Airworthiness Directives; General Electric Aircraft Engines (GE) CF34-3A1/-3B/-3B1 Turbofan Engines, 10054-10057 [E7-3833]

Download as PDF 10054 Federal Register / Vol. 72, No. 44 / Wednesday, March 7, 2007 / Rules and Regulations Effective Date Other FAA AD Provisions (a) This airworthiness directive (AD) becomes effective April 11, 2007. (d) The mandatory continuing airworthiness information (MCAI) states: This AD is issued following a nose landing gear collapse during takeoff roll. Several expertises proved that the locking device of the Nose Landing Gear (NLG) actuator rod was on several F406 airplanes not conforming with the installation approved by the manufacturer. There were two different landing gear actuator designs installed on the Model F406 airplanes (Teijin Seiki and Cessna). The actuators used different locking devices to retain the spherical rod-end to the actuator rod. Use of the incorrect locking device could allow the spherical rod-end to disconnect from the actuator rod, and consequently the landing gear could collapse. (f) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Staff, FAA, ATTN: Mike Kiesov, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4144; fax: (816) 329–4090, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. (2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service. (3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et. seq.), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056. Actions and Compliance Related Information (e) Unless already done, do the following actions: (1) Within 3 months or 100 hours time-inservice (TIS) after April 11, 2007 (the effective date of this AD), whichever occurs first: (i) For airplanes with Teijin Seiki Nose Landing Gear (NLG) P/N 9910139–9: inspect the NLG for conformity with the key lock system installation description in Figure 1 of the REIMS AVIATION INDUSTRIES Service Bulletin No. F406–56, dated April 12, 2005; (ii) For airplanes with Cessna NLG P/N 9910139–9: inspect the NLG for conformity with the key lock system installation description in Figure 2 of the REIMS AVIATION INDUSTRIES Service Bulletin No. F406–56, dated April 12, 2005; (iii) For airplanes with Teijin Seiki Main Landing Gear (MLG) P/N 9910136–8: inspect the MLG for conformity with the key lock system installation description in Figure 3 of the REIMS AVIATION INDUSTRIES Service Bulletin No. F406–56, dated April 12, 2005; and (iv) For airplanes with Cessna MLG P/N 9910136–8: inspect the MLG for conformity with the key lock system installation description in Figure 4 of the REIMS AVIATION INDUSTRIES Service Bulletin No. F406–56, dated April 12, 2005. (2) Before further flight after any inspection from (e)(1) of this AD where the key lock system does not conform to the appropriate installation description, install a key lock system that conforms to the appropriate installation description. ´ ´ (g) Refer to MCAI Direction generale de l’aviation civile AD No. F–2005–065, dated April 27, 2005, for related information. Affected ADs (b) None. Applicability (c) This AD applies to Model F406 airplanes, all serial numbers, certificated in any category. sroberts on PROD1PC70 with RULES Reason FAA AD Differences Note: This AD differs from the MCAI and/ or service information as follows: No differences. VerDate Aug<31>2005 15:48 Mar 06, 2007 Jkt 211001 DEPARTMENT OF TRANSPORTATION Material Incorporated by Reference (h) You must use REIMS AVIATION INDUSTRIES Service Bulletin No. F406–56, dated April 12, 2005, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact REIMS AVIATION ´ INDUSTRIES, Aerodrome de Reims Prunay, 51360 Prunay, France, A l’attention du Support Client; telephone: 03.26.48.46.53; fax: 03.26.49.18.57. (3) You may review copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http://www.archives.gov/federal-register/ cfr/ibr-locations.html. Issued in Kansas City, Missouri, on February 23, 2007. Kim Smith, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–3835 Filed 3–6–07; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00022 Fmt 4700 Sfmt 4700 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–27308; Directorate Identifier 2007–NE–06–AD; Amendment 39– 14977; AD 2007–05–16] RIN 2120–AA64 Airworthiness Directives; General