FEDERAL AVIATION ADMINISTRATION AIRWORTHINESS DIRECTIVES SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS BIWEEKLY 2004-25 This electronic copy may be printed and used in lieu of the FAA biweekly paper copy.
U.S. Department of Transportation Federal Aviation Administration Regulatory Support Division Delegation and Airworthiness Programs Branch, AIR-140 P. O. Box 26460 Oklahoma City, OK 73125-0460 FAX 405-954-4104
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SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS AD No.
Information
Manufacturer
Applicability
Info: E - Emergency; COR - Correction; S - Supersedes; R - Revision; - See AD for additional information; Biweekly 2004-01 2003-23-05 2003-24-13 2003-26-04 2003-26-06 2003-26-14 2004-01-09 2004-01-10 2004-01-14 2004-01-51
COR COR
E
Titeflex Corportation Cessna Aircraft Company Agusta S.p.A. Anjou Aeronautique Kiddie Aerospace Eurocopter France Eurocopter Deutschland Eurocopter France Eurocopter France
Appliance: Titeflex hoses 172R, 172S, 182S, 182T, T182T, 206H, and T206H Rotorcraft: A109E Appliance: Safety belts and restraint systems Appliance: Hand-held halon fire extinguishers Rotorcraft: AS355E, F, F1, F2, and N Rotorcraft: MBB-BK-117 A-1, A-3, A-4, B-1, B-2, and C-1 Rotorcraft: EC130B4 Rotorcraft: AS355E, F, F1, F2, and N
Cessna Aircraft Company Raytheon Aircraft Company
441 and F406 1900, 1900C, 1900 (C-12J), and 1900D
Agusta S.p.A. Air Cruisers Company
Rotorcraft: A109E Appliance: Emergency Evacuation Slide/Raft Systems
Learjet Eurocopter France Pacific Aerospace Corporation, Ltd. The New Piper Aircraft, Inc. Pilatus Aircraft LTD.
31, 31A, 35, 35A (C-21A), 36 and 36A Rotorcraft: AS332C, L, and L1 FU24-954 and FU24A-954
45 (YT-34), A45 (T-34A, B-45), and D45 (T-34B) MU-2B, MU-2B-10, MU-2B-15, MU-2B-20, MU-2B-25, MU-2B26, MU-2B-26A, MU-2B-30, MU-2B-35, MU-2B-36, MU-2B36A, MU-2B-40, and MU-2B-60 Rotorcraft: AS355E, F, F1, F2, and N Engine: CT58-100-2, CT58-140-1, -140-2, and T58-GE-1, -3, -5, 8E, -8F, -10, -100, and -402 Turboshaft Engine: JT15D-1, -1A, and -1B Turbofan Otter DHC-3 N22B, N22S, and N24A
Biweekly 2004-02 2003-09-09 R1 2004-01-13
R S 97-22-16
Biweekly 2004-03 2004-02-03 2004-03-01
S 2003-03-11
Biweekly 2004-04 2004-03-08 2004-03-27 2004-03-29 2004-03-32 2004-04-01
COR
S 2002-01-09
PA-46-500TP PC-7, PC-12, and PC-12/45
Biweekly 2004-05 2001-13-18 R1 2003-22-07 R1
R1, COR R
Raytheon Aircraft Company Mitsubishi Heavy Industries, Ltd
2004-01-51 2004-04-06
FR
Eurocopter France General Electric Company
2004-04-09 2004-05-01 2004-05-02
Pratt & Whitney Canada Bombardier Inc. Aerospace Technologies of Australia Pty Ltd.
Biweekly 2004-06 2004-03-01
Air Cruisers Company
Appliance: Emergency Evacuation Slide/Raft System
2004-05-23
COR, S 2003-0311 S 89-21-01
Eurocopter France
2004-05-24
S 2002-23-06
Lycoming Engines
2004-05-28 2004-05-29 2004-06-51
E
2004-06-52
E
Eurocopter France Eurocopter France Boeing Defense and Space Group Robinson Helicopter Company
Rotorcraft: AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, and AS355N Engine: AEIO-540, IO-540, LTIO-540, O-540, and TIO-540 Series Reciprocating Rotorcraft: AS 365 N3 Rotorcraft: EC 155B Rotorcraft: 234
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Rotorcraft: R22, R22 Alpha, R22 Beta, and R22 Mariner
SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS AD No.
Information
Manufacturer
Applicability
Info: E - Emergency; COR - Correction; S - Supersedes; R - Revision; - See AD for additional information; Biweekly 2004-07 2004-06-04 2004-06-05 2004-06-09 2004-06-10
Sikorsky Aircraft Corporation Pilatus Aircraft Ltd. The Lancair Company Aerospace Technologies of Australia Pty Ltd.
Rotorcraft: S-76 A, B, and C PC-12 and PC-12/45 LC40-550FG and LC42-550FG N22B, N22S, and N24A
Eurocopter France
Rotorcraft: AS332C, L, and L1
Bombardier Inc. Engine Components Incorporated (ECi) Schempp-Hirth Flugzeugbau Gmbh Burkhardt Grob Luft-und Raumfahrt Gmbh Co & KG Glasflugel Goodrich Avionics Systems, Inc. NARCO Avionics Inc. Cessna Aircraft Company HPH s. r. o. Cessna Airplane Company
Otter DHC-3 Engine: Teledyne TSIO-520-NB, -VB, -WB, 520 and 550 Series Reciprocating Glider: Discus-2a, Discus-2b, Ventus-2a, and Ventus-2b
Biweekly 2004-08 2004-03-27
COR
Biweekly 2004-09 2004-05-01 R1 2004-08-10
R
2004-08-12 2004-08-13 2004-08-14 2004-08-15 2004-08-16 2004-08-17 2004-09-03 2004-09-05
S 2003-13-08
Glider: G103 Twin ASTIR, G103 Twin II, G103 Twin III ACRO, and G103 C Twin III SL Glider: Mosquito and Club Libelle 205 Appliance: Terrain Awareness Warning System (TAWS) Appliance: AT150 Transponders 208 amd 208B Glider: Glasflügel 304CZ, 304CZ-17, and 304C 500, 501, 550, and 551
Biweekly 2004-10 2004-08-17 2004-09-02 2004-09-07 2004-09-29
COR
2004-09-30
Cessna Aircraft Company Glasflugel-Ing. E. Hanle Raytheon Aircraft Company Honeywell International Inc.
