Airworthiness Directives; Rolls-Royce plc Models RB211 Trent 768-60, Trent 772-60, and Trent 772B-60 Turbofan Engines, 72310-72314 [E8-27298]

Download as PDF 72310 Federal Register / Vol. 73, No. 230 / Friday, November 28, 2008 / Rules and Regulations together with instructions for placing the fuel system in a configuration used to show compliance with that section. (h) For each airplane showing compliance with § 23.1353(g)(2) or (g)(3), the operating procedures for disconnecting the battery from its charging source must be furnished. (i) Information on the total quantity of usable fuel for each fuel tank, and the effect on the usable fuel quantity, as a result of a failure of any pump, must be furnished. (j) Procedures for the safe operation of the airplane’s systems and equipment, both in normal use and in the event of malfunction, must be furnished. dwashington3 on PROD1PC60 with RULES § 23.1587 Performance information. Instead of compliance with § 23.1587, the following apply: Unless otherwise prescribed, performance information must be provided over the altitude and temperature ranges required by § 23.45(b). (a) For all airplanes, the following information must be furnished— (1) The stalling speeds VSO and VS1 with the landing gear and wing flaps retracted, determined at maximum weight under § 23.49, and the effect on these stalling speeds of angles of bank up to 60 degrees; (2) The steady rate and gradient of climb with all engines operating, determined under § 23.69(a); (3) The landing distance, determined under § 23.75 for each airport altitude and standard temperature, and the type of surface for which it is valid; (4) The effect on landing distances of operation on other than smooth hard surfaces, when dry, determined under § 23.45(g); and (5) The effect on landing distances of runway slope and 50 percent of the headwind component and 150 percent of the tailwind component. (b) Not applicable. (c) Not applicable. (d) In addition to paragraph (a) of this section, the following information must be furnished— (1) The accelerate-stop distance determined under § 23.55; (2) The takeoff distance determined under § 23.59(a); (3) At the option of the applicant, the takeoff run determined under § 23.59(b); (4) The effect on accelerate-stop distance, takeoff distance and, if determined, takeoff run, of operation on other than smooth hard surfaces, when dry, determined under § 23.45(g); (5) The effect on accelerate-stop distance, takeoff distance, and if determined, takeoff run, of runway slope and 50 percent of the headwind VerDate Aug<31>2005 14:57 Nov 26, 2008 Jkt 217001 component and 150 percent of the tailwind component; (6) The net takeoff flight path determined under § 23.61(b); (7) The enroute gradient of climb/ descent with one engine inoperative, determined under § 23.69(b); (8) The effect, on the net takeoff flight path and on the enroute gradient of climb/descent with one engine inoperative, of 50 percent of the headwind component and 150 percent of the tailwind component; (9) Overweight landing performance information (determined by extrapolation and computed for the range of weights between the maximum landing and maximum takeoff weights) as follows— (i) The maximum weight for each airport altitude and ambient temperature at which the airplane complies with the climb requirements of § 23.63(d)(2); and (ii) The landing distance determined under § 23.75 for each airport altitude and standard temperature. (10) The relationship between IAS and CAS determined in accordance with § 23.1323(b) and (c). (11) The altimeter system calibration required by § 23.1325(e). Issued in Kansas City, Missouri, on November 18, 2008. John Colomy, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E8–28025 Filed 11–26–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–23605; Directorate Identifier 2005–NE–48–AD; Amendment 39– 15743; AD 2008–24–03] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce plc Models RB211 Trent 768–60, Trent 772–60, and Trent 772B–60 Turbofan Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: SUMMARY: The FAA is superseding an existing airworthiness directive (AD) for Rolls-Royce plc (RR) models RB211 Trent 768–60, Trent 772–60, and Trent 772B–60 turbofan engines that have not incorporated RR Service Bulletin (SB) PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 No. RB.211–72–E708, SB No. RB.211– 72–F227, or SB No. RB.211–72–E965, at original issue or later revision. That AD currently requires initial and repetitive borescope inspections of the highpressure/intermediate-pressure (HP/IP) turbine bearing internal oil vent tube, scavenge tube, and tube heat shields for wear and cracking, and removing tubes from service if found with any cracks beyond serviceable limits. That AD also currently requires installation of a new or modified HP/IP turbine bearings support as terminating action for the repetitive borescope inspections. This AD has the same requirements, and adds a repetitive inspection of the vent flow restrictor for blockage. This AD results from RR revising their alert service bulletin for inspection of the HP/IP turbine bearing internal oil vent tube, scavenge tube, and tube heat shields for damage, to include a repetitive inspection of the vent flow restrictor for blockage. We are issuing this AD to prevent oil ejecting from the HP/IP turbine bearings chamber and igniting. Burning oil can cause the intermediate-pressure (IP) shaft to fracture, the IP turbine to overspeed, and possible uncontained failure of the engine. DATES: Effective December 15, 2008. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of December 15, 2008. We must receive any comments on this AD by January 27, 2009. ADDRESSES: Use one of the following addresses to comment on this AD. • Federal eRulemaking Portal: Go to http://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. • Fax: (202) 493–2251. Contact Rolls-Royce plc, PO Box 31, Derby, England, DE248BJ; telephone: 011–44–1332–242424; fax: 011–44– 1332–245418, for the service information identified in this AD. FOR FURTHER INFORMATION CONTACT: James Lawrence, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: james.lawrence@faa.gov; telephone (781) 238–7175; fax (781) 238–7199. E:\FR\FM\28NOR1.SGM 28NOR1 Federal Register / Vol. 73, No. 230 / Friday, November 28, 2008 / Rules and Regulations On February 24, 2006, the FAA issued AD 2006–05–03, Amendment 39–14500 (71 FR 11153, March 6, 2006). That AD requires initial and repetitive borescope inspections of the HP/IP turbine bearing internal oil vent tube, scavenge tube, and tube heat shields for wear and cracking, and removing tubes from service if found with any cracks beyond serviceable limits. That AD also requires installation of a new or modified HP/IP turbine bearings support as terminating action for the repetitive borescope inspections. That AD was the result of two reports of RR RB211 Trent 700 series engines found with the HP/IP internal oil vent tube and scavenge tube fretted by damaged heat shields on the tubes. That condition, if not corrected, could result in oil ejecting from the HP/ IP turbine bearings chamber and igniting. Burning oil can cause the IP shaft to fracture, the IP turbine to overspeed, and possible uncontained failure of the engine. SUPPLEMENTARY INFORMATION: dwashington3 on PROD1PC60 with RULES Actions Since AD 2006–05–03 Was Issued Since AD 2006–05–03 was issued, the European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, notified us that they issued EASA AD 2007–0255, dated September 14, 2007, to supersede EASA AD 2005– 0024, dated October 14, 2005. EASA AD 2007–0255 carries forward the requirements from EASA AD 2005– 0024. EASA AD 2007–0255 adds repetitive inspections of the vent flow restrictor for blockage, based on RR issuing Alert Service Bulletin (ASB) No. RB.211–72–AE792, Revision 3. ASB Revision 3, and now Revision 4, add repetitive visual inspections of the vent flow restrictor for blockage. This AD requires the same actions as EASA AD 2007–0255. Relevant Service Information We have reviewed and approved the technical contents of RR ASB No. RB.211–72–AE792, Revision 4, dated August 2, 2007. That ASB describes procedures for initial and repetitive borescope inspections of the HP/IP turbine bearing internal oil vent tube, scavenge tube, and tube heat shields for wear and cracking, and removing tubes from service if found with any cracks beyond serviceable limits. That ASB also describes procedures for performing repetitive inspections of the vent flow restrictor for blockage. That ASB also references recently published RR SB No. RB.211–72–F227 and RR SB No. RB.211–72–E965 as terminating actions for the inspection requirements. VerDate Aug<31>2005 14:57 Nov 26, 2008 Jkt 217001 72311 Bilateral Airworthiness Agreement Comments Invited This engine model is manufactured in the United Kingdom and is type certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. Under this bilateral airworthiness agreement, the EASA has kept the FAA informed of the situation described above. We have examined the findings of the EASA, 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. 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 send us any written relevant data, views, or arguments regarding this AD. Send your comments to an address listed under ADDRESSES. Include ‘‘AD Docket No. FAA–2006–23605; Directorate Identifier 2005–NE–48–AD’’ in the subject line of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the rule that might suggest a need to modify it. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this AD. Using the search function of the Web site, anyone can find and read the comments in any of our dockets, including, if provided, the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78). FAA’s Determination and Requirements of This AD Although no airplanes that are registered in the United States use these RR RB211 Trent 768–60, Trent 772–60, and Trent 772B–60 turbofan engines, the possibility exists that the engines could be used on airplanes that are registered in the United States in the future. The unsafe condition described previously is likely to exist or develop on other RR RB211 Trent 768–60, Trent 772–60, and Trent 772B–60 turbofan engines of the same type design. We are issuing this AD to prevent oil ejecting from the HP/IP turbine bearings chamber and igniting. Burning oil can cause the IP shaft to fracture, the IP turbine to overspeed, and possible uncontained failure of the engine. This AD requires: • Initial and repetitive borescope inspections of the HP/IP turbine bearing internal oil vent tube, scavenge tube, and tube heat shields for wear and cracking; and • Removing tubes from service if found with any cracks beyond serviceable limits; and • Performing repetitive inspections of the vent flow restrictor for blockage; and • As terminating action to the repetitive inspections required by the AD, at the next 05 module overhaul, but before May 31, 2010, removing the HP/ IP bearings support and replacing with serviceable parts. You must use the service information described previously to perform the inspections required by this AD. FAA’s Determination of the Effective Date Since there are currently no domestic operators of this engine model, notice and opportunity for public comment before issuing this AD are unnecessary. Therefore, a situation exists that allows the immediate adoption of this regulation. PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is the same as the Mail address provided in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. 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 E:\FR\FM\28NOR1.SGM 28NOR1 72312 Federal Register / Vol. 73, No. 230 / Friday, November 28, 2008 / Rules and Regulations 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 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 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 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Amendment 39–14500 71 FR 11153, March 6, 2006, and by adding a new airworthiness directive, Amendment 39–15743, to read as follows: ■ 2008–24–03 Rolls-Royce plc: Amendment 39–15743. Docket No. FAA–2006–23605; Directorate Identifier 2005–NE–48–AD. Effective Date (a) This airworthiness directive (AD) becomes effective December 15, 2008. Affected ADs (b) This AD supersedes AD 2006–05–03, Amendment 39–14500. Applicability (c) This AD applies to Rolls-Royce plc (RR) models RB211 Trent 768–60, Trent 772–60, and Trent 772B–60 turbofan engines that have not incorporated RR Service Bulletin (SB) No. RB.211–72–E708, SB No. RB.211– 72–F227, or SB No. RB.211–72–E965, at original issue or later revision. These engines are installed on, but not limited to, Airbus A330–243, A330–341, A330–342, and A330– 343 airplanes. Unsafe Condition (d) This AD results from RR revising their alert service bulletin for inspection of the high-pressure/intermediate-pressure (HP/IP) turbine bearing internal oil vent tube, scavenge tube, and tube heat shields for damage, to include a repetitive inspection of the vent flow restrictor for blockage. We are issuing this AD to prevent oil ejecting from the HP/IP turbine bearings chamber and igniting. Burning oil can cause the intermediate-pressure (IP) shaft to fracture, the IP turbine to overspeed, and possible uncontained failure of the engine. 