Airworthiness Directives; Rolls-Royce plc RB211 Series Turbofan Engines, 3863-3867 [05-1384]

Download as PDF Federal Register / Vol. 70, No. 17 / Thursday, January 27, 2005 / Rules and Regulations provide credit card loans and, instead, grant closed-ended and open-ended loans with the prerequisite underwriting documentation. Further, these smaller credit unions generally maintain a higher expense ratio, since many are involved with high-transaction accounts requiring higher personnel costs and related operational expenses, and lack economies of scale. Further, among the 450 federal credit unions where the most common rate is more than 15 percent for unsecured loans, 62 credit unions have 20 percent or more of their assets in this category and all but five credit unions have assets of less than $10 million. For these credit unions, lowering the rates would threaten their liquidity, capital, earnings, and growth. The Board has concluded that conditions exist to retain the federal credit union interest rate ceiling of 18 percent per year for the period March 9, 2005 through September 8, 2006. Finally, the Board is prepared to reconsider the 18 percent ceiling at any time during the extension period should changes in economic conditions warrant. Regulatory Procedures Administrative Procedure Act The Board has determined that notification and public comment on this rule are impractical and not in the public interest. 5 U.S.C. 553(b)(3)(B). Due to the need for a planning period before the March 9, 2005 expiration date of the current rule, and the threat to the safety and soundness of individual credit unions with insufficient flexibility to determine loan rates, final action on the loan rate ceiling is necessary. Regulatory Flexibility Act The Regulatory Flexibility Act requires NCUA to prepare an analysis to describe any significant economic impact a regulation may have on a substantial number of small credit unions (those under ten million dollars in assets). This final rule provides added flexibility to all federal credit unions regarding the permissible interest rate that may be used in connection with lending. The NCUA Board has determined and certifies that this rule will not have a significant economic impact on a substantial number of small credit unions. Small Business Regulatory Enforcement Fairness Act The Small Business Regulatory Enforcement Fairness Act of 1996 (Pub. L. 104–121) provides generally for congressional review of agency rules. A reporting requirement is triggered in instances where NCUA issues a final rule as defined by Section 551 of the Administrative Procedure Act. 5 U.S.C. 551. The Office of Management and Budget has determined that this is not a major rule. The Treasury and General Government Appropriations Act, 1999—Assessment of Federal Regulations and Policies on Families NCUA has determined that this rule will not affect family well-being within the meaning of Section 654 of the Treasury and General Government Appropriations Act, 1999, Pub. L. 105– 277, 112 Stat. 2681 (1998). List of Subjects in 12 CFR Part 701 Credit, Credit unions, Loan interest rates. By the National Credit Union Administration Board on January 13, 2005. Mary F. Rupp, Secretary to the Board. Accordingly, NCUA amends 12 CFR chapter VII as follows: I PART 701—ORGANIZATION AND OPERATION OF FEDERAL CREDIT UNIONS (AMENDED) 1. The authority citation for Part 701 continues to read as follows: NCUA has determined that this rule does not increase paperwork requirements under the Paperwork Reduction Act of 1995 and regulations 19:04 Jan 26, 2005 Executive Order 13132 Executive Order 13132 encourages independent regulatory agencies to consider the impact of their regulatory actions on state and local interest. In adherence to fundamental federalism principles, NCUA, an independent regulatory agency as defined in 44 U.S.C. 3502(5), voluntarily complies with the executive order. This rule applies only to federal credit unions and, thus, will not have substantial direct effects on the states, on the relationship between the national government and the states, nor materially affect state interests. The NCUA has determined that the rule does not constitute a policy that has any federalism implication for purposes of the executive order. I Paperwork Reduction Act VerDate jul<14>2003 of the Office of Management and Budget. Jkt 205001 Authority: 12 U.S.C. 1752(5), 1755, 1756, 1757, 1759, 1761a, 1761b, 1766, 1767, 1782, 1784, 1787, and 1789. Section 701.6 is also authorized by 15 U.S.C. 3717. Section 701.31 PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 3863 is also authorized by 15 U.S.C. 1601 et seq., 42 U.S.C. 1981 and 3601–3610. Section 701.35 is also authorized by 42 U.S.C. 4311– 4312. 