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FEDERAL AVIATION ADMINISTRATION AIRWORTHINESS DIRECTIVES

SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS

BIWEEKLY 2005-13

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


AD No. Information Manufacturer Applicability Info: E - Emergency; COR - Correction; S - Supersedes; R - Revision; - See AD for additional information;

3

Biweekly 2005-01 2004-26-09 Rolls-Royce Corporation Engine: 250-B17, -B17B, -B17C, -B17D, -B17E, 250-C20, -C20B,

-C20F, -C20J, -C20S, and -C20W Series Turboprop and Turboshaft

2004-26-11 Bell Helicopter Textron Canada Rotorcraft: 222, 222B, 222U, 230, 430 2005-01-04 S 98-15-13 Raytheon Aircraft Company 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

2005-01-10 S 74-06-01 The New Piper Aircraft, Inc PA-23-235, PA-23-250, and PA-E23-250 2005-01-11 Pilatus Aircraft Ltd. PC-12 and PC-12/45 Biweekly 2005-02 98-20-38 R1 R Raytheon Aircraft 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

2005-01-14 S 2002-21-16 Bombardier-Rotax GmbH Engine: 912 F, 912 S, and 914 F Series Reciprocating 2005-01-17 S 98-03-14 EXTRA Flugzeugbau GmbH EA–300 and EA–300/S 2005-01-18 S 93-25-07 Raytheon Aircraft Company 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

2005-01-19 S 2004-10-15 GARMIN International Inc Appliance: GTX 33, GTX 33D, GTX 330, and GTX 330D Mode S Transponders

2005-02-01 The Lancair Company LC40–550FG and LC42–550FG Biweekly 2005-03 2005-01-04 COR

S 98-15-13

Raytheon Aircraft Company 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

2005-01-18 COR S 93-25-07

Raytheon Aircraft Company 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

2005-02-11 COR Gippsland Aeronautics Pty. Ltd. GA8 2005-03-04 Pacific Aerospace Corp., Ltd. 750XL Biweekly 2005-04 2005-01-04 COR

S 98-15-13 Raytheon Aircraft Company 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

2005-03-07 Bell Helicopter Textron Canada Rotorcraft: 407 2005-03-08 Eurocopter France Rotorcraft: AS350B, BA, B1, B2, B3, C, D, D1, and EC130 B4 2005-03-09 Eurocopter France Rotorcraft: EC 155B, EC155B1, SA-360C, SA-365C, SA-365C1,

SA-365C2, SA-365N, SA-365N1, AS-365N2, AS 365 N3, and SA-366G1

2005-03-10 S 2002-08-54 Bell Helicopter Textron Rotorcraft: 222, 222B, 222U, and 230 2005-04-09 S 2004-26-11 Bell Helicopter Textron Canada Rotorcraft: 222, 222B, 222U, 230, and 430



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Biweekly 2005-05 2005-04-08 Hartzell Propeller Inc. Propeller: HC-B3TN-5( )/T10282( ) 2005-04-10 General Electric Company Engine: CT58-140-1, CT58-140-2, and surplus military T58-GE-5,

-10, -100, and ''402 turboshaft 2005-04-16 Pilatus Aircraft Ltd. PC-12 and PC-12/45 2005-05-51 E Cessna Aircraft Company 402C and 414A 2005-05-52 E, S 2005-05-51 Cessna Aircraft Company 402C and 414A 2005-05-53 E Cessna Aircraft Company 172R, 172S, 182T, and T182T 2005-05-53 R1 E, R, S 2005-05-

53 Cessna Aircraft Company 172R, 172S, 182T, and T182T

Biweekly 2005-06 2005-05-14 Eagle Aircraft (Malaysia) Eagle 150B 2005-05-15 Honeywell International Inc. Engine: TFE731-2 and -2C series, and TFE731-3, -3A, -3AR, -3B,

-3BR, and -3R series turbofan 2005-06-01 Eurocopter France Rotorcraft: EC 155B and EC 155B1 Biweekly 2005-07 2005-05-52 FR, S 2005-05-51

and 2000-23-01 Cessna 402C and 414A

2005-05-53 R1 R, 2005-05-53 Cessna 172R, 172S, 182T, and T182T 2005-06-13 S 99-0602 Fairchild Aircraft, Inc. SA226-AT, SA226-TC, SA226-T, SA226-T(B), SA227-TT,

SA227-TT(300), SA227-AC, SA227-AT, SA227-BC, and SA227-CC/DC

2005-07-01 Cessna 208 and 208B Biweekly 2005-08 83-08-01 R2 R, S 83-08-01 R1 Hartzell Propeller Inc. Propeller: HC-B3TN-2, HC-B3TN-3, HC-B3TN-5, HC-B4TN-3,

HC-B4TN-5, HC-B4MN-5, and HC-B5MP-3 turbopropellers 2005-07-01 COR Cessna 208 and 208B 2005-07-27 S 2000-18-04 Aviointeriors S.p.A. Appliance: Model 312 Seats

Biweekly 2005-09 2005-08-06 Centrair Glider: 101, 101A, 101AP, and 101P 2005-08-07 Pilatus Aircraft Limited Sailplane: B4-PC11, B4-PC11A, and B4-PC11AF 2005-08-12 Centrair Glider: 101, 101A, 101AP, and 101P 2005-08-13 Glaser-Dirks Flugzeugbau

GmbH Sailplane: DG-800B

2005-08-14 LET a.s. Sailplane: Blanik L-13 AC 2005-09-51 E Turbomeca S.A. Engine: Arrius 2F Turboshaft

Biweekly 2005-10 2004-25-16 R1 R, 2004-25-16 Kelly Aerospace Power Systems Appliance: Fuel regulator shutoff valve 2005-08-06 COR Centrair Glider: 101 Series 2005-09-05 Eurocopter France Rotorcraft: EC120B 2005-09-06 Agusta S.p.A. Rotorcraft: A119 2005-09-07 Agusta S.p.A. Rotorcraft: A109E



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Biweekly 2005-11 2005-09-51 FR Turbomeca S.A. Engine: Arrius 2F turboshaft 2005-10-12 Schweizer Aircraft Corporation Rotorcraft: 269C, C-1, and D 2005-10-13 Rolls-Royce Corporation Engine: 250-B17B, -B17C, -B17D, -B17E, -C20, -C20B, -C20F, -

C20J, -C20S, and -C20W turboprop and turboshaft 2005-10-14 S 2004-01-51 Eurocopter France Rotorcraft: AS355E, F, F1, F2, and N 2005-10-23 DG Flugzeubau GmbH and

Glaser-Dirks Flugzeubau GmbH Glider:DG-500MB and DG-800B

2005-10-24 S 2003-14-20 AeroSpace Technologies of Australia Pty. Ltd.

N22B, N22S and N24A

2005-11-01 Turbomeca S.A. Engine: Arrius 1A turboshaft Biweekly 2005-13 2005-12-03 Sikorsky Aircraft Corporation Rotorcraft: S-92A 2005-12-06 S 96-12-07 Teledyne Continental Motors Appliance: S-20, S-1200, D-2000, and D-3000 Series Magnetos 2005-12-08 Turbomeca S.A. Engine: Arrius 2 B1, 2 B1A, 2 B1A-1, and 2 B2 turboshaft 2005-12-09 Grob-Werke G120A 2005-12-12 S 79-10-15 Cessna Aircraft Company 401, 401A, 401B, 402, 402A, 402B, 411, and 411A 2005-12-13 S 2005-05-52 Cessna Aircraft Company 402C and 414A 2005-12-20 The Lancair Company LC41-550FG 2005-12-51 FR Rockwell International 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

2005-13-01 S 2004-18-01 Hoffmann Propeller GmbH & Co KG

Propeller: HO-V343 and HO-V343K

2005-13-07 Honeywell International Inc. Engine: TFE731-2 and -3 series turbofan 2005-13-09 GROB-WERKE G120A 2005-13-10 Cessna Aircraft Company 172R, 172S, 182T, T182T, 206H, T206H 2005-13-11 General Electric Company Engine: CT64-820-4 turboprop 2005-13-12 Air Tractor, Inc. AT–300, AT–301, AT–302, AT–400, and AT–400A, AT–

401/AT–402, AT–602, AT–802 and AT–802A 2005-13-13 Sikorsky Aircraft Corporation Rotorcraft: S-92A 2005-13-16 S 93-24-14 The New Piper Aircraft, Inc. PA-34-200, PA-34-200T, and PA-34-220T 2005-13-17 Agusta. S.p.A. Rotorcraft: AB412 Series 2005-13-23 S 2003-18-03 Eurocopter France Rotorcraft: EC 155B, EC155B1, SA-365N, SA-365N1, AS-

365N2, and AS 365 N3 2005-13-25 Turbomeca S.A. Engine: Arriel 2B

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SIKORSKY AIRCRAFT CORPORATION AIRWORTHINESS DIRECTIVE


2005-12-03 Sikorsky Aircraft Corporation: Amendment 39-14119. Docket No. FAA-2005-21373; Directorate Identifier 2005-SW-13-AD. Applicability

Model S-92A helicopters with main gearbox (MGB) lubrication/scavenge pump, part number (P/N) 92351-15800-101, with vespel spline adapter, P/N 1584000-1, installed, certificated in any category. Compliance

Required before further flight, unless accomplished previously, and thereafter, at intervals not to exceed 50 hours time-in-service. To prevent loss of lubrication to the MGB, which could cause failure of one or both engine input drives, or planetary gear to sun gear tooth mesh failure, resulting in loss of power to the rotor system and subsequent loss of control of the helicopter, accomplish the following: (a) Remove and replace each MGB lubrication/scavenge pump vespel spline adapter in accordance with paragraph 3.A., steps (1) through (6) of the Accomplishment Instructions in Sikorsky Aircraft Corporation Alert Service Bulletin No. 92-63-001, dated April 1, 2005. (b) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Boston Aircraft Certification Office, Engine and Propeller Directorate, FAA, for information about previously approved alternative methods of compliance. (c) The removals and replacements shall be done in accordance with paragraph 3.A., steps (1) through (6) of the Accomplishment Instructions in Sikorsky Aircraft Alert Service Bulletin No. 92-63-001, dated April 1, 2005. The Director of the Federal Register approved this incorporation by reference in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Sikorsky Aircraft Corporation, Attn: Manager, Commercial Tech Support, 6900 Main Street, Stratford, Connecticut 06614, phone (203) 386-3001, fax (203) 386-5983. Copies may be inspected 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. (d) This amendment becomes effective on June 29, 2005. Issued in Fort Worth, Texas, on June 1, 2005. Carl F. Mittag, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.

