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FEDERAL AVIATION ADMINISTRATION AIRWORTHINESS DIRECTIVES SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS BIWEEKLY 2005-17 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

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

COR

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BW 2005-17 ROLLS-ROYCE CORPORATION AIRWORTHINESS DIRECTIVE ENGINE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS

CORRECTION: [Federal Register: August 11, 2005 (Volume 70, Number 154); Page 46754; www.access.gpo.gov/su_docs/aces/aces140.html] 2004-14-02 Rolls-Royce Corporation (formerly Allison Engine Company, Allison Gas Turbine Division, and Detroit Diesel Allison): Amendment 39-13711. Docket No. FAA-2004-18538; Directorate Identifier 2004-NE-29-AD. Effective Date (a) This airworthiness directive (AD) becomes effective July 26, 2004. Affected ADs (b) None. Applicability (c) This AD applies to Rolls-Royce Corporation (formerly Allison Engine Company, Allison Gas Turbine Division, and Detroit Diesel Allison) (RRC) models 250-C28, -C28B, and -C28C turboshaft engines with third-stage turbine wheels, part number (P/N) 6899383, listed by serial number (SN) in the following Table 1:

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2004-14-02 2

TABLE 1.—SNs OF AFFECTED THIRD STAGE TURBINE WHEELS HX91922 X523242 X523281 HX91923 X523243 X523283 HX91925 X523244 X523284 HX91926 X523246 X523287 HX91928 X523249 X523288 HX91929 X523250 X523289 HX91930 X523251 X523290 HX91932 X523253 X523291 HX91934 X523255 X523292 HX91936 X523257 X523293 HX91937 X523260 X523294 HX91939 X523261 X523295 HX91940 X523262 X523296 HX91960 X523263 X523297 HX91962 X523264 X523298 HX91966 X523265 X523300 HX91976 X523266 X523305 HX91977 X523268 X523309 HX91979 X523269 X523313 HX91980 X523270 X523315 X523236 X523271 X523317 X523237 X523273 X523319 X523238 X523276 X523320 X523239 X523277 N/A X523241 X523278 N/A These engines are installed on, but not limited to, Bell Helicopter Textron 206L-1; Eurocopter Deutschland BO 105 LS A-1; and Eurocopter Canada BO 105 LS A-3 helicopters. Unsafe Condition (d) This AD results from three reports of third-stage turbine wheel blade and shroud failures. We are issuing this AD to prevent loss of power and uncommanded engine shutdown due to failure of the third-stage turbine wheel blade and shroud. 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. (f) For any third-stage turbine wheel with fewer than 250 operating hours time since new (TSN) on the effective date of this AD, replace turbine wheel before accumulating 300 operating hours TSN.

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2004-14-02 3

(g) For any third-stage turbine wheel with 250 or more operating hours TSN on the effective date of this AD, replace turbine wheel before accumulating an additional 50 operating hours. Definition (h) For the purposes of this AD, a replacement third-stage turbine wheel is a turbine wheel that does not have a SN listed in this AD. (i) After the effective date of this AD, do not install third-stage turbine wheels that are listed in Table 1 of this AD, into any engine. Alternative Methods of Compliance (j) The Manager, Chicago Aircraft 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. Special Flight Permits (k) Under 14 CFR 39.23, we are prohibiting special flight permits for this AD. Material Incorporated by Reference (l) None. Related Information (m) Rolls-Royce Corporation Alert Commercial Engine Bulletin No. CEB-A-72-2202, dated May 6, 2004, pertains to the subject of this AD. Issued in Burlington, Massachusetts, on July 1, 2004. Francis A Favara, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 04-15508 Filed 7-8-04; 8:45 am] BILLING CODE 4913-13-P

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BW 2005-17 BELL HELICOPTER TEXTRON AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS

