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2015-25-05: We are adopting a new airworthiness directive (AD) for certain [[Page 80237]] Bombardier, Inc. Model CL-600-2A12 (CL-601) and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604 Variants) airplanes. This AD was prompted by a report of an aft equipment bay fire due to chafing and subsequent arcing of the integrated drive generator (IDG) power cables. Additionally, we have received several reports of broken support brackets of the hydraulic line. This AD requires a one-time inspection of the IDG power cables for chafing, and for any cracked or broken support bracket of the hydraulic line; and corrective actions if necessary. We are issuing this AD to detect and correct broken support brackets of the hydraulic lines, which could result in inadequate clearance between the IDG power cables and hydraulic lines and chafing of the IDG power cables, and consequent high energy arcing and an uncontrolled fire in the aft equipment bay.
2023-09-01: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A318 series airplanes; Model A319 series airplanes; Model A320-211, -212, -214, -216, -231, -232, -233, -251N, -252N, - 253N, -271N, -272N, and -273N airplanes; and Model A321 series airplanes. This AD was prompted by a report that certain overheat detection system (OHDS) sensing elements installed at certain positions might not properly detect thermal bleed leak events due to a quality escape during the manufacturing process. This AD requires a one-time detailed inspection of each affected part installed at an affected position and replacement if necessary, and prohibits the installation of affected parts at affected positions, 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.
87-24-09: 87-24-09 BOEING: Amendment 39-5777. Applies to Model 747 and Model 767 series airplanes, specified in Boeing Service Bulletins 747-34A2286 dated April 30, 1987, and 767- 34A0055, Revision 1, dated September 17, 1987, certificated in any category. Compliance required within 12 months after the effective date of this AD, unless previously accomplished. \n\n\tTo minimize the possibility of misleading localizer deviation indication to the flight crew caused by electromagnetic interference, accomplish the following: \n\n\tA.\tReplace the existing weather radar receiver-transmitters with modified receiver- transmitters in accordance with the appropriate Boeing Service Bulletin 747-34A2286, or 767- 34A0055, both dated April 30, 1987, or later FAA-approved revision. \n\n\tB.\tAn alternate means 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, FAA, Northwest Mountain Region. \n\n\tC.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the modification required by this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124-2207. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment becomes effective December 29, 1987.
2022-19-02: The FAA is superseding Airworthiness Directive (AD) 2016-10- 08, AD 2017-05-10, and AD 2019-01-05, which applied to certain Airbus SAS Model A330-200, -200 Freighter, and -300 series airplanes; and AD 2019-20-13, which applied to certain Airbus SAS Model A330-200, A330- 200 Freighter, A330-300, A340-200, A340-300, A340-500, and A340-600 series airplanes. AD 2016-10-08 required determining the flight cycles accumulated on certain trimmable horizontal stabilizer actuators (THSAs), and replacing the THSA if necessary. AD 2017-05-10, AD 2019- 01-05, and AD 2019-20-13 required revising the existing maintenance or inspection program, as applicable. 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 additional 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.
2015-25-02: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200, -200 Freighter, and -300 series airplanes; and all Airbus Model A340-200, -300, -500, and -600 series airplanes. This AD was prompted by reports of cracks at certain frames of the forward cargo door. This AD requires a detailed inspection for cracking of certain forward cargo doors, and repair if necessary. We are issuing this AD to detect and correct cracking at certain frames, which could result in the loss of structural integrity of the forward cargo door.