2. Section 701.21(c)(7)(ii)(C) is revised to read as follows: I § 701.21 Loans to members and lines of credit to members. * * * * * (c) * * * (7) * * * (ii) * * * (C) Expiration. After September 8, 2006, or as otherwise ordered by the NCUA Board, the maximum rate on federal credit union extensions of credit to members shall revert to 15 percent per year. Higher rates may, however, be charged, in accordance with paragraph (c)(7)(ii)(A) and (B) of this section, on loans and line of credit balance existing on or before September 8, 2006. * * * * * [FR Doc. 05–1166 Filed 1–26–05; 8:45 am] BILLING CODE 7535–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. 2000–NE–13–AD; Amendment 39–13950; AD 2005–02–05] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce plc RB211 Series Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: SUMMARY: The FAA is superseding an existing airworthiness directive (AD) for Rolls-Royce (RR) plc RB211–535E4–37, RB211–535E4–B–37, and RB211– 535E4–B–75 series turbofan engines. That AD currently requires initial and repetitive ultrasonic inspections of installed LPC fan blade roots on-wing and during overhaul using a surface wave ultrasonic probe, and relubrication, according to accumulated life cycles. That AD also adds the application of Metco 58 blade root coating as an optional terminating action. This AD requires the same actions, but changes the reference to Mandatory Service Bulletin (MSB) No. RB.211–72–C879 from Revision 3 to Revision 4. This AD results from RR issuing MSB No. RB.211–72–C879, Revision 4, which contains revised Accomplishment Instructions and consumable materials list. We are E:\FR\FM\27JAR1.SGM 27JAR1 3864 Federal Register / Vol. 70, No. 17 / Thursday, January 27, 2005 / Rules and Regulations issuing this AD to detect cracks in low pressure compressor (LPC) fan blade roots, which if not detected, could lead to uncontained multiple fan blade failure, and damage to the airplane. DATES: Effective February 11, 2005. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of February 11, 2005. We must receive any comments on this AD by March 28, 2005. ADDRESSES: Use one of the following addresses to submit comments on this AD: • By mail: Federal Aviation Administration (FAA), New England Region, Office of the Regional Counsel, Attention: Rules Docket No. 2000–NE– 13–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 referenced in this AD from Rolls-Royce plc, PO Box 31, Derby, England, DE248BJ; telephone: 011–44–1332–242– 424; fax: 011–44–1332–249–936. 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: On June 13, 2003, we issued AD 2003–12–15, Amendment 39–13200 (68 FR 37735, June 25, 2003). That AD requires initial and repetitive ultrasonic inspections of installed LPC fan blade roots on-wing and during overhaul using a surface wave ultrasonic probe, and relubrication, according to accumulated life cycles. That AD also introduces an alternative technique to ultrasonically inspect installed fan blades on-wing using a surface wave ultrasonic probe. Also, that AD adds the application of Metco 58 blade root coating as an optional terminating action. That AD was the result of the discovery of cracks on LPC fan blade roots during an engine overhaul. That condition, if not corrected, could result in uncontained multiple fan blade failure, and damage to the airplane. Actions Since AD 2003–12–15 Was Issued Since AD 2003–12–15 was issued, the Civil Aviation Authority (CAA), which VerDate jul<14>2003 19:04 Jan 26, 2005 Jkt 205001 is the airworthiness authority for the United Kingdom (UK), notified us that Rolls-Royce plc has updated MSB No. RB.211–72–C879, Revision 3, dated October 3, 2002, to Revision 4, dated April 2, 2004, for RR RB211 series turbofan engines. The CAA advises that Revision 4 of the MSB contains revised Accomplishment Instructions and consumable materials list. Special Flight Permits Paragraph Removed Paragraph (h) of the current AD, AD 2003–12–15, contains a paragraph pertaining to special flight permits. Even though this final rule does not contain a similar paragraph, we have made no changes with regard to the use of special flight permits to operate the airplane to a repair facility to do the work required by this AD. In July 2002, we published a new part 39 that contains a general authority regarding special flight permits and airworthiness directives; see Docket No. FAA–2004– 8460, Amendment 39–9474 (69 FR 47998, July 22, 2002). Thus, when we now supersede ADs we will not include a specific paragraph on special flight permits unless we want to limit the use of that general authority granted in section 39.23. Relevant Service Information We have reviewed and approved the technical contents of RR MSB No. RB.211–72–C879, Revision 4, dated April 2, 2004. That MSB describes procedures for ultrasonic inspection of high cyclic life blades on-wing with either the LPC fan blades in place or removed from the LPC. The CAA classified the original issue of the service bulletin as mandatory and issued AD 002–01–2000 in order to ensure the airworthiness of these RR engines in the UK. Bilateral Airworthiness Agreement These engine models are manufactured in the U.K. and are 