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. On-Wing Initial Borescope Inspection (f) Borescope inspect and assess the condition of the HP/IP turbine support assembly internal oil vent and scavenge tubes and heat shields, using Section 3. of the Accomplishment Instructions Part A, of RR Alert Service Bulletin (ASB) No. RB.211–72– AE792, Revision 4, dated August 2, 2007, and Table 1 of this AD. (g) The threshold life of the 05 module for the initial borescope inspection is 10,000 operating hours since new or since overhaul, or 2,500 cycles since new or since overhaul, whichever occurs first. TABLE 1—ON-WING BORESCOPE INSPECTION CRITERIA For: Action: (1) 05 modules that exceed the threshold life on the effective date of this AD: (2) 05 modules that are below the threshold life on the effective date of this AD: Inspect within 1 month after the effective date of this AD. Inspect by the threshold life or within 3 months from the effective date of this AD, whichever occurs later. On-Wing Repetitive Borescope Inspections (h) Determine the serviceability and establish the repetitive inspection intervals using Table 2 of this AD. TABLE 2—DETERMINATION OF SERVICEABILITY AND REPETITIVE INSPECTION INTERVAL dwashington3 on PROD1PC60 with RULES For: Action: (1) Outer heat shields of the vent or scavenge tube with no visible damage: (2) Outer heat shields of the vent or scavenge tube with partial cracking up to 90 degrees around the circumference or 10 mm along the length of either outer heat shield: (3) Outer heat shields of the vent or scavenge tube with partial cracking in excess of item (2) above, but less than 360 degrees around the circumference of either outer heat shield: (4) Outer heat shields of the vent or scavenge tube with cracking around the complete circumference of either outer heat shield, or if there is any missing material from either outer heat shield: Re-inspect within intervals of 10,000 operating hours or 2,500 cycles, whichever occurs first. Re-inspect within intervals of 6,400 operating hours or 1,600 cycles, whichever occurs first. VerDate Aug<31>2005 14:57 Nov 26, 2008 Jkt 217001 PO 00000 Frm 00010 Fmt 4700 Re-inspect within intervals of 1,600 operating hours or 400 cycles, whichever occurs first. Re-inspect or reject using Table 3 of this AD. Sfmt 4700 E:\FR\FM\28NOR1.SGM 28NOR1 Federal Register / Vol. 73, No. 230 / Friday, November 28, 2008 / Rules and Regulations 72313 TABLE 3—INSPECTION AND REJECTION CRITERIA FOR HEAT SHIELDS MEETING CONDITIONS IN ITEM (4) OF TABLE 2 OF THIS AD Condition: Action: (1) If the insulation blanket is in place inside the heat shield and preventing fretting between the heat shield and the tube. (2) If either vent or scavenge tube has fretting at the outer heat shield position where the maximum depth of fretting at any point around the full 360 degrees of each tube is less than 0.46 mm (0.018 inch). (3) If it is not possible to determine the maximum depth of fretting around the full 360 degrees of each tube and item (1) above is not applicable, then the HP/IP turbine support assembly must be rejected from service. (4) If either vent or scavenge tube has fretting at the outer heat shield position and the maximum depth of fretting is greater than 0.46 mm (0.018 inch) then the HP/IP turbine support assembly must be rejected from service. Inspect within intervals of 1,600 operating hours or 400 cycles, whichever occurs first. Inspect within intervals of 400 operating hours or 100 cycles, whichever occurs first. (i) For HP/IP turbine support assemblies which have been previously inspected using the superseded AD, or this AD: (1) Re-inspect the internal oil vent and scavenge tubes and heat shields before exceeding the intervals established in Table 2 of this AD. (2) Determine the serviceability and intervals to the next inspection using Table 2 of this AD. Inspections of the Vent Flow Restrictor After On-Wing Borescope Inspection (j) After a high-power ground run or not later than 25 cycles after heat shield inspection, inspect the vent flow restrictor, Reject from service within 50 cycles of the inspection being carried out. Reject within 10 cycles of the inspection being carried out. using Section 3. of the Accomplishment Instructions of RR SB No. RB.211–72–AE792, Revision 4, dated August 2, 2007. Repetitive Inspections of the Vent Flow Restrictor After On-Wing Borescope Inspection (k) After each on-wing borescope inspection, specified in paragraphs (f) through (h) of this AD, repeat the inspection of the vent flow restrictor, as specified in paragraph (j) of this AD. In-Shop Borescope Inspection (l) For 05 modules in-shop which are not undergoing strip and overhaul: (1) Borescope inspect and assess the condition of the HP/IP turbine support assembly internal oil vent and scavenge tubes and heat shields. (2) Inspect the vent tubes and the vent flow restrictor for carbon, after performing a highpower ground run. (3) Use Section 3. of the Accomplishment Instructions Part B, of RR ASB No. RB.211– 72–AE792, Revision 4, dated August 2, 2007, and Table 4 of this AD to do the inspections. (4) Determine the serviceability and establish the interval to next inspection of the HP/IP turbine support assembly internal oil vent and scavenge tubes and heat shields, using Table 4 of this AD: TABLE 4—RE-INSPECTION CRITERIA For: Action: (i) Outer heat shields of the vent and