Electric Aircraft Engines (GE) CF34– 3A1/–3B/–3B1 Turbofan Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: SUMMARY: This action supersedes emergency airworthiness directive (AD) 2007–04–51 that was sent previously to all known U.S. owners and operators of GE CF34–3A1/–3B/–3B1 turbofan engines. That action required a onetime visual and tactile inspection of certain areas of certain serial number (SN) fan disks for an arc-out defect, within 20 engine flight hours after the effective date of that AD. This AD supersedes AD 2007–04–51 and adds eight SNs to the list of suspect fan disks. This AD results from GE discovering eight additional SNs of fan disks suspected of having an arc-out defect, and from the original report that a GE CF34–3B1 turbofan engine experienced an uncontained fan disk failure during flight operation. We are issuing this AD to prevent an uncontained fan disk failure and airplane damage. DATES: This AD becomes effective March 12, 2007. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of March 12, 2007. We must receive any comments on this AD by May 7, 2007. ADDRESSES: Use one of the following addresses to comment on this AD. • DOT Docket Web site: Go to http://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590– 0001. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, E:\FR\FM\07MRR1.SGM 07MRR1 Federal Register / Vol. 72, No. 44 / Wednesday, March 7, 2007 / Rules and Regulations 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Contact General Electric Company via Lockheed Martin Technology Services, 10525 Chester Road, Suite C, Cincinnati, Ohio 45215, telephone (513) 672–8400, fax (513) 672–8422 for the service information identified in this AD. 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 FURTHER INFORMATION CONTACT: On February 16, 2007, the FAA issued emergency AD 2007–04–51, that applies to GE CF34–3A1/–3B/–3B1 turbofan engines. That AD requires a onetime visual and tactile inspection of certain areas of certain SN fan disks, within 20 engine flight hours after the effective date of that AD. That AD resulted from a report that a GE CF34–3B1 turbofan engine experienced an uncontained fan disk failure during flight operation. After landing the airplane, an inspection of the GE CF34–3B1 engine showed the front section of the engine failed, resulting in the fan, forward cowlings, and fan reverser departing from the engine. The airplane sustained minor fuselage damage. A subsequent inspection of the recovered segments of the fan disk found an electrical arc-out defect at the fracture origin site. The fan disk was marked using the electrochemical etch marking (ECM) procedure during engine assembly. If the ECM procedure is performed incorrectly, an arc-out defect can occur. This arc-out defect, caused during part marking, resulted in the uncontained failure. This condition, if not corrected, could result in an uncontained fan disk failure and airplane damage. Since emergency AD 2007–04–51 was issued, GE discovered eight additional SNs of fan disks suspected of having an arc-out defect. SUPPLEMENTARY INFORMATION: sroberts on PROD1PC70 with RULES Relevant Service Information We have reviewed and approved the technical contents of GE Alert Service Bulletin (ASB) No. CF34–BJ S/B 72– A0213, dated February 15, 2007, and Revision 1, dated February 27, 2007, and GE ASB No. CF34–AL S/B 72– A0232, dated February 15, 2007, and Revision 1, dated February 27, 2007, that describe procedures for visual and tactile inspection of certain areas of certain SN fan disks suspected of having an arc-out defect. VerDate Aug<31>2005 15:48 Mar 06, 2007 Jkt 211001 FAA’s Determination and Requirements of This AD Since the unsafe condition described is likely to exist or develop on other engines of the same type design, we are issuing this AD to supersede emergency AD 2007–04–51 and to prevent an uncontained fan disk failure and airplane damage. This AD requires a onetime visual and tactile inspection of certain areas of certain SN fan disks for an arc-out defect, within 20 engine flight hours after the effective date of this AD. You must use the service information described previously to perform the actions required by this AD. FAA’s Determination of the Effective Date Since an