2005-16-04 Bell Helicopter Textron: Amendment 39-14209. Docket No. FAA-2005-21230; Directorate Identifier 2004-SW-51-AD. Applicability Model 206A and 206B helicopters modified by Aeronautical Accessories, Inc. Supplemental Type Certificate SH1392SO, with high forward crosstube, part number (P/N) 206-321-001 with serial number (S/N) 1001 through 1152, and high aft crosstube, P/N 206-321-002 with S/N 2001 through 2152, installed, certificated in any category. Compliance Required as indicated, unless accomplished previously. To detect a crack in the crosstube, which could lead to failure of the crosstube, collapse of the landing gear, and subsequent loss of control of the helicopter, accomplish the following: (a) Within 300 hours time-in-service (TIS) or 60 days, whichever occurs first, and after that at intervals not to exceed 300 hours TIS or 12 months, whichever occurs first, remove each crosstube and inspect it for cracks. Replace any cracked crosstube with an airworthy crosstube before further flight. Note: Aeronautical Accessories, Inc. Alert Service Bulletin No. AA-03121, dated October 25, 2004, pertains to the subject of this AD. (b) 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 Rotorcraft Certification Office, Rotorcraft Directorate, FAA, for information about previously approved alternative methods of compliance. (c) This amendment becomes effective on September 12, 2005. Issued in Fort Worth, Texas, on July 29, 2005. S. Frances Cox, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 05-15581 Filed 8-5-05; 8:45 am] BILLING CODE 4910-13-P

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BW 2005-17 ROBINSON HELICOPTER COMPANY AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS

2005-16-05 Robinson Helicopter Company: Amendment 39-14210. Docket No. FAA-2005-22026; Directorate Identifier 2005-SW-05-AD. Applicability Model R-22 series helicopters, modified with a door assembly manufactured by Tech-Tool Plastics, Inc., in accordance with STC No. SR09189RC, certificated in any category. Compliance Required as indicated, unless accomplished previously. To prevent separation of a door window or door assembly from the helicopter, which could damage the tail rotor during flight and result in loss of control of the helicopter, accomplish the following: (a) Within 30 days, inspect the left-hand and right-hand door assemblies as follows: (1) Visually inspect each pilot and copilot door assembly integral frame for a crack in the locations depicted in Figure 1 of this AD. If a crack is found, before further flight, replace the cracked door assembly, part number (P/N) R-22-101-51 or P/N R-22-101-53 (left-hand door assembly), or P/N R-22-101-52 or P/N R-22-101-54 (right-hand door assembly), with an airworthy door assembly. If you use door assembly, P/N R-22-101-51 or P/N R-22-101-53 (left-hand door assembly), or P/N R-22-101-52 or P/N R-22-101-54 (right-hand door assembly) as the replacement, then install it in accordance with Tech-Tool Plastics, Inc. Installation Instructions TTP-1R, Revision A, dated November 21, 1997, and with the sections titled ''Door Weather Seal Installation'' and ''Cotter Pin Installation'' in Tech-Tool Plastics, Inc. Service Bulletin No. TTP2005-01, Revision A, dated February 1, 2005 (SB).

11

2005-16-05 2

(2) If no crack is found in any door assembly integral frame, do the following: (i) Visually inspect the weather seal set in each door assembly to determine if it is airworthy and installed properly. If it is not airworthy, before further flight, replace it with either the weather seal set, P/N 74418X14L and P/N 74814X12BL, supplied by Tech-Tool Plastics, Inc., in accordance with the ''Door Weather Seal Installation'' section of the SB, or replace it with any other airworthy door weather seal set in accordance with the applicable FAA-approved installation instructions. If an airworthy weather seal set, P/N 74418X14L and P/N 74814X12BL, is not installed properly, before further flight, reinstall it in accordance with the ''Door Weather Seal Installation'' section of the SB. If the improperly installed weather seal set is not the weather seal set supplied by Tech-Tool Plastics, Inc., before further flight, reinstall it in accordance with the applicable FAA-approved installation instructions. (ii) Visually inspect each door hinge on each door assembly to determine if the cotter pins, P/N MS24665-136, are installed in accordance with the ''Cotter Pin Installation'' section of the SB. If a cotter pin is not installed in accordance with the ''Cotter Pin Installation'' section of the SB, before further flight, install the cotter pins in accordance with the ''Cotter Pin Installation'' section of the SB.

