Results
2003-04-04: This amendment adopts a new airworthiness directive (AD) for Robinson Helicopter Company (RHC) Model R22 helicopters that requires inspecting the tail rotor pitch control assembly for roughness or binding of the pitch control bearings (bearings) by hand-rotating the pitch control bearing housing (housing). If the housing does not rotate freely, the AD requires replacing the unairworthy pitch control assembly with an airworthy unit. This amendment is prompted by reports of failure of the tail rotor pitch control assembly due to improperly lubricated bearings on the RHC Model R22 helicopters. The actions specified by this AD are intended to detect corrosion of the bearings and to prevent bearing failure and subsequent loss of directional control of the helicopter.
2003-03-23: This amendment adopts a new airworthiness directive (AD) that is applicable to certain EMBRAER Model EMB-135 and -145 series airplanes. This action requires replacement of the horizontal stabilizer control units (HSCUs) with new upgraded HSCUs, and corrective actions if necessary. This action is necessary to prevent reversal of the pilot's pitch trim command for the horizontal stabilizer, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
92-13-02: 92-13-02 AEROSPATIALE: Amendment 39-8272. Docket No. 92-NM-19-AD. Applicability: Aerospatiale Model SN 601 Corvette series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent structural failure of the fuselage and associated decompression of the passenger cabin, accomplish the following: (a) Prior to the accumulation of 18,200 landings, or within 100 landings after the effective date of this AD, whichever occurs later, inspect the skin panels between Frame FR17 and FR19, on the right side below stringer 11, to detect cracks, using an eddy current procedure, in accordance with Aerospatiale Corvette Service Bulletin 53-24, dated January 25, 1991. (b) If no cracks are found as a result of the inspection required by paragraph (a) of this AD, repeat the eddy current inspection thereafter at intervals not to exceed 7,300 landings. (c) If any crack is found as a result of any inspection required by this AD, prior to further flight, install Modification 1399, in accordance with Aerospatiale Corvette Service Bulletin 53-15, dated January 22, 1991. (d) Installation of Modification 1399, in accordance with Aerospatiale Corvette Service Bulletin 53-15, dated January 22, 1991, constitutes terminating action for the requirements of this AD. (e) An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from Standardization Branch, ANM-113. (f) Special flight permits may beissued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (g) The inspections and modifications shall be done in accordance with Aerospatiale Corvette Service Bulletin 53-24, dated January 25, 1991; and Aerospatiale Corvette Service Bulletin 53-15, dated January 22, 1991. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, DC. (h) This amendment becomes effective on July 23, 1992.
2003-03-08: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, DC-9-20, DC-9- 30, DC-9-40, and DC-9-50 series airplanes, that requires a one-time inspection at a certain disconnect panel in the left forward cargo compartment to find contamination of electrical connectors and to determine if a dripshield is installed over the disconnect panel, and corrective actions if necessary. The actions specified by this AD are intended to find and fix contamination of certain electrical connectors and prevent future contamination of these connectors, which could cause electrical arcing that could result in a fire on the airplane. This action is intended to address the identified unsafe condition.
2003-03-04: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A300 B2 and B4; A300 B4-600, B4-600R, and F4-600R (collectively called A300-600); A310; and certain Airbus Model A319; A320; A321; A330; and A340 series airplanes, that requires repetitive visual inspections of the striker and guide valve of the passenger door actuators and certain emergency door actuators for corrosion, and corrective action, if necessary. This AD also requires modification of the striker mechanism of the emergency and passenger door actuators, which terminates the repetitive inspections. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent corrosion of the emergency actuator mechanism, which could cause failure of the emergency actuator striker mechanism on the passenger or emergency doors, and lead to difficulty in opening the passenger or emergency doors during an emergency evacuation.
