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FEDERAL AVIATION ADMINISTRATION AIRWORTHINESS DIRECTIVES SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS BIWEEKLY 2005-18 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

Kelly Aerospace Power Systems Centrair Eurocopter France Agusta S.p.A. Agusta S.p.A.

Appliance: Fuel regulator shutoff valve Glider: 101 Series Rotorcraft: EC120B Rotorcraft: A119 Rotorcraft: A109E

Sailplane: Blanik L-13 AC Engine: Arrius 2F Turboshaft

Biweekly 2005-10 2004-25-16 R1 2005-08-06 2005-09-05 2005-09-06 2005-09-07

R, 2004-25-16 COR

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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 2005-11 2005-09-51 2005-10-12 2005-10-13

FR

Turbomeca S.A. Schweizer Aircraft Corporation Rolls-Royce Corporation

2005-10-14 2005-10-23

S 2004-01-51

2005-10-24

S 2003-14-20

Eurocopter France DG Flugzeubau GmbH and Glaser-Dirks Flugzeubau GmbH AeroSpace Technologies of Australia Pty. Ltd. Turbomeca S.A.

2005-11-01

Engine: Arrius 2F turboshaft Rotorcraft: 269C, C-1, and D Engine: 250-B17B, -B17C, -B17D, -B17E, -C20, -C20B, -C20F, C20J, -C20S, and -C20W turboprop and turboshaft Rotorcraft: AS355E, F, F1, F2, and N Glider:DG-500MB and DG-800B N22B, N22S and N24A Engine: Arrius 1A turboshaft

Biweekly 2005-12 2005-11-05 2005-11-06 2005-11-07 2005-11-08 2005-12-01 2005-12-02

S 98-10-12

2005-12-51

E

Precise Flight, Inc. Pilatus Aircraft Ltd. Extra Flugzeugproduktions-Und Vertriebs-GmbH GROB-WERKE Agusta S.p.A. Revo, Incorporated Rockwell International and Autair Ltd.

Appliance: Standby vacuum system (SVS) PC-12 and PC-12/45 EA-300, EA-300S, ES-300L, and EA-300/200 G120A Rotorcraft: A109E Colonial C-2, Lake LA-4, Lake LA-4A, Lake LA-4P, and Lake LA-4-200 AT-6 (SNJ-2), AT-6A (SNJ-3), AT-6B, AT-6C (SNJ-4), AT-6D (SNJ-5), AT-6F (SNJ-6), BC-1A, Harvard (Army AT-16), SNJ-7, and T-6G

Biweekly 2005-13 2005-12-03 2005-12-06 2005-12-08 2005-12-09 2005-12-12 2005-12-13 2005-12-20 2005-12-51

2005-13-01

S 96-12-07

S 79-10-15 S 2005-05-52 FR

S 2004-18-01

2005-13-07 2005-13-09 2005-13-10 2005-13-11 2005-13-12 2005-13-13 2005-13-16 2005-13-17 2005-13-23

S 93-24-14 S 2003-18-03

2005-13-25

Sikorsky Aircraft Corporation Teledyne Continental Motors Turbomeca S.A. Grob-Werke Cessna Aircraft Company Cessna Aircraft Company The Lancair Company Rockwell International

Hoffmann Propeller GmbH & Co KG Honeywell International Inc. GROB-WERKE Cessna Aircraft Company General Electric Company Air Tractor, Inc.

Rotorcraft: S-92A Appliance: S-20, S-1200, D-2000, and D-3000 Series Magnetos Engine: Arrius 2 B1, 2 B1A, 2 B1A-1, and 2 B2 turboshaft G120A 401, 401A, 401B, 402, 402A, 402B, 411, and 411A 402C and 414A LC41-550FG AT-6 (SNJ-2), AT-6A (SNJ-3), AT-6B, AT-6C (SNJ-4), AT-6D (SNJ-5), AT-6F (SNJ-6), BC-1A, Harvard (Army AT-16), SNJ-7, and T-6G Propeller: HO-V343 and HO-V343K

Turbomeca S.A.