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. PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 FAA’s Determination and Requirements of This 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 issuing this AD, which requires initial and repetitive ultrasonic inspection of installed LPC fan blade roots on-wing and during overhaul using a surface wave ultrasonic probe, and relubrication, according to accumulated life cycles. This AD also maintains the application of Metco 58 blade root coating as an optional terminating action. You must use the service information described previously to perform the actions required by this AD. FAA’s Determination of the Effective Date Since an unsafe condition exists that requires the immediate adoption of this AD, we have found that notice and opportunity for public comment before issuing this AD are unnecessary, and that good cause exists for making this amendment effective in less than 30 days. Comments Invited This AD is a final rule that involves requirements affecting flight safety and was not preceded by notice and an opportunity for public comment; however, we invite you to submit any written relevant data, views, or arguments regarding this AD. Send your comments to an address listed under ADDRESSES. Include ‘‘AD Docket No. 2000–NE–13–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 rule that might suggest a need to modify it. If a person contacts us verbally, and that contact relates to a substantive part of this 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 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. E:\FR\FM\27JAR1.SGM 27JAR1 Federal Register / Vol. 70, No. 17 / Thursday, January 27, 2005 / Rules and Regulations Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in subtitle VII, part A, subpart III, section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the National Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. 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 by sending a request to us at the address listed under ADDRESSES. Include ‘‘AD Docket No. 2000–NE–13– AD’’ in your request. 3865 installed on, but not limited to, Boeing 757 and Tupolev Tu204 series airplanes. Table 1 follows: TABLE 1.—APPLICABLE LPC FAN BLADE P/NS List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. UL16135 UL16171 UL16182 UL19643 UL20044 UL20132 UL20616 UL21345 UL22286 UL23122 UL24525 UL24528 UL24530 UL24532 UL24534 UL27992 UL28601 Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I UL28602 UL29511 UL29556 UL30817 UL30819 UL30933 UL30935 UL33707 UL33709 UL36992 UL37090 UL37272 UL37274 UL37276 UL37278 UL38029 UL38032 Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 Unsafe Condition [Amended] 2. The FAA amends § 39.13 by removing Amendment 39–13200 (68 FR 37735, June 25, 2003), and by adding a new airworthiness directive, Amendment 39–13950, to read as follows: I Rolls-Royce plc: Amendment 39–13950. Docket No. 2000–NE–13–AD. Supersedes AD 2003–12–15, Amendment 39–13200. 2005–02–05 Effective Date (a) This airworthiness directive (AD) becomes effective February 11, 2005. Affected ADs (b) This AD supersedes AD 2003–12–15, Amendment 39–13200. Applicability (c) This AD applies to Rolls-Royce (RR) plc RB211–535E4–37, RB211–535E4–B–37, and RB211–535E4–B–75 series turbofan engines with low pressure compressor (LPC) fan blades with the part numbers (P/Ns) listed in Table 1 of this AD. These engines are (d) This AD results from RR issuing Mandatory Service Bulletin (MSB) No. RB.211–72–C879, Revision 4, which contains revised Accomplishment Instructions and consumable materials list. We are issuing this AD to detect cracks in low pressure compressor (LPC) fan blade roots, which if not detected, could lead to uncontained multiple fan blade 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. (f) If you have a full set of fan blades, modified using RR Service Bulletin No. RB.211–72–C946, Revision 2, dated September 26, 2002, that can be identified by a blue triangle etched on the blade airfoil suction surface close to the leading edge tip of each blade, no further action is required. (g) On RB211–535E4 engines, operated to Flight Profile A, ultrasonically inspect, and if required, relubricate using the following Table 2: TABLE 2.—RB211–535E4 FLIGHT PROFILE A Engine location (1) On-wing ......... (2) In Shop .......... Initial inspection within cycles-since-new (CSN) 17,350 17,350 Type action In accordance with (i) Root Probe, inspect and relubricate, OR (ii) Wave Probe .................. RB.211–72–C879 Revision 4, 3.A.(1) through 3.A.(7), dated April 2, 2004. RB.211–72–C879 Revision 4, 3.B.(1) through 3.B.(7), dated April 2, 2004. RB.211–72–C879 Revision 4, 3.C.(1) through 3.C.(4), dated April 2, 2004. Root Probe, inspect and relubricate. (h) On RB211–535E4 engines, operated to Flight Profile B, ultrasonically inspect, and if VerDate jul<14>2003 19:04 Jan 26, 2005 Jkt 205001 required, relubricate using the following Table 3: PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 E:\FR\FM\27JAR1.SGM 27JAR1 Repeat inspection within (CSN) 1,400 1,150 1,400 3866 Federal Register / Vol. 70, No. 17 / Thursday, January 27, 2005 / Rules and Regulations TABLE 3.