Airworthiness Directives; General Electric Company (GE) CF34-10E Series Turbofan Engines, 32775-32776 [07-2843]

Download as PDF Federal Register / Vol. 72, No. 114 / Thursday, June 14, 2007 / Rules and Regulations DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–25896; Directorate Identifier 2006–NE–33–AD; Amendment 39– 15093; AD 2007–12–15] RIN 2120–AA64 Airworthiness Directives; General Electric Company (GE) CF34–10E Series Turbofan Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: The FAA is superseding an existing airworthiness directive (AD) for GE CF34–10E series turbofan engines. That AD currently requires removing the fuel inlet strainer from main fuel pump (MFP) part number (P/N) 2043M12P03, installing a certain replacement flange as an interim repair, remarking the MFP to P/N 2043M12P04, and performing initial and repetitive visual inspections of the main fuel filter. This AD requires removing MFPs, P/Ns 2043M12P03, 2043M12P04, 837600–3, and 837600–4, from service and installing an improved MFP with a different P/N. This AD results from GE determining that the cause of MFP fuel strainer failure is a design problem with the strainer. We are issuing this AD to prevent engine in-flight shutdown due to MFP malfunctions. DATES: This AD becomes effective July 19, 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 W12–140 on the ground floor of the West Building, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Kenneth Steeves, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; telephone: (781) 238–7765, fax: (781) 238–7199. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 by superseding AD 2006–20–06, Amendment 39–14775 (71 FR 57403, September 29, 2006), with a proposed AD. The proposed AD applies to GE CF34–10E2A1, –10E5, –10E5A1, –10E6, pwalker on PROD1PC71 with RULES SUMMARY: VerDate Aug<31>2005 17:11 Jun 13, 2007 Jkt 211001 –10E6A1, and –10E7 turbofan engines, with MFP P/Ns 2043M12P03, P/N 2043M12P04, 837600–3, and 837600–4, installed. We published the proposed AD in the Federal Register on September 29, 2006 (71 FR 57403). That action proposed to require removing MFPs, P/N 2043M12P03, 2043M12P04, 83600–3, and 83600–4 from service and installing an improved MFP, not later than July 31, 2007. 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. Address the Use of Parts Manufacturer Approval (PMA) Parts One commenter, Mr. Jack Buster of the Modification and Repair Parts Association (MARPA), states that the PMA part may often share the identical design data with the original part while carrying a completely different part number; therefore, it is possible the AD will not address certain defective PMA parts installed on the aircraft, allowing the unsafe condition to continue. The same commenter also states that it is possible that a ‘‘new and improved’’ PMA version of the defective original part may already exist in the marketplace. Therefore, specifying one approved part in preference to a different, but also approved part, will impart a commercial advantage to one manufacturer over the other. We agree. We changed the final rule to add the PMA P/Ns 837600–3 and 837600–4 to the Applicability and replacement requirements of the final rule. Conclusion We have carefully reviewed the available data, including the comment received, and determined that air safety and the public interest require adopting the AD with the changes described previously. We have determined that these changes will neither increase the PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 32775 economic burden on any operator nor increase the scope of the AD. Costs of Compliance We estimate that this AD will affect 50 CF34–10E series turbofan engines installed on airplanes of U.S. registry. We also estimate that it will take about 3 work-hours per engine to perform the required actions, and that the average labor rate is $80 per work-hour. Required parts will cost about $4,226 per engine to upgrade the MFP to a different P/N to make it serviceable. Based on these figures, we estimate the total upgrade cost of this AD to U.S. operators to be $223,300. 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 E:\FR\FM\14JNR1.SGM 14JNR1 32776 Federal Register / Vol. 72, No. 114 / Thursday, June 14, 2007 / Rules and Regulations this summary at the address listed under ADDRESSES. P/N 2043M12P03, 2043M12P04, 837600–3 or 837600–4. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. Recommended Actions (h) We recommend that operators avoid performing the actions in this AD on both engines installed on the same airplane at the same time, if at all possible. Adoption of the Amendment Alternative Methods of Compliance (i) The Manager, Engine Certification Office, FAA, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. 