unsafe condition exists that requires the immediate adoption of this AD, we have found that notice and opportunity for public comment before issuing this AD are impracticable, and that good cause exists to make the AD effective immediately to all known U.S. owners and operators of GE CF34–3A1/ –3B/–3B1 turbofan engines. We are publishing the AD in the Federal Register as an amendment to Section 39.13 of part 39 of the Code of Federal Regulations (14 CFR part 39) to make it effective to all persons. Interim Action These actions are interim actions and we may take further rulemaking actions in the future. Comments Invited This AD is a final rule that involves requirements affecting flight safety and was not preceded by notice and an opportunity for public comment. However, we invite you to send us any written relevant data, views, or arguments regarding this AD. Send your comments to an address listed under ADDRESSES. Include ‘‘AD Docket No. FAA–2007–27308; Directorate Identifier 2007–NE–06–AD’’ in the subject line of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the rule that might suggest a need to modify it. We will post all comments we receive, without change, to http:// dms.dot.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this AD. Using the search function of the DMS Web site, anyone can find and read the comments in any of our dockets, including the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor PO 00000 Frm 00023 Fmt 4700 Sfmt 4700 10055 union, etc.). You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78) or you may visit http://dms.dot.gov. Examining the AD Docket You may examine the docket that contains the AD, any comments received, and any final disposition in person at the 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. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. E:\FR\FM\07MRR1.SGM 07MRR1 10056 Federal Register / Vol. 72, No. 44 / Wednesday, March 7, 2007 / Rules and Regulations 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, Incorporation by reference, Safety. Adoption of the Amendment Under the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: 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 2007–05–16 General Electric Aircraft Engines: Amendment 39–14977. Docket No. FAA–2007–27308; Directorate Identifier 2007–NE–06–AD. Effective Date (a) This airworthiness directive (AD) becomes effective March 12, 2007. Affected ADs (b) This AD supersedes emergency AD 2007–04–51. Applicability (c) This AD applies to General Electric Aircraft Engines (GE) CF34–3A1/-3B/-3B1 turbofan engines that have fan disks with serial numbers (SNs) listed in Table 1 of this AD. TABLE 1.—FAN DISK SNS AND LAST KNOWN ASSOCIATED ENGINE SERIAL NUMBER (ESN) sroberts on PROD1PC70 with RULES SN (Fan Disk) GEE148JH ................................ GEE01629 ................................ GEE01888 ................................ GEE147MF ............................... GEE147NA ............................... GEE147V5 ................................ GEE147VC ............................... GEE148JG ................................ GEE145LL ................................ GEE145NK ............................... GEE1466F ................................ GEE1466L ................................ GEE146H3 ................................ GEE146KD ............................... GEE146N7 ................................ GEE147N7 ................................ GEE147N8 ................................ VerDate Aug<31>2005 15:48 Mar 06, 2007 ESN (current) 872787 807168 807188 807620 807622 807624 807625 807633 872526 872545 872563 872568 872599 872604 872634 872705 872709 Jkt 211001 TABLE 1.—FAN DISK SNS AND LAST KNOWN ASSOCIATED ENGINE SERIAL NUMBER (ESN)—Continued SN (Fan Disk) ESN (current) GEE14818 ................................ GEE14815 ................................ GEE1480J ................................ GEE1485J ................................ GEE1480F ................................ GEE14885 ................................ GEE148EJ ................................ GEE148FT ................................ GEE148ER ............................... GEE148PN ............................... GEE148RN ............................... GEE148TW ............................... GEE03675 ................................ GEE148R0 ................................ GEE148VT ................................ GEE148WC .............................. GEE1F9G6 ............................... GEE1F9G8 ............................... GEE1F9GA ............................... GEE1F9WN .............................. GEE1FA22 ................................ GEE1FA6H ............................... 872727 872730 872731 872745 872750 872763 872780 872785 872790 872804 872811 872817 SPARE SPARE 872830 872837 872841 872846 872849 872857 872866 872886 (d) For reference, affected regional jet fan disk part numbers (P/Ns) are 5922T01G04, 5922T01G05, 6078T57G01, 6078T57G02, 6078T57G03, 6078T57G04, 6078T57G05, and 6078T57G06. (e) For reference, affected business jet fan disk P/Ns are 5921T18G01, 5921T18G09, 5921T18G10, 5921T54G01, 5922T01G02, 5922T01G04, 5922T01G05, 6020T62G04, 6020T62G05, 6078T00G01, 6078T57G01, 6078T57G02, 6078T57G03, 6078T57G04, 6078T57G05, and 6078T57G06. (f) These engines are installed on, but not limited to, Bombardier, Inc. CL–600–2B16 (CL–601–3R Variant), CL–600–2B16 (CL–604 Variant), and CL–600–2B19 (Regional Jet Series 100 and 440) model airplanes. Unsafe Condition (g) This AD results from GE discovering eight additional SNs of fan disks suspected of having an arc-out defect, and from the original report that a GE CF34–3B1 turbofan engine experienced an uncontained fan disk failure during flight operation. We are issuing this AD to prevent an uncontained fan disk failure and airplane damage. Compliance (h) You are responsible for having the actions required by this AD performed within 20 engine flight hours after the effective date of this AD, unless the actions have already been done. Inspection of the Fan Disk (i) Perform a onetime visual and tactile inspection of the bore area on the 39 fan disks listed in Table 1 of this AD, that have not had a shop-level inspection. (j) For regional jet engine models CF34– 3A1/–3B1, use paragraphs 3.A through 3.B.(2)(h) of the Accomplishment Instructions of GE Alert Service Bulletin (ASB) No. CF34–AL S/B 72–A0232, Revision PO 00000 Frm 00024 Fmt 4700 Sfmt 4700 1, dated February 27, 2007, to do the inspections. (k) For business jet engine models CF34– 3A1/–3B, use paragraphs 3.A through 3.B.(2)(h) of the Accomplishment Instructions of GE ASB No. CF34–BJ S/B 72– A0213, Revision 1, dated February 27, 2007, to do the inspections. Previous Inspection Credit (l) Previous inspection credit is allowed: (1) For regional jet engine models CF34– 3A1/–3B1, inspected using paragraphs 3.A through 3.B.(2)(g) of the Accomplishment Instructions of GE ASB No. CF34–AL S/B 72– A0232, dated February 15, 2007, for the fan disk SNs listed in emergency AD 2007–04– 51. (2) For business jet engine models CF34– 3A1/–3B, inspected using paragraphs 3.A through 3.B.(2)(g) of the Accomplishment Instructions of GE ASB No. CF34–BJ S/B 72– A0213, dated February 15, 2007, for the fan disk SNs listed in emergency AD 2007–04– 51. (m) Fan disks listed in Table 1 of this AD that have already had a full visual inspection, eddy current inspection, and fluorescent penetrant inspection using GE CF34–3 (BJ) Heavy Maintenance Manual SEI–782, Section 72–21–00, or using GE CF34–3 (RJ) Engine Manual SEI–756, Section 72–21–00, are considered in compliance with this AD. Alternative Methods of Compliance (n) 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 (o) AD 2006–05–04, dated March 3, 2006, also addresses the subject of this AD. GE ASB No. CF34–BJ S/B 72–A0088, dated August 21, 2000, and GE ASB No. CF34–AL S/B 72– A0103, dated August 4, 2000, pertain to the subject of this AD. (p) For further information, 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. Material Incorporated by Reference (q) You must use the service information specified in Table 2 of this AD to perform the actions required by this AD. The Director of the Federal Register approved the incorporation by reference of the documents listed in Table 2 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. You can get a copy 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 review copies at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http:// E:\FR\FM\07MRR1.SGM 07MRR1 10057 Federal Register / Vol. 72, No. 44 / Wednesday, March 7, 2007 / Rules and Regulations www.archives.gov/federal-register/cfr/ibrlocations.html. TABLE 2.