Airworthiness Directives; Rolls-Royce plc RB211 Series Turbofan Engines, 49339-49343 [E6-13910]

Download as PDF Federal Register / Vol. 71, No. 163 / Wednesday, August 23, 2006 / Rules and Regulations installation, or assembly to detect obvious damage, failure, or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to ensure visual access to all surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight, or droplight and may require removal or opening of access panels or doors. Stands, ladders, or platforms may be required to gain proximity to the area being checked.’’ 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. Previous Actions Accomplished According to Other Service Information (g) Actions accomplished before the effective date of this AD in accordance with Bombardier Drawing Number K601R50180, dated June 2, 2006; or Bombardier Service Bulletin 601R–24–122, dated June 27, 2006; are considered acceptable for compliance with the actions specified in paragraph (f) of this AD. BILLING CODE 4910–13–P Parts Installation (h) As of the effective date of this AD, no person may install AC contactor 1K4XD, 2K4XD, or K4XA, having an Ultem 2200 terminal base plate, on any airplane, unless RTV sealant has been applied to the terminal base plate in accordance with Bombardier Service Bulletin 601R–24–122, Revision A, dated July 13, 2006. Alternative Methods of Compliance (AMOCs) (i)(1) The Manager, New York Aircraft Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. (3) AMOCs approved previously in accordance with AD 2006–16–07, are approved as AMOCs for the corresponding provisions of this AD. sroberts on PROD1PC70 with RULES Related Information (j) Canadian airworthiness directive CF– 2006–17, dated July 11, 2006, also addresses the subject of this AD. Material Incorporated by Reference (k) You must use Bombardier Service Bulletin 601R–24–122, Revision A, dated July 13, 2006, to perform the actions that are required by this AD, unless the AD specifies otherwise. On August 9, 2006 (71 FR 45364, August 9, 2006), the Director of the Federal Register approved the incorporation by reference of this document. Contact Bombardier, Inc., Canadair, Aerospace Group, P.O. Box 6087, Station Centre-ville, Montreal, Quebec H3C 3G9, Canada, 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., Room PL–401, Nassif Building, Washington, DC; on the Internet at https://dms.dot.gov; or at the National Archives and Records VerDate Aug<31>2005 15:49 Aug 22, 2006 Jkt 208001 Issued in Renton, Washington, on August 14, 2006. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6–13831 Filed 8–22–06; 8:45 am] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–25584; Directorate Identifier 2000–NE–62–AD; Amendment 39– 14733; AD 2006–17–12] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce plc RB211 Series Turbofan Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: This amendment supersedes an existing airworthiness directive (AD), that is applicable to Rolls-Royce plc (RR) models RB211–535E4–37, RB211– 535E4––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. The manufacturer identified reaminginduced machining anomalies (RIMA) as the cause for the cracking. This amendment requires the same inspections, and reduces the compliance times for eddy current inspection (ECI) for the RR RB211–22B– 02 engines. This amendment results from the manufacturer reducing their recommended compliance times for inspections on RB211–22B–02 engines. We are issuing this AD to prevent possible disc failure, which could result in an uncontained engine failure and damage to the airplane. DATES: This AD becomes effective September 27, 2006. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of September 27, 2006. The Director of the Federal Register approved the incorporation by reference PO 00000 Frm 00031 Fmt 4700 Sfmt 4700 49339 of RR Alert Service Bulletin (ASB) No. RB211–72–AE651, dated November 22, 2004, as of January 13, 2005 (69 FR 77881, December 29, 2004) and RR Service Bulletin (SB) No. RB211–72– C877, Revision 1, dated March 7, 2001, listed in the AD, as of December 24, 2001 (66 FR 57859, November 19, 2001). ADDRESSES: 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 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: Ian Dargin, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; telephone (781) 238–7178, 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 RR models RB211–535E4–37, RB211–535E4–B–37, RB211–535C–37, RB211–535E4–B–75, and RB211–22B–02 turbofan engines. We published the proposed AD in the Federal Register on January 30, 2006 (71 FR 4832). That action proposed to reduce the inspection schedules required by AD 2004–26–03, for the high risk discs installed on model RB211–22B–02 engines. 