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FEDERAL AVIATION ADMINISTRATION AIRWORTHINESS DIRECTIVES SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS BIWEEKLY 2005-19 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

2005-18-12

Hartzell Propeller Inc. Propellers

2005-18-20

Goodrich De-icing and Specialty Systems

2005-18-21 2005-18-22 2005-19-07 2005-19-10 2005-19-11

Raytheon Aircraft Company Raytheon Aircraft Company Raytheon Aircraft Company Turbomeca Lycoming Engines

Propeller: HC–92W, BHC–92W, HC–92Z, BHC–92Z, HC–B3P, HC–B3R, HC–B3W, BHC–B3W, HA–B3Z, HC–B3Z Hub Model Series Appliance: P4E1188 series, P4E1601 series, P4E2200 series, P4E2271-10, P4E2575-7, P4E2575-10, P4E2598-10, P5855BSW, P6199SW, P6592SW, P6662SW, and P6975-11 1900, 1900C, 1900C (C–12J), 1900D 390 390 Engine: Arrius 2 F turboshaft Engine: AEIO-360, IO-360, O-360, LIO-360, LO-360, AEIO-540, IO-540, O-540, and TIO-540 series

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

Biweekly 2005-19

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BW 2005-19 HARTZELL PROPELLER INC. PROPELLERS AIRWORTHINESS DIRECTIVE PROPELLER SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2005-18-12 Hartzell Propeller Inc. Propellers: Amendment 39-14252. Docket No. FAA-200419955; Directorate Identifier. 2004-NE-17-AD. Effective Date (a) This airworthiness directive (AD) becomes effective October 14, 2005. Affected ADs (b) None. Applicability (c) This AD applies to Hartzell propeller assemblies with hub model series specified in Table 1 of this AD. These propellers are installed on, but not limited to, the aircraft listed in Table 2 of this AD. TABLE 1.—LIST OF APPLICABLE PROPELLER ASSEMBLIES BY HUB MODEL SERIES HC–92W Hub Model Series BHC–92W Hub Model Series HC–92Z Hub Model Series BHC–92Z Hub Model Series HC–B3P Hub Model Series HC–B3R Hub Model Series HC–B3W Hub Model Series BHC–B3W Hub Model Series HA–B3Z Hub Model Series HC–B3Z Hub Model Series TABLE 2.—LIST OF AIRPLANES THAT MIGHT USE AN AFFECTED PROPELLER ASSEMBLY Aircraft manufacturer Aircraft model AERMACCHI (AERONAUTICA MACCHI) AM–3C AERO COMMANDER 560–F680, 680E, 680F, 680FL, 680FLP, 720

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2005-18-12 2

Aircraft manufacturer AEROSPATIALE (MORANE SAULNIER) AEROSTAR AIRCRAFT CORP. AEROTEK II, INC. (CALLAIR) AIR & SPACE BEECH

BUSHMASTER AIRCRAFT CORP CESSNA

DE HAVILLAND CANADA DORNIER FOUND BROTHERS GOODYEAR (LOCKHEED MARTIN) GRUMMAN (GULFSTREAM AERO.) GRUMMAN (MCKINNON) HELIO

ICA (ROMANIA) JOBMASTER KWAD LAKE (REVO) LOCKHEED MESSERSCHMITT MOONEY NAVY NORD PACIFIC AEROSPACE (FLETCHER) PIAGGIO

Aircraft model 733 360 B1A (CALLAIR) 18, 18A 18 SERIES C45 35 SERIES A65, 65, 65–80, 65–A80, 65–B80, 65–88 95, B95, B95A, D95A, E95 70 C18S [(C–45(A, F), UC–45(B, F), AT–7 (A, B, C), JRB–(1, 2, 3, 4), SNB–2(C)] C18S, AT–11 C–45G,C–45H; TC–45G, H, J; RC–45J D18S,E18S, G18S, H18; 3N, 3NM, 3TM E50, F50, G50, H50, J50 BUSHMASTER 2000 172 175, 175A 190, 195, A, B 421, 421A A185E, A185F (SEAPLANES ONLY) T50 DHC–2 MKI DO28D, DO28D–1 100 FBA–2C GZ20, GZ20A G44, G44A G21A H–250 H–295, HT–295 (U–10D) H–395 (L–28A, U–10B) H–500 IAR–831 DGA–15P SUPER–V LA–4 12A 207 M20A N3N–3 3400, 3402 FU–24, FU–24A P–166B, C

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2005-18-12 3

Aircraft manufacturer PILATUS PIPER

PROCAER REVO (COLONIAL) SAAB SCHWEIZER (GRUMMAN) SIMMERING GRAZ PAUKER A.G SPARTON UTVA WDL AVIATION (formerly WDL FLUGDIENST) WEATHERLY

Aircraft model PC–6/350; PC–6/350–H1, –H2 PA–23 PA–24 PA–25 F15/B C–2 91D SAFIR G–164 SGP222 7W 66 An Airship 201B, 201C, 620, 620A, 620C

Unsafe Condition (d) This AD results from two events where a ''Z-shank'' blade failed and separated and the results of teardown inspections that detected corrosion in the blade bore. We are issuing this AD to detect corrosion and mechanical damage that can cause failure of a propeller, which could result in loss of control of the airplane. 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. Aircraft With Experimental Type Certificates (f) We recommend that you comply with the inspection requirements of this AD, if you have an aircraft with an experimental type certificate, and you have a propeller hub model listed in this AD installed on that aircraft. Inspection of the Propeller (g) If the time-since-overhaul (TSO) of the propeller is 10 years or fewer on the effective date of this AD, no further action is required. (h) If the propeller assembly was inspected using Hartzell Service Bulletin (SB) No. HC-SB61-136, Revision I, dated April 25, 2003; SB No. 136, Revision H, dated March 12, 1993; or SB No. 136, Revision G, dated November 15, 1991; no further action is required. (i) If the TSO of the propeller assembly is more than 10 years on the effective date of this AD, or if the TSO is unknown, or if the propeller has not complied with Hartzell SB No. HC-SB-61-136, Revision I, dated April 25, 2003; or SB No. 136, Revision H, dated March 12, 1993; or SB No. 136, Revision G, dated November 15, 1991; perform the actions specified in Table 3 of this AD. Use the compliance times specified in Table 3 of this AD. Information on inspecting the propeller assembly

