FEDERAL AVIATION ADMINISTRATION AIRWORTHINESS DIRECTIVES SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS BIWEEKLY 2004-10 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
2004-09-30
COR
Cessna Aircraft Company Glasflugel-Ing. E. Hanle Raytheon Aircraft Company Honeywell International Inc.
Raytheon Aircraft Company
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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
BW 2004-10 CESSNA AIRCRAFT COMPANY AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS CORRECTION: [Federal Register: May 3, 2004 (Volume 69, Number 85); Page 24225; www.access.gpo.gov/su_docs/aces/aces140.html] 2004-08-17 Cessna Aircraft Company: Amendment 39-13587; Docket No. 2004-CE-09-AD. When Does This AD Become Effective? (a) This AD becomes effective on May 17, 2004. Are Any Other ADs Affected By This Action? (b) None. What Airplanes Are Affected by This AD? (c) This AD affects the following airplane models and serial numbers that are certificated in any category: Model 208 208B
Serial Numbers 20800370 and 20800371. 208B1034 through 208B1043, 208B1045, 208B1046, and 208B1048.
What Is the Unsafe Condition Presented in This AD? (d) This AD is the result of a report of one airplane having loose and improperly tied nuts on the wing struts upper attachment bolts. We are issuing this AD to detect and correct loose and improperly tied nuts on the wing struts, which could result in an attachment nut coming off the bolt. This could lead to the failure of the wing structure 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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2004-08-17 2
Actions (1) Inspect any upper wing strut attach fitting part number (P/N) MS17826–14 nut for the P/N MS24665–360 cotter pin and any lower wing strut attach fitting P/N MS17826–12 nut for the P/N MS24665–357 cotter pin.
Compliance Within the next 10 hours time-in-service (TIS) after May 17, 2004, the effective date of this AD, unless already done. (2) If any P/N MS24665–360 or P/N Before further flight MS24665–357 cotter pin is not installed: after the inspection in (i) tighten the corresponding nut (P/N paragraph (e)(1) of MS17826–14 or P/N MS17826–12) and align this AD. the castellations of the nut and the cotter pin hole in the bolt; and (ii) install the corresponding P/N MS24665– 360 or P/N MS24665–357 cotter pin
Procedures Follow Cessna Special Service Project No. SSP04– 2, dated April 5, 2004. The applicable airplane maintenance manual also addresses this issue. Follow Cessna Special Service Project No. SSP04– 2, dated April 5, 2004. The applicable airplane maintenance manual also addresses this issue.
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 Paul Nguyen, Aerospace Engineer, FAA, Wichita ACO, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: 316-9464125; facsimile: 816-946-4107. Does This AD Incorporate Any Material by Reference? (g) You must do the actions required by this AD following the instructions in Cessna Special Service Project No. SSP04-2, dated April 5, 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. You may get a copy from Cessna Aircraft Company, Product Support, PO Box 7706, Wichita, Kansas 67277; telephone: (316) 517-5800; facsimile: (316) 942-9006. You may review copies at FAA, Central Region, Office of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 64106; or at the Office of the Federal Register, 800 North Capitol Street, NW, suite 700, Washington, DC. Issued in Kansas City, Missouri, on April 16, 2004. James E. Jackson, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 04-9115 Filed 4-23-04; 8:45 am] BILLING CODE 4910-13-P
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BW 2004-10 GLASFLUGEL-ING. E. HANLE AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2004-09-02 Glasflugel-Ing. E. Hanle: Amendment 39-13591; Docket No. 2003-CE-60-AD. When Does This AD Become Effective? (a) This AD becomes effective on June 18, 2004. What Other ADs Are Affected by This Action? (b) None. What Sailplanes Are Affected by This AD? (c) This AD affects Model GLASFLUGEL Kestrel 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 Germany. The actions specified in this AD are intended to detect and correct damage to the airbrake actuation shaft, which could result in failure of the airbrake control. 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 Compliance (1) Inspect the airbrake Within the next 25 hours time-in-service actuation shaft for cracks and (TIS) after June 18, 2004 the effective date of deformation (damage). this AD. Repetitively inspect thereafter at intervals not to exceed 12 calendar months. (2) Repair or replace any Before further flight after any inspection cracked or deformed airbrake required in paragraph (e)(1) of this AD in actuation shaft found during which damage is found. Continue with any inspection required in repetitive inspections after repairs or paragraph (e)(1) of the AD. replacements are made.
