Results
2000-04-19: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Dassault Model Mystere-Falcon 50 series airplanes, that currently requires a revision to the Limitations section of the FAA-approved Airplane Flight Manual (AFM) to include procedures to use certain values to correctly gauge the minimum allowable N1 speed of the operative engines during operation in icing conditions. This amendment adds a new requirement for operators to adjust the thrust reverser handle stop, install new wiring, and modify the Digital Electronic Engine Control (DEEC) software, which terminates the AFM revision. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent flightcrew use of erroneous N1 thrust setting information displayed on the Engine Indication Electronic Display (EIED), which could result in in-flight shutdown of engine(s).
2017-19-08: We are adopting a new airworthiness directive (AD) for all Airbus Defense and Space S.A. Model C-212-CB, C-212-CC, C-212-CD, C- 212-CE, and C-212-DF airplanes. This AD was prompted by reports of failures of the rudder pedal control system support. This AD requires modifying the rudder pedal adjustment system. We are issuing this AD to address the unsafe condition on these products.
2000-22-13: This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron Canada (BHTC) Model 430 helicopters that requires calibration of the fuel quantity indicating system. This amendment is prompted by an operator report of an inaccurate fuel quantity indicating system. The actions specified by this AD are intended to prevent an inaccurate fuel quantity indicating system reading, engine flameout due to fuel starvation, and a subsequent forced landing.
2005-22-04: The FAA adopts a new airworthiness directive (AD) for certain Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes. This AD requires you to determine (maintenance records check and/or inspection) whether certain nose landing gear (NLG), main landing gear (MLG), and MLG shock absorber assemblies with a serial number beginning with "AM" are installed, and, if installed, would require you to replace them with ones without the "AM." This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. We are issuing this AD to detect and correct the NLG, MLG, and MLG shock absorber assemblies that are affected by hydrogen embrittlement, which could result in failure of the landing gear. This failure could lead to nose or main landing gear collapse during operation with consequent loss of airplane control.
98-14-01: This amendment adopts a new airworthiness directive (AD), applicable to Model AS-350B, BA, B1, B2, and D, and Model AS-355E, F, F1, F2, and N helicopters, that requires inspections of the main gearbox suspension bi-directional cross-beam (cross-beam) for cracks, and replacement of the cross-beam if a crack is found. This amendment is prompted by several reports of cracks in the cross-beam. The actions specified by this AD are intended to provide a terminating action to prevent failure of the cross-beam that could cause the main gearbox to pivot, resulting in severe vibrations and a subsequent forced landing.
98-13-40: This amendment adopts a new airworthiness directive (AD), applicable to Eurocopter France Model SA 330F, G, and J helicopters, that requires verifying the torque on the nut that secures the two transformer-rectifiers' common ground; and subsequently installing a modification to separate the grounds of the two transformer-rectifiers. This amendment is prompted by a report from the airworthiness authority of France about an unsafe condition resulting from the loss of the common ground of the two transformer-rectifiers. The actions specified by this AD are intended to prevent loss of the common ground of the two transformer-rectifiers, which could result in a complete electrical failure (essential and secondary), loss of electrically-powered instrumentation, and subsequent loss of control of the helicopter.
83-20-01: 83-20-01 GARLICK HELICOPTERS, HAWKINS & POWERS AVIATION, INC., WILCO AVIATION (BELL) MODEL UH-1B HELICOPTERS: Amendment 39-4731. Applies to Garlick Helicopters, Hawkins & Powers Aviation, Inc., and Wilco Aviation (Bell) UH-1B helicopters certified in all categories. Compliance is required within the next 100 hours time in service after the effective date of this AD unless already accomplished. To prevent excessive structural loads which could lead to mechanical failure and possible loss of a helicopter, accomplish the following: (a) Inspect the tail rotor hub assembly and identify the part number of the tail rotor hub assembly. The tail rotor hub assembly part number is located on the yoke assembly. (b) If the tail rotor hub assembly, P/N 204-011-801-003, is installed, remove and replace with P/N 204-011-801-005, 009, or 017. (c) Any equivalent method of compliance with paragraph (b) above of this AD must be approved by the Manager, Aircraft CertificationDivision, Southwest Region, Federal Aviation Administration, P.O. Box 1689, Fort Worth, Texas 76101. (d) In accordance with FAR 21.197, flight is permitted to a base where the inspections required by this AD may be accomplished. This amendment becomes effective November 1, 1983.
2005-22-03: The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce Corporation (RRC) (formerly Allison Engine Company) 501- D22A, 501-D22C, and 501-D22G turboprop engines. This AD requires a onetime inspection for proper metal hardness of certain 1st stage, 2nd stage, 3rd stage, and 4th stage turbine wheels. This AD results from a report of a turbine wheel found to be over dimensional limits, caused by improper metal hardness. We are issuing this AD to prevent uncontained turbine wheel failure, leading to damage of the airplane and total loss of engine power.
98-13-32: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F.28 Mark 0100 series airplanes, that requires interim inspections to detect discrepancies of the main fitting subassembly of the main landing gear, and follow-on corrective actions, if necessary. This amendment also requires a one-time inspection to detect discrepancies of the fitting, repair of the fitting, if necessary, and application of new surface protection on the fitting, which would terminate the interim inspections. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent cracking of the main fitting subassembly of the main landing gear, which could result in collapse of the main landing gear.
2005-21-06: The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 737-600, -700, -700C, -800, and -900 series airplanes. This AD requires repetitive inspections of the aft pressure bulkhead web for fatigue cracks, crack indications, discrepant holes, and corrosion; and repair if necessary. This AD results from reports of fatigue cracks in the aft pressure bulkhead web. We are issuing this AD to detect and correct such fatigue cracks, which could result in a rapid decompression of the airplane.