Airworthiness Directives; Lycoming Engines (Formerly Textron Lycoming) AEIO-360, IO-360, O-360, LIO-360, LO-360, AEIO-540, IO-540, O-540, and TIO-540 Series Reciprocating Engines, 54618-54622 [05-18323]

Download as PDF 54618 Federal Register / Vol. 70, No. 179 / Friday, September 16, 2005 / Rules and Regulations determine its service history and the number of landings on the MLG shock strut cylinder. (2) For Group 3 airplanes identified in the service bulletin: Review the maintenance records to determine if the MLG cylinder on each Group 3 airplane has always been on a Group 3 airplane, and do the actions in paragraph (k) of this AD. Inspection (h) Inspect the MLG shock strut cylinders for cracks using the Option 1 or Option 2 non-destructive testing inspection described in the service bulletin. Inspect in accordance with the Accomplishment Instructions of the service bulletin. Do the detailed inspection before the accumulation of 60,000 total landings on the MLG, or at the applicable grace period specified in Table 1 of this AD, whichever occurs later, except as provided by paragraph (k) of this AD. If the review of maintenance records is not sufficient to conclusively determine the service history and number of landings on the MLG shock strut cylinder, perform the initial inspection at the applicable grace period specified in Table 1 of this AD. TABLE 1.—GRACE PERIOD AND REPETITIVE INTERVAL Airplanes identified in the service bulletin as group Grace period 1 ......................................................................... Within 18 months or 650 landings after the effective date of this AD, whichever occurs first. Within 18 months or 500 landings after the effective date of this AD, whichever occurs first. Within 18 months or 2,500 landings after the effective date of this AD, whichever occurs first. Within 18 months or 2,100 landings after the effective date of this AD, whichever occurs first. Intervals not to exceed 650 landings. Material Incorporated by Reference DEPARTMENT OF TRANSPORTATION 2 ......................................................................... 3, except as provided by paragraph (k) of this AD. 4 ......................................................................... No Crack Indication Found (i) If no crack indication is found during the inspection required by paragraph (h) of this AD, repeat the inspection at the applicable interval specified in Table 1 of this AD. Related Investigative and Corrective Actions (j) If any crack indication is found during any inspection required by paragraph (h) or (i) of this AD, before further flight: Confirm the crack indication by doing all applicable related investigative actions and doing the applicable corrective actions in accordance with the service bulletin. Repeat the inspection at the applicable threshold and interval specified in paragraph (h) of this AD. MLG Cylinder Previously Installed on Group 4 Airplanes (k) For MLG cylinders on Group 3 airplanes as identified in the service bulletin: If the MLG cylinder was previously installed on a Group 4 airplane, as identified in the service bulletin, or if the service history and number of landings cannot be determined, the MLG cylinder must be inspected at the grace period and repetitive interval that applies to Group 4 airplanes, as specified in Table 1 of this AD. Actions Accomplished in Accordance With Original Issue of Service Bulletin (l) Actions done before the effective date of this AD in accordance with Boeing Alert Service Bulletin DC9–32A350, dated December 3, 2004, are acceptable for compliance with the corresponding actions required by this AD. (n) You must use Boeing Alert Service Bulletin DC9–32A350, Revision 1, dated August 3, 2005, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Boeing Commercial Airplanes, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data and Service Management, Dept. C1–L5A (D800–0024), for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL–401, Nassif Building, Washington, DC; on the Internet at https:// dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741–6030, or go to https://www.archives.gov/federalregister/cfr/ibr-locations.html. Issued in Renton, Washington, on September 7, 2005. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–18314 Filed 9–15–05; 8:45 am] BILLING CODE 4910–13–P Alternative Methods of Compliance (AMOCs) (m) The Manager, Los Angeles Aircraft Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. VerDate Aug<31>2005 15:20 Sep 15, 2005 Jkt 205001 Repetitive interval PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 Intervals not to exceed 500 landings. Intervals not to exceed 2,500 landings. Intervals not exceed 2,100 landings. Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–21864; Directorate Identifier 2005–NE–29–AD; Amendment 39– 14276; AD 2005–19–11] RIN 2120–AA64 Airworthiness Directives; Lycoming Engines (Formerly Textron Lycoming) AEIO–360, IO–360, O–360, LIO–360, LO–360, AEIO–540, IO–540, O–540, and TIO–540 Series Reciprocating Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Lycoming Engines (formerly Textron Lycoming) AEIO–360, IO–360, O–360, LIO–360, LO–360, AEIO–540, IO–540, O–540, and TIO–540 series reciprocating engines rated at 300 horsepower (HP) or lower. This AD requires replacing certain crankshafts. This AD results from reports of 12 crankshaft failures in Lycoming 360 and 540 series engines rated at 300 HP or lower. We are issuing this AD to prevent failure of the crankshaft, which could result in total engine power loss, inflight engine failure, and possible loss of the aircraft. DATES: This AD becomes effective October 21, 2005. The Director of the Federal Register approved the incorporation by reference of certain E:\FR\FM\16SER1.SGM 16SER1 Federal Register / Vol. 70, No. 179 / Friday, September 16, 2005 / Rules and Regulations publications listed in the regulations as of October 21, 2005. ADDRESSES: You can get the service information identified in this AD from Lycoming, 652 Oliver Street, Williamsport, PA 17701; telephone (570) 323–6181; fax (570) 327–7101, or on the Internet at https:// www.Lycoming.Textron.com. You may examine the AD docket on the Internet at https://dms.dot.gov or in Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC. FOR FURTHER INFORMATION CONTACT: Norm Perenson, Aerospace Engineer, New York Aircraft Certification Office, FAA, Engine & Propeller Directorate, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone (516) 228–7337; fax (516) 794–5531. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 with a proposed airworthiness directive (AD). The proposed AD applies to Lycoming Engines (formerly Textron Lycoming) AEIO–360, IO–360, O–360, LIO–360, LO–360, AEIO–540, IO–540, O–540, and TIO–540 series reciprocating engines rated at 300 horsepower (HP) or lower. We published the proposed AD in the Federal Register on July 22, 2005 (70 FR 42282). That action proposed to require replacing certain crankshafts within 50 hours time-in-service or 6 months after the effective date of the proposed AD, whichever is earlier. Examining the AD Docket You may examine the docket that contains the AD, any comments received, and any final disposition in person at the Docket Management Facility Docket Offices between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone (800) 647–5227) is located on the plaza level of the Department of Transportation Nassif Building at the street address stated in ADDRESSES. Comments will be available in the AD docket shortly after the DMS receives them. