Airworthiness Directives; Pratt & Whitney JT8D-209, -217, -217A, -217C, and -219 Series Turbofan Engines, 38052-38056 [2010-16010]

Download as PDF 38052 Federal Register / Vol. 75, No. 126 / Thursday, July 1, 2010 / Proposed Rules [FR Doc. 2010–14750 Filed 6–30–10; 8:45 am] BILLING CODE 6450–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–0452; Directorate Identifier 98–ANE–80–AD] RIN 2120–AA64 Airworthiness Directives; Pratt & Whitney JT8D–209, –217, –217A, –217C, and –219 Series Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: SUMMARY: The FAA proposes to supersede an existing airworthiness directive (AD) for Pratt & Whitney (PW) JT8D–209, –217, –217A, –217C, and –219 series turbofan engines. That AD requires initial and repetitive torque inspections of the 3rd stage and 4th stage low-pressure turbine (LPT) blades for shroud notch wear and replacement of the blade if wear limits are exceeded. That AD also requires replacing LPT-toexhaust case bolts and nuts with bolts and nuts made of Tinidur material. This proposed AD would require the same actions but would require replacement of the LPT-to-exhaust case bolts and nuts with longer bolts made of Tinidur material, with nuts made of Tinidur material, and installation of crushable sleeve spacers on the bolts. This proposed AD results from nine reports of failure of Tinidur material LPT-toexhaust case bolts since AD 2005–02–03 became effective. We are proposing this AD to prevent turbine blade failures that could result in uncontained engine debris and damage to the airplane. DATES: We must receive any comments on this proposed AD by August 30, 2010. Use one of the following addresses to comment on this proposed AD. • Federal eRulemaking Portal: Go to https://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 WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS ADDRESSES: VerDate Mar<15>2010 15:20 Jun 30, 2010 Jkt 220001 p.m., Monday through Friday, except Federal holidays. • Fax: (202) 493–2251. FOR FURTHER INFORMATION CONTACT: Kevin Dickert, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: kevin.dickert@faa.gov; telephone (781) 238–7117; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments regarding this proposal. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA– 2010–0452; Directorate Identifier 98– ANE–80–AD’’ in the subject line of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. We will post all comments we receive, without change, to https:// 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 proposed 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 https:// 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 proposed 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. Discussion The FAA proposes to amend 14 CFR part 39 by superseding AD 2005–02–03, Amendment 39–13948 (70 FR 3867, January 27, 2005). That AD requires PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 torque inspection of the 3rd stage and 4th stage LPT blades for shroud notch wear and replacement of the blade if wear limits are exceeded. That AD also requires replacing LPT-to-exhaust case bolts and nuts with bolts and nuts made of Tinidur material. That AD was the result of reports of 194 blade fractures since 1991, with 37 of those blade fractures resulting in LPT case separation, and three reports of uncontained 3rd stage and 4th stage LPT blade failures with cowl penetration. That condition, if not corrected, could result in turbine blade failures that could result in uncontained engine debris and damage to the airplane. Actions Since AD 2005–02–03 Was Issued Since AD 2005–02–03 was issued, we received nine reports of failure of Tinidur material LPT-to-exhaust case bolts occurring during 3rd and/or 4th stage blade fracture events. Three of these events resulted in cowl penetration. The bolts mandated by AD 2005–02–03 do not provide enough energy absorption during a blade fracture event. PW has introduced longer bolts made of Tinidur and crushable sleeve spacers that will increase the energy absorption capability of the fasteners during a blade fracture event. Also since AD 2005–02–03 was issued, PW revised Alert Service Bulletin (ASB) No. JT8D A6224, Revision 5, dated June 11, 2004, with Revision 6, dated May 3, 2007. Relevant Service Information We have reviewed and approved the technical contents of PW ASB No. JT8D A6224, Revision 6, dated May 3, 2007. That ASB describes procedures for performing torque inspections of the 3rd and 4th stage turbine blades. FAA’s Determination and Requirements of the Proposed AD We have evaluated all pertinent information and identified an unsafe condition that is likely to exist or develop on other products of this same type design. For that reason, we are proposing this AD, which would require torque inspection of the 3rd stage and 4th stage LPT blades for shroud notch wear and replacement of the blade if wear limits are exceeded. This proposed AD would also require the replacement of LPT-to-exhaust case bolts and nuts with longer bolts made of Tinidur material, with nuts made of Tinidur material, and installation of crushable sleeve spacers on the bolts. E:\FR\FM\01JYP1.SGM 01JYP1 Federal Register / Vol. 75, No. 126 / Thursday, July 1, 2010 / Proposed Rules Costs of Compliance We estimate that this proposed AD would affect 1,143 engines installed on airplanes of U.S. registry. We also estimate that it would take about 1 work-hour per engine to perform the proposed blade inspection, and 1.5 work-hours per engine to replace the LPT-to-exhaust case bolts and nuts and install the crushable sleeve spacers. Required bolts, nuts, and sleeve spacers would cost about $4,576 per engine. We anticipate that 61 engines would require blade replacement each year. Required blades would cost about $131,560 per engine. The average labor rate is $85 per work-hour. Based on these figures, we estimate the total cost of the proposed AD to U.S. operators to be $13,617,671. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We have determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the proposed 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. Would not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD. See the ADDRESSES section for a location to examine the regulatory evaluation. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Under the authority delegated to me by the Administrator, the Federal Aviation Administration proposes to amend 14 CFR part 39 as follows: 38053 a new airworthiness directive to read as follows: Pratt & Whitney: Docket No. FAA–2010– 0452; Directorate Identifier 98–ANE–80– AD. Comments Due Date (a) The Federal Aviation Administration (FAA) must receive comments on this airworthiness directive (AD) action by August 30, 2010. Affected ADs (b) This AD supersedes AD 2005–02–03. Applicability (c) This AD applies to Pratt & Whitney (PW) JT8D–209, –217, –217A, –217C, and –219 series turbofan engines. These engines are installed on, but not limited to, Boeing 727 series and McDonnell Douglas MD–80 series airplanes. Unsafe Condition (d) This AD results from nine reports of failure of Tinidur material low-pressure turbine (LPT)-to-exhaust case bolts since AD 2005–02–03 became effective. We are issuing this AD to prevent turbine blade failures that could result in uncontained engine debris and damage to the airplane. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done. Requirements of AD 2005–02–03 PART 39—AIRWORTHINESS DIRECTIVES Initial Torque Inspection for JT8D–209, –217, and –217A Engines 1. The authority citation for part 39 continues to read as follows: (f) For JT8D–209, –217, and –217A engines, perform the initial torque inspection of 3rd and 4th stage LPT blades for shroud notch wear. Use the procedures described in Accomplishment Instructions, Part 1, Paragraphs 1 through 3, of PW Alert Service Bulletin (ASB) No. JT8D A6224, Revision 6, dated May 3, 2007, at the applicable threshold in the following Table 1: Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Amendment 39–13948 (70 FR 3867, January 27, 2005) and by adding TABLE 1—INITIAL TORQUE INSPECTION THRESHOLD FOR JT8D–209, –217, AND –217A ENGINES Hours time-in-service (TIS) as of March 3, 2005 (the effective date of AD 2005–02–03) WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS Blade type (1) New pre-Service Bulletin (SB) No. 5867 (small notch) 3rd stage turbine blades. (2) Refurbished pre-SB No. 5867 (small notch) 3rd stage turbine blades. Inspection threshold VerDate Mar<15>2010 15:20 Jun 30, 2010 Jkt 220001 PO 00000 (i) Fewer than 3,000 ........... Within 4,000 hours TIS. Any number ........................ Within 6,000 hours TIS, or within 1,000 hours TIS from March 3, 2005, whichever occurs first. Within 10,000 hours TIS. (i) Fewer than 6,000 ........... Within 7,000 hours TIS. (ii) 6,000 or more ................ (5) New pre-SB No. 6029 (small notch) 4th stage turbine blades. Within 6,000 hours TIS. (ii) 3,000 or more ................ (3) New post-SB No. 5867 (large notch) 3rd stage turbine blades. (4) Refurbished post-SB No. 5867 (large notch) 3rd stage turbine blades. Any number ........................ Within 8,000 hours TIS, or within 1,000 hours TIS from March 3, 2005, whichever occurs first. Within 6,000 hours TIS. Any number ........................ Frm 00012 Fmt 4702 Sfmt 4702 E:\FR\FM\01JYP1.SGM 01JYP1 38054 Federal Register / Vol. 75, No. 126 / Thursday, July 1, 2010 / Proposed Rules TABLE 1—INITIAL TORQUE INSPECTION THRESHOLD FOR JT8D–209, –217, AND –217A ENGINES—Continued Blade type Hours time-in-service (TIS) as of March 3, 2005 (the effective date of AD 2005–02–03) (6) Refurbished pre-SB No. 6029 (small notch) 4th stage turbine blades. (i) Fewer than 3,000 ........... Within 4,000 hours TIS. (ii) 3,000 or more ................ Any number ........................ Within 6,000 hours TIS, or within 1,000 hours TIS from March 3, 2005, whichever occurs first. Within 10,000 hours TIS. (i) Fewer than 6,000 ........... Within 7,000 hours TIS. (ii) 6,000 or more ................ Within 8,000 hours TIS, or within 1,000 hours TIS from March 3, 2005, whichever occurs first. (7) New post-SB No. 6029 or new post-SB No. 6308 (large notch) 4th stage turbine blades. (8) Refurbished post-SB No. 6029 or refurbished postSB No. 6308 (large notch) 4th stage turbine blades. Repetitive Torque Inspections for JT8D–209, –217, and –217A Engines (g) For JT8D–209, –217, and –217A engines, perform repetitive torque Inspection threshold inspections of 3rd and 4th stage LPT blades for shroud notch wear. Use the procedures described in Accomplishment Instructions, Part 1, Paragraph 1 of PW ASB No. JT8D A6224, Revision 6, dated May 3, 2007, at the applicable intervals in the following Table 2 and Table 3: TABLE 2—3RD STAGE REPETITIVE TORQUE INSPECTION INTERVALS FOR JT8D–209, –217, AND –217A ENGINES Inspection torque readings Number of readings Greater than or equal to 15 LB–IN (1.695 N.m) .............. All ....................................... Less than 15 LB–IN (1.695 N.m) but greater than or equal to 10 LB–IN (1.130 N.m). Less than 10 LB–IN (1.130 N.m) but greater than or equal to 5 LB–IN (0.565 N.m). Less than 10 LB–IN (1.130 N.m) but greater than or equal to 5 LB–IN (0.565 N.m). Less than 5 LB–IN (0.565 N.m) ....................................... One or more ....................... Disposition One to three ....................... Four or more ...................... One or more ....................... Repeat torque inspection within 1,000 hours TIS last inspection. Repeat torque inspection within 500 hours TIS last inspection. Repeat torque inspection within 125 hours TIS last inspection. Remove engine from service within 20 hours TIS last inspection. Remove engine from service within 20 hours TIS last inspection. since since since since since TABLE 3—4TH STAGE REPETITIVE TORQUE INSPECTION INTERVALS FOR JT8D–209, –217, AND –217A ENGINES Inspection torque readings Number of readings Greater than or equal to 15 LB–IN (1.695 N.m) .............. All ....................................... Less than 15 LB–IN (1.695 N.m) but greater than or equal to 10 LB–IN (1.130 N.m). Less