Results
2021-26-26: The FAA is superseding Airworthiness Directive (AD) 2005-12-08 for certain Safran Helicopter Engines, S.A. (Safran Helicopter Engines) Arrius 2B1, 2B1A, 2B1A-1, and 2B2 model turboshaft engines. AD 2005-12- 08 required replacing the software in the engine electronic control unit (EECU). This AD was prompted by a report of simultaneous loss of automatic control on both engines installed on an Airbus Helicopters Deutschland (formerly Eurocopter Deutschland) EC135 helicopter during flight. This AD requires replacement of the EECU or upgrade of the EECU software for engines with a certain EECU part number (P/N) installed. This AD also prohibits installation of an affected EECU onto any engine. The FAA is issuing this AD to address the unsafe condition on these products.
2012-12-21: We are superseding an existing airworthiness directive (AD) for all Eurocopter Deutschland GmbH (ECD) Model MBB-BK 117 C-2 helicopters. That AD currently requires revising the ``Emergency and Malfunction Procedures'' and ``Performance Data'' sections of the Rotorcraft Flight Manual (RFM) by inserting three temporary pages into the RFM to alert pilots to monitor the power display when a generator is deactivated and provides procedures to prevent failure of the remaining generator. Before we issued that AD, the manufacturer developed a procedure to modify the two ``After Junction Boxes'' by removing a diode from each box, which provides terminating action for our AD requirements. These actions are intended to require implementing this terminating action to prevent an electrical power system failure and subsequent loss of control of the helicopter and revising the RFM accordingly, by removing the temporary pages inserted to comply with the superseded AD.
95-03-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR72 series airplanes, that requires an inspection to determine the model and orientation of certain flight control rods, and replacement of the rods with modified rods, if necessary. This amendment is prompted by reports of corrosion found on the pitch and rudder trim and rudder travel limiter fail-safe rods. The actions specified by this AD are intended to prevent problems associated with corrosion of the flight control rods, which could compromise the required strength of these items.
48-19-03: 48-19-03\tDOUGLAS: Applies to DC-6 Serial Numbers 42854 Through 42896; 43000 Through 43024; 43035 Through 43052; 43055 Through 43058; 43061 Through 43064; and 43105 through 43110. \n\n\tCompliance required by September 15, 1958. \n\n\tDue to two failures in flight and to reported excessive looseness in the elevator trim tab operating mechanism, the following must be accomplished: \n\n\t1.\tRework drum, P/N 4344461 into drum, P/N 4357010-4, by boring hole in end of drum 0.8755-0.8745 diameter, 0.188-0.189 deep and concentric within 0.002 full indicator reading, and press in bushing 4357010-2 into hole. Remove nut, P/N 2335472, press in nut, P/N 2357008, in place so that two holes in nut match two holes in drum, P/N 4357010-4, and insert two pins, P/N 1335480, and stake in place. This rework changes jackshaft mechanism assembly, P/N 434460, into P/N 4357010. \n\n\t2.\tRework push-pull tubes, P/N 2344790, into P/N 2357984-2 by cutting off swaged end of tube 1/8 inch so that new tube lengthis 10 inches. Insert large end of plug, P/N 2357980, into tube 1 3/4 inches, drill two 0.161 diameter holes (No. 20 drill) and attach plug to tube with two rivets, P/N AN 430 AD5-16. Machine hex end on socket, P/N 2331924, and install in end of the tube opposite to plug, P/N 2357980. Rework end assemblies, P/N 2331925 into end assemblies, P/N 2357983, and install with locknuts, P/N AN 316-5R and washer 1357982. \n\n\tReassemble trim tab mechanism and install on aircraft. \n\n\t(Douglas Service Bulletin DC-6 No. 123 covers this same subject.)