12

2005-16-05 3

Note: The installation of nylon adjustment screws and the trimming of door assembly edges are important maintenance actions that may reduce the strength of a door assembly if not done properly. (b) After accomplishing the inspections in paragraphs (a) through (a)(2)(ii) of this AD, at intervals not to exceed 100 hours time-in-service, visually inspect each pilot and copilot door assembly integral frame for a crack in the locations depicted in Figure 1 of this AD. (c) If a crack is found, before further flight, replace the cracked door assembly, P/N R-22101-51 or P/N R-22-101-53 (left-hand door assembly), or P/N R-22-101-52 or P/N R-22-101-54 (right-hand door assembly), with an airworthy door assembly. If the replacement door assembly is P/N R-22-101-51 or P/N R-22-101-53 (left-hand door assembly), or P/N R-22-101-52 or P/N R-22101-54 (right-hand door assembly), then install it in accordance with Tech-Tool Plastics, Inc. Installation Instructions TTP-1R, Revision A, dated November 21, 1997, and ''Door Weather Seal Installation'' and ''Cotter Pin Installation'' sections of the SB. (d) If any of the inspections required by this AD reveal a crack in any door assembly frame, report the following information to the FAA within 30 days after discovering the crack: a description of the crack and the specific helicopter model involved. You may submit your report via mail, Fax, or telephone to the FAA, ATTN: ASW-170 (Marc Belhumeur), 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5177, fax (817) 222-5783. Information collection requirements contained in this AD have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-0056. (e) 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 Rotorcraft Certification Office, Rotorcraft Directorate, FAA, for information about previously approved alternative methods of compliance. (f) The inspections, repairs and replacements, if necessary, shall be done in accordance with the specified portions of Tech-Tool Plastics, Inc. Installation Instructions TTP-1R, Revision A, dated November 21, 1997, which provides door assembly installation instructions, and the specified portions of Tech-Tool Plastics, Inc. Service Bulletin No. TTP2005-01, Revision A, dated February 1, 2005, which describes door weather seal and cotter pin installation procedures and door assembly inspection procedures. The Director of the Federal Register approved this incorporation by reference in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Tech-Tool Plastics, Inc., 7800 Skyline Park Drive, Fort Worth, Texas, 76108; telephone: (817) 246-4694; fax: (817) 246-7402; E-mail: [email protected]. (g) This amendment becomes effective on August 26, 2005. Issued in Fort Worth, Texas, on July 29, 2005. S. Frances Cox, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 05-15580 Filed 8-10-05; 8:45 am] BILLING CODE 4910-13-P

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BW 2005-17 PILATUS AIRCRAFT LTD AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS

2005-17-01 Pilatus Aircraft Ltd.: Amendment 39-14221; Docket No. FAA-2005-20515; Directorate Identifier 2005-CE-09-AD. When Does This AD Become Effective? (a) This AD becomes effective on September 29, 2005. What Other ADs Are Affected By This Action? (b) None. What Airplanes Are Affected by This AD? (c) This AD affects the following airplanes, all manufacturer serial numbers (MSN), that are certificated in any category. Note 1: These airplanes are also identified as Fairchild Republic Company PC-6 series airplanes and Fairchild Heli Porter PC-6 series airplanes. Models (1) PC–6 (2) PC–6–H1 (3) PC–6–H2 (4) PC–6/350 (5) PC–6/350–H1 (6) PC–6/350–H2 (7) PC–6/A (8) PC–6/A–H1 (9) PC–6/A–H2 (10) PC–6/B–H2 (11) PC–6/B1–H2 (12) PC–6/B2–H2 (13) PC–6/B2–H4 (14) PC–6/C–H2 (15) PC–6/C1–H2

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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. We are issuing this AD to detect and correct cracks in the stabilizer-trim attachment and surrounding structural components, which could result in failure of the stabilizer-trim attachment. This failure could lead to loss of control of the airplane. What Must I Do To Address This Problem? (e) To address this problem, you must do the following: Actions (1) Inspect the following: (i) the stabilizer-trim attachment and structural components (fitting, connecting piece, bearing fork, bearing support assembly, and auxiliary frame, as applicable) for cracks and corrosion; and. (ii) the diameters of the actuator attachment bolt holes on the fittings, auxiliary frame, and connecting piece (as applicable) for discrepancies. (2) If cracks are found during any inspection required in paragraph (e)(1)(i) of this AD, replace the defective part with a new part.

