FEDERAL AVIATION ADMINISTRATION AIRWORTHINESS DIRECTIVES SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS BIWEEKLY 2004-12 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 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 2004-11-05 2004-11-06 2004-11-10 2004-11-12
FR
Boeing Defense And Space Group Eurocopter France Agusta S.p.A Przedsiebiorstwo Doswiadczalno-Produkcyjne Szybownictwa ''PZL-Bielsko'' Alexander Schleicher Gmbh & Co.
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Rotorcraft: 234 Rotorcraft: EC 130 B4 and AS 350 B3 Rotorcraft: A109E Glider: SZD-50-3 ''Puchacz'' Glider: ASW 27
BW 2004-12 BOEING DEFENSE AND SPACE GROUP AIRWORTHINESS DIRECTIVE FINAL RULE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2004-06-51 Boeing Defense and Space Group: Amendment 39-13651. Docket No. 2004-SW-09AD. Applicability: Model 234 helicopters, with aft vertical shaft assembly, part number (P/N) 234D3300, serial number-181 or lower with a prefix of A, installed, certificated in any category. Compliance: Required as indicated. To detect a crack in the upper shaft extension, which could result in catastrophic failure of the aft vertical shaft assembly and subsequent loss of control of the helicopter, accomplish the following: Note 1: Prepare the helicopter for safe ground maintenance and disconnect the battery. (a) Before further flight, unless accomplished previously, perform the following initial inspection and modification: (1) Remove the screws, P/N MS51957-63 or MS51958-63, and washers, P/N AN960-D10L, from the oil tank assembly. Remove the retainer, P/N 114R2059-1, cover, P/N 14R2054-1, and packing, P/N M83248/1-264, from the oil tank assembly. (2) Cut the sealant around the upper shaft extension plug, P/N 114D1246-1. Remove the (adhesive) sealant from the plug and the inside diameter of the upper shaft extension, P/N 114D3248, before removing the plug. (3) Tap one side of the rubber plug, P/N 114D1246-1, with a hammer and drift to raise and offset the opposite edge of the plug. Pull the plug from the upper shaft extension. (4) Remove any loose sealant that remains on the inside diameter of the aft vertical shaft assembly using care not to drop debris into the shaft. (5) Inspect the upper shaft extension, P/N 114D3248, using a borescope or other lighted device that provides direct visual observation of the interior of the aft rotor shaft. Inspect 360 degrees around the entire interior length of the upper shaft extension. If any crack is found, replace the aft vertical shaft assembly, P/N 234D3300, with an airworthy assembly before further flight. See the following Figure 1 of this AD for the area to inspect:
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2004-06-51 2
(6) If no crack is found, using a light source, visually inspect the aft vertical shaft assembly for debris or foreign object damage (FOD) inside the diameter of the assembly. 7
2004-06-51 3
(7) Manufacture an aluminum-threaded plug to replace the rubber plug, P/N 114D1246-1. The replacement plug is to be installed in the internal threads on the top of the upper shaft extension. Machine the plug from a block of 7050-T7451, 7075-T6 or 6061-T6, with 4.000'' -16 UNS-3A threads and a minor thread diameter of 3.920''. Machine a hex head to the center of the cap to aid in removal. Machine the hex head to fit a 1\1/4\'' wrench. See the following Figure 2 of this AD:
Note 2: All dimensions stated in this AD are in inches. (8) Install the aluminum-threaded plug with an o-ring, P/N M83248-1-153, in the internal threads on the top of the upper shaft extension (hand tighten only). Assure the safety wire for the rotor hub nut is clear of the plug.
