Airworthiness Directives; Rolls-Royce plc RB211-524 Series Turbofan Engines, 12060-12064 [E7-4536]

Download as PDF 12060 Federal Register / Vol. 72, No. 50 / Thursday, March 15, 2007 / Rules and Regulations M. Congressional Notification As required by 5 U.S.C. 801, DOE will submit to Congress a report regarding the issuance of today’s Final Rule prior to the effective date set forth at the outset of this Final Rule. The report will state that it has been determined that the rule is not a ‘‘major rule’’ as defined by 5 U.S.C. 801(2). Act (42 U.S.C. 13254(b)) is to achieve a production capacity of replacement fuels sufficient to replace, on an energy equivalent basis, at least 30 percent of motor fuel consumption in the United States by the year 2030. [FR Doc. E7–4324 Filed 3–14–07; 8:45 am] BILLING CODE 6450–01–P VIII. Approval by the Office of the Secretary DEPARTMENT OF TRANSPORTATION The issuance of this Final Rule for the Replacement Fuel Goal modification has been approved by the Office of the Secretary. Federal Aviation Administration List of Subjects in 10 CFR Part 490 Administrative practice and procedure, Energy conservation, Fuel economy, Gasoline, Motor vehicles, Natural gas, Penalties, Petroleum, Reporting, and recordkeeping requirements. Airworthiness Directives; Rolls-Royce plc RB211–524 Series Turbofan Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: For the reasons set forth in the Preamble, the Department of Energy is amending Chapter II of title 10 of the Code of Federal Regulations as set forth below: I PART 490—ALTERNATIVE FUEL TRANSPORTATION PROGRAM 1. The authority citation for part 490 is revised to read as follows: I Authority: 42 U.S.C. 7191 et seq.; 42 U.S.C. 13201, 13211, 13220, 13251 et seq. 2. In § 490.1 of subpart A, paragraph (b) is revised to read as follows: I Purpose and Scope. * * * * * (b) The provisions of this subpart cover: (1) The definitions applicable throughout this part; (2) Procedures to obtain an interpretive ruling and to petition for a generally applicable rule to amend this part; and (3) The goal of the replacement fuel supply and demand program established under section 502(a) of the Act (42 U.S.C. 13252(a)). I 3. Subpart A is amended by adding § 490.8 to read as follows: rmajette on PROD1PC67 with RULES § 490.8 Replacement fuel production goal. The goal of the replacement fuel supply and demand program established by section 502(b)(2) of the Act (42 U.S.C. 13252(b)(2)) and revised by DOE pursuant to section 504(b) of the VerDate Aug<31>2005 14:08 Mar 14, 2007 Jkt 211001 [Docket No. FAA–2007–27267; Directorate Identifier 2002–NE–40–AD; Amendment 39– 14991; AD 2007–06–10] RIN 2120–AA64 Issued in Washington, DC, on March 6, 2007. Alexander A. Karsner, Assistant Secretary, Energy Efficiency and Renewable Energy. § 490.1 14 CFR Part 39 SUMMARY: The FAA is superseding an existing airworthiness directive (AD) for Rolls Royce plc (RR) RB211–524 series turbofan engines with certain part number (P/N) intermediate pressure compressor (IPC) stage 5 disks installed. That AD currently requires new reduced IPC stage 5 disk cyclic limits. This AD requires the same reduced IPC stage 5 disk cyclic limits, requires removal from service of affected disks that already exceed the new reduced cyclic limit, and, removal from service of other affected disks before exceeding their cyclic limits using a drawdown schedule. This AD also exempts disks reworked to RR Service Bulletin (SB) No. RB.211–72–E182, Revision 1, dated July 30, 2004, and allows an on-wing eddy current inspection (ECI) on RB211–524G and RB211–524H series engines. This AD results from the manufacturer issuing a revised Alert Service Bulletin (ASB) to remove certain disks from applicability, and to allow an on-wing ECI on RB211–524G and RB211–524H series engines. We are issuing this AD to prevent failure of the IPC stage 5 disk, which could result in uncontained engine failure and possible damage to the airplane. DATES: This AD becomes effective April 19, 2007. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of April 19, 2007. ADDRESSES: You can get the service information identified in this AD from Rolls-Royce plc, P.O. Box 31 Derby, PO 00000 Frm 00030 Fmt 4700 Sfmt 4700 DE248BJ, United Kingdom; telephone 011–44–1332–242424; fax 011–44– 1332–249936. 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; e-mail: ian.dargin@faa.gov. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 with a proposed AD. The proposed AD applies to RR RB211–524 series turbofan engines with certain P/N IPC stage 5 disks installed. We published the proposed AD in the Federal Register on July 11, 2006 (71 FR 39025). That action proposed to require: • Establishing new reduced IPC stage 5 disk cyclic limits. • Removing from service affected disks that already exceed the new reduced cyclic limit. • Removing from service other affected disks before exceeding their cyclic limits, using a drawdown schedule. • Allowing optional inspections at each shop visit or an on-wing ECI to extend the disk life beyond the specified life. Examining the AD Docket You may examine the docket that contains the AD, any comments received, and any final disposition in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone (800) 647–5227) is located on the plaza level of the Department of Transportation Nassif Building at the street address stated in ADDRESSES. Comments will be available in the AD docket shortly after the DMS receives them. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments received. Request To Add a Note One commenter, Rolls-Royce plc, requests that we add a note, just above compliance paragraph (j)(5), that states: ‘‘To qualify for maximum alleviation since last NDT inspection (see Table 5 of this AD) it is recommended that discs be ECI inspected using paragraph 3.D. of the Accomplishment Instructions of RR E:\FR\FM\15MRR1.SGM 15MRR1 Federal Register / Vol. 72, No. 50 / Thursday, March 15, 2007 / Rules and Regulations Alert Service Bulletin No. RB.211–72– AD428, Revision 5, dated March 18, 2005.’’ The commenter feels that this note adds clarification to the AD compliance. We do not agree. The note is identified in the service bulletin that is incorporated by reference, and need not be included in the text of the AD. We did not change the AD. Request To Add Engine Series Rolls-Royce plc requests that we add the RB211–524B/B3 engine series to compliance paragraph (k)(1), and add the RB211–524H2 and RB211–524H2–T engine series to compliance paragraph (k)(2), as they need to be included, the same as they appear in the service bulletin. We agree and added those engine series to the paragraphs. Clarification of Paragraph (g) Since we issued the proposed AD, we reviewed the wording in paragraph (g) and realized that the compliance times in that paragraph were in conflict. We clarified that paragraph. It now states to comply with the reduced cyclic life limits in Table 3 of this AD within 30 days after the effective date of this AD, or conduct optional qualifying nondestructive test (NDT) inspections before December 1, 2008, to extend the IPC stage 5 disk life as specified in paragraph (i) of this AD. Conclusion We have carefully reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting the AD with the changes described previously. We have determined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD. 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–2007–27267. The old Docket No. became the Directorate Identifier, which is 2002– NE–40–AD. This AD might get logged into the DMS docket, ahead of the previously collected documents from the old docket file, as we are in the process of sending those items to the DMS. Costs of Compliance We estimate this AD will not affect any engines installed on airplanes of U.S. registry. Based on this, we estimate this AD will not have any cost to U.S. operators. 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 Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation Administration amends 14 CFR part 39 as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Amendment 39–14202 (70 FR 43036, July 26, 2005) and by adding a new airworthiness directive, Amendment 39–14991, to read as follows: I 2007–06–10 Rolls-Royce plc: Amendment 39–14991. Docket No. FAA–2007–27267; Directorate Identifier 2002–NE–40–AD. Effective Date (a) This airworthiness directive (AD) becomes effective April 19, 2007. Affected ADs (b) This AD supersedes AD 2005–15–13, Amendment 39–14202. Applicability (c) This AD applies to the Rolls-Royce plc (RR) RB211–524 series turbofan engines listed in the following Table 1, with intermediate pressure compressor (IPC) stage 5 disk part numbers (P/Ns) listed in Table 2 of this AD, installed. TABLE 1.—ENGINE MODELS AFFECTED rmajette on PROD1PC67 with RULES –524B–02 –524B2–19 –524D4–B–19 –524G2–19 –524H2–T–19 –524B–B–02 –524B2–B–19 –524D4X–19 –524G2–T–19 –524H–36 –524B3–02 –524C2–19 –524D4X–B–19 –524G3–19 –524H–T–36 –524B4–02 –524C2–B–19 –524D4–39 –524G3–T–19 –524B4–D–02 –524D4–19 –524D4–B–39 –524H2–19 These engines are installed on, but not limited to, Boeing 747, 767, and Lockheed L– 1011 series airplanes. VerDate Aug<31>2005 14:08 Mar 14, 2007 Jkt 211001 PO 00000 Frm 00031 Fmt 4700 Sfmt 4700 12061 E:\FR\FM\15MRR1.SGM 15MRR1 12062 Federal Register / Vol. 72, No. 50 / Thursday, March 15, 2007 / Rules and Regulations TABLE 2.—IPC STAGE 5 DISK P/NS AFFECTED LK60130 LK83283 UL19132 UL36821 UL36981 UL37080 LK65932 UL12290 UL20785 UL36977 UL36982 UL37081 LK69021 UL15743 UL20832 UL36978 UL36983 UL37082 Unsafe Condition (d) This AD results from the manufacturer issuing a revised Alert Service Bulletin (ASB) to remove certain disks from applicability and to allow an on-wing eddy current inspection (ECI) on RB211–524G and RB211– 524H series engines. The actions specified in this AD are intended to prevent failure of the IPC stage 5 disk, which could result in uncontained engine failure and possible damage to the airplane. LK81269 UL15744 UL23291 UL36979 UL37078 UL37083 LK83282 UL15745 UL25011 UL36980 UL37079 UL37084 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. dated July 30, 2004, no further action is necessary. Cycle Limits Exempted Disks (f) For engines with an IPC stage 5 disk P/ N listed in Table 2 of this AD, reworked to RR SB No. RB.211–72–E182, Revision 1, (g) Comply with the reduced cyclic life limits in Table 3 of this AD within 30 days after the effective date of this AD, or conduct optional qualifying nondestructive test (NDT) inspections before December 1, 2008 to extend the IPC stage 5 disk life, as specified in paragraph (i) of this AD. TABLE 3.—CYCLIC LIFE LIMITS WITHOUT QUALIFYING NDT INSPECTION Engine models Date of reduced life limit November 30, 2002 ........... April 1, 2003 December 1, December 1, December 1, ...................... 2003 ............. 2004 ............. 2005 ............. –524G2, G2–T, G3, G3–T, H2, H2–T, H–36, H–T–36 –524D4, D4–B, D4–B–39, D4X, D4X–B, D4–39 –524B2, B2–B, C2, C2–B 13,500 cycles-in-service (CIS). 13,500 CIS ........................ 12,000 CIS ........................ 11,000 CIS ........................ 11,000 CIS ........................ 16,150 CIS ........................ 16,000 CIS ........................ 16,200 CIS. 13,500 13,500 13,500 12,000 13,500 13,500 12,000 12,000 14,000 14,000 12,000 12,000 (h) On December 1, 2008, the revised cyclic life limits specified in Table 4 of this AD CIS CIS CIS CIS ........................ ........................ ........................ ........................ become effective. Incorporate the revised cyclic life limits specified in Table 4 of this CIS CIS CIS CIS ........................ ........................ ........................ ........................ –524B–02, B–B–02, B3– 02, B4–02, B4–D–02 CIS. CIS. CIS. CIS. AD into the RR Time Limits Manual, 05–10– 01. TABLE 4.—CYCLIC LIFE LIMITS ON DECEMBER 1, 2008 Engine models Date of reduced life limit December 1, 2008 ............. –524G2, G2–T, G3, G3–T, H2, H2–T, H–36, H–T–36 –524D4, D4–B, D4–B–39, D4X, D4X–B, D4–39 –524B2, B2–B, C2, C2–B 7,830 CIS .......................... 8,700 CIS .......................... 