Airworthiness Directives; Rolls-Royce plc RB211 Series Turbofan Engines, 4832-4836 [E6-1092]

Download as PDF 4832 Federal Register / Vol. 71, No. 19 / Monday, January 30, 2006 / Proposed Rules notice has been transmitted or received through EDI. Others in the industry have expressed concern about being charged a fee by the buyer to accept the notice to preserve their trust benefits through EDI or, about being charged a fee if they send a paper invoice or separate trust notice. cprice-sewell on PROD1PC66 with PROPOSALS Agency Request for Information AMS is soliciting comments on PACA trust rights in connection with EDI invoicing so that the Agency will be able to provide greater direction to the industry of how PACA trust rights can be preserved when invoicing electronically. In particular, AMS invites comments and information regarding how the Agency may best provide regulatory clarification or direction. Comments are specifically invited on: (1) The types of problems that may need to be addressed by new regulatory language; (2) any technological barriers and solutions; (3) any additional costs likely to be associated with appropriate regulations, and opinions regarding who should bear such costs; (4) whether the Agency should by regulation define EDI methods that must be made available by licensed buyers, (i.e., creating a separate field for trust notice in EDI); (5) should buyers be required to accept separate notices (i.e., electronic or paper PACA trust) without restriction or charge; and (6) other related issues and suggestions. This notice provides a 45-day comment period for interested parties to comment on the need for amending the regulations. Should AMS conclude, based on the comments received, that the purposes of the PACA would be advanced through new or revised regulations, the Agency will develop a notice of proposed rulemaking that will be published in the Federal Register with a request for comments in accordance with 5 U.S.C. 553. Executive Orders 12866 and 12988 This advance notice of proposed rulemaking has been determined to be not significant for the purposes of Executive Order 12866, and therefore, has not been reviewed by the Office of Management and Budget. This advance notice of proposed rulemaking has been reviewed under Executive Order 12988, Civil Justice Reform, and is not intended to have retroactive effect. This proposed rule will not preempt any State or local laws, regulations, or policies, unless they present an irreconcilable conflict with this rule. There are no administrative procedures that must be exhausted prior to any judicial challenge to the provisions of this advance notice of proposed rulemaking. VerDate Aug<31>2005 14:05 Jan 27, 2006 Jkt 208001 Effects on Small Business Pursuant to requirements set forth in the Regulatory Flexibility Act (RFA) (5 U.S.C. 601 et seq.), AMS has considered the economic impact on this proposed rule on small entities. The purpose of the RFA is to fit regulatory actions to the scale of businesses subject to such actions in order that small businesses will not be unduly or disproportionately burdened. Small agricultural service firms have been defined by the Small Business Administration (SBA) (13 CFR 121.601) as those whose annual receipts are less than $5,000,000. There are approximately 15,000 firms licensed under the PACA, many of which could be classified as small entities. The proposed regulations, if found to be necessary, would clarify how to preserve the trust benefit when using EDI. The use of EDI would provide companies an electronic alternative to paper documentation to give notice of intent to preserve trust rights, thereby reducing the time and expense associated with preserving trust rights under the PACA. Authority: 7 U.S.C. 499o. Dated: January 24, 2006. Lloyd C. Day, Administrator, Agricultural Marketing Service. [FR Doc. E6–1090 Filed 1–27–06; 8:45 am] BILLING CODE 3410–02–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. 2000–NE–62–AD] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce plc RB211 Series Turbofan Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to supersede an existing airworthiness directive (AD) for Rolls-Royce plc (RR) models RB211–535E4–37, RB211– 535E4–B–37, RB211–535C–37, RB211– 535E4–B–75, RB211–535E4–C, and RB211–22B–02 turbofan engines. That AD currently requires inspecting certain high pressure (HP) turbine discs, manufactured between 1989 and 1999, for cracks in the rim cooling air holes, and, if necessary, replacing the discs with serviceable parts. This proposed PO 00000 Frm 00002 Fmt 4702 Sfmt 4702 AD would require the same inspections, and would reduce the compliance times for eddy current inspection (ECI) for the RR RB211–22B–02 engines. This proposed AD results from the manufacturer reducing their recommended compliance times for inspections on RB211–22B–02 engines. We are proposing this AD to prevent possible disc failure, which could result in an uncontained engine failure and damage to the airplane. DATES: We must receive any comments on this proposed AD by March 31, 2006. ADDRESSES: Use one of the following addresses to comment on this proposed AD: • By mail: Federal Aviation Administration (FAA), New England Region, Office of the Regional Counsel, Attention: Rules Docket No. 2000–NE– 62–AD, 12 New England Executive Park, Burlington, MA 01803–5299. • By fax: (781) 238–7055. • By e-mail: 9-aneadcomment@faa.gov. You can get the service information identified in this proposed AD from Rolls-Royce plc, PO Box 31, Derby, England; telephone: 011 44 1332– 249428, fax: 011 44 1332–249223. You may examine the AD docket, by appointment, at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA. FOR FURTHER INFORMATION CONTACT: Ian Dargin, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803– 5299; telephone (781) 238–7178, fax (781) 238–7199. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments regarding this proposal. Send your comments to an address listed under ADDRESSES. Include ‘‘AD Docket No. 2000–NE–62–AD’’ in the subject line of your comments. If you want us to acknowledge receipt of your mailed comments, send us a self-addressed, stamped postcard with the docket number written on it; we will datestamp your postcard and mail it back to you. