Results
2008-05-17: This document supersedes an existing airworthiness directive (AD) for MD Helicopters, Inc. (MDHI) Model 600N helicopters. That AD currently requires interim initial and repetitive inspections of tailboom parts, installing six inspection holes in the aft fuselage skin panels, installing tailboom attachment bolt washers, modifying both access covers, and replacing broken attachment bolts. The current AD also provides for modifying the fuselage aft section as an optional terminating action. This amendment requires modifying the fuselage aft section within the next 24 months to strengthen the tailboom attachment fittings and upper longerons. The actions specified by this AD are intended to prevent failure of the tailboom attachment fittings, separation of the tailboom from the helicopter, and subsequent loss of control of the helicopter.
2008-06-04: We are adopting a new airworthiness directive (AD) for the products listed above. 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: Three cases of outer deflector panel found detached or broken during ground inspection have been reported to Airbus. * * * [A]n operator has also reported a missing portion of hinge on one panel. * * * Mishandling or failure of the small portion of hinge located inboard of the affected deflector panel is suspected to be the main cause of the deflector damage. This can cause misalignment of the deflector panel followed by hinge pin migration and possible further damages to the deflector on flap retraction. If not corrected, such situation could lead to the loss of deflector panel and injured people on the ground. We are issuing this AD to requireactions to correct the unsafe condition on these products.
2001-14-18: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that currently requires inspections to detect fatigue cracking of the vertical beam webs and chords of the nose wheel well (NWW) and of the inner chord and web of the fuselage frames at body station (BS) 300 and BS 320, and repair, if necessary. This amendment expands the applicability of the existing AD to include additional airplanes, and adds new requirements for repetitive inspections to detect fatigue cracking of the NWW vertical beam webs and frames from BS 260 to BS 320, and follow-on actions, if necessary, which would end the currently required inspections for airplanes subject to them. This amendment also provides terminating action for the new repetitive inspections. The actions specified by this AD are intended to detect and correct fatigue cracking of the NWW vertical beam webs and frames, which could result in collapse of the NWW pressure bulkhead and subsequent rapid decompression of the airplane. This action is intended to address the identified unsafe condition.
94-26-15: This amendment adopts a new airworthiness directive (AD), applicable to certain Lockheed Model 382 series airplanes, that requires inspection of a kingpin riser on the lower surface of the outer wing to determine fastener placement. This AD would also require repetitive inspections for fatigue cracks in the kingpin riser if the fasteners are positioned outside certain limits, and repair, if necessary. This amendment is prompted by reports of insufficient distance between the center of the outermost fastener on the kingpin riser and the edge of the riser, which can adversely affect the fatigue resistance of the outer wing assembly. The actions specified by this AD are intended to prevent structural failure of the lower surface of the outer wing due to fatigue cracks in the kingpin riser.
2008-06-09: We are adopting a new airworthiness directive (AD) for certain Boeing Model 737-200 series airplanes. This AD requires repetitive inspections to detect cracking of the support fittings of the Krueger flap actuators, and corrective actions if necessary. This AD also requires eventual replacement of any existing aluminum support fitting on each wing with a steel fitting, and modification of the aft attachment of the actuator. Doing these actions terminates the repetitive inspection requirements. This AD results from reports of cracking due to fatigue and stress corrosion of the support fittings of the Krueger flap actuator. We are issuing this AD to prevent cracking of the support fittings, which could result in fracturing of the actuator attach lugs, separation of the actuator from the support fitting, severing of the hydraulic lines, resultant loss of hydraulic fluids, and consequent reduced controllability of the airplane.
2001-14-51: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) AD 2001-14-51 that was made available previously to all known U.S. owners and operators of General Aviation aircraft equipped with certain UPS Aviation Technologies, Inc., Model Apollo SL30 VHF NAV/COMM radios. This AD requires determination of the version of software being used by the UPS Aviation Technologies, Inc., Model Apollo SL30 VHF NAV/COMM radio, and installation of a placard to prohibit use of the radio's very-high-frequency omnirange (VOR) function for navigation, if necessary. This action is prompted by a report that, during installation of a subject radio, an installer noted that the radio was providing incorrect radial bearing information. The actions specified by this AD are intended to prevent use of incorrect bearing information by the pilot, which could result in inaccurate navigation information.