8,900 CIS .......................... Optional Inspections (i) Before December 1, 2008, you may perform an optional NDT inspection on-wing or at each shop visit to extend the disk life. Guidance for these inspections is provided in paragraphs (j) or (k) of this AD. rmajette on PROD1PC67 with RULES Optional Inspections at Shop Visit (j) Perform optional inspections at shop visit, as follows: (1) Remove corrosion protection from IPC stage 5 disk. Information on corrosion protection removal can be found in the Engine Maintenance Manual. (2) Perform a visual inspection and a binocular inspection of the IPC stage 5 disk for corrosion pitting at the cooling air holes and defender holes in the disk front spacer arm. Follow paragraph 3.C. of the Accomplishment Instructions of RR ASB No. RB.211–72–AD428, Revision 5, dated March 18, 2005. The RR Engine Maintenance Manual, Inspection Check-00 (ATA 72–32– VerDate Aug<31>2005 14:08 Mar 14, 2007 Jkt 211001 31–200–000), contains limits for corrosion pitting of the IPC stage 5 disk. (3) If the disk has corrosion pitting in excess of limits, remove the disk from service. (4) If the disk is free from corrosion pitting, perform a magnetic penetrant inspection (MPI) of the entire disk as follows: (i) For RB211–524G2–T, RB211–524G3–T, and RB211–524H–T series engines, the RR Engine Maintenance Manual, Inspection Check 08 (ATA 72–32–31–200–008), contains limits for corrosion pitting of the IPC stage 5 disk. (ii) For RB211–524G2, RB211–524G3, and RB211–524H series engines, the RR Engine Maintenance Manual, Inspection Check 09 (ATA 72–32–31–200–009), contains limits for corrosion pitting of the IPC stage 5 disk. (iii) If the disk passes the MPI and you find no cracks, complete all other inspections, reapply corrosion protection to the disk, and return the disk to service using the cyclic limits allowed by paragraph (m) of this AD. PO 00000 Frm 00032 Fmt 4700 Sfmt 4700 –524B–02, B–B–02, B3– 02, B4–02, B4–D–02 9,000 CIS. RR Repair FRS5900 contains information on re-applying corrosion protection. (5) If the disk has corrosion pitting that is within limits, do the following: (i) Perform an ECI on all disk cooling air holes, defender holes, and inner and outer faces. Use paragraph 3.D. of the Accomplishment Instructions of RR ASB No. RB.211–72–AD428, Revision 5, dated March 18, 2005. The RR Engine Maintenance Manual, Inspection Check-00 (ATA 72–32– 31–200–000), contains limits for corrosion pitting of the IPC stage 5 disk. (ii) If the disk passes the ECI and you find no cracks, perform an MPI on the entire disk. (iii) If the disk passes the MPI and you find no cracks, re-apply corrosion protection to the disk, and return the disk to service using the cyclic limits allowed by paragraph (m) of this AD. E:\FR\FM\15MRR1.SGM 15MRR1 12063 Federal Register / Vol. 72, No. 50 / Thursday, March 15, 2007 / Rules and Regulations Optional On-Wing Eddy Current Inspections (k) You may perform an optional on-wing ECI of the IPC stage 5 disk only once between shop visit inspections as follows: (1) For RB211–524B2/C2, RB211–524B/B3, and RB211–524B4/D4 series engines, use paragraphs 3.A. through 3.F. of the Accomplishment Instructions of RR SB No. RB.211–72–E148, dated March 13, 2003, and RR SB No. RB.211–72–E150, Revision 1, dated June 4, 2003. (2) For RB211–524G2, RB211–524G2–T, RB211–524G3, RB211–524G3–T, RB211– 524H, RB211–524H–T, RB211–524H2, and RB211–524H2–T series engines, use paragraphs 3.A. through 3.M. of the Accomplishment Instructions of RR SB No. RB.211–72–E171, Revision 1, dated February 8, 2005. (3) If the disk passes the ECI and you find no cracks, you may extend the cycle life as specified in paragraph (m) of this AD. only field maintenance type activities are performed in lieu of performing them onwing (such as to perform an on-wing inspection of a tail engine installation on a Lockheed L–1011 series airplane). Cyclic Life Extension (m) Disks that pass an optional inspection may remain in service after that inspection for the additional cycles listed in the following Table 5, until the next inspection, until the cyclic life limit published in the RR Time Limits Manual, 05–10–01, is reached, or December 1, 2008, whichever occurs first. Definition of Shop Visit (l) The manufacturer defines a shop visit as the separation of an engine major case flange. This definition excludes shop visits when TABLE 5.—CYCLIC LIFE EXTENSION Engine models –524G2, G2– T, G3, G3–T, H2, H2–T, H– 36, H–T–36 (cycles) Type of extension –524D4, D4– B, D4–B–39, D4X, D4X–B, D4–39 (cycles) 1,600 3,800 1,000 2,000 4,500 1,200 Extension After Passing MPI ........................................................................... Extension After Passing In-Shop ECI ............................................................. Extension After Passing On-Wing ECI ............................................................ Disks That Have Been Intermixed Between Engine Models (n) The RR Time Limits Manual, 05–00–01, contains information on intermixing disks between engine models. Alternative Methods of Compliance (o) 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. Credit for Previous Inspections (p) Inspections done using RR SB No. RB.211–72–E150, dated April 17, 2003, SB No. RB.211–72–E171, dated December 14, 2004, SB No. RB.211–72–D428, Revision 3, dated June 30, 2003, and ASB No. RB.211– 72–AD428, Revision 4, dated March 7, 2005, meet the requirements of this AD. Reporting Requirement –524B2, B2– B, C2, C2–B (cycles) –524B–02, B– B–02, B3–02, B4–02, B4–D– 02 (cycles) 2,000 4,500 1,200 2,000 4,500 1,200 7199; e-mail: ian.dargin@faa.gov for more information about this AD. (q) Report findings of all inspections of the IPC stage 5 disk using paragraph 3.B.