Results
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.