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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. Delegation and Airworthiness Programs Branch, AIR-140 SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS
Info: E - Emergency; COR - Correction; S - Supersedes; R - Revision; - See AD for additional information;
Biweekly 2005-01
2004-26-09
Engine: 250-B17, -B17B, -B17C, -B17D, -B17E, 250-C20, -C20B, -C20F, -C20J, -C20S, and -C20W Series Turboprop and Turboshaft 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
Biweekly 2005-02
98-20-38 R1
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 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
Biweekly 2005-03
2005-01-04
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
Biweekly 2005-04
2005-01-04
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: 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, 230, and 430 SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS
Info: E - Emergency; COR - Correction; S - Supersedes; R - Revision; - See AD for additional information;
Biweekly 2005-05
2005-04-08
Engine: CT58-140-1, CT58-140-2, and surplus military T58-GE-5, -10, -100, and ''402 turboshaft
Biweekly 2005-06
2005-05-14
Engine: TFE731-2 and -2C series, and TFE731-3, -3A, -3AR, -3B, -3BR, and -3R series turbofan
Biweekly 2005-07
2005-05-52
SA226-AT, SA226-TC, SA226-T, SA226-T(B), SA227-TT, SA227-TT(300), SA227-AC, SA227-AT, SA227-BC, and SA227-CC/DC
Biweekly 2005-08
83-08-01 R2
Propeller: HC-B3TN-2, HC-B3TN-3, HC-B3TN-5, HC-B4TN-3, HC-B4TN-5, HC-B4MN-5, and HC-B5MP-3 turbopropellers
Biweekly 2005-09
2005-08-06
Sailplane: B4-PC11, B4-PC11A, and B4-PC11AF
Biweekly 2005-10
2004-25-16 R1
SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS
Info: E - Emergency; COR - Correction; S - Supersedes; R - Revision; - See AD for additional information;
Biweekly 2005-11
2005-09-51
Engine: 250-B17B, -B17C, -B17D, -B17E, -C20, -C20B, -C20F, -C20J, -C20S, and -C20W turboprop and turboshaft
Biweekly 2005-12
2005-11-05
EA-300, EA-300S, ES-300L, and EA-300/200 Colonial C-2, Lake LA-4, Lake LA-4A, Lake LA-4P, and Lake LA-4-200 and 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
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 401, 401A, 401B, 402, 402A, 402B, 411, and 411A 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 AT–300, AT–301, AT–302, AT–400, and AT–400A, AT–401/AT–402, AT–602, AT–802 and AT–802A Rotorcraft: EC 155B, EC155B1, SA-365N, SA-365N1, AS-365N2, and AS 365 N3
Biweekly 2005-14
2005-12-12
401, 401A, 401B, 402, 402A, 402B, 411, and 411A SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS
Info: E - Emergency; COR - Correction; S - Supersedes; R - Revision; - See AD for additional information;
Biweekly 2005-15
2005-12-51
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: HC-B3TN-2, HC-B3TN-3, HC-B3TN-5, HC-B3MN-3, HC-B4TN-3, HC-B4TN-5, HC-B4MN-5, HC-B4MP-3, HC-B4MP-5, and HC-B5MP-3
Biweekly 2005-16
2005-15-10
PA-34-200T, PA-34-220T, PA-44-180, and PA-44-180T
Biweekly 2005-17
2004-14-02
Engine: 250-C28, -C28B, and -C28C turboshaft 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 2005-18
95-19-15 R1
Engine: Artouste III B, B1, and D turboshaft
Biweekly 2005-19
2005-18-12
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 Engine: AEIO-360, IO-360, O-360, LIO-360, LO-360, AEIO-540, IO-540, O-540, and TIO-540 series 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-2004-
19955; Directorate Identifier. 2004-NE-17-AD.
Effective Date

(a) This airworthiness directive (AD) becomes effective October 14, 2005.
Affected ADs

(b)

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 Aircraft manufacturer
Aircraft model
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 172 175, 175A 190, 195, A, B 421, 421A A185E, A185F (SEAPLANES ONLY) T50 H–250 H–295, HT–295 (U–10D) H–395 (L–28A, U–10B) H–500 Aircraft manufacturer
Aircraft model

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-SB- 61-136, 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 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
propeller assembly
inspection.
on the effective date
of this AD is.
(a) Disassemble and clean the propeller assembly the TSO is not known. (b) Perform visual and nondestructive inspections of propeller components for cracks, corrosion or pits, nicks, scratches, wear, blade minimum dimensions, and damage 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. (a) Disassemble and clean the propeller assembly (b) Perform visual and nondestructive inspections of propeller components for cracks, corrosion or pits, nicks, scratches, wear, blade minimum dimensions, and damage 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 (b) Perform visual and nondestructive inspections of propeller components for cracks, corrosion or pits, nicks, scratches, wear, blade minimum dimensions, and damage 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 (b) Perform visual and nondestructive inspections of propeller components for cracks, corrosion or pits, nicks, scratches, wear, blade minimum dimensions, and damage 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.
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)

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 20590-0001, on the internet at http://dms.dot.gov, or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Burlington, Massachusetts, on August 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 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. FAA-
2005-20847; Directorate Identifier. 2004-NE-35-AD.
Effective Date

(a) This airworthiness directive (AD) becomes effective October 14, 2005.
Affected ADs

(b)