Raytheon Aircraft Company
208 and 208B Glider: Kestrel 1900, 1900C, 1900C (C12J), and 1900D Engine: TPE331-10-501C, -10-511C, -10-501K, -10-511K, -10501M, -10-511M, -10AV-511B, -10AV-511M, -10GP-511D, 10GT-511D, -10N-511S, -10N-512S, -10N-513S, -10N-514S, 10N-515S, -10N-531S, -10N-532S, -10N-533S, -10N-534S, -10N535S, -10P-511D, -10R-501C, -10R-502C, -10R-511C, -10R512C, -10R-513C, -10T-511D, -10T-511K, -10T-511M, -10T512K, -10T-513K, -10T-515K, -10T-516K, -10T-517K, -10U501G, -10U-502G, -10U-511G, -10U-512G, -10U-503G, -10U513G, -10UA-511G, -10UF-501H, -10UF-511H, -10UF-512H,10UF-513H, -10UF-514H, -10UF-515H, -10UF-516H, -10UG513H, -10UG-514H, -10UG-515H, -10UG-516H, -10UGR-513H, -10UGR-514H, -10UGR-516H, -10UR-513H, -10UR-516H, -11U601G, -11U-602G, -11U-611G, and -11U-612G Turboprop 1900C
Goodrich Avionics Systems, Inc.
Appliance: Terrain Awareness Warning System (TAWS)
Bell Helicopter Textron Canada Alexander Schleicher GmbH & Co. Segelflugzeugbau Lycoming Engines Garmin International Inc. Eagle Aircraft (Malaysia) SDN. BHD
Rotorcraft: 407 Glider: ASH 25M
Biweekly 2004-11 2004-08-15 2004-10-07 2004-10-08 2004-10-14 2004-10-15 2004-11-04
COR S 2003-13-08 S 2002-06-52 S 91-14-22
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Engine: Direct-Drive Reciprocating Engines Appliance: Mode S transponders Eagle 150B
SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS AD No.
Information
Manufacturer
Applicability
Info: E - Emergency; COR - Correction; S - Supersedes; R - Revision; - See AD for additional information; Biweekly 2004-12 2004-06-51
FR
2004-11-05 2004-11-06 2004-11-10 2004-11-12
Boeing Defense And Space Group Eurocopter France Agusta S.p.A Przedsiebiorstwo Doswiadczalno-Produkcyjne Szybownictwa ''PZL-Bielsko'' Alexander Schleicher Gmbh & Co.
Rotorcraft: 234
Agusta S.p.A. Burkhart Grob Luft-Und Raumfahrt GmbH & Co KG Cessna Airplane Company Eurocopter France Pilatus Aircraft Ltd. Dowty Aerospace Propellers
Rotorcraft: A109C, A109E, and A109K2 Glider: G103 Twin Astir, G103A Twin II Acro, G103C Twin III Acro 500, 501, 550, and 551 Rotorcraft: EC 155 B and B1 PC-12 and PC-12/45 Propeller: R321/4-82-F/8, R324/4-82-F/9, R333/4-82-F/12, and R334/4-82-F/13 Rotorcraft: MBB-BK 117 A-1, A-3, A-4, B-1, B-2, and C-1
Rotorcraft: EC 130 B4 and AS 350 B3 Rotorcraft: A109E Glider: SZD-50-3 ''Puchacz'' Glider: ASW 27
Biweekly 2004-13 2001-24-07 R1 2003-19-14 R1
R R
2004-09-05 2004-12-06 2004-12-11 2004-13-01
COR S 2002-01-28
2004-13-05
Eurocopter Deutschland
Biweekly 2004-14 95-26-05 R1 2003-13-15 R1 2004-10-14 2004-13-20 2004-13-26 2004-14-02 2004-14-12
Res. R COR, S 91-14-22
Robinson Helicopter Company Schweizer Aircraft Corporation Lycoming Engines Garmin AT Kaman Aerospace Corporation Rolls-Royce Corporation New Piper Aircraft, Inc.
Rotorcraft: R44 Rotorcraft: 269A, 269A-1, 269B, 269C, and TH-55A Engine: Direct-Drive Reciprocating Engines Appliance: Global positioning system (GPS) Rotorcraft: K-1200 Engine: 250-C28, -C28B and, -C28C Turboshaft PA-28-161, PA-28-181, PA-28R-201, PA-32R-301 (HP), PA-32R301T, PA-32R-301T, PA-32-301FT, PA-32-301XTC, PA-34220T, PA-44-180, PA-46-350P, and PA-46-500TP
The Cessna Aircraft Company
525
2004-14-21 2004-14-22
Stemme GmbH & Co. Pratt & Whitney Canada
2004-15-01
Raytheon Aircraft Company
Glider: S10-VT, S10-V, S10 Engine: PW206B, PW206C, PW206E, PW207D, and PW207E Turboshaft 390
Biweekly 2004-15 2004-14-20
COR S 2003-21-07
Biweekly 2004-16 2004-15-11 2004-15-15 2004-15-18 2004-15-19 2004-15-21 2004-15-22 2004-16-07
S 2002-19-10
Eurocopter France Air Tractor, Inc. Cessna Aircraft Company The New Piper Aircraft, Inc Agusta S.p.A. Sikorsky Aircraft Corp. General Electric Company
5
Rotorcraft: EC155B and B1 AT-401, AT-401B, AT-402, AT-402A, AT-402B, AT-501, AT-502, AT-502A, AT-502B, AT-503A, AT-602, AT-802 and AT-802A 172R, 172S, 182S, 182T, T182T, 206H, T206H PA-46-500TP Rotorcraft: A109K2 Rotorcraft: S-61L, S-61N, S-61-NM, and S-61R Engine: CT7-2D1 Turboshaft
SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS AD No.