(2) of the Accomplishment Instructions of RR No. ASB RB.211–72–AD428, Revision 5, dated March 18, 2005. The Office of Management and Budget (OMB) has approved the reporting requirements specified in Paragraph 3.B. of the Accomplishment Instructions of RR No. ASB RB.211–72– AD428, Revision 5, dated March 18, 2005, and assigned OMB control number 2120– 0056. Related Information (r) CAA airworthiness directive G–2005– 0008, dated March 8, 2005, also addresses the subject of this AD. (s) 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– Material Incorporated by Reference (t) You must use the service information specified in Table 6 to perform the actions required by this AD. The Director of the Federal Register approved the incorporation by reference of the documents listed in Table 6 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact RollsRoyce plc, P.O. Box 31 Derby, DE248BJ, United Kingdom; telephone 011–44–1332– 242424; fax 011–44–1332–249936 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 at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. TABLE 6.—INCORPORATION BY REFERENCE rmajette on PROD1PC67 with RULES Rolls-Royce plc Service Bulletin (SB)/Alert Service Bulletin (ASB) No. Page Revision SB No. RB.211–72–E148 ..................................................................................................... Total Pages: 83 SB No. RB.211–72–E150 ..................................................................................................... Total Pages: 72 SB No. RB.211–72–E171 ..................................................................................................... Total Pages: 71 ASB No. RB.211–72–AD428 ................................................................................................ Total Pages: 27 Appendix 1 of ASB No. RB.211–72–AD428 ........................................................................ Total Pages: 4 Appendix 2 of ASB No. RB.211–72–AD428 ........................................................................ Total Pages: 2 Appendix 3 of ASB No. RB.211–72–AD428 ........................................................................ Total Pages: 5 Appendix 4 of ASB No. RB.211–72–AD428 ........................................................................ Total Pages: 2 All ................ Original ........ March 13, 2003. All ................ 1 .................. June 4, 2003. All ................ 1 .................. February 8, 2005 All ................ 5 .................. March 18, 2005. All ................ 5 .................. March 18, 2005. All ................ 5 .................. March 18, 2005. All ................ 5 .................. March 18, 2005. All ................ 5 .................. March 18, 2005. VerDate Aug<31>2005 14:08 Mar 14, 2007 Jkt 211001 PO 00000 Frm 00033 Fmt 4700 Sfmt 4700 E:\FR\FM\15MRR1.SGM 15MRR1 Date 12064 Federal Register / Vol. 72, No. 50 / Thursday, March 15, 2007 / Rules and Regulations Issued in Burlington, Massachusetts, on March 7, 2007. Peter A. White, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E7–4536 Filed 3–14–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–26497; Directorate Identifier 2006–CE–082–AD; Amendment 39–14989; AD 2007–06–08] RIN 2120–AA64 Airworthiness Directives; Przedsiebiorstwo DoswiadczalnoProdukcyjne Szybownictwa ‘‘PZL– Bielsko’’ Model SZD–50–3 ‘‘Puchacz’’ Gliders Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: rmajette on PROD1PC67 with RULES Some cases of turnbuckle adjusting screws fatigue failure have occurred, due to lateral load component applied by pilot’s foot. Such events may lead to rudder and pedals disconnection. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective April 19, 2007. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of April 19, 2007. ADDRESSES: You may examine the AD docket on the Internet at https:// dms.dot.gov or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC. FOR FURTHER INFORMATION CONTACT: Gregory Davison, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329– 4130; fax: (816) 329–4090. SUPPLEMENTARY INFORMATION: VerDate Aug<31>2005 14:08 Mar 14, 2007 Jkt 211001 Streamlined Issuance of AD The FAA is implementing a new process for streamlining the issuance of ADs related to MCAI. The streamlined process will allow us to adopt MCAI safety requirements in a more efficient manner and will reduce safety risks to the public. This process continues to follow all FAA AD issuance processes to meet legal, economic, Administrative Procedure Act, and Federal Register requirements. We also continue to meet our technical decision-making responsibilities to identify and correct unsafe conditions on U.S.-certificated products. This AD references the MCAI and related service information that we considered in forming the engineering basis to correct the unsafe condition. The AD contains text copied from the MCAI and for this reason might not follow our plain language principles. Any such differences are highlighted in a NOTE within the AD. Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on January 5, 2007 (72 FR 485). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states that some cases of turnbuckle adjusting screws fatigue failure have occurred, due to lateral load component applied by pilot’s foot. Such events may lead to rudder and pedals disconnection. 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. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. Conclusion We reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. Differences Between This AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information. We might also have required different actions in this AD from those in the MCAI in order to follow FAA policies. PO 00000 Frm 00034 Fmt 4700 Sfmt 4700 Costs of Compliance We estimate that this AD will affect 8 products of U.S. registry. We also estimate that it will take about 2 workhours per product to comply with basic requirements of this AD. The average labor rate is $80 per work-hour. Required parts will cost about $100 per product. Where the service information lists required parts costs that are covered under warranty, we have assumed that there will be no charge for these parts. As we do not control warranty coverage for affected parties, some parties may incur costs higher than estimated here. Based on these figures, we estimate the cost of this AD to the U.S. operators to be $2,080, or $260 per product. Authority for This Rulemaking Regulatory Findings We 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 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 E:\FR\FM\15MRR1.SGM 15MRR1

