Results
2004-17-03: The FAA is superseding an existing airworthiness directive (AD) for Pratt & Whitney Canada (PWC) PW206A and PW206E turboshaft engines. That AD currently requires: Initial and repetitive borescope inspections of compressor turbine and power turbine blades for blade axial shift. Replacement of blade retaining rivets and certain rotor air seals as terminating action for the repetitive borescope inspections. This ad requires the same actions as AD 2003-NE-25-AD but the extent of engine disassembly that triggers the required part replacements needs clarification. This AD results from reports of engine shutdowns and emergency landings due to severe vibration, resulting in exhaust gases escaping from the engine-to-exhaust nozzle interface, thereby triggering in-flight engine fire warnings. We are issuing this AD to prevent turbine blade axial shift, which could cause high levels of vibration, loss of engine torque, in-flight engine shutdown, and loss of the airframe exhaust duct. DATES: This AD becomes effective September 24, 2004. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of August 29, 2003. The incorporation by reference of certain other publications, as listed in the regulations, was approved previously by the Director of the Federal Register as of August 29, 2003 (68 FR 48544; August 14, 2003).
96-19-02: This amendment adopts a new airworthiness directive (AD) that applies to Industrie Aeronautiche E Meccaniche (I.A.M.) Model Piaggio P-180 airplanes. This action requires modifying the passenger seat cushion next to the emergency exit door handle. Reports of interference between the passenger seat cushion and the emergency exit door handle, preventing the door from opening from the outside, prompted this AD action. The actions specified by the AD are intended to prevent the possibility of not being able to open the emergency exit door during an emergency evacuation of the airplane, which could result in injury to the passengers.
2022-11-14: The FAA is adopting a new airworthiness directive (AD) for certain De Havilland Aircraft of Canada Limited Model DHC-8-401 and - 402 airplanes. This AD was prompted by reports that following a main landing gear (MLG) extension, one of the MLGs could not be locked in the gear down position due to deterioration of greasing effectiveness over time. This AD requires repetitive lubrication of the MLG assembly. The FAA is issuing this AD to address the unsafe condition on these products.
2004-14-12: The FAA is adopting a new airworthiness directive (AD) for certain The New Piper Aircraft, Inc. (Piper), Models PA-28-161, PA-28-181, PA-28R-201, PA-32R-301 (HP), PA-32R-301T, PA-32-301FT, PA-32-301XTC, PA-34-220T, PA-44-180, PA-46-350P, and PA-46-500TP airplanes. This AD requires you to inspect the control wheel attaching hardware for proper installation, replace if required, add Loctite thread- locking compound to the screw installation, and install a retainer clip to the control wheel attachment. This AD is the result of inadequate control wheel attachment design. The screw used to attach the control wheel to the control column is too short in some installations, and the nut-plate does not have adequate locking features. In addition, the screw is installed from the bottom of the control wheel and will depart quickly after thread disengagement. We are issuing this AD to detect and correct inadequate control wheel attachment design features, which could result in loss of control of the ailerons and elevator. This failure could lead to loss of control of the aircraft.
99-19-27: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-100, -200, -300, -400, and -500 series airplanes, that requires a one-time inspection of the main landing gear (MLG) wheel assemblies to determine whether certain parts are installed, and follow-on corrective actions, if necessary. For certain airplanes, this amendment also requires eventual modification of MLG wheel assemblies, which terminates the requirements of this AD. This amendment is prompted by incidents of multiple tie bolt failures on certain BFGoodrich wheel assemblies. The actions specified by this AD are intended to prevent failure of multiple tie bolts of MLG wheel assemblies, which could result in failure of the wheel rim, rapid release of tire pressure, and possible consequent damage to the airplane and injury to passengers and flightcrew.
2012-14-08: We are adopting a new airworthiness directive (AD) for Sikorsky Aircraft Corporation (Sikorsky) Model S-92A helicopters. This AD requires inspecting the main gearbox (MGB) for a crack. This AD is prompted by a crack in the cored passage of the MGB housing, which may be indicated by oil on the housing. These actions are intended to detect a crack in the MGB housing, which could result in loss of oil, failure of the MGB, and subsequent loss of control of the helicopter.
2022-12-02: The FAA is adopting a new airworthiness directive (AD) for all Bombardier, Inc., Model BD-100-1A10 airplanes. This AD was prompted by a report of multiple in-service events where, following a STAB TRIM FAULT advisory message and auto-pilot disconnect, flightcrew commands for a nose-up trim resulted in nose-down trim movement of the horizontal stabilizer instead. This AD requires revising the existing airplane flight manual (AFM) to provide the flightcrew with instructions for an expanded pre-flight check of the pitch trim, trim malfunction procedures, and revised ''AP STAB TRIM FAIL'' caution and ''STAB TRIM FAULT'' advisory procedures. The FAA is issuing this AD to address the unsafe condition on these products.
71-25-08: 71-25-08 FAIRCHILD HILLER ROTORCRAFT: Amdt. 39-1356. Applies to Fairchild Hiller UH-12 helicopters certificated in all categories. Compliance required as indicated. Following an immediate visual inspection and within 10 hours time in service after the effective date of this airworthiness directive inspect main rotor blade P/N 53100 for cracks, using dye penetrant. Any blades found defective are to be removed from service prior to further flight and S/Ns reported to Engineering and Manufacturing Branch, Federal Aviation Administration, Eastern Region, JFK International Airport, Jamaica, New York 11430. Approval of this reporting procedure has been obtained from the Bureau of Budget in accordance with Federal Reports Act. Reporting approved by Bureau of Budget under BOB Number 04-R0174. This amendment is effective December 14, 1971 and was effective upon receipt by owners and operators of the letter dated November 9, 1971 which contained this amendment.
99-18-23: This amendment adopts a new airworthiness directive (AD), applicable to all McDonnell Douglas MD-90-30 series airplanes, that requires revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness (MD-90-30 Airworthiness Limitations Instructions (ALI)) to incorporate certain replacement times for safe-life limited parts. This amendment is prompted by analysis of data that identified reduced replacement times for certain safe-life limited parts. The actions specified by this AD are intended to prevent fatigue cracking of various safe-life limited parts; such fatigue cracking could adversely affect the structural integrity of these airplanes.
2013-05-16: We are adopting a new airworthiness directive (AD) for MD Helicopters, Inc. (MDHI) Model 369D, 369E, 369F, and 369FF helicopters with certain serial-numbered tailboom assemblies. This AD requires measuring the distance between aft longeron rivets and the outboard edge of frame rings. If the distance is too short to ensure a safe flight, the AD requires installing a doubler. This AD was prompted by the discovery of short-edge margin conditions on two tailboom assemblies. The actions are intended to detect a short-edge margin condition, prevent failure of the tailboom and loss of control of the helicopter.