FEDERAL AVIATION ADMINISTRATION AIRWORTHINESS DIRECTIVES SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS BIWEEKLY 2005-09 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

2004-26-11 2005-01-04

2005-01-10 2005-01-11

Rolls-Royce Corporation

S 98-15-13

S 74-06-01

Bell Helicopter Textron Canada Raytheon Aircraft Company

The New Piper Aircraft, Inc Pilatus Aircraft Ltd.

Engine: 250-B17, -B17B, -B17C, -B17D, -B17E, 250-C20, -C20B, -C20F, -C20J, -C20S, and -C20W Series Turboprop and Turboshaft Rotorcraft: 222, 222B, 222U, 230, 430 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 PA-23-235, PA-23-250, and PA-E23-250 PC-12 and PC-12/45

Biweekly 2005-02 98-20-38 R1

R

Raytheon Aircraft Company

2005-01-14 2005-01-17 2005-01-18

S 2002-21-16 S 98-03-14 S 93-25-07

Bombardier-Rotax GmbH EXTRA Flugzeugbau GmbH Raytheon Aircraft Company

2005-01-19

S 2004-10-15

GARMIN International Inc

2005-02-01

The Lancair Company

Beech 200 (A100-1 (U-21J)), Beech 200C, Beech 200CT, Beech 200T, Beech A200 (C-12A) or (C-12C), Beech A200C (UC-12B), Beech A200CT (C-12D), (FWC-12D), (RC-12D), (C-12F), (RC-12G), (RC-12H), (RC-12K), or (RC-12P), B200CT, and B200T Engine: 912 F, 912 S, and 914 F Series Reciprocating EA–300 and EA–300/S A100–1 (U–21J), 200, B200, A200 (C–12A), A200 (C–12C), A200C (UC–12B), A200CT (C–12D), A200CT (FWC–12D), A200CT (RC–12D), A200CT (C–12F), A200CT (RC–12G), A200CT (RC–12H), A200CT (RC–12K), A200CT (RC–12P), A200CT (RC–12K), 200C, B200C, 200CT, 200T, B200C (C-12F), B200C (UC–12F), B200C (UC–12M), B200CT, 300, B300, B300C, and B300C Appliance: GTX 33, GTX 33D, GTX 330, and GTX 330D Mode S Transponders LC40–550FG and LC42–550FG

Biweekly 2005-03 2005-01-04

COR S 98-15-13

Raytheon Aircraft Company

2005-01-18

COR S 93-25-07

Raytheon Aircraft Company

2005-02-11 2005-03-04

COR

Gippsland Aeronautics Pty. Ltd. Pacific Aerospace Corp., Ltd.

65–90, 65–A90, B90, C90, C90A, 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, and C99 A100–1 (U–21J), 200, B200, A200 (C–12A), A200 (C–12C), A200C (UC–12B), A200CT (C–12D), A200CT (FWC–12D), A200CT (RC–12D), A200CT (C–12F), A200CT (RC–12G), A200CT (RC–12H), A200CT (RC–12K), A200CT (RC–12P), A200CT (RC–12K), 200C, B200C, 200CT, B200CT, 200T, B200T, B200C (C–12F), B200C (UC–12F), B200C (UC–12M), B200CT, 300, B300C, and B300C GA8 750XL

Biweekly 2005-04 2005-01-04

COR S 98-15-13

2005-03-07 2005-03-08 2005-03-09

2005-03-10 2005-04-09

Raytheon Aircraft Company

Bell Helicopter Textron Canada Eurocopter France Eurocopter France

S 2002-08-54 S 2004-26-11

Bell Helicopter Textron Bell Helicopter Textron Canada

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65–90, 65–A90, B90, C90, C90A, 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 Rotorcraft: 407 Rotorcraft: AS350B, BA, B1, B2, B3, C, D, D1, and EC130 B4 Rotorcraft: EC 155B, EC155B1, SA-360C, SA-365C, SA-365C1, SA-365C2, SA-365N, SA-365N1, AS-365N2, AS 365 N3, and SA-366G1 Rotorcraft: 222, 222B, 222U, and 230 Rotorcraft: 222, 222B, 222U, 230, and 430

