Results
94-14-20: This amendment supersedes an existing airworthiness directive (AD), applicable to Sikorsky Aircraft Model S-76A series helicopters, that currently requires an initial and repetitive inspections of the tail rotor (T/R) blade spar elliptical centering plug (centering plug) for disbonding and adds a retaining pad between the T/R gearbox output shaft and the inboard T/R spar. This amendment requires the same design changes and procedures as the previous AD, except that it would eliminate the 500 hours' time-in-service repetitive inspections for centering plug disbonding. This amendment is prompted by an improved bonding and repair procedure and the lack of reports concerning the movement or disbonding of the centering plug. The actions specified by this AD are intended to prevent the centering plug from disbonding and moving out of position, which could result in loss of tail rotor control, and subsequent loss of control of the helicopter.
2002-14-23: This amendment adopts a new airworthiness directive (AD) that is applicable to certain EMBRAER Model EMB-135 and -145 series airplanes. This action requires a one-time inspection of the clutch assembly of the horizontal stabilizer actuator (HSA) to verify that at least one locking tab on the key washer is bent into the locking groove of the clutch nut, and follow-on actions. This action is necessary to prevent a loose or disengaged clutch nut on the HSA clutch assembly, which could result in loss of pitch trim and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2023-17-02: The FAA is adopting a new airworthiness directive (AD) for certain Saab AB, Support and Services Model 340A (SAAB/SF340A) and SAAB 340B airplanes. This AD was prompted by reports of a high number of events related to stall warnings upon landing, following introduction of the ice speed function within the stall warning system. This AD requires modification of the stall warning/identification system, 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.
2011-04-02: We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires removing affected propeller blades from service. This AD was prompted by reports of blades with corrosion pits in the tulip area of the blades. We are issuing this AD to prevent cracks from developing in the tulip area of the blade, which could result in separation of the blade and possible loss of airplane control.
2002-14-21: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 737-600, -700, and -800 series airplanes, that currently requires repetitive inspections to detect discrepancies of the quick-disconnect coupling on the fuel hose located at the fan case firewall; corrective action, if necessary; and installation of a clamp shell on the coupling to prevent separation of the coupling halves. This amendment limits the applicability of the existing requirements, clarifies certain existing requirements, and requires removal of the clamp shell installed previously and replacement of the existing quick-disconnect fuel supply hose, coupling, and strut fitting with new, fixed-B-nut-type parts. Such replacement ends the requirement for repetitive inspections. The actions specified by this AD are intended to prevent major fuel leakage due to excessive wear of the quick-disconnect coupling on the fuel hose, fire in the engine nacelle, and consequent loss of thrust from the affected engine, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition. \n\n\tThe incorporation by reference of Boeing Alert Service Bulletin 737-73A1011, Revision 2, dated July 13, 2000, as listed in the regulations, is approved by the Director of the Federal Register as of\nAugust 21, 2002.\n\n\tThe incorporation by reference of Boeing Alert Service Bulletin 737-73A1011, dated November 25, 1998, as listed in the regulations, was approved previously by the Director of the Federal Register as of February 19, 1999 (64 FR 5590, February 4, 1999).
2023-17-06: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model CL-600-1A11 (600), CL-600-2A12 (601), and CL-600-2B16 (601-3A, 601-3R, and 604 Variants) airplanes. This AD was prompted by an uncommanded flap extension accompanied by a flaps fail caution message during climb. This AD requires initial and repetitive operational tests of the flap control system. The FAA is issuing this AD to address the unsafe condition on these products.
2011-03-12: We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires a detailed inspection for proper sealant of the left and right pylon firewall structures, and corrective actions if necessary. This AD results from reports of missing sealant on the left and right pylon firewall structures. We are issuing this AD to detect and correct missing sealant on the left and right pylon firewall structures, which, in the event of an engine fire, could result in flames penetrating the seams in the firewall between the engine and the aft fuselage, and a subsequent uncontrolled fire in the aft fuselage.