than 10 LB–IN (1.130 N.m) but greater than or equal to 5 LB–IN (0.565 N.m). Less than 10 LB–IN (1.130 N.m) but greater than or equal to 5 LB–IN (0.565 N.m). Less than 5 LB–IN (0.565 N.m) ....................................... One or more ....................... WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS (h) Subsequent repeat inspection intervals must not exceed the previous inspection interval. JT8D–209, –217, and –217A Engines Removed From Service (i) JT8D–209, –217, and –217A engines removed from service may be returned to service after a detailed inspection and repair or replacement for all blades, of the failed VerDate Mar<15>2010 15:20 Jun 30, 2010 Jkt 220001 Disposition One to six ........................... Seven or more ................... One or more ....................... Repeat torque inspection within 1,000 hours TIS last inspection. Repeat torque inspection within 500 hours TIS last inspection. Repeat torque inspection within 125 hours TIS last inspection. Remove engine from service within 20 hours TIS last inspection. Remove engine from service within 20 hours TIS last inspection. stage, that exceed Engine Manual limits is done. Information on repairing or replacing turbine blades can be found in Sections 72– 53–12 through 72–53–13 of the JT8D–200 Engine Manual, Part No. 773128. Initial Inspection for JT8D–217C and –219 Engines (j) For JT8D–217C and –219 engines, perform the initial torque inspection of 4th PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 since since since since since stage LPT blades for shroud notch wear. Use the procedures described in Accomplishment Instructions, Part 2, Paragraphs 1 through 3 of PW ASB No. JT8D A6224, Revision 6 dated May 3, 2007, at the applicable threshold in the following Table 4: E:\FR\FM\01JYP1.SGM 01JYP1 Federal Register / Vol. 75, No. 126 / Thursday, July 1, 2010 / Proposed Rules 38055 TABLE 4—INITIAL TORQUE INSPECTION THRESHOLD FOR JT8D–217C AND –219 ENGINES Blade type TIS as of March 3, 2005 (1) New pre-SB No. 6090 (small notch) 4th stage turbine blades. (2) Refurbished pre-SB No. 6090 (small notch) 4th stage turbine blades. Any number ........................ Within 5,000 hours TIS. (i) Fewer than 3,000 ........... Within 4,000 hours TIS. (ii) 3,000 or more ................ Any number ........................ Within 5,000 hours TIS, or within 1,000 hours TIS from March 3, 2005, whichever occurs first. Within 10,000 hours TIS. Any number ........................ Within 7,000 hours TIS. (i) Fewer than 3,000 ........... Within 4,000 hours TIS. (ii) 3,000 or more ................ Within 7,000 hours TIS, or within 1,000 hours TIS from March 3, 2005, whichever occurs first. stage LPT blades for shroud notch wear. Use the procedures described in Accomplishment Instructions, Part 2, Paragraph 1 of PW ASB No. JT8D A6224, Revision 6, dated May 3, 2007, at the applicable intervals in the following Table 5: (3) New post-SB No. 6090, new post-SB No. 6402, or new post-SB No. 6412 (large notch) 4th stage turbine blades. (4) Refurbished ‘‘As-Cast’’ post-SB No. 6090, post-SB No. 6402, or post-SB No. 6412 (large notch) 4th stage turbine blades. (5) Refurbished ‘‘Modified’’ post-SB No. 6090, post-SB No. 6402, or post-SB No. 6412 (large notch) 4th stage turbine blades. Repetitive Torque Inspections for JT8D–217C and –219 Engines (k) For JT8D–217C and –219 engines, perform repetitive torque inspections of 4th Inspection threshold TABLE 5—REPETITIVE TORQUE INSPECTION INTERVALS FOR JT8D–217C AND –219 ENGINES Inspection torque readings Number of readings Greater than or equal to 15 LB–IN (1.695 N.m) .............. All ....................................... Less than 15 LB–IN (1.695 N.m) but greater than or equal to 10 LB–IN (1.130 N.m). Less than 10 LB–IN (1.130 N.m) but greater than or equal to 5 LB–IN (0.565 N.m). Less than 10 LB–IN (1.130 N.m) but greater than or equal to 5 LB–IN (0.565 N.m). Less than 5 LB–IN (0.565 N.m) ....................................... One or more ....................... (l) Subsequent repeat inspection intervals must not exceed the previous inspection interval. JT8D–217C and –219 Engines Removed From Service (m) JT8D–217C and –219 engines removed from service may be returned to service after a detailed inspection and repair or replacement for all blades, of the failed stage, that exceed Engine Manual limits is done. Information on repairing or replacing turbine blades can be found in Sections 72–53–12 through 72–53–13 of the JT8D–200 Engine Manual, Part No. 773128. WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS Other Criteria for All Engine Models Listed in This AD (n) Whenever a refurbished or used blade is intermixed with new blades in a rotor, use the lowest initial inspection threshold that is applicable. (o) The initial torque inspection or the repetitive inspection intervals for a particular stage may not be reset unless the blades for that stage are refurbished or replaced. (p) Whenever a used (service run) blade is reinstalled in a rotor, the previous used time should be subtracted from the initial torque inspection threshold. VerDate Mar<15>2010 15:20 Jun 30, 2010 Jkt 220001 Disposition One to six ........................... Seven or more ................... One or more ....................... Repeat torque inspection within 1,000 hours TIS last inspection. Repeat torque inspection within 500 hours TIS last inspection. Repeat torque inspection within 125 hours TIS last inspection. Remove engine from service within 20 hours TIS last inspection. Remove engine from service within 20 hours TIS last inspection. What This AD Changes LPT-to-Exhaust Case Bolts and Nuts Replacement, and Crushable Sleeve Spacer Installation (q) At next accessibility to the LPT-toExhaust Case bolts and nuts, do the following: (1) Replace the bolts with part number (P/ N) MS9557–26 bolts; and (2) Replace the nuts with P/N 375095 nuts or P/N 490270 nuts; and (3) Install crushable sleeve spacers, P/N 822903, under the head of the bolts. (4) Guidance on replacing the bolts and nuts and installing the crushable