Results
66-06-03: 66-06-03 LYCOMING: Amdt. 39-708. Applies to Model IO-360-A1A Engines with Serial Numbers 101-51 through 1231-51A, and All Engines Remanufactured by Lycoming Prior to December 1, 1964. Compliance required as indicated. To prevent further failures of connecting rod assemblies, P/N 74503 and P/N 74308, accomplish the following: (a) Replace connecting rod assemblies P/N 74503 and P/N 74308 with 200 or more hours' time in service on the effective date of this AD with connecting rod assembly P/N 75059 within the next 50 hours' time in service in accordance with Lycoming Service Bulletin No. 302 or later FAA-approved revision. (b) Replace connecting rod assemblies P/N 74503 and P/N 74308 with less than 200 hours' time in service on the effective date of this AD with connecting rod assembly P/N 75059 before the accumulation of 250 hours' time in service in accordance with Lycoming Service Bulletin No. 302 or later FAA-approved revision. Effective March 13, 1966.Revised January 16, 1969.
96-12-24: This amendment adopts a new airworthiness directive (AD) that is applicable to all Lockheed Model L-1011-385 series airplanes. This action requires inspections to detect cracking and other discrepancies of certain web-to-cap fasteners of the rear spar between inner wing stations (IWS) 310 and 343, and of the web area around those fasteners; and various follow-on actions. This AD also provides for an optional modification which, if accomplished, will defer the initiation of the inspections for a certain period of time. This amendment is prompted by a report of fatigue cracking in the web of the rear spar of the wing. The actions specified in this AD are intended to prevent such fatigue cracking, which could result in failure of the rear spar of the wing and consequent fuel spillage.
2008-08-13: 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: Due to the recalculation of loads for the Multi Role Transporter and Tanker (MRTT) aircraft, it has been found that a structural reinforcement at the aft section of the fuselage (FR (frame) 87- FR91) is required for A300-600 aircraft and A310 aircraft with a Trim Tank installed. * * * * * * * The unsafe condition is the potential loss of structural integrity in the aft section of the fuselage between FR87 through FR91, inclusive, during extreme rolling and vertical maneuver combinations. We are issuing this AD to require actions to correct the unsafe condition on these products.
2010-07-02: The FAA is superseding an existing airworthiness directive (AD) that applies to certain Honeywell Primus II RNZ-850( )/-851( ) integrated navigation units (INUs). As one alternative for compliance, the existing AD provides for a one-time inspection to determine whether a certain modification has been installed on the Honeywell Primus II NV-850 navigation receiver module (NRM), which is part of the INU. In lieu of accomplishing this inspection, and for aircraft found to have an affected NRM, that AD provides for revising the aircraft flight manual to include new limitations for instrument landing system approaches. That AD also requires an inspection to determine whether certain other modifications have been done on the NRM; and doing related investigative, corrective, and other specified actions, as applicable; as well as further modifications to address additional anomalies. This AD extends the compliance time for a certain inspection and associated actions. This AD also revises the applicability to include additional affected INUs. This AD results from reports indicating that erroneous localizer and glideslope indications have occurred on certain aircraft equipped with the subject INUs. We are issuing this AD to ensure that the flightcrew has accurate localizer and glideslope deviation indications. An erroneous localizer or glideslope deviation indication could lead to the aircraft making an approach off the localizer, which could result in impact with an obstacle or terrain.
96-12-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Superior Air Parts, Inc. Parts Manufacturer Approval (PMA) pistons installed on Teledyne Continental Motors O-470 series reciprocating engines, that requires removal from service of certain pistons. This amendment is prompted by piston failures. The actions specified by this AD are intended to prevent piston failure, which can result in engine power loss, engine failure and loss of the aircraft.
96-12-17: This amendment adopts a new airworthiness directive (AD), applicable to certain Beech (Raytheon) Model BAe 125 series 800A and 1000A, and Model Hawker 800 and 1000 airplanes, that requires an inspection to determine if the diode soldered connections are clean and functionally sound. This amendment also requires remake of the soldered connection and replacement of the diode with a new diode, if necessary. This amendment is prompted by reports of imperfect soldered connections in the engine starting and battery emergency control circuit. The actions specified by this AD are intended to prevent incorrect fault displays in the cockpit and intermittent fault symptoms in the engine starting and battery emergency control circuits, as a result of imperfect soldered connections.
2011-07-12: 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: * * * [T]he Federal Aviation Administration (FAA) has published Special Federal Aviation Regulation (SFAR) 88, and the Joint Aviation Authorities (JAA) has published Interim Policy INT/POL/25/ 12. The review conducted by Fokker Services on the Fokker 50 and Fokker 60 type design, in response to these regulations, revealed that the clearance between parts of the main landing gear (MLG) and the fuel pipes may be insufficient. This condition, if not detected and corrected, could lead to chafing, possibly resulting in fuel leakage and, in combination with other factors, a fuel fire. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2011-08-06: We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires removing certain power turbine rotors from service using a specific drawdown schedule. This AD was prompted by reports of fatigue cracks in the airfoil of the power turbine blades. We are issuing this AD to prevent fracture of the power turbine blade airfoil, which could result in sudden loss of engine power and prevent continued safe flight or safe landing.
96-12-08: This amendment adopts a new airworthiness directive (AD) that applies to Twin Commander Aircraft Corporation (Twin Commander) 500, 680, and 690 series airplanes that do not have a nose landing gear drag link bolt with the manufacturer s serial number, manufacture date, and the last three digits of the drawing number, 055, on the bolt head. This action requires replacing the nose landing gear (NLG) drag link bolt with one that has been manufactured with the proper heat treatment. This action was prompted by the failure of an improperly heat treated NLG drag link bolt causing collapse of the nose landing gear on a certain Twin Commander Model 690B airplane while taxiing. The actions specified by this AD are intended to prevent the NLG from collapsing, which if not corrected, could result in loss of the airplane.
96-12-11: This amendment adopts a new airworthiness directive (AD), applicable to all Canadair Model CL-215-1A10 series airplanes. This action requires repetitive inspections to detect discrepancies of the microswitches fitted at the water door actuator, and replacement of any discrepant microswitch. This action also requires a terminating action for the repetitive inspections. This amendment is prompted by a report indicating that the water doors on one airplane opened inadvertently during flight, due to corrosion of the microswitches fitted to the water door actuator. The actions specified in this AD are intended to prevent such uncommanded opening of the water doors, especially at high speed during a takeoff run, a water pick-up run, or a landing run, which could cause damage to the airplane.