FEDERAL AVIATION ADMINISTRATION AIRWORTHINESS DIRECTIVES SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS BIWEEKLY 2005-01 This electronic copy may be printed and used in lieu of the FAA biweekly paper copy. U.S. Department of Transportation Federal Aviation Administration Regulatory Support Division Delegation and Airworthiness Programs Branch, AIR-140 P. O. Box 26460 Oklahoma City, OK 73125-0460 FAX 405-954-4104
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SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS AD No. Information Manufacturer Applicability Info: E - Emergency; COR - Correction; S - Supersedes; R - Revision; - See AD for additional information; Biweekly 2005-01 2004-26-09 Rolls-Royce Corporation Engine: 250-B17, -B17B, -B17C, -B17D, -B17E, 250-C20, -C20B, -C20F, -C20J, -C20S, and -C20W Series Turboprop and Turboshaft 2004-26-11 Bell Helicopter Textron Canada Rotorcraft: 222, 222B, 222U, 230, 430 2005-01-04 S 98-15-13 Raytheon Aircraft Company 65-90, 65-A90, B90, C90, C90A, C90B, E90, F90, H90, 100, A100, A100-1, (RU-21J), B100, 200, 200C, 200CT, 200T, A200, A200C, A200CT, B200, B200C, B200CT, B200T, 300, B300, B300C, 99, 99A, A99,, A99A, B99, C99 2005-01-10 S 74-06-01 The New Piper Aircraft, Inc PA-23-235, PA-23-250, and PA-E23-250 2005-01-11 Pilatus Aircraft Ltd. PC-12 and PC-12/45 3
BW 2005-01 ROLLS-ROYCE CORPORATION AIRWORTHINESS DIRECTIVE ENGINE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2004-26-09 Rolls-Royce Corporation (formerly Allison Engine Company, Allison Gas Turbine Division, and Detroit Diesel Allison): Amendment 39-13921. Docket No. FAA-2004-18515; Directorate Identifier 2004-NE-12-AD. Effective Date Affected ADs (a) This airworthiness directive (AD) becomes effective February 8, 2005. (b) None. Applicability (c) This AD applies to Rolls-Royce Corporation (formerly Allison Engine Company, Allison Gas Turbine Division, and Detroit Diesel Allison) 250-B17, -B17B, -B17C, -B17D, -B17E, 250-C20, -C20B, -C20F, -C20J, -C20S, and -C20W series turboprop and turboshaft engines with the compressor adaptor couplings installed listed in the following Table 1: TABLE 1. AFFECTED COMPRESSOR ADAPTOR COUPLINGS Manufacturer Affected part numbers Alcor Engine Company (Alcor) P/Ns 23039791AL. 23039791AL 1/ 2/ 3. EXTEX Ltd. (EXTEX) A23039791. E23039791. E23039791 1/ 2/ 3. EH23039791. EH23039791 1/ 2/ 3. Rolls-Royce Corporation (RRC) 23039791 1/ 2/ 3. Superior Air Parts (SAP) A23039791. These engines are installed on, but not limited to, the aircraft in the following Table 2: 4
2004-26-09 2 Unsafe Condition TABLE 2. APPLICABLE AIRCRAFT Manufacturer Models Helicopters Agusta A109, A109A, A109A II. Bell 206A, 207B, 206L. Enstrom TH 28, 480, 480B. Eurocopter France AS355E, AS355F, AS355F1, AS355F2. Eurocopter Deutschland BO 105C, BO 105S. MDHI 369D, 369E, 369H, 369HM, 369HS, 369HE. Schweizer 269D. Airplanes B N Group Ltd. BN 2T. (d) This AD results from nine reports of engine shutdown caused by compressor adaptor coupling failure. 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. Alcor Compressor Adaptor Couplings (f) Remove Alcor compressor adaptor couplings, P/Ns 23039791AL, 23039791AL-1, -2, and -3 from service as follows: (1) For couplings with 600 or more operating hours-since-new as of the effective date of this AD, or the operating hours are unknown and cannot be determined, remove couplings from service at next access but not to exceed 50 additional operating hours. (2) For couplings with fewer than 600 operating hours-since-new on the effective date of this AD, remove couplings from service at next access but not to exceed 649 operating hours-since-new. EXTEX and SAP Compressor Adaptor Couplings (g) Remove EXTEX and SAP compressor adaptor couplings, P/Ns A23039791, E23039791, E23039791-1, -2, and -3, EH23039791, and EH23039791-1, -2, and -3, from service as follows: (1) For couplings with operating hours that are unknown and cannot be determined, remove couplings from service at next access but not to exceed 50 additional operating hours. (2) For couplings with 600 or more operating hours-since-new as of the effective date of this AD, remove couplings from service at next access but not to exceed 100 additional operating hours. (3) For couplings with fewer than 600 operating hours-since-new on the effective date of this AD, remove couplings from service at next access but not to exceed 150 additional operating hours. 5