sleeve spacers can be found in PW ASB No. JT8D A6494, Revision 1, dated January 26, 2010. Previous Credit (r) Initial inspections performed before the effective date of this AD using PW ASB No. JT8D A6224, Revision 5, dated June 11, 2004, or Revision 6, dated May 3, 2007, satisfy the initial inspection requirements of this AD. Definitions (s) For the purpose of this AD, refurbishment is defined as restoration of either the shrouds or blade retwist or both, PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 since since since since since per the JT8D–200 Engine Manual, Part No. 773128. (t) For the purpose of this AD, ‘‘As-Cast’’ refers to blades that were machined from new castings and ‘‘Modified’’ refers to blades that were derived from the pre-SB No. 6090 configuration. (u) For the purpose of this AD, ‘‘accessibility to the LPT-to-exhaust case bolts’’ refers to when the engine is disassembled sufficiently to give access to the LPT-to-exhaust case bolts, which is whenever the inner turbine fan ducts are removed. Alternative Methods of Compliance (v) The Manager, Engine Certification Office, has the authority to approve alternative methods of compliance (AMOCs) for this AD if requested using the procedures found in 14 CFR 39.19. AMOCs approved for the initial and repetitive inspection requirements of AD 2005–02–03 are approved as AMOCs for this AD. Related Information (w) Contact Kevin Dickert, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA E:\FR\FM\01JYP1.SGM 01JYP1 38056 Federal Register / Vol. 75, No. 126 / Thursday, July 1, 2010 / Proposed Rules 01803; e-mail: kevin.dickert@faa.gov; telephone (781) 238–7117; fax (781) 238– 7199, for more information about this AD. (x) Contact Pratt & Whitney, 400 Main St., East Hartford, CT 06108; telephone (860) 565–8770, fax (860) 565–4503, for a copy of the service information referenced in this AD. Issued in Burlington, Massachusetts, on June 22, 2010. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 2010–16010 Filed 6–30–10; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–0645; Directorate Identifier 2009–NM–200–AD] RIN 2120–AA64 Airworthiness Directives; McDonnell Douglas Corporation Model MD–90–30 Airplanes WReier-Aviles on DSKGBLS3C1PROD with PROPOSALS AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). SUMMARY: The FAA proposes to supersede an existing airworthiness directive (AD) that applies to certain Model MD–90–30 airplanes. The existing AD currently requires a detailed inspection for certain defects of the upper fasteners of the aft mount support fittings of the left and right engines, and corrective actions if necessary. This proposed AD would instead require repetitive replacement of the upper row of fasteners of the support fittings of the engine aft mount with new fasteners; and perform repetitive general visual inspections for defects of the lower row fasteners (Row B) of the support fittings of the left and right engine aft mounts, and replacement of all clearance fit fasteners in the lower row if necessary. This proposed AD results from reports of loose, cracked, or missing fasteners in the aft mount support fitting of the left and right engines. We are proposing this AD to prevent loose, cracked, or missing fasteners in the engine aft mount support fittings, which could lead to separation of the support fittings from the pylon, and could result in separation of the engine from the airplane. DATES: We must receive comments on this proposed AD by August 16, 2010. VerDate Mar<15>2010 15:20 Jun 30, 2010 Jkt 220001 You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, 3855 Lakewood Boulevard, MC D800 0019, Long Beach, California 90846–0001; telephone 206–544–5000, extension 2; fax 206 766–5683; e-mail dse.boecom@boeing.com; Internet https://www.myboeingfleet.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227– 1221. ADDRESSES: Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Roger Durbin, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712–4137; telephone (562) 627–5233; fax (562) 627–5210. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2010–0645; Directorate Identifier 2009–NM–200–AD’’ at the beginning of PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion On August 25, 2008, we issued AD 2008–18–10, Amendment 39–15667 (73 FR 52203, September 9, 2008), for certain McDonnell Douglas Corporation Model MD–90–30 airplanes. That AD requires a detailed inspection for certain defects of the upper fasteners of the aft mount support fittings of the left and right engines, and corrective actions if necessary. That AD resulted from reports of loose, cracked, or missing fasteners in the aft mount support fittings of the left and right engines. We issued that AD to detect and correct loose, cracked, or missing fasteners in the engine aft support mount fittings, which could lead to separation of the support fittings from the pylon, and could result in separation of the engine from the airplane. Actions Since Existing AD Was Issued The preamble to AD 2008–18–10 explains that we considered the requirements ‘‘interim action’’ and were considering further rulemaking. We now have determined that further rulemaking is indeed necessary, and this proposed AD follows from that determination. We also have received additional reports of loose, cracked, or missing fasteners in the aft mount support fitting of the left and right engines on 29 McDonnell Douglas Corporation Model MD–90–30 airplanes. The airplanes had accumulated between 15,560 and 37,298 total flight hours, and between 13,995 and 31,294 total flight cycles. Results of a safety assessment of the missing fasteners indicate that loose or otherwise discrepant fasteners in the top horizontal row, common with the pylon skin, significantly decrease the margin of safety of the aft mount support installation at the design limit load. Replacement of the upper row of fasteners at new specified intervals will help minimize the possibility of these fasteners becoming an unsafe condition while in service. Inspection of the lower E:\FR\FM\01JYP1.SGM 01JYP1