Agencies

[Federal Register Volume 72, Number 50 (Thursday, March 15, 2007)]
[Rules and Regulations]
[Pages 12060-12064]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-4536]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-27267; Directorate Identifier 2002-NE-40-AD;
Amendment 39-14991; AD 2007-06-10]
RIN 2120-AA64

Airworthiness Directives; Rolls-Royce plc RB211-524 Series
Turbofan Engines

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

ACTION: Final rule.

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SUMMARY: The FAA is superseding an existing airworthiness directive
(AD) for Rolls Royce plc (RR) RB211-524 series turbofan engines with
certain part number (P/N) intermediate pressure compressor (IPC) stage
5 disks installed. That AD currently requires new reduced IPC stage 5
disk cyclic limits. This AD requires the same reduced IPC stage 5 disk
cyclic limits, requires removal from service of affected disks that
already exceed the new reduced cyclic limit, and, removal from service
of other affected disks before exceeding their cyclic limits using a
drawdown schedule. This AD also exempts disks reworked to RR Service
Bulletin (SB) No. RB.211-72-E182, Revision 1, dated July 30, 2004, and
allows an on-wing eddy current inspection (ECI) on RB211-524G and
RB211-524H series engines. This AD results from the manufacturer
issuing a revised Alert Service Bulletin (ASB) to remove certain disks
from applicability, and to allow an on-wing ECI on RB211-524G and
RB211-524H series engines. We are issuing this AD to prevent failure of
the IPC stage 5 disk, which could result in uncontained engine failure
and possible damage to the airplane.

DATES: This AD becomes effective April 19, 2007. The Director of the
Federal Register approved the incorporation by reference of certain
publications listed in the regulations as of April 19, 2007.

ADDRESSES: You can get the service information identified in this AD
from Rolls-Royce plc, P.O. Box 31 Derby, DE248BJ, United Kingdom;
telephone 011-44-1332-242424; fax 011-44-1332-249936.
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; e-mail: ian.dargin@faa.gov.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39
with a proposed AD. The proposed AD applies to RR RB211-524 series
turbofan engines with certain P/N IPC stage 5 disks installed. We
published the proposed AD in the Federal Register on July 11, 2006 (71
FR 39025). That action proposed to require:
Establishing new reduced IPC stage 5 disk cyclic limits.
Removing from service affected disks that already exceed
the new reduced cyclic limit.
Removing from service other affected disks before
exceeding their cyclic limits, using a drawdown schedule.
Allowing optional inspections at each shop visit or an on-
wing ECI to extend the disk life beyond the specified life.