Engine: TFE731-2 and -3 series turbofan G120A 172R, 172S, 182T, T182T, 206H, T206H Engine: CT64-820-4 turboprop AT–300, AT–301, AT–302, AT–400, and AT–400A, AT– 401/AT–402, AT–602, AT–802 and AT–802A Rotorcraft: S-92A PA-34-200, PA-34-200T, and PA-34-220T Rotorcraft: AB412 Series Rotorcraft: EC 155B, EC155B1, SA-365N, SA-365N1, AS365N2, and AS 365 N3 Engine: Arriel 2B

Cessna Lancair Company

401, 401A, 401B, 402, 402A, 402B, 411, and 411A LC41-550FG

Sikorsky Aircraft Corporation The New Piper Aircraft, Inc. Agusta. S.p.A. Eurocopter France

Biweekly 2005-14 2005-12-12 2005-12-20

COR COR

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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 2005-15 2005-12-51

COR

2005-14-11

Rockwell International

Hartzell Propeller, Inc., McCauley Propeller, Sensenich Propeller Hartzell Propeller

2005-14-12

AT-6 (SNJ-2), AT-6A (SNJ-3), AT-6B, AT-6C (SNJ-4), AT-6D (SNJ-5), AT-6F (SNJ-6), BC-1A, Harvard (Army AT-16), SNJ-7, and T-6G Propeller: See AD

Propeller: HC-B3TN-2, HC-B3TN-3, HC-B3TN-5, HC-B3MN-3, HC-B4TN-3, HC-B4TN-5, HC-B4MN-5, HC-B4MP-3, HCB4MP-5, and HC-B5MP-3

Biweekly 2005-16 2005-15-10

New Piper Aircraft

PA-34-200T, PA-34-220T, PA-44-180, and PA-44-180T

Rolls-Royce Corporation Bell Helicopter Textron Robinson Helicopter Company Pilatus Aircraft Ltd.

Engine: 250-C28, -C28B, and -C28C turboshaft Rotorcraft: 206A and 206B Rotorcraft: R-22 Series PC–6, PC–6–H1, PC–6–H2, PC–6/350, PC–6/350–H1, PC–6/350– H2, PC–6/A, PC–6/A–H1, PC–6/A–H2, PC–6/B–H2, PC–6/B1– H2, PC–6/B2–H2, PC–6/B2–H4, PC–6/C–H2, PC–6/C1–H2

Tiger Aircraft LLC GROB-WERKE Turbomeca Cessna Turbomeca S.A. Turbomeca S.A. Cirrus Design Corporation

AA–5, AA–5A, AA–5B, AG–5B G120A Engine: Artouste III B, B1, and D turboshaft 525, 525A, and 525B Engine: Arrius 2F turboshaft Engine: Arrius 2F turboshaft SR20 and SR22

Biweekly 2005-17 2004-14-02 2005-16-04 2005-16-05 2005-17-01

COR

Biweekly 2005-18 95-19-15 R1 2005-13-09 2005-17-06 2005-17-11 2005-17-15 2005-17-17 2005-17-19

R 95-19-15 COR

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BW 2005-18 TIGER AIRCRAFT LLC AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 95-19-15 R1 Tiger Aircraft LLC: (Type Certificate A16EA formerly held by American General Aircraft Corporation and Grumman American Aviation Corporation): Amendment 39-14222; Docket No. FAA-2005-20968; Directorate Identifier 94-CE-15-AD. When Does This AD Become Effective? (a) This AD becomes effective on October 3, 2005. What Other ADs Are Affected By This Action? (b) This AD revises AD 95-19-15, Amendment 39-9377. 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 AA–5 AA–5A AA–5B AG–5B

Serial numbers All Serial Numbers. All Serial Numbers. All Serial Numbers. 99998, 10000 through 10174.