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Procedures Follow H. Streifeneder Technical Note TN 401–26, dated November 22, 2001. Follow H. Streifeneder Technical Note TN 401–26, dated November 22, 2001.
2004-09-02 2
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 H. Streifeneder Technical Note TN 401-26, dated November 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 Hansjorg Streifeneder, Glasfaser-Flugzeug-Service GmbH, Hofener Weg, D-72582 Grabenstetten, Germany; telephone: 07382 1032; facsimile: 07382 1629; email:
[email protected]. 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) Germany AD Number 2002-051, dated March 7, 2002, also addresses the subject of this AD. Issued in Kansas City, Missouri, on April 29, 2004. Scott L. Sedgwick, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 04-10180 Filed 5-6-04; 8:45 am] BILLING CODE 4910-13-P
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BW 2004-10 RAYTHEON AIRCRAFT COMPANY AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2004-09-07 Raytheon Aircraft Company: Amendment 39-13596; Docket No. 95-CE-46-AD. When Does This AD Become Effective? (a) This AD becomes effective on June 14, 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: (1) do not have canted bulkhead Kit No. 129-4005-1 incorporated; and (2) are certificated in any category: Model 1900 1900C 1900C (C12J) 1900D
Serial Nos. UA–1 through UA–3. UB–1 through UB–74 and UC–1 through UC–174. UD–1 through UD–6. UE–1 through UE–113.
What Is the Unsafe Condition Presented in This AD? (d) This AD is the result of numerous reports of multi-site cracks occurring in the canted bulkhead at FS 588.10. We are issuing this AD to detect and correct cracks in the canted bulkhead, which could result in failure of the bulkhead. Failure of the canted bulkhead could lead to loss of rudder and elevator control, which could result in 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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2004-09-07 2
Actions Compliance (1) Inspect the canted Initially inspect at whichever occurs later, bulkhead at Fuselage Station unless already done: Upon the accumulation (FS) 588.10 for fatigue cracks. of 5,000 hours time-inservice (TIS) or within the next 600 hours TIS after June 14, 2004 (the effective date of this AD). If no cracks are found, repetitively inspect thereafter at intervals not to exceed 600 hours TIS until Kit No. 129–4005–1 S is incorporated. When Kit No. 129–4005–1 S is incorporated, no further action is required. (2) If cracks exist or are found Before further flight after the inspection in during any inspection required which the cracks are found or known to in paragraph (e)(1) of this AD, exist. Kit No. 129–4005–1 S must be incorporated. (3) Incorporating Kit No. 129–4005–1 S is the terminating action for the repetitive inspection requirements specified in paragraph (e)(1) of this AD.
Kit No. 129–4005–1 S can be incorporated at any time. When incorporated, no further action is required.
Procedures Follow Raytheon Aircraft Company Mandatory Service Bulletin SB 53–2564, Revision 2, Revised: July, 2003.