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments received. Will Additional Engines and Crankshafts Be Affected in the Future One commenter asks if additional serial numbered engines and crankshafts will be affected in the future. At this time we do not anticipate that the affected population will increase, VerDate Aug<31>2005 15:20 Sep 15, 2005 Jkt 205001 but Lycoming and the FAA are monitoring crankshaft performance. Affected Engines and Crankshafts The same commenter asks why these engines and crankshafts are the only ones affected by the SB and AD. Both the previous AD (2002–19–03) and this AD advise that the affected population of engines and crankshafts were manufactured in a specific time period. We are addressing that time period. Suspect Crankshafts Should Be Either Tested or Replaced One commenter states that suspect crankshafts should be either tested or replaced before further flight, because the problem with these crankshafts is similar to the problem that caused the crankshaft failures on the 540 engines. We disagree. The compliance interval in this AD is based on an assessment of operating stresses, service experience, and duty cycle of the affected engine population. The compliance interval differs from that imposed in AD 2002– 19–03 due to differences in these parameters. Request To Include Lycoming TIO–540– AE2A and Other Unspecified Engine Models One commenter requests that we include the Lycoming TIO–540–AE2A and other unspecified engine models in this AD. The commenter states that many of the TIO–540–AE2A engines have never been recalled or replaced yet should be, because recent litigation has shown that Lycoming’s crankshaft end core sample test is insufficient. We disagree. We have seen no evidence that refutes the validity of the test. Further, AD 2002–19–03 (the previous AD) effective on September 20, 2002, described two groups of crankshafts. We required one crankshaft group to be removed before further flight, and we required the other crankshaft group to have a sample of the crankshaft material tested. The crankshafts in each group were selected based on our evaluation of the risk both groups presented. Crankshafts from either group may be installed in the TIO–540–AE2A engine model. No failures of crankshafts listed in either group have occurred since. Conclusion We have carefully reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting the AD as proposed. PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 54619 Costs of Compliance We estimate that this AD will affect 1,128 engines installed on aircraft of U.S. registry. We estimate that it will take the following work hours to perform the inspection: Type of application Helicopter ........ ConstantSpeed Propeller ........... Fixed-Pitch Propeller ...... Work-hours per engine Number of engines affected 12 200 3 557 1.5 371 We also estimate that it will take about 33 work hours to replace the crankshaft. We estimate the average labor rate is $65 per work hour and that required parts for each engine will cost about $16,218. Based on these figures, we estimate the total cost of the AD to U.S. operators to be $18,594,724. Lycoming Engines informed us that they intend to supply the new parts at no charge, which may substantially reduce the estimated cost of this AD. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in subtitle VII, part A, subpart III, section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866; E:\FR\FM\16SER1.SGM 16SER1 54620 Federal Register / Vol. 70, No. 179 / Friday, September 16, 2005 / Rules and Regulations (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a summary of the costs to comply with this AD and placed it in the AD Docket. You may get a copy of this summary at the address listed under ADDRESSES. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation Administration amends 14 CFR part 39 as follows: I FAA–2005–21864; Directorate Identifier 2005–NE–29–AD. Effective Date (a) This airworthiness directive (AD) becomes effective October 21, 2005. PART 39—AIRWORTHINESS DIRECTIVES Affected ADs 1. The authority citation for part 39 continues to read as follows: Applicability (b) None. I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: List of Subjects in 14 CFR Part 39 I Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. 2005–19–11 Lycoming Engines: Amendment 39–14276. Docket No. Engine model Manufacturer IO–540–V4A5 ..................................................... A.M.F ................................................................ Aero Commander ............................................. Aero Commander ............................................. Aerofab ............................................................. Aeronautica ...................................................... Aerostar ............................................................ Aircraft Manufacturing Factory ......................... Aviamilano ........................................................ Avions ............................................................... Beech ............................................................... ........................................................................... (c) This AD applies to Lycoming Engines (Formerly Textron Lycoming) AEIO–360, IO– 360, O–360, LIO–360, LO–360, AEIO–540, IO–540, O–540, and TIO–540 series reciprocating engines, rated at 300 horsepower (HP) or lower, manufactured new, rebuilt, overhauled after March 1, 1999, or that had a crankshaft installed after March 1, 1999. These engines are installed on, but not limited to, the following aircraft: IO–540–E1A5 ..................................................... IO–540–K1F5 ..................................................... O–540–E4A5 ...................................................... IO–540–C4B5 .................................................... LO–360–A1G6D ................................................. O–360–A1G6D ................................................... O–540–E4B5 ...................................................... O–540–E4C5 ..................................................... IO–540–K1B5 ..................................................... O–360–A1F6 ...................................................... O–360–A1F6D ................................................... O–540–J3C5D ................................................... IO–540–AB1A5 .................................................. O–360–F1A6 ...................................................... IO–540–AC1A5 .................................................. IO–360–A1B6D .................................................. TIO–540–AK1A .................................................. O–540–L3C5D ................................................... AEIO–540–D4A5 ................................................ IO–540–T4B5D .................................................. IO–540–T4B5 ..................................................... TIO–540–AG1A .................................................. IO–540–K1J5D ................................................... O–540–B4B5 ...................................................... AEIO–540–L1B5 ................................................ O–540–A1A5 ...................................................... AEIO–360–A1E6 ................................................ IO–540–M1C5 .................................................... O–540–J3A5 ...................................................... IO–540–W1A5 .................................................... IO–360–A3B6 ..................................................... VerDate Aug<31>2005 15:20 Sep 15, 2005 Jkt 205001 Aircraft model Bellanca ............................................................ Britten Norman ................................................. ........................................................................... ........................................................................... Celair ................................................................ Cessna ............................................................. ........................................................................... ........................................................................... ........................................................................... ........................................................................... ........................................................................... ........................................................................... ........................................................................... ........................................................................... Christen Pitts .................................................... Commander ...................................................... ........................................................................... ........................................................................... Dornier .............................................................. Embraer ............................................................ ........................................................................... Extra-Flugzeugbau ........................................... F.F.A ................................................................. H.A.L ................................................................ Helio Military ..................................................... Integrated Systems .......................................... King Engineering .............................................. Korean Air ........................................................ Lake .................................................................. Maule. ........................................................................... Mod Works ....................................................... Mooney ............................................................. PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 17–D Mushshak 500 B, S, U/Merlyn Products Conv. 500–E LA 250 Renegade Agricola Mexicana Quail 600 Mushshak F–250 Flamingo Pierre Robin HR–100/250 76 Duchess 76 Duchess C–24R Sierra or 200 Sierra Aircraft Aries T–250 BN–2 Islander BN–2A & BN–2B Islander BN–2A Islander Eagle 177 Cardinal 177 Cardinal 182–RG Skylane 182–S C–172RG Cutlass RG C–206 Stationair R–G Cardinal R–G Cardinal T182T Skylane TR–182 Turbo Skylane S–2S, S–2B 114 114B 114TC DO–28 EMB–201 Ipanema EMB–710 Corioca EMB–720 Minuano EMB–720 Minuano & EMB–721 Sertanejo EMB–721 Sertanejo Extra 300 FFA–2000 Eurotrainer HPT–32 H–250 Omega Angel Chang Gong–91 LA–4–200 Buccaneer MT–7–260 & M–7–260 MX–7–235 Star Rocket MX–7–235, MT–7–235 & M7–235 Trophy 212 Conversion 201 M–201 E:\FR\FM\16SER1.SGM 16SER1 Federal Register / Vol. 70, No. 179 / Friday, September 16, 2005 / Rules and Regulations Engine model Manufacturer IO–360–A1B6 ..................................................... IO–360–A3B6D .................................................. TIO–540–AF1B .................................................. ........................................................................... ........................................................................... ........................................................................... Moravan ........................................................... IO–540–K1J5 ..................................................... IO–540–S1A5 ..................................................... IO–540–AA1A5 .................................................. O–540–A1B5 ...................................................... Partenavia ........................................................ Piper ................................................................. ........................................................................... ........................................................................... ........................................................................... IO–540–J4A5 ..................................................... IO–540–C1B5 .................................................... TIO–540–C1A .................................................... ........................................................................... ........................................................................... ........................................................................... O–540–A1C5 ..................................................... O–540–A1D5 ..................................................... IO–540–D4A5 .................................................... ........................................................................... ........................................................................... ........................................................................... O–540–B2C5 ..................................................... O–540–B2B5 ...................................................... ........................................................................... ........................................................................... IO–360–C1C6 .................................................... IO–540–M1A5 .................................................... ........................................................................... ........................................................................... IO–540–K1G5 .................................................... IO–540–K1A5 ..................................................... IO–540–K1A5D .................................................. IO–540–K1G5D .................................................. ........................................................................... ........................................................................... ........................................................................... ........................................................................... IO–360–C1E6 .................................................... IO–540–K1G5 .................................................... O–360–A1H6 ..................................................... LO–360–A1H6 ................................................... IO–540–K1K5 ..................................................... ........................................................................... ........................................................................... ........................................................................... ........................................................................... ........................................................................... Robin ................................................................ Robinson .......................................................... Rockwell ........................................................... Ruschmeyer ..................................................... Saab ................................................................. Scottish Avia .................................................... Siai Marchetti ................................................... Siai Marchetti ................................................... Siai Marchetti ................................................... Siai Marchetti ................................................... Slingsby ............................................................ Socata .............................................................. O–540–F1B5 ...................................................... Aircraft model IO–540–C4D5D .................................................. ........................................................................... TIO–540–AB1AD ............................................... IO–540–AB1A5 .................................................. IO–540–K1H5 .................................................... IO–540–L1C5 ..................................................... ........................................................................... Stoddard Hamilton ........................................... Stoddard Hamilton ........................................... Swearingen Aircraft .......................................... Transava .......................................................... Valmet .............................................................. Wassmer .......................................................... Yoeman ............................................................ AEIO–360–A1B6 ................................................ Unsafe Condition (d) This AD results from 12 crankshaft failures in Lycoming model 360 and 540 series engines rated at 300 HP or lower. We are issuing this AD to prevent failure of the crankshaft, which could result in total engine power loss, in-flight engine failure, and possible loss of the airplane. Compliance (e) You are responsible for having the actions required by this AD performed within 50 hours time-in-service or 6 months after the VerDate Aug<31>2005 15:20 Sep 15, 2005 Jkt 205001 effective date of this AD, whichever is earlier, unless the actions have already been done. Engines Manufactured Before March 1, 1999 (f) If Lycoming Engines manufactured new, rebuilt, or overhauled your engine before March 1, 1999, and you haven’t had the crankshaft replaced, no further action is required. PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 54621 M–20–J M20J–201 M20M TLS Bravo Z143L Zlin Z242L Zlin P–68 Series Observer 600–A Aerostar 601–A, 601B & 601P Aerostar 602P Sequoia PA–23–235 Aztec & PA–24–250 Comanche PA–23–250 Aztec PA–23–250 Aztec PA–23–250 Aztec & PA–24–250 Comanche PA–23–250T Turbo Aztec PA–24–150 Comanche PA–24–250 Comanche PA–24–250 Comanche PA–24–260 Comanche PA–24–260 Comanche PA–25–235 Pawnee PA–28–235 Cherokee PA–28–235 Cherokee PA–28R–201 Arrow PA–31–300 Navajo PA–32–260 Cherokee 6 PA–32–300 & PA–32–301 Saratoga PA–32–300 Cherokee 6 PA–32–300 Cherokee 6 PA–32–300R Lance PA–32–301R Saratoga PA–34–200 Seneca I PA–36–300 Brave PA–44–180 PA–44–180 Seminole T–35 Pillan R–3000/235 R–44 114 MF–85 MFI–15 Safari or MFI–17 Supporter Bulldog S–205 S–208 & SF–260 SF–260 SF–260 Firefly T3A R–235 Rallye Cuerrier Rallye 235CA TB–20 Trinidad TB–200 TB–21 & TB–21–TC Trinidad TC Glasair Glasair III SX–300 T–300 Skyfarmer L–70 Vinka WA4–21 Aviation YA–1 AEIO–540, IO–540, O–540, and TIO–540 Series Engines Manufactured New or Rebuilt, Overhauled, or That Had a Crankshaft Installed After March 1, 1999 (g) For AEIO–540, IO–540, O–540, and TIO–540 series engines manufactured new or rebuilt, overhauled, or that had a crankshaft installed after March 1, 1999, do the following: (1) If Table 1 or Table 2 of Lycoming Mandatory Service Bulletin (MSB) No. 566, dated July 11, 2005, lists your engine serial E:\FR\FM\16SER1.SGM 16SER1 54622 Federal Register / Vol. 70, No. 179 / Friday, September 16, 2005 / Rules and Regulations number (SN), use Table 4 to verify the crankshaft SN. (2) If Table 4 of Lycoming MSB No. 566, dated July 11, 2005, lists your crankshaft SN, replace the crankshaft with a crankshaft that is not listed in Table 4 of Lycoming MSB No. 566, dated July 11, 2005. AEIO–360, IO–360, O–360, LIO–360, and LO–360 Series Engines Manufactured New or Rebuilt, Overhauled, or That Had a Crankshaft Installed After March 1, 1999 (h) For AEIO–360, IO–360, O–360, LIO– 360, and LO–360 series engines manufactured new or rebuilt, overhauled, or that had a crankshaft installed after March 1, 1999, do the following: (1) If Table 3 of Lycoming MSB No. 566, dated July 11, 2005, lists your engine SN, use Table 4 to verify the crankshaft SN. (2) If Table 4 of Lycoming MSB No. 566, dated July 11, 2005, lists your crankshaft SN, replace the crankshaft with a crankshaft that is not listed in Table 4 of Lycoming MSB No. 566, dated July 11, 2005. Prohibition Against Installing Certain Crankshafts (i) After the effective date of this AD, do not install any crankshaft that has a SN listed in Table 4 of Lycoming MSB No. 566, dated July 11, 2005, into any engine. Alternative Methods of Compliance (AMOCs) (j) The Manager, New York Aircraft Certification Office, has the authority to approve AMOCs for this AD if requested using the procedures found in 14 CFR 39.19. Related Information (k) None. Material Incorporated by Reference (l) You must use Lycoming Mandatory Service Bulletin No. 566, dated July 11, 2005, to perform the actions required by this AD. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Lycoming, 652 Oliver Street, Williamsport, PA 17701; telephone (570) 323–6181; fax (570) 327–7101, or on the Internet at https:// www.Lycoming.Textron.com for a copy of this service information. You may review copies at the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590–0001, on the Internet at https://dms.dot.gov, or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Burlington, Massachusetts, on September 9, 2005. Jay J. Pardee, Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 05–18323 Filed 9–15–05; 8:45 am] BILLING CODE 4910–13–P VerDate Aug<31>2005 15:20 Sep 15, 2005 Jkt 205001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2005–22430; Directorate Identifier 2005–NE–34–AD; Amendment 39– 14275; AD 2005–19–10] RIN 2120–AA64 Airworthiness Directives; Turbomeca Arrius 2 F Turboshaft Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for Turbomeca Arrius 2 F turboshaft engines. This AD requires removing from service certain serial number (SN) fuel control units (FCUs) or replacing the constant delta pressure diaphragm in those FCUs. This AD results from a report of an accident in July 2005 involving a Eurocopter EC120B helicopter. We are issuing this AD to prevent an uncommanded engine inflight shutdown on a single-engine helicopter, resulting in a forced autorotation landing or an accident. DATES: Effective October 3, 2005. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of October 3, 2005. We must receive any comments on this AD by November 15, 2005. ADDRESSES: Use one of the following addresses to comment on this AD: • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590– 0001. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Contact Turbomeca, 40220 Tarnos, France; telephone +33 05 59 74 40 00, fax +33 05 59 74 45 15, for the service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Christopher Spinney, Aerospace PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803–5299; telephone (781) 238–7175; fax (781) 238–7199. The Direction Generale de L’Aviation Civile (DGAC), which is the airworthiness authority for France, notified the FAA that an unsafe condition may exist on Turbomeca Arrius 2 F turboshaft engines. The DGAC advises that a Eurocopter EC120B helicopter powered by an Arrius 2 F turboshaft engine experienced an uncommanded in-flight engine shutdown. An increase in fuel flow led to an increase in gas generator and power turbine speeds. Turbine blades separated from the disk due to the overspeed. Turbomeca determined that the fuel flow increase was caused by an improperly assembled and subsequent failure of the constant delta pressure (delta P) diaphragm in the FCU. Only certain types of constant delta P diaphragms have been identified as being capable of being improperly assembled. Engine serial numbers that may have this type of constant delta P diaphragm are listed in Turbomeca Alert Mandatory Service Bulletin (MSB) No. A319 73 4825, dated August 3, 2005. The manufacturer is making spare FCUs available as fast as possible and has established a rotable pool of spares. After we reviewed the Turbomeca SB, we concluded that using the Turbomeca rotable pool of spares as soon as practicable effectively manages the risk of another failure of the uninspected engine population. To this end, we are requiring that FCUs identified in the Turbomeca SB be replaced as soon as practicable but not to exceed February 28, 2006. Because the practicable compliance time may be quite short for some operators and the rotable pool requires consistent participation, we are issuing this AD as final rule; request for comments. SUPPLEMENTARY INFORMATION: Relevant Service Information We have reviewed and approved the technical contents of Turbomeca Alert MSB No. A319 73 4825, dated August 3, 2005. That MSB lists the affected FCUs by SN and describes procedures for removing affected FCUs from service or replacing constant delta P diaphragms in those FCUs. The DGAC classified this service bulletin as mandatory and issued AD No. F–2005– 143, dated August 17, 2005, and AD No. F–2005–143 R1, dated August 31, 2005, in order to ensure the airworthiness of these Arrius 2 F turboshaft engines in France. E:\FR\FM\16SER1.SGM 16SER1