2004-26-09 3 RRC Compressor Adaptor Couplings (h) Remove RRC compressor adaptor couplings, P/Ns 23039791-1, -2, and -3 from service next time the compressor rotor is disassembled for any reason, but not later than March 1, 2012. Installation Requirements for Compressor Adaptor Couplings (i) Machine the compressor impeller as follows: (1) Select and measure the pilot outside diameter (OD) of a new larger dash size coupling. (2) For example, if a -1 coupling was removed, a -2 coupling must be installed. (3) If a -3 coupling is removed, a new impeller is required. (4) Machine the inside diameter (ID) of the compressor impeller to achieve a fit of 0.0000 to - 0.0013 inch. No fretting is allowed on the impeller after machining. (5) Due to previous fretting, an impeller with a -1 coupling removed might have to be machined for a -3 coupling. Plating of the impeller ID is not allowed. (6) Fluorescent penetrant inspect the impeller. (7) Install a new compressor adaptor coupling, P/N 23076559-2 or -3; or (8) If a new impeller is installed, then install compressor adaptor coupling, P/N 23076559-1. (9) Heating of the impeller per the engine overhaul manual is required to install the coupling to achieve the target fit specified in the following Table 3: TABLE 3. IMPELLER-TO-COUPLING TARGET FIT New adaptor Adaptor OD Fit (interference) (i) 23076559 1 0.9000 to 0.9008 inch 0.0000 to 0.0013 inch. (ii) 23076559 2 0.9020 to 0.9028 inch 0.0000 to 0.0013 inch. (iii) 23076559 3 0.9040 to 0.9048 inch 0.0000 to 0.0013 inch. (10) The mating surfaces of the impeller and coupling must not have any fretting. Do not install a -1 coupling into a used impeller. Definition (j) For the purposes of this AD, next access is defined as when the compressor module is separated from the engine and disassembled for any reason. Alternative Methods of Compliance (k) The Manager, Los Angeles Aircraft Certification Office, has the authority to approve alternative methods of compliance for Alcor, EXTEX, and SAP adaptor couplings addressed in this AD if requested using the procedures found in 14 CFR 39.19. The Manager, Chicago Aircraft Certification Office, has the authority to approve alternative methods of compliance for RRC adaptor couplings addressed in this AD if requested using the procedures found in 14 CFR 39.19. Related Information (l) Alcor SLB No. 814-3-1, Revision C, dated April 28, 2004, EXTEX Alert Service Bulletin T-081, Revision B, dated May 4, 2004, and RRC CEB-A-1392 and CEB-A-1334, dated September 9, 2003, pertain to the subject of this AD. 6
2004-26-09 4 Issued in Burlington, Massachusetts, on December 23, 2004. Jay J. Pardee, Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 05-14 Filed 1-3-05; 8:45 am] BILLING CODE 4910-13-P 7
BW 2005-01 BELL HELICOPTER TEXTRON CANADA AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS AD 2004-26-11 Bell Helicopter Textron Canada: Amendment 39-13923. Docket No. FAA-2004-19969; Directorate Identifier 2004-SW-43-AD. Applicability: The following helicopter models, identified by serial number and with the following part number (P/N) tail rotor blade (blade), installed, certificated in any category. Model Serial No. Blade P/N 222 47006 through 47089 222 016 001 123, 127, 131, and 135. 222B 47131 through 47156 222 016 001 123, 127, 131, and 135. 222U 47501 through 47574 222 016 001 123, and 131. 230 23001 through 23038 222 016 001 123, and 131. 430 49001 through 49105 222 016 001 123, and 131. Compliance: Required as indicated. To detect a crack in the blade and prevent loss of the blade and subsequent loss of control of the helicopter, accomplish the following: (a) Within 3 hours time-in-service (TIS) and at intervals not to exceed 3 hours TIS, clean and visually check both sides of each blade for a crack in the paint in the areas shown in Figure 1 of this AD. An owner/operator (pilot), holding at least a private pilot certificate, may perform this visual check and must enter compliance with this paragraph into the helicopter maintenance records by following 14 CFR sections 43.11 and 91.417(a)(2)(v). 8