Information
Manufacturer
Applicability
Info: E - Emergency; COR - Correction; S - Supersedes; R - Revision; - See AD for additional information; Biweekly 2004-17 2004-14-12 2004-16-08 2004-16-14
COR
2004-16-15 2004-17-01 2004-17-02 2004-17-03
The New Piper Aircraft, Inc. MD Helicopters Thales Avionics
Cessna Aircraft Company
See AD Rotorcraft: MD900 Appliance: Traffic advisory/resolution advisory (TA/RA) vertical speed indicator-traffic alert and collision avoidance system (VSITCAS) indicators Rotorcraft: AS-365N2, AS 365 N3, EC 155B, EC155B1, SA365N, N1 and SA-366G1 208 and 208B
Raytheon Aircraft Company Pratt & Whitney Canada
See AD Engine: PW206A and PW206E
Grob-Werke Gmbh & Co KG
Sailplane: G102 CLUB ASTIR III, G102 CLUB ASTIR IIIb, and G102 STANDARD ASTIR III Propeller: HO-V343 and HO-V343K
Eurocopter France S 2002-22-17, 2003-21-04 S 2003-16-10
Biweekly 2004-18 2004-17-04
S 2001-26-25
2004-18-01
Hoffmann Propeller GmbH & Co KG
Biweekly 2004-19 2004-18-12 2004-19-01
S 86-26-04
DG Flugzeugbau GmbH Cessna Aircraft Company
Glider: DG-500MB See AD
Cessna Aircraft Company
208, 208B
Robinson Helicopter Company Pratt & Whitney Canada
Rotorcraft: R22-Series Engine: PT6B-36A and PT6B-36B Turboshaft
Cessna Aircraft Company
See AD
Bell Helicopter Textron Canada MD Helicopters, Inc. Valentin GmbH & Co. PZL-Bielsko Becker Flugfunkwerk GmbH
222, 222B, 222U, 230 Rotorcraft: 500N and 600N Glider: Taifun 17E Glider: SZD-50-3 ''Puchacz'' Appliance: AR 4201 VHF AM Transceivers
Kelly Aerospace Power Systems deHavilland Inc. and Bombardier Inc. Cessna Aircraft Company MD Helicopters, Inc.
Appliance: B-Series Combustion Heaters DHC-2 Mk. I, DHC-2 Mk. II, (Otter) DHC-3
Eurocopter Deutschland GmbH Bell Helicopter Textron Canada Grob-Werke Raytheon Aircraft Company Pilatus Aircraft Ltd. Raytheon Aircraft Company
Rotorcraft: EC135 P1, P2, T1, and T2 Rotorcraft: 206L-1 and 206L-3 G120A B100 PC-7 See AD
Biweekly 2004-20 2004-17-01 2004-19-09 2004-20-04
COR S 2002-22-17, 2003-21-04 S 2004-06-52
Biweekly 2004-21 2004-19-01
COR S 86-26-04
2004-20-07 2004-20-08 2004-20-10 2004-21-02 2004-21-04
Biweekly 2004-22 2004-21-05 2004-21-06
S 96-20-07
2004-21-08 2004-22-12
190, 195 (L-126A, B, C), 195A, and 195B Rotorcraft: 600N
Biweekly 2004-23 2004-22-11 2004-22-13 2004-22-21 2004-22-28 2004-23-01 2004-23-02
S 2003-20-11
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SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS AD No.
Information
Manufacturer
Applicability
Info: E - Emergency; COR - Correction; S - Supersedes; R - Revision; - See AD for additional information; Biweekly 2004-24 2004-23-15 2004-23-17 2004-24-02 2004-24-03 2004-24-04
S 91-03-15
S 2003-13-10
MD Helicopters, Inc Mooney Airplane Company, Inc. Ostmecklenburgische Flugzeugbau GmbH Hamilton Sundstrand Power Sys. Rolls-Royce Corporation
Rotorcraft: MD900 M20M OMF-100-160 Appliance: Auxiliary Power Units Engine: 250-C30R/3, -C30R/3M, -C47B, and -C47M Turboshaft
Biweekly 2004-25 2004-24-01 2004-24-08 2004-24-09 2004-24-10 2004-24-11 2004-25-04 2004-25-51
E
Bombardier Inc. Bell Helicopter Textron Canada Rolls-Royce Corporation Bombardier, Inc. Schempp-Hirth Flugzeugbau GmbH Mooney Aircraft Corporation Raytheon Aircraft Company
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DHC-3 Rotorcraft: 206A, B, L, L-1, L-3, and L-4 Engine: 250-B and 250-C Series Turboshaft DHC-3 Sailplane: Duo-Discus M20C, M20D, M20E, M20F, M20G, and M20J 45 (YT-34), A45 (T-34A, B-45), and D45 (T-34B)
BW 2004-25 BOMBARDIER INC. AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2004-24-01 Bombardier Inc.: Amendment 39-13877; Docket No. FAA-2004-18606; Directorate Identifier 2004-CE-17-AD. When Does This AD Become Effective? (a) This AD becomes effective on December 28, 2004. 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: All Bombardier Inc. Model (Otter) DHC-3 airplanes incorporating 524085 BC, Ltd. Supplemental Type Certificate Number ST01243NY or SA01243NY. What Is the Unsafe Condition Presented in This AD? (d) This AD is the result of one incident of structural failure of the elevator servo tab balance assembly. The actions specified in this AD are intended to prevent the structural failure of the elevator servo tab, which could lead to loss of control of the airplane. What Must I Do To Address This Problem? (e) To address this problem, you must do the following: Actions (1) Perform the following actions: (i) Remove the existing elevator sevo tab assembly, consisting of the following part numbers (P/N): C3TE13–12, VALTOC1136–2, and NAS40–2A– LT; (ii) Install the redesigned elevator servo tab assembly, P/N V3TE1137–1. (2) Balance the servo tab assembly to achieve a nose heavy static moment within the limits set by Viking Air Ltd. Service Bulletin V3/01, dated March 6, 2002.