Examining the AD Docket

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

Comments

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

Request To Add a Note

One commenter, Rolls-Royce plc, requests that we add a note, just
above compliance paragraph (j)(5), that states: ``To qualify for
maximum alleviation since last NDT inspection (see Table 5 of this AD)
it is recommended that discs be ECI inspected using paragraph 3.D. of
the Accomplishment Instructions of RR

[[Page 12061]]

Alert Service Bulletin No. RB.211-72-AD428, Revision 5, dated March 18,
2005.'' The commenter feels that this note adds clarification to the AD
compliance. We do not agree. The note is identified in the service
bulletin that is incorporated by reference, and need not be included in
the text of the AD. We did not change the AD.

Request To Add Engine Series

Rolls-Royce plc requests that we add the RB211-524B/B3 engine
series to compliance paragraph (k)(1), and add the RB211-524H2 and
RB211-524H2-T engine series to compliance paragraph (k)(2), as they
need to be included, the same as they appear in the service bulletin.
We agree and added those engine series to the paragraphs.

Clarification of Paragraph (g)

Since we issued the proposed AD, we reviewed the wording in
paragraph (g) and realized that the compliance times in that paragraph
were in conflict. We clarified that paragraph. It now states to comply
with the reduced cyclic life limits in Table 3 of this AD within 30
days after the effective date of this AD, or conduct optional
qualifying nondestructive test (NDT) inspections before December 1,
2008, to extend the IPC stage 5 disk life as specified in paragraph (i)
of this AD.

Conclusion

We have carefully reviewed the available data, including the
comments received, and determined that air safety and the public
interest require adopting the AD with the changes described previously.
We have determined that these changes will neither increase the
economic burden on any operator nor increase the scope of the AD.

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-2007-27267. The old Docket No. became the
Directorate Identifier, which is 2002-NE-40-AD. This AD might get
logged into the DMS docket, ahead of the previously collected documents
from the old docket file, as we are in the process of sending those
items to the DMS.

Costs of Compliance

We estimate this AD will not affect any engines installed on
airplanes of U.S. registry. Based on this, we estimate this AD will not
have any cost to U.S. operators.

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 39-14202 (70 FR
43036, July 26, 2005) and by adding a new airworthiness directive,
Amendment 39-14991, to read as follows:

2007-06-10 Rolls-Royce plc: Amendment 39-14991. Docket No. FAA-2007-
27267; Directorate Identifier 2002-NE-40-AD.

Effective Date

(a) This airworthiness directive (AD) becomes effective April
19, 2007.

Affected ADs

(b) This AD supersedes AD 2005-15-13, Amendment 39-14202.

Applicability

(c) This AD applies to the Rolls-Royce plc (RR) RB211-524 series
turbofan engines listed in the following Table 1, with intermediate
pressure compressor (IPC) stage 5 disk part numbers (P/Ns) listed in
Table 2 of this AD, installed.

Table 1.--Engine Models Affected
----------------------------------------------------------------------------------------------------------------

----------------------------------------------------------------------------------------------------------------
-524B-02 -524B-B-02 -524B3-02 -524B4-02 -524B4-D-02
-524B2-19 -524B2-B-19 -524C2-19 -524C2-B-19 -524D4-19
-524D4-B-19 -524D4X-19 -524D4X-B-19 -524D4-39 -524D4-B-39
-524G2-19 -524G2-T-19 -524G3-19 -524G3-T-19 -524H2-19
-524H2-T-19 -524H-36 -524H-T-36
----------------------------------------------------------------------------------------------------------------

These engines are installed on, but not limited to, Boeing 747,
767, and Lockheed L-1011 series airplanes.

[[Page 12062]]

Table 2.--IPC Stage 5 Disk P/Ns Affected
----------------------------------------------------------------------------------------------------------------

----------------------------------------------------------------------------------------------------------------
LK60130 LK65932 LK69021 LK81269 LK83282
LK83283 UL12290 UL15743 UL15744 UL15745
UL19132 UL20785 UL20832 UL23291 UL25011
UL36821 UL36977 UL36978 UL36979 UL36980
UL36981 UL36982 UL36983 UL37078 UL37079
UL37080 UL37081 UL37082 UL37083 UL37084
----------------------------------------------------------------------------------------------------------------

Unsafe Condition

(d) This AD results from the manufacturer issuing a revised
Alert Service Bulletin (ASB) to remove certain disks from
applicability and to allow an on-wing eddy current inspection (ECI)
on RB211-524G and RB211-524H series engines. The actions specified
in this AD are intended to prevent failure of the IPC stage 5 disk,
which could result in uncontained engine failure and possible 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.

Exempted Disks

(f) For engines with an IPC stage 5 disk P/N listed in Table 2
of this AD, reworked to RR SB No. RB.211-72-E182, Revision 1, dated
July 30, 2004, no further action is necessary.

Cycle Limits

(g) Comply with the reduced cyclic life limits in Table 3 of
this AD within 30 days after the effective date of this AD, or
conduct optional qualifying nondestructive test (NDT) inspections
before December 1, 2008 to extend the IPC stage 5 disk life, as
specified in paragraph (i) of this AD.