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2005-18-12 4

for cracks, corrosion or pits, nicks, scratches, wear, blade minimum dimensions, and damage in the blade balance bore can be found in the applicable Hartzell maintenance manuals. TABLE 3.—COMPLIANCE TIMES FOR ONETIME INSPECTION If the TSO of the Then... Perform the the propeller assembly inspection... on the effective date of this AD is... (1) More 25 years or (a) Disassemble and clean the propeller assembly Within 12 the TSO is not known. (b) Perform visual and nondestructive inspections of months after the effective date of propeller components for cracks, corrosion or pits, nicks, scratches, wear, blade minimum dimensions, and damage this AD. in the blade balance hole. (c) Inspect and rework the propeller blade bore. Use 3.A. of the Accomplishment instructions of Hartzell SB No. HC–SB–61–136, Revision I, dated April 26, 2003. (d) Repair and replace with serviceable parts, as necessary. (e) Reassemble and test. (2) Twenty-one to 25 (a) Disassemble and clean the propeller assembly Within 18 years months after the (b) Perform visual and nondestructive inspections of effective date of propeller components for cracks, corrosion or pits, nicks, scratches, wear, blade minimum dimensions, and damage this AD. in the blade balance hole. (c) Inspect and rework the propeller blade bore. Use 3.A. of the Accomplishment instructions of Hartzell SB No. HC–SB–61–136, Revision I, dated April 26, 2003. (d) Repair and replace with serviceable parts, as necessary. (e) Reassemble and test. (3) Sixteen to 20 years (a) Disassemble and clean the propeller assembly Within 24 months after the (b) Perform visual and nondestructive inspections of effective date of propeller components for cracks, corrosion or pits, nicks, scratches, wear, blade minimum dimensions, and damage this AD. in the blade balance hole. (c) Inspect and rework the propeller blade bore. Use 3.A. of the Accomplishment instructions of Hartzell SB No. HC–SB–61–136, Revision I, dated April 26, 2003. (d) Repair and replace with serviceable parts, as necessary. (e) Reassemble and test. (4) Eleven to 15 years (a) Disassemble and clean the propeller assembly Within 36 months after the (b) Perform visual and nondestructive inspections of effective date of propeller components for cracks, corrosion or pits, nicks, scratches, wear, blade minimum dimensions, and damage this AD. in the blade balance hole. (c) Inspect and rework the propeller blade bore. Use 3.A. of the Accomplishment instructions of Hartzell SB No. HC–SB–61–136, Revision I, dated April 26, 2003. (d) Repair and replace with serviceable parts, as necessary. (e) Reassemble and test.

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2005-18-12 5

Propeller Overhaul (j) Performing an overhaul of the propeller assembly after the effective date of this AD constitutes compliance with the requirements specified in this AD. The latest applicable Maintenance Manuals issued by Hartzell Propeller Inc. contain information on overhauling a propeller assembly. (k) The time-since-overhaul only changes if you overhaul the propeller assembly while performing the requirements specified in this AD. Reporting Requirements (l) Report inspection results to the Manager, Chicago Aircraft Certification Office, FAA, Small Airplane Directorate, 2300 East Devon Ave, Des Plaines, IL 60018, within 15 working days of the inspection. The Office of Management and Budget (OMB) approved the reporting requirements and assigned OMB control number 2120-0056. Alternative Methods of Compliance (m) 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. Related Information (n) None. Material Incorporated by Reference (o) You must use Hartzell Service Bulletin No. HC-SB-61-136, Revision I, dated April 25, 2003, to perform the inspections and rework 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 Hartzell Propeller Inc. Technical Publications Department, One Propeller Place, Piqua, OH 45356; telephone (937) 778-4200; fax (937) 778-4391, 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 205900001, 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 29, 2005. Peter A. White, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 05-17667 Filed 9-8-05; 8:45 am] BILLING CODE 4910-13-P

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BW 2005-19 GOODRICH DE-ICING AND SPECIALTY SYSTEMS AIRWORTHINESS DIRECTIVE APPLIANCE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2005-18-20 Goodrich De-icing and Specialty Systems: Amendment 39-14261. Docket No. FAA2005-20847; Directorate Identifier. 2004-NE-35-AD. Effective Date (a) This airworthiness directive (AD) becomes effective October 14, 2005. Affected ADs (b) None. Applicability (c) This AD applies to Goodrich De-icing and Specialty Systems ''FASTprop'' propeller deicers, part numbers (P/Ns) P4E1188 series, P4E1601 series, P4E2200 series, P4E2271-10, P4E25757, P4E2575-10, P4E2598-10, P5855BSW, P6199SW, P6592SW, P6662SW, and P6975-11, installed. These propeller de-icers are installed on, but not limited to, the airplanes listed in Table 1 of this AD. TABLE 1.—GOODRICH "FASTPROP" PROPELLER DE-ICERS De-icer P/N Installed on, but not limited to P4E1188–2 Metal propellers operated up to 2,900 rpm on: Cessna 210E, 210F, 210G, 210H, 210J, 210K, 210L, T210F, T210G, T210H, T210J, T210K, and T210L. With Supplemental Type Certificate (STC) SA1–502 on Raytheon (Beech) D18C, D18S, E18S, G18S, H18, C45G, C45H, TC45G, and TC45H. P4E1188–3 Metal propellers operated up to 2,900 rpm on: Raytheon (Beech) D18C, D18S, E18S, E18S–9700, G18S, H18, C–45G, C–45H, C– 45J, TC–45G. TC–45H, TC–45J (SNB–5), and JRB–6. With STC SA1–503 on Raytheon (Beech), E50, F50, G50, H50, J50, and 65. With STC SA15EA on Raytheon (Beech) E50, F50, G50, H50, J50, 65, and 65–80. Raytheon (Beech) 55, B55, D55, D55A, E55, 95–C55, 95–C55A, 58, 95–55, 95–A55, 95–B55, 56TC, 60, 65, 65–80, 65–90, 65–A90, B90, C90, 99, 99A, A99, A99A, 100, and A100. With STC SA1–506 on Cessna 310. With McCauley props on Cessna 310, 320, 340, 401, 402, 411, 414, and 421.

