Results
95-09-05: This amendment adopts a new airworthiness directive (AD) that is applicable to certain British Aerospace Model Avro 146-RJ series airplanes. This action requires a revision to the FAA-approved Airplane Flight Manual (AFM) to alert the flightcrew of the potential for significant delays in the Honeywell Standard Windshear Detection and Recovery Guidance System (WSS) detecting windshear when the flaps of the airplane are in transition. This amendment is prompted by a report of an accident during which an airplane encountered severe windshear during a missed approach. The actions specified in this AD are intended to ensure that the flightcrew is aware that there may be significant delays in the WSS detecting windshear when the flaps of the airplane are in transition.
99-02-09: This amendment adopts a new airworthiness directive (AD), applicable to Agusta S.p.A. Model A109C and A109K2 helicopters. This amendment requires removing the main rotor pitch link assemblies, measuring the radial play of the upper and lower spherical bearings (bearings), and replacing any unairworthy bearings. This amendment is prompted by four reports of increased vibration of the helicopters caused by wear in the bearings of the main rotor pitch change link assembly. The actions specified by this AD are intended to detect unairworthy bearings on the pitch change link assembly and to prevent increased vibration and subsequent reduced controllability of the helicopter.
2007-08-03: The FAA is adopting a new airworthiness directive (AD) to supersede AD 2006-17-04, which applies to certain Cessna Aircraft Company (Cessna) Models 172R, 172S, 182T, T182T, 206H, and T206H airplanes. AD 2006-17-04 currently requires you to inspect the two end fittings on each of the flexible fuel hoses located in the engine compartment for the correct torque values, and, if any incorrect torque values are found during the inspection, tighten the hose end fittings to the correct torque values. This AD results from four reports of loose fuel lines connected to the fuel servo or fuel flow transducer. Two reports were of in-flight engine failure on a Model T182T airplane. A third report was of in-flight engine failure on a Model 206H airplane. A fourth report was of a Model 172S airplane losing engine power on final approach. Consequently, this AD would require you to establish the correct torque values of the end fittings on fuel hoses for certain Cessna Models 172R, 172S, 182T,T182T, 206H, and T206H airplanes. This AD clarifies that the torque values need to be physically established and visual inspection only is not sufficient. We are issuing this AD to detect and correct potential loss of fuel flow, which may result in partial or complete loss of engine power and/or uncontrolled engine compartment fire due to fuel leakage forward of the firewall.
2000-25-01: This amendment supersedes Airworthiness Directive (AD) 80-26-05, which currently requires you to repetitively inspect the main landing gear (MLG) inboard door hinges and attachment angles for cracks on certain The New Piper Aircraft, Inc. (Piper) PA-31 series airplanes. AD 80-26-05 also requires you to replace any cracked MLG inboard door hinge or attachment angle with parts of improved design. This AD results from the Federal Aviation Administration's policy on aging commuter-class aircraft and the determination that an improved design MLG inboard door hinge and attachment assembly, when incorporated, will eliminate the need for the currently required repetitive short-interval inspections; however, we have received reports of cracks in the improved design MLG inboard door hinge assemblies on the affected airplanes. This AD retains the current repetitive inspections contained in AD 80-26-05, and requires inspections on the improved design parts. The actions specified by this AD are intended to detect and correct cracked MLG inboard door hinge assemblies. These cracked door hinge assemblies could result in the MLG becoming jammed, with consequent loss of control of the airplane during landing operations.
2018-01-03: We are adopting a new airworthiness directive (AD) for certain Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300- 600 series airplanes); and Airbus Model A310 series airplanes. This AD requires contacting the FAA to obtain instructions for addressing the unsafe condition on these products, and doing the actions specified in those instructions. This AD was prompted by reports of the portable oxygen cylinder assembly (POCA) slipping from its bracket inside a one- frame overhead stowage compartment. We are issuing this AD to address the unsafe condition on these products.
97-14-11: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 97-14-11 that was sent previously to all known U.S. owners and operators of certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 and 200) series airplanes by individual notices. This AD requires repetitive inspections to detect cracks of a certain bulkhead web of the fuselage at certain locations, and repair, if necessary. This action is prompted by a report of a pressurization problem during flight, which was caused by fatigue cracking in the underfloor pressure bulkhead of the fuselage. The actions specified by this AD are intended to detect and correct such fatigue cracking, which could result in uncontrolled depressurization of the airplane and/or reduced structural integrity of the fuselage.
2007-08-02: The FAA is adopting a new airworthiness directive (AD) for Hartzell Propeller Inc. model HC-E4A-3( )/E10950( ) propellers. This AD requires initial and repetitive inspections and rework of the propeller blade retention radius, and replacement of the propeller blade thrust bearing, for each blade. This AD results from reports of excessive propeller vibration and of damaged or broken propeller blade thrust bearings found during routine and investigative propeller disassembly. We are issuing this AD to prevent propeller blade separation, damage to the airplane, and possible loss of airplane control.
95-10-03: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Industrie Model A300, A300-600, and A310 series airplanes, that requires inspections to detect cracks in the lower spar axis of the pylon between ribs 9 and 10, and repair, if necessary. This amendment is prompted by a report indicating that fatigue cracks have been found on the lower spar of the pylon. The actions specified by this AD are intended to prevent such fatigue cracking, which could result in reduced structural integrity of the lower spar of the pylon.
2000-25-03: This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron Inc. (BHTI) Model 205A-1, 205B, 212, 412, and 412CF helicopters. This action requires inspecting the locking washer on each main rotor actuator (actuator) for twisting or damage to the tab and replacing any locking washer that has a twisted or damaged tab. Replacing certain locking washers, regardless of condition, is also required within a specified time period. Installing a certain airworthy locking device on each actuator constitutes terminating action for the requirements of this AD. This amendment is prompted by an incident in which a damaged locking washer allowed the rod end to detach from the collective actuator, causing loss of collective control of the main rotor. The current locking washer is subject to mechanical damage and failure, which allows the actuator piston to unthread itself from its rod end. This condition, if not corrected, could cause loss of control of the main rotor and subsequent loss of control of the helicopter.
2004-13-08: This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3-60 series airplanes. This AD requires inspection of the welded joints of the balance weight brackets for the left and right elevator trim tabs for cracking; repetitive inspections, as applicable; and corrective actions including the eventual replacement of all brackets, which constitutes terminating action for the repetitive inspections. This action is necessary to prevent the loss of the balance weight for the elevator trim tab, which could result in incorrect trim during takeoff and landing, and reduced controllability of the airplane. This action is intended to address the identified unsafe condition.