—RB211–535E4 FLIGHT PROFILE B Engine location (1) On-wing ......... (2) In Shop .......... Initial inspection within (CSN) 12,350 12,350 Repeat inspection within (CSN) Type action In accordance with (i) Root Probe, inspect and relubricate, OR (ii) Wave Probe .................. RB.211–72–C879 Revision 4, 3.A.(1) through 3.A.(7), dated April 2, 2004. RB.211–72–C879 Revision 4, 3.B.(1) through 3.B.(7), dated April 2, 2004. RB.211–72–C879 Revision 4, 3.C.(1) through 3.C.(4), dated April 2, 2004. Root Probe, inspect and relubricate. (i) On RB211–535E4 engines, operated to combined Flight Profile A and B, 850 700 850 ultrasonically inspect, and if required, relubricate using the following Table 4: TABLE 4.—RB211–535E4 FLIGHT PROFILE A AND B Engine location (1) On-wing ......... (2) In Shop .......... Initial inspection within (CSN) Type action Repeat inspection within (CSN) In accordance with 65% hard life (To calculate, see Compliance Section 1.C(4)). ...................... (i) Root Probe, inspect and relubricate, OR RB.211–72–C879 Revision 4, 3.A.(7), dated April 2, 2004. 3.A.(1) through As current flight profile. (ii) Wave Probe ................ 3.B.(1) through 65% hard life (To calculate, see Compliance Section 1.C.(4)). Root Probe, inspect and relubricate. RB.211–72–C879 Revision 4, 3.B.(7), dated April 2, 2004. RB.211–72–C879 Revision 4, 3.C.(4), dated April 2, 2004. 3.C.(1) through As current flight profile. As current flight profile. (j) Fan blades that have been operated within RB211–535E4 Flight Profile A and B will have final life as defined in the Time Limits Manual. See References Section 1.G.(3), of MSB RB.211–72–C879, Revision 4, dated April 2, 2004. (k) On RB211–535E4–B engines, ultrasonically inspect, and if required, relubricate using the following Table 5: TABLE 5.—RB211–535E4–B Engine location (1) On-wing ......... (2) In Shop .......... Initial inspection within (CSN) 17,000 17,000 Type action In accordance with (i) Root Probe, inspect and relubricate, OR (ii) Wave Probe. ................. RB.211–72–C879 Revision 4, 3.A.(1) through 3.A.(7), dated April 2, 2004. RB.211–72–C879 Revision 4, 3.B.(1) through 3.B.(7), dated April 2, 2004. RB.211–72–C879 Revision 4, 3.C.(1) through 3.C.(4), dated April 2, 2004. Root Probe, inspect and relubricate.. Optional Terminating Action (l) Application of Metco 58 blade root coating using RR SB No. RB.211–72–C946, Revision 2, dated September 26, 2002, constitutes terminating action to the repetitive inspection requirements specified in paragraphs (g), (h), (i), and (k) of this AD. Alternative Methods of Compliance (m) 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 (n) Previous credit is allowed for initial and repetitive inspections performed using VerDate jul<14>2003 19:12 Jan 26, 2005 Jkt 205001 AD 2003–12–15 (Amendment 39–13200, 68 FR 37735, June 25, 2003) and RR MSB No. RB.211–72–C879, Revision 3, dated October 9, 2002. Repeat inspection within (CSN) 1,200 1,000 1,200 Material Incorporated by Reference (o) You must use Rolls-Royce Mandatory Service Bulletin No. RB.211–72–C879, Revision 4, dated April 2, 2004, to perform the inspections and relubrication required by this AD. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. You can get a copy from Rolls-Royce plc, PO Box 31, Derby, England, DE248BJ; telephone: 011– 44–1332–242–424; fax: 011–44–1332–249– 936. You may review copies at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA; or on the Internet at https://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741– 6030, or go to: https://www.archives.gov/ federal_register/code_of_federal_regulations/ ibr_locations.html. Related Information PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 (p) CAA airworthiness directive AD 002– 01–2000, dated October 9, 2002, also addresses the subject of this AD. E:\FR\FM\27JAR1.SGM 27JAR1 Federal Register / Vol. 70, No. 17 / Thursday, January 27, 2005 / Rules and Regulations Issued in Burlington, Massachusetts, on January 18, 2005. Jay J. Pardee, Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 05–1384 Filed 1–26–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. 