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De-icer P/N Installed on, but not limited to P4E1188–3 With STC SA2424WE on Cessna 402. (continued) With STC SA132EA on Twin Commander (Gulfstream) 560A, 560E, 680, 680E, and 720. With STC SA179EA on Twin Commander (Gulfstream) 560F, 680FL, 680FL(P), and 680–F. With STC SA1–520 on Twin Commander (Gulfstream) 560A, 560E 680, 680E, and 720. On the following models equipped with 90-amp generator: Twin Commander (Gulfstream) 500B, 500S, and 500U. With STC SA1–607 on Twin Commander (Gulfstream) 500A. With STC SA2478SW on Twin Commander (Gulfstream) 500. With STC SA2891WE or STC SA2691WE on Twin Commander (Gulfstream) 680F, 680FP, and 680FL(P). Twin Commander (Gulfstream) 680V, 680T, 680W, and 681. Mitsubishi Heavy Industries MU–2 series. With STC SA195EA on Piper PA–23–250, E23–250 (serial number (SN) 27–2505 up). Piper PA–31 (SN 31–5 up), PA–31–300 (SN 31–5 up), PA–31–325 (SN31–5 up), and PA–31–350 (SN 31–5001 up). P4E1188–4 Metal propellers operated up to 2,900 rpm on: B–N Group Ltd. (Britten Norman) BN–2, BN–2A, and BN–2A Mark III series, Vulcanair (Partenavia) P–68, Piper Aerostar 600, 601, and 601P. On the following models equipped with 3-blade props: Short Brothers SC7 series 3, M7 Aerospace (Fairchild) SA26–T, SA26–AT, SA226–T, SA226–AT, and SA226– TC. The following models equipped with 70-amp alternators and Hartzell HC–A3XK props: Twin Commander (Gulfstream) 500B, 500S, and 500U. The following models equipped with 70-amp alternator and Hartzell HC–C3YR–2 props: Twin Commander (Gulfstream) 500S and 500U. The following model with 70- or 100-amp alternators and Hartzell HC–C3YR–R props: Twin Commander (Gulfstream) 500S (SN 3115 up). With STC SA2478SW on model Twin Commander (Gulfstream) 500. With STC SA2691WE or SA2891WE on the following models: Twin Commander (Gulfstream) 680F, 680FL, and 680FLP. P4E1188–5 Metal propellers operated up to 2,900 rpm on: With Hartzell HC–B3TN–3 props on Raytheon (Beech) D18C, D18S, E18S, E18S– 9700, G18S, H18, C45G, C45H, TC45G, TC45H, C45J, TC45J (SN B–5), JRB–6, 99, 99A, A99, A99A, 99B, B99, 100, A100, A100A, A100C, and B100. With Hartzell HC–B3TN–3 props on Raytheon (Beech) 65–90, 65–A90, 65–A90–1, 65–A90–2, 65–A90–3, 65–A90–4, B90, C90, E90, and H90. With Hartzell HC–B3TN–3 props on Bombardier (deHavilland) DHC–6–300, Israel Aircraft Industries 101 Arava, Mitsubishi Heavy Industries MU–2B–10, –15, –20, – 25, –26, –30, –35, –36, MU–2 Series, Pilatus PC–6, Piper PA–31T (SN 31T–7400002 up), and PA31T1. With STC SA2293SW on British Aerospace (Scotland) Handley Page Jetstream 137 Mark I. AeroSpace Technologies of Australia (Government Aircraft Factories) N22B. Short Brothers SC7 series 3 equipped with 4-blade props.

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De-icer P/N Installed on, but not limited to P4E1188–6 Metal propellers operated up to 2,900 rpm on: With Hartzell HC–B3TN–5( ) props on Cessna 425 and 441. Embraer EMB–110P1 and 110P2. Short Brothers SC7 series 3 equipped with 3-blade props. M7 Aerospace (Fairchild) SA226–T, SA226–AT, and SA226–TC. P4E1188–7 Metal propellers operated up to 2,900 rpm on: Mitsubishi Heavy Industries MU–2B, MU–2B–26A, MU–2B–36A, MU–2B–40, and MU–2B–60. P4E1601–3 Metal propellers operated up to 2,900 rpm on: Piper PA31 (SN 5 up), PA31–300 (SN 5 up), PA31–325 (SN 5up), PA31P (SN 31P–3 up), and PA31–350 (SN 31–5001 up). P4E1601–4 Metal propellers operated up to 2,900 rpm on: Raytheon (Beech) 65–88. P4E1601–5 Metal propellers operated up to 2,900 rpm on: Casa C212CB. Twin Commander (Gulfstream) 690 and 690A. P4E1601–7 Metal propellers operated up to 2,900 rpm on: Raytheon (Beech) B55, E55, 56TC, 58P, and 60. With STC SA2369SW on Nord 262A. The following models equipped with 70- or 100-amp alternator and Hartzell HC– C3YR–2 props: Twin Commander (Gulfstream) 500S (SN 3115 up) and Twin Commander (Gulfstream) 685. Short Brothers SD3–30. P4E1601–10 Metal propellers operated up to 2,900 rpm on: Raytheon (Beech) B55, E55, 56TC, 58P, and 60. Twin Commander (Gulfstream) 690C and 695. M7 Aerospace (Fairchild) SA–226–TB, SA227–AC, SA227–TT, and SA227–AT. P4E2200–2 Metal propellers operated up to 2,900 rpm on: With STC SA00719LA on Raytheon (Beech) A36. With STC SA00718LA on Raytheon (Beech) B36TC. Raytheon (Beech) V35 equipped with 2- or 3-blade McCauley props. P4E2200–3 Metal propellers operated up to 2,900 rpm on: Raytheon (Beech) E50, F50, G50, H50, and J50. Cessna E310J, T310P, 310, 310E, 310J, 310K, 310L, 310N, 320, 320D, 320F, 40, 402A, 402B, 411, 411A, 414, 421, 421A, and 421B. Piper PA23–250. P4E2200–4 Metal propellers operated up to 2,900 rpm on: B–N Group Ltd. (Britten Norman) BN–2A Mark III, BN–2, BN–2A. Piper 600, 601, 601P. P4E2200–10 Metal propellers operated up to 2,900 rpm on: With Volpar Turboliner conversion on the following models: Raytheon (Beech) D18C and D18S. Raytheon (Beech) 56TC, A56TC, 65–90, 65–A90, B90, C90, E90, H90, 99, A99, 99A, B99, 99B, 100, A100, A100A, A100C, B100, and 200. Embraer EMB 110P1 and 110P2. Mitsubishi Heavy Industries MU–2B, MU–2B–10, MU–2B–15, MU–2B–20, MU– 2B–25, MU–2B–30, and MU–2B–35. 14