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TELEDYNE CONTINENTAL MOTORS AIRWORTHINESS DIRECTIVE

APPLIANCE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS

2005-12-06 Teledyne Continental Motors: Amendment 39-14122. Docket No. 93-ANE-07-AD. Effective Date (a) This AD becomes effective July 19, 2005. Affected ADs (b) This AD supersedes AD 96-12-07, Amendment 39-9649. Applicability

(c) This AD applies to Teledyne Continental Motors (TCM) (formerly Bendix) magnetos that have a magneto part number (P/N) listed in Table 1 of TCM Mandatory Service Bulletin (MSB) No. MSB645, dated April 4, 1994, installed on Lycoming AEIO-540, HIO-540, IO-540, 0-540, and TIO-540 series engines. These engines are installed on, but not limited to, airplanes manufactured by the Cessna Aircraft Company, Maule Aerospace Technology Corporation, Mooney Aircraft Corporation, The New Piper Aircraft Inc., and Raytheon Aircraft Company (Formerly Beech Aircraft Company). Unsafe Condition (d) This AD results from data provided by the manufacturer that indicates a need to reduce the inspection intervals for riveted-impulse coupling assemblies used on certain Lycoming engine models. We are issuing this AD to prevent failure of the magneto impulse coupling assembly and possible engine failure. 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. Initial Inspections of Impulse Coupling Assemblies (f) For all magnetos that have a P/N listed in Table 1 of TCM MSB No. MSB645, dated April 4, 1994, that have never been inspected, perform an initial inspection of the impulse coupling assembly for wear using paragraphs 1.2 through 1.4.5 of the Detailed Instructions of TCM MSB No. MSB645, dated April 4, 1994. Use the following Table 1 for the compliance times. Snap-ring impulse coupling assemblies will have an ''A'' stamped in the lower-right quarter of the magneto data plate.

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TABLE 1.—INITIAL INSPECTION COMPLIANCE TIMES Engine Model Type of impulse

coupling assemblyTime on impulse coupling assembly on the effective

date of this AD

Inspect

(i) 100 or more hours time-since-new or overhaul (TSN) or if the TSN is unknown.

Within 10 hours time-in-service (TIS) after the effective date of this AD.

(1) Riveted

(ii) Fewer than 100 hours TSN

Before accumulating 100 hours TSN.

(i) 450 or more hours TSN Within 50 hours TIS after the effective date of this AD.

Lycoming AEIO–540, HIO–540, IO-540, 0–540, and TIO–540 series engines.

(2) Snap ring

(ii) Fewer than 450 hours TSN

Before accumulating 500 hours TSN.

(g) Replace any impulse coupling assembly that fails the inspection with a serviceable riveted or snap-ring impulse coupling assembly. Paragraphs 2 through 2.6 of the Detailed Instructions of TCM MSB No. MSB645, dated April 4, 1994 contain information on replacing the impulse coupling assembly. (h) If you replace a snap-ring impulse coupling assembly with a riveted-impulse coupling assembly, strike out the ''A'' on the magneto data plate. Repetitive Inspections of Impulse Coupling Assemblies (i) For all magnetos that have a P/N listed in Table 1 of TCM MSB No. MSB645, dated April 4, 1994, that have had an initial inspection as specified in paragraph (f) of this AD, perform repetitive inspections of the impulse coupling assembly for wear using paragraphs 1.2 through 1.4.5 of the Detailed Instructions of TCM MSB No. MSB645, dated April 4, 1994. Use the following Table 2 for the compliance times. Snap-ring impulse coupling assemblies will have an ''A'' stamped in the lower-right quarter of the magneto data plate.

TABLE 2.—REPETITIVE INSPECTION COMPLIANCE TIMES Engine model Type of impulse

coupling assembly Inspect

Lycoming AEIO–540, HIO–540, IO–540, 0–540, and

(1) Riveted Within 100 hours time-since-last inspection (TSLI).

TIO–540 series engines (2) Snap ring Within 500 hours TSLI. (j) Replace any impulse coupling assembly that fails the inspection with a serviceable riveted or snap-ring impulse coupling assembly. Paragraphs 2 through 2.6 of the Detailed Instructions of TCM MSB No. MSB645, dated April 4, 1994 contain information on replacing the impulse coupling assembly. (k) If you replace a snap-ring impulse coupling assembly with a riveted-impulse coupling assembly, strike out the ''A'' on the magneto data plate.

2005-12-06 3

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Optional Terminating Action (l) Installing a ''Shower-of-Sparks'' ignition system in place of a magneto system that has a riveted-impulse coupling assembly or a snap-ring impulse coupling assembly ends the repetitive inspection requirements specified in paragraph (i) of this AD. You can find more information on installing a ''Shower-of-Sparks'' ignition system in TCM Service Information Letter No. SIL648, dated October 18, 1994. Description of Magneto Model Numbering System (m) To assist owners and operators, the description of the magneto numbering system used for TCM S-20, S-1200, D-2000, and D-3000 series magnetos is in the following Table 3:

TABLE 3.—MAGNETO NUMBERING SYSTEM Code: Signifies:

S or D Ignition Type (Single or Dual) 6 Number of Cylinders L or R Direction of Rotation (Left-hand or Right-hand) N (Not used on SC Models) Manufacturer Designation SC (if applicable) Short Cover Configuration –25, –1209, or –3200 Magneto Series

Examples: Description: S6LN–1209 Single type ignition, 6-cyclinder engine, left-hand rotation, TCM

(formerly Bendix), S–1200 series D6RN–3200 Dual type ignition, 6-cylinder engine, right-hand rotation, TCM

(formerly Bendix), D–3000 series S6LSC–25 Single type ignition, 6-cylinder engine, left-hand rotation, short cover

configuration, S–20 series Alternative Methods of Compliance (n) The Manager, Atlanta 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 (o) TCM SB No. 639, dated March 1993, contains additional information for replacing impulse coupling assemblies on a TCM magneto. TCM Service Information Letter No. SIL648, dated October 18, 1994, contains information for converting an engine to a ''Shower-of-Sparks'' ignition system.

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Material Incorporated by Reference (p) You must use Teledyne Continental Motors Mandatory Service Bulletin No. MSB645, dated April 4, 1994 to perform the inspections and replacements required by this AD. The Director of the Federal Register approved the incorporation by reference of this service bulletin as of July 18, 1996 (61 FR 29934, June 13, 1996). You can get a copy from Teledyne Continental Motors, P.O. Box 90, Mobile, AL 36601; telephone (334) 438-3411. For the Teledyne Continental Motors Web site: Go to http://www.TCMLINK.com. You can review copies at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA; 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 June 6, 2005. Jay J. Pardee, Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 05-11610 Filed 6-13-05; 8:45 am] BILLING CODE 4910-13-P

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TURBOMECA S.A. AIRWORTHINESS DIRECTIVE

ENGINE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS

2005-12-08 Turbomeca S.A.: Amendment 39-14124. Docket No. FAA-2005-21443; Directorate Identifier 2005-NE-08-AD. Effective Date (a) This airworthiness directive (AD) becomes effective June 29, 2005. Affected ADs (b) None. Applicability (c) This AD applies to Turbomeca S.A. Arrius 2 B1, 2 B1A, 2 B1A-1, and 2 B2 turboshaft engines. These engines are installed on, but not limited to, Eurocopter Deutschland GmbH EC 135 T1 and EC 135 T2 helicopters. Unsafe Condition (d) This AD results from a report of simultaneous loss of automatic control of both engines of a Eurocopter Deutschland EC 135 helicopter during flight. We are issuing this AD to prevent simultaneous loss of automatic control of both engines and subsequent loss of control of the helicopter. Compliance (e) You are responsible for having the actions required by this AD performed within 90 days after the effective date of this AD, unless the actions have already been done. Onetime Upgrade of Engine Electronic Control Unit (EECU) Software (f) Simultaneously, on both engines of the helicopter, perform a onetime upgrade of EECU software as follows: (1) Either replace the EECU; or (2) Upload the EECU software. (3) Use paragraph 2 of the applicable Turbomeca Mandatory Service Bulletin (MSB) listed in Table 1 of this AD, to do the onetime upgrade.

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TABLE 1.—APPLICABLE MSBS For— Use—

Arrius 2 B1 engines with EECUs that have incorporated Modification TU 19C.

MSB No. 319 73 2080, Update No. 1, dated February 13, 2004.

Arrius 2 B1 engines with EECUs that have incorporated Modification TU 67C or TU 23C.

MSB No. 319 73 2081, Update No. 1, dated February 13, 2004.

Arrius 2 B1A and 2 B1A–1 engines. MSB No. 319 73 2082, Update No. 1, dated February 13, 2004.

Arrius 2 B2 engines MSB No. 319 73 2090, dated February 13, 2004. Alternative Methods of Compliance (g) The Manager, Engine Certification Office, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. Material Incorporated by Reference (h) You must use the Turbomeca Mandatory Service Bulletins specified in Table 2 of this AD to perform the software upgrade required by this AD. The Director of the Federal Register approved the incorporation by reference of the documents listed in Table 2 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Turbomeca S.A., 40220 Tarnos, France; telephone 33 05 59 74 40 00, fax 33 05 59 74 45 15, for a copy of this service information. You may review copies at the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room 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.

TABLE 2.—INCORPORATION BY REFERENCE Mandatory service bulletin No. Page Revision Date

319 73 2080 ALL 1 February 13, 2004. Total Pages—6



319 73 2090 ALL Original February 13, 2004. Total Pages—7

Related Information (i) DGAC airworthiness directive F-2004-017 R1, dated March 3, 2004, also addresses the subject of this AD. Issued in Burlington, Massachusetts, on June 6, 2005. Jay J. Pardee, Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 05-11611 Filed 6-13-05; 8:45 am] BILLING CODE 4910-13-U

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GROB-WERKE AIRWORTHINESS DIRECTIVE

SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2005-12-09 Grob-Werke: Amendment 39-14125; Docket No. FAA-2005-20589; Directorate Identifier 2005-CE-12-AD. When Does This AD Become Effective? (a) This AD becomes effective on July 28, 2005. What Other ADs Are Affected by This Action? (b) None. What Airplanes Are Affected by This AD? (c) This AD affects Model G120A airplanes, all serial numbers, that are certificated in any category. What Is the Unsafe Condition Presented in This AD? (d) This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this AD to detect and correct cracks and damage in the nose landing gear (NLG) assembly, which could result in failure of the NLG. This failure could lead to a hard landing and/or loss of control of the airplane during landing operations. What Must I Do To Address This Problem? (e) To address this problem, you must do the following:

Actions Compliance Procedures (1) Inspect the nose landing gear (NLG) assembly for cracks or damages (defective) welding seams. Pay special attention to the NLG swivel tube and the engine truss in the area of the NLG attachment.

Initially inspect within the next 50 hours time-in-service (TIS) after July 28, 2005 (the effective date of this AD), unless already done. Repetitively inspect thereafter at intervals not to exceed 50 hours TIS.

Follow GRDB Service Bulletin No. MSB1121–055 dated November 26, 2004.

2005-12-09 2

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(2) If you find cracks or defects during any inspection required in paragraph (e)(1) of this AD, replace the cracked or defective part.

Replace before further flight after the inspection in which cracks and/or defects are found. After you replace the cracked or defective part, continue with the repetitive inspections required in paragraph (e)(1) of this AD at the 50 hours TIS intervals.

Follow GROB Service Bulletin No. MSB1121–055 dated November 26, 2004.