98–ANE–80–AD; Amendment 39–13948; AD 2005–02–03] RIN 2120–AA64 Airworthiness Directives; Pratt & Whitney JT8D–209, –217, –217A, –217C, and –219 Series Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: SUMMARY: The FAA is superseding an existing airworthiness directive (AD) for Pratt & Whitney (PW) JT8D–209, –217, –217A, –217C, and –219 series turbofan engines. That AD currently requires torque inspection of the 3rd stage and 4th stage low pressure turbine (LPT) blades for shroud notch wear and replacement of the blade if wear limits are exceeded. This AD continues to require those torque inspections at shorter inspection intervals of the refurbished 3rd stage and 4th stage LPT blades, but the same or longer inspection intervals of the new 3rd stage and 4th stage LPT blades, for shroud notch wear and replacement of the blade if wear limits are exceeded. This AD also requires replacing LPT-toexhaust case bolts and nuts with bolts and nuts made of Tinidur material. This AD results from reports of 194 blade fractures since 1991, with 37 of those blade fractures resulting in LPT case separation, and three reports of uncontained 3rd stage and 4th stage LPT blade failures with cowl penetration. We are issuing this AD to prevent an uncontained blade failure that could result in damage to the airplane. DATES: This AD becomes effective March 3, 2005. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of March 3, 2005. ADDRESSES: You can get the service information identified in this AD from Pratt & Whitney, 400 Main St., East Hartford, CT 06108; telephone (860) 565–8770, fax (860) 565–4503. VerDate jul<14>2003 19:04 Jan 26, 2005 Jkt 205001 You may examine the AD docket at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA. You may examine the service information, at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https://www.archives.gov/ federal_register/ code_of_federal_regulations/ ibr_locations.html. FOR FURTHER INFORMATION CONTACT: Keith Lardie, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803–5299; telephone (781) 238–7189, 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 Pratt & Whitney (PW) JT8D–209, –217, –217A, –217C, and -219 series turbofan engines. We published the proposed AD in the Federal Register on August 16, 2004 (69 FR 50346). That action proposed to require torque inspections of the 3rd stage and 4th stage LPT blades for shroud notch wear and replacement of the blade if wear limits are exceeded. That action also proposed to require replacing the LPT-to-exhaust case bolts and nuts with bolts and nuts made of Tinidur material. 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. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments received. Use of Radioisotope Inspection Procedure One commenter proposes to use a radioisotope inspection procedure, which they have developed and was approved as an alternative method of compliance (AMOC) for a previously issued AD. The commenter states that this inspection method is more reliable than the torque inspections mandated in this AD and provides an equivalent level of safety. The FAA does not agree. The commenter did not provide data to PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 3867 substantiate the claim of an equivalent level of safety as it relates to the revised inspection intervals. The commenter’s proposal is also operator-specific and does not provide literature for the rest of the fleet. The FAA will evaluate a request for an AMOC that includes data substantiating that an acceptable level of safety is maintained using this procedure. Costs of Compliance Underestimated Another commenter states that the costs of compliance are underestimated. The commenter requests that we consider the costs of numerous parts removed when complying with this AD. The FAA does not agree. The indirect costs associated with this AD are not directly related to the required actions, and therefore, are not addressed in the economic analysis for this AD. A finding that an AD is warranted means that the original engine design no longer achieves the level of safety specified by related airworthiness requirements and that other required actions are necessary. Another commenter states that the costs of compliance are underestimated. The commenter states that the cost of turbine blades and cost of labor to replace the blades when complying with this AD should be considered. The FAA agrees. We estimate that 10% of the blade sets will fail the inspection per year and will require replacement. Therefore, the estimated cost of turbine blades and labor to replace the blades is added to the total cost of the AD to U.S. operators to perform initial torque inspection and bolt and nut replacement. Request To Clearly Identify the Superseded AD Another commenter requests that the identification of the superseded AD be clarified. The FAA does not agree. The fact that this AD supersedes AD 99–27– 01 is clearly stated in the compliance section of this AD. Although AD 99–22– 14 requires replacement of the LPT-toexhaust case bolts and nuts, that AD primarily addresses installation of high pressure turbine (HPT) containment hardware. Further, a notice of proposed rulemaking was published in the Federal Register on July 15, 2004 (69 FR 42356), which moves the requirement to replace the LPT-to-exhaust case bolts and nuts from AD 99–22–14 to this AD. Request To Include Reference to NDIP– 662, Revision D Another commenter requests that this AD include a reference to NDIP–622, Revision D. The FAA does not agree. We assume that the commenter intended to E:\FR\FM\27JAR1.SGM 27JAR1