2005-18-20 4

De-icer P/N Installed on, but not limited to P4E2200–10 Pilatus PC–6. (continued) Piper PA31–350 (SN 5001 up) and PA31P (SN 31P–3 up). M7 Aerospace (Fairchild) SA26–T, SA26–AT, SA226–T, SA226TC, and SA226AT. Twin Commander (Gulfstream) 500B, 500U, 560F, 680F, 680FP, 680FL, and 680FLP. P4E2200–21 Metal propellers operated up to 2,900 rpm with STC SA812NE on the following models: Raytheon (Beech) 65–90 series, B90, C90, E90, F90, H90, 99 A99 series, C99, 100, A100 series, B100, and 200. Embraer EMB110 series. M7 Aerospace (Fairchild) SA226–AT, SA226–T, and SA–226TC. Mitsubishi Heavy Industries MU–2B, MU–2B–10, MU–2B–15, MU–2B–20, MU– 2B–25, MU–2B–26, MU–2B–30, MU– 2B–35, and MU–2B–36. Pilatus PC–6, PC–6B–H2, PC–6B1–H2, PC–6C–H2, PC–6C1–H2, and PC–7. Piper PA–31T, PA–31T1, PA–31T1A, PA–31T2A, PA–31T3, and PA–31T–1040. P4E2271–10 Metal propellers operated up to 2,900 rpm on: B–N Group Ltd. (Britten-Norman) BN–2, BN–2A series, and BN–2A Mark III. With Volpar Turboliner conversion on the following models: Raytheon (Beech) D18C, and D18S. The following models equipped with 2- or 3-blade props: S35, V35, V35A, V35B, 35– C33A, F33A, F33C, and A36. Raytheon (Beech) E50, F50, G50, H50, J50, E55, E55A, 56TC, A56TC, 58, 58A, 60, A60, B60, 65–90, 65–A90, B90, C90, E90, H90, 95–B55, 95–B55A, 99, A99, A99A, 99A, 100, A100, A100A, A100C, B100, and 200. With STC SA00966CH on Raytheon (Beech) C90B With STC SA3593NM on Raytheon (Beech) E90. With STC SA4131NM on Raytheon (Beech) F90. With STC SA2698NM on the following models: Raytheon (Beech) 200 and B200. Cessna 310, 310J, 310K, 310L, 310N, E310J, T310P, 320D, 320E, 320F, 340, 401A, 401B, 402A, 402B, 411, 411A, 414A, 414B, 421A, and 421B. With STC SA3532NM on Bombardier (deHavilland) DHC–6. With STC SA2369SW on Nord 262A. Mitsubishi Heavy Industries MU–2B–10, MU–2B–15, MU–2B–20, MU–2B–25, MU– 2B–26A, MU–2B–30, MU–2B–35, MU–2B–36A, MU–2B–40, and MU–2B–60. Piper PA23, PA23–160, PA23–250, PA–E23–250 (SN 27–2505 UP), PA31 (SN 31–5 up), PA31–300 (SN 31–5 up), PA31–325 (SN 31–5 up), PA31–350 (SN 5001 up) PA34–200, PA34–200T, PA600, PA601, and PA601P. Pilatus PC–6. Short Brothers SD–3–30. M7 Aerospace (Fairchild) SA26–T, SA26–AT, SA226–T, SA226–AT, SA226TB, and SA226–TC. Twin Commander (Gulfstream) 500B, and 500U. P4E2575–7 Metal propellers operated up to 1,700 rpm on Raytheon (Beech) 300. P4E2575–10 Metal propellers operated up to 1,700 rpm on Raytheon (Beech) 300. P4E2598–10 Metal propellers operated up to 1,591 rpm on: AvCraft (Dornier) 228, M7 Aerospace (Fairchild) SA227–TT (SN 421–541), SA227– AT (SN 423–549), and SA227–AC (SN 420–545).

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De-icer P/N Installed on, but not limited to P5855BSW Metal propellers on: Cessna T310Q, T310R, 340, 340A, 402B, 402C, 414, 414A, 421A, and 421B. P6199SW Metal propellers operated up to 2,900 rpm on: The following models equipped with McCauley D3A34C401 or D3A34C402 props: Cessna 210L, 210M, 210N, P210N, T210L, T210M, and T210N. P6592SW Metal propellers operated up to 2,900 rpm on: Various aircraft models equipped with McCauley 3AF32C504, 3AF32C505, 3AF32C506, or 3AF32C507 props. P6662SW Metal propellers operated up to 2,900 rpm on: Various aircraft models equipped with McCauley 3AF32C512/G–82NEA–5, 3AF32C511/G–82NEA–4, or 4HFR34C7 props. P6975–11 Metal propellers operated up to 2,900 rpm on: With STC SA812EA and equipped with Hartzell HC–B3TN–3D, HC–B3TN–5C, or HC–B3TN–5M props: Air Tractor, AT–302 and AT–400. With STC SA812EA and equipped with Hartzell HC–B3TN–3C or HC–B3TN–3D props: Quality Aerospace (Ayres) S2R–T11. With STC SA2204WE and equipped with Hartzell HC–B3TN–5C props: Raytheon (Beech) D18C, D18S, E18S–9700, C45G, C45H, TC–45G, TC–45H, and TC–45J. Raytheon (Beech) T–34C equipped with Hartzell HC–B3TN–3H props. The following models equipped with Hartzell HC–B3TN–2B, HC–B3TN–3B, or HC– B3TN–3M props: Raytheon (Beech) 65–90, 65–A–90, 65–A90–1, 65–A90–2, 65– A90–3, and 65–A90–4. The following models equipped with Hartzell HC–B3TN–3B or HC–B3TN–3M props: Raytheon (Beech) B90, C90, E90, and H90. Raytheon (Beech) F90 equipped with Hartzell HC–B4TN–3A or HC–B4TN–3B props. The following models equipped with Hartzell HC–B3TN–3B props: Raytheon (Beech) 99, 99A, A99, and A99A. The following models equipped with Hartzell HC–B3TN–3B or HC–B3TN–3M props: Raytheon (Beech) C99, and 100. The following models equipped with Hartzell HC–B4TN–3 or HC–4TN–3A props: Raytheon (Beech) A100, A100A, and A100–1. Raytheon (Beech) B100 equipped with Hartzell HC–B4TN–5C or HC–B4TN–5F props. The following models equipped with Hartzell HC–B3TN–3G or HC–B3TN–3N props: Raytheon (Beech) 200, 200C, 200CT, 200T, A200, A200C, A200CT, B200, B200C, B200CT, and B200T. Raytheon (Beech) JRB–6 with STC SA1171WE equipped with Hartzell HC–B3TN– 5C props. British Aerospace HP.137MK.1 with STC SA2293WE equipped with Hartzell HC– B3TN–3D props. CASA C212–100 Aviocar equipped with Hartzell HC–B4TN–5EL props. Cessna 441 equipped with Hartzell HC–B3TN–5E or HC–B3TN–5M props. Bombardier (deHavilland) DHC–2MK.III equipped with HC–B3TN–3, HC–B3TN– 3B, or HC–B3TN–3BY props. Bombardier (deHavilland) DHC–6–300 equipped with Hartzell HC–B3TN–3(D)(Y) props.