What Is the Unsafe Condition Presented in This AD? (d) AD 95-19-15 currently requires you to inspect the wing attach shoulder bolts for fretting, scoring, wear, or enlarged or elongated mounting holes (known as damage from hereon); replace any damaged parts; repair any damaged areas; inspect the wing spar at the center spar clearance gap for excessive clearance; and shim the spar if excessive clearance is found. That AD was written to apply to all serial numbers of all models. A design change was made in this area beginning with serial number 10175 of the Model AG-5B airplanes. Therefore, the action should not apply to Model AG5B airplanes with a serial number of 10175 or higher. This AD retains all the actions of AD 95-19-15 for all airplanes originally affected, but cuts off the applicability for the Model AG-5B airplanes at serial number 10174. We are issuing this AD to continue to prevent wing attach shoulder bolt failure, which, if not detected and corrected, could lead to structural damage of the wing/fuselage to the point of failure.

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95-19-15 R1 2

What Must I Do To Address This Problem? (e) To address this problem, you must do the following, unless already done: Actions (1) Inspect any inboard wing attach shoulder bolt for: (i) Fretting, scoring, or wear (removal of the cad plating) to the shoulder of the bolt (ii) A smooth machined area between the threads and the shoulder bevel of the shoulder bolt profile (2) Replace any inboard wing attach shoulder bolt with wear (removal of the cad plating from the shoulder of the bolt) or if the threads contact the shoulder of the bolt found during the inspections required in paragraph (e)(1) of this AD (3) Inspect the mounting holes in the wing spar and the center section spar for enlargement or elongation that exceeds the specified dimension

Compliance Within the next 100 hours aircraft time-in-service (TIS) after November 17, 1995 (the effective date of AD 95–19– 15, unless already done

Procedures Follow American General Aircraft Corporation Service Bulletin No. SB– 185–A, Revision A, dated January 10, 2005.

Before further flight after the Follow American General inspection required by Aircraft Corporation paragraph (e)(1) of this AD Service Bulletin No. SB– 185–A, Revision A, dated January 10, 2005.

Within the next 100 hours aircraft time-in-service (TIS) after November 17, 1995 (the effective date of AD 95–19– 15), unless already done (4) Ream and bush any mounting hole that Before further flight after the exceeds the specified dimension found inspection required by during the inspection required by paragraph (e)(3) of this AD paragraph (e)(3) of this AD

Follow American General Aircraft Corporation Service Bulletin No. SB– 185–A, Revision A, dated January 10, 2005. Follow American General Aircraft Corporation Service Bulletin No. SB– 185–A, Revision A, dated January 10, 2005 (5) Inspect the wing spar at the center spar Before further flight after the Follow American General clearance gap for excessive clearance, and inspections required by Aircraft Corporation shim the spar if excessive clearance is paragraphs (e)(1) and (e)(3) Service Bulletin No. SB– found of this AD 185–A, Revision A, dated January 10, 2005. (6) Do not install any wing attach shoulder As of October 3, 2005 (the Not Applicable. bolt that has wear resulting in removal of effective date of this AD) the cad plating from the shoulder of the bolt or if the threads contact the shoulder bevel of the shoulder bolt profile 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, New York Aircraft Certification Office (ACO), FAA. For information on any already approved alternative methods of compliance, contact Richard Beckwith, Aerospace Engineer, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone: 516-794-5531; facsimile: 516-794-5531. 8

95-19-15 R1 3

Does This AD Incorporate Any Material by Reference? (g) You must do the actions required by this AD following the instructions in American General Aircraft Corporation Service Bulletin No. SB-185-A, Revision A, dated January 10, 2005. 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 Tiger Aircraft LLC, 226 Pilot Way, Martinsburg, WV 25401. 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-2005-20968; Directorate Identifier 94-CE-15-AD. Issued in Kansas City, Missouri, on August 11, 2005. Kim Smith, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-16260 Filed 8-19-05; 8:45 am] BILLING CODE 4910-13-P