2004-26-11 2 Note 1: Bell Helicopter Textron Alert Service Bulletins 222-04-100, 222U-04-71, 230-04-31, and 430-04-32, all dated August 27, 2004, pertain to the subject of this AD. 9
2004-26-11 3 (b) If a crack is found in the paint while complying with paragraph (a) of this AD, before further flight, inspect the blade by removing the blade and by abrading the area and following the other requirements in paragraph (c) of this AD. (c) Within the next 50 hours TIS, unless accomplished previously, and at intervals not to exceed 50 hours TIS, clean the blade by wiping down both surfaces of each blade in the inspection area depicted in Figure 1 of this AD using aliphatic naptha (C-305) or detergent (C-318) or equivalents. Using a 10X or higher power magnifying glass, visually inspect both sides of the blade in the areas depicted in Figure 1 of this AD. (1) If even a crack is found in the paint, before further flight, remove the blade. (2) Remove the paint to the bare metal in the area of the suspected crack by using Plastic Metal Blasting (PMB) or a nylon web abrasive pad. Abrade the blade surface in a span-wise direction only. Note 2: PMB may cause damage to helicopter parts if performed by untrained personnel. BHT-ALL-SPM, chapter 3, paragraph 3-24 pertains to the subject of this AD. (3) Using a 10X or higher power magnifying glass, inspect the blade for a crack. (i) If a crack is found, before further flight, replace the blade with an airworthy blade. (ii) If no crack is found in the blade surface, refinish the blade by applying one coat of MIL-P- 23377 or MIL-P-85582 Epoxy Polyamide Primer so that the primer overlaps the existing coats just beyond the abraded area. Let the area dry for 30 minutes to 1 hour. Then, apply one sealer coat of Polyurethane MILC85285 TYI CL2, color Number 27925 (semi-gloss white) per Fed. Std. 595. Reinstall the blade. Note 3: BHT-ALL-SPM, chapter 4, pertains to painting. (d) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Safety Management Group, FAA, for information about previously approved alternative methods of compliance. (e) Special flight permits may be issued by following 14 CFR 21.197 and 21.199 to operate the helicopter to a location where the requirements of this AD can be accomplished provided you do not find a crack in the paint during a check or inspection. (f) This amendment becomes effective January 18, 2005. Note 4: The subject of this AD is addressed in Transport Canada (Canada) Airworthiness Directive CF-2004-21, dated October 28, 2004. Issued in Fort Worth, Texas, on December 23, 2004. Kim Smith, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 04-28628 Filed 12-30-04; 8:45 am] BILLING CODE 4910-13-P 10
BW 2005-01 RAYTHEON AIRCRAFT COMPANY AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2005-01-04 Raytheon Aircraft Company: Amendment 39-13928; Docket No. FAA-2004-19089; Directorate Identifier 2000-CE-38-AD. When Does This AD Become Effective? (a) This AD becomes effective on February 22, 2005. What Other ADs Are Affected by This Action? (b) This AD supersedes AD 98-15-13, Amendment 39-10664. What Airplanes Are Affected by This AD? (c) This AD affects the following airplane models and serial numbers that are certificated in any category: Model Series (1) 65 90 LJ 1 through LJ 75, and LJ 77 through LJ 113. (2) 65 A90 LJ 76, LJ 114 through LJ 317, and LJ 178A. (3) B90 LJ 318 through LJ 501. (4) C90 LJ 502 through LJ 1062. (5) C90A LJ 1063 through LJ 1287, LJ 1289 through LJ 1294, and LJ 1296 through LJ 1299. (6) C90B LJ 1288, LJ 1295, and LJ 1300 through LJ 1445. (7) E90 LW 1 through LW 347. (8) F90 LA 2 through LA 236. (9) H90 LL 1 through LL 61. (10) 100 B 2 through B 89, and B 93. (11) A100 B 1, B 90 through B 92, B 94 through B 204, and B 206 through B 247. (12) A100 1 (RU 21J) BB 3 through BB 5. (13) B100 BE 1 through BE 137. 11