2003-03-10: This amendment adopts a new airworthiness directive (AD), applicable to all BAE Systems (Operations) Limited Model BAe 146 and Avro 146-RJ series airplanes, that requires replacement of the existing "Low Temp" terminal blocks "G" with new, fireproof ceramic terminal blocks "G" in engine zones 412, 422, 432, and 442. This action is necessary to prevent failure of the engine fire detection and suppression systems to operate properly in the event of a fire due to failure of non-fireproof terminal blocks, which could result in an undetected and uncontrollable fire in an engine. This action is intended to address the identified unsafe condition.
2003-03-05: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 737-300, -400, and -500 series airplanes, that currently requires replacement, with new parts, of the existing actuators or the rod ends on the existing actuators at wing leading edge slat positions 1, 2, 5, and 6. This amendment adds a one-time inspection of all the rod ends on the actuators of the wing leading edge slats to determine if vibro-engraving was used to identify the parts, and corrective action, if necessary. This amendment is prompted by reports indicating that vibro-engraving was found on new rod ends during installation; such part markings create stress risers that reduce the fatigue life of the rod ends. The actions specified by this AD are intended to prevent fatigue cracking, which could result in failure of the rod ends, uncommanded deployment of the wing leading edge slat, and consequent reduced controllability of the airplane. This action is intended toaddress the identified unsafe condition.
2003-02-07: This amendment adopts a new airworthiness directive (AD), that is applicable to General Electric Company CF6-50 and CF6-80C2 turbofan engines. This amendment requires replacement of certain existing CF6-50 and CF6-80C2 low pressure turbine (LPT) shrouds with new design LPT shrouds. This amendment is prompted by 37 LPT uncontained events on the CF6-50, 24 uncontained events on the CF6-80C2 engine models since 1993, and the development and certification of newly designed shrouds that will improve LPT containment capability. The actions specified by this AD are intended to prevent uncontained engine failure and possible airplane damage.
2003-02-03: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) 65, 90, 99, 100, 200, and 300 series, and Model 2000 airplanes. This AD requires you to install new exterior operating instruction placards for the airstair door and emergency exits. This AD is the result of Raytheon improving the visibility and understandability of the door operating instruction placards. This was done as a result of difficulty opening the emergency exits of a similar type design airplane. The actions specified by this AD are intended to assure that clear and complete operating instructions are visible for opening the airstair door and emergency exits. If the operating instructions are not visible or understandable, this could result in the inability to open the airstair door or emergency exits during an emergency situation.
2003-02-01: This amendment adopts a new airworthiness directive (AD) that is applicable to Honeywell International, Inc., (formerly AlliedSignal, Inc. and Textron Lycoming) ALF502L-2, ALF502L-2C, ALF502R-3 and ALF502R-3A series turbofan engines. This action requires inspection of the flow divider primary, secondary, and drain tube assemblies for security and proper clamping. This amendment is prompted by a fire in the engine nacelle of an ALF502L-2C powered airplane caused by fracture of the flow divider left primary fuel tube, due to high-cycle fatigue resulting from a missing support clamp. The actions specified in this AD are intended to prevent fire in the engine nacelle, in-flight shutdown, and possible damage to the engine.
2003-01-05: This amendment adopts a new airworthiness directive (AD) that is applicable to General Electric Co. (GE) CF6-80A series turbofan engines. This action requires the following initial and repetitive inspections of certain part number (P/N) stage 1 high pressure turbine (HPT) rotor disks for cracks: Etch preparations and fluorescent penetrant inspections. Visual inspections. Eddy current inspections. This amendment is prompted by a Boeing 767 airplane recently experiencing a stage 1 HPT rotor disk separation resulting in uncontained engine failure. The actions specified in this AD are intended to detect cracks in the bottoms of the dovetail slots that could propagate to failure of the disk and cause an uncontained engine failure.
2002-26-16: This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F.28 Mark 0070 and 0100 series airplanes, that requires measurement of the over-center force of the thrust reverser operating levers, a functional test of the secondary lock solenoid of the thrust reversers, and corrective actions if necessary. The actions specified by this AD are intended to detect and correct an insufficient over-center force in the corresponding thrust reverser operating lever, and incorrect setting of the thrust reverser selector switch (S9), which could result in uncommanded deployment of the thrust reversers during flight and consequent reduced controllability of the airplane. This AD is intended to address the identified unsafe condition.