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2004-06-51 4
(9) Install packing, P/N M83248/1-264, into the o-ring groove of the oil tank assembly. Install the cover, P/N 114R2054-2, retainer, P/N 114R2059-1, washer, P/N AN960D10L, and screws, P/N MS51957-63 or MS51958-63, into the oil tank assembly that is installed on the aft rotary wing head assembly. Torque screws to 23 pounds-inches dry. (b) Before the first flight of each day, perform the following recurring inspection: (1) Remove the screws, P/N MS51957-63 or MS51958-63, and washers, P/N AN960D10L, from the oil tank assembly. Remove the retainer, P/N 114R2059-1, cover, P/N 114R2054-1, and packing, P/N M83248/1-264, from the oil tank assembly. (2) Remove the aluminum-threaded plug from the internal threads on the top of the upper shaft extension. (3) Inspect the upper shaft extension, P/N 114D3248, using a borescope or other lighted device that provides direct visual observation of the interior of the aft rotor shaft. Inspect 360 degrees around the entire interior length of the upper shaft extension (see Figure 1 of this AD). If any crack is found, replace the aft vertical shaft assembly, P/N 234D3300, with an airworthy assembly before further flight. (4) If no crack is found, install the aluminum-threaded plug with an o-ring, P/N M83248-1153, in the internal threads on the top of the upper shaft extension (hand tighten only). Assure the safety wire for the rotor hub nut is clear of the plug. (5) Install packing, P/N M83248/1-264, into the o-ring groove of the oil tank assembly. Install the cover, P/N 114R2054-2, retainer, P/N 114R2059-1, washer, P/N AN960D10L, and screws, P/N MS51957-63 or MS51958-63, into the oil tank assembly that is installed on the aft rotary wing head assembly. Torque screws to 23 pounds-inches dry. Note 3: Boeing BV234 Service Bulletin No. 234-63-1055, Revision 2, dated March 16, 2004, pertains to the subject of this AD. (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 Manager, New York Aircraft Certification Office (NYACO), Engine and Propeller Directorate, FAA, for information about previously approved alternative methods of compliance. (d) Special flight permits will not be issued. (e) This amendment becomes effective on June 18, 2004, to all persons except those persons to whom it was made immediately effective by Emergency AD 2004-06-51, issued March 18, 2004, which contained the requirements of this amendment. Issued in Fort Worth, Texas, on May 21, 2004. David A. Downey, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 04-12442 Filed 6-2-04; 8:45 am] BILLING CODE 4910-13-P
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BW 2004-12 EUROCOPTER FRANCE AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2004-11-05 Eurocopter France: Amendment 39-13650. Docket No. 2003-SW-29-AD. Applicability: Model EC 130 B4 helicopters with an optional engine flushing system installed, and AS 350 B3 helicopters with an optional engine flushing system installed and modified in accordance with MOD 073098, certificated in any category. Compliance: Required within 10 hours time-in-service, unless accomplished previously. To detect chafing wear of the air exhaust duct and the fuel transfer line, which could result in a hole in the fuel transfer line, fuel leaking into the engine compartment and creating a fire hazard that could lead to a fire and a subsequent forced landing, accomplish the following: (a) Inspect the fuel transfer line located between the bleed valve of the engine starting system and the engine fuel filter for chafing in the interference areas in accordance with the Operational Procedure, paragraph 2.B.1., of Eurocopter Alert Service Bulletin (ASB) No. 71A001, dated May 12, 2003, for Model EC 130 B4 helicopters, or Eurocopter ASB No. 71.00.16, dated May 12, 2003, for Model AS 350 B3 helicopters. (1) If the depth of the deepest wear mark is less than or equal to 0.05 mm (0.002 in), apply the maintenance procedure stated in the Engine Maintenance Manual. (2) If the depth of the deepest wear mark is more than 0.05 mm (0.002 in) and less than or equal to 0.2 mm (0.008 in), replace the fuel transfer line within the next 50 hours TIS or within one month, whichever occurs first. (3) If the depth of the deepest wear mark is more than 0.2 mm (0.008 in), replace the fuel transfer line before further flight. (b) Inspect the air exhaust duct located between the bleed valve of the engine starting system and the engine fuel filter for a hole in the interference areas in accordance with the Operational Procedure, paragraph 2.B.1., of Eurocopter ASB No. 71A001, dated May 12, 2003, for Model EC 130 B4 helicopters, or Eurocopter ASB No. 71.00.16, dated May 12, 2003, for Model AS 350 B3 helicopters. If there is a hole in the air exhaust duct, replace the air exhaust duct within one month or before performing any engine flushing operation, whichever occurs first. (c) Measure the clearances between the fuel transfer line and the air exhaust duct located between the bleed valve of the engine starting system and the engine fuel filter in the interference areas in accordance with the Operational Procedure, paragraph 2.B.1., of Eurocopter ASB No. 71A001, dated May 12, 2003, for Model EC 130 B4 helicopters, or Eurocopter ASB No. 71.00.16, dated May 12, 2003, for Model AS 350 B3 helicopters. If the clearance is less than 20 mm (0.8 in) in interference Area A or less than 12 mm (0.5 in) in interference Area B, reposition the air exhaust duct in accordance with the Operational Procedure, paragraph 2.B.2., of Eurocopter ASB No. 71A001, dated May 12, 2003, for Model EC 130 B4 helicopters, or Eurocopter ASB No. 71.00.16, dated May 12, 2003, for Model AS 350 B3 helicopters.