Agencies

[Federal Register Volume 70, Number 179 (Friday, September 16, 2005)]
[Rules and Regulations]
[Pages 54618-54622]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-18323]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2005-21864; Directorate Identifier 2005-NE-29-AD; 
Amendment 39-14276; AD 2005-19-11]
RIN 2120-AA64


Airworthiness Directives; Lycoming Engines (Formerly Textron 
Lycoming) AEIO-360, IO-360, O-360, LIO-360, LO-360, AEIO-540, IO-540, 
O-540, and TIO-540 Series Reciprocating Engines

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

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Lycoming Engines (formerly Textron Lycoming) AEIO-360, IO-360, 
O-360, LIO-360, LO-360, AEIO-540, IO-540, O-540, and TIO-540 series 
reciprocating engines rated at 300 horsepower (HP) or lower. This AD 
requires replacing certain crankshafts. This AD results from reports of 
12 crankshaft failures in Lycoming 360 and 540 series engines rated at 
300 HP or lower. We are issuing this AD to prevent failure of the 
crankshaft, which could result in total engine power loss, in-flight 
engine failure, and possible loss of the aircraft.

DATES: This AD becomes effective October 21, 2005. The Director of the 
Federal Register approved the incorporation by reference of certain

[[Page 54619]]

publications listed in the regulations as of October 21, 2005.

ADDRESSES: You can get the service information identified in this AD 
from Lycoming, 652 Oliver Street, Williamsport, PA 17701; telephone 
(570) 323-6181; fax (570) 327-7101, or on the Internet at https://
www.Lycoming.Textron.com.
    You may examine the AD docket on the Internet at https://dms.dot.gov 
or in Room PL-401 on the plaza level of the Nassif Building, 400 
Seventh Street, SW., Washington, DC.