2002-14-22: This amendment adopts a new airworthiness directive (AD) that applies to all Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes. This AD requires you to inspect the left and right main landing gear (MLG) assemblies for bolts with a serial number (S/N) beginning with the letters "AT" and numbers 299 or lower and replace each bolt with a bolt that does not have a S/N with both the letters "AT" and a number of 299 or lower. 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 detect and replace defective MLG assembly bolts that have an improper cadmium plating, which could cause hydrogen embrittlement and bolt failure. Such failure could lead to MLG collapse during landing.
2023-18-04: The FAA is adopting a new airworthiness directive (AD) for certain General Electric Company (GE) Model CF6-80E1A2, CF6-80E1A3, CF6-80E1A4, and CF6-80E1A4/B engines. This AD was prompted by a manufacturer investigation that revealed that a certain forward outer seal and certain high-pressure turbine rotor (HPTR) stage 1 disks and rotating seals were manufactured from material suspected to contain iron inclusion, which may cause reduced material properties and a lower fatigue life capability. This AD requires the replacement of the affected forward outer seal, HPTR stage 1 disks, and rotating seals. The FAA is issuing this AD to address the unsafe condition on these products.
94-11-11: This amendment supersedes an existing airworthiness directive (AD), applicable to Pratt & Whitney Canada PW100 series turboprop engines, that currently requires rework or replacement of the intercompressor case (ICC), and replacement of the low pressure rotor speed (NL) sensor port sealing tube and the external air tube connecting the P2.5/P3 switching valve to the rear inlet case. This amendment additionally requires installation of an airflow deflector bracket nozzle assembly, or modification of the No. 5 bearing pressure air system. Finally, this action requires installation of a No. 5 bearing vent tube assembly and allows extension of the compliance interval for reworking or replacing the ICC. This amendment is prompted by the development of additional hardware that will further reduce the risk of internal oil fires in the ICC. The actions specified by this AD are intended to prevent fire in the engine ICC and nacelle cavities, inflight engine shutdown, and aircraft damage.
2002-14-19: This amendment adopts a new airworthiness directive (AD) that applies to certain Rockwell Collins, Inc. (Rockwell Collins) ADC-85, ADC-85A, ADC-850D, and ADC-850F air data computers that are installed on airplanes. This AD requires you to replace any affected air data computer (ADC) with one that has a reprogrammed and tested central processing unit (CPU) circuit card and circuit card assembly. This AD is the result of a flight test that showed that these ADC's could display an unwarranted ADC flag in response to the airplane's "Normal/Alternate Air" static source selection capability. The actions specified by this AD are intended to prevent an unwarranted display of the ADC flag when switching static air sources. This could cause the flight crew to react to this incorrect flight information and possibly result in an unsafe operating condition.
2002-14-02: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 767-300 series airplanes equipped with Rolls Royce RB211-524H series engines. This action requires re-routing a certain wire bundle containing control wiring for the thrust reverser actuation system. This action is necessary to ensure that control wiring for the thrust reverser actuation system is adequately separated. Inadequately separated wiring could allow a single failure to result in uncommanded deployment of a thrust reverser and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2023-17-05: The FAA is adopting a new airworthiness directive (AD) for all Schempp-Hirth Flugzeugbau GmbH (Schempp-Hirth) Model Ventus-2a and Ventus-2b gliders. This AD is prompted by reports of the uncommanded extraction of the airbrakes on one or both wings, possibly resulting in reduced control of the glider. This AD requires repetitively inspecting airbrake bell cranks and airbrake drive funnels for cracking, repetitively inspecting the clearance of the airbrake control system, and taking corrective action as necessary. This AD also requires modifying the airbrake system, which is terminating action for the repetitive inspections. The FAA is issuing this AD to address the unsafe condition on these products.