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BW 2005-18 GROB-WERKE AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS CORRECTION: [Federal Register: August 23, 2005 (Volume 70, Number 162); Page 4918449185; www.access.gpo.gov/su_docs/aces/aces140.html] 2005-13-09 GROB-WERKE: Amendment 39-14146; Docket No. FAA-2005-19473; Directorate Identifier 2004-CE-35-AD. When Does This AD Become Effective? (a) The effective date of this AD (2005-13-09) remains July 26, 2005. What Other ADs Are Affected by This Action? (b) None. 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 G120A, all serial numbers beginning with 85001. What Is the Unsafe Condition Presented in This AD? (d) This AD results from a report that the main landing gear (MLG) may not extend because of contamination or misalignment of the assembly. The actions specified in this AD are intended to prevent the MLG from becoming jammed and not extending, which could result in loss of control of the airplane during landing. (e) To address this problem, you must do the following: Actions (1) Remove MLG up-lock hook assembly and replace with the new MLG up-lock hook assembly. (2) For all serial numbers: Do not install any elevator and aileron hinge pins that are not part number SY991A hinge pins.

Compliance Within 100 hours timein-service after July 26, 2005 (the effective date of this AD), unless already done. After July 26, 2005 (the effective date of this AD).

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Procedures Follow GROB–WERKE Service Bulletin No. MSB1121–052/2, dated February 14, 2005; and GROB–WERKE Service Bulletin No.MSB1121–060, dated March 7, 2005. Follow GROB–WERKE Service Bulletin No. MSB1121–052/2, datedFebruary 14, 2005; and GROB–WERKE Service Bulletin No. MSB1121–060, dated March 7, 2005.

2005-13-09 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 Karl Schletzbaum, Aerospace Engineer, ACE-112, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: 816-3294146; facsimile: 816-329-4090. Is There Other Information That Relates to This Subject? (g) Luftfahrt-Bundesamt Airworthiness Directive D-2004-299R2, dated March 15, 2005; GROB-WERKE Service Bulletin No. MSB1121-052/2, dated February 14, 2005; and GROBWERKE Service Bulletin No. MSB1121-060, dated March 7, 2005; also address 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 GROBWERKE Service Bulletin No. MSB1121-052/2, dated February 14, 2005; and GROB-WERKE Service Bulletin No. MSB1121-060, dated March 7, 2005. 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 GROB-WERKE, Burkart Grob e.K., Unternehmenbereich Luft-und Raumfahrt, Lettenbachstrasse 9, 86874 Tussenhausen-Mattsies, Germany; telephone: 011 49 8268 998 105; facsimile: 011 49 8268 998 200. 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 August 15, 2005. Terry L. Chasteen, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-16440 Filed 8-22-05; 8:45 am] BILLING CODE 4910-13-P

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BW 2005-18 TURBOMECA AIRWORTHINESS DIRECTIVE ENGINE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2005-17-06 Turbomeca: Amendment 39-14227. Docket No. FAA-2005-20849; Directorate Identifier. 2005-NE-04-AD. Effective Date (a) This airworthiness directive (AD) becomes effective September 27, 2005. Affected ADs (b) None. Applicability (c) This AD applies to Turbomeca Artouste III B, B1, and D turboshaft engines. These engines are installed on, but not limited to, Aerospatiale (Eurocopter–France) SA-315B LAMA, and Alouette III SA3160, SA-316B, and SA-316C helicopters. Unsafe Condition (d) This AD results from a report of an in-flight shutdown and subsequent loss of control of the helicopter, due to ice ingestion into the engine. We are issuing this AD to prevent ice ingestion into the engine, which could lead to an in-flight shutdown and subsequent loss of control of the helicopter. Compliance (e) You are responsible for having the actions required by this AD performed within nine months after the effective date of this AD, unless the actions have already been done. Addition of Water Drain Holes (Turbomeca Modification TU 171A) (f) Within nine months from the effective date of this AD, drill two additional water drain holes in each engine air intake assembly half-cover, using paragraph 2.B. and the air intake assembly dimensional flat view of Turbomeca Artouste III Mandatory Service Bulletin No. 218 72 0104, Update No. 1, dated March 25, 2005. 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.