Agencies

[Federal Register Volume 75, Number 126 (Thursday, July 1, 2010)]
[Proposed Rules]
[Pages 38052-38056]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-16010]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0452; Directorate Identifier 98-ANE-80-AD]
RIN 2120-AA64

Airworthiness Directives; Pratt & Whitney JT8D-209, -217, -217A,
-217C, and -219 Series Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) for Pratt & Whitney (PW) JT8D-209, -217, -217A, -217C,
and -219 series turbofan engines. That AD requires initial and
repetitive torque inspections of the 3rd stage and 4th stage low-
pressure turbine (LPT) blades for shroud notch wear and replacement of
the blade if wear limits are exceeded. That AD also requires replacing
LPT-to-exhaust case bolts and nuts with bolts and nuts made of Tinidur
material. This proposed AD would require the same actions but would
require replacement of the LPT-to-exhaust case bolts and nuts with
longer bolts made of Tinidur material, with nuts made of Tinidur
material, and installation of crushable sleeve spacers on the bolts.
This proposed AD results from nine reports of failure of Tinidur
material LPT-to-exhaust case bolts since AD 2005-02-03 became
effective. We are proposing this AD to prevent turbine blade failures
that could result in uncontained engine debris and damage to the
airplane.

DATES: We must receive any comments on this proposed AD by August 30,
2010.

ADDRESSES: Use one of the following addresses to comment on this
proposed AD.
Federal eRulemaking Portal: Go to https://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.

FOR FURTHER INFORMATION CONTACT: Kevin Dickert, Aerospace Engineer,
Engine Certification Office, FAA, Engine & Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803; e-mail:
kevin.dickert@faa.gov; telephone (781) 238-7117; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION:

Comments Invited

We invite you to send any written relevant data, views, or
arguments regarding this proposal. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2010-0452; Directorate
Identifier 98-ANE-80-AD'' in the subject line of your comments. We
specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of the proposed AD. We will consider
all comments received by the closing date and may amend the proposed AD
in light of those comments.
We will post all comments we receive, without change, to https://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 proposed 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 https://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 proposed 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.

Discussion

The FAA proposes to amend 14 CFR part 39 by superseding AD 2005-02-
03, Amendment 39-13948 (70 FR 3867, January 27, 2005). That AD requires
torque inspection of the 3rd stage and 4th stage LPT blades for shroud
notch wear and replacement of the blade if wear limits are exceeded.
That AD also requires replacing LPT-to-exhaust case bolts and nuts with
bolts and nuts made of Tinidur material. That AD was the result of
reports of 194 blade fractures since 1991, with 37 of those blade
fractures resulting in LPT case separation, and three reports of
uncontained 3rd stage and 4th stage LPT blade failures with cowl
penetration. That condition, if not corrected, could result in turbine
blade failures that could result in uncontained engine debris and
damage to the airplane.

Actions Since AD 2005-02-03 Was Issued

Since AD 2005-02-03 was issued, we received nine reports of failure
of Tinidur material LPT-to-exhaust case bolts occurring during 3rd and/
or 4th stage blade fracture events. Three of these events resulted in
cowl penetration. The bolts mandated by AD 2005-02-03 do not provide
enough energy absorption during a blade fracture event. PW has
introduced longer bolts made of Tinidur and crushable sleeve spacers
that will increase the energy absorption capability of the fasteners
during a blade fracture event.
Also since AD 2005-02-03 was issued, PW revised Alert Service
Bulletin (ASB) No. JT8D A6224, Revision 5, dated June 11, 2004, with
Revision 6, dated May 3, 2007.