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 2005-05 2005-04-08 2005-04-10 2005-04-16 2005-05-51 2005-05-52 2005-05-53 2005-05-53 R1

Hartzell Propeller Inc. General Electric Company

E E, S 2005-05-51 E E, R, S 2005-0553

Propeller: HC-B3TN-5( )/T10282( ) Engine: CT58-140-1, CT58-140-2, and surplus military T58-GE-5, -10, -100, and ''402 turboshaft PC-12 and PC-12/45 402C and 414A 402C and 414A 172R, 172S, 182T, and T182T 172R, 172S, 182T, and T182T

Pilatus Aircraft Ltd. Cessna Aircraft Company Cessna Aircraft Company Cessna Aircraft Company Cessna Aircraft Company

Biweekly 2005-06 2005-05-14 2005-05-15

Eagle Aircraft (Malaysia) Honeywell International Inc.

2005-06-01

Eurocopter France

Eagle 150B Engine: TFE731-2 and -2C series, and TFE731-3, -3A, -3AR, -3B, -3BR, and -3R series turbofan Rotorcraft: EC 155B and EC 155B1

Cessna

402C and 414A

Cessna Fairchild Aircraft, Inc.

172R, 172S, 182T, and T182T SA226-AT, SA226-TC, SA226-T, SA226-T(B), SA227-TT, SA227-TT(300), SA227-AC, SA227-AT, SA227-BC, and SA227CC/DC 208 and 208B

Biweekly 2005-07 2005-05-52 2005-05-53 R1 2005-06-13

FR, S 2005-05-51 and 2000-23-01 R, 2005-05-53 S 99-0602

2005-07-01

Cessna

Biweekly 2005-08 83-08-01 R2

R, S 83-08-01 R1

Hartzell Propeller Inc.

2005-07-01 2005-07-27

COR S 2000-18-04

Cessna Aviointeriors S.p.A.

Propeller: HC-B3TN-2, HC-B3TN-3, HC-B3TN-5, HC-B4TN-3, HC-B4TN-5, HC-B4MN-5, and HC-B5MP-3 turbopropellers 208 and 208B Appliance: Model 312 Seats

Biweekly 2005-09 2005-08-06 2005-08-07 2005-08-12 2005-08-13 2005-08-14 2005-09-51

E

Centrair Pilatus Aircraft Limited Centrair Glaser-Dirks Flugzeugbau GmbH LET a.s. Turbomeca S.A.

Glider: 101, 101A, 101AP, and 101P Sailplane: B4-PC11, B4-PC11A, and B4-PC11AF Glider: 101, 101A, 101AP, and 101P Sailplane: DG-800B Sailplane: Blanik L-13 AC Engine: Arrius 2F Turboshaft

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BW 2005-09 CENTRAIR AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2005-08-06 Centrair: Amendment 39-14058; Docket No. FAA-2004-19616; Directorate Identifier 2004-CE-38-AD. When Does This AD Become Effective? (a) This AD becomes effective on June 2, 2005. What Other ADs Are Affected by This Action? (b) None. What Gliders Are Affected by This AD? (c) This AD affects Models 101, 101A, 101AP, and 101P gliders, all serial numbers, without elevator and aileron part number SY991A hinge pins installed, 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 France. The actions specified in this AD are intended to replace incorrectly heat-treated elevator or aileron hinge pins, which could result in failure of the elevator or ailerons. Such failure during takeoff, landing, or flight operations could lead to loss of glider control. (e) To address this problem, you must do the following: Actions (1) Replace any installed elevator and aileron hinge pins that are not part number (P/N) SY991A hinge pins with P/N SY991A hinge pins. (2) Do not install any elevator and aileron hinge pins that are not P/N SY991A hinge pins as specified in paragraph (e)(1) of this AD.