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Compliance Replace the elevator servo tab assembly within 300 hours timein-service (TIS) after December 28, 2004 (the effective date of this AD). After installation of the redesigned servo tab assembly, balance prior to further flight.
Procedures Follow Viking Air Ltd. Service Bulletin V3/01, dated March 6, 2002.
Follow Viking Air Ltd. Service Bulletin V3/01, dated March 6, 2002.
2004-24-01 2
(3) Do not install any of the following part numbers as part of the servo tab assembly: (i) P/N C3TE13–12; (ii) P/N VALTOC1136–2; (iii) P/N NAS40–2A–LT.
The part numbers Not applicable. should not be installed as of December 28, 2004 (the effective date of this AD).
May I Request an Alternative Method of Compliance? (f) You may request a different method of compliance or a different compliance time for this AD by following the procedures in 14 CFR 39.19. Unless FAA authorizes otherwise, send your request to your principal inspector. The principal inspector may add comments and will send your request to the Manager, New York Aircraft Certification Office (ACO), FAA. For information on any already approved alternative methods of compliance, contact David Lawson, Aerospace Engineer, ANE-171, New York Aircraft Certification Office, 1600 Stewart Ave., Suite 410, Westbury, NY 11590; telephone: 516-228-7327; facsimile: 516-794-5531. Is There Other Information That Relates to This Subject? (g) Transport Canada Airworthiness Directive Number CF-2002-48, dated November 21, 2002, and Viking Air Ltd. Service Bulletin Number V3/01, dated March 6, 2002, 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 Viking Air Ltd. Service Bulletin Number V3/01, dated March 6, 2002. 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 Bombardier Inc., Regional Aircraft, 123 Garratt Boulevard, Downsview, Ontario, Canada M3K 1Y5. To review copies of this service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html or call (202) 741-6030. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590001 or on the Internet at http://dms.dot.gov. The docket number is FAA-2004-18606. Issued in Kansas City, Missouri, on November 15, 2004. Scott L. Sedgwick, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 04-25674 Filed 11-26-04; 8:45 am] BILLING CODE 4910-13-P
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BW 2004-25 BELL HELICOPTER TEXTRON CANADA AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2004-24-08 Bell Helicopter Textron Canada: Amendment 39-13884. Docket No. 2004-SW-12-AD. Applicability: Model 206A, B, L, L-1, L-3, and L-4 helicopters, with a tail rotor blade (blade) with the following part number (P/N) and serial number (S/N) installed, certificated in any category. Model 206A & B; Blade, P/N 206–016– 201–133, S/N with prefix ‘‘CS’’ and no ‘‘V’’ suffix 1381 through 1442 1492 through 1517 1520 through 1542 1550 1556 1560 1562 1564 through 1567 1569 through 1606 1609 1611 1612 1614 through 1631 1633 through 1675 1677 1678 1680 through 1682 1684 through 1787 1789 through 1803 1810 through 1812 1814 1816 1820 1823 through 1831 1834 through 1836 1838 1840 through 1844 1846 1848 through 1882 1884 through 1887
Model 206A, B, L, L–1, L–3, & L–4, Blade, P/N 206– 016–201–131, S/N with prefix ‘‘CS’’ and no ‘‘V’’ suffix 7000 through 7018 10174 through 10218. 7020 through 7043 10220. 7045 through 7050 10232. 7052 through 7132 10235. 7134 through 7246 10237 through 10241. 7248 through 7270 10244. 7272 through 7277 10245. 7279 through 7339 10248. 7342 through 7368 10250 through 10264. 7784 10266 through 10268. 7786 10270 through 10274. 7788 10276 through 10278. 7790 through 7796 10280 through 10282. 7798 through 7819 10284 through 10292. 7821 through 7833 10296. 7835 through 7839 10300 through 10330. 7841 through 8001 10332. 8003 through 8026 10333. 8029 through 8061 10335 through 10347. 8064 through 8117 10349. 8119 10351 through 10359. 8121 through 8139 10363 through 10365. 8142 through 8176 10367. 8178 through 8262 10373. 8264 through 8294 10374. 8298 through 8368 10377 through 10385. 8370 through 8375 10387 through 10408. 8378 through 8416 10410. 8419 10414 through 10417. 8421 10419 through 10427.