Table 3.--Cyclic Life Limits Without Qualifying NDT Inspection
----------------------------------------------------------------------------------------------------------------
Engine models
-------------------------------------------------------------------------------
Date of reduced life limit -524G2, G2-T, G3, -524D4, D4-B, D4-B- -524B-02, B-B-02,
G3-T, H2, H2-T, H- 39, D4X, D4X-B, D4- -524B2, B2-B, C2, B3-02, B4-02, B4-D-
36, H-T-36 39 C2-B 02
----------------------------------------------------------------------------------------------------------------
November 30, 2002............... 13,500 cycles-in- 16,150 CIS........ 16,000 CIS........ 16,200 CIS.
service (CIS).
April 1, 2003................... 13,500 CIS........ 13,500 CIS........ 13,500 CIS........ 14,000 CIS.
December 1, 2003................ 12,000 CIS........ 13,500 CIS........ 13,500 CIS........ 14,000 CIS.
December 1, 2004................ 11,000 CIS........ 13,500 CIS........ 12,000 CIS........ 12,000 CIS.
December 1, 2005................ 11,000 CIS........ 12,000 CIS........ 12,000 CIS........ 12,000 CIS.
----------------------------------------------------------------------------------------------------------------

(h) On December 1, 2008, the revised cyclic life limits
specified in Table 4 of this AD become effective. Incorporate the
revised cyclic life limits specified in Table 4 of this AD into the
RR Time Limits Manual, 05-10-01.

Table 4.--Cyclic Life Limits on December 1, 2008
----------------------------------------------------------------------------------------------------------------
Engine models
-------------------------------------------------------------------------------
Date of reduced life limit -524G2, G2-T, G3, -524D4, D4-B, D4-B- -524B-02, B-B-02,
G3-T, H2, H2-T, H- 39, D4X, D4X-B, D4- -524B2, B2-B, C2, B3-02, B4-02, B4-D-
36, H-T-36 39 C2-B 02
----------------------------------------------------------------------------------------------------------------
December 1, 2008................ 7,830 CIS......... 8,700 CIS......... 8,900 CIS......... 9,000 CIS.
----------------------------------------------------------------------------------------------------------------

Optional Inspections

(i) Before December 1, 2008, you may perform an optional NDT
inspection on-wing or at each shop visit to extend the disk life.
Guidance for these inspections is provided in paragraphs (j) or (k)
of this AD.

Optional Inspections at Shop Visit

(j) Perform optional inspections at shop visit, as follows:
(1) Remove corrosion protection from IPC stage 5 disk.
Information on corrosion protection removal can be found in the
Engine Maintenance Manual.
(2) Perform a visual inspection and a binocular inspection of
the IPC stage 5 disk for corrosion pitting at the cooling air holes
and defender holes in the disk front spacer arm. Follow paragraph
3.C. of the Accomplishment Instructions of RR ASB No. RB.211-72-
AD428, Revision 5, dated March 18, 2005. The RR Engine Maintenance
Manual, Inspection Check-00 (ATA 72-32-31-200-000), contains limits
for corrosion pitting of the IPC stage 5 disk.
(3) If the disk has corrosion pitting in excess of limits,
remove the disk from service.
(4) If the disk is free from corrosion pitting, perform a
magnetic penetrant inspection (MPI) of the entire disk as follows:
(i) For RB211-524G2-T, RB211-524G3-T, and RB211-524H-T series
engines, the RR Engine Maintenance Manual, Inspection Check 08 (ATA
72-32-31-200-008), contains limits for corrosion pitting of the IPC
stage 5 disk.
(ii) For RB211-524G2, RB211-524G3, and RB211-524H series
engines, the RR Engine Maintenance Manual, Inspection Check 09 (ATA
72-32-31-200-009), contains limits for corrosion pitting of the IPC
stage 5 disk.
(iii) If the disk passes the MPI and you find no cracks,
complete all other inspections, re-apply corrosion protection to the
disk, and return the disk to service using the cyclic limits allowed
by paragraph (m) of this AD. RR Repair FRS5900 contains information
on re-applying corrosion protection.
(5) If the disk has corrosion pitting that is within limits, do
the following:
(i) Perform an ECI on all disk cooling air holes, defender
holes, and inner and outer faces. Use paragraph 3.D. of the
Accomplishment Instructions of RR ASB No. RB.211-72-AD428, Revision
5, dated March 18, 2005. The RR Engine Maintenance Manual,
Inspection Check-00 (ATA 72-32-31-200-000), contains limits for
corrosion pitting of the IPC stage 5 disk.
(ii) If the disk passes the ECI and you find no cracks, perform
an MPI on the entire disk.
(iii) If the disk passes the MPI and you find no cracks, re-
apply corrosion protection to the disk, and return the disk to
service using the cyclic limits allowed by paragraph (m) of this AD.

[[Page 12063]]

Optional On-Wing Eddy Current Inspections

(k) You may perform an optional on-wing ECI of the IPC stage 5
disk only once between shop visit inspections as follows:
(1) For RB211-524B2/C2, RB211-524B/B3, and RB211-524B4/D4 series
engines, use paragraphs 3.A. through 3.F. of the Accomplishment
Instructions of RR SB No. RB.211-72-E148, dated March 13, 2003, and
RR SB No. RB.211-72-E150, Revision 1, dated June 4, 2003.
(2) For RB211-524G2, RB211-524G2-T, RB211-524G3, RB211-524G3-T,
RB211-524H, RB211-524H-T, RB211-524H2, and RB211-524H2-T series
engines, use paragraphs 3.A. through 3.M. of the Accomplishment
Instructions of RR SB No. RB.211-72-E171, Revision 1, dated February
8, 2005.
(3) If the disk passes the ECI and you find no cracks, you may
extend the cycle life as specified in paragraph (m) of this AD.

