Results
47-32-03: 47-32-03 BELL: (Was Mandatory Note 3 of AD-1H-1.) Applies Only to Model 47B Serial Numbers 2 Through 6, 10 Through 17, and 20 Through 22. Compliance required not later than next 25-hour inspection after September 15, 1947. To insure proper operation of the tail rotor control pedal adjustment mechanism at all times, replace the existing pawl stop, P/N 47-722-059-1 in each pedal assembly with a modified pawl stop, P/N 47-722-057-1. Check length of each pedal adjustment mechanism and adjust if necessary to 4 27/64 inches, tolerances +000, -1/32 inch, measured from the center of the pedal adjustment mechanism assembly AN 329-41 pin to lower end of pawl. (Bell Service Bulletin 47C23 dated April 10, 1947, also covers this subject.)
2001-20-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F.28 Mark 1000, 2000, 3000, and 4000 series airplanes, that requires repetitive eddy current inspections to detect cracks in the upper girder of the two main landing gear (MLG) brackets; and repair of a cracked bracket followed by repetitive inspections, or replacement of a cracked MLG bracket with an improved bracket, as applicable. This AD also provides for an optional terminating action for certain requirements of this AD. The actions specified by this AD are intended to detect and correct cracks in the upper girder of the MLG bracket, which could progress into the vertical stiffeners of the MLG bracket and result in reduced structural integrity of the landing gear. This action is intended to address the identified unsafe condition.
2024-24-11: The FAA is adopting a new airworthiness directive (AD) for certain Cirrus Design Corporation (Cirrus) Model SR20, SR22, and SR22T airplanes. This AD was prompted by a report of failure of the upper power lever. This AD requires repetitively inspecting (visual) the upper power lever for any crack(s) and depending on the results of any visual inspection, either inspecting (fluorescent penetrant) or replacing the upper power lever. This AD also requires reporting all inspection results to the FAA. The FAA is issuing this AD to address the unsafe condition on these products.
2016-05-02: We are superseding Airworthiness Directive (AD) 2011-13-11 and AD 2013-16-09 for all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2011-13-11 required an amendment of the airplane flight manual (AFM), repetitive checks of specific centralized fault display system (CFDS) messages, an inspection of the opening sequence of the main landing gear (MLG) door for discrepancies if certain messages are found, and corrective actions if necessary. AD 2013-16-09 required an inspection to determine airplane configuration and part numbers of the landing gear control interface unit and MLG door actuators; and, for affected airplanes, repetitive inspections of the opening sequence of the MLG door, and replacement of the MLG door actuator if necessary. AD 2013-16-09 also provided optional terminating action for the repetitive inspections. This new AD reduces the interval of the MLG door opening sequence inspection, requires replacing or modifying certain MLG door actuators, andalso requires a flushing procedure to be performed when installing a new MLG door actuator. This AD was prompted by a determination that the interval of the MLG door opening sequence inspection must be reduced. We are issuing this AD to detect and correct deterioration of the damping ring and associated retaining ring of the MLG door actuator, which can sufficiently increase the friction inside the actuator to restrict opening of [[Page 12414]] the MLG door by gravity, during operation of the landing gear alternate (free-fall) extension system. This condition could prevent the full extension and/or down-locking of the MLG, possibly resulting in MLG collapse during landing and consequent damage to the airplane and injury to occupants.
2024-24-51: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Model EC225LP helicopters. The FAA previously sent this AD as an emergency AD to all known U.S. owners and operators of these helicopters. This AD was prompted by a report of a cracked main rotor hub (MRH) sleeve. This AD requires repetitively inspecting certain MRH sleeves and prohibits installing those MRH sleeves unless the inspection is done, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
47-42-05: 47-42-05 DOUGLAS: (Was Mandatory Note 2 of AD-781-1.) Applies to the Following DC-6 Airplanes: AAL Serial Numbers 42854 to 42865, Inclusive; Serial Numbers 42879 and 42880; UAL Serial Numbers 42866 to 42875, Inclusive; and Panagra Serial Numbers 42876 to 42878, Inclusive. \n\nTo be accomplished not later than August 1, 1948. \n\nIn order to prevent window curtain interference when opening emergency exit doors, remove hook assemblies, 2346313, -500, from curtain track, 5337482, and from the window curtain assemblies, 3343932-512, and replace with new slides, 1335554 and hooks 1345849 on each side of the four forward and the two aft cabin emergency exit door window frames. \n\n(Douglas Service Bulletin DC-6 No. 15 covers this same subject.)
2024-23-01: The FAA is adopting a new airworthiness directive (AD) for certain Robinson Helicopter Company Model R44 and R44 II helicopters. This AD was prompted by several reports of failed clutch actuators and failed rivets attaching the belt tension clutch actuator brackets (bracket) to the fan scroll housing. This AD requires inspecting each bracket and, depending on the results, accomplishing additional inspections or taking any necessary corrective actions. The FAA is issuing this AD to address the unsafe condition on these products.
98-09-28: This amendment adopts a new airworthiness directive (AD), applicable to all Shorts Model SD3-30 and SD3-60 series airplanes equipped with certain fire extinguishers, that requires replacement of the covers for fire extinguisher adapter assemblies that are installed on certain bulkheads with new covers that swivel to lock the extinguishers in place; and replacement of nozzles and triggers on these fire extinguishers with better fitting nozzles and stronger triggers. It also requires the installation of new fire extinguisher point placards and a revision of the Airplane Flight Manual to instruct the flight crew in the use of the new covers for these adapter assemblies. This amendment is prompted by reports that these fire extinguishers are not discharging properly because they do not fit correctly with the adapter, and that triggers on these extinguishers are failing. The actions specified by this AD are intended to ensure that, in the event of fire in the baggage bay, extinguishing agent is properly distributed within this area, and portable extinguishers operate properly; and to prevent injury to crew and passengers when a portable extinguisher is discharged.
2016-04-04: We are adopting a new airworthiness directive (AD) for all M7 Aerospace LLC Models SA26-AT, SA226-T(B), SA226-AT, SA226-T, SA226-TC, SA227-AC (C-26A), SA227-AT, SA227-BC (C-26A), SA227-CC, SA227-DC (C- 26B), and SA227-TT airplanes. This AD was prompted by information that the airplane flight manual (AFM) does not provide adequate guidance in the handling of engine failures, which may lead to reliance on the negative torque system (NTS) for reducing drag. This condition could lead the pilot to not fully feather the propeller with consequent loss of control. This AD requires inserting updates into the airplane flight manual (AFM) and/or the pilot operating handbook (POH) that will clearly establish that the NTS is not designed to automatically feather the propeller but only to provide drag protection. We are issuing this AD to correct the unsafe condition on these products.
47-02-05: 47-02-05 DOUGLAS: (Was Mandatory Note 13 of AD-762-7.) Applies to C-54 and DC-4 Aircraft. \n\n\tTo be accomplished not later than next periodic inspection. \n\n\tInspect the entire electrical system for evidence of damage due to chafing, heat, or foreign matter; and of loose terminals and connections. Pay particular attention to wiring subjected to heat from voltage regulators; the buss to the main cabin junction box; and any screws projecting into cable ducts. Correct any unsatisfactory conditions.