Results
2003-09-09: This amendment supersedes Airworthiness Directive (AD) 2002-09-13, which currently requires a one-time inspection of the fuel boost pump wiring inside and outside the boost pump reservoir and repair or replacement of the wiring as necessary on certain Cessna Aircraft Company (Cessna) Model 441 airplanes. AD 2002-09-13 resulted from several reports of chafing and/or arcing of the fuel boost pump wiring inside and outside the fuel pump reservoir. This AD retains the actions required in AD 2002-09-13, makes the one-time inspection repetitive, requires the inspection and possible replacement of the wire harness, lead wires and fuel boost pump on Model F406 airplanes, and requires eventual installation of an improved design wire harness and fuel boost pump as terminating action for the repetitive inspections. The actions specified by this AD are intended to detect, correct, and prevent chafing and/or arcing fuel boost pump wiring, which could result in arcing within the wing fuel storage system. Such a condition could lead to ignition of explosive vapor within the fuel storage system.
2002-13-09: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Pratt & Whitney JT8D-200 series turbofan engines, that currently requires revisions to the Time Limits Section (TLS) of the JT8D-200 Turbofan Engine Manual to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This AD adds additional critical life-limited parts for enhanced inspection. This AD is prompted by additional focused inspection procedures that have been developed by the manufacturer. The actions specified by this AD are intended to prevent the failure of critical, life-limited, rotating engine parts, which could result in an uncontained engine failure and damage to the airplane.
2003-09-01: This amendment adopts a new airworthiness directive (AD) that applies to all Pilatus Aircraft Ltd. (Pilatus) Model PC-6 airplanes. This AD requires you to inspect and correct, as necessary, the aileron control bellcrank assemblies at the wing and fuselage locations. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. The actions specified by this AD are intended to detect and correct increased friction in the aileron control bellcrank assemblies, which could result in failure of the aileron flight-control system. Such failure could lead to problems in controlling flight.
2003-08-14: This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas airplane models. This action requires revising the airplane flight manual (AFM) to include new operating limitations, installing placards to advise the flightcrew of certain minimum fuel levels to be maintained in the fuel tanks, and deactivating certain auxiliary fuel tanks. For fuel tanks that are not deactivated, this AD also requires replacement of certain existing fuel boost/transfer pumps with pumps inspected-and modified, if necessary-per certain procedures. Accomplishment of this replacement will allow operators to remove the operating limitations from the AFM, remove the placards, and reactivate the auxiliary fuel tanks (if deactivated). This action is necessary to prevent electrical arcing in the connector for a fuel boost/transfer pump, which could result in a fire or explosion of a fuel tank. This action is intended to address the identified unsafe condition.
2003-08-13: This amendment adopts a new airworthiness directive (AD) that is applicable to various surplus military airplanes manufactured by Consolidated, Consolidated Vultee, and Convair. This action requires repetitive inspections to find fatigue cracks in the lower rear cap of the wing front spar, front spar web, and lower skin of the wings; repair or replacement of any cracked part with a new part; and follow- on inspections at new intervals. This action is necessary to find and fix fatigue cracking, which could result in structural failure of the wings and consequent loss of control of the airplane. This action is intended to address the identified unsafe condition.
2003-04-16: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and MD-11F airplanes that requires an inspection to detect chafed wires in the avionics equipment compartment, and repair, if necessary. This amendment also requires replacement of the existing cover of the avionics cooling fan with a new cover, and installation of a new placard on the cover. Additionally, this amendment specifies which previously accomplished actions are acceptable for compliance with certain requirements of this AD; and clarifies the applicability, a part number, and the inspection definition. The actions specified by this AD are intended to ensure that the cover of the avionics cooling fans is removed only for fan maintenance, and to prevent smoke and/or fire in the avionics equipment compartment due to chafing and arcing as a result of maintenance personnel lying against the removed cover and/ or insulation blankets that cover wire harnesses. Thisaction is intended to address the identified unsafe condition.
2003-08-04: This amendment adopts a new airworthiness directive (AD) for the specified model Eurocopter France (ECF) helicopters that requires inspecting the attachment of the bolted assemblies of the cyclic pitch flight control torque tube (torque tube) for an appropriate locking device. If a bolted assembly is single-locked, the AD requires, if necessary, tightening the self-locking nuts at certain intervals and modifying the torque tube after a certain time. This amendment is prompted by the discovery that some of the attachments of the torque tube were fastened with a single-locking device instead of the intended double-locking device. The actions specified by this AD are intended to prevent separation of the cyclic pitch stick yokes from the torque tube, loss of cyclic control, and subsequent loss of control of the helicopter.