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. If a person contacts us verbally, and that contact relates to a substantive part of this proposed AD, we will summarize the contact and place the summary in the docket. We will consider all comments received by the closing date and may amend the E:\FR\FM\30JAP1.SGM 30JAP1 Federal Register / Vol. 71, No. 19 / Monday, January 30, 2006 / Proposed Rules proposed AD in light of those comments. Examining the AD Docket You may examine the AD Docket (including any comments and service information), by appointment, between 8 a.m. and 4:30 p.m., Monday through Friday, except Federal holidays. See ADDRESSES for the location. Discussion On December 15, 2004, the FAA issued AD 2004–26–03, Amendment 39–13915 (69 FR 77881, December 29, 2004) for RR models RB211–535E4–37, RB211–535E4–B–37, RB211–535C–37, RB211–535E4–B–75, and RB211–22B– 02 turbofan engines. That AD requires inspecting certain HP turbine discs, manufactured between 1989 and 1999, for cracks in the rim cooling air holes, and, if necessary, replacing the discs with serviceable parts. cprice-sewell on PROD1PC66 with PROPOSALS Actions Since AD 2004–26–03 Was Issued Since we issued AD 2004–26–03, the Civil Aviation Authority (CAA), which is the airworthiness authority for the United Kingdom, notified us that an unsafe condition might exist on RR model RB211–22B–02 turbofan engines manufactured between 1989 and 1999. The CAA advises that cracks were found in a Trent 800 HP turbine disc attributable to machining anomalies during new manufacture. The RB211– 22B–02 HP turbine is similar in design to the Trent 800, manufactured at the same facility and with the same tooling. This proposed AD would require inspection of certain HP turbine discs, manufactured between 1989 and 1999, for cracks in the rim cooling air holes, and, if necessary, replacement with serviceable parts. We are reducing the inspection schedules required by AD 2004–26–03, for the high risk discs installed on model RB211–22B–02 engines. This AD retains the same inspection schedules, currently required for RR models RB211–535E4–37, RB211–535E4–B–37, RB211–535C–37, RB211–535E4–B–75 turbofan engines that were in AD 2004–26–03. The actions specified in this proposed AD are intended to prevent possible disc failure, which could result in an uncontained engine failure and damage to the airplane. Bilateral Airworthiness Agreement This engine model is manufactured in the United Kingdom and is type certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the VerDate Aug<31>2005 14:05 Jan 27, 2006 Jkt 208001 applicable bilateral airworthiness agreement. Under this bilateral airworthiness agreement, the CAA has kept the FAA informed of the situation described above. We have examined the findings of the CAA, reviewed all available information, and determined that AD action is necessary for products of this type design that are certificated for operation in the United States. Relevant Service Information We have reviewed and approved the technical contents of RR ASB RB.211– 72–AE717, dated January 21, 2005, that describes procedures for inspecting the RB211–22B disk for cracks. The CAA classified this service bulletin as mandatory and issued AD G–2005– 0003, dated January 24, 2005, in order to ensure the airworthiness of these RR RB211–22 turbofan engines in the U.K. FAA’s Determination and Requirements of the Proposed AD We have evaluated all pertinent information and identified an unsafe condition that is likely to exist or develop on other products of this same type design. Therefore, we are proposing this AD, which would require the same inspections specified in AD 2004–26–03, but would reduce the compliance times for the model RB211– 22B engine to: • Within 500 cycles-in-service (CIS) after January 1, 2005 or before accumulating 11,000 cycles-since-new (CSN), whichever occurs first, on engines with more than 9,000 CSN on January 1, 2005, and • Before accumulating 9,500 CSN or at the next shop visit after the effective date of this proposed AD, whichever occurs first, on engines with more than 1,500 CSN but fewer than 9,001 CSN on January 1, 2005. The proposed AD would require that you do these actions using the service information described previously. Costs of Compliance We estimate that this proposed AD would affect six RR RB211–22B engines installed on airplanes of U.S. registry. We also estimate that it would take about 4.0 work hours per engine to perform the proposed actions, and that the average labor rate is $65 per work hour. There are no required parts. Based on these figures, we estimate the total cost of the proposed AD to U.S. operators to be $1,560. 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 PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 4833 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 proposed AD would not have federalism implications under ExecutiveOrder 13132. This proposed AD would 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 proposed 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. Would 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 proposal and placed it in the AD Docket. You may get a copy of this summary by sending a request to us at the address listed under ADDRESSES. Include ‘‘AD Docket No. 2000–NE–62–AD’’ in your request. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation Administration proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. E:\FR\FM\30JAP1.SGM 30JAP1 4834 § 39.13 Federal Register / Vol. 71, No. 19 / Monday, January 30, 2006 / Proposed Rules [Amended] 2. The FAA amends § 39.13 by removing Amendment 39–13915 (69 FR 77881, December 29, 2004) and by adding a new airworthiness directive, to read as follows: Rolls-Royce plc: Docket No. 2000–NE–62– AD. Comments Due Date (a) The Federal Aviation Administration (FAA) must receive comments on this airworthiness directive (AD) action by March 31, 2006. Affected ADs (b) This AD supersedes AD 2004–26–03, Amendment 39–13915. Applicability (c) This AD applies to Rolls-Royce plc (RR) models RB211–535E4–37, RB211–535E4–B– 37, RB211–535C–37, RB211–535E4–B–75, RB211–535E4–C, and RB211–22B–02 turbofan engines with turbine discs having part numbers and serial numbers listed in the following Tables 1, 3, and 5 of this AD. These turbofan engines are installed on, but not limited to, Boeing 757, Tupolev Tu204, and Lockheed L–1011 series airplanes. Unsafe Condition (d) This AD results from the manufacturer reducing the inspection compliance times for the RB211–22B–02 turbofan engines. We are issuing this AD to prevent possible disc failure, which could result in an uncontained engine failure and damage to the airplane. 