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2005-17-06 2

Related Information (h) DGAC airworthiness directive F-2003-455, dated December 24, 2003, also addresses the subject of this AD. Material Incorporated by Reference (i) You must use Turbomeca Artouste III Mandatory Service Bulletin No. 218 72 0104, Update No. 1, dated March 25, 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 Turbomeca, 40220 Tarnos, France; telephone +33 05 59 74 40 00, fax +33 05 59 74 45 15, 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 http://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: http://www.archives.gov/federalregister/cfr/ibr-locations.html. Issued in Burlington, Massachusetts, on August 12, 2005. Peter A. White, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 05-16453 Filed 8-22-05; 8:45 am] BILLING CODE 4910-13-P

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BW 2005-18 CESSNA AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2005-17-11 The Cessna Aircraft Company: Amendment 39-14232; Docket No. FAA-2005-21109; Directorate Identifier 2005-CE-21-AD. When Does This AD Become Effective? (a) This AD becomes effective on October 7, 2005. What Other ADs Are Affected by This Action? (b) None. 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 525 525A 525B

Serial Nos. 525–0001 through 525–0600. 525A–0001 through 525A–0234. 525B–0001 through 525B–0035.

What Is the Unsafe Condition Presented in This AD? (d) This AD is the result of reports about the possibility to incorrectly connect the wires to the engine fire extinguisher bottles. The actions specified in this AD are intended to prevent incorrect installation of the wires to the engine fire extinguisher bottles, which could result in failure of the engine fire extinguisher bottles to discharge when activated. This failure could lead to the inability to control an engine fire. What Must I Do To Address This Problem? (e) To address this problem, you must do the following:

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Actions (1) Install identification sleeves on the wires for both engine fire extinguisher bottles.

Compliance Within the next 60 days or 100 hours time-in-service after October 7, 2005 (the effective date of this AD), whichever occurs first.

Procedures Follow the Accomplishment Instructions in: (i) Cessna Citation Service Bulletin SB525–26–01; (ii) Cessna Citation Service Bulletin SB525A–26–02; or (iii) Cessna Citation Service Bulletin SB525B–26–01, all dated April 5, 2005, as applicable. (2) Reconnect the wires Before further flight after the Use the service information specified in to both engine fire sleeve installation required in paragraphs (e)(1)(i) through (e)(1)(iii) of extinguisher bottles. paragraph (e)(1) of this AD. this AD. (3) Test the wires for Before further flight after Use the service information specified in correct installation reconnecting the wires as required paragraphs (e)(1)(i) through (e)(1)(iii) of in paragraph (e)(2) of this AD. this AD. 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, Wichita Aircraft Certification Office (ACO), FAA. For information on any already approved alternative methods of compliance, contact James P. Galstad, Aerospace Engineer, FAA Wichita ACO, 1801 Airport Road, Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316) 946-4135; facsimile: (316) 946-4107. Does This AD Incorporate Any Material by Reference? (g) You must do the actions required by this AD following the instructions in Cessna Citation Service Bulletin SB525-26-01; Cessna Citation Service Bulletin SB525A-26-02; and Cessna Citation Service Bulletin SB525B-26-01, all dated April 5, 2005 (as applicable). 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 The Cessna Aircraft Company, Citation Marketing Division, Product Support P.O. Box 7706, Wichita, Kansas 67277; telephone: (316) 517-6000; facsimile: (316) 517-8500. 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-2005-21109; Directorate Identifier 2005-CE-21-AD. Issued in Kansas City, Missouri, on August 16, 2005. Terry L. Chasteen, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-16530 Filed 8-22-05; 8:45 am] BILLING CODE 4910-13-P