scavenge tubes with no visible damage: Re-inspect at a threshold of 10,000 operating hours time-since-new or time-since-overhaul, or 2,500 cycles-since-new or cycles-since-overhaul, whichever occurs first. Re-inspect at a not to exceed interval of 6,400 operating hours or 1,600 cycles, whichever occurs first. (ii) Outer heat shields of the vent and scavenge tubes with cracking up to 90 degrees around the circumference or 10 mm along the length of either outer heat shield: (iii) Outer heat shields of the vent and scavenge tubes with visible cracking greater than 90 degrees of the circumference or 10 mm along the length of either outer heat shield: (m) For 05 modules in-shop which are undergoing strip and overhaul, carry out the terminating action specified in paragraph (n) of this AD. dwashington3 on PROD1PC60 with RULES Terminating Action (n) As terminating action to the repetitive inspections required by this AD, at the next 05 module overhaul, but before May 31, 2010, remove the affected HP/IP bearings supports and replace with serviceable parts. Information on serviceable parts can be found in RR SB No. RB.211–72–E708, Revision 2, dated September 6, 2005, or in RR SB No. RB.211–72–F227, Revision 1, dated October 8, 2007, or in RR SB No. RB.211–72–E965, Revision 1, dated October 4, 2005. To obtain these SBs, see paragraph (r) of this AD for RR contact information. VerDate Aug<31>2005 14:57 Nov 26, 2008 Jkt 217001 Reject the tube and perform the terminating action specified in paragraph (n) of this AD. Definition (o) For the purposes of this AD, serviceable parts are new or reworked bearings supports which reduce the adverse effects of HP3 cooling air turbulence on the HP/IP turbine bearing internal oil vent and scavenge tubes and tube heat shields, as described in RR SB No. RB.211–72–E708, Revision 2, dated September 6, 2005, or in RR SB No. RB.211– 72–F227, Revision 1, dated October 8, 2007, or in RR SB No. RB.211–72–E965, Revision 1, dated October 4, 2005. Alternative Methods of Compliance (p) 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. PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 Related Information (q) European Aviation Safety Agency AD 2007–0255, dated September 14, 2007, also addresses the subject of this AD. Material Incorporated by Reference (r) You must use the service information specified in Table 5 of this AD to perform the inspections required by this AD. The Director of the Federal Register approved the incorporation by reference of the documents listed in Table 5 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Rolls-Royce plc, PO Box 31, Derby, England, DE248BJ; telephone: 011–44–1332– 242424; fax: 011–44–1332–245418, for a copy of this service information. You may review copies at the FAA, New England Region, 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 E:\FR\FM\28NOR1.SGM 28NOR1 72314 Federal Register / Vol. 73, No. 230 / Friday, November 28, 2008 / Rules and Regulations 202–741–6030, or go to: http:// www.archives.gov/federal-register/cfr/ibrlocations.html. TABLE 5—INCORPORATION BY REFERENCE Rolls-Royce Alert Service Bulletin No. Page Revision RB.211–72–AE792, including Appendix A ......................................................... Total Pages: 31 All ............................................. 4 Issued in Burlington, Massachusetts, on November 12, 2008. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E8–27298 Filed 11–26–08; 8:45 am] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–1020 Directorate Identifier 2008–CE–053–AD; Amendment 39–15751; AD 2008–24–11] RIN 2120–AA64 Airworthiness Directives; Vulcanair S.p.A. Model P68 Series Airplanes 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: dwashington3 on PROD1PC60 with RULES The Safe Fatigue Limits (SFL) of the Wing Structure in the P68 Series aircraft have been redefined from the current 8,500 Flight Hours to a new value to be calculated up to a maximum of 17,500 Flight Hours. This has been developed by Vulcanair under Change No. MOD.P68/79 Rev. 1 and approved by EASA with No. EASA.A.C.02482 on 07 June 2006. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective January 2, 2009. On January 2, 2009, the Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD. ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov or in person at 14:57 Nov 26, 2008 Jkt 217001 August 2, 2007. Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Sarjapur Nagarajan, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329– 4145; fax: (816) 329–4090. SUPPLEMENTARY INFORMATION: 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. 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 September 26, 2008 (73 FR 55786). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: BILLING CODE 4910–13–P VerDate Aug<31>2005 Date Costs of Compliance Based on the service information, we estimate that this AD will affect 72 products of U.S. registry. We also estimate that it will take about 80 workhours per product to comply with basic requirements of this AD. The average labor rate is $80 per work-hour. Based on these figures, we estimate the cost of this AD to the U.S. operators to be $460,800, or $6,400 per product. We have no way of determining the number of products that may need any necessary follow-on actions. The Safe Fatigue Limits (SFL) of the Wing Structure in the P68 Series aircraft have been redefined from the current 8,500 Flight Hours to a new value to be calculated up to a maximum of 17,500 Flight Hours. This has been developed by Vulcanair under Change No. MOD.P68/79 Rev. 1 and approved by EASA with No. EASA.A.C.02482 on 07 June 2006. The new Safe Fatigue Limits depend on: (a) Status of the modification (reinforcement) of the wing structure itself (Partenavia Service Bulletin No. 65 refers); and (b) Aircraft Flight Hours accumulated before the modification (reinforcement) was implemented. Conclusion We reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. 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. 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 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 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. PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 E:\FR\FM\28NOR1.SGM 28NOR1

