Airworthiness Directives; General Electric Company CF34-1A, -3A, -3A1, -3A2, -3B, and -3B1 Series Turbofan Engines, 9257-9260 [06-1594]

Download as PDF Federal Register / Vol. 71, No. 36 / Thursday, February 23, 2006 / Rules and Regulations Building, Washington, DC; on the Internet at https://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741– 6030, or go to https://www.archives.gov/ federal_register/code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on February 10, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06–1596 Filed 2–22–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2004–18648; Directorate Identifier 2004–NE–26–AD; Amendment 39– 14494; AD 2006–04–12] RIN 2120–AA64 Airworthiness Directives; General Electric Company CF34–1A, –3A, –3A1, –3A2, –3B, and –3B1 Series Turbofan Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. rwilkins on PROD1PC63 with RULES AGENCY: SUMMARY: The FAA is superseding an existing airworthiness directive (AD) for General Electric Company (GE) CF34– 3A1 and –3B1 series turbofan engines. That AD requires initial and repetitive visual inspections and eddy current inspections (ECIs) of certain stage 5 low pressure turbine (LPT) disks and stage 6 LPT disks, installed in GE CF34–3A1 and –3B1 series turbofan engines. Those engines are installed in certain Bombardier Canadair Regional Jet (RJ) airplanes. This AD requires the same initial and repetitive visual inspections and ECIs, but adds SNs to the affected disk population for RJ airplanes. This AD also adds GE CF34–1 and –3 series turbofan engines with certain stage 5 and stage 6 LPT disks, to the applicability section. Those engines are installed in certain Bombardier Canadair Business Jet (BJ) airplanes. Also, this AD requires eventual replacement of the affected disks as terminating action to the repetitive inspections. This AD results from the discovery of an additional population of suspect stage 5 LPT disks and stage 6 LPT disks that could fail due to lowcycle fatigue cracking that may start at the site of an electrical arc-out on the disk. We are issuing this AD to prevent VerDate Aug<31>2005 16:10 Feb 22, 2006 Jkt 205001 low-cycle-fatigue (LCF) failure of stage 5 LPT disks and stage 6 LPT disks, which could lead to uncontained engine failure. This AD becomes effective March 30, 2006. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of March 30, 2006. ADDRESSES: You can get the service information identified in this AD from GE Aircraft Engines, 1000 Western Avenue, Lynn, MA 01910; Attention: CF34 Product Support Engineering, Mail Zone: 34017; telephone (781) 594– 6323; fax (781) 594–0600. You may examine the AD docket on the Internet at https://dms.dot.gov or in Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC. FOR FURTHER INFORMATION CONTACT: Tara Fitzgerald, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803– 5299; telephone (781) 238–7130; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 with a proposed airworthiness directive (AD). The proposed AD applies to GE CF34– 1A, –3A, –3A1, –3A2, –3B, and –3B1 series turbofan engines. We published the proposed AD in the Federal Register on September 1, 2005 (70 FR 52043). That action proposed to require the same initial and repetitive visual inspections and ECIs as AD 2004–15– 03R1, but adds SNs to the affected disk population for RJ airplanes. That action also proposed to add GE CF34–1 and –3 series turbofan engines with certain stage 5 and stage 6 LPT disks, installed in certain Bombardier Canadair BJ airplanes, to the applicability section. Also, that action requires eventual replacement of the affected disks as terminating action to the repetitive inspections. DATES: Examining the AD Docket You may examine the docket that contains the AD, any comments received, and any final disposition in person at the Docket Management Facility Docket Office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone (800) 647–5227) is located on the plaza level of the Department of Transportation Nassif Building at the street address stated in ADDRESSES. Comments will be available in the AD docket shortly after the DMS receives them. PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 9257 Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments received. Request To Clarify the Nine-Month Time Limit One commenter requests that we clarify the nine-month time limit imposed by compliance section paragraphs (f)(1) and (f)(2). We do not agree. The compliance section in the proposed AD does not contain a ninemonth time limit. The commenter appears to have commented in error, on the previous AD, AD 2004–15–03R1, which does contain a nine-month time limit. Request To Provide Reference to Business Jet Version of Service Bulletin The same commenter states that in the compliance section, for the Bombardier Canadair CL600–2B19 airplane, the GE service bulletin referenced is for engines used in airline service (RJ). The commenter requests that we also provide reference to the Business Jet version of the GE service bulletin, so they can apply it to their Bombardier Canadair CL600–2B19 airplane. We do not agree. The Bombardier Canadair CL600–2B19 airplane is designated as an RJ airplane. We have correctly referenced the RJ version of the GE service bulletin in the proposed AD and the AD for Bombardier Canadair CL600– 2B19 airplanes. The commenter appears to have commented in error, on the previous AD, AD 2004–15–03R1, which does not apply to CF–34 series engines on BJ airplanes. Conclusion We have carefully reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting the AD as proposed. Costs of Compliance About 683 GE CF34–3A1 and –3B1 series turbofan engines are installed on Bombardier Canadair RJ airplanes of U.S. registry. We estimate that 355 of those engines will be affected by this AD. About 690 CF34–1A, –3A, –3A1, –3A2, and –3B series turbofan engines are installed in Bombardier Canadair BJ airplanes of U.S. registry. We estimate that 249 of those engines will