Federal Register / Vol. 75, No. 225 / Tuesday, November 23, 2010 / Proposed Rules 71373

under the criteria of the Regulatory (i) For TAE 125–01 engines, Operation & DEPARTMENT OF TRANSPORTATION Flexibility Act. Maintenance Manual OM–01–02, Issue 3, We prepared a regulatory evaluation Revision 13. Federal Aviation Administration of the estimated costs to comply with (ii) For TAE 125–02–99 and TAE 125–02– this proposed AD and placed it in the 114 engines, Operation & Maintenance 14 CFR Part 39 AD docket. Manual OM–02–02, Issue 1, Revision 10. [Docket No. FAA–2010–0494; Directorate List of Subjects in 14 CFR Part 39 Prohibition of FADEC Software Earlier Identifier 2010–NE–20–AD] Versions Air transportation, Aircraft, Aviation (f) Once FADEC software version 2.91 is RIN 2120–AA64 safety, Safety. installed, do not install any earlier version of Airworthiness Directives; International FADEC software. The Proposed Amendment Aero Engines V2500–A1, V2522–A5, Accordingly, under the authority FAA AD Differences V2524–A5, V2525–D5, V2527–A5, delegated to me by the Administrator, (g) EASA AD 2010–0137 permits V2527E–A5, V2527M–A5, V2528–D5, the FAA proposes to amend 14 CFR part installation of earlier FADEC software V2530–A5, and V2533–A5 39 as follows: versions, once version 2.91 is installed. This Engines AD does not. AGENCY: Federal Aviation PART 39—AIRWORTHINESS (h) EASA AD 2010–0137 requires Administration (FAA), DOT. DIRECTIVES compliance within 110 flight hours after the effective date of the AD or during next ACTION: Notice of proposed rulemaking 1. The authority citation for part 39 maintenance, whichever occurs first, but no (NPRM). continues to read as follows: later than 6 months after the effective date of SUMMARY: The FAA proposes to adopt a Authority: 49 U.S.C. 106(g), 40113, 44701. the AD. This AD requires compliance within 110 flight hours after the effective date of the new airworthiness directive (AD) for § 39.13 [Amended] AD or during next maintenance, whichever International Aero Engines (IAE) 2. The FAA amends § 39.13 by adding occurs first. V2500–A1, V2522–A5, V2524–A5, the following new airworthiness V2525–D5, V2527–A5, V2527E–A5, directive (AD): Alternative Methods of Compliance V2527M–A5, V2528–D5, V2530–A5, (AMOCS) and V2533–A5 turbofan engines. This Thielert Aircraft Engines GmbH: Docket No. (i) The Manager, Engine Certification proposed AD would require initial and FAA–2010–0820; Directorate Identifier ° 2010–NE–31–AD. Office, FAA, has the authority to approve repetitive 360 borescope inspections of AMOCs for this AD, if requested using the high-pressure turbine (HPT) stage 1 Comments Due Date procedures found in 14 CFR 39.19. blade outer air seal segments for (a) We must receive comments by January evidence of certain distress conditions. Related Information 7, 2011. This proposed AD would also require (j) Refer to AD 2010–0137, dated June 30, Affected ADs incorporation of improved durability 2010, for related information. Contact (b) None. stage 1 blade outer air seal segments at Thielert Aircraft Engines GmbH, the next exposure to the HPT module Applicability Platanenstrasse 14 D–09350, Lichtenstein, subassembly, as terminating action to (c) This AD applies to Thielert Aircraft Germany, telephone: +49–37204–696–0; fax: the repetitive inspections. This Engines GmbH models TAE 125–01, TAE +49–37204–696–2912; e-mail: proposed AD results from three reports 125–02–99, and TAE 125–02–114 [email protected], for a copy of received of HPT case burn-through reciprocating engines installed in, but not the service information referenced in this events, numerous shop reports of loss of limited to, Cessna 172 and (Reims-built) F172 AD. stage 1 blade outer air seal segments, series (European Aviation Safety Agency (k) Contact Alan Strom, Aerospace and HPT case bulging. We are proposing (EASA) STC No. EASA.A.S.01527); Piper Engineer, Engine Certification Office, FAA, PA–28 series (EASA STC No. EASA.A.S. this AD to prevent HPT case burn- Engine and Propeller Directorate, 12 New through, uncontrolled under-cowl 01632); APEX (Robin) DR 400 series (EASA England Executive Park, Burlington, MA STC No. A.S.01380); and Diamond fire, and damage to the airplane. 01803; e-mail: [email protected]; telephone Industries Models DA 40, DA 42, and DA DATES: We must receive any comments 42M NG airplanes. (781) 238–7143; fax (781) 238–7199, for more information about this AD. on this proposed AD by January 24, Reason 2011. Issued in Burlington, Massachusetts, on (d) This AD results from mandatory November 16, 2010. ADDRESSES: Use one of the following continuing airworthiness information (MCAI) Peter A. White, addresses to comment on this proposed issued by an aviation authority of another AD. country to identify and correct an unsafe Assistant Manager, Engine and Propeller • Federal eRulemaking Portal: Go to condition on an aviation product. We are Directorate, Aircraft Certification Service. http://www.regulations.gov and follow issuing this AD to prevent engine in-flight [FR Doc. 2010–29449 Filed 11–22–10; 8:45 am] shutdown or power loss, possibly resulting in the instructions for sending your reduced control of the airplane. BILLING CODE 4910–13–P comments electronically. • Mail: Docket Management Facility, Actions and Compliance U.S. Department of Transportation, 1200 (e) Unless already done, do the following New Jersey Avenue, SE., West Building actions. Ground Floor, Room W12–140, (1) Within 110 flight hours after the Washington, DC 20590–0001. effective date of the AD or during next • maintenance, whichever occurs first, install Hand Delivery: Deliver to Mail full-authority digital electronic control address above between 9 a.m. and (FADEC) software version 2.91. 5 p.m., Monday through Friday, except (2) Guidance on FADEC software Federal holidays. installation can be found in the following: • Fax: (202) 493–2251.

