Results
2020-21-14: The FAA is adopting a new airworthiness directive (AD) for all ATR--GIE Avions de Transport R(eacute)gional Model ATR72 airplanes. This AD was prompted by reports of main landing gear (MLG) hinge pins found cracked or thermally abused. This AD requires replacing certain MLG hinge pins with serviceable parts, or replacing an MLG equipped with any affected MLG hinge pin with an MLG equipped with serviceable MLG hinge pins, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
95-21-15: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Teledyne Continental Motors (TCM) reciprocating engines installed on certain aircraft identified by registration numbers. This action supersedes priority letter AD 94-14-12 that currently requires engines certified to operate on 91 octane or higher aviation gasoline (avgas) to undergo a teardown and analytical inspection for detonation damage, and engines certified to operate on 80 octane avgas to undergo inspection for evidence of possible internal engine damage. This action revises incorrect engine model numbers and aircraft registration numbers listed in the priority letter AD. This amendment is prompted by the Federal Aviation Administration (FAA) receiving more accurate information concerning which aircraft were fueled with the contaminated mixture at the affected airports. The actions specified by this AD are intended to prevent detonation due to low octane, which can result in severe engine damage and subsequent failure.
2008-14-14: We are adopting a new airworthiness directive (AD) for certain Boeing Model 747-400 and 747-400D series airplanes. This AD requires a general visual inspection of the power feeder wire bundle of the auxiliary power unit (APU) where it crosses the hydraulic system 4 return tube to determine if parts are installed to provide separation between the wire bundle and hydraulic tube. This AD also requires related investigative and corrective actions if necessary. This AD results from a report that the power feeder wire bundle of the APU was found touching the hydraulic system return tube during inspection of an airplane. We are issuing this AD to prevent insufficient clearance between the wire bundle and hydraulic tube that could lead to chafing of the wire bundle, which could cause arcing and a consequent hydraulic fluid fire in an area outside of the smoke detection and fire extinguishing zone; this condition could result in an uncontrolled fire on the airplane.
2001-21-04: This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F.28 Mark 0070 and 0100 series airplanes, that requires revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness to incorporate life limits for certain items and inspections to detect fatigue cracking in certain structures. 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 ensure that fatigue cracking of certain structural elements is detected and corrected; such fatigue cracking could adversely affect the structural integrity of these airplanes. This action is intended to address the identified unsafe condition.
2020-21-02: The FAA is adopting a new airworthiness directive (AD) for Kidde Aerospace & Defense cargo fire extinguisher halon bottles installed on various transport category airplanes. This AD was prompted by a report indicating that certain cargo fire extinguisher halon bottles installed in the cargo compartment had low charge pressure. This AD requires an inspection to determine the part number and serial number of the cargo fire extinguisher halon bottles and replacement of affected parts with serviceable parts. The FAA is issuing this AD to address the unsafe condition on these products.
95-23-10: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 737 series airplanes, that requires revising the FAA-approved Airplane Flight Manual (AFM) to provide the flightcrew with additional procedures for shutting down the auxiliary power unit (APU) when an APU fire is indicated. This amendment is prompted by reports indicating that a latent electrical failure exists in the fire extinguishing system for the APU; this failure could prevent the APU from shutting down and fire extinguishant from discharging into the APU compartment in the event of an APU fire. The actions specified by this AD are intended to ensure that the flightcrew is provided with procedures for shutting down the APU in the event of an APU fire.
2005-07-19: The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD requires repetitive inspections for cracks in the fuselage skin, doubler, bearstrap, and frames surrounding the main, forward, and aft cargo doors; and repair of any cracking. This AD also requires inspections of certain existing repairs for cracking, and related corrective action if cracking is found. This AD is prompted by reports of multiple fatigue cracks in the fuselage skin and bonded skin doubler, bearstrap, and doorway frames surrounding the forward and aft cargo doors. We are issuing this AD to find and fix fatigue cracking in the fuselage skin, doubler, bearstrap, and frames, which could result in reduced structural integrity of the frames, possible loss of a cargo door, and consequent rapid decompression of the fuselage.
95-22-12: This amendment supersedes an existing airworthiness directive (AD), applicable to Hamilton Standard 14RF, 247F, 14SF, and 6/5500/F (formerly Hamilton Standard/British Aerospace 6/5500/F) series propellers, that currently requires initial and repetitive inspections of the propeller control unit (PCU) servo ballscrew internal spline (BIS) teeth for wear, and replacement, if necessary, of PCU servo BIS assemblies. This amendment increases the repetitive PCU servo BIS teeth inspection interval from 1,500 to 2,500 hours time in service (TIS) for propellers that have a ballscrew quill damper installed. In addition, the FAA has reevaluated the optional installation of the Secondary Drive Quill (SDQ), and has added a new compliance end-date of June 30, 1998, for the installation of the SDQ. This AD will also require initial and repetitive torque check inspections of the primary ballscrew quill once the SDQ is installed. This amendment is prompted by field service and laboratory test data that indicate that the repetitive inspection interval can be safely increased, and by the development and availability of the SDQ. The actions specified by this AD are intended to prevent inability to control the propeller blade angle due to tooth wear in the PCU servo BIS assembly.
2011-19-01: We are adopting a new airworthiness directive (AD) for the products listed above that would supersede an existing AD. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: In service experience has shown a number of events of pin to socket arcing at the Integrated Drive Generator (IDG) feeder cable pylon/nacelle interface connector. The fretting corrosion phenomenon was identified to be the root cause of the pin to socket arcing. Investigation has identified a non-optimised electrical harness installation as a contributing factor to this phenomenon that could lead to electrical arcs with possible electrical flickering. * * * * * [S]ome operators reported cases of Display Unit (DU) flickering, despite the fact that the engines installed did not belong to the affected batch,and that these aeroplanes had been modified to incorporate one of * * * two terminating actions, * * *. [S]ome intermittent electrical power supply interruptions may not be detectable by the electrical power monitoring system, thereby preventing an automatic disconnection of the failed generator. * * * * * The unsafe condition is transient loss of certain systems, which could result in the reduced ability of the flightcrew to cope with adverse flight conditions. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
95-22-07: This amendment supersedes Airworthiness Directive (AD) 83-26-05 and AD 86-15-08, which currently require repetitively inspecting the horizontal stabilizer attachment fittings for cracks or looseness on certain de Havilland DHC-6 series airplanes, and, if a cracked or loose part is found, modifying the horizontal stabilizer. This action retains the repetitive inspection requirement of the existing AD's, requires incorporating an improved modification for airplanes with a certain modification design as terminating action for the repetitive inspections, and making these inspection-terminating modifications optional for other affected airplanes. Reports of loose horizontal stabilizer attachment fittings on airplanes incorporating the inspection-terminating modifications required by AD 83-26-05 prompted this action. The actions specified by this AD are intended to prevent separation of the horizontal stabilizer from the airplane caused by a cracked attachment fitting, and subsequent loss of control of the airplane.