Note: The compliance time in this AD is different than the compliance time in GROB Service Bulletin No. MSB1121-055 dated November 26, 2004. The compliance time in this AD takes precedence over the compliance time in the service information. May I Request an Alternative Method of Compliance? (f) You may request a different method of compliance or a different compliance time for this AD by following the procedures in 14 CFR 39.19. Unless FAA authorizes otherwise, send your request to your principal inspector. The principal inspector may add comments and will send your request to the Manager, Standards Office, Small Airplane Directorate, FAA. For information on any already approved alternative methods of compliance, contact Karl Schletzbaum, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4146; facsimile: (816) 329-4090. Is There Other Information That Relates to This Subject? (g) German AD Number D-2004-514, effective date: December 9, 2004, also addresses the subject of this AD. Does This AD Incorporate Any Material by Reference? (h) You must do the actions required by this AD following the instructions in GROB Service Bulletin No. MSB1121-055 dated November 26, 2004. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of this service information, contact GROB Luft-und Raumfahrt, Lettenbachstrasse 9, D-86874 Tussenhausen-Mattsies, Federal Republic of Germany; telephone: 011 49 8268 998139; facsimile: 011 49 8268 998200. 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-2005-20589; Directorate Identifier 2005-CE-12-AD. Issued in Kansas City, Missouri, on June 6, 2005. Kim Smith, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-11614 Filed 6-13-05; 8:45 am] BILLING CODE 4910-13-P

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BW 2005-13

CESSNA AIRCRAFT COMPANY AIRWORTHINESS DIRECTIVE


CORRECTION: There are 2 critical typos in the table of AD 2005-12-12, Federal Register (FR), page 34332, June 14, 2005. "(i)", third column, should read "within 100 hours TIS...". "(ii)", first column, should read "12,000 hours TIS...". The Government Printing Office will issue a correction to the FR. We have corrected this copy. 2005-12-12 Cessna Aircraft Company: Amendment 39-14128; Docket No. FAA-05-21176; Directorate Identifier 2005-CE-25-AD. When Does This AD Become Effective? (a) This AD becomes effective on June 22, 2005. Are Any Other ADs Affected by This Action? (b) Yes. This AD supersedes AD 79-10-15; Amendment 39-3711. What Airplanes Are Affected by This AD? (c) This AD affects Models 401, 401A, 401B, 402, 402A, 402B, 411, and 411A, all serial numbers, that are certificated in any category. What Is the Unsafe Condition Presented in This AD? (d) This AD is the result of fatigue cracks found in the lower wing spar caps. We are issuing this AD to prevent wing spar cap failure caused by undetected fatigue cracks. Such failure could result in loss of a wing with consequent loss of airplane control. What Must I Do To Address This Problem? (e) Repetitive Inspection and Modification of the Wing Spars: (1) For Cessna Models 411 and 411A airplanes that do not incorporate Cessna Service Kit SK411-56, SK411-56A, SK411-56B, or SK411-59, maintain the repetitive inspections required by AD 79-10-15, Amendment 39-3711, and do the actions below. You may terminate the repetitive inspections of AD 79-10-15 after you incorporate the modification using the service information in paragraph (h)(2) of this AD:

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If you have equal to or more than—

But less than— Then initially inspect and modify using the service information in paragraph (h)(2) of this AD, and

reinspect as specified in paragraph (e)(3) of this AD(i) 18,000 hours time-in-service (TIS) on the wing or wing spar.

Not applicable Within 100 hours TIS after June 22, 2005 (the effective date of this AD), unless already done.

(ii) 12,000 hours TIS on the wing or wing spar

18,000 hours TIS Within 200 hours TIS after June 22, 2005 (the effective date of this AD), unless already done.

(iii) 10,000 hours TIS on the wing or wing spar


(iv) 5,500 hours TIS on the wing or wing spar


(v) 0 hours TIS on the wing or wing spar

5,500 hours TIS At whichever of the following occurs later: • Upon accumulating 5,500 hours TIS on the wing or

wing spar; or • Within 800 TIS after June 22, 2005 (the effective

date of this AD), unless already done. (vi) If the wings or wing spars were replaced with new or used wings or wing spars during the life of the airplane and logbook records positively show the TIS of the wings or wing spars, then initially inspect and modify at applicable wing or wing spar times in paragraphs (e)(1)(i) through (e)(1)(v) of this AD. (vii) If the wings or wing spars were replaced with new or used wings or wing spars during the life of the airplane and logbook records cannot positively show the TIS of the wings or wing spars, then inspect and modify within 100 hours TIS after June 22, 2005 (the effective date of this AD), unless already done. (2) For Cessna Models 401, 401A, 401B, 402, 402A, and 402B airplanes that do not incorporate Cessna Service Kit SK402-36, SK402-36A, SK402-36B, SK402-36C, SK402-46, or SK402-46A, maintain the repetitive inspections required by AD 79-10-15, Amendment 39-3711, and do the actions below. You may terminate the repetitive inspections of AD 79-10-15 after you incorporate the modification using the service information in paragraph (h)(1) of this AD: If you have equal to or

more than— But less than— Then initially inspect and modify using the service

information in paragraph (h)(1) of this AD, and reinspect as specified in paragraph (e)(4) of this AD

(i) 18,000 hours TIS on the wing or wing spar

Not applicable Within 100 hours TIS after June 22, 2005 (the effective date of this AD), unless already done.



(iii) 10,000 hours TIS on the wing or wing spar


(iv) 6,500 hours TIS on the wing or wing spar


(v) 0 hours TIS on the wing or wing spar


wing spar; or • Within 800 TIS after June 22, 2005 (the effective

date of this AD), unless already done.

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(vi) If the wings or wing spars were replaced with new or used wings or wing spars during the life of the airplane and logbook records positively show the TIS of the wings or wing spars, then initially inspect and modify at applicable wing or wing spar times in paragraphs (e)(2)(i) through (e)(2)(v) of this AD. (vii) If the wings or wing spars were replaced with new or used wings or wing spars during the life of the airplane and logbook records cannot positively show the TIS of the wings or wing spars, then inspect and modify within 100 hours TIS after June 22, 2005 (the effective date of this AD), unless already done. (3) For all Cessna Models 411 and 411A airplanes with Cessna Service Kit SK411-56, SK411-56A, SK411-56B, or SK411-59 incorporated, inspect in the following areas and repair or replace as necessary prior to further flight after the inspection where cracks are found. Inspection areas and procedures are defined in the Cessna Model 411 Supplemental Inspection Document (SID): (i) Area ''A'' (Inspection ID 57-10-11): Initially upon accumulating 5,500 hours TIS after incorporating the applicable service kit on a wing spar or within the next 100 hours TIS after June 22, 2005 (the effective date of this AD), whichever occurs later, unless already done, and thereafter at intervals not to exceed 2,500 hours TIS. (ii) Area ''B'' (Inspection ID 57-10-12): Initially upon accumulating 5,500 hours TIS after incorporating the applicable service kit on a wing spar or within the next 100 hours TIS after June 22, 2005 (the effective date of this AD), whichever occurs later, unless already done, and thereafter at intervals not to exceed 1,000 hours TIS. (iii) Area ''C'' (Inspection ID 57-10-08): Upon accumulating 20,000 hours TIS after incorporating the applicable service kit on a wing spar or within the next 100 hours TIS after June 22, 2005 (the effective date of this AD), whichever occurs later, unless already done, and thereafter at intervals not to exceed 2,000 hours TIS. (4) For all Cessna Models 401, 401A, 401B, 402, 402A, and 402B airplanes with Cessna Service Kit SK402-36, SK402-36A, SK402-36B, SK402-36C, SK402-46, or SK402-46A incorporated, inspect in the following areas and repair or replace as necessary prior to further flight after the inspection where cracks are found. Inspection areas and procedures are defined in the Cessna Models 401and 402 SID (compliance times in this AD take precedence over the compliance times in the SID): (i) Area ''A'' (Inspection ID 57-10-11): Initially upon accumulating 15,000 hours TIS after incorporating the applicable service kit on a wing spar or within the next 100 hours TIS after June 22, 2005 (the effective date of this AD), whichever occurs later, unless already done, and thereafter at intervals not to exceed 5,000 hours TIS. (ii) Area ''B'' (Inspection ID 57-10-12): Initially upon accumulating 7,500 hours TIS after incorporating the applicable service kit on a wing spar or within the next 100 hours TIS after June 22, 2005 (the effective date of this AD), whichever occurs later, unless already done, and thereafter not to exceed 5,000 hours TIS. You may request an alternative method of compliance to adjust the compliance times for these inspections by following the procedures in 14 CFR 39.19 and this AD. (iii) Area ''C'' (Inspection ID 57-10-08): Upon accumulating 20,000 hours TIS after incorporating the applicable service kit on a wing spar or within the next 100 hours TIS after June 22, 2005 (the effective date of this AD), whichever occurs later, unless already done, and thereafter at intervals not to exceed 2,500 hours TIS.

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(f) Wing Spar Replacement if Cracks Found During any Inspection Required by this AD: (1) Prior to further flight, replace the wing spar with a new wing spar or a used wing spar where wing or wing spar hours TIS can be positively identified. Do not install used wings spars when you are not able to positively identify total wing or wing spar hours TIS. (2) After replacement, initially inspect at the applicable time in paragraphs (e)(1)(i) through (e)(1)(vii) or (e)(2)(i) through (e)(2)(vii) of this AD and repetitively inspect at the times specified in paragraphs (e)(3)(i) through (e)(3)(iii) or (e)(4)(i) through (e)(4)(iii) of this AD. (g) Reporting Requirement: Report any cracks you find within 10 days after the cracks are found or within 10 days after June 22, 2005 (the effective date of this AD), whichever occurs later. Do not report if no cracks are found. Include in your report the aircraft serial number, aircraft TIS, wing spar cap TIS, crack location and size, corrective action taken, and a point of contact name and phone number. Send your report to Paul Nguyen, Aerospace Engineer, FAA, ACE-118W, Wichita Aircraft Certification Office, 1801 Airport Road, Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316) 946-4125; facsimile: (316) 946-4107. (h) Service Information to Perform the Actions of this AD: (1) Original issue dated September 24, 2001, and Revision 1, dated December 22, 2003, of both Cessna Multi-engine Service Bulletin MEB01-06 and Service Kit SK402-46A; and (2) Original issue dated September 24, 2001, of both Cessna Multi-engine Service Bulletin MEB01-07 and Service Kit SK411-59. May I Request an Alternative Method of Compliance? (i) 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 Paul Nguyen, Aerospace Engineer, FAA, ACE-118W, Wichita Aircraft Certification Office, 1801 Airport Road, Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316) 946-4125; facsimile: (316) 946-4107. Does This AD Incorporate Any Material by Reference? (j) You must do the actions required by this AD following the instructions in Cessna Multi-Engine Service Bulletin MEB01-6 and Service Kit SK402-46, both dated September 24, 2001; Cessna Multi-Engine Service Bulletin MEB01-6, Revision 1 and Service Kit SK402-46A, both dated December 22, 2003; and Cessna Multi-Engine Service Bulletin MEB01-7 and Service Kit SK411-59, both dated September 24, 2001. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of this service information, contact Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita, Kansas 67277; telephone: (316) 517-5800; facsimile: (316) 942-9006. 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-05-21176; Directorate Identifier 2005-CE-25-AD.