2002-14-18: This amendment adopts a new airworthiness directive (AD) that applies to all Glaser-Dirks Flugzeugbau GmbH (DG Flugzeugbau) Models DG-400 and DG-800A sailplanes. This AD requires you to inspect the rear plate of the propeller mount for marks and/or cracks and replace if necessary. This AD also requires you to inspect the mounting blocks for cracks and replace if necessary. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to detect and correct cracks in the propeller mount plate and mounting blocks, which could result in reduced structural integrity of the propeller mounting structure. This could lead to a hazardous flight condition or loss of control of the sailplane.
2023-17-11: The FAA is adopting a new airworthiness directive (AD) for all Rolls-Royce Deutschland Ltd & Co KG (RRD) Model BR700-715A1-30, BR700- 715B1-30, and BR700-715C1-30 engines. This AD was prompted by reports of malformed scallop edge geometry and surface conditions at the front flange scallops of affected low-pressure compressor (LPC) booster rotors. This AD requires repetitive fluorescent penetrant inspections (FPIs) of the front flange scallops of the LPC booster rotor for any cracks, replacement or repair of the LPC booster rotor if necessary and, as an optional terminating action to the repetitive FPIs, a visual inspection for malformed scallop edge geometry and malformed surface conditions, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference (IBR). The FAA is issuing this AD to address the unsafe condition on these products.
94-13-10: This amendment supersedes Airworthiness Directive (AD) 74-13-01, which currently requires inspecting (one-time) the stabilator torque tube bearing support fittings for looseness on certain Piper Aircraft Corporation (Piper) PA24, PA30, and PA39 series airplanes, and, if looseness is found, incorporating Piper Part No. 760 835 (Hi-Shear Rivet Replacement Kit). This action retains the initial inspection of the stabilator torque tube bearing support fittings, and makes these inspections repetitive unless the above referenced service kit is incorporated. Incidents of looseness of the stabilator torque tube bearing support fittings on several of the affected airplanes in compliance with the current AD prompted this action. The actions specified by this AD are intended to prevent loss of pitch control because of looseness of the stabilator torque tube bearing support fittings, which could result in loss of control of the airplane.
2002-14-01: This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (ECF) helicopters that requires adding a supplement to the Limitations section of the applicable Rotorcraft Flight Manual (RFM) for helicopters with "SEFA" skis installed. This amendment is prompted by the need to limit the taxi and Vne speed of those helicopters with skis. The actions specified by this AD are intended to prevent structural failure of a ski and subsequent loss of control of the helicopter.
94-12-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-300 series airplanes, that requires replacement of the forward and aft hinge shims and the lower hinge fairings of the main cargo door with new shims and fairings. This amendment is prompted by reports of a slight separation between the end hinge shims and the cargo door; this separation can cause bending loads on the fasteners. The actions specified by this AD are intended to prevent fatigue failure of the hinge fasteners, loss of structural integrity of the cargo door hinge, possible loss of the cargo door, and subsequent rapid decompression of the airplane.
2023-17-14: The FAA is superseding Airworthiness Directive (AD) 2022-18- 11, which applied to all The Boeing Company Model 777 airplanes. AD 2022-18-11 required repetitive inspections for cracking of the left- and right-side ring chords, repair angles, front spar lower chords, and front spar webs (depending on configuration) common to a certain underwing longeron; modification of the front spar lower chord for some airplanes; repetitive post-modification inspections; and applicable on- condition actions. This AD was prompted by a report of a crack found in a front spar lower chord, and the determination that errors in the service information mandated by AD 2022-18-11 introduced a new unsafe condition related to the application of certain fastener cap seals. This AD retains the actions required by AD 2022-18-11, and requires a maintenance records review of previously modified airplanes for the procedures used during that modification, and applicable corrective actions. The FAA is issuing this AD to address the unsafe condition on these products.
