of Federal Regulations, which is published under 50 titles pursuant to 44 U.S.C. 1510. The Code of Federal Regulations is sold by the Superintendent of Documents. Prices of new books are listed in the first FEDERAL REGISTER issue of each week. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–26585; Directorate Identifier 2006–NE–44–AD; Amendment 39– 15087; AD 2007–12–09] RIN 2120–AA64 Airworthiness Directives; General Electric Company CF34–10E 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) CF34–10E series turbofan engines. This AD requires revising the combustor case published life limit and removing combustor cases from service before reaching a reduced life limit. This AD results from GE’s evaluation of the effects to the combustor case due to installing version 5.10 software in the full-authority digital electronic control (FADEC), and revising the combustor case published life limit. We are issuing this AD to prevent uncontained combustor case failure resulting in an in-flight engine shutdown and possible damage to the airplane. This AD becomes effective July 10, 2007. ADDRESSES: You may examine the AD docket on the Internet at http:// 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: Tara Chaidez, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; cprice-sewell on PROD1PC71 with RULES DATES: VerDate Aug<31>2005 15:27 Jun 04, 2007 Jkt 211001 e-mail: tara.chaidez@faa.gov; telephone (781) 238–7773; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 with a proposed AD. The proposed AD applies to GE CF34–10E series turbofan engines. We published the proposed AD in the Federal Register on January 17, 2007 (72 FR 1946). That action proposed to require revising the combustor case published life limit and removing combustor cases from service before reaching a reduced life limit. 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 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 received no comments on the proposal or on the determination of the cost to the public. Elimination of Paragraph (g) After we issued the proposed AD, our review indicated that we should simplify the compliance by eliminating paragraph (g). That paragraph is redundant to paragraph (f), and would only add an additional requirement for the operators to show compliance after removal of every affected part. We eliminated the proposed AD paragraph (g), and re-codified the paragraphs, in this AD. 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 AD will affect 42 CF34–10E series turbofan engines installed on airplanes of U.S. registry. This combustor case removal does not impose any additional labor costs if performed at the time of scheduled PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 engine overhaul. The financial burden to the operators (prorate) is about $140,080 per engine due to the reduction in the life limit. Based on these figures, and on the prorating for the usage of the combustor cases, we estimate the cost of the AD on U.S. operators to be $5,886,720. 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. E:\FR\FM\05JNR1.SGM 05JNR1 30956 Federal Register / Vol. 72, No. 107 / Tuesday, June 5, 2007 / Rules and Regulations 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 2007–12–09 General Electric Company: Amendment 39–15087. Docket No. FAA–2006–26585; Directorate Identifier 2006–NE–44–AD. alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. Related Information (i) Contact Tara Chaidez, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: tara.chaidez@faa.gov; telephone (781) 238–7773, fax (781) 238– 7199, for more information about this AD. Issued in Burlington, Massachusetts, on May 30, 2007. Robert Ganley, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E7–10746 Filed 6–4–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 Effective Date (a) This airworthiness directive (AD) becomes effective July 10, 2007. [Docket No. FAA–2006–26488; Directorate Identifier 2006–NE–43–AD; Amendment 39– 15077; AD 2007–11–20] Affected ADs (b) None. RIN 2120–AA64 Applicability (c) This AD applies to General Electric Company (GE) CF34–10E2A1, CF34–10E5, CF34–10E5A1, CF34–10E6, CF34–10E6A1, and CF34–10E7 turbofan engines. These engines are installed on, but not limited to, Embraer ERJ–190 and –195 airplanes. cprice-sewell on PROD1PC71 with RULES Unsafe Condition (d) This AD results from GE’s evaluation of the effects to the combustor case due to installing version 5.10 software in the fullauthority digital electronic control (FADEC), and revising the combustor case published life limit. We are issuing this AD to prevent uncontained combustor case failure resulting in an in-flight engine shutdown and possible damage to the airplane. Compliance (e) You are responsible for having the actions required by this AD performed within 30 days after the effective date of this AD, unless the actions have already been done. (f) Revise the published life limit in the Airworthiness Limitations Section of the CF34–10E Engine Manual, for combustor cases, part number (P/N) 2070M47G02 and P/N 2070M47G03, from 39,600 cycles-sincenew (CSN) to 24,600 CSN. (g) The requirements of this AD have been met when the engine manual changes are made and operators have modified their continuous airworthiness maintenance plans to reflect the Engine Maintenance Program requirements specified in the GE CF34–10E Engine Manual. Alternative Methods of Compliance (h) The Manager, Engine Certification Office, has the authority to approve VerDate Aug<31>2005 15:27 Jun 04, 2007 Jkt 211001 Airworthiness Directives; General Electric Company (GE) CF6–80 Series Turbofan Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: The FAA is adopting a new airworthiness directive (AD) for GE CF6–80 series turbofan engines with fuel shroud retaining rings, part number (P/N) J204P0084, installed. This AD requires replacing those retaining rings with a more robust design fuel shroud retaining snap ring. This AD results from two events of external engine fuel leakage and a subsequent under-cowl engine fire. We are issuing this AD to prevent an under-cowl engine fire and damage to the airplane during an engine high vibration event. DATES: This AD becomes effective July 10, 2007. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of July 10, 2007. ADDRESSES: You can get the service information identified 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 http://dms.dot.gov or in Room PL–401 on the plaza level of the SUMMARY: PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 Nassif Building, 400 Seventh Street, SW., Washington, DC. FOR FURTHER INFORMATION CONTACT: James Lawrence, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: james.lawrence@faa.gov; telephone: (781) 238–7176, fax: (781) 238–7199. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 with a proposed AD. The proposed AD applies to GE CF6–80 series turbofan engines with fuel shroud retaining rings, part number (P/N) J204P0084, installed. We published the proposed AD in the Federal Register on February 15, 2007 (72 FR 7355). That action proposed to require replacing those retaining rings with a more robust design fuel shroud retaining snap ring. 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 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 comments received. Comment That Table 1 Compliance Schedule Is Somewhat Difficult To Follow One commenter, GE, states that the Table 1 compliance schedule in the proposed AD is somewhat difficult to follow. The commenter states that the table needs lines or spaces added, to separate some of the items in it, for clarity. We agree that the Table 1 compliance schedule in the proposed AD is difficult to follow. We have deleted the Table 1 compliance schedule from this AD, based on comments received on the proposed AD, and which are discussed in the paragraphs that follow. Request To Reduce the AD Applicability GE requests that we reduce the AD applicability to only engines with the drainless manifold configuration, since the drained manifold configuration is E:\FR\FM\05JNR1.SGM 05JNR1