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De-icer P/N Installed on, but not limited to P6975–11 Embraer EMB–110P1/2 equipped with Hartzell HC–B3TN–3C or HC–B3TN–3D (continued) props. The following models equipped with Hartzell HC–B3TN–5( ) props: M7 Aerospace (Fairchild) SA226–AT, and SA226T. M7 Aerospace (Fairchild) SA226–TC equipped with Hartzell HC–B4TN–5( ) props. M7 Aerospace (Fairchild) SA226–TC with STC SA344GL equipped with Hartzell HC–B3TN–5( ) props. M7 Aerospace (Fairchild) SA226–TC with STC SA344Gl. The following models equipped with Hartzell HC–A3VF–7 or HC–3VH–7B props: AeroSpace Technologies of Australia (Government Aircraft Factories) N22B and N24A. The following models equipped with Hartzell HC–B3TN–3D props: IAI Arava 101 and 101B. The following models equipped with Hartzell HC–B3TN–3DY props: McKinnon (Grumman) G–21E and G–21G. The following models equipped with HC–B3TN–5( ) props: Mitsubishi Heavy Industries MU–2B, and MU–2B–10. The following models equipped with Hartzell HC–B3TN–5 props: Mitsubishi Heavy Industries MU–2B–15, MU–2B–20, MU–2B–25, MU–2B–26, MU–2B–30, MU–2B– 35, and MU–2B–36. The following models equipped with Hartzell HC–B3TN–3C props: Pilatus PC–6, PC–6/B–H2, PC–6/B1–H2, PC–6/C– H2, PC–6/C1–H2. The following models equipped with Hartzell HC–B3TN–3B props: Piper PA–31T and PA31T1. The following models equipped with Hartzell HC–B3TN–3B or HC–B3TN–3K props: Piper PA42 and PA42–720. The following model equipped with Hartzell HC–B3TN–5( ) props: Short Brothers SC–7 series 3 Variant 200. With STC SA02059AK on the following model equipped with HC–B4TN–5 props: Short Brothers SC–7 series 3 Variant 200. The following models equipped with Hartzell HC–B3TN–5( ) props: Twin Commander (Gulfstream) 690, 690A, and 690B. Unsafe Condition (d) This AD results from reports of Goodrich ''FASTprop'' propeller de-icers becoming loose or debonded, and detaching from propeller blades during operation. We are issuing this AD to prevent Goodrich ''FASTprop'' propeller de-icers from detaching from the propeller blade, resulting in damage to the airplane, and possible injury to passengers and crewmembers. 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.

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(f) Properly certificated maintenance personnel must perform the initial inspection required in this AD. Thereafter, the pilot or properly certificated maintenance personnel may perform the repetitive visual check. Initial Visual Inspection of ''FASTprop'' Propeller De-Icers (g) Within 10 hours after the effective date of this AD, inspect the ''FASTprop'' propeller deicers. If any ''FASTprop'' propeller de-icer fails the inspection, then the ''FASTprop'' de-icer must be repaired or replaced as necessary before the next flight. Use paragraphs 2.A(3) through (5) of the Accomplishment Instructions of Goodrich De-icing and Specialty Systems Alert Service Bulletin (ASB) No. 30-60-00-1, dated November 15, 2004 to do these actions. Repetitive Visual Inspections of ''FASTprop'' Propeller De-Icers (h) After the initial inspection, visually check the ''FASTprop'' propeller de-icer once per day either during the pilot's first preflight inspection of the day or when maintenance personnel are available. If any ''FASTprop'' propeller de-icer fails the visual check, then the ''FASTprop'' de-icer must be inspected, repaired, or replaced as necessary before the next flight. Terminating action is accomplished when the ''FASTprop'' propeller de-icer is removed and replaced with an approved propeller de-icer. Use paragraph 2.A(2) of the Accomplishment Instructions of Goodrich De-icing and Specialty Systems Alert Service Bulletin (ASB) No. 30-60-00-1, dated November 15, 2004 to do these actions. Alternative Methods of Compliance (i) 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 (j) Under 14 CFR part 39.23, we are limiting the special flight permits for this AD by requiring that any propeller found with a loose or debonded ''FASTprop'' de-icer must have all propeller blade de-icers removed before the flight, to maintain a balanced propeller. Information on removing de-icers can be found in paragraph 1.K.(1) of Goodrich De-icing and Specialty Systems ASB No. 30-60-00-1, dated November 15, 2004. Related Information (k) None. Material Incorporated by Reference (l) You must use Goodrich De-icing and Specialty Systems Alert Service Bulletin No. 30-6000-1, dated November 15, 2004, to perform the inspections, repairs, and 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 Goodrich De-icing and Specialty Systems, 1555 Corporate Woods Parkway, Uniontown, Ohio 44685, telephone (330) 3743743, for a copy of this service information. You may review copies at the Docket Management

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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 September 1, 2005. Peter A. White, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 05-17773 Filed 9-8-05; 8:45 am] BILLING CODE 4910-13-P

19

BW 2005-19 RAYTHEON AIRCRAFT COMPANY AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2005-18-21 Raytheon Aircraft Company: Amendment 39-14262; Docket No. FAA-2005-22332; Directorate Identifier 2005-CE-46-AD. When Does This AD Become Effective? (a) This AD becomes effective on September 13, 2005. Are Any Other ADs 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: Models (1) 1900 (2) 1900C (3) 1900C (C–12J). (4) 1900D

Serial Nos. UA–3; UB–1 through UB–74 and UC–1 through UC–174; UD–1 through UD–6; and UE–1 through UE–439.

What Is the Unsafe Condition Presented in This AD? (d) This AD results from a report of excessive movement of the elevator and elevator trim. The hinge support bracket that attaches the elevator to the horizontal stabilizer was loose and had loose and missing rivets. The elevator counterweight horn showed evidence of rubbing against the horizontal stabilizer, indicating possible incorrect clearance. We are issuing this AD to detect and correct any looseness in the elevator hinge support attachments, which could result in binding of the elevator control system. This elevator binding 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:

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Actions (1) Inspect all elevator hinge support attachments on both left and right elevators on both left and right elevators for loose or missing rivets.

Compliance Within 50 hours time-in-service (TIS) after the effective date of this AD.

(2) If loose or missing rivets are Before further found in the inspection required in flight paragraph (e)(1) of this AD, replace reviets.

(3) Inspect the elevator hinge joints for looseness and the clearance of each elevator to its stabilizer.

Within 50 hours TIS after the effective date of this AD.