Relevant Service Information

We have reviewed and approved the technical contents of PW ASB No.
JT8D A6224, Revision 6, dated May 3, 2007. That ASB describes
procedures for performing torque inspections of the 3rd and 4th stage
turbine blades.

FAA's Determination and Requirements of the Proposed AD

We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other products
of this same type design. For that reason, we are proposing this AD,
which would require torque inspection of the 3rd stage and 4th stage
LPT blades for shroud notch wear and replacement of the blade if wear
limits are exceeded. This proposed AD would also require the
replacement of LPT-to-exhaust case bolts and nuts with longer bolts
made of Tinidur material, with nuts made of Tinidur material, and
installation of crushable sleeve spacers on the bolts.

[[Page 38053]]

Costs of Compliance

We estimate that this proposed AD would affect 1,143 engines
installed on airplanes of U.S. registry. We also estimate that it would
take about 1 work-hour per engine to perform the proposed blade
inspection, and 1.5 work-hours per engine to replace the LPT-to-exhaust
case bolts and nuts and install the crushable sleeve spacers. Required
bolts, nuts, and sleeve spacers would cost about $4,576 per engine. We
anticipate that 61 engines would require blade replacement each year.
Required blades would cost about $131,560 per engine. The average labor
rate is $85 per work-hour. Based on these figures, we estimate the
total cost of the proposed AD to U.S. operators to be $13,617,671.

Authority for This Rulemaking

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

Regulatory Findings

We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the proposed 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. Would not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD. See the ADDRESSES section for a location
to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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

Sec. 39.13 [Amended]

2. The FAA amends Sec. 39.13 by removing Amendment 39-13948 (70 FR
3867, January 27, 2005) and by adding a new airworthiness directive to
read as follows:

Pratt & Whitney: Docket No. FAA-2010-0452; Directorate Identifier
98-ANE-80-AD.

Comments Due Date

(a) The Federal Aviation Administration (FAA) must receive
comments on this airworthiness directive (AD) action by August 30,
2010.

Affected ADs

(b) This AD supersedes AD 2005-02-03.

Applicability

(c) This AD applies to Pratt & Whitney (PW) JT8D-209, -217, -
217A, -217C, and -219 series turbofan engines. These engines are
installed on, but not limited to, Boeing 727 series and McDonnell
Douglas MD-80 series airplanes.

Unsafe Condition

(d) This AD results from nine reports of failure of Tinidur
material low-pressure turbine (LPT)-to-exhaust case bolts since AD
2005-02-03 became effective. We are issuing this AD to prevent
turbine blade failures that could result in uncontained engine
debris and damage to the airplane.

Compliance

(e) You are responsible for having the actions required by this
AD performed within the compliance times specified unless the
actions have already been done.

Requirements of AD 2005-02-03

Initial Torque Inspection for JT8D-209, -217, and -217A Engines

(f) For JT8D-209, -217, and -217A engines, perform the initial
torque inspection of 3rd and 4th stage LPT blades for shroud notch
wear. Use the procedures described in Accomplishment Instructions,
Part 1, Paragraphs 1 through 3, of PW Alert Service Bulletin (ASB)
No. JT8D A6224, Revision 6, dated May 3, 2007, at the applicable
threshold in the following Table 1:

Table 1--Initial Torque Inspection Threshold for JT8D-209, -217, and -
217A Engines
------------------------------------------------------------------------
Hours time-in-
service (TIS) as
of March 3, 2005
Blade type (the effective Inspection threshold
date of AD 2005-
02-03)
------------------------------------------------------------------------
(1) New pre-Service Bulletin Any number....... Within 6,000 hours
(SB) No. 5867 (small notch) TIS.
3rd stage turbine blades.
(2) Refurbished pre-SB No. (i) Fewer than Within 4,000 hours
5867 (small notch) 3rd stage 3,000. TIS.
turbine blades.
(ii) 3,000 or Within 6,000 hours
more. TIS, or within 1,000
hours TIS from March
3, 2005, whichever
occurs first.
(3) New post-SB No. 5867 Any number....... Within 10,000 hours
(large notch) 3rd stage TIS.
turbine blades.
(4) Refurbished post-SB No. (i) Fewer than Within 7,000 hours
5867 (large notch) 3rd stage 6,000. TIS.
turbine blades.
(ii) 6,000 or Within 8,000 hours
more. TIS, or within 1,000
hours TIS from March
3, 2005, whichever
occurs first.
(5) New pre-SB No. 6029 (small Any number....... Within 6,000 hours
notch) 4th stage turbine TIS.
blades.