2020-09-15: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Model AS332C, AS332C1, AS332L, and AS332L1 helicopters. This AD was prompted by a report of vibrations around the 12Hz frequency due to the specific helicopter configuration. This AD requires removing the removable parts of the dual hoist installation or removing the de-icing system. This AD also allows, for certain helicopters, revising the Rotorcraft Flight Manual (RFM) for your helicopter and installing a placard as an optional method of compliance. The FAA is issuing this AD to address the unsafe condition on these products.
94-26-02: This amendment adopts a new airworthiness directive (AD), applicable to certain de Havilland Model DHC-8 series airplanes, that requires repetitive inspections of the passenger service unit (PSU) printed circuit boards and power supply connectors to detect corrosion and evidence of overheating; repair or replacement of the circuit boards or replacement of connectors, if necessary; and eventual installation of a terminating modification. This amendment is prompted by reports that certain PSU printed circuit boards and power supply connectors have overheated in service. The actions specified by this AD are intended to prevent overheating of the PSU printed circuit board and power supply connectors, which could lead to a fire in the PSU.
2008-05-15: We are adopting a new airworthiness directive (AD) for Eurocopter France Model EC130 B4 helicopters. 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 European Safety Agency (EASA), the Technical Agent for France, with which we have a bilateral agreement, states in the MCAI: This Airworthiness Directive (AD) is issued following the discovery of several cases of loosened rivets in the tube-to-flange attachment of the tail rotor drive center section shaft. In one case, this loosening of rivets was associated with a crack in the tube which started from a loosened-rivet hole. These occurrences can lead to failure of the tail rotor drive center section shaft. We are issuing this AD to correct the unsafe condition caused by cracks and loosened rivets in the tube-to-flange attachment of the tail rotor and the unsafecondition caused by the out-of-perpendicularity of the No. 1 bearing.
2001-14-19: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767 series airplanes. For certain airplanes this AD requires rework of the bonding jumper assemblies on the drain tube assemblies of the slat track housing of the wings. For certain other airplanes, this AD requires repetitive inspections of the drain tube assemblies of the slat track housing of the wings to find discrepancies, and corrective actions, if necessary. This AD also provides for terminating action for the repetitive inspections. These actions are necessary to find and fix discrepancies of the bonding jumper assemblies, which could result in an in-tank ignition source due to electrostatic discharge or lightning. The actions also are necessary to find and fix discrepancies of the slat track drain tubes, which could result in fuel migrating into the tubes and leaking onto an engine or exhaust nozzle, and consequent risk of a fire when the airplane is stationary or during low speed taxiing. This action is intended to address the identified unsafe conditions.
2014-04-14: We are adopting a new airworthiness directive (AD) for AgustaWestland Model A109S, AW109SP, A119, and AW119 MKII helicopters to require removing certain rod end assemblies from service. This AD was prompted by reports of fractures on the rod end assemblies that could damage the main rotor assembly and lead to loss of control of the helicopter.
2001-15-03: This amendment supersedes an existing airworthiness directive (AD), applicable to all Boeing Model 747 series airplanes, that currently requires repetitive inspections to detect cracking of the forward and aft inner chords and the splice fitting of the forward inner chord of the station 2598 bulkhead, and repair, if necessary. This amendment adds repetitive inspections of an expanded inspection area, which ends the inspections specified in the existing AD. This amendment also limits the applicability of the existing AD. This amendment is prompted by reports indicating that fatigue cracking was found on airplanes that had accumulated fewer total flight cycles than the threshold specified in the existing AD. The actions specified by this AD are intended to detect and correct fatigue cracking of the forward and aft inner chords, the frame support, and the splice fitting of the forward inner chord of the upper corner of the station 2598 bulkhead, which could result in reduced structural capability of the bulkhead and the inability of the structure to carry horizontal stabilizer flight loads. \n\nThe incorporation by reference of Boeing Alert Service Bulletin 747-53A2427, dated December 17, 1998; and Boeing Alert Service Bulletin 747-53A2427, Revision 1, dated October 28, 1999; as listed in the regulations, was approved previously by the Director of the Federal Register as of June 5, 2000 (65 FR 25281, May 1, 2000).
