Results
2003-05-09: This amendment adopts a new airworthiness directive (AD) that is applicable to all Dassault Model Falcon 2000 and Mystere-Falcon 900 series airplanes. This action requires a one-time inspection to detect discrepant wires in the fire control panel for the engines and auxiliary power unit (APU), and corrective action if necessary. This action is necessary to ensure that the correct wires are installed in the fire control panel so that the flight crew can activate the fire extinguishers in the event of an engine or APU fire. This action is intended to address the identified unsafe condition.
2002-21-06: This document corrects information in an existing airworthiness directive (AD) that applies to all McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD- 87), and MD-88 airplanes. That AD currently requires revisions to the Airplane Flight Manual; installation of inspection aids on the wing upper surfaces; and, among other actions, installation of an overwing heater blanket system or primary upper wing ice detection system, and installation of a heater protection panel or an equipment protection device on certain overwing heater blanket systems. That AD also requires disabling the anti-ice systems for the upper wing surface on certain airplanes. This document corrects a reference to an incorrect paragraph. This correction is necessary to provide the correct paragraph reference. \n\nDATES: Effective November 8, 2002.\n\n\tThe incorporation by reference of certain publications listed in the regulations was approved previously by the Director of the Federal Register as of November 8, 2002 (67 FR 65298, October 24, 2002).\n\n\tThe incorporation by reference of certain publications, as listed in the regulations, was approved previously by the Director of the Federal Register as January 17, 1992 (57 FR 2014, January 17, 1992).\n\n\tThe incorporation by reference of certain other publications, as listed in the regulations, was approved previously by the Director of the Federal Register as of May 7, 2001 (66 FR 17499, April 2, 2001).
2003-05-11: This amendment supersedes an existing emergency airworthiness directive (EAD), which was sent previously to all known U.S. owners and operators of Bell Helicopter Textron Canada (Bell) helicopters by individual letters. That EAD requires a visual check to ensure that the two swashplate drive link cup washers (cup washers) are installed correctly. If a cup washer is installed incorrectly, removing and replacing the swashplate outer ring, each cup washer, bearing and liner, and drive link where the cup washer was installed incorrectly are also required. This amendment requires the same actions as the existing EAD, but clarifies that only the visual check may be performed by the owner/operator. This amendment is prompted by two reported failures of the stud portion of the swashplate drive link. The actions specified by this AD are intended to detect an incorrectly installed cup washer, which could limit the travel of the swashplate outer ring and lead to failure of the stud portion of the swashplate drive link, and subsequent loss of control of the helicopter.
96-23-12: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Jetstream Model 4101 airplanes. This action requires a one-time check of the left and right main landing gear leg assemblies to determine whether certain assemblies have been installed; and the replacement of certain discrepant retaining bolts on these assemblies with correctly manufactured bolts. This amendment is prompted by a report indicating that some of these retaining bolts have failed during the assembly and installation of a main landing gear unit, due to an incorrect process that was used during the manufacture of the bolts. The actions specified in this AD are intended to prevent structural damage to the main landing gear due to failure of the retaining bolts which, if not corrected, could result in reduced controllability of the airplane during takeoff, landing, and taxiing.
2003-05-07: This amendment adopts a new airworthiness directive (AD), that is applicable to Pratt & Whitney (PW) JT8D-1, -1A, -1B, -7, -7A, -7B, - 9, -9A, -11, -15, -15A, -17, -17A, -17R, and -17AR turbofan engines. This amendment requires removal from service of certain part number (P/ N) 3rd-4th and 4th-5th stage compressor rotor spacer assemblies and incorporation of a new tierod retention configuration. This amendment is prompted by two reports of uncontained failure of JT8D turbofan engines, caused by turbine rotor overspeed resulting from first and second stage fan section separation from the low pressure compressor (LPC). The actions specified by this AD are intended to prevent first and second stage fan section separation from the LPC, resulting in turbine rotor overspeed, uncontained engine failure, and damage to the airplane.
2003-04-11: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-200B and -200F series airplanes powered by Pratt & Whitney JT9D-70 series engines, that requires repetitive detailed inspections of the pylon skin and internal structure of the nacelle struts adjacent to and aft of the precooler exhaust vent for heat damage (discoloration), wrinkling, and cracking; and corrective action, if necessary. The actions specified by this AD are intended to find and fix such damage, which could result in cracking or fracture of the nacelle struts, and consequent reduced structural integrity and possible separation of the strut and engine from the airplane. This action is intended to address the identified unsafe condition.
2003-04-19: This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F.28 Mark 0070 and 0100 series airplanes, that requires a one-time general visual inspection to detect any missing attachment bolts in the replaceable frame struts, and corrective actions, if necessary. This action is necessary to prevent excessive deformation of the floor structure in the event of rapid decompression in the lower cargo hold due to missing attachment bolts in the replaceable frame struts. Such deformation may result in the flight and engine control cables becoming jammed, and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2003-04-21: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 (Regional Jet Series 440) series airplanes, that requires replacement of the overwing emergency exit placards, door weight placards, and no baggage placards with new placards. This action is necessary to prevent the inability of a passenger to open and dispose of the overwing emergency exit door during an emergency evacuation due to incorrect placards. This action is intended to address the identified unsafe condition.
54-05-02: 54-05-02 SENSENICH: Applies to All Model M76AM-2 Propellers Installed on Lycoming Models O-290-D and O-290-D2 Engines. Compliance required by March 15, 1954, and at intervals not to exceed each 25 hours operation thereafter. To eliminate the possibility of blade tip failures on Model M76AM-2 propellers installed on the above Lycoming engines, all nicks, gouges and scratches within 8 inches of the blade tip should be removed. Care should be taken to be sure all trace of the damage is removed. Minor damaged areas may be removed by using coarse emery cloth. The repaired area should then be polished with fine emery cloth. Rebalancing is not necessary when repairing minor damage areas as defined in Civil Aeronautics Manual 18 (18.30-15) (Sensenich Service Bulletin No. R-2 covers this same subject.)
2003-04-02: This amendment supersedes Airworthiness Directive (AD) 98-12-10 and AD 99-21-23, which currently apply to APEX Aircraft (APEX) Model CAP 10B airplanes. AD 98-12-10 requires installing an inspection opening in the wing, repetitively inspecting the upper and lower wing spars for structural cracking, and, if any cracks are found, repairing the cracks in accordance with a repair method. AD 99-21-23 requires restricting the entry speed for performing flick maneuvers to 97 knots, inserting a copy of the AD into the Limitations Section of the CAP 10B flight manual, and fabricating and installing a placard (in the cockpit of the airplane within the pilot's clear view) that indicates this limitation. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. This AD retains the wing modification and repair requirements from AD 98-12-10. This AD also incorporates new repetitive inspection procedures, further reduces the flick maneuver speed specified in AD 99-21-23, and temporarily reduces the load factor limits prior to the initial inspection. The actions specified by this AD are intended to provide the flight information necessary to the pilot so that excessive speed is not used during aerobatic maneuvers and to detect and correct structural cracks in the wing spar, which could result in the wing separating from the airplane. Such failure could lead to loss of control of the airplane.
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.