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. Eddy Current Inspection for All Except Model RB211–22B–02 Engines (f) For all except model RB211–22B–02 engines, do the following: (1) Perform an eddy current inspection of the high pressure (HP) turbine discs listed in Table 1 of this AD, for cracks in the rim cooling air holes. Use paragraph 3. of the Accomplishment Instructions of RR Alert Service Bulletin (ASB) No. RB.211–72– AE651, dated November 22, 2004, to perform the eddy current inspection. TABLE 1.—AFFECTED HP TURBINE DISCS USING COMPLIANCE SCHEDULE IN TABLE 2 Part No. LK80623 LK80623 UL27680 UL27680 UL27680 UL27680 UL27680 UL27680 UL27680 UL27680 UL27680 UL27680 UL27680 UL27680 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 Serial No. .............................................................................................................................. .............................................................................................................................. ............................................................................................................................. ............................................................................................................................. ............................................................................................................................. ............................................................................................................................. ............................................................................................................................. ............................................................................................................................. ............................................................................................................................. ............................................................................................................................. ............................................................................................................................. ............................................................................................................................. ............................................................................................................................. ............................................................................................................................. ............................................................................................................................. ............................................................................................................................. ............................................................................................................................. ............................................................................................................................. ............................................................................................................................. ............................................................................................................................. ............................................................................................................................. ............................................................................................................................. ............................................................................................................................. ............................................................................................................................. ............................................................................................................................. ............................................................................................................................. ............................................................................................................................. ............................................................................................................................. ............................................................................................................................. Part No. CQDY6397 ....... CQDY6504 ....... CQDY6451 ....... CQDY6452 ....... CQDY6466 ....... CQDY6468 ....... CQDY6471 ....... CQDY6496 ....... CQDY6505 ....... CQDY6653 ....... CQDY6656 ....... CQDY6657 ....... CQDY6684 ....... CQDY6883 ....... CQDY6465 ....... LAQDY6002 ..... LAQDY6083 ..... LAQDY6087 ..... LDRCZ10247 .... LDRCZ10277 .... LDRCZ10318 .... LDRCZ10335 .... LDRCZ10430 .... LDRCZ10531 .... LDRCZ10750 .... LDRCZ10899 .... LDRCZ11616 .... LDRCZ11720 .... LDRCZ11893. UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... Serial No. LDRCZ12893 LDRCZ12985 LDRCZ13044 LDRCZ13047 LQDY6803 LQDY6814 LQDY6847 LQDY6868 LQDY6875 LQDY6892 LQDY6898 LQDY6904 LQDY6909 LQDY6910 LQDY9133 LQDY9574 LQDY9579 LQDY9672 LQDY9770 LQDY9783 LQDY9786 LQDY9900 LQDY9902 LQDY9929 LQDY9957 LQDY9982 LQDY9992 WGQDY90005 (2) Use the compliance schedule in Table 2 of this AD. TABLE 2.