94-26-10: This amendment supersedes an existing airworthiness directive (AD), applicable to Robinson Helicopter Company (RHC) Model R44 series helicopters, that currently requires removal and replacement of specific parts of the cyclic control system. This amendment requires the same removal and replacement of specific parts of the cyclic control system, corrects a replacement part number, and changes the applicability to cover certain serial-numbered helicopters. This amendment is prompted by the need to correct the existing AD by changing the applicability to include additional serial-numbered helicopters and to correct a replacement part number that was incorrectly stated in the existing AD. The actions specified by this AD are intended to prevent failure of the cyclic control system and subsequent loss of control of the helicopter.
2008-06-03: The FAA is adopting a new airworthiness directive (AD) for certain Boeing airplanes, identified above. This AD requires inspecting to determine if certain motor-operated shutoff valve actuators for the fuel tanks are installed, and related investigative and corrective actions if necessary. This AD also requires revising the Airworthiness Limitations (AWLs) section of the Instructions for Continued Airworthiness to incorporate AWL No. 28-AWL-21, No. 28-AWL-22, and No. 28-AWL-24 (for Model 737-600, -700, -700C, -800 and -900 series airplanes); and No. 28-AWL-23, No. 28-AWL-24, and No. 28-AWL-25 (for Model 757-200, -200PF, -200CB, and -300 series airplanes). This AD results from a design review of the fuel tank systems. We are issuing this AD to prevent electrical energy from lightning, hot shorts, or fault current from entering the fuel tank through the actuator shaft, which could result in fuel tank explosions and consequent loss of the airplane.
2001-14-23: This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR72-101, -201, -102, -202, - 211, and -212 series airplanes, that requires a one-time inspection of harness route 2P and the pitch control cable for wire chafing, corrective action, if necessary; and replacement of the clamp retaining the power supply cable loom of the green circuit hydraulic pump at frame 28 with a smaller clamp in a different orientation. This action is necessary to prevent the chafing of electrical wires, which could cause a short circuit and failure of the elevator control cable and the green system hydraulic pump, resulting in reduced controllability of the airplane and consequent injury to the crew and passengers. This action is intended to address the identified unsafe condition.
2022-19-05: The FAA is superseding Emergency Airworthiness Directive (AD) 2022-18-51, which applied to all Airbus SAS Model A330-841 and -941 airplanes. Emergency AD 2022-18-51 required revising the existing airplane flight manual (AFM) to incorporate additional limitations prohibiting takeoff for certain airplane configurations; specified airplane dispatch restrictions using certain provisions of the A330 master minimum equipment list (MMEL) or amending the existing FAA- approved operator's minimum equipment list (MEL); and required obtaining and accomplishing instructions following certain maintenance messages. Since the FAA issued Emergency AD 2022-18-51, additional instructions and maintenance procedures have been developed to address failures of the high pressure valve (HPV). This AD continues to require the actions specified in Emergency AD 2022-18-51, and also requires maintenance actions, including an HPV seal integrity test, repetitive replacement of the HPV clips, revision of the existing AFM, and implementation of updates to the FAA-approved operator's MEL, 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.
2001-14-20: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-100 and -200 series airplanes, that requires repetitive inspections to find fatigue cracking in the main deck floor beams located at certain body stations, and repair, if necessary. This AD also provides for optional terminating action for the repetitive inspections. This AD is prompted by reports of incidents involving fatigue cracking and corrosion in transport category airplanes that are approaching or have exceeded their design life goal. This AD relates to the recommendations of the Airworthiness Assurance Task Force assigned to review Model 737 series airplanes, which indicate that, to assure long term continued operational safety, various structural inspections should be accomplished. The actions specified by this AD are intended to prevent failure of the main deck floor beams at certain body stations due to fatigue cracking, which could result in rapid decompression and consequent reduced controllability of the airplane.