(3) If corrosion or discrepancies are found during any inspection required in paragraphs (e)(1)(i) and (e)(1)(ii) of this AD, do the following: (i) replace the defective part with a new part if the corrosion or discrepancy is beyond the repairable limits stated in the service information; or. (ii) repair the defective part if the corrosion or discrepancy is within the repairable limits stated in the service information.

Compliance Within the next 100 hours time-inservice (TIS) after September 29, 2005 (the effective date of this AD). Repetitively inspect thereafter at intervals not-to-exceed 3,500 hours TIS or 7 years, whichever occurs first.

Procedures Follow Pilatus PC–6 Service Bulletin No. 53–001, Rev. No. 1, dated June 1, 2005.

Replace the defective part before further flight after the inspection in which cracks are found. After each replacement, continue with the repetitive inspection requirement in paragraph (e)(1) of this AD. Replace or repair the defective part before further flight after the inspection in which corrosion or discrepancies are found. After each replacement or repair, continue with the repetitive inspection requirement in paragraph (e)(1) of this AD.

Follow Pilatus PC–6 Service Bulletin No. 53–001, Rev. No. 1, dated June 1, 2005.

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Follow Pilatus PC–6 Service Bulletin No. 53–001, Rev. No. 1, dated June 1, 2005.

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Actions (4) Replace the following: (i) all Fairchild connecting pieces, part number (P/N) 6232.0026.XX, with a Pilatus connecting piece, P/N 6232.0026.XX. The Fairchild part has a rivet in the middle that is not on the Pilatus part; and. (ii) all fittings, P/N 116.40.06.033 without an index after the P/N, with an improved part, P/N 116.40.06.033 with an index of "A"or "B" after the P/N or with P/N 116.40.06.112.

Compliance Within the next 100 hours TIS after September 29, 2005 (the effective date of this AD). After replacement, repetitively inspect thereafter at intervals not-to-exceed 3,500 hours TIS or 7 years, whichever occurs first. If after the inspection required in paragraph (e)(1) of this AD, you determine that you already have a P/N 116.40.06.033 with an index of "A"or "B"or a P/N 116.40.06.112 installed, repetitively inspect thereafter at intervals not-to-exceed 3,500 hours TIS or 7 years, whichever occurs first after the part was installed. (5) Do not install any of the following: As of September 29, 2005 (the (i) Fairchild connecting piece, effective date of this AD). P/N 6232.0026.XX (it has a rivet in the middle that is not on the Pilatus part); and. (ii) fitting, P/N 116.40.06.033, without an index after the part number.

Procedures Follow Pilatus PC–6 Service Bulletin No. 53–001, Rev. No. 1, dated June 1, 2005.

Follow Pilatus PC–6 Service Bulletin No. 53–001, Rev. No. 1, dated June 1, 2005.

Note 2: Even though not required in this AD, the FAA recommends that you send all defective parts to Pilatus at the address specified in paragraph (h) of this AD. With the part, include the aircraft serial number, flying hours, and cycles. 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? (g) Swiss AD HB-2005-263, effective date June 16, 2005, also addresses the subject of this AD.

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Does This AD Incorporate Any Material by Reference? (h) You must do the actions required by this AD following the instructions in Pilatus PC-6 Service Bulletin No. 53-001, Rev. No. 1, dated June 1, 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 Pilatus Aircraft Ltd., Customer Liaison Manager, CH-6371 Stans, Switzerland; telephone: +41 41 619 6580; facsimile: +41 41 619 6576. 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-2005-20515; Directorate Identifier 2005-CE-09-AD. Issued in Kansas City, Missouri, on August 8, 2005. Kim Smith, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-16000 Filed 8-12-05; 8:45 am] BILLING CODE 4910-13-P

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