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81-05-02: 81-05-02 AVIONS MARCEL DASSAULT - BREGUET AVIATION: Amendment 39-4048. Applies to all Model Falcon 10 airplanes certificated in all categories. Compliance required as indicated. To prevent overheating of the air conditioning system - freon compressor motor starting resistor and thus avoid the attendant potential fire hazard accomplish the following, unless already accomplished: Prior to May 1, 1981, remove the compressor motor starting resistor and thermostat, and install a time-delay device in the starting system in accordance with Avions Marcel Dassault- Breguet Aviation Service Bulletin No. F10 0177, dated December 5, 1978, or later FAA- approved revisions, or in a manner acceptable to the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Region. The 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 the addresses listed above. These documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. This amendment supersedes AD 78-22-03. This amendment becomes effective March 2, 1981.
2012-03-08: We are superseding an existing airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700, 701, & 702), CL-600-2D15 (Regional Jet Series 705), and CL-600- 2D24 (Regional Jet Series 900) airplanes. That AD currently requires repetitive detailed inspections for cracking or deformation, or pulled or missing fasteners, on the lower panel of the left- and right-hand main landing gear (MLG) doors, as applicable, and corrective actions if necessary. That AD also reduces the repetitive inspection interval for certain airplanes. This new AD adds a new modification of the MLG door configuration, and removes certain airplanes from the applicability. This AD was prompted by further analysis of the MLG door by the manufacturer. We are issuing this AD to prevent failure of the lower panel of the MLG door, departure of the lower panel from the airplane, and consequent damage to airplane structure, which could adversely affect the airplane's continuedsafe flight and landing.
97-18-06: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 737 series airplanes, that requires revising the FAA-approved maintenance program to prohibit the use of pressure washing within the wheel well or on the landing gear and to prohibit the use of pumps and/or nozzles for washing wheel wells or the landing gear; or incorporation of a certain Temporary Revision to the Boeing Airplane Maintenance Manual into the FAA-approved maintenance program. This amendment is prompted by a review of the design of the flight control systems on Model 737 series airplanes. The actions specified by this AD are intended to prevent corrosion of certain equipment due to the use of inappropriate pressure washing techniques. Corrosion of bearings, cables, electrical connectors, or other equipment in the main wheel well, if not detected and corrected in a timely manner, could result in reduced controllability of the airplane.
79-19-06: 79-19-06 CESSNA AIRCRAFT COMPANY: Amendment 39-3558. Applies to Cessna Model 210L, Model T210L, Serial Numbers 21061040 and subsequent, Model 210M, Model T210M and Model P210N series airplanes modified to incorporate Symbolic Displays, Inc. fuel flow indicating system per STC SA3835WE. Compliance required within 25 hours' time-in-service or thirty (30) days from the effective date of this AD, whichever occurs first, unless already accomplished. To prevent a possible fuel leak caused by the installation of Symbolic Displays, Inc. fuel flow indicating system per STC SA3835WE accomplish the following: (a) Inspect the fuel flow transducer installation on the upper left side of the engine near the fuel distributor manifold. (b) If a 4 inch long flexible hose (Aeroquip P/N AE7010001E0040 or Stratoflex P/N 111D417-4S-0040) is installed between the transducer and the fuel distributor, no further action is required per this AD. (c) If an NAS 424-4 coupling is installed between the fuel flow transducer and the fuel distributor, remove and replace the coupling with hose assembly Aeroquip Part Number AE7010001E0040 or hose assembly Part Number 111D417-4S-0040 (Stratoflex). NOTE: Symbolic Displays, Inc. Service Information Bulletin No. 72 dated June 15, 1979 and Installation Diagram Drawing No. 204724, Revision "B," pertain to this matter. (d) Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. This amendment becomes effective September 17, 1979.
2012-04-06: We are adopting a new airworthiness directive (AD) for all 328 Support Services GmbH (Type Certificate Previously Held by AvCraft Aerospace GmbH; Fairchild Dornier GmbH; Dornier Luftfahrt GmbH) Model 328-100 airplanes. This proposed AD was prompted by several runway excursion incidents and a single accident where the power lever could not be operated as intended during the landing roll-out on Model Dornier 328-100 airplanes. This proposed AD would require a modification of the engine control box assembly. We are proposing this AD to prevent runway excursion, which could result in damage to the airplane and injury to the occupants.