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 Offices between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone (800) 647–5227) is located on the plaza level of the Department of Transportation Nassif Building at the street address stated in ADDRESSES. Comments will be available in the AD docket shortly after the DMS receives them. Comments We provided the public the opportunity to participate in the development of this AD. We received no comments on the proposal or on the determination of the cost to the public. Editorial Change To Add Background Information to the Summary After we issued the NPRM, RR informed us that they identified reaming-induced machining anomalies (RIMA) as the cause for the cracking. E:\FR\FM\23AUR1.SGM 23AUR1 49340 Federal Register / Vol. 71, No. 163 / Wednesday, August 23, 2006 / Rules and Regulations Docket Number Change We are transferring the docket for this AD to the Docket Management System as part of our on-going docket management consolidation efforts. The new Docket No. is FAA–2006–25584. The old Docket No. became the Directorate Identifier, which is 2000– NE–62–AD. This final rule might get logged into the DMS docket, ahead of the proposed AD and comments received, as we are in the process of sending those items to the DMS. Conclusion We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. Costs of Compliance We estimate that this AD will affect six RR RB211–22B engines installed on airplanes of U.S. registry. We also estimate that it will take about 4.0 workhours per engine to perform the 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 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 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 § 39.13 [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, Amendment 39–14733, to read as follows: I 2006–17–12 Rolls-Royce plc: Amendment 39–14733. Docket No. FAA–2006–25584; Directorate Identifier 2000–NE–62–AD. Effective Date (a) This airworthiness directive (AD) becomes effective September 27, 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. Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation Administration amends 14 CFR part 39 as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. 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 sroberts on PROD1PC70 with RULES Part No. LK80623 LK80623 UL27680 UL27680 UL27680 UL27680 UL27680 UL27680 UL27680 UL27680 UL27680 UL27680 UL27680 Serial No. ............................................................... ............................................................... ............................................................... ............................................................... ............................................................... ............................................................... ............................................................... ............................................................... ............................................................... ............................................................... ............................................................... ............................................................... ............................................................... VerDate Aug<31>2005 15:49 Aug 22, 2006 Jkt 208001 CQDY6397 CQDY6504 CQDY6451 CQDY6452 CQDY6466 CQDY6468 CQDY6471 CQDY6496 CQDY6505 CQDY6653 CQDY6656 CQDY6657 CQDY6684 PO 00000 Frm 00032 Part No. Serial No. UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 Fmt 4700 .............................................................. .............................................................. .............................................................. .............................................................. .............................................................. .............................................................. .............................................................. .............................................................. .............................................................. .............................................................. .............................................................. .............................................................. .............................................................. Sfmt 4700 E:\FR\FM\23AUR1.SGM 23AUR1 LDRCZ12893 LDRCZ12985 LDRCZ13044 LDRCZ13047 LQDY6803 LQDY6814 LQDY6847 LQDY6868 LQDY6875 LQDY6892 LQDY6898 LQDY6904 LQDY6909 Federal Register / Vol. 71, No. 163 / Wednesday, August 23, 2006 / Rules and Regulations 49341 TABLE 1.—AFFECTED HP TURBINE DISCS USING COMPLIANCE SCHEDULE IN TABLE 2—Continued Part No. UL27680 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 UL27681 Serial No. ............................................................... ............................................................... ............................................................... ............................................................... ............................................................... ............................................................... ............................................................... ............................................................... ............................................................... ............................................................... ............................................................... ............................................................... ............................................................... ............................................................... ............................................................... ............................................................... Part No. 