Results
68-22-02: 68-22-02 ALLISON: Applies to Model 250-C18, 250-C18A, and 250-C10B engines, to wit Allison Model 250-C18 engines having compressor assemblies installed with serial numbers prior to Serial Number CAC 21073; Model 250-C18A engines having compressor assemblies installed with serial numbers prior to Serial Numbers CAC 20202; and all Model 250-C10B engines. The Allison model engines to which this AD is applicable must be modified in accordance with Allison Commercial Engine Bulletin 250 CEB-51 and 250 CEB-52 dated October 16, 1968, on or before May 1, 1969. Until modified, the engines to which this AD is applicable may be operated provided: (1) They are not operated with N1 (gas producer) rpm greater than 96.5 percent, except for "takeoff"; (2) Time operated at "takeoff" does not exceed two (2) minutes; (3) The generator load does not exceed 60 amps when the engine is operating above 70 percent N1 rpm.* NOTE: This amendment becomes effective November 1, 1968. *As a resultof these operating restrictions, the rotorcraft flight manual and certain power plant instrument markings for the Bell 206A, the Fairchild Hiller FH-1100, and the Hughes 369A and 369H helicopters in which these engines are installed may require modifications or the installation of suitable placards. The necessary information for such changes is available from the manufacturers of these helicopters.
54-21-01: 54-21-01 AC DIAPHRAGM TYPE FUEL PUMPS: Applies to All Aircraft Powered by Continental, Aircooled or Lycoming Engines Which Are Equipped With AC Diaphragm Type Fuel Pumps. Compliance required as soon as possible but not later than November 30, 1954. The occurrence of severe fuel leakage in flight, caused by loosening of AC fuel pump surge chambers, has revealed the existence of AC fuel pumps not adequately safetied to prevent loosening of the sediment bowl and the surge chamber. The following should be accomplished: 1. Inspect sediment bowl cap screw and surge chamber (if there is one) for adequate safetying. 2. If not safetied, lockwiring or equivalent must be accomplished in accordance with good aircraft practice. One acceptable method of safetying is described by Lycoming Service Bulletin No. 174.
98-04-36: This amendment adopts a new airworthiness directive (AD), applicable to all Gulfstream Model G-159 series airplanes, that requires revising the 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 amendment is prompted by results of a review of the requirements for certification of the airplane in icing conditions, new information on the icing environment, and icing data provided currently to the flight crews. The actions specified by this AD are intended to minimize the potential hazards associated with operating the airplane in severe icing conditions by providing more clearly defined procedures and limitations associated with such conditions.
2017-05-03: Main Rotor Blade
52-08-02: 52-08-02 NAVION: Applies to All Model B Aircraft and Cancels AD 51-19-03 Upon Compliance. Compliance required not later than June 15, 1952. Due to reports of engine malfunction caused by collapse of flexible ducts in the air induction system, it is necessary to replace the section P/N 146-42207 ducting between the carburetor air filter assembly and the carburetor air mix box with wire reinforced ducting, or its equivalent. (Ryan Field Service Bulletin No. 16, dated February 12, 1952, covers this same subject.) This supersedes AD 51-19-03.
73-14-04: 73-14-04 ROCKWELL INTERNATIONAL: Amdt. 39-1678. Applies to Rockwell Commander Model 112 airplanes, Serial Numbers 3 through 90 certificated in all categories. Compliance is required prior to next flight. Accomplish the following: (1) Remove engine control knobs (throttle, mixture, propeller, carburetor heat) (2) Remove cover from throttle quadrant (Royalite) (3) Remove knob from throttle friction lock (4) Remove microphone bracket (5) Remove knob from fuel selector (6) Remove forward arm rest (not applicable on all models) (7) Remove center console fuel selector insert (Royalite) (8) Remove center console cover (Royalite) (9) Remove throttle quadrant cover (aluminum) (10) Move controls to full aft position to expose cables (11) Using a sharp instrument remove the grommets which seal ends of the sliding control rod to the flex cable housing, if installed. Controls which may have these grommets are: throttle, mixture, propeller and carburetor heat (12) Remove upper engine cowl, and remove grommets from opposite ends of cables. (Do not remove grommets from ends of cowl flap controls) (13) A. Functionally check all controls for freedom of operation. B. Ascertain that no shavings from the grommets are lodged between the cable housing and movable cable. (14) Reassemble using existing hardware Rockwell International, Albany Aircraft Division, Service Bulletin, No. SB-112-5 relates to this same subject. This amendment is effective July 3, 1973, and was effective on receipt for all recipients of the telegram dated June 11, 1973, which contained this amendment.
2005-19-10: The FAA is adopting a new airworthiness directive (AD) for Turbomeca Arrius 2 F turboshaft engines. This AD requires removing from service certain serial number (SN) fuel control units (FCUs) or replacing the constant delta pressure diaphragm in those FCUs. This AD results from a report of an accident in July 2005 involving a Eurocopter EC120B helicopter. We are issuing this AD to prevent an uncommanded engine in-flight shutdown on a single-engine helicopter, resulting in a forced autorotation landing or an accident.
97-04-16: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F27 series airplanes, that requires increasing the torque value of the bolt that connects the gearbox housing assembly of the steering unit to the pivot bracket of the nose landing gear (NLG). This amendment also requires that periodic inspections of that torque value be incorporated into the FAA-approved maintenance program. This amendment is prompted by several reports that the dowel pins in the Walter Kidde nose wheel steering system were found broken and/or had elongated holes due to a reduced torque value of the subject bolt. The actions specified by this AD are intended to prevent such a reduction in the torque value, which could result in failure of the dowel pins in the Walter Kidde nose wheel steering system; this situation could result in reduced controllability of the airplane or the collapse of the NLG during landing.
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.