Agencies

[Federal Register Volume 73, Number 230 (Friday, November 28, 2008)]
[Rules and Regulations]
[Pages 72310-72314]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-27298]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-23605; Directorate Identifier 2005-NE-48-AD; 
Amendment 39-15743; AD 2008-24-03]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc Models RB211 Trent 768-
60, Trent 772-60, and Trent 772B-60 Turbofan Engines

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

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD) for Rolls-Royce plc (RR) models RB211 Trent 768-60, Trent 772-60, 
and Trent 772B-60 turbofan engines that have not incorporated RR 
Service Bulletin (SB) No. RB.211-72-E708, SB No. RB.211-72-F227, or SB 
No. RB.211-72-E965, at original issue or later revision. That AD 
currently requires initial and repetitive borescope inspections of the 
high-pressure/intermediate-pressure (HP/IP) turbine bearing internal 
oil vent tube, scavenge tube, and tube heat shields for wear and 
cracking, and removing tubes from service if found with any cracks 
beyond serviceable limits. That AD also currently requires installation 
of a new or modified HP/IP turbine bearings support as terminating 
action for the repetitive borescope inspections. This AD has the same 
requirements, and adds a repetitive inspection of the vent flow 
restrictor for blockage. This AD results from RR revising their alert 
service bulletin for inspection of the HP/IP turbine bearing internal 
oil vent tube, scavenge tube, and tube heat shields for damage, to 
include a repetitive inspection of the vent flow restrictor for 
blockage. We are issuing this AD to prevent oil ejecting from the HP/IP 
turbine bearings chamber and igniting. Burning oil can cause the 
intermediate-pressure (IP) shaft to fracture, the IP turbine to 
overspeed, and possible uncontained failure of the engine.

DATES: Effective December 15, 2008. The Director of the Federal 
Register approved the incorporation by reference of certain 
publications listed in the regulations as of December 15, 2008.
    We must receive any comments on this AD by January 27, 2009.

ADDRESSES: Use one of the following addresses to comment on this AD.
     Federal eRulemaking Portal: Go to http://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 1200 New Jersey Avenue, SE., West Building Ground 
Floor, Room W12-140, Washington, DC 20590-0001.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
     Fax: (202) 493-2251.
    Contact Rolls-Royce plc, PO Box 31, Derby, England, DE248BJ; 
telephone: 011-44-1332-242424; fax: 011-44-1332-245418, for the service 
information identified in this AD.

FOR FURTHER INFORMATION CONTACT: James Lawrence, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; e-mail: 
james.lawrence@faa.gov; telephone (781) 238-7175; fax (781) 238-7199.

[[Page 72311]]


SUPPLEMENTARY INFORMATION: On February 24, 2006, the FAA issued AD 
2006-05-03, Amendment 39-14500 (71 FR 11153, March 6, 2006). That AD 
requires initial and repetitive borescope inspections of the HP/IP 
turbine bearing internal oil vent tube, scavenge tube, and tube heat 
shields for wear and cracking, and removing tubes from service if found 
with any cracks beyond serviceable limits. That AD also requires 
installation of a new or modified HP/IP turbine bearings support as 
terminating action for the repetitive borescope inspections. That AD 
was the result of two reports of RR RB211 Trent 700 series engines 
found with the HP/IP internal oil vent tube and scavenge tube fretted 
by damaged heat shields on the tubes. That condition, if not corrected, 
could result in oil ejecting from the HP/IP turbine bearings chamber 
and igniting. Burning oil can cause the IP shaft to fracture, the IP 
turbine to overspeed, and possible uncontained failure of the engine.

