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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.
2021-25-05: The FAA is superseding Airworthiness Directive (AD) 2017-23- 02, which applied to certain The Boeing Company Model 737-200, -200C, - 300, -400, and -500 series airplanes. AD 2017-23-02 required repetitive inspections, replacement, and applicable on-condition actions for certain fuselage crown skin panels. This AD was prompted by an evaluation by the design approval holder indicating that the fuselage crown skin panels are subject to widespread fatigue damage. This AD retains the actions in AD 2017-23-02, revises certain airplane configurations and inspection locations, and adds airplanes to the applicability. The FAA is issuing this AD to address the unsafe condition on these products.
48-15-03: 48-15-03 DOUGLAS: Applies to C-54 and DC-4 Aircraft. \n\n\tCompliance required by November 1, 1948. \n\n\tBecause of service failures of hydraulic pressure regulator valves, the following must be accomplished: \n\n\t1.\t(a)\tModify Douglas hydraulic pressure regulator valve P/N 5104005, P/N 5231848, or P/N 5327293 to the equivalent of Douglas regulator P/N 5332857, or \n\n\t\t(b)\tConvert Douglas hydraulic pressure regulator valve P/N 5104005, P/N 5231848, or P/N 5327293 to Douglas regulator P/N 5332857, or \n\n\t\t(c)\tInstall Douglas hydraulic pressure regulator P/N 5332857, or \n\n\t\t(d)\tInstall Bendix hydraulic pressure regulator P/N 407484, or \n\n\t\t(e)\tInstall Air Associates hydraulic pressure regulator valve P/N HC-3600, or \n\n\t\t(f)\tInstall Vickers hydraulic pressure regulator valve P/N AA-34551, P/N AA-34552, or P/N AA-34585 which must have the letter "C" or subsequent terminating the regulator serial number, i.e., "Serial No. 0000C," "Serial No. 0000D," etc. \n\n\t2.\tInstall a hydraulic fluid filter with Purolator core in regulators listed in 1, (a) through (d). \n\n\t(Douglas Service Bulletin DC-4 No. 22, "Rework of Hydraulic Pressure Regulator Valve" with addendum, "Optional Installation of Hydraulic Pressure Regulators" covers part 1. Douglas Service Bulletin C-54-239, "Installation of Filter in Hydraulic Regulator Operating Line," covers part 2.)
96-12-09: This amendment adopts a new airworthiness directive (AD), applicable to PTC Seating Products Division, B/E Aerospace (PTC), formally known as PTC Aerospace, Model 950 series passenger seats with footrest assembly. This amendment will require the removal of the footrest assembly arms and the installation of a conversion kit on each PTC Model 950 series passenger seat equipped with footrest assembly. This amendment is prompted by two incidents of finger injuries that occurred during attempts to either extend or retract the footrest system on PTC Model 950 series passenger seats equipped with footrest assembly. The actions specified by this AD are intended to prevent injury to hands during the operation of a PTC Model 950 series passenger seat equipped with footrest assembly.
2004-13-13: This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-120 series airplanes, that requires a one-time inspection of the access door ramp of the fueling control panel for damage or deformation, and applicable corrective actions. This action is necessary to prevent inadvertent fuel transfer in flight due to fuel service personnel not repositioning the defuel valve switch control to the closed position after utilization on the ground, which could cause in-flight fuel starvation. This action is intended to address the identified unsafe condition.
2021-26-10: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-400, -400D, and -400F series airplanes. This AD was prompted by reports of burned Boeing Material Specification (BMS) 8-39 urethane foam, and a report from the airplane manufacturer that airplanes were assembled with seals throughout various areas of the airplane (including flight deck and cargo compartments) made of BMS 8-39 urethane foam, a material with fire- retardant properties that deteriorate with age. This AD requires replacing the system tube/wire seals made of BMS 8-39 urethane foam in certain areas of the airplane. The FAA is issuing this AD to address the unsafe condition on these products.