—INCORPORATION BY REFERENCE GE Aircraft Engines Alert Service Bulletin No. CF34–BJ S/B 72–A0213 Total Pages: 12 CF34–BJ S/B 72–A0213 Total Pages: 13 CF34–AL S/B 72–A0232 Total Pages: 12 CF34–AL S/B 72–A0232 Total Pages: 13 Page Revision ................................................................................. All ......................... Original ................ February 15, 2007. ................................................................................. All ......................... 1 ........................... February 27, 2007. ................................................................................ All ......................... Original ................ February 15, 2007. ................................................................................ All ......................... 1 ........................... February 27, 2007. Issued in Burlington, Massachusetts, on February 28, 2007. Peter A. White, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E7–3833 Filed 3–6–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–26707; Directorate Identifier 2006–NM–157–AD; Amendment 39–14973; AD 2007–05–12] RIN 2120–AA64 Airworthiness Directives; Airbus Model A330 Airplanes and Model A340–200 and –300 Series Airplanes 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 Airbus Model A330 airplanes and Model A340–200 and –300 series airplanes. This AD requires inspecting to determine the part number of certain S4- and MZ-type spoiler servo controls (SSCs). For certain other airplanes, this AD requires inspecting to determine the part number of all SSCs. This AD also requires replacing any affected SSC with a new SSC. This AD results from a new load duty cycle defined by the manufacturer. Additional fatigue tests and calculations done on this basis indicated that the spoiler valve manifold of the S4-type SSCs, and, on certain airplanes, the maintenance cover of the MZ-type SSCs, may crack during its service life due to pressure impulse fatigue. We are issuing this AD to prevent fatigue cracking of certain SSCs, which could result in hydraulic leakage and consequent loss of SSC function and loss of the associated hydraulic VerDate Aug<31>2005 15:48 Mar 06, 2007 Jkt 211001 system. These conditions could affect all three hydraulic systems, which could result in reduced controllability of the airplane. DATES: This AD becomes effective April 11, 2007. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of April 11, 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. Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, International Branch, ANM–116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2797; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Examining the Docket You may examine the airworthiness directive (AD) docket on the Internet at http://dms.dot.gov or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the street address stated in the ADDRESSES section. Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to certain Airbus Model A330 airplanes and Model A340–200 and –300 series airplanes. That NPRM was published in the Federal Register on December 28, 2006 (71 FR 78102). That PO 00000 Frm 00025 Fmt 4700 Sfmt 4700 Date NPRM proposed to require inspecting to determine the part number of certain S4- and MZ-type spoiler servo-controls (SSCs). For certain other airplanes, that NPRM proposed to require inspecting to determine the part number of all SSCs. That NPRM also proposed to require replacing any affected SSC with a new SSC. Comments We provided the public the opportunity to participate in the development of this AD. We received no comments on the NPRM 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 This AD affects about 27 airplanes of U.S. registry. It takes about 1 work hour per airplane to accomplish the inspection to determine the part number, at an average labor rate of $80 per work hour. Based on these figures, the estimated cost of the inspection required by this AD for U.S. operators is $2,160, or $80 per airplane. 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 E:\FR\FM\07MRR1.SGM 07MRR1

