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81-09-06: 81-09-06 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE: Amendment 39- 4161. Applies to Model AS350 series helicopters certificated in all categories which have Bevel Gear Module P/N 350A32.0300.00 or -.01 installed, except bevel gear modules which include nitrided shaft P/N 350A32.3107.23 or -.24. (Bevel Gear Module P/N 350A32.0300.02 includes nitrided shaft, P/N 350A32.3107.23 or -.24 and is exempt from this application.) Compliance required as follows, unless already accomplished: a. For bevel gear modules with 580 or more hours' time in service since new or last overhaul, comply within 20 hours time in service after the effective date of this AD, or b. For bevel gear modules with less than 580 hours' time in service since new or last overhaul on the effective date of this AD, comply prior to accumulation of 600 hours' time in service, and c. Thereafter at intervals not to exceed 300 hours' time in service. To prevent loss of mechanical drive between the bevel gear module and the epicyclic module of the main transmission gearbox, inspect the bevel gear module for wear in accordance with procedures specified in paragraph EE of Aerospatiale TELEX Service No. 05.05 (TELEX No. 22316) dated December 24, 1980, or paragraph BB of Aerospatiale TELEX Service No. 05.06 as it applies to measuring actual spline wear, or other FAA approved equivalent. If the maximum wear depth at the level of the step on the spline exceeds 1.0 mm (0.039 inch) or if the distance between two rods of 6.35 mm (.250 inch) exceeds 72.2 mm (2.84 inches), the bevel gear module must be replaced with a serviceable module before further flight. Report defects to the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium. Reporting approved by the Office of Management and Budget under OMB No. 04-R0174. Special flight permits may be issued in accordance with FAR 21.197 and FAR 21.199 to fly aircraftto a base where this AD can be accomplished. Equivalent methods of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration, P.O. Box 1689, Fort Worth, Texas 76101, or by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belguim. NOTE: Aerospatiale TELEX 22316, paragraph EE, is as follows: EE. Remove main rotor mast and sun gear according to Work Cards 65 13 401 and 65 30 404. Check the wear of vertical shaft splines either by mold print, (maximum wear depth at the level of the step, 1mm (0.039 inches)) or by measurement of distance between two rods of 6.35 mm diameter. Distance between two opposite rods shall be less than 72.2 mm. If the value obtained by either one of the above methods is out of limit, return bevel gear module to an approved repair station. This AirworthinessDirective supersedes AD 81-01-05. This amendment becomes effective July 23, 1981, for all persons except those to whom it was made immediately effective by priority mail AD No. 81-09-06 dated April 23, 1981.
2020-07-17: The FAA is adopting a new airworthiness directive (AD) for all Saab AB, Support and Services Model SAAB 2000 airplanes. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
92-15-01: 92-15-01 BEECH: Amendment 39-8294. Docket No. 92-CE-18-AD. Applicability: The following model and serial numbered airplanes, certificated in any category: Models Serial Numbers T-34C GP-1 through GP-50, GL-1 through GL-353, and GM-2 through GM-98 65-90, 65-A90, 65-A90-1, 65-A90-2, 65-A90-3, 65-A90-4, B90, C90, C90A, E90, F90, and H90 LJ-1 through LJ-1285, LW-1 through LW-347, LA-2 through LA-236, LM-1 through LM-141, LS-1, LS-2, LS-3, LT-1, LT-2, LU-1 through LU-15, and LL-1 through LL-61 99, 99A, A99A, B99, and C99 U-1 through U-239 100, A100, and B100 B-1 through B-247 and BE-1 through BE-137 200, 200C, 200CT, 200T, A200, A100-1, A200CT, B200, B200C, B200CT, and B200T BB-2 through BB-1405, BC-1 through BC-75, BD-1 through BD-30, BJ-1 through BJ-66, BL-1 through BL-137, BN-1 through BN-4, BP-1 through BP-71, BT-1 through BT-33, BU-1 through BU-12, BV-1 through BV-12, FC-1, FC-2, FC-3, FE-1 through FE-9, FG-1, and FG-2 300, 300C, B300, and B300C FA-1 through FA-217, FF-1 through FF-19, FL-1 through FL-60, and FM-1 Compliance: Required as indicated, unless already