—COMPLIANCE SCHEDULE FOR HP TURBINE DISCS LISTED IN TABLE 1 If Disc Cycles-Since-New (CSN) on October 8, 2004 are: Then Eddy Current Inspect: (1) 12,750 CSN or more .................................................... Within 250 cycles-in-service (CIS) from October 8, 2004 or within 14,500 CSN, whichever occurs first. Within 500 CIS from October 8, 2004. Before 11,000 CSN or at next shop visit after the effective date of this AD, whichever occurs first. cprice-sewell on PROD1PC66 with PROPOSALS (2) Fewer than 12,750 CSN but 10,500 CSN or more ...... (3) Fewer than 10,500 CSN ............................................... (3) On discs that pass inspection, use paragraph 3. of the Accomplishment Instructions of RR ASB No. RB.211–72– AE651, dated November 22, 2004, to VerDate Aug<31>2005 14:05 Jan 27, 2006 Jkt 208001 permanently etch NMSB 72–AE651 onto the disc, adjacent to the part number. (4) Perform an eddy current inspection of the HP turbine discs listed in Table 3 of this AD, for cracks in the rim cooling air holes. PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 Use paragraph 3. of the Accomplishment Instructions of RR ASB No. RB.211–72– AE651, dated November 22, 2004, to perform the eddy current inspection. E:\FR\FM\30JAP1.SGM 30JAP1 4835 Federal Register / Vol. 71, No. 19 / Monday, January 30, 2006 / Proposed Rules TABLE 3.—AFFECTED HP TURBINE DISCS USING COMPLIANCE SCHEDULE IN TABLE 4 Part No. TABLE 3.—AFFECTED HP TURBINE DISCS USING COMPLIANCE SCHEDULE IN TABLE 4—Continued Part No. Serial No. UL10323 ........... UL27680 ........... UL27681 ........... Serial No. LK80622 ........... LK80623 ........... UL28267 ........... CQDY6070 and higher. All. All. (5) Use the compliance schedule in Table 4 of this AD. LQDY6316 and higher. CQDY5945 and higher. All. TABLE 4.—COMPLIANCE SCHEDULE FOR HP TURBINE DISCS LISTED IN TABLE 3 If Disc CSN on January 29, 2001 are: Then Eddy Current Inspect: (1) Fewer than 13,700 CSN ............................................... Before reaching 14,500 CSN, or at the next shop visit after the effective date of this AD, whichever occurs first. Before reaching one of the following, whichever occurs first after the effective date of this AD: (i) 15,300 CSN. (ii) Within 800 CIS since January 29, 2001. (iii) At next shop visit. (2) 13,700 CSN or more .................................................... (6) For discs that pass inspection, use paragraph 3. of the Accomplishment Instructions of RR ASB No. RB.211–72– AE651, dated November 22, 2004, to permanently etch NMSB 72–AE651 onto the disc, adjacent to the part number. AD, for cracks in the rim cooling air holes. Use paragraph 3. of the Accomplishment Instructions of RR ASB No. RB.211–72– AE717, dated January 21, 2005, to perform the eddy current inspection. Eddy Current Inspection for Model RB211– 22B–02 Engines (g) For model RB211–22B–02 engines, do the following: (1) Perform an eddy current inspection of the HP turbine discs listed in Table 5 of this TABLE 5.—AFFECTED HP TURBINE DISCS IN RR MODEL RB211–02 TURBOFAN ENGINES Part No. LK80622 ........... LK80623 ........... UL28267 ........... Serial No. LQDY6316 and higher. CQDY5945 and higher. All. (2) Use the compliance schedule in Table 6 of this AD. TABLE 6.—COMPLIANCE SCHEDULE FOR HP TURBINE DISCS LISTED IN TABLE 5 If Disc CSN on January 1, 2005 are: Then Eddy Current Inspect: (1) More than 9,000 CSN .................................................. (2) More than 1,500, but fewer than 9,001 CSN ............... Within 500 CIS after January 1, 2005, but before 11,000 CSN, whichever is sooner. Before exceeding 9,500 CSN, or at the next shop visit after the effective date of this AD, whichever occurs first. (3) For discs that pass inspection, use paragraph 3. of the Accomplishment Instructions of RR ASB No. RB.211–72– AE717, dated January 21, 2005, to permanently etch NMSB 72–AE717 onto the disc, adjacent to the part number. cprice-sewell on PROD1PC66 with PROPOSALS Other Conditions for All Engines (h) Do not perform the actions of this AD to a disc until that disc has reached at least 1,500 CSN. (i) Engines with an affected HP turbine disc at shop visit on the effective date of this AD and without the HP turbine rotor installed in the combustor outer case, must have the disc eddy current inspected before assembling the engine. (j) Engines with an affected HP turbine disc at shop visit on the effective date of this AD with the HPT rotor installed in the combustor case need not have the disc eddy current inspected at this time. (k) HP turbine discs previously eddy current inspected at fewer than 1,500 CSN must be inspected again using this AD. (l) Replace cracked HP turbine discs with a serviceable disc. VerDate Aug<31>2005 14:05 Jan 27, 2006 Jkt 208001 Definition Reporting Requirements (m) For the purpose of this AD, next shop visit is defined as the first shop visit opportunity when the HPT rotor is removed from the combustion case. (n) For the purpose of this AD, a serviceable part is one with cyclic life remaining and either not listed in any of the preceding tables or one listed in a preceding table, but previously eddy current inspected and permanently etch marked with the Service Bulletin (SB) number NMSB 72– AE651 or NMSB 72–C877 on the disc. (p) For all except model RB211–22B–02 engines, report findings of the inspection using paragraph 3.E. of the Accomplishment Instructions of RR ASB RB.211–72–AE651, dated November 22, 2004. The Office of Management and Budget (OMB) has approved the reporting requirements specified in paragraph 3.E. of the Accomplishment Instructions of RR ASB RB.211–72–AE651, dated November 22, 2004, and assigned OMB control number 2120–0056. (q) For model RB211–22B–02 engines, report findings of the inspection using paragraph 3.E. of the Accomplishment Instructions of RR ASB RB.211–72–AE717, dated January 21, 2005. The OMB has approved the reporting requirements specified in paragraph 3.E. of the Accomplishment Instructions of RR ASB RB.211–72–AE717, dated January 21, 2005, and assigned OMB control number 2120– 0056. Previous Credit (o) Previous credit is allowed for the actions in this AD for HP turbine discs with 1,500 CSN or more that were eddy current inspected using applicable RR SB No. RB.211–72-C817, Revision 2, dated March 7, 2001, RR TSD 594–J, Overhaul Processes Manual, Task 70–00–00–200–223, or RR SB No. RB.211–72–C877, Revision 1, dated March 7, 2001. PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 E:\FR\FM\30JAP1.SGM 30JAP1 4836 Federal Register / Vol. 71, No. 19 / Monday, January 30, 2006 / Proposed Rules Alternative Methods of Compliance (r) 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 (s) CAA Airworthiness Directive G–2004– 0027, dated November 19, 2004, and CAA Airworthiness Directive G–2005–0003, dated January 24, 2005, also address the subject of this AD. Issued in Burlington, Massachusetts, on January 19, 2006. Peter