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 Serial No. .............................................................. .............................................................. .............................................................. .............................................................. .............................................................. .............................................................. .............................................................. .............................................................. .............................................................. .............................................................. .............................................................. .............................................................. .............................................................. .............................................................. .............................................................. 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: (i) 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. (ii) Fewer than 12,750 CSN but 10,500 CSN or more. (iii) 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 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. Before 11,000 CSN or at next shop visit after the effective date of this AD, whichever occurs first. TABLE 3.—AFFECTED HP TURBINE DISCS USING COMPLIANCE SCHEDULE IN TABLE 4 Part No. UL10323 UL27680 UL27681 LK80622 LK80623 Serial No. ............... ............... ............... ............... ............... CQDY6070 and higher. All. All. LQDY6316 and higher. CQDY5945 and higher. TABLE 3.—AFFECTED HP TURBINE DISCS USING COMPLIANCE SCHEDULE IN TABLE 4—Continued Part No. UL28267 ............... Serial No. 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: (i) 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: (A) 15,300 CSN. (B) Within 800 CIS since January 29, 2001. (C) At next shop visit. sroberts on PROD1PC70 with RULES (ii) 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. VerDate Aug<31>2005 15:49 Aug 22, 2006 Jkt 208001 Eddy Current Inspection for Model RB211– 22B–02 Engines AE717, dated January 21, 2005, to perform the eddy current inspection. (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– PO 00000 Frm 00033 Fmt 4700 Sfmt 4700 E:\FR\FM\23AUR1.SGM 23AUR1 49342 Federal Register / Vol. 71, No. 163 / Wednesday, August 23, 2006 / Rules and Regulations TABLE 5.—AFFECTED HP TURBINE DISCS IN RR MODEL RB211–02 TURBOFAN ENGINES Part No. TABLE 5.—AFFECTED HP TURBINE DISCS IN RR MODEL RB211–02 TURBOFAN ENGINES—Continued Serial No. LK80622 ............... LK80623 ............... Part No. LQDY6316 and higher. CQDY5945 and higher. (2) Use the compliance schedule in Table 6 of this AD. Serial No. UL28267 ............... All. TABLE 6.—COMPLIANCE SCHEDULE FOR HP TURBINE DISCS LISTED IN TABLE 5 If disc CSN on January 1, 2005 are: Then eddy current inspect: (i) More than 9,000 CSN .................................... (ii) 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. 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. 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. 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. Material Incorporated by Reference (s) You must use the service information specified in Table 7 of this AD to perform the inspections required by this AD. The Director of the Federal Register approved the incorporation by reference of RR ASB RB.211–72–AE717, dated January 21, 2005, listed in Table 7 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. The incorporation by reference of RR ASB No. RB.211–72–AE651, dated November 22, 2004, was approved previously by the Director of the Federal Register as of January 13, 2005 (69 FR 77881, December 29, 2004). The incorporation by reference of RR SB No. RB.211–72–C877, Revision 1, dated March 7, 2001, was approved previously by the Director of the Federal Register as of December 24, 2001 (66 FR 57859, November 19, 2001). You can get a copy from RollsRoyce plc, PO Box 31, Derby, England; telephone: 011 44 1332–249428, fax: 011 44 1332–249223, for a copy of this service information. You may review copies at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA; or 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/federalregister/cfr/ibr-locations.html. 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. TABLE 7.—INCORPORATION BY REFERENCE sroberts on PROD1PC70 with RULES Service Bulletin Page Nos. Revision RB.211–72–AE651 .............................. Total Pages—7 RB.211–72–AE717 .............................. Total Pages—8 RB.211–72–C877 ................................ Total Pages—5 All ........................................................ Original ............................................... November 22, 2004. All ........................................................ Original ............................................... January 21, 2005. All ........................................................ 