Agencies

[Federal Register Volume 72, Number 44 (Wednesday, March 7, 2007)]
[Rules and Regulations]
[Pages 10054-10057]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-3833]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-27308; Directorate Identifier 2007-NE-06-AD; 
Amendment 39-14977; AD 2007-05-16]
RIN 2120-AA64


Airworthiness Directives; General Electric Aircraft Engines (GE) 
CF34-3A1/-3B/-3B1 Turbofan Engines

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

ACTION: Final rule; request for comments.

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

SUMMARY: This action supersedes emergency airworthiness directive (AD) 
2007-04-51 that was sent previously to all known U.S. owners and 
operators of GE CF34-3A1/-3B/-3B1 turbofan engines. That action 
required a onetime visual and tactile inspection of certain areas of 
certain serial number (SN) fan disks for an arc-out defect, within 20 
engine flight hours after the effective date of that AD. This AD 
supersedes AD 2007-04-51 and adds eight SNs to the list of suspect fan 
disks. This AD results from GE discovering eight additional SNs of fan 
disks suspected of having an arc-out defect, and from the original 
report that a GE CF34-3B1 turbofan engine experienced an uncontained 
fan disk failure during flight operation. We are issuing this AD to 
prevent an uncontained fan disk failure and airplane damage.

DATES: This AD becomes effective March 12, 2007. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in the regulations as of March 12, 2007.
    We must receive any comments on this AD by May 7, 2007.

ADDRESSES: Use one of the following addresses to comment on this AD.
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590-0001.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building,

[[Page 10055]]

400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    Contact General Electric Company via Lockheed Martin Technology 
Services, 10525 Chester Road, Suite C, Cincinnati, Ohio 45215, 
telephone (513) 672-8400, fax (513) 672-8422 for the service 
information identified in this AD.

FOR FURTHER INFORMATION 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.

SUPPLEMENTARY INFORMATION: On February 16, 2007, the FAA issued 
emergency AD 2007-04-51, that applies to GE CF34-3A1/-3B/-3B1 turbofan 
engines. That AD requires a onetime visual and tactile inspection of 
certain areas of certain SN fan disks, within 20 engine flight hours 
after the effective date of that AD. That AD resulted from a report 
that a GE CF34-3B1 turbofan engine experienced an uncontained fan disk 
failure during flight operation. After landing the airplane, an 
inspection of the GE CF34-3B1 engine showed the front section of the 
engine failed, resulting in the fan, forward cowlings, and fan reverser 
departing from the engine. The airplane sustained minor fuselage 
damage. A subsequent inspection of the recovered segments of the fan 
disk found an electrical arc-out defect at the fracture origin site. 
The fan disk was marked using the electro-chemical etch marking (ECM) 
procedure during engine assembly. If the ECM procedure is performed 
incorrectly, an arc-out defect can occur. This arc-out defect, caused 
during part marking, resulted in the uncontained failure.
    This condition, if not corrected, could result in an uncontained 
fan disk failure and airplane damage. Since emergency AD 2007-04-51 was 
issued, GE discovered eight additional SNs of fan disks suspected of 
having an arc-out defect.

Relevant Service Information

    We have reviewed and approved the technical contents of GE Alert 
Service Bulletin (ASB) No. CF34-BJ S/B 72-A0213, dated February 15, 
2007, and Revision 1, dated February 27, 2007, and GE ASB No. CF34-AL 
S/B 72-A0232, dated February 15, 2007, and Revision 1, dated February 
27, 2007, that describe procedures for visual and tactile inspection of 
certain areas of certain SN fan disks suspected of having an arc-out 
defect.

FAA's Determination and Requirements of This AD

    Since the unsafe condition described is likely to exist or develop 
on other engines of the same type design, we are issuing this AD to 
supersede emergency AD 2007-04-51 and to prevent an uncontained fan 
disk failure and airplane damage. This AD requires a onetime visual and 
tactile inspection of certain areas of certain SN fan disks for an arc-
out defect, within 20 engine flight hours after the effective date of 
this AD. You must use the service information described previously to 
perform the actions required by this AD.

FAA's Determination of the Effective Date

    Since an unsafe condition exists that requires the immediate 
adoption of this AD, we have found that notice and opportunity for 
public comment before issuing this AD are impracticable, and that good 
cause exists to make the AD effective immediately to all known U.S. 
owners and operators of GE CF34-3A1/-3B/-3B1 turbofan engines. We are 
publishing the AD in the Federal Register as an amendment to Section 
39.13 of part 39 of the Code of Federal Regulations (14 CFR part 39) to 
make it effective to all persons.

Interim Action

    These actions are interim actions and we may take further 
rulemaking actions in the future.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment. However, we invite you to send us any written relevant data, 
views, or arguments regarding this AD. Send your comments to an address 
listed under ADDRESSES. Include ``AD Docket No. FAA-2007-27308; 
Directorate Identifier 2007-NE-06-AD'' in the subject line of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify it.
    We will post all comments we receive, without change, to http://
dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this AD. Using the search function of the DMS Web 
site, anyone can find and read the comments in any of our dockets, 
including the name of the individual who sent the comment (or signed 
the comment on behalf of an association, business, labor union, etc.). 
You may review the DOT's complete Privacy Act Statement in the Federal 
Register published on April 11, 2000 (65 FR 19477-78) or you may visit 
http://dms.dot.gov.