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Issued in Kansas City, Missouri, on June 7, 2005. Kim Smith, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-11612 Filed 6-13-05; 8:45 am] BILLING CODE 4910-13-U

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BW 2005-13



2005-12-13 Cessna Aircraft Company: Amendment 39-14129; Docket No. FAA-05-21177; Directorate Identifier 2005-CE-26-AD. When Does This AD Become Effective? (a) This AD becomes effective on June 22, 2005. Are Any Other ADs Affected by This Action? (b) Yes. This AD supersedes AD 2005-05-52; Amendment 39-14022. What Airplanes Are Affected by This AD? (c) This AD affects Models 402C and 414A, all serial numbers, that are certificated in any category. What is the Unsafe Condition Presented in This AD? (d) This AD is the result of fatigue cracks found in the lower wing spar caps. We are issuing this AD to prevent wing spar cap failure caused by undetected fatigue cracks. Such failure could result in loss of a wing with consequent loss of airplane control. What Must I Do To Address This Problem? (e) Modification of the Wing Spars: (1) For Cessna Model 414A airplanes, serial numbers 414A0001 through 414A0047 and 414A0049 through 414A0200, incorporate a spar strap modification on each wing (Cessna Multi-Engine Service Kit SK402-47B, dated August 2, 2003), following Cessna Multi-Engine Service Bulletin MEB02-5, Revision 2, dated August 2, 2004, unless Cessna Multi-Engine Service Kit SK402-47, SK402-47A, or SK402-47B has already been done. The above modifications terminate the repetitive inspection requirements of AD 2005-05-52: If you have equal to or

more than— But less than— Modification of the lower Wing Spar Cap compliance

times (i) 12,000 hours time-in-service (TIS)

Not Applicable Within 400 hours TIS after June 22, 2005 (the effective date of this AD).


12,000 hours TIS Within 800 hours TIS after June 22, 2005 (the effective date of this AD).

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(iii) 0 hours TIS on the wing or wing spar;

9,000 hours TIS At whichever of the following occurs later: • Upon accumulating 9,000 hours TIS or • Within 800 hours TIS after June 22, 2005 (the

effective date of this AD). (2) For Cessna Model 402C airplanes, all serial numbers; and Model 414A airplanes, serial numbers 414A0201 through 414A1212, incorporate a spar strap modification on each wing (Cessna Multi-Engine Service Kit SK402-47B, dated August 2, 2003), following Cessna Multi-Engine Service Bulletin MEB02-5, Revision 2, dated August 2, 2004, unless Cessna Multi-Engine Service Kit SK402-47, SK402-47A, or SK402-47B has already been done. The above modifications terminate the repetitive inspection requirements of AD 2005-05-52: If you have equal to or

more than— But less than— Modification of the lower Wing Spar Cap compliance

times (i) 20,000 hours TIS Not Applicable Within 400 hours TIS after June 22, 2005 (the effective

date of this AD). (ii) 15,000 hours TIS on the wing or wing spar

20,000 hours TIS Within 800 hours TIS after June 22, 2005 (the effective date of this AD).

(iii) 0 hours TIS on the wing or wing spar


wing spar; or • Within 800 TIS after June 22, 2005 (the effective date

of this AD). (f) Repetitive Inspection of the Wing Spar: Until the modification in paragraph (e)(1) and (e)(2) of this AD is done, continue the repetitive eddy current inspections of the forward wing spars combined with visual inspections of the aft and auxiliary spars as mandated by AD 2005-05-52. Do these inspections following the ACCOMPLISHMENT INSTRUCTIONS section of Cessna Service Bulletin MEB99-3 (Model 402C) or Cessna Service Bulletin MEB00-7 (Model 414A), both at Revision 2 and both dated February 28, 2005. The modification required in paragraph (e)(1) and (e)(2) of this AD terminates the repetitive inspection requirements of AD 2005-05-52.

Affected airplanes Eddy current and visual inspections Repetitive Eddy current and

visual inspection interval

(1) For Model 414A airplanes, serial numbers 414A0001 through 414A0047 and 414A0049 through 414A0200.

At whichever of the following occurs later: • Upon accumulating 8,500 hours TIS on the

airplane; • At the next inspection that would have been

required by emergency AD 2005–05–51 (required at intervals not to exceed 15 hours TIS); or.

• Within the next 2 days after the March 21, 2005 (the effective date of AD 2005–05–52) (2 days after receipt for those who received this AD as an emergency AD)

Thereafter at intervals not to exceed 100 hours TIS.

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(2) For the following airplanes that have 15,000 hours or more TIS or upon accumulating 15,000 hours TIS:

(i) All Model 402C airplanes.

(ii) Model 414A airplanes, serial numbers 414A0201 through 414A1212.

At whichever of the following occurs later: • Upon accumulating 15,000 hours TIS on the

airplane; • At the next inspection that would have been

required by emergency AD 2005–05–51 (required at intervals not to exceed 15 hours TIS); or

• Within the next 2 days after March 21, 2005 (the effective date of AD 2005–05–52) (2 days after receipt for those who received this AD as an emergency AD).

Thereafter at intervals not to exceed 100 hours TIS.

(g) If the wings or wing spars were replaced with new or used wings or wing spars during the life of the airplane and logbook records positively show the TIS of the wings or wing spars, then initially inspect and modify at applicable wing or wing spar times in paragraphs (e)(1), (e)(2), and (f) of this AD. (h) If the wings or wing spars were replaced with new or used wings or wing spars during the life of the airplane and logbook records cannot positively show the TIS of the wings or wing, then inspect and modify within 400 hours TIS after June 22, 2005 (the effective date of this AD), unless already done. (i) For all Cessna Models 402C and 414A airplanes with Cessna Service Kit SK402-47, SK402-47A, or SK402-47B incorporated, inspect and repair or replace as necessary prior to further flight after the inspection where cracks are found. Inspect following the procedures in Cessna Model 402C and 414A Supplemental Inspection Document (SID), Inspection ID 57-10-16 (compliance times in this AD take precedence over the compliance times in the SID): Initially upon accumulating 12,500 hours TIS after incorporating the applicable service kit on a wing spar or within the next 100 hours TIS after June 22, 2005 (the effective date of this AD), whichever occurs later, unless already done, and thereafter at intervals not to exceed 500 hours TIS. You may request an alternative method of compliance to adjust the compliance times for these inspections by following the procedures in 14 CFR 39.19 and this AD. (j) Wing Spar Replacement if Cracks Found During any Inspection Required by this AD: Prior to further flight, replace the wing spar with a new wing spar or a used wing spar where wing or wing spar hours TIS can be positively identified. Do not install used wings spars when you are not able to positively identify total wing or wing spar hours TIS. (k) Reporting Requirement: Report any cracks you find within 10 days after the cracks are found or within 10 days after June 22, 2005 (the effective date of this AD), whichever occurs later. Do not report if no cracks are found. Include in your report the aircraft serial number, aircraft TIS, wing spar cap TIS, crack location and size, corrective action taken, and a point of contact name and phone number. Send your report to Paul Nguyen, Aerospace Engineer, FAA, ACE-118W, Wichita Aircraft Certification Office, 1801 Airport Road, Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316) 946-4125; facsimile: (316) 946-4107.

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May I Request an Alternative Method of Compliance? (l) 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 Paul Nguyen, Aerospace Engineer, FAA, ACE-118W, Wichita Aircraft Certification Office, 1801 Airport Road, Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316) 946-4125; facsimile: (316) 946-4107. Does This AD Incorporate Any Material by Reference? (m) You must do the actions required by this AD following the instructions in Cessna Multi-Engine Service Bulletin MEB02-5, Revision 2, dated August 2, 2004, and Service Kit SK402-47B, dated August 2, 2003. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of this service information, contact Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita, Kansas 67277; telephone: (316) 517-5800; facsimile: (316) 942-9006. 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-05-21177; Directorate Identifier 2005-CE-26-AD. Issued in Kansas City, Missouri, on June 7, 2005. Kim Smith, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-11613 Filed 6-13-05; 8:45 am] BILLING CODE 4910-13-U

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BW 2005-13

THE LANCAIR COMPANY AIRWORTHINESS DIRECTIVE

SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS CORRECTION: There is a typo in AD 2005-12-20, paragraph (c) of today's, June 20, 2005, Federal Register (FR), page 35371, third column. The correct affected model should read "LC41-550FG". We will issue a correction to the FR. We have corrected this copy. 2005-12-20 The Lancair Company: Amendment 39-14136; Docket No. FAA-2005-21357; Directorate Identifier 2005-CE-29-AD. When Does This AD Become Effective? (a) This AD becomes effective on June 21, 2005. Are Any Other ADs Affected by This Action? (b) None. What Airplanes Are Affected by This AD? (c) This AD affects Model LC41-550FG airplanes, serial numbers 41001 through 41082, that are certificated in any category. What Is the Unsafe Condition Presented in This AD? (d) This AD results from cracks found in the weld area of the elevator torque tube assembly. We are issuing this AD to detect and correct cracks in the elevator torque tube assembly, which could result in failure of the elevator torque tube assembly and subsequent loss of control of the airplane. What Must I Do To Address This Problem? (e) To address this problem, you must do the following: Note 1: The Lancair Company Certified Aircraft Mandatory Service Bulletin SB-05-005A, Model 400, dated May 20, 2005, allows the pilot to perform the visual inspection of the elevator torque tube assembly. The Federal Aviation Regulations (14 CFR 43.3) only allow the pilot to perform preventive maintenance as described in 14 CFR part 43, App. A, paragraph (c). These visual inspections are not considered preventive maintenance under 14 CFR part 43, App. A, paragraph (c). Therefore, an appropriately-rated mechanic must perform all actions of this AD.

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Actions Compliance Procedures (1) Visually inspect the area of weld joining the torque tube to the elevator end rib for cracks.

Before further flight after June 21, 2005 (the effective date of this AD), and before each flight until the action required in paragraph (e)(2) of this AD is done until a crack is found, whichever occurs first. It is acceptable to do the dye penetrant inspection and modification required in paragraph (e)(2) of this AD before further flight and eliminate the need for the visual inspection(s).

Follow Part 1 of The Lancair Company Certified Aircraft Mandatory Service Bulletin SB–05–005A, Model 400, dated May 20, 2005.

(2) Do a dye penetrant inspection of the area of weld joining the torque tube to the elevator end rib for cracks and modify the elevator torque tube assembly by installing a steel doubler.

Within 10 hours TIS after June 21, 2005 (the effective date of this AD). Doing the dye penetrant inspection and modification terminates the repetitive visual inspection required in paragraph (e)(1) of this AD. This modified elevator torque tube assembly has a safe limit of 300 hours TIS or 18 months after modification, whichever occurs first, and you must replace it at that interval.

Follow Part 2 of The Lancair Company Certified Aircraft Mandatory Service Bulletin SB–05–005A, Model 400, dated May 20, 2005, and Revision B to Chapter 4 of Maintenance Manual RC050001, dated May 25, 2005.

(3) Replace the elevator torque tube assembly with a new assembly that incorporates a steel doubler in the area of weld joining the torque tube to the elevator end rib.