Applicability

(c) This AD applies to Goodrich De-icing and Specialty Systems ''FASTprop'' propeller de- icers, part numbers (P/Ns) P4E1188 series, P4E1601 series, P4E2200 series, P4E2271-10, P4E2575-7, 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
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. 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. De-icer P/N
Installed on, but not limited to
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). 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. 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. De-icer P/N
Installed on, but not limited to
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. 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. 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). Metal propellers operated up to 2,900 rpm on: Raytheon (Beech) 65–88. Metal propellers operated up to 2,900 rpm on: Casa C212CB. Twin Commander (Gulfstream) 690 and 690A. 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. 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. 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. 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. 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. 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). De-icer P/N
Installed on, but not limited to
Metal propellers on: Cessna T310Q, T310R, 340, 340A, 402B, 402C, 414, 414A, 421A, and 421B. 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. Metal propellers operated up to 2,900 rpm on: Various aircraft models equipped with McCauley 3AF32C504, 3AF32C505, 3AF32C506, or 3AF32C507 props. 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. 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. De-icer P/N
Installed on, but not limited to
Embraer EMB–110P1/2 equipped with Hartzell HC–B3TN–3C or HC–B3TN–3D 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. (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 de- icers. 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)

Material Incorporated by Reference

(l) You must use Goodrich De-icing and Specialty Systems Alert Service Bulletin No. 30-60- 00-1, 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) 374-3743, for a copy of this service information. You may review copies at the Docket Management 2005-18-20 8 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/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 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)

What Airplanes Are Affected by This AD?

(c) This AD affects the following airplane models and serial numbers that are certificated in Models Serial
UB–1 through UB–74 and UC–1 through UC–174;
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: Actions Compliance Procedures
As specified in Raytheon Aircraft Company support attachments on both left and time-in-service Safety Communiqué No. 261, dated August right elevators on both left and right (TIS) after the elevators for loose or missing rivets. effective date of Chapter 5–20–07 and Structural Repair Manual, Chapter 51–40–02. As specified in Raytheon Aircraft Company Safety Communiqué No. 261, dated August Aircraft Company Maintenance Manual, Chapter 5–20–07 and Structural Repair Manual, Chapter 51–40–02. (3) Inspect the elevator hinge joints Within 50 hours As specified in Raytheon Aircraft Company Safety Communiqué No. 261, dated August Aircraft Company Maintenance Manual, Chapter 5–20–07. (4) If looseness of the elevator hinge Before further As specified in Raytheon Aircraft Company Safety Communiqué No. 261, dated August In addition to Raytheon Aircraft Company, Aircraft Company Elevator Inspection form, found in Raytheon Aircraft Company Safety collection requirements contained in and (e)(3) of this this regulation under the provisions AD. Road, Wichita, Kansas 67209. Also include replacement, if elevator has been replaced. following sections) and assigned
OMB Control Number 2120–0056.
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) 946-
4124; 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 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 20590-001 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 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)

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
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: Actions Compliance
Procedures
Verify minimum clearances to correct chafing conditions in the powerplant left-hand and right- in-service (TIS) or 6 months after Aircraft Company hand engine assembly cable, wire, and hose November 14, 2005 (the effective Mandatory routing by installation of the following: (i) If Kit No. 390–9104–0001 has already been installed and the tube cleared successfully, compliance time to coincide with Issued May 2005, (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. time and not have to recomply. (iii) If Kit No. 390–9104–0001 has not been installed, then install Kit No. 390–9104–0005.
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 FAA-2005-21239; 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 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)

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. 2005-19-07 2
What Must I Do To Address This Problem?

(e) To address this problem, you must do the following: Actions Compliance
Procedures
524350–0001, 390–524350–0002, 390– or within 100 hours TIS after Bulletin, SB 27–3691, Rev. 524351–0001, and 390–524351–0002 524400–0001, 390–524400–0002, 390– whichever occurs later, 524401–0003, and 390–524401–0004. unless already done. (2) Do not install rudder pedal arm 390–524350–0002, 390–524351–0001, and 390–524351–0002. 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: david.ostrodka@faa.gov.
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 20590-001 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 BW 2005-19
TURBOMECA
AIRWORTHINESS DIRECTIVE
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)

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. 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-2005- 143 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 BW 2005-19
LYCOMING ENGINES
AIRWORTHINESS DIRECTIVE
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)

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
Manufacturer
Aircraft model
Engine model
Manufacturer
Aircraft model
EMB–710 Corioca EMB–720 Minuano EMB–720 Minuano & EMB–721 Sertanejo EMB–721 Sertanejo MT–7–260 & M–7–260 MX–7–235 Star Rocket MX–7–235, MT–7–235 & M7–235 PA–23–235 Aztec & PA–24–250 Comanche PA–23–250 Aztec Engine model
Manufacturer
Aircraft model
PA–23–250 Aztec & PA–24–250 Comanche PA–23–250T Turbo Aztec PA–24–150 Comanche PA–24–260 Comanche PA–24–260 Comanche PA–28–235 Cherokee PA–28–235 Cherokee PA–31–300 Navajo PA–32–260 Cherokee 6 PA–32–300 & PA–32–301 Saratoga PA–32–300R Lance PA–32–301R Saratoga 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 (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. 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)

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 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. 05-18323 Filed 9-15-05; 8:45 am] BILLING CODE 4910-13-P

Source: http://mooney.free.fr/Sauvegarde%20AFS/FAA%20AD/AD%20Bi%20Weekly/SM2005-19.pdf