2005-01-04 2 (14) 200 BB 2, BB 6 through BB 185, BB 187 through BB 202, BB 204 through BB 269, BB 271 through BB 407, BB 409 through BB 468, BB 470 through BB 488, BB 490 through BB 509, BB 511 through BB 529, BB 531 through BB 550, BB 552 through BB 562, BB 564 through BB 572, BB 574 through BB 590, BB 592 through BB 608, BB 610 through BB 626, BB 628 through BB 646, BB 648 through BB 664, BB 735 through BB 792, BB 794 through BB 797, BB 799 through BB 822, BB 824 through BB 828, BB 830 through BB 853, BB 872, BB 873, BB 892, BB 893, and BB 912. (15) 200C BL 1 through BL 23, and BL 25 through BL 36. (16) 200CT BN 1. (17) 200T BT 1 through BT 22, and BT 28. (18) A200 BC 1 through BC 75, and BD 1 through BD 30. (19) A200C BJ 1 through BJ 66. (20) A200CT BP 1, BP 7 through BP 11, BP 22, BP 24 through BP 63, FC 1 through FC 3, FE 1 through FE 36, and GR 1 through GR 19. (21) B200 BB 829, BB 854 through BB 870, BB 874 through BB 891, BB 894, BB 896 through BB 911, BB 913 through BB 990, BB 992 through BB 1051, BB 1053 through BB 1092, BB 1094, BB 1095, BB 1099 through BB 1104, BB 1106 through BB 1116, BB 1118 through BB 1184, BB 1186 through BB 1263, BB 1265 through BB 1288, BB 1290 through BB 1300, BB 1302 through BB 1425, BB 1427 through BB 1447, BB 1449, BB 1450, BB 1452, BB 1453, BB 1455, BB 1456, and BB 1458 through BB 1536. (22) B200C BL 37 through BL 57, BL 61 through BL 140, BU 1 through BU 10, BV 1 through BV 12, and BW 1 through BW 21. (23) B200CT BN 2 through BN 4, BU 11, BU 12, FG 1, and FG 2. (24) B200T BT 23 through BT 27, and BT 29 through BT 38. (25) 300 FA 1 through BA 230, and FF 1 through FF 19. (26) B300 FL 1 through FL 141. (27) B300C FM 1 through FM 9, and FN 1. (28) 99, 99A, A99, U 1 through U 49, U 51 through U 145, and U 147. A99A (29) B99 U 146, and U 148 through U 164. (30) C99 U 50, and U 165 through U 239. What Is the Unsafe Condition Presented in This AD? (d) This AD is the result of blockage of fuel hose due to hose delamination. The actions specified in this AD are intended to prevent fuel flow interruption, which could lead to uncommanded loss of engine power and loss of control of the airplane. What Must I Do To Address This Problem? (e) To address this problem, you must do the following: 12
Actions Compliance Procedures For all affected airplanes other than Models 99, 99A, A99, A99A, B99, and C99: Within 200 hours time-in-service (TIS) after August 28, 1998 (the effective date of AD 98 15 13). For all affected Models 99, 99A, A99, A99A, B99, and C99 airplanes: Within the next 200 hours TIS after February 22, 2005 (the effective date of this AD). (1) For airplanes manufactured prior to January 1, 1994, check airplane maintenance records for any MIL-H 6000B fuel hose replacement from January 1, 1994, up to and including the effective date of this AD. (2) If the airplane records show that a MIL H 6000B fuel hose has been replaced, inspect the airplane fuel hoses for a 3 / 8 -inch-wide red or orange-red, length-wise stripe, with manufacturer s code, 94519, printed periodically along the line in red letters on one side. The hoses have a spiral or diagonal outer wrap with a fabric-type texture on the rubber surface. (3) Replace any fuel hose that matches the description in paragraph (e)(2) of this AD with an FAA-approved MIL H 6000B fuel hose that has a criss-cross or braided external wrap. For all affected airplanes other than the Models 99, 99A, A99, A99A, B99, and C99: Within 200 hours TIS after August 28, 1998 (the effective date of AD 98 15 13). For all affected Models 99, 99A, A99, A99A, B99, and C99 airplanes: Within the next 200 hours TIS after February 22, 2005 (the effective date of this AD). For all affected airplanes other than the Models 99, 99A, A99, A99A, B99, and C99: Within 200 hours TIS after August 28, 1998 (the effective date of AD 98 15 13). For all affected Models 99, 99A, A99, A99A, B99, and C99 airplanes: Within the next 200 hours TIS after February 22, 2005 (the effective date of this AD). 2005-01-04 3 Documented compliance with AD 98 15 13 or follow PART II of the ACCOMPLISHMENT INSTRUCTIONS section in Raytheon Aircraft Mandatory Service Bulletin SB 2718, Revision 1, dated June 1997; or Revision 2, dated April 2000. An owner/operator holding at least a private pilot certificate as authorized by section 43.7 of the Federal Aviation Regulations 914 CFR 43.7), and must be entered into the aircraft records showing compliance with this AD in accordance with section 43.7 of the Federal Aviation Regulations (14 CFR 43.9) can accomplish paragraph (e)(1) required by this AD. Documented compliance with AD 98 15 13 or follow PART II of the ACCOMPLISHMENT INSTRUCTIONS Section in Raytheon Aircraft Mandatory Service Bulletin SB 2718, Revision 1, dated June 1997; or Revision 2, dated April 2000. Documented compliance with AD 98 15 13 or follow PART II of the ACCOMPLISHMENT INSTRUCTIONS Section in Raytheon Aircraft Mandatory Service Bulletin SB 2718, Revision 1, dated June 1997; or Revision 2, dated April 2000. 13