Any time a crack is found during any inspection required in paragraphs (e)(1) and (e)(2) of this AD. You may do the replacement sooner if desired, in which case, you may discontinue the inspections in paragraphs (e)(1) and (e)(2) of this AD. The new replacement assembly has a safe life limit of 300 hours TIS or 18 months after replacement, whichever occurs first, and you must replace it at that interval.

Follow Part 2 of The Lancair Company Certified Aircraft Mandatory Service Bulletin SB–05–005A, Model 400, dated May 20, 2005, and Revision B to Chapter 4 of Maintenance Manual RC050001, dated May 25, 2005.

Note 2: The compliance times in this AD take precedence over the compliance times in the service information. 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, Seattle Aircraft Certification Office, FAA. For information on any already approved alternative methods of compliance, contact Mr. Jeffrey Morfitt, Program Manager, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue, SW., Renton, Washington 98055-4065; telephone: (425) 917-6405; facsimile: (425) 917-6590. Does This AD Incorporate Any Material by Reference? (g) You must do the actions required by this AD following the instructions in The Lancair Company Certified Aircraft Mandatory Service Bulletin SB-05-005A, Model 400, dated May 20, 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 The Lancair Company 22550 Nelson Road, Bend Oregon 97701; telephone: (541) 330-4191; e-mail: [email protected]. To review copies of this service information,

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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-05-21357; Directorate Identifier 2005-CE-29-AD. Issued in Kansas City, Missouri, on June 10, 2005. Kim Smith, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-11880 Filed 6-17-05; 8:45 am] BILLING CODE 4910-13-P

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ROCKWELL INTERNATIONAL AIRWORTHINESS DIRECTIVE


2005-12-51 Rockwell International (Aircraft Specification No. A-2-575 previously held by North American and recently purchased by Boeing) and Autair Ltd. (Aircraft Specification No. AR-11 previously held by Noorduyn Aviation Ltd.): Amendment 39-14144; Docket No. FAA-2005-24163; Directorate Identifier 2005-CE-30-AD. When Does This AD Become Effective? (a) This AD becomes effective on June 23, 2005, to all affected persons who did not receive emergency AD 2005-12-51, issued June 8, 2005. Emergency AD 2005-12-51 contained the requirements of this amendment and became effective immediately upon receipt. Are Any Other ADs Affected By This Action? (b) None. What Airplanes Are Affected by This AD? (c) This AD affects Models 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 airplanes, all serial numbers, that are certificated in any category. What Is the Unsafe Condition Presented in This AD? (d) This AD is the result of a report of a Rockwell International Model SNJ-6 (AT-6F) airplane crash that occurred on May 9, 2005, resulting in two fatalities. We are issuing this AD to detect and correct cracking in the wing spars before the cracks grow to failure. Such a wing failure could result in the wing separating from the airplane with consequent 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 Compliance Procedures (1) Perform a fluorescent penetrant inspection of all inboard and outboard, upper and lower wing attach angles (except for the nose an-gles) of both wings for cracks. Replace the angles as necessary.

(i) Initially inspect before further flight after June 23, 2005 (the effective date of this AD), unless previously done within the last 10 hours time-in-service (TIS), except for those who received emergency AD 2005– 12–51, issued June 8, 2005. Emergency AD 2005–12–51 contained the require-ments of this amendment and became ef-fective immediately upon receipt. (ii) Repetitively inspect thereafter every

200 hours TIS. (iii) Replace angles as necessary prior

to fur-ther flight after the inspection where cracks are found.

Follow the Appendix to this AD.

(2) For all airplanes: Report to FAA the results of the initial inspection required by paragraph (e)(1) of this AD even if no damage is found and even if the inspection was previously done. The Office of Management and Budget (OMB) approved the information collection re-quirements contained in this regulation under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 and those fol-lowing sections) and assigned OMB Control Number 2120–0056.

Within 7 days after the inspection required by paragraph (e)(1) of this AD or within 7 days after June 23, 2005 (the effective date of this AD), except that this action was already required upon receipt for those who re-ceived emergency AD 2005–12–51.Therefore, those who sent in a report through emergency AD 2005–12–51 do not have to resend that initial report.

Send the form (Figure 1 of this AD) to FAA, Los Angeles ACO, 3960 Paramount Blvd., Lakewood, CA 90712; facsimile: (562) 627– 5210. E-mail: [email protected].

(3) You may operate the airplane to return/posi-tion the airplane to a home base, hangar, maintenance facility, etc., for the purpose of doing the inspection required by this AD pro-vided you follow the limitations in paragraph (f) of this AD.

You may operate the airplane up to 10 hours TIS provided the flight(s) occur(s) no later than 30 days after June 8, 2005. This is a one-time provision.

Not Applicable.

(4) Special flight permits are allowed for this AD. See paragraph (f) of this AD for restric-tions.

Use the procedures in 14 CFR part 39 and the restrictions in paragraph (f) of this AD.

Not Applicable.

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What Are the Flight Restrictions Specified in Paragraphs (e)(3) and (e)(4) of This AD? (f) During the time allowed before compliance with the initial inspection required by paragraph (e)(1) of this AD, or for any approved special flight permit, you must adhere to the following limitations: (1) Acrobatic maneuvers are prohibited. (2) Flight into known or forecast moderate or severe turbulence is prohibited. (3) Day visual flight rules (VFR) operation only. (4) Single pilot operation only (Passengers prohibited).

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May I Request an Alternative Method of Compliance? (g) 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, Los Angeles Aircraft Certification Office (ACO), FAA. For information on any already approved alternative methods of compliance or for further information about this AD, contact Fred Guerin, Aerospace Engineer, FAA, Los Angeles ACO, 3960 Paramount Blvd., Lakewood, CA 90712; telephone: (562) 627-5232; facsimile: (562) 627-5210; e-mail: [email protected]. Where Do I View the AD Docket? (h) 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-2005-24163. Issued in Kansas City, Missouri, on June 14, 2005. John R. Colomy, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. Appendix to AD 2005-12-51 Wing Attachment Angle Inspection for: Models 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 Airplanes Procedures: (1) Remove all outboard wing attach angle covers. (2) Support outboard wing on appropriate stands to relieve the weight on the wing attach bolts. (3) On the upper wing attach angles, except for the forward and aft five bolts on the angle, remove all of the through bolts that attach the outboard wing (Do not remove bolts in the nose angle). (4) Remove all paint down to the bare metal using solvent on outer surface of affected angles. Do not sand or use media blasting or use any method that would cover up or contaminate a crack. This means not using Scotchbrite or a similar abrasive, which can contaminate a crack for penetrant inspection. (5) Use the penetrant manufacturer's cleaner, acetone, or 90-percent or more alcohol solution to do a final surface cleaning preparation step before the fluorescent penetrant inspection. (6) Perform an inspection of the outboard and inboard wing attach angles using a high sensitivity fluorescent dye penetrant inspection procedure per the penetrant manufacturer's instructions. Pay particular attention to cracks that may be present in the edge of the spot faces closest to the radius of the angle. Also pay attention to any small cracks that may be emanating from the edge of the fasteners in any row of installed fasteners. Choose a commercially available fluorescent inspection method that requires the use of an ultraviolet (black light) in a darkened environment. Do not use dye penetrant, which is read under normal lighting conditions. (7) Check the wing attachment angle for condition and for security of rivets and bolts. (8) If no cracks or major defects are found, replace nuts and bolts following directions in paragraphs (11) and (12) of this appendix of this AD, clean angle, and apply a corrosion protectant coating paint (Alodine alone is not acceptable).

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(9) On the upper wing, remove the forward and aft five bolts that were previously left in place, and inspect the remaining uninspected portion of the angles following the above procedure. (10) On the lower wings, repeat the inspection on the bottom two attach angles in the same sequence as on the top angles. (11) When replacing bolts in angles, use only nuts, bolts, and torque values as specified in ''Erection and Maintenance No. AN01-60FFA-2'' or ''Erection and Maintenance No. AN01-60F-2'' as applicable to the aircraft model. Bolts may be reused if upon inspection they are found to be in airworthy condition. Nuts may be reused as long as the nylon-locking feature is functional, and they cannot be turned onto the bolt with fingers. Torque values for \1/4\-inch bolts are 60-65 inch/lb, and for \5/16\-inch bolts are 100-105 inch/lb. These torque values supersede those in the manuals. (12) To assure that the nuts do not contact the shoulder of the wing attach bolts and cause an under torque condition, assure that no more than two threads are protruding from nut after torquing. If more than two threads are protruding, replace with a bolt of the correct length. (13) If any cracks are found, replace the angle with a new part. Send all cracked angles to Fred Guerin, Aerospace Engineer, FAA, Los Angeles ACO, 3960 Paramount Blvd., Lakewood, CA 90712.

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HOFFMANN PROPELLER GMBH & CO KG AIRWORTHINESS DIRECTIVE

PROPELLER SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS

2005-13-01 Hoffmann Propeller GmbH & Co KG: Amendment 39-14137. Docket No. FAA-2004-18958; Directorate Identifier 2004-E-32-AD. Effective Date (a) This airworthiness directive (AD) becomes effective July 7, 2005. Affected ADs (b) This AD supersedes AD 2004-18-01, Amendment 39-13778. Applicability (c) This AD applies to Hoffmann Propeller GmbH & Co KG (Hoffmann Propeller) models HO-V343 and HO-V343K propellers. These propellers are installed on, but not limited to, general aviation airplanes possibly having an FAA-approved Supplemental Type Certificate. Unsafe Condition (d) This AD results from a report of a blade separating from either a model HO-V343 or HO-V343K propeller. We are issuing this AD to prevent propeller hub failure and blade separation due to an unknown root cause, leading to damage and possible 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. Propeller Blade Shake Inspection During Preflight Inspection (f) For all propellers, perform an inspection for propeller blade shake at each preflight inspection. If you have any blade shake, replace the propeller assembly. Propeller Blade Nut Preload Inspection (g) For all propellers, use paragraph 2.1 of the Accomplishment Instructions of Hoffmann Propeller Service Instruction (SI) No. 61-10-05 SI E 4D, dated March 16, 2005, to inspect blade nut preload at the following intervals: (1) Before further flight after the effective date of this AD. (2) Inspect within 50 flight hours (FH) time-since-initial inspection.