1 .......................................................... March 7, 2001. VerDate Aug<31>2005 15:49 Aug 22, 2006 Jkt 208001 PO 00000 Frm 00034 Fmt 4700 Sfmt 4700 E:\FR\FM\23AUR1.SGM Date 23AUR1 Federal Register / Vol. 71, No. 163 / Wednesday, August 23, 2006 / Rules and Regulations Related Information (t) 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 August 15, 2006. Thomas A. Boudreau, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E6–13910 Filed 8–22–06; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA–2006–24781; Airspace Docket No. 06–AWP–8] Modification of Class E Airspace; Half Moon Bay, CA Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: sroberts on PROD1PC70 with RULES SUMMARY: This action modifies the Class E airspace area at Half Moon Bay, CA. The establishment of an Area Navigation (RNAV) Global Positioning System (GPS) Z Instrument Approach Procedure (IAP) to Runway (RWY) 30 to Half Moon Bay Airport, Half Moon Bay, CA has made this action necessary. Additional controlled airspace extending upward from 700 feet or more above the surface of the earth is needed to contain aircraft executing this RNAV (GPS) ZIAP to RWY 30 at Half Moon Bay Airport. The intended effect of this action is to provide adequate controlled airspace for Instrument Flight Rules operations at Half Moon Bay Airport, Half Moon Bay, CA EFFECTIVE DATE: 0901 UTC September 28, 2006. The Director of the Federal Register approves this incorporation by reference action under 1 CFR part 51, subject to the annual revision of FAA Order 7400.9 and publication of conforming amendments. FOR FURTHER INFORMATION CONTACT: The Office of the Regional Western Terminal Operations, Federal Aviation Administration, OF 15000 Aviation Boulevard, Lawndale, California 90261, telephone (310) 725–6502. SUPPLEMENTARY INFORMATION: History On June 14, 2006, the FAA proposed to amend 14 CFR part 71 by modifying the Class E airspace area at Half Moon Bay, CA (06 FR 34296). Additional controlled airspace extending upward VerDate Aug<31>2005 15:49 Aug 22, 2006 Jkt 208001 from 700 feet or more above the surface is needed to contain aircraft executing the RNAV (GPS) Z IAP RWY 30 to Half Moon Bay Airport. This action will provide adequate controlled airspace for aircraft executing the RNAV (GPS) Z IAP RWY 30 to Half Moon Bay Airport, Half Moon Bay, CA. Interested parties were invited to participate in this rulemaking proceeding by submitting written comments on the proposal to the FAA. No comments to the proposal were received. Class E airspace designations for airspace extending from 700 feet or more above the surface of the earth are published in paragraph 6005 of FAA Order 7400.9N, dated September 1, 2005, and effective September 15, 2005, which is incorporated by reference in 14 CFR 71.1. The Class E airspace designation listed in this document will be published subsequently in the Order. The Rule This amendment to 14 CFR part 71 modifies the Class E airspace area at Half Moon Bay, CA. The establishment of a RNAV (GPS) Z IAP RWY 30 to Half Moon Bay Airport has made this action necessary. The effect of this action will provide adequate airspace for aircraft executing the RNAV (GPS) Z IAP RWY 30 to Half Moon Bay Airport, Half Moon Bay, CA. The FAA has determined that this regulation only involves an established body of technical regulations for which frequent and routine amendments are necessary to keep them operationally current. Therefore, this regulation—(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) does not warrant preparation of a Regulatory Evaluation as the anticipated impact is so minimal. Since this is a routine matter that will only affect air traffic procedures and air navigation, it is certified that this rule will not have a significant economic impact on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 71 Airspace, Incorporation by reference, Navigation (air). Adoption of the Amendment In consideration of the foregoing, the Federal Aviation Administration amends 14 CFR part 71 as follows: I PO 00000 Frm 00035 Fmt 4700 Sfmt 4700 49343 PART 71—DESIGNATION OF CLASS A, CLASS B, CLASS C, CLASS D, AND CLASS E AIRSPACE AREAS; AIRWAYS, ROUTES; AND REPORTING POINTS 1. The authority citation for 14 CFR part 71 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40103, 40113, 40120; E.O. 10854, 24 FR 9565, 3 CFR, 1959– 1963 Comp., p. 389. § 71.1 [Amended] 2. The incorporation by reference in 14 CFR 71.1 of the Federal Aviation Administration Order 7400.9N, Airspace Designations and Reporting Points, dated September 1, 2005, and effective September 15, 2005, is amended as follows: I Paragraph 6005 Class E airspace areas extending upward from 700 feet or more above the surface of the earth. * * * * * AWP CA E5 Half Moon Bay, CA [Amended] Half Moon Bay Airport (Lat. 37°30′48″ N, long. 122°30′04″ W) That airspace extending upward from 700 feet above the surface, bounded on the north by lat. 37°35′00″ N, on the east by long. 122°14′00″ W, on the south by lat. 37°18′00″ N, on the west by long. 122°35′04″ W. * * * * * Issued in Los Angeles, California, on August 7, 2006. Leonard A. Mobley, Acting Area Director, Western Terminal Operations. [FR Doc. 06–7062 Filed 8–22–06; 8:45 am] BILLING CODE 4910–13–M DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA–2006–23714; Airspace Docket No. 06–AAL–07] Revision of Class E Airspace; Barter Island, AK Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: SUMMARY: This action revises Class E airspace at Barter Island, AK to provide adequate controlled airspace to contain aircraft executing two new Standard Instrument Approach Procedures (SIAPs) and one amended SIAP. This rule results in revised Class E airspace established upward from 700 feet (ft.) and 1,200 ft. above the surface at Barter Island Airport, AK. E:\FR\FM\23AUR1.SGM 23AUR1