accomplished. To prevent undetected failure of engine truss-to-firewall bolts, which could eventually lead to separation of the engine mount from the airplane, accomplish the following: (a) Within the next 150 hours time-in-service after the effective date of this AD, accomplish the following: (1) Individually remove each engine truss-to-firewall bolt and determine whether the bolt is manufactured by Dumont Aviation as specified by Figure 2 of, and in accordance with paragraphs 1 and 2 of the ACCOMPLISHMENT INSTRUCTIONS section of, Beech Service Bulletin (SB) No. 2432, dated February 1992. Only one engine truss-to-firewall bolt shall be removed at any given time. (2) Prior to further flight, replace any bolt manufactured by Dumont Aviation as identified in paragraph (a)(1) of this AD with a new bolt part number (P/N) MS20006-20 /M/. NOTE 1: The inspection of the engine truss-to-firewall bolts and associated hardware for corrosion that is referenced in Beech SB No. 2432, dated February 1992, is recommended but is not required by this AD. (b) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (c) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Mid-Continent Airport, Wichita, Kansas 67209. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Wichita Aircraft Certification Office. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita Aircraft Certification Office. (d) The inspection required by this AD shall be done in accordance with Beech Service Bulletin No. 2432, dated February 1992. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from the Beech Aircraft Corporation, P.O. Box 85, Wichita, Kansas 67201-0085. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 1100 L Street, NW; Room 8401, Washington, DC. (e) This amendment becomes effective on August 21, 1992.
96-11-01: This amendment adopts a new airworthiness directive (AD) that applies to Jetstream Aircraft Limited (JAL) Jetstream Models 3101 and 3201 airplanes. This action requires modifying the automatic airframe de-ice system to allow the wing and tail de-ice boots to automatically operate through one cycle. The present system repeats the wing de-ice boot inflation cycle before starting to inflate the tail de-ice boots. Reports of ice accumulating on the tail faster than the automatic tail de-ice boots inflate on the affected airplanes prompted this action. The actions specified by this AD are intended to prevent excessive ice accretion on the tail or wings of the affected airplanes, which could result in loss of control of the airplane.
91-21-03: 91-21-03 MCDONNELL DOUGLAS: Amendment 39-8050. Docket No. 91-NM-74-AD. \n\n\tApplicability: Model DC-9 series airplanes, listed in Heath Tecna Service Bulletin ESCI-25-A1, dated April 30, 1990, certificated in any category. \n\n\tCompliance: Required within 18 months after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent the occurrence of fire and smoke in the passenger cabin, accomplish the following: \n\n\t(a)\tVisually inspect the electrical wiring along the left and right overhead stowage compartment rail assemblies in the vicinity of each electrical bonding strap for evidence of arcing, burning, or chafing. If damage is found, prior to further flight, repair in accordance with McDonnell Douglas DC-9 Maintenance Manual, Chapters 20-50-01 and 20-50-02. \n\n\t(b)\tModify the electrical bonding strap installation of the left and right overhead stowage compartment rail assemblies in accordance with Heath Tecna Aerospace Co. Alert Service Bulletin ESCI-25-A1, dated April 30, 1990. \n\n\t(c)\tAn alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Seattle ACO. \n\n\t(d)\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. \n\n\t(e)\tThe modification requirements of this rule shall be done in accordance with Heath Tecna Aerospace Company Alert Service Bulletin ESCI-25-A1, dated April 30, 1990. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Heath Tecna Aerospace Company, 19819 84th Avenue South, Kent, Washington 98032. Copies may be inspected at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington, or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. \n\n\tThis amendment (39-8050, AD 91-21-03) becomes effective on November 29, 1991.