2011-03-11: 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: A recent Wide spread Fatigue Damage (WFD) calculation on A300- 600 aeroplanes has shown that a reinforcement of the upper fuselage circumferential joint at FR (frame) 58 is necessary to enable the aeroplane to reach the Extended Service Goal (ESG). The failure of the circumferential joint of the upper fuselage could affect the structural integrity of the aeroplane. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
2002-13-12: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, -30, and - 40 series airplanes and Model C-9 airplanes, that currently requires an inspection to detect chafing of the wiring of the attendants' work light of the aft cabin, and repair of chafed wiring. That AD also requires modification and reidentification of the attendants' work light assemblies of the aft cabin. This amendment revises the applicability of the existing AD. The actions specified by this AD are intended to prevent chafing of the ground wire against the positive contact of the lamp of the attendants' work light of the aft cabin, and consequent arcing or arcing damage to the wiring of the attendants' work light and transformer of the aft cabin. Such arcing or arcing damage could result in short circuits and consequent smoke and fire in the aft cabin area. The actions of this AD are intended to address the identified unsafe condition.The incorporation by reference of McDonnell Douglas Alert Service Bulletin DC9-33A058, Revision 02, dated January 27, 2000, as listed in the regulations, was approved previously by the Director of the Federal Register as of January 16, 2002 (66 FR 64133, December 12, 2001).
2023-14-05: The FAA is superseding Airworthiness Directive (AD) 2022-10- 08, which applied to certain Airbus SAS Model A320-214, -251N, and - 271N airplanes. AD 2022-10-08 required a one-time detailed inspection of the affected passenger seats and corrective actions if necessary. Since the FAA issued AD 2022-10-08, it was determined that additional passenger seats are affected. This AD continues to require the actions in AD 2022-10-08, and also requires inspecting additional affected passenger seats; 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.
2020-20-17: The FAA is adopting a new airworthiness directive (AD) for all General Electric Company GE90-110B1 and GE90-115B model turbofan engines. This AD was prompted by an in-service occurrence of loss of engine thrust control resulting in uncommanded high thrust. This AD prohibits dispatch of an airplane if certain status messages are displayed on the engine indicating and crew alerting system (EICAS) and if certain conditions are present per the manufacturer's service information. As a terminating action, this AD requires revision of the existing FAA-approved minimum equipment list (MEL) by incorporating into the MEL the dispatch restrictions listed in this AD. The FAA is issuing this AD to address the unsafe condition on these products.
2002-13-02: This amendment adopts a new airworthiness directive (AD) that applies to all Air Tractor, Inc. (Air Tractor) Models AT-300, AT-301, AT-302, and AT-400A airplanes that have aluminum spar caps; certain Air Tractor Models AT-400 airplanes that have aluminum spar caps; and all Models AT-300 and AT-301 airplanes that have aluminum spar caps and are or have been converted to turbine power. This AD requires you to inspect (one-time) the wing centerline splice joint for cracks and, if any crack is found, replace the affected wing spar lower cap. This AD also requires you to report the results of the inspection to the Federal Aviation Administration (FAA) and replace the wing spar lower caps after a certain amount of usage. This AD is the result of an incident on one of the affected airplanes where the wing separated from the airplane. Preliminary reports indicate that fatigue caused the lower aluminum spar cap to fail across the 3/8-inch bolt hole (6.5 inches outboard of the fuselagecenterline in the centersplice connection). The actions specified by this AD are intended to detect and correct cracks in the wing centerline splice joint. If not detected and corrected, these cracks could eventually result in the wing separating from the airplane during flight.
2002-13-07: This amendment adopts a new airworthiness directive (AD) that applies to certain Honeywell, Inc. part number (P/N) HG1075AB05 and HG1075GB05 inertial reference units (IRU) that are installed on aircraft. This AD requires you to inspect the affected IRU's for proper function and remove the IRU either immediately or at a certain time depending on the result of the inspection. This AD is the result of a report that these IRU's may not function when using backup battery power in certain installations. The actions specified by this AD are intended to ensure the correct transition of the IRU to backup battery power upon the loss of primary power. Failure of an IRU to transition to backup battery power could result in loss of attitude, heading, and position reference and lead to the pilot making flight decisions that put the aircraft in unsafe flight conditions.