A. White, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E6–1092 Filed 1–27–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 73 [Docket No. FAA–2006–23531; Airspace Docket No. 04–ASO–14] Comments Invited RIN 2120–AA66 Proposed Modification of Restricted Areas R–3002A, B, C, D, E, and F; and Establishment of Restricted Area R– 3002G; Fort Benning, GA Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking. cprice-sewell on PROD1PC66 with PROPOSALS AGENCY: SUMMARY: This action proposes to modify the boundaries of the Restricted Area R–3002 range complex at Fort Benning, GA. The U.S. Army proposed these modifications as a result of a land exchange agreement between Fort Benning and the City of Columbus, GA. Specifically, the proposal would eliminate restricted airspace over a parcel of land that has been transferred from the Army to the City of Columbus. The proposal would also add new restricted airspace over a parcel of land to the south of the current restricted area complex, that was ceded by the City to the Army. In addition, a portion of the southwest section of R–3002, within the existing restricted airspace, would be redesignated as a separate restricted area, R–3002G, to better accommodate instrument approach procedures at Lawson Army Air Field (AAF). The internal boundaries between restricted area subdivisions would also be realigned slightly to permit more efficient scheduling and utilization of the range complex. Finally, the names of the controlling agency and using agency for the restricted areas would be changed to reflect their current titles. VerDate Aug<31>2005 14:05 Jan 27, 2006 Jkt 208001 Comments must be received on or before March 16, 2006. ADDRESSES: Send comments on this proposal to the Docket Management System, U.S. Department of Transportation, Room Plaza 401, 400 Seventh Street, SW., Washington, DC 20590–0001. You must identify FAA Docket Number FAA–2006–23531 and Airspace Docket No. 04–ASO–14, at the beginning of your comments. You may also submit comments through the Internet at https://dms.dot.gov. Comments on environmental and land use aspects should be directed to: Chief of Environmental Branch, Ft. Benning, GA; (Mr. Patrick Chauvey, telephone: 706–545–4211). FOR FURTHER INFORMATION CONTACT: Paul Gallant, Airspace and Rules, Office of System Operations Airspace and AIM, Federal Aviation Administration, 800 Independence Avenue, SW., Washington, DC 20591; telephone: (202) 267–8783. SUPPLEMENTARY INFORMATION: DATES: Interested parties are invited to participate in this proposed rulemaking by submitting such written data, views, or arguments as they may desire. Comments that provide the factual basis supporting the views and suggestions presented are particularly helpful in developing reasoned regulatory decisions on the proposal. Comments are specifically invited on the overall regulatory, aeronautical, economic, environmental, and energy-related aspects of the proposal. Communications should identify both docket numbers (FAA Docket No. FAA– 2006–23531 and Airspace Docket No. 04–ASO–14) and be submitted in triplicate to the Docket Management System (see ADDRESSES section for address and phone number). You may also submit comments through the Internet at https://dms.dot.gov. Commenters wishing the FAA to acknowledge receipt of their comments on this action must submit with those comments a self-addressed, stamped postcard on which the following statement is made: ‘‘Comments to FAA Docket No. FAA–2006–23531 and Airspace Docket No. 04–ASO–14.’’ The postcard will be date/time stamped and returned to the commenter. All communications received on or before the specified closing date for comments will be considered before taking action on the proposed rule. The proposal contained in this action may be changed in light of comments received. All comments submitted will be available for examination in the PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 public docket both before and after the closing date for comments. A report summarizing each substantive public contact with FAA personnel concerned with this rulemaking will be filed in the docket. Availability of NPRM’s An electronic copy of this document may be downloaded through the Internet at https://dms.dot.gov. Recently published rulemaking documents can also be accessed through the FAA’s Web page at https://www.faa.gov, or the Federal Register’s Web page at https:// www.gpoaccess.gov/fr/. You may review the public docket containing the proposal, any comments received, and any final disposition in person in the Dockets Office (see ADDRESSES section for address and phone number) between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. An informal docket may also be examined during normal business hours at the office of the Regional Air Traffic Division, Federal Aviation Administration, 1701 Columbia Avenue, College Park, GA 30337. Persons interested in being placed on a mailing list for future NPRM’s should contact the FAA’s Office of Rulemaking, (202) 267–9677, for a copy of Advisory Circular No. 11–2A, Notice of Proposed Rulemaking Distribution System, which describes the application procedure. Background In the year 2000, a State and Federal Land Exchange action was completed whereby a portion of Fort Benning Military Reservation land, in the northwest section of the Restricted Area R–3002 range complex, was transferred by the Army to the City of Columbus, GA. In addition, a parcel of City-owned land located adjacent to, and south of, the existing restricted areas was ceded to Fort Benning for military use. As a result of the land swap, the boundaries of the R–3002 complex must be adjusted to eliminate restricted airspace that overlies the land ceded to the City of Columbus, and add restricted airspace over the land transferred by the City to Fort Benning. With the transfer of land to the City, there is no longer a requirement for restricted airspace over that section. Elimination of that section of restricted airspace would enhance safety for instrument flight rules (IFR) and visual flight rules (VFR) aircraft operations at the Columbus Metropolitan Airport, Columbus, GA, by moving the boundary of the restricted area farther away from the airport. The new restricted area over the land transferred to Fort Benning would E:\FR\FM\30JAP1.SGM 30JAP1