Agencies

[Federal Register Volume 72, Number 107 (Tuesday, June 5, 2007)]
[Rules and Regulations]
[Pages 30955-30956]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-10746]



========================================================================
Rules and Regulations
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains regulatory documents 
having general applicability and legal effect, most of which are keyed 
to and codified in the Code of Federal Regulations, which is published 
under 50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by the Superintendent of Documents. 
Prices of new books are listed in the first FEDERAL REGISTER issue of each 
week.

========================================================================


Federal Register / Vol. 72, No. 107 / Tuesday, June 5, 2007 / Rules 
and Regulations

[[Page 30955]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-26585; Directorate Identifier 2006-NE-44-AD; 
Amendment 39-15087; AD 2007-12-09]
RIN 2120-AA64


Airworthiness Directives; General Electric Company CF34-10E 
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) CF34-10E series turbofan engines. This AD 
requires revising the combustor case published life limit and removing 
combustor cases from service before reaching a reduced life limit. This 
AD results from GE's evaluation of the effects to the combustor case 
due to installing version 5.10 software in the full-authority digital 
electronic control (FADEC), and revising the combustor case published 
life limit. We are issuing this AD to prevent uncontained combustor 
case failure resulting in an in-flight engine shutdown and possible 
damage to the airplane.

DATES: This AD becomes effective July 10, 2007.

ADDRESSES: You may examine the AD docket on the Internet at http://
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: Tara Chaidez, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; e-mail: 
tara.chaidez@faa.gov; telephone (781) 238-7773; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 
with a proposed AD. The proposed AD applies to GE CF34-10E series 
turbofan engines. We published the proposed AD in the Federal Register 
on January 17, 2007 (72 FR 1946). That action proposed to require 
revising the combustor case published life limit and removing combustor 
cases from service before reaching a reduced life limit.

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

Elimination of Paragraph (g)

    After we issued the proposed AD, our review indicated that we 
should simplify the compliance by eliminating paragraph (g). That 
paragraph is redundant to paragraph (f), and would only add an 
additional requirement for the operators to show compliance after 
removal of every affected part. We eliminated the proposed AD paragraph 
(g), and re-codified the paragraphs, in this AD.

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 AD will affect 42 CF34-10E series turbofan 
engines installed on airplanes of U.S. registry. This combustor case 
removal does not impose any additional labor costs if performed at the 
time of scheduled engine overhaul. The financial burden to the 
operators (prorate) is about $140,080 per engine due to the reduction 
in the life limit. Based on these figures, and on the prorating for the 
usage of the combustor cases, we estimate the cost of the AD on U.S. 
operators to be $5,886,720.

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.

[[Page 30956]]

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:

2007-12-09 General Electric Company: Amendment 39-15087. Docket No. 
FAA-2006-26585; Directorate Identifier 2006-NE-44-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective July 10, 
2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to General Electric Company (GE) CF34-
10E2A1, CF34-10E5, CF34-10E5A1, CF34-10E6, CF34-10E6A1, and CF34-
10E7 turbofan engines. These engines are installed on, but not 
limited to, Embraer ERJ-190 and -195 airplanes.

Unsafe Condition

    (d) This AD results from GE's evaluation of the effects to the 
combustor case due to installing version 5.10 software in the full-
authority digital electronic control (FADEC), and revising the 
combustor case published life limit. We are issuing this AD to 
prevent uncontained combustor case failure resulting in an in-flight 
engine shutdown and possible damage to the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within 30 days after the effective date of this AD, 
unless the actions have already been done.
    (f) Revise the published life limit in the Airworthiness 
Limitations Section of the CF34-10E Engine Manual, for combustor 
cases, part number (P/N) 2070M47G02 and P/N 2070M47G03, from 39,600 
cycles-since-new (CSN) to 24,600 CSN.
    (g) The requirements of this AD have been met when the engine 
manual changes are made and operators have modified their continuous 
airworthiness maintenance plans to reflect the Engine Maintenance 
Program requirements specified in the GE CF34-10E Engine Manual.

Alternative Methods of Compliance

    (h) 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

    (i) Contact Tara Chaidez, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
tara.chaidez@faa.gov; telephone (781) 238-7773, fax (781) 238-7199, 
for more information about this AD.

    Issued in Burlington, Massachusetts, on May 30, 2007.
Robert Ganley,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
 [FR Doc. E7-10746 Filed 6-4-07; 8:45 am]
BILLING CODE 4910-13-P