Results
2017-02-01: We are adopting a new airworthiness directive (AD) for certain Rolls-Royce plc (RR) Trent 1000-A, Trent 1000-C, Trent 1000-D, Trent 1000-E, Trent 1000-G, and Trent 1000-H turbofan engines. This AD requires initial and repetitive inspections of affected high-pressure turbine (HPT) blades for cracks. This AD was prompted by high engine vibration due to HPT blade deterioration resulting in operational disruptions. We are issuing this AD to correct the unsafe condition on these products.
2010-19-51: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2010-19-51, which was sent previously to all known U.S. owners and operators of the specified model Bell Helicopter Textron Canada (Bell) helicopters by individual letters. This AD requires inspecting parts of the main rotor hydraulic servo actuator (servo actuator) for certain conditions and replacing any unairworthy parts before further flight. This AD is prompted by a collective servo actuator malfunction and a subsequent investigation that revealed the output piston rod assembly (piston rod) had fractured at the threaded end because of stress corrosion cracking. Also, during the investigation of that servo actuator malfunction, a nonconforming grind relief was discovered on a separate piston rod. The actions specified by this AD are intended to detect corrosion or a nonconforming piston rod that, if not detected and corrected, could result in failure of the piston rod, failure of the servo actuator, and subsequent loss of control of the helicopter.
2005-19-08: The FAA is adopting a new airworthiness directive (AD) for all transport category airplanes listed above. This AD requires repetitive inspections for cracks of the main landing gear (MLG) shock strut cylinder, and related investigative and corrective actions if necessary. This AD results from two reports of a collapsed MLG and a report of cracks in two MLG cylinders. We are issuing this AD to detect and correct fatigue cracks in the shock strut cylinder of the MLG, which could result in a collapsed MLG during takeoff or landing, and possible reduced structural integrity of the airplane.
70-15-10: 70-15-10 BRITISH AIRCRAFT CORPORATION: Amdt. 39-1039. Applies to Model BAC 1-11 200 and 400 series airplanes which do not have BAC Modification PM3791 (or Normalair Modification No. 271 TC) incorporated. To prevent penetration of compressor wheel shroud fragments through the air conditioning system cold air unit compressor scrolls in the event of compressor failure, within the next 1,200 hours' time in service after the effective date of this AD, unless already accomplished, install containment guards on the cold air units P/N 12-525350 (R.H.) and P/N 13-525350 (L.H.) in accordance with Normalair-Garrett, Ltd., Service Bulletin No. 21-314 dated August 18, 1969, or later ARB-approved issue, or an FAA-approved equivalent. (British Aircraft Corporation Model BAC 1-11 Service Bulletin No. 21-PM4350 refers to this subject.) This amendment becomes effective August 16, 1970.
98-04-29: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 727 series airplanes, that requires a one-time visual inspection of the manual extension gearbox assembly of the main landing gear (MLG) to detect whether certain gearbox housings have been installed; repetitive dye penetrant inspections of these housings to determine whether cracking has occurred; and ultimately, replacement of these housings with correct housings. This amendment is prompted by a report indicating that a manual gearbox assembly which contained an incorrect housing was installed on a Model 727 series airplane. The actions specified by this AD are intended to detect the installation of manual extension gearbox assemblies with incorrect housings. This condition, if not corrected, could reduce the structural integrity of the manual extension gearbox assembly, and ultimately result in an inability to lock the MLG in a down position during landing.
98-04-23: This amendment adopts a new airworthiness directive (AD) that applies to Aerostar Aircraft Corporation Models PA-60-600, PA-60-601, PA-60-601P, PA-60-602P, and PA-60-700P airplanes. This action requires revising the FAA-approved Airplane Flight Manual (AFM) to specify procedures that would prohibit flight in severe icing conditions (as determined by certain visual cues), limit or prohibit the use of various flight control devices while in severe icing conditions, and provide the flight crew with recognition cues for, and procedures for exiting from, severe icing conditions. This AD is prompted by the results of a review of the requirements for certification of these airplanes in icing conditions, new information on the icing environment, and icing data provided currently to the flight crew. The actions specified by this AD are intended to minimize the potential hazards associated with operating these airplanes in severe icing conditions by providing more clearly defined procedures and limitations associated with such conditions.
59-05-01: 59-05-01 BELL: Applies to All Model 47 Helicopters Having Metal Tail Rotor Blades, P/N's 47-642-102-1; -5; -7; -9; -17; and -19 Installed. Compliance required as indicated. As a result of several cracks having occurred (in most instances following known damage due to the tail rotor striking water, tall grass, or underbrush) the following inspection of the metal tail rotor blades, to preclude loss of tail rotor control, must be accomplished as indicated: (1) On trailing edge of blade, remove paint in the area of Numbers 3, 4, 5 and 6 rivets to the bare metal, with a suitable lacquer thinner only. Feather edges of remaining paint with thinner. DO NOT use sandpaper, steel-wool, or other sharp objects to remove paint. DO NOT use a paint stripper. NOTE: The removal of paint does not affect the balance. (2) Visually inspect for chordwise cracks along the trailing edge of blade, in the area of rivets Numbers 3, 4, 5 and 6 counting from the butt end towards tip end.It is mandatory that the tail rotor blades be replaced if any cracks are found. (3) If no cracks are found, it is mandatory that the bare metal portion of blades be left unpainted to facilitate daily inspection. To protect the bare metal, a thin coat of clear lacquer, cosmolene, or grease shall be applied to the area. (4) Tail rotor blades, installed on float equipped helicopters or which have had any service time on float equipped helicopters, shall be inspected prior to each flight. (5) Tail rotor blades installed on helicopters not operated on floats shall be inspected daily. (Bell Service Bulletin No. 128SB, dated January 27, 1959, covers the same subject.)
2005-19-09: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747 airplanes. This AD requires repetitive inspections of the dual side braces (DSBs), underwing midspar fittings, and associated parts; other specified actions; and corrective actions if necessary. This AD also provides an optional terminating action for the inspections and other specified actions. This AD is prompted by reports of corroded, migrated, and rotated bearings for the DSBs in the inboard and outboard struts, a report of a fractured retainer for the eccentric bushing for one of the side links of a DSB, and reports of wear and damage to the underwing midspar fitting on the outboard strut. We are issuing this AD to prevent the loss of a DSB or underwing midspar fitting load path, which could result in the transfer of loads and motion to other areas of a strut, and possible separation of a strut and engine from the airplane during flight.
2017-04-01: We are adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace Corporation Model GVI airplanes. This AD was prompted by a report indicating that there are design deficiencies in the software used for monitoring the disconnect for the flight control computer (FCC)-hosted flight controls actuation main ram linear variable differential transducer (LVDT). This AD requires an update of the FCC software. We are issuing this AD to address the unsafe condition on these products.
2016-24-08: We are adopting a new airworthiness directive (AD) for all \n\n((Page 86568)) \n\nRolls-Royce plc (RR) RB211-Trent 875-17, RB211-Trent 877-17, RB211- Trent 884-17, RB211-Trent 884B-17, RB211-Trent 892-17, RB211-Trent 892B-17, and RB211-Trent 895-17 turbofan engines. This AD requires repetitive inspections of the engine upper bifurcation fairing and repairing or replacing any fairing that fails inspection. This AD was prompted by a report of cracking and material release from an engine upper bifurcation fairing. We are issuing this AD to prevent failure of the engine fire protection system, engine fire, and damage to the airplane.