2003-07-15: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 767-300 series airplanes modified by Supplemental Type Certificate ST01783AT-D, that requires modifying the in-flight entertainment (IFE) system and revising the airplane flight manual. The actions specified by this AD are intended to ensure that the flight crew is able to remove electrical power from the IFE system when necessary and is advised of appropriate procedures for such action. Inability to remove power from the IFE system during a non- normal or emergency situation could result in inability to control smoke or fumes in the airplane flight deck or cabin. This action is intended to address the identified unsafe condition.
2003-07-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes, that requires inspection of landing gear parts and/or their records to see that parts have serial numbers and that each part's number of flight cycles has been tracked; assignment of serial numbers and flight cycle use numbers if necessary; and removal of individual landing gear components from service when they reach their life limit. This amendment also requires adding landing gear parts to the lists of safe-life components, and assigning life limits to landing gear parts already in service. The actions specified by this AD are intended to prevent failure of landing gear parts, which could lead to landing gear collapse. This action is intended to address the identified unsafe condition.
2003-07-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon airplanes, that requires inspection of the main landing gear (MLG) wheels to determine the part numbers of the tie-bolt nuts, and replacement of nuts that have the incorrect part number with nuts that have the correct part number. The actions specified by this AD are intended to prevent separation of an MLG wheel due to loose or missing tie-bolts or tie-bolt nuts, with consequent damage to airplane structure or systems, decompression, loss of full braking ability, or injury to personnel on the ground. This action is intended to address the identified unsafe condition.
2003-07-10: 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 you to replace certain push switch caps on the electrical power management overhead panel with parts of improved design. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. The actions specified by this AD are intended to prevent the inability to operate the switch, which could result in failure to activate the related operational system. Such failure could adversely affect the operation and control of the airplane.
2003-07-06: This amendment adopts a new airworthiness directive (AD) that applies to all British Aerospace Model HP.137 Jetstream Mk.1, Jetstream Series 200, Jetstream Series 3101, and Jetstream Model 3201 airplanes. This AD requires you to inspect the steering jack piston rod for cracks and replace if necessary; measure the torque setting of the steering jack piston rod end fitting and stop bolt; and measure the thickness of the tab washers. This AD also requires you to calculate a new safe life limit for the steering jack piston rod based on the results of the inspection and the measurements. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to detect, correct, and prevent cracks in the steering jack piston rod, which could result in failure of the steering jack piston rod. Such failure could lead to loss of steering control of the airplane during takeoff, landing, and taxi operations.
2001-25-51: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2001-25-51, 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 performing a dual power confirmation test on the Integrated Instrument Display System (IIDS) and inserting a revision to the Rotorcraft Flight Manual (RFM), as applicable. If the IIDS fails the power test, replacing it is required before further flight. Removing the temporary revision when the IIDS is replaced and inserting the applicable revision into the RFM is also required. This AD is prompted by the failure of the IIDS during a helicopter hover operation. The actions specified by this AD are intended to prevent total power failure of the IIDS and the subsequent inability to monitor information and warning indications essential for the operation of the helicopter.
2003-07-01: This amendment supersedes Airworthiness Directive (AD) 2000- 11-16, which currently applies to certain Quality Aerospace, Inc. (Quality Aerospace) (formerly Ayres Corporation) S2R series and Model 600 S2D airplanes. AD 2000-11-16 requires you to repetitively inspect the \1/4\-inch and \5/16\-inch bolt hole areas on the lower spar caps for fatigue cracking; replace or repair any lower spar cap where fatigue cracking is found; and report any fatigue cracking found. AD 2000-11-16 resulted from an accident of an Ayres S2R series airplane where the wing separated from the airplane in flight. Since AD 2000-11- 16, additional airplanes have been identified that were manufactured with a similar design to those affected by the AD and a third repair option has been developed. This AD retains the repetitive inspections and replacement (if necessary) requirements of the lower spar caps that are currently required in AD 2000-11-16, adds additional airplanes to the Applicability of the AD,and adds a third repair option. The actions specified by this AD are intended to detect and correct fatigue cracking of the lower spar caps, which could result in the wing separating from the airplane with consequent loss of control of the airplane.
2003-04-21 R1: This document corrects information in an existing airworthiness directive (AD) that applies to certain Bombardier Model CL-600-2B19 (Regional Jet Series 440) series airplanes. That AD currently requires replacement of the overwing emergency exit placards, door weight placards, and no baggage placards with new placards. This document corrects the applicability of AD 2003-04-21 to identify affected model designations as published in the most recent type certificate data sheet. This correction is necessary to ensure that operators of all affected airplanes accomplish the requirements of this AD. DATES: Effective April 4, 2003. The incorporation by reference of a certain publication, as listed in the regulations, was approved previously by the Director of the Federal Register as of April 4, 2003 (68 FR 9509, February 28, 2003).
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.