Definition of Shop Visit

(l) The manufacturer defines a shop visit as the separation of
an engine major case flange. This definition excludes shop visits
when only field maintenance type activities are performed in lieu of
performing them on-wing (such as to perform an on-wing inspection of
a tail engine installation on a Lockheed L-1011 series airplane).

Cyclic Life Extension

(m) Disks that pass an optional inspection may remain in service
after that inspection for the additional cycles listed in the
following Table 5, until the next inspection, until the cyclic life
limit published in the RR Time Limits Manual, 05-10-01, is reached,
or December 1, 2008, whichever occurs first.

Table 5.--Cyclic Life Extension
----------------------------------------------------------------------------------------------------------------
Engine models
---------------------------------------------------------------
-524G2, G2-T,
Type of extension G3, G3-T, H2, -524D4, D4-B, -524B2, B2-B, -524B-02, B-B-
H2-T, H-36, H- D4-B-39, D4X, C2, C2-B 02, B3-02, B4-
T-36 (cycles) D4X-B, D4-39 (cycles) 02, B4-D-02
(cycles) (cycles)
----------------------------------------------------------------------------------------------------------------
Extension After Passing MPI..................... 1,600 2,000 2,000 2,000
Extension After Passing In-Shop ECI............. 3,800 4,500 4,500 4,500
Extension After Passing On-Wing ECI............. 1,000 1,200 1,200 1,200
----------------------------------------------------------------------------------------------------------------

Disks That Have Been Intermixed Between Engine Models

(n) The RR Time Limits Manual, 05-00-01, contains information on
intermixing disks between engine models.

Alternative Methods of Compliance

(o) 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.

Credit for Previous Inspections

(p) Inspections done using RR SB No. RB.211-72-E150, dated April
17, 2003, SB No. RB.211-72-E171, dated December 14, 2004, SB No.
RB.211-72-D428, Revision 3, dated June 30, 2003, and ASB No. RB.211-
72-AD428, Revision 4, dated March 7, 2005, meet the requirements of
this AD.

Reporting Requirement

(q) Report findings of all inspections of the IPC stage 5 disk
using paragraph 3.B.(2) of the Accomplishment Instructions of RR No.
ASB RB.211-72-AD428, Revision 5, dated March 18, 2005. The Office of
Management and Budget (OMB) has approved the reporting requirements
specified in Paragraph 3.B. of the Accomplishment Instructions of RR
No. ASB RB.211-72-AD428, Revision 5, dated March 18, 2005, and
assigned OMB control number 2120-0056.

Related Information

(r) CAA airworthiness directive G-2005-0008, dated March 8,
2005, also addresses the subject of this AD.
(s) 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; e-mail: ian.dargin@faa.gov for more information
about this AD.

Material Incorporated by Reference

(t) You must use the service information specified in Table 6 to
perform the actions required by this AD. The Director of the Federal
Register approved the incorporation by reference of the documents
listed in Table 6 of this AD in accordance with 5 U.S.C. 552(a) and
1 CFR part 51. Contact Rolls-Royce plc, P.O. Box 31 Derby, DE248BJ,
United Kingdom; telephone 011-44-1332-242424; fax 011-44-1332-249936
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 at the National Archives
and Records Administration (NARA). For information on the
availability of this material at NARA, call 202-741-6030, or go to:
https://www.archives.gov/federal-register/cfr/ibr-locations.html.

Table 6.--Incorporation by Reference
----------------------------------------------------------------------------------------------------------------
Rolls-Royce plc Service Bulletin
(SB)/Alert Service Bulletin (ASB) Page Revision Date
No.
----------------------------------------------------------------------------------------------------------------
SB No. RB.211-72-E148............ All.................. Original............. March 13, 2003.
Total Pages: 83 ...............................
SB No. RB.211-72-E150............ All.................. 1.................... June 4, 2003.
Total Pages: 72 ...............................
SB No. RB.211-72-E171............ All.................. 1.................... February 8, 2005
Total Pages: 71 ...............................
ASB No. RB.211-72-AD428.......... All.................. 5.................... March 18, 2005.
Total Pages: 27 ...............................
Appendix 1 of ASB No. RB.211-72- All.................. 5.................... March 18, 2005.
AD428.
Total Pages: 4 ...............................
Appendix 2 of ASB No. RB.211-72- All.................. 5.................... March 18, 2005.
AD428.
Total Pages: 2 ...............................
Appendix 3 of ASB No. RB.211-72- All.................. 5.................... March 18, 2005.
AD428.
Total Pages: 5 ...............................
Appendix 4 of ASB No. RB.211-72- All.................. 5.................... March 18, 2005.
AD428.
Total Pages: 2 ...............................
----------------------------------------------------------------------------------------------------------------

[[Page 12064]]

Issued in Burlington, Massachusetts, on March 7, 2007.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E7-4536 Filed 3-14-07; 8:45 am]
BILLING CODE 4910-13-P

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