Results
2001-09-13: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 767-200, -300, and -300F series airplanes. This action requires inspections for fatigue cracking of the horizontal stabilizer pivot bulkhead, and repetitive inspections or other follow-on actions. This action also provides a permanent repair, which is optional for airplanes with no cracks, and, if accomplished, ends the repetitive inspections. This action is necessary to find and fix fatigue cracking of the horizontal stabilizer pivot bulkhead and adjacent structure, which could result in loss of the horizontal stabilizer. This action is intended to address the identified unsafe condition.
90-20-03: 90-20-03 WYTWORNIA SPRZETU KOMUNIKACYJNEGO PZL-MIELEC: Amendment 39-6723. Docket No. 90-CE-16-AD. Applicability: Models M18 and M18A (Dromader) (Serial Numbers 1Z00-101 through 1Z021-07) airplanes, certificated in any category. Compliance: Required within the next 50 hours time-in-service (TIS) after the effective date of this AD and thereafter at intervals of 500 hours TIS until the aileron hinge is replaced with improved parts, unless already accomplished. To prevent failure of the aileron control system, accomplish the following: (a) Visually inspect with a 5x magnifying glass, or with fluorescent penetrant or magnetic crack detection methods, as appropriate, all aileron control system hinges for cracks and deformation in accordance with the instructions in PZL-Mielec, Mandatory Engineering Bulletin (MEB) No.K/02.132/89, approved September 7, 1989; Revised April 4, 1990. (1) If cracks or damage are found on any aileron hinge, prior to further flight remove the aileron and replace the aileron hinge with an aileron hinge having Engineering Change Notice (ECN) 9183 or ECN 9187, incorporated in accordance with the MEB referenced in paragraph (a) of this AD. (2) If no cracks or damage are found to any aileron hinge, repeat the above inspection every 500 hours TIS until all aileron hinges are replaced with an aileron having ECN 9183 or ECN 9187, incorporated in accordance with the MEB referenced in paragraph (a) of this AD. (b) The airplane may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (c) An alternate method of compliance or adjustment of the initial or repetitive compliance times, which provides an equivalent level of safety, may be approved by the Manager, Brussels Aircraft Certification Office, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, B-1000 Brussels, Belgium; Telephone (322) 513.38.30 extension 2710/2711; Facsimile (322) 230.05.34. NOTE:The request should be forwarded through an FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Office. All persons affected by this directive may obtain copies of the document referred to herein upon request to Wytwornia Sprzetu Komunikacyjnego PZL-Mielec 39-301 Mielec, Poland; or may examine this document at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. This amendment (39-6723, AD 90-20-03) becomes effective on October 17, 1990.
94-06-03: This amendment adopts a new airworthiness directive (AD), applicable to General Electric Company (GE) CF6-80C2 series turbofan engines, that requires an inspection for cracks in the stage 1 high pressure turbine (HPT) disk rim bolt holes, and replacement, if necessary, with serviceable parts. This amendment is prompted by a report of an uncontained stage 1 HPT disk failure which resulted in an aborted takeoff. The actions specified by this AD are intended to prevent an uncontained stage 1 HPT disk failure, which could result in an inflight engine shutdown, rejected takeoff, or damage to the aircraft.
2007-23-10: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737-600, -700, -700C, -800 and -900 series airplanes. This AD requires an inspection of the fillet sealant at the inboard and outboard sides of the receptacles in the wheel wells of the main landing gear, and related investigative/corrective actions if necessary. This AD results from reports of in-production airplanes with missing or insufficient fillet sealant around the receptacles at the disconnect bracket. We are issuing this AD to prevent corrosion damage due to missing or insufficient fillet sealant. Such corrosion could result in insufficient electrical bonding between the connectors and the disconnect bracket, and consequent loss of the shielding that protects the wire bundles from lightning, electromagnetic interference (EMI), and high intensity radiated field (HIRF). Loss of lightning, EMI, and HIRF protection at those receptacles could cause failure of multiple electrical systems and subsequent loss of several critical control systems that are necessary for safe flight. In addition, a lightning strike could cause arcing in the fuel tank; this potential ignition source, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
2001-09-11: This amendment supersedes an existing airworthiness directive (AD) that applies to certain serial-numbered Bell Helicopter Textron, Inc. (Bell) Model 412 helicopters and Agusta S.p.A. (Agusta) Model AB412 helicopters. That AD currently requires a temporary reduction of the never-exceed velocity (Vne) limitation until an inspection of the tail rotor yoke (yoke) assembly for fatigue damage and installation of a redesigned yoke flapping stop are accomplished. Recurring periodic and special inspections to detect occurrences of yoke overload are also required. This amendment requires the same actions as the previous AD but expands the applicability of the AD to all Bell Model 412, 412CF, 412EP, and Agusta Model AB412 helicopters. This amendment is prompted by the determination that the unsafe condition exists on all Bell Model 412 and all Agusta Model AB412 helicopters, regardless of serial number. The actions specified by this AD are intended to prevent static and dynamic overloaddamage to the yoke that could result in loss of the tail rotor and subsequent loss of control of the helicopter. The incorporation by reference of certain publications listed in the regulations was approved previously by the Director of the Federal Register as of April 8, 1998 (63 FR 14026, March 24, 1998), as corrected on July 20, 1998 (63 FR 38742).