[[Page 38054]]

(6) Refurbished pre-SB No. (i) Fewer than Within 4,000 hours
6029 (small notch) 4th stage 3,000. TIS.
turbine blades.
(ii) 3,000 or Within 6,000 hours
more. TIS, or within 1,000
hours TIS from March
3, 2005, whichever
occurs first.
(7) New post-SB No. 6029 or Any number....... Within 10,000 hours
new post-SB No. 6308 (large TIS.
notch) 4th stage turbine
blades.
(8) Refurbished post-SB No. (i) Fewer than Within 7,000 hours
6029 or refurbished post-SB 6,000. TIS.
No. 6308 (large notch) 4th
stage turbine blades.
(ii) 6,000 or Within 8,000 hours
more. TIS, or within 1,000
hours TIS from March
3, 2005, whichever
occurs first.
------------------------------------------------------------------------

Repetitive Torque Inspections for JT8D-209, -217, and -217A Engines

(g) For JT8D-209, -217, and -217A engines, perform repetitive
torque inspections of 3rd and 4th stage LPT blades for shroud notch
wear. Use the procedures described in Accomplishment Instructions,
Part 1, Paragraph 1 of PW ASB No. JT8D A6224, Revision 6, dated May
3, 2007, at the applicable intervals in the following Table 2 and
Table 3:

Table 2--3rd Stage Repetitive Torque Inspection Intervals for JT8D-209,
217, and -217A Engines
------------------------------------------------------------------------
Number of
Inspection torque readings readings Disposition
------------------------------------------------------------------------
Greater than or equal to 15 LB- All.............. Repeat torque
IN (1.695 N.m). inspection within
1,000 hours TIS
since last
inspection.
Less than 15 LB-IN (1.695 N.m) One or more...... Repeat torque
but greater than or equal to inspection within
10 LB-IN (1.130 N.m). 500 hours TIS since
last inspection.
Less than 10 LB-IN (1.130 N.m) One to three..... Repeat torque
but greater than or equal to inspection within
5 LB-IN (0.565 N.m). 125 hours TIS since
last inspection.
Less than 10 LB-IN (1.130 N.m) Four or more..... Remove engine from
but greater than or equal to service within 20
5 LB-IN (0.565 N.m). hours TIS since last
inspection.
Less than 5 LB-IN (0.565 N.m). One or more...... Remove engine from
service within 20
hours TIS since last
inspection.
------------------------------------------------------------------------

Table 3--4th Stage Repetitive Torque Inspection Intervals for JT8D-209,
217, and -217A Engines
------------------------------------------------------------------------
Number of
Inspection torque readings readings Disposition
------------------------------------------------------------------------
Greater than or equal to 15 LB- All.............. Repeat torque
IN (1.695 N.m). inspection within
1,000 hours TIS
since last
inspection.
Less than 15 LB-IN (1.695 N.m) One or more...... Repeat torque
but greater than or equal to inspection within
10 LB-IN (1.130 N.m). 500 hours TIS since
last inspection.
Less than 10 LB-IN (1.130 N.m) One to six....... Repeat torque
but greater than or equal to inspection within
5 LB-IN (0.565 N.m). 125 hours TIS since
last inspection.
Less than 10 LB-IN (1.130 N.m) Seven or more.... Remove engine from
but greater than or equal to service within 20
5 LB-IN (0.565 N.m). hours TIS since last
inspection.
Less than 5 LB-IN (0.565 N.m). One or more...... Remove engine from
service within 20
hours TIS since last
inspection.
------------------------------------------------------------------------

(h) Subsequent repeat inspection intervals must not exceed the
previous inspection interval.

JT8D-209, -217, and -217A Engines Removed From Service

(i) JT8D-209, -217, and -217A engines removed from service may
be returned to service after a detailed inspection and repair or
replacement for all blades, of the failed stage, that exceed Engine
Manual limits is done. Information on repairing or replacing turbine
blades can be found in Sections 72-53-12 through 72-53-13 of the
JT8D-200 Engine Manual, Part No. 773128.

Initial Inspection for JT8D-217C and -219 Engines

(j) For JT8D-217C and -219 engines, perform the initial torque
inspection of 4th stage LPT blades for shroud notch wear. Use the
procedures described in Accomplishment Instructions, Part 2,
Paragraphs 1 through 3 of PW ASB No. JT8D A6224, Revision 6 dated
May 3, 2007, at the applicable threshold in the following Table 4:

[[Page 38055]]

Table 4--Initial Torque Inspection Threshold for JT8D-217C and -219
Engines
------------------------------------------------------------------------
TIS as of March
Blade type 3, 2005 Inspection threshold
------------------------------------------------------------------------
(1) New pre-SB No. 6090 (small Any number....... Within 5,000 hours
notch) 4th stage turbine TIS.
blades.
(2) Refurbished pre-SB No. (i) Fewer than Within 4,000 hours
6090 (small notch) 4th stage 3,000. TIS.
turbine blades.
(ii) 3,000 or Within 5,000 hours
more. TIS, or within 1,000
hours TIS from March
3, 2005, whichever
occurs first.
(3) New post-SB No. 6090, new Any number....... Within 10,000 hours
post-SB No. 6402, or new post- TIS.
SB No. 6412 (large notch) 4th
stage turbine blades.
(4) Refurbished ``As-Cast'' Any number....... Within 7,000 hours
post-SB No. 6090, post-SB No. TIS.
6402, or post-SB No. 6412
(large notch) 4th stage
turbine blades.
(5) Refurbished ``Modified'' (i) Fewer than Within 4,000 hours
post-SB No. 6090, post-SB No. 3,000. TIS.
6402, or post-SB No. 6412
(large notch) 4th stage
turbine blades.
(ii) 3,000 or Within 7,000 hours
more. TIS, or within 1,000
hours TIS from March
3, 2005, whichever
occurs first.
------------------------------------------------------------------------