Follow Raytheon Aircraft Company Mandatory Service Bulletin SB 53–2564, Revision 2, Revised: July, 2003. Follow Raytheon Aircraft Company Mandatory Service Bulletin SB 53–2564, Revision 2, Revised: July, 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, Wichita Aircraft Certification Office (ACO), FAA. For information on any already approved alternative methods of compliance, contact Steven E. Potter, Aerospace Engineer, Wichita ACO, FAA, 1801 Airport Road, Wichita, Kansas 67209; telephone: (316) 946-4124; facsimile: (316) 946-4407. Does This AD Incorporate Any Material by Reference? (g) You must do the actions required by this AD following the instructions in Raytheon Aircraft Company Mandatory Service Bulletin SB 53-2564, Revision 2, Revised: July, 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 Raytheon Aircraft Company, 9709 E. Central, Wichita, Kansas 67201-0085; telephone: (800) 429-5372 or (316) 6763140. 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 April 21, 2004. Dorenda D. Baker, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 04-9898 Filed 5-4-04; 8:45 am] BILLING CODE 4910-13-P 10
BW 2004-10 HONEYWELL INTERNATIONAL INC. AIRWORTHINESS DIRECTIVE ENGINE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS
2004-09-29 Honeywell International Inc. (formerly AlliedSignal Inc., Garrett Turbine Engine Company, and AiResearch Manufacturing Company of Arizona): Amendment 39-13619. Docket No. 2003-NE-02-AD. Effective Date (a) This airworthiness directive (AD) becomes effective June 15, 2004. Affected ADs (b) None. Applicability (c) This AD applies to Honeywell International Inc. (formerly AlliedSignal Inc., Garrett Turbine Engine Company and AiResearch Manufacturing Company of Arizona) TPE331-10-501C, 10-511C, -10-501K, -10-511K, -10-501M, -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, -10N-535S, -10P-511D, -10R-501C, -10R-502C, -10R-511C, -10R-512C, 10R-513C, -10T-511D, -10T-511K, -10T-511M, -10T-512K, -10T-513K, -10T-515K, -10T-516K, 10T-517K, -10U-501G, -10U-502G, -10U-511G, -10U-512G, -10U-503G, -10U-513G, -10UA511G, -10UF-501H, -10UF-511H, -10UF-512H,-10UF-513H, -10UF-514H, -10UF-515H, -10UF516H, -10UG-513H, -10UG-514H, -10UG-515H, -10UG-516H, -10UGR-513H, -10UGR-514H, 10UGR-516H, -10UR-513H, -10UR-516H, -11U-601G, -11U-602G, -11U-611G, and -11U-612G turboprop engines with first stage turbine disk part number (P/N) 3101520-1 or P/N 3107079-1, with serial numbers (SNs) listed in Table 1 of Honeywell International Inc. Alert Service Bulletin (ASB) TPE331-A72-2102, dated March 28, 2002, installed. These engines are installed on, but not limited to Mitsubishi MU-2B series, Construcciones Aeronauticas S.A. (CASA) C-212 series, Fairchild SA226 series (Swearingen Merlin and Metro series), Twin Commander 680 and 690 series (Jetprop Commander), Dornier 228 series, Beech 18 and 45 series, Beech Models JRB-6, 3N, 3TM, and B100, Cessna Aircraft Company Model 441 Conquest, and Jetstream 3201 series airplanes. Unsafe Condition (d) This AD results from a report of a first stage turbine disk found cracked at the disk bore. We are issuing this AD to prevent cracked first stage turbine disks from causing uncontained disk separation, resulting in engine damage and shutdown and damage to the airplane.