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 removing Amendment 39–14775 (71 FR 57403, September 29, 2006) and by adding a new airworthiness directive, Amendment 39–15093, to read as follows: I 2007–12–15 General Electric Company: Amendment 39–15093. Docket No. FAA–2005–25896; Directorate Identifier 2006–NE–33–AD. DEPARTMENT OF TRANSPORTATION Affected ADs (b) This AD supersedes AD 2006–20–06, Amendment 39–14755. Federal Aviation Administration Applicability (c) This AD applies to General Electric Company (GE) CF34–10E2A1, –10E5, –10E5A1, –10E6, –10E6A1, and –10E7 turbofan engines, with main fuel pump (MFP) part number (P/N) 2043M12P03, P/N 2043M12P04, P/N 837600–3, and P/N 837600–4 installed. These engines are installed on, but not limited to, Embraer ERJ 190–100–STD, ERJ 190–100–LR, and ERJ 190–100–IGW airplanes. Unsafe Condition (d) This AD results from GE determining that the cause of MFP fuel strainer failure is a design problem with the strainer. We are issuing this AD to prevent engine in-flight shutdown due to MFP malfunctions. pwalker on PROD1PC71 with RULES 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. Definition (g) For the purpose of this AD, a serviceable MFP is one that does not have VerDate Aug<31>2005 17:11 Jun 13, 2007 Jkt 211001 Issued in Burlington, Massachusetts, on June 1, 2007. Peter A. White, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 07–2843 Filed 6–13–07; 8:45 am] BILLING CODE 4910–13–P Effective Date (a) This airworthiness directive (AD) becomes effective July 19, 2007. MFP Removal and Installation (f) Not later than July 31, 2007, remove MFPs, P/Ns 2043M12P03, 2043M12P04, 837600–3, and 837600–4 from service and install a serviceable MFP. Related Information (j) GE Service Bulletin No. CF34–10E S/B 73–0013, dated December 15, 2006, pertains to the subject of this AD. (k) Contact Kenneth Steeves, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; telephone (781) 238–7765, fax (781) 238–7199, for more information about this AD. 14 CFR Part 39 [Docket No. FAA–2007–27849; Directorate Identifier 2006–NM–249–AD; Amendment 39–15094; AD 2007–12–16] RIN 2120–AA64 Airworthiness Directives; Dassault Model Falcon 2000EX and Falcon 900EX Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an airworthiness authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as some stringer reinforcements (F900DX) and some rivets (F900DX/F2000EX) missing from the skin panels on each side of the fuselage between frames 9 and 10 on certain Falcon 900DX and Falcon 2000EX EASy aircraft; this situation PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 affects the structural integrity of the fuselage. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective July 19, 2007. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of July 19, 2007. ADDRESSES: You may examine the AD docket on the Internet at http:// dms.dot.gov or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC. FOR FURTHER INFORMATION CONTACT: Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1137; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Discussion The FAA is implementing a new process for streamlining the issuance of ADs related to MCAI. This streamlined process will allow us to adopt MCAI safety requirements in a more efficient manner and will reduce safety risks to the public. This process continues to allow all FAA AD issuance processes to meet legal, economic, Administrative Procedure Act, and Federal Register requirements. We also continue to meet our technical decision-making responsibilities to identify and correct unsafe conditions on U.S.-certificated products. This AD references the MCAI and related service information that we considered in forming the engineering basis to correct the unsafe condition. The AD contains text copied from the MCAI and for this reason might not follow our plain language principles. We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on April 12, 2007 (72 FR 18415). That NPRM proposed to require inspecting skin panels on each side of the fuselage between frames 9 and 10, including holes and structure, where missing rivets are found, adding missing rivets and stringer caps, as applicable, and contacting the manufacturer if the holes are out-of-round beyond tolerance, or if cracks are found, as applicable. The MCAI states that following the incorporation of a design change to the Karman fairing, it has been determined that some stringer reinforcements E:\FR\FM\14JNR1.SGM 14JNR1