Compliance Within the next 25 hours timein-service (TIS) after June 2, 2005 (the effective date of this AD), unless already done. As of June 2, 2005 (the effective date of this AD).

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Procedures Follow Société Nouvelle Centrair Service Bul-letin No. 101–22, dated March 13, 2001. Not Applicable.

2005-08-06 2

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, Small Airplane Directorate, FAA. For information on any already approved alternative methods of compliance, contact Greg Davison, Aerospace Engineer, FAA, Small Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4130; facsimile: (816) 329-4090. Is There Other Information That Relates to This Subject? (g) French AD Number 2001-247(A), dated June 27, 2001, also addresses the subject of this AD. Does This AD Incorporate Any Material by Reference? (h) You must do the actions required by this AD following the instructions in Société Nouvelle Centrair Service Bulletin No. 101-22, dated March 13, 2001. 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 CENTRAIR, Aerodome B.P.N. 44, 36300 Le Blanc, France; telephone: 02.54.37.07.96; facsimile: 02.54.37.48.64. 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 20590001 or on the Internet at http://dms.dot.gov. The docket number is FAA-2004-19616. Issued in Kansas City, Missouri, on April 11, 2005. Nancy C. Lane, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-7564 Filed 4-18-05; 8:45 am] BILLING CODE 4910-13-P

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BW 2005-09 PILATUS AIRCRAFT LIMITED AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS

2005-08-07 Pilatus Aircraft Limited: Amendment 39-14059; Docket No. FAA-2004-20006; Directorate Identifier 2004-CE-49-AD. When Does This AD Become Effective? (a) This AD becomes effective on June 2, 2005. What Other ADs Are Affected by This Action? (b) None. What Sailplanes Are Affected by This AD? (c) This AD affects Models B4-PC11, B4-PC11A, and B4-PC11AF sailplanes, 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 detect and correct cracks in the control-column support, which could result in failure of the support. This failure could lead to loss of the primary flight control system. What Must I Do To Address This Problem? (e) To address this problem, you must do the following: Actions (1) Inspect the controlcolumn support (part number (P/N) 112.35.11.072) for cracks.

Compliance Initially inspect within 12 calendar months after the last inspection under Pilatus Aircraft Ltd. Service Bulletin No. 1005, Revision No. 1, dated April 9, 2003, or Pilatus Aircraft Ltd. Service Bulletin No. 1005, Revision No. 2, dated April 22, 2004, where no cracks were found or within the next 30 days after June 2, 2005 (the effective date of this AD), whichever occurs later, unless already done. Repetitively inspect 2004. thereafter at intervals not to exceed every 12 calendar months regardless of whether the control-column support was replaced.

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Procedures Follow Pilatus B4– PC 11 Aircraft Ltd. Service Bulletin No. 1005, Revision No. 2, dated April 22, 2004.

2005-08-07 2

(2) If any cracks are found after the inspection required by paragraph (e)(1) of this AD, replace the control-column support (P/N 112.35.11.072) with a new control-column support (P/N 112.35.11.072).

Before further flight after the inspection required by paragraph (e)(1) of this AD where you found the crack. Continue the repetitive inspections required by paragraph (e)(1) of this AD.

Follow Pilatus B4– PC 11 Aircraft Ltd. Service Bulletin No. 1005, Revision No. 2, dated April 22, 2004.