be affected by this AD. We also estimate that it will take about 70 work hours per engine to perform the disk inspections when the LPT module is exposed in the shop, and about 94 work hours per engine to perform the disk inspections when the LPT module is forced off- E:\FR\FM\23FER1.SGM 23FER1 9258 Federal Register / Vol. 71, No. 36 / Thursday, February 23, 2006 / Rules and Regulations wing. We also estimate that the average labor rate is $65 per work hour. Prorated stage 5 LPT disks will cost about $42,650 (RJ), and $71,083 (BJ) per engine and prorated stage 6 LPT disks will cost about $30,110 (RJ) and $50,183 (BJ) per engine. We also estimate that about 24 stage 5 LPT disks and about 24 stage 6 LPT disks will be found with the arc-out condition and require replacement. Based on these figures, we estimate the total cost of the AD to U.S. operators to be $14,409,772. (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. Authority for This Rulemaking List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. 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; 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 removing Amendment 39–13773 (69 FR 50299, August 16, 2004), and by adding a new airworthiness directive, Amendment 39–14494, to read as follows: I 2006–04–12 General Electric Company: Amendment 39–14494. Docket No. FAA–2004–18648; Directorate Identifier 2004–NE–26–AD. Effective Date (a) This airworthiness directive (AD) becomes effective March 30, 2006. Affected ADs (b) This AD supersedes AD 2004–15–03R1, Amendment 39–13773. Applicability (c) This AD applies to the following two groups of engine models: (1) General Electric Company (GE) CF34– 3A1 and –3B1 series turbofan engines with stage 5 low pressure turbine (LPT) disks, part number (P/N) 6078T92P01 or stage 6 LPT disks P/N 6078T89P01, or both, with serial numbers (SNs) listed in Figure 3 or Figure 4 of GE Alert Service Bulletin (ASB) No. CF34– AL S/B 72–A0173, Revision 05, dated May 24, 2005. These engines are installed on Bombardier Canadair CL600–2B19 Regional Jet (RJ) airplanes. (2) GE CF34–1A, –3A, –3A1, –3A2, and –3B series turbofan engines with stage 5 LPT disks P/N 4922T16P01, 5024T53P01, 5024T53P02, or 6078T92P01 or stage 6 LPT disks P/Ns 4922T17P01, 5023T45P03, 5023T45P04, or 6078T89P01, or both, with SNs listed in Figure 3 or Figure 4 of GE ASB No. CF34–BJ S/B 72–A0148, Revision 02, dated May 24, 2005. These engines are installed on Bombardier Canadair Models CL–600–2A12 (CL–601), CL–600–2B16 (CL– 601–3A), (CL–601–3R), and (CL–604) Business Jet (BJ) airplanes. Unsafe Condition (d) This AD results from the discovery of an additional population of suspect stage 5 LPT disks and stage 6 LPT disks that could fail due to low-cycle fatigue cracking that may start at the site of an electrical arc-out on the disk. We are issuing this AD to prevent low-cycle-fatigue (LCF) failure of stage 5 LPT disks and stage 6 LPT disks, which could lead to uncontained engine failure. 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. Initial Inspection or Replacement (f) Using the compliance schedule in Table 1 of this AD, do the following: (1) For engines installed in Bombardier Canadair RJ airplanes, if a stage 5 LPT disk or stage 6 LPT disk listed in Figure 3 of GE ASB No. CF34–AL S/B 72–A0173, Revision 05, dated May 24, 2005 or listed in any previous issue of ASB No. CF34–AL S/B 72– A0173 did not complete a visual inspection and eddy current inspection (ECI) using paragraphs 3.C.(1) through 3.D.(2) and paragraphs 3.E. through 3.E.(6) of the Accomplishment Instructions of that SB before June 1, 2005, then replace that disk at the next piece-part exposure. TABLE 1.—COMPLIANCE SCHEDULE rwilkins on PROD1PC63 with RULES On the effective date of this AD, if the disk has Then perform the actions defined in paragraph (f) of this AD at next piece-part exposure, not to exceed the accumulation of (i) 14,750 or more cycles-since-new (CSN) and has not been fluorescent penetrant inspected (FPI) at an earlier piece-part exposure. (ii) 14,750 or more CSN and has been FPI at an earlier piece-part exposure. (iii) 14,500 or more CSN but fewer than 14,750 CSN .............................. (iv) 14,250 or more CSN but fewer than 14,500 CSN ............................. (v) 13,000 or more CSN but fewer than 14,250 CSN .............................. (vi) 2,500 or more CSN but fewer than 13,000 CSN ............................... An additional 250 cycles-in-service (CIS) after the effective date of this AD. An additional 500 CIS after the effective date of this AD. (vii) Fewer than 2,500 cycles-since-new (CSN) ....................................... VerDate Aug<31>2005 16:10 Feb 22, 2006 Jkt 205001 PO 00000 Frm 00004 Fmt 4700 An additional 500 CIS after the effective date of this AD. An additional 750 CIS after the effective date of this AD. An additional 1,000 CIS after the effective date of this AD. An additional 4,000 CIS after the effective date of this AD, or 14,000 CSN, whichever comes first. 6,500 CSN. Sfmt 4700 E:\FR\FM\23FER1.SGM 23FER1 9259 Federal Register / Vol. 71, No. 36 / Thursday, February 23, 2006 / Rules and Regulations (2) For engines installed in Bombardier Canadair BJ airplanes, perform an initial visual inspection and ECI of stage 5 LPT disks and stage 6 LPT disks listed in Figure 3 of GE ASB No. CF34–BJ S/B 72–A0148, Revision 02, dated May 24, 2005, before January 1, 2010. Use paragraphs 3.C.(1) through 3.D.(2) and paragraphs 3.E. through 3.E.(6) of Accomplishment Instructions of GE ASB No. CF34–BJ S/B 72–A0148, Revision 02, dated May 24, 2005 to do the inspections. Repetitive Inspections (g) For engines installed in Bombardier Canadair RJ airplanes with stage 5 LPT disks and stage 6 LPT disks listed in Figure 3 of GE ASB No. CF34–AL S/B 72–A0173, Revision 05, dated May 24, 2005, that were initially visually inspected and ECI’ed before June 1, 2005, do the following: (1) Perform repetitive visual inspections and ECIs within every 3,100 cycles-sincelast-inspection (CSLI), until the life limit of the disk is reached. (2) Use paragraphs 3.C.