Results
2004-14-20: The FAA supersedes Airworthiness Directive (AD) 2003-21-07, which applies to certain The Cessna Aircraft Company (Cessna) Model 525 airplanes. AD 2003-21-07 currently requires you to disengage the pitch trim circuit breaker and AP servo circuit breaker and then tie strap each of them to prevent them from being engaged. Not utilizing this equipment prevents a single-point failure. This AD is the result of Cessna having now developed and made changes in the design of the affected trim printed circuit board (PCB) assembly to allow the use of the assembly and the prevention of the single-point failure, and identification of additional airplanes that have the same unsafe condition. Consequently, this AD requires you to remove and replace an old trim PCB assembly with a new design assembly or modify an old trim PCB assembly to the new design. We are issuing this AD to correct this single-point failure in the electric pitch trim system, which will result in a runaway pitch trim condition where the pilot could not disconnect using the control wheel autopilot/trim disconnect switch. Failure of the electric trim system would result in a large pitch mistrim and would cause excessive control forces that the pilot could not overcome.
2022-04-07: The FAA is adopting a new airworthiness directive (AD) for certain General Electric Company (GE) GEnx-1B64, -1B64/P1, -1B64/P2, - 1B67, -1B67/P1, -1B67/P2, -1B70, -1B70/75/P1, -1B70/75/P2, -1B70/P1, - 1B70/P2, -1B70C/P1, -1B70C/P2, -1B74/75/P1, -1B74/75/P2, -1B76/P2, - 1B76A/P2, GEnx-2B67, -2B67B, and -2B67/P model turbofan engines. This AD was prompted by an in-flight shutdown (IFSD) of an engine and subsequent investigation by the manufacturer that revealed an improperly torqued fuel metering unit (FMU) bypass valve (BPV) plug. This AD requires a shim check inspection of the FMU BPV plug and, depending on the results of the inspection, replacement of the FMU. The FAA is issuing this AD to address the unsafe condition on these products.
2022-03-17: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model AS332L2 and EC225LP helicopters. This AD was prompted by a report of loss of tightening torque on the nut that attaches the tail gear box (TGB) bevel wheel. This AD requires repetitive inspections (measurements) of the angular clearances of the TGB, and, depending on the findings, replacement of the TGB with a serviceable TGB, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also provides terminating action for certain repetitive inspections. The FAA is issuing this AD to address the unsafe condition on these products.
2022-03-12: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A330-200, -300, -800, and -900 series airplanes; and Model A340-200, -300, -500, and -600 series airplanes. This AD was prompted by reports that the instructions on the doghouse door lock placard are unclear and incomplete. This AD requires replacing the placard with an improved instruction placard, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also prohibits the installation of affected parts under certain conditions. The FAA is issuing this AD to address the unsafe condition on these products.
47-32-08: 47-32-08 BELL: (Was Mandatory Note 8 of AD-1H-1.) Applies to Models 47B and 47B3 Serial Numbers 2 Through 5, 7 Through 11, 13 Through 17, 19 Through 25, 27 Through 78. Compliance required not later than 25 hours operation after September 15, 1947. The stabilizer bar dampers should be inspected for the presence of an "AL" stamped on one of the attachment lugs. If such a marking does not appear, thoroughly inspect visually for leakage or other defects and replace if necessary with P/N A12141 (Houds) (stamped "AL"). A cracking or failing of the phenolic abutments has been reported, wherein the subject dampers have been rendered ineffective, thus affecting the flight characteristics of the helicopter. (Bell Service Bulletin 47C47 covers this same subject.)
2004-14-07: This amendment adopts a new airworthiness directive (AD), applicable to all BAE Systems (Operations) Limited (Jetstream) Model 4101 airplanes, that requires a test for free movement of the capsule/ bearing of the nose landing gear (NLG), and related investigative, significant, and corrective actions. This action is necessary to prevent failure of the NLG to extend fully, which could result in reduced controllability of the airplane during landing. This action is intended to address the identified unsafe condition.
2012-21-14: We are superseding an existing airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. That AD currently requires a one-time inspection of the shafts of the main landing gear (MLG) side-brace fittings to detect corrosion, and the forward and aft bushings in the left-hand and right- hand MLG side-brace fittings to detect discrepancies. The existing AD also requires corrective and related actions if necessary. This new AD requires repetitive detailed inspections for corrosion and damage of the MLG side-brace fitting, and replacing the side-brace fitting shaft with the re-designed side-brace fitting shaft of the MLG if necessary. This AD also requires eventual replacement of certain side-brace fitting shafts with the re-designed part. Replacement with a re- designed side-brace fitting shaft of the MLG is terminating action for the repetitive inspections. This AD was prompted by reports of failure of the side-brace fitting shaft of the main landing gear (MLG) due to corrosion. We are issuing this AD to prevent fractures of the side- brace fitting shafts of the MLG, and possible collapse of the MLG.
2011-18-51R1: We are revising an existing emergency airworthiness directive (AD) for all Honeywell International Inc. TPE331 model turboprop engines with a part manufacturer approval (PMA) replacement Dixie Aerospace, LLC main shaft bearing part number (P/N) 3108098-1WD, installed. That emergency AD was not published in the Federal Register, but was sent to all known U.S. owners and operators of these engines. That AD currently requires an inspection of the airplane records to determine if a Dixie Aerospace, LLC main shaft bearing, P/N 3108098- 1WD, is installed in the engine, and if installed, removal of that bearing from service, before further flight. This AD requires the same actions. This AD revision was prompted by the need to list the affected bearings by serial number (S/N) in the AD for clarification. We are issuing this AD to correct the unsafe condition on these products.
96-16-01: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10-10 and DC-10-15 series airplanes, that requires an inspection for evidence of missing chrome and for corrosion on the chrome surfaces, or verification that the forward trunnion bolts have been chrome plated in a specific manner; and rework or replacement of the bolts, if necessary. This amendment is prompted by a report of chrome flaking on the bearing surface of the trunnion bolts due to improper cleaning of the base material prior to chrome plating. The actions specified by this AD are intended to prevent premature failure of the trunnion bolts and subsequent collapse of the main landing gear (MLG) as a result of chrome flaking and severe corrosion on the bearing surface and in the mechanical fuse.
48-44-01: 48-44-01 DOUGLAS: Applies to All C-54 and DC-4 Series Aircraft. \n\n\tTo be accomplished not later than March 1, 1949. \n\n\tIn order to preclude nose gear retractions malfunction due to particles of disintegrated packing clogging the present upline orifice fitting, it is necessary to install an orifice fitting having a floating pin in the orifice hole and to replace the present packing used on the retracting cylinder with a more satisfactory packing. To accomplish this change: \n\n\t1.\tReplace the present upline orifice fitting with a union fitting and rework the existing tee fitting to include an orifice fitting (0.063-inch diameter floating pin in 0.090-inch diameter orifice hole) in the pipe threaded end. \n\n\t2.\t(a)\tReplace the existing chevron packing on the nose gear piston assembly with two synthetic chevron packings and two leather chevrons. Install two dural packing rings on each respective end of the piston head. \n\n\t\t(b)\tReplace existing packing on the nose gear cylinder end assembly with one dural packing ring, three synthetic chevron packings, and one leather chevron packing. \n\n\t\t(c)\tInstall two new washers over the end of the cylinder barrel. \n\n\t(Douglas Service Bulletin DC-4 No. 78 dated May 4, 1948 covers this same subject.)