(4) If looseness of the elevator hinge joints or incorrect clearance between the elevators and their stabilizers is found, correct the discrepancies. (5) Report the results found in the inspections required in paragraph (e)(1) and (e)(3) of this AD. The Office of Management and Budget (OMB) approved the information collection requirements contained in this regulation under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 and those following sections) and assigned OMB Control Number 2120–0056.

Before further flight

Within 7 days after the inspections required in paragraph (e)(1) and (e)(3) of this AD.

Procedures As specified in Raytheon Aircraft Company Safety Communiqué No. 261, dated August 2005, following the applicable Raytheon Aircraft Company Maintenance Manual, Chapter 5–20–07 and Structural Repair Manual, Chapter 51–40–02. As specified in Raytheon Aircraft Company Safety Communiqué No. 261, dated August 2005, following the applicable Raytheon Aircraft Company Maintenance Manual, Chapter 5–20–07 and Structural Repair Manual, Chapter 51–40–02. As specified in Raytheon Aircraft Company Safety Communiqué No. 261, dated August 2005, following the applicable Raytheon Aircraft Company Maintenance Manual, Chapter 5–20–07. As specified in Raytheon Aircraft Company Safety Communiqué No. 261, dated August 2005, following the applicable Raytheon Aircraft Company Maintenance Manual, Chapter 5–20–07. In addition to Raytheon Aircraft Company, send a completed copy of the Raytheon Aircraft Company Elevator Inspection form, found in Raytheon Aircraft Company Safety Communiqué No. 261, dated August 2005, to Steven E. Potter, FAA, 1801 Airport Road, Wichita, Kansas 67209. Also include in your report TIS since elevator replacement, if elevator has been replaced.

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, FAA. For information on any already approved alternative methods of compliance, contact Steven E. Potter, Aerospace Engineer, Airframe and Services Branch, ACE-118W, 1801 Airport Road, Wichita, Kansas 67209; telephone: (316) 9464124; 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 Raytheon Aircraft Company Safety Communiqué No. 261, dated August 2005. The Director of the Federal Register 21

2005-18--21 3

approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of this service information, contact Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 67201; telephone: (800) 625-7043. To review copies of this service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html or call (202) 741-6030. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590001 or on the Internet at http://dms.dot.gov. The docket number is FAA-2005-22332; Directorate Identifier 2005-CE-46-AD. Issued in Kansas City, Missouri, on September 2, 2005. Kim Smith, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-17890 Filed 9-12-05; 8:45 am] BILLING CODE 4910-13-P

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BW 2005-19 RAYTHEON AIRCRAFT COMPANY AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2005-18-22 Raytheon Aircraft Company: Amendment 39-14263; Docket No. FAA-2005-21239; Directorate Identifier 2005-CE-27-AD. When Does This AD Become Effective? (a) This AD becomes effective on November 14, 2005. What Other ADs Are Affected by This Action? (b) None. What Airplanes Are Affected by This AD? (c) This AD affects Model 390 airplanes that: (1) Incorporate a serial number of RB-1, RB-4 through RB-84, RB-87 through RB-90, RB-92 through RB-96, RB-98 through RB-101, and RB-103 through RB-107; and (2) Are certificated in any category. What Is the Unsafe Condition Presented in This AD? (d) This AD is the result of reports of inadequate left-hand and right-hand engine assembly cable, wire, and hose routing clearance. The actions specified in this AD are intended to detect and correct chafing conditions in the engine installation, which could result in leaking flammable fluids near an ignition source. This failure could lead to fire damage or loss of airplane control. What Must I Do To Address This Problem? (e) To address this problem, you must do the following:

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2005-18-22 2

Actions Verify minimum clearances to correct chafing conditions in the powerplant left-hand and righthand engine assembly cable, wire, and hose routing by installation of the following: (i) If Kit No. 390–9104–0001 has already been installed and the tube cleared successfully, then no further action is necessary. (ii) If Kit No. 390–9104–0001 has already been installed and clearance with the tube was not obtained, then install Kit No. 390–9104–0003. (iii) If Kit No. 390–9104–0001 has not been installed, then install Kit No. 390–9104–0005.

Compliance Within the next 100 hours timein-service (TIS) or 6 months after November 14, 2005 (the effective date of this AD), whichever occurs first. We established this compliance time to coincide with the next regularly scheduled inspection. You may comply with this AD at any time prior to this time and not have to recomply.

Procedures Follow Raytheon Aircraft Company Mandatory Service Bulletin No. SB 71–3685, Issued May 2005, Revised: July 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, 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, 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 Raytheon Aircraft Company Mandatory Service Bulletin No. SB 71-3685, Rev. 1, Issued May 2005, Revised July 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 Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 67201-0085; telephone: (800) 429-5372 or 316-676-3140. To review copies of this service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html or call (202) 741-6030. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590-001 or on the Internet at http://dms.dot.gov. The docket number is FAA2005-21239; Directorate Identifier 2005-CE-27-AD. Issued in Kansas City, Missouri, on September 2, 2005. John R. Colomy, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-17889 Filed 9-12-05; 8:45 am] BILLING CODE 4910-13-P

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BW 2005-19 RAYTHEON AIRCRAFT COMPANY AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2005-19-07 Raytheon Aircraft Company: Amendment 39-14272; Docket No. FAA-2005-21410; Directorate Identifier 2005-CE-31-AD. When Does This AD Become Effective? (a) This AD becomes effective on October 31, 2005. What Other ADs Are Affected by This Action? (b) None. What Airplanes Are Affected by This AD? (c) This AD affects the following serial-numbered Model 390 airplanes that are certificated in any category: Serial Numbers (1) RB-1 (2) RB-4 through RB-36 (3) RB-38 through RB-41 (4) RB-43 through RB-67 (5) RB-69 through RB-80 (6) RB-82 through RB-84 (7) RB-87 through RB-94 (8) RB-96 through RB-101 (9) RB-103 through RB-115 (10) RB-117 through RB-119 (11) RB-121 What Is the Unsafe Condition Presented in This AD? (d) This AD is the result of reports of cracks found on the rudder pedal arm assemblies used in the rudder control system. The actions specified in this AD are intended to prevent failure of the rudder pedal arm assemblies caused by fatigue cracks. This failure could lead to loss of rudder control, loss of nose gear steering, and loss of toe brakes on the side on which the failure occurs.

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2005-19-07 2

What Must I Do To Address This Problem? (e) To address this problem, you must do the following: Actions (1) Replace rudder pedal arm assemblies, part numbers (P/Ns) 390– 524350–0001, 390–524350–0002, 390– 524351–0001, and 390–524351–0002 with improved design parts, P/Ns 390– 524400–0001, 390–524400–0002, 390– 524401–0003, and 390–524401–0004. (2) Do not install rudder pedal arm assemblies, P/Ns 390–524350–0001, 390–524350–0002, 390–524351–0001, and 390–524351–0002.