(1) through 3.D.(2) and paragraphs 3.E. through 3.E.(6) of Accomplishment Instructions of GE ASB No. CF34–AL S/B 72–A0173, Revision 05, dated May 24, 2005 to do the inspections. (h) For engines installed in Bombardier Canadair BJ airplanes, with stage 5 LPT disks and stage 6 LPT disks initially inspected as specified in paragraph (f)(2) of this AD, do the following: (1) Perform repetitive visual inspections and ECIs within every 3,100 CSLI, until the life limit of the disk is reached. (2) Use paragraphs 3.C.(1) through 3.D.(2) and paragraphs 3.E. through 3.E.(6) of Accomplishment Instructions of GE ASB No. CF34–BJ S/B 72–A0148, Revision 02, dated May 24, 2005, to do the inspections. Disks That Pass Inspection (i) Reinstall disks that pass the inspections in paragraphs (f), (g), and (h) of this AD into the same LPT module from which they were removed. Stage 5 and Stage 6 LPT Disk Removal (j) Remove any disk from service if there is an arc-out found on that disk. (k) At the next piece-part exposure for engines installed in Bombardier Canadair RJ airplanes, remove from service stage 5 LPT disks and stage 6 LPT disks listed in Figure 4 of GE ASB No. CF34–AL S/B 72–A0173, Revision 05, dated May 24, 2005. (l) At the next piece-part exposure for engines installed in Bombardier Canadair BJ airplanes, remove from service stage 5 LPT disks and stage 6 LPT disks listed in Figure 4 of GE ASB No. CF34–BJ S/B 72–A0148 Revision 02, dated May 24, 2005. (r) For the purpose of this AD, the definition of piece-part exposure for the stage 6 LPT disk is when the disk is separated from the forward bolted joint. Optional Terminating Action (m) Replacement of an affected stage 5 LPT disk or affected stage 6 LPT disk, with a disk not listed in Figure 3 or Figure 4 of GE ASB No. CF34–AL S/B 72–A0173 Revision 05, dated May 24, 2005 or not listed in Figure 3 or Figure 4 of GE ASB No. CF34–BJ S/B 72– A0148, Revision 02, dated May 24, 2005 is terminating action to the repetitive inspections and removals required by this AD for that disk. (s) For the purpose of this AD, the definition of a replacement engine or replacement LPT module is an engine or LPT module that does not have installed any of the suspect disks listed in Figure 3 or Figure 4 of GE ASB No. CF34–AL S/B 72–A0173 Revision 05, dated May 24, 2005, or Figure 3 or Figure 4 of GE ASB No. CF34–BJ S/B 72– A0148, Revision 02, dated May 24, 2005. Terminating Action (n) As terminating action to the repetitive inspections and removals in this AD, replace all disks by January 1, 2013 that are listed in Figure 3 and Figure 4 of GE ASB No. CF34– AL S/B 72–A0173, Revision 05, dated May 24, 2005, and that are listed in Figure 3 and Figure 4 of GE ASB No. CF34–BJ S/B 72– A0148, Revision 02, dated May 24, 2005. (t) 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. Actions Completed per Previous Releases of Alert Service Bulletins (o) Actions completed before the effective date of this AD using GE ASB No. CF34–AL S/B 72–A0173, dated April 2, 2004; or Revision 01, dated May 20, 2004; or Revision 02, dated June 22, 2004; or Revision 03, dated July 20, 2004; or Revision 04, dated February 7, 2005; or GE ASB No. CF34–BJ S/B 72– A0148, dated September 2, 2004; or Revision 01, dated March 10, 2005, are considered acceptable for compliance with the corresponding action in this AD. Serviceable LPT Disk Definition (p) For the purpose of this AD, a serviceable LPT disk is a disk not listed in Figure 3 or Figure 4 of GE ASB No. CF34– AL S/B 72–A0173, Revision 05, dated May 24, 2005, or Figure 3 or Figure 4 of GE ASB No. CF34–BJ S/B 72–A0148, Revision 02, dated May 24, 2005. Piece-Part Exposure Definitions (q) For the purpose of this AD, the definition of piece-part exposure for the stage 5 LPT disk is when the disk is separated from the forward and aft bolted joints. Replacement Engine or Replacement LPT Module Definition Alternative Methods of Compliance Related Information (u) GE ASB No. CF34–AL S/B 72–A0178 and ASB No. CF34–BJ S/B 72–A0152 contain the information necessary to identify and inspect the suspect disks that are the subject of this AD. Material Incorporated by Reference (v) You must use the General Electric Company 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. Contact GE Aircraft Engines, 1000 Western Avenue, Lynn, MA 01910; Attention: CF34 Product Support Engineering, Mail Zone: 34017; telephone (781) 594–6323; fax (781) 594–0600, for a copy of this service information. You may review copies at the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590–0001, on the internet at https://dms.dot.gov, 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: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. TABLE 2.—INCORPORATION BY REFERENCE Page CF34–AL S/B 72–A0173, Total Pages: 37 ............................................................................................. CF34–BJ S/B 72–A0148, Total Pages: 39 ............................................................................................. rwilkins on PROD1PC63 with RULES Alert Service Bulletin No. ALL ........ ALL ........ VerDate Aug<31>2005 16:10 Feb 22, 2006 Jkt 205001 PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 E:\FR\FM\23FER1.SGM 23FER1 Revision 05 02 Date May 24, 2005. May 24, 2005. 