Agencies

[Federal Register Volume 71, Number 19 (Monday, January 30, 2006)]
[Proposed Rules]
[Pages 4832-4836]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-1092]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NE-62-AD]
RIN 2120-AA64

Airworthiness Directives; Rolls-Royce plc RB211 Series Turbofan
Engines

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

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) for Rolls-Royce plc (RR) models RB211-535E4-37, RB211-
535E4-B-37, RB211-535C-37, RB211-535E4-B-75, RB211-535E4-C, and RB211-
22B-02 turbofan engines. That AD currently requires inspecting certain
high pressure (HP) turbine discs, manufactured between 1989 and 1999,
for cracks in the rim cooling air holes, and, if necessary, replacing
the discs with serviceable parts. This proposed AD would require the
same inspections, and would reduce the compliance times for eddy
current inspection (ECI) for the RR RB211-22B-02 engines. This proposed
AD results from the manufacturer reducing their recommended compliance
times for inspections on RB211-22B-02 engines. We are proposing this AD
to prevent possible disc failure, which could result in an uncontained
engine failure and damage to the airplane.

DATES: We must receive any comments on this proposed AD by March 31,
2006.

ADDRESSES: Use one of the following addresses to comment on this
proposed AD:
By mail: Federal Aviation Administration (FAA), New
England Region, Office of the Regional Counsel, Attention: Rules Docket
No. 2000-NE-62-AD, 12 New England Executive Park, Burlington, MA 01803-
5299.
By fax: (781) 238-7055.
By e-mail: 9-ane-adcomment@faa.gov.
You can get the service information identified in this proposed AD
from Rolls-Royce plc, PO Box 31, Derby, England; telephone: 011 44
1332-249428, fax: 011 44 1332-249223.
You may examine the AD docket, by appointment, at the FAA, New
England Region, Office of the Regional Counsel, 12 New England
Executive Park, Burlington, MA.

FOR FURTHER INFORMATION CONTACT: Ian Dargin, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803-5299; telephone (781) 238-
7178, fax (781) 238-7199.

SUPPLEMENTARY INFORMATION:

Comments Invited

We invite you to send any written relevant data, views, or
arguments regarding this proposal. Send your comments to an address
listed under ADDRESSES. Include ``AD Docket No. 2000-NE-62-AD'' in the
subject line of your comments. If you want us to acknowledge receipt of
your mailed comments, send us a self-addressed, stamped postcard with
the docket number written on it; we will date-stamp your postcard and
mail it back to you. We specifically invite comments on the overall
regulatory, economic, environmental, and energy aspects of the proposed
AD. If a person contacts us verbally, and that contact relates to a
substantive part of this proposed AD, we will summarize the contact and
place the summary in the docket. We will consider all comments received
by the closing date and may amend the

[[Page 4833]]

proposed AD in light of those comments.

Examining the AD Docket

You may examine the AD Docket (including any comments and service
information), by appointment, between 8 a.m. and 4:30 p.m., Monday
through Friday, except Federal holidays. See ADDRESSES for the
location.

Discussion

On December 15, 2004, the FAA issued AD 2004-26-03, Amendment 39-
13915 (69 FR 77881, December 29, 2004) for RR models RB211-535E4-37,
RB211-535E4-B-37, RB211-535C-37, RB211-535E4-B-75, and RB211-22B-02
turbofan engines. That AD requires inspecting certain HP turbine discs,
manufactured between 1989 and 1999, for cracks in the rim cooling air
holes, and, if necessary, replacing the discs with serviceable parts.

Actions Since AD 2004-26-03 Was Issued

Since we issued AD 2004-26-03, the Civil Aviation Authority (CAA),
which is the airworthiness authority for the United Kingdom, notified
us that an unsafe condition might exist on RR model RB211-22B-02
turbofan engines manufactured between 1989 and 1999. The CAA advises
that cracks were found in a Trent 800 HP turbine disc attributable to
machining anomalies during new manufacture. The RB211-22B-02 HP turbine
is similar in design to the Trent 800, manufactured at the same
facility and with the same tooling. This proposed AD would require
inspection of certain HP turbine discs, manufactured between 1989 and
1999, for cracks in the rim cooling air holes, and, if necessary,
replacement with serviceable parts. We are reducing the inspection
schedules required by AD 2004-26-03, for the high risk discs installed
on model RB211-22B-02 engines. This AD retains the same inspection
schedules, currently required for RR models RB211-535E4-37, RB211-
535E4-B-37, RB211-535C-37, RB211-535E4-B-75 turbofan engines that were
in AD 2004-26-03. The actions specified in this proposed AD are
intended to prevent possible disc failure, which could result in an
uncontained engine failure and damage to the airplane.

Bilateral Airworthiness Agreement

This engine model is manufactured in the United Kingdom and is type
certificated for operation in the United States under the provisions of
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. Under this bilateral
airworthiness agreement, the CAA has kept the FAA informed of the
situation described above. We have examined the findings of the CAA,
reviewed all available information, and determined that AD action is
necessary for products of this type design that are certificated for
operation in the United States.

Relevant Service Information

We have reviewed and approved the technical contents of RR ASB
RB.211-72-AE717, dated January 21, 2005, that describes procedures for
inspecting the RB211-22B disk for cracks. The CAA classified this
service bulletin as mandatory and issued AD G-2005-0003, dated January
24, 2005, in order to ensure the airworthiness of these RR RB211-22
turbofan engines in the U.K.

FAA's Determination and Requirements of the Proposed AD

We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other products
of this same type design. Therefore, we are proposing this AD, which
would require the same inspections specified in AD 2004-26-03, but
would reduce the compliance times for the model RB211-22B engine to:
Within 500 cycles-in-service (CIS) after January 1, 2005
or before accumulating 11,000 cycles-since-new (CSN), whichever occurs
first, on engines with more than 9,000 CSN on January 1, 2005, and
Before accumulating 9,500 CSN or at the next shop visit
after the effective date of this proposed AD, whichever occurs first,
on engines with more than 1,500 CSN but fewer than 9,001 CSN on January
1, 2005.
The proposed AD would require that you do these actions using the
service information described previously.

Costs of Compliance

We estimate that this proposed AD would affect six RR RB211-22B
engines installed on airplanes of U.S. registry. We also estimate that
it would take about 4.0 work hours per engine to perform the proposed
actions, and that the average labor rate is $65 per work hour. There
are no required parts. Based on these figures, we estimate the total
cost of the proposed AD to U.S. operators to be $1,560.

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 proposed AD would not have federalism
implications under ExecutiveOrder 13132. This proposed AD would 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 proposed
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. Would 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 proposal and
placed it in the AD Docket. You may get a copy of this summary by
sending a request to us at the address listed under ADDRESSES. Include
``AD Docket No. 2000-NE-62-AD'' in your request.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

Accordingly, under the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend 14
CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

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

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

[[Page 4834]]

Sec. 39.13 [Amended]

2. The FAA amends Sec. 39.13 by removing Amendment 39-13915 (69 FR
77881, December 29, 2004) and by adding a new airworthiness directive,
to read as follows:

Rolls-Royce plc: Docket No. 2000-NE-62-AD.