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Contact International Aero Engines Discussion improved durability stage 1 blade outer AG, 400 Main Street, East Hartford, CT Since August 2006 we have received air seal segments, and that the average 06108; telephone: (860) 565–5515; fax: three reports of IAE V2500 series labor rate is $85 per work-hour. (860) 565–5510, for a copy of the service engines experiencing HPT case burn- Required parts would cost about information identified in this proposed through events. There have also been $150,882 (V2500 A1 series) and AD. numerous shop reports of loss of stage $155,195 (V2500 A5/D5 series), per FOR FURTHER INFORMATION CONTACT: 1 blade outer air seal segments, and engine. Based on these figures, we Carlos Fernandes, Aerospace Engineer, reports of HPT case bulging. estimate the total cost of the proposed Engine Certification Office, FAA, Engine Investigation revealed the cause to be AD to U.S. operators to be $84,556,878. & Propeller Directorate, 12 New England due to HPT stage 1 blade outer air seal Authority for This Rulemaking Executive Park, Burlington, MA 01803; distress. Distress initially starts with e-mail: [email protected]; surface erosion and cracking of the Title 49 of the United States Code telephone (781) 238–7189; fax (781) blade outer air seal segments. Continued specifies the FAA’s authority to issue 238–7199. engine operation then leads to burn- rules on aviation safety. Subtitle I, through, radial bowing of the segments Section 106, describes the authority of SUPPLEMENTARY INFORMATION: into the gas path, contact with the HPT the FAA Administrator. Subtitle VII, Comments Invited stage 1 blades, and loss of the segments Aviation Programs, describes in more from the HPT case. This condition, if detail the scope of the Agency’s We invite you to send us any written not corrected, could then result in HPT authority. relevant data, views, or arguments case burn-through, uncontrolled under- We are issuing this rulemaking under regarding this proposal. Send your cowl engine fire, and damage to the the authority described in Subtitle VII, comments to an address listed under airplane. Part A, Subpart III, Section 44701, ADDRESSES. Include ‘‘Docket No. FAA– ‘‘General requirements.’’ Under that 2010–0494; Directorate Identifier 2010– Relevant Service Information section, Congress charges the FAA with NE–20–AD’’ in the subject line of your We have reviewed and approved the promoting safe flight of civil aircraft in comments. We specifically invite technical contents of IAE Service air commerce by prescribing regulations comments on the overall regulatory, Bulletin (SB) No. V2500–ENG–72–0580, for practices, methods, and procedures economic, environmental, and energy Revision 2, dated August 12, 2010, that the Administrator finds necessary for aspects of the proposed AD. We will describes procedures for initial and safety in air commerce. This regulation consider all comments received by the repetitive 360° borescope inspections of is within the scope of that authority closing date and may amend the stage 1 blade outer air seal segments for because it addresses an unsafe condition proposed AD in light of those evidence of distress. We have also that is likely to exist or develop on comments. reviewed and approved IAE SB No. products identified in this rulemaking We will post all comments we V2500–ENG–72–0483, Revision 3, dated action. January 7, 2009, and IAE SB No. V2500– receive, without change, to http:// Regulatory Findings www.regulations.gov, including any ENG–72–0542, Revision 1, dated personal information you provide. We January 7, 2009, which incorporate We have determined that this will also post a report summarizing each improved durability stage 1 blade outer proposed AD would not have federalism substantive verbal contact with FAA air seal segments. implications under Executive Order personnel concerning this proposed AD. FAA’s Determination and Requirements 13132. This proposed AD would not Using the search function of the Web of the Proposed AD have a substantial direct effect on the site, anyone can find and read the States, on the relationship between the We have evaluated all pertinent comments in any of our dockets, national Government and the States, or information and identified an unsafe including, if provided, the name of the on the distribution of power and condition that is likely to exist or individual who sent the comment (or responsibilities among the various develop on other products of this same levels of government. signed the comment on behalf of an type design. We are proposing this AD, For the reasons discussed above, I association, business, labor union, etc.). which would require initial and certify that the proposed AD: You may review the DOT’s complete repetitive 360° borescope inspections of Privacy Act Statement in the Federal HPT stage 1 blade outer air seal 1. Is not a ‘‘significant regulatory Register published on April 11, 2000 segments for evidence of distress. This action’’ under Executive Order 12866; (65 FR 19477–78). proposed AD would also require 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures Examining the AD Docket incorporation of improved design stage 1 blade outer air seal segments at the (44 FR 11034, February 26, 1979); and You may examine the AD docket on next exposure to the HPT module 3. Would not have a significant the Internet at http:// subassembly. The proposed AD would economic impact, positive or negative, www.regulations.gov; or in person at the require you to use the service on a substantial number of small entities Docket Operations office between 9 a.m. information described previously to under the criteria of the Regulatory and 5 p.m., Monday through Friday, perform these actions. Flexibility Act. except Federal holidays. The AD docket We prepared a regulatory evaluation contains this proposed AD, the Costs of Compliance of the estimated costs to comply with regulatory evaluation, any comments We estimate that this proposed AD this proposed AD. You may get a copy received, and other information. The would affect 34 V2500 A1 series and of this summary at the address listed street address for the Docket Operations 510 V2500 A5/D5 series engines under ADDRESSES. office (telephone (800) 647–5527) is the installed on airplanes of U.S. registry. same as the Mail address provided in We also estimate that it would take List of Subjects in 14 CFR Part 39 the ADDRESSES section. Comments will about 3 work-hours per engine to Air transportation, Aircraft, Aviation be available in the AD docket shortly perform one proposed inspection, about safety, Incorporation by reference, after receipt. 3 work-hours per engine to install the Safety.

