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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.)