Comments Due Date

(a) The Federal Aviation Administration (FAA) must receive
comments on this airworthiness directive (AD) action by March 31,
2006.

Affected ADs

(b) This AD supersedes AD 2004-26-03, Amendment 39-13915.

Applicability

(c) This AD applies to Rolls-Royce plc (RR) models RB211-535E4-
37, RB211-535E4-B-37, RB211-535C-37, RB211-535E4-B-75, RB211-535E4-
C, and RB211-22B-02 turbofan engines with turbine discs having part
numbers and serial numbers listed in the following Tables 1, 3, and
5 of this AD. These turbofan engines are installed on, but not
limited to, Boeing 757, Tupolev Tu204, and Lockheed L-1011 series
airplanes.

Unsafe Condition

(d) This AD results from the manufacturer reducing the
inspection compliance times for the RB211-22B-02 turbofan engines.
We are issuing this AD to prevent possible disc failure, which could
result in an uncontained engine failure and damage to the airplane.

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.

Eddy Current Inspection for All Except Model RB211-22B-02 Engines

(f) For all except model RB211-22B-02 engines, do the following:
(1) Perform an eddy current inspection of the high pressure (HP)
turbine discs listed in Table 1 of this AD, for cracks in the rim
cooling air holes. Use paragraph 3. of the Accomplishment
Instructions of RR Alert Service Bulletin (ASB) No. RB.211-72-AE651,
dated November 22, 2004, to perform the eddy current inspection.

Table 1.--Affected HP Turbine Discs Using Compliance Schedule in Table 2
----------------------------------------------------------------------------------------------------------------
Part No. Serial No. Part No. Serial No.
----------------------------------------------------------------------------------------------------------------
LK80623.......................... CQDY6397................. UL27681................. LDRCZ12893
LK80623.......................... CQDY6504................. UL27681................. LDRCZ12985
UL27680.......................... CQDY6451................. UL27681................. LDRCZ13044
UL27680.......................... CQDY6452................. UL27681................. LDRCZ13047
UL27680.......................... CQDY6466................. UL27681................. LQDY6803
UL27680.......................... CQDY6468................. UL27681................. LQDY6814
UL27680.......................... CQDY6471................. UL27681................. LQDY6847
UL27680.......................... CQDY6496................. UL27681................. LQDY6868
UL27680.......................... CQDY6505................. UL27681................. LQDY6875
UL27680.......................... CQDY6653................. UL27681................. LQDY6892
UL27680.......................... CQDY6656................. UL27681................. LQDY6898
UL27680.......................... CQDY6657................. UL27681................. LQDY6904
UL27680.......................... CQDY6684................. UL27681................. LQDY6909
UL27680.......................... CQDY6883................. UL27681................. LQDY6910
UL27681.......................... CQDY6465................. UL27681................. LQDY9133
UL27681.......................... LAQDY6002................ UL27681................. LQDY9574
UL27681.......................... LAQDY6083................ UL27681................. LQDY9579
UL27681.......................... LAQDY6087................ UL27681................. LQDY9672
UL27681.......................... LDRCZ10247............... UL27681................. LQDY9770
UL27681.......................... LDRCZ10277............... UL27681................. LQDY9783
UL27681.......................... LDRCZ10318............... UL27681................. LQDY9786
UL27681.......................... LDRCZ10335............... UL27681................. LQDY9900
UL27681.......................... LDRCZ10430............... UL27681................. LQDY9902
UL27681.......................... LDRCZ10531............... UL27681................. LQDY9929
UL27681.......................... LDRCZ10750............... UL27681................. LQDY9957
UL27681.......................... LDRCZ10899............... UL27681................. LQDY9982
UL27681.......................... LDRCZ11616............... UL27681................. LQDY9992
UL27681.......................... LDRCZ11720............... UL27681................. WGQDY90005
UL27681.......................... LDRCZ11893...............
----------------------------------------------------------------------------------------------------------------

(2) Use the compliance schedule in Table 2 of this AD.

Table 2.--Compliance Schedule for HP Turbine Discs Listed in Table 1
------------------------------------------------------------------------
If Disc Cycles-Since-New (CSN) on
October 8, 2004 are: Then Eddy Current Inspect:
------------------------------------------------------------------------
(1) 12,750 CSN or more............ Within 250 cycles-in-service (CIS)
from October 8, 2004 or within
14,500 CSN, whichever occurs first.
(2) Fewer than 12,750 CSN but Within 500 CIS from October 8, 2004.
10,500 CSN or more.
(3) Fewer than 10,500 CSN......... Before 11,000 CSN or at next shop
visit after the effective date of
this AD, whichever occurs first.
------------------------------------------------------------------------

(3) On discs that pass inspection, use paragraph 3. of the
Accomplishment Instructions of RR ASB No. RB.211-72-AE651, dated
November 22, 2004, to permanently etch NMSB 72-AE651 onto the disc,
adjacent to the part number.
(4) Perform an eddy current inspection of the HP turbine discs
listed in Table 3 of this AD, for cracks in the rim cooling air
holes. Use paragraph 3. of the Accomplishment Instructions of RR ASB
No. RB.211-72-AE651, dated November 22, 2004, to perform the eddy
current inspection.

