Results
2005-19-20: The FAA adopts a new airworthiness directive (AD) for certain The New Piper Aircraft, Inc. (Piper) Models PA-28-160, PA-28-161, PA- 28-180, and PA-28-181 airplanes that incorporate Petersen Aviation, Inc. Supplemental Type Certificate (STC) SA2660CE installed between April 20, 1998, and April 1, 2005, and incorporate Petersen Aviation, Inc. Service Bulletin SB98-1. This AD requires you to replace the AN894-6-4 bushing screw thread expanders on the gascolator and bushing attached to the inlet of the top fuel pump with NAS1564-6-4J reducers and AN818-6 nuts. This AD results from reports of fuel leaks during the post STC installation tests. We are issuing this AD to prevent fuel fittings used in STC SA2660CE from leaking fuel in the engine compartment, which could result in an engine fire. This condition could lead to loss of control of the airplane.
98-04-41: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737-200 and -300 series airplanes. This action requires repetitive inspections to detect cracks in the hinge and lift actuator box area of the main deck cargo door and upper jamb of the fuselage; and repair or replacement of any cracked part with a new part having the same part number. This amendment is prompted by a report that, during a periodic heavy maintenance check, cracks were found in the upper jamb area of the fuselage and in the main deck cargo door. The actions specified in this AD are intended to detect and correct such cracking, which could result in reduced structural integrity of the main cargo door and/or fuselage, and consequent loss or opening of the main deck cargo door while the airplane is in flight, or reduced controllability of the airplane.
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.
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.
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.
83-07-22 R1: 83-07-22 R1 PARTENAVIA COSTRUZIONI AERONAUTICHE S.p.A.: Amendment 39- 4624 as amended by Amendment 39-4700. Applies to Model P-68B, P-68C, and P-68C-TC airplanes (all S/Ns up to S/N 255 excluding S/Ns 220, 224, 227, 228, 234, 235, 236, 239, 249, 251, 252, 253, and 254) certificated in any category. Compliance: Required within the next 100 hours time-in-service, unless already accomplished. To prevent unintentional return of flaps to the zero degree position, accomplish the following: (a) Replace the flap selector switch with a new type switch, P/N 7.2345D-1 (MS25201-5) as prescribed in Service Bulletin No. 55 dated September 2, 1982. (b) Aircraft may be flown in accordance with Federal Aviation Regulation 21.197 to a location where this AD can be accomplished. (c) An equivalent method of compliance with this AD, if used, must be approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy,1000 Brussels, Belgium. Amendment 39-4624 became effective on April 14, 1983. This Amendment 39-4700 becomes effective August 9, 1983.