Agencies

[Federal Register Volume 71, Number 163 (Wednesday, August 23, 2006)]
[Rules and Regulations]
[Pages 49339-49343]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-13910]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-25584; Directorate Identifier 2000-NE-62-AD;
Amendment 39-14733; AD 2006-17-12]
RIN 2120-AA64

Airworthiness Directives; Rolls-Royce plc RB211 Series Turbofan
Engines

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

ACTION: Final rule.

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SUMMARY: This amendment supersedes an existing airworthiness directive
(AD), that is applicable to Rolls-Royce plc (RR) models RB211-535E4-37,
RB211-535E4--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. The manufacturer identified
reaming-induced machining anomalies (RIMA) as the cause for the
cracking. This amendment requires the same inspections, and reduces the
compliance times for eddy current inspection (ECI) for the RR RB211-
22B-02 engines. This amendment results from the manufacturer reducing
their recommended compliance times for inspections on RB211-22B-02
engines. We are issuing this AD to prevent possible disc failure, which
could result in an uncontained engine failure and damage to the
airplane.

DATES: This AD becomes effective September 27, 2006. The Director of
the Federal Register approved the incorporation by reference of certain
publications listed in the regulations as of September 27, 2006.
The Director of the Federal Register approved the incorporation by
reference of RR Alert Service Bulletin (ASB) No. RB211-72-AE651, dated
November 22, 2004, as of January 13, 2005 (69 FR 77881, December 29,
2004) and RR Service Bulletin (SB) No. RB211-72-C877, Revision 1, dated
March 7, 2001, listed in the AD, as of December 24, 2001 (66 FR 57859,
November 19, 2001).

ADDRESSES: 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 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: Ian Dargin, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; telephone (781) 238-7178,
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 RR models RB211-535E4-37, RB211-535E4-B-37, RB211-535C-37, RB211-
535E4-B-75, and RB211-22B-02 turbofan engines. We published the
proposed AD in the Federal Register on January 30, 2006 (71 FR 4832).
That action proposed to reduce the inspection schedules required by AD
2004-26-03, for the high risk discs installed on model RB211-22B-02
engines.

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 Offices between 9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The Docket Office (telephone (800)
647-5227) is located on the plaza level of the Department of
Transportation Nassif Building at the street address stated in
ADDRESSES. Comments will be available in the AD docket shortly after
the DMS receives them.

Comments

We provided the public the opportunity to participate in the
development of this AD. We received no comments on the proposal or on
the determination of the cost to the public.