Actions Since AD 2006-05-03 Was Issued

    Since AD 2006-05-03 was issued, the European Aviation Safety Agency 
(EASA), which is the Technical Agent for the Member States of the 
European Community, notified us that they issued EASA AD 2007-0255, 
dated September 14, 2007, to supersede EASA AD 2005-0024, dated October 
14, 2005. EASA AD 2007-0255 carries forward the requirements from EASA 
AD 2005-0024. EASA AD 2007-0255 adds repetitive inspections of the vent 
flow restrictor for blockage, based on RR issuing Alert Service 
Bulletin (ASB) No. RB.211-72-AE792, Revision 3. ASB Revision 3, and now 
Revision 4, add repetitive visual inspections of the vent flow 
restrictor for blockage. This AD requires the same actions as EASA AD 
2007-0255.

Relevant Service Information

    We have reviewed and approved the technical contents of RR ASB No. 
RB.211-72-AE792, Revision 4, dated August 2, 2007. That ASB describes 
procedures for initial and repetitive borescope inspections of the HP/
IP turbine bearing internal oil vent tube, scavenge tube, and tube heat 
shields for wear and cracking, and removing tubes from service if found 
with any cracks beyond serviceable limits. That ASB also describes 
procedures for performing repetitive inspections of the vent flow 
restrictor for blockage. That ASB also references recently published RR 
SB No. RB.211-72-F227 and RR SB No. RB.211-72-E965 as terminating 
actions for the inspection requirements.

Bilateral Airworthiness Agreement

    This engine model is manufactured in the United Kingdom and is type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. Under this bilateral 
airworthiness agreement, the EASA has kept the FAA informed of the 
situation described above. We have examined the findings of the EASA, 
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

    Although no airplanes that are registered in the United States use 
these RR RB211 Trent 768-60, Trent 772-60, and Trent 772B-60 turbofan 
engines, the possibility exists that the engines could be used on 
airplanes that are registered in the United States in the future. The 
unsafe condition described previously is likely to exist or develop on 
other RR RB211 Trent 768-60, Trent 772-60, and Trent 772B-60 turbofan 
engines of the same type design. We are issuing this AD to prevent oil 
ejecting from the HP/IP turbine bearings chamber and igniting. Burning 
oil can cause the IP shaft to fracture, the IP turbine to overspeed, 
and possible uncontained failure of the engine. This AD requires:
     Initial and repetitive borescope inspections of the HP/IP 
turbine bearing internal oil vent tube, scavenge tube, and tube heat 
shields for wear and cracking; and
     Removing tubes from service if found with any cracks 
beyond serviceable limits; and
     Performing repetitive inspections of the vent flow 
restrictor for blockage; and
     As terminating action to the repetitive inspections 
required by the AD, at the next 05 module overhaul, but before May 31, 
2010, removing the HP/IP bearings support and replacing with 
serviceable parts.
    You must use the service information described previously to 
perform the inspections required by this AD.

FAA's Determination of the Effective Date

    Since there are currently no domestic operators of this engine 
model, notice and opportunity for public comment before issuing this AD 
are unnecessary. Therefore, a situation exists that allows the 
immediate adoption of this regulation.

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 send us any written relevant data, 
views, or arguments regarding this AD. Send your comments to an address 
listed under ADDRESSES. Include ``AD Docket No. FAA-2006-23605; 
Directorate Identifier 2005-NE-48-AD'' in the subject line of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify it.
    We will post all comments we receive, without change, to http://
www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact 
with FAA personnel concerning this AD. Using the search function of the 
Web site, anyone can find and read the comments in any of our dockets, 
including, if provided, the name of the individual who sent the comment 
(or signed the comment on behalf of an association, business, labor 
union, etc.). You may review the DOT's complete Privacy Act Statement 
in the Federal Register published on April 11, 2000 (65 FR 19477-78).

Examining the AD Docket

    You may examine the AD docket on the Internet at http://
www.regulations.gov; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Operations office (telephone (800) 647-5527) is the same as 
the Mail address provided in the ADDRESSES section. Comments will be 
available in the AD docket shortly after receipt.

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

[[Page 72312]]

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 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 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
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 39-14500 71 FR 
11153, March 6, 2006, and by adding a new airworthiness directive, 
Amendment 39-15743, to read as follows:

2008-24-03 Rolls-Royce plc: Amendment 39-15743. Docket No. FAA-2006-
23605; Directorate Identifier 2005-NE-48-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective December 
15, 2008.

Affected ADs

    (b) This AD supersedes AD 2006-05-03, Amendment 39-14500.

