Results
2007-06-14: 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 discovery of propeller control cables with a defective crimping. Two cable ends were found uncrimped at the factory after an engine run-up test, and one cable end was also found uncrimped on the first 100-hour aircraft maintenance check. We are issuing this AD to require actions to correct the unsafe condition on these products.
2021-18-02: The FAA is adopting a new airworthiness directive (AD) for certain Fokker Services B.V. Model F28 Mark 0070 and Mark 0100 airplanes. This AD was prompted by a report of a crack found on the forward pressure bulkhead web plate, at the edge of a bonded doubler. This AD requires a one-time inspection of the forward bulkhead for cracking, repair if necessary, and a report of inspection results, 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.
2005-25-12: The FAA is adopting a new airworthiness directive (AD) for Turbomeca Astazou XIV B and XIV H turboshaft engines that have operated with air intake noise suppressors. This AD requires ensuring proper installation of air intake noise suppressors, and ultrasonically inspecting 2nd stage axial compressor wheel blades operated in engines with improperly installed intake noise suppressors. This AD results from several reports of failure of 2nd stage axial compressor wheel blades. We are issuing this AD to prevent failure of 2nd stage axial compressor wheel blades, leading to in-flight engine shutdown and autorotation landing.
2021-16-12: The FAA is adopting a new airworthiness directive (AD) for certain Bell Textron Canada Limited Model 505 helicopters. This AD was prompted by three occurrences of metallic debris in the engine oil lubrication system causing the 12 volts direct current (VDC) reference voltage to be shorted to ground and loss of important flight information to the pilot. This AD requires replacing a certain part- numbered relay panel assembly. The FAA is issuing this AD to address the unsafe condition on these products.
2021-06-01: The FAA is adopting a new airworthiness directive (AD) for all Pilatus Aircraft Ltd. (Pilatus) Model PC-24 airplanes. This AD was prompted by a report that electronic circuit breakers (ECBs) were found in a locked state after maintenance, but before flight. This AD requires revising the airplane flight manual (AFM) to incorporate a procedure to check for the ECB status. The FAA is issuing this AD to address the unsafe condition on these products.
2007-06-08: 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: Some cases of turnbuckle adjusting screws fatigue failure have occurred, due to lateral load component applied by pilot's foot. Such events may lead to rudder and pedals disconnection. We are issuing this AD to require actions to correct the unsafe condition on these products.
2021-19-04: The FAA is adopting a new airworthiness directive (AD) for Helicopteres Guimbal Model Cabri G2 helicopters with any metal bushing installed on the main rotor (M/R) swashplate guide bellcrank. This AD was prompted by a report of cracks discovered on the M/R scissor link during scheduled maintenance on several helicopters. This AD requires removing all metal bushings from service, visually inspecting the lug bore area and depending on the inspection results, removing certain parts from service and installing certain part- numbered plastic bushings. This AD also prohibits installing any metal bushing on any helicopter. The FAA is issuing this AD to address the unsafe condition on these products.
2021-16-11: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350D, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters. This AD was prompted by a report of reduced yaw control, during an approach for landing, that resulted from rupture of the tail rotor gearbox (TGB) actuating rod and uncoupling of the steel sleeve from inside the external aluminum tube. This AD requires dye penetrant inspecting certain TGB actuating rods for a crack, and depending on the inspection results, replacing the TGB actuating rod, 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.
2021-16-07: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Defense and Space S.A. Model C-212-CB, C-212-CC, C-212- CD, C-212-CE, C-212-CF, C-212-DE, and C-212-DF airplanes. This AD was prompted by a report of cracks on the left-hand (LH) and right-hand (RH) side fuselage skin and on a certain frame underneath the skin, near the leading edge of the wing. This AD requires repetitive inspections of the LH and RH side center wing fairings at a certain frame, around the wing leading edge for discrepancies (cracks), and repair if necessary, 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.
2007-06-07: The FAA adopts a new airworthiness directive (AD) for certain Raytheon Aircraft Company (RAC) Models 58 and G58 airplanes with optional propeller unfeathering accumulators installed. This AD requires you to inspect the left propeller accumulator oil tube assembly for any chafing; replace the propeller accumulator oil tube assembly if any chafing is found; and reposition and secure with clamps both the left engine manifold pressure hose and its metal identification tags to avoid contact with other tubes, hoses, electrical wires, parts, components, and structure. This AD results from several reports on the affected airplanes of chafing damage on the left propeller accumulator oil tube assembly. We are issuing this AD to detect, correct, and prevent any chafing damage of the left propeller accumulator oil tube assembly, which could result in loss of engine oil. Loss of engine oil may lead to fire or smoke in the engine compartment, inability to unfeather the propeller, engine damage, or loss of engine power.