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(3) Thereafter, inspect within 100 FH time-since-last inspection (TSLI). (h) If the blade nut preload inspection shows a loss of the blade nut preload, before further flight perform an ultrasonic inspection (UI) as specified in paragraph (i) of this AD. Ultrasonic Inspection (i) If the propeller meets any of the conditions detailed in subparagraphs (1) and (2) below, before further flight, calibrate the ultrasonic probe and conduct an ultrasonic inspection of the propeller hub blade retaining threads for cracks inserting the probe in each hub arm bore. Use paragraph 2.2 of the Accomplishment Instructions of Hoffmann Propeller Service Instruction (SI) No. 61-10-05 SI E 4D, dated March 16, 2005, to perform the inspection. (1) The propeller hub has accumulated 500 or more FH time-since-new (TSN), and has not been inspected using an ultrasonic or eddy current method, or (2) The blade nut preload and final retorque force inspection called for in paragraph (g) of this AD indicates a loss of blade retention nut preload torque below allowable limits. (j) For propellers with hubs that have accumulated 500 or more FH TSN repeat the ultrasonic inspection within intervals of 100 FH TSLI. Eddy Current Inspection (k) If the ultrasonic inspection shows any signs of cracks or damage, conduct an eddy current inspection of the threads in the hub bore before further flight. Use paragraph 2.3 of the Accomplishment Instructions of Hoffmann Propeller Service Instruction (SI) No. 61-10-05 SI E 4D, dated March 16, 2005, to perform this inspection. (l) If you find any signs of cracks or damage to the propeller hub outside serviceable limits during the eddy current inspection, repair or replace the propeller before further flight. Credit for Previous Inspections (m) Previous credit is allowed for propeller hub inspections performed under the requirements of AD 2004-18-01. Hub Inspection Report (n) Complete Hoffmann Hub Inspection Report HO-V343 detailing any blade shake, blade nut preload history and final blade nut retorque force and forward report to Hoffmann Propeller GmbH & Co KG, Küpferlingstraße 9, D-83022 Rosenheim, Germany, telephone ++49-(0)8031-1878-0; fax ++49-(0)8031-1878-78. Alternative Methods of Compliance (AMOCs) (o) The Manager, Boston 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.

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Material Incorporated by Reference (p) You must use Hoffmann Propeller Service Instruction No. 61-10-05 SI E 4D, dated March 16, 2005, to perform the checks and inspections 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. You can get a copy from Hoffmann Propeller GmbH & Co KG, Küpferlingstraße 9, D-83022 Rosenheim, Germany, telephone ++49-(0)8031-1878-0; fax ++49-(0)8031-1878-78; 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. Related Information (q) LBA airworthiness directive D-2004-352R4, dated April 10, 2005, which holds EASA Approval No. 2005-2514, also addresses the subject of this AD. Issued in Burlington, Massachusetts, on June 13, 2005. Francis A. Favara, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 05-12172 Filed 6-21-05; 8:45 am] BILLING CODE 4910-13-P

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HONEYWELL INTERNATIONAL INC.. AIRWORTHINESS DIRECTIVE


2005-13-07 Honeywell International Inc. (formerly AlliedSignal Inc. and Garrett Turbine Engine Co.): Amendment 39-14143. Docket No. FAA-2004-18496; Directorate Identifier. 2004-NE-04-AD. Effective Date (a) This airworthiness directive (AD) becomes effective July 27, 2005. Affected ADs (b) None. Applicability (c) This AD applies to Honeywell International Inc. (formerly AlliedSignal Inc. and Garrett Turbine Engine Co.) TFE731-2 and -3 series turbofan engines with the following low pressure (LP) 1st and 2nd stage turbine rotor disc part numbers (P/Ns), with serial numbers (SNs) listed in Tables 1, 2, and 3 of Honeywell International Inc. SB No. TFE731-72-3682, dated November 26, 2002, initially installed as new parts before April 1, 1991:

PART NUMBERS 3072069-All 3073014-All 3072070-All 3073113-All 3072351-All 3071114-All 3072542-All 3074103-All 3073013-All 3074105-All (All denotes all dash numbers installed)

These engines are installed on, but not limited to, the following airplanes: Avions Marcel Dassault Mystere-Falcon 10 and 50 series Cessna Model 650, Citation III, and Citation VI Gulfstream Aerospace LP (formerly IAI) 1125 Westwind Astra series Israel Aircraft Industries (IAI) 1124 series Learjet 31, 35, 36, and 55 series Lockheed-Georgia 1329-25 series (731 Jetstar, Jetstar II) Raytheon Corporate Jets (formerly British Aerospace) DH/HS/BH-125 series; Sabreliner NA-265-65 (Sabreliner 65)

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Unsafe Condition (d) This AD results from a report of an uncontained failure of an LP 2nd stage turbine rotor disc that resulted in an in-flight engine shutdown. We are issuing this AD to prevent LP turbine rotor disk separation, which could result in an uncontained engine failure and damage to 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. Removal From Service of LP 1st and 2nd Stage Turbine Rotor Discs (f) For TFE731-2-2J, TFE731-2-2N, TFE731-2A-2A, and TFE731-3-1J engines, replace discs that are listed by SN in Tables 1 and 3 of SB No. TFE731-72-3682, dated November 26, 2002, within 100 hours time-in-service (TIS) after the effective date of this AD. (g) For TFE731-2 series engines except TFE731-2-2J, TFE731-2-2N, and TFE731-2A-2A engines, replace discs that are listed by SN in Tables 1 and 2 of SB No. TFE731-72-3682, dated November 26, 2002, at the next Major Periodic Inspection (MPI) or next access to the turbine discs after the effective date of this AD, but within 2,200 hours TIS since the last disc inspection, whichever occurs first. (h) For TFE731-3 series engines except TFE731-3-1J, replace discs that are listed by SN in Table 3 of SB No. TFE731-72-3682, dated November 26, 2002, at the next MPI or next access to the turbine discs after the effective date of this AD, but within 1,500 hours TIS since the last disc inspection, whichever occurs first. (i) Information on replacing affected discs can be found in Honeywell International Inc. SB No. TFE731-72-3682, dated November 26, 2002. (j) After the effective date of this AD, do not install any LP 1st and 2nd stage turbine rotor disc that has a SN listed in Table 1, 2, or 3 of SB No. TFE731-72-3682, dated November 26, 2002, and determined to be manufactured before April 1, 1991. Definitions (k) For the purposes of this AD, access to the turbine discs is the level of disassembly that has removed the tie-shaft nut. Alternative Methods of Compliance (l) The Manager, Los Angeles 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.

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Material Incorporated by Reference (m) You must use Honeywell International, Inc. Service Bulletin No. TFE731-72-3682, dated November 26, 2002, to perform the replacements required by this AD. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Honeywell Engines and Systems Technical Publications and Distribution, M/S 2101-201, P.O. Box 52170, Phoenix, AZ 85072-2170; telephone: (602) 365-2493 (General Aviation), (602) 365-5535 (Commercial Aviation), fax: (602) 365-5577 (General Aviation), (602) 365-2832 (Commercial Aviation) 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/code_of_federal_regulations/ibr_locations.html. Related Information (n) None. Issued in Burlington, Massachusetts, on June 13, 2005. Francis A. Favara, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 05-12080 Filed 6-21-05; 8:45 am] BILLING CODE 4910-13-P

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GROB-WERKE AIRWORTHINESS DIRECTIVE


2005-13-09 GROB-WERKE: Amendment 39-14146; Docket No. FAA-05-19473; Directorate Identifier 2004-CE-35-AD. When Does This AD Become Effective? (a) This AD becomes effective on July 26, 2005. What Other ADs Are Affected by This Action? (b) None. What Airplanes Are Affected by This AD? (c) This AD affects the following airplane models and serial numbers that are certificated in any category: Model G120A, all serial numbers beginning with 85001. What Is the Unsafe Condition Presented in This AD? (d) This AD is the result of a report that the main landing gear (MLG) may not extend because of contamination or misalignment of the assembly. The actions specified in this AD are intended to prevent the MLG from becoming jammed and not extending, which could result in loss of control of the airplane during landing. What Must I Do To Address This Problem? (e) To address this problem, you must do the following:

Actions Compliance Procedures (1) Remove MLG lock-up hook assembly and replace with the new MLG lock-up hook assembly.

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

Follow GROB–WERKE Service Bulletin No. MSB1121–060, dated March 7, 2005.

(2) Inspect the MLG for proper operation and adjust as needed.

Prior to further flight after the installation of the new MLG lock-up hook assembly.

Follow GROB–WERKE Service Bulletin No. MSB1121–060, dated March 7, 2005.

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May I Request an Alternative Method of Compliance? (f) You may request a different method of compliance or a different compliance time for this AD by following the procedures in 14 CFR 39.19. Unless FAA authorizes otherwise, send your request to your principal inspector. The principal inspector may add comments and will send your request to the Manager, Standards Office, FAA. For information on any already approved alternative methods of compliance, contact Karl Schletzbaum, Aerospace Engineer, ACE-112, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: 816-329-4146; facsimile: 816-329-4090. Is There Other Information That Relates to This Subject? (g) Luftfahrt-Bundesamt Airworthiness Directive D-2004-299R2, dated March 15, 2005; and GROB-WERKE Service Bulletin No. MSB1121-060, dated March 7, 2005, also address the subject of this AD. Does This AD Incorporate Any Material by Reference? (h) You must do the actions required by this AD following the instructions in GROB-WERKE Service Bulletin No. MSB1121-060, dated March 7, 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 GROB-WERKE, Burkart Grob e.K., Unternehmenbereich Luft-und Raumfahrt, Lettenbachstrasse 9, 86874 Tussenhausen-Mattsies, Germany; telephone: 011 49 8268 998 105; facsimile: 011 49 8268 998 200. To review copies of this service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html or call (202) 741-6030. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590-001 or on the Internet at http://dms.dot.gov. The docket number is FAA-05-19473; Directorate Identifier 2004-CE-35-AD. Issued in Kansas City, Missouri, on June 14, 2005. John R. Colomy, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-12152 Filed 6-21-05; 8:45 am] BILLING CODE 4910-13-P

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2005-13-10 Cessna Aircraft Company: Amendment 39-14147; Docket No. FAA-2005-20438; Directorate Identifier 2005-CE-03-AD. When Does This AD Become Effective? (a) This AD becomes effective on August 9, 2005. What Other ADs Are Affected by This Action? (b) None. What Airplanes Are Affected by This AD? (c) This AD affects the following airplane models and serial numbers that are certificated in any category: Model Serial Nos.

172R 17281186 through 17281232. 172S 172S9476 through 172S9689, and 172S9691 through 172S9770. 182T 18281242 through 18281502, 18281506, and 18281507. T182T T18208212 through T18208357. 206H 20608195 through 20608223, 20608225, and 20608226. T206H T20608410 through T20608475, T20608477 through T20608501, T20608503, and

T20608506. What Is the Unsafe Condition Presented in This AD? (d) This AD is the result of several reports of circuit breakers that are not the correct 40-amp circuit breaker installed in the MC01-3A I.C. 9 or MC01-3A I.C. 10 main electrical power junction box. The actions specified in this AD are intended to replace any incorrect circuit breaker installed in the MC01-3A main electrical power junction box, which could result in premature tripping of the power junction box main feeder circuit breakers and could lead to partial or complete loss of all electrical power on the airplane. This condition could lead to the loss of all navigation and communication equipment and lighting in the cockpit. What Must I Do To Address This Problem? (e) To address this problem, you must do the following:

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Actions Compliance Procedures (1) Inspect any MC01–3A I.C. 9 (part number (P/N) S3100–297) or MC01–3A I.C. 10 (P/N S3100–344) main electrical power junction box for any incorrect amperage (amp) circuit beaker installed in place of the required 40-amp circuit breakers.

Within the next 30 days after August 9, 2005 (the effective dated date of this AD), unless already done.

Follow Cessna Service Bulletin No. SB05–24–01, January 31, 2005.

(2) Replace any incorrect amp circuit breaker with the required 40-amp circuit breaker.

Before further flight after the inspection required by paragraph (e)(1) of this AD.

Follow Cessna Service Bulletin No. SB05–24–01, dated January 31, 2005.