Applicability

    (c) This AD applies to Rolls-Royce plc (RR) models RB211 Trent 
768-60, Trent 772-60, and Trent 772B-60 turbofan engines that have 
not incorporated RR Service Bulletin (SB) No. RB.211-72-E708, SB No. 
RB.211-72-F227, or SB No. RB.211-72-E965, at original issue or later 
revision. These engines are installed on, but not limited to, Airbus 
A330-243, A330-341, A330-342, and A330-343 airplanes.

Unsafe Condition

    (d) This AD results from RR revising their alert service 
bulletin for inspection of the high-pressure/intermediate-pressure 
(HP/IP) turbine bearing internal oil vent tube, scavenge tube, and 
tube heat shields for damage, to include a repetitive inspection of 
the vent flow restrictor for blockage. We are issuing this AD to 
prevent oil ejecting from the HP/IP turbine bearings chamber and 
igniting. Burning oil can cause the intermediate-pressure (IP) shaft 
to fracture, the IP turbine to overspeed, and possible uncontained 
failure of the engine.

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.

On-Wing Initial Borescope Inspection

    (f) Borescope inspect and assess the condition of the HP/IP 
turbine support assembly internal oil vent and scavenge tubes and 
heat shields, using Section 3. of the Accomplishment Instructions 
Part A, of RR Alert Service Bulletin (ASB) No. RB.211-72-AE792, 
Revision 4, dated August 2, 2007, and Table 1 of this AD.
    (g) The threshold life of the 05 module for the initial 
borescope inspection is 10,000 operating hours since new or since 
overhaul, or 2,500 cycles since new or since overhaul, whichever 
occurs first.

             Table 1--On-Wing Borescope Inspection Criteria
------------------------------------------------------------------------
                   For:                                Action:
------------------------------------------------------------------------
(1) 05 modules that exceed the threshold    Inspect within 1 month after
 life on the effective date of this AD:      the effective date of this
                                             AD.
(2) 05 modules that are below the           Inspect by the threshold
 threshold life on the effective date of     life or within 3 months
 this AD:                                    from the effective date of
                                             this AD, whichever occurs
                                             later.
------------------------------------------------------------------------

On-Wing Repetitive Borescope Inspections

    (h) Determine the serviceability and establish the repetitive 
inspection intervals using Table 2 of this AD.

   Table 2--Determination of Serviceability and Repetitive Inspection
                                Interval
------------------------------------------------------------------------
                   For:                                Action:
------------------------------------------------------------------------
(1) Outer heat shields of the vent or       Re-inspect within intervals
 scavenge tube with no visible damage:       of 10,000 operating hours
                                             or 2,500 cycles, whichever
                                             occurs first.
(2) Outer heat shields of the vent or       Re-inspect within intervals
 scavenge tube with partial cracking up to   of 6,400 operating hours or
 90 degrees around the circumference or 10   1,600 cycles, whichever
 mm along the length of either outer heat    occurs first.
 shield:
(3) Outer heat shields of the vent or       Re-inspect within intervals
 scavenge tube with partial cracking in      of 1,600 operating hours or
 excess of item (2) above, but less than     400 cycles, whichever
 360 degrees around the circumference of     occurs first.
 either outer heat shield:
(4) Outer heat shields of the vent or       Re-inspect or reject using
 scavenge tube with cracking around the      Table 3 of this AD.
 complete circumference of either outer
 heat shield, or if there is any missing
 material from either outer heat shield:
------------------------------------------------------------------------


[[Page 72313]]


   Table 3--Inspection and Rejection Criteria for Heat Shields Meeting
              Conditions in Item (4) of Table 2 of This AD
------------------------------------------------------------------------
                Condition:                             Action:
------------------------------------------------------------------------
(1) If the insulation blanket is in place   Inspect within intervals of
 inside the heat shield and preventing       1,600 operating hours or
 fretting between the heat shield and the    400 cycles, whichever
 tube.                                       occurs first.
(2) If either vent or scavenge tube has     Inspect within intervals of
 fretting at the outer heat shield           400 operating hours or 100
 position where the maximum depth of         cycles, whichever occurs
 fretting at any point around the full 360   first.
 degrees of each tube is less than 0.46 mm
 (0.018 inch).
(3) If it is not possible to determine the  Reject from service within
 maximum depth of fretting around the full   50 cycles of the inspection
 360 degrees of each tube and item (1)       being carried out.
 above is not applicable, then the HP/IP
 turbine support assembly must be rejected
 from service.
(4) If either vent or scavenge tube has     Reject within 10 cycles of
 fretting at the outer heat shield           the inspection being
 position and the maximum depth of           carried out.
 fretting is greater than 0.46 mm (0.018
 inch) then the HP/IP turbine support
 assembly must be rejected from service.
------------------------------------------------------------------------

    (i) For HP/IP turbine support assemblies which have been 
previously inspected using the superseded AD, or this AD:
    (1) Re-inspect the internal oil vent and scavenge tubes and heat 
shields before exceeding the intervals established in Table 2 of 
this AD.
    (2) Determine the serviceability and intervals to the next 
inspection using Table 2 of this AD.