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2004-11-05 2
(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 Manager, Safety Management Office, Rotorcraft Directorate, FAA, for information about previously approved alternative methods of compliance. (e) The inspections, measuring, and repositioning, if necessary, shall be done in accordance with Eurocopter ASB No. 71A001 for Model EC 130 B4 helicopters and ASB No. 71.00.16 for Model AS 350 B3 helicopters, both dated May 12, 2003. 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. Copies may be inspected at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas; 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. (f) This amendment becomes effective on July 9, 2004. Note: The subject of this AD is addressed in Direction Generale De L'Aviation Civile (France) AD 2003-208(A) and AD 2003-209(A), both dated May 28, 2003. Issued in Fort Worth, Texas, on May 21, 2004. David A. Downey, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 04-12441 Filed 6-3-04; 8:45 am] BILLING CODE 4910-13-P
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BW 2004-12 AGUSTA S.P.A AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2004-11-06 Agusta S.p.A: Amendment 39-13652. Docket No. 2003-SW-32-AD. Applicability: Model A109E helicopters, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent the incompatibility of certain relays with the windshield wiper electrical system, overheating of the resistor due to system overload, and an electrical fire, accomplish the following: (a) For helicopters, serial number (S/N) 11502 through 11504, and 11122 through 11130, except 11123, 11127, and 11129: (1) Within 5 hours time-in-service, do the following: (i) Disable the windshield wipers by following the Compliance Instructions, Part I, paragraphs 2.1 through 2.5, of Agusta Alert Bollettino Tecnico No. 109EP-27, Revision A, dated February 7, 2003 (ABT). (ii) Install a placard stating that the windshield wipers are inoperative by following the Compliance Instructions, Part I, paragraph 2.6, of the ABT. (2) Within 6 months, modify the electrical system of the windshield wipers using the Compliance Instructions, Part II, paragraphs 1. through 15., of the ABT, and remove the placard that was installed as required by paragraph (a)(1)(ii) of this AD. (b) For helicopters, S/Ns 11151, 11501, and 11001 through 11133, except 11122, 11124 through 11128, and 11130, with timed relay, part number (P/N) T412-DJ1001-C installed, on or before June 6, 2005, or when you replace a timed relay, P/N T412-DJ1001-C, with either relay, P/N TDH-8070-1001P or P/N T412-2006, whichever occurs first: (1) If windshield wiper kit, P/N 109-0811-44-105 or -106 is installed, modify the windshield wiper electrical system and replace the timed relay, P/N T412-DJ1001-C, with a timed relay, P/N TDH-8070-1001P or P/N T412-2006, by following the Compliance Instructions, Part III, paragraphs 1. through 1.16, of the ABT. (2) If windshield wiper kit, P/N 109-0811-44-101 or -102 is installed, modify the windshield wiper electrical system and replace the timed relay, P/N T412-DJ1001-C, with a timed relay, P/N TDH-8070-1001P or P/N T412-2006, by following the Compliance Instructions, Part III, paragraphs 2. through 2.19, of the ABT. (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 Safety Management Group, FAA, for information about previously approved alternative methods of compliance. (d) Modifying the windshield wiper electrical system shall be done following the Agusta Alert Bollettino Tecnico No. 109EP-27, Revision A, dated February 7, 2003. 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 Agusta 520, telephone 39 (0331) 229111, fax 39 (0331) 229605-222595. Copies may be inspected at 12
2004-11-06 2
the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas; 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 (e) This amendment becomes effective on July 9, 2004. Note: The subject of this AD is addressed in Ente Nazionale per l'Aviazione Civile (Italy), AD No. 2003-032, dated February 10, 2003. Issued in Fort Worth, Texas, on May 21, 2004. David A. Downey, Manager, Rotorcraft Directorate, Aircraft Certification Service. [FR Doc. 04-12440 Filed 6-3-04; 8:45 am] BILLING CODE 4910-13-P
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BW 2004-12 PRZEDSIEBIORSTWO DOSWIADCZALNO-PRODUKCYJNE SZYBOWNICTWA ''PZL-BIELSKO'' AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2004-11-10 Przedsiebiorstwo Doswiadczalno-Produkcyjne Szybownictwa ''PZL-Bielsko'': Amendment 39-13656; Docket No. 2003-CE-66-AD. When Does This AD Become Effective? (a) This AD becomes effective on July 19, 2004. What Other ADs Are Affected by This Action? (b) None. What Sailplanes Are Affected by This AD? (c) This AD affects Model SZD-50-3 ''Puchacz'' sailplanes, 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 Poland. We are issuing this AD to detect and correct cracks in the airbrake torque tube, which could result in failure of the airbrake system. This failure could lead to loss of control of the sailplane. What Must I Do To Address This Problem? (e) To address this problem, you must do the following: Actions (1) Using a flourescent dye-penetrant or dye-check method, inspect the airbrake torque tube for cracks and corrosion pits. Visually inspect for permanent distortions and surface corrosion (damage).
Compliance Within the next 25 hours timein-service (TIS) after July 19, 2004 (the effective date of this AD). Repetitively inspect thereafter at intervals not to exceed 12 calendar months or 100 hours TIS, whichever occurs later.
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Procedures Follow Allstar PZL Glider SP. Z o.o. Mandatory Bulletin No. BE–052/SZD– 50–3/2003 ‘‘Puchacz’’, dated July 22, 2003.