2021-16-01: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A318 series airplanes; Model A319-111, -112, - 113, -114, -115, -131, -132, -133, -151N, and -153N airplanes; Model A320 series airplanes; and Model A321 series 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.
2007-05-20: 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: It has been reported that with the existing configuration, a certain failure could cause overspeed of the gas generator rotor resulting in uncontained burst of the turbine liberating high-energy fragments. We are issuing this AD to require actions to correct the unsafe condition on these products.
2007-05-13: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A319, A320, and A321 airplanes. This AD requires installing spacer assemblies at the attachment points of the YZ-latches of the cargo loading system in the forward and aft cargo compartments, as applicable. This AD results from tests that have shown that the attachment points of the YZ-latches of the cargo loading system fail under maximum loads. We are issuing this AD to prevent failure of the attachment points of the YZ-latches, which could result in unrestrained cargo causing damage to the fire protection system, hydraulic system, electrical wiring, or other equipment located in the forward and aft cargo compartments. This damage could adversely affect the continued safe flight of the airplane.
2005-24-03 R1: The FAA is revising an existing airworthiness directive (AD) that applies to certain Boeing Model 737-600, -700, -700C, and -800 series airplanes. That AD currently requires inspecting/measuring the length of the attachment fasteners between the nacelle support fittings and the lower wing skin panels, and related investigative/corrective actions if necessary. That AD resulted from a report from the manufacturer that in production, during the installation of certain attachment fasteners for the nacelle support fittings, only one washer was installed instead of two. This new AD corrects errors found in the existing AD. We are issuing this AD to prevent inadequate fastener clamp-up, which could result in cracking of the fastener holes, cracking along the lower wing skin panels, fuel leaking from the wing fuel tanks onto the engines, and possible fire.
2021-15-08: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by a report that during an inspection of the flight deck escape hatches it was found that they were difficult to open from the inside, and several hatches were found impossible to open from the outside. Subsequent investigation revealed corrosion on the flight deck escape hatch mechanism due to condensation penetrating inside the mechanism. This AD requires replacing all affected flight deck escape hatches with serviceable hatches, 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.
2021-15-07: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A330-200, -200 Freighter, -300, -800, and -900 series airplanes; and Model A340-200 and -300 series airplanes. This AD was \n\n((Page 42692)) \n\nprompted by reports of incorrect installation of the lower attachment parts of the trimmable horizontal stabilizer actuator (THSA). This AD requires doing a detailed inspection of the THSA lower attachment parts for discrepancies and corrective action if necessary, and prohibits using earlier versions of certain airplane maintenance manual (AMM) tasks, 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.
2020-23-12:
2007-05-18: 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 finding of an improper geometry of some pulley brackets, which can offset the cable in the sheave. We are issuing this AD to require actions to correct the unsafe condition on these products.
2021-14-04: The FAA is adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 7X airplanes and Model FALCON 2000EX airplanes. This AD was prompted by a report that non-certified ANCRA seat tracks were installed on some airplanes and that those seat tracks might not sustain required loads during an emergency landing. This AD requires replacement of certain ANCRA seat tracks with certified (Brownline) seat tracks, 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.
2007-05-10: The FAA adopts a new airworthiness directive (AD) for certain Cessna Aircraft Company (Cessna) Models 172R, 172S, 182S, 182T, T182T, 206H, and T206H airplanes. This AD requires you to install Modification Kit MK172-25-10C or a steel lock rod/bar on both crew seat back cylinder lock assemblies. If a steel lock rod/bar has already been installed on the crew seat back cylinder lock assembly, no further action is required. If you have already installed Modification Kit MK172-25-10A or MK172-25-10B, this AD requires you to do an installation inspection and correct any discrepancies found. This AD results from reports of the crew seat back cylinder lock assembly failing at the aft end and other cylinder lock assemblies found cracked. We are issuing this AD to prevent the crew seat back cylinder lock assembly from bending, cracking, or failing. This failure could cause uncontrolled movement of the seat back, resulting in possible backward collapse during flight. Backward collapse ofeither crew seat back could result in an abrupt pitch-up if the affected crew member continues to hold on to the control yoke during this failure and could cause difficulty in exiting the airplane from an aft passenger seat after landing.