Agencies

[Federal Register Volume 70, Number 17 (Thursday, January 27, 2005)]
[Rules and Regulations]
[Pages 3863-3867]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-1384]

=======================================================================
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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NE-13-AD; Amendment 39-13950; AD 2005-02-05]
RIN 2120-AA64

Airworthiness Directives; Rolls-Royce plc RB211 Series Turbofan
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: The FAA is superseding an existing airworthiness directive
(AD) for Rolls-Royce (RR) plc RB211-535E4-37, RB211-535E4-B-37, and
RB211-535E4-B-75 series turbofan engines. That AD currently requires
initial and repetitive ultrasonic inspections of installed LPC fan
blade roots on-wing and during overhaul using a surface wave ultrasonic
probe, and relubrication, according to accumulated life cycles. That AD
also adds the application of Metco 58 blade root coating as an optional
terminating action. This AD requires the same actions, but changes the
reference to Mandatory Service Bulletin (MSB) No. RB.211-72-C879 from
Revision 3 to Revision 4. This AD results from RR issuing MSB No.
RB.211-72-C879, Revision 4, which contains revised Accomplishment
Instructions and consumable materials list. We are

[[Page 3864]]

issuing this AD to detect cracks in low pressure compressor (LPC) fan
blade roots, which if not detected, could lead to uncontained multiple
fan blade failure, and damage to the airplane.

DATES: Effective February 11, 2005. The Director of the Federal
Register approved the incorporation by reference of certain
publications listed in the regulations as of February 11, 2005.
We must receive any comments on this AD by March 28, 2005.

ADDRESSES: Use one of the following addresses to submit comments on
this AD:
By mail: Federal Aviation Administration (FAA), New
England Region, Office of the Regional Counsel, Attention: Rules Docket
No. 2000-NE-13-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 referenced in this AD from
Rolls-Royce plc, PO Box 31, Derby, England, DE248BJ; telephone: 011-44-
1332-242-424; fax: 011-44-1332-249-936.
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: On June 13, 2003, we issued AD 2003-12-15,
Amendment 39-13200 (68 FR 37735, June 25, 2003). That AD requires
initial and repetitive ultrasonic inspections of installed LPC fan
blade roots on-wing and during overhaul using a surface wave ultrasonic
probe, and relubrication, according to accumulated life cycles. That AD
also introduces an alternative technique to ultrasonically inspect
installed fan blades on-wing using a surface wave ultrasonic probe.
Also, that AD adds the application of Metco 58 blade root coating as an
optional terminating action. That AD was the result of the discovery of
cracks on LPC fan blade roots during an engine overhaul. That
condition, if not corrected, could result in uncontained multiple fan
blade failure, and damage to the airplane.

Actions Since AD 2003-12-15 Was Issued

Since AD 2003-12-15 was issued, the Civil Aviation Authority (CAA),
which is the airworthiness authority for the United Kingdom (UK),
notified us that Rolls-Royce plc has updated MSB No. RB.211-72-C879,
Revision 3, dated October 3, 2002, to Revision 4, dated April 2, 2004,
for RR RB211 series turbofan engines. The CAA advises that Revision 4
of the MSB contains revised Accomplishment Instructions and consumable
materials list.

Special Flight Permits Paragraph Removed

Paragraph (h) of the current AD, AD 2003-12-15, contains a
paragraph pertaining to special flight permits. Even though this final
rule does not contain a similar paragraph, we have made no changes with
regard to the use of special flight permits to operate the airplane to
a repair facility to do the work required by this AD. In July 2002, we
published a new part 39 that contains a general authority regarding
special flight permits and airworthiness directives; see Docket No.
FAA-2004-8460, Amendment 39-9474 (69 FR 47998, July 22, 2002). Thus,
when we now supersede ADs we will not include a specific paragraph on
special flight permits unless we want to limit the use of that general
authority granted in section 39.23.

Relevant Service Information

We have reviewed and approved the technical contents of RR MSB No.
RB.211-72-C879, Revision 4, dated April 2, 2004. That MSB describes
procedures for ultrasonic inspection of high cyclic life blades on-wing
with either the LPC fan blades in place or removed from the LPC. The
CAA classified the original issue of the service bulletin as mandatory
and issued AD 002-01-2000 in order to ensure the airworthiness of these
RR engines in the UK.

Bilateral Airworthiness Agreement

These engine models are manufactured in the U.K. and are 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.

FAA's Determination and Requirements of This 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 issuing this AD, which
requires initial and repetitive ultrasonic inspection of installed LPC
fan blade roots on-wing and during overhaul using a surface wave
ultrasonic probe, and relubrication, according to accumulated life
cycles. This AD also maintains the application of Metco 58 blade root
coating as an optional terminating action. You must use the service
information described previously to perform the actions required by
this AD.

FAA's Determination of the Effective Date

Since an unsafe condition exists that requires the immediate
adoption of this AD, we have found that notice and opportunity for
public comment before issuing this AD are unnecessary, and that good
cause exists for making this amendment effective in less than 30 days.