Compliance Upon accumulating 300 hours time-in-service (TIS) or within 100 hours TIS after October 31, 2005 (the effective date of this AD), whichever occurs later, unless already done. As of October 31, 2005 (the effective date of this AD).

Procedures Follow Raytheon Aircraft Company Mandatory Service Bulletin, SB 27–3691, Rev. 1, Revised: February, 2005, and the applicable maintenance manual. Not applicable.

Note: Replacing the rudder pedal arm assemblies following Raytheon Aircraft Company Mandatory Service Bulletin, SB 27-3691, Issued: October 2004, does not comply with 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 David Ostrodka, Aerospace Engineer, Wichita ACO, FAA, 1801 Airport Road, Wichita, Kansas 67209; telephone: (316) 946-4129; facsimile: (316) 946-4107; e-mail: [email protected]. Does This AD Incorporate Any Material by Reference? (g) You must do the actions required by this AD following the instructions in Raytheon Aircraft Company Mandatory Service Bulletin, SB 27-3691, Rev. 1, Revised: February, 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 Raytheon Aircraft Company, 9709 E. Central, Wichita, Kansas 67201-0085; telephone: (800) 429-5372 or (316) 676-3140. 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-2005-21410; Directorate Identifier 2005-CE-31-AD. Issued in Kansas City, Missouri, on September 8, 2005. David R. Showers, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-18199 Filed 9-14-05; 8:45 am] BILLING CODE 4910-13-P 26

BW 2005-19 TURBOMECA AIRWORTHINESS DIRECTIVE ENGINE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2005-19-10 Turbomeca: Amendment 39-14275. Docket No. FAA-2005-22430; Directorate Identifier 2005-NE-34-AD. Effective Date (a) This airworthiness directive (AD) becomes effective October 3, 2005. Affected ADs (b) None. Applicability (c) This AD applies to Turbomeca Arrius 2 F turboshaft engines with the fuel control units listed by serial number (SN) in Turbomeca Alert Mandatory Service Bulletin (MSB) No. A319 73 4825, dated August 3, 2005. These engines are installed on, but not limited to, Eurocopter EC120B helicopters. Unsafe Condition (d) This AD results from a report of an accident in July 2005 involving a Eurocopter EC120B helicopter. We are issuing this AD to prevent an uncommanded engine in-flight shutdown on a single-engine helicopter, resulting in a forced autorotation landing or an accident. Compliance (e) You are responsible for having the actions required by this AD performed as soon as practicable after the effective date of this AD but no later than February 28, 2006, unless the actions have already been done. (f) Remove FCUs listed by serial number (SN) in Turbomeca Alert Mandatory Service Bulletin (MSB) No. A319 73 4825, dated August 3, 2005. (g) Install an FCU not listed in Turbomeca Alert MSB No. A319 73 4825, dated August 3, 2005; or one with a new constant delta pressure diaphragm installed using paragraph 2.B. of Turbomeca Alert MSB No. A319 73 4825, dated August 3, 2005.

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2005-19-10 2

Alternative Methods of Compliance (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 directives No. F-2005-143, dated August 17, 2005, and No. F-2005143 R1, dated August 31, 2005, also address the subject of this AD. Material Incorporated by Reference (j) You must use Turbomeca Alert Mandatory Service Bulletin (MSB) No. A319 73 4825, dated August 3, 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/federal-register/cfr/ibr-locations.html. Issued in Burlington, Massachusetts, on September 9, 2005. Jay J. Pardee, Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 05-18322 Filed 9-15-05; 8:45 am] BILLING CODE 4910-13-P

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BW 2005-19 LYCOMING ENGINES AIRWORTHINESS DIRECTIVE ENGINE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2005-19-11 Lycoming Engines: Amendment 39-14276. Docket No. FAA-2005-21864; Directorate Identifier 2005-NE-29-AD. Effective Date (a) This airworthiness directive (AD) becomes effective October 21, 2005. Affected ADs (b) None. Applicability (c) This AD applies to Lycoming Engines (Formerly Textron Lycoming) AEIO-360, IO-360, O-360, LIO-360, LO-360, AEIO-540, IO-540, O-540, and TIO-540 series reciprocating engines, rated at 300 horsepower (HP) or lower, manufactured new, rebuilt, overhauled after March 1, 1999, or that had a crankshaft installed after March 1, 1999. These engines are installed on, but not limited to, the following aircraft: Engine model IO–540–V4A5

Manufacturer

Aircraft model

O–540–E4A5 IO–540–C4B5 LO–360–A1G6D O–360–A1G6D

A.M.F Aero Commander Aero Commander Aerofab Aeronautica Aerostar Aircraft Manufacturing Factory Aviamilano Avions Beech Beech

O–540–E4B5 O–540–E4C5

Bellanca Britten Norman Britten Norman

IO–540–E1A5

IO–540–K1F5

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17–D Mushshak 500 B, S, U/Merlyn Products Conv. 500–E LA 250 Renegade Agricola Mexicana Quail 600 Mushshak F–250 Flamingo Pierre Robin HR–100/250 76 Duchess 76 Duchess C–24R Sierra or 200 Sierra Aircraft Aries T–250 BN–2 Islander BN–2A & BN–2B Islander

2005-19-11 2

Engine model IO–540–K1B5 O–360–A1F6 O–360–A1F6D O–540–J3C5D IO–540–AB1A5 O–360–F1A6 IO–540–AC1A5 IO–360–A1B6D TIO–540–AK1A O–540–L3C5D AEIO–540–D4A5 IO–540–T4B5D IO–540–T4B5 TIO–540–AG1A IO–540–K1J5D O–540–B4B5

AEIO–540–L1B5

O–540–A1A5 AEIO–360–A1E6 IO–540–M1C5

O–540–J3A5 IO–540–W1A5 IO–360–A3B6 IO–360–A1B6 IO–360–A3B6D TIO–540–AF1B

IO–540–K1J5 IO–540–S1A5 IO–540–AA1A5 O–540–A1B5

Manufacturer Britten Norman Celair Cessna Cessna Cessna Cessna Cessna Cessna

Aircraft model BN–2A Islander Eagle 177 Cardinal 177 Cardinal 182–RG Skylane 182–S C–172RG Cutlass RG C–206 Stationair R–G Cardinal R–G Cardinal T182T Skylane TR–182 Turbo Skylane S–2S, S–2B 114 114B 114TC DO–28 EMB–201 Ipanema EMB–710 Corioca EMB–720 Minuano EMB–720 Minuano & EMB–721 Sertanejo EMB–721 Sertanejo Extra 300 FFA–2000 Eurotrainer HPT–32 H–250 Omega Angel Chang Gong–91 LA–4–200 Buccaneer MT–7–260 & M–7–260 MX–7–235 Star Rocket MX–7–235, MT–7–235 & M7–235 Trophy 212 Conversion 201 M–201 M–20–J M20J–201 M20M TLS Bravo Z143L Zlin Z242L Zlin P–68 Series Observer 600–A Aerostar 601–A, 601B & 601P Aerostar 602P Sequoia PA–23–235 Aztec & PA–24–250 Comanche PA–23–250 Aztec

