Results
2011-11-07: 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: Cracks have been reportedly found on DA 42 Main Landing Gear (MLG) Damper-to-Trailing Arm joints during standard maintenance. Depending on environmental-, operating- and runway conditions, the affected MLG joint, Part Number (P/N) D60-3217-23-5x (4 different lengths are available), which is made of aluminum, is susceptible to cracking. This condition, if not detected and corrected, may lead to failure of the joint and subsequent damage or malfunction of the MLG, possibly resulting in damage to the aeroplane during landing and injury to occupants. We are issuing this AD to require actions to correct the unsafe condition on these products.
62-05-01: 62-05-01 AERO COMMANDER: Amdt. 403 Part 507 Federal Register March 6, 1962. Applies to All Model 680F Aircraft, Including Pressurized Versions, With Serial Numbers 871 Through 1170. Compliance required within the next 25 hours' time in service after the effective date of this directive. In order to preclude failure of the alternate induction air valve and shaft assembly resulting in loss of engine power, replace the original air valve and shaft and rig in accordance with instructions outlined in Aero Commander Service Bulletin No. 76A dated February 5, 1962, or FAA approved equivalent. This directive effective March 6, 1962.
99-21-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330-301, and Model A340-211, -212, -311, and -312 series airplanes, that requires repetitive detailed visual inspections of the fuselage belly fairing support structure to detect cracks; and corrective action, if necessary. This amendment also provides an optional terminating action for the repetitive inspections. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct fatigue cracking of the fuselage belly fairing support structure, which could result in reduced structural integrity of the fuselage belly fairing support structure.
2011-09-04: We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires repetitive inspections for any damage of the lower surface of the center wing box, and corrective actions if necessary. This AD was prompted by reports of fatigue cracks of the lower surface of the center wing box. We are issuing this AD to detect and correct such cracks, which could result in the structural failure of the wings.
2011-11-02: 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 airworthiness authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: During production quality inspections of the aeroplane fuel motive flow system, it was discovered that some motive flow check valves (MFCV) were manufactured with an outlet fitting containing red anodized threads. These MFCV do not provide adequate electrical bonding between the valve and the adjacent fitting. In the absence of proper electrical bonding within the motive flow system, the aeroplane fuel tank could be exposed to ignition sources in the case of a lightning strike. * * * * * The unsafe condition is the potential for ignition sources inside the fuel tanks, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
2002-26-15: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires repetitive inspections to detect evidence of wear damage in the area at the interface between the vertical stabilizer and fuselage skin, and corrective actions, if necessary. This amendment also provides for an optional terminating action for the repetitive inspections. The actions specified by this AD are intended to detect and correct wear damage of the fuselage skin, which could result in thinning and cracking of the fuselage skin, and consequent in-flight depressurization of the airplane. This action is intended to address the identified unsafe condition.
96-25-20: This amendment adopts a new airworthiness directive (AD), applicable to Hamilton Standard 14RF and 14SF series, and Hamilton Standard/British Aerospace Model 6/5500/F propellers, that requires initial and repetitive inspections of critical control components, and removal and replacement with serviceable parts those critical control components that do not meet the return to service criteria. This amendment is prompted by failure modes effects analysis (FMEA), certification test data, engineering analysis, and repair actions performed at overhaul depots. The actions specified by this AD are intended to prevent loss of propeller control due to failure of critical control components, which could result in loss of control of the aircraft.
97-01-06: This amendment adopts a new airworthiness directive (AD), applicable to Bell Helicopter Textron, Inc. (BHTI)-manufactured restricted category Model HH-1K, TH-1F, TH-1L, UH-1A, UH-1B, UH-1E, UH-1F, UH-1H, UH-1L, and UH-1P helicopters, that requires a one-time inspection of the tail rotor slider (slider) to verify that it was manufactured with the correct outside diameter. This amendment is prompted by a United States (U.S.) Army Safety of Flight message that reports that some sliders may have been improperly manufactured with an undersized wall thickness by U.S. Army vendors. The actions specified by this AD are intended to prevent fatigue failure of the slider, which could cause loss of tail rotor control and subsequent loss of control of the helicopter.
98-07-22: This amendment adopts a new airworthiness directive (AD), applicable to all British Aerospace Model HS 748 series airplanes. This action requires revising the Airplane Flight Manual (AFM) to modify the limitation that prohibits the positioning of the power levers below the flight idle stop during flight, and to add a statement of the consequences of positioning the power levers below the flight idle stop during flight. This amendment is prompted by incidents and accidents involving airplanes equipped with turboprop engines in which the propeller ground beta range was used improperly during flight. The actions specified in this AD are intended to prevent loss of airplane controllability, or engine overspeed and consequent loss of engine power caused by the power levers being positioned below the flight idle stop while the airplane is in flight.
2002-26-12: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A330 and A340 series airplanes, that requires a one-time inspection to determine the manufacturer's name, part number, and date code of certain circuit breakers; and replacement of any suspect circuit breaker with a new improved circuit breaker. The actions specified by this AD are intended to ensure that proper circuit breakers are installed for the fire extinguishing system or part of the supplemental oxygen supply. A defective circuit breaker, if not corrected, could trip without the cockpit indication light illuminating. If the flightcrew is unaware of this situation while operating the airplane, this latent failure in combination with other failures could present an immediate hazard to the airplane. This action is intended to address the identified unsafe condition.