Inspections of the Vent Flow Restrictor After On-Wing Borescope 
Inspection

    (j) After a high-power ground run or not later than 25 cycles 
after heat shield inspection, inspect the vent flow restrictor, 
using Section 3. of the Accomplishment Instructions of RR SB No. 
RB.211-72-AE792, Revision 4, dated August 2, 2007.

Repetitive Inspections of the Vent Flow Restrictor After On-Wing 
Borescope Inspection

    (k) After each on-wing borescope inspection, specified in 
paragraphs (f) through (h) of this AD, repeat the inspection of the 
vent flow restrictor, as specified in paragraph (j) of this AD.

In-Shop Borescope Inspection

    (l) For 05 modules in-shop which are not undergoing strip and 
overhaul:
    (1) Borescope inspect and assess the condition of the HP/IP 
turbine support assembly internal oil vent and scavenge tubes and 
heat shields.
    (2) Inspect the vent tubes and the vent flow restrictor for 
carbon, after performing a high-power ground run.
    (3) Use Section 3. of the Accomplishment Instructions Part B, of 
RR ASB No. RB.211-72-AE792, Revision 4, dated August 2, 2007, and 
Table 4 of this AD to do the inspections.
    (4) Determine the serviceability and establish the interval to 
next inspection of the HP/IP turbine support assembly internal oil 
vent and scavenge tubes and heat shields, using Table 4 of this AD:

                     Table 4--Re-Inspection Criteria
------------------------------------------------------------------------
                   For:                                Action:
------------------------------------------------------------------------
(i) Outer heat shields of the vent and      Re-inspect at a threshold of
 scavenge tubes with no visible damage:      10,000 operating hours time-
                                             since-new or time-since-
                                             overhaul, or 2,500 cycles-
                                             since-new or cycles-since-
                                             overhaul, whichever occurs
                                             first.
(ii) Outer heat shields of the vent and     Re-inspect at a not to
 scavenge tubes with cracking up to 90       exceed interval of 6,400
 degrees around the circumference or 10 mm   operating hours or 1,600
 along the length of either outer heat       cycles, whichever occurs
 shield:                                     first.
(iii) Outer heat shields of the vent and    Reject the tube and perform
 scavenge tubes with visible cracking        the terminating action
 greater than 90 degrees of the              specified in paragraph (n)
 circumference or 10 mm along the length     of this AD.
 of either outer heat shield:
------------------------------------------------------------------------

    (m) For 05 modules in-shop which are undergoing strip and 
overhaul, carry out the terminating action specified in paragraph 
(n) of this AD.

Terminating Action

    (n) As terminating action to the repetitive inspections required 
by this AD, at the next 05 module overhaul, but before May 31, 2010, 
remove the affected HP/IP bearings supports and replace with 
serviceable parts. Information on serviceable parts can be found in 
RR SB No. RB.211-72-E708, Revision 2, dated September 6, 2005, or in 
RR SB No. RB.211-72-F227, Revision 1, dated October 8, 2007, or in 
RR SB No. RB.211-72-E965, Revision 1, dated October 4, 2005. To 
obtain these SBs, see paragraph (r) of this AD for RR contact 
information.

Definition

    (o) For the purposes of this AD, serviceable parts are new or 
reworked bearings supports which reduce the adverse effects of HP3 
cooling air turbulence on the HP/IP turbine bearing internal oil 
vent and scavenge tubes and tube heat shields, as described in RR SB 
No. RB.211-72-E708, Revision 2, dated September 6, 2005, or in RR SB 
No. RB.211-72-F227, Revision 1, dated October 8, 2007, or in RR SB 
No. RB.211-72-E965, Revision 1, dated October 4, 2005.

Alternative Methods of Compliance

    (p) The Manager, Engine Certification Office, has the authority 
to approve alternative methods of compliance for this AD if 
requested using the procedures found in 14 CFR 39.19.

Related Information

    (q) European Aviation Safety Agency AD 2007-0255, dated 
September 14, 2007, also addresses the subject of this AD.

Material Incorporated by Reference

    (r) You must use the service information specified in Table 5 of 
this AD to perform the inspections required by this AD. The Director 
of the Federal Register approved the incorporation by reference of 
the documents listed in Table 5 of this AD in accordance with 5 
U.S.C. 552(a) and 1 CFR part 51. Contact Rolls-Royce plc, PO Box 31, 
Derby, England, DE248BJ; telephone: 011-44-1332-242424; fax: 011-44-
1332-245418, for a copy of this service information. You may review 
copies at the FAA, New England Region, 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

[[Page 72314]]

202-741-6030, or go to: http://www.archives.gov/federal-register/
cfr/ibr-locations.html.

                                       Table 5--Incorporation by Reference
----------------------------------------------------------------------------------------------------------------
 Rolls-Royce Alert Service Bulletin No.             Page             Revision                 Date
----------------------------------------------------------------------------------------------------------------
RB.211-72-AE792, including Appendix A..  All......................          4   August 2, 2007.
    Total Pages: 31
----------------------------------------------------------------------------------------------------------------


    Issued in Burlington, Massachusetts, on November 12, 2008.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
 [FR Doc. E8-27298 Filed 11-26-08; 8:45 am]
BILLING CODE 4910-13-P