Repetitive Torque Inspections for JT8D-217C and -219 Engines

(k) For JT8D-217C and -219 engines, perform repetitive torque
inspections of 4th stage LPT blades for shroud notch wear. Use the
procedures described in Accomplishment Instructions, Part 2,
Paragraph 1 of PW ASB No. JT8D A6224, Revision 6, dated May 3, 2007,
at the applicable intervals in the following Table 5:

Table 5--Repetitive Torque Inspection Intervals for JT8D-217C and -219
Engines
------------------------------------------------------------------------
Number of
Inspection torque readings readings Disposition
------------------------------------------------------------------------
Greater than or equal to 15 LB- All.............. Repeat torque
IN (1.695 N.m). inspection within
1,000 hours TIS
since last
inspection.
Less than 15 LB-IN (1.695 N.m) One or more...... Repeat torque
but greater than or equal to inspection within
10 LB-IN (1.130 N.m). 500 hours TIS since
last inspection.
Less than 10 LB-IN (1.130 N.m) One to six....... Repeat torque
but greater than or equal to inspection within
5 LB-IN (0.565 N.m). 125 hours TIS since
last inspection.
Less than 10 LB-IN (1.130 N.m) Seven or more.... Remove engine from
but greater than or equal to service within 20
5 LB-IN (0.565 N.m). hours TIS since last
inspection.
Less than 5 LB-IN (0.565 N.m). One or more...... Remove engine from
service within 20
hours TIS since last
inspection.
------------------------------------------------------------------------

(l) Subsequent repeat inspection intervals must not exceed the
previous inspection interval.

JT8D-217C and -219 Engines Removed From Service

(m) JT8D-217C and -219 engines removed from service may be
returned to service after a detailed inspection and repair or
replacement for all blades, of the failed stage, that exceed Engine
Manual limits is done. Information on repairing or replacing turbine
blades can be found in Sections 72-53-12 through 72-53-13 of the
JT8D-200 Engine Manual, Part No. 773128.

Other Criteria for All Engine Models Listed in This AD

(n) Whenever a refurbished or used blade is intermixed with new
blades in a rotor, use the lowest initial inspection threshold that
is applicable.
(o) The initial torque inspection or the repetitive inspection
intervals for a particular stage may not be reset unless the blades
for that stage are refurbished or replaced.
(p) Whenever a used (service run) blade is reinstalled in a
rotor, the previous used time should be subtracted from the initial
torque inspection threshold.

What This AD Changes

LPT-to-Exhaust Case Bolts and Nuts Replacement, and Crushable Sleeve
Spacer Installation

(q) At next accessibility to the LPT-to-Exhaust Case bolts and
nuts, do the following:
(1) Replace the bolts with part number (P/N) MS9557-26 bolts;
and
(2) Replace the nuts with P/N 375095 nuts or P/N 490270 nuts;
and
(3) Install crushable sleeve spacers, P/N 822903, under the head
of the bolts.
(4) Guidance on replacing the bolts and nuts and installing the
crushable sleeve spacers can be found in PW ASB No. JT8D A6494,
Revision 1, dated January 26, 2010.

Previous Credit

(r) Initial inspections performed before the effective date of
this AD using PW ASB No. JT8D A6224, Revision 5, dated June 11,
2004, or Revision 6, dated May 3, 2007, satisfy the initial
inspection requirements of this AD.

Definitions

(s) For the purpose of this AD, refurbishment is defined as
restoration of either the shrouds or blade retwist or both, per the
JT8D-200 Engine Manual, Part No. 773128.
(t) For the purpose of this AD, ``As-Cast'' refers to blades
that were machined from new castings and ``Modified'' refers to
blades that were derived from the pre-SB No. 6090 configuration.
(u) For the purpose of this AD, ``accessibility to the LPT-to-
exhaust case bolts'' refers to when the engine is disassembled
sufficiently to give access to the LPT-to-exhaust case bolts, which
is whenever the inner turbine fan ducts are removed.

Alternative Methods of Compliance

(v) The Manager, Engine Certification Office, has the authority
to approve alternative methods of compliance (AMOCs) for this AD if
requested using the procedures found in 14 CFR 39.19. AMOCs approved
for the initial and repetitive inspection requirements of AD 2005-
02-03 are approved as AMOCs for this AD.

Related Information

(w) Contact Kevin Dickert, Aerospace Engineer, Engine
Certification Office, FAA, Engine & Propeller Directorate, 12 New
England Executive Park, Burlington, MA

[[Page 38056]]

01803; e-mail: kevin.dickert@faa.gov; telephone (781) 238-7117; fax
(781) 238-7199, for more information about this AD.
(x) Contact Pratt & Whitney, 400 Main St., East Hartford, CT
06108; telephone (860) 565-8770, fax (860) 565-4503, for a copy of
the service information referenced in this AD.

Issued in Burlington, Massachusetts, on June 22, 2010.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 2010-16010 Filed 6-30-10; 8:45 am]
BILLING CODE 4910-13-P

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