9260 Federal Register / Vol. 71, No. 36 / Thursday, February 23, 2006 / Rules and Regulations Issued in Burlington, Massachusetts, on February 14, 2006. Ann C. Mollica, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 06–1594 Filed 2–22–06; 8:45 am] DEPARTMENT OF COMMERCE Patent and Trademark Office 37 CFR Part 1 [Docket No.: PTO–P–2006–0007] BILLING CODE 4910–13–P RIN 0651–AC02 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration United States Patent and Trademark Office, Commerce. ACTION: Interim rule. AGENCY: 14 CFR Part 71 [Docket No. FAA–2005–23375; Airspace Docket No. 05–ACE–35] Modification of Class E Airspace; Beatrice, NE Federal Aviation Administration (FAA), DOT. AGENCY: Direct final rule; confirmation of effective date. ACTION: SUMMARY: This document confirms the effective date of the direct final rule which revises Class E airspace at Beatrice, NE. Effective Date: 0901 UTC, April 13, 2006. DATES: FOR FURTHER INFORMATION CONTACT: Brenda Mumper, Air Traffic Division, Airspace Branch, ACE–520A, DOT Regional Headquarters Building, Federal Aviation Administration, 901 Locust, Kansas City, MO 64106; telephone: (816) 329–2524. The FAA published this direct final rule with a request for comments in the Federal Register on January 5, 2006 (71 FR 537). The FAA uses the direct final rulemaking procedure for a noncontroversial rule where the FAA believes that there will be no adverse public comment. This direct final rule advised the public that no adverse comments were anticipated, and that unless a written adverse comment, or a written notice of intent to submit such an adverse comment, were received within the comment period, the regulation would become effective on April 13, 2006. No adverse comments were received, and thus this notice confirms that this direct final rule will become effective on that date. rwilkins on PROD1PC63 with RULES SUPPLEMENTARY INFORMATION: Issued in Kansas City, MO, on February 7, 2006. Elizabeth S. Wallis, Acting Area Director, Western Flight Services Operations. [FR Doc. 06–1644 Filed 2–22–06; 8:45 am] BILLING CODE 4910–13–M VerDate Aug<31>2005 16:10 Feb 22, 2006 Clarification of Filing Date Requirements for Ex Parte and Inter Partes Reexamination Proceedings Jkt 205001 SUMMARY: The United States Patent and Trademark Office (Office) is revising the rules of practice relating to the filing date requirements for ex parte and inter partes reexamination proceedings for consistency with the provisions of the patent statute governing ex parte and inter partes reexamination proceedings. The Office is specifically revising the rules to require that a request for ex parte reexamination or for inter partes reexamination must meet all the applicable statutory requirements before a filing date is accorded to the request for ex parte reexamination or for inter partes reexamination. DATES: Effective Date: March 27, 2006. Comment Deadline Date: To be ensured of consideration, written comments must be received on or before April 24, 2006. No public hearing will be held. ADDRESSES: Comments should be sent by electronic mail message over the Internet addressed to: ac2/ comments@uspto.gov. Comments may also be submitted by mail addressed to: Box Comments—Patents, Commissioner for Patents, P.O. Box 1450, Alexandria, VA, 22313–1450, or by facsimile transmission to (571) 273–7710 marked to the attention of Kenneth M. Schor. Although comments may be submitted by mail or facsimile, the Office prefers to receive comments via the Internet. If comments are submitted by mail, the Office prefers that the comments be submitted on a DOS formatted 31⁄2 inch disk accompanied by a paper copy. Comments may also be sent by electronic mail message over the Internet via the Federal eRulemaking Portal. See the Federal eRulemaking Portal Web site (https:// www.regulations.gov) for additional instructions on providing comments via the Federal eRulemaking Portal. The comments will be available for public inspection at the Office of the Commissioner for Patents, located in Madison East, Tenth Floor, 600 Dulany Street, Alexandria, Virginia, and will be PO 00000 Frm 00006 Fmt 4700 Sfmt 4700 available via the Office Internet Web site (address: https://www.uspto.gov). Because comments will be made available for public inspection, information that is not desired to be made public, such as an address or phone number, should not be included in the comments. FOR FURTHER INFORMATION CONTACT: By telephone—Kenneth M. Schor, at (571) 272–7710 or Robert J. Spar at (571) 272– 7700; by mail addressed to U.S. Patent and Trademark Office, Mail Stop Comments—Patents, Commissioner for Patents, P.O. Box 1450, Alexandria, VA 22313–1450, marked to the attention of Kenneth M. Schor; by facsimile transmission to (571) 273–7710 marked to the attention of Kenneth M. Schor; or by electronic mail message over the Internet addressed to kenneth.schor@uspto.gov. SUPPLEMENTARY INFORMATION: The Office is revising the rules of practice in title 37 of the Code of Federal Regulations (CFR) to require that a request for ex parte reexamination or for inter partes reexamination must meet all the applicable statutory requirements in 35 U.S.C. 302 or 311 before a filing date is accorded to the request for ex parte reexamination or for inter partes reexamination. Thus, the Office is amending the rules to clearly require compliance with all the requirements of filing an ex parte reexamination request (set forth in 37 CFR 1.510(b)) before a filing date will be assigned to an ex parte reexamination request, and to clearly require compliance with all the requirements of filing an inter partes reexamination request (set forth in 37 CFR 1.915(b)) before a filing date will be assigned to an inter partes reexamination request. Section 1.510 sets forth the requirements for the content of a request for ex parte reexamination. Section 1.915 sets forth the requirements for the content of a request for inter partes reexamination. Former § 1.510(d) states that the filing date of a request for ex parte reexamination is ‘‘(1) The date on which the request including the entire fee for requesting reexamination is received in the Patent and Trademark Office; or (2) The date on which the last portion of the fee for requesting reexamination is received’’ (emphasis added). In like manner, former § 1.919(a) states that ‘‘[t]he filing date of a request for inter partes reexamination is the date on which the request satisfies the fee requirement of § 1.915(a)’’ (emphasis added). Given the former rule language, it may have appeared that compliance with the provisions of § 1.510(b) or E:\FR\FM\23FER1.SGM 23FER1