2002-26-19: This amendment adopts a new airworthiness directive (AD), applicable to all Saab Model SAAB 2000, SAAB SF340A, and SAAB 340B series airplanes, that requires replacing the main pitot static tube on each side of the airplane with a new improved pitot static tube, and installing a gasket between the tube and the airplane structure. The actions specified by this AD are intended to prevent ice from blocking the pitot system, due to the pitot tube not having enough heating capacity to stay above freezing temperature, which could result in erroneous airspeed indications. This action is intended to address the identified unsafe condition.
2002-26-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 757-200 series airplanes with stowage bins installed forward of door 2 at Station 680. This AD requires a one-time inspection to determine if a certain intercostal is installed for support of the overhead stowage bin(s) at Station 680, and follow-on actions, if necessary. This action is necessary to prevent failure of the stowage bin attachment fitting at Station 680, which could result in the overhead stowage bin falling onto the passenger seats below and injuring passengers or impeding the evacuation of passengers in an emergency. This action is intended to address the identified unsafe condition.
2002-26-18: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-600, -700, -700C, -800, and -900 series airplanes, that requires replacement of the existing fueling float switch and conduit assemblies in the main and center fuel tanks with new, improved assemblies. The actions specified by this AD are intended to prevent fluid contamination inside the fueling float switch or chafing of the wiring to the in-tank conduit, which could generate an ignition source and consequent fire and explosion in the fuel tank. This action is intended to address the identified unsafe condition.
2002-24-52: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2002-24-52 that was sent previously to all known U.S. owners and operators of all Boeing Model 747-400, -400D, and -400F series airplanes by individual notices. This AD continues to require revising the Airplane Flight Manual to require the flightcrew to maintain certain minimum fuel levels in the center fuel tanks, and to prohibit the use of the horizontal stabilizer fuel tank. This AD also removes the reference to placards that was specified in the operating limitations required by another AD. This action is prompted by reports indicating that two fuel pumps showed evidence of extreme localized overheating of parts in the priming and vapor pump section of the fuel pump. Such overheating provides an ignition source in the fuel tank during dry running of the pump, which could result in fire/explosion of the fuel tank. The actions specified by this AD are intended to require the flightcrew to maintain certain minimum fuel levels in the center fuel tanks, and to prohibit the use of the horizontal stabilizer fuel tank.
2002-20-06: This amendment adopts a new airworthiness directive (AD), applicable to all Gulfstream Aerospace LP Model Astra SPX and 1125 Westwind Astra series airplanes, that requires revising the Airplane Flight Manual to advise the flightcrew to don oxygen masks as a first and immediate step following a cabin altitude alert. This action is necessary to prevent incapacitation of the flightcrew due to lack of oxygen. This action is intended to address the identified unsafe condition.
2002-25-07: This amendment supersedes an existing airworthiness directive (AD) for the specified Bell Helicopter Textron Canada Limited (BHTCL) model helicopters that currently requires removing the horizontal stabilizer supports and inspecting the edges of the tailboom skins around the horizontal stabilizer openings for a crack. This amendment requires checking and inspecting the tailboom for a crack and modifying or replacing the tailboom as necessary. This amendment also provides a terminating action, incorporates a more recent alert service bulletin (ASB), and increases the compliance time for performing the inspections. This amendment is prompted by several reports of cracks found during mandatory inspections. The actions specified by this AD are intended to detect a crack in the tailboom skin and to prevent separation of the tailboom and subsequent loss of control of the helicopter.
2002-25-04: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, -20, -30, -40, and -50 series airplanes, and C-9 (military) airplanes, that requires a one-time visual inspection of circuit breakers to determine the manufacturer of the circuit breakers, and corrective action, if necessary. The actions specified by this AD are intended to prevent internal overheating and arcing of circuit breakers and airplane wiring due to long-term use and breakdown of internal components of the circuit breakers, which could result in smoke and fire in the flight compartment and main cabin. This action is intended to address the identified unsafe condition.