Cessna Cessna Cessna Christen Pitts Commander Commander Commander Dornier Embraer Embraer

Extra-Flugzeugbau F.F.A H.A.L Helio Military Integrated Systems King Engineering Korean Air Lake Maule. Maule. Mod Works Mooney Mooney Mooney Mooney Moravan Partenavia Piper Piper Piper Piper

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Engine model IO–540–J4A5 IO–540–C1B5 TIO–540–C1A

Piper Piper Piper

O–540–A1C5 O–540–A1D5 IO–540–D4A5

Piper Piper Piper

O–540–B2C5 O–540–B2B5

Piper Piper

IO–360–C1C6 IO–540–M1A5

Piper Piper

IO–540–K1G5 IO–540–K1A5 IO–540–K1A5D IO–540–K1G5D

Piper Piper Piper Piper

IO–360–C1E6 IO–540–K1G5 O–360–A1H6 LO–360–A1H6 IO–540–K1K5

Piper Piper Piper Piper Piper Robin Robinson Rockwell Ruschmeyer Saab Scottish Avia Siai Marchetti Siai Marchetti Siai Marchetti Siai Marchetti Slingsby Socata

O–540–F1B5

Manufacturer

IO–540–C4D5D

Socata

TIO–540–AB1AD IO–540–AB1A5 IO–540–K1H5 IO–540–L1C5

Socata Stoddard Hamilton Stoddard Hamilton Swearingen Aircraft Transava Valmet Wassmer Yoeman

AEIO–360–A1B6

Aircraft model PA–23–250 Aztec PA–23–250 Aztec & PA–24–250 Comanche PA–23–250T Turbo Aztec PA–24–150 Comanche PA–24–250 Comanche PA–24–250 Comanche PA–24–260 Comanche PA–24–260 Comanche PA–25–235 Pawnee PA–28–235 Cherokee PA–28–235 Cherokee PA–28R–201 Arrow PA–31–300 Navajo PA–32–260 Cherokee 6 PA–32–300 & PA–32–301 Saratoga PA–32–300 Cherokee 6 PA–32–300 Cherokee 6 PA–32–300R Lance PA–32–301R Saratoga PA–34–200 Seneca I PA–36–300 Brave PA–44–180 PA–44–180 Seminole T–35 Pillan R–3000/235 R–44 114 MF–85 MFI–15 Safari or MFI–17 Supporter Bulldog S–205 S–208 & SF–260 SF–260 SF–260 Firefly T3A R–235 Rallye Cuerrier Rallye 235CA TB–20 Trinidad TB–200 TB–21 & TB–21–TC Trinidad TC Glasair Glasair III SX–300 T–300 Skyfarmer L–70 Vinka WA4–21 Aviation YA–1 31

2005-19-11 4

Unsafe Condition (d) This AD results from 12 crankshaft failures in Lycoming model 360 and 540 series engines rated at 300 HP or lower. We are issuing this AD to prevent failure of the crankshaft, which could result in total engine power loss, in-flight engine failure, and possible loss of the airplane. Compliance (e) You are responsible for having the actions required by this AD performed within 50 hours time-in-service or 6 months after the effective date of this AD, whichever is earlier, unless the actions have already been done. Engines Manufactured Before March 1, 1999 (f) If Lycoming Engines manufactured new, rebuilt, or overhauled your engine before March 1, 1999, and you haven't had the crankshaft replaced, no further action is required. AEIO-540, IO-540, O-540, and TIO-540 Series Engines Manufactured New or Rebuilt, Overhauled, or That Had a Crankshaft Installed After March 1, 1999 (g) For AEIO-540, IO-540, O-540, and TIO-540 series engines manufactured new or rebuilt, overhauled, or that had a crankshaft installed after March 1, 1999, do the following: (1) If Table 1 or Table 2 of Lycoming Mandatory Service Bulletin (MSB) No. 566, dated July 11, 2005, lists your engine serial number (SN), use Table 4 to verify the crankshaft SN. (2) If Table 4 of Lycoming MSB No. 566, dated July 11, 2005, lists your crankshaft SN, replace the crankshaft with a crankshaft that is not listed in Table 4 of Lycoming MSB No. 566, dated July 11, 2005. AEIO-360, IO-360, O-360, LIO-360, and LO-360 Series Engines Manufactured New or Rebuilt, Overhauled, or That Had a Crankshaft Installed After March 1, 1999 (h) For AEIO-360, IO-360, O-360, LIO-360, and LO-360 series engines manufactured new or rebuilt, overhauled, or that had a crankshaft installed after March 1, 1999, do the following: (1) If Table 3 of Lycoming MSB No. 566, dated July 11, 2005, lists your engine SN, use Table 4 to verify the crankshaft SN. (2) If Table 4 of Lycoming MSB No. 566, dated July 11, 2005, lists your crankshaft SN, replace the crankshaft with a crankshaft that is not listed in Table 4 of Lycoming MSB No. 566, dated July 11, 2005. Prohibition Against Installing Certain Crankshafts (i) After the effective date of this AD, do not install any crankshaft that has a SN listed in Table 4 of Lycoming MSB No. 566, dated July 11, 2005, into any engine.

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Alternative Methods of Compliance (AMOCs) (j) The Manager, New York Aircraft Certification Office, has the authority to approve AMOCs for this AD if requested using the procedures found in 14 CFR 39.19. Related Information (k) None. Material Incorporated by Reference (l) You must use Lycoming Mandatory Service Bulletin No. 566, dated July 11, 2005, to perform the actions required by this AD. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Lycoming, 652 Oliver Street, Williamsport, PA 17701; telephone (570) 323-6181; fax (570) 327-7101, or on the Internet at http://www.Lycoming.Textron.com for a copy of this service information. You may review copies at the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 205900001, 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 September 9, 2005. Jay J. Pardee, Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 05-18323 Filed 9-15-05; 8:45 am] BILLING CODE 4910-13-P

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