2021-13-20: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Canada Limited Partnership Model BD-500-1A10 and BD-500- 1A11 airplanes. This AD was prompted by reports of corrosion on the waste box, waste access doubler, and waste service door of the rear fuselage due to contamination from waste valve leakage. This AD requires an inspection for corrosion of the waste box, waste access doubler, and waste service door, and corrective actions if necessary, as specified in a Transport Canada Civil Aviation (TCCA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
89-08-03 R1: 89-08-03 R1 BOEING: Amendment 39-6183 as revised by Amendment 39-6389. Docket No. 89-NM-104-AD. \n\n\tApplicability: Model 747 series airplanes, listed in Boeing Service Bulletin 747-53-2297, dated June 30, 1988, certificated in any category, except line number 001 through 065. \n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent depressurization as a result of failure of the crease beam and resultant adjacent frame failure, accomplish the following: \n\n\tA.\tFor airplanes not modified in accordance with Boeing Service Bulletin 747-53-2297, dated June 30, 1988, or Boeing Service Bulletin 747-53-2244, dated September 20, 1985. \n\n\t\t1.\tPerform detailed visual and dye penetrant inspections of the body crown crease beam for cracks, from BS 940 to BS 1000 and from stringers S-8L to S-8R, at the times specified in the table below, in accordance with Boeing Service Bulletin 747-53-2297, dated June 30, 1988. In addition, perform a detailed visual inspection for cracks in all adjacent intercostals, skins (internal and external), and stringers in the same area, in accordance with Boeing Service Bulletin 747-53-2297, dated June 30, 1988. \n\n\t\n\nFor Unmodified Airplanes: \n\nAccumulated landings as of effective date of AD\nInitial Compliance Period for Paragraph A. of this AD\n13,000 or more\t\nWithin 1,000 landings after the effective date of this AD.\nBetween 7,500 and 13,000\nWithin 2,500 landings after the effective date of this AD, but not to exceed 14,000 total landings on the airplane. \n7,500 or less\nPrior to accumulation of 10,000 landings. \n\n\t\t2.\tIf no cracks are found, repeat the detailed visual and penetrant inspections required by paragraph A.1., above, at intervals not to exceed 6,000 landings. \n\n\t\t3.\tIf cracks are found, repair in accordance with Boeing Service Bulletin 747-53-2297, dated June 30, 1988, prior to further flight, except as noted in paragraph A.4, below. \n\n\t\t4.\tRepair of cracks less than 1.5 inches:If there are no more than three cracks in the web and no more than three cracks in any one flange of the outer tee chord, repair of the crease beam crack may be deferred for up to 1,500 landings by stop-drilling crack ends in accordance with Boeing Service Bulletin 747-53-2297, dated June 30, 1988, and repeating the detailed visual and penetrant inspection required by paragraph A.1., above, at intervals not to exceed 250 landings until repair in accordance with paragraph A.3., above, is accomplished. \n\n\t\t5.\tPrior to the accumulation of 6,000 landings after a repair and thereafter at intervals not to exceed 6,000 landings, perform the detailed visual and penetrant inspections for cracks required by paragraph A., above, including any crease beam area where cracks were found. Before further flight, repair any additional cracks found, in accordance with a method approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tB.\tFor airplanes thathave been modified in accordance with Boeing Service Bulletin 747-53-2297, dated June 30, 1988, or Boeing Service Bulletin 747-53-2244, dated September 20, 1985: Prior to the accumulation of 10,000 landings after the modification, or within the next 500 landings after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 6,000 landings, perform the body crown crease beam detailed visual and penetrant inspections for cracks as required by paragraph A., above. If cracks are found, prior to further flight, repair in accordance with Boeing Service Bulletin 747-53-2297, dated June 30, 1988. \n\n\tC.\tAn alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any commentsand then send it to the Manager, Seattle Aircraft Certification Office. \n\n\tD.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis AD revises AD 89-08-03 (Amendment 39-6183) which became effective on May 8, 1989. \n\n\tThis amendment (39-6389, AD 89-08-03 R1) becomes effective on November 3, 1989.
2007-05-06: The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas Model 717-200 airplanes. This AD requires replacing certain attaching hardware of the bulkhead nipple assemblies of the left and right wing vent boxes with new electrical bonding attaching hardware, doing resistance testing of the new electrical bonds, and doing fuel leakage testing of the reworked nipple assemblies. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to provide a conductive path, from the bulkhead nipple assemblies of the left and right wing vent boxes to the airframe structure inside the wing fuel tanks, to dissipate high- amperage lightning-induced currents, which might otherwise create an ignition source for fuel vapors inside the wing vent boxes and lead to an explosion of the fuel tanks.
2021-13-14: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Deutschland GmbH (AHD) Model BO-105A, BO- 105C, BO-105S, and BO-105LS A-3 helicopters. This AD was prompted by an uncommanded activation of the hoist cable cutter function on an MBB- BK117 C-1 helicopter, which prompted a design review of the BO105 hoist control grip with coiled cable. This AD requires inspections of the hoist control grip with coiled cable and deactivation of the hoist cutter function, as specified in a European Aviation Safety Agency (now 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.
2007-05-03: 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: An occurrence of inadvertent manipulation of the fuel shut-off control has been reported. We are issuing this AD to require actions to correct the unsafe condition on these products.