Agencies

[Federal Register Volume 71, Number 36 (Thursday, February 23, 2006)]
[Rules and Regulations]
[Pages 9257-9260]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-1594]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2004-18648; Directorate Identifier 2004-NE-26-AD;
Amendment 39-14494; AD 2006-04-12]
RIN 2120-AA64

Airworthiness Directives; General Electric Company CF34-1A, -3A,
-3A1, -3A2, -3B, and -3B1 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 General Electric Company (GE) CF34-3A1 and -3B1 series
turbofan engines. That AD requires initial and repetitive visual
inspections and eddy current inspections (ECIs) of certain stage 5 low
pressure turbine (LPT) disks and stage 6 LPT disks, installed in GE
CF34-3A1 and -3B1 series turbofan engines. Those engines are installed
in certain Bombardier Canadair Regional Jet (RJ) airplanes. This AD
requires the same initial and repetitive visual inspections and ECIs,
but adds SNs to the affected disk population for RJ airplanes. This AD
also adds GE CF34-1 and -3 series turbofan engines with certain stage 5
and stage 6 LPT disks, to the applicability section. Those engines are
installed in certain Bombardier Canadair Business Jet (BJ) airplanes.
Also, this AD requires eventual replacement of the affected disks as
terminating action to the repetitive inspections. This AD results from
the discovery of an additional population of suspect stage 5 LPT disks
and stage 6 LPT disks that could fail due to low-cycle fatigue cracking
that may start at the site of an electrical arc-out on the disk. We are
issuing this AD to prevent low-cycle-fatigue (LCF) failure of stage 5
LPT disks and stage 6 LPT disks, which could lead to uncontained engine
failure.

DATES: This AD becomes effective March 30, 2006. The Director of the
Federal Register approved the incorporation by reference of certain
publications listed in the regulations as of March 30, 2006.

ADDRESSES: You can get the service information identified in this AD
from GE Aircraft Engines, 1000 Western Avenue, Lynn, MA 01910;
Attention: CF34 Product Support Engineering, Mail Zone: 34017;
telephone (781) 594-6323; fax (781) 594-0600.
You may examine the AD docket on the Internet at https://dms.dot.gov
or in Room PL-401 on the plaza level of the Nassif Building, 400
Seventh Street, SW., Washington, DC.