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The Proposed Amendment A5, V2525–D5, V2527–A5, V2527E–A5, (i) Inspect within 1,000 operating hours V2527M–A5, V2528–D5, V2530–A5, and Under the authority delegated to me after the engine meets all criteria as defined V2533–A5 turbofan engines. These engines in Table 1 of this AD, or within 600 operating by the Administrator, the Federal are installed on, but not limited to, hours after the effective date of this AD, Aviation Administration proposes to A319, A320, A321, and McDonnell Douglas whichever is greater. amend 14 CFR part 39 as follows: MD–90 airplanes. (ii) Thereafter, re-inspect within every PART 39—AIRWORTHINESS Unsafe Condition 1,000 operating hours or as defined in DIRECTIVES (d) This AD results from three reports Appendix D of IAE SB No. V2500–ENG–72– received of high-pressure turbine (HPT) case 0580, Revision 2, dated August 12, 2010, 1. The authority citation for part 39 burn-through events. There have also been whichever is less. continues to read as follows: numerous shop reports of loss of stage 1 (iii) Use Accomplishment Instructions blade outer air seal segments, and HPT case paragraphs 3.B.(1) through 3.B.(3), and Authority: 49 U.S.C. 106(g), 40113, 44701. bulging. We are issuing this AD to prevent Appendices A through D of IAE SB No. HPT case burn-through, uncontrolled under- V2500–ENG–72–0580, Revision 2, dated § 39.13 [Amended] cowl engine fire, and damage to the airplane. August 12, 2010, to do these inspections. 2. The FAA amends § 39.13 by adding Compliance (2) For V2500–A1, V2522–A5, V2524–A5, the following new airworthiness V2527–A5, V2527E–A5, V2527M–A5, directive: (e) You are responsible for having the actions required by this AD performed within V2530–A5, and V2533–A5 turbofan engines: International Aero Engines: Docket No. the compliance times specified unless the (i) Inspect within 1,200 operating hours FAA–2010–0494; Directorate Identifier actions have already been done. after the engine meets all criteria as defined 2010–NE–20–AD. (f) For engines that have incorporated IAE in Table 1 of this AD, or within 600 operating Service Bulletin (SB) No. V2500–ENG–72– hours after the effective date of this AD, Comments Due Date 0483, Revision 3 or earlier, or IAE SB No. whichever is greater. (a) The Federal Aviation Administration V2500–ENG–72–0542, Revision 1 or earlier, (ii) Thereafter, re-inspect within every (FAA) must receive comments on this no further action is required. 1,200 operating hours or as defined in airworthiness directive (AD) action by Borescope Inspections Appendix D of IAE SB No. V2500–ENG–72– January 24, 2011. (g) Perform 360° borescope inspections of 0580, Revision 2, dated August 12, 2010, Affected ADs the HPT stage 1 blade outer air seal segments whichever is less. (b) None. for evidence of the distress conditions listed (iii) Use Accomplishment Instructions in Appendix D of IAE SB No. V2500–ENG– paragraphs 3.A.(1) through 3.A.(3), and Applicability 72–0580, Revision 2, dated August 12, 2010. Appendices A through D of IAE SB No. (c) This AD applies to International Aero (1) For V2525–D5 and V2528–D5 turbofan V2500–ENG–72–0580, Revision 2, dated Engines (IAE) V2500–A1, V2522–A5, V2524– engines: August 12, 2010, to do these inspections.