2005-01-04 4 (4) For Raytheon Models C90A, B200, and B300 airplanes that were manufactured on January 1, 1994, and after, replace the MIL H 6000B fuel hoses. (5) Do not install a rubber fuel hose having spiral or diagonal external wrap with a 3 / 8 -inch-wide red or orange-red, length-wise stripe running down the side of the hose, with the manufacturer s code, 94519, printed periodically along the line in red letters on any of the affected airplanes. Within 200 hours TIS after August 28, 1998 (the effective date of AD 98 15 13). As of February 22, 2005 (the effective date of this AD). Documented compliance with AD 98 15 13 or follow PART I of the ACCOMPLISHMENT INSTRUCTIONS Section in Raytheon Aircraft Mandatory Service Bulletin SB 2718, Revision 1, dated June 1997; or Revision 2, dated April 2000. Not applicable. May I Request an Alternative Method of Compliance? (f) You may request a different method of compliance or a different compliance time for this AD by following the procedures in 14 CFR 39.19. Unless FAA authorizes otherwise, send your request to your principal inspector. The principal inspector may add comments and will send your request to the Manager, Standards Office, Small Airplane Directorate, FAA. For information on any already approved alternative methods of compliance, contact Jeffrey A. Pretz, Aerospace Engineer, ACE-116W, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946-4153; facsimile: (316) 946-4407. Does This AD Incorporate Any Material by Reference? (g) You must do the actions required by this AD following the instructions in Raytheon Aircraft Mandatory Service Bulletin SB 2718, Revision 1, dated June 1997; or Revision 2, dated April 2000. 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. To get a copy of this service information, contact Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 67201-0085; telephone: (800) 625-7043. To review copies of this service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html or call (202) 741-6030. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590-001 or on the Internet at http://dms.dot.gov. The docket number is FAA- 2004-19089. Issued in Kansas City, Missouri, on December 27, 2004. William J. Timberlake, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-35 Filed 1-5-05; 8:45 am] BILLING CODE 4910-13-P 14
BW 2005-01 THE NEW PIPER AIRCRAFT, INC.: AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2005-01-10 The New Piper Aircraft, Inc.: Amendment 39-13934; Docket No. FAA-2004-18597; Directorate Identifier 2004-CE-21-AD. When Does This AD Become Effective? (a) This AD becomes effective on February 22, 2005. What Other ADs Are Affected by This Action? (b) This AD supersedes AD 74-06-01. What Airplanes Are Affected by This AD? (c) This AD affects Models PA-23-235, PA-23-250, and PA-E23-250 airplanes, all serial numbers, that are (1) certificated in any category; and (2) equipped with Garrett Aviation Services (Garrett) (formerly AiResearch) turbosuperchargers installed under supplemental type certificate (STC) SA852WE, SA909WE, or SA978WE; or installed under The New Piper, Inc. (Piper) Aircraft Drawing Number 32016. Note: Piper manufactured the majority of affected airplanes with the turbocharger system. The turbocharger system installed under Piper Aircraft Drawing Number 32016 (STC SA909WE) was a factory option on the Piper Model PA-23-250 or PA-E23-250 with serial numbers 27-2505 through 27-3943. What is the Unsafe Condition Presented in This AD? (d) This AD is the result of a report of a fatal accident related to the breakdown of the turbocharger oil reservoir following a fire in the engine nacelle. The actions specified in this AD are intended to prevent turbosupercharger oil reservoirs with inadequate fire resistance from failing when exposed to flame or exhaust gases. This failure could lead to an in-flight fire within the nacelle area penetrating the firewall and subsequent failure of the wing spar. What Must I do to Address This Problem? (e) To address this problem, you must do the following: 15
