Results
94-04-09: This amendment adopts a new airworthiness directive (AD), applicable to certain de Havilland Model DHC-8-100 and DHC-8-300 series airplanes, that requires inspections to detect breakage in the engine rear mount strut assemblies, and replacement of broken struts. This amendment also requires eventual replacement of all currently installed struts with new and/or reworked struts, as terminating action for the inspections. This amendment is prompted by several reports of failure of the engine rear mount struts, due to fracture at one of the rosette welds on the shank of the strut where full weld depth was not achieved during manufacture. The actions specified by this AD are intended to prevent fracture of the engine rear mount struts, which could reduce the structural integrity of the nacelle and engine support structure.
2021-23-51: The FAA is adopting a new airworthiness directive (AD) for certain General Electric Company (GE) CF34-8C and CF34-8E model turbofan engines. This AD was prompted by an in-flight shutdown of an engine and subsequent investigation by the manufacturer that revealed a broken variable geometry (VG) actuator rod end caused by corrosion and seizure of the rod end bearing. This AD requires performing an inspection of the master compressor VG actuator and slave compressor VG actuator and, depending on the results of the inspection, replacement of the part with a part eligible for installation. This AD also requires reporting the results of the inspection to GE. The FAA previously sent an emergency AD to all known U.S. owners and operators of these GE CF34-8C and CF34-8E model turbofan engines and is now issuing this AD to address the unsafe condition on these products.
2018-10-12: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD requires repetitive high frequency eddy current (HFEC) and detailed inspections, as applicable, for cracking of certain aft vertical stiffeners; repetitive detailed inspections for cracking of time-limited repairs, as applicable; a one-time HFEC inspection for cracking of the keel beam upper chord inboard flanges; a one-time general visual inspection for cracking of a certain angle; and applicable on-condition actions. This AD was prompted by a report of cracks in the left-side and right-side keel beam upper chords and aft vertical stiffeners. We are issuing this AD to address the unsafe condition on these products.
2001-08-16: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-8 series airplanes, that requires a one-time inspection to determine the manufacturer of the circuit breakers, and corrective action, if necessary. This amendment is prompted by reports of smoke and electrical odor in the flight compartment and cabin area as a result of failure of circuit breakers. The actions specified by this AD are intended to prevent internal overheating and arcing of the circuit breakers and airplane wiring due to long-term use and breakdown of internal components of the circuit breakers, which could result in smoke and fire in the flight compartment and main cabin.
94-04-13: This amendment supersedes Airworthiness Directive (AD) 65-06-01, which currently requires repetitively inspecting the wing front spar lower cap (spar cap) of both the left and right wings on certain Twin Commander Aircraft Corporation (Twin Commander) 500 and 600 series airplanes, and replacing any cracked spar cap. Front spar cap cracks developing on certain Twin Commander model airplanes not affected by that AD prompted this action. In addition, the manufacturer has updated the inspection procedures through improved service information. This action retains the inspection and repair requirements of AD 65-06-01, and requires inspecting in accordance with updated service information and increases the applicability to include other model airplanes. The actions specified by this AD are intended to prevent failure of the wing structure caused by cracks in the spar cap.
2011-09-06: We are superseding an existing airworthiness directive (AD) for all Model A330 and A340 series airplanes. 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: \n\n\n\tAt the end of an escape slide deployment test performed on the left-hand forward pax (passenger)/crew door of an A330 aeroplane, the girt bar attaching the escape slide to the fuselage was found not in a locked position and detached from the aeroplane. \n* * * * *\n\n\tThis condition, if not corrected, could result in the slide detaching from the door after being inflated which, during an emergency, would impair the safe evacuation of occupants, possibly resulting in personal injuries. \n* * * * *\nThis AD requires actions that are intended to address the unsafe condition described in the MCAI.
94-04-15: This amendment adopts a new airworthiness directive (AD) that applies to certain Twin Commander Aircraft Corporation (Twin Commander) Models 500, 560A, 560E, 680, 680E, and 720 airplanes. This action requires inspecting the wing front spar lower cap (spar cap) for interference, fretting, or corrosion between the firewall flange and spar cap flange at Wing Station (WS) 96, and clearing any interference, repairing any fretting or corrosion damage, and replacing any cracked spar cap. Reports of two of the affected airplanes having cracked spar caps at WS 96 prompted this action. The actions specified by this AD are intended to prevent failure of the wing structure caused by a cracked spar cap at WS 96.
2018-11-01: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Model AS332L2 and EC225LP helicopters. This AD requires installing a cut-out for the left-hand (LH) and right-hand (RH) rail support junction profiles and inspecting splices, frame 5295, and related equipment for a crack. This AD was prompted by reports of cracks on frame 5295 and on splices installed to prevent those cracks. The actions of this AD are intended to prevent an unsafe condition on these products.