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. May I Obtain a Special Flight Permit for the Initial Inspection Requirement of This AD? (g) No. Special flight permits are not allowed for this AD. Is There Other Information That Relates to This Subject? (h) Swiss AD Number HB 2004-491, dated December 23, 2004, also addresses the subject of this AD. Does This AD Incorporate Any Material by Reference? (i) You must do the actions required by this AD following the instructions in Pilatus B4-PC 11 Aircraft Ltd. Service Bulletin No. 1005, Revision No. 2, dated April 22, 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; email: [email protected] 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 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 20590001 or on the Internet at http://dms.dot.gov. The docket number is FAA-2004-20006; Directorate Identifier 2004-CE-49-AD. Issued in Kansas City, Missouri, on April 11, 2005. Nancy C. Lane, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-7563 Filed 4-20-05; 8:45 am] BILLING CODE 4910-13-P 8

BW 2005-09 CENTRAIR AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS

2005-08-12 Centrair: Amendment 39-14064; Docket No. FAA-2004-19522; Directorate Identifier 2004-CE-36-AD. When Does This AD Become Effective? (a) This AD becomes effective on June 6, 2005. What Other ADs Are Affected by This Action? (b) None. What Gliders Are Affected by This AD? (c) This AD affects Models 101, 101A, 101AP, and 101P gliders, serial numbers 101xx001 through 101xx285 and 101D0501 through 101D0530, 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 France. We are issuing this AD to replace the non-strengthened rudder pedals, and prevent failure of the rudder controls. This failure could lead to loss of directional control of the glider. What Must I Do To Address This Problem? (e) To address this problem, you must do the following: Actions (1) Replace any non-strengthened rudder ped-als with reinforced rudder pedals. (i) the left-hand reinforced rudder pedal is part number (P/N) $Y185A; and. (ii) the right-hand reinforced rudder pedal is P/N $Y196A. (2) Do not install any non-strengthened rudder pedal as specified in paragraphs (e)(1)(i) and (e)(1)(ii) of this AD.

Compliance Within the next 25 hours time-in-service (TIS) after June 6, 2005 (the effective date of this AD), unless already done. As of June 6, 2005 (the effective date of this AD).

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Procedures Follow Société Nouvelle Centrair Service Bul-letin No. 101–24, dated March 5, 2003 (this is the date of French AD 2003–095(a) that transmitted the service bulletin). Not Applicable.

2005-08-12 2

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, Small Airplane Directorate, FAA. For information on any already approved alternative methods of compliance, contact Greg Davison, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4130; facsimile: (816) 329-4090. Is There Other Information That Relates to This Subject? (g) French AD 2003-095(A), dated March 5, 2003, also addresses the subject of this AD. Does This AD Incorporate Any Material by Reference? (h) You must do the actions required by this AD following the instructions in Société Nouvelle Centrair Service Bulletin No. 101-24, dated March 5, 2003 (this is the date of French AD 2003-095(a) that transmitted the service bulletin). 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 CENTRAIR, Aerodome B.P.N. 44, 36300 Le Blanc, France; telephone: 02.54.37.07.96; facsimile: 02.54.37.48.64. 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 205900001 or on the Internet at http://dms.dot.gov. The docket number is FAA-2004-19522. Issued in Kansas City, Missouri, on April 12, 2005. Nancy C. Lane, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-7784 Filed 4-20-05; 8:45 am] BILLING CODE 4910-13-P

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BW 2005-09 GLASER-DIRKS FLUGZEUGBAU GMBH AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS

2005-08-13 Glaser-Dirks Flugzeugbau GmbH: Amendment 39-14065; Docket No. 2003-CE-65AD. When Does This AD Become Effective? (a) This AD becomes effective on June 6, 2005. What Other ADs Are Affected by This Action? (b) None. What Sailplanes Are Affected by This AD? (c) This AD affects all Model DG-800B sailplanes, all serial numbers, that are: (1) Certificated in any category; and (2) Equipped with a SOLO 2625 engine or a Mid-West AE 50T engine. 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 Germany. The actions specified in this AD are intended to prevent electrical failure of the fuel and coolant pumps if a non-resettable circuit breaker trips. This could result in power loss with the inability to restart the fuel pump during a critical phase of flight (for example, takeoff under own power). What Must I Do To Address This Problem? (e) To address this problem, you must do the following: Actions (1) Modify the coolant pump and fuel pump electrical circuits.