2005-01-10 2 Actions Compliance Procedures Within the next 100 hours timein-service (TIS) after February 22, 2005 (the effective date of this AD), unless already done. (1) For Any turbosupercharger installation under supplemental type certificate (STC) SA852WE, SA909WE, or SA978WE: (2) For Any turbosupercharger installation under Piper Aircraft Drawing Number 32016: (3) For Any turbosupercharger installation under STC SA852WE, SA909WE, Or SA978WE; or Piper Aircraft Drawing Number 32016: Do not install any oil reservoir (P/N 286 P23 028 81 or 286 P23 028 111, Or FAAapproved equivalent P/N). Do not install any oil reservoir hose that is not fire-shielded. Within the next 100 hours TIS after February 22, 2005 (the effective date of this AD), unless already done. As of February 22, 2005 (the effective date of this AD). May I Request an Alternative Method of Compliance? Follow the procedures in Garrett Aviation Service Bulletin No. 1002143, Revision A, dated June 18, 2004. (i) Replace any oil reservoir (part number (P/N) 286 P23 028 81 or 286 P23 028 111, or FAA-approved equivalent P/N) with a fireproof oil tank (P/N 10ND79200 1 or 10ND79200 3, or FAA-approved equivalent P/N); and (ii) Replace the installed oil reservoir hoses with fire-shielded hoses. Follow the procedures in The New Piper Aircraft, Inc. Vendor Service Publication No. 166, dated August 20, 2004 and the procedures in Garrett Aviation Service Bulletin No. 1002143, Revision A, dated June 18, 2004. (i) Replace any oil reservoir (P/N 286 P23 028 81 or 286 P23 028 111, or FAA-approved equivalent P/N) with a fireproof oil tank (P/N 10ND79200 1 or 10ND79200 3, or FAAapproved equivalent P/N); and (ii) Replace the installed oil reservoir hoses with fire-shielded hoses. Not Applicable. (f) You may request a different method of compliance or a different compliance time for this AD by following the procedures in 14 CFR 39.19. Unless FAA authorizes otherwise, send your request to your principal inspector. The principal inspector may add comments and will send your request to the Manager, Los Angeles Aircraft Certification Office (ACO), FAA. For information on any already approved alternative methods of compliance, contact Roger Pesuit, Aerospace Engineer, FAA, Los Angeles ACO, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; telephone: (562) 627-5251; facsimile: (562) 627-5210. 16
2005-01-10 3 Does This AD Incorporate Any Material by Reference? (g) You must do the actions required by this AD following the instructions in The New Piper Aircraft, Inc. Vendor Service Publication No. 166, dated August 20, 2004, and the procedures in Garrett Aviation Service Bulletin No. 1002143, Revision A, dated June 18, 2004. The Director of the Federal Register approved the incorporation by reference of these service bulletins in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of this service information, contact: (for any installation under STC SA852WE, SA909WE, or SA978WE) The Nordam Group Nacelle/Thrust Reverser Systems Division, 6911 N. Whirlpool Drive, Tulsa, OK 74117 telephone: (918) 878-4000; facsimile: (918) 878-4808; and (for any installation under Piper Aircraft Drawing Number 32016) The New Piper Aircraft, Inc., 2926 Piper Drive, Vero Beach, Florida, 32960; and The Nordam Group Nacelle/Thrust Reverser Systems Division 6911 N. Whirlpool Drive, Tulsa, OK 74117 telephone: (918) 878-4000; facsimile: (918) 878-4808. To review copies of this service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html or call (202) 741-6030. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590-001 or on the Internet at http://dms.dot.gov. The docket number is FAA-2004-18597. Issued in Kansas City, Missouri, on December 28, 2004. David A. Downey, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-184 Filed 1-6-05; 8:45 am] BILLING CODE 4910-13-P 17