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2004-24-08 2
1889 through 1893 1896 through 1898 1900 1904 1909 through 1912 1915 1916 1919 through 1921 1924 1928 through 1931 1933 1934 through 1939 1943 1945 1947 1948 1952 through 1957 1960 1962 through 1965
8425 through 8428 8430 through 8438 8440 8441 8443 8445 through 8447 8449 through 8606 8608 through 8622 8624 through 8626 8628 through 8632 8635 through 8653 8655 through 8686 8690 8692 through 8700 8703 through 8715 8717 through 8722 8724 through 8742 8745 through 8828 8830 through 8835 8838 through 8840 8842 through 8881 8883 through 9032 9034 through 9139 9141 through 9198 9200 9202 through 9302 9304 through 9339 9341 through 9371 9373 through 9411 9413 9415 through 9417 9419 through 9496 9498 through 9585 9587 through 9594 9596 through 9618 9621 through 9629 9632 through 9642 9645 through 9651 9653 through 9673 9675 through 9707 9709 through 9724 9727 through 9731 9733 through 9735 9737 through 9739 9741 through 9748 9751 through 9785 11
10430. 10432. 10437. 10438. 10442 through 10445. 10458 through 10466. 10469. 10470. 10474. 10476 through 10478. 10480 through 10487. 10489 through 10491. 10493 through 10495. 10497 through 10503. 10505 through 10588. 10591 through 10606. 10608 through 10610. 10612 through 10620. 10623. 10624. 10631 through 10655. 10657 through 10669. 10672. 10673. 10676 through 10678. 10680 through 10683. 10685. 10687. 10689 through 10702. 10707. 10712. 10715. 10730. 10732 through 10734. 10736. 10738. 10739. 10746. 10750. 10756. 10760. 10761. 10765. 10770. 10774 through 10776. 10778.
2004-24-08 3
9787 9788 9790 through 9792 9795 through 9847 9849 through 9928 9930 through 9937 9940 through 9942 9944 through 9952 9955 through 9972 9974 through 9989 9991 through 9995 9997 through 10004 10006 through 10009 10011 10013 through 10018 10021 through 10030 10034 10036 through 10057 10061 through 10082 10090 through 10092 10094 through 10100 10116 10119 10121 10123 through 10134 10136 through 10140 10142 through 10144 10146 through 10172
10781. 10783 through 10785. 10792. 10794. 10798. 10799. 10806 through 10808. 10811. 10814 through 10822. 10824. 10825. 10829. 10831. 10917. 10923. 10931. 10936. 10937. 10940. 10943. 10945. 10947. 10948. 10964. 10965. 10973. 10982. 10985. 10986.
Compliance: Required as indicated. To prevent blade failure and subsequent loss of control of the helicopter, do the following: (a) Before further flight, unless accomplished previously, and before installing any blade with a P/N and S/N listed in the applicability section of this AD, clean the blade. Using a 10X or higher magnifying glass, inspect both sides of each blade for a deformation, a crack, and a bent or deformed weight in the area shown in Figure 1 of this AD. Note 1: Paint irregularities on the blade may indicate a crack.
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2004-24-08 4
(b) After doing paragraph (a) of this AD, at the following intervals, clean both sides of each blade and do either paragraph (1) or (2) as follows: (1) At intervals not to exceed 12 hours time-in-service (TIS), using a 10X or higher magnifying glass, inspect both sides of each blade for a deformation, a crack, and a bent or deformed weight in the area shown in Figure 1 of this AD, or (2) Inspect and check both sides of each blade for a deformation, a crack, and a bent or deformed weight in the area shown in Figure 1 of this AD as follows: (i) Using a 10X or higher magnifying glass, inspect at intervals not to exceed 24 hours TIS, and (ii) Check at intervals not to exceed 3 hours TIS between the inspections required by paragraph (b)(2)(i) of this AD. An owner/operator (pilot), holding at least a private pilot certificate, may perform this visual check and must enter compliance with this paragraph into the helicopter maintenance records by following 14 CFR sections 43.11 and 91.417(a)(2)(v). (c) Before further flight, replace any blade that has a deformation, a crack, or a bent or deformed weight with an airworthy blade. Note 2: Bell Helicopter Textron Alert Service Bulletin No. 206-04-100 for Model 206A and B and No. 206L-04-127 for Model 206L series, both Revision B, both dated May 28, 2004, pertain to the subject of this AD. (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) This amendment becomes effective on December 16, 2004. Note 3: The subject of this AD is addressed in Transport Canada (Canada) AD No. CF-200405R1, dated June 28, 2004. 13
2004-24-08 5
Issued in Fort Worth, Texas, on November 22, 2004. Kim Smith, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 04-26425 Filed 11-30-04; 8:45 am] BILLING CODE 4910-13-P
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BW 2004-25 ROLLS-ROYCE CORPORATION AIRWORTHINESS DIRECTIVE ENGINE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2004-24-09 Rolls-Royce Corporation: Amendment 39-13885. Docket No. 2004-NE-10-AD. Effective Date (a) This airworthiness directive (AD) becomes effective January 5, 2005. Affected ADs (b) None. Applicability (c) This AD applies to Rolls-Royce Corporation (formerly Allison Engine Company, Allison Gas Turbine Division, and Detroit Diesel Allison) (RRC) 250-B and 250-C series turboshaft and turboprop engines in the following Table 1: TABLE 1.—250–B AND 250–C SERIES TURBOSHAFT AND TURBOPROP ENGINES AFFECTED –B15A –B15E –B15G –B17 –B17B –B17C –B17D –B17E –B17F –B17F/1 –B17F/2 –C18 –C18A –C18B –C18C –C20 –C20B –C20C –C20F –C20J –C20R –C20R/1 –C20R/2 –C20R/4 –C20S –C20W –C28 –C28B –C28C –C30 –C30G –C30G/2 –C30M –C30P –C30R –C30R/1 –C30R/3 –C30R/3M –C30S –C30U –C40B –C47B –C47M These engines are installed on, but not limited to, Agusta Models A109, A109A, A109AII, and A109C; Bell Helicopter Textron Models 47, 206A, 206B, 206L, 206L-1, 206L-3, 206L-4, 407, and 430; B-N Group Models BN-2T and BN-2T-4R; Enstrom Models TH28, 480; and 480B; Eurocopter Canada Limited Model BO 105 LS A-3; Eurocopter France Models AS355E, AS355F, AS355I, and AS355F2; Eurocopter Deutschland Models BO-105A, BO-105C, BO-105S, and BO105LS A-1; Hiller Aviation Model FH-1100; McDonnell Douglas 369D, 369E, 369F, 369H, 369HE, 369HM, 369HS, 369FF, and 500N; Schweizer TH269D; SIAI Marchetti s.r.l. Models SF600 and SF600A; and Sikorsky S-76A helicopters and airplanes.