Compliance Within the next 50 hours timein-service (TIS) after June 6, 2005 (the effective date of this AD), unless already done.

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Procedures For sailplanes with a SOLO 2625 engine: Follow DG Flugzeugbau GmbH Technical Note No. 873/26, dated November 12, 2001; For sailplanes with a Mid-West AE 50T engine: Follow DG Flugzeugbau GmbH Technical Note No. 873/27, dated November 29, 2001.

2005-08-13 2

(2) Remove the nonresettable digital engine indicator (DEI) circuit breaker (4-ampere) and replace with a resettable 5ampere circuit breaker. (3) For sailplanes with engine SOLO 2625 (New version Mikuni carburetor): Secure the choke butterfly valve axis.

(4) Install edge protection at the sharp edges of the resettable 5-ampere DEI circuit breaker.

Before further flight after the modification of the coolant pump and fuel pump electrical circuits required by paragraph (e)(1) of this AD.

For sailplanes with a SOLO 2625 engine: Follow DG Flugzeugbau GmbH Technical Note No. 873/26, dated November 12, 2001; For sailplanes with a Mid-West AE 50T engine: Follow GD Flugzeugbau GmbH Technical Note No. 873/27, dated November 29, 2001. Before further flight after the For sailplanes with a SOLO 2625 engine: modificaiton of the coolant pump Follow DG Flugzeugbau GmbH Technical and fuel pump electrical circuits Note No. 873/26, dated November 12, required by paragraph (e)(1) of 2001. this AD and the removal and replacement required by paragraph (e)(2) of this AD. Before further flight after the For sailplanes with a SOLO 2625 engine: modification of the coolant pump Follow DG Flugzeugbau GmbH Technical and fuel pump electrical circuits Note No. 873/26, dated November 12, required by paragraph (e)(1) of 2001; For sailplanes with a Mid-West AE this AD and the removal and 50T engine: Follow DG Flugzeugbau replacement required by GmbH Technical Note No. 873/27, dated paragraph (e)(2) of this AD. November 29, 2001.

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, FAA. For information on any already approved alternative methods of compliance, contact Greg Davison, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4130; facsimile: (816) 329-4090. Does This AD Incorporate Any Material by Reference? (g) You must do the actions required by this AD following the instructions in DG Flugzeugbau GmbH Technical Note No. 873/26, dated November 12, 2001, and DG Flugzeugbau GmbH Technical Note No. 873/27, dated November 29, 2001. 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. You may get a copy from DG Flugzeugbau, Postbox 41 20, D-76625 Bruchsal, Federal Republic of Germany; telephone: 011-49 7257-890; facsimile: 011-49 7257-8922. You may review copies at FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106; 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: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

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2005-08-13 3

Is There Other Information That Relates to This Subject? (h) German AD Number 2002-083, dated April 4, 2002, also addresses the subject of this AD. Issued in Kansas City, Missouri, on April 12, 2005. Nancy C. Lane, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-7790 Filed 4-20-05; 8:45 am] BILLING CODE 4910-13-P

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BW 2005-09 LET A.S. AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS

2005-08-14 LET a.s. (Formerly LET n.p.): Amendment 39-14066; Docket No. 2003-CE-57-AD. When Does This AD Become Effective? (a) This AD becomes effective on June 6, 2005. What Other ADs Are Affected by This Action? (b) None. What Sailplanes Are Affected by This AD? (c) This AD affects Model Blanik L-13 AC sailplanes, serial numbers 988601, 988603, 008605, 008606, and 028902, that are certificated in any category. What Is the Unsafe Condition Presented in This AD? (d) This AD is the result of a report of one case of cracks in the attachment of control levers on the control bridge. The actions specified in this AD are intended to correct cracks in the bedding of the front and rear control levers, which could result in failure of the control bridge for the sailplane. This failure could lead to loss of sailplane control. What Must I Do To Address This Problem? (e) To address this problem, you must do the following: Actions (1) Replace the original control bridge (Drawing No. A741 210N) with the new strengthened control column mounting bridge (Drawing No. A740 370N). (2) Do not install any original control bridge (Drawing No. A741 210N).