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BW 2005-18 TURBOMECA S.A. AIRWORTHINESS DIRECTIVE ENGINE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2005-17-15 Turbomeca S.A: Amendment 39-14236. Docket No. FAA-2005-21924; Directorate Identifier 2005-NE-30-AD. Effective Date (a) This airworthiness directive (AD) becomes effective September 12, 2005. Affected ADs (b) None. Applicability (c) This AD applies to Turbomeca S.A. Arrius 2F turboshaft engines. These engines are installed on, but not limited to, Eurocopter EC120 helicopters. Unsafe Condition (d) This AD results from incorrect positioning of the FCU filter that could limit the fuel flow downstream of the filter. We are issuing this AD to detect incorrect positioning of the FCU filter that could lead to an undetected limitation of fuel flow, limiting the maximum power available in-flight, which could result in the inability to continue safe flight, avoid obstacles or land safely. 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. Check Position of Fuel Control Unit (FCU) Fuel Filter (f) Within 25 engine-operating-hours after the effective date of this AD, remove the fuel filter-holder assembly and check that the FCU fuel filter is in the correct position using Paragraph 2 of Turbomeca Mandatory Alert Service Bulletin No. A319 73 4823, dated May 11, 2005. (g) Within 30 days, revise your engine maintenance manual to include a dimensional check to ensure the correct position of the FCU filter after every installation of the fuel filter element into the fuel filter-holder assembly. The latest revision of the Arrius 2F maintenance manual includes the dimensional check in Sub-Task 73-23-06-901-002 paragraph (2)(e).

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Alternative Methods of Compliance (AMOCs) (h) 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 (i) DGAC airworthiness directive No. F-2005-088, dated June 8, 2005, also addresses the subject of this AD. Material Incorporated by Reference (j) You must use Turbomeca Mandatory Alert Service Bulletin No. A319 73 4823, dated May 11, 2005, to perform the check 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 Turbomeca S.A., 40220 Tarnos, France; telephone 33 05 59 74 40 00, fax 33 05 59 74 45 15, 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 PL401, Washington, DC 20590-0001, on the internet at http://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: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. Issued in Burlington, Massachusetts, on August 17, 2005. Richard Noll, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 05-16902 Filed 8-25-05; 8:45 am] BILLING CODE 4910-13-P

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BW 2005-18 TURBOMECA S.A. AIRWORTHINESS DIRECTIVE ENGINE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2005-17-17 Turbomeca S.A: Amendment 39-14238. Docket No. FAA-2005-22039; Directorate Identifier 2005-NE-33-AD. Effective Date (a) This airworthiness directive (AD) becomes effective September 12, 2005. Affected ADs (b) None. Applicability (c) This AD applies to Turbomeca S.A. Arrius 2F turboshaft engines. These engines are installed on, but not limited to, Eurocopter EC120B helicopters. Unsafe Condition (d) This AD results from a report of a forced landing of a Eurocopter EC120B helicopter. We are issuing this AD to prevent an uncommanded in-flight shutdown of the engine, which could result in a forced autorotation landing and damage to the helicopter. 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. O-Ring Replacement (f) Replace the O-ring on the check valve piston in the lubrication unit at the intervals specified in Table 1 of this AD. Use the ''Instructions to be Incorporated,'' 2.A. through 2.C. (2) of Turbomeca Alert Service Bulletin No. A319 79 4802, dated June 21, 2005, to replace the O-ring.

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TABLE 1.—COMPLIANCE TIMES FOR O-RING REPLACEMENT If the class of oil is * * * Then replace the O-ring by the later of * * * Thereafter, replace the O-ring within * * * (1) HTS or unknown 300 hours time-since-new (TSN) or 50 hours 300 hours time-since-last after the effective date of this AD. replacement (TSR). (2) STD 450 hours TSN or 50 hours after the effective 500 hours TSR. date 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) DGAC airworthiness directive F-2005-122, dated July 20, 2005, also addresses the subject of this AD. Material Incorporated by Reference (i) You must use Turbomeca Alert Service Bulletin No. A319 79 4802, dated June 21, 2005 to perform the replacements 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 Turbomeca S.A., 40220 Tarnos, France; telephone 33 05 59 74 40 00, fax 33 05 59 74 45 15, 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 PL401, Washington, DC 20590-0001, on the Internet at http://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: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Burlington, Massachusetts, on August 17, 2005. Richard Noll, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 05-16834 Filed 8-25-05; 8:45 am] BILLING CODE 4910-13-P

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BW 2005-18 CIRRUS DESIGN CORPORATION AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS CORRECTION: Today, September 1, 2005, there is a typo in the table, "compliance" column, page 52001, AD 2005-17-19. It should read "...(the effective date of this AD.) We've corrected this copy. 2005-17-19 Cirrus Design Corporation: Amendment 39-14240; Docket No. FAA-2004-19694; Directorate Identifier 2004-CE-41-AD. When Does This AD Become Effective? (a) This AD becomes effective on October 13, 2005. What Other ADs Are Affected by This Action? (b) None. 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 (1) SR20 (2) SR22

Serial Nos. 1005 through 1455. 0002 through 1044.