Examining the AD Docket

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

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national Government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that the regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

[[Page 10056]]

    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, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Under the authority delegated to me by the Administrator, the Federal 
Aviation Administration amends part 39 of the Federal Aviation 
Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive:

2007-05-16 General Electric Aircraft Engines: Amendment 39-14977. 
Docket No. FAA-2007-27308; Directorate Identifier 2007-NE-06-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective March 
12, 2007.

Affected ADs

    (b) This AD supersedes emergency AD 2007-04-51.

Applicability

    (c) This AD applies to General Electric Aircraft Engines (GE) 
CF34-3A1/-3B/-3B1 turbofan engines that have fan disks with serial 
numbers (SNs) listed in Table 1 of this AD.

  Table 1.--Fan Disk SNs and Last Known Associated Engine Serial Number
                                  (ESN)
------------------------------------------------------------------------
                                                                 ESN
                       SN (Fan Disk)                          (current)
------------------------------------------------------------------------
GEE148JH...................................................       872787
GEE01629...................................................       807168
GEE01888...................................................       807188
GEE147MF...................................................       807620
GEE147NA...................................................       807622
GEE147V5...................................................       807624
GEE147VC...................................................       807625
GEE148JG...................................................       807633
GEE145LL...................................................       872526
GEE145NK...................................................       872545
GEE1466F...................................................       872563
GEE1466L...................................................       872568
GEE146H3...................................................       872599
GEE146KD...................................................       872604
GEE146N7...................................................       872634
GEE147N7...................................................       872705
GEE147N8...................................................       872709
GEE14818...................................................       872727
GEE14815...................................................       872730
GEE1480J...................................................       872731
GEE1485J...................................................       872745
GEE1480F...................................................       872750
GEE14885...................................................       872763
GEE148EJ...................................................       872780
GEE148FT...................................................       872785
GEE148ER...................................................       872790
GEE148PN...................................................       872804
GEE148RN...................................................       872811
GEE148TW...................................................       872817
GEE03675...................................................        SPARE
GEE148R0...................................................        SPARE
GEE148VT...................................................       872830
GEE148WC...................................................       872837
GEE1F9G6...................................................       872841
GEE1F9G8...................................................       872846
GEE1F9GA...................................................       872849
GEE1F9WN...................................................       872857
GEE1FA22...................................................       872866
GEE1FA6H...................................................       872886
------------------------------------------------------------------------

    (d) For reference, affected regional jet fan disk part numbers 
(P/Ns) are 5922T01G04, 5922T01G05, 6078T57G01, 6078T57G02, 
6078T57G03, 6078T57G04, 6078T57G05, and 6078T57G06.
    (e) For reference, affected business jet fan disk P/Ns are 
5921T18G01, 5921T18G09, 5921T18G10, 5921T54G01, 5922T01G02, 
5922T01G04, 5922T01G05, 6020T62G04, 6020T62G05, 6078T00G01, 
6078T57G01, 6078T57G02, 6078T57G03, 6078T57G04, 6078T57G05, and 
6078T57G06.
    (f) These engines are installed on, but not limited to, 
Bombardier, Inc. CL-600-2B16 (CL-601-3R Variant), CL-600-2B16 (CL-
604 Variant), and CL-600-2B19 (Regional Jet Series 100 and 440) 
model airplanes.

Unsafe Condition

    (g) This AD results from GE discovering eight additional SNs of 
fan disks suspected of having an arc-out defect, and from the 
original report that a GE CF34-3B1 turbofan engine experienced an 
uncontained fan disk failure during flight operation. We are issuing 
this AD to prevent an uncontained fan disk failure and airplane 
damage.