Comments Invited

This AD is a final rule that involves requirements affecting flight
safety and was not preceded by notice and an opportunity for public
comment; however, we invite you to submit any written relevant data,
views, or arguments regarding this AD. Send your comments to an address
listed under ADDRESSES. Include ``AD Docket No. 2000-NE-13-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 rule
that might suggest a need to modify it. If a person contacts us
verbally, and that contact relates to a substantive part of this 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 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.

[[Page 3865]]

Authority for This Rulemaking

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

Regulatory Findings

We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the National Government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
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 by
sending a request to us at the address listed under ADDRESSES. Include
``AD Docket No. 2000-NE-13-AD'' in your request.

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 part 39 of the Federal
Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

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

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

Sec. 39.13 [Amended]

0
2. The FAA amends Sec. 39.13 by removing Amendment 39-13200 (68 FR
37735, June 25, 2003), and by adding a new airworthiness directive,
Amendment 39-13950, to read as follows:

2005-02-05 Rolls-Royce plc: Amendment 39-13950. Docket No. 2000-NE-
13-AD. Supersedes AD 2003-12-15, Amendment 39-13200.

Effective Date

(a) This airworthiness directive (AD) becomes effective February
11, 2005.

Affected ADs

(b) This AD supersedes AD 2003-12-15, Amendment 39-13200.

Applicability

(c) This AD applies to Rolls-Royce (RR) plc RB211-535E4-37,
RB211-535E4-B-37, and RB211-535E4-B-75 series turbofan engines with
low pressure compressor (LPC) fan blades with the part numbers (P/
Ns) listed in Table 1 of this AD. These engines are installed on,
but not limited to, Boeing 757 and Tupolev Tu204 series airplanes.
Table 1 follows:

Table 1.--Applicable LPC Fan Blade P/Ns
------------------------------------------------------------------------

------------------------------------------------------------------------
UL16135 UL28602
UL16171 UL29511
UL16182 UL29556
UL19643 UL30817
UL20044 UL30819
UL20132 UL30933
UL20616 UL30935
UL21345 UL33707
UL22286 UL33709
UL23122 UL36992
UL24525 UL37090
UL24528 UL37272
UL24530 UL37274
UL24532 UL37276
UL24534 UL37278
UL27992 UL38029
UL28601 UL38032
------------------------------------------------------------------------

Unsafe Condition

(d) This AD results from RR issuing Mandatory Service Bulletin
(MSB) No. RB.211-72-C879, Revision 4, which contains revised
Accomplishment Instructions and consumable materials list. We are
issuing this AD to detect cracks in low pressure compressor (LPC)
fan blade roots, which if not detected, could lead to uncontained
multiple fan blade 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.
(f) If you have a full set of fan blades, modified using RR
Service Bulletin No. RB.211-72-C946, Revision 2, dated September 26,
2002, that can be identified by a blue triangle etched on the blade
airfoil suction surface close to the leading edge tip of each blade,
no further action is required.
(g) On RB211-535E4 engines, operated to Flight Profile A,
ultrasonically inspect, and if required, relubricate using the
following Table 2:

Table 2.--RB211-535E4 Flight Profile A
----------------------------------------------------------------------------------------------------------------
Initial
inspection
Engine location within cycles- Type action In accordance with Repeat inspection
since-new within (CSN)
(CSN)
----------------------------------------------------------------------------------------------------------------
(1) On-wing................ 17,350 (i) Root Probe, RB.211-72-C879 Revision 1,400
inspect and 4, 3.A.(1) through
relubricate, OR 3.A.(7), dated April 2,
2004.
.............. (ii) Wave Probe...... RB.211-72-C879 Revision 1,150
4, 3.B.(1) through
3.B.(7), dated April 2,
2004.
(2) In Shop................ 17,350 Root Probe, inspect RB.211-72-C879 Revision 1,400
and relubricate. 4, 3.C.(1) through
3.C.(4), dated April 2,
2004.
----------------------------------------------------------------------------------------------------------------

(h) On RB211-535E4 engines, operated to Flight Profile B,
ultrasonically inspect, and if required, relubricate using the
following Table 3:

[[Page 3866]]