94-04-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires replacement of the existing ground/flight microswitches located in the main landing gear with improved microswitches, and installation of an anti-skid system ON/OFF switch in the flight compartment. This amendment is prompted by an incident involving loss of braking, which was caused by mechanical ground/flight microswitches that froze while in the flight position. The actions specified by this AD are intended to prevent loss of braking below 40 miles per hour, when the anti-skid system is activated.
2007-19-11: The FAA is superseding an existing airworthiness directive (AD) for Turbomeca Artouste III B, Artouste III B1, and Artouste III D turboshaft engines. That AD currently requires removing certain fuel pumps from service and installing serviceable fuel pumps. This AD requires the same actions and adds to the applicability, additional fuel pumps by serial number (SN). This AD results from Turbomeca identifying a number of fuel pump SNs that they omitted from the original population. We are issuing this AD to prevent reduced engine fuel flow and subsequent loss of control of the helicopter, or an accident.
2000-26-09 R1: This amendment revises an existing airworthiness directive (AD), applicable to all Dornier Model 328-100 series airplanes, that currently 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 adds information pertaining to certain material incorporated by reference. This amendment is prompted by the issuance of revisions to the Dornier 328 Airworthiness Limitations Document. 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.
2018-09-17: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601 Variant), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604 Variants) airplanes. This AD was prompted by reports of fractured rudder pedal tubes on the pilot-side rudder bar assembly. This AD requires repetitive inspections of the rudder pedal tubes for cracking and corrective actions if necessary. Replacement of both pilot-side rudder bar assemblies terminates the inspections. We are issuing this AD to address the unsafe condition on these products.
2007-21-01: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: During a recent flight with a DG-500 ELAN Trainer, the bolt of bearing stand 5RU61, which is the pivot for bell crank 5St19, failed in-flight, leading to loss of control of the aircraft. Although the occupants managed to exit the aircraft safely, the aircraft crashed and was damaged beyond repair. While the investigation continues, the most likely cause is suspected to be insufficient tightening of the nut on the bolt of bearing stand 5RU61. This condition, if not corrected, may cause excessive bending loads, leading to premature failure of the bolt and loss of control of the aircraft. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2021-24-01: The FAA is adopting a new airworthiness directive (AD) for Pilatus Aircraft Ltd. (Pilatus) Model PC-12/45, PC-12/47, and PC-12/47E airplanes with Supplemental Type Certificate (STC) SA00634DE installed. This AD was prompted by a report of strake attachment brackets and the fuselage frame failing at the upper most bracket attachment location. This AD requires inspecting the strake, attachment brackets, surrounding structure, and bolts and replacing components and repairing damage if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
94-03-05: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-200B, -200C, -300, -400, and 400D series airplanes, that requires a revision to the FAA-approved maintenance program to require unrestricted opening of the passenger service unit (PSU) door during functional testing of the passenger oxygen system; and requires an inspection to detect leaks in certain passenger oxygen system reservoir bags, and marking and replacement of damaged mask assemblies. This amendment is prompted by reports that the passenger oxygen mask reservoir bags became overpressurized and split at the seams, resulting in failure of the bags. The actions specified by this AD are intended to ensure the delivery of emergency oxygen through the passenger oxygen system reservoir mask assemblies.
2008-23-08: 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: In-service experience indicates that the powder coating of the rear right hand (RH) engine support bracket degrades over time, leading to a reduced torque of the engine mountings bolts. In some cases, bolts had fully unscrewed and fell into the engine cowling. One case was reported where the pilot had to shut down an engine in flight because of a failed V-belt, the cause of failure assumed to be one of these bolts. This condition, if not corrected, may lead to further cases of loose bolts and subsequent damage to the engine or accessories in the engine compartment, possibly resulting in in- flight engine shut-down and reduced control of the aircraft. Weare issuing this AD to require actions to correct the unsafe condition on these products.
94-01-13: This amendment adopts a new airworthiness directive (AD), applicable to certain de Havilland Model DHC-8-300 series airplanes, that requires modifying the airplane fire detection system and revising the Airplane Flight Manual (AFM) to include procedures related to operating the system. This amendment is prompted by reports of several oil fires in the inter compressor case (ICC) assembly. The actions specified by this AD are intended to prevent severe structural damage to the airplane due to an internal engine fire within the ICC.