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Unsafe Condition (d) This AD results from 10 reports of engine power loss with accompanying collapse of the screen in the fuel nozzle, due to fuel contamination. We are issuing this AD to minimize the risk of sudden loss of engine power and uncommanded shutdown of the engine due to fuel contamination and collapse of the screen in the fuel nozzle. 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) Perform a onetime inspection of the fuel nozzle screen for contamination, within 150 operating hours after the effective date of this AD. (g) Inspect and clean the entire aircraft fuel system before further flight if there is any contamination on the screen. (h) Remove from service fuel nozzles, part numbers (P/Ns) 6890917, 6899001, and 6852020, and replace with a serviceable fuel nozzle, at the next fuel nozzle overhaul after the effective date of this AD, or by June 30, 2006, whichever occurs first. Definition (i) For the purposes of this AD, a serviceable fuel nozzle is defined as a nozzle that has a P/N not specified in, or addressed by, this AD. Alternative Methods of Compliance (j) The Manager, Chicago Aircraft Certification Office, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. Related Information (k) Information related to the subject of this AD can be found in Rolls-Royce Corporation Alert Commercial Engine Bulletin, with the identification numbers of CEB-A-313, CEB-A-1394, CEB-A-73-2075, CEB–A-73-3118, CEB-A-73-4056, CEB-A-73-5029, CEB-A-73-6041, TP CEB-A183, TP CEB-A-1336, and TP CEB-A-73-2032, dated September 4, 2003. Material Incorporated by Reference (l) None. Issued in Burlington, Massachusetts, on November 22, 2004. Francis A. Favara, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 04-26424 Filed 11-30-04; 8:45 am] BILLING CODE 4910-13-P 16
BW 2004-25 BOMBARDIER, INC. AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2004-24-10 Bombardier, Inc.: Amendment 39-13886; Docket No. 2003-CE-48-AD. When Does This AD Become Effective? (a) This AD becomes effective on January 6, 2005. What Other ADs Are Affected by This Action? (b) None. What Airplanes Are Affected by This AD? (c) This AD affects the Model DHC-3 airplanes, all serial numbers, that are: (1) Modified with STC number SA3777NM; and (2) Certificated in any category. What Is the Unsafe Condition Presented in This AD? (d) This AD is the result of a drawing error on Revisions G and H of Sheet 1 of Drawing 20075, Electrical System Schematic. The actions specified in this AD are intended to detect and correct wiring installed according to an incorrect drawing, which shows the pneumatic heating blankets to the P3 and PY pneumatic lines wired in series with the indicator lights, rather than parallel. This can result in insufficient electrical energy for the heating blankets and loss of pneumatic heating, which can lead to loss of engine power or reverse propeller overspeed governing protection and ultimately loss of control of the airplane. What Must I Do To Address This Problem? (e) To address this problem, you must do the following: Actions (1) Inspect the electrical wiring to the P3 and PY engine pneumatic line heating blankets and the P3 heater warning light to determine if they are wired in a parallel configuration. If they are not wired in a parallel configuration, they must be rewired.
Compliance Inspect within 4 months after January 6, 2005 (the effective date of this AD) or 300 hours time in service (TIS) after January 6, 2005 (the effective date of this AD), whichever occurs first. Rewire prior to further flight after the inspection.
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Procedures Follow the procedures in the A.M. Luton Service Information Letter SIL–00–10–10, revision dated, March 22, 2001.
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(2) Replace Flight Manual Supplement currently in use with Revision G, dated March 28, 2001. This flight manual revision corrects the drawing error on Revisions G and H of Sheet 1 of the Electrical System Schematic Drawing 20075 by incorporating Revision I of Sheet 1 of Drawing 20075, ‘‘Electrical System Schematic,’’ dated October 10, 2000. (i) The owner/operator holding at least a private pilot certificate as authorized by section 43.7 of the Federal Aviation Regulations (14 CFR 43.7) may accomplish the flight manual replacement requirement of this AD. (ii) Make an entry into the aircraft records showing compliance with this portion of the AD in accordance with section 43.9 of the Federal Aviation Regulations (14 CFR 43.9). (3) Inspect circuit breaker switch for heated engine pneumatic lines circuit. If an engine is installed that uses both P3 and PY heated pneumatic lines, circuit breaker switch, Part Number (P/N) 20075– 3 (5 amp), must be replaced with circuit breaker switch P/N 20075– 59 (7.5 amp).
Replace within 4 months after January 6, 2005 (the effective date of this AD) or 300 hours TIS after January 6, 2005 (the effective date of this AD), whichever occurs first.
Follow the procedures in the A.M. Luton Service Information Letter SIL–00–10–10, revision dated, March 22, 2001.
Inspect within 4 months after January 6, 2005 (the effective date of this AD), or 300 hours TIS after January 6, 2005 (the effective date of this AD), whichever occurs first. Replace prior to further flight after the inspection.
Follow the procedures in the A.M. Luton Service Information Letter SIL–00–10–10, revision dated, March 22, 2001.
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, Special Certifications Branch, Transport Airplane Directorate, FAA. For information on any already approved alternative methods of compliance, contact Richard Simonson, Aerospace Engineer, Special Certifications Branch, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, WA 98055; telephone: 425-917-6507; facsimile: 816-917-6590.