[[Page 4835]]

Table 3.--Affected HP Turbine Discs Using Compliance Schedule in Table 4
------------------------------------------------------------------------
Part No. Serial No.
------------------------------------------------------------------------
UL10323............................... CQDY6070 and higher.
UL27680............................... All.
UL27681............................... All.
LK80622............................... LQDY6316 and higher.
LK80623............................... CQDY5945 and higher.
UL28267............................... All.
------------------------------------------------------------------------

(5) Use the compliance schedule in Table 4 of this AD.

Table 4.--Compliance Schedule for HP Turbine Discs Listed in Table 3
------------------------------------------------------------------------
If Disc CSN on January 29, 2001
are: Then Eddy Current Inspect:
------------------------------------------------------------------------
(1) Fewer than 13,700 CSN......... Before reaching 14,500 CSN, or at
the next shop visit after the
effective date of this AD,
whichever occurs first.
(2) 13,700 CSN or more............ Before reaching one of the
following, whichever occurs first
after the effective date of this
AD:
(i) 15,300 CSN.
(ii) Within 800 CIS since January
29, 2001.
(iii) At next shop visit.
------------------------------------------------------------------------

(6) For discs that pass inspection, use paragraph 3. of the
Accomplishment Instructions of RR ASB No. RB.211-72-AE651, dated
November 22, 2004, to permanently etch NMSB 72-AE651 onto the disc,
adjacent to the part number.

Eddy Current Inspection for Model RB211-22B-02 Engines

(g) For model RB211-22B-02 engines, do the following:
(1) Perform an eddy current inspection of the HP turbine discs
listed in Table 5 of this AD, for cracks in the rim cooling air
holes. Use paragraph 3. of the Accomplishment Instructions of RR ASB
No. RB.211-72-AE717, dated January 21, 2005, to perform the eddy
current inspection.

Table 5.--Affected HP Turbine Discs in RR Model RB211-02 Turbofan
Engines
------------------------------------------------------------------------
Part No. Serial No.
------------------------------------------------------------------------
LK80622............................... LQDY6316 and higher.
LK80623............................... CQDY5945 and higher.
UL28267............................... All.
------------------------------------------------------------------------

(2) Use the compliance schedule in Table 6 of this AD.

Table 6.--Compliance Schedule for HP Turbine Discs Listed in Table 5
------------------------------------------------------------------------
If Disc CSN on January 1, 2005
are: Then Eddy Current Inspect:
------------------------------------------------------------------------
(1) More than 9,000 CSN........... Within 500 CIS after January 1,
2005, but before 11,000 CSN,
whichever is sooner.
(2) More than 1,500, but fewer Before exceeding 9,500 CSN, or at
than 9,001 CSN. the next shop visit after the
effective date of this AD,
whichever occurs first.
------------------------------------------------------------------------

(3) For discs that pass inspection, use paragraph 3. of the
Accomplishment Instructions of RR ASB No. RB.211-72-AE717, dated
January 21, 2005, to permanently etch NMSB 72-AE717 onto the disc,
adjacent to the part number.

Other Conditions for All Engines

(h) Do not perform the actions of this AD to a disc until that
disc has reached at least 1,500 CSN.
(i) Engines with an affected HP turbine disc at shop visit on
the effective date of this AD and without the HP turbine rotor
installed in the combustor outer case, must have the disc eddy
current inspected before assembling the engine.
(j) Engines with an affected HP turbine disc at shop visit on
the effective date of this AD with the HPT rotor installed in the
combustor case need not have the disc eddy current inspected at this
time.
(k) HP turbine discs previously eddy current inspected at fewer
than 1,500 CSN must be inspected again using this AD.
(l) Replace cracked HP turbine discs with a serviceable disc.

Definition

(m) For the purpose of this AD, next shop visit is defined as
the first shop visit opportunity when the HPT rotor is removed from
the combustion case.
(n) For the purpose of this AD, a serviceable part is one with
cyclic life remaining and either not listed in any of the preceding
tables or one listed in a preceding table, but previously eddy
current inspected and permanently etch marked with the Service
Bulletin (SB) number NMSB 72-AE651 or NMSB 72-C877 on the disc.

Previous Credit

(o) Previous credit is allowed for the actions in this AD for HP
turbine discs with 1,500 CSN or more that were eddy current
inspected using applicable RR SB No. RB.211-72-C817, Revision 2,
dated March 7, 2001, RR TSD 594-J, Overhaul Processes Manual, Task
70-00-00-200-223, or RR SB No. RB.211-72-C877, Revision 1, dated
March 7, 2001.

Reporting Requirements

(p) For all except model RB211-22B-02 engines, report findings
of the inspection using paragraph 3.E. of the Accomplishment
Instructions of RR ASB RB.211-72-AE651, dated November 22, 2004. The
Office of Management and Budget (OMB) has approved the reporting
requirements specified in paragraph 3.E. of the Accomplishment
Instructions of RR ASB RB.211-72-AE651, dated November 22, 2004, and
assigned OMB control number 2120-0056.
(q) For model RB211-22B-02 engines, report findings of the
inspection using paragraph 3.E. of the Accomplishment Instructions
of RR ASB RB.211-72-AE717, dated January 21, 2005. The OMB has
approved the reporting requirements specified in paragraph 3.E. of
the Accomplishment Instructions of RR ASB RB.211-72-AE717, dated
January 21, 2005, and assigned OMB control number 2120-0056.

[[Page 4836]]

Alternative Methods of Compliance

(r) 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

(s) CAA Airworthiness Directive G-2004-0027, dated November 19,
2004, and CAA Airworthiness Directive G-2005-0003, dated January 24,
2005, also address the subject of this AD.

Issued in Burlington, Massachusetts, on January 19, 2006.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E6-1092 Filed 1-27-06; 8:45 am]
BILLING CODE 4910-13-P

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