2002-22-51: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2002-22-51, which was sent previously to all known U.S. owners and operators of MD Helicopters, Inc. (MDHI) Model MD900 helicopters by individual letters. This AD requires, before further flight, certain procedures and inspections of the main rotor support static mast (mast) and the mast threads for any crack or pitting. If any crack or pitting is found, this AD requires removing the mast from service. The actions specified by this AD are intended to detect any crack or pitting in the mast that could result in failure of the mast, separation of the main rotor, and subsequent loss of control of the helicopter.
2002-24-04: This amendment adopts a new airworthiness directive (AD) that is applicable to all Airbus Model A300 B2 and B4 series airplanes; A300 B4-600, B4-600R, and F4-600R (collectively called A300-600) series airplanes; and Model A310 series airplanes. This amendment requires revising the Airplane Flight Manual to advise the flightcrew to don oxygen masks as a first and immediate step when the cabin altitude warning horn sounds. This action is necessary to prevent incapacitation of the flightcrew due to lack of oxygen, which could result in loss of control of the airplane. This action is intended to address the identified unsafe condition.
2002-23-08: This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce plc. (RR) models RB211-535E4-37, RB211-535E4-B-37, and RB211-535E4-B-75 turbofan engines, with certain part number (P/N) low pressure (LP) turbine stage 2 discs installed. This action requires establishing new reduced LP turbine stage 2 disc cyclic limits. This action also requires removing from service affected discs that already exceed the new reduced cyclic limit, and removing other affected discs before exceeding their cyclic limits, using a drawdown schedule. The actions specified in this AD are intended to prevent LP turbine stage 2 disc failure, which could result in uncontained engine failure and possible loss of the airplane.
2002-23-13: This amendment adopts a new airworthiness directive (AD), that is applicable to Pratt & Whitney Canada PT6A series turboprop engines that have certain turbine exhaust ducts that were modified by a number of different companies. This amendment requires inspections for low-quality welds and cracks of a large population of turbine exhaust ducts. This amendment is prompted by reports of cracks along the weld seams of certain turbine exhaust ducts. The actions specified by this AD are intended to prevent failure of the turbine exhaust duct due to cracking that could result in possible separation of the reduction gearbox and propeller from the engine, and possible loss of control of the airplane.
2002-23-18: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes equipped with certain Collins LRA-900 radio altimeters, that currently requires a revision to the Airplane Flight Manual to prohibit autopilot coupled autoland operations in certain conditions; or, for certain airplanes, replacement of certain Collins LRA-900 radio altimeters with Collins LRA-700 radio altimeters. This amendment also requires a one-time inspection to determine whether a Collins LRA-900 radio altimeter receiver/transmitter with a certain part number is installed, and modification of such a radio altimeter. This amendment is prompted by reports indicating that a fault in Collins LRA-900 radio altimeters having a certain part number could result in an incorrect and unbounded output of radio altitude to other airplanes. The actions specified by this AD are intended to prevent an undetected anomalous radio altitude signal that ispassed along to the flare control law of the flight control computer, which could cause the airplane to flare too high or too low during landing, and consequently result in a hard landing. This action is intended to address the identified unsafe condition.
2002-23-03: This amendment adopts a new airworthiness directive (AD) for MD Helicopters, Inc. (MDHI) Model MD900 helicopters that requires inspecting and, if necessary, repairing the longitudinal drive link (drive link) and modifying certain nonrotating swashplate (swashplate) assemblies. This AD also requires recording compliance with the AD on a component history card or equivalent record. This amendment is prompted by reports of damage to the drive link assembly caused by the sharp inner edge of the bushing in the swashplate assembly. The actions specified by this AD are intended to prevent damage to the drive link, loss of control of the main rotor system, and subsequent loss of control of the helicopter.