Compliance

    (h) You are responsible for having the actions required by this 
AD performed within 20 engine flight hours after the effective date 
of this AD, unless the actions have already been done.

Inspection of the Fan Disk

    (i) Perform a onetime visual and tactile inspection of the bore 
area on the 39 fan disks listed in Table 1 of this AD, that have not 
had a shop-level inspection.
    (j) For regional jet engine models CF34-3A1/-3B1, use paragraphs 
3.A through 3.B.(2)(h) of the Accomplishment Instructions of GE 
Alert Service Bulletin (ASB) No. CF34-AL S/B 72-A0232, Revision 1, 
dated February 27, 2007, to do the inspections.
    (k) For business jet engine models CF34-3A1/-3B, use paragraphs 
3.A through 3.B.(2)(h) of the Accomplishment Instructions of GE ASB 
No. CF34-BJ S/B 72-A0213, Revision 1, dated February 27, 2007, to do 
the inspections.

Previous Inspection Credit

    (l) Previous inspection credit is allowed:
    (1) For regional jet engine models CF34-3A1/-3B1, inspected 
using paragraphs 3.A through 3.B.(2)(g) of the Accomplishment 
Instructions of GE ASB No. CF34-AL S/B 72-A0232, dated February 15, 
2007, for the fan disk SNs listed in emergency AD 2007-04-51.
    (2) For business jet engine models CF34-3A1/-3B, inspected using 
paragraphs 3.A through 3.B.(2)(g) of the Accomplishment Instructions 
of GE ASB No. CF34-BJ S/B 72-A0213, dated February 15, 2007, for the 
fan disk SNs listed in emergency AD 2007-04-51.
    (m) Fan disks listed in Table 1 of this AD that have already had 
a full visual inspection, eddy current inspection, and fluorescent 
penetrant inspection using GE CF34-3 (BJ) Heavy Maintenance Manual 
SEI-782, Section 72-21-00, or using GE CF34-3 (RJ) Engine Manual 
SEI-756, Section 72-21-00, are considered in compliance with this 
AD.

Alternative Methods of Compliance

    (n) 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

    (o) AD 2006-05-04, dated March 3, 2006, also addresses the 
subject of this AD. GE ASB No. CF34-BJ S/B 72-A0088, dated August 
21, 2000, and GE ASB No. CF34-AL S/B 72-A0103, dated August 4, 2000, 
pertain to the subject of this AD.
    (p) For further information, 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.

Material Incorporated by Reference

    (q) You must use the service information specified in Table 2 of 
this AD to perform the actions required by this AD. The Director of 
the Federal Register approved the incorporation by reference of the 
documents listed in Table 2 of this AD in accordance with 5 U.S.C. 
552(a) and 1 CFR part 51. You can get a copy 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 review copies at the FAA, New England Region, 
Office of the Regional Counsel, 12 New England Executive Park, 
Burlington, MA; or at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at NARA, call 202-741-6030, or go to: http://

[[Page 10057]]

www.archives.gov/federal-register/cfr/ibr-locations.html.

                                      Table 2.--Incorporation by Reference
----------------------------------------------------------------------------------------------------------------
GE Aircraft Engines Alert Service
           Bulletin No.                    Page                Revision                      Date
----------------------------------------------------------------------------------------------------------------
CF34-BJ S/B 72-A0213.............  All.................  Original...........  February 15, 2007.
    Total Pages: 12                                                           ..................................
CF34-BJ S/B 72-A0213.............  All.................  1..................  February 27, 2007.
    Total Pages: 13                                                           ..................................
CF34-AL S/B 72-A0232.............  All.................  Original...........  February 15, 2007.
    Total Pages: 12                                                           ..................................
CF34-AL S/B 72-A0232.............  All.................  1..................  February 27, 2007.
    Total Pages: 13                                                           ..................................
----------------------------------------------------------------------------------------------------------------


    Issued in Burlington, Massachusetts, on February 28, 2007.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
 [FR Doc. E7-3833 Filed 3-6-07; 8:45 am]
BILLING CODE 4910-13-P