2004-11-10 2
(2) Based on the results of the inspection: (a) Repair the airbrake torque tube if slight, uniform corrosive deposits are found during the inspection required in paragraph (e)(1) of this AD by removing the corrosive deposits with a fine abrasive paper; and (b) Replace the airbrake torque tube if any other damage is found during the inspection required in paragraph (e)(1) of this AD.
Prior to further flight after the inspection in which the damage is found. Continue with the repetitive inspections required in paragraph (e)(1) of this AD after each repair or replacement is made.
Follow Allstar PZL Glider Sp. Z o.o. Mandatory Bulletin No. BE–052/SZD– 50–3/2003 ‘‘Puchacz’’, dated July 22, 2003.
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 Greg Davison, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329-4130; facsimile: (816) 329-4090. Does This AD Incorporate Any Material by Reference? (g) You must do the actions required by this AD following the instructions in Allstar PZL Glider Sp. Z o.o. Mandatory Bulletin No. BE-052/SZD-50-3/2003 ''Puchacz'', dated July 22, 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. You may get a copy from Allstar PZL Glider Sp. z o.o., ul. Cieszyńska 325, 43-300 Bielsko-Biala. 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) Republic of Poland AD Number SP-0052-2003-A, dated July 22, 2003, also addresses this subject. Issued in Kansas City, Missouri, on May 27, 2004. Scott L. Sedgwick, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 04-12573 Filed 6-7-04; 8:45 am] BILLING CODE 4910-13-P
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BW 2004-12 ALEXANDER SCHLEICHER GMBH & CO. AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2004-11-12 Alexander Schleicher Gmbh & Co.: Amendment 39-13658; Docket No. 2003-CE-53AD. When Does This AD Become Effective? (a) This AD becomes effective on July 27, 2004. What Other ADs Are Affected by This Action? (b) None. What Sailplanes Are Affected by This AD? (c) This AD affects the following Alexander Schleicher Model ASW 27 sailplanes that are certificated in any category: Serial numbers Condition (1) 27105, 27109, 27110, 27113, 27115, Equipped with integrated (wet inner surface) water ballast 27116, and 27119 through 27177. tanks on the wing at manufacture. (2) 27001 and up Equipped with integrated (wet inner surface) water ballast tanks through wing replacement per Technical Note No. 2. What Is the Unsafe Condition Presented in This AD? (d) This AD is the result of water ballast in the integral wing water ballast tanks that may cause a stronger nose heavy moment than the soft water ballast bags, putting the center-of-gravity (CG) out of acceptable range. To compensate for this, pilots over a certain weight must only use the rearmost backrest position. The actions specified in this AD are intended to correct the forward empty weight CG and prevent loss of sailplane control. What Must I Do To Address This Problem? (e) To address this problem, you must do the following:
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Actions (1) Fabricate (using letters at least 1/8-inch in height) a warning placard with the following language and install this placard in the cockpit in full view of the pilot: ‘‘When water ballast is used, pilots weighing 105 kg (231.5 lbs) or more including parachute must use the rearmost back rest hinge position!’’. (2) Determine the forward empty weight CG (i) If the CG is out of acceptable range, prior to further flight, contact the manufacturer at Alexander Schleicher GmbH & Co., Seglflugzeugbau, D-36163 Poppenhausen, Germany for corrective action and perform the corrective action. (ii) If CG is within acceptable range, no further action is necessary.
Compliance Warning placard must be installed within 25 hours time-in-service (TIS) after July 27, 2004 (the effective date of this AD). Within the next 50 hours TIS after July 27, 2004 (the effective date of this AD).
Procedures Install placard following Alexander Schleicher Technical Note No. 9, dated February 27, 2002. Check forward empty weight of CG following Alexander Schleicher Technical Note No. 9, dated February 27, 2002.
Note: Alexander Schleicher Technical Note No. 9, dated February 27, 2002, changes some pages to the maintenance manual. We recommend that you review those changes. 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, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, MO 64106. For information on any already approved alternative methods of compliance, contact Gregory Davison, Aerospace Engineer, Small Airplane Directorate, ACE-112, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: 816-329-4130; facsimile: 816-3294090. Does This AD Incorporate Any Material by Reference? (g) You must do the actions required by this AD following the instructions in Alexander Schleicher Technical Note No. 9, dated February 27, 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. You may get a copy from Alexander Schleicher GmbH & Co., Seglflugzeugbau, D-36163 Poppenhausen, Germany. 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) LBA AD 2002-086, dated March 7, 2002, and Alexander Schleicher Technical Note No. 9, dated February 27, 2002 also address the subject of this AD. Issued in Kansas City, Missouri, on May 27, 2004. Scott L. Sedgwick, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 04-12574 Filed 6-7-04; 8:45 am] BILLING CODE 4910-13-P 17