(3) Only install in any MC01–3A I.C. 9 (P/N S3100–297) or MC01–3A I.C. 10 (P/N S3100–344) main electrical power junction box the required 40-amp circuit breakers.

As of August 9, 2005 (the effective date of this AD).

Not Applicable.

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 Jose Flores, Aerospace Engineer, Wichita ACO, FAA, 1801 Airport Road, Wichita, Kansas 67209; telephone: (316) 946-4133; facsimile: (316) 946-4107. May I Obtain a Special Flight Permit for the Initial Inspection Requirement of This AD? (g) Yes, special flight permits are allowed per 14 CFR 39.19 provided airplane operations are limited to Day and/or visual flight rules (VFR) flight. Does This AD Incorporate Any Material by Reference? (h) You must do the actions required by this AD following the instructions in Cessna Service Bulletin No. SB05-24-01, dated January 31, 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 Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita, Kansas 67277; telephone: (316) 517-5800; facsimile: (316) 942-9006. 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-2005-20438; Directorate Identifier 2005-CE-03-AD. Issued in Kansas City, Missouri, on June 14, 2005. John R. Colomy, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-12175 Filed 6-21-05; 8:45 am] BILLING CODE 4910-13-P

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GENERAL ELECTRIC COMPANY AIRWORTHINESS DIRECTIVE


2005-13-11 General Electric Company: Amendment 39-14148. Docket No. FAA-2005-21586; Directorate Identifier 2005-NE-16-AD. Effective Date (a) This airworthiness directive (AD) becomes effective July 6, 2005. Affected ADs (b) None. Applicability (c) This AD applies to General Electric Company (GE) CT64-820-4 turboprop engines with stage 1 turbine disk and shaft, part number (P/N) 6004T47P03 or 4921T10P02 installed. These engines are installed on, but not limited to, DeHavilland DHC-5D Buffalo airplanes. Unsafe Condition (d) This AD results from the discovery by the manufacturer of low-cycle fatigue (LCF) cracks found in stage 1 turbine disk and shafts, P/Ns 6004T47P03 and 4921T10P02. We are issuing this AD to prevent uncontained failure of the stage 1 turbine disk and shaft, resulting in damage to 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. Engine Serial Numbers (SNs) 268537, 268565, and 268637 (f) For engine serial number (SN) 268537, remove the stage 1 turbine disk and shaft from service at or before accumulating 1,700 cycles-since-new (CSN), or by December 31, 2005, whichever occurs first. (g) For engine SN 268565, remove the stage 1 turbine disk and shaft from service at or before accumulating 1,585 CSN, or by December 31, 2005, whichever occurs first.

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(h) For engine SN 268637, remove the stage 1 turbine disk and shaft from service at or before accumulating 1,345 CSN, or by December 31, 2005, whichever occurs first. All Other Engines (i) For all other engines that have accumulated 590 CSN or more on the stage 1 turbine disk and shaft on the effective date of this AD, remove stage 1 turbine disk and shaft from service at or before accumulating an additional 10 cycles-in-service, at or before accumulating the service life limit of 1,700 CSN, or by December 31, 2005, whichever occurs first. (j) For all other engines that have accumulated fewer than 590 CSN on the stage 1 turbine disk and shaft on the effective date of this AD, remove stage 1 turbine disk and shaft from service at the next piece-part-exposure, or before accumulating 600 CSN, or by December 31, 2005, whichever occurs first. (k) After the effective date of this AD, do not install any stage 1 turbine disk and shaft, P/N 6004T47P03 or 4921T10P02, into any engine. (l) After the effective date of this AD, do not install any engine with stage 1 turbine disk and shaft, P/N 6004T47P03 or 4921T10P02, into any airplane. Definition (m) For the purpose of this AD, piece-part exposure is defined as the stage 1 disk and shaft is completely disassembled using the disassembly instructions of the manufacturer's engine manual, or other FAA-approved engine manual. Alternative Methods of Compliance (n) 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 (o) Information on determining engine usage in cycles for comparison to CT64 service life limits can be found in GE Service Bulletin CEB No. 93, Revision 2, dated May 30, 1984. GE Alert Service Bulletin No. CT64 S/B 72-A0113, Revision 1, dated May 16, 2005, also pertains to the subject of this AD. Material Incorporated by Reference (p) None. Issued in Burlington, Massachusetts, on June 14, 2005. Robert Ganley, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 05-12173 Filed 6-20-05; 8:45 am] BILLING CODE 4910-13-P

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AIR TRACTOR, INC. AIRWORTHINESS DIRECTIVE


2005-13-12 Air Tractor, Inc.: Amendment 39-14149; Docket No. FAA-2004-19837; Directorate Identifier 2004-CE-43-AD. When Does This AD Become Effective? (a) This AD becomes effective on August 5, 2005. What Other ADs Are Affected by This Action? (b) None. What Airplanes Are Affected by This AD? (c) This AD affects the following airplane models and serial numbers that are certificated in any category:

Models Serial Nos. AT–300, AT–301, AT–302, AT–400, and AT–400A.

All serial numbers.

AT–401/AT–402 All through 401–0700. AT–602 All through 602–0695 that have any 7/16-inch eyebolt (part number

(P/N) AN47–22A) installed; all beginning with 602–0703; and all that have any 9/16-inch eyebolt (P/N 30774–1) installed.

AT–802 and AT–802A All through 802A–0188 that have any 7/16-inch eyebolt (P/N AN47–30A) installed; all beginning with 802A–0189; and all that have any 9/16-inch eyebolt (P/N 30775–1) installed.

What Is the Unsafe Condition Presented in This AD? (d) This AD is the result of reports of failures of the subject eyebolt. The actions specified in this AD are intended to detect, correct, and prevent future fatigue failure in any eyebolt that attaches the front and rear spar of the horizontal stabilizer to the respective stabilizer strut. Failure of the eyebolt could lead to an abrupt change or complete loss of pitch control and/or the airplane departing from controlled flight. What Must I Do To Address This Problem? (e) To address this problem, you must do the following:

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Actions Compliance Procedures (1) Tighten the four eyebolts that attach the front and rear spar of the horizontal stabilizer to the respective stabilizer strut using the torque values referenced in Snow Engineering Co. Service Letter #129, revised October 21, 2004.

Within the next 100 hours time-in-service (TIS) or 12 calendar months after August 5, 2005 (the effective date of this AD), whichever occurs first, unless already done. Repetitively tighten thereafter at every 12 calendar months after the date of the initial tightening to the specified torque.

Follow Snow Engineering Co. Service Letter #129, Issued September 26, 1994, Revised October 21, 2004.

(2) Repetitively replace any eyebolts that attach the front and rear spar of the horizontal sta-bilizer to the respective stabilizer strut.

Initially replace upon accumulating the appli-cable number of hours TIS referenced in Snow Engineering Co. Service Letter #129, revised October 21, 2004, or within 50 hours TIS after August 5, 2005 (the effec-tive date of this AD), whichever occurs later. Replace repetitively thereafter at the intervals referenced in Snow Engineering Co. Service Letter #129, revised October 21, 2004.

Follow Snow Engineering Co. Service Letter #129, Issued September 26, 1994, Revised October 21, 2004.

(3) For Model AT–602 airplanes through serial number 602–0695 and AT–802, and 802A airplanes through serial number 802A–0188: As an alternative in order to use the in-creased replacement compliance times in paragraph (e)(2) of this AD, you may replace the steel brace assembly inside the stabilizer with a new steel brace assembly with larger bushings, and (i) For the Model AT–602 airplane: replace any 7/16-inch eyebolt with the 9/16-inch eyebolt (P/N 30774–1) (ii) For the Model AT–802 and AT–802A air-planes: replace any 7/16-inch eyebolt with the 9/16-inch eyebolt (P/N 30775–1)

At any time after August 5, 2005 (the effective of this AD). Use the applicable time in Snow Engineering Co. Service Letter #129A, dated August 7, 2004. The repet-itive replacement of paragraph (e)(2) of this AD is still required.

Follow Snow Engineering Co. Service Letter #129A, Dated August 7, 2004.

(4) Do not install any 5/16-inch eyebolt (P/N AN44–17A or AN44–21A), 7/16-inch eyebolt (AN47–22A or AN47–30A), or 9/16-inch eye-bolt (P/N 30774–1 or 30775–1) that exceeds the corresponding cumulative hours TIS specified in paragraphs (e)(2) or (e)(3) of this AD.

As of August 5, 2005 (the effective date of this AD).

Not Applicable.

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, Fort Worth Airplane Certification Office (ACO), FAA. For information on any already

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approved alternative methods of compliance, contact Andrew D. McAnaul, Aerospace Engineer, FAA, Fort Worth ACO, ASW-150, 2601 Meacham Boulevard, Fort Worth, Texas 76193-0150. Current duty station: San Antonio Manufacturing Inspection District Office (MIDO-43), 10100 Reunion Place, Suite 650, San Antonio, Texas 78216; telephone: (210) 308-3365; facsimile: (210) 308-3370. Does This AD Incorporate Any Material by Reference? (g) You must do the actions required by this AD following the instructions in Snow Engineering Co. Service Letter 129, Issued September 26, 1994, Revised October 21, 2004, and Snow Engineering Co. Service Letter 129A, dated August 7, 2004. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of this service information, contact Air Tractor, Incorporated, P.O. Box 485, Olney, Texas 76374. 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-2004-19837; Directorate Identifier 2004-CE-43-AD. Issued in Kansas City, Missouri, on June 14, 2005. John R. Colomy, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-12177 Filed 6-21-05; 8:45 am] BILLING CODE 4910-13-P

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SIKORSKY AIRCRAFT CORPORATION AIRWORTHINESS DIRECTIVE


2005-13-13 Sikorsky Aircraft Corporation: Amendment 39-14150. Docket No. FAA-2005-21588; Directorate Identifier 2005-SW-24-AD. Applicability

Model S-92A helicopters, with a gear box output housing, part number (P/N) 92358-06109-043, installed, certificated in any category. Compliance

Required as indicated, unless accomplished previously. To prevent fatigue failure of the tail gear box output housing, loss of tail rotor drive, and subsequent loss of control of the helicopter, do the following: (a) Before further flight, replace each tail gear box output housing, P/N 92358-06109-043, with 600 or more hours time-in-service (TIS) with an airworthy tail gear box housing with less than 600 hours TIS. Note: Sikorsky Maintenance Manual SA S92A-AWL-000, Airworthiness Limitations and Inspection Requirements, Chapter 4, dated March 3, 2005, contains the limitation for the tail gear box output housing. (b) This AD revises the Airworthiness Limitations section of the maintenance manual by reducing the life limit of the tail gear box output housing from 4500 hours TIS to 600 hours TIS. (c) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Boston Aircraft Certification Office, FAA, for information about previously approved alternative methods of compliance. (d) This amendment becomes effective on July 8, 2005. Issued in Fort Worth, Texas, on June 10, 2005. S. Frances Cox, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 05-12417 Filed 6-22-05; 8:45 am] BILLING CODE 4910-13-P

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THE NEW PIPER AIRCRAFT, INC. AIRWORTHINESS DIRECTIVE


2005-13-16 The New Piper Aircraft, Inc.: Amendment 39-14153; Docket No. FAA-2004-19960; Directorate Identifier 2004-CE-47-AD. When Does This AD Become Effective? (a) This AD becomes effective on August 8, 2005. What Other ADs Are Affected by This Action? (b) This AD supersedes AD 93-24-14, Amendment 39-8762. What Airplanes Are Affected by This AD? (c) This AD affects Models PA-34-200, PA-34-200T, and PA-34-220T airplanes, all serial numbers, that are certificated in any category. What Is the Unsafe Condition Presented in This AD? (d) This AD is the result of service difficulty reports related to the collapse or involuntary retraction of the nose landing gear (NLG). The actions specified in this AD are intended to detect, correct, and prevent failure in certain components of the NLG, lack of cleanliness of the NLG due to inadequate maintenance, or lack of lubricant in the NLG or NLG components. This failure of the NLG could lead to loss of control of the airplane during take-off, landing, or taxiing operations. What Must I Do To Address This Problem? (e) To address this problem, you must do the following:

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Actions Compliance Procedures (1) Replace the bolt and stack up that connects the upper drag link to the nose gear trunnion with new parts (or FAA-approved equivalent part numbers (P/N)) of the following: (i) Piper P/N 400 274 (AN7–35) bolt; (ii) Piper P/N 407 591 (AN960–716L)

washer, as applicable; (iii) Piper P/N 407 568 (AN960–716); (iv) Piper P/N 404 396 (AN320–7) nut; and (v) Piper P/N 424 085 cotter pin.