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Does This AD Incorporate Any Material by Reference? (g) You must do the actions required by this AD following the instructions in A.M. Luton Service Information Letter SIL-00-10-10, revision dated March 22, 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. You may get a copy from A.M. Luton, 3025 Eldridge Ave., Bellingham, WA 98225. You may review copies at FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106; 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 Is There Other Information That Relates to This Subject? (h) Airworthiness Directive CF-2002-38, dated August 29, 2002, and Service Information Letter SIL-00-10-10, revision dated March 22, 2001, also pertain to the subject of this AD. Issued in Kansas City, Missouri, on November 23, 2004. David A. Downey, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 04-26421 Filed 12-3-04; 8:45 am] BILLING CODE 4910-13-P
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BW 2004-25 SCHEMPP-HIRTH FLUGZEUGBAU GMBH AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2004-24-11 Schempp-Hirth Flugzeugbau GmbH: Amendment 39-13887; Docket No. FAA-200419556; Directorate Identifier 2004-CE-37-AD. When Does This AD Become Effective? (a) This AD becomes effective on December 30, 2004. Are Any Other ADs Affected by This Action? (b) None. What Gliders Are Affected by This AD? (c) This AD affects Model Duo-Discus gliders, serial numbers 1 through 164, 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. The actions specified by this AD are intended to detect and correct failure of the bonding of the spar cap and spar web, which, if not detected and corrected, could result in an in-flight failure of the wing. What Must I Do To Address This Problem? (e) To address this problem, you must do the following, unless already done: Actions (1) Inspect the bonding between the spar cap and the spar web for defects. (2) Repair any defect in the bonding between the spar cap and the spar web.
Compliance Within the next 10 hours time-in-service (TIS) after December 30, 2004 (the effective date of this AD). Prior to further flight after the inspection required by paragraph (e)(1) of this AD.
Procedures Follow SCHEMPP–HIRTH Flugzeugbau GmbH. Kircheim/Teck Technical Note No. 396–9, dated January 30, 2004; and SCHEMPP–HIRTH Flugzeugbau GmbH. Kircheim/Teck Appendix to Technical Note No. 396–9, dated January 30, 2004. Follow SCHEMPP–HIRTH Flugzeugbau GmbH. Kircheim/Teck Technical Note No. 396–9, dated January 30, 2004; SCHEMPP–HIRTH Flugzeugbau GmbH. Kircheim/Teck Appendix to Technical Note No. 396–9, dated January 30, 2004; And the applicable maintenance manual.
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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, Small Airplane Directorate, FAA. For information on any already approved alternative methods of compliance, contact Gregory Davison, Aerospace Engineer, FAA, Small Airplane Directorate, Room 301, 901 Locust, Kansas City, Missouri 64106; telephone: (816) 329-4130; facsimile: (816) 329-4090. Is There Other Information That Relates to This Subject? (g) German AD Number D-2004-084, dated February 4, 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 SCHEMPPHIRTH Flugzeugbau GmbH. Kircheim/Teck Technical Note No. 396-9, dated January 30, 2004; and SCHEMPP-HIRTH Flugzeugbau GmbH. Kircheim/Teck Appendix to Technical Note No. 396-9, dated January 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 Schempp-Hirth Flugzeugbau GmbH, Postfach 1443, 73222 Kircheim/Teck, Federal Republic of Germany; telephone: 49 7021 7298-0; facsimile: 49 7021 7298199. To review copies of this service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html or call (202) 741-6030. To view the AD docket, go to the Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, Washington, DC 20590001 or on http://dms.dot.gov. The docket number is FAA-2004-19556. Issued in Kansas City, Missouri, on November 26, 2004. James E. Jackson, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 04-26640 Filed 12-8-04; 8:45 am] BILLING CODE 4910-13-P
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BW 2004-25 MOONEY AIRCRAFT CORPORATION AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2004-25-04 Mooney Aircraft Corporation: Amendment 39-13891; Docket No. 98-CE-64-AD. When Does This AD Become Effective? (a) This AD becomes effective on January 21, 2005. What Other ADs Are Affected By This Action? (b) None. What Airplanes Are Affected by This AD? (c) This AD affects Models M20C, M20D, M20E, M20F, M20G, and M20J airplanes, all serial numbers, that are: (1) certificated in any category; (2) equipped with an O & N Bladder Fuel Cell installed per Supplemental Type Certificate (STC) SA2277CE or STC SA2350CE; and (3) This AD affects Model M20B airplanes, all serial numbers, that are certificated in any category and have any of the STCs referenced in paragraph (c)(2) incorporated by field approval. What Is the Unsafe Condition Presented in This AD? (d) This AD is the result of reports of rain water entering the fuel bladders and the information from the subsequent evaluation of the fuel systems. The actions specified in this AD are intended to assist in preventing water from entering the fuel bladders, which could result in rough engine operation or complete loss of engine power. What Must I Do To Address This Problem? (e) To address this problem, you must do the following: Actions Compliance (1) On both the left and right wing, inspect the Within the next 12 months drain valve to assure that it was inserted after January 21, 2005 (the fully into the drain nipple effective date of this AD), unless already done (see Note 1)
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Procedures Follow O & N Aircraft Modifications Inc. Mandatory Service Bulletin No. ON–100, dated February 1, 1998.
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(2) Modify any drain valve found not to be inserted fully into the drain nipple
(3) On both the left and right wing do the following: (i) Install a foam wedge to reduce the amount of trapped fluids in the center fuel cell; (ii) Install an anti-ice mast forward of the vent tubes to prevent icing of the fuel tank vents; (iii) Drill a vent hole to prevent icing of the engine’s crankcase breathers; and (iv) Replace the flush style fuel caps and adapters with raised style caps and adapters. Follow the instructions in paragraph (f) of this AD as an alternative method of compliance for replacing the flush style fuel caps
Prior to further flight after the inspection required in paragraph (e)(1) of this AD, unless already done (see Note 1). Within the next 12 months after January 21, 2005 (the effective date of this AD), unless already done (see Note 1).