2007-20-04: The FAA is superseding an existing airworthiness directive (AD) that applies to all Airbus Model A300 and A310 airplanes, and certain Model A300-600 series airplanes. That AD currently requires an inspection of the wing and center fuel tanks to determine if certain P- clips are installed and corrective action if necessary. That AD also requires an inspection of electrical bonding points of certain equipment in the center fuel tank for the presence of a blue coat and related investigative and corrective actions if necessary. That AD also requires installation of new bonding leads and electrical bonding points on certain equipment in the wing, center, and trim fuel tanks, as necessary. This new AD requires, for certain airplanes, installation of bonding on an additional bracket and modification of the fuel/defuel valves on the left-hand wing. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to ensure continuous electrical bonding protection of equipment in the wing, center, and trim fuel tanks and to prevent damage to wiring in the wing and center fuel tanks, due to failed P-clips used for retaining the wiring and pipes, which could result in a possible fuel ignition source in the fuel tanks.
2019-20-08: The FAA is adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace Corporation (Gulfstream) Model G-IV and Model GIV-X airplanes. This AD was prompted by a revision to the airworthiness limitations section (ALS) of the aircraft maintenance manual (AMM) based on fatigue and damage tolerance testing and updated analysis. This AD requires revising the maintenance or inspection program to incorporate updated inspection requirements and life limits that address fatigue cracking of principal structural elements. The FAA is issuing this AD to address the unsafe condition on these products.
2010-04-11: 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: The manufacturer has advised that the combination of a redesigned tail spring support with a stiffer tail spring and rough field operations has led to cracks in the tail spring support mounting base. Cracks have also been reported on aeroplanes already compliant with Part II of Extra Service Bulletin No. SB-300-2-97 issue A, as mandated by the LBA AD D-1998-001, dated 15 January 1998. We are issuing this AD to require actions to correct the unsafe condition on these products.
94-01-01: This amendment adopts a new airworthiness directive (AD) that applies to certain Beech Aircraft Corporation (Beech ) Models B300 and B300C airplanes that do not have all cabin seats modified through the incorporation of Beech Kit No. 303-307. This action requires inspecting the cabin seat frames for cracks, repairing any cracks, and modifying the cabin seat frames by incorporating the kit referenced above. Inspection of affected in-service airplanes reveals cracking of these cabin seats around the welded-in bushings. The bearing shafts, which retain the seat frame and belted occupant, are bolted to the frame through these bushings. The actions specified by this AD are intended to prevent separation of the seat from its base caused by cracks around the welded-in bushings, which, in the event of an accident, could result in occupant injury.
2007-20-06: 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: It has been revealed that the control surface balancing procedure in the * * * SAAB 2000 SRM (structural repair manual) * * * is incorrect. Incorrect balance, outside the tolerance of the aileron control surface, may lead to vibrations that in [the] worst case can result in flutter. We are issuing this AD to require actions to correct the unsafe condition on these products.
2001-08-02: This amendment supersedes two existing airworthiness directives (AD), applicable to all Boeing Model 707 and 720 series airplanes, that currently require inspections of the upper chords of the wing front and rear spars, repair, if necessary, and application of corrosion inhibitor to the inspected areas. This amendment requires repetitive inspections of the upper and lower chords on the wing front and rear spars, repair, if necessary, and application of corrosion inhibitor to the inspected areas. These actions are necessary to find and fix stress corrosion cracking of the upper and lower chords on the wing front and rear spars, which could result in reduced structural integrity of the wing. This action is intended to address the identified unsafe condition. \n\n\tThe incorporation by reference of certain publications, as listed in the regulations, is approved by the Director of the Federal Register as of May 8, 2001. \nThe incorporation by reference of Boeing Service Bulletin3240, Revision 3, dated October 18, 1985, as listed in the regulations, was approved previously by the Director of the Federal Register as of March 10, 1992 (57 FR 4153, February 4, 1992). \n\n\tComments for inclusion in the Rules Docket must be received on or before June 22, 2001.
2001-08-03: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 777-200 series airplanes. This action requires repetitive inspections of the upper housing assembly of the forward trunnion of the main landing gear (MLG) for discrepancies (migrated or missing wearplates, loose or fractured attachment screws); and corrective action, if necessary. This action also provides for an optional modification of the upper housing assembly for airplanes without discrepant wearplates, which would end the repetitive inspections. This action is necessary to prevent migration or loss of the upper housing wearplate, which could result in loss of the MLG during the takeoff roll; consequent damage to the airplane structure; and injury to flight crew, passengers, or ground personnel. This action is intended to address the identified unsafe condition.
94-01-06: This amendment adopts a new airworthiness directive (AD) that applies to certain Rockwell International, Collins Air Transport Division (Collins), Traffic Alert and Collision Avoidance System (TCAS) II processors that are installed on aircraft. This action requires replacing the existing TCAS II processor with a new processor that incorporates updated computer logic or reprogramming certain processors while they are still on board the aircraft. The development of candidate enhancements to TCAS II logic that improves its utility and increases its overall operational acceptance prompted the proposed action. The actions specified by this AD are intended to prevent collisions or near misses caused by incompatibility between the TCAS II processors and the current air traffic control system.