Compliance Within the next 25 hours time-in-service (TIS) after June 6, 2005 (the effective date of this AD), unless already done. As of the effective date of this AD

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Procedures Follow the WORK PROCEDURE paragraph of LET Letecke Zavody Mandatory Bulletin No.: L13AC/014a, dated July 17, 2003. Not Applicable.

2005-08-14 2

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, FAA. For information on any already approved alternative methods of compliance, contact Greg Davison, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4130; facsimile: (816) 329-4090. Does This AD Incorporate Any Material by Reference? (g) You must do the actions required by this AD following the instructions in LET Letecke Zavody Mandatory Bulletin No.: L13AC/014a, dated July 17, 2003. 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. You may get a copy from LET a.s., Kunovice 686 04, Czech Republic; telephone: +420 572 817 650; facsimile: +420 572 617 653. You may review copies at FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106; 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: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. Is There Other Information That Relates to This Subject? (h) Czech Airworthiness Directive CAA-AD-090/2001, dated October 25, 2001, also addresses the subject of this AD. Issued in Kansas City, Missouri, on April 14, 2005. Nancy C. Lane, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-7990 Filed 4-22-05; 8:45 am] BILLING CODE 4910-13-P

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BW 2005-09 TURBOMECA AIRWORTHINESS DIRECTIVE ENGINE EMERGENCY SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS

2005-09-51 Turbomeca: Directorate Identification No. 2005-NE-14-AD. Effective Date (a) Emergency AD 2005-09-51, issued on April 28, 2005, is effective upon receipt. Affected ADs (b) None. Applicability (c) This AD applies to certain Turbomeca Arrius 2F turboshaft engines listed by serial number (SN) in Table 1 of this AD. Table 1. Engine and Module Serial Numbers Engine SN Module 2 SN Engine SN Module 2 SN 34416 01045 34435 01110 34417 01063 34436 01121 34418 01052 34437 01122 34419 01053 34438 01123 34420 01067 34439 01136 34421 01068 34440 01139 34422 01051 34441 01140 34423 01078 34442 01138 34424 01079 34443 01141 34425 01080 34444 01142 34426 01083 34445 01146 34427 01089 34446 01147 34428 01090 34447 01148 34429 01097 34448 01164 34430 01098 34449 01165 34431 01099 34450 01177 34432 01102 Not Installed 01149 34433 01103 34033 00125 34434 01109 34177 00446

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2005-09-51 2

Unsafe Condition (d) This AD results from failure of a high pressure turbine (HPT) blade and damage to two other HPT blades in a Turbomeca Arrius 2F turboshaft engine on March 31, 2005. We are issuing this AD to prevent failure of the engine and subsequent loss of power. Compliance (e) You are responsible for having the actions required by this AD performed before further flight, unless the actions have already been done. Replacing the Module 2 (f) Before further flight, on Turbomeca Arrius 2F engines that have a SN listed in Table 1 of this AD, remove the Module 2 and replace the Module with a Module 2 that was overhauled or that has a SN not listed in Table 1 of this AD. Alternative Methods of Compliance (g) The Manager, Engine Certification Office, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. Related Information (h) Direction General De L’Aviation Civile Emergency airworthiness directive No. UF-2005073, dated April 27, 2005, also addresses the subject of this AD. Contact Information (i) For further information, contact: Christopher Spinney, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803-2599, telephone (781) 238-7175; fax (781) 238-7199. Issued in Burlington, MA, on April 28, 2005.

Jay J. Pardee Manager, Engine and Propeller Directorate Aircraft Certification Service

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