2008-10-08: The FAA is superseding an existing airworthiness directive (AD) that applies to certain EMBRAER Model EMB-135 airplanes; and Model EMB-145, -145ER, -145MR, -145LR, -145XR, -145MP, and -145EP airplanes. The existing AD currently requires performing repetitive inspections for cracks, ruptures, or bends in certain components of the elevator control system; replacing discrepant components; and, for certain airplanes, installing a new spring cartridge and implementing new logic for the electromechanical gust lock system. The existing AD also requires eventual modification of the elevator gust lock system to replace the mechanical system with an electromechanical system, which terminates the repetitive inspections. This AD reduces the compliance time for doing the modification. This AD results from additional reports of failure of the mechanical gust lock system to protect the elevator control surfaces and components from high wind gusts. We are issuing this AD to prevent discrepancies in the elevator control system, which could result in reduced control of the elevator and consequent reduced controllability of the airplane. DATES: This AD becomes effective May 23, 2008. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of May 23, 2008. On February 3, 2006 (70 FR 77303, December 30, 2005), the Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD. We must receive any comments on this AD by June 9, 2008.
2008-05-18: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Subsequent to accidents involving Fuel Tank System explosions in flight * * * and on ground, * * * Special Federal Aviation Regulation 88 (SFAR88) * * * required a safety review of the aircraft Fuel Tank System * * *. * * * * * Fuel Airworthiness Limitations are items arising from a systems safety analysis that have been shown to have failure mode(s) associated with an `unsafe condition' * * *. These are identified in Failure Conditions for which an unacceptable probability of ignition risk could exist if specific tasks and/or practices are not performed in accordance with the manufacturers' requirements. We are issuing this AD to require actions to correct the unsafe condition on these products.
2020-07-18: The FAA is superseding Airworthiness Directive (AD) 2017-05- 12, which applied to certain Airbus SAS Model A318-112 airplanes; Model A319-111, -112, -115, -132, and -133 airplanes; Model A320-214, -232, and -233 airplanes; and Model A321-211, -212, -213, -231, and -232 airplanes. AD 2017-05-12 required a one-time eddy current conductivity measurement of certain cabin, cargo compartment, and frame structural parts to determine if aluminum alloy with inadequate heat treatment was used, and replacement if necessary. This AD retains the requirements of AD 2017-05-12, and for certain airplanes, requires additional work, as specified in a European Union \n\n((Page 21760)) \n\nAviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by a determination that aluminum alloy with inadequate heat treatment had been used for additional structural parts. The FAA is issuing this AD to address the unsafe condition on these products.
81-15-03: 81-15-03 (BRACKETT AIRCRAFT COMPANY, INC. Brackett Aircraft Specialties, Inc.): Amendment 39-4160. Applies to Brackett Aircraft Company, Inc., engine inlet air filters installed in accordance with Supplemental Type Certificate (STC) SA693CE and STC SA71GL on the following aircraft: \n\n\tBeech A65, 70, 65-B80, 65-88, C-23, A-24R, and B-24R; Bonanza 33, 35, and 36, all models; Cessna Model 120, 140, 140A, 150, 150B, 150C, 150D, 150E, 150F, 150G, 150H, 150J, 150K, 150L, 150M, A150L, and A150M, 170, 170A, 170B, 172, 172A, 172B, 172C, 172D, 172E, 172F, 172G, 172H, 172I, 172K, 172L, and 172M, 177, 177A, 177B, 177RG, and F177RG, 180C, 180D, 180E, 180F, 180G, 180H, 180J, 180K, 182B, 182C, 182D, 182E, 182F, 182G, 182H, 182J, 182K, 182L, 182M, 182N, 182P, 182Q, 185, 185A, 185B, 185C, 185D, 185E, and A185F, 210A, B, C, D, E, and 310A, B, C, D, F, G, H, I, J, K, L; Consolidated Aeronautics (Lake) LA4-200; Grumman American Model AA-1, AA-1A, AA-1B, and AA-5; Mooney M18C, M20, M20A, M20B, M20C, M20D, and M20G; Piper Model PA-20, PA-20-115, and PA-20-135, PA-23-150, 160, PA-24-180 to S/N 1477, PA31, 31-300, 31-350; and Varga (Shinn) Model 2150A, certificated in all categories. \n\n\tCompliance required as indicated, unless already accomplished. \n\n\tTo prevent possible failure of the aluminum air filter