Results
2005-26-05: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC-8-400 series airplanes. This AD requires an inspection of the laminated shims for cracks, damage, or extrusion between the forward attachment fittings of the horizontal stabilizer and the top rib of the vertical stabilizer; a torque check of the attachment bolts in the attachment fittings of the front, middle, and rear spars; and corrective actions if necessary. This AD results from a report indicating that delaminated shims extruded from the interface between the forward attaching fittings of the horizontal stabilizer and the top rib of the vertical stabilizer, and that inadequate torque values of some bolts were found. We are issuing this AD to prevent reduced structural integrity of the horizontal stabilizer, and consequent loss of controllability of the airplane.
99-01-04: This amendment adopts a new airworthiness directive (AD) that applies to certain Avions Pierre Robin Model R2160 airplanes. This AD requires replacing the left and right rudder bars with improved design rudder bars. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified in this AD are intended to prevent distortion of the original design rudder bars during operation, which could result in reduced or loss of control of the airplane.
99-01-02: This amendment adopts a new airworthiness directive (AD) that is applicable to Westland Helicopters Ltd. (Westland) 30 Series 100 and 100-60 helicopters. This action requires the removal and replacement of conformal pinion quill shafts installed in certain main rotor gearboxes that fail to pass a magnetic drain plug inspection. This amendment is prompted by a report of a forced landing that occurred when a single conformal pinion quill shaft failed in a main rotor gearbox (MRGB). This condition, if not corrected, could result in the failure of a MRGB, and a subsequent forced landing or loss of control of the helicopter.
80-25-01: 80-25-01 HUGHES HELICOPTERS: Amendment 39-3980. Applies to Model 369 Series Helicopters certified in all categories. Compliance is required as indicated unless already accomplished. To prevent possible fatigue failure of the Hughes couplings in the tail rotor drive shaft and loss of tail rotor power, accomplish the following: (a) Within 25 hours' time in service from the effective date of this AD, inspect the fore and aft tail rotor drive shaft couplings to determine the serial numbers of the installed couplings. The serial number is on the Bendix part number decal. (b) For those helicopters with the following couplings installed, prior to further flight, remove couplings from service and label couplings "Unairworthy." Hughes Part No. 369H92564, serial numbers 0883U, 0932U, 0933U, 0935U, 0940U, 0950U, 0957U, 0961U, 0971U; and for Hughes Part No. 369A5501, serial numbers 10670U and 10672U. Replace removed coupling with like serviceable part. (c) Installation of any coupling listed in paragraph (b) will render the helicopter unairworthy. (d) Report the serial number of each suspect coupling listed in paragraph (b) found as a result of the inspection of paragraph (a) to the Chief, Engineering and Manufacturing Branch, FAA, Western Region, P.O. Box 92007, World Way Postal Center, Los Angeles, California 90009. Negative reports are not necessary. Reporting approved by Office of Management and Budget, OMB No. 04/R0174. (e) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate helicopters to a base for the accomplishment of inspections required by this AD. (f) Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Engineering and Manufacturing Branch, FAA Western Region. This amendment becomes effective December 4, 1980.
2005-25-22: The FAA adopts a new airworthiness directive (AD) for all Przedsiebiorstwo Doswiadczalno-Produkcyjne Szybownictwa "PZL-Bielsko" Model SZD-50-3 "Puchacz" gliders. This AD requires you to perform a visual inspection of the turnbuckle link for cracks or wear and replace if cracks or wear is found. This action only applies to those gliders where the turnbuckle is directly connected to the pedal. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Poland. We are issuing this AD to detect and correct cracks in the turnbuckle link, which could result in failure of the rudder cable. This failure could lead to loss of control of the glider.
2019-12-15: We are adopting a new airworthiness directive (AD) for certain Leonardo S.p.A. (Leonardo) Model AB139 and AW139 helicopters. This AD requires replacing screws installed on the left and right main landing gear (MLG) shock absorber assembly. This AD was prompted by a report that some screws may have been manufactured without meeting specifications. We are issuing this AD to address the unsafe condition on these products.
2011-18-04: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: It has been reported during operational checks that some failures of the Escape Slide * * * installed on the forward passenger and service door have occurred which prevented the door from opening. * * * [T]his condition * * * could delay an emergency evacuation and increase the chance of injury to passengers and flight crew * * *. We are issuing this AD to require actions to correct the unsafe condition on these products.
98-25-52: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) T98-25-52 that was sent previously to all known U. S. owners and operators of all Boeing Model 747 series airplanes by individual telegrams. This AD requires revising the Airplane Flight Manual to include procedures to prevent dry operation of the center wing fuel tank override/jettison pumps and, for certain airplanes, to prohibit operation of the horizontal stabilizer tank transfer pumps in flight. This action is prompted by a report indicating that several override/jettison fuel pumps from the center wing tanks and main tanks had been removed because circuit breakers for the override/jettison fuel pumps were tripped, or low pump output pressure was indicated. The actions specified by this AD are intended to prevent contact between the rotating paddle wheel and the stationary end plates within the center wing tank override/jettison fuel pumps or horizontal stabilizer tanktransfer pumps due to excessive wear of the pump shaft carbon thrust bearing, which could cause sparks and/or a hot surface condition and consequent ignition of fuel vapor in the center wing tank or horizontal stabilizer tank during dry pump operation (no fuel flowing).
98-09-16: This amendment adopts a new airworthiness directive (AD) that is applicable to all Aerospatiale Model ATR-42 and ATR-72 series airplanes. This action requires revising the Airplane Flight Manual (AFM) to add specific flightcrew instructions to be followed in the event of failure of one or both of the direct current (DC) generators. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent failure of the second of two DC generators after the failure of the first generator, which could lead to the loss of main battery power and result in the loss of all electrical power, except the emergency battery supply, during flight.
2009-18-07: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 747 series airplanes. That AD currently requires repetitive inspections to detect cracks in various areas of the fuselage internal structure, and related investigative/corrective actions if necessary. This new AD requires additional repetitive inspections for cracking of certain fuselage structure, and related investigative/corrective actions if necessary. This AD results from fatigue tests and analysis by Boeing that identified areas of the fuselage where fatigue cracks can occur. We are issuing this AD to prevent the loss of the structural integrity of the fuselage, which could result in rapid depressurization of the airplane.