Agencies

[Federal Register Volume 72, Number 114 (Thursday, June 14, 2007)]
[Rules and Regulations]
[Pages 32775-32776]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 07-2843]



[[Page 32775]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-25896; Directorate Identifier 2006-NE-33-AD; 
Amendment 39-15093; AD 2007-12-15]
RIN 2120-AA64


Airworthiness Directives; General Electric Company (GE) CF34-10E 
Series Turbofan Engines

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

ACTION: Final rule.

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

SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD) for GE CF34-10E series turbofan engines. That AD currently 
requires removing the fuel inlet strainer from main fuel pump (MFP) 
part number (P/N) 2043M12P03, installing a certain replacement flange 
as an interim repair, remarking the MFP to P/N 2043M12P04, and 
performing initial and repetitive visual inspections of the main fuel 
filter. This AD requires removing MFPs, P/Ns 2043M12P03, 2043M12P04, 
837600-3, and 837600-4, from service and installing an improved MFP 
with a different P/N. This AD results from GE determining that the 
cause of MFP fuel strainer failure is a design problem with the 
strainer. We are issuing this AD to prevent engine in-flight shutdown 
due to MFP malfunctions.

DATES: This AD becomes effective July 19, 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 W12-140 on the ground floor of the West Building, 1200 New 
Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Kenneth Steeves, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; telephone: (781) 238-
7765, fax: (781) 238-7199.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 by 
superseding AD 2006-20-06, Amendment 39-14775 (71 FR 57403, September 
29, 2006), with a proposed AD. The proposed AD applies to GE CF34-
10E2A1, -10E5, -10E5A1, -10E6, -10E6A1, and -10E7 turbofan engines, 
with MFP P/Ns 2043M12P03, P/N 2043M12P04, 837600-3, and 837600-4, 
installed. We published the proposed AD in the Federal Register on 
September 29, 2006 (71 FR 57403). That action proposed to require 
removing MFPs, P/N 2043M12P03, 2043M12P04, 83600-3, and 83600-4 from 
service and installing an improved MFP, not later than July 31, 2007.

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.

Address the Use of Parts Manufacturer Approval (PMA) Parts

    One commenter, Mr. Jack Buster of the Modification and Repair Parts 
Association (MARPA), states that the PMA part may often share the 
identical design data with the original part while carrying a 
completely different part number; therefore, it is possible the AD will 
not address certain defective PMA parts installed on the aircraft, 
allowing the unsafe condition to continue.
    The same commenter also states that it is possible that a ``new and 
improved'' PMA version of the defective original part may already exist 
in the marketplace. Therefore, specifying one approved part in 
preference to a different, but also approved part, will impart a 
commercial advantage to one manufacturer over the other.
    We agree. We changed the final rule to add the PMA P/Ns 837600-3 
and 837600-4 to the Applicability and replacement requirements of the 
final rule.

Conclusion

    We have carefully reviewed the available data, including the 
comment received, and determined that air safety and the public 
interest require adopting the AD with the changes described previously. 
We have determined that these changes will neither increase the 
economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

    We estimate that this AD will affect 50 CF34-10E series turbofan 
engines installed on airplanes of U.S. registry. We also estimate that 
it will take about 3 work-hours per engine to perform the required 
actions, and that the average labor rate is $80 per work-hour. Required 
parts will cost about $4,226 per engine to upgrade the MFP to a 
different P/N to make it serviceable. Based on these figures, we 
estimate the total upgrade cost of this AD to U.S. operators to be 
$223,300.

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

[[Page 32776]]

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 removing Amendment 39-14775 (71 FR 
57403, September 29, 2006) and by adding a new airworthiness directive, 
Amendment 39-15093, to read as follows:

2007-12-15 General Electric Company: Amendment 39-15093. Docket No. 
FAA-2005-25896; Directorate Identifier 2006-NE-33-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective July 19, 
2007.

Affected ADs

    (b) This AD supersedes AD 2006-20-06, Amendment 39-14755.

Applicability

    (c) This AD applies to General Electric Company (GE) CF34-
10E2A1, -10E5, -10E5A1, -10E6, -10E6A1, and -10E7 turbofan engines, 
with main fuel pump (MFP) part number (P/N) 2043M12P03, P/N 
2043M12P04, P/N 837600-3, and P/N 837600-4 installed. These engines 
are installed on, but not limited to, Embraer ERJ 190-100-STD, ERJ 
190-100-LR, and ERJ 190-100-IGW airplanes.

Unsafe Condition

    (d) This AD results from GE determining that the cause of MFP 
fuel strainer failure is a design problem with the strainer. We are 
issuing this AD to prevent engine in-flight shutdown due to MFP 
malfunctions.

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.

MFP Removal and Installation

    (f) Not later than July 31, 2007, remove MFPs, P/Ns 2043M12P03, 
2043M12P04, 837600-3, and 837600-4 from service and install a 
serviceable MFP.

Definition

    (g) For the purpose of this AD, a serviceable MFP is one that 
does not have P/N 2043M12P03, 2043M12P04, 837600-3 or 837600-4.

Recommended Actions

    (h) We recommend that operators avoid performing the actions in 
this AD on both engines installed on the same airplane at the same 
time, if at all possible.

Alternative Methods of Compliance

    (i) The Manager, Engine Certification Office, FAA, 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) GE Service Bulletin No. CF34-10E S/B 73-0013, dated December 
15, 2006, pertains to the subject of this AD.
    (k) Contact Kenneth Steeves, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; telephone (781) 238-
7765, fax (781) 238-7199, for more information about this AD.

    Issued in Burlington, Massachusetts, on June 1, 2007.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 07-2843 Filed 6-13-07; 8:45 am]
BILLING CODE 4910-13-P