Follow O & N Aircraft Modifications Inc. Mandatory Service Bulletin No. ON–100, dated February 1, 1998. Follow O & N Aircraft Modifications Inc. Mandatory Service Bulletin No. ON–100, dated February 1, 1998.
Note 1: All kits installed by (or obtained from) O&N Aircraft Modifications Inc. after February 1, 1998, incorporate the actions of this AD. If you have one of these kits installed, you may take ''unless already done'' credit for the actions of this AD. What Is the Alternate Method of Compliance (AMOC) for Replacing the Flush Style Fuel Caps as Required in Paragraph (e)(3)(iv) of This AD? (f) Instead of replacing the flush style fuel caps as required in paragraph (e)(3)(iv) of this AD, you may do a preflight fuel system check prior to each flight. To do this, you must insert the following ''Pilot Operating Procedures–Preflight Fuel System Check'' (paragraphs (f)(1), (f)(2), (f)(3), and (f)(4) of this AD) into the Limitation Section of the FAA-approved Airplane Flight Manual (AFM): (1) Place a suitable container under the fuel strainer drain outlet prior to operating the strainer drain control for at least 4 seconds. Check strainer to ensure drain is closed.(2) Inspect the fluid drained from the fuel strainer and each wing tank quick drain for evidence of fuel contamination in the form of water, rust, sludge, ice, or any other substance not compatible with fuel. Also check for proper fuel grade before the first flight of each day and after each refueling. If any contamination is detected, comply with paragraph (f)(4) of this AD. (3) Repeat steps in paragraph (f)(1) and (f)(2) of this AD on each wing tank quick drain. (4) If the airplane has been exposed to rain, sleet, or snow, or if the wing fuel tanks or fuel strainer drains produce water or other contamination, you must purge the airplane fuel system to the extent necessary to ensure that there is no water, ice, or other fuel contamination.
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May I Request Another AMOC for This AD? (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, Wichita Aircraft Certification Office (ACO), FAA. For information on any already approved alternative methods of compliance, contact Paul O. Pendleton, Aerospace Engineer, FAA, Wichita ACO, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316) 946-4143; facsimile: (316) 946-4107. Does This AD Incorporate Any Material by Reference? (h) You must do the actions required by this AD following the instructions in O & N Aircraft Modifications Inc. Mandatory Service Bulletin No. ON-100, dated February 1, 1998. 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 may get a copy from O & N Aircraft Modifications Inc., 210 Windsock Lane, Seamans Airport, Factoryville, PA 18419. You may review copies at FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106; 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 Kansas City, Missouri, on December 1, 2004. David A. Downey, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 04-26915 Filed 12-8-04; 8:45 am] BILLING CODE 4910-13-P
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BW 2004-25 RAYTHEON AIRCRAFT COMPANY AIRWORTHINESS DIRECTIVE EMERGENCY SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2004-25-51 RAYTHEON AIRCRAFT COMPANY: Directorate Identifier 2004-CE-44-AD. When Does This AD Become Effective? (a) This AD becomes effective upon receipt of this emergency AD. Are Any Other ADs Affected By This Action? (b) None. For clarification, this AD provides no relief from the requirements of AD 2001-1318 R1. What Airplanes Are Affected by This AD? (c) This AD affects Beech Models 45 (YT-34), A45 (T-34A, B-45), and D45 (T-34B) 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 cracks found in a location that was previously inspected and found to comply with AD 2001-13-18 R1; and two new locations. We are issuing this AD to detect and correct such cracking, which 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) The following specifies action you must do per this AD and other pertinent information to address this problem: Actions
Compliance
(1) Perform an inspection and/or modification program approved specifically for this AD by the FAA Wichita Aircraft Certification Office (ACO).
Prior to further flight after the receipt of this emergency AD.
(2) To return/position the airplane to a home base, hangar, maintenance facility, etc., you may operate the airplane provided you follow the limitations in paragraph (f) of this AD.
You may operate the airplane up to 10 hours time-in-service (TIS) provided the flight(s) occur(s) no later than 30 days after receipt of this emergency AD.
(3) Special flight permits are allowed for this AD. See paragraph (f) of this AD for restrictions.
Use the procedures in 14 CFR part 39 and the restrictions in paragraph (f) of this AD. 25
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(4) To help in the long-term airworthiness solution for the safety and continued airworthiness of these airplanes, FAA is requesting data from every owner/operator on the following on these airplanes: (i) Service/Repair History (cracked/fatigued structure); (ii) Maintenance Schedule; and (iii) Total Hours Time-In-Service (TIS).
Send to Paul Nguyen, Aerospace Engineer, FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316) 946-4125; facsimile: (316) 946-4107; e-mail:
[email protected].
What are the Flight Restrictions Specified in Paragraph (e)(2) and (e)(3) of this AD? (f) During the time allowed before compliance with paragraph (e)(1) of this AD or for any approved special flight permit, you must adhere to the following limitations: (1) NEVER EXCEED SPEED, VNE-175 MPH (152 knots); (2) NORMAL ACCELERATION (G) LIMITS – 0, and +2.5; (3) ACROBATIC MANEUVERS PROHIBITED. (4) FLIGHT INTO KNOWN OR FORECAST MODERATE OR SEVERE TURBULENCE IS PROHIBITED. (5) DAY VISUAL FLIGHT RULES (VFR) OPERATION ONLY. (6) PILOT AND ANY ADDITIONAL FLIGHT CREW MEMBER REQUIRED FOR SAFE OPERATION. Who do I Contact for Further Information? (g) If you need additional information relating to this AD, contact: Paul Nguyen, Aerospace Engineer, FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Mid-Continent Airport, Wichita, Kansas 67209; telephone: (316) 946-4125; facsimile: (316) 946-4107; e-mail:
[email protected]. Issued in Kansas City, Missouri, on December 10, 2004.
David A. Downey, Acting Manager, Small Airplane Directorate, Aircraft Certification Service.
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