FOR FURTHER INFORMATION CONTACT: Tara Fitzgerald, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803-5299; telephone (781)
238-7130; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39
with a proposed airworthiness directive (AD). The proposed AD applies
to GE CF34-1A, -3A, -3A1, -3A2, -3B, and -3B1 series turbofan engines.
We published the proposed AD in the Federal Register on September 1,
2005 (70 FR 52043). That action proposed to require the same initial
and repetitive visual inspections and ECIs as AD 2004-15-03R1, but adds
SNs to the affected disk population for RJ airplanes. That action also
proposed to add GE CF34-1 and -3 series turbofan engines with certain
stage 5 and stage 6 LPT disks, installed in certain Bombardier Canadair
BJ airplanes, to the applicability section. Also, that action requires
eventual replacement of the affected disks as terminating action to the
repetitive inspections.

Examining the AD Docket

You may examine the docket that contains the AD, any comments
received, and any final disposition in person at the Docket Management
Facility Docket Office between 9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The Docket Office (telephone (800)
647-5227) is located on the plaza level of the Department of
Transportation Nassif Building at the street address stated in
ADDRESSES. Comments will be available in the AD docket shortly after
the DMS receives them.

Comments

We provided the public the opportunity to participate in the
development of this AD. We have considered the comments received.

Request To Clarify the Nine-Month Time Limit

One commenter requests that we clarify the nine-month time limit
imposed by compliance section paragraphs (f)(1) and (f)(2). We do not
agree. The compliance section in the proposed AD does not contain a
nine-month time limit. The commenter appears to have commented in
error, on the previous AD, AD 2004-15-03R1, which does contain a nine-
month time limit.

Request To Provide Reference to Business Jet Version of Service
Bulletin

The same commenter states that in the compliance section, for the
Bombardier Canadair CL600-2B19 airplane, the GE service bulletin
referenced is for engines used in airline service (RJ). The commenter
requests that we also provide reference to the Business Jet version of
the GE service bulletin, so they can apply it to their Bombardier
Canadair CL600-2B19 airplane. We do not agree. The Bombardier Canadair
CL600-2B19 airplane is designated as an RJ airplane. We have correctly
referenced the RJ version of the GE service bulletin in the proposed AD
and the AD for Bombardier Canadair CL600-2B19 airplanes. The commenter
appears to have commented in error, on the previous AD, AD 2004-15-
03R1, which does not apply to CF-34 series engines on BJ airplanes.

Conclusion

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

Costs of Compliance

About 683 GE CF34-3A1 and -3B1 series turbofan engines are
installed on Bombardier Canadair RJ airplanes of U.S. registry. We
estimate that 355 of those engines will be affected by this AD. About
690 CF34-1A, -3A, -3A1, -3A2, and -3B series turbofan engines are
installed in Bombardier Canadair BJ airplanes of U.S. registry. We
estimate that 249 of those engines will be affected by this AD. We also
estimate that it will take about 70 work hours per engine to perform
the disk inspections when the LPT module is exposed in the shop, and
about 94 work hours per engine to perform the disk inspections when the
LPT module is forced off-

[[Page 9258]]

wing. We also estimate that the average labor rate is $65 per work
hour. Prorated stage 5 LPT disks will cost about $42,650 (RJ), and
$71,083 (BJ) per engine and prorated stage 6 LPT disks will cost about
$30,110 (RJ) and $50,183 (BJ) per engine. We also estimate that about
24 stage 5 LPT disks and about 24 stage 6 LPT disks will be found with
the arc-out condition and require replacement. Based on these figures,
we estimate the total cost of the AD to U.S. operators to be
$14,409,772.

Authority for This Rulemaking

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

Regulatory Findings

We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a summary of the costs to comply with this AD and
placed it in the AD Docket. You may get a copy of this summary at the
address listed under ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by
reference, 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 39-13773 (69 FR
50299, August 16, 2004), and by adding a new airworthiness directive,
Amendment 39-14494, to read as follows:

2006-04-12 General Electric Company: Amendment 39-14494. Docket No.
FAA-2004-18648; Directorate Identifier 2004-NE-26-AD.

Effective Date

(a) This airworthiness directive (AD) becomes effective March
30, 2006.

Affected ADs

(b) This AD supersedes AD 2004-15-03R1, Amendment 39-13773.