FOR FURTHER INFORMATION CONTACT: Norm Perenson, Aerospace Engineer, New 
York Aircraft Certification Office, FAA, Engine & Propeller 
Directorate, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; 
telephone (516) 228-7337; fax (516) 794-5531.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 
with a proposed airworthiness directive (AD). The proposed AD applies 
to Lycoming Engines (formerly Textron Lycoming) AEIO-360, IO-360, O-
360, LIO-360, LO-360, AEIO-540, IO-540, O-540, and TIO-540 series 
reciprocating engines rated at 300 horsepower (HP) or lower. We 
published the proposed AD in the Federal Register on July 22, 2005 (70 
FR 42282). That action proposed to require replacing certain 
crankshafts within 50 hours time-in-service or 6 months after the 
effective date of the proposed AD, whichever is earlier.

Examining the AD Docket

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

Comments

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

Will Additional Engines and Crankshafts Be Affected in the Future

    One commenter asks if additional serial numbered engines and 
crankshafts will be affected in the future.
    At this time we do not anticipate that the affected population will 
increase, but Lycoming and the FAA are monitoring crankshaft 
performance.

Affected Engines and Crankshafts

    The same commenter asks why these engines and crankshafts are the 
only ones affected by the SB and AD.
    Both the previous AD (2002-19-03) and this AD advise that the 
affected population of engines and crankshafts were manufactured in a 
specific time period. We are addressing that time period.

Suspect Crankshafts Should Be Either Tested or Replaced

    One commenter states that suspect crankshafts should be either 
tested or replaced before further flight, because the problem with 
these crankshafts is similar to the problem that caused the crankshaft 
failures on the 540 engines.
    We disagree. The compliance interval in this AD is based on an 
assessment of operating stresses, service experience, and duty cycle of 
the affected engine population. The compliance interval differs from 
that imposed in AD 2002-19-03 due to differences in these parameters.

Request To Include Lycoming TIO-540-AE2A and Other Unspecified Engine 
Models

    One commenter requests that we include the Lycoming TIO-540-AE2A 
and other unspecified engine models in this AD. The commenter states 
that many of the TIO-540-AE2A engines have never been recalled or 
replaced yet should be, because recent litigation has shown that 
Lycoming's crankshaft end core sample test is insufficient.
    We disagree. We have seen no evidence that refutes the validity of 
the test. Further, AD 2002-19-03 (the previous AD) effective on 
September 20, 2002, described two groups of crankshafts. We required 
one crankshaft group to be removed before further flight, and we 
required the other crankshaft group to have a sample of the crankshaft 
material tested. The crankshafts in each group were selected based on 
our evaluation of the risk both groups presented. Crankshafts from 
either group may be installed in the TIO-540-AE2A engine model. No 
failures of crankshafts listed in either group have occurred since.

Conclusion

    We have carefully reviewed the available data, including the 
comments received, and determined that air safety and the public 
interest require adopting the AD as proposed.

Costs of Compliance

    We estimate that this AD will affect 1,128 engines installed on 
aircraft of U.S. registry. We estimate that it will take the following 
work hours to perform the inspection:

------------------------------------------------------------------------
                                                              Number of
             Type of  application               Work-hours     engines
                                                per engine     affected
------------------------------------------------------------------------
Helicopter...................................          12            200
Constant-Speed Propeller.....................           3            557
Fixed-Pitch Propeller........................           1.5          371
------------------------------------------------------------------------

    We also estimate that it will take about 33 work hours to replace 
the crankshaft. We estimate the average labor rate is $65 per work hour 
and that required parts for each engine will cost about $16,218. Based 
on these figures, we estimate the total cost of the AD to U.S. 
operators to be $18,594,724. Lycoming Engines informed us that they 
intend to supply the new parts at no charge, which may substantially 
reduce the estimated cost of this AD.

Authority for This Rulemaking

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

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;

[[Page 54620]]

    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and
    (3) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a summary of the costs to comply with this AD and 
placed it in the AD Docket. You may get a copy of this summary at the 
address listed under ADDRESSES.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the Federal Aviation Administration amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive:

2005-19-11 Lycoming Engines: Amendment 39-14276. Docket No. FAA-
2005-21864; Directorate Identifier 2005-NE-29-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective October 
21, 2005.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Lycoming Engines (Formerly Textron 
Lycoming) AEIO-360, IO-360, O-360, LIO-360, LO-360, AEIO-540, IO-
540, O-540, and TIO-540 series reciprocating engines, rated at 300 
horsepower (HP) or lower, manufactured new, rebuilt, overhauled 
after March 1, 1999, or that had a crankshaft installed after March 
1, 1999. These engines are installed on, but not limited to, the 
following aircraft:

------------------------------------------------------------------------
          Engine model               Manufacturer       Aircraft model
------------------------------------------------------------------------
IO-540-V4A5.....................  A.M.F.............  17-D Mushshak
                                  Aero Commander....  500 B, S, U/Merlyn
                                                       Products Conv.
IO-540-E1A5.....................  Aero Commander....  500-E
                                  Aerofab...........  LA 250 Renegade
                                  Aeronautica.......  Agricola Mexicana
                                                       Quail
IO-540-K1F5.....................  Aerostar..........  600
                                  Aircraft            Mushshak
                                   Manufacturing
                                   Factory.
O-540-E4A5......................  Aviamilano........  F-250 Flamingo
IO-540-C4B5.....................  Avions............  Pierre Robin HR-
                                                       100/250
LO-360-A1G6D....................  Beech.............  76 Duchess
O-360-A1G6D.....................  ..................  76 Duchess
                                                      C-24R Sierra or
                                                       200 Sierra
                                  Bellanca..........  Aircraft Aries T-
                                                       250
O-540-E4B5......................  Britten Norman....  BN-2 Islander
O-540-E4C5......................  ..................  BN-2A & BN-2B
                                                       Islander
IO-540-K1B5.....................  ..................  BN-2A Islander
                                  Celair............  Eagle
O-360-A1F6......................  Cessna............  177 Cardinal
O-360-A1F6D.....................  ..................  177 Cardinal
O-540-J3C5D.....................  ..................  182-RG Skylane
IO-540-AB1A5....................  ..................  182-S
O-360-F1A6......................  ..................  C-172RG Cutlass RG
IO-540-AC1A5....................  ..................  C-206 Stationair
                                                      R-G Cardinal
IO-360-A1B6D....................  ..................  R-G Cardinal
TIO-540-AK1A....................  ..................  T182T Skylane
O-540-L3C5D.....................  ..................  TR-182 Turbo
                                                       Skylane
AEIO-540-D4A5...................  Christen Pitts....  S-2S, S-2B
IO-540-T4B5D....................  Commander.........  114
IO-540-T4B5.....................  ..................  114B
TIO-540-AG1A....................  ..................  114TC
                                  Dornier...........  DO-28
IO-540-K1J5D....................  Embraer...........  EMB-201 Ipanema
O-540-B4B5......................  ..................  EMB-710 Corioca
                                                      EMB-720 Minuano
                                                      EMB-720 Minuano &
                                                       EMB-721 Sertanejo
                                                      EMB-721 Sertanejo
AEIO-540-L1B5...................  Extra-Flugzeugbau.  Extra 300
                                  F.F.A.............  FFA-2000
                                                       Eurotrainer
                                  H.A.L.............  HPT-32
O-540-A1A5......................  Helio Military....  H-250
AEIO-360-A1E6...................  Integrated Systems  Omega
IO-540-M1C5.....................  King Engineering..  Angel
                                  Korean Air........  Chang Gong-91
                                  Lake..............  LA-4-200 Buccaneer
O-540-J3A5......................  Maule.............
                                                      MT-7-260 & M-7-260
                                                      MX-7-235 Star
                                                       Rocket
IO-540-W1A5.....................  ..................  MX-7-235, MT-7-235
                                                       & M7-235
                                  Mod Works.........  Trophy 212
                                                       Conversion
IO-360-A3B6.....................  Mooney............  201
                                                      M-201

[[Page 54621]]

 
IO-360-A1B6.....................  ..................  M-20-J
IO-360-A3B6D....................  ..................  M20J-201
TIO-540-AF1B....................  ..................  M20M TLS Bravo
                                  Moravan...........  Z143L Zlin
                                                      Z242L Zlin
                                  Partenavia........  P-68 Series
                                                       Observer
IO-540-K1J5.....................  Piper.............  600-A Aerostar
IO-540-S1A5.....................  ..................  601-A, 601B & 601P
                                                       Aerostar
IO-540-AA1A5....................  ..................  602P Sequoia
O-540-A1B5......................  ..................  PA-23-235 Aztec &
                                                       PA-24-250
                                                       Comanche
                                                      PA-23-250 Aztec
IO-540-J4A5.....................  ..................  PA-23-250 Aztec
IO-540-C1B5.....................  ..................  PA-23-250 Aztec &
                                                       PA-24-250
                                                       Comanche
TIO-540-C1A.....................  ..................  PA-23-250T Turbo
                                                       Aztec
                                                      PA-24-150 Comanche
O-540-A1C5......................  ..................  PA-24-250 Comanche
O-540-A1D5......................  ..................  PA-24-250 Comanche
IO-540-D4A5.....................  ..................  PA-24-260 Comanche
                                                      PA-24-260 Comanche
O-540-B2C5......................  ..................  PA-25-235 Pawnee
O-540-B2B5......................  ..................  PA-28-235 Cherokee
                                                      PA-28-235 Cherokee
IO-360-C1C6.....................  ..................  PA-28R-201 Arrow
IO-540-M1A5.....................  ..................  PA-31-300 Navajo
                                                      PA-32-260 Cherokee
                                                       6
IO-540-K1G5.....................  ..................  PA-32-300 & PA-32-
                                                       301 Saratoga
IO-540-K1A5.....................  ..................  PA-32-300 Cherokee
                                                       6
IO-540-K1A5D....................  ..................  PA-32-300 Cherokee
                                                       6
IO-540-K1G5D....................  ..................  PA-32-300R Lance
                                                      PA-32-301R
                                                       Saratoga
IO-360-C1E6.....................  ..................  PA-34-200 Seneca I
IO-540-K1G5.....................  ..................  PA-36-300 Brave
O-360-A1H6......................  ..................  PA-44-180
LO-360-A1H6.....................  ..................  PA-44-180 Seminole
IO-540-K1K5.....................  ..................  T-35 Pillan
                                  Robin.............  R-3000/235
O-540-F1B5......................  Robinson..........  R-44
                                  Rockwell..........  114
                                  Ruschmeyer........  MF-85
                                  Saab..............  MFI-15 Safari or
                                                       MFI-17 Supporter
                                  Scottish Avia.....  Bulldog
                                  Siai Marchetti....  S-205
                                  Siai Marchetti....  S-208 & SF-260
                                  Siai Marchetti....  SF-260
                                  Siai Marchetti....  SF-260
                                  Slingsby..........  Firefly T3A
                                  Socata............  R-235 Rallye
                                                       Cuerrier
                                                      Rallye 235CA
IO-540-C4D5D....................  ..................  TB-20 Trinidad
                                                      TB-200
TIO-540-AB1AD...................  ..................  TB-21 & TB-21-TC
                                                       Trinidad TC
IO-540-AB1A5....................  Stoddard Hamilton.  Glasair
IO-540-K1H5.....................  Stoddard Hamilton.  Glasair III
IO-540-L1C5.....................  Swearingen          SX-300
                                   Aircraft.
                                  Transava..........  T-300 Skyfarmer
AEIO-360-A1B6...................  Valmet............  L-70 Vinka
                                  Wassmer...........  WA4-21
                                  Yoeman............  Aviation YA-1
------------------------------------------------------------------------