2019-23-18: The FAA is adopting a new airworthiness directive (AD) for all Dassault Aviation Model MYSTERE FALCON 50, MYSTERE FALCON 900, and FALCON 900EX airplanes; and Model FALCON 2000 and FALCON 2000EX airplanes. This AD was prompted by a report that the Dassault maintenance planning document (MPD) of the related Dassault aircraft maintenance manual (AMM) states that the ``combined service/storage life'' of the fire extinguisher percussion cartridges is longer than it should be, and could have a safety impact in case of fire. This AD requires replacing the fire extinguisher percussion cartridges with serviceable parts. The FAA is issuing this AD to address the unsafe condition on these products.
92-15-11: 92-15-11 PRATT & WHITNEY CANADA: Amendment 39-8305. Docket No. 91-ANE-06. Applicability: Pratt & Whitney Canada (PWC) PT6A-6, PT6A-6/C20, PT6A-20, PT6A-20A, PT6A-21, PT6A-27, PT6A-28, PT6A-34, PT6A-34B, and PT6A-36 turboprop engines installed on Beech Aircraft Corporation Models 65-90, 65-A90, 65-A90-1, 65-A90-2, 65-A90-3, 65-A90-4, 99, 100, 99A, B90, C90, C90A, E90, H90, A99, A99A, B99, and C99 aircraft. Compliance: Required within the next 180 days after the effective date of this AD, unless accomplished previously. To prevent excessive engine acceleration time that could result in an aircraft's inability to safely perform the balked landing maneuver required by Federal Aviation Regulations (FAR) part 23, paragraphs 23.75(d), 23.77 and 23.143(a)(5), accomplish the following: (a) Perform a visual inspection to determine if a compressor delivery air line (P3) filter assembly has been installed on the engine. NOTE: The compressor delivery air line assembly may have been installed on the engine as original equipment, or may have been installed per any of the following PWC Service Bulletins: 1205, 1253, 1290, 1294, 1330, 1343, or 1378. (b) Remove from service, if installed, the P3 filter assembly. NOTE: The engine compressor delivery air line assembly can be returned to an approved configuration without a P3 filter. For information, refer to the applicable PWC Maintenance Manual and Parts Catalog. (c) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Engine Certification Office, FAA, Engine and Propeller Directorate. The request should be forwarded through an FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained fromthe Engine Certification Office. (d) 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. (e) This amendment becomes effective on August 17, 1992.
2007-23-05: 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.
94-06-04: This amendment adopts a new airworthiness directive (AD), applicable to EROS series MF10-( )-( ) full face quick donning mask regulators, that requires replacement of the face piece and the mask shell securing screw. This amendment is prompted by reports of the plastic pin breaking which secures the mask shell with the face piece. The actions specified by this AD are intended to prevent the failure of the pin securing the mask shell to the face piece, which could result in a mask leaking oxygen and the crew losing consciousness.
2001-09-08: This amendment adopts a new airworthiness directive (AD), applicable to all CASA Model CN-235 series airplanes, that requires installing a second electrical connector in the electrical Master Central Unit. The actions specified by this AD are intended to prevent the loss of electrical power, other than that provided by the emergency system, in the event of disconnection of the single electrical connector within the electrical Master Central Unit. This action is intended to address the identified unsafe condition.