Results
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.
63-03-02: 63-03-02 CANADAIR: Amdt. 533 Part 507 Federal Register February 6, 1963. Applies to all Model CL-44D4 aircraft. Compliance required as indicated. As a result of failure of a riveted rudder lower balance weight, the following must be accomplished: (a) Prior to each departure from the principal maintenance base, inspect the rudder bottom closing rib for any indication of a balance weight becoming detached and dropping on to the rib. If so found, repair per (c) prior to further flight. (b) Within the next 35 hours' time in service after the effective date of this AD, unless already accomplished, inspect the rivet attachment of the two weights (P/N 28-21250-16) to the bottom rudder balance weight assembly (P/N 28-21250-14). There are five 1/8-inch rivets per weight, a total of ten for the entire assembly. If any looseness or failure of the rivets is found, replace all rivets with bolts in accordance with (c). (c) Within the next 250 hours' time in service after theeffective date of this AD, replace the ten 1/8-inch rivets referred to in (b) with AN 509-10R-30 bolts, AN 960-10 washers and NAS 679A3W lock nuts. This requires countersinking the aft face of the P/N 28-21250-14 assembly to accommodate the bolt heads. When this modification has been accomplished, the inspection in (a) may be discontinued. (Canadair Service Information Circular 262-CL44D4 covers this subject.) This directive effective February 6, 1963.
2005-19-11: The FAA is adopting a new airworthiness directive (AD) for certain Lycoming Engines (formerly Textron Lycoming) AEIO-360, IO-360, O-360, LIO-360, LO-360, AEIO-540, IO-540, O-540, and TIO-540 series reciprocating engines rated at 300 horsepower (HP) or lower. This AD requires replacing certain crankshafts. This AD results from reports of 12 crankshaft failures in Lycoming 360 and 540 series engines rated at 300 HP or lower. We are issuing this AD to prevent failure of the crankshaft, which could result in total engine power loss, in-flight engine failure, and possible loss of the aircraft.
2016-08-01: We are adopting a new airworthiness directive (AD) for all Dassault Aviation Model FALCON 7X airplanes. This AD was prompted by reports of multiple cases of ram air turbine (RAT) blade damage. This AD requires deployment of the RAT, replacement of the RAT placard with a new RAT placard, and re-identification of the RAT. We are issuing this AD to prevent blade damage to the RAT, which could prevent RAT deployment in flight during an emergency, possibly resulting in reduced control of the airplane.
98-04-16: This amendment adopts a new airworthiness directive (AD) that applies to certain Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes. This AD requires inspecting the aileron tie-rod jam nuts for looseness, tightening any loose jam nuts, and installing a locking sleeve on both ends of the aileron tie-rod in the chain-drive of the aileron system. The AD results from an incident where the aileron tie-rod jam nuts on the chain-drive of the aileron system became loose. This caused a differential of aileron control between the pilot's control wheel and the co-pilot's control wheel. The actions specified by this AD are intended to prevent such aileron control differential caused by the aileron tie-rod jam nuts becoming loose, which could result in loss of aileron control and consequent loss of control of the airplane.