2008-06-06: The FAA is adopting a new airworthiness directive (AD) for all Boeing Model 767 airplanes. This AD requires the following actions for the drive mechanism of the horizontal stabilizer: Repetitive detailed inspections for discrepancies and loose ball bearings; repetitive lubrication of the ballnut and ballscrew; repetitive measurements of the freeplay between the ballnut and the ballscrew; and corrective action if necessary. This AD also requires initial and repetitive inspections of the ballscrew-to-ballnut freeplay for certain airplanes. This AD results from a report of extensive corrosion of a ballscrew in the drive mechanism of the horizontal stabilizer on a similar airplane model. We are issuing this AD to prevent an undetected failure of the primary load path for the ballscrew in the drive mechanism of the horizontal stabilizer and subsequent wear and failure of the secondary load path, which could lead to loss of control of the horizontal stabilizer and consequent loss ofcontrol of the airplane.
94-25-08: This amendment supersedes an existing airworthiness directive (AD), applicable to Turbomeca Arriel 1 series turboshaft engines, that currently requires a gearbox chip detector inspection prior to further flight, subsequent inspection at designated intervals, and if necessary, removal of the gearbox, and also requires modification of the gearbox if not accomplished previously. This amendment requires modification to the intermediate gear that would constitute terminating action to the repetitive chip detector inspections. On certain engines this amendment requires immediate modification of the intermediate gear prior to further flight. This amendment is prompted by the availability of design improvements to the intermediate gear. The actions specified by this AD are intended to prevent damage to the aircraft resulting from engine debris following an uncontained engine failure.
94-25-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Model DC-9-80 series airplanes and Model MD-88 airplanes, that requires modification of the engine nose cowls. This amendment is prompted by several in-flight incidents in which the engine nose cowl separated or nearly separated from the airplane. The actions specified by this AD are intended to prevent separation of the engine nose cowl from the airplane during severe vibration of the engine.
2001-15-01: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 727, 737, 757-200, 757-200CB, and 757-300 series airplanes. This AD requires modification of the latch assembly of the escape slides. For certain airplanes, this AD also requires installation of a cover assembly on the trigger housing of the inflation cylinder on the escape slides. This action is necessary to prevent failure of an escape slide to deploy or inflate correctly, which could result in the slide being unusable during an emergency evacuation and consequent injury to passengers or airplane crewmembers. This action is intended to address the identified unsafe condition.
2008-06-12: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued 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: Two incidents have been reported where the normal hydraulic supplies were lost due to failure/loss of the steering jack gland housing. This has been attributed to pre-existing thread damage on the steering jack gland housing. Three previous failures may also be due to this failure mechanism. Failure of the steering jack gland housing resulted in significant damage to the right hand undercarriage bay door, and could result in the nose landing gear jamming in a fully or partially retracted position. Landing in such a condition is considered as potentially unsafe due to the degraded control of the aircraft post touch down. We are issuing this AD to require actions to correct the unsafe condition on these products.
2001-15-02: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that currently requires repetitive inspections and torque checks of the hanger fittings and strut forward bulkhead of the forward engine mount and adjacent support structure, and corrective actions, if necessary. The existing AD also provides for optional terminating action for the repetitive inspections and checks. This amendment requires certain new repetitive torque checks and the previously optional terminating action. The actions specified by this AD are intended to prevent loose fasteners and associated damage to the hanger fittings and bulkhead of the forward engine mount, which could result in separation of the engine from the airplane.
2020-09-13: The FAA is adopting a new airworthiness directive (AD) for all 328 Support Services GmbH Model 328-300 airplanes. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, 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.
2001-14-16: This amendment adopts a new airworthiness directive (AD), applicable to certain Gulfstream Model G-V series airplanes, that requires repetitively replacing the existing nose wheel steering actuator with a new or reworked actuator having the same part number. The actions specified by this AD are intended to prevent loss of nose wheel steering control without a corresponding alert message annunciation due to the effects of moisture intrusion into the rotary variable displacement transducer (RVDT) inside the steering actuator, and consequently, an over steering condition. If an over steering condition were to occur during landing, the airplane could depart the runway. This action is intended to address the identified unsafe condition.