Unsafe Condition

    (d) This AD results from 12 crankshaft failures in Lycoming 
model 360 and 540 series engines rated at 300 HP or lower. We are 
issuing this AD to prevent failure of the crankshaft, which could 
result in total engine power loss, in-flight engine failure, and 
possible loss of the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within 50 hours time-in-service or 6 months after the 
effective date of this AD, whichever is earlier, unless the actions 
have already been done.

Engines Manufactured Before March 1, 1999

    (f) If Lycoming Engines manufactured new, rebuilt, or overhauled 
your engine before March 1, 1999, and you haven't had the crankshaft 
replaced, no further action is required.

AEIO-540, IO-540, O-540, and TIO-540 Series Engines Manufactured New or 
Rebuilt, Overhauled, or That Had a Crankshaft Installed After March 1, 
1999

    (g) For AEIO-540, IO-540, O-540, and TIO-540 series engines 
manufactured new or rebuilt, overhauled, or that had a crankshaft 
installed after March 1, 1999, do the following:
    (1) If Table 1 or Table 2 of Lycoming Mandatory Service Bulletin 
(MSB) No. 566, dated July 11, 2005, lists your engine serial

[[Page 54622]]

number (SN), use Table 4 to verify the crankshaft SN.
    (2) If Table 4 of Lycoming MSB No. 566, dated July 11, 2005, 
lists your crankshaft SN, replace the crankshaft with a crankshaft 
that is not listed in Table 4 of Lycoming MSB No. 566, dated July 
11, 2005.

AEIO-360, IO-360, O-360, LIO-360, and LO-360 Series Engines 
Manufactured New or Rebuilt, Overhauled, or That Had a Crankshaft 
Installed After March 1, 1999

    (h) For AEIO-360, IO-360, O-360, LIO-360, and LO-360 series 
engines manufactured new or rebuilt, overhauled, or that had a 
crankshaft installed after March 1, 1999, do the following:
    (1) If Table 3 of Lycoming MSB No. 566, dated July 11, 2005, 
lists your engine SN, use Table 4 to verify the crankshaft SN.
    (2) If Table 4 of Lycoming MSB No. 566, dated July 11, 2005, 
lists your crankshaft SN, replace the crankshaft with a crankshaft 
that is not listed in Table 4 of Lycoming MSB No. 566, dated July 
11, 2005.

Prohibition Against Installing Certain Crankshafts

    (i) After the effective date of this AD, do not install any 
crankshaft that has a SN listed in Table 4 of Lycoming MSB No. 566, 
dated July 11, 2005, into any engine.

Alternative Methods of Compliance (AMOCs)

    (j) The Manager, New York Aircraft Certification Office, has the 
authority to approve AMOCs for this AD if requested using the 
procedures found in 14 CFR 39.19.

Related Information

    (k) None.

Material Incorporated by Reference

    (l) You must use Lycoming Mandatory Service Bulletin No. 566, 
dated July 11, 2005, to perform the actions required by this AD. The 
Director of the Federal Register approved the incorporation by 
reference of this service bulletin in accordance with 5 U.S.C. 
552(a) and 1 CFR part 51. Contact Lycoming, 652 Oliver Street, 
Williamsport, PA 17701; telephone (570) 323-6181; fax (570) 327-
7101, or on the Internet at https://www.Lycoming.Textron.com for a 
copy of this service information. You may review copies at the 
Docket Management Facility; U.S. Department of Transportation, 400 
Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 
20590-0001, on the Internet at https://dms.dot.gov, or at the 
National Archives and Records Administration (NARA). For information 
on the availability of this material at NARA, call 202-741-6030, or 
go to: https://www.archives.gov/federal-register/cfr/ibr-
locations.html.

    Issued in Burlington, Massachusetts, on September 9, 2005.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 05-18323 Filed 9-15-05; 8:45 am]
BILLING CODE 4910-13-P

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