BW 2005-01 PILATUS AIRCRAFT LTD. AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2005-01-11 Pilatus Aircraft Ltd.: Amendment 39-13935; Docket No. FAA-2004-19221; Directorate Identifier 2004-CE-28-AD. When Does This AD Become Effective? (a) This AD becomes effective on February 22, 2005. What Other ADs Are Affected by This Action? (b) None. What Airplanes Are Affected by This AD? (c) This AD affects Models PC-12 and PC-12/45 airplanes, all serial numbers, that are certificated in any category. What Is the Unsafe Condition Presented in This AD? (d) This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. The actions specified in this AD are intended to prevent failure of the MLG actuator caused by an incorrect heat treating process, which could result in loss of hydraulic extension/retraction of the MLG. This failure could lead to loss of control during ground operations. What Must I Do To Address This Problem? (e) To address this problem, you must do the following: Actions Compliance Procedures Within 90 days after February 22, 2005 (the effective date of this AD), unless already done. (1) Check the airplane logbook to ensure that no main landing gear (MLG) actuator (part number (P/N) 960.30.01.103) with serial numbers (SN) 830E through 881E is installed. The owner/operator holding at least a private pilot certificate as authorized by section 43.7 of the Federal Aviation Regulations (14 CFR 43.7) may do this check. 18
2005-01-11 2 (2) If you can positively determine that no MLG actuator (P/N 960.30.01.103) with SN 830E through 881E is installed, then no further action is required. (3) If you cannot positively determine that no MLG actuator (P/N 960.30.01.103) with SN 830E through 881E is installed, then inspect any MLG actuator (P/N 960.30.01.103) for SN 830E through 881E. (4) If any MLG actuator (P/N 960.30.01.103) with SN 830E through 881E is found during the inspection required by paragraph (e)(3) of this AD, replace the MLG actuator with a P/N 960.30.01.103 actuator that has a SN other than 830E through 881E. (5) Do not install any MLG actuator (P/N 960.30.01.103) with SN 830E through 881E. Not Applicable Within 90 days after February 22, 2005 (the effective date of this AD), unless already done. Before further flight after the inspection required by paragraph (e)(3) of this AD in which any actuator with SN 830E through 881E is found. As of February 22, 2005 (the effective date of this AD). Make an entry in the aircraft records showing compliance with paragraphs (e)(1) and (e)(2) of this AD per section 43.9 of the Federal Aviation Regulations (14 CFR 43.9). Follow the Accomplishment Instructions Aircraft section in Pilatus PC 12 Service Bulletin No. 32 017, dated August 3, 2004. Follow the Accomplishment Instructions Aircraft section in Pilatus PC 12 Service Bulletin No. 32 017, dated August 3, 2004. Not Applicable. May I Request an Alternative Method of Compliance? (f) You may request a different method of compliance or a different compliance time for this AD by following the procedures in 14 CFR 39.19. Unless FAA authorizes otherwise, send your request to your principal inspector. The principal inspector may add comments and will send your request to the Manager, Standards Office, Small Airplane Directorate, FAA. For information on any already approved alternative methods of compliance, contact Doug Rudolph, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4059; facsimile: (816) 329-4090. Is There Other Information That Relates to This Subject? AD. (g) Swiss AD Number HB 2004-330, dated August 18, 2004, also addresses the subject of this Does This AD Incorporate Any Material by Reference? (h) You must do the actions required by this AD following the instructions in Pilatus PC-12 Service Bulletin No. 32-017, dated August 3, 2004. 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. To get a copy of this service information, contact Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371 Stans, Switzerland; telephone: +41 41 619 6208; facsimile: +41 41 619 7311; e- mail: SupportPC12@pilatus-aircraft.com or from Pilatus Business Aircraft Ltd., Product Support Department, 11755 Airport Way, Broomfield, Colorado 80021; telephone: (303) 465-9099; facsimile: (303) 465-6040. To review copies of this service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, go 19
2005-01-11 3 to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html or call (202) 741-6030. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590-001 or on the Internet at http://dms.dot.gov. The docket number is FAA-2004-19221. Issued in Kansas City, Missouri, on December 28, 2004. David A. Downey, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-185 Filed 1-6-05; 8:45 am] BILLING CODE 4910-13-P 20