Within the next 100 hours time-in-service (TIS) after January 28, 1994 (the effective date of AD 93–24–14), unless already done within the last 400 hours TIS before January 28, 1994 (compliance with AD 93–24–14). Repetitively replace thereafter at intervals not to exceed 500 hours TIS. Continue to repetitively replace until the actions in paragraphs (e)(2) and (e)(3) of this AD begin.

Follow Figure 1 of this AD.

(2) Do the inspections, replacements, and other corrective actions specified in Table 1 ‘‘Specified Maintenance’’of Piper Service Bulletin No. 1123A, dated November 30, 2004.

Within the next 100 hours TIS after August 8, 2005 (the effective date of this AD), unless already done. Repetitively inspect thereafter at the intervals referenced in the Inspection Time column of the INSTRUCTIONS paragraph in Piper Service Bulletin No. 1123A, dated November 30, 2004.

Follow The New Piper Aircraft, Inc. Service Bulletin No. 1123A, dated November 30, 2004.

(3) Do any necessary corrective actions as a result of the actions specified in Table 1 ‘‘Specified Maintenance’’of Piper Service Bulletin No. 1123A, dated November 30, 2004.

Before further flight after any action required by paragraph (e)(2) of this AD.

Follow The New Piper Aircraft, Inc. Service Bulletin No. 1123A, dated November 30, 2004.

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Note 1: Paragraph 2. Modified Components of the INSTRUCTIONS section of The New Piper Aircraft, Inc. Service Bulletin No. 1123A, dated November 30, 2004, specifies modified parts that you may install for improved service life. Note 2: The Actions column of the table in paragraph (e) of this AD may include one or a combination of these actions: replacement, repair, adjustment, alignment, cleaning, lubricating, or other action. 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, Atlanta Aircraft Certification Office (ACO), FAA. For information on any already approved alternative methods of compliance, contact Hassan Amini, Aerospace Engineer, FAA, Atlanta ACO, One Crown Center, 1895 Phoenix Boulevard, Suite 450, Atlanta, Georgia 30349; telephone: (770) 703-6080; facsimile: (770) 703-6097. Does This AD Incorporate Any Material by Reference? (g) You must do the actions required by this AD following the instructions in The New Piper Aircraft, Inc. Service Bulletin No. 1123A, dated November 30, 2004. The Director of the Federal Register approved the incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get a copy of this service information, contact The New Piper Aircraft, Inc., 2926 Piper Drive, Vero Beach, Florida 32960. 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-2004-19960; Directorate Identifier 2004-CE-47-AD. Issued in Kansas City, Missouri, on June 15, 2005. John R. Colomy, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-12176 Filed 6-21-05; 8:45 am] BILLING CODE 4910-13-P

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AGUSTA. S.P.A. AIRWORTHINESS DIRECTIVE


2005-13-17 Agusta. S.p.A.: Amendment 39-14154. Docket No. FAA-2005-21589; Directorate Identifier 2004-SW-44-AD. Applicability

Model AB412 Series helicopters, with a tail rotor blade (blade), part number (P/N) 212-010-750-All, having a serial number (S/N) with a prefix of ''A'' or ''A-FS'' and number 11530 through 13618, except numbers 13595 through 13602, installed, certificated in any category. Compliance

Within 100 hours time-in-service, unless accomplished previously. To prevent loss of the forward tip weight retention block (tip block) or aft tip closure (tip closure), loss of a blade, and subsequent loss of control of the helicopter, accomplish the following: (a) Inspect the tip block and tip closure for voids. Before further flight, remove any blade with a void in excess of that allowed by the Component Repair and Overhaul Manual limitations. (b) Inspect the tip block attachment countersink screws in four locations to determine if the head of each countersunk screw is flush with the surface of the abrasion strip and the skin. The location of these four screws is depicted on Figure 2 of Agusta Bollettino Tecnico No. 412-88, Revision A, dated August 17, 2004 (BT 412-88, Revision A). If any of these screws are set below the surface of the abrasion strip or are covered with filler material, before further flight, install shear pins by following the Accomplishment Instructions, Part A, Tip Block: Shear Pin Installation, paragraphs 1 through 3, of BT 412-88, Revision A. (c) Install the tip closure rivets on all affected blades by following the Accomplishment Instructions, Part B, Aft Tip Closure: Rivet Installation, paragraphs 1 through 6, of BT 412-88, Revision A. (d) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Safety Management Group, FAA, for information about previously approved alternative methods of compliance. (e) The inspections and modification must be done by following the specified portions of Agusta Bollettino Tecnico No. 412-88, Revision A, dated August 17, 2004. The Director of the Federal Register approved this incorporation by reference in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Agusta, 21017 Cascina Costa di Samarate (VA) Italy, Via Giovanni

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Agusta 520, telephone 39 (0331) 229111, fax 39 (0331) 229605-222595. Copies may be inspected 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. (f) This amendment becomes effective on July 11, 2005. Note: The subject of this AD is addressed in Ente Nazionale per l'Aviazione Civile (Italy) AD 2004-351, dated September 3, 2004. Issued in Fort Worth, Texas, on June 8, 2005. S. Frances Cox, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 05-12419 Filed 6-23-05; 8:45 am] BILLING CODE 4910-13-P

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EUROCOPTER FRANCE AIRWORTHINESS DIRECTIVE

SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2005-13-23 Eurocopter France: Amendment 39-14160. Docket No. FAA-2005-20512; Directorate Identifier 2004-SW-35-AD. Supersedes AD 2003-18-03, Amendment 39-13294, Docket No. 2002-SW-53-AD. Applicability

Model EC 155B, EC155B1, SA-365N, SA-365N1, AS-365N2, and AS 365 N3 helicopters, with emergency flotation gear installed, certificated in any category. Compliance

Required as indicated, unless accomplished previously. To prevent failure of a hydraulic brake hose (hose), resulting in failure of hydraulic pressure to the brakes on the affected landing gear wheel and subsequent loss of control of the helicopter during a run-on landing, accomplish the following: (a) Within 10 hours time-in-service (TIS), inspect the hose for crazing, pinching, distortion, or leaks as illustrated in Area A of Figure 1 of Eurocopter Alert Service Bulletin No. 32.00.09, dated October 27, 2003 (ASB No. 32.00.09), for Model SA-365N and N1, AS-365N2, and AS 365 N3 helicopters, and Eurocopter Alert Service Bulletin No. 32A004, Revision 1, dated June 16, 2004 (ASB No. 32A004R1), for Model EC 155B and EC155B1 helicopters. (b) If crazing, pinching, distortion, or leaks exist, replace the hose with an airworthy hose before further flight. (c) At the next 100-hour TIS inspection, inspect the hose and the emergency flotation gear pipe to ensure adequate clearance and adjust the landing gear leg, if necessary, in accordance with the Operational Procedure, paragraph 2.B.2., of ASB No. 32.00.09 or ASB No. 32A004R1, as applicable. (d) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Safety Management Group, Rotorcraft Directorate, FAA, for information about previously approved alternative methods of compliance. (e) The inspections and adjustments shall be done in accordance with the specified portions of Eurocopter Alert Service Bulletin No. 32.00.09, dated October 27, 2003, or Eurocopter Alert Service Bulletin No. 32A004, Revision 1, dated June 16, 2004, as applicable. The Director of the Federal Register approved this incorporation by reference in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053-4005, telephone (972) 641-3460, fax (972) 641-3527. Copies may be inspected

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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. (f) This amendment becomes effective on July 29, 2005. Note: The subject of this AD is addressed in Direction Générale De L'Aviation Civile (France) AD No. F-2002-474-058 R1, dated March 3, 2004 and AD No. F-2004-099, dated July 7, 2004. Issued in Fort Worth, Texas, on June 10, 2005. S. Frances Cox, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 05-12418 Filed 6-23-05; 8:45 am] BILLING CODE 4910-13-P

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TURBOMECA S.A. AIRWORTHINESS DIRECTIVE


2005-13-25 Turbomeca S.A.: Amendment 39-14162. Docket No. FAA-2005-21624; Directorate Identifier 2005-NE-17-AD. Effective Date (a) This airworthiness directive (AD) becomes effective July 11, 2005. Affected ADs (b) None. Applicability (c) This AD applies to Turbomeca S.A. Arriel 2B turboshaft engines with Modification TU62A incorporated. These engines are installed on, but not limited to, Eurocopter AS350B3 helicopters. Unsafe Condition (d) This AD results from several reports of the hydromechanical unit (HMU) acceleration controller axle sticking. We are issuing this AD to prevent loss of control of engine fuel flow in the manual control mode or mixed control mode, leading to engine overspeed and in-flight engine shutdown, or uncommanded in-flight engine shutdown. 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) Within 20 operating hours after the effective date of this AD, inspect, clean, lubricate, and check for proper operation of the HMU acceleration controller axle. Use paragraph 2 of Instructions to be Incorporated of Turbomeca Alert Mandatory Service Bulletin No. A292 73 2814, Update No. 1, dated January 11, 2005, to do these actions. (g) Thereafter, repeat the actions specified in paragraph (f) of this AD within every 210 operating hours.

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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 directive F-2004-139, dated August 18, 2004, also addresses the subject of this AD. Material Incorporated by Reference (j) You must use Turbomeca Alert Mandatory Service Bulletin (ASB) No. A292 73 2814, Update No. 1, dated January 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 Turbomeca S.A., 40220 Tarnos, France; telephone 33 05 59 74 40 00, fax 33 05 59 74 45 15, for a copy of this service information. You may review copies at the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room 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 June 16, 2005. Jay J. Pardee, Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 05-12415 Filed 6-23-05; 8:45 am] BILLING CODE 4910-13-P

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