Applicability

(c) This AD applies to the following two groups of engine
models:
(1) General Electric Company (GE) CF34-3A1 and -3B1 series
turbofan engines with stage 5 low pressure turbine (LPT) disks, part
number (P/N) 6078T92P01 or stage 6 LPT disks P/N 6078T89P01, or
both, with serial numbers (SNs) listed in Figure 3 or Figure 4 of GE
Alert Service Bulletin (ASB) No. CF34-AL S/B 72-A0173, Revision 05,
dated May 24, 2005. These engines are installed on Bombardier
Canadair CL600-2B19 Regional Jet (RJ) airplanes.
(2) GE CF34-1A, -3A, -3A1, -3A2, and -3B series turbofan engines
with stage 5 LPT disks P/N 4922T16P01, 5024T53P01, 5024T53P02, or
6078T92P01 or stage 6 LPT disks P/Ns 4922T17P01, 5023T45P03,
5023T45P04, or 6078T89P01, or both, with SNs listed in Figure 3 or
Figure 4 of GE ASB No. CF34-BJ S/B 72-A0148, Revision 02, dated May
24, 2005. These engines are installed on Bombardier Canadair Models
CL-600-2A12 (CL-601), CL-600-2B16 (CL-601-3A), (CL-601-3R), and (CL-
604) Business Jet (BJ) airplanes.

Unsafe Condition

(d) This AD results from the discovery of an additional
population of suspect stage 5 LPT disks and stage 6 LPT disks that
could fail due to low-cycle fatigue cracking that may start at the
site of an electrical arc-out on the disk. We are issuing this AD to
prevent low-cycle-fatigue (LCF) failure of stage 5 LPT disks and
stage 6 LPT disks, which could lead to uncontained engine failure.

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.

Initial Inspection or Replacement

(f) Using the compliance schedule in Table 1 of this AD, do the
following:
(1) For engines installed in Bombardier Canadair RJ airplanes,
if a stage 5 LPT disk or stage 6 LPT disk listed in Figure 3 of GE
ASB No. CF34-AL S/B 72-A0173, Revision 05, dated May 24, 2005 or
listed in any previous issue of ASB No. CF34-AL S/B 72-A0173 did not
complete a visual inspection and eddy current inspection (ECI) using
paragraphs 3.C.(1) through 3.D.(2) and paragraphs 3.E. through
3.E.(6) of the Accomplishment Instructions of that SB before June 1,
2005, then replace that disk at the next piece-part exposure.

Table 1.--Compliance Schedule
------------------------------------------------------------------------
Then perform the actions defined
On the effective date of this AD, if in paragraph (f) of this AD at
the disk has next piece-part exposure, not to
exceed the accumulation of
------------------------------------------------------------------------
(i) 14,750 or more cycles-since-new An additional 250 cycles-in-
(CSN) and has not been fluorescent service (CIS) after the
penetrant inspected (FPI) at an effective date of this AD.
earlier piece-part exposure.
(ii) 14,750 or more CSN and has been An additional 500 CIS after the
FPI at an earlier piece-part effective date of this AD.
exposure.
(iii) 14,500 or more CSN but fewer An additional 500 CIS after the
than 14,750 CSN. effective date of this AD.
(iv) 14,250 or more CSN but fewer An additional 750 CIS after the
than 14,500 CSN. effective date of this AD.
(v) 13,000 or more CSN but fewer than An additional 1,000 CIS after the
14,250 CSN. effective date of this AD.
(vi) 2,500 or more CSN but fewer than An additional 4,000 CIS after the
13,000 CSN. effective date of this AD, or
14,000 CSN, whichever comes
first.
(vii) Fewer than 2,500 cycles-since- 6,500 CSN.
new (CSN).
------------------------------------------------------------------------

[[Page 9259]]

(2) For engines installed in Bombardier Canadair BJ airplanes,
perform an initial visual inspection and ECI of stage 5 LPT disks
and stage 6 LPT disks listed in Figure 3 of GE ASB No. CF34-BJ S/B
72-A0148, Revision 02, dated May 24, 2005, before January 1, 2010.
Use paragraphs 3.C.(1) through 3.D.(2) and paragraphs 3.E. through
3.E.(6) of Accomplishment Instructions of GE ASB No. CF34-BJ S/B 72-
A0148, Revision 02, dated May 24, 2005 to do the inspections.

Repetitive Inspections

(g) For engines installed in Bombardier Canadair RJ airplanes
with stage 5 LPT disks and stage 6 LPT disks listed in Figure 3 of
GE ASB No. CF34-AL S/B 72-A0173, Revision 05, dated May 24, 2005,
that were initially visually inspected and ECI'ed before June 1,
2005, do the following:
(1) Perform repetitive visual inspections and ECIs within every
3,100 cycles-since-last-inspection (CSLI), until the life limit of
the disk is reached.
(2) Use paragraphs 3.C.(1) through 3.D.(2) and paragraphs 3.E.
through 3.E.(6) of Accomplishment Instructions of GE ASB No. CF34-AL
S/B 72-A0173, Revision 05, dated May 24, 2005 to do the inspections.
(h) For engines installed in Bombardier Canadair BJ airplanes,
with stage 5 LPT disks and stage 6 LPT disks initially inspected as
specified in paragraph (f)(2) of this AD, do the following:
(1) Perform repetitive visual inspections and ECIs within every
3,100 CSLI, until the life limit of the disk is reached.
(2) Use paragraphs 3.C.(1) through 3.D.(2) and paragraphs 3.E.
through 3.E.(6) of Accomplishment Instructions of GE ASB No. CF34-BJ
S/B 72-A0148, Revision 02, dated May 24, 2005, to do the
inspections.