Table 3.--RB211-535E4 Flight Profile B
----------------------------------------------------------------------------------------------------------------
Initial
Engine location inspection Type action In accordance with Repeat inspection
within (CSN) within (CSN)
----------------------------------------------------------------------------------------------------------------
(1) On-wing................ 12,350 (i) Root Probe, RB.211-72-C879 Revision 850
inspect and 4, 3.A.(1) through
relubricate, OR 3.A.(7), dated April 2,
2004.
.............. (ii) Wave Probe...... RB.211-72-C879 Revision 700
4, 3.B.(1) through
3.B.(7), dated April 2,
2004.
(2) In Shop................ 12,350 Root Probe, inspect RB.211-72-C879 Revision 850
and relubricate. 4, 3.C.(1) through
3.C.(4), dated April 2,
2004.
----------------------------------------------------------------------------------------------------------------

(i) On RB211-535E4 engines, operated to combined Flight Profile
A and B, ultrasonically inspect, and if required, relubricate using
the following Table 4:

Table 4.--RB211-535E4 Flight Profile A and B
----------------------------------------------------------------------------------------------------------------
Initial inspection Repeat inspection within
Engine location within (CSN) Type action In accordance with (CSN)
----------------------------------------------------------------------------------------------------------------
(1) On-wing........... 65% hard life (To (i) Root Probe, RB.211-72-C879 As current flight
calculate, see inspect and Revision 4, 3.A.(1) profile.
Compliance Section relubricate, OR through 3.A.(7),
1.C(4)). dated April 2, 2004.
..................... (ii) Wave Probe. RB.211-72-C879 As current flight
Revision 4, 3.B.(1) profile.
through 3.B.(7),
dated April 2, 2004.
(2) In Shop........... 65% hard life (To Root Probe, RB.211-72-C879 As current flight
calculate, see inspect and Revision 4, 3.C.(1) profile.
Compliance Section relubricate. through 3.C.(4),
1.C.(4)). dated April 2, 2004.
----------------------------------------------------------------------------------------------------------------

(j) Fan blades that have been operated within RB211-535E4 Flight
Profile A and B will have final life as defined in the Time Limits
Manual. See References Section 1.G.(3), of MSB RB.211-72-C879,
Revision 4, dated April 2, 2004.
(k) On RB211-535E4-B engines, ultrasonically inspect, and if
required, relubricate using the following Table 5:

Table 5.--RB211-535E4-B
----------------------------------------------------------------------------------------------------------------
Initial
Engine location inspection Type action In accordance with Repeat inspection
within (CSN) within (CSN)
----------------------------------------------------------------------------------------------------------------
(1) On-wing................ 17,000 (i) Root Probe, RB.211-72-C879 Revision 1,200
inspect and 4, 3.A.(1) through
relubricate, OR 3.A.(7), dated April 2,
2004.
.............. (ii) Wave Probe...... RB.211-72-C879 Revision 1,000
4, 3.B.(1) through
3.B.(7), dated April 2,
2004.
(2) In Shop................ 17,000 Root Probe, inspect RB.211-72-C879 Revision 1,200
and relubricate.. 4, 3.C.(1) through
3.C.(4), dated April 2,
2004.
----------------------------------------------------------------------------------------------------------------

Optional Terminating Action

(l) Application of Metco 58 blade root coating using RR SB No.
RB.211-72-C946, Revision 2, dated September 26, 2002, constitutes
terminating action to the repetitive inspection requirements
specified in paragraphs (g), (h), (i), and (k) of this AD.

Alternative Methods of Compliance

(m) 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

(n) Previous credit is allowed for initial and repetitive
inspections performed using AD 2003-12-15 (Amendment 39-13200, 68 FR
37735, June 25, 2003) and RR MSB No. RB.211-72-C879, Revision 3,
dated October 9, 2002.

Material Incorporated by Reference

(o) You must use Rolls-Royce Mandatory Service Bulletin No.
RB.211-72-C879, Revision 4, dated April 2, 2004, to perform the
inspections and relubrication required by this AD. The Director of
the Federal Register approved the incorporation by reference of this
service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part
51. You can get a copy from Rolls-Royce plc, PO Box 31, Derby,
England, DE248BJ; telephone: 011-44-1332-242-424; fax: 011-44-1332-
249-936. You may review copies at the FAA, New England Region,
Office of the Regional Counsel, 12 New England Executive Park,
Burlington, MA; or on the Internet at https://dms.dot.gov; or at the
National Archives and Records Administration (NARA). For information
on the availability of this material at NARA, call (202) 741-6030,
or go to: https://www.archives.gov/federal_register/code_of_
federal_regulations/ibr_locations.html.

Related Information

(p) CAA airworthiness directive AD 002-01-2000, dated October 9,
2002, also addresses the subject of this AD.

[[Page 3867]]

Issued in Burlington, Massachusetts, on January 18, 2005.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 05-1384 Filed 1-26-05; 8:45 am]
BILLING CODE 4910-13-P

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