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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 Inspection (f) Perform a fluorescent penetrant inspection (FPI) of first stage turbine disks, P/N 31015201, in accordance with 2.A.(4)(a) through 2.A.(4)(d) of Accomplishment Instructions of ASB TPE331A72-2102, dated March 28, 2002, and the following: (1) For first stage turbine disks with 4,100 cycles-since-new (CSN) or less, inspect at next access, but no later than 4,500 CSN. (2) For first stage turbine disks with more than 4,100 CSN, inspect at next access, but within 400 cycles-in-service (CIS) after the effective date of this AD. (3) First stage turbine disks that pass FPI must be eddy current inspected (ECI) before return to service. Information on procedures for returning disks to Honeywell Engines, Systems, & Services, for ECI, can be found in ASB TPE331-A72-2102, dated March 28, 2002. (4) First stage turbine disks, P/N 3107079-1, do not require initial inspection because they received an initial FPI and ECI at the time of conversion. Repetitive Inspections (g) Perform repetitive FPIs of first stage turbine disks P/N 3101520-1 and P/N 3107079-1, in accordance with 2.B.(3)(a) through 2.B.(3)(d) of Accomplishment Instructions of ASB TPE331-A722102, dated March 28, 2002 and the following: (1) FPI first stage turbine disks at each scheduled hot section inspection. (2) First stage turbine disks that pass FPI must be ECI before they are returned to service. Information on procedures for returning disks to Honeywell Engines, Systems, & Services, for ECI, can be found in ASB TPE331-A72-2102, dated March 28, 2002. Optional Terminating Action (h) Replacing a first stage turbine disk, that has a SN specified in this AD, with a disk that does not have a SN specified in this AD, is terminating action for the repetitive inspection requirements specified in paragraphs (g)(1) through (g)(2) of this AD. Definition (i) For the purposes of this AD, next access is when the turbine wheel assembly is removed from the engine or before installation into an engine. Alternative Methods of Compliance (j) The Manager, Los Angles 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 (k) You must use Honeywell International Inc. ASB TPE331-A72-2102, dated March 28, 2002 to perform the inspections required by this AD. The Director of the Federal Register approved the incorporation by reference of this service bulletin under 5 U.S.C. 552(a) and 1 CFR part 51. You can get the service information identified in this AD from Honeywell Engines, Systems & Services, Technical Data Distribution, M/S 2101-201, P.O. Box 52170, Phoenix, AZ 85072-2170; telephone: (602) 365-2493 (General Aviation); (602) 365-5535 (Commercial); fax: (602) 365-5577 (General Aviation and Commercial). You may examine the service information, 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. Related Information (l) None. Issued in Burlington, Massachusetts, on April 28, 2004. Jay J. Pardee, Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 04-10241 Filed 5-10-04; 8:45 am] BILLING CODE 4910-13-P
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BW 2004-10 RAYTHEON AIRCRAFT COMPANY AIRWORTHINESS DIRECTIVE SMALL AIRCRAFT, ROTORCRAFT, GLIDERS, BALLOONS, & AIRSHIPS 2004-09-30 Raytheon Aircraft Company: Amendment 39-13620; Docket No. 2003-CE-27-AD. When Does This AD Become Effective? (a) This AD becomes effective on June 18, 2004. What Other ADs Are Affected by This Action? (b) None. What Airplanes Are Affected by This AD? (c) This AD affects Model 1900C airplanes, serial numbers UB-1 through UB-35, that are certificated in any category. What Is the Unsafe Condition Presented in This AD? (d) This AD is the result of reports about the inability to automatically lower the landing gear and the inability to operate other related electrical systems. The actions specified in this AD are intended to prevent heat damage to the electrical wiring in and around the landing gear electrical systems components, which could result in the inability to operate critical control systems. This failure 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 Incorporate Kit No. 114–3036–1, which replaces the 200-amp landing gear electrical power current limiter with a 60-amp circuit breaker.
Compliance Within the next 600 hours timein-service (TIS) after June 18, 2004 (the effective date of this AD), unless already done.
Procedures Following the procedures in Raytheon Mandatory Service Bulletin SB 24–2616, Rev. 1, Revised: April, 2002.
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
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Manager, Wichita Aircraft Certification Office (ACO), FAA. For information on any already approved alternative methods of compliance, contact Bryan Easterwood, Aerospace Engineer, Wichita ACO, FAA, 1801 Airport Road, Wichita, Kansas 67209; telephone: (316) 946-4132; facsimile: (316) 946-4107. Does This AD Incorporate Any Material by Reference? (g) You must do the actions required by this AD following the instructions in Raytheon Aircraft Mandatory Service Bulletin SB 24-2616, Rev. 1, Revised: April, 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 Raytheon Aircraft Company, 9709 E. Central, Wichita, Kansas 67201-0085; telephone: (800) 429-5372 or (316) 676-3140. 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 April 29, 2004. Scott L. Sedgwick, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 04-10179 Filed 5-10-04; 8:45 am] BILLING CODE 4910-13-P
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