TABLE 1—STAGE 1 BLADE OUTER AIR SEAL SEGMENT INSPECTION COMPLIANCE CRITERIA

Stage 1 blade Stage 1 blade outer air seal outer air seal Exhaust gas segments hours- segments cycles- temperature Engine model since-new or since-new or margin degrees since-last-repair since-last-repair celsius (less than) (greater than) (greater than)

A1 ...... 6,000 3,800 45 A5 ...... 6,000 3,500 45 D5 ...... 5,000 3,500 45

(h) Exhaust Gas Temperature Margin is 0483, Revision 3, dated January 7, 2009, to (781) 238–7189; fax (781) 238–7199, for more defined as the expected margin during a sea- do the installation. information about this AD. level takeoff on a 30-degree Celsius Outside (3) Both IAE SBs No. V2500–ENG–72– (l) Contact International Aero Engines AG, Air Temperature Day. 0542, Revision 1, and SB No. V2500–ENG– 400 Main Street, East Hartford, CT 06108; 72–0483, Revision 3, require modification of telephone: (860) 565–5515; fax: (860) 565– Terminating Action the stage 1 HPT support assembly before 5510, for a copy of the service information installing the new blade outer air seal (i) As terminating action to the repetitive referenced in this AD. 360° borescope inspections required in segments. You must complete the paragraphs (g)(1)(ii) and (g)(2)(ii) above, modification using those SBs, as applicable Issued in Burlington, Massachusetts, on install improved durability stage 1 blade to the appropriate engine model, to properly November 16, 2010. perform the mandatory terminating action of outer air seal segments at the next HPT Peter A. White, module subassembly exposure. this AD. Assistant Manager, Engine and Propeller (1) For V2500–A1 turbofan engines, use Alternative Methods of Compliance Directorate, Aircraft Certification Service. paragraphs 1.B., Concurrent Requirements, (j) The Manager, Engine Certification and paragraphs 3.(1) through 3.(2)(b) of the [FR Doc. 2010–29450 Filed 11–22–10; 8:45 am] Office, has the authority to approve BILLING CODE 4910–13–P Accomplishment Instructions of IAE SB No. alternative methods of compliance for this V2500–ENG–72–0542, Revision 1, dated AD if requested using the procedures found January 7, 2009, to do the installation. in 14 CFR 39.19. (2) For V2522–A5, V2524–A5, V2525–D5, V2527–A5, V2527E–A5, V2527M–A5, Related Information V2528–D5, V2530–A5, and V2533–A5 (k) Contact Carlos Fernandes, Aerospace turbofan engines, use paragraphs 1.B., Engineer, Engine Certification Office, FAA, Concurrent Requirements, and paragraphs Engine & Propeller Directorate, 12 New 3.(1) through 3.(2)(b) of the Accomplishment England Executive Park, Burlington, MA Instructions of IAE SB No. V2500–ENG–72– 01803; e-mail: [email protected]; telephone

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