Editorial Change To Add Background Information to the Summary

After we issued the NPRM, RR informed us that they identified
reaming-induced machining anomalies (RIMA) as the cause for the
cracking.

[[Page 49340]]

Docket Number Change

We are transferring the docket for this AD to the Docket Management
System as part of our on-going docket management consolidation efforts.
The new Docket No. is FAA-2006-25584. The old Docket No. became the
Directorate Identifier, which is 2000-NE-62-AD. This final rule might
get logged into the DMS docket, ahead of the proposed AD and comments
received, as we are in the process of sending those items to the DMS.

Conclusion

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

Costs of Compliance

We estimate that this AD will affect six RR RB211-22B engines
installed on airplanes of U.S. registry. We also estimate that it will
take about 4.0 work-hours per engine to perform the 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 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 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 39-13915 (69 FR
77881, December 29, 2004) and by adding a new airworthiness directive,
Amendment 39-14733, to read as follows:

2006-17-12 Rolls-Royce plc: Amendment 39-14733. Docket No. FAA-2006-
25584; Directorate Identifier 2000-NE-62-AD.

Effective Date

(a) This airworthiness directive (AD) becomes effective
September 27, 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

[[Page 49341]]

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:
------------------------------------------------------------------------
(i) 12,750 CSN or more....... Within 250 cycles-in-service (CIS) from
October 8, 2004 or within 14,500 CSN,
whichever occurs first.
(ii) Fewer than 12,750 CSN Within 500 CIS from October 8, 2004.
but 10,500 CSN or more.
(iii) 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.

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:
------------------------------------------------------------------------
(i) 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.
(ii) 13,700 CSN or more...... Before reaching one of the following,
whichever occurs first after the
effective date of this AD:
(A) 15,300 CSN.
(B) Within 800 CIS since January 29,
2001.
(C) 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.

[[Page 49342]]

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:
------------------------------------------------------------------------
(i) More than 9,000 CSN...... Within 500 CIS after January 1, 2005, but
before 11,000 CSN, whichever is sooner.
(ii) More than 1,500, but Before exceeding 9,500 CSN, or at the
fewer than 9,001 CSN. 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.

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.

Material Incorporated by Reference

(s) You must use the service information specified in Table 7 of
this AD to perform the inspections required by this AD. The Director
of the Federal Register approved the incorporation by reference of
RR ASB RB.211-72-AE717, dated January 21, 2005, listed in Table 7 of
this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. The
incorporation by reference of RR ASB No. RB.211-72-AE651, dated
November 22, 2004, was approved previously by the Director of the
Federal Register as of January 13, 2005 (69 FR 77881, December 29,
2004). The incorporation by reference of RR SB No. RB.211-72-C877,
Revision 1, dated March 7, 2001, was approved previously by the
Director of the Federal Register as of December 24, 2001 (66 FR
57859, November 19, 2001). You can get a copy from Rolls-Royce plc,
PO Box 31, Derby, England; telephone: 011 44 1332-249428, fax: 011
44 1332-249223, for a copy of this service information. You may
review copies at the FAA, New England Region, Office of the Regional
Counsel, 12 New England Executive Park, Burlington, MA; or 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 7.--Incorporation by Reference
----------------------------------------------------------------------------------------------------------------
Service Bulletin Page Nos. Revision Date
----------------------------------------------------------------------------------------------------------------
RB.211-72-AE651.................. All................. Original............ November 22, 2004.
Total Pages--7
RB.211-72-AE717.................. All................. Original............ January 21, 2005.
Total Pages--8
RB.211-72-C877................... All................. 1................... March 7, 2001.
Total Pages--5
----------------------------------------------------------------------------------------------------------------

[[Page 49343]]

Related Information

(t) 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 August 15, 2006.
Thomas A. Boudreau,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E6-13910 Filed 8-22-06; 8:45 am]
BILLING CODE 4910-13-P

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