97-20-14: This amendment adopts a new airworthiness directive (AD) that applies to all Mitsubishi Heavy Industries, Ltd. (Mitsubishi) MU-2B series airplanes. This AD requires incorporating information into the Limitations Section of the Airplane Flight Manual (AFM) that would require pilot training before flight into known or forecast icing conditions after a certain date. This AD results from the Federal Aviation Administration's analysis that the current training level of the pilots-in-command (PIC) of the MU-2B series airplanes makes it difficult for pilots to recognize adverse operating conditions and operate safely while flying in icing conditions. Similar training to that required in this AD for pilots of other high performance airplanes has shown a lower accident rate over time after the training than before. The actions specified by this AD are intended to decrease the chance of icing-related incidents or accidents of the MU-2B series airplanes due to pilot error.
97-20-12: This amendment adopts a new airworthiness directive (AD), applicable to McDonnell Douglas Helicopter Systems (MDHS) Model MD-900 helicopters, that requires removing certain serial-numbered main rotor swashplate bearings (bearings) and replacing them with airworthy bearings. This amendment is prompted by reports that inspections of several helicopters revealed that the outer bearing race had been rotating relative to the swashplate assembly, which was evidenced by wear marks in the rotating swashplate. The actions specified by this AD are intended to prevent possible heat accumulation and resulting damage to the bearing caused by the bearing races rotating relative to the bearing seat, which could result in degraded helicopter response to pilot control input and possible loss of control of the helicopter.
2012-03-03: We are adopting a new airworthiness directive (AD) for certain Fokker Services B.V. Model F.27 Mark 050 and F.28 Mark 0070 and 0100 airplanes. This AD was prompted by reports that the brightness of the tritium exit signs and lighting strips deteriorated below accepted levels. This AD requires a detailed inspection of tritium exit signs and emergency lighting strips, and replacement if necessary. We are issuing this AD to detect and correct insufficient brightness of the tritium exit signs and lighting strips, which could lead to an unsafe evacuation during an emergency, possibly resulting in injury to occupants. [[Page 12177]]
2012-02-15: We are superseding an existing airworthiness directive (AD) for certain Model 757-200, -200PF, -200CB, and -300 series airplanes. That AD currently requires inspecting certain power feeder wire bundles for damage, inspecting the support clamps for these wire bundles to determine whether the clamps are properly installed, and performing corrective actions if necessary. This new AD requires additional inspections for certain airplanes. This AD was prompted by a report that a power feeder wire bundle chafed against the number six auxiliary slat track, causing electrical wires in the bundle to arc, which damaged both the auxiliary slat track and power feeder wires. We are issuing this AD to prevent arcing that could be a possible ignition source for leaked flammable fluids, which could result in a fire. Arcing could also result in a loss of power from the generator connected to the power feeder wire bundle, and consequent loss of systems, which could reduce controllability of theairplane.
83-06-09: 83-06-09 WYTWORNIA SPRZETU KOMUNIKACYJNEGO, PZL-MIELEC: Amendment 39-4596. Applies to Model PZL M18 (Serial Nos. 1Z001-01 through 1Z001-05, 1Z001-08 through 1Z001-10, 1Z002-01 through 1Z002-05, 1Z003-01 through 1Z003-10, 1Z004- 01 through 1Z004-10, and 1Z005-01 through 1Z005-14) airplanes certificated in any category. Compliance: Required as indicated, unless already accomplished. Within the next 50 hours time-in-service after the effective date of this AD accomplish the following: a) To prevent inflight engine shutdown due to unmonitored fuel transfer between tanks, install non-return (check) valves Part Number (P/N) D61.170.00.G, install a second fuel quantity gauge, P/N 64126 or 6246-8, and install fuel filler placards in accordance with procedures III. A., III. B., and III. H. of Mandatory Bulletin I/009/81 and ERRATA sheet. NOTE: The modifications required by paragraph a) have been accomplished by the manufacturer on aircraft Serial Numbers 1Z001-02, 1Z004-02, 1Z004-05, 1Z004-06, and 1Z004- 10. b) To eliminate mechanical linkage interference in the power controls, inspect the support tube (P/N D65.250.00.2) installation to assure that the propeller governor push rod to carburetor orifice and carburetor (R.P.M.) adjustment levers clearance is as prescribed in procedures III. D. of Mandatory Bulletin I/009/81. If clearance is insufficient, readjust support tube and modify the carburetor orifice as prescribed to meet the clearances specified in procedures III. D. c) To eliminate a possible source of head injury to the pilot during a hard landing, replace the sunlight filter position adjustment butterfly nut, P/N 1414s49-8-ka, with ball knob P/N D74.280.00.0 as prescribed in procedures III. F. of Mandatory Bulletin I/009/81. d) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. e) An equivalent means of compliance with this AD may be used if approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, c/o American Embassy, 1000 Brussels, Belgium. This amendment becomes effective on April 4, 1983.