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International Aero Engines V2500-A1, V2522-A5

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International Aero Engines V2500-A1, V2522-A5 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 Turbofan 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 Aircraft engine 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. VerDate Mar<15>2010 14:36 Nov 22, 2010 Jkt 223001 PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 E:\FR\FM\23NOP1.SGM 23NOP1 erowe on DSK5CLS3C1PROD with PROPOSALS-1 71374 Federal Register / Vol. 75, No. 225 / Tuesday, November 23, 2010 / Proposed Rules 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.
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