2012-13-51: We are adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace LP (Type Certificate previously held by Israel Aircraft Industries, Ltd.) Model Gulfstream G150 airplanes. This emergency AD was sent previously to all known U.S. owners and operators of these airplanes. This AD requires a one-time detailed or borescope inspection of the left- and right-hand inboard vent holes for debris or obstructions, and repair if necessary. This AD was prompted by a report indicating that an inboard vent tube hole was completely covered with sealant, which blocked airflow through the vent. Under these conditions, the rise of internal pressure during pressure fueling or due to thermal expansion is sufficient to damage the wing. We are issuing this AD to detect and correct compromised integrity of the wing structure.
2021-26-03: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-300, -400, and -500 series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the frame splice between certain stringers is subject to widespread fatigue damage (WFD). This AD requires an inspection of certain fuselage frame splices for existing repairs, repetitive inspections of certain fuselage frame splices for cracking, and applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
2012-16-11: We are adopting a new airworthiness directive (AD) for certain Airbus Model A318-112 and -121 airplanes; Model A319-111, -112, -115, - 132, and -133 airplanes; Model A320-214, -232, and -233 airplanes; and Model A321-211, -212, -213, and -231 airplanes. This AD was prompted by reports that some nuts installed on the wing, including on primary structural elements, were found cracked. This AD requires inspecting to determine if certain nuts are installed or cracked, and replacing the affected nuts if necessary. We are issuing this AD to detect and correct missing and cracked nuts, which could result in the structural integrity of the airplane wings being impaired.
50-18-02: 50-18-02 DOUGLAS: Applies to All Model DC-6 Aircraft Equipped With Hamilton Standard 43D60/6841A-O, 6851A-O, and 6873A-O Propeller Blades and R-2800-83AM4, R-2800-83A or CA Type Engines. \n\n\tTo have been accomplished by April 28, 1950. \n\n\tA recent propeller blade tip failure of a Hamilton Standard 43D60/6851A-O propeller on a DC-6 powered with R-2800-CA-15 engines probably resulted from a worn 4 1/2 order engine crankshaft torsional damper P/N 101169. Until further notice or until the engines are known definitely to comply with P&W Service Bulletin No. 1033 dated November 30, 1949, all DC-6 aircraft using Hamilton Standard 6841A-O, 6851A-O and 6873A-O blades and R-2800-83AM4 or CA type engines shall be placarded to avoid all operation between 1,800 and 1,975, between 2,025 and 2,175 and between 2,225 and 2,450 r.p.m. Only acceleration and deceleration through placarded ranges shall be permitted. For gross weights above 80,000 pounds, 2,450 r.p.m. is permissible for normal climb. For gross weights below 80,000 pounds, climbing r.p.m. between 2,450 and 2,600 permissible. For gross weights above 80,000 pounds avoid operation above 2,450 r.p.m. except for takeoff and emergencies. For R-2800-83A engine installations, operating restriction presently covered in Aircraft Specification A781, Note 5C (1) applicable and until further notice operation between 1,800 and 1,975 and between 2,025 and 2,175 shall be prohibited.
2004-13-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-301, -311, and -315 airplanes. This AD requires determining the modification number of the angle of attack (AOA) sensor vanes; testing the movement of the affected vanes to evaluate sticking against both the upper and the lower vane travel end stops; and corrective action, if necessary. This action is necessary to prevent an incorrect AOA indication to the stall warning system in flight, which could result in an inadvertent stall and consequent loss of control of the airplane. This action is intended to address the identified unsafe condition.
98-26-13: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires a one-time inspection to determine the material type of the stop support fittings of the main entry doors. This AD also requires repetitive visual inspections to detect cracks of certain stop support fittings of the main entry doors, and replacement of any cracked stop support fitting with a certain new stop support fitting. This amendment is prompted by reports that stress corrosion cracking was found on certain stop support fittings of the main entry doors. The actions specified by this AD are intended to detect and correct such stress corrosion cracking, which could lead to failure of the stop support fittings. Failure of the stop support fittings could result in loss of a main entry door and consequent rapid decompression of the airplane.