85-07-06: 85-07-06 WESTLAND HELICOPTERS LIMITED: Amendment 39-5019. Applies to Westland 30 helicopters certificated in all categories that are equipped with main rotor tie-bar pin Part Number (P/N) WK 3069-0020-101 or WK 3069-0016-101. Compliance is required as indicted, unless already accomplished. To prevent cracking of the main rotor blade sleeve tie-bar pin and possible loss of a main rotor blade, accomplish the following: (a) Within 50 hours time in service after the effective date of this AD or prior to attaining 500 hours total time in service, whichever occurs later, remove tie-bar pins before further flight. (b) An equivalent method of compliance with this AD may be used when approved by the Manager of the Brussels Aircraft Certification Office, Brussels, Belgium. (c) Special flight permits may be issued in accordance with FAR Sections 21.197 and 21.199 to ferry aircraft to a maintenance base in order to comply with the requirements of this AD. Alert Service Bulletin W30-05-A38, Rev. 1 dated February 26, 1985, pertains to this subject. This amendment becomes effective April 9, 1985.
2015-25-07: We are superseding Airworthiness Directive (AD) 2008-09-01 for certain Alpha Aviation Concept Limited Model R2160 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued 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 a need to revise the maintenance program to include the revised airworthiness limitations for the internal wing structure and wing attachment inspections. We are issuing this AD to require actions to address the unsafe condition on these products.
56-20-05: 56-20-05 DOUGLAS: Applies to All DC3 Series, DC-4 and C54-DC Series Aircraft Powered With Pratt & Whitney Military R-2000 and Twin Wasp D Series Engines. \n\n\tCompliance required not later than December 1, 1956. \n\n\tTo avoid crankshaft bending failures, the following placard must be placed on the instrument panel in a conspicuous place: "Avoid Continuous Operation of the Engines between 2310 and 2510 r.p.m." The tachometers must be marked with a red radial band in the above range. \n\n\tThis supersedes AD 48-03-01, which applied only to DC-4 airplanes.
2002-18-06: This amendment supersedes an existing airworthiness directive (AD), applicable to Eurocopter France (ECF) Model AS332C, L, and L1 and Model SA330F, G, and J helicopters, that currently requires an inspection to determine the angular play of the tail rotor gearbox (gearbox) at specified intervals. This amendment changes the measurement limits and the load to be applied to a tail rotor blade (blade) when determining the angular play. This amendment is prompted by a review of design data and a determination that the amount of play can be increased with an increase in the amount of applied load during the inspection. The actions specified by this AD are intended to detect excessive angular play and to prevent failure of a gearbox, loss of tail rotor drive, and subsequent loss of control of the helicopter.
85-12-08: 85-12-08 BOEING: Amendment 39-5081. Applies to Boeing Model 757-200 series airplanes, certificated in all categories, listed in Boeing Service Bulletins 757-38-008 dated February 1, 1985, and 757-24-0025 dated May 3, 1985. To prevent the electrical shorting of certain wire bundles due to damaged wire and leaking lavatory waste fluids onto the wire, accomplish the following within the next 50 hours time in service after the effective date of this AD, unless already accomplished: \n\n\tA.\tPerform a visual inspection of the forward lavatory waste drain ducts, to determine if there is any leakage from the duct seals. Repeat the inspection at intervals not to exceed 100 hours time in service. \n\n\tB.\tIf leaks are detected, clean and replace forward lavatory waste drain clamps in accordance with Boeing Service Bulletin 757-38-008, dated February 1, 1985, or later FAA approved revision, and continue to inspect in accordance with paragraph A. at intervals not to exceed 250 hours time inservice. \n\n\tC.\tIncorporation of Boeing Service Bulletin 757-38-008 dated February 1, 1985, or later FAA approved revision, to replace specified narrow clamps with wider clamps on the forward lavatory waste ducts, and incorporation of Boeing Service Bulletin 757-24-0025 dated May 3, 1985, or later FAA approved revision, to replace the damaged wire and to reroute the specified wire bundles from beneath the lavatories, terminates the repetitive inspection requirement of paragraph A., above. \n\n\tD.\tAlternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tE.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD.\n \n\tAll persons affected by this proposal who have not already received copies of the service bulletins may obtain copies upon request from the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, 1900 Pacific Highway South, Seattle, Washington, or 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment becomes effective June 28, 1985.