retainer screen or gaskets with potential ingestion of the screen, filter element and/or gasket particles into the carburetor throat, which could result in partial or complete loss of engine power, accomplish the following: \n\n\t(a)\tWithin 25 hours of time in service after the effective date of this AD, inspect aircraft as identified in Brackett Service Bulletin No. 3, Revision 1, dated March 1, 1979, or No. 6, Revision 1, dated June 29, 1981, as applicable, equipped with the Brackett Aircraft Company, Inc. engine inlet air filters, to determine \n\n\t\t(1)\twhether the air filter retainer screen is aluminum or steel, and \n\n\t\t(2)\twhether or not certain air filter frames incorporate a gasket retainer. Brackett filter assemblies Part Number BA 100, BA 2310, BA5710, BA 7110, BA 7210, BA 7310, BA 7410 and BA 7510 are required to have a gasket retainer incorporated. The gasket retainer may be a gasket retainer strip kit installed in accordance with Brackett Service Bulletin No. 5, dated July 28, 1980, or an extruded lip which is 1/32 inch high and an integral part of the filter frame furnished by Brackett Aircraft Company, Inc. \n\n\tNOTE: The aluminum air filter retainer screen can be identified by any one of the following: \n\n\t\tThe screen has diamond shaped mesh with openings 1-3/4 inch x 3/4 inch; aluminum screen is not magnetic; the date of manufacture was ink stamped on each retainer and may still be legible. Only retainers dated August 1978 and earlier have aluminum mesh screen. \n\n\tNOTE: The steel retainer screen can be identified by any one of the following: \n\n\t\tThe screen is 1/8 inch diamond mesh; the screen is magnetic; date of manufacture is ink stamped on each retainer and may still be legible. Retainers dated September 1978 and later have steel mesh screen. \n\n\t(b)\tA determination that the air filter retainer screen is steel and that a gasket retainer is incorporated in the filter frame constitutes terminating action for this AD. \n\n\t(c)\tUpon determination that the retainer screen is aluminum, visually inspect the aluminum retainer assembly for cracks or failed areas. \n\n\t\t(1)\tIf cracks or failed areas are found, prior to further flight, replace the aluminum retainer screen assembly with a steel screen assembly kit in accordance with Brackett Service Bulletin No. 3, Revision 1 dated March 1, 1979 or No. 6, Revision 1 dated June 29, 1981, as applicable. Each model air filter requires that a different Brackett kit be installed to comply with this AD. \n\n\t\t(2)\tIf cracks or failed areas are not found, the air filter assembly may be temporarily returned to service. Remove retainers with aluminum screen from service priorto the accumulation of 100 hours additional time in service. \n\n\t(d)\tAfter the inspection required in Paragraph (a) and upon determination that a gasket retainer is not incorporated in the filter retainer, prior to the accumulation of 25 additional hours of service, install gasket retainer strips in accordance with Brackett Service Bulletin No. 5 dated July 28, 1980. \n\n\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate aircraft to a base for the accomplishment of inspections or modifications required by this AD. \n\n\tAlternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Engineering and Manufacturing Branch, FAA Western Region. \n\n\tThe manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive, who have not already received these documents from the manufacturer, may obtain copies upon request to: Brackett Aircraft Company, Inc., 5015 Roadrunner Drive, Falcon Field, Mesa, Arizona 85205. These documents may also be examined at: FAA Western Region Office, 15000 Aviation Boulevard, Hawthorne, California 90261 and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. 20591. A historical file on this AD, which includes the incorporated material in full, is maintained by the FAA at its Headquarters in Washington, D.C. and at FAA Western Region Office. \n\n\tThis supersedes AD 78-25-05, Amendment 39-3365 (43 FR 57865). \n\n\tThis amendment becomes effective July 20, 1981.
2020-08-10: The FAA is adopting a new airworthiness directive (AD) for Robinson Helicopter Company (Robinson) Model R44 and R44 II helicopters. This AD was prompted by reports of cracking in certain tail rotor blades. This AD requires visually checking each tail rotor blade for a crack. The FAA is issuing this AD to address the unsafe condition on these products.