Disks That Pass Inspection

(i) Reinstall disks that pass the inspections in paragraphs (f),
(g), and (h) of this AD into the same LPT module from which they
were removed.

Stage 5 and Stage 6 LPT Disk Removal

(j) Remove any disk from service if there is an arc-out found on
that disk.
(k) At the next piece-part exposure for engines installed in
Bombardier Canadair RJ airplanes, remove from service stage 5 LPT
disks and stage 6 LPT disks listed in Figure 4 of GE ASB No. CF34-AL
S/B 72-A0173, Revision 05, dated May 24, 2005.
(l) At the next piece-part exposure for engines installed in
Bombardier Canadair BJ airplanes, remove from service stage 5 LPT
disks and stage 6 LPT disks listed in Figure 4 of GE ASB No. CF34-BJ
S/B 72-A0148 Revision 02, dated May 24, 2005.

Optional Terminating Action

(m) Replacement of an affected stage 5 LPT disk or affected
stage 6 LPT disk, with a disk not listed in Figure 3 or Figure 4 of
GE ASB No. CF34-AL S/B 72-A0173 Revision 05, dated May 24, 2005 or
not listed in Figure 3 or Figure 4 of GE ASB No. CF34-BJ S/B 72-
A0148, Revision 02, dated May 24, 2005 is terminating action to the
repetitive inspections and removals required by this AD for that
disk.

Terminating Action

(n) As terminating action to the repetitive inspections and
removals in this AD, replace all disks by January 1, 2013 that are
listed in Figure 3 and Figure 4 of GE ASB No. CF34-AL S/B 72-A0173,
Revision 05, dated May 24, 2005, and that are listed in Figure 3 and
Figure 4 of GE ASB No. CF34-BJ S/B 72-A0148, Revision 02, dated May
24, 2005.

Actions Completed per Previous Releases of Alert Service Bulletins

(o) Actions completed before the effective date of this AD using
GE ASB No. CF34-AL S/B 72-A0173, dated April 2, 2004; or Revision
01, dated May 20, 2004; or Revision 02, dated June 22, 2004; or
Revision 03, dated July 20, 2004; or Revision 04, dated February 7,
2005; or GE ASB No. CF34-BJ S/B 72-A0148, dated September 2, 2004;
or Revision 01, dated March 10, 2005, are considered acceptable for
compliance with the corresponding action in this AD.

Serviceable LPT Disk Definition

(p) For the purpose of this AD, a serviceable LPT disk is a disk
not listed in Figure 3 or Figure 4 of GE ASB No. CF34-AL S/B 72-
A0173, Revision 05, dated May 24, 2005, or Figure 3 or Figure 4 of
GE ASB No. CF34-BJ S/B 72-A0148, Revision 02, dated May 24, 2005.

Piece-Part Exposure Definitions

(q) For the purpose of this AD, the definition of piece-part
exposure for the stage 5 LPT disk is when the disk is separated from
the forward and aft bolted joints.
(r) For the purpose of this AD, the definition of piece-part
exposure for the stage 6 LPT disk is when the disk is separated from
the forward bolted joint.

Replacement Engine or Replacement LPT Module Definition

(s) For the purpose of this AD, the definition of a replacement
engine or replacement LPT module is an engine or LPT module that
does not have installed any of the suspect disks listed in Figure 3
or Figure 4 of GE ASB No. CF34-AL S/B 72-A0173 Revision 05, dated
May 24, 2005, or Figure 3 or Figure 4 of GE ASB No. CF34-BJ S/B 72-
A0148, Revision 02, dated May 24, 2005.

Alternative Methods of Compliance

(t) 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

(u) GE ASB No. CF34-AL S/B 72-A0178 and ASB No. CF34-BJ S/B 72-
A0152 contain the information necessary to identify and inspect the
suspect disks that are the subject of this AD.

Material Incorporated by Reference

(v) You must use the General Electric Company 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.
Contact GE Aircraft Engines, 1000 Western Avenue, Lynn, MA 01910;
Attention: CF34 Product Support Engineering, Mail Zone: 34017;
telephone (781) 594-6323; fax (781) 594-0600, for a copy of this
service information. You may review copies at the Docket Management
Facility; U.S. Department of Transportation, 400 Seventh Street,
SW., Nassif Building, Room PL-401, Washington, DC 20590-0001, on the
internet at https://dms.dot.gov, 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: https://
www.archives.gov/federal-register/cfr/ibr-locations.html.

Table 2.--Incorporation by Reference
----------------------------------------------------------------------------------------------------------------
Alert Service Bulletin No. Page Revision Date
----------------------------------------------------------------------------------------------------------------
CF34-AL S/B 72-A0173, Total Pages: 37.... ALL..................... 05 May 24, 2005.
CF34-BJ S/B 72-A0148, Total Pages: 39.... ALL..................... 02 May 24, 2005.
----------------------------------------------------------------------------------------------------------------

[[Page 9260]]

Issued in Burlington, Massachusetts, on February 14, 2006.
Ann C. Mollica,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 06-1594 Filed 2-22-06; 8:45 am]
BILLING CODE 4910-13-P

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