What Is the Unsafe Condition Presented in This AD? (d) This AD is the result of discovering that the crew seats, under emergency landing dynamic loads, may fold forward at less than 26 g required by the regulations, 14 Code of Federal Regulations (CFR) Section 23.562(b)(2). The actions specified in this AD are intended to prevent the crew seats from folding forward during emergency landing dynamic loads with consequent occupant injury. What Must I Do To Address This Problem? (e) To address this problem, you must do the following:

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Actions (1) For Models SR20, serial numbers 1005 through 1423, and SR22, serial numbers 0002 through 0972, do the following actions: (i) Move the lower portion of the crew seat upholstery upward to expose the seat frame and locking mechanism. Measure the clearance between the break-over bolt and the seat frame for a clearance that meets the requirements in the service bulletin. (ii) If the clearance does not meet that specified in the service bulletin, do the crew seat break-over bolt adjustment and recover the crew seat frame and locking mechanism with the upholstery. (iii) If the clearance does meet that specified in the service bulletin, re-cover the crew seat frame and locking mechanism. (iv) Repeat the above actions for the opposite crew seat. (2) For Models SR20, serial numbers 1005 through 1455, and SR22, serial numbers 0002 through 1044, do the following actions: (i) Identify whether the recline lock is secured with two bolts or three bolts. (ii) If the recline locks are secured with two bolts, remove the existing recline locks and replace with the new recline locks kit, kit number 70084–001. (iii) If the recline locks are secured with three bolts, remove existing recline locks and replace with the new recline locks kit, kit number 70084–002. (iv) Check break-over pin alignment and adjust as necessary. (v) Check that the locks engage with the break-over bolts with the seat in the full recline position. If full seat recline is not possible or difficult to engage, grinding of the lower aft seat frame is necessary. (vi) Repeat the above actions for the opposite crew seat.

Compliance Within 50 hours time-in-service (TIS) or within 180 days, whichever occurs first after October 13, 2005 (the effective date of this AD).

Procedures Follow Cirrus Design Corporation Alert Service Bulletin SB A2X–25–08, dated June 22, 2004.

Within 50 hours TIS or within 180 days, whichever occurs first after October 13, 2005 (the effective date of this AD).

Follow Cirrus Design Corporation Service Bulletin SB 2X–25–06 R4, revised May 5, 2005.

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, Chicago Aircraft Certification Office, FAA. For information on any already approved alternative methods of compliance, please contact one of the following: (1) Wess Rouse, Small Airplane Project Manager, ACE-117C; Chicago Aircraft Certification Office, 2300 East Devon Avenue, Roon 107, Des Plaines, Illinois 60018; telephone: (847) 294-8113; facsimile: (847) 294-7834; e-mail: [email protected]; or (2) Angie Kostopoulos, Aerospace Engineer, ACE-116C, Chicago Aircraft Certification Office, 2300 East Devon Avenue, Room 107, Des Plaines, Illinois 60018; telephone: (847) 294-7426; facsimile: (847) 294-7834; e-mail: [email protected].

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Does This AD Incorporate Any Material by Reference? (g) You must do the actions required by this AD following the instructions in Cirrus Design Corporation Alert Service Bulletin SB A2X-25-08, dated June 22, 2004; and Service Bulletin SB 2X25-06 R4, revised May 5, 2005. 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 Cirrus Design Corporation, 4515 Taylor Circle, Duluth, Minnesota 55811; telephone: (218) 727-2737; Internet address: http://www.cirrusdesign.com. 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-2004-19694; Directorate Identifier 2004-CE-41-AD. Issued in Kansas City, Missouri, on August 19, 2005. Terry L. Chasteen, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-16980 Filed 8-31-05; 8:45 am] BILLING CODE 4910-13-P

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